公开(公告)号：US06817573B2

公开(公告)日：2004-11-16

申请号：US10186665

申请日：2002-07-02

Applicant: Richard George Harrison ,  Terry Prendergast ,  Geoffrey Salkeld ,  Darren Holdcroft

Inventor： Richard George Harrison ,  Terry Prendergast ,  Geoffrey Salkeld ,  Darren Holdcroft

IPC: B64C1324

CPC classification number: B64C39/024 ,  B64C29/0075 ,  B64C2201/086 ,  B64C2201/088 ,  B64C2201/102 ,  B64C2201/104 ,  B64C2201/121 ,  B64C2201/127 ,  B64C2201/128 ,  B64C2201/165 ,  B64C2201/187

Abstract: An aircraft 1 comprising interchangeable wings 5 detachedly connected to a fuselage 3, each wing 5 containing the fuel and flight systems 13,15 for engines 7 mounted to the wings 5, so that the fuselage 3 need contain no flight systems, simply a “bus” 23 for communication and the transfer of data between the wings.

Abstract translation: 飞机1包括分离地连接到机身3的可互换翼5，每个翼5包含燃料和飞行系统13,15，用于安装到翼5上的发动机7，使得机身3不需要包含飞行系统，简单地是“总线 “23”用于沟通和传递数据之间的翅膀。

公开(公告)号：US20040135031A1

公开(公告)日：2004-07-15

申请号：US10341206

申请日：2003-01-13

Applicant: BoXaiR Engineering LLC.

Inventor： John S. Stupakis

IPC: B64C001/00

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。

公开(公告)号：US20040118969A1

公开(公告)日：2004-06-24

申请号：US10600258

申请日：2003-06-20

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

IPC: B64B001/20 ,  B64C017/00

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：US06550717B2

公开(公告)日：2003-04-22

申请号：US09826424

申请日：2001-04-03

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

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

IPC: B64C100

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：US20020092949A1

公开(公告)日：2002-07-18

申请号：US09761076

申请日：2001-01-17

Applicant: Lockheed Martin Corporation

Inventor： Leland M. Nicolai

IPC: B64C037/02 ,  B64D005/00 ,  B64C035/00

CPC classification number: B64C35/005 ,  B60V1/08 ,  B64C39/024 ,  B64C2201/048 ,  B64C2201/086 ,  B64C2201/088 ,  B64C2201/102 ,  B64C2201/104 ,  B64C2201/127 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/162 ,  B64C2201/167 ,  B64C2201/187

Abstract: An anti-submarine warfare system includes an unmanned nullsea-sittingnull aircraft housing submarine detecting equipment, the aircraft including a body portion having a catamaran configuration adapted for stably supporting the body portion when sitting in water, the body portion including a fuselage and laterally disposed sponsons connected to the fuselage via platforms, and submarine detecting equipment housed within the fuselage and adapted to be electronically linked to sonobuoys disposed in adjacent water locations.

Abstract translation: 一种反潜战系统包括一个无人“海坐”飞机舱潜艇检测设备，该飞机包括一个主体部分，该主体部分具有适于在坐在水中时稳定地支撑主体部分的双体船结构，该主体部分包括机身和横向 通过平台连接到机身的安装支架，以及容纳在机身内的潜艇检测设备，并且适于与设置在相邻水位的声波电子电子连接。

公开(公告)号：US06131854A

公开(公告)日：2000-10-17

申请号：US131136

申请日：1998-08-07

Applicant: Leland M. Nicolai

Inventor： Leland M. Nicolai

IPC: B64C39/02 ,  B64F1/04 ,  B64F1/22

CPC classification number: B64F1/04 ,  B64C39/024 ,  B64F1/222 ,  B64C2201/086 ,  B64C2201/187

Abstract: A system for servicing unmanned aircraft includes an aircraft service area located adjacent a landing strip, a track and follower mechanism, and a plurality of stations disposed along the track and follower mechanism including a first station having apparatus for connecting the aircraft to the track and follower mechanism, a second station for reading information from and to a computer located onboard the aircraft, a third station for removing old weapons from and securing new weapons to the aircraft, and a fourth station for refueling the aircraft. The aircraft is able to move under its own power from the runway to the aircraft service area following landing on the runway, and from the aircraft service area to the runway for takeoff following servicing of the aircraft. A differential GPS apparatus is used to navigate the aircraft from the runway to the aircraft service area and the apparatus for connecting the aircraft to the track means at the first station includes apparatus for engaging a front wheel of the aircraft.

