Research On Blended Control For Missile With Adjustable Lateral Thrust And Aerodynamics

The background of this thesis is the missile with adjustable lateral thrust andaerodynamic surfaces. It focuses on the special guidance and control problems for thenonlinear blended control system with uncertainty, lateral jet interaction andmeasurement noise. The main researches and achievements are as follows.Firstly, for the characteristics of the missile with blended control, mathematicalmodels are established, which consist of kinematics model, dynamics model andmissile-target relative motion model. Meanwhile, based on reasonable assumptions, thedynamics model is transformed into attitude control model. The whole mathematicalmodels of blended control missile provide foundations for the subsequent study ofguidance and control problems.Secondly, because of the nonlinear feature of attitude control system, piecewise affinemodel is obtained by using the small deviation linearization method. Based on theequivalence between piecewise affine system and mixed logical dynamical system, themixed logical dynamical model of attitude control system is established as well. Then, ahybrid model predictive control method is employed to design the autopilot of missilewith blended control. In addition, numerical simulations are presented to show theeffectiveness of the proposed method.Thirdly, the target maneuver estimation and terminal guidance law of missile withblended control are obtained based on auto disturbance rejection controller, takingmeasurement noise, uncertainty and overload response characteristics into consideration.Since the lateral thrust is adjustable, a control allocation algorithm is presented, whichgets access to the overload allocation between lateral jets and aerodynamic surfaces.Moreover, by analysis of lateral jet engine configuration and thrust characteristics,dynamic system model of lateral regulation process is established. In order to ensureboth rapidity and stationarity of thrust regulation process, a proper performance index isproposed. By solving the constrained optimization problem, the thrust regulation law isobtained.Finally, combining the attitude control method, guidance law, control allocationalgorithm and thrust regulation law proposed previously, a full simulation is employedfor a certain blended control missile, which verifies the effectiveness of the results inthis thesis.