CN102596722B - 用于远程工作的无人驾驶航空飞行器的带有便携式rf透明发射管的抑制爆炸声的发射器的系统和设备 - Google Patents
用于远程工作的无人驾驶航空飞行器的带有便携式rf透明发射管的抑制爆炸声的发射器的系统和设备 Download PDFInfo
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F1/00—Ground or aircraft-carrier-deck installations
- B64F1/04—Launching or towing gear
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C13/00—Control systems or transmitting systems for actuating flying-control surfaces, lift-increasing flaps, air brakes, or spoilers
- B64C13/02—Initiating means
- B64C13/16—Initiating means actuated automatically, e.g. responsive to gust detectors
- B64C13/20—Initiating means actuated automatically, e.g. responsive to gust detectors using radiated signals
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
- B64C39/02—Aircraft not otherwise provided for characterised by special use
- B64C39/024—Aircraft not otherwise provided for characterised by special use of the remote controlled vehicle type, i.e. RPV
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F1/00—Ground or aircraft-carrier-deck installations
- B64F1/04—Launching or towing gear
- B64F1/06—Launching or towing gear using catapults
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U70/00—Launching, take-off or landing arrangements
- B64U70/50—Launching from storage containers, e.g. from submarine missile tubes
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U70/00—Launching, take-off or landing arrangements
- B64U70/70—Launching or landing using catapults, tracks or rails
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F41—WEAPONS
- F41A—FUNCTIONAL FEATURES OR DETAILS COMMON TO BOTH SMALLARMS AND ORDNANCE, e.g. CANNONS; MOUNTINGS FOR SMALLARMS OR ORDNANCE
- F41A21/00—Barrels; Gun tubes; Muzzle attachments; Barrel mounting means
- F41A21/02—Composite barrels, i.e. barrels having multiple layers, e.g. of different materials
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F41—WEAPONS
