TWM509068U - Landing positioning system of propeller flying vehicle - Google Patents
Landing positioning system of propeller flying vehicle Download PDFInfo
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- TWM509068U TWM509068U TW104209332U TW104209332U TWM509068U TW M509068 U TWM509068 U TW M509068U TW 104209332 U TW104209332 U TW 104209332U TW 104209332 U TW104209332 U TW 104209332U TW M509068 U TWM509068 U TW M509068U
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Description
本創作係有關於一種飛行器降落定位系統,尤指一種具有定點導引降落承接及具有立即充電運作之螺旋槳飛行器降落定位系統。The present invention relates to an aircraft landing positioning system, and more particularly to a propeller aircraft landing positioning system with fixed-point guided landing and immediate charging operation.
按,飛行器遙控飛行活動是現代新興的休閒娛樂,更有諸多熱愛此項活動之團體、聯盟產生,也有相關之表演、競賽推出,而飛行器遙控飛行於當今更可結合照相、攝影器材發揮其空照勘查之效果。傳統遙控飛行器以直升機為架構主體,其前進後退及左右轉之操作是靠主螺旋槳的傾角(傾斜)方位來操控,而較新的多軸飛行器則靠多個螺旋槳來達到需要的升力,並透過各螺旋槳轉速的配合(如轉速差)來進行方向操控,其飛行穩定,且可免除如傳統直升機以螺旋傾角方式運動而需於各螺旋槳設置傾角之控制機構,不會大幅增加其技術升級之經濟耗費。According to the aircraft, the remote control flight activity is a modern and emerging leisure entertainment. There are many groups and alliances that love this activity. There are also related performances and competitions. The aircraft remote control flight can be used in conjunction with photography and photographic equipment. The effect of the survey. The traditional remote-controlled aircraft uses a helicopter as the main body of the structure. Its forward and backward movements are controlled by the inclination (tilt) of the main propeller, while the newer multi-axis aircraft relies on multiple propellers to achieve the required lift and The rotation speed of each propeller (such as the difference in rotational speed) is used for direction control, and its flight is stable, and the control mechanism that needs to set the inclination angle of each propeller as in the case of the traditional helicopter to move in a spiral tilt angle can be dispensed with, and the economic upgrade economy is not greatly increased. Cost.
習知多軸(多螺旋槳)飛行器結構及操控架構如第1、2圖所示,該多軸(多螺旋槳)飛行器90係為一四軸飛行器,其包括有一主機架座91及由該主機架座91延伸出之四機架92,該機架92上係設有一馬達93(如無刷馬達)及由該馬達93帶動之螺旋槳94,該主機架座91上並設有一電池95、飛行控制器96及電子變速器98(參第2圖所示之電子變速器98),該主機架座91下方並設有用以降落之腳架97。其中,該電池95係提供該飛行控制器96及馬達93電源,並使電壓符合該電子變速器98輸入之電壓範圍;該飛行控制器96係電性連接(或內設)有遙控器接收器99(導航系統)及陀螺儀(未圖示),該飛行控制器96用以接受GPS導航(依設定軌跡飛行)或遙控器的訊號(使用者操作),來判斷目前該飛行器90的狀態並傳送控制訊號到該電子變速器98,繼 由該電子變速器98放大控制訊號成可驅動該馬達93的對應電壓電流,來達到操控飛行器90的飛行要求動作;該電子變速器98係接收輸入該電池95之電源及該飛行控制器96之訊號,用以輸出該馬達93之三相控制以操控其轉速。Conventional Multi-Axis (Multi-Propeller) Aircraft Structure and Control Architecture As shown in Figures 1 and 2, the multi-axis (multi-propeller) aircraft 90 is a four-axis aircraft comprising a main frame base 91 and the main frame mount 91 extends from the four frame 92, the frame 92 is provided with a motor 93 (such as a brushless motor) and a propeller 94 driven by the motor 93. The main frame holder 91 is provided with a battery 95 and a flight controller. 96 and an electronic transmission 98 (refer to the electronic transmission 98 shown in FIG. 2), and a stand 97 for landing is provided below the main frame base 91. The battery 95 is provided with the power of the flight controller 96 and the motor 93, and the voltage is matched with the voltage range input by the electronic transmission 98; the flight controller 96 is electrically connected (or built) with a remote controller receiver 99. (navigation system) and gyroscope (not shown), the flight controller 96 is configured to receive GPS navigation (by setting a trajectory flight) or a remote control signal (user operation) to determine the current state of the aircraft 90 and transmit Control signal to the electronic transmission 98, following The electronic transmission 98 amplifies the control signal to drive the corresponding voltage current of the motor 93 to achieve the flight request action of the control aircraft 90; the electronic transmission 98 receives the signal input to the battery 95 and the flight controller 96. It is used to output the three-phase control of the motor 93 to control its rotational speed.
