公开(公告)号：US20050274845A1

公开(公告)日：2005-12-15

申请号：US10509659

申请日：2004-02-19

Applicant: Stephen Miller ,  Matthew Velazquez

Inventor： Stephen Miller ,  Matthew Velazquez

IPC: B64B20060101 ,  B64B1/00 ,  B64C3/56 ,  B64C39/02 ,  B64F1/04 ,  B64F1/06

CPC classification number: B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/084 ,  B64C2201/102 ,  B64C2201/165 ,  B64C2201/201 ,  B64C2201/203 ,  B64F1/06

Abstract: A portable unmanned air vehicle and launcher system is provided that includes a foldable unmanned air vehicle having a pressure tube; a launch gas reservoir for holding launch gas; a launch tube operatively connected to the launch gas reservoir and having a free end that is positioned in the pressure tube of the air vehicle; a free piston positioned within the launch tube; and a free piston stop to prevent the free piston from leaving the launch tube. A first portion of the launch gas in the launch gas reservoir is released into the launch tube and forces the free piston from an initial position to an end position at which the free piston is stopped by the free piston stop.

Abstract translation: 提供了一种便携式无人驾驶飞行器和发射系统，其包括具有压力管的可折叠无人驾驶飞行器; 用于发射气体的发射气藏; 操作地连接到发射气体储存器并具有位于空中载体的压力管中的自由端的发射管; 位于发射管内的自由活塞; 和自由活塞止挡件，以防止自由活塞离开发射管。 发射气体储存器中的发射气体的第一部分被释放到发射管中，并且将自由活塞从初始位置推动到自由活塞由自由活塞停止的终止位置。

公开(公告)号：US20050230536A1

公开(公告)日：2005-10-20

申请号：US10758943

申请日：2004-01-16

Applicant: Brian Dennis ,  Clifford Jackson ,  Brian McGeer

Inventor： Brian Dennis ,  Clifford Jackson ,  Brian McGeer

IPC: B64C39/02 ,  B64F1/02 ,  B64F1/06

CPC classification number: B64C39/024 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/048 ,  B64C2201/084 ,  B64C2201/102 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/182 ,  B64C2201/201 ,  B64C2201/205 ,  B64F1/06

Abstract: Methods and apparatuses for capturing, recovering, disassembling, and storing unmanned aircraft and other flight devices or projectiles are described. In one embodiment, the boom can be extended to deploy a recovery line to capture the aircraft in flight, a process that can be aided by a line capture device having retainers in accordance with further aspects of the invention. The aircraft can then be returned to its launch platform, disassembled, and stored, again with little or no direct manual contact between the operator and the aircraft, for example, by capturing a first wing of the aircraft and securing a second wing before releasing the first.

Abstract translation: 描述了用于捕获，恢复，拆卸和存储无人驾驶飞机和其他飞行装置或射弹的方法和装置。 在一个实施例中，吊杆可以被延伸以部署回收线以在飞行中捕获飞行器，这是根据本发明的其它方面能够由具有保持器的线捕获装置辅助的过程。 然后，飞机然后可以返回到其发射平台，拆卸和存储，再次与操作者和飞机之间的很少或没有直接的手动接触，例如通过捕获飞行器的第一翼并且在释放之前固定第二翼 第一。

公开(公告)号：US06923404B1

公开(公告)日：2005-08-02

申请号：US10339908

申请日：2003-01-10

Applicant: Danny D. Liu ,  Ping-Chih Chen ,  Darius Sarhaddi

Inventor： Danny D. Liu ,  Ping-Chih Chen ,  Darius Sarhaddi

IPC: B64C1/00 ,  B64C3/40 ,  B64C3/56 ,  B64C5/12 ,  B64C9/00 ,  B64C30/00 ,  B64C39/02 ,  B64C39/08 ,  B64F1/04 ,  F42B10/14 ,  F42B10/64

