The invention belongs to the field of aerodynamic configuration design of aerospace aircrafts, and relates to a structure and a design method for adjusting the zero-lift torque of an aircraft, the structure comprises a non-circular-section fuselage, the tail of the non-circular-section fuselage is contracted, the tail contraction section is provided with a vertical tail and a horizontal tail, and a tail fin is arranged between the horizontal tail and the fuselage and used for adjusting the zero-lift torque of the whole aircraft. The requirement for the aerodynamic performance of the aircraft can be met, and meanwhile the requirement for the installation space of the steering engine can be met through the integrated design of the tail fin and the steering engine.
本发明属于航空航天飞行器气动外形设计领域,涉及一种调整飞行器零升力矩的结构及设计方法,结构包括非圆截面机身,所述非圆截面机身尾部收缩,尾部收缩段设置垂尾及平尾,平尾与机身之间设置尾鳍,用于调整全机零升力矩,本发明能满足飞行器气动性能的要求,同时通过尾鳍与舵机的一体化设计又能满足舵机安装空间的要求。
Structure for adjusting zero lift moment of aircraft and design method
一种调整飞行器零升力矩的结构及设计方法
2025-03-14
Patent
Electronic Resource
Chinese
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