M395641 五、新型說明： 【新型所屬之技術領域】 本創作係有關一種空拍飛行器之承載架結構及其空 拍飛行器，特別指一種模組結構設計且具有高結構強度與 • 質量輕的空拍飛行器之承載架結構及其空拍飛行器。 【先前技術】 目前空拍技術正在快速發展，例如運用遙控之無人載 φ 具可以針對小地區或是災區等人員無法進入勘查之區 域，得以快速地取得實地影像，符合機動性的地面調查或 快速勘查之需求。 針對空拍的領域，遙控直昇機運動之技術已相當成熟 而廣泛應用於空拍的任務，對其性能及安全性，結構剛性 之要求也越來越高，但多年來遙控直昇機之機體結構，重 量，均無重大之改良，因此，如何在相同的引擎動力條件 下，具有較長的飛行時間，以擷取到足夠多的影像資訊， • 則為目前研發的方向。 另一方面，由於攝影鏡頭通常係掛載於一支撐架上， 並利用支撐架組合於遙控直昇機，故為了具有較佳的飛行 態樣，支撐架的剛性、結構性必須符合要求。因此，上述 支撐架必須具備有高強度及質量輕的特色，方能使空拍作 業得以順利執行。 本案創作人有鑑於上述習用的結構裝置於實際施用 時的缺失，且積累個人從事相關產業開發實務上多年之經 驗，精心研究，終於提出一種設計合理且有效改善上述問 3/12 M395641 題之結構。 【新型内容】 本創作之主要目的，在於提供一種空拍飛行器之承載 架結構，其具有模組化之結構，且整體結構具有高強度、 韌性佳、質量輕的特性，以提升空拍飛行器執行空拍作業 的性能。 為了達到上述目的，本創作係提供一種空拍飛行器之 承載架結構，係包含：一承載架主體，其係連接於一空拍 _ 飛行器之底部，該承載架主體係由一第一主板體與一第二 主板體所建構形成；一儀器承載架，該儀器承載架係可動 地連接於該承載架主體；以及一控制單元，其係安裝於承 載架主體上。 本創作更提出一種具有上述承載架結構之空拍飛行 器。 如上述構造，本創作利用第一主板體與一第二主板體 建構形成該承載架主體，並以該承載架主體做為主結構 · 體，以裝設儀器承載架、控制單元以及其他組件，因此， 承載架結構的整體結構簡單、穩定，且本創作之承載架主 體採用複合材料，以達到高強度、高韌性及減輕重量的優 點。 為使能更進一步瞭解本創作之特徵及技術内容，請參 閱以下有關本創作之詳細說明與附圖，然而所附圖式僅提 供參考與說明用，並非用來對本創作加以限制者。 4/12 M395641 【實施方式】 首先，請參閱第一圖所示之空拍飛行器之承載架結構 1二其主要係設置於一空拍飛行器2之底部，例如一遙控 直昇機或是類似於無載人型之飛行器等，但不以上述^ 限，而該承載架結構1包括承载架主體1 0、儀器承载架 11及控制單兀12;其中該承載架主體1〇係由一第— 主板體1 0A與一第二主板體工〇B所建構形成，而儀器 承載架1 1則樞接於該承載架主體丄〇，以用於承載、; 設一影像榻取模組i 4，故本創作之承載架結構工桓 組化的結構，其整體結構強度大，且承載架結構工可具有 減重特!·生，可大幅減輕裝設本創作之承載架結構1的 飛的結構重量’增加其引擎工作效率，降低油：， 亚k升空拍飛行器2執行空拍任務的能力。 二參考第-圖至第三圖，承载架主體i 〇係為本創 =主體結構，其係連接於上述空拍飛行器2之底部，用以 裝设影像擷取模組i 4、控制單元1 2等纟且 例中，承載架主體10係由第—主板體1〇八與== 體1 0B所組農構成，例如利用多個連接件 主板體iQA與第二主板體1GB相互固定“弟— 載架主體！〇形成一容置空 ^该承 器承則及影像擷取模組“;更I::::述 將兩者對應_颜料構成—倒 _ k構’ f置空間100。另-方面，複合材料的;該 輕量化的雜亦細於本，為了 5/12 M395641 載架主體1 0的重量，本創作採用碳纖維材質之第一主板 體1 〇Α、第一主板體1 QB及儀器承載架1 1等機構 件，以減輕承載架結構1的整體重量。 、 另一方面，儀器承載架1 1係可動地連接於該承载架 主體10,具體而言，儀器承載架係設於容置办門工 0 0中以螺鎖裝㈣像擷取模組i 4。在本具體^例 中，該儀器承載架1 1係包括一儀器承载件丄丄i及分別 設於該儀器承載件1 i i兩側之支fi 2，儀器承&件 1 1 1係用於裝設影像擷取模組1 4，且該支臂1 1 2中 設有至少一個活動關節，而承載架結構丄更包括有一連接 於該儀器承載架1 1之驅動件丄3，驅動件i 3可包括動 力輸出端1 3 1、-第一連動件工3 2與一第二連動件丄 3 3 ’該第-連動件！ 3 2的一端連接於該動力輸出端工 3 1上，該第一連動件工3 2的另一端枢接於該第二連動 件13 3,-端，而該第二連動件133的自由端則樞接 於該儀器承载架1 1上（如該支臂工工2上），因此，藉 由驅動件1 3之動力輸出端χ 3工的動作可連動地帶“ 第一連動件132與第二連動件133的動作，進而改變 儀器承載架1 1之儀器承載件丄1丄的位置、角度，以控 制影像擷取模組14的取景位置及取景角度，如第四A圖 與第四B圖即顯示兩種不同拍攝角度的示意圖。 如第一圖所不，該控制單元丄2係設於承载架主體1 上，例如將其固定於第—主板體i QA與第二主板體i B之間。S本具體實施例巾’該控制單^ 2可包含訊 接收模組（如天線1 2 1 )、動態控制模組（圖未示） 0 0 號 6/12 M395641 圖未示)，該動態控制模組可包含馬達 二 ^ =達與該馬達控制器電性連接（請注 i線等物^之簡潔，本案並未繪製出電性連接之電線、 ^線專物件），而該馬達係為該動力輸出端丄3丄之動力 源，该拍攝控制模組則電性連接於該影像掘取模組工4， 因此，#控者即可利用遙控模組（圖未示 脑號被㈣單元12线號接收模_接收:，，=^ 之馬達控制器與馬達調整儀器承载架η! =承載件1 1 1的位置、角度，以控制影像擷取模組工 4的取景位置及取景角度’接著即可再·遙控模组發出 ^線訊號，該訊朗樣被控制單元12之訊號接收模組所 收，以利用拍攝控制模组控制影像榻取模組 照、攝影等作業。 4 ▲再-方面，為了達到較佳的影像擷取、攝影的效果， 該承載架主體1 Q更包括有減震元件1 Q 2，例如，彈性 塾等類似元件，以避免空拍飛行器2的震動影響影像擷取 核組1 4 ’故在本具體實施例中，該減震元件工◦ 2可設 置於承载架主體1 〇與該空拍飛行器2之間，或是第一主 板體1 Q A與第二主板體；[QB之間，以降低不同轴向的 震動對影像擷取模組1 4的影響，而減震元件i 〇 2的位 置及其數量均可依據實際的應用加以調整。 再者，為了提高承載架主體！ 〇的結構強度，本實施 例之承載架主體1 〇更包括有補強片丄〇3，如第一主板 體1 0A與第二主板體i 〇B之間即可設有補強片上〇 3，以提高承載架主體！ 〇的結構強度。更為了使空拍飛 7/12 M395641 行器2降落於地面的穩定性，該承载架主體i 〇更進一步 具有支撐件1 0 4 ’如前文所述之倒u形結構體的兩自= 端均設有支撐件1 〇 4，以使空拍飛行器2可穩定地放置 於地面上。 而在另一變化實施例中，該承载架主體丄〇上更可設 有轉盤裝置及飛行器固定座，該轉盤裝置係樞設於該飛行 器固定座之底面，該飛行器固定座之頂面係可固定於空拍 飛行器2之底部；該轉盤裝置設有複數個連接部，以^接 該承載架主體1 〇 ^操控者亦可利用遙控模組（圖未示） 發出無線訊號，使該轉盤裝置進行轉動，進而帶動該承'載 架主體1 0作轉動動作，以調整影像擷取模組丄：的方 位。 因此’藉由上述構造，本創作提出之承载架結Μ具 有，組化之結構’且其材質係為高剛性、高強度、拿刃性佳、 質量輕的複合材料，故可大幅提高空拍飛行 之功能性。 μ叮仕粉 、，示上所述，本創作具有以下功效： 1、本創作之承載架結構可應用於空拍飛㈣，使— 二飛：器得以負载影像摘取模組以進行空中拍攝❹ 必仰賴人員親自乘坐飛行機進行實地拍攝，故可 震=難以進人之炎區進行無人探勘作業，並取得實地 〜像、旦面，以加速救災、重建的工作。 