Re-entry aerodynamics derived from space debris trajectory analysis

Details Re-entry aerodynamics derived from space debris trajectory analysis Re-entry aerodynamics derived from space debris trajectory analysis

May 1992

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1992p%26ss...40..641c&link_type=abstract

Planetary and Space Science (ISSN 0032-0633), vol. 40, no. 5, May 1992, p. 641-646.

Computer Science

1

Aerodynamic Characteristics, Atmospheric Entry, Earth Orbital Environments, Space Debris, Trajectory Analysis, Atmospheric Models, Drag Coefficients, Gas-Solid Interfaces, Trajectory Planning

Scientific paper

This paper considers the technique of orbital analysis as a means of determining the ill-defined gas-surface interaction between spacecraft and atmospheric molecules in low earth orbit. The interaction is a major uncertainty in trajectory predictions for a body moving within an atmosphere. The rate of change of the orbital period of a debris object, the uncontrolled Salyut 7/Kosmos 1686 space station, is analyzed in order to determine the free molecular drag coefficient. The results are compared with theoretical values for the drag coefficient calculated using a complex representation of the vehicle configuration and motion and applying the Monte Carlo Test Particle method. Results suggest a nature of re-emission very close to the classical diffuse, totally accommodated case was occurring at the surface of the debris object as it approached re-entry. However, the determined drag coefficient and therefore the derived interaction are found to be very sensitive to the neutral density and therefore the atmospheric model used in the analysis.

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