公开(公告)号：US20050178916A1

公开(公告)日：2005-08-18

申请号：US11042731

申请日：2005-01-24

申请人： Mark Howe

发明人： Mark Howe

IPC分类号： B64D37/04 ,  B64D39/00 ,  B64D37/00

CPC分类号： B64D37/04 ,  B64D39/00 ,  Y10T137/86228

摘要： Auxiliary fuel tank systems for aircraft and methods for their manufacture and use. In one embodiment, an aircraft can include a fuselage, at least one engine, and a fuel system configured to distribute fuel to at least one of the engine and an aerial refueling manifold. The aircraft can further include an auxiliary fuel tank system operably coupled to the fuel system. The auxiliary fuel tank system can include a master tank assembly and at least one slave tank assembly. The master tank assembly can be removably installed in the fuselage, and can include a master tank body configured to hold fuel. The master tank body can be configured to pass through a door in the fuselage without disassembly. The slave tank assembly can be removably installed in the fuselage at least proximate to the master tank assembly, and can include a slave tank body configured to hold fuel.

公开(公告)号：US20050116109A1

公开(公告)日：2005-06-02

申请号：US10967127

申请日：2004-10-19

申请人： Jeremy Berard

发明人： Jeremy Berard

IPC分类号： B64D39/00 ,  G01N15/06

CPC分类号： B64D39/00

摘要： Procedure and device for optimizing the quantity of fuel transferred on an aircraft during at least one in-flight fuel transfer. The optimization device (1) comprises a means (3) for making a prediction to determine a first quantity corresponding to the quantity of fuel remaining on board the aircraft at a first flight point in the flight plan of the aircraft, taking into account the current status of the aircraft and the current flying conditions, a means (4) for making an estimation to determine a second quantity corresponding to the quantity of fuel enabling the aircraft to fly from said first flight point to a second flight point later in the flight plan, a means (5) for determining, from said first and second quantities, a third quantity corresponding to the quantity of fuel to be transferred at said first flight point, and display means (6) for presenting said third duly determined quantity to at least one pilot of the aircraft.

摘要翻译： 在至少一次飞行中燃料转移期间优化飞机上传输的燃料量的程序和装置。 优化装置（1）包括一个装置（3），用于进行预测以确定对应于在飞行器的飞行计划中的第一个飞行点在飞机上剩余的燃料量的第一数量，同时考虑到当前的 飞机的状态和当前的飞行状况，一种用于进行估计的装置（4），用于确定对应于飞行器数量的第二数量，使得飞行器能够在飞行计划中稍后从所述第一飞行点飞行到第二飞行点 ，用于根据所述第一和第二数量确定与在所述第一飞行点处要传送的燃料量相对应的第三数量的装置（5），以及用于将所述第三适当确定数量呈现至少 一架飞机飞行员。

公开(公告)号：US06889940B1

公开(公告)日：2005-05-10

申请号：US10768269

申请日：2004-01-29

申请人： Mark E. Howe

发明人： Mark E. Howe

IPC分类号： B64D37/04 ,  B64D39/00 ,  B64D37/00

CPC分类号： B64D37/04 ,  B64D39/00 ,  Y10T137/86228

摘要： Auxiliary fuel tank systems for aircraft and methods for their manufacture and use. In one embodiment, an aircraft can include a fuselage, at least one engine, and a fuel system configured to distribute fuel to at least one of the engine and an aerial refueling manifold. The aircraft can further include an auxiliary fuel tank system operably coupled to the fuel system. The auxiliary fuel tank system can include a master tank assembly and at least one slave tank assembly. The master tank assembly can be removably installed in the fuselage, and can include a master tank body configured to hold fuel. The master tank body can be configured to pass through a door in the fuselage without disassembly. The slave tank assembly can be removably installed in the fuselage at least proximate to the master tank assembly, and can include a slave tank body configured to hold fuel.

