公开(公告)号：US20030155463A1

公开(公告)日：2003-08-21

申请号：US10194814

申请日：2002-07-12

Applicant: MISSION TECHNOLOGIES, INC.

Inventor： Beverly Cox ,  Hampton Dews ,  Nicholas Nyroth

IPC: F41G007/00

CPC classification number: F41G3/02 ,  B64C39/024 ,  B64C2201/044 ,  B64C2201/102 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/185 ,  B64C2201/201 ,  B64C2201/203 ,  B64F1/06 ,  Y02T50/82

Abstract: An unmanned airborne reconnaissance system, the unmanned airborne reconnaissance system including a lightweight, portable, powered aircraft and a foldable launch rail, the aircraft, in a broken down condition and the launch rail in a broken down condition fitable inside a box, the box capable of being carried by one man. The launch system includes an elongated launch rail with the carriage assembly, and a propulsion means for accelerating the carriage assembly from one end of the launch rail to the other. The carriage assembly releasably engages the aircraft so as to propel the aircraft from one end of the launch rail to the other. The propulsion may be by a cartridge that explodes and releases a gas through a cylinder, or by elastic cords. The aircraft is guided through the air either by a programmed onboard computer which controls the control surfaces of the aircraft and/or by remote control. The aircraft typically contains a camera for recording and transmitting images received from the ground below.

Abstract translation: 一种无人机载侦察系统，无人机载侦察系统，包括轻型便携式动力飞机和折叠式发射轨道，该飞机处于分解状态，发射导轨处于可折叠状态的箱体内，该箱体能够 由一个男人携带。 发射系统包括具有滑架组件的细长的发射轨道和用于将滑架组件从发射轨道的一端加速到另一端的推进装置。 滑架组件可释放地接合飞行器，以便将飞机从发射轨的一端推动到另一端。 推进可以是通过气缸爆炸和释放气体的弹药筒或弹性帘线。 飞机通过编程的机载计算机被引导通过空中，控制飞机的控制面和/或通过遥控。 飞机通常包含用于记录和发射从下面接地的图像的照相机。

公开(公告)号：US20030089821A1

公开(公告)日：2003-05-15

申请号：US10323512

申请日：2002-12-18

Inventor： Carlos T. Miralles ,  Bart D. Hibbs

IPC: B64C003/56

CPC classification number: B64G1/222 ,  B64C1/30 ,  B64C3/56 ,  B64C39/024 ,  B64C2201/042 ,  B64C2201/082 ,  B64C2201/102 ,  B64C2201/126 ,  B64C2201/127 ,  B64C2201/128 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/148 ,  B64C2201/185 ,  B64C2201/203 ,  B64G1/105 ,  B64G1/62

Abstract: Disclosed is a spacecraft carrying a number of pods, each containing an aircraft that has been folded to fit in the pod. Each aircraft has a vertical stabilizer and outboard wing-portions that fold around fore-and-aft axes. Each aircraft also has a fuselage that folds around a lateral axis. The spacecraft releases one or more of the pods into an atmosphere. Each of the pods is configured with an ablative heat shield and parachutes to protect its aircraft when the pod descends through the atmosphere. The pod releases its aircraft at a desired altitude or location, and the aircraft unfolds while free-falling. The aircraft then acquires and follows a flight path, and activates scientific experiments and instruments that it carries. The aircraft relays results and readings from the experiments and instruments to the spacecraft, which in turn relays the results and readings to a mission command center.

公开(公告)号：US20030089820A1

公开(公告)日：2003-05-15

申请号：US10150726

申请日：2002-05-17

Inventor： Richard T. Martorana ,  Jamie Anderson ,  Simon Mark Spearing ,  Seth Kessler ,  Brent Appleby ,  Edward Bergmann ,  Sean George ,  Steven Jacobson ,  Donald Fyler ,  Mark Drela ,  Gregory Kirkos ,  William McFarland JR.

