公开(公告)号：US20050178895A1

公开(公告)日：2005-08-18

申请号：US10808725

申请日：2004-03-24

Applicant: Brian McGeer ,  Andreas von Flotow ,  Cory Roeseler

Inventor： Brian McGeer ,  Andreas von Flotow ,  Cory Roeseler

IPC: B64C3/56 ,  B64F1/06

CPC classification number: B64F1/06 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/084 ,  B64C2201/104 ,  B64C2201/123 ,  B64C2201/127 ,  B64C2201/165

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 a launch carriage that moves along a launch guide. The carriage can accelerate when portions of the carriage and/or the launch guide move relative to each other. A gripper carried by the launch carriage can have at least one grip portion in contact with the aircraft while the launch carriage accelerates along the launch axis. The at least one grip portion can move out of contact with the aircraft as the launch carriage decelerates, releasing the aircraft for takeoff. A brake can arrest the motion of the gripper after launch.

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，飞行器可以从包括沿发射导向装置移动的发射台的装置发射。 当滑架和/或发射引导件的部分相对于彼此移动时，托架可以加速。 由发射托架携带的夹具可以具有至少一个与飞行器接触的抓握部分，同时发射托架沿着发射轴加速。 当发射架减速时，至少一个把手部分可以与飞行器脱离接触，释放飞机起飞。 制动器可以在发射后阻止夹具的运动。

公开(公告)号：US06607162B2

公开(公告)日：2003-08-19

申请号：US10049044

申请日：2002-02-07

Applicant: Clyde Warsop ,  Mike Woods ,  James Henderson ,  Gary Lock

Inventor： Clyde Warsop ,  Mike Woods ,  James Henderson ,  Gary Lock

IPC: B64C3906

CPC classification number: B64C39/062 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/162

Abstract: A ring-wing aircraft suited particularly, although not exclusively, to use in micro-unmanned air vehicles (UAV's) with ring-wings. An aircraft (10) according to the invention comprises a ring-wing (11) defining a duct (16) with a longitudinally-extending central axis (31), propulsion element (15) located within the duct and moveable aerofoils (13, 18) for controlling the aircraft in flight, the ring-wing being truncated obliquely at one end, that end being the rear (11b) when in horizontal flight, to form a ring-wing with opposed sides of unequal length. This arrangement produces center of mass offset from the central axis of the ring-wing, the pendulum effect will ensure that the aircraft will roll so that its center of mass will always be at the lowest height possible when the aircraft is airborne. Therefore the aircraft has a preferred orientation, and the control surfaces can be oriented with respect to this preferred orientation. In addition, the oblique truncation at the rear keeps the center of mass towards the front of the aircraft thereby giving improved stability in all three axes.

Abstract translation: 特别适用于环形翼的微型无人驾驶飞行器（UAV）的环形飞机虽然并非完全适用。 根据本发明的飞机（10）包括限定具有纵向延伸的中心轴线（31）的管道（16）的环形翼（11），位于管道内的推进元件（15）和可移动的机翼（13,18） ）用于控制飞行中的飞行器，环形翼在一端倾斜地截取，当水平飞行时，该端部是后部（11b），以形成具有不相等长度的相对侧的环形翼。 这种布置产生的偏心距离环形翼的中心轴线，摆锤效应将确保飞机将滚动，使其质心总是在飞机空降时始终处于最低的高度。 因此，飞行器具有优选的取向，并且控制表面可以相对于该优选取向被定向。 此外，后方的倾斜截面使质心朝向飞机的前方，从而提高了所有三个轴线的稳定性。

公开(公告)号：US06565041B1

公开(公告)日：2003-05-20

申请号：US10028956

申请日：2001-12-27

Applicant: Eric P. Young ,  John Reynolds ,  Mathew Curran ,  Danny Gast ,  Joseph Wurts

Inventor： Eric P. Young ,  John Reynolds ,  Mathew Curran ,  Danny Gast ,  Joseph Wurts

IPC: B64D1780

CPC classification number: B64D17/40 ,  B64C39/024 ,  B64C39/028 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/165 ,  B64C2201/185 ,  B64D17/54 ,  B64D17/76 ,  B64D17/80

Abstract: A parachute system for a miniature aircraft having a storable parachute mounted on an upper surface of the aircraft. The system includes a canopy having a stored condition and an expanded condition. A plurality of suspension lines have first ends connected to the periphery of the canopy and second ends connected to an elastic member. First and second risers are connected by their first ends to the upper surface of the aircraft between the front end and center of gravity on either side of the longitudinal axis and by their second ends to the elastic member. A restraint system releasably restrains the parachute in the stored condition on the top surface of the aircraft; and a release system coupled to the restraint system releases the parachute upon command such that aerodynamic forces will cause the parachute to open.

