公开(公告)号：US07487937B2

公开(公告)日：2009-02-10

申请号：US11394018

申请日：2006-03-30

Applicant: Peter G. Ifju ,  Bret K. Stanford ,  Roberto Albertani

Inventor： Peter G. Ifju ,  Bret K. Stanford ,  Roberto Albertani

IPC: B64C3/38 ,  B64C3/52 ,  B64C1/26 ,  B64C31/028

CPC classification number: B64C3/18 ,  B64C3/42 ,  B64C3/44 ,  B64C3/52 ,  B64C39/028 ,  B64C2201/028 ,  Y02T50/14

Abstract: An airfoil for a micro air vehicle that includes components enabling the airfoil to adjust the angle of attack (AOA) of the airfoil in response to wind gusts, thereby enabling the airfoil to provide smooth flight. The airfoil may include a first compliant region positioned between an inboard section and a first outboard section and may include a second compliant region between a second outboard section and the inboard section. The compliant regions enable the first and second outboard sections to bend about a leading edge section and move relative to an inboard section. This action creates smoother flight due to numerous aerodynamic advantages such as a change in the angle of attack and improved wind gust rejection due to adaptive washout as a result of the airfoil flexing, twisting and decambering.

Abstract translation: 一种用于微型飞行器的翼型件，其包括能够使翼型件响应于阵风而调节翼型的迎角（AOA）的部件，从而使翼型件能够提供平稳的飞行。 翼型件可以包括位于内侧部分和第一外侧部分之间的第一顺应性区域，并且可以包括第二外侧部分和内侧部分之间的第二顺应区域。 顺从区域使得第一和第二外侧部分能够围绕前缘部分弯曲并且相对于内侧部分移动。 由于翼型的弯曲，扭转和回旋的结果，由于许多空气动力学优点，例如迎角的变化和改善的阵风排除，由于适应性冲洗，这种动作产生更平滑的飞行。

公开(公告)号：US20090014596A1

公开(公告)日：2009-01-15

申请号：US12058466

申请日：2008-03-28

Applicant: Jerome Pearson ,  Gerald M. Gregorek ,  Harry B. Wykes

Inventor： Jerome Pearson ,  Gerald M. Gregorek ,  Harry B. Wykes

IPC: B64C3/50 ,  B64C3/38

CPC classification number: B64C39/024 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/102

Abstract: A long endurance powered aircraft includes a central spar, a propeller coupled to the central spar, and a wing coupled to the central spar. The wing includes a first spar and an opposing second spar. Leading ends of the first and second spars are coupled to the central spar and trailing ends of the first and second spars selectively diverge from the central spar to define a morphing wing configured change shape to optimize aircraft flight parameters in response to changes in at least one flight condition.

Abstract translation: 长寿命的动力飞机包括一个中心翼梁，一个连接到中央翼梁的螺旋桨，以及一个与中心翼梁连接的翼。 翼包括第一翼梁和相对的第二翼梁。 第一和第二翼梁的前端连接到第一和第二翼梁的中心翼梁和后端，从中心翼梁选择性地分离，以限定变形翼构造的变形形状，以响应于至少一个 飞行情况。

公开(公告)号：US20070252034A1

公开(公告)日：2007-11-01

申请号：US11603815

申请日：2006-11-21

Applicant: Brian McGeer ,  Andreas von Flotow ,  Cory Roeseler

Inventor： Brian McGeer ,  Andreas von Flotow ,  Cory Roeseler

IPC: B64F1/04

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.

