Analysis of Some Ballistic Features of a Crewed Transport Spacecraft Descent from Solar-Synchronous Orbit of the Earth Artificial Satellite
Authors: Kudryavtsev S.I.
Published in issue: #5(173)/2026
Category: Aviation and Rocket-Space Engineering | Chapter: Aircraft Dynamics, Ballistics, Motion Control
Ballistic features of prospective manned transport spacecraft's (MTS) reentry from solar-synchronous orbit of Russian orbital station being designed are considered. Analysis of reentry module's (RM) entry condition to the dense layers of atmosphere against the Earth rotation's direction is performed. The estimation of maximum equilibrium temperature of RM body is given. Possibilities of RM landing at one selected landing site are analyzed. The necessity of required landing site number's determination in dependence of the concept of flight safety is marked. The results of ballistic calculations for a solution of the task of RM engine module (EM) safe flight termination after EM separation from RM. The estimation of required duration of EM autonomous flight after pre-auction maneuver to final deorbiting and unburned elements of structure splash-down is given. Problems of MTS reentry organization in the cases of off-nominal situation are marked.
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