公开(公告)号：US08800936B2

公开(公告)日：2014-08-12

申请号：US13007515

申请日：2011-01-14

Applicant: Martyn Cowley ,  Matthew Todd Keennon

Inventor： Martyn Cowley ,  Matthew Todd Keennon

IPC: G05D1/00 ,  G05D1/06 ,  G05D1/12 ,  B64C11/08

CPC classification number: G05D1/0676 ,  B64C11/002 ,  B64C11/04 ,  B64C11/08 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/086 ,  B64C2201/104 ,  B64C2201/141 ,  B64C2201/187

Abstract: An air vehicle configured to augment effective drag to change the rate of descent of the air vehicle in flight via propeller shaft rotation direction reversal, i.e., thrust reversal.

Abstract translation: 一种空中飞行器，其构造成增加有效阻力，以经由传动轴转动方向反转（即，推力反转）来改变飞行中的空中飞行器的下降速率。

公开(公告)号：US08141819B2

公开(公告)日：2012-03-27

申请号：US12100252

申请日：2008-04-09

Applicant: Keith M. Brock

Inventor： Keith M. Brock

IPC: B64C1/26 ,  B64C3/18

CPC classification number: B64C39/024 ,  B64C2201/021 ,  B64C2201/086

Abstract: Methods and apparatus for aircraft according to various aspects of the present invention operate in conjunction with a fuselage and a wing. The fuselage may be configured to generate lift in response to airflow over the fuselage. In addition, the fuselage may have at least one hole defined therethrough. A spar may be disposed through the hole and extend into at least a portion of the wing and at least a portion of the fuselage. The spar may connect the fuselage to the wings.

Abstract translation: 根据本发明的各个方面的用于飞行器的方法和装置与机身和机翼结合操作。 机身可以配置成响应于机身上的气流产生升力。 此外，机身可以具有穿过其中限定的至少一个孔。 翼梁可以穿过孔布置并延伸到机翼的至少一部分和机身的至少一部分。 翼梁可以将机身连接到机翼上。

公开(公告)号：US08108085B2

公开(公告)日：2012-01-31

申请号：US13110692

申请日：2011-05-18

Applicant: Kenneth E. Builta ,  James E. Harris ,  Bryan P. Honza ,  Jeffrey W. Epp ,  Kynn J. Schulte

Inventor： Kenneth E. Builta ,  James E. Harris ,  Bryan P. Honza ,  Jeffrey W. Epp ,  Kynn J. Schulte

IPC: G06F17/00 ,  B64C13/00

CPC classification number: B64C39/024 ,  B64C13/20 ,  B64C2201/021 ,  B64C2201/086 ,  B64C2201/108 ,  B64C2201/141 ,  B64C2201/165 ,  B64C2201/187 ,  B64C2201/205 ,  G05D1/0027 ,  G05D1/0684

Abstract: A system for controlling flight of an aircraft has sensors, a receiver, and a digital control system, all of which are carried aboard the aircraft. The sensors determine the position of the aircraft relative to the earth and the inertial movement of the aircraft. The receiver receives transmitted data communicating the position and movement of a reference vehicle relative to the earth. The control system calculates the position and velocity of the aircraft relative to the reference vehicle using the data from the sensors and the receiver and then commands flight control devices on the aircraft for maneuvering the aircraft in a manner that maintains a selected position and/or velocity relative to the reference vehicle. The system allows use of a graphical or tactile user interfaces.

Abstract translation: 用于控制飞机飞行的系统具有传感器，接收器和数字控制系统，所有这些系统都携带在飞行器上。 传感器确定飞机相对于地球的位置和飞机的惯性运动。 接收器接收传送参考车辆相对于地球的位置和运动的传送数据。 控制系统使用来自传感器和接收器的数据来计算飞机相对于参考车辆的位置和速度，然后命令飞机上的飞行控制装置以维持选定位置和/或速度的方式操纵飞行器 相对于参考车辆。 该系统允许使用图形或触觉的用户界面。

公开(公告)号：US20110270474A1

公开(公告)日：2011-11-03

申请号：US13110692

申请日：2011-05-18

Applicant: Kenneth E. Builta ,  James E. Harris ,  Bryan P. Honza ,  Jeffrey W. Epp ,  Kynn J. Schulte

Inventor： Kenneth E. Builta ,  James E. Harris ,  Bryan P. Honza ,  Jeffrey W. Epp ,  Kynn J. Schulte

IPC: G05D1/00

CPC classification number: B64C39/024 ,  B64C13/20 ,  B64C2201/021 ,  B64C2201/086 ,  B64C2201/108 ,  B64C2201/141 ,  B64C2201/165 ,  B64C2201/187 ,  B64C2201/205 ,  G05D1/0027 ,  G05D1/0684

Abstract: A system for controlling flight of an aircraft has sensors, a receiver, and a digital control system, all of which are carried aboard the aircraft. The sensors determine the position of the aircraft relative to the earth and the inertial movement of the aircraft. The receiver receives transmitted data communicating the position and movement of a reference vehicle relative to the earth. The control system calculates the position and velocity of the aircraft relative to the reference vehicle using the data from the sensors and the receiver and then commands flight control devices on the aircraft for maneuvering the aircraft in a manner that maintains a selected position and/or velocity relative to the reference vehicle. The system allows use of a graphical or tactile user interfaces.