CPC classification number: B64F1/04 ,  B64C3/40 ,  B64C3/56 ,  B64C5/12 ,  B64C30/00 ,  B64C39/024 ,  B64C39/028 ,  B64C39/08 ,  B64C2201/044 ,  B64C2201/046 ,  B64C2201/048 ,  B64C2201/102 ,  B64C2201/121 ,  B64C2201/125 ,  B64C2201/127 ,  B64C2201/141 ,  B64C2201/146 ,  F42B10/14 ,  F42B10/64 ,  Y02T50/14

Abstract: An unmanned air vehicle (“UAV”) apparatus is configured to have a body and a body-conformal wing. The body-conformal wing is configured to variably sweep from a closed position to a fully deployed position. In the closed position, the body-conformal wing span is aligned with the body axis and in the fully deployed position the body-conformal wing span is perpendicular to the axial direction of the body. Delivery of the UAV comprises the steps of: positioning the span of a body conformal wing in alignment with the axis of the body of the UAV; initiating the flight of the UAV; and adjusting the sweep angle of the body-conformal wing as a function of the current speed, altitude, or attack angle of the UAV, with the adjustment starting at a 0 degree position and varying between a closed position and a fully deployed position. The UAV also has a control mechanism configured to variably adjust the sweep of the body-conformal wing to achieve a high lift over drag ratio through out the flight path of the UAV.

Abstract translation: 无人驾驶飞行器（“UAV”）装置被配置为具有主体和主体保形翼。 身体适形翼被配置为从关闭位置可变地扫掠到完全展开位置。 在关闭位置，身体共形翅膀跨度与身体轴线对齐，并且在完全展开位置，身体共形翅膀跨度垂直于身体的轴向。 无人机的交付包括以下步骤：将身体保形翼的跨度定位成与UAV的身体的轴线对准; 启动无人机的飞行; 并且根据UAV的当前速度，高度或攻角来调节身体保形翼的扫掠角度，调整从0度位置开始，并且在关闭位置和完全展开位置之间变化。 无人机还具有控制机构，其配置为可变地调整身体保形翼的扫掠，以通过无人机的飞行路径实现高的牵引比。

公开(公告)号：US20050151009A1

公开(公告)日：2005-07-14

申请号：US10760150

申请日：2004-01-16

Applicant: Cory Roeseler ,  Andreas von Flotow

Inventor： Cory Roeseler ,  Andreas von Flotow

IPC: B64C39/02 ,  B64F1/04 ,  B64F1/06

CPC classification number: B64C39/024 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/048 ,  B64C2201/084 ,  B64C2201/102 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/182 ,  B64C2201/201 ,  B64C2201/205 ,  B64F1/06

Abstract: Methods and apparatuses for launching unmanned aircraft and other flight devices or projectiles are described. In one embodiment, the aircraft can be launched from an apparatus that operates with a wedge action. A launch carriage carrying an unmanned aircraft is positioned on first and second launch members. At least one of the launch members moves relative to the other from a first position to a second position, causing the launch carriage to move from a first launch carriage position to a second launch carriage position. As the launch carriage moves, it accelerates the aircraft and releases the aircraft for takeoff.

Abstract translation: 描述了发射无人机和其他飞行装置或射弹的方法和装置。 在一个实施例中，飞行器可以从用楔形动作操作的装置发射。 携带无人机的发射架位于第一和第二发射构件上。 发射构件中的至少一个相对于另一个从第一位置移动到第二位置，使得发射托架从第一发射托架位置移动到第二发射托架位置。 随着发射架移动，它加速飞机并释放飞机起飞。

公开(公告)号：US20050133665A1

公开(公告)日：2005-06-23

申请号：US10759545

申请日：2004-01-16

Applicant: Brian Dennis ,  Brian McGeer ,  Cory Roeseler

Inventor： Brian Dennis ,  Brian McGeer ,  Cory Roeseler

IPC: B64C25/68 ,  B64C39/02 ,  B64F1/02 ,  B64F1/04 ,  B64F1/06 ,  B64C25/00

CPC classification number: B64C39/024 ,  B64C25/68 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/048 ,  B64C2201/084 ,  B64C2201/102 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/182 ,  B64C2201/205 ,  B64F1/02 ,  B64F1/04 ,  B64F1/06

Abstract: Methods and apparatuses for capturing and constraining motion of unmanned aircraft and other flight devices or projectiles are described. In one embodiment, the aircraft can be captured at an extendable boom. The boom can be extended to deploy a recovery line to retrieve the aircraft in flight. A trigger mechanism coupled to the recovery line can actuate a hoist device to reduce slack in the recovery line. A tension device coupled to the recovery line can absorb forces associated with the impact of the aircraft on the recovery line.

