RCS对舵面控制特性影响的数值模拟

可重复使用运载器等采用反作用控制系统（RCS）/舵面复合控制技术进行配平和控制，由于舵面和喷口的位置相距很近，同时工作时将产生相互干扰效应。采用非定常数值模拟方法，结合动网格技术和喷流模拟技术，针对可重复使用运载器外形开展了侧向喷流开启和关闭对舵面控制特性的影响研究，分析了飞行器俯仰运动对不同舵面操纵方式的动态响应过程。研究发现，在超声速来流条件下，侧向喷口前方的弓形激波会打到方向升降舵的下表面产生一个局部高压区，使得飞行器产生附加的低头力矩，导致喷流开启时的配平攻角相对关闭时要低约1°。同时，侧向喷流与襟副翼之间存在非定常、非线性干扰现象，在RCS/舵面复合控制系统设计时，需要对此进行一定的补偿。

Numerical simulation of influence of RCS on control characteristics of aerodynamic surfaces

Reusable launch vehicles use combined control techniques of Reaction Control System (RCS) and aerodynamic surfaces for trim and control; however, the aerodynamic surfaces and RCS may affect each other because of the short distance between them. The control characteristic of aerodynamic surfaces when the jet is on and off is investigated using the unsteady numerical simulation method, moving grid technique and simulation technique of lateral jet. The dynamic response processes in pitching of the reusable launch vehicle with different maneuver modes are analyzed. The study shows that the trim angle of attack when the jet is on is one degree smaller than that when the jet is off at supersonic flow, in which the bow shock before the jet nozzle hits on the ruddervator and result in high pressure causing the nose-down pitching moment. Meanwhile, the unsteady and nonlinear interaction between the lateral jet and the flaperon is found, so the compensation mechanism is needed in the design of the combined control system.