The Contribution of Thermal Effects to the Acceleration of the Deep-Space Pioneer Spacecraft

Abstract

A method for the computation of the radiative momentum transfer in the Pioneer 10 & 11 spacecraft due to the diffusive and specular components of reflection is presented. The method provides a reliable estimate of the thermal contribution to the acceleration of these deep space probes and allows for a Monte-Carlo analysis from which an estimate of the impact of a possible variability of the parameters. It is shown that the whole anomalous acceleration can be explained by thermal effects. The model also allows one to estimate the expected time evolution of the acceleration due to thermal effects. The issue of thermal conduction between the different components of the spacecraft is discussed and confirmed to be negligible.

arXiv comment17 pages, 5 figures. To appear in the Proceedings of the "1st IAA Conference on Dynamics and Control of Space Systems", 19-21 March 2012, Porto, Portugal

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