201206767 殼體棒放該負載。 在不同實施例中，該負載可包含一照相機組件，係設 置以通過在該底壁的該開口樞轉出該殼體。在一些實施 例中)該可撓纜繩係一皮帶。該偏壓元件可驅使該負載 至一展開位置，且該偏壓元件可包含一彈簧。在不同實 施例中，該負載係經由一鉸鏈樞接至該殼體的一前壁。 在一些實施例中，該鉸鏈可包含一樞軸桿，且該偏壓元 件包含一彈簧’該彈簧係圍繞該柩軸桿而設置。 在不同實施例中，該負載更包含一照相機組件，其具 有一盤狀托盤裝設於其十，該盤狀托盤係經由一鉸鏈樞 接至該殼體，該盤狀托盤包含該絞盤及一盤致動器，同 時該盤致動器係位於該鉸鏈與該絞盤之間。 【實施方式】 水路兩用的無人飛行載具 圖1繪示一水路兩用的無人飛行載具（unmanned aerial vehicle)或UAV 1〇的一透視簡圖。水路兩用的無人飛 打載具10具有一機身1〇〇,其具有模組化隔間12〇、13〇 及1牟〇以容納模組化的組件或模組，例如一電池模組 2〇負載模組30、及航空電子模組40。在各種實施例 2，翼部15及/或16可由多個零件構成，在降落期間， 它們可為分離的及/或「可拆開的」或與機身1〇〇是分離 的。 圖2繪不圖i之水路兩用的無人飛行載具的機身 201206767 100的簡化上視圖。機身100的壁11〇係由能漂浮材 料所’·=£成以使機身1 〇〇在該機身滿載組件如圖i所示 的電池20、負載30與航空電子4〇及其他非機零件與組 件時斯•在/又有裝設翼部（未圖示）的情況下而漂浮。 例如，壁11 0可具有以一防水層密封的一模製發泡體核 心，雖然此非為必要的。壁110可為一單一連續壁或多 個壁片段’或類似物。 在此實施例中，機身被分成三個隔間，一前電池隔間 120、一中央負載隔間13〇、及一後航空電子隔間14〇。 前電池隔間120與中央負載隔間13〇係以分隔壁15〇隔 開。中央負載隔間130與後航空電子隔間14〇係以分隔 壁160隔開。在所示實施例中’突耳1〇4、ι〇5及ι〇6係 用作固定組件（未圖示）於隔間12〇、130及140内的一 裝置。突耳105可藉由可旋轉的把手1〇5h而手動旋轉， 以安裝一電池（未圖示）’然後再被轉回至如圖示的位 置，以鎖定電池於前電池隔間120内。亦可使用可旋轉 的突耳104、105及106以外的其他固定機構。 電池隔間120具有安裝表面122，其支撐一電池（未 圖示 >。在此實施例中，一連接器124，可為一表面安裝 連接器或類似物’一般係與安裝表面122齊平。通道126f 與126r係凹設於安裝表面122之下。排水口，如通道126f 内的滴流孔128b ’係延伸穿過機身1 〇〇的底壁丨丨〇b。通 道126r•内的滴流孔128s (如圖1-3所示）係延伸穿過機 身100的側壁1 l〇s。 6 201206767 若機身露出水面，連接器124的接合表面124m係位 於通道126f與126r的上方，會使在電池2〇 (圖n連 接/分開時，該接合表面不會浸入水中。配線12訂與123b 可刀別行進於通道126f與126b中，並且嵌壁式及/或嵌 入式地經由機身100以提供電力至馬達（未圖示）、及航 空電子模組40及/或一負載模組43〇。 中央負載隔間130具有前安裝表面132f與後安裝表面 132r ’其支撐一負載，如一照相機組件（未圖示）。負載 模組30可包含攝相的、偵測的、或其他被動的、主動的、 非致命的（non-lethal)、或致命的（iethal)負載裝置。 在此實施例中，一連接器134係與安裝表面n2r齊平， 其可為表面女裝連接器或類似物。安裝表面usr可形 成-外殼163以容納連接器134與相關的配線。該外殼 可形成分隔壁160的一下部。滴流孔228s (如圖3所 示）可從外殼163之内開始延伸而穿過側壁n〇s，允許 將水排出外殼163。在此實施例中，中央隔間13〇具有 大型開口 13 1於該底部，使得可應用一照相機，例如 向下觀看，或經由該大型開口 131將其降下至氣流中。 大型^ 口 131亦允許從中央隔間13〇排出流體。 在各種實施例中，連接器134的接合表面134m可位 在高於㈣163頂部的開卩131之上，以使即便該機身 沒有完全露出水面’當負载％ (圖1)在連接/分開情況 下’該接合表面不會浸入水中。 後航空電子隔間140具有一安裝表面142，位於航空 201206767 電子隔間140的一底部。安裝表面142具有一前通道146f 及一後通道146r。通道U6f與146r係凹設於安裝表面 142之下。排水口，例如通道146f中的滴流孔228s (如 圖1-3所示）’係延伸穿過機身1〇〇的侧壁11〇s。通道 146r中的滴流孔228b (如圖2與3所示）延伸穿過機身 1 00的底壁11 Ob。安裝表面142内的一傾斜的凹部229 將水排出安裝表面142外而進入通道146r。 圖3中所示實施例具有一開口 ι41，位於機身11〇的 側壁1.10s内，以暴露出一散熱器41 (圖〇，且允許釋 出由航空電子40 (圖1)所產生的熱。 圖3繪示圖1之水路兩用的無人飛行載具1〇的機身 100的一簡化側視圖。在此實施例中，選擇性滑行墊丄8 〇 與190係固定於機身1〇〇的底壁滑行塾180與190 在此實施例中係於降落在於堅硬表面。滑行墊丨8〇可位 於前隔間120的正下方，且可以具有足夠厚度與密度的 一耐久吸震材料來組裝，以進一步保護在隔間丨2〇内的 組件如電池2 0 (圖1 )的衝擊。類似地，滑行墊19 〇可 位於後隔間140的正下方’且可以具有足夠厚度與密度 的一耐久吸震材料來組裝，以進一步保護在隔間14〇内 的組件，例如航空電子40 (圖1 )。 滴流孔128s係延伸穿過機身1〇〇的側壁u〇s。滴流孔 128s延伸穿過側壁ii〇s並進入電池隔間12〇的後通道 126r。滴流孔228s延伸穿過側壁11〇s並進入中央負載隔 間130的外殼163。 201206767 流體排水埠、或類似物。201206767 The housing rod puts the load. In various embodiments, the load can include a camera assembly configured to pivot out of the housing by the opening in the bottom wall. In some embodiments) the flexible cable is a belt. The biasing element urges the load to a deployed position and the biasing element can include a spring. In various embodiments, the load is pivotally coupled to a front wall of the housing via a hinge. In some embodiments, the hinge can include a pivot rod and the biasing member includes a spring that is disposed about the yoke shaft. In various embodiments, the load further includes a camera assembly having a disc-shaped tray mounted to the housing, the disc-shaped tray being pivotally coupled to the housing via a hinge, the disc-shaped tray including the winch and a A disk actuator, while the disk actuator is located between the hinge and the winch. [Embodiment] Unmanned Aerial Vehicle for Waterway Dual Use Figure 1 shows a perspective schematic view of an unmanned aerial vehicle or UAV 1〇 for a waterway. The dual-purpose unmanned flying vehicle 10 has a fuselage 1〇〇 with modular compartments 12〇, 13〇 and 1牟〇 to accommodate modular components or modules, such as a battery module. 