-
1.发明授权Fuselage shaping and inclusion of spike on a supersonic aircraft for controlling and reducing sonic boom 有权船体设计和芯轴的整合在超音速飞机，以控制和减少音爆
公开(公告)号：EP2110312B1
公开(公告)日：2014-01-01
申请号：EP09010045.4
申请日：2003-01-30
-
2.发明公开Fuselage shaping and inclusion of spike on a supersonic aircraft for controlling and reducing sonic boom 有权船体设计和芯轴的整合在超音速飞机，以控制和减少音爆
公开(公告)号：EP2110312A2
公开(公告)日：2009-10-21
申请号：EP09010045.4
申请日：2003-01-30
摘要： Method and apparatus for configuring and operating an aircraft for minimizing sonic boom effects at ground level during supersonic flight of the aircraft including configuring the aircraft so that in flight, with landing gear retracted, a lower profile of the aircraft is substantially liner or slightly concave downward. A nose portion of the aircraft is arranged so that an apex thereof is coincident with the lower profile of the aircraft. The aircraft is flown at supersonic speed and oriented during supersonic flight so that the substantially linear lower profile of the aircraft is orientated substantially parallel to onset airflow. Weak pressure disturbances are generated below the aircraft, and waves thereof are radiated below the aircraft toward the ground. These disturbances below the aircraft are of lesser magnitude than pressure disturbances simultaneously generated and radiated above the aircraft. The weak pressure disturbances generated below the aircraft are controlled so that differentials thereamong are sufficiently minimized that ground level sonic boom effects are minimized during sonic flight. In a second aspect, a retractable spike is included at the nose or rear of the aircraft for minimizing sonic boom effects at ground level during supersonic flight.
摘要翻译： 用于配置和用于飞机，包括配置所述飞机在飞行中这样做的超音速飞行期间最小化在地面水平爆音效果飞行器（120）的操作，与起落架收起的方法和装置，较低的轮廓（164）的飞机是 实质上衬垫或向下微凹。 飞行器的鼻部（162）被配置成没有在先端（163）其是与所述飞行器的下轮廓相一致。 该机在超音速飞行和超音速飞行时定向成DASS死基本上线性飞行器的下轮廓被定向平行于基本上发病气流。 弱的压力扰动产生飞机下方，并且其波辐射朝向接地飞机下方。 飞机下方这些干扰是小的幅度的比压力扰动同时生成和飞行器上方放射。 飞机下方产生微弱的压力扰动进行控制，从而做到thereamong是音速飞行时最小化并充分地平面音爆影响减至最小差距。 在第二个方面，一个可伸缩的尖峰（223）被包括在所述飞机的前端或后端为超音速飞行期间最小化在地面水平爆音的效果。
-
3.发明公开Fuselage shaping and inclusion of spike on a supersonic aircraft for controlling and reducing sonic boom 有权船体设计和芯轴的整合在超音速飞机，以控制和减少音爆
公开(公告)号：EP2110312A3
公开(公告)日：2012-12-12
申请号：EP09010045.4
申请日：2003-01-30
摘要： Method and apparatus for configuring and operating an aircraft (120) for minimizing sonic boom effects at ground level during supersonic flight of the aircraft including configuring the aircraft so that in flight, with landing gear retracted, a lower profile (164) of the aircraft is substantially liner or slightly concave downward. A nose portion (162) of the aircraft is arranged so that an apex (163) thereof is coincident with the lower profile of the aircraft. The aircraft is flown at supersonic speed and oriented during supersonic flight so that the substantially linear lower profile of the aircraft is orientated substantially parallel to onset airflow. Weak pressure disturbances are generated below the aircraft, and waves thereof are radiated below the aircraft toward the ground. These disturbances below the aircraft are of lesser magnitude than pressure disturbances simultaneously generated and radiated above the aircraft. The weak pressure disturbances generated below the aircraft are controlled so that differentials thereamong are sufficiently minimized that ground level sonic boom effects are minimized during sonic flight. In a second aspect, a retractable spike (223) is included at the nose or rear of the aircraft for minimizing sonic boom effects at ground level during supersonic flight.
-
-
搜索结果
3 条记录 (耗时 0.008 秒)
