|국가/구분||United States(US) Patent 등록|
|국제특허분류(IPC7판)||B64C-030/00 B64D-029/04 B64C-001/26|
|발명자 / 주소|
|출원인 / 주소|
|대리인 / 주소||
|인용정보||피인용 횟수 : 0 인용 특허 : 45|
A supersonic aircraft having unique structural, geometrical, electromagnetic, mechanical, thermal and aerodynamic configuration is described. Its design characteristics maximize aerodynamic performance, speed, efficiency, comfort and range in the operational affect of carrying passengers over long distances at very high flight speeds and Mach numbers, generally above Mach 4.0+. It has fully integrated-mated fuselage twin engine nacelle structures which reduce and stabilize wave drag, wherein engines sit forward of the sonic boom electrode swept aerospace...
1. A hypersonic aircraft comprising: a fuselage; a highly swept parabolic wing planform extending from the fuselage at an angle of 77 degrees, wherein a parabolic leading edge of the wing planform has a mean average of 72 degrees aft sweep, and the parabolic leading edge of the wing planform maintains a Mach cone angle perpendicular to the wing planform; a pair of engine nacelles attached to the fuselage, the pair of engine nacelles containing a. pair of engine exhaust nozzles; a butterfly tail attached to the fuselage aft of the wing planform; a canard ...