A preliminary study for re-entry dimensioning of a 200 kg class satellite in earth circular orbit is presented. A tapered cone shape is assumed. The re-entry conditions are determined from an altitude scan in intensity and direction of the transfer orbit impulsion. The variations of the CX as a function of Mach number, an atmospheric table, and the overall satellite mass are assumed to be given. An iterative method was used to perform the dimensional analysis of the re-entry body given the ablative nose cone thickness temperature distribution and mechanical characteristics of the component materials at various temperatures. Buckling calculations are detailed. The mass balance derived from this study is applied to the rocket characterization and thrust required to orient the re-entry body.
Preliminary Study of a Reentry Body Etude Preliminaire d'UN Corps de Rentree
1973
109 pages
Report
Keine Angabe
Englisch