Analysis of the features of the implementation of the launch unit flight scheme for micro spacecraft injections in an intermediate orbit with synchronous precession
Authors: Zelvin D.A., Toporkov A.G.
Published in issue: #9(93)/2019
DOI: 10.18698/2308-6033-2019-9-1918
Category: Aviation and Rocket-Space Engineering | Chapter: Aircraft Dynamics, Ballistics, Motion Control
The article considers features of the implementation of the launching scheme for a group of small spacecraft at the stage of the Volga type launch unit operation during the transition from the reference orbit formed by the “Soyuz 2.1 v” launch vehicle to the intermediate orbit, where the small spacecraft separate. The orbit with synchronous precession velocity of the ascending node longitude with respect to the working orbit is chosen as an intermediate orbit, to which the small spacecraft transfer independently, using their propulsion system, after separation from the launch unit. The article solves the problem of choosing the rational orientation of the launch unit during the release of pulses, in the passive flight segments, as well as for the safe separation of the small spacecraft in an intermediate orbit with synchronous precession. Parameters of maneuvers to flood launch unit after separation of small spacecraft are calculated. Numerical results of fuel consumption for direct deorbiting and selection of maneuvering intervals for launch unit submersion in a given area of the world ocean are obtained. The calculations of the Earth shadow- and semishadow-sunlight time for small spacecraft are performed.
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