Micro-Scale Nozzle Technology Used in a Compact Thermal Management System for Solid-State Lasers

Award Information
Agency: Department of Defense
Branch: Missile Defense Agency
Contract: FA9453-04-M-0245
Agency Tracking Number: B041-006-1480
Amount: $99,956.00
Phase: Phase I
Program: SBIR
Awards Year: 2004
Solicitation Year: 2004
Solicitation Topic Code: MDA04-006
Solicitation Number: 2004.1
Small Business Information
RINI TECHNOLOGIES, INC.
3267 Progress Drive, Orlando, FL, 32826
DUNS: 608777798
HUBZone Owned: N
Woman Owned: N
Socially and Economically Disadvantaged: N
Principal Investigator
 Daniel P Rini
 President
 (407) 384-7840
 dan@rinitech.com
Business Contact
 Daneil Rini
Title: President
Phone: (407) 384-7840
Email: dan@rinitech.com
Research Institution
N/A
Abstract
Solid-state lasers (SSL's) are the most likely near term lasers that can be considered for deployment on space-based platforms. These electric laser systems pose unique challenges in that the cooling system must dissipate heat loads that are often ten times greater than the laser output, with high heat fluxes over large surface areas and limited heat rejection. Existing water-based micro-channel cooling technology requires large coolant flow rates and high pressure heads, leading to heavy and bulky thermal management systems that are not suited for deployment in space, and existing space qualified heat pipe cooling technologies are not capable of handling the heat fluxes of 100-350 W/cm2 generated by the laser diodes. In this effort Rini Technologies, Inc. proposes an innovative evaporative spray cooling (ESC) technique that will reduce the mass and volume of SSL cooling systems in space. The ESC system utilizes unique micro-nozzle arrays can dissipate the high heat fluxes generated by the laser diodes with substantially lower coolant flow rates and reduced pressure drops compared to micro-channel cooling techniques. If shown to be feasible, the proposed micro-nozzle ESC system can provide high heat flux thermal control to space based SSL's with acceptable weight impacts to the spacecraft increasing the laser power-to-mass and laser power-to-volume ratios.

* information listed above is at the time of submission.

Agency Micro-sites

US Flag An Official Website of the United States Government