- F41F—APPARATUS FOR LAUNCHING PROJECTILES OR MISSILES FROM BARRELS, e.g. CANNONS; LAUNCHERS FOR ROCKETS OR TORPEDOES; HARPOON GUNS
- F41F1/00—Launching apparatus for projecting projectiles or missiles from barrels, e.g. cannons; Harpoon guns
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F41—WEAPONS
- F41F—APPARATUS FOR LAUNCHING PROJECTILES OR MISSILES FROM BARRELS, e.g. CANNONS; LAUNCHERS FOR ROCKETS OR TORPEDOES; HARPOON GUNS
- F41F3/00—Rocket or torpedo launchers
- F41F3/04—Rocket or torpedo launchers for rockets
- F41F3/042—Rocket or torpedo launchers for rockets the launching apparatus being used also as a transport container for the rocket
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B39/00—Packaging or storage of ammunition or explosive charges; Safety features thereof; Cartridge belts or bags
- F42B39/14—Explosion or fire protection arrangements on packages or ammunition
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/25—Fixed-wing aircraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U2201/00—UAVs characterised by their flight controls
- B64U2201/20—Remote controls
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U30/00—Means for producing lift; Empennages; Arrangements thereof
- B64U30/10—Wings
- B64U30/12—Variable or detachable wings, e.g. wings with adjustable sweep
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U70/00—Launching, take-off or landing arrangements
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U80/00—Transport or storage specially adapted for UAVs
- B64U80/70—Transport or storage specially adapted for UAVs in containers
Abstract
一种无人驾驶的航空飞行器(UAV)发射管(100)包括:围绕一个正平行六面体的开口(305)布置的至少一个预浸渍基片的内层(370)、围绕该正平行六面体的开口(305)布置的至少一个预浸渍基片的外层(380)、以及在该至少一个预浸渍基片的内层(340)与该至少一个预浸渍基片的外层(380)之间布置的一个或多个结构板(341?344)。一种无人驾驶的航空飞行器(UAV)发射管(100)包括一个栓系的弹底板(700,740),该弹底板被配置成与由一个内壁限定的发射器体积内的一个UAV相接合,该栓系的弹底板(700,740)的尺寸被确定为在内壁处提供一种压力密封并且被栓系到该内壁上,并且其中该栓系的弹底板(700,740)是空心的而具有一个指向高压体积的开放端以及一个系绳(740),该系绳被附接在该弹底板(700)的空心体(910)之内并且被附接到保持该高压体积的内壁上或附接到基部内壁(1013)上。一种系统包括一个通信节点(1500?1505)以及一个发射器(1520),该发射器包含一个无人驾驶的航空飞行器(UAV),这种航空飞行器在发射前状态的中被配置成接受并且响应于来该通信节点(1500?1505)的命令输入。
