Status Report

NASA JSC Solicitation: Composite Sandwich Habitable Pressurized Structures

By SpaceRef Editor
January 14, 2014
Filed under , ,

Synopsis – Jan 13, 2014

Statement of Interest Form – Posted on Jan 13, 2014 


General Information

    Solicitation Number: NNJ14ZBH027L

    Posted Date: Jan 13, 2014

    FedBizOpps Posted Date: Jan 13, 2014

    Recovery and Reinvestment Act Action: No

    Original Response Date: Apr 11, 2014

    Current Response Date: Apr 11, 2014

    Classification Code: A — Research and Development

    NAICS Code: 541712

Contracting Office Address

NASA/Lyndon B. Johnson Space Center, Houston Texas, 77058-3696, Mail Code: BH


The National Aeronautics and Space Administration (NASA) Johnson Space Center (JSC) is seeking parties interested in collaborative development and mature technologies required for NASA’s future missions and to enhance life on Earth. JSC is looking to partner on the development of broadly applicable technologies as a means to accelerate technology development and strengthen commercialization of federally-funded research and development.


NASA JSC seeks parties interested in co-developing technology associated with Composite Sandwich Habitable Pressurized Structures (CSHPS).

CSHPS technology includes permeability, radiation and Micrometeoroid and Orbital Debris (MM/OD) shielding which are built into the structure along with embedded sensor technology for structural and thermal health monitoring. This co-development opportunity focuses on advancing the technology in design, analysis and manufacturing of a multi-functional composite structural system through the fabrication of a habitable composite cabin structure.

This technology can be modified and adapted to accommodate many applications that can benefit from lightweight, thermally protected and impact resistant habitable structures.


Over the past two years, NASA JSC has been leading the design, fabrication, and testing of multi-functional structural sandwich panels constructed of composite face sheets and metallic foam core. Evaluations of these panels have demonstrated that this structural system has a high potential to successfully be utilized in design and fabrication of large habitable structures. In 2012, composite tooling was designed, fabricated and used in the manufacture of a solid laminate structure. The objective of this effort was to use these tools to manufacture a multi-functional cabin structure. This structure will be pressure and modal tested and subsequently outfitted with an internal structure to simulate a deep space Advanced Exploration System (AES).

Currently, NASA JSC is bonding the MM/OD shielding with high and low density foam core and performing mechanical testing to understand the synergism of a focused, system designed structure. Analytical models for structural and environmental response are being developed and correlated to test data. The resultant structure is being built into prototypes at component and full-scale levels. The fundamental objectives are to save mass (~20%) and volume by incorporating capability into (not onto) the structure. The end goal is a human-rated, single wall vehicle technology with pressure inside and Thermal Protection System (TPS) outside. More specifically, this effort intends to provide a platform for space vehicle applications.

NASA JSC is currently on track to narrow-down/define design parameters and to begin producing demonstrators to enable advancement toward production with notable capability at significant weight savings. Products include test data, demo hardware and reports.

The proposed sandwich composite system using an aluminum foam core has never been utilized in a habitable structure configuration. Material/System configuration property development and damage tolerance require significant resources for testing. Additionally, manufacturing processes for large complex structures have yet to be demonstrated.

R&D Status:

This technology has become part of the Human Asteroid Lander (HAL)/ Multi-mission Space Exploration Vehicle (MMSEV), supports Lagrange Point 2 (L2) habitable vehicles, and is tied to Dryden Research Center (DRC) test development and Ames Research Center (ARC) composite heat shield development.

Intellectual Property (IP):

* Multi-Functional Composite Structure for Deep Space * Inside-Out Manufacturing of Multifunctional Composite Structures

Detailed information for the above mentioned technologies furnished upon request.

This co-development project may produce new IP that could be jointly owned by NASA and the partner or may become the property of the partner.

This announcement is not to be construed as a Request for Proposal and is not a commitment by the government, nor will the government pay for any information provided. Since this is an Announcement, no evaluation letters or results will be issued to the respondents.

Please submit the attached Statement of Interest Form to Mark Dillard

To view all Co-Development and Partnering Opportunities with the NASA Johnson Space Center please visit our website at

Point of Contact

    Name: Mark A. Dillard

    Title: Lead Partnership Development Office Integration

    Phone: 281-244-8640

    Fax: 281-483-4146



    Name: Dana Altmon-Cary

    Title: Contracting Officer

    Phone: 281-483-8228

    Fax: 281-483-4066


SpaceRef staff editor.