i 201010908 九、發明說明： 【發明所屬之技術領域】 本發明為有關一種可簡易操控之飛行器，尤指可供上升 飛行後並操控轉向移動飛行之飛行器，透過二螺旋槳以不同 旋轉方向而帶動飛行器本體上升、再以轉向控制部操控轉向 ’達到多方向性操控飛行器本體橫向位移、飛行之目的。 _ 【先前技術】 響 按，自從萊特兄弟研發出飛機後，將人類的飛行歷史帶 入了全新的領域，由地面行進提升至空中的飛行，可以移動 更遠的距離、飛行更遠的地方，而大咖賴颂有操作飛 機飛行之駕駛技術，並非所有人都可以飛行，因此為了滿足 無法飛行飛機的缺失，則有遙控型的飛機問世，以供飛行克 好者可以制㈣飛行的意願，目前#遍使用的遙控飛機: e 大都利用機翼二側透過馬達驅動式之螺旋紫的動力驅動飛行 ’且透過雜飛_平衡錄域_行進，在_行&㈣ 到迎面而來的風力，容易與麵__產生紐干擾，導 致賴失控或墜落；此外，有直升機式的遙控賴，係利用 直升機的頂部之職槳旋動’以帶動直升機作垂直的升降， 達到遙控直升機飛行之目的，·再者，如公告第5 i 9 5 2 8 號『可垂直_之飛行器』，係於民國91年3$22日& 出申請，並核准公告於民國9 2年2月！日之專利公報，社 6 201010908 I > 參閱第七、/V圖所示’其係於飛行器之機心頂面中央具有 第一容室A 1，第一容室A工中裝設有旋翼反向機構卜旋 翼反向機構B為設有上、下錯位呈反向旋轉之上、下旋翼b 1、B 2 ’而第-容室Α χ内周壁具有多數等分佈之垂昇氣i 201010908 IX. Description of the invention: [Technical field of the invention] The present invention relates to an aircraft that can be easily manipulated, in particular, an aircraft that can be used for ascending flight and maneuvering a steering mobile flight, and the aircraft is driven by two propellers in different directions of rotation. The body rises, and then the steering control unit controls the steering to achieve multi-directional control of the aircraft body lateral displacement, flight purposes. _ [Prior Art] Ringing, since the Wright brothers developed the aircraft, the human flight history has been brought into a new field, and the flight from the ground to the air can move farther and farther. And the big squat has the driving skills of operating the aircraft, not everyone can fly, so in order to meet the lack of flight, there is a remote-controlled aircraft, for the flight can be made (4) the willingness to fly, At present, the remote control aircraft used in ##: e mostly use the power-driven flight of the motor-driven spiral purple on both sides of the wing' and travels through the _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ It is easy to interfere with the surface __, causing the loss of control or fall; in addition, there is a helicopter-type remote control, which uses the top of the helicopter to rotate the 'to drive the helicopter for vertical lifting, to achieve the purpose of RC helicopter flight , and, in addition, the announcement of the 5th 9 5 2 8 "vertical aircraft", in the Republic of China on the 3rd of March 22nd & application, and approved the announcement in the Republic of China 9 2 years February! Japanese Patent Gazette, Society 6 201010908 I > Refer to the seventh, /V diagram, which has a first chamber A in the center of the top surface of the aircraft, and a rotor in the first chamber A. The reverse mechanism of the rotor reversing mechanism B is provided with upper and lower misalignment in the opposite direction, and the lower rotor b 1 , B 2 ' and the inner circumference of the first chamber 具有 具有 has a plurality of equal distributions of the hoisting gas
