A 55 foot diameter disk-gap-band parachute was deployed behind an expandable 15 foot diameter, 120 deg blunted-cone simulated spacecraft. The spacecraft was carried to altitude in the folded condition. An automatic control system kept the folded spacecraft pointing in the desired direction after booster separation. The aeroshell was then erected at the desired conditions by ground command. When the desired parachute test conditions were reached, another ground command deployed the test parachute. The test Mach number and dynamic pressure obtained at the parachute peak load were 2.62 and 19.4 pounds per square foot respectively. A large disturbance after aeroshell erection caused a large angle of attack to exist at parachute deployment. Methods of preventing this disturbance are discussed.


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    Titel :

    Flight test of an erectable spacecraft used for decelerator testing at simulated Mars entry conditions


    Beteiligte:
    Henning, A. B. (Autor:in) / Lundstrom, R. R. (Autor:in)

    Erscheinungsdatum :

    1972-10-01


    Medientyp :

    Sonstige


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :





    Deployable and erectable concepts for large spacecraft

    Bush, H. G. / Heard, W. L., Jr. / Walz, J. E. et al. | NTRS | 1980


    Large-scale decelerator flight tests simulating a Mars environment.

    Darnell, W. L. / Henning, A. B. / Lundstrom, R. R. | NTRS | 1968