Reconfigurable control system design based on control allocation for HLV

The attitude control of new generation heavy launch vehicles (HLV) is executed by the joint swing of both core and booster engines. Considering this characteristic, a method of designing and reconfiguring the attitude control system of HLV, especially when actuators fail using the allocation strategy, is proposed. HLV adopts the nonlinear dynamic inverse control law, which consists of two loops, a fast inner loop and a slow outer one. Based on pseudo-inverse and fixed-point method, this paper introduces a hybrid control allocation optimization strategy. This strategy has minor calculation and involves the restraints of actuators. Moreover, the strategies of reconfiguration under different fault scenarios are presented. The results of Matlab/Simulink simulation show that this reconfigurable control method of HLV can effectively solve the problem of control allocation of multi-actuators and observably improve the safety and reliability of the HLV.