孔A2 ’且垂昇氣孔A 2貫通至機體A底面形成多數開口A 3 ’第—容室A 1並具有至少一推進氣孔厶4，且推進氣孔 ❹ A 4係貫通至尾翼A 5而形成嗔射孔a 51，使喷射孔a 5 1與第-容室A 1連通’且各垂昇氣孔A 2及推進氣孔A 4 分別设有開關HA2 1 ;係彻機體a於第二容室a 6所 没之馬達A 6 1帶雜翼反向機制之旋轉細3轉動，形 成正向扭力輸出，並帶動上旋抑i形成正向扭力的輸出轉 動’同時翼反向機構B會形成相同扭力值的反向扭力之 旋轉，使下旋翼B 2與上旋翼B1轉向相反且扭力輸出平衡 φ ’推進氣孔A4則受開關閥HA 21封閉，而上、下旋翼b 1、B 2呈相對旋轉時，會將外界氣流吸入機體a的第一容 至A 1内，且朝垂昇氣孔A 2排出往機體A底面之開口A 3 喷射’有助機體A的垂直上昇，然在實際使用時，仍存在諸 多缺失與不便，如： (1 )第一容室A1内的垂昇氣孔A2、推近氣孔A4分別 裝設有開關閥門A21，而在上、下旋翼B1、B 2 旋轉時才產生抽氣或吸氣的現象The hole A2′ and the swell hole A 2 penetrate to the bottom surface of the body A to form a plurality of openings A 3 ′—the chamber A 1 and have at least one propulsion hole 厶 4 , and the propeller ❹ A 4 is connected to the empennage A 5 to form a crucible The perforation a 51 connects the injection hole a 5 1 to the first chamber A 1 and the respective vertical air holes A 2 and the propulsion holes A 4 are respectively provided with a switch HA2 1 ; the body a is in the second chamber a 6 The motor A 6 1 with the reverse rotation mechanism of the wing reverse mechanism rotates to form a positive torque output, and drives the upper rotation to suppress the output of the positive torsion. The simultaneous wing reversal mechanism B forms the same torque value. The rotation of the reverse torque causes the lower rotor B 2 to be opposite to the upper rotor B1 and the torque output balance φ 'the propeller hole A4 is closed by the on-off valve HA 21, and the upper and lower rotors b 1 and B 2 are relatively rotated. The external airflow is sucked into the first volume of the body a into the A1, and is discharged to the opening A3 of the bottom surface of the body A toward the vertical air hole A2. The injection "helps the vertical rise of the body A, but in actual use, it still exists. Many defects and inconveniences, such as: (1) The vertical vent A2 in the first chamber A1 and the vent A4 are installed separately. There is a switch valve A21, and the phenomenon of pumping or inhaling occurs when the upper and lower rotors B1 and B 2 rotate.
，而控制開關闊門A 7 201010908 21的開啟或關閉，但因第一容…與外部均有一 段距離’則抽氣時間容易拖延，機體A上升的速度也 較慢。 (2)她僅可_向的上升、下降飛行，使得飛行的 空間及移動的領域均受到限制，無法擴大飛行的範圍 〇 ❹ 是以，如何解決習用飛行器在上昇時氣流循環、導引、 流通之問題’即為從事此行業之_廠商所亟欲研究改盖之 方向所在者。 ° 【發明内容】 -故’發明人有鑑於上述之問題與缺失，乃搜集相闕資料 ’經由多将估及考4，並峨事於此㈣累積之多年經驗 ’經由不斷試作及修改，始設計出此種可祕操控飛行器上 升及轉向齡之可簡綠控之飛行㈣研發專利誕生者。 本發明之主要目的乃在浦飛行H本體m卩具有容置空 間’底部设有平衡座體及轉向控制部，且容置空間内為展設 驅動模組’為_驅動單元可驅動二職賴轉，分別呈不 同方疋向（順、逆時針）轉動，而驅動模組之傳動單元係連設 於轉向控制部’且以傳動單元操控擾流體活動旋轉、轉向， 並透過供電單元提供該驅動單元所需電源、供電系統提供傳 動單元所需電源’ _糊二職樂料同旋射向帶動容 8 201010908 置空間内的氣流，而驅動飛行器本體上升，並透過轉向控制 部，擾流體旋動，控制飛行器本體轉向飛行，達到可控制飛 行器本體橫向飛行、位移及轉向之目的。 本發明之次要目的乃在於飛行!!本體之容置郎，係貫 通外部空間而於其頂部及底部分別設有呈十字狀、米字狀之 支架，以供驅動模組的螺旋槳之中心軸桿卡固定位。 ❹ 【實施方式】 為達成上述目的及功效，本發明所採用之技術手段及其 構造’ 就本個之較佳實_詳加綱其特徵與功能 如下，俾利完全瞭解。 請參閱第-、二、三圖所示，係為本發明之立體外觀圖 、立體分解圖、底部立體外觀圖，所示可以清楚看出 本發日月之飛行器係包括飛行器本體工、驅動模组2所组成 ，其中： 該飛行器本體1係於内部具容置空間i 〇，且容置空間 1〇係貫通之外部而於頂部及底部分別設有上、下支架工〇 1 1〇 2，且底部之下支架1〇 2側邊為設有呈對稱式之 平衡座體1i，平衡座體i U呈中空式半圓球形狀，並介 於平衡座體11之間設有轉向控制部丄2，而轉向控制部工 2係具有呈四分之一中空式圓球狀之基座工2工，再於基座 121—侧活動連設有四分之一中空式圓球狀之擾流體工2 9 i 201010908 2。 