Temperature control of the Mariner Venus 67 spacecraft
Temperature control design, instrumentation, and performance characteristics of Mariner 5 spacecraft
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Temperature control design, instrumentation, and performance characteristics of Mariner 5 spacecraft
Passive temperature control system for aerospace instruments, discussing physical design and components reliability
Precision temperature control of large orbiting telescopes
Feasibility of movable surface fins for spacecraft temperature control
Design study of temperature control flux monitor for Mariner Mars 1969 spacecraft
Temperature control and thermal coupling of cesium adsorption porous tungsten, charcoal and graphite reservoirs
Spacecraft applications that require the efficient cooling of high-powered components, the precise temperature control of sensitive electronic and optical components, and the protection of cooled components from temporary, adverse environmental conditions are increasing. Heat pipes using gas, vapor, liquid, or voltage control to provide variable conductance or diode thermal behavior have been and are continuing to be developed to meet increasingly difficult requirements. The various control techniques are critically evaluated using characteristic features and properties, including heat transport capability, volume and mass requirements, complexity and ease of fabrication, reliability, and control characteristics. As a result, advantages and disadvantages of specific approaches are derived and discussed. Using four development levels, the state-of-the-art of the various heat pipe temperature control techniques is assessed.
Design and performance of Mariner 5 temperature control assembly coatings
Mariner 5 temperature control reference design, test and performance
Computer optimization of spacecraft optical coatings for temperature control, using finite element analysis and matrix inversion
Fluidic temperature control system for liquid cooled space suits
Computer optimization of spacecraft optical coatings for temperature control, using finite element analysis and matrix inversion
Definition and design study of temperature control flux monitor for Mariner Mars 1969
Optimization for selection of optical coating patterns of external surfaces of spacecraft for temperature control
Spacecraft surface temperature-control coating requirements, selection and performance in prelaunch and space environments
Spacecraft surface temperature-control coating requirements, selection and performance in prelaunch and space environments
A temperature control system, which includes a modified wheatstone bridge with a resistive-capacitive (RC) circuit in one leg of the bridge, is disclosed. The RC circuit includes a resistor which provides an effective resistance as a function of its absolute resistance and the on-time to off-time ratio of pulses supplied to a switch connected across it. A sawtooth voltage is produced across the RC circuit. The voltage is compared with the voltage across a temperature sensor with heat being applied during each pulse period portion when the sawtooth voltage exceeds the voltage across the temperature sensor.
Passive temperature control coatings for Apollo spacecraft ablative thermal protection system