A Halley's comet rendezvous mission was investigated at the Jet Propulsion Laboratory using either a solar sail or an ion propulsion spacevehicle. This paper discusses a number of thermal control aspects of the two types of solar sails studied: the square sail and the heliogyro sail. The sail vehicle (sail plus spacecraft) would be launched in 1982, navigated into a 0.25 AU cranking orbit about the Sun to develop a retrograde orbit, rendezvous with Halley during 1986, and continue its mission to 4 AU. Such a mission would subject many exposed surfaces of the sail vehicle to solar intensities ranging from 16 to less than 0.1 solar constant. A highly reflective coating required for the sunlit side of the sail to produce the necessary propulsive force and a highly emittive coating for the back to maintain a low sail temperature were developed during the study. The thermal environments for the sail and spacecraft (attached to the center of the sail) and spacecraft shielding requirements are described with presentation of analytical results. (De Posamentier)
Thermal control of a solar sail
Temperatursteuerung bei Raumfahrten mit Sonnensegel
AIAA-Papers ; 1-9
1978
9 Seiten, 19 Bilder, 3 Quellen
Aufsatz (Konferenz)
Englisch
Thermal control of a solar sail
NTRS | 1978
|Thermal control of a solar sail
AIAA | 1978
|Spacecraft solar sail processing method and solar sail
Europäisches Patentamt | 2023
|NTRS | 2018
|