TWI627103B - Coaxial double-rotor turbine drive unmanned vehicle mechanism system - Google Patents
Coaxial double-rotor turbine drive unmanned vehicle mechanism system Download PDFInfo
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Abstract
一種同軸雙旋翼渦輪傳動無人載具機構系統,包括機身、渦輪引擎及同軸雙旋翼機構。渦輪引擎包含傳動輸出結構。同軸雙旋翼機構包含大、小主軸及上、下主旋翼組及上、下旋翼葉片氣動構型及上、下同軸雙旋翼十字盤相位控制固定座結構。傳動輸出結構可外速拆裝且利於加工,節省更換及維修時間;上主旋翼組的滑動穩定性佳,晃動程度小;上、下旋翼葉片氣動構型產生的升力和降低阻力的效果佳;維持上、下同軸雙旋翼十字盤相位控制固定座結構改變本發明的飛行角度的功能,並且精確地控制上、下主旋翼組同步相對機身偏轉,使本發明穩定地改變飛行角度。A coaxial dual-rotor turbine-driven unmanned vehicle mechanism system includes a fuselage, a turbine engine, and a coaxial dual-rotor mechanism. The turbine engine contains a transmission output structure. The coaxial double-rotor mechanism includes large and small main shafts, upper and lower main rotor groups, upper and lower rotor blade aerodynamic configurations, and upper and lower coaxial double-rotor swashplate phase control fixed seat structures. The transmission output structure can be disassembled at external speeds and is convenient for processing, saving replacement and maintenance time. The upper main rotor group has good sliding stability and small sloshing; the lift and drag resistance generated by the aerodynamic configuration of the upper and lower rotor blades are good; The function of maintaining the upper and lower coaxial dual-rotor swashplate phase control fixed seat structure to change the flying angle of the present invention, and accurately controlling the upper and lower main rotor groups to synchronously deflect relative to the fuselage, so that the present invention can stably change the flying angle.
Description
本發明係有關一種同軸雙旋翼渦輪傳動無人載具機構系統,特別是一種在飛航能力、安全性、穩定度、加工製造及拆裝等各方面性能全面進化的同軸雙旋翼渦輪傳動無人載具機構系統。The invention relates to a coaxial dual-rotor turbo-drive unmanned vehicle mechanism system, in particular to a coaxial dual-rotor turbo-drive unmanned vehicle that has comprehensively evolved in all aspects of flight capabilities, safety, stability, manufacturing and disassembly. Institutional system.
遙控無人直昇機以旋翼軸的數量來區分的話主要有:單旋翼、雙旋翼以及多旋翼等三種類型。其中雙旋翼遙控直昇機又可細分成同軸式、縱列式、橫列式、交叉式等四種。一般的同軸雙旋翼渦輪傳動無人載具機構系統包含一機身、一渦輪引擎以及一同軸雙旋翼機構等三個主要的機構。There are mainly three types of remotely controlled unmanned helicopters based on the number of rotor shafts: single rotor, double rotor, and multiple rotors. The double-rotor remote-control helicopter can be subdivided into four types: coaxial, tandem, horizontal, and cross. A common coaxial dual-rotor turbo-drive unmanned vehicle mechanism system includes three main mechanisms, such as a fuselage, a turbine engine, and a coaxial dual-rotor mechanism.
渦輪引擎又叫渦輪軸發動機,利用燃燒室產生的氣流帶動自由渦輪輸出軸功率,而不是噴射推力。結構上類似於渦輪旋槳發動機,但主要區別在於渦輪旋槳發動機排出的尾氣還會產生一些殘餘推進力。另外對於渦輪旋槳發動機,傳動系統的主減速器是集成在發動機上的,而對於渦輪軸發動機,則是分離開的。Turbine engines are also called turboshaft engines. The airflow generated by the combustion chamber drives the free turbine output shaft power instead of jet thrust. The structure is similar to the turboprop, but the main difference is that the exhaust from the turboprop also generates some residual propulsion. In addition, for turboprop engines, the main reduction gear of the transmission system is integrated on the engine, while for turboshaft engines, it is separated.
習知的渦輪引擎的傳動輸出結構為一體成型方式製造,由於其一體結構,在輸出齒輪出現損壞老化等問題時,以及需要更換齒輪比時就顯十分複雜。其拆裝方式需將整體進行拆裝,工序繁複。另,若對傳動輸出結構進行加工時,也非常困難。The conventional transmission output structure of the turbine engine is manufactured in an integrated manner. Due to its integrated structure, it is very complicated when the output gear is damaged and aging, and when the gear ratio needs to be replaced. The disassembly method requires disassembly of the whole, and the process is complicated. In addition, it is very difficult to process the transmission output structure.
同軸雙旋翼機構包含一大主軸、一小主軸、一上主旋翼組、一下主旋翼組、複數上旋翼葉片、複數下旋翼葉片、一上同軸雙旋翼十字盤相位控制固定座結構及一下同軸雙旋翼十字盤相位控制固定座結構,其結構與一般大型直昇機有所不同。 大主軸可旋轉地設於機身,延伸穿過機身的頂部,並且具有一軸孔。小主軸可旋轉地設於機身並且延伸穿過大主軸的軸孔。上主旋翼組設於小主軸,下主旋翼組設於大主軸。該等上旋翼葉片設於上主旋翼組,該等下旋翼葉片設於下主旋翼組。上同軸雙旋翼十字盤相位控制固定座結構設於小主軸,複數連接桿連結於上主旋翼組和上同軸雙旋翼十字盤相位控制固定座結構之間。下同軸雙旋翼十字盤相位控制固定座結構設於大主軸,複數連接桿連結於下主旋翼組和下同軸雙旋翼十字盤相位控制固定座結構之間。上、下主旋翼組上下排列而且分別藉由同軸的小、大主軸驅動二者在同一個軸線上反向旋轉(亦即,小、大主軸分別驅動上、下主旋翼組往不同方向旋轉),並且藉由上、下旋翼葉片在旋轉時所產生的升力,使同軸雙旋翼遙控直昇機能夠穩定地起降。其中,旋翼是圓周運動,由於半徑的關係,上、下旋翼葉片的翼尖部的線速度已經接近音速時,圓心處線速度為零,所以旋翼靠近圓周的地方產生最大的升力,而靠近圓心的地方只產生微不足道的升力。小、大主軸則藉由上、下同軸雙旋翼十字盤相位控制固定座結構以及該等連接桿的組合同步驅動上、下主旋翼組相對機身傾斜,以改變同軸雙旋翼遙控直昇機的飛行角度(例如,前進、後退、左轉、右轉)。The coaxial dual-rotor mechanism includes a large main shaft, a small main shaft, an upper main rotor group, a lower main rotor group, a plurality of upper rotor blades, a plurality of lower rotor blades, an upper coaxial double rotor swash plate phase control fixed seat structure, and a lower coaxial double The structure of the rotor swashplate phase control fixed seat is different from that of a large helicopter. The main shaft is rotatably provided on the fuselage, extends through the top of the fuselage, and has a shaft hole. The small main shaft is rotatably provided on the fuselage and extends through the shaft hole of the large main shaft. The upper main rotor group is set on the small main axis, and the lower main rotor group is set on the main main axis. The upper rotor blades are provided in the upper main rotor group, and the lower rotor blades are provided in the lower main rotor group. The upper coaxial double-rotor swashplate phase control fixed seat structure is arranged on the small main shaft, and a plurality of connecting rods are connected between the upper main rotor group and the upper coaxial double-rotor swashplate phase control fixed seat structure. The lower coaxial double-rotor swashplate phase control fixed seat structure is arranged on the main shaft, and a plurality of connecting rods are connected between the lower main rotor group and the lower coaxial double-rotor swashplate phase control fixed seat structure. The upper and lower main rotor groups are arranged on top of each other and are driven by the coaxial small and large spindles to rotate in opposite directions on the same axis (that is, the small and large spindles respectively drive the upper and lower main rotor groups to rotate in different directions). And, with the lift generated by the upper and lower rotor blades during rotation, the coaxial dual-rotor remote-control helicopter can take off and land stably. Among them, the rotor is a circular motion. Due to the radius, when the linear velocity of the wing tip of the upper and lower rotor blades is close to the speed of sound, the linear velocity at the center of the circle is zero. The place produces only negligible lift. The small and large spindles use the upper and lower coaxial dual-rotor swashplate phase control fixed seat structure and the combination of these connecting rods to synchronously drive the upper and lower main rotor groups to tilt relative to the fuselage to change the flight angle of the coaxial dual-rotor remote-control helicopter. (E.g. forward, backward, turn left, turn right).
上主旋翼組包含一上主旋翼固定座以及一同軸雙旋翼方向控制固定座結構。上主旋翼固定座包含一座體、複數延伸臂及複數槳夾頭,上主旋翼固定座的座體設於小主軸,該等延伸臂間隔地突出於座體的一外環壁,該等槳夾頭分別設於該等延伸臂的末端。同軸雙旋翼方向控制固定座結構設於上主旋翼固定座的座體的上方。The upper main rotor group includes an upper main rotor fixed base and a coaxial double rotor direction control fixed base structure. The upper main rotor fixed seat includes a body, a plurality of extension arms and a plurality of paddle chucks. The seat of the upper main rotor fixed seat is provided on a small main shaft, and the extension arms protrude from an outer ring wall of the seat at intervals. The chucks are respectively disposed at the ends of the extension arms. The coaxial double-rotor direction control fixing seat structure is arranged above the seat body of the upper main rotor fixing seat.
然而,前述習知的同軸雙旋翼方向控制固定座結構只靠一根軸桿與上主旋翼固定座的座體結合以及靠三根連桿與上主旋翼固定座的該等延伸臂連結,使得上主旋翼組穩定性不佳而容易相對小主軸晃動,產生偏移,進而造成小、大主軸藉由上、下同軸雙旋翼十字盤相位控制固定座結構以及該等連接桿同步驅動上、下主旋翼組相對機身傾斜,以改變同軸雙旋翼遙控直昇機的飛行角度而相對機身傾斜的時候,該等上旋翼葉片的傾斜角度無法保持一致,導致同軸雙旋翼渦輪傳動無人載具機構系統無法精準地維持在預設角度上飛行。However, the above-mentioned conventional coaxial double-rotor direction control fixing seat structure only uses one shaft to combine with the seat body of the upper main rotor fixing seat and three extension links to the extension arms of the upper main rotor fixing seat, so that the upper The main rotor group has poor stability and is prone to sway relative to the small main shaft, causing offsets, which in turn causes the small and large main shafts to use the upper and lower coaxial dual-rotor swashplate phase control fixed seat structures and these connecting rods to simultaneously drive the upper and lower main shafts. When the rotor group is tilted relative to the fuselage to change the flight angle of the coaxial dual-rotor remote-control helicopter and tilted relative to the fuselage, the tilt angles of the upper rotor blades cannot be consistent, resulting in the inaccuracy of the coaxial dual-rotor turbine-driven unmanned vehicle mechanism system. The ground is maintained to fly at a preset angle.
另一種習知的同軸雙旋翼方向控制固定座結構包含本體和二滑銷,該二滑銷設於同軸雙旋翼方向控制固定座結構的本體與上主旋翼固定座的座體之間,藉以提升上主旋翼組的穩定性,使得上主旋翼組相對小主軸晃動的程度變小。Another conventional coaxial double-rotor direction control fixing structure includes a body and two sliding pins. The two sliding pins are arranged between the body of the coaxial double-rotor direction control fixing structure and the seat of the upper main rotor fixing base, thereby improving The stability of the upper main rotor group makes the degree of sloshing of the upper main rotor group relative to the small main shaft smaller.
惟,此種雙滑銷的同軸雙旋翼方向控制固定座結構僅能夠讓三個上旋翼葉片的傾斜角度的誤差縮小,而讓同軸雙旋翼渦輪傳動無人載具機構系統較能夠接近預設角度飛行,但仍舊無法讓三個上旋翼葉片的傾斜角度保持一致,所以裝載有此種雙滑銷的同軸雙旋翼方向控制固定座結構的同軸雙旋翼渦輪傳動無人載具機構系統依然無法精準地維持在預設角度上飛行,不能夠徹底解決前述無滑銷的同軸雙旋翼方向控制固定座結構所產生的問題。However, this type of dual-spin coaxial dual-rotor direction control fixed seat structure can only reduce the error of the tilt angles of the three upper rotor blades, and the coaxial dual-rotor turbine-driven unmanned vehicle mechanism system can fly closer to a preset angle. However, the inclination angles of the three upper rotor blades still cannot be kept the same, so the coaxial double rotor turbine-driven unmanned carrier mechanism system equipped with the coaxial double rotor direction control fixed seat structure of such a double sliding pin still cannot be accurately maintained at Flying at a predetermined angle cannot completely solve the problems caused by the structure of the above-mentioned coaxial double-rotor direction control fixing base without sliding pin.
再者,兩根滑銷容易受力變形,當其中一根滑銷受到碰撞而產生變形或彎曲的時候,此種雙滑銷的同軸雙旋翼方向控制固定座結構「提升上主旋翼組的穩地性」的功效立即喪失,即使另一根滑銷完好如初,也是無濟於事。In addition, the two sliding pins are easily deformed by force. When one of the sliding pins is deformed or bent due to collision, the coaxial double-rotor direction control fixing structure of this double-slide pin "improves the stability of the upper main rotor group. The "earthly" effect was immediately lost, and even if the other slip pin remained intact, it would not help.
請參閱圖1,圖1為習知的旋翼葉片的俯視圖。上、下旋翼葉片的結構是一模一樣的,因此以下將以「旋翼葉片」代表上、下旋翼葉片。一般的旋翼葉片A包含一槳葉本體A1、一結合部A2及一翼尖部A3。槳葉本體A1呈直線狀,其長度方向的二端界定為一第一端及一第二端,其寬度方向的二側界定為一第一側邊A13及一第二側邊A14。結合部A2設於槳葉本體A1的第一端並且設於上、下主旋翼組的槳夾頭。翼尖部A3設於槳葉本體A1的第二端,與槳葉本體A1位在同一個平面上,往遠離結合部A2的方向直線延伸並且漸縮,使得其長度方向與槳葉本體A1的長度方向相同而與槳葉本體A1的長度方向平行。簡言之,一般的旋翼葉片A的整體構造呈直線狀。此種直線狀的旋翼葉片A的渦線與升力線保持垂直,導致其所產生的升力十分有限。Please refer to FIG. 1, which is a top view of a conventional rotor blade. The structure of the upper and lower rotor blades is exactly the same, so the "rotor blades" will be used to represent the upper and lower rotor blades. A general rotor blade A includes a blade body A1, a joint portion A2, and a wing tip portion A3. The blade body A1 is linear, and two ends in the length direction are defined as a first end and a second end, and two sides in the width direction are defined as a first side A13 and a second side A14. The joint portion A2 is provided at the first end of the blade body A1 and is provided at the paddle chuck of the upper and lower main rotor groups. The wing tip A3 is provided at the second end of the blade body A1, is located on the same plane as the blade body A1, and extends straight and tapered in a direction away from the joint A2, so that its length direction is in line with that of the blade body A1. The longitudinal direction is the same and parallel to the longitudinal direction of the blade body A1. In short, the general structure of a general rotor blade A is straight. The vortex of the linear rotor blade A and the lift line remain perpendicular, resulting in a very limited lift.
再者,此種直線狀的旋翼葉片A的翼尖部A3在高速旋轉的情況下所產生的區域性振動波的可能性高,從而提高阻力。Furthermore, the wing tip A3 of such a linear rotor blade A is highly likely to generate a regional vibration wave when it rotates at a high speed, thereby increasing the resistance.
請參閱圖2,圖2為習知的旋翼葉片的剖視圖。槳葉本體A1具有一頂面A15及一底面A16;從剖視圖來看,槳葉本體A1的頂面A15和底面A16從槳葉本體A1的第一側邊A13往槳葉本體A1的第二側邊A14彎曲的曲率相等;槳葉本體A1的頂面A15從槳葉本體A1的第一側邊A13先向上彎曲,然後向下彎曲至槳葉本體A1的第二側邊A14;槳葉本體A1的底面A16從槳葉本體A1的第一側邊A13先向下彎曲,然後向上彎曲至槳葉本體A1的第二側邊A14。換句話說,槳葉本體A1的頂面A15和底面A16從第一側邊A13到第二側邊A14的弧長相等,而且槳葉本體A1的頂面A15和底面A16的彎曲方式彼此相對應,所以高低起伏相當一致,使得槳葉本體A1的整體結構呈對稱狀。然而,此種對稱狀的槳葉本體A1所產生的升力十分有限。Please refer to FIG. 2, which is a cross-sectional view of a conventional rotor blade. The blade body A1 has a top surface A15 and a bottom surface A16. From a sectional view, the top surface A15 and the bottom surface A16 of the blade body A1 are from the first side A13 of the blade body A1 to the second side of the blade body A1. The curvature of the side A14 is equal; the top surface A15 of the blade body A1 is bent upward from the first side A13 of the blade body A1, and then bent down to the second side A14 of the blade body A1; the blade body A1 The bottom surface A16 of the blade body A1 is bent downward from the first side edge A13 of the blade body A1 and then bent upward to the second side edge A14 of the blade body A1. In other words, the arc lengths of the top surface A15 and the bottom surface A16 of the blade body A1 from the first side A13 to the second side A14 are equal, and the bending manners of the top surface A15 and the bottom surface A16 of the blade body A1 correspond to each other Therefore, the height fluctuations are quite consistent, so that the overall structure of the blade body A1 is symmetrical. However, the lift generated by this symmetrical blade body A1 is very limited.
習知的上同軸雙旋翼十字盤相位控制固定座結構包含一上內環組、一上外環組、一上內環相位固定座組以及一上外環相位固定座組。上內環組套設於小主軸並且具有複數上內環球頭,複數第一連接桿連接於上內環球頭與上主旋翼組的球頭之間。上外環組環設於上內環組並且具有複數上外環球頭。上內環相位固定座組包含一上內環相位固定座本體、一上內環卡榫及一上內環接柄。上內環相位固定座本體套設於小主軸。上內環卡榫樞設於上內環相位固定座。上內環接柄的一端設於其中一上內環球頭,上內環卡榫可旋轉地扣住上內環接柄的另一端。上外環相位固定座組包含一上外環相位固定座本體、一上外環卡榫及一上外環接柄。上外環相位固定座本體套設於小主軸。上外環卡榫樞設於上外環相位固定座。上外環接柄的一端設於其中一上外環球頭,上外環卡榫可旋轉地扣住上外環接柄的另一端。The conventional upper coaxial dual-rotor swashplate phase control fixed seat structure includes an upper inner ring group, an upper outer ring group, an upper inner ring phase fixed seat group, and an upper outer ring phase fixed seat group. The upper inner ring group is sleeved on the small main shaft and has a plurality of upper inner ring and ball heads. A plurality of first connecting rods are connected between the upper inner ring and ball heads and the upper main rotor group. The upper outer ring group ring is provided in the upper inner ring group and has a plurality of upper and outer ring heads. The upper inner ring phase fixing base group includes an upper inner ring phase fixing base body, an upper inner ring tongue and groove and an upper inner ring connecting handle. The upper inner ring phase fixing seat body is sleeved on the small spindle. The upper inner ring tongue is pivotally arranged on the upper inner ring phase fixing seat. One end of the upper inner ring connecting handle is provided on one of the upper inner ring heads, and the upper inner ring tongue can rotatably fasten the other end of the upper inner ring connecting handle. The upper outer ring phase fixing seat group includes an upper outer ring phase fixing seat body, an upper outer ring tongue and groove, and an upper outer ring connecting handle. The main body of the upper outer ring phase fixing seat is sleeved on the small spindle. The upper outer ring tongue is pivotally arranged on the upper outer ring phase fixing seat. One end of the upper outer ring connecting handle is arranged on one of the upper and outer ring heads, and the upper outer ring tenon is rotatably fastened to the other end of the upper outer ring connecting handle.
習知的下同軸雙旋翼十字盤相位控制固定座結構包含一下內環組、一下外環組、一下內環相位固定座組以及一下外環相位固定座組。換句話說,下同軸雙旋翼十字盤相位控制固定座結構與上同軸雙旋翼十字盤相位控制固定座結構的結構一模一樣,該等元件之間連結關係也完全相同,差別在於:下內環組套設於大主軸,複數第二連接桿連接於上外環球頭與下內環球頭之間,複數第三連接桿連接於下內環球頭與下主旋翼組的球頭之間,複數第四連接桿連接於下外環球頭與遙控直昇機內部的球頭之間。The conventional lower coaxial dual-rotor swashplate phase control fixed base structure includes a lower inner ring group, a lower outer ring group, a lower inner ring phase fixed block group, and a lower outer ring phase fixed block group. In other words, the structure of the lower coaxial dual-rotor swashplate phase control fixing structure is exactly the same as that of the upper coaxial dual-rotor swashplate phase control fixing structure, and the connection relationship between these components is also the same, the difference is: the lower inner ring set It is set on the main shaft. A plurality of second connecting rods are connected between the upper and outer globe heads and a lower inner and round head. The third connecting rods are connected between the lower inner globe head and the ball head of the lower main rotor group. The fourth connection is plural. The rod is connected between the lower outer globe head and the ball head inside the remote control helicopter.
