Modelling of Propellant Management Systems in Early-Phase Launcher Development

Abstract

Liquid propellant storage, feed and management systems are an important domain in preliminary launcher design activities, as they drive system-level masses and vehicle layout. The Propellant Management Program (PMP) was developed by the German Aerospace Centre (DLR) department of Space Launcher Systems Analysis (SART) for rapid tank, feedline, pressurisation, cross-feeding and venting analysis. This program is an important part of DLR-SART’s development toolbox, and has an intended application in the initial sizing of propellant storage and management systems for new launcher concepts. While the physical models behind the program, such as thermal behaviour of propellant and tanks in flight, are welldeveloped, the application of the program as a preliminary design tool is yet to be validated. A wealth of data is publicly available for the Saturn-V rocket, including stage fact sheets flight data from the Apollo missions. This paper details the simulation of the Saturn-V rocket propellant storage, feed and pressurisation systems, undertaken as part of the validation of PMP as a preliminary design tool. The high complexity of the layout and propellant management strategy of the Saturn-V rocket also provided additional functional requirements for future versions of PMP, and highlighted the need for a new pressurisation system control scheme.