Abstract translation: 用于具有安装在飞行器的上表面上的可存放降落伞的微型飞机的降落伞系统。 该系统包括具有存储条件和扩展状态的遮篷。 多个悬挂线具有连接到顶盖的周边的第一端和连接到弹性构件的第二端。 第一和第二立管通过其第一端连接到飞行器的上表面，在纵轴的任一侧上的前端和重心之间，并且通过其第二端连接到弹性构件。 约束系统可释放地将降落伞限制在飞机顶表面上的储存状态; 并且联接到约束系统的释放系统根据命令释放降落伞，使得空气动力将使降落伞打开。

公开(公告)号：US20020005454A1

公开(公告)日：2002-01-17

申请号：US09826424

申请日：2001-04-03

Inventor： Paul B. MacCready ,  Bart D. .Hibbs ,  Robert F. Curtin ,  Kyle D. Swanson ,  Paul Belik

IPC: B64C001/00 ,  B64B001/20 ,  B64C017/00

CPC classification number: B64D27/24 ,  B64C1/26 ,  B64C3/10 ,  B64C3/14 ,  B64C9/24 ,  B64C39/024 ,  B64C39/10 ,  B64C2201/021 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/086 ,  B64C2201/104 ,  B64C2201/122 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/187 ,  B64D27/02 ,  B64D37/30 ,  B64D2041/005 ,  Y02T50/12 ,  Y02T50/32 ,  Y02T50/44 ,  Y02T50/64 ,  Y02T90/36

Abstract: Disclosed is an aircraft, configured to have a wide range of flight speeds, consuming low levels of power for an extended period of time, while supporting a communications platform with an unobstructed downward-looking view. The aircraft includes an extendable slat at the leading edge of the wing, and a reflexed trailing edge. The aircraft comprises a flying wing extending laterally between two ends and a center point. The wing is swept and has a relatively constant chord. The aircraft also includes a power module configured to provide power via a fuel cell. The fuel cell stores liquid hydrogen as fuel, but uses gaseous hydrogen in the fuel cell. A fuel tank heater is used to control the boil-rate of the fuel in the fuel tank. The aircraft of the invention includes a support structure including a plurality of supports, where the supports form a tetrahedron that affixes to the wing.

Abstract translation: 公开了一种被配置为具有宽范围的飞行速度的飞机，在延长的时间段内消耗低水平的功率，同时以无阻碍的向下观看的方式支持通信平台。 飞机在翼的前缘包括可延伸的板条，以及反射的后缘。 飞机包括在两端之间横向延伸的飞翼和中心点。 机翼被扫掠并具有相对恒定的和弦。 该飞机还包括被配置为经由燃料电池提供电力的功率模块。 燃料电池将液态氢作为燃料储存，而在燃料电池中使用气态氢。 燃料箱加热器用于控制燃料箱中的燃料的沸腾率。 本发明的飞行器包括支撑结构，该支撑结构包括多个支撑件，其中支撑件形成固定在机翼上的四面体。

公开(公告)号：US5503350A

公开(公告)日：1996-04-02

申请号：US145204

申请日：1993-10-28

Applicant: Howard A. Foote

Inventor： Howard A. Foote

IPC: B64C39/02 ,  B64D27/24 ,  H01Q1/24

CPC classification number: G05D1/0038 ,  B64C39/024 ,  B64D27/24 ,  H01Q1/248 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/122 ,  B64C2201/165 ,  Y02T50/44 ,  Y02T50/64 ,  Y10S320/33

Abstract: An unmanned, remotely controlled microwave-powered aircraft for use as a stationary communications platform. The aircraft is generally a flying wing with a large, flat inner wing having a rectenna on the underside. Rectennas may also be provided on the underside of the wings, the combined output from the rectenna being used to provide power to two electric motors housed within torpedo-shaped nacelles which drive two rear propellers. The rectenna converts a microwave signal at 35 GHz generated by a ground power station utilizing dual gyrotrons and a 34-meter diameter antenna dish. The aircraft has a preferred airfoil cross section throughout and is constructed of lightweight but strong materials in order to provide an enhanced flying time of several months. A power management and distribution system manages the DC power produced by the rectenna to supply power to the flight controls, propulsion system and payload.