當上內環連結件的第一、第二內環連桿向外旋轉的時候,下內環連結件的第一、第二內環連桿向內旋轉。當上內環連結件的第一、第二內環連桿向內旋轉的時候,下內環連結件的第一、第二內環連桿向外旋轉。藉以控制下內環組和下外環組的組合相對大主軸的偏斜,同時上內環組和上外環組的組合相對小主軸偏斜,進而控制上、下主旋翼組同步相對機身偏轉,以改變同軸雙旋翼遙控直昇機的飛行角度。When the first and second inner ring links of the upper inner ring link rotate outward, the first and second inner ring links of the lower inner ring link rotate inward. When the first and second inner ring links of the upper inner ring link rotate inward, the first and second inner ring links of the lower inner ring link rotate outward. In this way, the deflection of the combination of the lower inner ring group and the lower outer ring group relative to the major axis is controlled, while the combination of the upper inner ring group and the upper outer ring group is deflected relative to the small main axis, and then the upper and lower main rotor groups are synchronized with respect to the fuselage. Deflection to change the flight angle of the coaxial twin-rotor remote control helicopter.
然而,上內環卡榫和上內環接柄之間有間隙,下內環卡榫和下內環接柄之間有間隙,上外環卡榫和上外環接柄之間有間隙,下外環卡榫和下外環接柄之間有間隙。因此,當上、下主旋翼組分別藉由同軸的小、大主軸驅動二者在同一個軸線上反向旋轉的時候,同軸雙旋翼機構整體會產生振動,導致,上內環接柄從上內環卡榫上逐漸鬆脫,上外環接柄從上外環卡榫上逐漸鬆脫,下外環接柄從下外環卡榫上逐漸鬆脫,下內環接柄從下內環卡榫上逐漸鬆脫,從而讓上、下同軸雙旋翼十字盤相位控制固定座結構喪失功效而無法改變同軸雙旋翼遙控直昇機的飛行角度。However, there is a gap between the upper inner ring tongue and the upper inner ring adapter, there is a gap between the lower inner ring tongue and the lower inner ring adapter, and there is a gap between the upper outer ring tongue and the upper outer ring adapter. There is a gap between the lower outer ring mortise and the lower outer ring shank. Therefore, when the upper and lower main rotor groups are driven by the coaxial small and large spindles to rotate in opposite directions on the same axis, the coaxial double rotor mechanism will generate vibration as a whole, resulting in the upper inner ring connecting handle from above. The inner ring tongue is gradually loosened, the upper outer ring adapter is gradually loosened from the upper outer ring tongue, the lower outer ring adapter is gradually released from the lower outer ring tongue, and the lower inner ring adapter is released from the lower inner ring. The tenon is gradually loosened, so that the structure of the upper and lower coaxial dual-rotor swashplate phase control mounts is ineffective and the flight angle of the coaxial dual-rotor remote-control helicopter cannot be changed.
再者,上內環卡榫、上外環卡榫、下內環卡榫以及下外環卡榫的材質均為塑膠,結構強度較差。在長期使用下,上內環卡榫、上外環卡榫、下內環卡榫以及下外環卡榫容易因為振動而磨損,使得上內環接柄、上外環接柄、下內環接柄以及下外環接柄更加容易分別從上內環卡榫、上外環卡榫、下內環卡榫以及下外環卡榫上鬆脫,從而讓上、下同軸雙旋翼十字盤相位控制固定座結構喪失功效而無法改變同軸雙旋翼遙控直昇機的飛行角度。Furthermore, the materials of the upper inner ring tenon, the upper outer ring tenon, the lower inner ring tenon, and the lower outer ring tenon are all made of plastic, which has poor structural strength. Under long-term use, the upper inner ring tenon, the upper outer ring tenon, the lower inner ring tenon, and the lower outer ring tenon are prone to wear due to vibration, making the upper inner ring joint, the upper outer ring joint, and the lower inner ring The adapter and the lower outer ring adapter are easier to release from the upper inner ring tongue, the upper outer ring tongue, the lower inner ring tongue, and the lower outer ring tongue, respectively, so that the upper and lower coaxial double rotor swashplates are phased. The control mount structure loses its effectiveness and cannot change the flight angle of the coaxial dual-rotor remote-control helicopter.
此外,上內環連結件與小主軸的距離小於下內環連結件與大主軸的距離,因此上內環連結件的第一、第二內環連桿向外旋轉到極限的時候,下內環連結件的第一、第二內環連桿與大主軸還有一點空間而會繼續向內旋轉至同時碰觸到大主軸為止,造成下內環組和下外環組的組合相對大主軸的偏斜角度大於上內環組和上外環組的組合相對小主軸的偏斜角度,進而導致上、下主旋翼組無法同步相對機身偏轉,因而造成同軸雙旋翼遙控直昇機在改變飛行角度的過程中失控。In addition, the distance between the upper inner ring connector and the small main shaft is smaller than the distance between the lower inner ring connector and the large main shaft. Therefore, when the first and second inner ring links of the upper inner ring connector rotate outward to the limit, the lower inner ring The first and second inner ring links of the ring link and the main spindle still have a little space and will continue to rotate inward until they touch the main spindle at the same time, resulting in the combination of the lower inner ring group and the lower outer ring group being relatively large. The angle of deflection is larger than the deflection angle of the combination of the upper inner ring group and the upper outer ring group with respect to the relatively small main axis. As a result, the upper and lower main rotor groups cannot synchronously deflect relative to the fuselage, which causes the coaxial dual-rotor remote control helicopter to change the flight angle Out of control.
由上可知,習知的同軸雙旋翼渦輪傳動無人載具機構系統在同軸雙旋翼以及渦輪引擎方面各自有諸多不理想之處,且該等不理想之處彼此互相影響整體系統的飛航能力、安全性、穩定度、加工製造及拆裝,因此亟需開發一種能夠全方面地改善上述問題的同軸雙旋翼渦輪傳動無人載具機構系統。It can be seen from the above that the conventional coaxial double-rotor turbo-drive unmanned vehicle mechanism system has many unsatisfactory aspects in terms of the coaxial double-rotor and the turbine engine, and these unsatisfactory aspects mutually affect the flight capability of the overall system, Safety, stability, manufacturing and disassembly, therefore, there is an urgent need to develop a coaxial dual-rotor turbo-drive unmanned vehicle mechanism system that can comprehensively improve the above problems.
本發明的主要目的在於提供一種同軸雙旋翼渦輪傳動無人載具機構系統,渦輪引擎的傳動輸出結構在更換、拆裝等應用上更為便利快捷且利於加工製造,節省更換及維修時間;上主旋翼組的滑動穩定性佳,相對小主軸晃動的程度小;上、下旋翼葉片氣動構型產生的升力和降低阻力的效果佳;維持上、下同軸雙旋翼十字盤相位控制固定座結構改變本發明的飛行角度的功能,並且精確地控制上、下主旋翼組同步相對機身偏轉,使本發明能夠穩定地改變飛行角度。The main purpose of the present invention is to provide a coaxial dual-rotor turbine-driven unmanned vehicle mechanism system. The transmission output structure of the turbine engine is more convenient and fast in replacement, disassembly and other applications, and is conducive to processing and manufacturing, saving replacement and maintenance time. The rotor group has good sliding stability, and the degree of sloshing is relatively small. The aerodynamic configuration of the upper and lower rotor blades has good lift and lower drag effects. Maintaining the upper and lower coaxial dual-rotor swashplate phase control fixed structure changes the cost. The function of the invented flight angle, and the precise control of the upper and lower main rotor groups to synchronously deflect relative to the fuselage, enable the present invention to stably change the flight angle.
為了達成前述的目的,本發明將提供一種同軸雙旋翼渦輪傳動無人載具機構系統,包括一機身、一渦輪引擎及一同軸雙旋翼機構。In order to achieve the foregoing object, the present invention provides a coaxial dual-rotor turbine-driven unmanned vehicle mechanism system, including a fuselage, a turbine engine, and a coaxial dual-rotor mechanism.
渦輪引擎設於機身並且包括一傳動輸出結構,傳動輸出結構包括一渦輪發動機、一轉接座及一輸出齒輪,渦輪發動機包括一發動機本體、一渦輪傳動軸及一固定環,渦輪傳動軸可旋轉地設於發動機本體並且其一側突出於發動機本體的一側,固定環設於渦輪傳動軸的一端,轉接座設於固定環,輸出齒輪設於轉接座。The turbine engine is provided on the fuselage and includes a transmission output structure. The transmission output structure includes a turbine engine, an adapter, and an output gear. The turbine engine includes an engine body, a turbine transmission shaft, and a fixed ring. It is rotatably arranged on the engine body and one side of the engine body protrudes from one side of the engine body. A fixed ring is provided on one end of the turbine transmission shaft. An adapter seat is provided on the fixed ring. An output gear is provided on the adapter seat.
同軸雙旋翼機構包括一大主軸、一小主軸、一上主旋翼組、一下主旋翼組、複數上旋翼葉片氣動構型、複數下旋翼葉片氣動構型、一上同軸雙旋翼十字盤相位控制固定座結構以及一下同軸雙旋翼十字盤相位控制固定座結構。The coaxial dual-rotor mechanism includes a large main shaft, a small main shaft, an upper main rotor group, a lower main rotor group, a plurality of upper rotor blade aerodynamic configurations, a plurality of lower rotor blade aerodynamic configurations, and an upper coaxial dual rotor swashplate phase control and fixed Seat structure and lower coaxial double-rotor swashplate phase control fixed seat structure.
大主軸可旋轉地設於機身,延伸穿過機身的頂部,並且具有一軸孔。The main shaft is rotatably provided on the fuselage, extends through the top of the fuselage, and has a shaft hole.
小主軸可旋轉地設於機身並且延伸穿過大主軸的軸孔。The small main shaft is rotatably provided on the fuselage and extends through the shaft hole of the large main shaft.
上主旋翼組包括一上主旋翼固定座及一同軸雙旋翼方向控制固定座結構,上主旋翼固定座設於小主軸並且包括複數上槳夾頭,同軸雙旋翼方向控制固定座結構設於上主旋翼固定座並且包括一本體、一軸桿、複數連桿及至少三支撐結構,本體位於上主旋翼固定座的上方且與上主旋翼固定座同軸,軸桿設於本體與上主旋翼固定座之間且延伸於本體的一軸線與上主旋翼固定座的一軸線上,該等連桿分別設於本體的外側與上主旋翼固定座的外側之間,該等支撐結構圍繞軸桿而分別設於本體的底部與上主旋翼固定座的頂部之間。The upper main rotor set includes an upper main rotor fixed base and a coaxial double rotor direction control fixed base structure. The upper main rotor fixed base is provided on the small main shaft and includes a plurality of upper paddle chucks. The coaxial double rotor direction controlled fixed base structure is provided on the upper side. The main rotor fixed base includes a body, a shaft, a plurality of links and at least three supporting structures. The main body is located above the upper main rotor fixed base and is coaxial with the upper main rotor fixed base. The shaft is provided on the main body and the upper main rotor fixed base. Between the axis of the main body and the axis of the upper main rotor fixed seat, the connecting rods are respectively arranged between the outer side of the main body and the outer side of the upper main rotor fixed seat, and the supporting structures are respectively arranged around the shaft Between the bottom of the body and the top of the upper main rotor fixed seat.
下主旋翼組包括一下主旋翼固定座,下主旋翼固定座設於大主軸並且包括複數下槳夾頭。The lower main rotor set includes a lower main rotor fixing seat, the lower main rotor fixing seat is provided on the main shaft and includes a plurality of lower paddle chucks.
該等上旋翼葉片氣動構型各包括一上槳葉本體、一上結合部及一上翼尖部,上槳葉本體呈直線狀,其長度方向的二端分別界定為一第一端及一第二端,其寬度方向的二側分別界定為一第一側邊及一第二側邊,並且具有一頂面及一底面,上結合部設於上槳葉本體的第一端並且設於上槳夾頭,上翼尖部設於上槳葉本體的第二端,與上槳葉本體在同一個平面上延伸,並且往遠離上結合部以及上槳葉本體的第一側邊的方向延伸,使得上翼尖部的長度方向不同於上槳葉本體的長度方向而與上槳葉本體的長度方向具有一夾角。The aerodynamic configurations of the upper rotor blades each include an upper blade body, an upper joint portion, and an upper wing tip portion. The upper blade body is linear, and the two ends in the length direction are respectively defined as a first end and a The second end has two sides in the width direction defined as a first side and a second side, respectively, and has a top surface and a bottom surface. The upper joint portion is provided at the first end of the upper blade body and is provided at Upper paddle chuck, the upper wing tip is set on the second end of the upper blade body, extends on the same plane as the upper blade body, and is away from the upper joint and the first side of the upper blade body Extend so that the length direction of the tip of the upper wing is different from the length direction of the upper blade body and has an angle with the length direction of the upper blade body.
該等下旋翼葉片氣動構型各包括一下槳葉本體、一下結合部及一下翼尖部,下槳葉本體呈直線狀,其長度方向的二端分別界定為一第一端及一第二端,其寬度方向的二側分別界定為一第一側邊及一第二側邊,並且具有一頂面及一底面,下結合部設於下槳葉本體的第一端並且設於下槳夾頭,下翼尖部設於下槳葉本體的第二端,與下槳葉本體在同一個平面上延伸,並且往遠離下結合部以及下槳葉本體的第一側邊的方向延伸,使得下翼尖部的長度方向不同於下槳葉本體的長度方向而與下槳葉本體的長度方向具有一夾角。The aerodynamic configurations of the lower rotor blades each include a lower blade body, a lower joint portion, and a lower wing tip portion. The lower blade body is linear, and the two ends in the length direction are respectively defined as a first end and a second end. The two sides in the width direction are defined as a first side and a second side, respectively, and have a top surface and a bottom surface. The lower joint portion is provided on the first end of the lower blade body and on the lower blade clamp. The head and the lower wing tip are located on the second end of the lower blade body, and extend on the same plane as the lower blade body, and extend away from the lower joint portion and the first side of the lower blade body, so that The length direction of the lower wing tip is different from the length direction of the lower blade body and has an angle with the length direction of the lower blade body.
上同軸雙旋翼十字盤相位控制固定座結構包括一上內環組、一上外環組、一上內環相位固定座組及一上外環相位固定座組,上內環組套設於小主軸並且具有一上內環球頭,上外環組環設於上內環組並且具有一上外環球頭,上內環相位固定座組包括一上內環相位固定座本體、一上內環連結件、一上內環接柄及複數上內環固定件,上內環相位固定座本體套設於小主軸,上內環連結件具有一第一端及一第二端,至少一上內環固定件螺設於上內環連結件的第一端與上內環相位固定座本體,使得上內環連結件的第一端被上內環固定件固定於上內環相位固定座本體,上內環接柄具有一第一端及一第二端,至少一上內環固定件螺設於上內環接柄的第一端與上內環連結件的第二端,使得上內環接柄的第一端被上內環固定件固定於上內環連結件的第二端,上內環接柄的第二端設於上內環球頭,上外環相位固定座組包括一上外環相位固定座本體、一上外環連結件、一上外環接柄及複數上外環固定件,上外環相位固定座本體套設於小主軸,上外環連結件具有一第一端及一第二端,至少一上外環固定件螺設於上外環連結件的第一端與上外環相位固定座本體,使得上外環連結件的第一端被上外環固定件固定於上外環相位固定座本體,上外環接柄具有一第一端及一第二端,至少一上外環固定件螺設於上外環接柄的第一端與上外環連結件的第二端,使得上外環接柄的第一端被上外環固定件固定於上外環連結件的第二端,上外環接柄的第二端設於上外環球頭。 The upper coaxial double-rotor swashplate phase control fixed seat structure includes an upper inner ring group, an upper outer ring group, an upper inner ring phase fixed seat group and an upper outer ring phase fixed seat group. The upper inner ring group is set in a small The main shaft has an upper inner ring head, the upper outer ring ring is arranged on the upper inner ring ring and has an upper and outer ring ring head. The upper inner ring phase fixing seat group includes an upper inner ring phase fixing seat body and an upper inner ring connection. Pieces, an upper inner ring connecting handle and a plurality of upper inner ring fixing pieces, the upper inner ring phase fixing seat body is sleeved on the small spindle, and the upper inner ring connecting piece has a first end and a second end, at least one upper inner ring The fixing member is screwed on the first end of the upper inner ring connecting member and the upper inner ring phase fixing base body, so that the first end of the upper inner ring connecting member is fixed to the upper inner ring phase fixing base body by the upper inner ring fixing member. The inner ring connecting handle has a first end and a second end. At least one upper inner ring fixing member is screwed on the first end of the upper inner ring connecting handle and the second end of the upper inner ring connecting member, so that the upper inner ring is connected. The first end of the handle is fixed to the second end of the upper inner ring connecting member by the upper inner ring fixing member, and the upper inner ring is connected to the handle The second end is located on the upper and inner ring heads. The upper and outer ring phase fixing base group includes an upper and outer ring phase fixing base body, an upper and outer ring connecting piece, an upper and outer ring connecting handle, and a plurality of upper and outer ring fixing pieces. The ring phase fixing body is sleeved on the small main shaft. The upper outer ring connecting member has a first end and a second end. At least one upper outer ring fixing member is screwed on the first end and the upper outer ring of the upper outer ring connecting member. The phase fixing base body, so that the first end of the upper outer ring connecting member is fixed to the upper outer ring phase fixing base body by the upper outer ring fixing member, and the upper outer ring connecting handle has a first end and a second end, at least one upper The outer ring fixing member is screwed on the first end of the upper outer ring connecting handle and the second end of the upper outer ring connecting member, so that the first end of the upper outer ring connecting handle is fixed to the upper outer ring connecting member by the upper outer ring fixing member. The second end of the upper outer ring connecting handle is provided on the upper and outer round heads.
下同軸雙旋翼十字盤相位控制固定座結構包括一下內環組、一下外環組、一限制旋轉角度的下內環相位固定座組及一下外環相位固定座組,下內環組套設於大主軸並且具有一下內環球頭,下外環組環設於該下內環組並且具有一下外環球頭,限制旋轉角度的下內環相位固定座組包括一下內環相位固定座本體、一下內環連結件、一下內環接柄、複數下內環固定件及一限位裝置,下內環相位固定座本體套設於大主軸,下內環連結件包含一第一下內環連桿及一第二下內環連桿,第一下內環連桿具有一第一端及一第二端,第二下內環連桿具有一第一端及一第二端,至少一下內環固定件螺設於第一下內環連桿的第一端與下內環相位固定座本體,使得第一下內環連桿的第一端被下內環固定件固定於下內環相位固定座本體,至少一下內環固定件螺設於第二下內環連桿的第一端與第一下內環連桿的第二端,使得第二下內環連桿的第一端被下內環固定件固定於第一下內環連桿的第二端,下內環接柄具有一第一端及一第二端,至少一下內環固定件螺設於下內環接柄的第一端與第二下內環連桿的第二端,使得下內環接柄的第一端被下內環固定件固定於第二下內環連桿的第二端,下內環接柄的第二端設於下內環球頭,限位裝置至少一部分位於下內環連結件的內側與該大主軸的外側之間,其中,當下內環連結件向外旋轉至一第一位置時,下內環連結件遠離大主軸;當下內環連結件向內旋轉至一第二位置時,限位裝置限制第一下內環連桿和第二下內環連桿向內旋轉的角度,以使下內環連結件的內側與大主軸的外側隔開一段距離,下外環相位固定座組包括一下外環相位固定座本體、一下外環連結件、一下外環接柄及複數下外環固定件,下外環相位固定座本體套設於大主軸,下外環連結件具有一第一端及一第二端,至少一下外環固定件螺設於下外環連結件的第一端與下外環相位固定座本體,使得下外環連結件的第一端被下外環固定件固定於下外環相位固定座本體,下外環接柄具有一第一端及一第二端,至少一下外環固定件螺設於下外環接柄的第一端與下外環連結件的第二端,使得下外環接柄的第一端被下外環固定件固定於下外環連結件的第二端,下外環接柄的第二端設於下外環球頭。The lower coaxial double-rotor swashplate phase control fixed seat structure includes a lower inner ring group, a lower outer ring group, a lower inner ring phase fixed seat group and a lower outer ring phase fixed seat group that limit the rotation angle. The lower inner ring group is set on The main shaft has a lower inner ring head, and a lower outer ring group ring is arranged on the lower inner ring group and has a lower outer ring head. The lower inner ring phase fixing seat group which restricts the rotation angle includes a lower inner ring phase fixing body, a lower inner ring A ring link, a lower inner ring connecting handle, a plurality of lower inner ring fixing members, and a limiting device. The lower inner ring phase fixing body is sleeved on the main shaft. The lower inner ring link includes a first lower inner ring link and A second lower inner ring link, the first lower inner ring link has a first end and a second end, the second lower inner ring link has a first end and a second end, and at least the lower inner ring is fixed Pieces are screwed on the first end of the first lower inner ring link and the lower inner ring phase fixing seat body, so that the first end of the first lower inner ring link is fixed to the lower inner ring phase fixing seat by the lower inner ring fixing member Body, at least the lower inner ring fixing part is screwed on the second lower inner ring The first end and the second end of the first lower inner link are such that the first end of the second lower inner link is fixed to the second end of the first lower inner link by the lower inner ring fixing member. The inner ring connecting handle has a first end and a second end, and at least the lower inner ring fixing member is screwed on the first end of the lower inner ring connecting handle and the second end of the second lower inner ring connecting rod, so that the lower inner ring The first end of the connecting handle is fixed to the second end of the second lower inner ring connecting rod by the lower inner ring fixing member. The second end of the lower inner ring connecting handle is provided on the lower inner ring head. At least a part of the limiting device is located in the lower inner ring. Between the inside of the ring link and the outside of the major axis, when the lower inner ring link rotates outward to a first position, the lower inner ring link moves away from the main axis; when the lower inner ring link rotates inward to one In the second position, the limiting device limits the inward rotation angle of the first lower inner link and the second lower inner link so that the inside of the lower inner ring link is separated from the outside of the main shaft by a distance. Outer ring phase fixing block group includes lower outer phase fixing base body, lower outer ring connecting piece, lower outer ring connecting handle and a plurality of lower rings A ring fixing member, the lower outer ring phase fixing seat body is sleeved on the main shaft, the lower outer ring connecting member has a first end and a second end, and at least the lower outer ring fixing member is screwed on the first of the lower outer ring connecting member; The end and the lower outer ring phase fixing seat body, so that the first end of the lower outer ring connecting member is fixed to the lower outer ring phase fixing seat body by the lower outer ring fixing member, and the lower outer ring connecting handle has a first end and a second End, at least the lower outer ring fixing member is screwed on the first end of the lower outer ring connecting handle and the second end of the lower outer ring connecting member, so that the first end of the lower outer ring connecting handle is fixed to the lower part by the lower outer ring fixing member. The second end of the outer ring connecting piece and the second end of the lower outer ring connecting handle are arranged on the lower outer ring head.
