On-Orbit Cryogenic Propellant Storage Optimization

<p>The optimization of an on-orbit Cryogenic Propellant Storage (CPS) system enables human exploration missions by reducing launch vehicle mass to orbit requirements and providing an extensible approach for human spaceflight missions to near-Earth asteroids, the moon, and Mars. The optimal CPS sun-shield design and attitude control approach documented herein minimizes LH2 boiloff to near zero boiloff in Low Earth Orbit (LEO) using only passive thermal control techniques, eliminating the need for developing complex and costly active thermal control systems. The optimal CPS system design leverages the current human spaceflight infrastructure resulting in a new mission concept that achieves lower tank temperatures, leading to boiloff rates more than six times better than the best published results. The complexities and interdependencies of the CPS system design variables led to the creation of a tool capable of automated exploration of the CPS system design space using a Monte Carlo process with variable manipulation, as well as a new orbital thermal analysis global optimization tool that can be utilized for other complex orbital thermal design problems. The optimization tool interface provides a new industry approach for design optimization of on-orbit spacecraft.</p>

Name thesis:degree_name

Ph.D.

Level thesis:degree_level

Dissertation

Year

2014

Author dc:creator

• Lee, James T.

Contributors dc:contributor

• Corinne Lengsfeld

• Cryogenic propellant storage
• Spaceflight
• Thermal control
• Engineering
• Heat Transfer, Combustion
• Other Mechanical Engineering
• Space Vehicles

Statement dc:rights

• <p>Copyright is held by the author. Permanently suppressed.</p>

Language dc:language

en

Repository record dc:identifier

https://digitalcommons.du.edu/etd/2192

OAI identifier oai:identifier

oai:digitalcommons.du.edu:etd-3184