公开(公告)号：US07281681B2

公开(公告)日：2007-10-16

申请号：US10600258

申请日：2003-06-20

Applicant: Paul B. MacCready ,  Bart D. Hibbs ,  Robert F. Curtin

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

IPC: B64D27/00

CPC classification number: B64C1/26 ,  B64C3/10 ,  B64C3/14 ,  B64C9/24 ,  B64C39/024 ,  B64C39/10 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/086 ,  B64C2201/104 ,  B64C2201/122 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/187 ,  B64D27/02 ,  B64D27/24 ,  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 fuel cell compresses ambient air for an oxidizer, and operates with the fuel and oxidizer at pressures below one atmosphere. 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。 燃料电池压缩氧化剂的环境空气，并在低于一个大气压的燃料和氧化剂下操作。 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：US20050178885A1

公开(公告)日：2005-08-18

申请号：US10758294

申请日：2004-01-15

Applicant: Clifford Jackson

Inventor： Clifford Jackson

IPC: B64C3/56 ,  B64C7/00 ,  B64C13/20 ,  B64C39/02

CPC classification number: B64C39/024 ,  B64C2201/028 ,  B64C2201/104 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/165

Abstract: Methods and apparatuses for supporting aircraft components, including actuators are disclosed. An apparatus in accordance with one embodiment of the invention includes an actuator housing having an actuator receptacle that securely yet releasably receives an actuator. The actuator receptacle can include conformal walls that conform at least in part to the shape of the actuator and can accordingly squeeze the actuator and properly align the actuator. At least one of the actuator walls can further include a projection that is releasably received in a corresponding recess of the actuator. One of both of these features can releasably secure the actuator relative to the aircraft, reducing and/or eliminating the likelihood that the actuator will be misaligned and/or mispositioned relative to the aircraft during installation and/or replacement.

Abstract translation: 公开了用于支持飞机部件（包括致动器）的方法和装置。 根据本发明的一个实施例的装置包括具有可靠地可释放地接收致动器的致动器插座的致动器壳体。 致动器容器可以包括至少部分地符合致动器的形状的适形壁，并且可以相应地挤压致动器并且正确对准致动器。 致动器壁中的至少一个还可以包括可释放地容纳在致动器的相应凹部中的突起。 这两个特征之一可以相对于飞行器可释放地固定致动器，减少和/或消除在安装和/或更换期间致动器相对于飞行器不对准和/或错位的可能性。

公开(公告)号：US06931247B2

公开(公告)日：2005-08-16

申请号：US09789450

申请日：2001-02-20

Applicant: Earl C. Cox ,  Kyle D. Swanson

Inventor： Earl C. Cox ,  Kyle D. Swanson

IPC: B64C39/00 ,  B64C3/42 ,  B64C3/52 ,  B64C15/02 ,  B64C39/02 ,  B64C39/10 ,  B64D27/24 ,  B64D31/06 ,  G05D1/00 ,  H04B7/185 ,  H04Q7/20

CPC classification number: B64C3/42 ,  B64C3/52 ,  B64C15/02 ,  B64C39/024 ,  B64C39/10 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/102 ,  B64C2201/122 ,  B64C2201/126 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/165 ,  B64D27/24 ,  B64D31/06 ,  B64D2211/00 ,  G05D1/0022 ,  G05D1/0077 ,  H04B7/18504 ,  Y02T50/12 ,  Y02T50/14 ,  Y02T50/44 ,  Y02T50/55 ,  Y02T50/62

Abstract: This disclosure provides a solar rechargeable aircraft that is inexpensive to produce, is steerable, and can remain airborne almost indefinitely. The preferred aircraft is a span-loaded flying wing, having no fuselage or rudder. Traveling at relatively slow speeds, and having a two-hundred foot wingspan that mounts photovoltaic cells on most all of the wing's top surface, the aircraft uses only differential thrust of its eight propellers to turn. Each of five segments of the wing has one or more motors and photovoltaic arrays, and produces its own lift independent of the other segments, to avoid loading them. Five two-sided photovoltaic arrays, in all, are mounted on the wing, and receive photovoltaic energy both incident on top of the wing, and which is incident also from below, through a bottom, transparent surface. The aircraft includes hinges and actuators capable of providing an adjustable dihedral for the wing. The actuators can be motors or control surfaces. Alternately, the actuators can be movable masses within the wing, which may be capable of deforming the wing to alter the aerodynamics of the wing, and thereby actuate the hinges. Because of wing dihedral, the aircraft includes motors both above and below the center of drag, and the aircraft uses differential thrust to control aircraft pitch. The aircraft has a wide variety of applications, which include serving as a long term high altitude platform that serves to link a ground station using radio wave signals and a satellite using optical signals.