Description
本申请要求以下专利申请的优选权和权益:于2009年9月9日提交的美国临时专利申请序列号61/240,996、于2009年9月9日提交的美国临时专利申请序列号61/240,987、以及于2009年9月9日提交的美国临时专利申请序列号61/241,001,为了所有目的,所有这些申请都以其全文通过引用的方式结合在此。
技术领域
多个实施方案包括用于无人驾驶的航空飞行器(UAV)的发射管和罐、抑制爆炸声的(report-suppressing)发射管、以及弹底板。实施方案还涉及包括一个或多个UAV的系统,并且涉及一个系统,该系统包括一个命令节点以及容纳了一个处于预发射状态的UAV的一个发射器,处于预发射状态的该UAV被配置成接收来自该命令节点的命令信号。
背景
典型地UAV是以一个未组装的状态运送到一个发射现场的。在现场它们被组装、测试、并且然后发射。发射典型地是通过手、通过一个弹性系绳、一个有动力的绞盘(从一个移动的运载工具)或者它们的一些组合来执行的。此类方法会是耗时的和/或麻烦的。一旦发射,一个UAV可以接收上行链路传输并且可以通过在环路中的一个人(一个间歇地上行链路传输过程校正的人)例如,通过监控来制导,或者通过与一个机载的飞行路径制导发生器以及惯性传感器的输出和/或来自一个全球定位系统(GPS)接收器的输出相组合的一个预装入的拦截/攻击点来制导。
披露内容
实施方案可包括多种物品,如一个无人驾驶的航空飞行器(UAV)发射管,包括:(a)围绕一个正平行六面体的开口布置的至少一个预浸渍基片的内层;(b)围绕该正平行六面体的开口布置的至少一个预浸渍基片的外层;以及(c)在该至少一个预浸渍基片的内层与该至少一个预浸渍基片的外层之间布置的一个或多个结构板。该至少一个预浸渍基片的内层可以包括环氧预浸渍材料KevlarTM或其他轻重量的复合材料。该至少一个预浸渍基片的外层可以包括环氧预浸渍材料KevlarTM或其他轻重量的复合材料。该一个或多个结构板可以包括轻木或者一种轻型复合材料。在某些实施方案中,该一个或多个结构板可以包括四个结构板,其中每个板包括一个圆柱形的区段,并且每个板具有一个由一个弦长和一个圆柱形的高度所限定的平面的表面。每个近似平面的板可以相对于彼此正交地进行布置,每个结构板具有一个第一侧向边缘以及与该弦长相垂直的一个第二侧向边缘,其中一个第一结构板的第一侧向边缘是接近于但不接触一个第二结构板的一个第一侧向边缘。该第一结构板的第二侧向边缘可以接近于但不接触一个第三结构板的一个第一侧向边缘。一个第四结构板的第一侧向边缘可以接近于但不接触一个第二结构板的一个第二侧向边缘。该第四结构板的第二侧向边缘可以接近但不接触一个第三结构板的一个第二侧向边缘,其中这四个结构板的每一个的这些平面的表面可以是与一个发射管的中心线相对齐。此外,这四个结构板中的每一个都可以被布置在该环氧预浸渍基片的内层与该环氧预浸渍基片的外层之间。实施方案包括多个物品,如一种无人驾驶的航空飞行器(UAV)发射管,该发射管被配置用于抑制爆炸声,包括被配置成与由一个内壁限定的发射器体积内的UAV相接合的一个结构元件。该物品可以被确定尺寸为在内壁处提供一种压力密封件并且被栓系到该内壁上。该结构元件可以具有一个空心体、或空腔,具有指向一个高压体积的一个开放端以及一个系绳,该系绳被附接在该物品的空心体或空腔之内的并且被附接到保持该高压体积的内壁上。
另外的实施方案可以包括多种方法以及UAV系统,包括:(a)一个通信节点;以及(b)一个包括UAV的发射器,该UAV被配置成在一种预发射的状态下接收来自该通信节点的命令输入。在某些实施方案中,处于预发射状态的UAV进一步被配置成将响应于一个接收的查询信号向一个通信节点发送UAV状态数据。在某些实施方案中,该UAV的RF天线包含在该发射器体积之内。在某些实施方案中,该发射推进系统被配置成接收RF信号。
附图简要说明
在附图中通过举例而非限制的方式展示了多个实施方式,并且在附图中:
图1是一个示例性发射管实施方案的顶侧透视图;
图2是一个示例性发射管实施方案的一部分的底侧透视图;
图3是一个示例性发射管实施方案的截面视图;
图4是本发明的被配置成一个UAV携带箱实施方案的一个发射管的示例性描绘;
图5是本发明的被配置成一个UAV携带箱实施方案的一个发射管的示例性描绘;