Abstract translation: 描述了用于捕获和约束无人驾驶飞机和其他飞行装置或射弹的运动的方法和装置。 在一个实施例中，飞机可以在可延伸的吊杆上被捕获。 可以扩展繁荣部署恢复线以在飞行中检索飞机。 联接到回收管线的触发机构可以启动提升装置以减少回收管线中的松弛。 耦合到回收管线的张紧装置可以吸收与飞机在回收管线上的冲击相关联的力。

公开(公告)号：US4410151A

公开(公告)日：1983-10-18

申请号：US182021

申请日：1980-08-28

Applicant: Heinz-Jochen Hoppner ,  Ulrich Kramer ,  Hugo Sgarz ,  Herbert Sadowski

Inventor： Heinz-Jochen Hoppner ,  Ulrich Kramer ,  Hugo Sgarz ,  Herbert Sadowski

IPC: B64C39/02 ,  F42B10/14 ,  B64F1/04 ,  F41F3/00

CPC classification number: B64C39/024 ,  F42B10/14 ,  B64C2201/084 ,  B64C2201/102 ,  B64C2201/165 ,  B64C2201/201 ,  B64C2201/208

Abstract: A vehicle or craft is provided for propeller propulsion with start assist by a releasable rocket engine. The craft is launched from a silo of square-shaped cross-section containing the starter motor for the propeller, whose engine is started while the craft is still in the silo. Diagonally opposed corners of the silo are provided with rails, in which run guides on rudder fins of the craft. The wings are pivoted to the fuselage for deployment whereby the wing tips do not move forward. The rocket engine is jettisoned shortly after take-off by simple disengagement. Parts of the wings and/or the rear of the fuselage may be jettisoned shortly before the craft reaches the target area.

Abstract translation: 提供用于螺旋桨推进的车辆或工具，由可释放的火箭发动机开始辅助。 该工艺是从一个方形截面的筒仓中推出的，包含用于螺旋桨的起动电机，当发动机仍然在筒仓中时，发动机起动。 筒仓的对角线相对的角落设有导轨，其中在工艺的方向舵鳍上的行进导轨。 机翼枢转到机身进行部署，由此机翼尖端不向前移动。 火箭发动机在起飞后不久就被简单的分离。 机翼的部分和/或机身的后部可能在飞机到达目标区域之前不久就被抛弃。

公开(公告)号：US20230271700A1

公开(公告)日：2023-08-31

申请号：US17652705

申请日：2022-02-28

Applicant: Matthew W. TOWNSEND

Inventor： Matthew W. TOWNSEND

IPC: B64C29/02 ,  B64C39/02 ,  B64C17/02 ,  B64C3/40

CPC classification number: B64C29/02 ,  B64C39/024 ,  B64C17/02 ,  B64C3/40 ,  B64C2201/028 ,  B64C2201/102 ,  B64C2201/088 ,  B64C2201/128

Abstract: A drone can be used to carry a payload. The drone can include at least two wings extending from a fuselage and propellers that allow the drone to fly in a horizontal orientation. The drone can takeoff and land from a vertical orientation via landing rods at the rear of the fuselage. The drone also includes an adjustable center of gravity and/or an adjustable center of lift. The center of gravity can be adjusted by changing the weight of payload located fore and aft of the center of gravity or moving at least a portion of the payload fore or aft along the fuselage. The center of lift can be adjusted by swinging the wings away from or towards the fuselage or sliding the wings fore or aft along the fuselage such that the center of lift is adjacent to the center of gravity.

