This content is not included in
your SAE MOBILUS subscription, or you are not logged in.
Thermal Design and Performance of the Axial Scientific Instrument Protective Enclosure (ASIPE) for Hubble Space Telescope On-Orbit Servicing
Annotation ability available
Sector:
Language:
English
Abstract
Thermal design and verification testing of the ASIPE, one element of the re-usable Space Support Equipment (SSE), are discussed with respect to how unique and competing requirements are satisfied for Scientific Instrument (SI) conditioning, safety, and on-orbit servicing operations. A system approach, rather than optimizing any one performance characteristic, results in a robust design. The special thermal testing required to verify the unique enclosure is described. Analytical modeling predictions are compared with on-orbit telemetry from the Hubble Space Telescope (HST) First Servicing Mission (FSM). Emphasis is on why the design works well, rather than the specific hardware selected. Those involved in thermal designs of hardware with astronaut interaction may find interest in this paper.
Authors
Citation
Krein, S., Ducas, W., Niedringhaus, W., and Ousley, W., "Thermal Design and Performance of the Axial Scientific Instrument Protective Enclosure (ASIPE) for Hubble Space Telescope On-Orbit Servicing," SAE Technical Paper 951744, 1995, https://doi.org/10.4271/951744.Also In
References
- Ousley, W. “Thermal Design of Space Support Equipment for the Hubble Space Telescope Servicing Mission” 24th ICES Conference SAE Paper No. 941571 Friedrichshafen, Germany June 20-23 1994
- Davis, A. “HST Servicing Mission Space Support Equipment Thermal Analysis Report” NASA GSFC Report P4420561 May 1993
- The First HST Servicing Mission ORU Carrier Design and Performance Specification NASA GSFC Document 408-ST-1105-0002 February 1992