2 load module 30 and avionics module 40. In various embodiments 2, the wings 15 and/or 16 may be constructed from a plurality of parts that may be separate and/or "detachable" or separate from the fuselage 1 during landing. Figure 2 depicts a simplified top view of the fuselage 201206767 100 of the unmanned aerial vehicle of the dual-purpose waterway. The wall 11 of the fuselage 100 is made of a floatable material so that the fuselage 1 is placed on the full load component of the fuselage, as shown in Figure i, the battery 20, the load 30 and the avionics 4 and other non- The machine parts and components float when they are equipped with wings (not shown). For example, wall 110 may have a molded foam core sealed with a waterproof layer, although this is not essential. Wall 110 can be a single continuous wall or a plurality of wall segments' or the like. In this embodiment, the fuselage is divided into three compartments, a front battery compartment 120, a central load compartment 13A, and a rear avionics compartment 14A. The front battery compartment 120 is separated from the central load compartment 13 by a partition wall 15〇. The central load compartment 130 is separated from the rear avionics compartment 14 by a partition wall 160. In the illustrated embodiment, the lugs 1〇4, ι〇5, and 〇6 are used as a means for securing components (not shown) within the compartments 12, 130, and 140. The lug 105 can be manually rotated by a rotatable handle 1 〇 5h to mount a battery (not shown) and then rotated back to the position as shown to lock the battery within the front battery compartment 120. Other fixing mechanisms than the rotatable lugs 104, 105 and 106 can also be used. The battery compartment 120 has a mounting surface 122 that supports a battery (not shown). In this embodiment, a connector 124, which may be a surface mount connector or the like, is generally flush with the mounting surface 122. The passages 126f and 126r are recessed below the mounting surface 122. The drain opening, such as the drip hole 128b' in the passage 126f, extends through the bottom wall 丨丨〇b of the fuselage 1 。. The drip hole 128s (shown in Figures 1-3) extends through the side wall 1 〇s of the fuselage 100. 6 201206767 If the fuselage is exposed to the water surface, the joint surface 124m of the connector 124 is located above the passages 126f and 126r The bonding surface will not be immersed in the water when the battery is connected or separated. The wiring 12 and 123b can travel in the channels 126f and 126b, and can be embedded and/or embedded. The body 100 provides power to a motor (not shown), and an avionics module 40 and/or a load module 43. The central load compartment 130 has a front mounting surface 132f and a rear mounting surface 132r 'which supports a load , such as a camera component (not shown). The load module 30 can be packaged A phased, detected, or other passive, active, non-lethal, or iethal load device. In this embodiment, a connector 134 is flush with the mounting surface n2r. Flat, which may be a surface women's connector or the like. The mounting surface usr may form a housing 163 to accommodate the connector 134 and associated wiring. The housing may form a lower portion of the dividing wall 160. The drip hole 228s (as shown 3) can extend from within the outer casing 163 through the side wall n〇s, allowing water to drain out of the outer casing 163. In this embodiment, the central compartment 13A has a large opening 13 1 at the bottom, making it applicable. A camera, for example, is viewed downwardly or lowered into the airflow via the large opening 131. The large port 131 also allows fluid to be expelled from the central compartment 13A. In various embodiments, the