Abstract translation: 一种无人遥控的微波动力飞机，用作固定通信平台。 该飞机通常是具有大的，平坦的内翼的飞翼，其在下侧具有直角天线。 也可以在机翼的下侧设置整流器，来自整流罩的组合输出用于向容纳在用于驱动两个后部螺旋桨的鱼雷型发动机舱内的两个电动机提供动力。 整流天线使用双回旋加速器和直径34米的天线盘转换由地面电站产生的35GHz的微波信号。 该飞机具有优选的翼型横截面，并且由轻质但坚固的材料构成，以便提供几个月的增强的飞行时间。 电力管理和分配系统管理由天线产生的直流电力，为飞行控制，推进系统和有效载荷提供动力。

公开(公告)号：US4601442A

公开(公告)日：1986-07-22

申请号：US545083

申请日：1983-10-25

Applicant: Franz Friedel ,  Werner Fruhauf ,  Gunter Harms ,  Georg Heise ,  Heinrich Lukewille

Inventor： Franz Friedel ,  Werner Fruhauf ,  Gunter Harms ,  Georg Heise ,  Heinrich Lukewille

IPC: B64C39/02 ,  F16D7/02 ,  F42B10/64 ,  F42B15/10 ,  F42B15/02

CPC classification number: F42B10/64 ,  B64C39/024 ,  F16D7/021 ,  F42B15/105 ,  B64C2201/028 ,  B64C2201/044 ,  B64C2201/165 ,  B64C2201/201

Abstract: Unmanned missile with strongly backswept wing unit, in particular delta wings, which is transported in a container and is launched from the container by means of an auxiliary drive after release of a lock, and which during cruise flight is drivable by a propeller engine, lateral force surfaces (25) being deployable for stabilization of the missile during cruise flight, from retraction spaces (26) in the region of the wing root of the delta wings, and further a friction clutch (64, 65) is provided at the missile which, without supply of energy from the outside, couples the standing propeller 6 with the drive motor (7) running in the container, after leaving the container.

Abstract translation: 具有强力后卫的翼单元，特别是三角翼的无人驾驶导弹，其在集装箱中运输并且在释放锁之后通过辅助驱动从容器发射，并且在巡航飞行期间由螺旋桨发动机驱动，横向 力表面（25）可展开用于在巡航飞行期间稳定导弹，来自三角翼机翼根部区域中的缩回空间（26），并且在该导弹处提供摩擦离合器（64,65） 在没有从外部供应能量的情况下，在离开容器之后将立式螺旋桨6与在容器中运行的驱动马达（7）相耦合。

公开(公告)号：WO2016114851A1

公开(公告)日：2016-07-21

申请号：PCT/US2015/060805

申请日：2015-11-16

Applicant: SIKORSKY AIRCRAFT CORPORATION

Inventor： ALBER, Mark R.

IPC: B64D27/06

CPC classification number: B64D35/04 ,  B64C29/02 ,  B64C39/024 ,  B64C2201/028 ,  B64C2201/048 ,  B64C2201/088

Abstract: A vertical take-off and landing (VTOL) aircraft is provided and includes wings, first and second nacelles supported on each of the wings, each of the first and second nacelles including a propeller drivable to generate aircraft thrust, and an asymmetrical power generation unit. The asymmetrical power generation unit includes a single engine unit disposed in only one of the first and second nacelles to generate power to drive the propellers of both the first and second nacelles.

Abstract translation: 提供垂直起飞和着陆（VTOL）飞机，并且包括翼，每个翼上支撑的第一和第二机舱，第一和第二机舱中的每一个包括可驱动以产生飞机推力的螺旋桨，以及不对称发电单元 。 不对称发电单元包括仅设置在第一和第二机舱中的一个机舱中的单个发动机单元，以产生驱动第一和第二机舱的螺旋桨的动力。

公开(公告)号：WO2016062921A1

公开(公告)日：2016-04-28

申请号：PCT/FI2015/050710

申请日：2015-10-20

Applicant: HOHENTHAL, Markus

Inventor： HOHENTHAL, Markus

IPC: B64C29/02 ,  B64C39/02 ,  B64D27/24

CPC classification number: B64C29/02 ,  B64C39/024 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/088 ,  B64C2201/104 ,  B64D27/24

Abstract: An electrically powered vertical takeoff and vertical landing (VTOL) aircraft, which comprises at least two main propellers (101a, 101b), wherein the main propellers are adapted to generate at least 70% of the aircraft propulsion. The aircraft also comprises at least one adjustment propeller (101a, 101b, 102), which has its propeller slipstream adapted to produce a torque (113, 114, 115) relative to a first axis (103) or the first and second (104) axes with respect to a fuselage (119) of the aircraft for turning the aircraft relative to said first axis or said first and second axes. In addition, not less than 35%, but not more than 85%, of the aircraft's mass is adapted to lie, during takeoff and/or landing, on a rear side (109) of a propeller line (108) of said main propellers with respect to a nose (111) of the aircraft.