摘要翻译： 用于飞机的辅助燃料箱系统及其制造和使用方法。 在一个实施例中，飞行器可以包括机身，至少一个发动机和配置成将燃料分配到发动机和空中加油歧管中的至少一个的燃料系统。 飞机还可以包括可操作地连接到燃料系统的辅助燃料箱系统。 辅助燃料箱系统可以包括主油箱组件和至少一个从油箱组件。 主油箱组件可以可拆卸地安装在机身中，并且可以包括构造成保持燃料的主箱体。 主罐体可以配置成通过机身的门而不拆卸。 副油箱组件可以至少靠近主油箱组件可拆卸地安装在机身中，并且可以包括构造成保持燃料的副罐体。

公开(公告)号：US6142421A

公开(公告)日：2000-11-07

申请号：US231368

申请日：1999-01-13

申请人： Miles R. Palmer

发明人： Miles R. Palmer

IPC分类号： B64C39/02 ,  B64D1/22 ,  B64D37/04 ,  B64D37/06 ,  B64D37/12 ,  B64D39/00 ,  F42B15/00 ,  B64C39/00 ,  B64D37/02

CPC分类号： B64D37/12 ,  B64C39/024 ,  B64D1/22 ,  B64D37/04 ,  B64D37/06 ,  B64D39/00 ,  F42B15/00 ,  B64C2201/044 ,  B64C2201/084 ,  B64C2201/088 ,  B64C2201/105 ,  B64C2201/121 ,  B64C2201/126 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/205

摘要： A vehicle refueling system includes an aero vehicle and a fuel bladder system. The fuel bladder system includes a fuel bladder, a pickup loop of a predetermined loop size, a reel mechanism to retract at least one side of the pickup loop to reduce the loop size, a snag sensor to sense when the pickup loop has been hooked by the retractable hook, the snag sensor initiating the reel mechanism, a compass to sense the random orientation of the loop, a radio navigation receiver to sense a location of the loop, and a transmitter to transmit the random orientation and the location. The vehicle includes a fuselage, a retractable hook with a hook sensor to detect when a fuel bladder is hooked and the loop size has been reduced by the reel mechanism, a fuel bladder stowage chamber within the fuselage, a fuel intake tube capable of drawing fuel from the fuel bladder stowed in the stowage chamber, a retraction mechanism to retract the retractable hook, a fuel transfer mechanism to transfer fuel from the fuel bladder into an internal fuel tank, and a fuel bladder discard mechanism to discard the fuel bladder after the fuel has been drawn from the fuel bladder.

摘要翻译： 车辆加油系统包括航空车辆和燃料囊系统。 燃料囊系统包括燃料囊，预定环尺寸的拾取环，卷绕机构，用于缩回拾取环的至少一侧以减小环的尺寸;阻挡传感器，用于感测拾取环何时已被钩住 可伸缩钩，启动卷轴机构的阻塞传感器，用于感测环路的随机取向的罗盘，用于感测回路位置的无线电导航接收器，以及发送器，以发送随机取向和位置。 车辆包括机身，具有钩传感器的可伸缩钩，用于检测燃料囊何时被钩住，并且通过卷轴机构减小了环路尺寸，机身内部的燃料囊存放室，能够吸引燃料的燃料进入管 从装载在储存室中的燃料气囊，收回缩回钩的缩回机构，用于将燃料从燃料气囊输送到内部燃料箱中的燃料转移机构，以及在燃料之后废弃燃料气囊的燃料气体排出机构 已从燃油囊中抽出。

公开(公告)号：US6119985A

公开(公告)日：2000-09-19

申请号：US813476

申请日：1997-03-07

申请人： Mitchell B. Clapp ,  Robert M. Zubrin

发明人： Mitchell B. Clapp ,  Robert M. Zubrin

IPC分类号： B64C39/02 ,  B64D27/02 ,  B64D39/00 ,  B64G1/00 ,  B64G1/14 ,  B64G1/40 ,  B64G1/58 ,  B64G1/62

CPC分类号： B64G1/005 ,  B64C39/02 ,  B64D27/023 ,  B64D39/00 ,  B64G1/14 ,  B64G1/401 ,  B64G1/402 ,  B64G1/58 ,  B64G1/62 ,  F05B2220/50 ,  Y02T50/44

摘要： A reusable rocket airplane which may be utilized to launch satellites and other payloads into space. The airplane may also be used for rapid surface to surface flight. The reusable rocket airplane may be safely supplied with oxidizer in mid-air, achieve an altitude outside the Earth's atmosphere, and return safely to be used again. The rocket airplane utilizes unique concepts to secure its gas turbine engines for high speed flight, minimize fluid spillage during mid-air oxidizer transfer, as well as employs design features advantageous to the economical building and reuse of the rocket airplane.

