A thermal shield concept for the Solar Probe missionThe Solar Probe spacecraft will travel to within 4 solar radii of the sun's center while performing a variety of fundamental experiments in space physics. Exposure to 2900 earth suns (400 W/sq cm) at perihelion imposes severe thermal and material demands on a solar shield system designed to protect the payload that will reside within the shield's shadow envelope or umbra. The design of the shield subsystem is a thermal/materials challenge requiring new technology development. While currently in the preproject study phase, anticipating a 1995 project start, shield preliminary design efforts are currently underway. This paper documents the current status of the mission concept, the materials issues, the configuration concept for the shield subsystem, the current configuration studies performed to date, and the required material testing to provide a database to support a design effort required to develop the shield subsystem.
Document ID
19910058767
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Miyake, Robert N. (Jet Propulsion Lab., California Inst. of Tech. Pasadena, CA, United States)
Millard, Jerry M. (Jet Propulsion Lab., California Inst. of Tech. Pasadena, CA, United States)
Randolph, James E. (JPL Pasadena, CA, United States)