Patent ID: 6698684
Filing Date: 2004-03-02
Classification: B64C

Abstract:
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; and a first spike operably associated with said leading end of said fuselage, said first spike having a leading end portion and a trailing end portion, said leading end portion tapering toward a predetermined cross-section; said first spike comprising a first section aft of said leading end portion, wherein said first section has a first cross-sectional area; said first spike further comprising a first transition region between said predetermined cross-section and said first section; said first spike further comprising a second section aft of said first section, wherein said second section has a second cross-sectional area, said second cross-sectional area being different than said first cross-sectional area; and said first spike further comprising a second transition region between said first section and said second section.