本發明的功效在於,渦輪引擎的傳動輸出結構在更換、拆裝等應用上更為便利快捷且利於加工製造,節省更換及維修時間;上主旋翼組的滑動穩定性佳,相對小主軸晃動的程度小;上、下旋翼葉片氣動構型產生的升力和降低阻力的效果佳;維持上、下同軸雙旋翼十字盤相位控制固定座結構改變本發明的飛行角度的功能,並且精確地控制上、下主旋翼組同步相對機身偏轉,使本發明能夠穩定地改變飛行角度。藉此,本發明在飛航能力、安全性、穩定度、加工製造及拆裝等各方面性能全面進化。The effect of the present invention is that the transmission output structure of the turbine engine is more convenient and fast in replacement, disassembly and other applications, and is conducive to processing and manufacturing, saving time for replacement and maintenance. The sliding stability of the upper main rotor group is better, and the relatively small main shaft swayes. The degree is small; the lift and drag generated by the aerodynamic configuration of the upper and lower rotor blades are good; the function of maintaining the structure of the upper and lower coaxial dual-rotor swashplate phase control mounts to change the flight angle of the present invention and accurately control the upper and lower rotors The lower main rotor group is simultaneously deflected relative to the fuselage, so that the present invention can stably change the flight angle. With this, the present invention has comprehensively evolved in all aspects of flight capability, safety, stability, processing, manufacturing, disassembly and the like.
以下配合圖式及元件符號對本發明的實施方式做更詳細的說明,俾使熟習該項技藝者在研讀本說明書後能據以實施。The following describes the embodiments of the present invention in more detail with reference to the drawings and element symbols, so that those skilled in the art can implement them after studying this specification.
請參閱圖3,圖3是本發明的同軸雙旋翼渦輪傳動無人載具機構系統的示意圖,本發明係提供一種同軸雙旋翼渦輪傳動無人載具機構系統,包括一機身10、一渦輪引擎20及一同軸雙旋翼機構30。Please refer to FIG. 3. FIG. 3 is a schematic diagram of a coaxial dual-rotor turbine-driven unmanned vehicle mechanism system of the present invention. The present invention provides a coaxial dual-rotor turbine-driven unmanned vehicle mechanism system, which includes a fuselage 10 and a turbine engine 20. And a coaxial double rotor mechanism 30.
請參閱圖4a至圖4d,圖4a是本發明的渦輪引擎的傳動輸出結構的立體圖,圖4b是本發明的渦輪引擎的傳動輸出結構的分解圖,圖4c是本發明的渦輪引擎的傳動輸出結構的側視圖,圖4d是本發明的渦輪引擎的傳動輸出結構的剖視圖。渦輪引擎20設於機身10並且包括一傳動輸出結構21,傳動輸出結構21包含一渦輪發動機22、一轉接座23、複數轉接螺絲24、一輸出齒輪25、複數齒輪螺絲26及一傳動齒輪27。渦輪引擎20的其餘結構係屬習知,在此不予贅述。Please refer to FIG. 4a to FIG. 4d. FIG. 4a is a perspective view of the transmission output structure of the turbine engine of the present invention, FIG. 4b is an exploded view of the transmission output structure of the turbine engine of the present invention, and FIG. 4c is the transmission output of the turbine engine of the present invention A side view of the structure. FIG. 4D is a cross-sectional view of a transmission output structure of a turbine engine of the present invention. The turbine engine 20 is disposed on the fuselage 10 and includes a transmission output structure 21. The transmission output structure 21 includes a turbine engine 22, an adapter 23, a plurality of adapter screws 24, an output gear 25, a plurality of gear screws 26, and a transmission. Gear 27. The rest of the structure of the turbine engine 20 is known and will not be described in detail here.
渦輪發動機22包含一發動機本體221、一渦輪傳動軸222、一固定環223及一突管224。渦輪傳動軸222可旋轉地設於發動機本體221並且其一側突出於發動機本體221的一側。固定環223設於渦輪傳動軸222突出於發動機本體221的一側的軸心上。固定環223開設複數固定螺孔2231。突管224突出於固定環223遠離發動機本體221的一側的軸心上。The turbine engine 22 includes an engine body 221, a turbine transmission shaft 222, a fixing ring 223, and a protruding tube 224. The turbine transmission shaft 222 is rotatably provided on the engine body 221 and one side thereof protrudes from one side of the engine body 221. The fixing ring 223 is provided on a shaft center of the turbine transmission shaft 222 protruding from one side of the engine body 221. The fixing ring 223 defines a plurality of fixing screw holes 2231. The protruding tube 224 protrudes from an axis of the fixing ring 223 on a side away from the engine body 221.
轉接座23包含一轉接環231、一轉接管232及一軸孔233。轉接環231開設複數轉接螺孔2311。轉接管232突出於轉接環231遠離發動機本體221的一側的軸心並且開設複數輸出螺孔2321。轉接座23的軸孔233貫穿轉接環231及轉接管232的軸心。轉接環231貼合於固定環223,該等轉接螺孔2311對應該等固定螺孔2231,該等轉接螺絲24分別螺設於該等轉接螺孔2311與該等固定螺孔2231。然而,轉接環231與固定環223的固定方式並非以此為限,在其他實施例中,亦可以卡合固定、旋轉固定、黏合固定或者其他固定方式將轉接環231固定在固定環223,合先敘明。突管224從轉接環231貼合於固定環223的一側對接卡合於轉接座23的軸孔233。藉此,當渦輪發動機22啟動時,渦輪傳動軸222開始相對發動機本體221旋轉並且驅動轉接座23同步旋轉。The adapter seat 23 includes an adapter ring 231, a adapter tube 232 and a shaft hole 233. The adapter ring 231 defines a plurality of adapter screw holes 2311. The adapter pipe 232 protrudes from the shaft center of the side of the adapter ring 231 away from the engine body 221 and defines a plurality of output screw holes 2321. The shaft hole 233 of the adapter seat 23 passes through the shaft centers of the adapter ring 231 and the adapter tube 232. The adapter ring 231 is attached to the fixing ring 223, the adapter screw holes 2311 correspond to the fixing screw holes 2231, and the adapter screws 24 are screwed in the adapter screw holes 2311 and the fixing screw holes 2231, respectively. . However, the fixing manner of the adapter ring 231 and the fixing ring 223 is not limited to this. In other embodiments, the adapter ring 231 may be fixed to the fixing ring 223 by snap-fitting, rotation fixing, adhesive fixing, or other fixing methods. , He Xianxian. The protruding tube 224 is abutted from one side of the adapter ring 231 to the fixing ring 223 and engaged with the shaft hole 233 of the adapter seat 23. Thereby, when the turbine engine 22 is started, the turbine transmission shaft 222 starts to rotate relative to the engine body 221 and drives the adapter seat 23 to rotate synchronously.
輸出齒輪25包含一齒輪管251、一軸孔252及複數輸出輪齒253。齒輪管251的外環面開設複數齒輪螺孔2511。軸孔252貫穿齒輪管251的軸心及齒輪管251的前後端。該等輸出輪齒253環設於齒輪管251的外環面。轉接管232插設於輸出齒輪25的軸孔252。該等齒輪螺孔2511對應該等輸出螺孔2321,該等齒輪螺絲26分別螺設於該等齒輪螺孔2511與該等輸出螺孔2321。然而,轉接管232與齒輪管251的固定方式並非以此為限,在其他實施例中,亦可以卡合固定、旋轉固定、黏合固定或者其他固定方式將轉接管232固定在齒輪管251,合先敘明。藉此,當轉接座23旋轉時,轉接座23能夠驅動輸出齒輪25同步旋轉。The output gear 25 includes a gear tube 251, a shaft hole 252 and a plurality of output gear teeth 253. A plurality of gear screw holes 2511 are formed on an outer circumferential surface of the gear tube 251. The shaft hole 252 penetrates the shaft center of the gear tube 251 and the front and rear ends of the gear tube 251. The output gear teeth 253 are provided on the outer ring surface of the gear tube 251. The transfer pipe 232 is inserted into the shaft hole 252 of the output gear 25. The gear screw holes 2511 correspond to the output screw holes 2321, and the gear screws 26 are screwed in the gear screw holes 2511 and the output screw holes 2321, respectively. However, the fixing manner of the transfer tube 232 and the gear tube 251 is not limited to this. In other embodiments, the transfer tube 232 can also be fixed to the gear tube 251 by snap fixing, rotation fixing, adhesive fixing, or other fixing methods. , He Xianxian. Thereby, when the adapter seat 23 rotates, the adapter seat 23 can drive the output gear 25 to rotate synchronously.
傳動齒輪27包含複數傳動輪齒271。該等傳動輪齒271嚙合於該等輸出輪齒253。藉此,當輸出齒輪25旋轉時,輸出齒輪25能夠驅動傳動齒輪27同步旋轉。The transmission gear 27 includes a plurality of transmission gear teeth 271. The transmission gear teeth 271 mesh with the output gear teeth 253. Thereby, when the output gear 25 rotates, the output gear 25 can drive the transmission gear 27 to rotate synchronously.
因為渦輪發動機22、轉接座23及輸出齒輪25等構件為分段式固接(亦即,依次相互連接並固定),在更換輸出齒輪25的齒輪比時,或者由於長期使用導致輸出齒輪25老化或損壞需更換輸出齒輪25時,僅需將轉接座23與輸出齒輪25的連接關係解除,也就是說,直接取下齒輪螺絲26,或將轉接管232與齒輪管251的卡合固定打開,即可更換輸出齒輪25的齒輪比。另外在選擇不同口徑的輸出齒輪25時,可直接對轉接座23進行加工,更改對應輸出齒輪25的口徑的轉接座23,即可實現更換不同口徑大小的輸出齒輪25。相較於習知技術,本發明的傳動輸出結構21不需做整體更換零件,結構在更換、拆裝等應用上更為便利快捷,節省更換及維修時間。Because the components such as the turbine engine 22, the adapter 23, and the output gear 25 are fixed in sections (that is, they are connected and fixed to each other in sequence), when the gear ratio of the output gear 25 is changed, or the output gear 25 is caused by long-term use When the output gear 25 needs to be replaced after aging or damage, the connection relationship between the adapter seat 23 and the output gear 25 only needs to be released, that is, directly remove the gear screw 26, or the engagement of the adapter tube 232 and the gear tube 251 When it is fixedly opened, the gear ratio of the output gear 25 can be replaced. In addition, when selecting the output gears 25 of different calibers, the adapter 23 can be directly processed, and the adapter 23 corresponding to the caliber of the output gear 25 can be changed, so that the output gears 25 of different calibers can be replaced. Compared with the conventional technology, the transmission output structure 21 of the present invention does not need to be replaced as a whole, and the structure is more convenient and quicker in replacement, disassembly and other applications, saving replacement and maintenance time.
請參閱圖3及圖5,圖3是本發明的同軸雙旋翼渦輪傳動無人載具機構系統的示意圖,圖5為本發明的同軸雙旋翼機構的立體圖。同軸雙旋翼機構30包括一大主軸40、一小主軸50、一上主旋翼組60、一下主旋翼組70、複數上旋翼葉片氣動構型80、複數下旋翼葉片氣動構型90、一上同軸雙旋翼十字盤相位控制固定座結構100以及一下同軸雙旋翼十字盤相位控制固定座結構110。Please refer to FIG. 3 and FIG. 5. FIG. 3 is a schematic diagram of the coaxial dual-rotor turbine-driven unmanned vehicle mechanism system of the present invention. FIG. 5 is a perspective view of the coaxial dual-rotor mechanism of the present invention. The coaxial dual-rotor mechanism 30 includes a large main shaft 40, a small main shaft 50, an upper main rotor group 60, a lower main rotor group 70, a plurality of upper rotor blade aerodynamic configurations 80, a plurality of lower rotor blade aerodynamic configurations 90, and an upper coaxial The dual-rotor swashplate phase control mount structure 100 and the lower coaxial dual-rotor swashplate phase control mount structure 110.
大主軸40可旋轉地設於機身10,延伸穿過機身10的頂部,並且具有一軸孔(圖未示)。The main shaft 40 is rotatably disposed on the fuselage 10, extends through the top of the fuselage 10, and has a shaft hole (not shown).
小主軸50可旋轉地設於機身10並且延伸穿過大主軸40的軸孔。The small main shaft 50 is rotatably provided in the fuselage 10 and extends through a shaft hole of the large main shaft 40.
請參閱圖3以及圖6a至圖6d,圖3是本發明的同軸雙旋翼渦輪傳動無人載具機構系統的示意圖,圖6a為本發明的上主旋翼組的示意圖,圖6b為本發明的同軸雙旋翼方向控制固定座結構的立體圖,圖6c為本發明的同軸雙旋翼方向控制固定座結構的分解圖,圖6d為本發明的同軸雙旋翼方向控制固定座結構的另一角度分解圖。上主旋翼組60包括一上主旋翼固定座61及一同軸雙旋翼方向控制固定座結構62。Please refer to FIG. 3 and FIGS. 6 a to 6 d. FIG. 3 is a schematic diagram of a coaxial dual-rotor turbine-driven unmanned vehicle mechanism system of the present invention. FIG. 6 a is a schematic diagram of an upper main rotor set of the present invention, and FIG. 6 b is a coaxial of the present invention. A perspective view of the structure of the dual-rotor direction control fixing base. FIG. 6C is an exploded view of the coaxial double-rotor direction-control fixing base structure according to the present invention, and FIG. The upper main rotor group 60 includes an upper main rotor fixing base 61 and a coaxial double rotor direction control fixing structure 62.
上主旋翼固定座61設於小主軸50並且包括一上座體611、至少三上延伸臂612及至少三上槳夾頭613。至少三上延伸臂612間隔地突出於上座體611的一外環壁,各上延伸臂612與相鄰的二上延伸臂612的間隔距離相等。至少三上槳夾頭613設於至少三上延伸臂612的末端(亦即,遠離上座體611的一端)。通常來說,上延伸臂612的數量和上槳夾頭613的數量均為三個而且相鄰的二上延伸臂612之間的角度為一百二十度,所以上主旋翼固定座61的整體外觀呈人字形,如圖6a所示。The upper main rotor fixing seat 61 is disposed on the small main shaft 50 and includes an upper seat body 611, at least three upper extension arms 612, and at least three upper paddle chucks 613. At least three upper extension arms 612 protrude from an outer ring wall of the upper base 611 at intervals, and each of the upper extension arms 612 and an adjacent two upper extension arms 612 are spaced apart at the same distance. At least three upper paddle chucks 613 are provided at the ends of the at least three upper extension arms 612 (that is, the end away from the upper seat body 611). Generally speaking, the number of the upper extension arms 612 and the number of the upper paddle chucks 613 are three and the angle between the adjacent two upper extension arms 612 is one hundred and twenty degrees. Therefore, the The overall appearance is herringbone-shaped, as shown in Figure 6a.
同軸雙旋翼方向控制固定座結構62包括一本體63、一軸桿64、複數連桿65以及至少三支撐結構66,如圖6a所示。The coaxial double-rotor direction control fixing seat structure 62 includes a body 63, a shaft 64, a plurality of links 65, and at least three supporting structures 66, as shown in FIG. 6a.
本體63位於上主旋翼固定座61的上方且與上主旋翼固定座61同軸。在本實施例中,本體63包括一基座631及複數樞座632,該等樞座632樞設於基座631的外側。具體而言,基座631的一外環壁間隔地突出複數懸臂6311,該等樞座632分別樞設於該等懸臂6311。The main body 63 is located above the upper main rotor fixing base 61 and is coaxial with the upper main rotor fixing base 61. In this embodiment, the main body 63 includes a base 631 and a plurality of pivot bases 632, and the pivot bases 632 are pivotally disposed outside the base 631. Specifically, an outer ring wall of the base 631 protrudes from a plurality of cantilever arms 6311 at intervals, and the pivot bases 632 are respectively pivoted on the cantilever 6311.
軸桿64設於本體63與上主旋翼固定座61之間且延伸於本體63的一軸線與上主旋翼固定座61的一軸線上。具體來說,基座631於軸心處開設一基座軸孔6312,如圖6c及圖6d所示;上座體611於軸心處開設一上座體軸孔6111,如圖6a所示;軸桿64設於基座631與上座體611之間,兩端分別設於基座軸孔6312和上座體軸孔6111,並且延伸於基座631的一軸線113與上座體611的一軸線6112上,如圖6a和圖6b所示。The shaft 64 is provided between the main body 63 and the upper main rotor fixing base 61 and extends on an axis of the main body 63 and an axis of the upper main rotor fixing base 61. Specifically, the base 631 has a base shaft hole 6312 at the shaft center, as shown in FIG. 6c and FIG. 6d; the upper base 611 has an upper shaft hole 6111 at the shaft center, as shown in FIG. 6a; The rod 64 is provided between the base 631 and the upper base 611, and the two ends are respectively provided in the base shaft hole 6312 and the upper base shaft hole 6111, and extend on an axis 113 of the base 631 and an axis 6112 of the upper base 611. , As shown in Figure 6a and Figure 6b.
該等連桿65分別設於本體63的外側與上主旋翼固定座61的外側之間。更詳言之,該等連桿65的一端分別樞設於該等樞座632的外側,另一端分別樞設於至少三上延伸臂612的外側。The connecting rods 65 are respectively provided between the outside of the main body 63 and the outside of the upper main rotor fixing base 61. More specifically, one end of the connecting rods 65 is respectively pivoted on the outer side of the pivot bases 632, and the other end is respectively pivoted on the outer sides of the at least three upper extension arms 612.
