Abstract Performing the sensitivity analyses of the contact conduction and the position of thermostat on the basis of the thermal model established, the study of thermal design is accomplished for the preparation of possible mechanical interface change of the satellite propulsion system depending on the satellite system design. A relatively simple thermal model is taken into consideration for the convenience of the analysis. A variety of the spacecraft bus voltages and the contact resistances are examined as well as the position of thermostat on propulsion components. As a consequence, even though the mechanical interface condition is changed on the same module, the successful thermal design could be achieved if we design the heater to have sufficiently large power with reference to the heritage value of contact resistance. Besides the reasonable performance on the thermal control is assured with the thermostat location errors, if the uncertainty in the position of thermostat is not quite large when assembling tank module.
Sensitivity analyses of satellite propulsion components with their thermal modelling
Advances in Space Research ; 47 , 3 ; 466-479
2010-09-19
14 pages
Article (Journal)
Electronic Resource
English
Sensitivity analyses of satellite propulsion components with their thermal modelling
Online Contents | 2011
|THERMAL TRANSPIRATION APPLIED TO SMALL SATELLITE PROPULSION
TIBKAT | 2020
|