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Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.
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The circuit diagram for a temperature controller for use with very fast-acting (low thermal mass) furnace systems is presented and its features described. The operation of the slow response temperature controller is discussed.
Temperature control engineering of a nuclear electric spacecraft
Space suit internal temperature control by integration of heat pipe thermal radiator devices into external suit surface
Temperature control system, surface finishes and materials, thermal shields, and louvers of Mariner IV space probe
A closed loop thermoelectric temperature control system is developed for stabilizing sensitive RF integrated circuits within a microwave radiometer to an accuracy of + or - 0.1 C over a range of ambient conditions from -20 C to +45 C. The dual mode (heating and cooling) control concept utilizes partial thermal isolation of the RF units from an instrument deck which is thermally controlled by thermoelectric coolers and thin film heaters. The temperature control concept is simulated with a thermal analyzer program (MITAS) which consists of 37 nodes and 61 conductors. A full scale thermal mockup is tested in the laboratory at temperatures of 0 C, 21 C, and 45 C to confirm the validity of the control concept. A flight radiometer and temperature control system is successfully flight tested on the NASA Skyvan aircraft.
A thermoelectrically temperature controlled quartz crystal microbalance (QCM) system was developed for the measurement of ion thrustor generated mercury contamination on spacecraft. Meaningful flux rate measurements dictated an accurately held sensing crystal temperature despite spacecraft surface temperature variations from -35 C to +60 C over the flight temperature range. An electronic control unit was developed with magentic amplifier transformer secondary power supply, thermal control electronics, crystal temperature analog conditioning and a multiplexed 16 bit frequency encoder.
Human body temperature regulation feedback control system model by electric circuit analog, discussing digital simulation for static and dynamic responses
Ranger and Mariner spacecraft temperature control design, test and flight results
Temperature control of orbital otolith experiment on Apollo flight
Thermal radiation characteristics of spacecraft temperature control louvers in solar space environment, discussing specular reflection
Temperature control in interplanetary spacecraft
The concept of temperature control of an electronic component using a single Loop Heat Pipe (LHP) is well established for Aerospace applications. Using two LHPs is often desirable for redundancy/reliability reasons or for increasing the overall heat source-sink thermal conductance. This effort elaborates on temperature controlling operation of a thermal system that includes two small ammonia LHPs thermally coupled together at the evaporator end as well as at the condenser end and operating "in parallel". A transient model of the LHP system was developed on the Thermal Desktop (TradeMark) platform to understand some fundamental details of such parallel operation of the two LHPs. Extensive thermal-vacuum testing was conducted with two thermally coupled LHPs operating simultaneously as well as with only one LHP operating at a time. This paper outlines the temperature control procedures for two LHPs operating simultaneously with widely varying sink temperatures. The test data obtained during the thermal-vacuum testing, with both LHPs running simultaneously in comparison with only one LHP operating at a time, are presented with detailed explanations.
Temperature control system for space shuttles
Skin and auditory meatus temperature readings supply control signal for temperature control valve in fluid temperature control system which provides increased subject comfort and responds to directly measured physiological cooling needs. System applications include medical care and thermal protection garment manufacturing.
Design considerations for thermostatic fin spacecraft temperature control
Temperature control engineering of nuclear- electric spacecraft
Apparatus for measuring emittance and absorptivity of satellite temperature control surfaces
Sensitivities of condenser, radiator, and pump bypass temperature controls to control flow