Micropropulsion Research at AFRL (Postprint)
Abstract
There is an increased requirement for microsatellites to support such future missions as formation-flying space-based surveillance, space control, and on-orbit satellite servicing. Devices that can provide precise impulse bits in the 10-micro-Newton range may be enabling for a new fleet of 25-kg class spacecraft supporting these missions. In response to this need, the Air Force Research Laboratory is developing a miniaturized propulsion unit: the Micro-Pulsed Plasma Thruster (Micro-PPT). Like a standard PPT, the Micro-PPT uses a surface discharge across the face of a solid Teflon(trademark) propellant to create and accelerate a combination of plasma and neutral vapor. The Micro-PPT substantially differs from the standard design by using a self-igniting discharge, eliminating the separate igniter circuit from the thruster. This simplification enables order-of-magnitude reductions in the thruster size and operational power level. A technique for accurately measuring the performance of microthrusters has also been developed. Proof-of-concept performance measurements have been performed that indicate a non-optimized Micro-PPT has a thrust-to-power ratio that is approximately half that of LES-8/9 with a 60X reduction in mass.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jul 01, 2000
- Accession Number
- ADA462314
Entities
People
- Frank S. Gulczinski Iii
- Gregory G. Spanjers
- James P. Lake
- Michael J. Dulligan
Organizations
- Air Force Research Laboratory