前述該習知飛行器90雖可達其由飛行控制器96依來自使用者或GPS導航的指令進行飛行及降落之操作,然,仍有其缺失存在,例如:該飛行器90主要係以電源為動力進行飛行,故該飛行器90之充電操作係為一持續性之工作,該習知飛行器90降落後並無法立即自動進行充電,而需待人力搬移至充電設備處方得進行充電作業,相當繁瑣費時,且會降低其飛行使用時間,由於該飛行器90無法達到降落之立即性充電而受限於充電操作,故也難以應付緊急飛行任務或需大量飛行時間之特定工作需求,顯非理想之設計;再者,該習知飛行器90雖可藉由導航或遙控操作進行定點降落,但其確實降落點仍具有相當之地面範圍,使得該飛行器90降落時並無法得到一妥善接應及安置之保護、防護,導致其降落角度偏頗或遇到特殊地面將可能損毀腳架97,而影響其使用及增加維修費用,亦有一併加以改善之必要。因此,如何改善習知此類飛行器該等缺失問題,乃為業界應努力解決、克服之進一步課題。Although the aforementioned conventional aircraft 90 can reach its flight and landing operations by the flight controller 96 according to instructions from the user or GPS navigation, there are still some missing, for example, the aircraft 90 is mainly powered by power. The flight operation is performed, so the charging operation of the aircraft 90 is a continuous operation. The conventional aircraft 90 cannot be automatically charged immediately after landing, and it is quite cumbersome and time-consuming to wait for the manpower to be moved to the charging device for charging. And it will reduce its flight use time. Because the aircraft 90 can not reach the immediate charging of the landing and is limited by the charging operation, it is also difficult to cope with the emergency mission or the specific work demand requiring a large flight time, which is not ideal design; Although the conventional aircraft 90 can be fixedly landed by navigation or remote control operation, the actual landing point still has a considerable ground range, so that the aircraft 90 cannot be properly protected and protected when landing. The result is that the angle of the landing is biased or that encountering a special ground may damage the stand 97, affecting its use and increasing maintenance. Use, it is necessary also to be improved together. Therefore, how to improve such missing problems of such aircraft is a further problem that the industry should strive to solve and overcome.
緣此,本創作人有鑑於習知飛行器系統架構充電使用上之缺失及其結構設計上未臻理想之事實,本案創作人即著手研發其解決方案,希望能開發出一種更具充電立即性、效益性及便利操作性之螺旋槳飛行器降落定位系統,以服務社會大眾及促進此業之發展,遂經多時之構思而有本創作之產生。Therefore, the creator of this creator has developed a solution based on the lack of charging of the aircraft system architecture and the unsatisfactory design of its structure design, hoping to develop a more charge immediate, The efficiency and convenience of the operation of the propeller aircraft landing positioning system to serve the public and promote the development of this industry, through the long-term concept of the creation of this creation.
本創作之目的係在提供一種螺旋槳飛行器降落定位系統,其能使飛行器在定點降落後能夠得到一妥善之接應安置,進而確保其降落之安全性及增加其使用之時間、壽命者。The purpose of this creation is to provide a propeller aircraft landing positioning system that enables the aircraft to be properly placed after landing at a fixed point, thereby ensuring the safety of its landing and increasing the time and life of its use.
本創作之再一目的係在提供一種螺旋槳飛行器降落定位系 統,其能使飛行器在定點降落後可立即性自動進行充電操作,達到充電作業極佳之效益性、便利性及提升其飛行操作時間者。A further object of the present invention is to provide a propeller aircraft landing positioning system System, which enables the aircraft to automatically perform charging operations immediately after landing at a fixed point, achieving excellent efficiency, convenience and speed up the flight operation time of the charging operation.
