High Performance Pulse Motor for Mission Flexibility

Award Information
Agency:
Department of Defense
Branch
n/a
Amount:
$749,132.00
Award Year:
2010
Program:
SBIR
Phase:
Phase II
Contract:
FA9300-10-C-3004
Award Id:
86181
Agency Tracking Number:
O2-0865
Solicitation Year:
2008
Solicitation Topic Code:
OSD08-PR4
Solicitation Number:
2008.1
Small Business Information
2750 Indian Ripple Road, Dayton, OH, -
Hubzone Owned:
N
Minority Owned:
N
Woman Owned:
N
Duns:
130020209
Principal Investigator:
Michael Fisher
Prog Mgr, Propulsion Tech
(937) 320-1877
fishermj@crgrp.net
Business Contact:
Stephen Vining
Vice President, Governmen
(937) 320-1877
viningsd@crgrp.net
Research Institution:
n/a
Abstract
Although solid rocket motors (SRM) are ideally suited to many propulsion applications, their lack of controllability restricts their mission flexibility. Following ignition of an SRM"s propellant grain, combustion continues until all propellant is consumed. Controllability of the motor"s thrust profile can provide improved missile performance and multi-role capability. One approach to gaining controllability is to use a pulse motor configuration, in which multiple solid propellant grains, physically separated by a barrier, are ignited individually, and burn independently, thereby providing multiple, discreet thrust pulses. Past development programs have proven technologies capable of providing thrust management but have not entered service mainly due to reduced propellant mass fraction and resulting loss in total impulse. A need exists for advanced materials and processes to overcome these performance losses and provide pulse motor thrust management payoffs at affordable cost and with high reliability and safety. Cornerstone Research Group Inc. (CRG) proposes to demonstrate feasibility of high performance solid rocket pulse motors with bonded end closures, incorporating innovative materials and manufacturing processes. Low cost, reliable manufacturing processes, coupled with advanced, lightweight, high performance materials, will provide the capability to achieve the desired thrust management and resulting performance enhancements.

* information listed above is at the time of submission.

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