SOLICITATION NOTICE
A -- CREW EXPLORATION VEHICLE ALTERNATE LAUNCH ABORT SYSTEM WIND TUNNEL TEST IN POLYSONIC TEST FACILITY
- Notice Date
- 12/27/2006
- Notice Type
- Solicitation Notice
- NAICS
- 488190
— Other Support Activities for Air Transportation
- Contracting Office
- NASA/Langley Research Center, Mail Stop 144, Industry Assistance Office, Hampton, VA 23681-0001
- ZIP Code
- 23681-0001
- Solicitation Number
- NNL07183781Q
- Response Due
- 1/5/2007
- Archive Date
- 12/27/2007
- Small Business Set-Aside
- N/A
- Description
- NASA/LaRC has a requirement to conduct a wind tunnel test in a Polysonic Wind Tunnel (PSWT). The Orion Vehicle is the payload for the AresI and is composed of the Service Module (SM), Comand Module (CM) and the Launch Abort System (LAS), which when used to abort the CM to save the crew becomes the Launch Abort Vehicle (LAV). Currently there is a study underway to assess the possibility of Alternate Launch Abort Systems (ALAS) in order to improve structural efficiency and aerodynamic and aeroacoustic performance of the LAV. Any configuration changes to the LAV can have significant impact on the entire AresI vehicle. The AresI is particularly susceptible to changes in nose geometry (i.e., LAV) which can change configuration drag and stability and control characteristics. Therefore a combination of Computational Fluid Dynamic calculations and experimental results are required for a valid assessment of these effects. NASA/LaRC intends to purchase the services from Boeing, Inc. who is the only known responsible source. To support the assessment of possible ALAS configuration effects on the AresI, an existing 0.01-scale ( ~ 38? long) wind tunnel model, which has been tested in the PSWT, will be modified by NASA/LaRC as required and provided for testing in the PSWT. The proposed Polysonic wind tunnel test covers the Mach range 0.4-4.0, providing aerodynamic pressure data for the Crew Exploration Vehicle (CEV) Alternate Launch Abort System (ALAS) Project. This is required to support aerodynamic loads database validation in support of vehicle outer mold line refinement. This facility allows the use of the existing model and sting hardware, which will provide savings in both setup time and cost. There are no NASA facilities available with this Mach range and size. The Boeing Polysonic tunnel is the only known blow-down facility with the specific Mach number range, Reynolds number, and size to satisfy the wind tunnel testing requirement. Also, to eliminate tunnel to tunnel differences, both the force and moment model and the pressure model should be tested in the same facilities. The force and moment model was tested in the Boeing Polysonic facility due to AresI?specific test requirements, so for the complimentary pressure model, the Boeing Polysonic facility is also required. The authority for this action is the test program for commercial items (section 4202 of the Clinger-Cohen Act of 1996), and 10 USC 2304(c)(1). The Government intends to acquire a commercial item using FAR Part 12 and Part 13.5, Test Program for Certain Commercial Items. 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 January 5, 2007. 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.
- Web Link
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- Record
- SN01203086-W 20061229/061227220619 (fbodaily.com)
- Source
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