NASA SBIR 2008 Solicitation


PROPOSAL NUMBER: 08-1 X4.05-9752
SUBTOPIC TITLE: Composite Structures - Cryotanks
PROPOSAL TITLE: Composite Matrix Systems for Cryogenic Applications

SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Applied Poleramic Inc
6166 Egret Court
Benicia, CA 94510 - 1269
(707) 747-6738

PRINCIPAL INVESTIGATOR/PROJECT MANAGER (Name, E-mail, Mail Address, City/State/Zip, Phone)
Rich Moulton
6166 Egret Court
Benicia, CA 94510 - 1269
(707) 747-6738

Expected Technology Readiness Level (TRL) upon completion of contract: 3 to 4

TECHNICAL ABSTRACT (Limit 2000 characters, approximately 200 words)
As an alternative material to aluminum-lithium, cryotanks developed from fiber reinforced composites can offer significant weight savings in applications for fuel containment of liquid oxygen and hydrogen. For composite materials to be accepted and utilized in these structures, they must be resistant to microcracking. It is the objective of this work to develop a matrix system for aerospace composites that alleviates all forms of microcracking from cryogenic cycling regardless of the lay-up and configuration. This will be accomplished by using a novel chemistry that provides the necessary inherent network and backbone structure for this environment combined with newly developed nano-modifiers. This technology and approach will result in a high performance matrix system that has low or no cure shrinkage combined with very low CTE and extremely high toughness. Such a matrix will be combined with carbon fibers to fabricate lightweight, high performance composites that are expected to have the microcrack and permeability resistance required for cryotank structures. It is expected that the Technology Readiness Level will be 3-4 at the end of this Phase I research.

POTENTIAL NASA COMMERCIAL APPLICATIONS (Limit 1500 characters, approximately 150 words)
The successful completion of the Phase 1 and 2 research programs will enable the development of lower weight cryotanks for NASA launch vehicles. The microcrack resistant composite cryotanks will also provide reduced hydrogen permeability over that of traditional composite materials. Applications that would benefit from this technology include EDS propellant tanks, Altair propellant tanks, lunar cryogenic storage tanks, and Ares V tanks. In addition to the utilization of these materials for cryotanks, other space and aerospace applications may be found which require highly tough, low CTE composite matrices such as space and aerospace structures.

POTENTIAL NON-NASA COMMERCIAL APPLICATIONS (Limit 1500 characters, approximately 150 words)
In addition to cryotank composite structures, many composite applications and designs will benefit from the high toughness, low cure shrinkage, and low CTE of the matrix technology developed in this research. Commercial composite applications that have been limited by current matrix technology can be found in space, aerospace, and airplane structures. Specific applications that may benefit from the low CTE include high precision antennas, reflector components, and precision optical devices. The high toughness of these matrices will enable more damage tolerant composite for commercial aircraft structures, engine components such as fan blades and core cowls, and ballisitic applications. Also, this technology will enable stitched and advanced multiaxial perform to be utilized in many new applications that have been limited before by microcracking. Film adhesives for advanced structural bonding and composite cocure applications will also benefit from this technology.

NASA's technology taxonomy has been developed by the SBIR-STTR program to disseminate awareness of proposed and awarded R/R&D in the agency. It is a listing of over 100 technologies, sorted into broad categories, of interest to NASA.

Fluid Storage and Handling

Form Generated on 11-24-08 11:56