公开(公告)号：WO2014126860A1

公开(公告)日：2014-08-21

申请号：PCT/US2014/015600

申请日：2014-02-10

Applicant: GULFSTREAM AEROSPACE CORPORATION ,  FREUND, Donald

Inventor： FREUND, Donald

IPC: B64C30/00

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

Abstract: 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.

Abstract translation: 用于控制由超音速飞行器的脱离设计操作引起的声音吊杆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与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。

公开(公告)号：WO2014126858A1

公开(公告)日：2014-08-21

申请号：PCT/US2014/015591

申请日：2014-02-10

Applicant: GULFSTREAM AEROSPACE CORPORATION ,  FREUND, Donald

Inventor： FREUND, Donald

IPC: B64C30/00

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

Abstract: Methods and systems for controlling a magnitude of a sonic boom caused by off-design-condition operation of a supersonic aircraft at supersonic speeds are disclosed herein. The method includes, but is not limited to, monitoring, with a processor, a weight of the supersonic aircraft and a distribution of fuel onboard the supersonic aircraft. The method further includes, but is not limited to, determining, with the processor, that there is a deviation of the weight of the supersonic aircraft from a design-condition weight. The method still further includes, but is not limited to, controlling, with the processor, a redistribution of the fuel onboard the supersonic aircraft to adjust an amount of fuel stored within a wing to minimize a twist in the wing caused by the deviation. Such redistribution will reduce the magnitude of the sonic boom caused by the deviation.

Abstract translation: 本文公开了用于控制由超音速飞行器超超速度的偏离设计条件操作引起的声波起重量的方法和系统。 该方法包括但不限于用处理器监测超音速飞机的重量和超音速飞机上的燃料分配。 该方法还包括但不限于与处理器确定超音速飞机的重量与设计条件权重的偏差。 该方法还包括但不限于与处理器一起控制超音速飞机上的燃料的重新分配，以调节存储在机翼内的燃料量，以最小化由偏差引起的机翼扭转。 这种重新分配将减少由偏差引起的声波爆震的大小。

公开(公告)号：WO2014126855A1

公开(公告)日：2014-08-21

申请号：PCT/US2014/015585

申请日：2014-02-10

Applicant: GULFSTREAM AEROSPACE CORPORATION ,  FREUND, Donald

Inventor： FREUND, Donald

IPC: B64C3/20

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

Abstract: 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.

Abstract translation: 控制由超音速飞行器在超音速下的非设计状态操作引起的声波爆震震级的方法包括但不限于在超音速和非设计状态下操作超音速飞行器的步骤。 超音速飞机具有一对扫掠翼，其具有多个以一定角度定向的复合层，使得最大刚度的轴相对于该对扫掠翼的每个翼的后翼片不平行。 该方法还包括但不限于在复合帘布层的脱离设计条件下以超音速速度降低由超音速飞行器操作引起的机翼扭转的步骤。 该方法还包括但不限于通过减少机翼扭曲来最小化声音吊杆的大小。