AbstractIn this paper, we present the development of a retro-thruster, the design of a retro-propulsion module, and a preliminary flight of the module in a landing demonstration. First, a retro-monopropellant thruster with the maximum thrust of 350N that employs hydrogen peroxide as a monopropellant was developed. It's thrust force, efficiency of characteristic velocity, and specific impulse were evaluated during the course of it's development. To control the thrust force, two solenoid valves and a pulse width modulation (PWM) flow control valve were incorporated into the thruster design. Second, a retro-propulsion module with a wet mass of 23kg was designed and fabricated. All the required components including tanks, propellant tubes, a pressure regulator, valves, a retro-thruster, and support structure were integrated into the module. Finally, a preliminary flight test with thrust and altitude control was carried out successfully. In this test, the throttling of the thrust force and altitude control was performed manually for safety purposes.


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    Title :

    Preliminary flight test of hydrogen peroxide retro-propulsion module


    Contributors:
    An, Sungyong (author) / Jo, Sungkwon (author) / Wee, Jeonghyun (author) / Yoon, Hosung (author) / Kwon, Sejin (author)

    Published in:

    Acta Astronautica ; 67 , 5-6 ; 605-612


    Publication date :

    2010-04-13


    Size :

    8 pages




    Type of media :

    Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    English





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