engagement surface 134m of the connector 134 can be Positioned above the opening 131 above the top of the (four) 163, so that even if the fuselage is not completely exposed to the water surface 'when the load % (Fig. 1) is connected/separated, the joint surface will not be immersed in the water. Between 140 has an The mounting surface 142 is located at a bottom of the aviation 201206767 electronic compartment 140. The mounting surface 142 has a front channel 146f and a rear channel 146r. The channels U6f and 146r are recessed below the mounting surface 142. The drain port, such as the channel 146f The drip holes 228s (shown in Figures 1-3) extend through the side walls 11〇 of the fuselage 1〇〇. The drip holes 228b (shown in Figures 2 and 3) in the passage 146r extend through Pass through the bottom wall 11 Ob of the fuselage 100. An inclined recess 229 in the mounting surface 142 drains water out of the mounting surface 142 to enter the passage 146r. The embodiment shown in Figure 3 has an opening ι 41 located in the side wall 1.10s of the fuselage 11 to expose a heat sink 41 (Fig. 允许 and permitting the release of heat generated by the avionics 40 (Fig. 1) Figure 3 is a simplified side view of the fuselage 100 of the unmanned aerial vehicle of the waterway of Figure 1. In this embodiment, the selective sliding pads 8 and 190 are fixed to the body 1 The bottom wall slides 180 and 190 of the crucible are in this embodiment in a landing on a hard surface. The glide pad 8 can be located directly below the front compartment 120 and can be assembled with a durable shock absorbing material of sufficient thickness and density. To further protect the components in the compartment 〇2〇 such as the impact of the battery 20 (Fig. 1). Similarly, the gliding pad 19 〇 can be located directly below the rear compartment 140' and can have a sufficient thickness and density The durable shock absorbing material is assembled to further protect the components within the compartment 14 ,, such as avionics 40 (Fig. 1). The drip holes 128s extend through the side wall u〇s of the fuselage 1。. The drip holes 128s A rear channel 126r that extends through the side wall ii〇s and into the battery compartment 12〇. 11〇s extending through the sidewall 228s and into the load compartment between the central housing 130 163.201206767 fluid drain port, or the like.
線密封。 流體排水口可為滴流孔、流: 各種實施例提供一機身i 〇〇， 這使得飛行器的其他部分能保持漂浮，且當該UAV從 水中退出時，藉由一組流體排出埠，將任何飛行器内的 水排出。以此方式，電氣的與電子組件的保護即非依賴 於保持機身100或外壁 110的整體性，因機身1〇〇或外 壁110可能會在降落於堅硬及/或起伏地形（一般為降落 於地面）期間受損壞。 這今使得飛行器内需要進行防水的體積達到最小化， 從而減低整個系統的重量和複雜性。 再者’該飛行器能降落於堅硬表面或起伏地形而不損 壞電氣的與電子組件的能力，不僅是藉由將這些組件置 於模组化隔間120、130、及140内來達成，亦藉由允許 隔間120、130、及140的壁110能部分地變形而不致造 成UAV故障來達成。該壁110形成一衝擊區圍繞在隔間 120、130、及140内的電氣的與電子組件，且分隔板能 抑制組件20、30、及40相撞。可選擇地，在一些實施 例中，壁110與安裝座122、132f、132r、及142係為從 壁110及/或其相對的分隔板150與160 (圖2 )處嵌設 的組件20、30、及40 (圖1 )。額外的吸震材料（未圖 201206767 示）可加入至隔間120、130、或140内以更減少任何因 衝擊而損壞組件20、30、或40的機會。 如圖1與2所示，機身11〇可含有一選擇性的外通道 110c於機身11 〇的側面11 〇s，於航空電子隔間140的側 壁Π0上’從一孔218向後延伸至飛行器1〇的尾部。配 線203延伸通過孔2 1 8並沿著外通道11 Oc以將航空電子 組件40連接至一驅動器組件2〇2,用來致動在飛行器10 尾部的翼面（control surfaces)。外通道110c使得可以很 容易地接觸配線以進行檢查、維修和更換。 收放式照相機組件 (圖 4-7) 圖4繪示一負載模組3〇之一實施例的一簡化的剖開侧 視圖。參照圖1、3及4-7，提供一負載400的一回縮機 構410係用來將負載4〇〇從uav 1〇内的一停佇位置（如 圖6所示）’且因此從uav 10的機身100的底部1 i〇b， 移動至延伸至如圖4所示的負載模組3 0之外的一位置。 圖5繪示圖4的一負載模組30之一實施例的一簡化的剖 開側視圖，負載4〇〇係部分地收進殼體35内，而圖6繪 示圖4的一負載模組3 〇之一實施例的一簡化的剖開側視 圖’貪載係全部收進殼體35内。 負載4 0 0 了為一萬向盤，及如所示的傾斜照相機組件 405，其在延伸位置可在UAV 1〇下方並繞其而觀看。在 照相機組件405的收回或延伸期間，照相機組件4〇5繞 10 201206767 著一單一樞轉點/軸或鉸鏈420移動。照相機組件4〇5以 延著該殼體35之外的箭頭422d所示的調動的方向而移 動，及延著將負載400裝進殼體35内的箭頭422s所示 的方向而移動。在其他實施例中，鉸鏈42〇可具有多個 樞轉軸（未圖示）的多個樞轉點。 一般而言，在照相機組件405上的此鉸鏈42〇的另一 端係一絞盤430。絞盤430接著係直接地或間接地透過 一纜繩440連接於、連接至、或與殼體35之一壁35你 連接，例如與一鎖固件450,或其他對前壁35f的鎖定構 件，·以，使得透過操作絞盤430而能將照相機組件4〇5全 部收回於模組30的殼體35内。