承餘結構具有模組化態樣，整體、_ ’早〃有间強度、韌性佳、質量輕的優點 低空拍飛行器的耗油量” 田条 攸而捻间空拍飛行器的飛行距離 8/12 M395641 與飛行時間。 m =上所述僅為袖作之較佳可行實_，非因此褐限 所A :專利範圍’故舉凡運用本創作說明書及圖示内容 所為U效技術變化，均包含於本創作之範圍内。 【圖式簡單說明】 Ϊ圖圖係為本創作之承载架結構與空拍飛行器的組合示 結構的立體示意圖。 之組合示意圖。 義。。承載架與驅動件 承載架之第 第四Α圖係為本創作之承 角度示意圖。 戰木、、、σ構的儀器 儀器承载架 之第 為本創作之承載架結構的M395641 V. New description: [New technical field] This creation is about the carrier structure of an aerial camera and its aerial camera, especially a modular structure design with high structural strength and light weight. The carrier structure of the aircraft and its aerial aircraft. [Prior Art] At present, the aerial photography technology is developing rapidly. For example, the remote control unmanned vehicle can be used to locate the area in the small area or the disaster area, and the field image can be quickly obtained. The need for exploration. In the field of aerial photography, the technology of remote-controlled helicopter movement is quite mature and widely used in the task of aerial photography. The requirements for its performance and safety and structural rigidity are also getting higher and higher, but the structure and weight of the remote-controlled helicopter for many years. There are no major improvements, so how to get enough image information under the same engine power conditions to capture enough image information, and the current research and development direction. On the other hand, since the photographic lens is usually mounted on a support frame and combined with the RC helicopter by using the support frame, the rigidity and structure of the support frame must meet the requirements in order to have a better flight condition. Therefore, the above-mentioned support frame must have the characteristics of high strength and light weight, so that the aerial work can be smoothly executed. In view of the lack of the above-mentioned conventional structural devices in actual application, and the accumulated experience of individuals engaged in relevant industry development practice, the creators of this case have finally made a reasonable design and effectively improve the structure of the above question 3/12 M395641. . [New content] The main purpose of this creation is to provide a carrier structure for an aerial camera, which has a modular structure, and the overall structure has the characteristics of high strength, good toughness and light weight to enhance the execution of the aerial aircraft. The performance of an aerial job. In order to achieve the above object, the present invention provides a carrier structure for an aerial vehicle, comprising: a carrier body connected to the bottom of an aerial camera, the main system of the carrier is composed of a first main body and a The second main body is constructed; an instrument carrier, the instrument carrier is movably coupled to the carrier body; and a control unit is mounted on the carrier body. The present invention further proposes an aerial camera having the above-described carrier structure. According to the above configuration, the present invention constructs the carrier body by using the first main body and the second main body, and the main body of the carrier is used as a main structure to install an instrument carrier, a control unit and other