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.


    Access

    Check access

    Check availability in my library

    Order at Subito €


    Export, share and cite



    Title :

    Maximum crossrange for hypersonic boost-glide missile


    Contributors:
    Yu Li, (author) / Nai-gang Cui, (author)


    Publication date :

    2008-12-01


    Size :

    527247 byte




    Type of media :

    Conference paper


    Type of material :

    Electronic Resource


    Language :

    English




    Trajectory optimization for hypersonic boost-glide missile considering aeroheating

    Li, Yu / Cui, Naigang / Rong, Siyuan | Emerald Group Publishing | 2009



    Some aspects of the design of hypersonic boost-glide aircraft

    Seiff, Alvin / Allen, H Julian | NTRS | 1955


    Coupled Vehicle and Trajectory Design Optimization for Boost-Glide Hypersonic Systems

    Gottlieb, Jonah R. / Mines, John M. / Garmendia, Daniel C. et al. | AIAA | 2024