Abstract translation: 一种电力垂直起飞和垂直着陆（VTOL）飞机，其包括至少两个主推进器（101a，101b），其中所述主推进器适于产生至少70％的飞行器推进。 飞行器还包括至少一个调节螺旋桨（101a，101b，102），其具有适于相对于第一轴线（103）或第一和第二（104）产生扭矩（113,114,115）的螺旋桨滑流， 相对于用于使飞行器相对于所述第一轴线或所述第一和第二轴线转动的飞机的机身（119）的轴线。 此外，飞机的质量不小于35％但不超过85％适于在起飞和/或着陆期间位于所述主推进器的螺旋桨线（108）的后侧（109）上 相对于飞机的鼻子（111）。

公开(公告)号：WO2014025617A1

公开(公告)日：2014-02-13

申请号：PCT/US2013/053271

申请日：2013-08-01

Applicant: AURORA FLIGHT SCIENCES CORPORATION

Inventor： WOODWORTH, Adam ,  PEVERILL, James ,  VULIKH, Greg ,  HOLLMAN, Jeremy

IPC: B64C15/12 ,  B64C39/02

CPC classification number: B64C29/0033 ,  B64C39/024 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/104 ,  B64C2201/201 ,  B64C2211/00

Abstract: An aircraft for unmanned aviation is described. The aircraft includes an airframe, a pair of fins attached to a rear portion of the airframe, a pair of dihedral braces attached to a bottom portion of the airframe, a first thrust-vectoring ("T/V") module and a second T/V module, and an electronics module. The electronics module provides commands to the two T/V modules. The two T/V modules are configured to provide lateral and longitudinal control to the aircraft by directly controlling a thrust vector for each of the pitch, the roll, and the yaw of the aircraft. The use of directly articulated electrical motors as T/V modules enables the aircraft to execute tight-radius turns over a wide range of airspeeds.

Abstract translation: 描述了一种无人驾驶飞机。 飞行器包括机身，连接到机身的后部的一对翼片，连接到机身的底部的一对二面支架，第一推力矢量（“T / V”）模块和第二T / V模块，以及电子模块。 电子模块向两个T / V模块提供命令。 两个T / V模块被配置为通过直接控制飞行器的俯仰，滚动和偏航中的每一个的推力矢量来向飞行器提供侧向和纵向控制。 使用直接连接的电动机作为T / V模块，使飞机能够在大范围的空速下执行紧半径的转弯。

公开(公告)号：WO2009094566A2

公开(公告)日：2009-07-30

申请号：PCT/US2009031870

申请日：2009-01-23

Applicant: INSITU INC ,  HEPPE STEPHEN B ,  MACK JAIME

Inventor： HEPPE STEPHEN B ,  MACK JAIME

IPC: B64F1/00

CPC classification number: B64F1/02 ,  B64C2201/028 ,  B64C2201/182

Abstract: Systems and methods for recovering unmanned aircraft and controlling post- recovery motion of the aircraft are disclosed herein. An aircraft recovery system for recovering an unmanned aircraft in flight in accordance with one embodiment of the disclosure, for example, can include an inflatable aircraft recovery system having an inflatable portion with a generally vertical orientation. The inflatable portion can also include a landing pocket extending at least partially therethrough. The landing pocket is sized to receive at least a portion of a fuselage of the aircraft. The aircraft recovery system can also include a guidance system at least proximate to the landing pocket and positioned to guide the aircraft toward the landing pocket.

Abstract translation: 本文公开了用于恢复无人飞机并控制飞机的后恢复运动的系统和方法。 例如，根据本公开的一个实施例，用于在飞行中恢复无人飞行器的飞行器恢复系统可以包括具有大致垂直取向的可充气部分的可充气飞行器回收系统。 可充气部分还可以包括至少部分地延伸穿过其中的着陆口袋。 登陆口袋的大小可以接收飞机的机身的至少一部分。 飞机恢复系统还可以包括至少靠近着陆口袋并定位成引导飞行器朝着着陆口袋的引导系统。