摘要翻译： 一种可重复使用的火箭飞机，可用于将卫星和其他有效载荷发射到太空。 飞机也可用于快速的表面飞行。 可重复使用的火箭飞机可以在半空中安全地供应氧化剂，实现地球大气层外的高度，并安全返回再次使用。 火箭飞机利用独特的概念来确保其燃气涡轮发动机的高速飞行，使中空氧化器传输期间的流体溢出最小化，并且采用有利于经济建筑和火箭飞机重用的设计特征。

公开(公告)号：US5785276A

公开(公告)日：1998-07-28

申请号：US577034

申请日：1995-12-22

申请人： Dennis E. Ruzicka

发明人： Dennis E. Ruzicka

IPC分类号： B64D39/00

CPC分类号： B64D39/00

摘要： An improvement in an airplane mounted aerial refueling boom wherein the boom assembly mounting permits motion about three axes. A first pivot attached to the fuselage of the airplane provides for radial or azimuth motion of the boom about a vertical or yaw axis of rotation essentially normal to the air stream. The second axis of motion, the pitch axis, is located below the airplane fuselage and perpendicular to the yaw axis so that the pitch axis rotates with any yaw motion of the boom and allows vertical displacement of the boom. Vertical and yaw displacement takes place in a conventional fashion. The third axis of motion, the roll axis, is located in-plane with and perpendicular to the pitch axis. This roll axis is coincident with the longitudinal centerline of the boom structural tube and a helical rotary actuator that produces a commanded roll motion as a function of pitch and yaw motion of the boom assembly. Rolling motion of the boom assembly serves to align the cross-sectional vertical chord axis of the boom and boom mounted aerodynamic surfaces with the local free stream air flow about the tanker airplane to minimize drag and optimize control authority.

摘要翻译： 飞机安装的空中加油臂的改进，其中吊杆组件安装允许围绕三个轴线的运动。 附接到飞机的机身上的第一枢轴提供了起重臂围绕基本垂直于空气流的垂直或偏转旋转轴的径向或方位运动。 运动的第二轴（俯仰轴）位于飞机机身的正下方并垂直于偏航轴线，以便俯仰轴随着悬臂的任何偏转运动而旋转，并允许悬臂的垂直位移。 垂直和偏航位移以常规方式进行。 运动的第三轴，滚动轴线位于与俯仰轴线垂直的平面内。 该滚动轴线与起重臂结构管的纵向中心线和螺旋旋转致动器重合，该螺旋旋转致动器产生作为悬臂组件的俯仰和偏转运动的函数的命令滚动运动。 起重臂组件的滚动运动用于使悬臂和悬臂安装的空气动力学表面的横截面垂直弦线与罐车附近的局部自由流空气流对齐，以最小化阻力并优化控制权限。

公开(公告)号：US5573206A

公开(公告)日：1996-11-12

申请号：US293177

申请日：1994-08-19

申请人： Elmer F. Ward

发明人： Elmer F. Ward

IPC分类号： B64D39/00 ,  B64D37/16

CPC分类号： B64D39/00

摘要： An aerial refueling system for refueling aircraft in flight from a tanker airplane, via a fuel supply hose and drogue system comprising an elongated boom having inboard and outboard end portions, and having pivotal support structure at the inboard end portion to accommodate pivoting of the boom between retracted position adjacent the airplane fuselage and extended position in which the boom projects away from the fuselage; the boom having a guide to guide endwise extension and retraction of the hose and drogue to and from aircraft refueling deployed position; and hose and drogue control structure carried by the aircraft fuselage for effecting storage, and hose and drogue endwise extension and retraction via the guide.