絞盤430係位於盤狀托 盤415内。 在於或圍繞於鉸鏈420的一偏壓元件，如一彈簧46〇， 係用来將負載400偏向朝其延伸位置的下方（如圖4所 示）。連接至照相機組件4〇5及/或殼體35的停止件、座 或限制器（未圖示）可用來限制該照相機組件在它的延 伸位置的運動。在一些實施例中，纜繩44〇可以其本身 或額外地與其他限制器，限制照相機組件405在它的延 伸的位置處的運動’並因此在該照相機完全延伸時處於 張力狀態"再者’在一些實施例中’當照相機組件 伸入氣流中時’彈簧460提供足夠的力量以保持照相機 組件405穩定。在其他實施例中，當其在延伸時若需要 的話’可使用—可致動的鎖固機構（未圖示）來固定該 照相機組件。 ~ 201206767 負載400可設置於UAV 1 0中，如此沿著UAV 10行進 fL. _ >— > ' 句會使照相機組件405繞鉸鏈420旋轉而進入該殼 〇 如. I回縮機構410故障的情況下，當其在降落而接觸 地面時’此配置將允許照相機組件405縮回至UAV 10 令’從而降低損及負載400的可能性與嚴重性。為利於 此目的’欽鍵420或其他樞軸構件係位於前方且靠近殼 體35的底部。因此，鉸鏈42〇可置於該殼體的前壁 35f使得鉸鏈樞軸桿795(圖7)的中心軸係垂直於UAV W運動的方向。 纜繩440的使用進一步提供了可靠的操作和環境的適 應能力，及重置的減輕。此處述及的用語窥绳，包括了 編織纜繩、帶狀纜繩、一皮帶、一帶子、一繩子、一鎖 鏈、或其他用來支撐張力或拉力的可撓構件。在一實施 例中；纜繩44〇可為一尼龍（NYL〇N)、克維拉纖維 (KEVLAR )、或其他材料的可靠的、重量輕的不易腐 鞋的帶子。 在此實施例中，鎖固件45〇可作為供照相機組件4〇5 的一停止件或座450p在此實施例中，當該照相機組件 如圖6所示全部縮回時，盤狀托盤415面向座450r而置 放。在其他實施例中，鎖固件45〇與座45〇r可為不同的 機構？ 圖7繪不照相機組件4〇5 #盤狀托& 4! 5之一實施例 的-剖開上視簡圖。盤狀托# 415包覆盤狀馬達組件 745，其係用來使照相機組件4〇5移動拍攝。絞盤馬達 12 201206767 735亦被包覆於盤狀托盤415中’並經由同樣包覆於盤 狀托盤415中的蝸輪755而耦接至絞盤滾筒785。絞盤 滾筒785係在盤狀托盤415之外部，並位於樞軸桿795 對面。 在此實施例中，殼體35的底部35b未密封，所以負載 模組30具有一開放式底部35b以利於負載4〇〇的調動。 因此，在此實施例中，盤狀托盤415及傾斜圓柱425係 個別地被密封。傾斜圓柱725 —般係包覆俯仰操縱電動 機組件（未圖示）及攝相的、偵測的、或其他被動的、 主動的、非致命的、或致命的負載裝置465與475。 值得注意的是任何參照「一個實施例」或「__實施例」 意指任何描述與該實施财關的—衫特徵、結構或特 性，必要時應包含於-實施例中。在本說明書不同處的 用詞「在-實施例中」，並非皆指相同實施例。 此處提供的圖式和例子係為說明之目的，而不是為了 用來限制所附的申請專利範圍。本揭示應視為本發明的 例證原則，所附實❹!並無意限制本發明的精神和範圍 及/或申請專利範圍。 該領域中的技術者可將本發明進行修改’以達到本發 明特定的應用。 本專利中所含的討論目的 者應知道，具體的討論可能 施例1且替代方案是隱含的 解釋本發明的一般性質，亦 疋作為—個基本的描述。讀 不會明破描述所有可行的實 。此外’此討論可能未完全 可能沒有明確說明每個功能 13 201206767 $件可如何破取代或等效置換。再者，這些概念是隱 含在本揭示中的。在本發明中介紹了裝置導向的用注： 軸元件的隱含地執行該裝置的—項功能。還應該了解 的疋’可作出各種變化而不偏離本發明的本質。這種變 化也隱含在此描述中。這些變化仍屬於本發明所要求保 護的範圍。 此外’本發明*申請專利範圍中的每一不同的元件亦 可以各種方式來實現。本揭示應理解為包括#個這樣的 變型，無論是任何裝置實施例、—方法實施例的變型， 甚至僅僅是任何這些元件的__個變化。特別是，應理解 的是與本發明元件相關的揭示’即使僅功能或結果相 同，其每個元件的用語可用等價的設備用語來表示。這 種等效，更廣泛，更通用的用語，甚至應該被認為是涵 蓋在描述每個元件或動作。這些用語可為了顯現本發明 所賦手的隱含的範圍的目的而被替代❶同樣地，每個所 揭示的物理元件應被理解為涵蓋物理元件利於達成的所 揭示的動作。這些變化和替代用語應被認為是此詳細說 明所明確揭示。 在描述了與本發明相關的數個實施例後，應對於該技 術領域者具有將其變化的建議。此處的例示實施例非用 於限制，而各種配置和特徵的組合均為可能的。因此， 本發明不僅限於所揭實施例，應以所附的申請專利範圍 為準。 201206767 【圖k簡單說明】 本發明的特徵與優點可藉由詳細說明、後附申請專利 範圍、及隨附的圖式而更易於理解，其中： 圖1繪示一水路兩用無人飛行載具的一透視簡圖。 圖2緣示圖！之水路兩用無人飛行載具的機身的一簡 化上視圖。 圖3繪示圖丨之水路兩用無人飛行载具的機身的一簡 化側視圖。 圖4繪示一負載模組之一實施例的一簡化的剖開側視 圖。 圖5 %示圖4的一負載模組之一實施例的一簡化的剖 開側視圖’該負載係部分地收進該殼體内。 圖6繪示圖4的一負載模組之一實施例的一簡化的剖 開侧視圖’該負載係全部收進該殼體内。 圖7繪示照相機組件的盤狀托盤之一實施例的一簡化 的剖開上視圖。 【主要元件符號說明】 10 無人機（UAV ) 15 翼部 16 翼部 20 電池模組 30 負載模組 35 殼體 35b 底部 15 104、. 105、106 105h 201206767 35f 3 5 w 40 100 110 110b 110c 110s 120 122 123b 123f 124 124m 126f 126r, 128b 128s 130 131 132f 132r 134 134m 140 141 142 前壁 壁 航空電子模組 機身 突耳 把手 壁 底壁 外通道 側壁 電池隔間 安裝座 配線 配線 連接器 接合表面 前通道 後通道Line seal. The fluid drain can be a drip hole, flow: various embodiments provide a fuselage i 〇〇 that allows other parts of the aircraft to remain floating, and when the UAV exits from the water, it is discharged by a set of fluids, The water in any aircraft is discharged. In this manner, the protection of the electrical and electronic components is independent of maintaining the integrity of the fuselage 100 or the outer wall 110, as the fuselage 1 or outer wall 110 may land on hard and/or undulating terrain (generally landing) Damaged during the ground). This now minimizes the volume of water that needs to be waterproofed within the aircraft, thereby reducing the weight and complexity of the overall system. Furthermore, the ability of the aircraft to land on hard surfaces or undulating terrain without damaging electrical and electronic components is achieved not only by placing these components in modular compartments 120, 130, and 140, but also by borrowing This is achieved by allowing the walls 110 of the compartments 120, 130, and 140 to be partially deformed without causing a UAV failure. The