图6是被配置成一个UAV携带箱实施方案的发射管的带有多个支持支撑件以及展开的基脚的一个示例性描绘;
图7是本发明的一个示例性栓系的弹底板(tethered sabot)的实施方案的顶侧透视图;
图8是本发明的一个示例性栓系的弹底板的实施方案的俯视图;
图9是本发明的一个示例性栓系的弹底板的实施方案的截面视图;
图10A到10E描绘一个使用本发明的栓系的弹底板实施方案的示例性UAV发射;并且
图11A到11B以发射管的远端的截面视图描绘了使用本发明的栓系的弹底板实施方案的一个示例性UAV发射。
图12A是处于预发射状态下的一个示例性UAV的底侧透视图;
图12B描绘了一个示例性UAV,其中其翼面被展开并且其推动器推进器正在旋转;
图13是一个示例性发射管的实施方案的一部分的底侧透视图;
图14描绘UAV处理和制导以及控制系统的示例性功能框图;并且
图15是一个系统实施方案的顶层系统架构。
最佳模式
图1是一个示例性发射管100的实施方案的顶侧透视图。该示例性发射管的顶部或开放端110呈现一种方形具有圆角的开口。在预浸渍基片120的外层与预浸渍基片130之间布置的是四个结构板141-144。
图2是一个示例性发射管的实施方案200的一部分的底侧透视图。该示例性发射管的底部或封闭端210呈现为围绕一个轴线弯曲的一个末端220,这个轴线与一个第一基脚枢轴点凸出部230共线,其中一个第二基脚枢轴点凸出部与该第一基脚枢轴点凸出部230相反,但在图中未示出。
图3是图1的示例性发射管的实施方案的截面视图300,示出了围绕一个发射管中心线布置的四个结构板141-144。这样的一个体积可放置一个非圆柱形的UAV并且被从中发射。每个板被示出具有一个外表面曲率311,该外表面曲率311以一个曲率半径322为代表,该曲率半径322大于从外表面350到发射管中心线360的距离323。每个板141-144被示出具有一个平的内表面312,该平的内表面代表了弦长313。相应地,在本截面视图中每个板141-144的端面314是一个圆形的区段。每个板被示出为布置在预浸渍基片的内层370与预浸渍基片的外层380之间。这些板被示出彼此分开布置,在这些板的侧向边缘318、319之间存在一个空间390。相应地,预浸渍基片的内层370和该预浸渍基片的外层380彼此在正平行六面体的形状的体积305的这些拐角301-304处相接触。预浸渍基片的外层380在截面视图中限定了一个基本上卵形体形状的外周长。在某些实施方案中,该内层370和外层380可以包括环氧预浸渍材料KevlarTM或一种复合材料、或两者的组合,并且这些结构板可以包括轻木或者一种轻重量的复合材料、或两者的组合。
图4是被配置成一个UAV携带箱400实施方案的一个发射管的示例性描绘。一个基脚410被示出通过一个基脚枢轴点凸出部230可转动地附接到该发射管405上。一个第一支撑件或支腿420被示出在该发射管的顶部110的附近被可转动地附接到该发射管405上。一个第二支撑件或支腿是与该第一支撑件相反地进行布置的,并且在这个图中未被示出。一个帽430被示出覆盖了该发射管的在其他情况下开放的末端,并且被示出由一个环外周的束带431来限制。
图5是被配置成一个UAV携带箱实施方案的一个发射管处于一个部分被展开状态下的示例性描绘。即,帽430被示出为移开的从而暴露出该发射管的开放端,该发射管可以如所示的具有一个可任选的隔膜密封件540。该密封件540可以是一个易碎的薄膜,该薄膜被用于抵御砂子、泥土、湿气、和/或砂砾在预发射准备的过程中进入到该发射管中。基脚410被示出为部分地旋转远离该发射管,并且该第一支撑件或支腿420被示出为部分地旋转进入一个支持位置中。
图6是被配置成一个UAV携带箱实施方案的一个发射管600带有多个支持支撑件420以及展开的基脚410的示例性描绘。如此使用的术语“管”旨在表示一个UAV可以从其中发射的体积而非旨在将该体积的形状限制为一个圆柱形的管。这对支撑件或支腿的角度610可以被调整为适应与现场水平602相关的一个希望的发射角601。同样地,在该发射管与该基脚之间的角度620可以被调整为适应这个希望的发射角601。在一些实施方案中,这对支撑件或这对支腿420可以包括不同直径的多个区段,从而允许远端区段422缩入近端区段421和从其中拉出。在这些实施方案中,这些支腿的总长度可以调整为适应不平坦的现场地形和适应一个希望的发射角601之一,或两者。基脚410的尺寸可以被确定为接收来自一个靴子和/或一个质量的下压力以便进一步提高在该基脚的下表面与现场地面602之间的静摩擦。发射管630的顶部可以包括一个易碎的隔膜以便保护内部的发射器体积免受砂砾、砂子、湿气以及气候的影响。一旦该发射器被定位在一个表面上,该发射器600可以被遥控而用于在该UAV处于预发射状态时将任务信息上载到UAV的目的,并且用于接收UAV状态信息的目的。
