SOLICITATION NOTICE
B -- TESTING AND ANALYSIS OF PROPULSION SYSTEM MATERIALS FOR MSFC
- Notice Date
- 9/21/2006
- Notice Type
- Solicitation Notice
- NAICS
- 541380
— Testing Laboratories
- Contracting Office
- NASA/George C. Marshall Space Flight Center, Procurement Office, Marshall Space Flight Center, AL 35812
- ZIP Code
- 35812
- Solicitation Number
- NNM06174232
- Response Due
- 10/6/2006
- Archive Date
- 9/21/2007
- Small Business Set-Aside
- N/A
- Description
- NASA/MSFC has a requirement for testing and analysis of materials used in human-rated propulsion systems. Marshall Space Flight Center requires testing of materials such as carbon phenolic and graphite phenolic materials and carbon/carbon, ceramic, insulation, ceramic matrix composite, and advanced and polymer composite materials supporting propulsion and space transportation applications. The properties generated shall be measured under conditions designed to simulate the conditions in application including temperatures up to 5500 degrees F, oxidizing environments up to temperatures and in excess of 3000 degrees F, and cryogenic temperatures as low as -450 degrees F at a minimum. The Contractor shall have the capability to prepare specimens, design unique test hardware and specimens, fabricate hardware test fixtures, ensure sufficient alignment for data accuracy, and generate test procedures to achieve the most accurate data possible. Experimental results shall be analyzed and correlations developed in accordance with the objectives of the specific test series, comparing test behavior and environment with propulsion and space transportation application behavior and environment. Historical property test data, material pedigree, and test techniques shall be used in the failure analysis when analyzing current test data and test techniques. NASA/MSFC intends to purchase the services from Southern Research Institute (SRI), Birmingham, Alabama, pursuant to FAR 6.302-1 which implements 10 U.S.C. 2304(c)(1) for acquisition of supplies or services from only one source and no other supplies or services will satisfy agency requirement. Competition is impractical for the following reasons: 1. This effort involves the testing of materials and the generation of testing data that are used in human-rated propulsion systems, which is critical in the mitigation of risks associated with the operation of those systems. Due to the nature of the effort required, SRI is the only known source with the capability to generate test results with demonstrated reliability (i.e., repeatability, accuracy, and resolution) at extreme and typically non-standard testing conditions such as high temperature testing up to 5000 degrees F. SRI is the only known source that can provide the unique combination of data understanding (i.e., failure mechanisms, component and specimen processing, specimen testing conditions, specimen design, component operation conditions, and data history), reliability, and component design accuracy to enable the most efficient and effective operating system to meet NASA?s goals, thus allowing for the safest system. SRI uniquely provides an ability to obtain maximum data understanding, data reliability, and design accuracy, using a unique combination of properties, such as tensile, compression, flexure strengths, in-plane shear strength with 45 degree tension, and in-plane shear strength with 45 degree compression configurations for composites and monolithic ceramic materials at temperatures greater than 5000 degrees F. Only SRI has demonstrated they can generate specific heat data, unrestrained electrical conductivity data, thermal expansion data, Rumanian in-plane shear data, saddle in-plane shear data, and torsional in-plane shear data, creep with a circumferential coupon data, interlaminar shear data, double notch shear data, and tensile creep data at temperatures greater than 4600 degrees F, as well as fatigue data at a frequency of greater than 500 Hz, load ratio of 0.1, and temperature of 1800 degrees F. Only SRI has demonstrated they can generate biaxial tension-tension and compression-torsion testing data from -250 degrees F to 1500 degrees F, among other testing capabilities. This combination of unique data is necessary to produce and operate these human-rated propulsion systems with the most accurate hardware designs and design safety margin. 2. The data generated by SRI from room temperature to 5000 degrees F is the only data validated to model the Reusable Solid Rocket Motor (RSRM) and 1st stage Crew Launch Vehicle (CLV) nozzle ablative material. All of the ablative nozzle data used for thermo-structural analytical models to support flight and flight anomaly investigation is generated by SRI. Critical thermal properties for the External Tank (ET) composite nose-cap used to perform the thermo-structural analysis were generated by SRI along with lot and individual cone testing to verify flight worthiness on initial flight articles. No other source has been qualified to produce this thermal data. 3. SRI is the only organization that has developed a material property database from room temperature to 5000 degrees F on the graphite throat used in the Solid Rocket Booster (SRB) Booster Separation Motor (BSM). This database is used in the thermo-structural analysis used for BSM. They provided test and failure analysis on the recent BSM throat factor of safety investigation and will generate the database for the new graphite material currently being qualified for the BSM built by ATK Thiokol. Use of the BSM is expected to continue to the CLV system and continued access to SRI expertise is necessary. 4. SRI is the only known source of elevated temperature permeability with the specimen under a tensile or compressive load. Further, SRI is the only firm with analog test capability which has been used to develop unique data to develop and validate thermal models for RSRM nozzle ablative liners. The restrained thermal growth test developed by and available exclusively from SRI is also necessary in characterizing and modeling next generation nozzle materials for the RSRM and 1st stage CLV. 5. SRI is the only source to have generated high temperature mechanical and thermal properties for Reinforced Carbon-Carbon (RCC) on-orbit repair material or Non-Oxide Adhesive eXperimental (NOAX). This data provides both an understanding of the characteristics governing the NOAX behavior and supports the only thermal-structural analysis model of NOAX known to exist. This unique expertise and understanding of this critical shuttle system material is available in no other organization and is essential in support of NASA efforts to develop a RCC repair material in the event of damage to the thermal protection system. 6. SRI is the only organization that has developed a material property database on the cryogenic foam used in the Shuttle External Tank. This data provides both understanding of the characteristics governing the foam loss (and resultant shuttle orbiter tile damage) and supports the only thermo-structural analysis model of the ET foam known to exist. This unique expertise and understanding of this critical shuttle system material is available in no other organization and is essential in support of MSFC efforts to develop a superior foam which will not damage the Orbiter?s thermal protection system. The Government does not intend to acquire a commercial item using FAR Part 12. See Note 26. Interested organizations may submit their capabilities and qualifications to perform the effort in writing to the identified point of contact not later than 4:30 p.m. local time on October 6, 2006. Such capabilities/qualifications will be evaluated solely for the purpose of determining whether or not to conduct this procurement on a competitive basis. A determination by the Government not to compete this proposed effort on a full and open competition basis, based upon responses to this notice, is solely within the discretion of the government. Oral communications are not acceptable in response to this notice. All responsible sources may submit an offer which shall be considered by the agency. An Ombudsman has been appointed. See NASA Specific Note "B". Any referenced notes may be viewed at the following URLs linked below.
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