In response to future large payload launches, the increasing complexity of the power system leads to a higher probability of power system fault. For the power system fault in the ascent phase of the heavy lift launch vehicle, this paper presents a guidance method that can autonomously reconstruct the trajectory, where different methods are applied based on the power system fault moment. As to the exo-atmospheric fault, the orbit injection point adaptive updated iterative guidance method is adopted, where the argument of latitude is adjusted online to improve the accuracy of other five orbital elements. For the endo-atmospheric fault, the online trajectory optimization closed-loop guidance algorithm based on the indirect method is applied. The necessary conditions of the optimal control problem are re-derived based on the calculus of variations. To satisfy the real-time requirement, finite element method is used to transform the optimal control problem into root-finding problem of algebraic equations, which is finally solved through Newton iteration, by discretizing the necessary conditions. A series of cases for a two stage heavy lift launch vehicle are tested, with variations on the degree of the engine failures. The results showed that the proposed guidance algorithm effectively improve the reliability against power system faults. The impact of different degrees of failure on fuel consumption is analysed, which will be beneficial to heavy lift launch vehicle design for future missions.


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    Title :

    Ascent Adaptive Guidance for Power System Fault of Heavy Lift Launch Vehicle


    Contributors:
    Wang, Jiegang (author) / Pu, Jialun (author) / Cui, Naigang (author) / Li, Yuan (author) / Han, Yepeng (author)


    Publication date :

    2018-08-01


    Size :

    155202 byte




    Type of media :

    Conference paper


    Type of material :

    Electronic Resource


    Language :

    English



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