To improve the performance of terminal area energy management control system for reusable launch vehicle

the pitch attitude control system architecture based on trajectory linearization was developed

which includes two parts: pseudo-inverse model and feedback control system.Using the concept of instantaneous equilibrium

the pseudo-inverse model was designed by trimming the whole profile and the pitch attitude control system architecture was built.Take example for the flight phase of high altitude and super sonic

the system was designed and compared with traditional feedback control system.The results show that the control system by trajectory linearization can improve the transition performance

offload the feedback loop

and reduce the possibility of integrator saturation.