NASA SBIR 2010 Solicitation

FORM B - PROPOSAL SUMMARY


PROPOSAL NUMBER: 10-1 X9.02-9877
SUBTOPIC TITLE: Advanced Integrated Hypersonic Entry Systems
PROPOSAL TITLE: Integrated Composite Structure for EDL Application

SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Fiber Materials, Inc.
5 Morin St
Biddeford, ME 04005 - 4497
(207) 282-5911

PRINCIPAL INVESTIGATOR/PROJECT MANAGER (Name, E-mail, Mail Address, City/State/Zip, Phone)
Benjamin N. Dwyer
bdwyer@fibermaterialsinc.com
5 Morin Street
Biddeford, ME 04005 - 4497
(207) 282-5911

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 3
End: 5

TECHNICAL ABSTRACT (Limit 2000 characters, approximately 200 words)
NASA has defined a need for higher performance ablative Thermal Protection System (TPS) materials for future exploration of our solar system's inner and outer planets than is currently available. Of particular interest are: 1) Materials with performance analogous to fully dense, heritage rayon-based carbon phenolic ; 2) Mid-density ablative systems ; and 3) Highly insulative, low-density materials. New Frontiers, Mars Sample Return (MSR), and Mars Entry, Descent & Landing (Mars EDL) are all potential missions for these new and/or enhanced TPS materials, but the general desire is that these TPS be tunable for cross-cutting mission applications. In addition to improved TPS performance, NASA would benefit from a TPS integrated with the sub-structure thereby improving thermal efficiency, insulation performance, system thermal-structural performance, and system integrity with the goal of achieving increased system reliability, reduced areal mass, and/or decreased costs over the current state-of-the-art (SOTA).FMI proposes developing its multi-layered, graded, hybrid ICS system for application to NASA missions. The system is comprised of distinct material layers encompassing different fillers or reinforcements, but maintaining the same resin so the materials are compatible for co-curing to yield a continuous rigid heatshield and sub-structure (ICS).

POTENTIAL NASA COMMERCIAL APPLICATIONS (Limit 1500 characters, approximately 150 words)
NASA has defined a need for higher performance ablative Thermal Protection System (TPS) materials for future exploration of our solar system's inner and outer planets than is currently available. New Frontiers, Mars Sample Return (MSR), and Mars Entry, Descent & Landing (Mars EDL) are all potential missions for these new and/or enhanced TPS materials, but the general desire is that these TPS be tunable for cross-cutting mission applications.

POTENTIAL NON-NASA COMMERCIAL APPLICATIONS (Limit 1500 characters, approximately 150 words)
The proposed multi-layered Integrated Composite Structure airframe technologies will be advantageous for DoD applications, including Missile Defense interceptor airframes, and aeroshell/insulation systems for Air Force and AMRDEC extended-flight vehicles.

TECHNOLOGY TAXONOMY MAPPING (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.)
Composites
Entry, Descent, & Landing (see also Planetary Navigation, Tracking, & Telemetry)
In Situ Manufacturing
Isolation/Protection/Shielding (Acoustic, Ballistic, Dust, Radiation, Thermal)
Joining (Adhesion, Welding)
Passive Systems
Processing Methods


Form Generated on 09-03-10 12:12