Abstract translation: 用于控制飞机飞行的系统具有传感器，接收器和数字控制系统，所有这些系统都携带在飞行器上。 传感器确定飞机相对于地球的位置和飞机的惯性运动。 接收器接收传送参考车辆相对于地球的位置和运动的传送数据。 控制系统使用来自传感器和接收器的数据来计算飞机相对于参考车辆的位置和速度，然后命令飞行器上的飞行控制装置以维持选定位置和/或速度的方式操纵飞行器 相对于参考车辆。 该系统允许使用图形或触觉的用户界面。

公开(公告)号：US07806365B2

公开(公告)日：2010-10-05

申请号：US11428706

申请日：2006-07-05

Applicant: Gerald D. Miller ,  Wesley Moore ,  Adrian Viisoreanu ,  Russell W. Morris ,  Ronald W. Davidson ,  Shailesh Atreya ,  Albert D. Olsen ,  William Bigbee-Hansen

Inventor： Gerald D. Miller ,  Wesley Moore ,  Adrian Viisoreanu ,  Russell W. Morris ,  Ronald W. Davidson ,  Shailesh Atreya ,  Albert D. Olsen ,  William Bigbee-Hansen

IPC: B64D27/00

CPC classification number: B64D37/30 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/086 ,  B64C2201/127 ,  B64C2201/165 ,  Y02T10/16 ,  Y02T50/44 ,  Y02T90/44

Abstract: Hydrogen powered air vehicles that in some embodiments can fly with very long endurance (10 or more days) at altitudes over 60,000 ft carrying payloads of up to 2,000 pounds. Embodiments may include features such as large wingspan relative to fuselage and an all composite or partial composite structure for light weight and strength. The aircraft of the invention use one or more internal combustion engines adapted for hydrogen combustion, each engine driving propellers. The hydrogen fuel is stored on board in containers, located within the fuselage, as a cryogenic liquid, and is vaporized in a heat exchanger before delivery to the internal combustion engine.

Abstract translation: 在一些实施例中的氢动力空中飞行器可以在高达60,000英尺的高度上以非常长的耐久性（10或更多天）飞行，承载高达2,000磅的有效载荷。 实施例可以包括相对于机身的大翼展以及用于轻量化和强度的全复合或部分复合结构的特征。 本发明的飞机使用一个或多个适于氢燃烧的内燃机，每个发动机都驱动螺旋桨。 氢燃料被储存在位于机身内的容器中，作为低温液体，并且在输送到内燃机之前在热交换器中蒸发。

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：US07261257B2

公开(公告)日：2007-08-28

申请号：US10996799

申请日：2004-11-23

Applicant: Elie Helou, Jr.

Inventor： Elie Helou, Jr.

IPC: B64C1/22

CPC classification number: B64C1/10 ,  B64C1/00 ,  B64C1/061 ,  B64C1/065 ,  B64C39/02 ,  B64C39/024 ,  B64C2001/0072 ,  B64C2201/021 ,  B64C2201/048 ,  B64C2201/086 ,  B64C2201/104 ,  B64C2201/128 ,  B64C2201/162 ,  B64C2201/167 ,  B64C2211/00 ,  Y02T50/43

Abstract: An aircraft for carrying at least one rigid cargo container includes a beam structure with a forward fuselage attached to the forward end of the beam structure and an empennage attached to the rearward end of the beam structure. Wings and engines are mounted relative to the beam structure and a fairing creates a cargo bay able to receive standard sized intermodal cargo containers. Intermodal cargo containers of light construction and rigid structure are positioned within the cargo bay and securely mounted therein. The beam structure is designed to support flight, takeoffs and landings when the aircraft is empty but requires the added strength of the containers securely mounted to the beam structure when the aircraft is loaded. The aircraft is contemplated to be a drone.