多个实施方案包括一个无人驾驶的航空飞行器(UAV)发射管,该发射管可以包括一个栓系的弹底板,该栓系的弹底板被配置成在由一个内壁限定的一个发射器体积内接合一个UAV,该栓系的弹底板被确定尺寸为在该内壁处提供压力密封并且被栓系到该内壁上。在某些实施方案中,这个拴系的弹底板可以是空心的、具有朝向一个高压体积而定向的一个开放端以及一个系绳,该系绳被附接在该弹底板的空心体之内并且被附接到维持该高压体积的内壁上。
对于具有一个正平行六面体开口的发射器,可以使用如图7中所描绘的一个示例性栓系的弹底板700实施方案。该弹底板可以由碳纤维制成,例如,以一种形式成形并且被加工为产生一端是开放的一个空心物品的一种预浸渍材料碳纤维。该弹底板可以具有用于接收一个UAV的推动器推进器组件的一个通道710。该弹底板还可以具有用于接收在该空心体所提供的体积外侧的气体的一个凹陷720。该弹底板被示出为描绘了一个结构元件的末端部分730,这个结构元件可以横跨该弹底板的宽度以便提供用于系绳的一个结构附件。系绳740的一个部分被显示从该弹底板的空心体中开始延伸。
图8是一个示例性栓系的弹底板700实施方案的俯视图。该结构元件810可以是一个棒,并且可以横跨该弹底板700的宽度。该系绳的圈环部分820可以与该结构元件810接合。该系绳740可以是有机硅预浸渍材料编结的KevlarTM,其中该系绳740的一个末端可以在圈绕该结构元件810之后被卷进该栓系740的编结之内并且进一步被加工。
图9是从图8的俯视图中截取的弹底板700的截面视图,描绘了该系绳740与该弹底板700的空心体910内的结构元件810相接合。
图10A展示了一个装载的发射器1010的截面视图,如在图1和图2中描述的发射器;装载有一个UAV 1020(如在图3中描绘的UAV)。在这个实例中,发射器1010被示出具有一个可任选的易碎的密封件1030。两个气体发生罐1041、1042被示出为布置在该发射器1010的后部体积1001之内。一个示例性拴系的弹底板1050被示出为布置在该气体发生罐1041、1042与该UAV 1020之间。
图10B以图10A的截面视图展示了一个第一气体发生罐1041增加发射器1010的后部内壁1011与该弹底板1050之间的体积1001之内的压力,如烟云1002所描绘的。系绳1060可以通过一个栓系卷或者缠绕元件1014来附接到基部内壁1013上。相对于图10A,弹底板1050被示出沿着该发射管(在这个实例中是一个正平行六面体的体积)移位并且使得UAV 1020与其一起移动。该UAV被示出正在破坏该易碎的密封件1030并且正开始离开该发射器1010。
图10C以图10A的截面视图展示了第二气体发生罐1042增加或保持发射器1010的后部内壁1012与该弹底板1050之间的体积之内的压力(如第二烟云1003所描绘的)。弹底板1050被示出为沿着该发射管进一步移位,该系绳1060被示出为处于一个放出的长度并且与弹底板1050一起被移动,该UAV 1020被示出为基本上在该发射器外。
图10D以图10A的截面视图展示了,该弹底板1050在该发射管内被完全移位,被系绳1060束缚而不能进一步行进,并且将气体保持在该发射器体积之内。
图10E以图10A的截面视图展示了,该弹底板1050在该发射管内被完全移位,被系绳1060束缚而不能进一步行进,并且将气体保持在该发射器体积之内并且允许气体从该发射器体积中渗出1090进入周围大气中。
图11A描绘了,在弹底板1050接近完全放出时(如在图10D所描绘的),一个发射管1100的远端(未密封的)的一个截面视图。在某些使用热的或温的气体发生器的实施方案中,该弹底板1050行进大致不会远于图11A中所描绘的位置,并且由于该弹底板可以在已经被气体加热之后的一个冷却周期中收缩所以气体到大气的渗出是在该弹底板的周围。在某些使用热的或冷的气体发生器的实施方案中,该弹底板1050可以行进到从该发射器的边缘1120部分地伸出(图11B),其中一旦该弹底板唇缘701已经越过该发射器边缘1120,气体1110就可以从该侧凹陷720渗出。通过由系绳1060来保持弹底板1050,该发射器将一个实质性部分的压力波(即,由快速的气体产生而引起的爆炸声和热量)保留了一个短暂的时间段。发射后,该发射器通过围绕该弹底板1050的渗出而将压力从该发射器中扩散。
