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  • Space Simulation: Designing Update Tools for Spacecraft Thermal Vacuum Tests

    Paper number

    IAC-05-C2.6.03

    Author

    Dr. Jose Sergio Almeida, Instituto Nacional de Pesquisas Espaciais (INPE), Brazil

    Year

    2005

    Abstract
    This work presents an overview of the technology available today for the specification and design of space simulation chambers as an appropriate and reliable tool dedicated to spacecraft testing.
    A space simulation chamber, together with its complementary test equipment, has the hard and challenging task of reproducing the environmental conditions in terms of low pressure and the extremes of temperature that the spacecraft will face when lunched into orbit or, in the case of probes, on their way to the planets or other celestial bodies.
    Some decades ago, the technology available and applied to obtain high vacuum levels and to produce the required temperature conditioning on flight hardware were quite often limited whilst relatively expensive. The space simulation chambers were then built and operated with a margin of uncertainty.
    Today with the modern spacecraft, payloads and other flight hardware becoming more and more complex in terms of geometry, size, subsystem layout, operating temperature limits, contamination sensitivity, reliability on the test data, etc, the requirements for the qualification of such flight hardware have demanding more technology in order to reach the expected success of the tests. Nowadays it is not difficult to have geostationary satellites with an operational lifetime of 15 years or more, not mentioning the deep space probes that quite often should operate for many years before reaching its final approach and goals of their mission. All these demand high reliability on the qualification tests.
    An example of the significant improvements in terms of spacecraft qualification for flight operation was the advance obtained by the computer modeling of the applied heat loads using the techniques of infrared lamps, cal-rods, etc. in contrast with the classic solar simulation technique. Although the technique of solar simulation can present the most accurate results, the cost of operation and maintenance of this testing equipment is still very high.
    In this work, an analytical comparison of the over-the-years differential design of the chamber vessel is presented. In additional, for the integrated main subsystems and new testing and analysis equipment of the updated thermal vacuum chambers, their main characteristics and performance are also included and discussed.
    
    
    Keywords: Space Simulation, Thermal Vacuum Chamber, Spacecraft Testing Techniques
    
    Abstract document

    IAC-05-C2.6.03.pdf

    Manuscript document

    IAC-05-C2.6.03.pdf (🔒 authorized access only).

    To get the manuscript, please contact IAF Secretariat.