本創作為達到上述目的所採用之技術手段,其包括有一飛行器,該飛行器具有一主機架座,該主機架座設有至少一機架,該機架上係設有一馬達及被該馬達所帶動之螺旋槳,該主機架座設有向下延伸之底架,該底架係呈一上寬下窄之錐形或弧錐形體構成。The technical means for achieving the above object includes an aircraft having a mainframe base, the mainframe mount being provided with at least one frame, the frame being provided with a motor and driven by the motor The propeller is provided with a downwardly extending chassis, and the chassis is formed by a wide or narrow tapered or arcuate body.
前述構成,其中該底架之底端係設有一充電座,該充電座係設有至少一充電接點。In the above configuration, the bottom end of the chassis is provided with a charging base, and the charging base is provided with at least one charging contact.
前述構成,其中該主機架座設有至少一容置空間,該機架係延伸進入該容置空間。In the above configuration, the main frame holder is provided with at least one accommodating space, and the frame extends into the accommodating space.
前述構成,其中該主機架座上係設有電性連接之一電池、飛行控制器及電子變速器,該電池係電性導接該充電接點。In the above configuration, the mainframe mount is electrically connected to a battery, a flight controller and an electronic transmission, and the battery electrically connects the charging contact.
前述構成,其進一步包括有一降落裝置,該降落裝置係包括有一定位降落接座,該定位降落接座係呈一上寬下窄之錐形或弧錐形盤體,使該降落接座內形成一錐形或弧錐形承接面;該降落接座於該錐形或弧錐形承接面之底端部中央位置係設有一充電座,該充電座係設有至少一充電接點。The foregoing structure further includes a landing device, the landing device includes a positioning landing socket, and the positioning landing socket is formed by a wide or narrow tapered or arc-shaped conical disk body to form the landing socket. a tapered or arc-conical receiving surface; the landing seat is provided with a charging seat at a central position of the bottom end of the tapered or arc-conical receiving surface, and the charging base is provided with at least one charging contact.
本創作之技術手段係進一步包括有一定位降落裝置,該定位降落裝置係包括有一降落接座,該降落接座係呈一上寬下窄之錐形或弧錐形盤體,使該降落接座內形成一錐形或弧錐形承接面,該降落接座於該錐形或弧錐形承接面之底端部中央位置係設有一充電座。The technical means of the present invention further includes a positioning landing device, the positioning landing device comprising a landing socket, the landing bracket being a wide or narrow tapered or arc-shaped conical disc body, such that the landing bracket A tapered or arcuate bearing surface is formed therein, and the landing seat is provided with a charging seat at a central position of the bottom end of the tapered or arc tapered receiving surface.
前述構成,其中該定位降落裝置係包括有一用以承接該降落接座之底座,該充電座係設有至少一充電接點。In the above configuration, the positioning and landing device includes a base for receiving the landing socket, and the charging base is provided with at least one charging contact.
前述構成,其進一步包括有一飛行器,該飛行器具有一主機架座,該主機架座設有至少一機架,該機架上係設有一馬達及被該馬達所帶動之螺旋槳,該主機架座設有向下延伸之底架,該底架係呈一上寬下窄之錐形或弧錐形體構成。The foregoing structure further includes an aircraft having a mainframe base, the mainframe mount being provided with at least one frame, the frame being provided with a motor and a propeller driven by the motor, the mainframe mount There is a downwardly extending chassis which is formed by a wide or narrow tapered or arcuate body.
前述構成,其中該錐形或弧錐形底架之底端係設有一充電座,該充電座係設有至少一充電接點。In the above configuration, the bottom end of the tapered or arc-conical chassis is provided with a charging base, and the charging base is provided with at least one charging contact.
前述構成,其中該主機架座設有至少一容置空間,該機架係延伸進入該容置空間,該主機架座上係設有電性連接之一電池、飛行控制器及電子變速器,該電池係電性導接該充電接點。In the above configuration, the main frame holder is provided with at least one accommodating space, and the frame extends into the accommodating space, and the main frame holder is electrically connected with a battery, a flight controller and an electronic transmission. The battery is electrically connected to the charging contact.