公开(公告)号：US20230202652A1

公开(公告)日：2023-06-29

申请号：US17645752

申请日：2021-12-23

Applicant: OCTOFAN SAS

Inventor： Pierre Convert

IPC: B64C29/00 ,  B64C3/54 ,  B64C11/00 ,  B64C11/48 ,  B64C39/02 ,  B64C39/08

CPC classification number: B64C29/0033 ,  B64C3/54 ,  B64C11/001 ,  B64C11/48 ,  B64C39/024 ,  B64C39/08 ,  B64C2201/088 ,  B64C2201/042 ,  B64C2201/102 ,  B64C2201/162

Abstract: The aircraft comprises a fuselage defining a fuselage main axis. The fuselage comprises a docking system for fixing removable nacelles. The aircraft has wings equipped with tilting actuators for rotating wings about rotation axes parallel to the fuselage main axis and at least six propellers mechanically connected to the fuselage. The aircraft also has at least one cryo-hydrogen tank and at least one fuel cell for supplying power to the propellers, and
A capacitor for supplying power to the propellers, charged by at least one fuel cell. This capacitor stores electrical energy greater than the energy needed by all the propellers for ten seconds of hovering flight. Each propeller is equipped with a tilting actuator for rotating the propeller about a rotation axis making an angle of less than 45 degrees with a plane perpendicular to the fuselage main axis. The fuselage having a forward and a rear portion defining a forward to rear order of the propellers, in cruise flight, the two forward propellers are activated to provide vertical thrust, the intermediate propellers between the forward and rearmost propellers are not activated and the two rearmost propellers are activated to provide horizontal thrust.

公开(公告)号：US20190248469A1

公开(公告)日：2019-08-15

申请号：US15895192

申请日：2018-02-13

Applicant: Bell Helicopter Textron Inc.

Inventor： Levi Charles HEFNER ,  Danielle Lynn MOORE ,  Dakota Charles EASLEY

IPC: B64C9/02 ,  B64C5/02 ,  B64C39/02 ,  B64C29/02

CPC classification number: B64C9/02 ,  B64C5/02 ,  B64C29/02 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/024 ,  B64C2201/102 ,  B64C2201/108

Abstract: An example of an aerial vehicle includes a rudder removably connected to the aerial vehicle by a twist lock mechanism. The twist lock mechanism is biased in a locked position by an elastic member.

公开(公告)号：US20190210725A1

公开(公告)日：2019-07-11

申请号：US16352694

申请日：2019-03-13

Applicant: Walmart Apollo, LLC

Inventor： Robert L. Cantrell ,  John P. Thompson ,  David C. Winkle ,  Michael D. Atchley ,  Donald R. High ,  Todd D. Mattingly ,  John J. O'Brien ,  John F. Simon

IPC: B64C39/02 ,  B64C33/02 ,  B64C3/56 ,  B64C3/42

CPC classification number: B64C39/024 ,  B64C3/42 ,  B64C3/56 ,  B64C33/02 ,  B64C2201/021 ,  B64C2201/022 ,  B64C2201/025 ,  B64C2201/027 ,  B64C2201/102 ,  B64C2201/108 ,  B64C2201/127 ,  B64C2201/128 ,  B64C2201/14 ,  B64C2201/162

Abstract: Systems, apparatuses, and methods are provided herein for unmanned flight optimization. A system for unmanned flight comprises a set of motors configured to provide locomotion to an unmanned aerial vehicle, a set of wings coupled to a body of the unmanned aerial vehicle via an actuator and configured to move relative to the body of the unmanned aerial vehicle, a sensor system on the unmanned aerial vehicle, and a control circuit. The control circuit being configured to: control the unmanned aerial vehicle, cause the set of motors to lift the unmanned aerial vehicle, detect condition parameters based on the sensor system, determine a position for the set of wings based on the condition parameters, and cause the actuator to move the set of wings to the wing position while the unmanned aerial vehicle is in flight.