Low Cost, High Efficiency, Pressurization System for Responsive Launch Operations

Award Information
Agency:
National Aeronautics and Space Administration
Branch
n/a
Amount:
$124,351.00
Award Year:
2012
Program:
SBIR
Phase:
Phase I
Contract:
NNX12CF02P
Award Id:
n/a
Agency Tracking Number:
115932
Solicitation Year:
2011
Solicitation Topic Code:
O2.03
Solicitation Number:
n/a
Small Business Information
238 Business Park Boulevard, Building 23B Suite J, Madison, AL, 35758-7552
Hubzone Owned:
N
Minority Owned:
N
Woman Owned:
N
Duns:
127963515
Principal Investigator:
Dave Sisk
Principal Investigator
(256) 461-8522
dave.sisk@kte-aerospace.com
Business Contact:
Dave Sisk
Business Official
(256) 461-8522
dave.sisk@kte-aerospace.com
Research Institution:
Stub




Abstract
KT Engineering (KTE) is pleased to submit this proposal to address the stated need for "innovative solutions that will allow spaceport launch service providers to operate in an efficient, low cost manner and increases capabilities associated with integration, checkout, and preparations required to configure and ready space systems for launch." We propose to conduct research and demonstrate feasibility of a novel launch vehicle pressurization system concept that will increase performance and reliability compared with traditional approaches, reduce dependence upon helium up to 50%, enable the use of low-cost commercial off the shelf technology, and demonstrate the automated ground processing associated with this technology. Our innovation is based on five major technology and operational elements including: 1) Tridyne Pressurant, 2) Distributed Storage and Control, 3) Cold Gas Storage / Warm Gas Delivery, 4) Bang-Bang Pressure Control, and 5) End-of-burn Tank Pressure Decay. Pump-fed launch vehicles will benefit from our innovative concept but the most significant benefits are achieved in cost-optimized pressure-fed systems such as KT Engineering's Radially Segmented Launch Vehicle (RSLV). We propose a six month Phase I program to refine the designs of the critical ground and airborne elements of this distributed pressurization system. We intend to demonstrate feasibility and more accurately quantify the benefits of our approach through analytical modeling, preliminary design, and high-flow, high-pressure testing of a prototype Tridyne catalytic reactor. The product of this effort will be engineering analysis and models, presentation materials from major reviews, a comprehensive final report, and our Phase II proposal. Under Phase II we will proposed to demonstrate design and operation of the ground and airborne elements of our pressurization system through prototype hardware fabrication and testing in the NASA KSC Launch Equipment Test Facility (LETF).

* information listed above is at the time of submission.

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