Active disturbance rejection predictive guidance method for launch vehicle in enter-orbit segment
As the motion of launch vehicle during the enter-orbit segment has a great influence on the orbiting accuracy,in order to cope with the perturbation situations,an active disturbance rejec-tion predictive guidance method is proposed.Firstly,based on the three-degree-of-freedom model of the launch vehicle,an improved trajectory planning algorithm is formed by introducing average grav-ity field and simplifying terminal constraints,which accelerates the convergence speed and satisfies the needs of online trajectory planning.Then,an active disturbance rejective trajectory tracker is designed,combining with the online trajectory planning algorithm,an active disturbance predictive guidance method is formed.The numerical simulation indicates that the proposed method has a high orbiting accuracy and robustness in dealing with thrust fault and other typical deviation disturbances,which can provide a reference for the adaptability of the guidance control system during the enter-or-bit segment of the launch vehicle.
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