|국가/구분||United States(US) Patent 등록|
|미국특허분류(USC)||244/001N; 244/130; 181/211|
|발명자 / 주소|
|출원인 / 주소|
|대리인 / 주소||
|인용정보||피인용 횟수 : 0 인용 특허 : 82|
Method and arrangement for reducing the effects of a sonic boom created by an aerospace vehicle when the 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 there between and each of the sections having different cross-sectional are...
1. An aerospace vehicle configured to reduce the effects of a sonic boom created by said vehicle when said vehicle is flown at supersonic speed, said aerospace vehicle comprising: a fuselage having a leading end, a trailing end, a top, and a bottom;a spike operably associated with the leading end of said fuselage, the spike having a spike leading end and a spike trailing end, the spike leading end tapering toward the spike trailing end, a cross-sectional magnitude of the spike not decreasing from the spike leading end to the spike trailing end, the spike...