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：US4106727A

公开(公告)日：1978-08-15

申请号：US795052

申请日：1977-05-09

Applicant: Alexander Rudolph Ortell

Inventor： Alexander Rudolph Ortell

IPC: B64C3/56 ,  F42B10/18

CPC classification number: F42B10/18 ,  B64C39/024 ,  B64C2201/102

Abstract: A folding airfoil for an aircraft in which the wing or stabilizer airfoil n be folded and contained entirely within the fuselage of the aircraft. The airfoil comprises a series of elongated sheet metal channel sections of generally C-shaped cross section with the cross sectional dimension of successive channels decreasing so that each can nest entirely within an adjacent channel. The channels are each pivotally connected at the root end to the aircraft fuselage structure at spaced intervals along the chord line of the extended airfoil and the end sections of the channels are pivotally connected to each other such that the channels are pivotable between (1) an extended position extending spanwise of the extended airfoil to lie in tandem one behind the other, with adjacent channels partially overlapping and (2) a retracted or folded position in which the channels are nested within the leading edge channel section and lie along the chord line of the extended airfoil along the line of channel root end pivotal connections.

Abstract translation: 用于飞机的折叠翼型件，其中机翼或稳定器翼型件可以被折叠并完全容纳在飞行器的机身内。 翼型件包括大致C形横截面的一系列细长的金属板通道部分，其中相继通道的横截面尺寸减小，使得每个可以完全嵌套在相邻通道内。 通道各自在根​​部沿着延伸翼型件的弦线以间隔的间隔枢转地连接到飞行器机身结构，并且通道的端部部分彼此枢转地连接，使得通道可以在（1） 延伸位置延伸到延伸翼型件的翼展方向，彼此并排地彼此串联，相邻通道部分重叠，和（2）缩回或折叠位置，其中通道嵌套在前缘通道部分内并且沿着 延伸翼型沿着通道根端枢转连接。

公开(公告)号：US3703998A

公开(公告)日：1972-11-28

申请号：US3703998D

申请日：1970-12-28

Applicant: TELEDYNE RYAN AERONAUTICAL CO

Inventor： GIRARD PETER F

IPC: B64C1/00 ,  B64C39/02 ,  B64C1/28 ,  B64C3/56

CPC classification number: B64C39/024 ,  B64C1/00 ,  B64C2001/0045 ,  B64C2201/048 ,  B64C2201/102 ,  B64C2201/121 ,  B64C2201/146 ,  B64C2201/162 ,  B64C2201/167

Abstract: A drone type aircraft having a telescopic fuselage and folding aerodynamic surfaces to facilitate installation in a limited capacity bomb bay or storage compartment of a launch aircraft. Prior to launch, the drone is lowered from the aircraft on a supporting frame, the aerodynamic surfaces are extended, and the nose section of the fuselage is extended. The added fuselage capacity is used as fuel tankage, which is filled from the launch aircraft to increase the operating range of the drone.

Abstract translation: 具有伸缩机身和折叠空气动力学表面的无人机型飞机，以便于安装在发射飞机的有限容量的炸弹舱或储藏室中。 在发射之前，无人机在支架上从飞机上下降，空气动力学表面延伸，机身的鼻部延伸。 增加的机身容量用作燃油箱，由发射机充满，以增加无人机的运行范围。

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：US11649051B2

公开(公告)日：2023-05-16

申请号：US17007647

申请日：2020-08-31

Applicant: Paul E. Arlton ,  David J. Arlton

Inventor： Paul E. Arlton ,  David J. Arlton

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

CPC classification number: B64C39/024 ,  B64C7/00 ,  B64C27/10 ,  B64C27/14 ,  B64C27/605 ,  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：US20190248492A1

公开(公告)日：2019-08-15

申请号：US16322557

申请日：2017-07-26

Applicant: Sylvain ROLDAN DE PERERA

Inventor： Sylvain ROLDAN DE PERERA

IPC: B64D1/02 ,  B64C39/02 ,  B64C27/37 ,  B64C27/50 ,  B64C3/56 ,  B64C3/40 ,  B64C9/08

CPC classification number: B64D1/02 ,  B64C3/40 ,  B64C3/56 ,  B64C9/08 ,  B64C27/24 ,  B64C27/37 ,  B64C27/50 ,  B64C39/024 ,  B64C2009/005 ,  B64C2201/021 ,  B64C2201/024 ,  B64C2201/08 ,  B64C2201/084 ,  B64C2201/102 ,  B64C2201/108 ,  B64C2201/12

Abstract: An assembly comprising a drone (1) and at least one releasable load (37) mounted on the drone, the drone comprising an on-board data processing system, the releasable load (37) comprising at least one sensor delivering a piece of information that can be used to ascertain the path of same and actuators for controlling flight control surfaces allowing it to be oriented as it falls, being linked to the drone (1) by an optical fibre (70), the load and the drone being arranged to exchange information via the optical fibre while the load is falling, the load transmitting data originating from said at least one sensor and the drone transmitting data for controlling the actuators, established taking into account that received from the load, in order to guide the load towards a predefined target.