至少三支撐結構66圍繞軸桿64而分別設於本體63的底部與上主旋翼固定座61的頂部之間,如圖6a所示。具體來說,基座631的外環壁間隔地突出至少三凸出部6314,各凸出部6314與相鄰的二凸出部6314的間隔距離相等,每個凸出部6314設於二懸臂6311之間並且長度比各懸臂6311的長度短;至少三支撐結構66均呈桿狀,並且圍繞軸桿64而分別設於至少三凸出部6314的底部與上主旋翼固定座61的頂部之間;其中,懸臂6311、凸出部6314、樞座632、連桿65和支撐結構66的數量均與上延伸臂612的數量相等,本實施例的上延伸臂612數量為三個,所以懸臂6311、凸出部6314、樞座632、連桿65和支撐結構66的數量皆同為三個。藉此,該等支撐結構66可提供三點支撐的效果,使得上主旋翼組60的穩定性比習知技術佳,所以相對小主軸50晃動的程度比習知技術小,進而在小主軸50和大主軸40藉由上同軸雙旋翼十字盤相位固定座100和下同軸雙旋翼十字盤相位固定座110以及複數第一連桿121和複數第三連桿123(參見圖8a)同步驅動上主旋翼組60與下主旋翼組70相對機身10傾斜,以改變本發明的飛行角度而相對機身10傾斜的時候,該等上旋翼葉片氣動構型80的傾斜角度比習知技術誤差更小;是以,與習知技術相較之下,本發明可更接近在預設角度上飛行。At least three supporting structures 66 are respectively arranged around the shaft 64 between the bottom of the body 63 and the top of the upper main rotor fixing base 61, as shown in FIG. 6a. Specifically, the outer ring wall of the base 631 protrudes at least three protrusions 6314 at intervals, and the distance between each protrusion 6314 and the adjacent two protrusions 6314 is equal, and each protrusion 6314 is provided on two cantilevers. 6311 and the length is shorter than the length of each cantilever 6311; at least three supporting structures 66 are rod-shaped, and are arranged around the shaft 64 at the bottom of at least three protrusions 6314 and the top of the upper main rotor fixing seat 61 respectively Among them, the number of the cantilever 6311, the projection 6314, the pivot base 632, the link 65 and the support structure 66 are all equal to the number of the upper extension arms 612. The number of the upper extension arms 612 in this embodiment is three, so the cantilever The number of 6311, the protruding portion 6314, the pivot base 632, the connecting rod 65 and the supporting structure 66 are all three. In this way, the supporting structures 66 can provide the effect of three-point support, so that the stability of the upper main rotor group 60 is better than that of the conventional technology. Therefore, the degree of shaking of the relatively small main shaft 50 is smaller than that of the conventional technology. The main spindle 40 and the main spindle 40 drive the upper main shaft synchronously by the upper coaxial double-rotor swashplate phase fixing base 100, the lower coaxial double-rotor swashplate phase fixing base 110, and a plurality of first connecting rods 121 and a plurality of third connecting rods 123 (see FIG. 8a). When the rotor group 60 and the lower main rotor group 70 are inclined with respect to the fuselage 10 to change the flight angle of the present invention and are inclined with respect to the fuselage 10, the tilt angles of the aerodynamic configurations 80 of the upper rotor blades are smaller than those of conventional techniques. Therefore, compared with the conventional technology, the present invention can be closer to flying at a preset angle.
較佳地,該等支撐結構66分別延伸通過並且垂直於該等上延伸臂612的軸線6121;換句話說,該等支撐結構66分別位在該等上延伸臂612的軸線6121上,而且分別垂直於該等上延伸臂612的延伸方向,如圖6a所示;各支撐結構66與相鄰的二支撐結構66的間隔距離相等。更明確地說,該等凸出部6314的延伸方向分別平行於該等上延伸臂612的延伸方向,各凸出部6314的一軸線63141位在對應的上延伸臂612的軸線6121的正上方,如圖6a所示;該等凸出部6314的底部分別開設一孔洞63142,該等孔洞63142分別延伸穿過並且垂直於該等凸出部6314的軸線63141;也就是說,該等孔洞63142分別位在該等凸出部6314的軸線63141上,而且分別垂直於該等凸出部6314的延伸方向,如圖6d所示;上主旋翼固定座61的頂部開設三穿孔614,該等穿孔614分別延伸穿過並且垂直於該等上延伸臂612的軸線6121,並且位於該等孔洞63142的正下方,如圖6a所示;也就是說,該等穿孔614分別位在各上延伸臂612的軸線6121上,而且分別垂直於該等上延伸臂612的延伸方向。較佳地,該等穿孔614進一步延伸貫穿上主旋翼固定座61的底部(圖未示)。在本實施例中,該等孔洞63142分別位在上座體611和該等上延伸臂612的交接處的正上方,該等穿孔614分別位在上座體611和該等上延伸臂612的交接處上,如圖6a所示。在其他實施例中,該等凸出部6314可延伸得比圖6a的實施例所顯示的更長,使得該等孔洞63142位在該等上延伸臂612的上方,該等穿孔614分別位在該等上延伸臂612上,亦無不可。該等支撐結構66的二端分別插設於該等孔洞63142與該等穿孔614。較佳地,該等孔洞63142為螺孔,該等支撐結構66的外側鄰近頂端處呈螺桿狀而螺設於該等孔洞63142中,如圖6d所示。藉此,該等支撐結構66可提供最穩固的三點支撐的效果,使得上主旋翼組60的穩定性達到最佳,所以完全不會相對小主軸50晃動,進而在小主軸50和大主軸40藉由上同軸雙旋翼十字盤相位固定座100和下同軸雙旋翼十字盤相位固定座110以及複數第一連桿121和複數第三連桿123(參見圖8a)同步驅動上主旋翼組60與下主旋翼組70相對機身10傾斜,以改變本發明的飛行角度而相對機身10傾斜的時候,該等上旋翼葉片氣動構型80的傾斜角度達到零誤差的效果而真正保持一致;藉此,本發明可精準地維持在預設角度上飛行,徹底解決習知技術的問題。Preferably, the support structures 66 respectively extend through and are perpendicular to the axis 6121 of the upper extension arms 612; in other words, the support structures 66 are respectively located on the axis 6121 of the upper extension arms 612, and respectively The extending directions perpendicular to the upper extending arms 612 are shown in FIG. 6a; the distance between each supporting structure 66 and the adjacent two supporting structures 66 is equal. More specifically, the extending directions of the protruding portions 6314 are parallel to the extending directions of the upper extending arms 612, respectively. An axis 63141 of each protruding portion 6314 is directly above the axis 6121 of the corresponding upper extending arm 612. As shown in FIG. 6a; a hole 63142 is respectively opened at the bottom of the protrusions 6314, and the holes 63142 respectively extend through and are perpendicular to the axis 63141 of the protrusions 6314; that is, the holes 63142 They are respectively located on the axis 63141 of the protrusions 6314, and are perpendicular to the extension direction of the protrusions 6314, respectively, as shown in FIG. 6d; the top of the upper main rotor fixing base 61 is provided with three perforations 614, and the perforations 614 respectively extend through and are perpendicular to the axis 6121 of the upper extension arms 612, and are located directly below the holes 63142, as shown in FIG. 6a; that is, the perforations 614 are located at the upper extension arms 612, respectively. The axis 6121 is perpendicular to the extending direction of the upper extending arms 612. Preferably, the perforations 614 further extend through the bottom of the upper main rotor fixing base 61 (not shown). In this embodiment, the holes 63142 are respectively located directly above the junctions of the upper base 611 and the upper extension arms 612, and the perforations 614 are respectively located at the junctions of the upper base 611 and the upper extension arms 612. Up, as shown in Figure 6a. In other embodiments, the protrusions 6314 may extend longer than shown in the embodiment of FIG. 6a, so that the holes 63142 are located above the upper extension arms 612, and the perforations 614 are located at On the upper extending arms 612, nothing is impossible. Two ends of the supporting structures 66 are respectively inserted in the holes 63142 and the perforations 614. Preferably, the holes 63142 are screw holes, and the outer sides of the supporting structures 66 are screw-shaped near the top end and are screwed in the holes 63142, as shown in FIG. 6d. In this way, the support structures 66 can provide the most stable three-point support effect, and make the upper main rotor group 60 have the best stability, so it will not shake relative to the small main shaft 50, and then the small main shaft 50 and the large main shaft. 40 The upper main rotor group 60 is synchronously driven by the upper coaxial double-rotor swashplate phase fixing base 100 and the lower coaxial double-rotor swashplate phase fixing base 110 and a plurality of first links 121 and a plurality of third links 123 (see FIG. 8a). When tilting with the lower main rotor group 70 relative to the fuselage 10 to change the flight angle of the present invention and tilting relative to the fuselage 10, the tilt angles of the upper rotor blade aerodynamic configurations 80 reach the effect of zero error and truly remain consistent; With this, the present invention can accurately maintain the flight at a preset angle and completely solve the problems of the conventional technology.
值得一提的是,由於本發明至少有三個支撐結構66,三支撐結構66的滑動與強度足以改善先前技術容易受力變形的問題,使上主旋翼組60的穩定性能夠維持在一定的水準,至少保有「該等上旋翼葉片氣動構型80的傾斜角度比習知技術誤差更小」的功效;藉此,與習知技術相較之下,本發明仍然維持可更接近在預設角度上飛行的效果,不會因轉動變形而發生喪失「提升上主旋翼組60的穩定性」的功效的問題。It is worth mentioning that since the present invention has at least three support structures 66, the sliding and strength of the three support structures 66 are sufficient to improve the problem of easy deformation of the prior art, so that the stability of the upper main rotor group 60 can be maintained at a certain level. , At least retain the effect of "the tilt angle of the upper rotor blade aerodynamic configuration 80 is smaller than the conventional technology error"; thus, compared with the conventional technology, the present invention still maintains closer to the preset angle The effect of the upward flight will not cause the loss of the effect of "improving the stability of the upper main rotor group 60" due to the rotation deformation.
請參閱圖8a,圖8a為本發明的同軸雙旋翼機構的立體放大示意圖。下主旋翼組70包括一下主旋翼固定座71,下主旋翼固定座71設於大主軸40並且包括一下座體711、至少三下延伸臂712及至少三下槳夾頭713。實際上,下主旋翼固定座71的下座體711、該等下延伸臂712及該等下槳夾頭713等構件的結構及其連結關係,大致上與上主旋翼固定座61的上座體611、該等上延伸臂612及該等上槳夾頭613等構件及其連結關係的結構相似,故在此不予贅述。值得一提的是,下主旋翼組70不包括同軸雙旋翼方向控制固定座結構,此點與上主旋翼組60不同。Please refer to FIG. 8a, which is an enlarged three-dimensional schematic diagram of the coaxial dual-rotor mechanism of the present invention. The lower main rotor set 70 includes a lower main rotor fixing base 71. The lower main rotor fixing base 71 is disposed on the main shaft 40 and includes a lower base body 711, at least three lower extension arms 712, and at least three lower paddle chucks 713. In fact, the structure of the lower base body 711 of the lower main rotor fixed seat 71, the lower extension arms 712, and the lower paddle chucks 713 and their connection relationship are substantially the same as those of the upper seat of the upper main rotor fixed seat 61. 611. The components such as the upper extension arms 612 and the upper paddle chucks 613 and their connection relationships are similar, so they are not described herein again. It is worth mentioning that the lower main rotor group 70 does not include a coaxial double rotor direction control fixed seat structure, which is different from the upper main rotor group 60.
請參閱圖3、圖7a、圖7b,圖3是本發明的同軸雙旋翼渦輪傳動無人載具機構系統的示意圖,圖7a為本發明的上、下旋翼葉片氣動構型的第一實施例的俯視圖,圖7b為本發明的上、下旋翼葉片氣動構型的第一實施例的槳葉本體的剖視圖。上旋翼葉片氣動構型80包括一上槳葉本體81、一上結合部82以及一上翼尖部83。下旋翼葉片氣動構型90包括一下槳葉本體91、一下結合部92以及一下翼尖部93Please refer to FIG. 3, FIG. 7a, and FIG. 7b. FIG. 3 is a schematic diagram of the coaxial dual-rotor turbine-driven unmanned vehicle mechanism system of the present invention. FIG. 7a is a first embodiment of the aerodynamic configuration of the upper and lower rotor blades of the present invention. In a top view, FIG. 7b is a sectional view of the blade body of the first embodiment of the aerodynamic configuration of the upper and lower rotor blades of the present invention. The upper rotor blade aerodynamic configuration 80 includes an upper blade body 81, an upper joint portion 82, and an upper wing tip portion 83. The lower rotor blade aerodynamic configuration 90 includes a lower blade body 91, a lower coupling portion 92, and a lower wing tip portion 93.
上、下槳葉本體81、91呈直線狀,其長度方向的二端分別界定為一第一端811、911及一第二端812、912,其寬度方向的二側分別界定為一第一側邊813、913及一第二側邊814、914,並且具有一頂面815、915及一底面816、916。請參閱圖7b,上、下槳葉本體81、91的底面816、916從上、下槳葉本體81、91的第一側邊813、913往上、下槳葉本體81、91的第二側邊814、914彎曲的曲率大於上、下槳葉本體81、91的頂面815、915從上、下槳葉本體81、91的第一側邊813、913往上、下槳葉本體81、91的第二側邊814、914彎曲的曲率,使得上、下槳葉本體81、91的頂面815、915和底面816、916的高低起伏不一致而呈非對稱狀。換句話說,上、下槳葉本體81、91的底面816、916從第一側邊813、913至第二側邊814、914的弧長大於上、下槳葉本體81、91的頂面815、915從第一側邊813、913至第二側邊814、914的弧長,也就是說,上、下槳葉本體81、91的頂面815、915比上、下槳葉本體81、91的底面816、916還要平坦。更明確地說,在本實施例中,上、下槳葉本體81、91的頂面815、915從上、下槳葉本體81、91的第一側邊813、913先向上彎曲,然後平坦地往上、下槳葉本體81、91的第二側邊814、914延伸;上、下槳葉本體81、91的底面816、916從上、下槳葉本體81、91的第一側邊813、913先向下彎曲,然後向上彎曲至上、下槳葉本體81、91的第二側邊814、914。一般來說,上、下槳葉本體81、91的第一側邊813、913為前側,上、下槳葉本體81、91的第二側邊814、914為後側;上、下旋翼葉片氣動構型80、90在旋轉時,通常是往後側方向轉動;藉此,氣流在通過上、下旋翼葉片氣動構型80、90時,上、下槳葉本體81、91的底面816、916產生的渦流足以讓本發明所產生的升力大於習知技術所產生的升力。The upper and lower blade bodies 81 and 91 are linear, and the two ends in the length direction are respectively defined as a first end 811, 911 and a second end 812, 912, and the two sides in the width direction are respectively defined as a first The side edges 813, 913 and a second side edge 814, 914 have a top surface 815, 915 and a bottom surface 816, 916. Referring to FIG. 7b, the bottom surfaces 816, 916 of the upper and lower blade bodies 81, 91 are from the first sides 813, 913 of the upper and lower blade bodies 81, 91 toward the second of the upper and lower blade bodies 81, 91. The curvature of the sides 814, 914 is larger than the top surfaces 815, 915 of the upper and lower blade bodies 81, 91. From the first sides 813, 913 of the upper and lower blade bodies 81, 91, the upper and lower blade bodies 81 are curved. The curved curvature of the second side edges 814 and 914 of the first and second blades 91 and 91 makes the heights of the top surfaces 815 and 915 and the bottom surfaces 816 and 916 of the upper and lower blade bodies 81 and 91 inconsistent and uneven. In other words, the arc lengths of the bottom surfaces 816, 916 of the upper and lower blade bodies 81, 91 from the first side edges 813, 913 to the second side edges 814, 914 are larger than the top surfaces of the upper and lower blade bodies 81, 91. 815, 915 arc length from the first side 813, 913 to the second side 814, 914, that is, the top surfaces 815, 915 of the upper and lower blade bodies 81, 91 are longer than the upper and lower blade bodies 81 The bottom surfaces 816, 916 of 91 are also flat. More specifically, in this embodiment, the top surfaces 815, 915 of the upper and lower blade bodies 81, 91 are bent upward from the first sides 813, 913 of the upper and lower blade bodies 81, 91, and then flattened. Ground extends to the second sides 814, 914 of the upper and lower blade bodies 81, 91; the bottom surfaces 816, 916 of the upper and lower blade bodies 81, 91 are from the first sides of the upper and lower blade bodies 81, 91 813 and 913 are bent down first, and then bent up to the second sides 814 and 914 of the upper and lower blade bodies 81 and 91. Generally, the first sides 813 and 913 of the upper and lower blade bodies 81 and 91 are front sides, and the second sides 814 and 914 of the upper and lower blade bodies 81 and 91 are rear sides. The upper and lower rotor blades are When the aerodynamic configuration 80, 90 rotates, it usually rotates in the backward direction; thereby, when the airflow passes through the upper and lower rotor blades aerodynamic configuration 80, 90, the bottom surfaces 816 of the upper and lower blade bodies 81, 91, The vortex generated by 916 is sufficient to make the lift produced by the present invention greater than that produced by conventional techniques.
上、下結合部82、92設於上、下槳葉本體81、91的第一端811、911並且設於上、下槳夾頭613、713,如圖7a及圖5所示。The upper and lower coupling portions 82 and 92 are provided on the first ends 811 and 911 of the upper and lower blade bodies 81 and 91 and on the upper and lower blade chucks 613 and 713, as shown in FIGS. 7a and 5.
上、下翼尖部83、93設於上、下槳葉本體81、91的第二端812、912,與上、下槳葉本體81、91在同一個平面上延伸,並且往遠離上、下結合部82、92以及上、下槳葉本體81、91的第一側邊813、913的方向延伸,使得上、下翼尖部83、93的長度方向不同於上、下槳葉本體81、91的長度方向而與上、下槳葉本體81、91的長度方向具有一夾角Θ1。換句話說,上、下翼尖部83、93的延伸方向與上、下槳葉本體81、91的延伸方向不同。由於上、下槳葉本體81、91的第一側邊813、913為前側,上、下槳葉本體81、91的第二側邊814、914為後側,所以上、下翼尖部83、93實質上是往上、下槳葉本體81、91的斜後方延伸而呈現「後掠」的型態。藉此,渦線在離開升力線的情況將不再與升力線保持垂直狀態,因此可透過改善升力線分析法修正本發明沿升力線向上所產生的誘導速度,進而改善上、下翼尖部83、93的渦流特性,使得本發明所產生的升力大於習知技術所產生的升力,同時能夠降低上、下翼尖部83、93在高速旋轉的情況下所產生的區域性振動波的可能性,以達到降低阻力的效果。上述效果可在夾角Θ1的角度為20~45度有顯著的成效;尤其是當夾角Θ1的角度為35度時,上述效果能夠達到最佳。其中,上、下翼尖部83、93的寬度自靠近上、下槳葉本體81、91的第二端812、912往遠離上、下槳葉本體81、91的方向漸縮,也就是說,上、下翼尖部83、93的寬度往上、下槳葉本體81、91的斜後方漸縮,藉以輔助提升上述效果。The upper and lower wing tips 83, 93 are provided on the second ends 812, 912 of the upper and lower blade bodies 81, 91, and extend on the same plane as the upper and lower blade bodies 81, 91, and away from the upper, The lower joint portions 82 and 92 and the first side edges 813 and 913 of the upper and lower blade bodies 81 and 91 extend in directions, so that the length directions of the upper and lower wing tip portions 83 and 93 are different from the upper and lower blade bodies 81 And 91 have an angle Θ1 with the longitudinal direction of the upper and lower blade bodies 81 and 91. In other words, the extending directions of the upper and lower wing tip portions 83 and 93 are different from the extending directions of the upper and lower blade bodies 81 and 91. Since the first sides 813 and 913 of the upper and lower blade bodies 81 and 91 are front sides and the second sides 814 and 914 of the upper and lower blade bodies 81 and 91 are rear sides, the upper and lower wing tips 83 , 93 are essentially obliquely rearward of the upper and lower blade bodies 81 and 91 and present a "swept back" pattern. As a result, when the vortex line leaves the lift line, it will no longer remain perpendicular to the lift line, so the improved induction line analysis method can be used to correct the induction speed generated by the upward direction of the lift line, thereby improving the tip of the upper and lower wings. The eddy current characteristics of 83 and 93 make the lift generated by the present invention greater than that produced by the conventional technology, and at the same time can reduce the possibility of regional vibration waves generated by the upper and lower wing tips 83 and 93 under high-speed rotation. To achieve the effect of reducing resistance. The above effect can have significant effects when the angle of the included angle Θ1 is 20 to 45 degrees; especially when the angle of the included angle Θ1 is 35 degrees, the above effects can achieve the best. Among them, the widths of the upper and lower wing tip portions 83 and 93 are gradually tapered away from the upper and lower blade bodies 81 and 91 toward the second ends 812 and 912 of the upper and lower blade bodies 81 and 91, that is, The widths of the upper and lower wing tip portions 83 and 93 are gradually tapered to the oblique rear of the upper and lower blade bodies 81 and 91, so as to help enhance the above effects.
值得一提的是,第一實施例的非對稱狀的上、下槳葉本體81、91配合後掠式的上、下翼尖部83、93,使其整體結構型態可稱之為「第一種非對稱翼之旋翼翼型,有後掠翼尖」的上、下旋翼葉片氣動構型80、90。It is worth mentioning that the asymmetrical upper and lower blade bodies 81 and 91 of the first embodiment cooperate with the swept-up upper and lower wing tips 83 and 93, so that the overall structure can be called " The first asymmetric airfoil rotor airfoil has aerodynamic configurations 80 and 90 of the upper and lower rotor blades with swept wing tips.
