A heating system for a component within a compartment of a spacecraft includes a fuel source, a gas generator, and a heat sink. The fuel source includes hydrazine. The gas generator is in fluid communication with the fuel source. The gas generator includes a catalyst. The catalyst is configured to decompose the hydrazine and generate an exhaust gas. The heat sink is thermally coupled to the gas generator and configured to receive heat from the exhaust gas of the gas generator. The heat sink is thermally coupled to the component within the compartment of the spacecraft to transfer heat from the exhaust gas to the component.


    Access

    Download


    Export, share and cite



    Title :

    Heating system for a spacecraft



    Publication date :

    2024-02-13


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64G Raumfahrt , COSMONAUTICS / F02K JET-PROPULSION PLANTS , Strahltriebwerke



    Heating system for an aircraft or spacecraft

    ALTAY MEHMET | European Patent Office | 2016

    Free access

    Spacecraft external heating variations in orbit

    Leffler, J.M. | Tema Archive | 1987



    Numerical Model for Solar Heating of Spacecraft

    Likissas, J. P. / Nguyen, T. H. / Canadian Aeronautics and Space Institute | British Library Conference Proceedings | 1994


    Radiation Heating Analysis of Hypersonic Re-entry Spacecraft

    Hao, Jingke / Zhang, Liang / Lyu, Junming et al. | British Library Conference Proceedings | 2019