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45 条记录 (耗时 0.01 秒)

    AIRCRAFT STRUCTURE FATIGUE ALLEVIATION
    13.
    发明公开
    AIRCRAFT STRUCTURE FATIGUE ALLEVIATION 有权
    疲劳缓解飞行器的结构

    公开(公告)号：EP1183181A1

    公开(公告)日：2002-03-06

    申请号：EP00931421.2

    申请日：2000-05-25

    申请人： BAE Systems PLC

    发明人： TIGHE, David John ,  WILLIAMS, Andrew David

    IPC分类号： B64C17/10

    CPC分类号： B64C17/10 ,  B64D37/00 ,  Y02T50/44

    摘要： A fuel transfer apparatus for an aircraft comprises: two or more fuel tanks (2, 3, 4, 5, 6) arranged in an inboard to outboard alignment, at least one being situated in the wing (1) of the aircraft, means for transferring fuel between the tanks (8, 9), and a fuel management system (10) for controlling and monitoring the transfer of fuel between tanks; the fuel management system comprises: means for receiving a first input signal that the aircraft has left the ground, means for receiving a second input signal that the aircraft is approaching its destination, means for initiating the transfer of the fuel from a relatively inboard tank location to a relatively outboard tank location in response to the first input signal, and means for initiating the transfer of the fuel from a relatively outboard tank location to a relatively inboard tank location in response to the second input signal.

    SYSTEMS AND METHODS FOR CONTROLLING A MAGNITUDE OF A SONIC BOOM
    15.
    发明公开
    SYSTEMS AND METHODS FOR CONTROLLING A MAGNITUDE OF A SONIC BOOM 审中-公开
    用于控制过渡臂的体积的系统和方法

    公开(公告)号：EP2956355A4

    公开(公告)日：2016-11-02

    申请号：EP14751877

    申请日：2014-02-10

    申请人： GULFSTREAM AEROSPACE CORP

    发明人： FREUND DONALD

    IPC分类号： B64C3/20 ,  B64C30/00

    CPC分类号： B64C23/00 ,  B64C3/185 ,  B64C3/20 ,  B64C3/38 ,  B64C3/42 ,  B64C9/00 ,  B64C17/10 ,  B64C30/00 ,  B64D37/00 ,  Y02T50/145 ,  Y02T50/44

    摘要： A system for controlling a magnitude of a sonic boom caused by off-design operation of a supersonic aircraft includes a sensor configured to detect a condition of the supersonic aircraft. The system further includes a control surface that is mounted to a wing of the supersonic aircraft. The system still further includes a processor communicatively coupled to the sensor and operatively coupled with the control surface. The processor is configured to (1) receive information from the sensor indicative of the condition of the supersonic aircraft, (2) determine that there is a deviation between a lift distribution and a design-condition lift distribution based on the information, and (3) control the control surface to move in a manner that reduces the deviation. The magnitude of the sonic boom is reduced when the deviation is reduced.

    SYSTEMS AND METHODS FOR CONTROLLING A MAGNITUDE OF A SONIC BOOM
    16.
    发明公开
    SYSTEMS AND METHODS FOR CONTROLLING A MAGNITUDE OF A SONIC BOOM 审中-公开
    用于控制声学升降机的幅度的系统和方法

    公开(公告)号：EP2956356A1

    公开(公告)日：2015-12-23

    申请号：EP14751133.1

    申请日：2014-02-10

    申请人： Gulfstream Aerospace Corporation

    发明人： FREUND, Donald

    IPC分类号： B64C30/00

    CPC分类号： B64C23/00 ,  B64C3/185 ,  B64C3/20 ,  B64C3/38 ,  B64C3/42 ,  B64C9/00 ,  B64C17/10 ,  B64C30/00 ,  B64D37/00 ,  Y02T50/14 ,  Y02T50/44

    摘要： A method of controlling a magnitude of a sonic boom caused by off-design-condition operation of a supersonic aircraft at supersonic speeds includes, but is not limited to the step of operating the supersonic aircraft at supersonic speeds and at an off-design-condition. The supersonic aircraft has a pair of swept wings having a plurality of composite plies oriented at an angle such that an axis of greatest stiffness is non-parallel with respect to a rear spar of each wing of the pair of swept wings. The method further includes, but is not limited to the step of reducing wing twist caused by operation of the supersonic aircraft at supersonic speeds at the off-design condition with the composite plies. The method still further includes, but is not limited to, minimizing the magnitude of the sonic boom through reduction of wing twist.

    摘要翻译： 用于控制音爆的幅度的系统包括配置成检测超音速飞行器的第一状态的第一传感器。 该系统还包括构造成前后移动的一对翼。 该系统还包括处理器，该处理器与传感器通信地耦合并且与该对翼可操作地耦合。 处理器被配置为（1）从第一传感器接收指示第一条件的第一信息，（2）基于第一信息计算超音速飞行器的升力分布，（3）确定 （4）根据飞行条件从期望的升力分布中提升分布，以及（4）控制该对翼以更紧密地符合期望升力分布的方式移动以重新分配升力。 当偏差减小时，音爆的幅度减小。

    Improvements in and relating to aircraft wings and fuel tanks
    19.
    发明公开
    Improvements in and relating to aircraft wings and fuel tanks 审中-公开
    飞机机翼和油箱的改进

    公开(公告)号：EP1762487A2

    公开(公告)日：2007-03-14

    申请号：EP06254424.2

    申请日：2006-08-23

    申请人： Airbus UK Limited

    发明人： Ward, Michael David

    IPC分类号： B64C3/34 ,  B64D37/04 ,  B64D37/32

    CPC分类号： B64D37/04 ,  B64C3/34 ,  B64C17/10

    摘要： On failure, a burst rotor of a wing-mounted engine (13, 23) can penetrate fuel tank walls in the wing of an aircraft. There exists a zone that is at risk of such damage. The layout of fuel tanks (3, 11C, 21C) in the wing of an aircraft in accordance with this invention includes port and starboard inner fuel tanks (11C, 21C) that are positioned adjacent to a central fuel tank (3) in the central wing section, but outside of the at-risk zone. Each of the port and starboard inner fuel tanks (11C, 21C) is defined in part by a respective inner boundary member (5RP, 5RS) that when viewed in plan extends, at least in part, in a direction at an angle of less than 20° to the adjacent vertical plane (A-A) defining the at-risk zone. Thus the amount of fuel stored in fuel tanks (11C, 21C) in the wing assembly that cover a region outside of the at-risk zone and that do not extend into the at-risk zone may be increased.

    摘要翻译： 失败时，翼式发动机（13,23）的爆裂转子可以穿透飞机机翼中的燃料箱壁。 存在可能造成这种损害的区域。 根据本发明的飞机机翼中的燃料箱（3,11C，21C）的布局包括位于中央燃料箱（3）附近的端口和右舷内部燃料箱（11C，21C） 机翼部分，但在危险区域之外。 左舷和右舷内燃料箱（11C，21C）中的每一个部分由相应的内边界构件（5RP，5RS）限定，当沿平面观察时，该内边界构件至少部分地以小于 20°到相邻的垂直面（AA），定义危险区域。 因此，储存在翼组件中的燃料箱（11C，21C）中的燃料量可以增加，该燃料箱覆盖处于危险区之外并且不延伸到危险区的区域。