在第二實施例中,省略了第一實施例的「上、下翼尖部83、93與上、下槳葉本體81、91在同一個平面上延伸,並且往遠離上、下結合部82、92以及上、下槳葉本體81、91的第一側邊813、913的方向延伸,使得上、下翼尖部83、93的長度方向不同於上、下槳葉本體81、91的長度方向而與上、下槳葉本體81、91的長度方向具有一夾角Θ1」等技術特徵,保留第一實施例的「上、下槳葉本體81、91的底面816、916從上、下槳葉本體81、91的第一側邊813、913往上、下槳葉本體81、91的第二側邊814、914彎曲的曲率大於上、下槳葉本體81、91的頂面815、915從上、下槳葉本體81、91的第一側邊813、913往上、下槳葉本體81、91的第二側邊814、914彎曲的曲率,使得上、下槳葉本體81、91的頂面815、915和底面816、916的高低起伏不一致而呈非對稱狀」等技術特徵及其功效。至於,第二實施例的上、下翼尖部83、93與上、下槳葉本體81、91的關係則無特別限制。舉例來說,第二實施例的上、下翼尖部83、93可能與上、下槳葉本體81、91在不同一個平面上延伸,亦即,上、下翼尖部83、93相對上、下槳葉本體81、91垂直向上、垂直向下、傾斜向上或者傾斜向下。或者,上、下翼尖部83、93與上、下槳葉本體81、91在同一個平面上延伸,並且往遠離上、下結合部82、92的方向直線延伸,使得其長度方向與上、下槳葉本體81、91的長度方向相同而與上、下槳葉本體81、91的長度方向平行。整體來說,第二實施例的任意一種實施態樣皆可統攝稱之為「非對稱翼之旋翼翼型,無後掠翼尖」的上、下旋翼葉片氣動構型80、90。In the second embodiment, "the upper and lower wing tips 83, 93 and the upper and lower blade bodies 81, 91 extend on the same plane, and are away from the upper and lower joints 82," the first embodiment is omitted. , 92, and the first side edges 813, 913 of the upper and lower blade bodies 81, 91 extend so that the length direction of the upper and lower wing tip portions 83, 93 is different from the length of the upper and lower blade bodies 81, 91 It has technical characteristics such as an angle θ1 with the longitudinal direction of the upper and lower blade bodies 81 and 91, and retains the bottom surfaces 816 and 916 of the upper and lower blade bodies 81 and 91 from the upper and lower blades of the first embodiment. The first side edges 813, 913 of the blade bodies 81, 91 go up and down, and the second side edges 814, 914 of the blade bodies 81, 91 have a curved curvature greater than the top surfaces 815, 915 of the upper and lower blade bodies 81, 91. The curvature from the first sides 813, 913 of the upper and lower blade bodies 81, 91 to the second sides 814, 914 of the upper and lower blade bodies 81, 91 is curved, so that the upper and lower blade bodies 81, 91 The top and bottom surfaces 815 and 915 and the bottom surface 816 and 916 have different heights and inconsistencies and are asymmetrical "and other technical characteristics and their effects. As for the relationship between the upper and lower wing tip portions 83 and 93 and the upper and lower blade bodies 81 and 91 of the second embodiment, there is no particular limitation. For example, the upper and lower wing tip portions 83, 93 of the second embodiment may extend on a different plane from the upper and lower blade body 81, 91, that is, the upper and lower wing tip portions 83, 93 are relatively upward , The lower blade bodies 81, 91 are vertically upward, vertically downward, inclined upward, or inclined downward. Alternatively, the upper and lower wing tips 83, 93 and the upper and lower blade bodies 81, 91 extend on the same plane, and extend linearly in a direction away from the upper and lower joint portions 82, 92, so that the length direction is equal to the upper direction The longitudinal directions of the lower blade bodies 81 and 91 are the same and parallel to the longitudinal directions of the upper and lower blade bodies 81 and 91. In general, any of the implementation forms of the second embodiment can collectively capture the aerodynamic configurations 80 and 90 of the upper and lower rotor blades called "asymmetric airfoil rotor airfoil, without swept-back wing tip".
在第三實施例中,省略了第一實施例的「上、下槳葉本體81、91的底面816、916從上、下槳葉本體81、91的第一側邊813、913往上、下槳葉本體81、91的第二側邊814、914彎曲的曲率大於上、下槳葉本體81、91的頂面815、915從上、下槳葉本體81、91的第一側邊813、913往上、下槳葉本體81、91的第二側邊814、914彎曲的曲率,使得上、下槳葉本體81、91的頂面815、915和底面816、916的高低起伏不一致而呈非對稱狀」等技術特徵,保留了第一實施例的「上、下翼尖部83、93與上、下槳葉本體81、91在同一個平面上延伸,並且往遠離上、下結合部82、92以及上、下槳葉本體81、91的第一側邊813、913的方向延伸,使得上、下翼尖部83、93的長度方向不同於上、下槳葉本體81、91的長度方向而與上、下槳葉本體81、91的長度方向具有一夾角Θ1」等技術特徵及其功效。至於,第三實施例的上、下槳葉本體81、91的頂面815、915和底面816、916的關係則無特別限制。舉例來說,第三實施例的上、下槳葉本體81、91的頂面815、915和底面816、916從上、下槳葉本體81、91的第一側邊813、913往上、下槳葉本體81、91的第二側邊814、914彎曲的曲率相等,上、下槳葉本體81、91的頂面815、915從上、下槳葉本體81、91的第一側邊813、913先向上彎曲,然後向下彎曲至上、下槳葉本體81、91的第二側邊814、914,上、下槳葉本體81、91的底面816、916從上、下槳葉本體81、91的第一側邊813、913先向下彎曲,然後向上彎曲至上、下槳葉本體81、91的第二側邊814、914,使得上、下槳葉本體81、91的頂面815、915和底面816、916的高低起伏一致,此種實施態樣的第三實施例可稱之為「對稱翼之旋翼翼型,有後掠翼尖」的上、下旋翼葉片氣動構型80、90。或者,上、下槳葉本體81、91的底面816、916從上、下槳葉本體81、91的第一側邊813、913往上、下槳葉本體81、91的第二側邊814、914彎曲的曲率小於上、下槳葉本體81、91的頂面815、915從上、下槳葉本體81、91的第一側邊813、913往上、下槳葉本體81、91的第二側邊814、914彎曲的曲率,使得上、下槳葉本體81、91的頂面815、915和底面816、916的高低起伏不一致而呈非對稱狀,此種實施態樣的第三實施例可稱之為「第二種非對稱翼型,有後掠翼尖」的上、下旋翼葉片氣動構型80、90。In the third embodiment, "the bottom surfaces 816, 916 of the upper and lower blade bodies 81, 91 are omitted from the first side edges 813, 913 of the upper and lower blade bodies 81, 91, The second side edges 814, 914 of the lower blade bodies 81, 91 have a curved curvature greater than the top surfaces 815, 915 of the upper and lower blade bodies 81, 91, from the first side edges 813 of the upper and lower blade bodies 81, 91. The curved curvature of the second side edges 814 and 914 of the upper and lower blade bodies 81 and 91 is caused by the upward and downward movements of the upper and lower blade bodies 81 and 91, so that the top and bottom surfaces 815 and 915 of the upper and lower blade bodies 81 and 91 and the bottom surfaces 816 and 916 are inconsistent. "Asymmetrical" and other technical features, retaining the "upper and lower wing tips 83 and 93 and the upper and lower paddle bodies 81 and 91 on the same plane extending from the upper and lower blades of the first embodiment, and combined away from the upper and lower The sections 82, 92 and the first side edges 813, 913 of the upper and lower blade bodies 81, 91 extend in directions such that the length direction of the upper and lower wing tip portions 83, 93 is different from the upper and lower blade bodies 81, 91. It has technical characteristics such as an angle θ1 ″ with the longitudinal direction of the upper and lower blade bodies 81 and 91 and their effects. As for the relationship between the top surfaces 815 and 915 and the bottom surfaces 816 and 916 of the upper and lower blade bodies 81 and 91 of the third embodiment, there is no particular limitation. For example, the top surfaces 815 and 915 and the bottom surfaces 816 and 916 of the upper and lower blade bodies 81 and 91 of the third embodiment are upward from the first sides 813 and 913 of the upper and lower blade bodies 81 and 91, The second sides 814, 914 of the lower blade bodies 81, 91 have the same curvature, and the top surfaces 815, 915 of the upper and lower blade bodies 81, 91 are from the first sides of the upper and lower blade bodies 81, 91. 813, 913 bend upward first, then bend down to the second sides 814, 914 of the upper and lower blade bodies 81, 91, and the bottom surfaces 816, 916 of the upper and lower blade bodies 81, 91 from the upper and lower blade bodies The first sides 813, 913 of 81, 91 are bent down first, and then bent up to the second sides 814, 914 of the upper and lower blade bodies 81, 91, so that the top surfaces of the upper and lower blade bodies 81, 91 The 815, 915 and the bottom surface 816, 916 have the same height fluctuations. The third embodiment of this embodiment can be referred to as the aerodynamic configuration of the upper and lower rotor blades of a "symmetry wing rotor airfoil with swept-back wing tips". 80, 90. Alternatively, the bottom surfaces 816, 916 of the upper and lower blade bodies 81, 91 go from the first sides 813, 913 of the upper and lower blade bodies 81, 91 toward the second sides 814 of the upper and lower blade bodies 81, 91. , 914 The curvature of the curvature is smaller than that of the top surfaces 815, 915 of the upper and lower blade bodies 81, 91 from the first sides 813, 913 of the upper and lower blade bodies 81, 91 toward the upper and lower blade bodies 81, 91. The curved curvature of the second side edges 814 and 914 makes the top and bottom surfaces 815 and 915 and bottom surfaces 816 and 916 of the upper and lower blade bodies 81 and 91 inconsistent and undulating and asymmetric. The third aspect of this embodiment The embodiment may be referred to as the aerodynamic configuration 80, 90 of the upper and lower rotor blades of the "second asymmetric airfoil with swept-back wing tips".
請參閱圖7c、表一以及表二,圖7c為習知技術、本發明的第一實施例和第二實施例的同軸雙旋翼渦輪傳動無人載具機構系統的升力比較圖,表一為習知技術、本發明的第一實施例和第二實施例的同軸雙旋翼渦輪傳動無人載具機構系統在俯仰角為12度以及轉速為1000RPM、1200RPM和1400RPM等條件下的升力比較表格,表二為習知技術、本發明的第一實施例和第二實施例的同軸雙旋翼渦輪傳動無人載具機構系統在俯仰角為12度以及轉速為1000RPM、1200RPM和1400RPM等條件下的升力倍率差異比較表格。其中,N為牛頓,升力係數為CT=升力/ρπR2U2tip。Please refer to FIG. 7c, Table 1 and Table 2. FIG. 7c is a lift comparison diagram of a conventional coaxial double-rotor turbine-driven unmanned vehicle mechanism system of the first embodiment and the second embodiment of the present invention. Lifting force comparison table of the known technology, the first embodiment and the second embodiment of the coaxial dual-rotor turbine-driven unmanned vehicle system at a pitch angle of 12 degrees and a rotation speed of 1000 RPM, 1200 RPM, and 1400 RPM, Table 2 Comparison of lift ratios of coaxial dual-rotor turbine-driven unmanned vehicle mechanism systems for conventional technology, the first embodiment and the second embodiment of the invention under the conditions of a pitch angle of 12 degrees and a rotation speed of 1000 RPM, 1200 RPM, and 1400 RPM form. Among them, N is Newton, and the lift coefficient is CT = lift / ρπR2U2tip.
表一 <TABLE border="1" borderColor="#000000" width="85%"><TBODY><tr><td> 旋翼 名稱 </td><td> 習知技術 </td><td> 第二實施例 </td><td> 第一實施例 </td></tr><tr><td> 俯仰角 </td><td> 12° </td></tr><tr><td> 轉速(RPM) </td><td> 1000 </td><td> 1200 </td><td> 1400 </td><td> 1000 </td><td> 1200 </td><td> 1400 </td><td> 1000 </td><td> 1200 </td><td> 1400 </td></tr><tr><td> 升力(N) </td><td> 284.3 </td><td> 372.2 </td><td> 467 </td><td> 320.91 </td><td> 421.45 </td><td> 536.87 </td><td> 362.81 </td><td> 461.57 </td><td> 558.37 </td></tr><tr height="0"><td></td><td></td><td></td><td></td><td></td><td></td><td></td><td></td><td></td><td></td><td></td><td></td></tr></TBODY></TABLE>Table I <TABLE border = "1" borderColor = "# 000000" width = "85%"> <TBODY> <tr> <td> Rotor name </ td> <td> Know-how </ td> <td> Second Example </ td> <td> First example </ td> </ tr> <tr> <td> Pitch angle </ td> <td> 12 ° </ td> </ tr> <tr> < td> Speed (RPM) </ td> <td> 1000 </ td> <td> 1200 </ td> <td> 1400 </ td> <td> 1000 </ td> <td> 1200 </ td> <td> 1400 </ td> <td> 1000 </ td> <td> 1200 </ td> <td> 1400 </ td> </ tr> <tr> <td> Lift (N) </ td> <td> 284.3 </ td> <td> 372.2 </ td> <td> 467 </ td> <td> 320.91 </ td> <td> 421.45 </ td> <td> 536.87 </ td> <td > 362.81 </ td> <td> 461.57 </ td> <td> 558.37 </ td> </ tr> <tr height = "0"> <td> </ td> <td> </ td> <td > </ td> <td> </ td> <td> </ td> <td> </ td> <td> </ td> <td> </ td> <td> </ td> <td> </ td> <td> </ td> <td> </ td> </ tr> </ TBODY> </ TABLE>
表二 <TABLE border="1" borderColor="#000000" width="85%"><TBODY><tr><td> 旋翼比較組合 </td><td> 第一實施例/ 第二實施例 </td><td> 第一實施例/ 習知技術 </td><td> 第二實施例/ 習知技術 </td></tr><tr><td> 俯仰角12 ˚&轉速1000RPM時的升力倍率差異 </td><td> 1.131倍 </td><td> 1.276倍 </td><td> 1.128倍 </td></tr><tr><td> 俯仰角12 ˚&轉速1200RPM時的升力倍率差異 </td><td> 1.095倍 </td><td> 1.240倍 </td><td> 1.132倍 </td></tr><tr><td> 俯仰角12 ˚&轉速1400RPM的升力倍率差異 </td><td> 1.040倍 </td><td> 1.195倍 </td><td> 1.149倍 </td></tr></TBODY></TABLE>Table II <TABLE border = "1" borderColor = "# 000000" width = "85%"> <TBODY> <tr> <td> Comparison of rotors </ td> <td> First embodiment / second embodiment </ td td> <td> First embodiment / known technology </ td> <td> Second embodiment / known technology </ td> </ tr> <tr> <td> Pitch angle 12 ˚ & rotation speed 1000RPM Lift magnification difference at different times </ td> <td> 1.131 times </ td> <td> 1.276 times </ td> <td> 1.128 times </ td> </ tr> <tr> <td> Pitch angle 12 ˚ & Difference in lift magnification at 1200 RPM </ td> <td> 1.095 times </ td> <td> 1.240 times </ td> <td> 1.132 times </ td> </ tr> <tr> <td> Pitch angle 12 ˚ & RPM 1400RPM lift magnification difference </ td> <td> 1.040 times </ td> <td> 1.195 times </ td> <td> 1.149 times </ td> </ tr> </ TBODY > </ TABLE>
根據圖7c、表一以及表二,在俯仰角為12度以及轉速為1000RPM等條件之下,第一實施例所產生的升力約為第二實施例所產生的升力的1.131倍,第一實施例所產生的升力約為習知技術所產生的升力的1.276倍,第二實施例所產生的升力約為習知技術所產生的升力的1.128倍;在俯仰角為12度以及轉速為1200RPM等條件之下,第一實施例所產生的升力約為第二實施例所產生的升力的1.095倍,第一實施例所產生的升力約為習知技術所產生的升力的1.240倍,第二實施例所產生的升力約為習知技術所產生的升力的1.132倍;在俯仰角為12度以及轉速為1400RPM等條件之下,第一實施例所產生的升力約為第二實施例所產生的升力的1.040倍,第一實施例所產生的升力約為習知技術所產生的升力的1.195倍,第二實施例所產生的升力約為習知技術所產生的升力的1.149倍。總的來說,在俯仰角為12度以及轉速為1000RPM、1200RPM和1400RPM等條件之下,第一實施例所產生的升力明顯大於第二實施例以及習知技術所產生的升力,第二實施例所產生的升力大於習知技術所產生的升力。According to Fig. 7c, Tables 1 and 2, under the conditions of a pitch angle of 12 degrees and a rotation speed of 1000 RPM, the lift generated by the first embodiment is about 1.131 times the lift generated by the second embodiment. The lift generated by the example is about 1.276 times the lift generated by the conventional technology. The lift generated by the second embodiment is about 1.128 times the lift generated by the conventional technology. At a pitch angle of 12 degrees and a rotation speed of 1200 RPM, etc. Under the conditions, the lift generated by the first embodiment is about 1.095 times the lift generated by the second embodiment, and the lift generated by the first embodiment is about 1.240 times the lift generated by the conventional technology. The lift generated by the example is about 1.132 times the lift generated by the conventional technology. Under the conditions of a pitch angle of 12 degrees and a rotation speed of 1400 RPM, the lift generated by the first embodiment is about the same as that produced by the second embodiment. 1.040 times the lift, the lift generated by the first embodiment is about 1.195 times the lift generated by the conventional technology, and the lift produced by the second embodiment is about 1.149 times the lift generated by the conventional technology. In general, under the conditions of a pitch angle of 12 degrees and a rotation speed of 1000 RPM, 1200 RPM, and 1400 RPM, the lift generated by the first embodiment is significantly greater than that produced by the second embodiment and the conventional technology. The lift generated by the example is greater than the lift generated by the conventional technology.
值得一提的是,在相同的俯仰角的條件之下,轉速愈大,第二實施例的升力愈趨近於第一實施例的升力。It is worth mentioning that, under the condition of the same pitch angle, the larger the rotation speed, the closer the lift of the second embodiment is to the lift of the first embodiment.
請參閱圖3以及圖8a至圖8e,圖3是本發明的同軸雙旋翼渦輪傳動無人載具機構系統的示意圖,圖8a為本發明的上同軸雙旋翼十字盤相位控制固定座結構的立體圖,圖8b為本發明的上內環相位固定座組的立體圖,圖8c為本發明的上內環相位固定座組的分解圖,圖8d為本發明的上外環相位固定座組的立體圖,圖8e為本發明的上外環相位固定座組的分解圖。上同軸雙旋翼十字盤相位控制固定座結構100包括一上內環組101、一上外環組102、一上內環相位固定座組103以及一上外環相位固定座組104。Please refer to FIG. 3 and FIG. 8a to FIG. 8e. FIG. 3 is a schematic diagram of the coaxial dual-rotor turbo-drive unmanned vehicle mechanism system of the present invention. FIG. FIG. 8b is a perspective view of the upper inner ring phase fixing seat group of the present invention, FIG. 8c is an exploded view of the upper inner ring phase fixing seat group of the present invention, and FIG. 8d is a perspective view of the upper outer ring phase fixing seat group of the present invention. 8e is an exploded view of the upper outer ring phase fixing block group of the present invention. The upper coaxial double-rotor swashplate phase control fixed seat structure 100 includes an upper inner ring group 101, an upper outer ring group 102, an upper inner ring phase fixed seat group 103, and an upper outer ring phase fixed seat group 104.
上內環組101套設於小主軸50並且具有一上內環球頭1011。具體來說,上內環組101包含一上球型軸承1012、一上球型軸環1013及一上內環基座1014,小主軸50穿設於上球型軸承1012的一軸孔,上球型軸環1013環設於上球型軸承1012的外側,上內環基座1014環設於上球型軸環1013的外側且其上部的外周側突出複數上內環球頭1011,如圖8a及圖8b所示。The upper inner ring group 101 is sleeved on the small spindle 50 and has an upper inner ring head 1011. Specifically, the upper inner ring group 101 includes an upper ball bearing 1012, an upper ball collar 1013, and an upper inner ring base 1014. The small spindle 50 passes through a shaft hole of the upper ball bearing 1012, and the upper ball A ring 1013 is provided on the outer side of the upper ball bearing 1012. An upper inner ring base 1014 is provided on the outer side of the upper ball collar 1013 and a plurality of upper and lower ring heads 1011 protrude from the outer peripheral side of the upper portion, as shown in Figs. 8a and 8a. Figure 8b.
上外環組102環設於上內環組101並且具有一上外環球頭1021。更詳言之,上外環組102包含一上環型軸承1022及一上外環基座1023,上環型軸承1022環設於上內環基座1014的下部的外周側,上外環基座1023環設於上環型軸承1022的外側且其外周側突出複數上外環球頭1021,如圖8a及圖8d所示。The upper outer ring group 102 is arranged on the upper inner ring group 101 and has an upper and outer ring head 1021. In more detail, the upper outer ring group 102 includes an upper ring bearing 1022 and an upper outer ring base 1023. The upper ring bearing 1022 is ringed on the outer peripheral side of the lower portion of the upper inner ring base 1014, and the upper outer ring base 1023 A ring is provided on the outside of the upper ring bearing 1022 and a plurality of upper and outer ring heads 1021 protrude from the outer peripheral side thereof, as shown in FIGS. 8a and 8d.
