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.
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