茲為使 貴審查委員對本創作之技術特徵及所達成之功效更有進一步之瞭解與認識,謹佐以較佳之實施例圖及配合詳細之說明,說明如後:In order to give your reviewers a better understanding and understanding of the technical features of the creation and the efficacies achieved, please refer to the preferred embodiment diagram and the detailed description to illustrate the following:
10‧‧‧飛行器10‧‧‧Aircraft
10A‧‧‧飛行器10A‧‧‧Aircraft
11‧‧‧主機架座11‧‧‧ mainframe base
12‧‧‧容置空間12‧‧‧ accommodating space
13‧‧‧機架13‧‧‧Rack
14‧‧‧馬達14‧‧‧Motor
15‧‧‧螺旋槳15‧‧‧propeller
16‧‧‧電池16‧‧‧Battery
17‧‧‧飛行控制器17‧‧‧ Flight controller
18‧‧‧底架18‧‧‧ Chassis
18A‧‧‧底架18A‧‧‧ Chassis
19‧‧‧充電座19‧‧‧Charging stand
191‧‧‧充電接點191‧‧‧Charging contacts
30‧‧‧定位降落裝置30‧‧‧ Positioning landing gear
30A‧‧‧定位降落裝置30A‧‧‧ Positioning landing gear
31‧‧‧降落接座31‧‧‧ Landing Seating
311‧‧‧錐形承接面311‧‧‧Conical bearing surface
311A‧‧‧錐形承接面311A‧‧‧Conical bearing surface
32‧‧‧底座32‧‧‧Base
33‧‧‧充電座33‧‧‧Charging stand
331‧‧‧充電接點331‧‧‧Charging contacts
40‧‧‧電源線40‧‧‧Power cord
第1圖係習知螺旋槳飛行器結構示意圖。Figure 1 is a schematic view of the structure of a conventional propeller aircraft.
第2圖係習知螺旋槳飛行器操控架構示意圖。Figure 2 is a schematic diagram of a conventional propeller aircraft control architecture.
第3圖係本創作第一實施例之立體分解示意圖。Figure 3 is a perspective exploded view of the first embodiment of the present creation.
第4圖係本創作第一實施例之底視方向立體分解示意圖。Fig. 4 is a perspective exploded perspective view showing the bottom view of the first embodiment of the present invention.
第5圖係本創作第一實施例之降落立體示意圖一。Figure 5 is a schematic perspective view of the landing of the first embodiment of the present invention.
第6圖係本創作第一實施例之降落立體示意圖二。Figure 6 is a schematic perspective view of the landing of the first embodiment of the present invention.
第7圖係本創作第一實施例之充電操座示意圖。Fig. 7 is a schematic view showing the charging operation of the first embodiment of the present invention.
第8圖係本創作第二實施例之立體分解示意圖。Figure 8 is a perspective exploded view of the second embodiment of the present creation.
第9圖係本創作第二實施例之底視方向立體分解示意圖。Figure 9 is a perspective exploded perspective view of the bottom view of the second embodiment of the present invention.
第10圖係本創作第二實施例之降落立體示意圖一。Figure 10 is a schematic perspective view of the landing of the second embodiment of the present invention.
第11圖係本創作第二實施例之降落立體示意圖二。Figure 11 is a perspective view of the second embodiment of the second embodiment of the present invention.
第12圖係本創作第二實施例之充電操座示意圖。Fig. 12 is a schematic view showing the charging operation of the second embodiment of the present invention.
