The first step in the approach to developing guidance laws for a horizontal take-off, air breathing single-stage-to-orbit vehicle is to characterize the minimum-fuel ascent trajectories. The capability to generate constrained, minimum fuel ascent trajectories for a single-stage-to-orbit vehicle was developed. A key component of this capability is the general purpose trajectory optimization program OTIS. The pre-production version, OTIS 0.96 was installed and run on a Convex C-1. A propulsion model was developed covering the entire flight envelope of a single-stage-to-orbit vehicle. Three separate propulsion modes, corresponding to an after burning turbojet, a ramjet and a scramjet, are used in the air breathing propulsion phase. The Generic Hypersonic Aerodynamic Model Example aerodynamic model of a hypersonic air breathing single-stage-to-orbit vehicle was obtained and implemented. Preliminary results pertaining to the effects of variations in acceleration constraints, available thrust level and fuel specific impulse on the shape of the minimum-fuel ascent trajectories were obtained. The results show that, if the air breathing engines are sized for acceleration to orbital velocity, it is the acceleration constraint rather than the dynamic pressure constraint that is active during ascent.


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    Titel :

    Trajectory Optimization and Guidance for an Aerospace Plane


    Beteiligte:
    K. D. Mease (Autor:in) / M. A. Vanburen (Autor:in)

    Erscheinungsdatum :

    1989


    Format / Umfang :

    42 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch




    Trajectory optimization and guidance for an aerospace plane

    Mease, Kenneth D. / Vanburen, Mark A. | NTRS | 1989





    Rapid near-optimal aerospace plane trajectory generation and guidance

    Calise, A. J. / Corban, J. E. / Markopoulos, N. | NTRS | 1991