Small Business Innovation Research/Small Business Tech Transfer
Cryogenic Composite Tank Fabrication for Reusable Launch Vehicles, Phase I
Project Introduction
XCOR has conducted extensive research and development, and material characterization analysis of a nonflammable, high-strength, lightweight thermoplastic fluoropolymer composite material, trademarked NonburniteTM, which is suitable for making reusable, reliable, low cost cryogenic tanks and structures for space flight service. XCOR's composite material is lighter than metal, and unlike graphite/epoxy, nonflammable. The material is immune to microcracking, has a low coefficient of thermal expansion (CTE), and is capable of withstanding hundreds of cryogenic temperature cycles. Additionally, it is durable, repairable, and can withstand extreme hot and cold temperatures. The fluoropolymer composite maintains strength and flexibility at extreme temperatures (-260 to plus 280 degrees C/-436 to plus 536 degrees F).Low CTE also allows this composite to be built into a vehicle's primary structure. Used as the internal skin in a sandwich structure (Nonburnite, foam, and carbon/epoxy) the composite skin-foam-skin material provides both thermal insulation and structure. These features, along with the high strength-to-weight ratio, make it an enabling technology for building lighter, highly reusable, and more robust propellant tanks, thus reducing need for maintenance between flights. Further, XCOR believes significant commercialization opportunities exist for the material after its manufacturing processes have matured.
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Anticipated Benefits
XCOR believes there are significant commercialization opportunities for the material once manufacturing processes are matured. NonburniteTM is suitable for lightweight, linerless oxygen-compatible tanks for propulsion, fuel cell, life support, and related infrastructure applications, including aircraft cargo hold structures and containers, high and low temperature environments where flammability is of concern, and large volume commercial or retail applications such as in home oxygen tanks that are lighter weight and easier to maneuver by typically elderly or infirm users. This proposed effort has particular relevance to several key programs at NASA. First, the Space Operations Mission Directorate (SOMD) provides a foundation of science and technology for many aspects of manned and robotic space travel and payloads ranging from micro satellites to manned systems. The pursuit of high reliability, safety and affordability is clearly relevant as it applies to NonburniteTM and SOMD's objectives. The use of a human rated (nonflammable) cryogenically capable, reliable, high strength, low weight composite structures could save significant weight throughout the Orion and Heavy Lift Crew Exploration vehicle programs. The Human Research Program (HRP) seeks to perform advanced high risk technology development in support of human exploration systems. The fundamental nature of Nonburnite also has particular potential relevance to HRP. Finally, the Exploration Technology Development Program (ETDP) at Langley Research Center (LaRC) has a mission to look at advanced technology insertion into space vehicle programs.
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Primary U.S. Work Locations and Key Partners
| Organizations Performing Work | Role | Type | Location |
|---|---|---|---|
| XCOR Aerospace | Lead Organization | Industry | Mojave, California |
Marshall Space Flight Center
(MSFC)
|
Supporting Organization | NASA Center | Huntsville, Alabama |
Primary U.S. Work Locations
-
Alabama
-
California
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Organizational Responsibility
Responsible Mission Directorate:
- Space Technology Mission Directorate (STMD)
Lead Organization:
- XCOR Aerospace
Responsible Program:
- Small Business Innovation Research/Small Business Tech Transfer
Project Management
Program Director:
Program Manager:
Principal Investigator:
- Jeff Greason
Project Duration
Start: Feb 2011
End: Sep 2011
Technology Maturity (TRL)
| Start: | 3 |
| Current: | 5 |
| Estimated End: | 5 |
Applied Research
Development
Demo & Test
Technology Areas
Primary:
- TX12 Materials, Structures, Mechanical Systems, and Manufacturing
- TX12.1 Materials
- TX12.1.1 Lightweight Structural Materials
Target Destinations
The Moon, Mars
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