针对火箭动力的翼身组合体,通过机头弯度、翼型弯度和机翼扭转角三个布局特征参数的定义,对高超声速下机身、机翼形成的激波升力体、激波升力面进行研究,确定它们对全机升阻比的影响,给出了适应临近空间高超声速巡航的布局设计准则以及由此得到的优化构型。研究表明,通过激波升力体和激波升力面的相互耦合设计,可以满足小迎角下高超声速巡航的气动特性要求,以及低速大迎角飞行的要求,实现翼身组合体布局的优化。

Based on rocket-powered wing-fuselage combination, the nose camber, airfoil camber and wing torsion angle were defined as three configuration characteristic parameters. In order to investigate the effect of hypersonic shock wave lifting body/surface on lift-drag ratio of the wing-fuselage combination, the design rules adaptable to near-space hypersonic cruise and optimizing configuration generated by them were presented. The research indicates coupling shock wave lifting body with surface is able to meet the aerodynamic requirements of both hypersonic cruise at low angle of attack and low speed flight at high angle of attack, and then wing-fuselage combination configuration optimization can be realized.