Research on variable structure control law of advanced aerocraft

The ability of a combined control system to control the attitude of mass moment and lateral thrust flight aerocraft in intro-atmospheric space is investigated. The nonlinear equations of motion which provide the basis for a detailed simulation model are derived. And then through an analysis of control principle for lateral thrust control and mass moment, a compound strategy for the hybrid control system, which forms the basis of the study, is presented and discussed. Based on the compound strategy, the design of the control law for lateral thrust control and mass moment respectively using variable structure control method is presented in detail. A nonlinear seven-degree-of-freedom simulation of the typical intro-atmospheric aerocraft with mass moment and lateral thrust demonstrates the ability of the compound strategy and the control law to effectively control the aerocraftpsilas attitude. Dynamic, aerodynamic, and inertial cross-coupling do not appear to significantly degrade the control systempsilas response.