該驅動模組2係具有二相對式之驅動單元2 ^2 2， 各驅動單元21、2 2係分別設有馬達2丄工、2 21 各馬達211、2 21為分別利用軸心212、2 2 2之 紋銜接齒輪組213、2 2 3，而由各齒輪組2 i 3、= 3分別利用動力傳輸部2工4、2 24連接至中心轴桿2 3 鲁 上所設之上齒輪2 31、中心套桿2 4之下齒輪2 41，並 於中心軸桿2 3上裝設上螺旋槳2 3 2、中心轴桿2 3外再 套設有中心套桿2 4，而於中心套桿2 4上渡設下螺旋樂2 4 2，達到上、下螺㈣2 3 2、2 4 2受到不同驅動單元 21、2 2驅動，而產生不同扭力之不同旋轉方向（順時針 、逆時針）旋轉’該驅動單元21、2 2係分別透過供電單 5、2 6提供所需之電源’各供電單元2 5、2 6則以 魏電源（如··乾電池、小财電池、㈣鱗）提供電源 至電路板，再傳輸至馬達211、2 21運轉以產生動力； 另於驅動單元21、2 2之間設有傳動單元2 7、2 8，各 專動單元2 7、2 8係分別設有傳動馬達2 71、2 81， 並透過傳動轴桿2 7 2、2 8 2連接傳動齒輪2 7 3、2 8 3 ’並由供電系統274、284提供傳動馬達2 71、2 81所需之電源。 上述各構件於組裝時，為利用飛行器本體1之容置空間 201010908However, the control switch wide door A 7 201010908 21 is turned on or off, but because the first capacity ... has a distance from the outside, the pumping time is prone to delay, and the body A rises at a slower speed. (2) She can only fly up and down, making the space of flight and the field of movement restricted, and it is impossible to expand the scope of flight. How to solve the problem of air circulation, guidance and circulation of the conventional aircraft when it rises? The problem is the one in which the manufacturer is eager to study the direction of the change. ° [Summary of the Invention] - Therefore, the inventor has collected the relevant information and the lack of the above-mentioned problems, and has collected the relevant information, and will continue to test and modify it. Designed to be able to control the flight of the aircraft and the steering age of the simple green control of the flight (four) the birth of the patent. The main purpose of the present invention is to provide a balance seat and a steering control unit at the bottom of the main body of the Pu-H flight, and a drive unit for the drive space in the accommodating space. Rotating, respectively, in different directions (shun, counterclockwise), and the drive unit of the drive module is connected to the steering control unit and is operated by the transmission unit to disturb the fluid to rotate, turn, and provide the drive through the power supply unit. The power required by the unit and the power supply system provide the power required by the transmission unit. _ Paste the second grade of the same material to the same direction. The airflow in the space is set to drive the aircraft body to rise and pass through the steering control unit to disturb the fluid. Control the flight of the aircraft body to achieve the purpose of controlling the lateral flight, displacement and steering of the aircraft body. The secondary purpose of the present invention is to fly!! The body of the body is placed in the outer space, and is provided with a cross-shaped, m-shaped bracket at the top and the bottom thereof for driving the central axis of the propeller of the module. The pole card is fixed. ❹ [Embodiment] In order to achieve the above objects and effects, the technical means and the structure thereof used in the present invention are as described above, and the features and functions thereof are as follows. Please refer to the first, second and third figures, which are the three-dimensional external view, the three-dimensional exploded view and the bottom three-dimensional external view of the