Design of a 3-D Printed Unified Hybrid Motor
暂无分享,去创建一个
Nanoscale satellites have emerged as an area of interest to a variety of entities. Due to their small volume and weight, nanoscale satellites can easily travel as secondary payloads on a launch vehicle, but they are typically limited in orbit selection due to the target orbit of the primary payload. This orbit selection limitation can be mitigated through the addition of a propulsion system to a nanoscale satellite. This paper details the design analysis of a printed hybrid thruster for use in a nanoscale satellite propulsion module. The thruster design uses nitrous oxide and a nylon based fuel propellant combination. The analysis predicts an average thrust of 65 N and a specific impulse of 217 s for the thruster. Future work will include experimental testing at the University of Alabama in Huntsville Propulsion Research Center to provide validation of the analysis for use in design of a propulsion module.
[1] Travis S. Taylor,et al. Introduction to Rocket Science and Engineering , 2009 .
[2] H. Seifert,et al. Rocket Propulsion Elements , 1963 .
[3] Frank P. Incropera,et al. Fundamentals of Heat and Mass Transfer , 1981 .
[4] Robert A. Frederick,et al. Testing and Modeling of a Porous Polyethylene Axial-Injection, End-Burning Hybrid Rocket Motor , 2015 .