在一些实施方案中,因为由来自气体发生器的气体施加在弹底板1050的内部上的压力,该弹底板1050可以膨胀出来而接触该发射器的这个内壁或这些内壁。这种膨胀可以引起或者至少协助在该弹底板1050与这个内壁或这些内壁之间形成密封,并且这样做防止或限制了在该弹底板1050沿着管移动的过程中气体在该弹底板周围的通过。在某些实施方案中,该弹底板可以被配置成在该弹底板与该发射器的这个内壁或这些内壁之间的形成多个空隙。这些空隙的尺寸可以被设定为提供一个希望量值的气体泄漏。在一些实施方案中,该弹底板1050可以被确定尺寸为允许足够的气体泄漏以便防止发射器由容纳这些发射气体而变得过热,而这种变得过热使得该发射器的结构完整性被折损或破坏。相应地,弹底板1050的多个实施方案可以被确定尺寸为限制气体泄漏以便限制在发射的过程中产生的声波的声音传播。
图12A以一个底侧透视图描绘了处于预发射状态的一个示例性UAV 1200,即,它的多个机翼面1210以及尾翼面1220被折叠在该飞行器的机身之下。还示出的是一个推进器毂1230,一个推进器可以围绕该推进器毂可转动地进行安装。该航空飞行器可以包括一个与该飞行器形状相符的或者从其上延伸的射频(RF)天线1231。无论该管体积是否是一个正圆柱体、一个正平行六面体、或者一些其他形状,该UAV的这个截面或这些截面都可能不足以在该飞行器与该发射器的这些内壁之间保持一种气密配合。因此,对于基于气体压力的发射而言,可以在该气体源与该UAV之间布置一个弹底板。图12B描绘了一个处于已发射状态的示例性的UAV 1201,其中其翼面1210、1220是展开的并且其推动器推进器1232正在旋转。
图13是装载进入一个发射器1310的前面部分中的航空飞行器1300实施方案的一个侧正视图。该发射器1320的后部部分被示出具有一对气体发生罐1331、1332并且可以包括一个RF天线1333和接收器单元1334、以及一个动力源1336(如用于为该发射器提供动力的电池)。在某些实施方案中,该动力源1336还可以在UAV 1300处于发射器1310中时为该UAV提供动力,从而允许了该UAV的电池在离开发射器1310之后的最大的电池寿命。轻木和环氧预浸渍材料KelvarTM是具有高RF透过性的结构元件的实例。相应地,UAV的RF天线和接收器元件和/或发射推进单元的RF天线和接收器元件可以接收来自一个命令节点的RF命令并且由于发射器的结构引起的信号衰减是可忽略的。
图14描绘了UAV处理以及制导和控制子系统1400的示例性功能框图,其中,制导传感器1414提供涉及寻的器(seeker)处理1420的寻的处理的有关外部环境信息。一个制导传感器1414,且更加总体上的一个制导传感器套件,可包括被动和/或主动雷达子系统、红外检测子系统、红外成像子系统、可见光成像子系统(如基于视频照相机的子系统)、紫外线检测子系统、以及它们的多种组合。寻的器处理1420可以包括图像处理和目标跟踪处理二者、以及目标指定或再指定输入1421,这种目标指定或重新指定的输入可从上行链路接收器1435接收和/或作为制导处理1430的输出来接收。图像处理和/或目标跟踪信息1422可以通过下行链路发送器1423来发送,该下行链路发送器可以是一个上行链路/下行链路收发器的一部分。在执行用于制导处理的指令时,制导处理器1430可以接受来自寻的器处理1420的目标信息1424、以及来自GPS接收器1431和多个陀螺仪以及加速度计1432(如果有的话)的UAV飞行状态信息,例如,位置、速度、以及姿态。一旦处于飞行中,制导处理器1430为接收多个侦查航路点(reconnaissance waypoints)和/或搜索优化轨迹(surveillance optimizing trajectories)而可以参照存储器1433。对于多个系统的实施方案,制导处理1430可以通过一个外部数据端口1434(例如在预发射的阶段过程中)或通过上行链路接收器1435(例如在发射后的阶段过程中)来接收和/或上传侦查航路点和/或搜索优化轨迹。制导处理器1430,作为执行指令以确定飞行路径、轨迹或航路操纵角度(course steering angle)和方向的部分,可以参照这种航路点和/或搜索优化轨迹信息,尤其是在不处于末段自导引模式时。该制导处理器1430可以通过一个上行链路接收器1435来接收一个命令以便设定一个初始的发射后模式或飞行计划。该上行链路接收器1435可以在该UAV处于预发射状态下时接收来自一个通信节点的命令、目标数据、和或飞行计划信息。
