Two-Phase Ammonia Pump for Mono-Propellant Warm Gas Pressurization

Award Information
Agency:
Department of Defense
Branch
n/a
Amount:
$742,748.00
Award Year:
2011
Program:
SBIR
Phase:
Phase II
Contract:
FA9300-11-C-3003
Award Id:
n/a
Agency Tracking Number:
F083-111-2293
Solicitation Year:
2008
Solicitation Topic Code:
AF083-111
Solicitation Number:
2008.3
Small Business Information
MA, Natick, MA, 01760-1023
Hubzone Owned:
N
Minority Owned:
N
Woman Owned:
N
Duns:
184629491
Principal Investigator:
Lynn Olson
Senior Scientist
(508) 655-5565
lynn@busek.com
Business Contact:
Judy Budny
Contracts Administrator
(508) 655-5565
judy@busek.com
Research Institution:
Stub




Abstract
ABSTRACT: An integrated warm gas pressurization of the main and ACS propulsion system offers simpler, more efficient propellant management than existing designs. The most operationally versatile system is based on a unique pump that forces liquid through a gasifier thus creating both the pressurant gas and warm gas for ACS thrusters. All components of such a system are COTS with the exception of the pump which is the focus of this program. The proposed pump uses no motors or mechanisms and has only one slowly moving part. In addition to mass and volume reduction, the system offers benefits such as launching the entire propulsion system unpressurized and a constant tank pressure operation which improves thruster performance. Furthermore, the warm gas can be used in place of cold gas for attitude control thrusters, providing increased specific impulse. In Phase I we built and demonstrated a proof of concept pump and modeled the dynamics of the entire propellant storage and management system. In Phase II we will produce and characterize the entire system and investigate its dynamics. The goals will be more than a factor of two reduction in pressurization system mass and a greater than 10% increase in thruster performance. BENEFIT: Successful demonstration of the proposed technique will enable use of warm gas pressurization on any spacecraft using mono-propellants, significantly improving propulsion system performance while reducing the system mass and volume. Warm gas pressurization could also possibly be used for bi-propellant systems. A majority of spacecraft have one or the other, so significant impact is expected.

* information listed above is at the time of submission.

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