Hybrid LHP/Composite Heat Rejection Panels for UAV

Period of Performance: 05/17/1999 - 06/17/2001

$358K

Phase 2 SBIR

Recipient Firm

Thermacore, Inc.
780 Eden Rd Ofc
Lancaster, PA 17601
Principal Investigator

Abstract

Phase I showed that LHP condenser tubing can be embedded into the composite skin of the aircraft, essentially turning the aircraft skin into a radiator which can reject heat by both convection and radiation. With the addition of a single moving part, a by-pass valve which is activated by the internal pressure of the LHP, the system can autonomously add and subtract radiator surface in response to changing conditions and maintain operating temperatures within a relatively narrow range. The proposed Phase II effort would demonstrate the system by extensive prototype ground testing. The proposed Phase II effort would also pursue solutions to protential issues raised in the phase I work as well as system improvements and mass reduction. These areas include: - Freeze/thaw tolerance for extremely cold (