Concept Development and Feasibility Study for In-Space Propellant Tank Venting
Abstract
Lead Researchers
- Prof. Bingbing Li, Department of Manufacturing Systems Engineering and Management
- Prof. Christoph Schaal, Department of Mechanical Engineering
Collaborators
- NASA JPL: Dr. Douglas Hoffman, Dr. Richard Otis, Dr. Ryan Watkins, Dr. Bryan McEnerney
- NASA Goddard Space Flight Center: Ryan McClelland at Instrument Systems and Technology
- UCLA: Dr. Xiaochun Li, Dr. Morris Wang
- Honeywell Aerospace: Gregory Colvin, Bob DeMers
- Castheon Inc: Dr. Youping Gao, Mr. Steve James
- ASTM Additive Manufacturing Center of Excellence (AM CoE): Mr. Shane Collins
- SimInsights Inc: Mr. Rajesh Jha
- El Camino College: Mr. Jose Anaya
Student Team
- Dr. Changyu Ma, Postdoc in ARCS at CSUN
- Donald Palomino, Fellow, M.S. candidate in Manufacturing Systems Engineering at CSUN
- Paula Logozzo, Fellow, undergraduate student in Mechanical Engineering at CSUN
- Elliot Sadler, Fellow, M.S. candidate in Manufacturing Systems Engineering at CSUN
- Bodia Borijin, Intern, B.S. candidate in Structural Engineering at UCSD
- Andrew Wang, Intern, Portola High School
Funding
- Funding Organization: NASA
- Funding Program: MUREP Aerospace High-Volume Manufacturing and Supply Chain Management (MUREP High Volume), Grant number: 80NSSC22M0132
Alignment, Engagement and Contributions to the priorities of NASA’s Mission Directorates
Research Objectives
This work seeks solutions to propellant tank venting in micro-gravity with minimal loss. Although all concepts will be considered, solutions external to the propellant tank are preferred, as they could use existing (heritage) propellant tanks and avoid development costs related to designing and qualifying a new (or modified) tank.
Three objectives are proposed:
- Conduct research of the existing state-of-the-art for propellant management devices and in-space propellant transfer operations
- Develop a solution(s) to propellant tank venting in micro-gravity with minimal loss of propellant during a propellant transfer operation, preferably which can be applied to existing propellant tank designs, with a design goal of maximizing the propellant transfer flow rate
- Carry out a thorough analysis program to demonstrate concept design under differing operating conditions and use cases
Research Methods
This theoretical study encompasses analytical solution methods and an associated parametric study.
Research Deliverables and Products
- A final briefing to the Aerospace Corporation at the conclusion of the performance period
- Development of a model and associated computer code or software used to develop final modeling results
- Data files of final modeling results
Research Timeline
Start Date: 3/1/2024
End Date: 2/28/2025
Lead Researchers
- Prof. Vinicius Sauer
- Dr. Nhut Ho
- Prof. Bingbing Li
Collaborators
- Dr. Matthew E. Taliaferro, Dr. Samuel R. Darr, and Dr. Paul D. Lee at The Aerospace Corporation
Student Team
- Carl Bejosano
- Nathan Gabriel
- Jesus Sanchez
- Jessica Vasquez
- Cole Millett
Funding
- Funding Organization: The Aerospace Corporation