上內環相位固定座組103包括一上內環相位固定座本體1031、一上內環連結件1032、一上內環接柄1033及複數上內環固定件1034,如圖8a、圖8b及圖8c所示。上內環相位固定座本體1031套設於小主軸50且位於上內環組101的上方。上內環連結件1032具有一第一端及一第二端,至少一上內環固定件1034螺設於上內環連結件1032的第一端與上內環相位固定座本體1031,使得上內環連結件1032的第一端被該上內環固定件1034固定於上內環相位固定座本體1031。上內環接柄1033具有一第一端及一第二端,至少一上內環固定件1034螺設於上內環接柄1033的第一端與上內環連結件1032的第二端,使得上內環接柄1033的第一端被該上內環固定件1034固定於上內環連結件1032的第二端。上內環接柄1033的第二端設於其中一上內環球頭1011。The upper inner ring phase fixing block group 103 includes an upper inner ring phase fixing base body 1031, an upper inner ring connecting piece 1032, an upper inner ring connecting handle 1033, and a plurality of upper inner ring fixing pieces 1034, as shown in Figs. 8a, 8b and Figure 8c. The upper inner ring phase fixing base body 1031 is sleeved on the small main shaft 50 and is located above the upper inner ring group 101. The upper inner ring connecting piece 1032 has a first end and a second end. At least one upper inner ring fixing piece 1034 is screwed on the first end of the upper inner ring connecting piece 1032 and the upper inner ring phase fixing base body 1031, so that the upper The first end of the inner ring connecting member 1032 is fixed to the upper inner ring phase fixing base body 1031 by the upper inner ring fixing member 1034. The upper inner ring connecting handle 1033 has a first end and a second end. At least one upper inner ring fixing member 1034 is screwed on the first end of the upper inner ring connecting handle 1033 and the second end of the upper inner ring connecting member 1032. The first end of the upper inner ring connecting handle 1033 is fixed to the second end of the upper inner ring connecting member 1032 by the upper inner ring fixing member 1034. The second end of the upper inner ring connecting handle 1033 is set on one of the upper inner ring heads 1011.
在一較佳實施例中,上內環連結件1032包含一第一上內環連桿1035及一第二上內環連桿1036。第一上內環連桿1035具有一第一端及一第二端,第二上內環連桿1036具有一第一端及一第二端。至少一上內環固定件1034螺設於第一上內環連桿1035的第一端與上內環相位固定座本體1031,使得第一上內環連桿1035的第一端被該上內環固定件1034固定於上內環相位固定座本體1031。至少一上內環固定件1034螺設於第二上內環連桿1036的第一端與第一上內環連桿1035的第二端,使得第二上內環連桿1036的第一端被該上內環固定件1034固定於第一上內環連桿1035的第二端。至少一上內環固定件1034螺設於上內環接柄1033的第一端與第二上內環連桿1036的第二端,使得上內環接柄1033的第一端被該上內環固定件1034固定於第二上內環連桿1036的第二端。In a preferred embodiment, the upper inner ring link 1032 includes a first upper inner ring link 1035 and a second upper inner ring link 1036. The first upper inner ring link 1035 has a first end and a second end, and the second upper inner ring link 1036 has a first end and a second end. At least one upper inner ring fixing member 1034 is screwed on the first end of the first upper inner ring link 1035 and the upper inner ring phase fixing seat body 1031, so that the first end of the first upper inner ring link 1035 is the upper inner The ring fixing member 1034 is fixed to the upper inner ring phase fixing base body 1031. At least one upper inner ring fixing member 1034 is screwed on the first end of the second upper inner ring link 1036 and the second end of the first upper inner ring link 1035, so that the first end of the second upper inner ring link 1036 The upper inner ring fixing member 1034 is fixed to the second end of the first upper inner ring link 1035. At least one upper inner ring fixing member 1034 is screwed on the first end of the upper inner ring connecting handle 1033 and the second end of the second upper inner ring connecting rod 1036, so that the first end of the upper inner ring connecting handle 1033 is the upper inner The ring fixing member 1034 is fixed to the second end of the second upper inner ring link 1036.
更清楚地說,第一上內環連桿1035包含一連接臂10351、二延伸臂10352及一柄部10353,第一上內環連桿1035的二延伸臂10352從第一上內環連桿1035的連接臂10351的二端延伸並且被界定為第一上內環連桿1035的第一端並且分別開設一穿孔10354,第一上內環連桿1035的二延伸臂10352的穿孔10354分別橫向貫穿第一上內環連桿1035的二延伸臂10352的二側,第一上內環連桿1035的柄部10353從第一上內環連桿1035的連接臂10351的中央往遠離第一上內環連桿1035的二延伸臂10352的方向延伸並且被界定為第一上內環連桿1035的第二端並且開設一貫穿其二側的螺孔10355;上內環相位固定座本體1031位於第一上內環連桿1035的連接臂10351與二延伸臂10352所圍構的空間中並且開設一貫穿其二側的螺孔10311,其中二上內環固定件1034分別橫向穿過第一上內環連桿1035的二延伸臂10352的穿孔10354並且分別從上內環相位固定座本體1031的螺孔10311的兩端開口螺設於該螺孔10311中,使得第一上內環連桿1035的二延伸臂10352分別被該二上內環固定件1034固定於上內環相位固定座本體1031的二側。第二上內環連桿1036包含一連接臂10361及二延伸臂10362,第二上內環連桿1036的二延伸臂10362從第二上內環連桿1036的連接臂10361的二端延伸並且被界定為第二上內環連桿1036的第一端並且分別開設一穿孔10363,第二上內環連桿1036的二延伸臂10362的穿孔10363分別橫向貫穿第二上內環連桿1036的二延伸臂10362的二側,第一上內環連桿1035的柄部10353位於第二上內環連桿1036的連接臂10361與二延伸臂10362所圍構的空間中,第二上內環連桿1036的連接臂10361被界定為第二上內環連桿1036的第二端並且開設一穿孔10364,第二上內環連桿1036的連接臂10361的穿孔10364縱向貫穿第二上內環連桿1036的連接臂10361的頂、底部;較佳地,第二上內環連桿1036的連接臂10361的穿孔10364位於第二上內環連桿1036的連接臂10361的中央;其中二上內環固定件1034分別橫向穿過第二上內環連桿1036的二延伸臂10362的穿孔10363並且分別從第一上內環連桿1035的柄部10353的螺孔10355的兩端開口螺設於該螺孔10355中,使得第二上內環連桿1036的二延伸臂10362分別被該二上內環固定件1034固定於第一上內環連桿1035的柄部10353的二側;上內環接柄1033的第一端開設一螺孔10331,其中一上內環固定件1034縱向穿過第二上內環連桿1036的連接臂10361的穿孔10364並且螺設於上內環接柄1033的第一端的螺孔10331,使得上內環接柄1033的第一端被該上內環固定件1034固定於第二上內環連桿1036的連接臂10361的底部。More specifically, the first upper inner link 1035 includes a connecting arm 10351, two extension arms 10352, and a handle 10353. The two upper arms 10352 of the first upper inner link 1035 extend from the first upper inner link The two ends of the connecting arm 10351 of 1035 extend and are defined as the first end of the first upper inner ring link 1035 and respectively have a perforation 10354. The perforations 10354 of the two extending arms 10352 of the first upper inner ring link 1035 are respectively transverse. Through both sides of the two extending arms 10352 of the first upper inner link 1035, the handle 10353 of the first upper inner link 1035 is away from the center of the first upper inner link 1035 The two extension arms 10352 of the inner ring link 1035 extend in the direction and are defined as the second end of the first upper inner ring link 1035 and open a screw hole 10355 penetrating the two sides thereof; the upper inner ring phase fixing body 1031 is located at In the space surrounded by the connecting arm 10351 and the two extension arms 10352 of the first upper inner ring link 1035, a screw hole 10311 is formed through the two sides of the first upper inner link 1035, and the two upper inner ring fixing members 1034 respectively pass through the first upper The perforations 10354 of the two extension arms 10352 of the inner ring link 1035 are respectively from the upper inner The two ends of the screw holes 1011 of the phase fixing base body 1031 are screwed in the screw holes 10311, so that the two extension arms 10352 of the first upper inner ring link 1035 are fixed by the two upper inner ring fixing members 1034 respectively in the upper inside. Two sides of the ring phase fixing base body 1031. The second upper inner ring link 1036 includes a connecting arm 10361 and two extending arms 10362. The two extending arms 10362 of the second upper inner ring link 1036 extend from two ends of the connecting arm 10361 of the second upper inner ring link 1036. A perforation 10363 is defined as the first end of the second upper inner ring link 1036, and the perforations 10363 of the two extension arms 10362 of the second upper inner ring link 1036 respectively penetrate the second upper inner ring link 1036 laterally. On both sides of the two extension arms 10362, the handle 10353 of the first upper inner ring link 1035 is located in the space surrounded by the connecting arm 10361 and the two extension arms 10362 of the second upper inner ring link 1036. The second upper inner ring The connecting arm 10361 of the connecting rod 1036 is defined as the second end of the second upper inner ring link 1036 and a perforation 10364 is opened. The perforating 10364 of the connecting arm 10361 of the second upper inner ring link 1036 penetrates the second upper inner ring longitudinally. The top and bottom of the connecting arm 10361 of the connecting rod 1036; preferably, the perforation 10364 of the connecting arm 10361 of the second upper inner ring connecting rod 1036 is located in the center of the connecting arm 10361 of the second upper inner ring connecting rod 1036; The inner ring fixing member 1034 passes through the two extension arms 1036 of the second upper inner ring link 1036 respectively. Two perforations 10363 are screwed into the screw holes 10355 from both ends of the screw holes 10355 of the shank portion 10353 of the first upper inner ring link 1035, so that the two extension arms 10362 of the second upper inner ring link 1036 The two upper inner ring fixing members 1034 are respectively fixed to two sides of the handle portion 10353 of the first upper inner ring link 1035; the first end of the upper inner ring connecting handle 1033 is provided with a screw hole 10331, and one of the upper inner ring is fixed The piece 1034 passes longitudinally through the through hole 10364 of the connecting arm 10361 of the second upper inner ring link 1036 and is screwed in the screw hole 10331 of the first end of the upper inner ring connecting handle 1033, so that the first end of the upper inner ring connecting handle 1033 The upper inner ring fixing member 1034 is fixed to the bottom of the connecting arm 10361 of the second upper inner ring link 1036.
上外環相位固定座組104包括一上外環相位固定座本體1041、一上外環連結件1042、一上外環接柄1043及複數上外環固定件1044,如圖8a、圖8d及圖8e所示。上外環相位固定座本體1041套設於小主軸50且位於上外環組102的下方。上外環連結件1042具有一第一端及一第二端,至少一上外環固定件1044螺設於上外環連結件1042的第一端與上外環相位固定座本體1041,使得上外環連結件1042的第一端被該上外環固定件1044固定於上外環相位固定座本體1041。上外環接柄1043具有一第一端及一第二端,至少一上外環固定件1044螺設於上外環接柄1043的第一端與上外環連結件1042的第二端,使得上外環接柄1043的第一端被該上外環固定件1044固定於上外環連結件1042的第二端。上外環接柄1043的第二端設於其中一上外環球頭1021。The upper outer ring phase fixing base group 104 includes an upper outer ring phase fixing base body 1041, an upper outer ring connecting piece 1042, an upper outer ring connecting handle 1043, and a plurality of upper outer ring fixing pieces 1044, as shown in Figs. 8a, 8d and Figure 8e. The upper outer ring phase fixing base body 1041 is sleeved on the small main shaft 50 and is located below the upper outer ring group 102. The upper outer ring connecting piece 1042 has a first end and a second end. At least one upper outer ring fixing piece 1044 is screwed on the first end of the upper outer ring connecting piece 1042 and the upper outer ring phase fixing base body 1041, so that the upper The first end of the outer ring connecting member 1042 is fixed to the upper outer ring phase fixing base body 1041 by the upper outer ring fixing member 1044. The upper outer ring connecting handle 1043 has a first end and a second end. At least one upper outer ring fixing member 1044 is screwed on the first end of the upper outer ring connecting handle 1043 and the second end of the upper outer ring connecting member 1042. The first end of the upper outer ring connecting handle 1043 is fixed to the second end of the upper outer ring connecting member 1042 by the upper outer ring fixing member 1044. The second end of the upper outer ring connecting handle 1043 is set on one of the upper and outer ring heads 1021.
在一較佳實施例中,上外環連結件1042包含一第一上外環連桿1045及一第二上外環連桿1046。第一上外環連桿1045具有一第一端及一第二端,第二上外環連桿1046具有一第一端及一第二端。至少一上外環固定件1044螺設於第一上外環連桿1045的第一端與上外環相位固定座本體1041,使得第一上外環連桿1045的第一端被該上外環固定件1044固定於上外環相位固定座本體1041。至少一上外環固定件1044螺設於第二上外環連桿1046的第一端與第一上外環連桿1045的第二端,使得第二上外環連桿1046的第一端被該上外環固定件1044固定於第一上外環連桿1045的第二端。至少一上外環固定件1044螺設於上外環接柄1043的第一端與第二上外環連桿1046的第二端,使得上外環接柄1043的第一端被該上外環固定件1044固定於第二上外環連桿1046的第二端。In a preferred embodiment, the upper outer ring link 1042 includes a first upper outer ring link 1045 and a second upper outer ring link 1046. The first upper outer ring link 1045 has a first end and a second end, and the second upper outer ring link 1046 has a first end and a second end. At least one upper outer ring fixing member 1044 is screwed on the first end of the first upper outer ring link 1045 and the upper outer ring phase fixing base body 1041, so that the first end of the first upper outer ring link 1045 is fixed by the upper and outer rings. The ring fixing member 1044 is fixed to the upper outer ring phase fixing base body 1041. At least one upper outer ring fixing member 1044 is screwed on the first end of the second upper outer ring link 1046 and the second end of the first upper outer ring link 1045, so that the first end of the second upper outer ring link 1046 The upper outer ring fixing member 1044 is fixed to the second end of the first upper outer ring link 1045. At least one upper outer ring fixing member 1044 is screwed on the first end of the upper outer ring connecting handle 1043 and the second end of the second upper outer ring connecting rod 1046, so that the first end of the upper outer ring connecting handle 1043 is upper and outer. The ring fixing member 1044 is fixed to the second end of the second upper outer ring link 1046.
更清楚地說,第一上外環連桿1045包含一連接臂10451、二延伸臂10452及一柄部10453,第一上外環連桿1045的二延伸臂10452從第一上外環連桿1045的連接臂10451的二端延伸並且被界定為第一上外環連桿1045的第一端並且分別開設一穿孔10454,第一上外環連桿1045的二延伸臂10452的穿孔10454分別橫向貫穿第一上外環連桿1045的二延伸臂10452的二側,第一上外環連桿1045的柄部10453從第一上外環連桿1045的連接臂10451的中央往遠離第一上外環連桿1045的二延伸臂10452的方向延伸並且被界定為第一上外環連桿1045的第二端並且其二側分別開設一螺孔10455;上外環相位固定座本體1041位於第一上外環連桿1045的連接臂10451與二延伸臂10452所圍構的空間中並且開設二螺孔10411,其中二上外環固定件1044分別橫向穿過第一上外環連桿1045的二延伸臂10452的穿孔10454並且分別螺設於上外環相位固定座本體1041的二螺孔10411中,使得第一上外環連桿1045的二延伸臂10452分別被二上外環固定件1044固定於上外環相位固定座本體1041的二側。第二上外環連桿1046包含一連接臂10461及二延伸臂10462,第二上外環連桿1046的二延伸臂10462從第二上外環連桿1046的連接臂10461的二端延伸並且被界定為第二上外環連桿1046的第一端並且分別開設一穿孔10463,第二上外環連桿1046的二延伸臂10462的穿孔10463分別橫向貫穿第二上外環連桿1046的二延伸臂10462的二側,第一上外環連桿1045的柄部10453位於第二上外環連桿1046的連接臂10461與二延伸臂10462所圍構的空間中,第二上外環連桿1046的連接臂10461被界定為第二上外環連桿1046的第二端並且開設一穿孔10464,第二上外環連桿1046的連接臂10461的穿孔10464縱向貫穿第二上外環連桿1046的連接臂10461的頂、底部;較佳地,第二上外環連桿1046的連接臂10461的穿孔10464位於第二上外環連桿1046的連接臂10461的中央;其中二上外環固定件1044分別橫向穿過第二上外環連桿1046的二延伸臂10462的穿孔10463並且分別螺設於第一上外環連桿1045的柄部10453的二螺孔10455中,使得第二上外環連桿1046的二延伸臂10462分別被該二上外環固定件1044固定於第一上外環連桿1045的柄部10453的二側;上外環接柄1043的第一端開設一螺孔10431,其中一上外環固定件1044縱向穿過第二上外環連桿1046的連接臂10461的穿孔10464並且螺設於上外環接柄1043的第一端的螺孔10431,使得上外環接柄1043的第一端被該上外環固定件1044固定於第二上外環連桿1046的連接臂10461的頂部。More specifically, the first upper outer ring link 1045 includes a connecting arm 10451, two extension arms 10452, and a handle 10453. The two upper arms 10452 of the first upper outer ring link 1045 extend from the first upper outer ring link. The two ends of the connecting arm 10451 of 1045 extend and are defined as the first end of the first upper outer ring link 1045 and each have a perforation 10454, and the perforations 10454 of the two extending arms 10452 of the first upper outer ring link 1045 are respectively transverse. Through both sides of the two extension arms 10452 of the first upper outer ring link 1045, the handle portion 10453 of the first upper outer ring link 1045 is far from the center of the connecting arm 10451 of the first upper outer ring link 1045. The two extension arms 10452 of the outer ring link 1045 extend in the direction and are defined as the second end of the first upper outer ring link 1045 and two screw holes 10455 are respectively opened on the two sides thereof; the upper outer ring phase fixing body 1041 is located at the first Two screw holes 10411 are opened in the space surrounded by the connecting arm 10451 and the two extending arms 10452 of the upper outer ring link 1045. The two upper outer ring fixing members 1044 pass through the first upper outer ring link 1045 respectively. The two extension arms 10452 are perforated 10454 and are screwed on the upper outer ring and fixed in phase. 10411 two screw holes 1041 in the body, such that the first upper outer link two extending arms 1045 are two of the 10452 on the outer ring fixing member 1044 is fixed to the outer sides of the holder body 1041 phase. The second upper outer ring link 1046 includes a connecting arm 10461 and two extension arms 10462. The two extending arms 10462 of the second upper outer ring link 1046 extend from two ends of the connecting arm 10461 of the second upper outer ring link 1046. It is defined as the first end of the second upper outer link 1046 and a perforation 10463 is respectively opened. The perforations 10463 of the two extension arms 10462 of the second upper outer link 1046 penetrate the second upper outer link 1046 laterally. On both sides of the two extension arms 10462, the handle 10453 of the first upper outer ring link 1045 is located in the space surrounded by the connecting arm 10461 and the two extension arms 10462 of the second upper outer ring link 1046. The second upper outer ring The connecting arm 10461 of the link 1046 is defined as the second end of the second upper outer ring link 1046 and a perforation 10464 is opened. The perforation 10464 of the connecting arm 10461 of the second upper outer ring link 1046 penetrates the second upper outer ring longitudinally. The top and bottom of the connecting arm 10461 of the connecting rod 1046; preferably, the perforation 10464 of the connecting arm 10461 of the second upper outer ring link 1046 is located in the center of the connecting arm 10461 of the second upper outer ring link 1046; The outer ring fixing member 1044 passes through the two extension arms 1046 of the second upper outer ring link 1046, respectively. The two perforations 10463 are screwed in the two screw holes 10455 of the handle 10453 of the first upper outer ring link 1045, respectively, so that the two extension arms 10462 of the second upper outer ring link 1046 are fixed by the two upper outer rings, respectively. The member 1044 is fixed to both sides of the handle 10453 of the first upper outer ring link 1045; the first end of the upper outer ring connecting handle 1043 defines a screw hole 10431, and one of the upper outer ring fixing members 1044 passes longitudinally through the second upper The perforation 10464 of the connecting arm 10461 of the outer ring link 1046 is screwed into the screw hole 10431 of the first end of the upper outer ring connecting handle 1043, so that the first end of the upper outer ring connecting handle 1043 is fixed by the upper outer ring fixing member 1044. The top of the connecting arm 10461 of the second upper outer ring link 1046 is fixed.