components. Therefore, the overall structure of the carrier structure is simple and stable, and the main body of the carrier of the present invention adopts a composite material to achieve the advantages of high strength, high toughness and weight reduction. In order to further understand the features and technical contents of the present invention, please refer to the following detailed description and drawings of the present invention. However, the drawings are only for reference and explanation, and are not intended to limit the creation. 4/12 M395641 [Embodiment] First, please refer to the carrier structure of the aerial vehicle shown in the first figure. The main structure is set at the bottom of an aerial camera 2, such as a remote control helicopter or similar to no-loader. An aircraft or the like, but not limited to the above, and the carrier structure 1 includes a carrier body 10, an instrument carrier 11 and a control unit 12; wherein the carrier body 1 is composed of a first main body 1 0A is formed by a second main body workbench B, and the instrument carrier 1 1 is pivotally connected to the main body of the carrier for carrying, and an image reclining module i 4 is provided. The structural structure of the carrier structure is large, and the overall structural strength is large, and the structural structure of the carrier can have a weight reduction characteristic, and the structure weight of the flying structure of the carrier structure 1 of the present invention can be greatly reduced. Its engine work efficiency, reducing oil:, the ability of the sub-k liter aerials aircraft 2 to perform aerial missions. Referring to the first to third figures, the carrier body i is a main body structure, which is connected to the bottom of the above-mentioned aerial camera 2 for mounting the image capturing module i 4 and the control unit 1 2, and in the example, the carrier body 10 is composed of the first main body body 1-8 and the == body 10B, for example, using a plurality of connector main body iQA and the second main body 1GB to fix each other. — The main body of the carrier! 〇 形成 形成 形成 形成 形成 形成 形成 形成 形成 形成 形成 形成 形成 形成 形成 形成 形成 形成 形成 形成 形成 形成 形成 形成 形成 形成 形成 形成 形成 形成 形成 形成 形成 形成 形成 形成 形成 形成 形成 形成 形成 形成 形成 形成On the other hand, the composite material; the lightweight and finer is also finer than this. For the weight of the 5/12 M395641 carrier body 10, the first main body of the carbon fiber material is used, and the first main body 1 is used. The QB and the instrument carrier 1 1 are mechanical components to reduce the overall weight of the carrier structure 1. On the other hand, the instrument carrier 1 1 is movably connected to the carrier body 10, specifically, the instrument carrier is installed in the accommodating door operator 0 0 to be screw-locked (4) like the capturing module i 4 . In this embodiment, the instrument carrier 1 1 includes an instrument carrier 丄丄i and a pair of fi 2 disposed on both sides of the instrument carrier 1 ii, and the instrument bearing 1 1 1 is used for An image capturing module 14 is disposed, and at least one movable joint is disposed in the arm 112, and the carrier structure further includes a driving member 连接3 connected to the instrument carrier 11, the driving member i 3 may include a power output end 1 3 1 , a