wall 110 defines an electrical and electronic component that surrounds the impact zones 20, 130, and 140, and the dividers inhibit the components 20, 30, and 40 from colliding. Alternatively, in some embodiments, wall 110 and mounts 122, 132f, 132r, and 142 are components 20 that are embedded from wall 110 and/or its opposing dividers 150 and 160 (FIG. 2). , 30, and 40 (Figure 1). Additional shock absorbing material (not shown in Fig. 201206767) can be added to the compartments 120, 130, or 140 to further reduce any chance of damaging the components 20, 30, or 40 due to impact. As shown in Figures 1 and 2, the fuselage 11A can include a selective outer channel 110c on the side 11 〇s of the fuselage 11 ,, extending rearwardly from a hole 218 to the side wall Π0 of the avionics compartment 140. The tail of the aircraft 1 。. Wiring line 203 extends through aperture 2 1 8 and along outer passage 11 Oc to connect avionics assembly 40 to a driver assembly 2〇2 for actuating the control surfaces at the tail of aircraft 10. The outer passage 110c makes it easy to contact the wiring for inspection, repair, and replacement. Retractable Camera Assembly (Fig. 4-7) Fig. 4 illustrates a simplified cutaway side view of one embodiment of a load module 3'. Referring to Figures 1, 3 and 4-7, a retracting mechanism 410 for providing a load 400 is used to load the load 4 from a parking position in the uav 1 (as shown in Figure 6) and thus from the uav The bottom 1 i〇b of the body 100 of 10 moves to a position that extends beyond the load module 30 as shown in FIG. 5 is a simplified cross-sectional side view of an embodiment of a load module 30 of FIG. 4, the load 4 is partially received into the housing 35, and FIG. 6 is a load mode of FIG. A simplified cut-away side view of one of the embodiments of the group 3 is carried out into the housing 35. The load 400 is a universal disk, and the tilt camera assembly 405 as shown, which can be viewed under and around the UAV 1〇 in the extended position. During retraction or extension of camera assembly 405, camera assembly 4〇5 moves about a single pivot point/shaft or hinge 420 around 10 201206767. The camera unit 4〇5 is moved in a direction in which the movement indicated by an arrow 422d outside the casing 35 is moved, and is moved in a direction indicated by an arrow 422s for loading the load 400 into the casing 35. In other embodiments, the hinge 42A can have a plurality of pivot points of a plurality of pivot axes (not shown). In general, the other end of the hinge 42'' on the camera assembly 405 is a winch 430. The winch 430 is then directly or indirectly connected to, connected to, or connected to a wall 35 of the housing 35 via a cable 440, such as with a locking member 450, or other locking member for the front wall 35f, The camera assembly 4〇5 can be fully retracted into the housing 35 of the module 30 by operating the winch 430. The winch 430 is located within the disc tray 415. A biasing element, such as a spring 46, in or around the hinge 420 is used to bias the load 400 below its extended position (as shown in Figure 4). A stop, seat or limiter (not shown) coupled to camera assembly 4〇5 and/or housing 35 can be used to limit movement of the camera assembly in its extended position. In some embodiments, the cable 44〇 may, by itself or additionally with other limiters, limit the movement of the camera assembly 405 at its extended position and thus be in tension when the camera is fully extended " In some embodiments 'the spring 460 provides sufficient force to keep the camera assembly 405 stable when the camera assembly is extended into the airflow. In other embodiments, the camera assembly can be secured by an actuatable