Transfer Line Chilldown Heat Transfer of Cryogenic Propellant in Microgravity using Low-thermally Conductive Coating and Pulse Flow for Space Exploration

Abstract

The enabling of in-space cryogenic engines and cryogenic fuel depots for future space exploration missions begins with development of cryogenic fluid management systems upstream in the propellant feed system. Before single-phase liquid can flow to the engine or customer spacecraft receiver tank, the connecting transfer line can be chilled down to cryogenic temperatures. In some examples, a method to quench the line is to use the cold propellant itself. When a cryogenic fluid is introduced into a warm transfer system, two-phase flow quenching ensues. Due to the projected cost of space exploration, it is desired to perform this chilldown process using the least amount of propellant. The embodiments include enhancements that reduce the amount of propellant consumed during chilldown while in a microgravity environment. Experiments were performed to examine the effects of using low thermally conductive coatings and pulse flow on the chilldown process.

Dependencies are inferred from the claim text.