Refrigerant-Based Propulsion System for Small Spacecraft
Abstract
The recent increase in demand and the technological advances related to small spacecraft have driven the need to develop small subsystem components. in particular, more technically demanding mission objectives have given rise to the need for small, safe and efficient propulsion systems capable of maintaining orbit and attitude control. This paper presents the design, performance, and ground test of a low-pressure cold gas refrigerant propulsion system for use on a micro to nano class spacecraft (20-100 kg). the advantages of a refrigerant-Based propulsion system include spatial volume savings and good performance characteristics that are demonstrated through analysis and testing results. the inherent safety, ease of use and availability of the refrigerant, R-134a, makes it an ideal propellant for university-class satellite projects with modest budgets and for future small spacecraft in general.
Recommended Citation
C. R. Seubert et al., "Refrigerant-Based Propulsion System for Small Spacecraft," Collection of Technical Papers - 43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference, vol. 2, pp. 1347 - 1359, Curran Assocciates, Inc., Dec 2007.
Department(s)
Mechanical and Aerospace Engineering
International Standard Book Number (ISBN)
978-156347903-8
Document Type
Article - Conference proceedings
Document Version
Citation
File Type
text
Language(s)
English
Rights
© 2024 Curran Associates Inc., All rights reserved.
Publication Date
10 Dec 2007
