Solar Thermal Propulsion for Microsatellite Manoeuvring
Abstract
The thesis will trace the development of the microsatellite solar thermal engine from conception through mission analysis design, modelling, fabrication, component, and system testing. On-sun testing of 14-cm and 56-cm diameter solar concentrating mirrors has clearly validated initial optical ray trace modelling and suggests that there is significant performance margin built into test concentrators. Electrical heating tests on two solar cavity receivers the Mk. I and Mk. II, have demonstrated the designs robustness at temperatures approaching 2,000 K. over many thermal cycles. Flow testing in nitrogen, helium and ammonia demonstrated the Mk. I's excellent heat transfer capability and the Mk. II's survivability over multiple firing cycles. A novel solar thermal engine concept, utilizing low-attenuation optical fibre for power transfer to a remote receiver has been shown to permit the decoupling of the receiver from the concentrating mirror's focus, permitting multiple mirror inputs to heat a single receiver and allowing the receiver to be placed anywhere on the host spacecraft, minimizing design and operational impacts. A variant of this engine is intended to fly aboard a Surrey satellite by 2006.
Document Details
- Document Type
- Technical Report
- Publication Date
- Sep 01, 2004
- Accession Number
- ADA428170
Entities
People
- F. G. Kennedy
Organizations
- University of Surrey