An approximate solution for the maximum payload trajectory of a two-stage launch vehicle using a regular perturbation technique is presented. A zero-order solution for a two-stage vehicle based on a flat-earth approximation and negligible atmospheric effects is obtained in closed form. High-order correction terms are obtained from the solution of nonhomogeneous, first-order linear differential equations by quadrature. This promises the capability for an onboard optimal guidance law implementation.


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    Title :

    An approach to optimal guidance of an advanced launch vehicle concept


    Contributors:

    Publication date :

    1990-01-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English




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