present invention. It can be clearly seen that the aircraft of the present day and the moon includes the aircraft body and the driving mode. The group 2 is composed of: the aircraft body 1 is internally provided with an accommodation space i 〇, and the accommodation space 1 is connected to the outside of the space, and the upper and lower brackets are respectively disposed at the top and the bottom, respectively. And the side of the bracket 1〇2 under the bottom is provided with a symmetrical balance seat 1i, the balance seat i U is in the shape of a hollow semi-spherical ball, and a steering control unit 设有2 is arranged between the balance seat body 11 The steering control unit 2 has a quarter-shaped hollow ball-shaped pedestal work, and then a quarter-shaped hollow spherical fluent fluid is connected to the pedestal 121-side movable 2 9 i 201010908 2. The driving module 2 has two relative driving units 2^2 2, and each of the driving units 21 and 2 2 is provided with a motor 2 and 2 21 motors 211 and 2 21 respectively for utilizing the axes 212 and 2 The 2 2 pattern connects the gear sets 213, 2 2 3, and the gear sets 2 i 3 and = 3 are respectively connected to the central shaft 2 by the power transmission unit 2, 4 24, and the upper gear 2 is provided. 31. The center sleeve 2 4 has a lower gear 2 41, and the upper shaft 2 3 is provided with a propeller 2 3 2. The central shaft 2 3 is externally sleeved with a central sleeve rod 2 4, and the center sleeve rod 2 4 Set up the lower spiral 2 2 2, reach the upper and lower snails (4) 2 3 2, 2 4 2 are driven by different drive units 21, 2 2, and produce different torque directions of different rotation directions (clockwise, counterclockwise) 'The drive units 21, 2 2 provide the required power through the power supply units 5, 26 respectively. The power supply units 2 5 and 26 provide power to the Wei power supply (such as dry batteries, small batteries, and (four) scales). To the circuit board, and then transmitted to the motors 211, 21 to operate to generate power; and between the drive units 21, 2 2 are provided with transmission units 2 7, 2, each of the dedicated units 2 7 The 2 8 series are respectively provided with transmission motors 2 71, 2 81 , and the transmission gears 2 7 3, 2 8 3 ' are connected through the transmission shafts 2 7 2, 2 8 2 and the transmission motors 2 71 are provided by the power supply systems 274, 284, 2 81 required power. When assembling the above components, the space for accommodating the aircraft body 1 is used 201010908