摘要翻译： 一种空中加油系统，用于通过燃料供应软管和冷水系统从油罐飞机加油飞行器，该系统包括具有内侧和外侧端部的细长悬臂，并且在内侧端部具有枢转支撑结构，以适应臂 靠近飞机机身的缩回位置和悬臂从机身伸出的延伸位置; 引导臂具有引导件，用于引导软管的端部延伸和缩回，并且从飞机加油部署位置引导; 以及由飞机机身承载的软管和水龙头控制结构进行存储，并通过导轨软管和锥形终端伸缩。

公开(公告)号：US5564648A

公开(公告)日：1996-10-15

申请号：US504261

申请日：1995-07-19

申请人： William R. Palmer

发明人： William R. Palmer

IPC分类号： B64D39/00 ,  B64G1/00 ,  B64G1/14 ,  B64G1/24 ,  B64G1/40

CPC分类号： B64G1/401 ,  B64D39/00 ,  B64G1/005 ,  B64G1/007 ,  B64G1/14 ,  B64G1/242 ,  B64G1/402

摘要： A high altitude launch platform, used to launch a payload into earth orbit, is part of a payload launch system having a payload launching rocket with an engine carried by the high altitude launch platform. A first amount of fuel, substantially less than the capacity of the fuel tanks, is provided to the fuel tanks of the engines for the launch platform while the launch platform is on the ground. The launch platform is flown to a first altitude and the fuel tanks are provided with a second amount of fuel while the high altitude launch platform is at the first altitude. The addition of the second amount of fuel is sufficient to allow the payload to be launched into orbit.

公开(公告)号：US5456424A

公开(公告)日：1995-10-10

申请号：US215506

申请日：1994-03-22

申请人： William R. Palmer

发明人： William R. Palmer

IPC分类号： B64D39/00 ,  B64G1/00 ,  B64G1/14 ,  B64G1/24 ,  B64G1/40

CPC分类号： B64G1/401 ,  B64D39/00 ,  B64G1/005 ,  B64G1/007 ,  B64G1/14 ,  B64G1/242 ,  B64G1/402

摘要： A high altitude launch platform, used to launch a payload into earth orbit, is part of a payload launch system having a payload launching rocket with an engine carried by the high altitude launch platform. A first amount of fuel, substantially less than the capacity of the fuel tanks, is provided to the fuel tanks of the engines for the launch platform while the launch platform is on the ground. The launch platform is flown to a first altitude and the fuel tanks are provided with a second amount of fuel while the high altitude launch platform is at the first altitude. The addition of the second amount of fuel is sufficient to allow the payload to be launched into orbit.

摘要翻译： 用于向地球轨道发射有效载荷的高空发射平台是有效载荷发射系统的一部分，其具有载荷发射火箭与高空发射平台携带的引擎。 当发射平台在地面上时，向发射平台的发动机的燃料箱提供了基本上小于燃料箱容量的第一燃料量。 发射平台飞行到第一高度，并且燃料箱被提供有第二量的燃料，而高空发射台处于第一高度。 第二量的燃料的添加足以允许有效载荷发射进入轨道。

公开(公告)号：US5326052A

公开(公告)日：1994-07-05

申请号：US769435

申请日：1991-10-02

申请人： Yaacov Krispin ,  Mordekhai Velger

发明人： Yaacov Krispin ,  Mordekhai Velger

IPC分类号： B64D39/06 ,  B64D39/00

CPC分类号： B64D39/06

摘要： An in-flight hose-and-drogue refueling system has the capability of steering the drogue using four thrusters which are energized by pressurized air. The system measures the drogue's 3-dimensional position relative to either the refueling aircraft or the probe on the receiver aircraft. A control system utilizes the measurements of the drogue's 3-dimensional position to activate the thrusters so as to either minimize the excursions of the drogue due to turbulence, thus enabling easier hook-up, or alternatively, to track the receiver's probe and automatically guide and contact the drogue to the probe.

摘要翻译： 飞行中的软管和锥形加油系统具有使用由加压空气通电的四个推进器来转向锥套的能力。 该系统相对于加油飞机或接收机上的探头来测量锥套的三维位置。 一个控制系统利用锥形三维位置的测量来激活推进器，以便最小化由于湍流引起的锥套的偏移，从而实现更容易的连接，或者可以跟踪接收器的探头并自动引导和 将探头接触探头。