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1.发明公开SYSTEMS AND METHODS FOR CONTROLLING A MAGNITUDE OF A SONIC BOOM 审中-公开系统VERFAHREN ZUR STEUERUNG DES VOLUMENS EINESÜBERSCHALLKNALLS
公开(公告)号：EP2956356A4
公开(公告)日：2016-11-30
申请号：EP14751133
申请日：2014-02-10
发明人： FREUND DONALD
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 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： 用于控制由超音速飞行器的脱离设计操作引起的声波起重器的大小的系统包括被配置为检测超音速飞行器的状况的传感器。 该系统还包括安装在超音速飞行器的机翼上的控制表面。 系统还包括通信地耦合到传感器并且与控制表面可操作地耦合的处理器。 处理器被配置为（1）从传感器接收指示超音速飞行器的状况的信息，（2）基于该信息确定升力分布和设计状况提升分布之间存在偏差，并且（3 ）控制控制面以减少偏差的方式移动。 当偏差减小时，声音臂的大小减小。
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公开(公告)号：EP2956357A4
公开(公告)日：2016-11-02
申请号：EP14751160
申请日：2014-02-10
发明人： FREUND DONALD
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 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： 用于控制由超音速飞行器的脱离设计操作引起的声波起重器的大小的系统包括被配置为检测超音速飞行器的状况的传感器。 该系统还包括安装在超音速飞行器的机翼上的控制表面。 系统还包括通信地耦合到传感器并且与控制表面可操作地耦合的处理器。 处理器被配置为（1）从传感器接收指示超音速飞行器的状况的信息，（2）基于该信息确定升力分布和设计状况提升分布之间存在偏差，并且（3 ）控制控制面以减少偏差的方式移动。 当偏差减小时，声音臂的大小减小。
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公开(公告)号：EP2956357A1
公开(公告)日：2015-12-23
申请号：EP14751160.4
申请日：2014-02-10
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.
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公开(公告)号：EP2517957A3
公开(公告)日：2015-12-16
申请号：EP12165221.8
申请日：2012-04-23
IPC分类号： B64D39/00
摘要： An aircraft aerial refuelling system including at least one pressure controlled fuel pump (20) having a control system (33) adapted to regulate the pump outlet fuel pressure using an outlet fuel pressure signal as control feedback (42). Also, methods of operating an aircraft aerial refuelling system.
摘要翻译： 一种包括至少一个压力控制燃料泵（20）的飞机空中加油系统，所述压力控制燃料泵具有适于使用出口燃料压力信号作为控制反馈（42）调节泵出口燃料压力的控制系统（33）。 此外，操作飞机空中加油系统的方法。
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5.发明公开AIRCRAFT FUEL TANKS, SYSTEMS AND METHODS FOR INCREASING AN AIRCRAFT'S ON-BOARD FUEL CAPACITY 有权飞机油箱，系统和方法来放大主机板燃油容量
公开(公告)号：EP2114766A4
公开(公告)日：2014-04-02
申请号：EP07845468
申请日：2007-12-12
CPC分类号： B64D37/04 , B64C17/10 , B64D37/08 , B64D37/32 , Y02T50/44 , Y10T137/86324 , Y10T137/86348
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公开(公告)号：EP2349834B1
公开(公告)日：2014-03-05
申请号：EP08875685.3
申请日：2008-11-25
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公开(公告)号：EP3109165B1
公开(公告)日：2018-02-28
申请号：EP16176290.1
申请日：2016-06-24
发明人： RIBAROV, LubomirA. , CARPENTER, Richard J. , ROURKE, Russell P. , RUSSO, Charles J , LUKER, WILLIAM
IPC分类号： B64D37/04
摘要： A method of aircraft fuel distribution includes selecting a longitudinal center of gravity and predicting a rate of change of the center of gravity during flight. Fuel is located in a tail fm tank of a vertical tail fin of the aircraft, and is transferred from the tail fin tank forward at a predetermined transfer rate to counteract the predicted rate of change thereby maintaining the selected center of gravity. An aircraft fuel distribution system includes a center main fuel tank, a tail fin tank and a tail fin fuel pump to pump fuel between the tail fin tank and the center main fuel tank. An electronic controller operates the tail fin fuel pump such that fuel is flowed between the tail fin tank and the center main fuel tank at a predetermined transfer rate to maintain automatically an optimal position of a longitudinal center of gravity of the aircraft.
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公开(公告)号：EP2956355A1
公开(公告)日：2015-12-23
申请号：EP14751877.3
申请日：2014-02-10
发明人： FREUND, Donald
IPC分类号： B64C3/20
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 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.
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公开(公告)号：EP1762487A3
公开(公告)日：2007-12-05
申请号：EP06254424.2
申请日：2006-08-23
申请人： Airbus UK Limited
发明人： Ward, Michael David
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.
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