Guidance of a spacecraft with low lift-to-drag ratio to a landing point

Details Guidance of a spacecraft with low lift-to-drag ratio to a landing point Guidance of a spacecraft with low lift-to-drag ratio to a landing point

Dec 2010

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=2010cosre..48..534u&link_type=abstract

Cosmic Research, Volume 48, Issue 6, pp.534-541

Physics

1

Scientific paper

The problem of terminal control over a deorbiting spacecraft at the stage of its flight after leaving plasma (altitude of ˜40 km) is considered, the aim being to guide it to a preset landing point. The algorithm is based on a modification of the well-known method of proportional navigation, when a fixed point is the target. It is suggested to use satellite navigation systems (of the GLONASS or GPS types) and/or radio beacons, which should allow one to determine the spacecraft trajectory parameters with high precision. Single-channel control is performed by changing the roll angle according to current parameters of the trajectory, which ensures adaptability of the method. Examples of three-dimensional trajectories of flight are presented for a manned spacecraft with low lift-to-drag ratio (˜0.5), currently under design in Russia. The results of statistical modeling taking into account initial deviations of the trajectory parameters and wind disturbances are presented. A method of statistical choice of a reference trajectory for the guidance stage is suggested. A theoretical possibility of using the algorithm of spacecraft guidance (in case of in-light accident with a carrier launcher) to preset regions in the vicinity of launching route is demonstrated. A qualitative analysis of proportional navigation with a fixed target is presented.

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