10收納驅動模組2，並藉由容置空間i 〇頂部及底部之上 、下支架101、102供中心軸桿23卡固、定位，且將 驅動模組2之中心軸桿2 3上穿套之中心套桿2 4，所分別 穿設之上、下螺旋槳2 3 2、2 4 2位於容置空間丄〇的内 部上、下支架1〇1、102之間’而容置空間i 〇底部所 設之轉向控制部12，則以基座121上活動套設之擾流體 122，藉由轉轴1221穿設於傳動單元27、28之傳 動齒輪2 7 3、2 8 3，即組裝成本發明之飛行器。 再請參閱第二、三、四、五圖所示，係為本發明之立體 分解圖、底部立體外觀圖、俯視圖、側視剖面圖，由圖中所 示可以清楚看出，當飛行器飛行時係利用外部預設遙控琴（ 係為一般使用之遙控器，並非本發明之研發重點故未予贅述 )，以遙控方式啟動飛行器本體i的容置空間1〇内之驅動 模組2，而使驅動模組2之各驅動單元21、2 2的馬達2 11、2 21啟動，並利用轴心212、2 2 2之螺紋連動 齒輪組213、2 2 3，而由齒輪組213、2 2 3帶動該 動力傳輸部214、2 2 4，以分別驅動該動力傳輸部2丄 4、2 2 4另側之中心轴桿2 3上的上齒輪2 31、中心套 桿2 4上之下齒輪2 41轉動，即藉由上齒輪2 31在中心 轴桿2 3上產生扭力，並驅動上螺旋槳2 3 2旋轉，而下齒 輪2 41則於中心套桿2 4上產生反向之扭力，以驅動下螺 11 201010908 旋槳2 4 2產生與上螺旋槳2 3 2相反方向的旋轉，並透過 上下螺旋樂2 3 2、2 4 2的相反旋轉方向，則使中心軸 柃2 3、中心套桿2 4之相反扭力相互抵消，即可由上、下 累旋樂2 3 2、2 4 2將外部空氣吸入容置空間1〇，再由 底部向外排出，則可使飛行ϋ本體1上升飛行。 請參閱第三、五、六圖所示，係為本發明之底部立體外 觀圖/侧視剖面圖、較佳實施例之飛行狀態示意圖，由圖中 所不可以清楚看出，本發明之飛行器在飛行器本體1飛行時 ，為可利用預設遙控器操控傳動單元2 7、2 8，而啟動傳 動馬達2 7 1、2 8 1運作，為利轉動螺桿2 7 2、2 8 2帶動傳動齒輪2 7 3、2 8 3轉動，則傳動齒輪2 7 3、 2 8 3底部銜接之轉向控制部12的擾流體工2 2，即隨著 =:Γ3、2 8 3而呈左、右方向的旋轉，藉以控制 。體1底部之氣流的流向，達到使飛行器本體i可以 左轉或右轉的橫向位移飛行，在飛行器本則的上升飛行時 /時可以操控左、右方向的旋轉，供飛行器本體^具有更 多不同的橫向飛行路徑與方式。 、 上述之飛行器本體1係可為飛碟（u F 〇)造型 、直升機、太空船、飛行船等各種飛行而1 空間10頂部及底部分別設有上、下支架 4 該上、下差牟ini ί/λλ 1〇2’ 卜102係可呈十字狀、米字狀、放射 12 201010908 線狀的設計；則該飛行本體1在上升飛行時，呈現橫向移動 、飛行的模式，進行轉向。10 accommodating the driving module 2, and the central shaft 23 is clamped and positioned by the accommodating space i 〇 top and bottom upper and lower brackets 101 and 102, and the central shaft 2 3 of the driving module 2 is worn. The center sleeve rods 2 4 are respectively disposed above and below the propellers 2 3 2, 2 4 2 are located between the inner upper and lower brackets 1〇1 and 102 of the accommodating space '' and the accommodation space i 〇 The steering control unit 12 provided at the bottom is provided with the turbulent fluid 122 disposed on the base 121, and the transmission shafts of the transmission units 27 and 28 are passed through the rotating shaft 1221, that is, the assembly cost. Invented aircraft. Referring to the second, third, fourth and fifth figures, it is a perspective exploded view, a bottom perspective view, a top view and a side cross-sectional view of the present invention. It can be clearly seen from the figure when the aircraft is flying. The external preset remote control piano (which is a general-purpose remote control, which is not the focus of research and development of the present invention, is not described), and the drive module 2 in the accommodating space 1 of the aircraft body i is activated in a remote manner. The motors 2 11 and 2 21 of the drive units 21 and 22 of the drive module 2 are activated, and the gear sets 213 and 2 2 3 are interlocked by the threads of the shafts 212 and 2 2 2, and the gear sets 213 and 2 2 3 are used. The power transmission portions 214, 2 24 are driven to respectively drive the upper gear 2 31 on the central shaft 2 3 on the other side of the power transmission portion 2丄4, 2 2 4, and the lower gear 2 on the center sleeve 2 4 41 rotation, that is, by the upper gear 2 31, a torsion force is generated on the central shaft 23, and the upper propeller 2 3 2 is rotated, and the lower gear 2 41 is reversely twisted on the center sleeve 24 to drive Under the screw 11 201010908 The propeller 2 4 2 produces a rotation in the opposite direction to the upper propeller 2 3 2 and passes through the upper and lower The opposite direction of rotation of the knobs 2 3 2, 2 4 2 causes the opposite