Abstract translation: 用于维修无人飞行器的系统包括邻近着陆带，轨道和从动机构以及沿着轨道和从动机构设置的多个台站的飞机服务区域，包括具有用于将飞行器连接到轨道和跟随器的装置的第一站 机构，用于从飞机上的计算机读取信息的第二站，用于从飞机上移除旧武器并将新武器固定的第三站以及用于加油的第四站。 飞机能够在跑道上着陆后从飞机运行到飞机服务区，从飞机服务区到飞机跑道，以便飞机维修后起飞。 使用差分GPS装置将飞机从跑道导航到飞机服务区域，并且用于将飞行器连接到第一站处的轨道装置的装置包括用于接合飞行器前轮的装置。

公开(公告)号：US5941478A

公开(公告)日：1999-08-24

申请号：US66980

申请日：1998-04-28

Applicant: Hugh Schmittle

Inventor： Hugh Schmittle

IPC: B64C1/00 ,  B64C3/38 ,  B64C29/00 ,  B64C39/02 ,  B64C39/04

CPC classification number: B64C39/04 ,  B64C1/00 ,  B64C29/0033 ,  B64C3/385 ,  B64C39/024 ,  B64C2201/086 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/127 ,  B64C2201/165 ,  B64C2201/187

Abstract: A mechanism for quickly removing and installing the free wings and/or the tail booms of a freewing aircraft to the fuselage. The fuselage includes a free wing cross tube extending transversely through the fuselage at the spanwise axis, and each of the left and right free wings includes a support tube disposed therein, also along the spanwise axis, with a portion of the wing structural tube being received within the fuselage cross tube. A quick-release pin is insertable in holes disposed in both the structural tube and the cross tube when the holes are placed in alignment. A second cross tube extends transversely through the rear end of the fuselage at the tail boom pivot axis. At least a portion of each tail boom member is disposed in surrounding relationship to the cross tube. In a preferred embodiment, a quick-release pin is insertable in holes disposed in both the tail boom member portion and the cross tube when the holes are placed in alignment.

Abstract translation: 用于快速拆卸和安装自由翼的自由翼和/或尾翼到机身的机构。 该机身包括横跨翼展横向穿过机身的自由翼横管，并且左右自由翼中的每一个还包括沿着翼展方向轴线设置在其中的支撑管，翼结构管的一部分被接收 在机身横管内。 当孔对准时，快速释放销可插入设置在结构管和横管中的孔中。 第二横管在尾臂枢轴上横向延伸穿过机身的后端。 每个尾臂构件的至少一部分设置成与横管的关系。 在优选实施例中，当孔对准时，快速释放销可插入设置在尾梁构件部分和横管中的孔中。

公开(公告)号：US5890441A

公开(公告)日：1999-04-06

申请号：US709488

申请日：1996-09-06

Applicant: Johnny Swinson, deceased ,  by Sueanne Walker, executrix ,  Terry J. James

Inventor： Johnny Swinson, deceased ,  by Sueanne Walker, executrix ,  Terry J. James

IPC: B64C29/00 ,  B64C39/02 ,  B64C29/04

CPC classification number: B64C39/024 ,  B64C29/0025 ,  B64C2201/027 ,  B64C2201/044 ,  B64C2201/086 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/126 ,  B64C2201/127 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/162 ,  B64C2201/185 ,  B64C2201/187

