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Solid Rocket Motor for Ultralow Temperature Operation During the Mars Sample Return Mission

Award Information
Agency: National Aeronautics and Space Administration
Branch: N/A
Contract: NNX13CM23P
Agency Tracking Number: 125385
Amount: $124,868.00
Phase: Phase I
Program: SBIR
Solicitation Topic Code: S4.03
Solicitation Number: N/A
Timeline
Solicitation Year: 2012
Award Year: 2013
Award Start Date (Proposal Award Date): 2013-05-23
Award End Date (Contract End Date): 2013-11-23
Small Business Information
AL
Huntsville, AL 35806-3200
United States
DUNS: 839422763
HUBZone Owned: No
Woman Owned: No
Socially and Economically Disadvantaged: Yes
Principal Investigator
 Robert Askins
 Principal Investigator
 (256) 714-9771
 reaskins@aol.com
Business Contact
 Sandra Fossett
Title: Business Official
Phone: (256) 562-2165
Email: Sandra.Fossett@asi-hsv.com
Research Institution
 Stub
Abstract

A small Mars (or other celestial body) ascent vehicle is unlikely to achieve the necessary propellant fraction required to achieve orbit. Scaling down of liquid propulsion systems, as shown in the figure, is difficult. In the 100-kg class of vehicles, liquid propellant vehicle designers should expect a propellant fraction of only 0.75. In contrast, solid rocket motors (SRM) scale down much easier, so designers should expect a propellant fraction of at least 0.92. To be practical, however, the SRM must operate in extreme low temperature environments, which is difficult for state of the art polybutadiene binders. ASI proposes to develop a new, low temperature binder based upon siloxane. Siloxane polymers have glass transition temperatures below 150K, making them ideal for use on Mars with little or no external heaters required. A siloxane binder SRM-based MAV will easily achieve the propellant fraction needed for a sample return mission.

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

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