torsion forces of the central shaft 柃 2 3 and the center sleeve rod 4 to cancel each other out, which can be externally applied by the upper and lower slewing rollers 2 3 2, 2 4 2 When the air is sucked into the accommodating space 1 〇 and then discharged outward from the bottom, the flying raft body 1 can be raised and flew. Please refer to the third, fifth and sixth figures, which are schematic diagrams of the bottom perspective view/side cross-sectional view of the present invention, and the flight state of the preferred embodiment. It can be clearly seen from the figure that the aircraft of the present invention When the aircraft body 1 is flying, the transmission motor 2 7 1 , 2 8 1 can be operated by using the preset remote controller to operate the transmission unit 2 7 , 2 8 , and the transmission gear is driven by the rotating screw 2 7 2 , 2 8 2 2 7 3, 2 8 3 rotation, the disturbing fluid 2 2 of the steering control unit 12 at the bottom of the transmission gear 2 7 3, 2 8 3 is in the left and right directions with =: Γ 3, 2 8 3 Rotate to control. The flow direction of the airflow at the bottom of the body 1 reaches a lateral displacement flight that allows the aircraft body i to turn left or right, and can rotate the left and right directions during the ascending flight of the aircraft, so that the aircraft body has more differences. The horizontal flight path and the way. The above-mentioned aircraft body 1 can be a flying saucer (u F 〇) shape, a helicopter, a space ship, a flying ship, and the like. 1 Space 10 top and bottom are respectively provided with upper and lower brackets 4, the upper and lower differentials ini ί / Λλ 1〇2' Bu 102 can be in the shape of a cross, a meter, and a radiation 12 201010908. The flight body 1 exhibits a lateral movement, flight mode, and steering when it is flying upward.
而該驅動單元2為於二側驅動單元21、2 2之馬達2 1 1、2 21，係以軸心2工2、2 2 2連設有動力傳輸部 214、2 2 4，動力傳輸部214、2 2 4係以複數齒輪 組213、2 2 3轉動’並帶動環狀齒條、皮帶輪、鍵輪等 轉動以傳輸動力至上、下螺旋槳2 3 2、2 4 2。 是以，以上所述僅為本發明之較佳實施例而已，非因此 侷限本發明之專利細，本拥之精^，為_飛行器本 體1於容置空間10底部裝設之活動式轉向控制部12，透 過驅動模組2以傳動料2 7、2 8之傳動馬達2 7 1、2 81經傳動螺桿2 7 2、2 8 2帶動傳動齒輪2 7 3、2 8 3 ’而達到驅動轉向控制部！2的擾流體}22旋轉之目的 ’並利用擾流體12 2的左、右轉向’俾可達到控制飛行器 本=的橫向移動，左、右旋轉之目的’以供飛行器具有上 升飛行及左、右働之雜魏，故軌可奴前述效果之 結構、裝置皆應受本發鴨，此_易修飾及等效 變化’均_理包含於本㈣之翻細内，合予陳明。 上述本發明之可_触之翁ϋ於實際使㈣，為可 具有下列各項優點，如： )飛行器本體1透過容置空間1〇底部裝設活動式轉向 13 201010908 制邛12，透過驅動模組2驅動轉向控制部12的 擾賴1 2 2旋轉之作S，並利用擾流體1 2 2的左 、右轉向’俾可達到控制飛行器本體1的橫向移動飛 行’左、右旋轉之目的。 (-）飛行ϋ本體1除了上、下升降的飛行之外，並可以在 飛行過程中崎向飾、飛行的效果，提升飛行器本 參 體1的飛行、移動效率，並擴大飛行領域、範圍。 故’本發明為主要針對飛行器之飛行中轉向移動，係利 用飛行器本體於底部所設之轉向控制部，而透過驅動模組之 驅動單元驅動，並使飛行器本體在飛行過財可作橫向飛行 、位移之左、右轉向旋轉為主要保護重點，以方便飛行器的 飛仃操控’乃做航H本體在讀齡時，射同步進行 ^向的移動飛行，並_飛行器具有左、右方向移動飛行控 4之優勢’惟’以上所_為本發明之較佳實施例而已，非 因此即触本發明之專利範圍，故舉凡運用本發明說明書及 ，式内容所為之簡絲氣等效結構，均朗理包含於 本發明之專利範圍内，合予陳明。 2所述’本發明上述可簡錢控之飛行器於使用時， 恭實成達到其功效及目的，故本發明誠為一實用性優異之 發明，為符合發明專利之申請 、 τ月要件’麦依法提出申請，盼 審委早日賜准本案，以保障發明人之辛苦創作，倘若釣局 201010908 審委有任何稽疑，請不吝來函指示，發明人定當竭力配合， 實感德便。