請參閱第3、4圖,係本創作螺旋槳飛行器定位降落系統第一實施例,該螺旋槳飛行器降落定位系統包括有一飛行器10及定位降落裝置30;該飛行器10係以一四軸(或多軸)飛行器進行實施說明,該飛行器10係包括有一主機架座11,該主機架座11設有四個(或複數個)容置空間12,該主機 架座11延伸有一進入該容置空間12之機架13,即該主機架座11具有四個容置空間12及四個機架13,該機架13上係設有一馬達14(如無刷馬達)及螺旋槳15,該馬達14係帶動該螺旋槳15進行旋轉;該主機架座11上係設有一電池16、飛行控制器17及電子變速器(ESC/未圖示),該電池16係提供該飛行控制器17及馬達14電源,且其電壓符合該電子變速器輸入之電壓範圍,該飛行控制器17係電性連接(或內設)有遙控器接收器(導航系統)及陀螺儀(未圖示),該飛行控制器17用以接受GPS導航(依設定軌跡飛行)或遙控器的訊號(使用者操作),來判斷目前該飛行器10的狀態並傳送控制訊號到該電子變速器,繼由該電子變速器放大控制訊號成可驅動該馬達14的對應電壓電流,來達到操控飛行器10的飛行要求動作,該電子變速器係接收輸入該電池16之電源及該飛行控制器17之訊號,用以輸出該馬達14之三相控制以操控其轉速,相關本創作之操控架構可如第2圖所示;再者,該主機架座11並設有向下延伸之底架18,在本實施例中,該底架18係由複數管體(或桿體、板體或其他構件)所整體形成呈一上寬下窄之錐形體構成,該底架18之底端係設有一充電座19,該充電座19之中央部位係設有一充電接點191,該充電接點191(充電座19)係電性導接該電池16,在適當之實施方式中,該充電接點191(充電座19)與電池16之電性導接係通過該底架18及主機架座11內部之連通設置形成。Please refer to Figures 3 and 4, which is a first embodiment of the present propeller aircraft positioning landing system. The propeller aircraft landing positioning system includes an aircraft 10 and a positioning landing device 30; the aircraft 10 is a four-axis (or multi-axis) The aircraft is described as an implementation. The aircraft 10 includes a main frame base 11 , and the main frame base 11 is provided with four (or plural) accommodating spaces 12 . The frame 11 extends to a frame 13 that enters the accommodating space 12, that is, the main frame base 11 has four accommodating spaces 12 and four frames 13. The frame 13 is provided with a motor 14 (such as a brushless a motor 14 and a propeller 15 for driving the propeller 15 to rotate; the main frame base 11 is provided with a battery 16, a flight controller 17, and an electronic transmission (ESC/not shown), and the battery 16 provides the The flight controller 17 and the motor 14 are powered, and the voltage thereof is in accordance with the voltage range of the electronic transmission input. The flight controller 17 is electrically connected (or built) with a remote controller receiver (navigation system) and a gyroscope (not shown). The flight controller 17 is configured to receive GPS navigation (by a set trajectory flight) or a remote control signal (user operation) to determine the current state of the aircraft 10 and transmit a control signal to the electronic transmission, followed by The electronic transmission amplifies the control signal into a corresponding voltage and current that can drive the motor 14 to achieve the flight request action of the control aircraft 10. The electronic transmission receives the signal input to the battery 16 and the flight controller 17 for outputting the signal. Motor 1 4 three-phase control to control its rotational speed, the control structure of the present invention can be as shown in FIG. 2; further, the main frame base 11 is provided with a downwardly extending chassis 18, in this embodiment, The bottom frame 18 is formed by a plurality of tubular bodies (or a rod body, a plate body or other members) integrally formed as a wide and narrow tapered body. The bottom end of the bottom frame 18 is provided with a charging seat 19, and the charging base is provided. The central portion of the 19 is provided with a charging contact 191. The charging contact 191 (the charging stand 19) electrically connects the battery 16. In a suitable embodiment, the charging contact 191 (charging stand 19) and the battery The electrical guiding of 16 is formed by the communication arrangement between the chassis 18 and the main frame base 11.
該定位降落裝置30係包括有一底座32及設於該底座32上之降落接座31,該降落接座31係呈一上寬下窄之錐形盤體,使該降落接座31內形成一錐形承接面311;該降落接座31於其錐形承接面311之底端部中央位置係設有一充電座33,該充電座33之中央部位係設有一充電接點331。The positioning and landing device 30 includes a base 32 and a landing socket 31 disposed on the base 32. The landing bracket 31 is a conical disk having a width and a narrow upper and lower sides, so that a recessed socket 31 is formed therein. The charging base 33 is provided with a charging seat 33 at a central portion of the bottom end of the tapered receiving surface 311. A charging contact 331 is disposed at a central portion of the charging base 33.