first linkage member 3 2 and a second linkage member 丄 3 3 'the first linkage member! One end of the third connecting member 3 is connected to the power output end 31, and the other end of the first linking member 3 2 is pivotally connected to the second linking member 13 3, the end, and the free end of the second linking member 133 Then, it is pivotally connected to the instrument carrier 1 1 (such as the arm worker 2). Therefore, the action of the power output end of the driving member 13 can be linked to the "first linkage 132" The action of the second linking member 133 further changes the position and angle of the instrument carrier 丄1丄 of the instrument carrier 1 1 to control the framing position and the framing angle of the image capturing module 14, such as the fourth A and fourth B The figure shows a schematic diagram of two different shooting angles. As shown in the first figure, the control unit 丄 2 is attached to the carrier body 1, for example, to the first main body i QA and the second main body i B Between the embodiment of the present invention, the control unit 2 can include a receiving module (such as an antenna 1 2 1 ), a dynamic control module (not shown) 0 0 6/12 M395641 (not shown), The dynamic control module can include a motor 2^ to electrically connect with the motor controller (please note that the i line and the like are simple, the case is The electrical connection wire and the wire object are drawn, and the motor is the power source of the power output terminal, and the shooting control module is electrically connected to the image capturing module 4, , #控者 can use the remote control module (not shown in the figure is the (four) unit 12 line number receiving mode _ receiving:,, = ^ motor controller and motor adjustment instrument carrier η! = carrier 1 1 1 The position and angle are controlled by the image capture module 4 and the viewing angle of the image capture module 4, and then the remote control module sends a ^ line signal, which is received by the signal receiving module of the control unit 12 to The shooting control module is used to control the operation of the image pickup module, photography, etc. 4 ▲Re-, in order to achieve better image capturing and photography effects, the carrier body 1 Q further includes a damping component 1 Q 2. For example, an elastic cymbal or the like is used to prevent the vibration of the aerial vehicle 2 from affecting the image capturing core group 1 4 ′. Therefore, in the present embodiment, the damper element workpiece 2 may be disposed on the carrier body 1 〇 Between the aerial vehicle 2 or the first main body 1 QA The second main body; [between QBs, to reduce the influence of different axial vibrations on the image capturing module 14 , and the position and the number of the damping elements i 〇 2 can be adjusted according to the actual application. In order to improve the structural strength of the carrier body, the carrier body 1 of the embodiment further includes a reinforcing sheet 3, such as between the first motherboard body 10A and the second motherboard body i 〇B. The upper part of the reinforcing sheet is provided to increase the structural strength of the main body of the carrier. The stability of the aerial flying 7/12 M395641 row 2 is lowered to the ground. The