公开(公告)号：US20180354612A1

公开(公告)日：2018-12-13

申请号：US15620317

申请日：2017-06-12

Applicant: Bell Helicopter Textron Inc.

Inventor： Levi Charles Hefner ,  Danielle Lynn Moore ,  Sung Kim

IPC: B64C27/605 ,  B64C39/02 ,  B64C29/02 ,  B64C25/52 ,  B64C9/00

CPC classification number: B64C27/605 ,  B64C3/546 ,  B64C11/48 ,  B64C27/10 ,  B64C29/02 ,  B64C39/024 ,  B64C2201/102 ,  B64C2201/108 ,  B64C2201/165

Abstract: An Unmanned Aerial Vehicle (UAV) has a first blade assembly configured to rotate in a first direction about an axis of rotation and a second blade assembly configured to rotate in a second direction opposite the first direction about the axis of rotation, wherein the second blade assembly can be selectively cocked relative to the axis of rotation.

公开(公告)号：US10054958B2

公开(公告)日：2018-08-21

申请号：US14695693

申请日：2015-04-24

Applicant: Son F. Creasman

Inventor： Son F. Creasman

IPC: G05D1/10 ,  B64C29/02 ,  B64C3/56 ,  B64C9/00 ,  B64C39/02 ,  B64C11/48 ,  B64F1/00 ,  B64C3/54 ,  B64C25/04 ,  G05D1/00

CPC classification number: G05D1/102 ,  B64C3/546 ,  B64C3/56 ,  B64C9/00 ,  B64C11/48 ,  B64C25/04 ,  B64C29/02 ,  B64C39/024 ,  B64C2201/028 ,  B64C2201/102 ,  B64C2201/108 ,  B64F1/007 ,  G05D1/0011

Abstract: One example embodiment includes a vertical takeoff and landing (VTOL) unmanned aerial vehicle (UAV). The VTOL UAV includes a flight control system configured to provide avionic control of the VTOL UAV in a hover mode and in a level-flight mode. The VTOL UAV also includes a body encapsulating an engine and the flight control system. The VTOL UAV further includes a propeller disk coupled to the engine and configured to provide vertical thrust in the hover mode and to provide horizontal thrust for flight during the level-flight mode.

公开(公告)号：US20180164820A1

公开(公告)日：2018-06-14

申请号：US15073403

申请日：2016-03-17

Applicant: NORTHROP GRUMMAN SYSTEMS CORPORATION

Inventor： OMAR ABOUTALIB ,  David W. Evans ,  Gregory L. Larson ,  Annie D. Nguyen ,  Richard R. Ramroth

IPC: G05D1/00 ,  H04N7/18 ,  G06K9/00 ,  G06T7/73 ,  G06K9/62 ,  B64C39/02

CPC classification number: G05D1/0094 ,  B64C39/02 ,  B64C39/024 ,  B64C2201/082 ,  B64C2201/102 ,  B64C2201/121 ,  G05D1/00 ,  G06K9/0063 ,  G06K9/6202 ,  G06K2209/21 ,  G06T7/74 ,  G06T2207/10048 ,  G06T2207/30212 ,  G06T2207/30252 ,  H04N7/185

Abstract: A system and method for controlling a swarm of UAVs that are stored on and released from an airborne platform, fly to and destroy a target, where the UAVs download target information from the airborne platform before being released therefrom, do not communicate with each other or the airborne platform while in flight, and do not depend of the presence of GPS. Each UAV includes a vision sensor that provides image data, a navigation module that receives the image data and causes the UAV to navigate and fly towards the target, and a target destruction module that receives the image data and causes the UAV to destroy the target.

公开(公告)号：US09988138B2

公开(公告)日：2018-06-05

申请号：US14250385

申请日：2014-04-11

Applicant: The Boeing Company

Inventor： Kevin Reed Lutke ,  Aaron Jonathan Kutzmann

IPC: B64C3/30 ,  B64C39/02

CPC classification number: B64C3/30 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/102 ,  B64C2201/105

Abstract: A method and apparatus for operating an airfoil system. A gas may be generated. The gas may be sent into an inflatable airfoil system comprising an inflatable air foil and a section. The inflatable airfoil may have an inner end and an outer end in which the inflatable airfoil may be comprised of a number of materials that substantially pass electromagnetic waves through the inflatable airfoil. The section may have a number of openings in which the inner end of the inflatable airfoil may be associated with the section. The section may be configured to be associated with a fuselage. The number of openings may be configured to provide communications with an interior of the inflatable airfoil. The section with the number of openings may be configured to reduce reflection of the electromagnetic waves encountering the section.