前述該主機架座11之底架18其構形係對應或吻合該降落接座31(錐形承接面311)之構形,而該底架18之充電座19(充電接點191)與該降落接座31之充電座33(充電接點331)對接(或對應設置)時可進行充電操作,其對接充電方式可為接觸電極式充電、感應式充電或其他充電方式。The chassis 18 of the main frame base 11 has a configuration corresponding to or conforms to the configuration of the landing socket 31 (the tapered receiving surface 311), and the charging base 19 (charging contact 191) of the chassis 18 is When the charging stand 33 (charging contact 331) of the landing connector 31 is docked (or correspondingly disposed), the charging operation can be performed, and the docking charging mode can be contact electrode charging, inductive charging or other charging mode.
請一併參閱第5、6圖,本創作螺旋槳飛行器定位降落系統應用時,該飛行器10藉由GPS導航、基地台、遙控器等系統輔助定位(如WiFi、 4G、藍芽、紅外線、超音波等無線傳輸定位),使當該飛行器10(底架18)飛行至該定位降落裝置30之錐形承接面311向上延伸範圍時,即可使該飛行器10停降於該降落接座31上,並以重力輔助使該飛行器10之底架18滑降於該降落接座31底部之充電座33上,使該底架18恰被承接安置於該降落接座31。又如第7圖所示,該定位降落裝置30係連接有一電源線40,該電源線40係電性導接該充電座33(充電接點331);此時該底架18之充電座19係與該降落接座31之充電座33呈接合(或相對應)之狀態,並藉該充電座19、充電座33(充電接點191、充電接點331)之相互對接或感應進行立即式之充電操作。Please refer to Figures 5 and 6 together. When the propeller aircraft positioning and landing system is applied, the aircraft 10 is assisted by GPS navigation, base station, remote control, etc. (such as WiFi, 4G, Bluetooth, infrared, ultrasonic, etc. wireless transmission positioning, so that when the aircraft 10 (chassis 18) flies to the upwardly extending range of the tapered receiving surface 311 of the positioning and landing device 30, the aircraft 10 can be stopped Lowering on the landing joint 31, and assisting the base frame 18 of the aircraft 10 to descend on the charging base 33 at the bottom of the landing socket 31 by gravity, so that the chassis 18 is just received and placed on the landing socket 31. . As shown in FIG. 7, the positioning and landing device 30 is connected to a power cord 40, and the power cable 40 electrically connects the charging base 33 (the charging contact 331); at this time, the charging stand 19 of the chassis 18 And the charging seat 33 of the landing socket 31 is in a state of being engaged (or corresponding), and the charging seat 19, the charging base 33 (the charging contact 191, the charging contact 331) are mutually coupled or sensed for immediate use. Charging operation.
請參閱第8至12圖,係本創作螺旋槳飛行器定位降落系統第二實施例,其係基於第一實施例之結構基礎上加以變換設置,其差異係在於:該飛行器10A之底架18A係呈一上寬下窄之弧錐形體構成,而該定位降落裝置30A之錐形承接面311A亦呈相對應上寬下窄之弧錐形(盤體)接面構成,使當該飛行器10A(底架18A)飛行至該定位降落裝置30A之錐形承接面311A上而依重力輔助滑降於該充電座33上時,得以具有對應順暢之承接滑落及接合安置之穩定狀態,並便利後續之充電操作,如第12圖所示。Referring to Figures 8 to 12, a second embodiment of the propeller aircraft positioning landing system of the present invention is based on the structure of the first embodiment. The difference is that the chassis 18A of the aircraft 10A is The upper and lower narrow arc-shaped cones are formed, and the tapered receiving surface 311A of the positioning and lowering device 30A is also formed by a corresponding upper and lower narrow arc-conical (disc) joint surface, so that when the aircraft 10A (bottom) When the frame 18A) is flying onto the tapered receiving surface 311A of the positioning and landing device 30A and assisting to slide down on the charging base 33 by gravity, it has a stable state of corresponding smooth sliding and joint placement, and facilitates subsequent charging operations. As shown in Figure 12.
