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Determination of Optimum Thermal Phase Angles at Mercury Perihelion for an Orbiting Spacecraft
Technical Paper
1999-01-2123
ISSN: 0148-7191, e-ISSN: 2688-3627
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English
Abstract
Due to the elliptical shape of Mercury’s orbit and the slow planetary spin rate, Mercury has a large surface temperature difference that creates highly variable spacecraft thermal environments that are a function of both planet solar distance and spacecraft orbit plane position. Being able to analytically simulate the severe thermal environments experienced by a spacecraft over the lifetime of a Mercury orbiting mission make it possible to realize a feasiable spacecraft thermal design.
The analysis described throughout this paper was used to characterize the temperature response as a function of initial phase angle conditions (αρ) when referenced at Mercury perihelion for a 3-axis stabilized spacecraft. Variables in the analysis include solar distance, argument of periapsis, and αρ. The selected orbit is highly elliptical, with a 720-minute period and a near polar inclination. Analysis results presented in this paper are specific for the spacecraft configuration, orbit geometry and inclination used, but the analytical techniques described can be applied to any spacecraft configuration, orbit geometry or inclination.
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Citation
Ercol, C. and Santo, A., "Determination of Optimum Thermal Phase Angles at Mercury Perihelion for an Orbiting Spacecraft," SAE Technical Paper 1999-01-2123, 1999, https://doi.org/10.4271/1999-01-2123.Also In
References
- MESSENGER Concept Study, JHU/APL April 1999
- Saito, H Yamakawa, H Kobayashi, Y Niukal, T Mercury Orbiter Mission with Chemical or Electric Propulsion 49th International Astronautical Congress Melbourne, Australia Sept 28 Oct 2 1998
- Ercol, C. J. Krein, S. J. An Efficient Procedure for Multiple Case Thermal Radiation Analysis of Spacecraft External Surfaces Proc. SAE International Conference on Environmental Systems (ICES), Paper 972534 July 1997