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Low-Shock Release Mechanism with Structural Function

Award Information
Agency: Department of Defense
Branch: Missile Defense Agency
Contract: F29601-02-C-0199
Agency Tracking Number: 02-0701
Amount: $69,974.00
Phase: Phase I
Program: SBIR
Solicitation Topic Code: N/A
Solicitation Number: N/A
Timeline
Solicitation Year: N/A
Award Year: 2002
Award Start Date (Proposal Award Date): N/A
Award End Date (Contract End Date): N/A
Small Business Information
111 Downey Street
Norwood, MA 02062
United States
DUNS: 076603836
HUBZone Owned: No
Woman Owned: No
Socially and Economically Disadvantaged: No
Principal Investigator
 Michael Gilbert
 Senior Scientist
 (781) 769-9450
 gilbert@eiclabs.com
Business Contact
 R. David Rauh
Title: President
Phone: (781) 769-9450
Email: drauh@eiclabs.com
Research Institution
N/A
Abstract

"The development of a multi-functional system for release or jettisoning of structures on launch vehicles and spacecraft is proposed. The system acts as both a release mechanism and as a structural component of an assembly prior to release. The primaryinnovation is the use of a high-strength adhesive, recently developed at EIC Laboratories, that is rapidly disbonded from a metallic surface by the application of a low-current voltage to the adhesive-substrate bondline. This electrically disbondingfunction allows the design of delatching and deployment mechanisms that consume very little power and avoids the extensive use of pyrotechnics or other high-energy sources for separating mechanical components. Advantages of the system include: reducedvibration, shock, and pyrotechnic contamination when jettisoning large structures such as fairings; reduced weight, volume and power consumption relative to paraffin-based or shape-memory-alloy thermal or motor-driven delatching mechanisms; and greaterflexibility in the design of space structures and launch vehicles. In Phase I, a low-outgassing version of the adhesive will be developed and incorporated into release mechanisms. The functional performance of the release mechanisms will be evaluated andthe pre-launch, launch, and space-environment stability and disbonding properties of the adhesive determined. Commercial applications in DoD, NASA and commercial launch vehicles and satellites are ant

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

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