Hypersonic Boost-Glide Missile is a new intercontinental guided weapon intends to fly along an optimized trajectory. Its glide warhead with sharp nose needs to endure long-time serious aeroheating to long-range glide in atmosphere. The trajectory optimization problem is an important aspect for HBG missile design. The trajectory optimization problem is characterized by a boost phase followed by a glide phase. A multi-constraints multi-phase trajectory optimization method is adopted to optimize the crossrange, under near-real condition. The associated optimal control problem has been solved by selecting a direct method approach. The dynamics has been transcribed to a set of nonlinear constraints and the arising nonlinear programming problem has been solved through a sequential quadratic programming solver. Numerical results represent the optimal trajectory solved is a combined boost-glide-dive trajectory, and the crossrange can attain 4748.4km.


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    Titel :

    Maximum crossrange for hypersonic boost-glide missile


    Beteiligte:
    Yu Li, (Autor:in) / Nai-gang Cui, (Autor:in)


    Erscheinungsdatum :

    01.12.2008


    Format / Umfang :

    527247 byte




    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch