A Polytope-Based Adaptive Attitude Control Framework of Launch Vehicle
Regarding the performance of less adaptability of the traditional launch vehicle attitude control system which is designed based on the parameters of time retention method that deteriorates drastically when the practical operation condition abnormally deviating from the designed one,a polytope based adaptive control framework is proposed in this paper,which is well suitable for attitude control of rocket's flight in the aerosphere.The premise of the framework is that the dynamics of rocket in aerosphere can be described by a convex polytope combination through characteristic time operation points retention modelling.On the basis of this assumption,an adaptive control algorithm is designed to solve aerodynamic and rudder efficient un-certainties.Furthermore,parameter-identification based and disturbance-compensation based improvements are proposed,which are capable of dealing with parameter oscillation and model mismatch in normal adap-tive control respectively.All three methods are proved to be stable theoretically.These methods can control the attitude of rocket effectively and steadily,and have less parameters to be adjusted,therefore have fairly good industrial prospect.
Carrier rocketAttitude controlPolytope based adaptive controlParameter identificationDisturbance compensation
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