Abstract: A semiautonomously directed, autonomously controlled, gyroscopically stabilized, horizontal or vertical take off and landing (HOVTOL) flying apparatus employing two vertical lift devices equally and longitudinally spaced from the center of gravity of the apparatus; continuously integrated with a drive train apparatus, optional single or multiple power means; congruously connected thereto horizontal thrust devices. Integral to the vertical lift devices; pitch axis control devices situated at the exhaust orifices therein to vector said devices exhaust slip stream by a autonomous flight control system providing pitch stability. The autonomous flight control system providing continuously all flight control of the apparatus and said system being interfaced to a semiautonomous flight director device providing discrete flight direction function codes thereto. The combined effect of the apparatus is: When the power system rotates; coincident rotation of the drive train causes the vertical lift apparatus and horizontal thrust apparatus to counter rotate at right angles simultaneously providing both vertical lift and gyroscopic roll stability and simultaneously providing both horizontal thrust and gyroscopic yaw stability during flight; the continuous control thereof being accomplished by the autonomous flight control system and the directional steering, and function thereof in four axis effected by the semiautonomous flight director device which provides discrete flight function codes to the autonomous flight control system so as to disallow the initiation of negative flight maneuvers and/or functions providing for the safe unskilled pilot operation of the apparatus or any aircraft employing a autopilot having a autonomous digital flight control system.

Abstract translation: 使用两个垂直升降装置的半自主导向的，自主控制的，陀螺稳定的，水平或垂直的起飞和着陆（HOVTOL）飞行装置，该装置与装置的重心相等地纵向间隔开; 与传动系统设备连续集成，可选单个或多个动力装置; 一致地连接到水平推力装置。 与垂直升降装置成一体; 位于其排气孔处的俯仰轴控制装置通过提供俯仰稳定性的自主飞行控制系统向所述装置排出滑移流。 该自主飞行控制系统连续地提供装置的所有飞行控制，并且所述系统正在连接到半自主飞行指导装置，从而向其提供离散的飞行方向功能代码。 该装置的组合效果是：当电力系统旋转时; 驱动系统的一致旋转导致垂直提升装置和水平推力装置逆时针旋转，同时提供垂直提升和陀螺辊稳定性，同时在飞行期间同时提供水平推力和陀螺仪横摆稳定性; 其连续控制由自主飞行控制系统和定向转向完成，并且其功能由四通道由半自主飞行指导装置实现，该自主飞行控制系统向自主飞行控制系统提供离散飞行功能代码，从而不允许启动负 飞行机动和/或功能，提供设备的安全非技术型飞行员操作或使用具有自主数字飞行控制系统的自动驾驶仪的任何飞行器。

公开(公告)号：US5560568A

公开(公告)日：1996-10-01

申请号：US261901

申请日：1994-06-15

Applicant: Hugh Schmittle

Inventor： Hugh Schmittle

IPC: B64C3/38 ,  B64C29/00 ,  B64C29/02 ,  B64C39/02 ,  B64C39/04

CPC classification number: B64C29/02 ,  B64C29/0033 ,  B64C3/385 ,  B64C39/024 ,  B64C39/04 ,  B64C2201/044 ,  B64C2201/046 ,  B64C2201/084 ,  B64C2201/086 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/182 ,  B64C2201/187 ,  B64D2201/00 ,  Y10S446/901

Abstract: Apparatus and method for recovering and arresting an aircraft on a floating platform is disclosed. The aircraft has a fuselage, a wing, and a source of propulsion for propelling the aircraft in flight. During landing approach, an inflatable cushion attached to the fuselage is deployed below the fuselage via inflation. In the inflated condition, a fastening material disposed on a downward facing surface of the cushion is thereby adapted to adhesively contact the floating platform deck so that the forward motion of the aircraft is slowed and arrested. In the preferred embodiment, the fastening material is one of male or female VELCRO.RTM. which is adapted to mate with corresponding VELCRO.RTM. material covering the platform deck.

Abstract translation: 公开了一种用于在浮动平台上恢复和拦截飞行器的装置和方法。 这架飞机有一个机身，一个机翼和一个推进的来源，用于在飞行中推进飞机。 在着陆过程中，通过充气将附着在机身上的充气垫部署在机身的下方。 在充气状态下，设置在缓冲垫的向下的表面上的紧固材料因此适于与浮动平台甲板粘合地接触，使得飞行器的向前运动变慢并且被阻止。 在优选实施例中，紧固材料是男性或女性VELCRO TM之一，其适于与覆盖平台甲板的相应的VELCRO TM材料配合。