Configuration and adaptive control law design for a mass moment missile

The mass moment missile is a typical kind of fast and time-varying multi-body system with nonlinear input, whose attitude dynamics equations are functions of moving-mass position, velocity and acceleration. The attitude control problem of mass moment missile is analyzed from perspectives of both configuration and control law. A new configuration of mass moment missile is presented with the in-depth analysis of attitude dynamics model, which can ensure that the system has better dynamic quality. On the basis of this, an affine attitude dynamics model is established and the attitude control law is designed by using backstepping control method. Taking into account the existing uncertainties of pneumatic parameters, external disturbances and dynamic characteristics of actuator, the robust adaptive compensation is designed. Finally, numerical simulation is conducted and a comparison with the normal backstepping control method is made, which demonstrates the validity of the proposed method.