Integrated Lightweight Structure and Thermal Insulation for Mars Rover

951523

07/01/1995

Event
International Conference on Environmental Systems
Authors Abstract
Content
An integrated lightweight structure and thermal insulation has been developed for the Mars Rover Warm Electronics Box (WEB). It combines a low thermal conductivity fiber reinforced composite structure with co-cured thermal control surfaces and an ultralightweight hydrophobic solid silica aerogel which eliminates convection and minimizes conduction and radiation. It provides excellent thermal insulation both at low gas pressures and in vacuum; and meets the structural requirements for spacecraft launch loads and for a 60 g impact landing at Mars without damage to the insulation or structure. The integrated design provides for variable conductance to meet the different thermal requirements for the different phases of operation. The system incorporates heat conduction paths to provide thermal control on the ground and during interplanetary cruise, which are then disconnected for Mars operation. The thermal performance of the design was evaluated at prototype level, and as a full structural engineering model and flight system. The thermal conductivity for the structure with insulation was measured at the prototype level to have a value of 0.033 W/mK and 24 °C at 1 atmosphere pressure, and in a10 torr CO2 simulated Mars environment to be 0.0163 W/mK at 24 °C, 0.0126 W/mK at -27 °C and 0.0089 W/mK at -80 °C.
Meta TagsDetails
DOI
https://doi.org/10.4271/951523
Pages
13
Citation
Hickey, G., Braun, D., Wen, L., and Eisen, H., "Integrated Lightweight Structure and Thermal Insulation for Mars Rover," SAE Technical Paper 951523, 1995, https://doi.org/10.4271/951523.
Additional Details
Publisher
Published
Jul 1, 1995
Product Code
951523
Content Type
Technical Paper
Language
English