The Compatibility Evaluation Method of the 500N ^|^amp; 120N Japanese Bi-Propellant Thrusters with the HTV System ^|^amp; Operation Design

Abstract

This paper describes the evaluation method of the new Japanese thrusters design, balancing and verification of interface compatibility with the HTV system and operation design. Thruster performance directly affects the performance of the space craft. Therefore, the thruster replacement from the imported thrusters to the new Japanese thrusters required the evaluation from the view point of high-order system level. It is important to select the appropriate elements, verify their relationships, and create a feedback mechanism which allows modification of each element. This method will facilitate the overall systems design for future inter-orbit transfer vehicles.

Visualization of Coolant Liquid Film Dynamics in Hypergolic Bipropellant Thruster

“…Combinations of hypergolic fuel and oxidizer, such as hydrazine or monomethylhydrazine (MMH) for fuel and a mixture of nitrogen tetroxide with approximately 3% nitric oxide (MON3) for oxidizer, eliminate complex ignition systems. In the recent and future cargo spacecraft for the International Space Station [3][4][5][6] and in planetary exploration missions for descent and ascent modules [7][8][9], the bipropellant thrusters keep playing an essential role. The bipropellant thrusters use a combustion chamber generally made of ceramic [10] or high-temperature heat-resistant metal, such as niobium alloy [11,12] or one of the precious metals [13,14].…”