Ionic Liquid Propellants

Award Information
Agency:
Department of Defense
Branch
Missile Defense Agency
Amount:
$100,000.00
Award Year:
2009
Program:
STTR
Phase:
Phase I
Contract:
HQ0147-09-C-7060
Agency Tracking Number:
B08B-001-0014
Solicitation Year:
2008
Solicitation Topic Code:
MDA08-T001
Solicitation Number:
2008.B
Small Business Information
Orbital Technologies Corporation (ORBITE
Space Center, 1212 Fourier Drive, Madison, WI, 53717
Hubzone Owned:
N
Socially and Economically Disadvantaged:
N
Woman Owned:
N
Duns:
196894869
Principal Investigator:
Millicent Coil
Senior Propulsion Engineer
(608) 229-2812
coilm@orbitec.com
Business Contact:
Eric Rice
President and CEO
(608) 229-2730
knaufs@orbitec.com
Research Institution:
University of Wisconsin-Madison
Juan J DePablo
1415 Engineering Drive
Madison, WI, 53706-1691
(608) 262-7727
Nonprofit college or university
Abstract
Future BMDS interceptor systems require innovative propellants that provide significantly increased performance and, simultaneously, improved safety, insensitivity, and economy. ORBITEC and partner University of Wisconsin-Madison propose to develop a family of ionic liquid propellants to meet these needs. Ionic liquids are inherently non-volatile, stable, and dense, and have a large liquidus range; thus they are well-suited to be rocket propellants. A non-volatile yet highly energetic rocket propellant would not only improve insensitive munitions compliance but could also potentially enable shipboard use. The proposed Phase I program will include the design of the propellants, synthesis of small quantities, materials testing, and energy and performance calculations. The end result of the initial phase will be a set of the most promising samples for in-depth analysis in future work. Phase II work will synthesize larger quantities of the top formulations, conduct more extensive materials testing, and progress to combustion tests. This research program will produce a set of new liquid ionic rocket propellants for mono- and bi-propellant systems that will exceed the state of the art propellants in density specific impulse, insensitivity, and safety and will allow engineering of novel electrical ignition systems.

* information listed above is at the time of submission.

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