Design of interplanetary hybrid cubesat and smallsat propulsion systems

Elizabeth T. Jens, Ashley C. Karp, Jason Rabinovitch, Barry Nakazono, Antonietta Conte, David A. Vaughan

Research output: Chapter in Book/Report/Conference proceedingConference contributionpeer-review

21 Scopus citations

Abstract

Adoption of CubeSat technology is dramatically reducing the cost of entrance to space and broadening the participant base. Miniaturization of electronics and the development of small-scale components has allowed these small spacecraft to be developed into meaningful tools for science and technology. However, these small spacecraft have primarily been constrained to LEO due to a lack of viable small-scale propulsion systems. Stand-alone interplanetary CubeSat and SmallSat mission concepts require small propulsion systems capable of providing attitude control and completing relatively large ∆V maneuvers such as to achieve orbit insertion and orbit clean-up. There is currently no off-the-shelf propulsion system capable of delivering the impulse required for orbit insertion around another planet whilst fitting within the CubeSat form factor. It is assumed that standalone interplanetary CubeSats and SmallSats will be jettisoned shortly after receiving the required C3 (exit velocity from earth) to travel to the destination planet. Since these small spacecraft will be launched as a secondary payload on a high priority mission, any hazard introduced by the propulsion system must be mitigated. Propellant selection is a key factor that defines a propulsion system’s criticality to hazards such as leakage, explosive yield, fire, and pressure. Hybrid motors are well suited to this application as they have high performance and are inherently safe, due to the physical distance and phase separation of the fuel and oxidizer. In this paper the designs of two propulsion systems using a hybrid rocket motor are presented for a 12 U CubeSat and a 100 kg SmallSat. These designs are informed by recent test data. A discussion of the performance of these systems compared to alternative propulsion concepts is provided. The sensitivity of the designs to the various design assumptions is described along with a discussion of the steps required to progress this technology towards a flight demonstration.

Original languageEnglish
Title of host publication2018 Joint Propulsion Conference
DOIs
StatePublished - 2018
Event54th AIAA/SAE/ASEE Joint Propulsion Conference, 2018 - Cincinnati, United States
Duration: 9 Jul 201811 Jul 2018

Publication series

Name2018 Joint Propulsion Conference

Conference

Conference54th AIAA/SAE/ASEE Joint Propulsion Conference, 2018
Country/TerritoryUnited States
CityCincinnati
Period9/07/1811/07/18

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