locking mechanism (not shown) as needed when extended. ~ 201206767 The load 400 can be set in the UAV 1 0, so traveling along the UAV 10 fL. _ > - > 'sentence will cause the camera assembly 405 to rotate around the hinge 420 into the shell, such as. I retraction mechanism 410 failure In the event that this configuration will allow the camera assembly 405 to retract to the UAV 10 when it is landing to contact the ground, thereby reducing the likelihood and severity of damage to the load 400. To facilitate this purpose, the key 420 or other pivot member is located forward and near the bottom of the housing 35. Thus, the hinge 42A can be placed in the front wall 35f of the housing such that the central axis of the hinge pivot rod 795 (Fig. 7) is perpendicular to the direction of movement of the UAV W. The use of cable 440 further provides a reliable operational and environmental adaptability, as well as a reduction in reset. The term plucking rope as referred to herein includes a braided cable, a ribbon cable, a belt, a belt, a string, a chain, or other flexible member for supporting tension or tension. In one embodiment, the cable 44 can be a nylon (NYL® N), Kevlar, or other material that is a reliable, lightweight, non-corrosive shoe strap. In this embodiment, the fastener 45A can serve as a stop or seat 450p for the camera assembly 4〇5. In this embodiment, when the camera assembly is fully retracted as shown in FIG. 6, the disc tray 415 faces Place it on the 450r. In other embodiments, the lock 45 〇 and the seat 45 〇 r can be different mechanisms? Figure 7 is a cross-sectional elevational view of one embodiment of the camera assembly 4〇5#disk tray&4! The disc tray #415 covers the disc motor assembly 745, which is used to move the camera assembly 4〇5. The winch motor 12 201206767 735 is also wrapped in the disc tray 415' and coupled to the winch drum 785 via a worm gear 755 that is also wrapped in the disc tray 415. The winch drum 785 is external to the disc tray 415 and is located opposite the pivot rod 795. In this embodiment, the bottom 35b of the housing 35 is unsealed, so the load module 30 has an open bottom 35b to facilitate the transfer of the load. Therefore, in this embodiment, the disc tray 415 and the inclined cylinder 425 are individually sealed. Tilting cylinder 725 typically encloses a pitching motor assembly (not shown) and phased, detected, or other passive, active, non-fatal, or deadly load devices 465 and 475. It is to be noted that any reference to "an embodiment" or "__embodiment" means any feature, structure, or characteristic of the description and the implementation of the money, if necessary, included in the embodiment. The word "in the embodiment" in the different parts of the specification does not refer to the same embodiment. The drawings and examples are provided for illustrative purposes and are not intended to limit the scope of the appended claims. The present disclosure is to be considered as illustrative of the invention, and is not intended to limit the scope of the invention. The invention may be modified by those skilled in the art to achieve a particular application of the invention. The subject matter of the discussion contained in this patent should be understood that the specific discussion may be the embodiment 1 and the alternatives are implicit in explaining the general nature of the invention, and also as a basic description. Reading will not clearly describe all feasible facts. In addition, this discussion may not be entirely possible without clearly stating each function. 