Abstract translation: 用于承载至少一个刚性货物集装箱的飞机包括具有附接到梁结构的前端的前机身的梁结构和附接到梁结构的后端的后轮。 翼和发动机相对于梁结构安装，整流罩产生能够接收标准尺寸的联运货物集装箱的货舱。 轻型结构和刚性结构的多式联运集装箱定位在货舱内并牢固地安装在货舱内。 梁结构设计用于在飞机空置时支持飞行，起飞和着陆，但是当飞机加载时，需要将集装箱的强度牢固地安装到梁结构上。 飞机被认为是无人机。

公开(公告)号：US20070021878A1

公开(公告)日：2007-01-25

申请号：US10575223

申请日：2004-03-25

Applicant: Kenneth Builta ,  James Harris ,  Bryan Honza ,  Jeffrey Epp ,  Kynn Schulte

Inventor： Kenneth Builta ,  James Harris ,  Bryan Honza ,  Jeffrey Epp ,  Kynn Schulte

IPC: G06F17/00

CPC classification number: B64C39/024 ,  B64C13/20 ,  B64C2201/021 ,  B64C2201/086 ,  B64C2201/108 ,  B64C2201/141 ,  B64C2201/165 ,  B64C2201/187 ,  B64C2201/205 ,  G05D1/0027 ,  G05D1/0684

Abstract: A system for controlling flight of an aircraft has sensors (37, 43), a receiver (45), and a digital control system (57), all of which are carried aboard the aircraft. The sensors (37, 43) determine the position of the aircraft relative to the earth and the inertial movement of the aircraft. The receiver (45) receives transmitted data (51, 55) communicating the position and movement of a reference vehicle relative to the earth. The control system (57) calculates the position and velocity of the aircraft relative to the reference vehicle using the data from the sensors (37, 43) and the receiver (45) and then commands flight control devices (33) on the aircraft for maneuvering the aircraft in a manner that maintains a selected position and/or velocity relative to the reference vehicle. The system allows use of a graphical or tactile user interfaces.

Abstract translation: 用于控制飞机飞行的系统具有传感器（37,43），接收器（45）和数字控制系统（57），所有这些都被携带在飞行器上。 传感器（37,43）确定飞行器相对于地球的位置和飞行器的惯性运动。 接收器（45）接收传送参考车辆相对于地球的位置和移动的传送数据（51,55）。 控制系统（57）使用来自传感器（37,43）和接收器（45）的数据来计算飞行器相对于参考车辆的位置和速度，然后命令飞行器上的飞行控制装置（33）进行操纵 飞行器以相对于参考车辆保持选定位置和/或速度的方式。 该系统允许使用图形或触觉的用户界面。

公开(公告)号：US20060006281A1

公开(公告)日：2006-01-12

申请号：US11098529

申请日：2005-04-05

Applicant: Omri Sirkis

Inventor： Omri Sirkis

IPC: B64C25/56

CPC classification number: B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/048 ,  B64C2201/086 ,  B64C2201/104 ,  B64C2201/167 ,  B64C2201/187

Abstract: There is provided an Unmanned Air Vehicle (UAV) including an engine and an airframe, including means for performing a deep stall maneouvre; at least one inflatable sleeve connected or connectable to the airframe, and means for inflating the sleeve during flight, wherein the inflated sleeve extends along the lower side of the airframe so as to protect same during deep stall landing. A method for operating an Unmanned Air Vehicle (UAV), including an engine and an airframe is also provided.

Abstract translation: 提供了包括发动机和机身在内的无人机（UAV），其中包括进行深层失速行动的手段; 连接或连接到机身的至少一个可充气套筒，以及用于在飞行期间使套筒充气的装置，其中，所述膨胀的套筒沿着机身的下侧延伸，以便在深度失速着陆期间保护该套筒。 还提供了一种用于操作无人机（UAV）的方法，包括发动机和机身。

公开(公告)号：US06948681B2

公开(公告)日：2005-09-27

申请号：US10341206

申请日：2003-01-13

Applicant: John S. Stupakis

Inventor： John S. Stupakis

IPC: B64C39/02 ,  B64C1/00

CPC classification number: B64C39/024 ,  B64C39/02 ,  B64C2201/048 ,  B64C2201/086 ,  B64C2201/104 ,  B64C2201/128 ,  B64C2201/141 ,  B64C2201/165 ,  B64C2201/187 ,  B64C2211/00 ,  B64D2011/0046 ,  Y10S244/903

Abstract: A modular automated air transport system comprising an unmanned autonomous aircraft having a selectively detachable control systems portion and a structural air frame portion, wherein the structural air frame portion contains an interior cargo hold, aerodynamic members having control surfaces and at least one propulsion device attached to the structural air frame portion; and wherein the control system portion includes a control computer for autonomously controlling the flight of said air transport system from one known location to a second known location.

Abstract translation: 一种模块化的自动航空运输系统，包括具有可选择地可拆卸的控制系统部分和结构空气框架部分的无人自主飞行器，其中结构空气框架部分包含内部货舱，具有控制表面的空气动力部件和至少一个推进装置 结构空气框架部分; 并且其中所述控制系统部分包括用于自主地控制所述空中运输系统从一个已知位置到第二已知位置的飞行的控制计算机。