公开(公告)号：US07165745B2

公开(公告)日：2007-01-23

申请号：US10808725

申请日：2004-03-24

Applicant: Brian T. McGeer ,  Andreas H. von Flotow ,  Cory Roeseler

Inventor： Brian T. McGeer ,  Andreas H. von Flotow ,  Cory Roeseler

IPC: 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：US20060284005A1

公开(公告)日：2006-12-21

申请号：US11510013

申请日：2006-08-25

Applicant: Peter Ifju ,  Kyu-Ho Lee ,  Roberto Albertani ,  Shawn Mitryk ,  Frank Boria ,  Mujahid Abdulrahim

Inventor： Peter Ifju ,  Kyu-Ho Lee ,  Roberto Albertani ,  Shawn Mitryk ,  Frank Boria ,  Mujahid Abdulrahim

IPC: B64C3/56 ,  B64C3/00

CPC classification number: B64C39/028 ,  A63H27/007 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/048 ,  B64C2201/082 ,  B64C2201/102 ,  B64C2201/123 ,  B64C2201/127 ,  B64C2201/165 ,  B64C2201/201

Abstract: A micro air vehicle having a bendable wing enabling the micro air vehicle to fly. The bendable wing may be bent downwards so that the wingspan may be reduced for storing the micro air vehicle. The bendable wing may be formed from one or more layers of material, and the wing may have a camber such that a concave surface of the wing faces downward. The wing may substantially resist flexing upwards and may transfer uplift forces to a central body of the micro air vehicle. In addition, the wing may be bent severely downwards by applying a force to tips of the wing. The micro air vehicle is capable of being stored in a small cylindrical tube and may be deployed from the tube by simply releasing the micro air vehicle from the tube.

Abstract translation: 具有能够使微型飞行器飞行的可弯曲翼的微型飞行器。 可弯曲翼可以向下弯曲，使得翼展可以减小以存储微型飞行器。 可弯曲翼可以由一层或多层材料形成，并且翼可以具有弯曲，使得翼的凹面朝向下方。 机翼可以基本上抵抗向上弯曲并且可以将提升力传递到微型飞行器的中心体。 此外，机翼可能通过对机翼的尖端施加力而严重地向下弯曲。 微型飞行器能够存储在小圆柱形管中，并且可以通过从管中简单地释放微型飞行器而从管展开。

公开(公告)号：US20060175463A1

公开(公告)日：2006-08-10

申请号：US11269395

申请日：2005-11-08

Applicant: Brian McGeer

Inventor： Brian McGeer

IPC: B64F5/00

CPC classification number: B64F1/04 ,  B64C25/68 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/048 ,  B64C2201/084 ,  B64C2201/102 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/182 ,  B64C2201/201 ,  B64C2201/205 ,  B64F1/02 ,  B64F1/06

Abstract: Methods and apparatuses for launching, capturing, and storing unmanned aircraft and other flight devices or projectiles are described. In one embodiment, the aircraft can be assembled from a container with little or no manual engagement by an operator. The container can include a guide structure to control motion of the aircraft components. The aircraft can be launched from an apparatus that includes an extendable boom. The boom can be extended to deploy a recovery line to capture the aircraft in flight. The aircraft can then be returned to its launch platform, disassembled, and stored in the container, again with little or no direct manual contact between the operator and the aircraft.

Abstract translation: 描述了用于发射，捕获和存储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，飞行器可以由操作者很少或没有手动接合的容器组装。 容器可以包括用于控制飞机部件的运动的引导结构。 飞机可以从包括可伸缩吊杆的装置发射。 可以扩展繁荣部署一个恢复线，以便在飞行中捕获飞机。 飞机然后可以返回到其发射平台，拆卸并存储在容器中，再次与操作员和飞机之间的很少或没有直接的手动接触。

公开(公告)号：US20050224657A1

公开(公告)日：2005-10-13

申请号：US10782253

申请日：2004-02-19

Applicant: John Bolling

Inventor： John Bolling

IPC: B64C1/00 ,  B64C39/02 ,  B64D39/00

CPC classification number: B64D39/00 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/028 ,  B64C2201/104

Abstract: An in-flight refueling system for an unmanned aircraft is responsive to sensed forces acting on a refueling receptacle of the aircraft by a separate refueling probe, to control movements of the aircraft as it is being refueled to reduce the magnitude of the sensed forces and thereby maintain the coupling of the aircraft with the refueling probe.