13 201206767 $ How can a piece be broken or equivalently replaced. Again, these concepts are implicit in this disclosure. In the present invention, a device-oriented note is described: The shaft element implicitly performs the function of the device. It should also be understood that various changes may be made without departing from the essence of the invention. This change is also implicit in this description. These variations are still within the scope of the claimed invention. Further, each of the different elements of the scope of the invention can be implemented in various ways. The present disclosure is to be understood to include any such variations, whether any device embodiments, variations of method embodiments, or even only __ variations of any of these elements. In particular, it is to be understood that the disclosure relating to the elements of the present invention, even if only the functions or results are the same, the terms of each of the elements may be represented by equivalent device terms. This equivalent, broader, and more general term should even be considered as covering each element or action. These terms may be substituted for the purpose of embodying the implicit scope of the invention, and each disclosed physical element should be understood to encompass the disclosed actions that are beneficial to the physical elements. These variations and alternative terms should be considered as clearly disclosed in this detailed description. After describing a number of embodiments relating to the present invention, there should be suggestions for those skilled in the art to change them. The illustrative embodiments herein are not intended to be limiting, and various configurations and combinations of features are possible. Therefore, the invention is not limited to the disclosed embodiments, but should be based on the scope of the appended claims. BRIEF DESCRIPTION OF THE DRAWINGS [0009] The features and advantages of the present invention are more readily understood by the detailed description, the appended claims, and the accompanying drawings, wherein: Figure 1 illustrates a waterway dual-purpose unmanned aerial vehicle A perspective sketch of the one. Figure 2 shows the picture! A simplified top view of the fuselage of the dual-purpose unmanned aerial vehicle. Figure 3 is a simplified side elevational view of the fuselage of the dual-purpose unmanned aerial vehicle of the waterway of the Figure. 4 is a simplified cross-sectional side view of one embodiment of a load module. Figure 5 is a simplified cutaway side view of one embodiment of a load module of Figure 4. The load is partially received within the housing. 6 is a simplified cross-sectional side view of one embodiment of a load module of FIG. 4. The load is fully received within the housing. Figure 7 is a simplified cutaway top plan view of one embodiment of a disc tray of a camera assembly. [Main component symbol description] 10 UAV 15 Wing 16 Wing 20 Battery module 30 Load module 35 Housing 35b Bottom 15 104, 105, 106 105h 201206767 35f 3 5 w 40 100 110 110b 110c 110s 120 122 123b 123f 124 124m 126f 126r, 128b 128s 130 131 132f 132r 134 134m 140 141 142 Front wall avionics module body lug handle wall bottom wall outer channel side wall battery compartment mount wiring wiring connector front surface Channel rear channel
