Optimal design of a thermodynamic control system for cryogenic propellant storage.

Future operations in space exploration require to store cryogenic liquids for long duration. Residual heat loads, due to heat conduction in the launcher structure or solar radiation, induce cryogenic propellant vaporization and tank self-pressurization. The Thermodynamic Vent System (TVS) permits to control self–pressurization using the following procedure: a fraction of liquid propellant is removed from the tank by a pump, cooled down by a heat exchanger and re-injected inside the tank as a jet or a spray. As no natural heat sink is available in space, the cold source is created by removing another fraction of liquid propellant which is expanded in a Joule-Thomson valve and vented to space. The subcooled injection is followed by vapor condensation and liquid bath de-stratification due to mixing. In this work, a 0D transient thermodynamic model is applied to design a TVS system maximizing the storage duration under various heat load and tank size assumptions.