Planar relative motion between target and interceptor satellite is treated by perturbation techniques to obtain linearized equations of motion which are valid in vicinity of collision course; terminal guidance law is formulated for attaining collision course and for achievement of satellite rendezvous using constant thrust rocket motors.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Terminal guidance technique for satellite interception utilizing constant thrust rocket motor


    Additional title:

    ARS -- J


    Contributors:
    Nason, M.L. (author)

    Published in:

    ARS Journal ; 30 , n 9


    Publication date :

    1960


    Size :

    2 pages


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English


    Keywords :


    Constant Thrust Hybrid Rocket Motor

    A. L. Holzman | NTIS | 1981


    Midcourse guidance problem in satellite interception -- 1

    Skalafuris, A.J. / Schiller, D.H. | Engineering Index Backfile | 1960


    Relativistic Flight with a Constant Thrust Rocket

    G. M. Anderson / D. T. Greenwood | NTIS | 1970