Abstract translation: 本公开提供了一种太阳能可再充电飞机，其生产便宜，是可操纵的，并且几乎可以无限期地保持空中飞行。 首选飞机是一个装有跨距的飞翼，没有机身或方向舵。 以相对较慢的速度行驶，并且拥有两百英尺的翼展，将光伏电池安装在大部分机翼的顶部表面上，飞机只使用其八个螺旋桨的差动推力来转动。 翼的五个部分中的每一个具有一个或多个电动机和光伏阵列，并且独立于其它部分产生其自身的升降机，以避免加载它们。 五个双面光伏阵列总体上安装在机翼上，并且接收能量入射到机翼的顶部并且从下方入射的光能通过底部的透明表面。 飞机包括铰链和致动器，能够为机翼提供可调节的二面体。 执行器可以是电机或控制面。 或者，致动器可以是机翼内的可移动质量块，其可以使机翼变形以改变机翼的空气动力学，从而致动铰链。 由于机翼二面体，飞机包括在阻力中心上方和下方的电机，飞机使用差速推力来控制飞机俯仰。 该飞机具有广泛的应用，其中包括作为长期高空平台，用于使用无线电波信号连接地面站和使用光信号的卫星。

公开(公告)号：US06892981B2

公开(公告)日：2005-05-17

申请号：US10408981

申请日：2003-04-08

Applicant: Jay Lipeles

Inventor： Jay Lipeles

IPC: B64C3/30 ,  B64C3/56 ,  B64C39/02 ,  B64C39/10 ,  B64D33/04 ,  B64C39/00

CPC classification number: B64C39/024 ,  B64C3/30 ,  B64C3/56 ,  B64C39/10 ,  B64C2201/028 ,  B64C2201/044 ,  B64C2201/046 ,  B64C2201/105 ,  B64C2201/127 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/203 ,  B64C2201/22 ,  B64D33/04 ,  B64D2033/045

Abstract: The Duffel Bag Airplane is an inflatable flying wing unmanned airborne vehicle (UAV). The fuselage will house everything but the wings. The wing can be rolled up around the fuselage into a small package when deflated for easy transportation, such as by being carried in a duffle bag. Fabric construction, a small internal combustion engine with cooled exhaust, and wing warping controls combine to make the airplane inexpensive and extremely stealthy. All the usual signatures have been suppressed, which allow it to be used to make observations from close range under combat conditions. Control of this airplane is accomplished by warping the wings and is supplemented with stability augmentation.

Abstract translation: Duffel Bag飞机是一种充气飞翼无人机载机（UAV）。 机身将会容纳除翅膀之外的所有东西。 机翼可以卷绕在机身周围，当放气以便于运输时，例如通过携带在行李箱中，成为小包装。 织物结构，具有冷却排气的小型内燃机和机翼翘曲控制相结合，使飞机廉价而且非常隐蔽。 所有通常的签名已经被压制，这允许它用于在战斗条件下从近距离观察。 这架飞机的控制是通过扭转机翼来实现的，并补充了稳定性增强。

公开(公告)号：US20040245379A1

公开(公告)日：2004-12-09

申请号：US10456176

申请日：2003-06-06

Applicant: Northrop Grumman Corporation

Inventor： Walter D. Clark

IPC: B64C001/00

CPC classification number: B64C1/0009 ,  B64C5/08 ,  B64C9/12 ,  B64C9/32 ,  B64C9/323 ,  B64C9/34 ,  B64C39/024 ,  B64C2001/0045 ,  B64C2039/105 ,  B64C2201/028 ,  B64C2201/127 ,  B64C2201/22 ,  Y02T50/12 ,  Y02T50/32 ,  Y02T50/44