Abstract translation: 用于无人驾驶飞机的飞行中加油系统响应于通过单独的加油探针作用在飞机的加油容器上的感测力，以控制飞机在被加油时的运动，以减小感测力的大小，从而 保持飞机与加油探头的耦合。

公开(公告)号：US06845939B1

公开(公告)日：2005-01-25

申请号：US10693800

申请日：2003-10-24

Applicant: G. Douglas Baldwin

Inventor： G. Douglas Baldwin

IPC: B64C29/00 ,  B64C39/02 ,  B64C27/28

CPC classification number: B64C29/02 ,  B64C29/0033 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/024 ,  B64C2201/048 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/128 ,  B64C2201/165

Abstract: A disclosed flying craft includes a suspension structure having a first end and a second end, a lift unit, and a payload unit. The lift unit includes a nacelle and a tailboom, and pivotally couples to the first end of the suspension structure, and a payload unit couples to the structure's second end. Thus the tailboom can pivotally couple with respect to the payload unit, which advantageously permits the tailboom to assume an orientation desirable for a particular mode of flight. During vertical flight or hover, the tailboom can hang from the lift unit in an orientation that is substantially parallel to the suspension structure and that minimizes resistance to downwash from the lift unit. During horizontal flight, the tailboom can be orthogonal to the suspension structure, extending rearward in an orientation where it can develop pitching and yawing moments to control and stabilize horizontal flight. Advantageous variations and methods are also disclosed.

Abstract translation: 公开的飞行技术包括具有第一端和第二端的悬挂结构，升降单元和有效载荷单元。 提升单元包括机舱和尾巴，并且枢转地联接到悬架结构的第一端，并且有效载荷单元耦合到结构的第二端。 因此，尾巴可以相对于有效载荷单元枢转地联接，这有利地允许尾巴呈现对于特定飞行方式所需的取向。 在垂直飞行或悬停期间，尾巴可以以与悬挂结构基本平行的方向从提升单元悬挂，并且使得抵抗来自提升单元的降洗的阻力最小化。 在水平飞行期间，尾翼可以与悬架结构正交，向后延伸，在该方向上可以产生俯仰和偏转力矩以控制和稳定水平飞行。 还公开了有利的变型和方法。

公开(公告)号：US06845937B2

公开(公告)日：2005-01-25

申请号：US10453777

申请日：2003-06-03

Applicant: Henry August

Inventor： Henry August

IPC: B64C5/12 ,  B64C39/02 ,  B64C39/06 ,  B64C39/12 ,  B64D1/06 ,  F42B10/16 ,  F42B10/62 ,  F42B12/58 ,  F42B12/62 ,  F42B15/00 ,  B64C37/02

CPC classification number: B64C39/024 ,  B64C2201/021 ,  B64C2201/046 ,  B64C2201/104 ,  B64C2201/121 ,  F42B10/16 ,  F42B10/62 ,  F42B12/58 ,  F42B12/62 ,  F42B15/00

Abstract: A reusable, mach-velocity mobile platform delivers a weapons payload via vertical launch, powerless glide, weapons release, and landing operation phases. The platform includes a generally tubular shaped body having an aft and forward end, and a payload section. An arch wing is supported by the body aft end. The arch wing has an upper and a lower wing joined at distal ends by two curved end plates. A nose assembly is connected at the forward end having an upward directed fixed angle-of-attack to generate forward end lift. Thermal tiles attached under the body and the lower wing under-side radiate/dissipate heat generated during a high angle-of-attack platform reentry. Radar absorptive or radar translucent material is used. The platform preferably discharges payload from the aft end for safe separation. A landing gear is extended for the landing phase of operation.

