公开(公告)号：US20060151667A1

公开(公告)日：2006-07-13

申请号：US10758948

申请日：2004-01-16

Applicant: Brian Dennis ,  Andreas von Flotow

Inventor： Brian Dennis ,  Andreas von Flotow

IPC: B64F1/04

CPC classification number: B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/048 ,  B64C2201/102 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/182 ,  B64C2201/201 ,  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 includes an extendable boom. A launch carriage is positioned on a launch guide structure of the boom and carries the aircraft during takeoff. An energy reservoir is configured to provide energy to the launch carriage during takeoff of the aircraft, and can absorb energy from the launch carriage to decelerate the launch carriage after takeoff. The apparatus can further include a transmission that smoothly and rapidly accelerates and/or decelerates the launch carriage.

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，飞行器可以从包括可扩展起重臂的装置发射。 发射架位于起重臂的发射导向结构上，并在起飞时承载飞机。 能量储存器构造成在飞行器起飞期间向发射台提供能量，并且可以从起飞台吸收能量，以在起飞后减速发射台。 该装置还可以包括使发射台平滑且快速地加速和/或减速的变速器。

公开(公告)号：US07066430B2

公开(公告)日：2006-06-27

申请号：US10758956

申请日：2004-01-16

Applicant: Brian D. Dennis ,  Clifford Jackson ,  Brian T. McGeer ,  Andreas H. von Flotow

Inventor： Brian D. Dennis ,  Clifford Jackson ,  Brian T. McGeer ,  Andreas H. von Flotow

IPC: B64F1/02

CPC classification number: B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/048 ,  B64C2201/084 ,  B64C2201/102 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/182 ,  B64C2201/201 ,  B64C2201/205 ,  B64F1/06 ,  B64F1/222

Abstract: Methods and apparatuses for capturing and recovering 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. The boom can be retracted when not in use to reduce the volume it occupies. A tension device coupled to the recovery line can absorb forces associated with the impact of the aircraft and the recovery line.

Abstract translation: 描述了用于捕获和恢复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，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。 当不使用吊杆时，可以收起吊杆，以减少其占用的体积。 耦合到回收管线的张紧装置可以吸收与飞机和回收管线的冲击相关联的力。

公开(公告)号：US20060011777A1

公开(公告)日：2006-01-19

申请号：US11105746

申请日：2005-04-14

Applicant: Paul Arlton ,  David Arlton

Inventor： Paul Arlton ,  David Arlton

IPC: B64C27/22

CPC classification number: B64C27/10 ,  B64C27/22 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/082 ,  B64C2201/102 ,  B64C2201/108 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/201 ,  B64C2201/203 ,  B64C2201/205

Abstract: A rotary wing vehicle includes a body structure having an elongated tubular backbone or core, and a counter-rotating coaxial rotor system having rotors with each rotor having a separate motor to drive the rotors about a common rotor axis of rotation. The rotor system is used to move the rotary wing vehicle in directional flight.

公开(公告)号：US20050093507A1

公开(公告)日：2005-05-05

申请号：US10976566

申请日：2004-10-29

Applicant: Steven Sliwa ,  Andreas von Flotow ,  Brian Dennis

Inventor： Steven Sliwa ,  Andreas von Flotow ,  Brian Dennis

IPC: B63H20060101 ,  B64C11/00 ,  B64C11/04 ,  B64C11/14 ,  B64C11/28 ,  B64C39/02 ,  B64D41/00 ,  F02K5/02 ,  H02J7/00

CPC classification number: B64C11/003 ,  A63H27/02 ,  B64C11/04 ,  B64C11/14 ,  B64C11/28 ,  B64C39/024 ,  B64C2201/044 ,  B64C2201/082 ,  B64C2201/102 ,  B64C2201/165 ,  B64C2201/182 ,  B64C2201/201 ,  B64C2201/206 ,  B64D41/007 ,  F02K5/023 ,  F05D2260/85 ,  Y02T50/44 ,  Y02T50/672

Abstract: Methods and systems for starting propeller driven aircraft and other devices are disclosed. A system in accordance with one embodiment of the invention includes a removable fixture that is coupled to the propeller and has at least one portion exposed to a flowstream to rotate the propeller during engine start-up. The fixture is configured to separate from the propeller after the engine begins to turn over (e.g., after the engine starts and/or rotates above a threshold rate). Accordingly, the system can include a releasable link between the fixture and the propeller.

Abstract translation: 公开了用于启动螺旋桨驱动的飞机和其他装置的方法和系统。 根据本发明的一个实施例的系统包括可拆卸的固定装置，其连接到螺旋桨并且具有暴露于流动流中的至少一个部分以在发动机起动期间旋转螺旋桨。 发动机开始翻转（例如在发动机起动和/或旋转高于阈值速率之后），该固定装置构造成与螺旋桨分离。 因此，系统可以包括夹具和螺旋桨之间的可释放的连接。

公开(公告)号：US06576880B2

公开(公告)日：2003-06-10

申请号：US10150726

申请日：2002-05-17

Applicant: 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.

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: B64C351

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.