The driving unit 2 is a motor 2 1 1 and 2 21 of the two-side driving units 21 and 2, and is provided with a power transmission unit 214, 2 2 4 and a power transmission unit. 214, 2 2 4 rotates with the plurality of gear sets 213, 2 2 3 and drives the annular rack, the pulley, the key wheel and the like to transmit power to the upper and lower propellers 2 3 2, 2 4 2 . Therefore, the above description is only a preferred embodiment of the present invention, and thus the patent of the present invention is not limited thereto, and the movable steering control of the aircraft body 1 at the bottom of the accommodating space 10 is provided. The portion 12 drives the drive gear through the drive module 2 to drive the drive gears 2 7 3, 2 8 3 ' with the drive screws 2 7 2, 2 8 2 of the drive material 2 7 , 2 8 to drive the steering Control Department! 2 disturbing fluid} 22 rotation purpose 'and use the disturbing fluid 12 2 left and right steering '俾 can achieve the lateral movement of the control aircraft =, the purpose of left and right rotation 'for the aircraft to have a rising flight and left, The right-handed Wei Wei, the structure and device of the above-mentioned effects of the track can be slaved to the hair duck, this _ easy to modify and equivalent changes 'all _ rationally included in the (4) of the fine, combined with Chen Ming. The above-mentioned invention can be used in the following (4), and can have the following advantages, such as:) the aircraft body 1 is disposed through the accommodating space 1 活动 the bottom of the movable steering 13 201010908 邛 12, through the driving mode The group 2 drives the steering control unit 12 to disturb the 1 2 2 rotation S, and utilizes the left and right steering '俾 of the disturbance fluid 1 2 2 to achieve the purpose of controlling the lateral movement of the aircraft body 1 to fly left and right. . (-) In addition to the up and down flight, the flying raft body 1 can improve the flight and movement efficiency of the aircraft body 1 and improve the flight field and scope during the flight. Therefore, the present invention is mainly directed to the in-flight steering movement of the aircraft, which is driven by the steering unit provided at the bottom of the aircraft body, and is driven by the driving unit of the driving module, and enables the aircraft body to fly in a flight, The left and right steering rotation of the displacement is the main protection focus, so as to facilitate the flying control of the aircraft. It is the moving movement of the H body when the body is in the reading stage, and the aircraft has the left and right direction of flight control. The advantages of 4 are only the preferred embodiments of the present invention, and thus do not touch the scope of the patent of the present invention, so that the equivalent structure of the present invention and the content of the present invention are uniform. It is included in the scope of the patent of the present invention and is combined with Chen Ming. 2 The above-mentioned simple money-controlled aircraft