A thermal control approach for a solar electric propulsion thrust subsystem

Technical Report · Fri Jun 01 00:00:00 EDT 1979

OSTI ID:5595026

Maloy, J E; Oglebay, J C

A thrust subsystem thermal control design is defined for a Solar Electric Propulsion System (SEPS) proposed for the comet Halley Flyby/comet Tempel 2 rendezvous mission. A 114 node analytic model, developed and coded on the systems improved numerical differencing analyzer program, was employed. A description of the resulting thrust subsystem thermal design is presented as well as a description of the analytic model and comparisons of the predicted temperature profiles for various SEPS thermal configurations that were generated using this model. It was concluded that: (1) a BIMOD engine system thermal design can be autonomous; (2) an independent thrust subsystem thermal design is feasible; (3) the interface module electronics temperatures can be controlled by a passive radiator and supplementary heaters; (4) maintaining heat pipes above the freezing point would require an additional 322 watts of supplementary heating power for the situation where no thrusters are operating; (5) insulation is required around the power processors, and between the interface module and the avionics module, as well as in those areas which may be subjected to solar heating; and (6) insulation behind the heat pipe radiators is not necessary.

• Research Organization: National Aeronautics and Space Administration, Cleveland, OH (USA). Lewis Research Center
• OSTI ID: 5595026
• Report Number(s): N-79-27236
• Country of Publication: United States
• Language: English

Related Subjects

14 SOLAR ENERGY
140600* -- Solar Energy-- Photovoltaic Power Systems
ANALYTICAL SOLUTION
CONTROL
CONTROL SYSTEMS
COOLING SYSTEMS
ELECTRONIC EQUIPMENT
EQUIPMENT
HEAT EXCHANGERS
HEAT PIPES
ION THRUSTERS
MATHEMATICAL MODELS
PHOTOVOLTAIC POWER SUPPLIES
POWER SUPPLIES
PROPULSION
RADIATORS
SOLAR ELECTRIC PROPULSION
SOLAR EQUIPMENT
SPACE VEHICLES
SPACECRAFT POWER SUPPLIES
TEMPERATURE CONTROL