公开(公告)号：US4530476A

公开(公告)日：1985-07-23

申请号：US292260

申请日：1981-08-12

Applicant: Charles H. Thurber, Jr. ,  Frederick A. Behrens ,  John H. Hunton

Inventor： Charles H. Thurber, Jr. ,  Frederick A. Behrens ,  John H. Hunton

IPC: B64C39/02 ,  B64F1/10 ,  F41G7/00 ,  F41G7/22 ,  F41F3/00 ,  F42B15/16

CPC classification number: F41G7/22 ,  B64C39/024 ,  B64F1/06 ,  F41G7/007 ,  B64C2201/021 ,  B64C2201/046 ,  B64C2201/084 ,  B64C2201/102 ,  B64C2201/127 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/201 ,  B64C2201/208

Abstract: A method and system for delivering ordnance to a target via a remotely piloted or programmable aircraft including a yaw-to-turn guidance system, a deployment and launching system and packaging for the aircraft are disclosed.

Abstract translation: 公开了一种用于通过远程驾驶或可编程飞行器向目标提供弹药的方法和系统，包括偏航转弯引导系统，用于飞行器的展开和发射系统和包装。

公开(公告)号：US2382442A

公开(公告)日：1945-08-14

申请号：US53124344

申请日：1944-04-15

Applicant: RICH PAUL J ,  GRIESINGER JOHN W

Inventor： RICH PAUL J ,  GRIESINGER JOHN W

IPC: B64D1/02 ,  F41J9/04 ,  F42B10/56

CPC classification number: F42B10/56 ,  B64C2201/102 ,  B64C2201/201 ,  B64D1/02 ,  F41J9/04

公开(公告)号：US20180273166A1

公开(公告)日：2018-09-27

申请号：US15995419

申请日：2018-06-01

Applicant: Paul E. ARLTON ,  David J. ARLTON

Inventor： Paul E. ARLTON ,  David J. ARLTON

IPC: B64C27/605 ,  B64C27/10 ,  B64C27/14 ,  B64C39/02 ,  B64C7/00 ,  B64C27/82

CPC classification number: B64C27/605 ,  B64C7/00 ,  B64C27/10 ,  B64C27/14 ,  B64C39/024 ,  B64C2027/8236 ,  B64C2027/8281 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/082 ,  B64C2201/102 ,  B64C2201/108 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/201 ,  B64C2201/203 ,  B64C2201/205

Abstract: A rotary wing vehicle includes a body structure having an elongated tubular backbone or core, and a counter-rotating coaxial rotor system having rotors with each rotor having a separate motor to drive the rotors about a common rotor axis of rotation. The rotor system is used to move the rotary wing vehicle in directional flight.

公开(公告)号：US20180244402A1

公开(公告)日：2018-08-30

申请号：US15755699

申请日：2016-08-25

Applicant: UVISION AIR LTD

Inventor： MOSHE KAHLON ,  SHLOMO HAKIM

IPC: B64F1/04 ,  B64C39/02

CPC classification number: B64F1/04 ,  B64C39/024 ,  B64C2201/08 ,  B64C2201/102 ,  B64C2201/201

Abstract: A launcher for unmanned aerial vehicles (UAV), the launcher having a foldable UAV stowed within said launcher, the launcher includes, a launch tube configured as a UAV launcher and a UAV carrying case. The launcher further includes a pneumatic booster connected to said UAV for accelerating said UAV during launching phase. The launcher further includes a separation mechanism operated to permits separation of the booster from the UAV when the UAV leaves the launcher tube and to transfer the kinetic energy that is created from the pneumatic booster to the UAV in the launching phase. The UAV is propelled off of the launch tube by the booster that transmits thrust in the launch tube to the space below said booster. The UAV which is connected to the booster by the separation mechanism is pushed out of the launcher tube body and leaves the launch tube, the booster is separated from the UAV by the separation mechanism and the UAV is automatically deployed. The UAV propellers are activated to propel the UAV and driven the UAV.

公开(公告)号：US10035589B2

公开(公告)日：2018-07-31

申请号：US15035934

申请日：2015-12-29

Applicant: BEIJING ZERO ZERO INFINITY TECHNOLOGY CO., LTD

Inventor： Tong Zhang ,  Mengqiu Wang ,  Zhaozhe Wang ,  Xuyang Zhang ,  Guanqun Zhang ,  Shuang Gong ,  Yalin Zhang ,  Jinglong Wang ,  Lixin Liu

IPC: B64C27/08 ,  B64C27/00 ,  B64C1/30 ,  B64C39/02

CPC classification number: B64C27/006 ,  B64C1/30 ,  B64C27/08 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/108 ,  B64C2201/20 ,  B64C2201/201

Abstract: A foldable drone is provided to improve the portability of the drone, which includes a drone body and a rotary wing part connected to the drone body. The rotary wing part includes a first rotary wing module and a second rotary wing module with each having at least one rotary wing, and the first rotary wing module and the second rotary wing module are respectively articulated to two sides of the drone body, to allow the first rotary wing module and the second rotary wing module to rotate about their respective articulating shafts, so as to be folded or unfolded.