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1.发明公开FUSELAGE SHAPING AND INCLUSION OF SPIKE ON A SUPERSONIC AIRCRAFT FOR CONTROLLING AND REDUCING SONIC BOOM 有权船体教育和顶部安装上的超级平面控制和减少ÜBERSCHALLBANG
公开(公告)号：EP1478569A2
公开(公告)日：2004-11-24
申请号：EP03707587.6
申请日：2003-01-30
摘要： Method and arrangement for reducing the effects of a sonic boom created by an aerospace vehicle when said vehicle is flown at supersonic speed. The method includes providing the aerospace vehicle with a first spike extending from the nose thereof substantially in the direction of normal flight of the aerospace vehicle, the first spike having a second section aft of a first section that is aft of a leading end portion, the first and second sections having a second transition region therebetween and each of the sections having different cross-sectional areas, the leading end portion of the first spike tapering toward a predetermined cross-section with a first transition region between the predetermined cross-section and the first section. The first transition region is configured so as to reduce the coalescence of shock waves produced by the first spike during normal supersonic flight of the aerospace vehicle. A spike may also be included that extends from the tail of the aerospace vehicle to reduce the coalescence of shock waves produced by the spike during normal supersonic flight of the aerospace vehicle.
摘要翻译： 方法和装置，用于降低由关于航空航天车辆产生的爆音的影响，当所述车辆以超音速飞行。 该方法包括提供航空航天车辆与第一穗在航天飞行器的正常飞行方向从鼻子延伸其基本上，具有一第一部分的第二部分后所做的第一尖峰是船尾的前端部的，所述 具有第二过渡区域存在之间以及第一和第二部分，每个部分具有不同的横截面面积的部分的，朝向预定的横截面具有预定的横截面和所述之间的第一过渡区域逐渐变细的第一尖峰的前端部 首节。 第一过渡区域被配置成以降低航天飞行器的正常超音速飞行期间由第一尖峰产生冲击波的聚结。 因此，一个尖峰可以包括没有从航天飞行器的尾部延伸，以减少航天飞行器的正常超音速飞行期间由尖峰产生冲击波的聚结。
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2.发明授权FUSELAGE SHAPING AND INCLUSION OF SPIKE ON A SUPERSONIC AIRCRAFT FOR CONTROLLING AND REDUCING SONIC BOOM 有权船体教育和顶部安装上的超级平面控制和减少ÜBERSCHALLBANG
公开(公告)号：EP1478569B1
公开(公告)日：2009-09-23
申请号：EP03707587.6
申请日：2003-01-30
摘要： Method and arrangement for reducing the effects of a sonic boom created by an aerospace vehicle when said vehicle is flown at supersonic speed. The method includes providing the aerospace vehicle with a first spike extending from the nose thereof substantially in the direction of normal flight of the aerospace vehicle, the first spike having a second section aft of a first section that is aft of a leading end portion, the first and second sections having a second transition region therebetween and each of the sections having different cross-sectional areas, the leading end portion of the first spike tapering toward a predetermined cross-section with a first transition region between the predetermined cross-section and the first section. The first transition region is configured so as to reduce the coalescence of shock waves produced by the first spike during normal supersonic flight of the aerospace vehicle. A spike may also be included that extends from the tail of the aerospace vehicle to reduce the coalescence of shock waves produced by the spike during normal supersonic flight of the aerospace vehicle.
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