Abstract translation: 可重复使用的马赫速度移动平台通过垂直发射，无力滑翔，武器释放和着陆操作阶段提供武器有效载荷。 平台包括具有尾部和前端的大致管状的主体和有效载荷部分。 一个弓翼由身体后端支撑。 拱翼具有通过两个弯曲端板在远端连接的上翼和下翼。 前端组件在前端连接，具有向上定向的固定迎角，以产生前端提升。 安装在车体下方的散热瓦片和下部翼片下侧辐射/消散在高角度攻角平台折返期间产生的热量。 使用雷达吸收或雷达半透明材料。 该平台优选地从尾端排出有效载荷以进行安全分离。 起落架延伸到着陆阶段。

公开(公告)号：US20040245393A1

公开(公告)日：2004-12-09

申请号：US10731777

申请日：2003-12-09

Applicant: University of Florida

Inventor： Peter Ifju ,  Kyu-Ho Lee ,  Roberto Albertani ,  Shawn J. Mitryk ,  Frank J. Boria ,  Mujahid Abdulrahim

IPC: B64C001/00

CPC classification number: B64C39/028 ,  A63H27/007 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/048 ,  B64C2201/082 ,  B64C2201/102 ,  B64C2201/123 ,  B64C2201/127 ,  B64C2201/165 ,  B64C2201/201

Abstract: A micro air vehicle having a bendable wing enabling the micro air vehicle to fly. The bendable wing may be bent downwards so that the wingspan may be reduced for storing the micro air vehicle. The bendable wing may be formed from one or more layers of material, and the wing may have a camber such that a concave surface of the wing faces downward. The wing may substantially resist flexing upwards and may transfer uplift forces to a central body of the micro air vehicle. In addition, the wing may be bent severely downwards by applying a force to tips of the wing. The micro air vehicle is capable of being stored in a small cylindrical tube and may be deployed from the tube by simply releasing the micro air vehicle from the tube.

Abstract translation: 具有能够使微型飞行器飞行的可弯曲翼的微型飞行器。 可弯曲翼可以向下弯曲，使得翼展可以减小以存储微型飞行器。 可弯曲翼可以由一层或多层材料形成，并且翼可以具有弯曲，使得翼的凹面朝向下方。 机翼可以基本上抵抗向上弯曲并且可以将提升力传递到微型飞行器的中心体。 此外，机翼可能通过对机翼的尖端施加力而严重地向下弯曲。 微型飞行器能够存储在小圆柱形管中，并且可以通过从管中简单地释放微型飞行器而从管展开。

公开(公告)号：US20020070313A1

公开(公告)日：2002-06-13

申请号：US10073828

申请日：2002-02-11

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

IPC: B64B001/20 ,  B64C001/00 ,  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.

公开(公告)号：US20020070312A1

公开(公告)日：2002-06-13

申请号：US10073518

申请日：2002-02-11

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

IPC: B64B001/20 ,  B64C001/00 ,  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：US11866164B2

公开(公告)日：2024-01-09

申请号：US16932138

申请日：2020-07-17

Applicant: SpyDar Sensors, Inc.

Inventor： Samuel Jacob Winkelstein

IPC: B64C29/00 ,  B64D27/24 ,  B64C39/02

CPC classification number: B64C29/0025 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/108 ,  B64C2201/162 ,  B64D27/24

Abstract: The present invention provides an aircraft design which incorporates a modular design including the use of one or more multi-motor assemblies where the motors are in series within the multi-motor assembly. Still further, the multi-motor assemblies may be configured to include modular motor assemblies or modular sections. Ultimately, the present invention provides an aircraft with the ability to easily assemble or expand the multi-motor assemblies and, in doing so, modify the characteristics of the aircraft. The modularity also enhances the ability to maintain the aircraft by enabling motors or the units housing each motor to easily be replaced.