发明名称 |
SUPERSONIC AIRCRAFT WITH CHANNEL RELIEF CONTROL |
摘要 |
A supersonic aircraft comprises a fuselage extending forward and aft along a longitudinal axis, the fuselage having a lower surface and an upper surface, a highly swept low aspect ratio wing coupled to the fuselage and having a forward leading edge and an aft trailing edge, an effector flap coupled to the wing trailing edge, and a tail empennage. The tail empennage is coupled to the fuselage aft of the wing on the fuselage upper surface in a position high relative to the wing. The tail empennage forms a channel region subject to complex shock patterns at transonic conditions. The aircraft further comprises an effector coupled to the tail empennage and a controller coupled to the effector flaps and the effectors. The controller further comprises a control process that reduces drag through channel relief by deflecting both the effector flap down and the effector up.
|
申请公布号 |
US2005103929(A1) |
申请公布日期 |
2005.05.19 |
申请号 |
US20030696796 |
申请日期 |
2003.10.30 |
申请人 |
SUPERSONIC AEROSPACE INTERNATIONAL, LLC |
发明人 |
CHANG MING;MEZA VICTOR;MORGENSTERN JOHN M.;ARSLAN ALAN E. |
分类号 |
B64C3/16;B64C5/02;B64C9/00;B64C13/50;B64C23/04;B64C30/00;B64C39/06;(IPC1-7):B64C5/02 |
主分类号 |
B64C3/16 |
代理机构 |
|
代理人 |
|
主权项 |
|
地址 |
|