NASA SBIR 2018-I Solicitation

Proposal Summary


PROPOSAL NUMBER:
 18-1- Z8.01-2763
SUBTOPIC TITLE:
 Cubesat Propulsion Systems
PROPOSAL TITLE:
 Compact High Performance Plasma Propulsion System
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Busek Company, Inc.
11 Tech Circle
Natick , MA 01760-1023
(508) 655-5565

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)
James Szabo
jszabo@busek.com
11 Tech Circle Natick, MA 01760 - 1023
(508) 655-5565

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)
Judy Budny
judy@busek.com
11 Tech Circle Natick, MA 01760 - 1023
(508) 655-5565
Estimated Technology Readiness Level (TRL) :
Begin: 2
End: 3
Technical Abstract

The Compact High Performance Plasma Propulsion System (CHPPPS) is an electric propulsion system for 12U – 27U CubeSats.  CHPPS is designed for high-value science missions which require high specific impulse, high reliability, and radiation tolerance.  CHPPPS includes a low power Hall Effect Thruster (HET), a hollow cathode for neutralizing the ion beam, a propellant management system, and a power processing unit (PPU).  The system is highly modular and appropriate for 12U – 27 U CubeSats in terms of size, mass, and power.  CHPPPS may be as small as 4U, depending upon the fuel load and specific component selection.  Thrust will be 3-8 mN, depending on the power supplied (60 – 135 W) and peak specific impulse will be >1100 s.  The thruster will be fueled with xenon or with game-changing iodine, which stores as a solid at very low pressure and much higher density than xenon.  The use of iodine significantly decreases spacecraft dry mass, and dramatically decreases propellant volume.  The impact of switching from xenon to iodine is most significant for volume limited spacecraft like CubeSats.  Whether the thruster is fueled by xenon or by iodine, the ion beam will be neutralized by a hollow cathode flowing noble gas.  The thruster will be powered by a compact, radiation tolerant power processing unit (PPU) previously developed for NASA and Air Force applications.  ACS may be provided by cold gas thrusters fed from the noble gas storage system.  In Phase I, the system design will be detailed and studied.  Work will include a proof of concept hardware demonstration at relevant power levels.

Potential NASA Applications

The proposed system would propel a small earth orbiting or interplanetary spacecraft, targeting 12U and 27U CubeSats and small satellites.  Applications include orbit raising and lowering, compensating for drag at low altitude, de-orbiting a spacecraft at EOL, changing orbit inclination and phase, NS and EW station-keeping in GEO, and constellation deployment and maintenance.  The system also enables a low cost demonstration of HET magnetic shielding with iodine propellant. 

Potential Non-NASA Applications

The integrated system will be actively marketed spacecraft platform providers, targeting CubeSats and small commercial buses.  Commercial and DoD applications include orbit raising and lowering, compensating for drag at low altitude, de-orbiting a spacecraft at EOL, changing orbit inclination and phase, NS and EW station-keeping in GEO, and constellation deployment and maintenance.


Form Generated on 05/25/2018 12:03:01