本創作螺旋槳飛行器降落定位系統藉由前述構成,其能引導飛行器降落後,自動定位停放,使飛行器降落後能夠得到一妥善之接應安置,進而確保其降落之安全性;且其定點降落後並可立即性自動進行充電操作,達到充電作業極佳之效益性及便利性。本創作螺旋槳飛行器降落定位系統的優點,可讓飛行器在具成本效益的降落機制外,而仍保有精準定點降落的目的,此外,本創作也可用於物聯網防災系統中,監視設備飛行器空拍機的引導降落使用。According to the foregoing configuration, the propeller aircraft landing positioning system can guide the aircraft to fall behind and automatically locate and park, so that the aircraft can get a proper connection after landing, thereby ensuring the safety of the landing; Immediately and automatically perform the charging operation to achieve excellent efficiency and convenience of the charging operation. The advantages of the propeller aircraft landing positioning system can make the aircraft have a cost-effective landing mechanism, but still maintain the purpose of accurate fixed-point landing. In addition, this creation can also be used in the Internet of Things disaster prevention system, monitoring equipment aircraft aerial camera The guide is used for landing.
綜上所述,本創作確已符合新型專利之要件,爰依法提出專利申請。惟以上所述者,僅為本創作較佳實施例而已,並非用來限定本創作實施之範圍,故舉凡依本創作申請專利範圍所述之形狀、構造、特徵及精神所為之均等變化與修飾,均應包括於本創作之申請專利範圍內。In summary, this creation has indeed met the requirements of the new patent, and filed a patent application in accordance with the law. However, the above description is only for the preferred embodiment of the present invention, and is not intended to limit the scope of the present invention. Therefore, the shape, structure, characteristics and spirit described in the scope of the patent application are equally changed and modified. , should be included in the scope of the patent application of this creation.
10‧‧‧飛行器10‧‧‧Aircraft
11‧‧‧主機架座11‧‧‧ mainframe base
12‧‧‧容置空間12‧‧‧ accommodating space
13‧‧‧機架13‧‧‧Rack
14‧‧‧馬達14‧‧‧Motor
15‧‧‧螺旋槳15‧‧‧propeller
18‧‧‧底架18‧‧‧ Chassis
19‧‧‧充電座19‧‧‧Charging stand
191‧‧‧充電接點191‧‧‧Charging contacts
30‧‧‧定位降落裝置30‧‧‧ Positioning landing gear
31‧‧‧降落接座31‧‧‧ Landing Seating
311‧‧‧錐形承接面311‧‧‧Conical bearing surface
32‧‧‧底座32‧‧‧Base
33‧‧‧充電座33‧‧‧Charging stand
331‧‧‧充電接點331‧‧‧Charging contacts
Claims (5)
Priority Applications (1)
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TW104209332U TWM509068U (en) | 2015-03-13 | 2015-03-13 | Landing positioning system of propeller flying vehicle |
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TW104209332U TWM509068U (en) | 2015-03-13 | 2015-03-13 | Landing positioning system of propeller flying vehicle |
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TWM509068U true TWM509068U (en) | 2015-09-21 |
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Cited By (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
TWI571045B (en) * | 2015-12-25 | 2017-02-11 | Methods and systems for abnormal detection of solar power plants | |
TWI586413B (en) * | 2015-12-03 | 2017-06-11 | A flight mechanism with a multiprocessing module | |
TWI672887B (en) * | 2016-12-27 | 2019-09-21 | 財團法人工業技術研究院 | Charging station and charging station module |
US10843573B2 (en) | 2016-12-27 | 2020-11-24 | Industrial Technology Research Institute | Charging station and charging station module |
-
2015
- 2015-03-13 TW TW104209332U patent/TWM509068U/en unknown
Cited By (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
TWI586413B (en) * | 2015-12-03 | 2017-06-11 | A flight mechanism with a multiprocessing module | |
TWI571045B (en) * | 2015-12-25 | 2017-02-11 | Methods and systems for abnormal detection of solar power plants | |
TWI672887B (en) * | 2016-12-27 | 2019-09-21 | 財團法人工業技術研究院 | Charging station and charging station module |
US10843573B2 (en) | 2016-12-27 | 2020-11-24 | Industrial Technology Research Institute | Charging station and charging station module |
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