In this paper we have considered the problem of optimizing the ascent trajectory of a small spacecraft launched by an air-based two-stage rocket. The control is provided by the angle of attack and thrust of the engines while a restriction on the angle of attack is introduced. The thrust of engines at active trajectory phases is considered to be constant. The optimum control criterion is the maximum of the finite mass. To determine the optimal control programs, we have applied Pontryagin's maximum principle. We have conducted the analysis of the parameters of the trajectory and rocket flight modes. We have also calculated the payload mass launched into low-earth orbit.


    Access

    Check access

    Check availability in my library

    Order at Subito €


    Export, share and cite



    Title :

    Optimizing an Ascent Trajectory of a Small Spacecraft Launched by an Air-based Two-Stage Rocket


    Contributors:


    Publication date :

    2019-06-01


    Size :

    366668 byte




    Type of media :

    Conference paper


    Type of material :

    Electronic Resource


    Language :

    English



    Boost and Ascent Trajectory Design and Guidance Approach for Rocket Launched Supersonic Aircraft

    Liu, Jianhui / Wang, Lansong / Zhang, Mingang et al. | British Library Conference Proceedings | 2020




    Aerothermal–Structural Analysis of a Rocket-Launched Mach 8 Scramjet Experiment: Ascent

    Capra, Bianca R. / Brown, L. M. / Boyce, R. R. et al. | AIAA | 2015