The invention relates to the technical field of aircrafts and especially relates to a hypersonic aircraft capable of improving course stability without depending on a stabilizer and a design method thereof. A wing body is included. The wing body comprises a fuselage and wings arranged on the two sides of the fuselage. The fuselage comprises a tail section and a head section connected with the tailsection, the tail section comprises a first tail section located on one side of the wing and a second tail section located on the other side of the wing, and a length of an end surface of the end, away from the head section, of the first tail section is smaller than that of the end, away from the head section, of the second tail section. Strong shock waves generated by the tail are reduced, a heat protection risk is relieved, a lift force is generated while resistance is generated through tail modification, and therefore a lift-drag ratio loss can be greatly reduced while the course stabilityis improved.
本发明涉及飞行器的技术领域,涉及一种不依靠安定面提升航向稳定性的高超声速飞行器及其设计方法,包括翼身,所述翼身包括机身和设置在机身两侧的机翼,所述机身包括机尾段和与机尾段相连的机头段,所述机尾段包括位于机翼一侧的第一机尾段和位于机翼另一侧的第二机尾段,所述第一机尾段远离机头段一端的端面长度小于所述第二机尾段远离机头段一端的端面长度。本发明其不仅降低尾部产生强激波,缓解防热风险,而且通过尾部修型在产生阻力的同时,还产生升力,从而在提升航向稳定性的同时可以大大降低升阻比损失。
Hypersonic aircraft and design method thereof
一种高超声速飞行器及其设计方法
2020-11-27
Patent
Electronic Resource
Chinese
IPC: | B64C AEROPLANES , Flugzeuge |
NTIS | 1990
|NTRS | 1990
|Advanced hypersonic aircraft design
NTRS | 1992
|Advanced Hypersonic Aircraft Design
NTIS | 1992
|Engineering Index Backfile | 1964
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