Thermal Management for Space Based High Energy Lasers

Award Information
Agency: Department of Defense
Branch: Missile Defense Agency
Contract: FA9453-04-M-0244
Agency Tracking Number: B041-005-1481
Amount: $99,951.00
Phase: Phase I
Program: SBIR
Awards Year: 2004
Solicitation Year: 2004
Solicitation Topic Code: MDA04-005
Solicitation Number: 2004.1
Small Business Information
3267 Progress Drive, Orlando, FL, 32826
DUNS: 608777798
HUBZone Owned: N
Woman Owned: N
Socially and Economically Disadvantaged: N
Principal Investigator
 Daniel P Rin
 President
 (407) 384-7840
 dan@rinitech.com
Business Contact
 Daniel Rini
Title: President
Phone: (407) 384-7840
Email: dan@rinitech.com
Research Institution
N/A
Abstract
In the proposed SBIR effort RTI will investigate an innovative cooling approach to dissipate the high heat fluxes generated by diode-pumped solid-state laser (SSL) systems. SSL systems require efficient heat transfer techniques that are capable of managing high heat fluxes and high transient loads (laser "on" vs laser "off"). Existing water-based micro-channel cooling technology is not suited for deployment of high-power SSL's in space due to high system weight. Existing space-qualified heat pipe cooling technologies are not capable of handling the heat fluxes of 100-350W/cm2 generated by the laser diodes. RTI's cooling approach dissipates the high heat flux with Evaporative Spray Cooling (ESC) technology and transports the heat via a pump loop to a thermal energy storage (TES) unit featuring enhanced phase change material encapsulated in a porous graphite matrix. TES is the key technology that enables a laser operating heat load an order of magnitude greater than the ultimate heat rejection rate to space. RTI will perform sub-scale demonstrations to determine feasibility, and provide a conceptual design for a 1kWo SSL system with traceability to a 100kWo system. If shown to be feasible, the proposed cooling techniques can provide high heat flux thermal management to space based solid-state lasers with acceptable weight impacts to the spacecraft.

* Information listed above is at the time of submission. *

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