Self-contained heat rejection module for future spacecraftThis paper discusses development of a Self-Contained Heat Rejection Module (SHRM) which can be used on a wide variety of future spacecraft launched by the space shuttle orbiter. The SHRM contains radiators which are deployed by a scissor-mechanism and the flow equipment including pumps, accumulator, by-pass valves, and controllers necessary to reject heat from those radiators. Heat transfer between SHRM and the parent vehicle is effected by a contact heat exchanger. This device provides heat transfer between two separate flow loops through a mechanical connection. This approach reduces the time required to attach the SHRM to the payload, and increases the reliability of the SHRM flow loop since breaking into the fluid system in the field is not required. The SHRM concept also includes a refrigeration system to increase heat rejection capacity in adverse environments, or to provide for a lower return temperature, down to -23 C.
Document ID
19750056795
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Fleming, M. L.
Williams, J. L.
Baskett, J. D.
Leach, J. W. (LTV Aerospace Corp. Vought Systems Div., Dallas, Tex., United States)
Date Acquired
August 8, 2013
Publication Date
July 1, 1975
Subject Category
Man/System Technology And Life Support
Report/Patent Number
ASME PAPER 75-ENAS-42
Meeting Information
Meeting: Intersociety Conference on Environmental Systems