Simplified Algorithm for Closed Cycle Engines

Paper number

IAC-08.E2.1.3

Author

Ms. Victoria Lowe, United Kingdom

Year

2008

Abstract

Rocket engine efficiency is measured by its specific impulse (Isp), which is defined by the change in momentum per unit of propellant. This leads to the understanding that for a greater specific impulse, a smaller amount of propellant is required for a specified momentum.

As part of a study for Reaction Engines Ltd, a design investigation was initiated for a Martian rocket engine, and with in-situ propellant manufacturing it was appropriate to consider improved rocket engine efficiency or specific impulse as key requirements. One of the first considerations during the design process was to decide whether it was appropriate to use an open or closed engine cycle. After initial investigations an open cycle engine design was discounted, one reason being due to the fact that its specific impulse is inherently limited, and a closed cycle engine design was chosen. A closed cycle has many advantages, with limited pumping losses and high chamber pressures, but the closed cycle rocket engine is typically more difficult to design. This has lead to the development of a simplified and unique algorithm for closed cycle engines.

With a simplified algorithm for closed cycle engines, it will allow for many more efficient engines designs to move from imagination to reality.

Abstract document

IAC-08.E2.1.3.pdf

Manuscript document

IAC-08.E2.1.3.pdf (🔒 authorized access only).

To get the manuscript, please contact IAF Secretariat.