main body of the carrier i further has a support member 1 0 4 'The two self-ends of the inverted u-shaped structure as described above are each provided with a support member 1 〇 4 so that the aerial vehicle 2 can be stably placed on the ground. In another variation, the carrier body can be further provided with a turntable device and an aircraft mount. The turntable device is pivotally disposed on a bottom surface of the aircraft mount, and the top surface of the aircraft mount can be Fixed to the bottom of the aerial vehicle 2; the turntable device is provided with a plurality of connecting portions for connecting the carrier body 1 to the controller. The controller can also use the remote control module (not shown) to send a wireless signal to make the turntable device The rotation is performed to drive the carrier body 10 to rotate to adjust the orientation of the image capturing module. Therefore, by the above-mentioned structure, the carrier of the present invention has a structure of a group, and the material is a composite material with high rigidity, high strength, good blade quality and light weight, so that the aerial shot can be greatly improved. The functionality of flight. According to the above, the creation has the following functions: 1. The frame structure of the creation can be applied to the aerial shooting (four), so that the two flying: the device can load the image capturing module for aerial shooting. ❹ Depends on the personnel to take a flight to the field to shoot, so it is difficult to enter the flaming area to carry out unmanned exploration operations, and to obtain the field ~ image, Dan face, to speed up disaster relief, reconstruction work. The residual structure has a modular appearance, and the overall, _ 'early strength, toughness, and light weight advantages of the low-altitude aircraft fuel consumption." The flight distance of the field and the airborne aircraft 8/12 M395641 and flight time. m = the above is only a better feasible for the sleeve. _, therefore, the brown limit A: the scope of the patent's use of this creation manual and the content of the illustration is a U-technology change, are included in Within the scope of this creation. [Simple diagram of the diagram] The diagram is a three-dimensional diagram of the combined structure of the carrier structure and the aerial vehicle of the creation. The combination diagram. The carrier and the driver carrier The fourth map is a schematic diagram of the angle of the creation. The instrument and instrument carrier of the war wood, and σ structure is the foundation of the carrier structure of the creation.
【主要元件符號說明】 1 承載架結構 10 承載架主體 1 0Α 1 0Β 1 0 0 1 〇 1 1 0 2 1 0 3 1 0 4 苐一主板體 苐二主板體 谷置空間 連接件 減震元件 補強片 支撐件 9/12 M395641 11 儀器承載架 1 1 1 儀器承載件 1 1 2 支臂 12 控制單元 1 2 1 天線 13 驅動件 1 3 1 動力輸出端 1 3 2 第一連動件 1 3 3 第二連動件 14 影像擷取模組 2 空拍飛行器 10/12[Main component symbol description] 1 Carrier structure 10 Carrier body 1 0Α 1 0Β 1 0 0 1 〇1 1 0 2 1 0 3 1 0 4 主板一 motherboard body 苐2 motherboard body space connection connector damping component reinforcement Sheet support 9/12 M395641 11 Instrument carrier 1 1 1 Instrument carrier 1 1 2 Arm 12 Control unit 1 2 1 Antenna 13 Drive 1 3 1 Power take-off 1 3 2 First link 1 3 3 Second Linkage 14 image capture module 2 aerial camera 10/12