末段自导引模式的一个实例可以是比例式导航,这种比例式导航带有用于末段自导引模式的攻击子模式的重力偏置(gravity bias)以及用于末段自导引模式的空中拦截子模式的加速度偏置(acceleration bias)。制导处理1430和自动驾驶处理1440可以执行指令以在例如升降副翼实施方案中实现侧滚转弯引导(bank-to-turn guidance),以通过重新定向航空飞行器的速度向量来使航空飞行器改变方向。例如,一个或多个控制表面可以通过一个或多个控制表面致动器1450而被重新定向,这个或这些控制表面致动器产生力和力矩以重新定向航空飞行器及其线性加速度中正交于其速度向量的部分。航空飞行器的线性加速度沿着速度向量的部分受到空气动力学阻力的极大影响,并且线性加速度可通过马达处理器1460和推进器马达1470而增加。对于具有完整的三轴线控制的实施方案而言,可以实施额外的控制型态,包括侧滑转弯(skid-to-turn)以及其他比例-积分-微分制导和控制处理架构。寻的器处理1420、制导处理1430、马达处理1460、和/或自动驾驶处理1440可由具有可寻址存储器的单个微处理器来执行,和/或该处理可以例如通过数据总线来分配给处于分布式通信中的两个或多个微处理器。
图15是一个系统1500实施方案的顶层系统架构。地面运载工具1501,航空器1502,太空飞行器1503,机载搜索或机载通信节点1504,或地面的、单兵携带的通信节点1505可以通过一个RF链路1511-1515将命令信号发送给一个发射器1520实施方案,该发射器实施方案可以是例如在图13中描绘的实施方案。在某些实施方案中,处于预发射状态的UAV可以沿一个RF链路1511-1515将状态信息,例如电池水平以及自诊断的结果,输出到一个请求的节点1501-1505。发射器实施方案通过容纳在该发射器中的UAV提供了一个自备的RF节点。例如,该UAV可以被置于一种备用的模式中,并且保持对接收到的RF信号的做出响应,这个信号可以命令完全通电,并且此后,在该发射器中的UAV可以准备好以便(例如)通过一个非现场的命令节点的RF命令来执行发射。这种整备发射器-UAV可以被展开并且置留于一个预期的发射场地持续一个延长的时间段,并且此后可以响应于一个或多个来自一个非现场的或另外的远程命令节点的命令信号而通电并且发射。
考虑到可以对以上实施方案的特定特征和方面作出不同组合和/或子组合并且仍然落在本发明的范围之内。因此,应理解,所披露的实施方案的不同特征和方面可以彼此组合或互相替换,以便形成所披露的本发明的变化模式。此外,在此通过举例方式披露的本发明的范围旨在不应受上述具体披露的实施方式的限制。
Claims (6)
1.一种无人驾驶的航空飞行器(UAV)发射管,该发射管包括:
围绕一个正平行六面体的开口布置的至少一个预浸渍基片的内层;
围绕该正平行六面体的开口布置的至少一个预浸渍基片的外层;以及
在该至少一个预浸渍基片的内层与该至少一个预浸渍基片的外层之间布置的四个结构板;
其中每个结构板包括一个圆柱形的区段,每个结构板具有由一个圆柱形截面的弦长和一个圆柱形的轴向高度限定的一个平面的内表面,并且每个结构板具有一个外表面曲率,该外表面曲率以一个曲率半径为代表,该曲率半径大于从该结构板的外表面到正平行六面体的开口中心线的距离,并且
其中该四个结构板彼此分开布置,每个结构板具有一个第一侧向边缘以及一个第二侧向边缘,在该四个结构板的相邻的侧向边缘之间存在空间,并且该至少一个预浸渍基片的内层和该至少一个预浸渍基片的外层彼此在这些空间处相接触。
2.如权利要求1所述的UAV发射管,其中该至少一个预浸渍基片的内层包括环氧预浸渍材料KevlarTM。
3.如权利要求1所述的UAV发射管,其中该至少一个预浸渍基片的外层包括环氧预浸渍材料KevlarTM。
4.如权利要求1所述的UAV发射管,其中该结构板包括轻木。
5.如权利要求1所述的UAV发射管,其中每个平面的表面相对于下一个平面的表面正交地进行布置,其中一个第一结构板的第一侧向边缘邻近但不接触一个第二结构板的一个第一侧向边缘,该第一结构板的第二侧向边缘接近但不接触一个第三结构板的一个第一侧向边缘,并且其中一个第四结构板的第一侧向边缘接近但不接触一个第二结构板的第二侧向边缘,该第四结构板的第二侧向边缘接近但不接触一个第三结构板的一个第二侧向边缘。
6.如权利要求1所述的UAV发射管,进一步包括:
一个内壁,该内壁是由该至少一个预浸渍基片的内层形成的;
以及一个栓系的弹底板,该栓系的弹底板被配置成与该正平行六面体的开口内的一个UAV相接合,该栓系的弹底板被确定尺寸为在该内壁处提供一种压力密封并且被栓系到该内壁上。
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