Computation Cost of Attitude Controller Based on Dynamic Inversion Theory with Adaptive Gain Tuning

Recently, the development of reusable space transportation systems is being actively promoted all over the world to reduce the operational cost. Automatic control system is an important research subject for the complex and nonlinear flight dynamics in terms of Mach number, dynamic pressure, angle of attack and etc. not only for unmanned but also piloted vehicle. Dynamic Inversion is one of the promising theories applicable to the nonlinear control system, but needs high calculation cost for the onboard computer to guarantee the stability. In this paper, the computation cost of attitude controller based on Dynamic Inversion theory with adaptive gain tuning is evaluated for the automatic control system of small scaled winged rocket called WIRES#015.