AbstractThermal decomposition of hydrazine can be achieved when the fluid propellant is sprayed on an electrically heated surface. After the exothermal hydrazine decomposition reaction has been triggered, the electrical heating may be reduced or stopped completely. Investigations are made using an experimental thruster at a thrust level of 100 mN to 500 mN to achieve advantageous power consumption and thruster behavior by means of an optimal adjustment of heater configuration and propellant distribution within the reactor. Uniform distribution of very small quantities of propellant over the heater surface is essential for good performance. Tests have been most successful when the propellant is sprayed on fine-meshed screen. Further tests have been made using metal foam for distributing the propellant over a large surface. The foam pack has been heated up by internal heater coils to initiate decomposition. Metal foam offers some advantages when especially low propellant mass flowrates are used, but suitable foam materials are not available at this time.


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    Title :

    Investigation on an electrothermal hydrazine thruster


    Contributors:
    Twardy, H. (author)

    Published in:

    Acta Astronautica ; 4 , 7-8 ; 875-893


    Publication date :

    1976-09-17


    Size :

    19 pages




    Type of media :

    Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    English



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