of the present invention is used in courty to achieve its efficacy and purpose. Therefore, the present invention is an invention with excellent practicability, and is an application for conforming to the invention patent, and a requirement for the invention of the invention. Applying in accordance with the law, I hope that the trial committee will grant this case as soon as possible to protect the inventor's hard work. If there is any doubt in the 201010908 audit committee of the fishing bureau, please do not hesitate to give instructions, the inventor will try his best to cooperate, and feel really good.
15 201010908 【圖式簡單說明】 第一圖係為本發明之立體外觀圖。 第二圖係為本發明之立體分解圖。 第三圖係為本發明之底部立體外觀圖。 第四圖係為本發明之俯視圖。 第五圖係為本發明之側視剖面圖。 第六圖係為本發明較佳實施例之飛行狀態示意圖。 第七圖係為習用飛行器之立體分解圖。 第八圖係為習用飛行器之侧視剖面圖。 【主要元件符號說明】15 201010908 [Simple description of the drawings] The first figure is a three-dimensional appearance of the present invention. The second figure is a perspective exploded view of the present invention. The third figure is a bottom perspective view of the present invention. The fourth figure is a top view of the present invention. The fifth drawing is a side cross-sectional view of the present invention. Figure 6 is a schematic view of the flight state of the preferred embodiment of the present invention. The seventh figure is an exploded view of a conventional aircraft. The eighth figure is a side cross-sectional view of a conventional aircraft. [Main component symbol description]
1、飛行器本體 10、 容置空間 1 01、上支架 1 0 2、下支架 11、 平衡座體 12、轉向控制部 1 2 1、'基座 12 2、擾流體 12 21、轉軸 2、驅動模組 21、驅動單元 211、 馬達 212、 轴心 2 41、下齒輪 2 4 2、下螺旋槳 2 5、供電單元 16 201010908 2 1 3、齒輪組 214、動力傳輸部 2 2、驅動單元 2 2 1、馬達 2 2 2、軸心 2 2 3、齒輪組 2 2 4、動力傳輸部 2 3、中心軸桿 2 31、上齒輪 2 3 2、上螺旋槳 2 4、中心套桿 2 6 2 7 2 7 1 2 7 2 273 274 2 8 28 1 282 28 3 284 、供電單元 、傳動單元 、傳動馬達 、傳動軸桿 、傳動齒輪 、供電糸統 、傳動單元 、傳動馬達 、傳動轴桿 、傳動齒輪 、供電系統 A、機體 A 1、第一容室 A2、垂昇氣孔 A 21、開關閥門 A 3、開口 A 4、推進氣孔 A5 A5 1 A6 A6 1 尾翼 喷射孔 第二容室 馬達 B、旋翼反向機構 B 1、上旋翼 B 3 旋轉軸 17 2010109081. Aircraft body 10, accommodating space 101, upper bracket 10, lower bracket 11, balance base 12, steering control unit 1 21, 'base 12, scramble fluid 12 21, shaft 2, drive mode Group 21, driving unit 211, motor 212, axis 2 41, lower gear 2 4 2, lower propeller 2 5, power supply unit 16 201010908 2 1 3, gear set 214, power transmission unit 2, drive unit 2 2, Motor 2 2 2, Axis 2 2 3, Gear set 2 2 4, Power transmission unit 2 3, Center shaft 2 31, Upper gear 2 3 2, Upper propeller 2 4, Center sleeve 2 6 2 7 2 7 1 2 7 2 273 274 2 8 28 1 282 28 3 284, power supply unit, transmission unit, transmission motor, transmission shaft, transmission gear, power supply system, transmission unit, transmission motor, transmission shaft, transmission gear, power supply system A , body A 1, first chamber A2, vertical air hole A 21, switch valve A 3, opening A 4, propulsion air hole A5 A5 1 A6 A6 1 tail air injection hole second chamber motor B, rotor reversing mechanism B 1 , upper rotor B 3 rotating shaft 17 201010908