Abstract: An aircraft with swept back wings and spoilers inlaid into the top surface near the tips of the wings. The aircraft also includes an elevator formed in the center back portion of the aircraft, which is also aft of the spoilers. It is aft to allow an auxiliary control in the elevator signal to cancel the unwanted pitch up moment caused by the spoilers only going up and being aft of the center of gravity of the aircraft. Roll is achieved with these spoilers by the direct action of the lift dumping on one side or the other and by taking advantage of the transformation of yaw into roll by the sweep back of the wings.

Abstract translation: 一架飞机将翅膀和扰流板扫到靠近机翼尖端的顶面。 飞机还包括形成在飞行器的中心后部的电梯，其也是扰流板的后部。 这是为了允许电梯信号中的辅助控制来消除由扰流板仅上升并且处于飞机重心的后方引起的不期望的俯仰上升时刻。 通过电梯倾倒在一侧或另一侧上的直接作用，并且通过翼的扫掠利用偏转转动的优点，利用这些扰流板实现滚动。

公开(公告)号：US5289994A

公开(公告)日：1994-03-01

申请号：US855254

申请日：1992-03-23

Applicant: Juan Del Campo Aguilera

Inventor： Juan Del Campo Aguilera

IPC: B64C27/22 ,  B64C29/02 ,  B64C39/02 ,  B64C29/00

CPC classification number: B64C27/22 ,  B64C29/02 ,  B64C39/024 ,  B64C2201/028 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/165

Abstract: It works like a helicopter in vertical flight or like an airplane in horizontal flight, being able to land accurately on a small area. It is equipped with a rotor, a couple of wings fitted with ailerons and other control surfaces actuated differentially, with support wheels at their ends. It has a vertical stabilizer at the end of which there is a wheel. It has a horizontal stabilizer with elevators that are actuated simultaneously or differentially. It incorporates a propeller ahead of the rotor.

Abstract translation: 它像垂直飞行中的直升机一样工作，或像水平飞行中的飞机一样工作，能够在一个小区域上准确地着陆。 它配备了一个转子，一对翅膀配有副翼和其他控制面差速驱动，其支撑轮在其末端。 它有一个垂直的稳定器，其末端有一个轮子。 它具有水平稳定器，其具有同时或差异地致动的电梯。 它在转子前方装有螺旋桨。

公开(公告)号：US20190185155A1

公开(公告)日：2019-06-20

申请号：US16280021

申请日：2019-02-19

Applicant: DeLorean Aerospace, LLC

Inventor： Paul J. DeLorean

IPC: B64C29/00 ,  B64C39/04 ,  B64C39/10 ,  B64C39/12 ,  B64D27/24 ,  B64C27/32

CPC classification number: B64C29/0033 ,  B64C27/32 ,  B64C39/04 ,  B64C39/10 ,  B64C39/12 ,  B64C2201/021 ,  B64C2201/028 ,  B64D27/24 ,  Y02T50/12 ,  Y02T50/64

Abstract: The disclosure generally pertains to a vertical take-off and landing (VTOL) aircraft comprising a fuselage and at least one fixed wing. The aircraft may include at least two powered rotors located generally along a longitudinal axis of the fuselage. The rotor units may be coupled to the fuselage via a rotating chassis, which allows the rotors to provide directed thrust by movement of the rotor units about at least one axis. The VTOL aircraft may include instructions to perform a degraded rotor landing protocol. The degraded rotor landing protocol may include adjusting a power to an operable rotor unit to control a rate of descent and/or slow a rate of acceleration toward a landing surface. The VTOL aircraft may be configured to impact the landing surface from a substantially vertical configuration, and adjust a thrust vector to cause the aircraft to come to rest in a generally upright configuration.