IPC: F42B015/01 ,  F42B015/10 ,  F42B015/20 ,  F42B015/22

CPC classification number: F42B15/105 ,  B64C39/024 ,  B64C2201/042 ,  B64C2201/084 ,  B64C2201/102 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/185 ,  B64C2201/201

Abstract: A flyer assembly is adapted for launching with, transit in, and deployment from an artillery shell having a central void region extending along a ballistic shell axis. The flyer assembly includes a jettisonable shroud and a flyer. The shroud extends along a shroud axis, and is positionable within the central void region with the shroud axis substantially parallel to the shell axis. The flyer is adapted to withstand a launch acceleration force along a flyer axis when in a first state, and to effect aerodynamic flight when in a second state. When in the first state, the flyer is positionable within the shroud with the flyer axis parallel to the shroud axis and the shell axis. The flyer includes a body member disposed about the flyer axis, and a foldable wing assembly mounted to the body member. The wing assembly is configurable in a folded state characterized by a plurality of nested wing segments when the flyer is in the first state. The wing assembly is configurable in an unfolded state characterized by a substantially uninterrupted aerodynamic surface when the flyer is in the second state. The flyer assembly is adapted to be launched from a ballistic delivery system such as an artillery cannon, and can thus reach a target quickly, without expending system energy stored within the flyer. During launch, the flyer is coupled to the shroud so as to maintain a portion of the flyer in tension during an acceleration of the flyer along the flyer axis resulting from the launch. The flyer assembly is adapted to withstand the high g-load and high temperature environments of a cannon launch, and can tolerate a set-back g load of about 16,000 g.

Abstract translation: 飞行器组件适用于从具有沿弹道壳轴线延伸的中心空隙区域的炮弹发射，转移和展开。 传单组件包括可喷射的护罩和传单​​。 护罩沿护罩轴线延伸，并且可定位在中心空隙区域内，护罩轴线基本上平行于外壳轴线。 飞行器适于在处于第一状态时承受沿飞行器轴的发射加速力，并且在处于第二状态时实现空气动力学飞行。 当处于第一状态时，传单可定位在护罩内，飞翼轴线平行于护罩轴线和外壳轴线。 传单包括围绕飞翼轴设置的主体部件和安装到主体部件的可折叠翼组件。 翼组件可配置成折叠状态，其特征在于当传单处于第一状态时由多个嵌套翼片段组成。 机翼组件可配置为展开状态，其特征在于当传单处于第二状态时基本上不间断的空气动力学表面。 飞行器组件适于从诸如炮兵炮的弹道传送系统发射，并且因此可以快速到达目标，而不会消耗存储在飞行物内的系统能量。 在发射期间，传单联接到护罩上，以便在飞行物沿着由发射引起的飞翼轴的加速期间，使传单的一部分保持张紧。 飞行器组件适于承受大炮发射的高负载和高温环境，并且可以容忍约16,000g的安装载荷。

公开(公告)号：US20030006340A1

公开(公告)日：2003-01-09

申请号：US10186665

申请日：2002-07-02

Applicant: BAE SYSTEMS plc

Inventor： Richard George Harrison ,  Terry Prendergast ,  Geoffrey Salkeld ,  Darren Holdcroft

IPC: B64C015/02 ,  B64C029/00

CPC classification number: B64C39/024 ,  B64C29/0075 ,  B64C2201/086 ,  B64C2201/088 ,  B64C2201/102 ,  B64C2201/104 ,  B64C2201/121 ,  B64C2201/127 ,  B64C2201/128 ,  B64C2201/165 ,  B64C2201/187

Abstract: An aircraft 1 comprising interchangeable wings 5 detachedly connected to a fuselage 3, each wing 5 containing the fuel and flight systems 13, 15 for engines 7 mounted to the wings 5, so that the fuselage 3 need contain no flight systems, simply a nullbusnull 23 for communication and the transfer of data between the wings.

Abstract translation: 飞机1包括分离地连接到机身3的可互换翼5，每个翼5包含用于安装到翼5上的发动机7的燃料和飞行系统13,15，使得机身3不需要包含飞行系统，简单地是“总线 “23”用于沟通和传递数据之间的翅膀。

公开(公告)号：US4659038A

公开(公告)日：1987-04-21

申请号：US657601

申请日：1984-10-04

Applicant: Hans-Jochen Hoeppner ,  Ulrich Kraemer ,  Michael Soelter

Inventor： Hans-Jochen Hoeppner ,  Ulrich Kraemer ,  Michael Soelter

IPC: B64C3/56 ,  B64C39/02 ,  F42B10/16

CPC classification number: B64C39/024 ,  B64C3/56 ,  F42B10/16 ,  B64C2201/046 ,  B64C2201/102 ,  B64C2201/165 ,  B64C2201/201

Abstract: The deployment of folded down wings in an aircraft following, for example, rocket assisted launching from the container is carried out through gas pressure springs with strong attenuation in the final phase, the springs being releasably coupled to the wings for being jettisoned upon completion of deployment.

Abstract translation: 在飞机后面展开折叠的机翼，例如从容器的火箭辅助发射通过在最后阶段具有强衰减的气体压力弹簧进行，弹簧可释放地联接到机翼，以在完成展开后被放弃 。