請參閱圖9a至圖9f,圖9a為本發明的同軸雙旋翼機構的另一視角立體放大示意圖,圖9b為本發明的上內環相位固定座組的另一視角立體圖,圖9c為本發明的限制旋轉角度的下內環相位固定座組的立體圖,圖9d為本發明的限制旋轉角度的下內環相位固定座組的分解圖,圖9e為本發明的限制旋轉角度的下內環相位固定座組的剖視圖,圖9f為本發明的下內環連結件向內旋轉至第二位置的剖視圖,圖9g為本發明的上內環連結件向外旋轉至最極限以及下內環連結件向內旋轉至第二位置的立體圖。下同軸雙旋翼十字盤相位控制固定座結構110包括一下內環組111、一下外環組112、一限制旋轉角度的下內環相位固定座組113以及一下外環相位固定座組。限制旋轉角度的下內環相位固定座組113設於大主軸40與下內環組111之間並且包括一下內環相位固定座本體114、一下內環連結件115、一下內環接柄116以及一限位裝置117。基本上,下同軸雙旋翼十字盤相位控制固定座結構110與上同軸雙旋翼十字盤相位控制固定座結構100的主要結構大致相同,二者差別之處在於;其一,上同軸雙旋翼十字盤相位控制固定座結構100設於小主軸50且藉由複數第一連桿121與上主旋翼組60相接;其二,上、下同軸雙旋翼十字盤相位控制固定座結構100、110藉由複數第二連桿122相接;其三,下同軸雙旋翼十字盤相位控制固定座結構110設於大主軸40且藉由複數第三連桿123與下主旋翼組70相接且藉由複數第四連桿124與機身10相接;其四,下同軸雙旋翼十字盤相位控制固定座結構110的限制旋轉角度的下內環相位固定座組113包括限位裝置117。Please refer to FIG. 9a to FIG. 9f. FIG. 9a is a perspective enlarged schematic view of the coaxial double rotor mechanism of the present invention from another perspective. FIG. 9b is another perspective perspective view of the upper inner ring phase fixing block of the present invention. A perspective view of the lower inner ring phase fixed seat group with limited rotation angle. FIG. 9d is an exploded view of the lower inner ring phase fixed seat group with limited rotation angle. FIG. 9e is a lower inner ring phase with limited rotation angle of the invention. 9f is a cross-sectional view of the lower inner ring link rotating inwardly to the second position, and FIG. 9g is a view of the upper inner ring link rotating outward to the extreme limit and the lower inner ring link of the present invention. A perspective view that rotates inward to the second position. The lower coaxial double-rotor swashplate phase control fixed structure 110 includes a lower inner ring group 111, a lower outer ring group 112, a lower inner ring phase fixed seat group 113 that restricts a rotation angle, and a lower outer ring phase fixed seat group. A lower inner ring phase fixing block group 113 with a restricted rotation angle is provided between the main spindle 40 and the lower inner ring group 111 and includes a lower inner ring phase fixing block body 114, a lower inner ring connecting member 115, a lower inner ring connecting handle 116, and A limiting device 117. Basically, the main structure of the lower coaxial dual-rotor swashplate phase control mount structure 110 and the upper coaxial dual-rotor swashplate phase control mount structure 100 are substantially the same, and the difference between the two lies in: first, the upper coaxial dual-rotor swashplate phase control The phase control fixed structure 100 is arranged on the small main shaft 50 and is connected to the upper main rotor group 60 through a plurality of first links 121. Second, the upper and lower coaxial double-rotor swashplate phase control fixed structures 100 and 110 are provided by The plurality of second connecting rods 122 are connected; third, the lower coaxial double-rotor swashplate phase control fixing structure 110 is provided on the main shaft 40 and is connected to the lower main rotor group 70 through a plurality of third connecting rods 123 and is connected through a plurality of The fourth link 124 is connected to the fuselage 10; fourthly, the lower inner ring phase fixed seat group 113 of the lower coaxial double-rotor swashplate phase control fixed seat structure 110 that restricts the rotation angle includes a limiting device 117.
藉此,本發明藉由上內環固定件1034以螺固的方式提升上內環相位固定座本體1031、上內環連結件1032以及上內環接柄1033三者的結合緊密度,同時藉由上外環固定件1044以螺固的方式提升上外環相位固定座本體1041、上外環連結件1042以及上外環接柄1043三者的結合緊密度,使得上內環相位固定座組103以及上外環相位固定座組104的整體結構的結合緊密度被提高;更且,藉由下內環固定件以螺固的方式提升下內環相位固定座本體114、下內環連結件115以及下內環接柄116三者的結合緊密度,同時藉由下外環固定件以螺固的方式提升下外環相位固定座本體、下外環連結件以及下外環接柄三者的結合緊密度,使得限制旋轉角度的下內環相位固定座組113以及下外環相位固定座組的整體結構的結合緊密度被提高。藉此,當上、下主旋翼組60、70分別藉由同軸的小、大主軸50、40驅動二者在同一個軸線上反向旋轉的時候,同軸雙旋翼機構30整體會產生振動,此時上、下內環連結件完全不會從上、下內環相位固定座本體上鬆脫,上、下內環接柄完全不會從上、下內環連結件上鬆脫,上、下外環連結件完全不會從上、下外環相位固定座本體上鬆脫,上、下外環接柄完全不會從上、下外環連結件上鬆脫,從而維持上、下同軸雙旋翼十字盤相位控制固定座結構100、110改變本發明的飛行角度的功能。With this, the present invention improves the tightness of the combination of the upper inner ring phase fixing base body 1031, the upper inner ring connecting piece 1032, and the upper inner ring connecting handle 1033 by means of the upper inner ring fixing member 1034 in a screwing manner. The tightness of the upper outer ring phase fixing base body 1041, the upper outer ring connecting piece 1042, and the upper outer ring connecting handle 1043 is improved by the upper outer ring fixing part 1044 in a screwing manner, so that the upper inner ring phase fixing seat group The overall tightness of the overall structure of the 103 and the upper and outer ring phase fixing base groups 104 is improved; moreover, the lower inner ring phase fixing base body 114 and the lower inner ring connecting piece are screwed up by the lower inner ring fixing members. The tightness of the combination of 115 and the lower inner ring connecting handle 116, and at the same time, the lower outer ring phase fixing seat body, the lower outer ring connecting piece and the lower outer ring connecting handle are screwed up by the lower outer ring fixing member. The tightness of the combination makes the tightness of the overall structure of the lower inner ring phase fixed seat group 113 and the lower outer ring phase fixed seat group limited to the rotation angle. Therefore, when the upper and lower main rotor groups 60 and 70 are driven by the coaxial small and large main shafts 50 and 40 to rotate in opposite directions on the same axis, the coaxial double rotor mechanism 30 will generate vibration as a whole. At this time, the upper and lower inner ring connecting members will not loosen from the upper and lower inner ring phase fixing bases, and the upper and lower inner ring connecting handles will never loosen from the upper and lower inner ring connecting members. The outer ring connecting piece will not be loosened from the upper and lower outer ring phase fixing base body, and the upper and lower outer ring connecting handles will not be loosened from the upper and lower outer ring connecting piece at all, thereby maintaining the upper and lower coaxial double The function of the rotor swashplate phase control mount structure 100, 110 to change the flight angle of the present invention.
值得一提的是,當該等上內環固定件32以及該等上外環固定件42的材質均為金屬時,上內環相位固定座本體1031、上內環連結件1032以及上內環接柄1033三者能夠藉由上內環固定件1034以螺固的方式結合的更加緊密,同時上外環相位固定座本體1041、上外環連結件1042以及上外環接柄1043三者也能夠藉由上外環固定件1044以螺固的方式結合的更加緊密,更加提高上內環相位固定座組103以及上外環相位固定座組104的整體結構的結合緊密度以及結構強度;更且,當該等下內環固定件以及該等下外環固定件的材質均為金屬時,下內環相位固定座本體114、下內環連結件115以及下內環接柄116三者能夠藉由下內環固定件以螺固的方式結合的更加緊密,同時下外環相位固定座本體、下外環連結件以及下外環接柄三者也能夠藉由下外環固定件以螺固的方式結合的更加緊密,更加提高限制旋轉角度的下內環相位固定座組以及下外環相位固定座組的整體結構的結合緊密度以及結構強度。藉此,本發明的上、下同軸雙旋翼十字盤相位控制固定座結構100、110較不易磨損,更加耐用,壽命更持久。It is worth mentioning that when the materials of the upper inner ring fixing members 32 and the upper outer ring fixing members 42 are metal, the upper inner ring phase fixing base body 1031, the upper inner ring connecting member 1032, and the upper inner ring The three joints 1033 can be screwed together tighter by the upper inner ring fixing member 1034, while the upper outer ring phase fixing base body 1041, the upper outer ring connecting member 1042, and the upper outer ring connecting rod 1043 are also tightly connected. The upper and outer ring fixing members 1044 can be combined tighter by screwing, and the overall tightness and structural strength of the overall structure of the upper inner ring phase fixing base group 103 and the upper and outer ring phase fixing base group 104 can be further improved; more In addition, when the materials of the lower inner ring fixing members and the lower outer ring fixing members are metal, the lower inner ring phase fixing seat body 114, the lower inner ring connecting member 115, and the lower inner ring connecting handle 116 can be all three. The lower inner ring fixing member is screwed tighter, and the lower outer ring phase fixing base body, the lower outer ring connecting member and the lower outer ring connecting handle can also be screwed by the lower outer ring fixing member. The solid way combines tighter and more Binding tightness and overall configuration of the outer group of fixed base phase angle of the high-limit rotational phase of the inner holder groups and structural strength. Accordingly, the upper and lower coaxial dual-rotor swashplate phase control fixed seat structures 100 and 110 of the present invention are less prone to wear, more durable, and have a longer life.
以下將針對限制旋轉角度的下內環相位固定座組113與上內環相位固定座組103的差異之處進一步說明。Differences between the lower inner ring phase fixing seat group 113 and the upper inner ring phase fixing seat group 103 that limit the rotation angle will be further described below.
下內環相位固定座本體114套設於大主軸40。下內環連結件115包括一第一下內環連桿1151及一第二下內環連桿1152,下內環連結件115的第一下內環連桿1151樞設於下內環相位固定座本體114,下內環連結件115的第二下內環連桿1152樞設於下內環連結件115的第一下內環連桿1151。下內環接柄116設於下內環連結件115的第二下內環連桿1152與下內環組111之間。限位裝置117至少一部分位於下內環連結件115的內側與大主軸40的外側之間。其中,當下內環連結件115向外旋轉至一第一位置時,下內環連結件115遠離大主軸40,如圖9c及圖9e所示;此時下內環連結件115向外旋轉至最極限。當下內環連結件115向內旋轉至一第二位置時,限位裝置117限制下內環連結件115的第一下內環連桿1151和第二下內環連桿1152向內旋轉的角度,以使下內環連結件115的內側與大主軸40的外側隔開一段距離,如圖9f及圖9g所示;此時下內環連結件115向內旋轉至最極限,同時上內環連結件1032向外旋轉至最極限,藉以使下內環組111和下外環組112的組合相對大主軸40的偏斜角度保持在等於上內環組101和上外環組102的組合相對小主軸50的偏斜角度的狀態,俾利精確地控制上主旋翼組60和下主旋翼組70同步相對機身偏轉,使本發明能夠穩定地改變飛行角度,不會失控。The lower inner ring phase fixing base body 114 is sleeved on the main spindle 40. The lower inner ring link 115 includes a first lower inner ring link 1151 and a second lower inner ring link 1152. The first lower inner ring link 1151 of the lower inner ring link 115 is pivotally fixed to the lower inner ring. The seat body 114 and the second lower inner ring link 1152 of the lower inner ring link 115 are pivotally disposed on the first lower inner ring link 1151 of the lower inner ring link 115. The lower inner ring connecting handle 116 is disposed between the second lower inner ring link 1152 of the lower inner ring link 115 and the lower inner ring group 111. At least a part of the limiting device 117 is located between the inner side of the lower inner ring link 115 and the outer side of the main shaft 40. Among them, when the lower inner ring link 115 is rotated outward to a first position, the lower inner ring link 115 is far away from the main shaft 40, as shown in FIGS. 9c and 9e; at this time, the lower inner ring link 115 is rotated outward to The most extreme. When the lower inner ring link 115 rotates inward to a second position, the limiting device 117 restricts the angle of the first lower inner ring link 1151 and the second lower inner ring link 1152 of the lower inner ring link 115 to rotate inward. So that the inside of the lower inner ring link 115 is separated from the outside of the major spindle 40 by a distance, as shown in Figures 9f and 9g; at this time, the lower inner ring link 115 is rotated inward to the maximum while the upper inner ring The connecting member 1032 is rotated outward to the maximum limit, so that the deflection angle of the combination of the lower inner ring group 111 and the lower outer ring group 112 with respect to the major axis 40 is equal to the combination of the upper inner ring group 101 and the upper outer ring group 102. The state of the deflection angle of the small main shaft 50 accurately controls the upper main rotor group 60 and the lower main rotor group 70 to deflect relative to the fuselage synchronously, so that the present invention can stably change the flight angle without losing control.
在一較佳實施例中,下內環連結件115的第一下內環連桿1151開設一穿孔11511,限位裝置117設於穿孔11511並且其一端延伸至穿孔11511之外而突出於下內環連結件115的第一下內環連桿1151的內側,如圖9c及圖9e所示。當下內環連結件115向內旋轉至第二位置時,限位裝置117突出於下內環連結件115的第一下內環連桿1151的內側的部分抵頂於大主軸40的外側,如圖9f及圖9g所示。較佳地,下內環連結件115的第一下內環連桿1151具有一第一端11512及一第二端11513,下內環連結件115的第二下內環連桿1152具有一第一端11521及一第二端11522,下內環連結件115的第一下內環連桿1151的第一端11512樞設於下內環相位固定座本體114,下內環連結件115的第一下內環連桿1151的第二端11513樞設於下內環連結件115的第二下內環連桿1152的第一端11521,下內環接柄116設於下內環連結件115的第二下內環連桿1152的第二端11522,穿孔11511位於下內環連結件115的第一下內環連桿1151的第一端11512與第二端11513之間並且靠近下內環連結件115的第一下內環連桿1151的第一端11512,如圖9d及圖9e所示。In a preferred embodiment, the first lower inner ring link 1151 of the lower inner ring link 115 is provided with a perforation 11511. The limiting device 117 is provided in the perforation 11511 and one end thereof extends beyond the perforation 11511 and protrudes from the lower inside. The inside of the first lower inner ring link 1151 of the ring link 115 is shown in FIGS. 9c and 9e. When the lower inner ring link 115 rotates inward to the second position, the portion of the stop device 117 protruding from the inner side of the first lower inner ring link 1151 of the lower inner ring link 115 abuts against the outer side of the main shaft 40, such as 9f and 9g. Preferably, the first lower inner ring link 1151 of the lower inner ring link 115 has a first end 11512 and a second end 11513, and the second lower inner ring link 1152 of the lower inner ring link 115 has a first One end 11521 and one second end 11522. The first end 11512 of the first lower inner ring link 1151 of the lower inner ring link 115 is pivoted to the lower inner ring phase fixing base body 114, and the first The second end 11513 of the lower inner ring link 1151 is pivoted on the first end 11521 of the second lower inner ring link 1152 of the lower inner ring link 115, and the lower inner ring connecting handle 116 is provided on the lower inner ring link 115 The second end 11522 of the second lower inner ring link 1152, the perforation 11511 is located between the first end 11512 and the second end 11513 of the first lower inner ring link 1151 of the lower inner ring link 115 and is close to the lower inner ring The first end 11512 of the first lower inner ring link 1151 of the link 115 is shown in Figs. 9d and 9e.
在一較佳實施例中,限位裝置117可調整其突出於下內環連結件115的第一下內環連桿1151的內側的程度。因此,使用者能夠視其需求調整當下內環連結件115向內旋轉至第二位置時第一下內環連桿1151與第二下內環連桿1152的夾角Θ3的角度。較佳地,下內環連結件115的第一下內環連桿1151的穿孔11511具有內螺紋,限位裝置117包含一螺栓1171及一螺帽1172;螺栓1171具有一螺桿11711及一頭部11712;螺栓1171的螺桿11711具有外螺紋,螺設於穿孔11511,並且其靠近大主軸40的一端延伸至穿孔11511之外而突出於下內環連結件115的第一下內環連桿1151的內側;螺栓1171的頭部11712設於螺桿11711遠離大主軸40的一端,螺帽1172螺設於螺栓1171的螺桿11711靠近大主軸40的一端。藉此,使用者可直接調整螺栓突出於下內環連結件115的第一下內環連桿1151的內側的程度,或者藉由調整螺帽1172與下內環連結件115的第一下內環連桿1151的內側的距離,控制限位裝置117突出於下內環連結件115的第一下內環連桿1151的內側的程度。在其他實施例中,亦可省略螺帽1172,使得限位裝置117僅包含螺栓1171。在其他實施例中,限位裝置117亦可為一插銷。In a preferred embodiment, the position-limiting device 117 can adjust the degree that it protrudes from the inside of the first lower inner ring link 1151 of the lower inner ring link 115. Therefore, the user can adjust the angle between the first lower inner ring link 1151 and the second lower inner ring link 1152 when the lower inner ring link 115 is rotated inward to the second position. Preferably, the perforation 11511 of the first lower inner ring link 1151 of the lower inner ring connecting member 115 has an internal thread, and the limiting device 117 includes a bolt 1171 and a nut 1172; the bolt 1171 has a screw 11711 and a head 11712; the screw 11711 of the bolt 1171 has an external thread, and the screw is provided in the perforation 11511, and an end thereof near the main shaft 40 extends beyond the perforation 11511 and protrudes from the first lower inner ring link 1151 of the lower inner ring link 115 Inside; the head 11712 of the bolt 1171 is provided on the end of the screw 11711 away from the main spindle 40, and the nut 1172 is screwed on the end of the screw 11711 of the bolt 1171 near the main spindle 40. Thereby, the user can directly adjust the extent to which the bolt protrudes inside the first lower inner ring link 1151 of the lower inner ring link 115, or by adjusting the nut 1172 and the first lower inner ring of the lower inner ring link 115 The distance of the inner side of the ring link 1151 controls the extent to which the limiter 117 protrudes from the inside of the first lower inner ring link 1151 of the lower inner ring link 115. In other embodiments, the nut 1172 may be omitted, so that the limiting device 117 includes only the bolt 1171. In other embodiments, the limiting device 117 may also be a latch.
在另一較佳實施例中,限位裝置117一體成型於下內環連結件115的第一下內環連桿1151的內側,藉以使限位裝置117突出於下內環連結件115的第一下內環連桿1151的內側的程度保持固定(亦即,恆久不變,不可調整),使得當下內環連結件115向內旋轉至第二位置時,下內環連結件115的第一下內環連桿1151與第二下內環連桿1152的夾角Θ3的角度保持固定,可確保限位裝置117不會被調整到錯誤的突出程度(例如:過於突出、突出過短、完全縮入穿孔內而沒有突出、甚至完全被拔除),避免下內環組111和下外環組112的組合相對大主軸40的偏斜角度與上內環組101和上外環組102的組合相對小主軸50不一致。再者,此實施例的限位裝置117還有不易磨損以及耐用性佳等好處。In another preferred embodiment, the limiting device 117 is integrally formed on the inside of the first lower inner ring link 1151 of the lower inner ring link 115, so that the limiting device 117 protrudes from the first link of the lower inner ring link 115. The degree of the inner side of the lower inner ring link 1151 remains fixed (that is, permanent and cannot be adjusted), so that when the lower inner ring link 115 rotates inward to the second position, the first of the lower inner ring link 115 The angle of the included angle Θ3 between the lower inner ring link 1151 and the second lower inner ring link 1152 is kept constant, which can ensure that the limit device 117 will not be adjusted to the wrong degree of protrusion (for example: too much protrusion, too short protrusion, completely shrinking Into the perforation without protruding or even being completely removed), to avoid the deflection angle of the combination of the lower inner ring group 111 and the lower outer ring group 112 relative to the major axis 40 compared to the combination of the upper inner ring group 101 and the upper outer ring group 102 The minor spindle 50 is inconsistent. Furthermore, the limiting device 117 in this embodiment has the advantages of not being easy to wear and having good durability.
在其他實施例中,限位裝置117亦可設於大主軸40並且至少一部分位於下內環連結件115的內側與大主軸40的外側之間,亦可達到上述較佳實施例所能達成的功效。In other embodiments, the limiting device 117 may also be provided on the major axis 40 and at least a part is located between the inner side of the lower inner ring link 115 and the outer side of the major axis 40, which can also achieve the above-mentioned preferred embodiment. efficacy.
