抄録
This paper aims to design guidance and control laws that are derived from a minimum fuel-consumption problem and has robustness against various disturbances such as dispersion of initial condition and thruster failure. The nonlinear robust control system is proposed to track the reference profiles, which are expressed by exponential functions. An adjustment law in the tracking controller is given in the form of the differential equations in tetms of the contoller's variable gains. Computer simulations are performed to verify the tracking accuracy, the robustness in a thrust failure mode, and the achievement of vertical/soft landing at a pre-assigned point on the lunar surface. The results of numerical simulation show the effectiveness of the proposed control law.