滴流？L 滴流孔 負載隔間 大型開口 前安裝表面 後安裝表面 連接器 接合表面 航空電子隔間 開口 安裝座 16 201206767 146f 146r 150 、 160 163 180 . 190 202 203 218 22 8b' 228s 229 400 405 410 415 420 422d ' 422s 425 430 440 450 450r 460 465 、 475 735 745 .-. 755 前通道 後通道 分隔板 外殼 滑行墊 滑行墊 驅動器組件 配線 孔 滴流子匕 滴流孔 凹部 負載 照相機組件 回縮機構 盤狀托盤 欽鏈 箭頭 傾斜圓柱 絞盤 纜繩 固定件 座 彈簧 負載裝置 絞盤馬達 盤狀馬達組件 蜗輪 絞盤滚筒 17 785 201206767 樞軸桿 795 18 201206767 發明專利說明書 (本說明書格式、順序，請勿任意更動，※記號部分請勿填寫；惟已有申請案號者諳填寫） ※申請案號：100122918 ※申請日期：2011年6月29日 分類： (2006.0ί,, 一、 發明名稱：（中文/英文） $$t2006.0i,Drip? L drip hole load compartment large opening front mounting surface rear mounting surface connector joint surface avionics compartment opening mount 16 201206767 146f 146r 150 , 160 163 180 . 190 202 203 218 22 8b' 228s 229 400 405 410 415 420 422d ' 422s 425 430 440 450 450r 460 465 , 475 735 745 .-. 755 Front Channel Rear Channel Separator Shell Slide Pad Slide Pad Driver Assembly Wiring Hole Dropper Trickle Hole Concave Load Camera Assembly Retraction Mechanism Disk Tray Qinling arrow inclined cylindrical winch cable fixing seat spring load device winch motor disc motor assembly worm wheel winch roller 17 785 201206767 Pivot rod 795 18 201206767 Patent description (this manual format, order, please do not change, ※ mark part Please do not fill in; only the application number is filled in) ※Application number: 100122918 ※Application date: June 29, 2011 Classification: (2006.0ί,, I. Invention name: (Chinese / English) $$t2006 .0i,
無人機負載模組照相機組件和回縮機構 UAV PAYLOAD MODULE CAMERA ASSEMBLY AND RETRACTION MECHANISM Θ 二、 中文發明摘要： 在一個可行的實施例中，提出一無人機（UAV )負載 模組回縮機構，其包含一負載柩接於一殼體。一偏壓元 件係裝設用以將該負載偏向出該殼體外，及一絞盤係連 接至該負載。一伸長的可撓拉引元件係耦接在該殼體與 該絞盤之間，該伸長的可撓拉引元件能被該絞盤拉動， 以回縮該負載於該殼體内。 三、 英文發明摘要： 〇 .UAV load module camera assembly and retracting mechanism UAV PAYLOAD MODULE CAMERA ASSEMBLY AND RETRACTION MECHANISM Θ II. Abstract: In a possible embodiment, a UAV load module retracting mechanism is proposed, which comprises A load is coupled to a housing. A biasing element is mounted to bias the load out of the housing and a winch is coupled to the load. An elongated flexible pull-out element is coupled between the housing and the winch, and the elongated flexible pull-out element can be pulled by the winch to retract the load within the housing. Third, the English invention summary: 〇 .
In one possible embodiment, a UAV payload module retraction mechanism is provided including a payload pivotally attached to a housing. A biasing member is mounted to bias the payload out of the housing and a winch is attached to the payload. An elongated flexible drawing member is coupled between the housing and the winch, the elongated drawing flexible member being capable of being drawn by the winch to retract the payload within the housing. 201206767 七、申請專利範圍： 1. 一無人機負載模組回縮機構，包含： a) —負載模組殼體； b) 一負載，樞接至該殼體； c) —絞盤，連接至該負載； d) 一偏壓元件，係裝設用以將該負載偏向出該殼體 外；以及 e) 伸長的可撓拉引元件’耦接於該殼體與該絞盤之 門該伸長的可撓拉引元件能被該絞盤拉動，以回縮該負 載於該殼體内。 如咐求項1之機構，其中該偏壓元件包含一彈簧。 如响求項1之機構，其中該負載係枢接至該殼體内的一 前位置。 如睛求項3之機構， 其中該負載係樞接至該殼體的一前 5 ·如請求項j 該殼體。 之機構’其中該負載係經由 一绞鏈而樞接至 如請求項5之機構， 一收起位置。 其中該鉸鏈係在該負載的前方位於 19A biasing member is mounted to bias the payload out of the housing and a winch is attached to the payload. A elongated flexible drawing member is Between the housing and the winch, the elongated drawing flexible member being capable of being drawn by the winch to retract the payload within the housing. 201206767 VII. Patent application scope: 1. A UAV load module retracting mechanism, comprising: a) - a load module housing; b) a load pivotally connected to the housing; c) a winch connected to the load; d) a biasing element mounted to bias the load out of the housing And the e) elongated flexible pull element 'coupled to the housing and the door of the winch. The elongated flexible pull element can be pulled by the winch to retract the load in the housing. The mechanism of claim 1, wherein the biasing element comprises a spring. The mechanism of claim 1, wherein the load is pivotally coupled to a front position within the housing. The mechanism of claim 3, wherein the load is pivotally connected to a front portion of the housing. The mechanism 'where the load is pivoted to a mechanism as claimed in claim 5 via a hinge, a stowed position. Where the hinge is located in front of the load 19