值得一提的是,當下內環連結件115向內旋轉至第一位置時,下內環連結件115的第一下內環連桿1151與第二下內環連桿1152的夾角Θ2的角度小於或者等於110°,如圖9c及圖9e所示;當下內環連結件115向內旋轉至第二位置時,下內環連結件115的第一下內環連桿1151與第二下內環連桿1152的夾角Θ3的角度小於或者等於170°;在上述角度範圍之內(亦即,在夾角Θ2與夾角Θ3的範圍110°~170°之內),本發明更能夠確實地將下內環組111和下外環組112的組合相對大主軸40的偏斜角度保持在等於上內環組101和上外環組102的組合相對小主軸50的偏斜角度的狀態,更加精準地控制上主旋翼組60和下主旋翼組70同步相對機身偏轉,使本發明能夠更穩定地改變飛行角度,不會失控。It is worth mentioning that when the lower inner ring link 115 is rotated inward to the first position, the angle between the first lower inner ring link 1151 and the second lower inner ring link 1152 of the lower inner ring link 115 is an angle Θ2 Less than or equal to 110 °, as shown in FIGS. 9c and 9e; when the lower inner ring link 115 is rotated inward to the second position, the first lower inner ring link 1151 and the second lower inner link of the lower inner ring link 115 The angle of the included angle Θ3 of the ring link 1152 is less than or equal to 170 °; within the above-mentioned angle range (that is, within the range of the included angle Θ2 and the included angle Θ3 between 110 ° and 170 °), the present invention can more reliably reduce the following The deflection angle of the combination of the inner ring group 111 and the lower outer ring group 112 with respect to the large main shaft 40 is maintained at a state equal to the deflection angle of the combination of the upper inner ring group 101 and the upper outer ring group 102 with respect to the small main shaft 50, which is more accurate. The upper main rotor group 60 and the lower main rotor group 70 are controlled to deflect synchronously with respect to the fuselage, so that the present invention can change the flight angle more stably without losing control.
綜上所述,本發明的同軸雙旋翼渦輪傳動無人載具機構系統的渦輪引擎20的傳動輸出結構21在更換、拆裝等應用上更為便利快捷且利於加工製造,節省更換及維修時間;本發明的同軸雙旋翼渦輪傳動無人載具機構系統的同軸雙旋翼機構30的上主旋翼組60的滑動穩定性佳,相對同軸雙旋翼機構30的小主軸50晃動的程度小;本發明的同軸雙旋翼渦輪傳動無人載具機構系統的同軸雙旋翼機構30的上、下旋翼葉片氣動構型80、90產生的升力和降低阻力的效果佳;本發明的同軸雙旋翼渦輪傳動無人載具機構系統能夠維持同軸雙旋翼機構30的上、下同軸雙旋翼十字盤相位控制固定座結構100、110改變本發明的飛行角度的功能,並且精確地控制同軸雙旋翼機構30的上、下主旋翼組60、70同步相對機身10偏轉,使本發明能夠穩定地改變飛行角度。藉此,本發明在飛航能力、安全性、穩定度、加工製造及拆裝等各方面性能全面進化。In summary, the transmission output structure 21 of the turbo engine 20 of the coaxial dual-rotor turbo-drive unmanned vehicle mechanism system of the present invention is more convenient and quicker for replacement, disassembly, and other applications, and is conducive to manufacturing, saving replacement and maintenance time; The coaxial dual-rotor turbodrive unmanned vehicle mechanism system of the present invention has good sliding stability of the upper main rotor group 60 of the coaxial dual-rotor mechanism 30, and the degree of shaking with respect to the small main shaft 50 of the coaxial dual-rotor mechanism 30 is small; the coaxial of the present invention The upper and lower rotor blade aerodynamic configurations 80 and 90 of the coaxial double-rotor mechanism 30 of the dual-rotor turbine-driven unmanned vehicle mechanism system have good lift and drag reduction effects; the coaxial double-rotor turbine-driven unmanned vehicle mechanism system of the present invention The function of changing the flight angle of the present invention by maintaining the upper and lower coaxial double rotor swashplate phase control mount structures 100 and 110 of the coaxial double rotor mechanism 30 and accurately controlling the upper and lower main rotor groups 60 of the coaxial double rotor mechanism 30 The 70 and 70 are deflected synchronously with respect to the fuselage 10, so that the present invention can stably change the flight angle. With this, the present invention has comprehensively evolved in all aspects of flight capability, safety, stability, processing, manufacturing, disassembly and the like.
以上所述者僅為用以解釋本發明的較佳實施例,並非企圖據以對本發明做任何形式上的限制,是以,凡有在相同的創作精神下所作有關本發明的任何修飾或變更,皆仍應包括在本發明意圖保護的範疇。The above are only used to explain the preferred embodiments of the present invention, and are not intended to limit the present invention in any form. Therefore, any modification or change related to the present invention made under the same creative spirit Should still be included in the scope of the present invention.
A‧‧‧上、下旋翼葉片氣動構型
A1‧‧‧槳葉本體
A13‧‧‧第一側邊
A14‧‧‧第二側邊
A15‧‧‧頂面
A16‧‧‧底面
A2‧‧‧結合部
A3‧‧‧翼尖部
10‧‧‧機身
20‧‧‧渦輪引擎
21‧‧‧傳動輸出結構
22‧‧‧渦輪發動機
221‧‧‧發動機本體
222‧‧‧渦輪傳動軸
223‧‧‧固定環
2231‧‧‧固定螺孔
224‧‧‧突管
23‧‧‧轉接座
231‧‧‧轉接環
2311‧‧‧轉接螺孔
232‧‧‧轉接管
2321‧‧‧輸出螺孔
233‧‧‧軸孔
24‧‧‧轉接螺絲
25‧‧‧輸出齒輪
251‧‧‧齒輪管
2511‧‧‧齒輪螺孔
252‧‧‧軸孔
253‧‧‧輸出輪齒
26‧‧‧齒輪螺絲
27‧‧‧傳動齒輪
271‧‧‧傳動輪齒
30‧‧‧同軸雙旋翼機構
40‧‧‧大主軸
50‧‧‧小主軸
60‧‧‧上主旋翼組
61‧‧‧上主旋翼固定座
611‧‧‧上座體
6111‧‧‧上座體軸孔
6112‧‧‧軸線
612‧‧‧上延伸臂
6121‧‧‧軸線
613‧‧‧上槳夾頭
614‧‧‧穿孔
62‧‧‧同軸雙旋翼方向控制固定座結構
63‧‧‧本體
631‧‧‧基座
6311‧‧‧懸臂
6312‧‧‧基座軸孔
6313‧‧‧軸線
6314‧‧‧凸出部
63141‧‧‧軸線
63142‧‧‧孔洞
632‧‧‧樞座
64‧‧‧軸桿
65‧‧‧連桿
66‧‧‧支撐結構
70‧‧‧下主旋翼組
71‧‧‧下主旋翼固定座
711‧‧‧下座體
712‧‧‧下延伸臂
713‧‧‧下槳夾頭
80‧‧‧上旋翼葉片氣動構型
81‧‧‧上槳葉本體
811‧‧‧第一端
812‧‧‧第二端
813‧‧‧第一側邊
814‧‧‧第二側邊
815‧‧‧頂面
816‧‧‧底面
82‧‧‧上結合部
83‧‧‧上翼尖部
90‧‧‧下旋翼葉片氣動構型
91‧‧‧下槳葉本體
911‧‧‧第一端
912‧‧‧第二端
913‧‧‧第一側邊
914‧‧‧第二側邊
915‧‧‧頂面
916‧‧‧底面
92‧‧‧下結合部
93‧‧‧下翼尖部
100‧‧‧上同軸雙旋翼十字盤相位控制固定座結構
101‧‧‧上內環組
1011‧‧‧上內環球頭
1012‧‧‧上球型軸承
1013‧‧‧上球型軸環
1014‧‧‧上內環基座
102‧‧‧上外環組
1021‧‧‧上外環球頭
1022‧‧‧上環型軸承
1023‧‧‧上外環基座
103‧‧‧上內環相位固定座組
1031‧‧‧上內環相位固定座本體
10311‧‧‧螺孔
1032‧‧‧上內環連結件
1033‧‧‧上內環接柄
10331‧‧‧螺孔
1034‧‧‧上內環固定件
1035‧‧‧第一上內環連桿
10351‧‧‧連接臂
10352‧‧‧延伸臂
10353‧‧‧柄部
10354‧‧‧穿孔
10355‧‧‧螺孔
1036‧‧‧第二上內環連桿
10361‧‧‧連接臂
10362‧‧‧延伸臂
10363‧‧‧穿孔
10364‧‧‧穿孔
104‧‧‧上外環相位固定座組
1041‧‧‧上外環相位固定座本體
10411‧‧‧螺孔
1042‧‧‧上外環連結件
1043‧‧‧上外環接柄
10431‧‧‧螺孔
1044‧‧‧上外環固定件
1045‧‧‧第一上外環連桿
10451‧‧‧連接臂
10452‧‧‧延伸臂
10453‧‧‧柄部
10454‧‧‧穿孔
10455‧‧‧螺孔
1046‧‧‧第二上外環連桿
10461‧‧‧連接臂
10462‧‧‧延伸臂
10463‧‧‧穿孔
10464‧‧‧穿孔
110‧‧‧下同軸雙旋翼十字盤相位控制固定座結構
111‧‧‧下內環組
112‧‧‧下外環組
113‧‧‧限制旋轉角度的下內環相位固定座組
114‧‧‧下內環相位固定座本體
115‧‧‧下內環連結件
1151‧‧‧第一下內環連桿
11511‧‧‧穿孔
11512‧‧‧第一端
11513‧‧‧第二端
1152‧‧‧第二下內環連桿
11521‧‧‧第一端
11522‧‧‧第二端
116‧‧‧下內環接柄
117‧‧‧限位裝置
1171‧‧‧螺栓
11711‧‧‧螺桿
11712‧‧‧頭部
1172‧‧‧螺帽
121‧‧‧第一連桿
122‧‧‧第二連桿
123‧‧‧第三連桿
124‧‧‧第四連桿
Θ1~3‧‧‧夾角A‧‧‧ Upper and lower rotor blade aerodynamic configuration
A1‧‧‧ Paddle Body
A13‧‧‧First side
A14‧‧‧Second side
A15‧‧‧Top
A16‧‧‧ Underside
A2‧‧‧Combination
A3‧‧‧wing tip
10‧‧‧Airframe
20‧‧‧Turbine engine
21‧‧‧Drive output structure
22‧‧‧Turbine engine
221‧‧‧Engine body
222‧‧‧Turbine drive shaft
223‧‧‧Fixed ring
2231‧‧‧Fixing screw holes
224‧‧‧ tube
23‧‧‧ adapter
231‧‧‧Adapter ring
2311‧‧‧Adapter screw hole
232‧‧‧Adapter
2321‧‧‧Output screw hole
233‧‧‧shaft hole
24‧‧‧ Adapter Screw
25‧‧‧output gear
251‧‧‧ Gear tube
2511‧‧‧Gear screw hole
252‧‧‧shaft hole
253‧‧‧Output Gear
26‧‧‧Gear Screw
27‧‧‧Drive gear
271‧‧‧ transmission gear
30‧‧‧ Coaxial Double Rotor Mechanism
40‧‧‧ Major Spindle
50‧‧‧ small spindle
60‧‧‧ Upper main rotor group
61‧‧‧Upper main rotor mount
611‧‧‧ Upper seat
6111‧‧‧ Upper body shaft hole
6112‧‧‧ axis
612‧‧‧ Upper extension arm
6121‧‧‧ axis
613‧‧‧Upper paddle chuck
614‧‧‧perforation
62‧‧‧Coaxial double-rotor direction control fixing structure
63‧‧‧ Ontology
631‧‧‧ base
6311‧‧‧ cantilever
6312‧‧‧Base shaft hole
6313‧‧‧ axis
6314‧‧‧ protrusion
63141‧‧‧ axis
63142‧‧‧hole
632‧‧‧ Pivot
64‧‧‧ shaft
65‧‧‧ connecting rod
66‧‧‧ support structure
70‧‧‧ lower main rotor group
71‧‧‧ Lower Main Rotor Mount
711‧‧‧lower body
712‧‧‧ Lower extension arm
713‧‧‧ Lower Paddle Chuck
80‧‧‧ Upper rotor blade aerodynamic configuration
81‧‧‧Upper blade body
811‧‧‧ the first end
812‧‧‧second end
813‧‧‧first side
814‧‧‧second side
815‧‧‧Top
816‧‧‧ Underside
82‧‧‧ Upper Joint
83‧‧‧ Upper wing tip
90‧‧‧ lower rotor blade aerodynamic configuration
91‧‧‧ lower blade body
911‧‧‧ the first end
912‧‧‧second end
913‧‧‧first side
914‧‧‧second side
915‧‧‧Top
916‧‧‧underside
92‧‧‧ lower joint
93‧‧‧ lower wing tip
100‧‧‧ Upper coaxial double rotor swashplate phase control fixed seat
101‧‧‧ Upper Inner Ring
1011‧‧‧ Upper Inner Globe Head
1012‧‧‧up ball bearing
1013‧‧‧up ball collar
1014‧‧‧ Upper inner ring base
102‧‧‧Sheung Wai Wan Group
1021‧‧‧Shangwai Global Head
1022‧‧‧Upper ring bearing
1023‧‧‧ Upper outer ring base
103‧‧‧ Upper inner ring phase fixing block group
1031‧‧‧ Upper inner ring phase fixing base body
10311‧‧‧Thread hole
1032‧‧‧ Upper inner ring connector
1033‧‧‧ Upper inner ring adapter
10331‧‧‧Thread hole
1034‧‧‧ Upper inner ring fastener
1035‧‧‧First upper inner link
10351‧‧‧Connecting arm
10352‧‧‧Extended arm
10353‧‧‧Handle
10354‧‧‧perforation
10355‧‧‧Thread hole
1036‧‧‧Second upper inner link
10361‧‧‧Connecting arm
10362‧‧‧Extended arm
10363‧‧‧perforation
10364‧‧‧perforation
104‧‧‧ Upper Outer Ring Phase Fixed Block Set
1041‧‧‧Upper outer ring phase fixing base body
10411‧‧‧Thread hole
1042‧‧‧ Upper outer ring connector
1043‧‧‧ Upper outer ring adapter
10431‧‧‧Thread hole
1044‧‧‧ Upper outer ring fixings
1045‧‧‧First upper outer link
10451‧‧‧Connecting arm
10452‧‧‧Extended arm
10453‧‧‧Handle
10454‧‧‧perforation
10455‧‧‧Thread hole
1046‧‧‧Second upper outer link
10461‧‧‧Connecting arm
10462‧‧‧Extended arm
10463‧‧‧perforation
10464‧‧‧perforation
110‧‧‧ lower coaxial dual-rotor swashplate phase control fixed seat structure
111‧‧‧ Lower inner ring group
112‧‧‧Lower outer ring group
113‧‧‧Lower inner ring phase fixed seat group with limited rotation angle
114‧‧‧ Lower inner ring phase fixing base body
115‧‧‧ Lower inner ring connector
1151‧‧‧First lower inner link
11511‧‧‧perforation
11512‧‧‧ the first end
11513‧‧‧ second end
1152‧‧‧Second lower inner link
11521‧‧‧ the first end
11522‧‧‧second end
116‧‧‧ Lower inner ring adapter
117‧‧‧ limit device
1171‧‧‧Bolt
11711‧‧‧Screw
11712‧‧‧Head
1172‧‧‧nut
121‧‧‧ First connecting rod
122‧‧‧Second Link
123‧‧‧Third Link
124‧‧‧ Fourth link Θ1 ~ 3‧‧‧ included angle
圖1為習知的旋翼葉片的俯視圖。 圖2為習知的旋翼葉片的剖視圖。 圖3是本發明的同軸雙旋翼渦輪傳動無人載具機構系統的示意圖。 圖4a是本發明的渦輪引擎的傳動輸出結構的立體圖。 圖4b是本發明的渦輪引擎的傳動輸出結構的分解圖。 圖4c是本發明的渦輪引擎的傳動輸出結構的側視圖。 圖4d是本發明的渦輪引擎的傳動輸出結構的剖視圖。 圖5為本發明的同軸雙旋翼機構的立體圖。 圖6a為本發明的上主旋翼組的示意圖。 圖6b為本發明的同軸雙旋翼方向控制固定座結構的立體圖。 圖6c為本發明的同軸雙旋翼方向控制固定座結構的分解圖。 圖6d為本發明的同軸雙旋翼方向控制固定座結構的另一角度分解圖。 圖7a為本發明的上、下旋翼葉片氣動構型的第一實施例的俯視圖。 圖7b為本發明的上、下旋翼葉片氣動構型的第一實施例的槳葉本體的剖視圖。 圖7c為習知技術、本發明的第一實施例和第二實施例的同軸雙旋翼渦輪傳動無人載具機構系統的升力比較圖。 圖8a為本發明的同軸雙旋翼機構的立體放大示意圖。 圖8b為本發明的上內環相位固定座組的立體圖。 圖8c為本發明的上內環相位固定座組的分解圖。 圖8d為本發明的上外環相位固定座組的立體圖。 圖8e為本發明的上外環相位固定座組的分解圖。 圖9a為本發明的同軸雙旋翼機構的另一視角立體放大示意圖。 圖9b為本發明的上內環相位固定座組的另一視角立體圖。 圖9c為本發明的限制旋轉角度的下內環相位固定座組的立體圖。 圖9d為本發明的限制旋轉角度的下內環相位固定座組的分解圖。 圖9e為本發明的限制旋轉角度的下內環相位固定座組的剖視圖。 圖9f為本發明的下內環連結件向內旋轉至第二位置的剖視圖。 圖9g為本發明的上內環連結件向外旋轉至最極限以及下內環連結件向內旋轉至第二位置的立體圖。FIG. 1 is a plan view of a conventional rotor blade. Fig. 2 is a sectional view of a conventional rotor blade. FIG. 3 is a schematic diagram of a coaxial dual-rotor turbine-driven unmanned vehicle mechanism system of the present invention. 4a is a perspective view of a transmission output structure of a turbine engine according to the present invention. Fig. 4b is an exploded view of the transmission output structure of the turbine engine of the present invention. 4c is a side view of a transmission output structure of a turbine engine according to the present invention. 4d is a sectional view of a transmission output structure of a turbine engine according to the present invention. FIG. 5 is a perspective view of a coaxial double-rotor mechanism of the present invention. Fig. 6a is a schematic diagram of the upper main rotor group of the present invention. Fig. 6b is a perspective view of the coaxial double-rotor direction control fixing base structure of the present invention. FIG. 6c is an exploded view of the coaxial double-rotor direction control fixing base structure of the present invention. Fig. 6d is another angle exploded view of the coaxial double-rotor direction control fixing base structure of the present invention. 7a is a top view of a first embodiment of the aerodynamic configuration of the upper and lower rotor blades of the present invention. 7b is a cross-sectional view of a blade body of the first embodiment of the aerodynamic configuration of the upper and lower rotor blades of the present invention. FIG. 7c is a lift comparison diagram of a coaxial twin-rotor turbo-drive unmanned vehicle mechanism system of the conventional technology, the first embodiment and the second embodiment of the present invention. FIG. 8a is an enlarged perspective view of the coaxial double-rotor mechanism of the present invention. FIG. 8b is a perspective view of an upper inner ring phase fixing seat group according to the present invention. FIG. 8c is an exploded view of the upper inner ring phase fixing block group of the present invention. FIG. 8d is a perspective view of an upper outer ring phase fixing seat group according to the present invention. FIG. 8e is an exploded view of the upper outer ring phase fixing seat group of the present invention. FIG. 9a is another perspective enlarged schematic view of the coaxial double-rotor mechanism of the present invention. FIG. 9b is another perspective view of the upper inner ring phase fixing seat group according to the present invention. FIG. 9c is a perspective view of a lower inner ring phase fixing seat group with a restricted rotation angle according to the present invention. FIG. 9d is an exploded view of the lower inner ring phase fixing seat group with limited rotation angle according to the present invention. 9e is a cross-sectional view of a lower inner ring phase fixing seat group with a restricted rotation angle according to the present invention. FIG. 9f is a cross-sectional view of the lower inner ring link of the present invention rotated inward to a second position. 9g is a perspective view of the upper inner ring link rotating outward to the extreme limit and the lower inner ring link rotating inward to a second position according to the present invention.
Claims (10)
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TW106118405A TWI627103B (en) | 2017-06-03 | 2017-06-03 | Coaxial double-rotor turbine drive unmanned vehicle mechanism system |
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TW106118405A TWI627103B (en) | 2017-06-03 | 2017-06-03 | Coaxial double-rotor turbine drive unmanned vehicle mechanism system |
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JP2005289128A (en) * | 2004-03-31 | 2005-10-20 | Nagasaki Prefecture | Pitch angle variable mechanism for double inversion wing, and flying device having double inversion wing equipped with the same |
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JP2014104802A (en) * | 2012-11-26 | 2014-06-09 | Tadashi Iwata | Rotary wing system for helicopter |
CN104760696A (en) * | 2015-04-22 | 2015-07-08 | 深圳市艾特航空科技股份有限公司 | Multi-rotor aircraft |
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CN106314785A (en) * | 2016-08-30 | 2017-01-11 | 中航沈飞民用飞机有限责任公司 | Coaxial double-rotor aircraft |
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JP2005289128A (en) * | 2004-03-31 | 2005-10-20 | Nagasaki Prefecture | Pitch angle variable mechanism for double inversion wing, and flying device having double inversion wing equipped with the same |
WO2008085547A2 (en) * | 2006-07-27 | 2008-07-17 | Sikorsky Aircraft Corporation | Aerodynamic integration of a payload container with a vertical take-off and landing aircraft |
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