FIELD: transport.
SUBSTANCE: invention relates to spacecraft (SC) motion control during placing it into orbit of planet artificial satellite using aeroassisted maneuver. In the phase of airbraking, following parameters are forecasted for the time of SC exiting planetary atmosphere: SC speed, angle to inclination to local horizon and altitude of transfer orbit apofocus. In this process in each of successive forecast points, SC motion is considered on remaining atmospheric flight segments for roll angles γ = 0 rad and γ = π. The mentioned above forecasted manoeuvring parameters are found for each of these angles. Their values are used during control of SC incidence change (close to its value corresponding to maximum quality) and issuing pulse of SC speed in transfer orbit apofocus.
EFFECT: higher efficiency of SC aeroassisted maneuver due to specified control.
1 dwg
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