SOURCES SOUGHT
A -- PROPULSION TESTING UNIQUE CAPABILITIES
- Notice Date
- 1/29/2015
- Notice Type
- Sources Sought
- NAICS
- 336414
— Guided Missile and Space Vehicle Manufacturing
- Contracting Office
- NASA/Lyndon B. Johnson Space Center, Houston Texas, 77058-3696, Mail Code: BH
- ZIP Code
- 00000
- Solicitation Number
- NNJ15ZBH004L
- Response Due
- 8/3/2015
- Archive Date
- 1/29/2016
- Point of Contact
- Mark A. Dillard, Lead Partnership Development Office Integration, Phone 281-244-8640, Fax 281-483-4146, Email mark.a.dillard@nasa.gov
- E-Mail Address
-
Mark A. Dillard
(mark.a.dillard@nasa.gov)
- Small Business Set-Aside
- N/A
- Description
- There are many challenges facing our world today: Finding a cure for cancer; discovering safer and cleaner alternative energy sources; making transportation safer and more effective; producing durable, environmentally friendly materials; protecting our national assets; exploring Space, and rehabilitating our soldiers, just to name a few. NASAs Lyndon B. Johnson Space Center (JSC) shares common, complex problems with many industries. We are seeking partners interested in using our unique propulsion testing technical capabilities to help solve both space related and earthbound problems. For the past 50+ years, this nation has made a great investment in space exploration and NASA JSC, resulting in JSC capabilities (disruptive technologies, expertise, knowledge, specialized skills, experience, facilities, labs and tools) that are used to better life here on Earth. Utilizing these national assets to further technological advances also saves money, not only for the taxpayer, but across industry, academia, and Government agencies. In todays global economy, the key to our nations future is dependent on our ability to advance technologies in all industries and operate in the most innovative, efficient and effective ways. With the release of this Announcement, JSC looks forward to sharing its unique capabilities to meet the needs of others. Partnering will foster innovation through collaboration, assist in solving complex problems relevant to life on earth and create a more efficient and effective Government. Interested parties should respond in accordance with the language provided in the Announcement. I. Description and Purpose of this Announcement NASA Johnson Space Center (JSC) seeks to identify potential partners for utilization of JSC's unique propulsion testing resources to support government, university, and commercial activities. These resources include technical expertise, knowledge, specialized skills, experience, facilities, labs, and tools not reasonably available in the commercial sector. These resources are frequently referred to as capabilities throughout this document. These capabilities can be of great benefit to the nation by enhancing technological research and development, increasing the nations economic vitality, expanding human knowledge, and preserving United States critical skills. These capabilities, as outlined in Section IV, have broad application within diverse industries including, but not limited to, energy, petrochemical, medical, transportation, advanced manufacturing, robotics, aerospace, commercial space, and first responders. The capabilities also have broad application in academia and other government agencies (e.g., Department of Defense, Department of Homeland Security). This NASA JSC Announcement of Unique Capabilities, hereafter referred to as Announcement, is solely for information and planning purposes and does not constitute a Request for Proposal (RFP). It is not to be construed as 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. The expectation is that NASA JSC will be fully reimbursed for all costs incurred in the performance of work as described in the agreement. The purpose of this Announcement is to engage prospective partners in dialogue leading to research and development (R&D) efforts utilizing these unique capabilities. In selecting potential partners, JSC will assess the best-fit use of its resources consistent with the NASA mission. II. The Process The government and partner will jointly define the partnership, develop mutually agreed to statements of work, cost, and schedule. The government anticipates some respondents may be interested in only one area or sub-area while others may be interested in broad efforts requiring more than one capability. Some entities may want to partner because of their direct needs, or there may be respondents who wish to utilize JSC capabilities to meet the needs of third parties. NASA will identify the appropriate legal instrument for partnering on a case-by-case basis. III. Information Requested from Respondents If interested, parties will submit statements of interest electronically, via email, to the Technical Point of Contact listed below. The statement of interest shall consist of a one-page summary and one additional pages of supporting detail if needed. The one page summary response form can be found here. Responses shall contain a minimum font size of 12. To facilitate a prompt review, the one-page summary shall clearly identify planned utilization of capabilities consistent with those described in this document. Responses are required no later than close of business (COB) on the response date specified above. Information received after this date will only be considered if deemed in the Government's best interest. Please reference this Announcement, "NNJ15ZBH004L", in any inquiries. Respondents are cautioned to mark any information confidential if it is to be treated as proprietary. IV. Propulsion Test Capabilities The NASA JSC White Sands Test Facility (WSTF) offers numerous ambient pressure and altitude stands to test rocket propulsion test systems as well as single rocket engines. Propellant capabilities include hypergolic and liquid oxygen/hydrocarbons. Both propellant and test article temperature conditioning is available, as well as the capability to provide saturated propellants to the test article inlets. Six test stands provide vacuum test capability to altitudes greater than 100,000 ft (30,000 m) and three test stands provide ambient testing to an altitude of 5000 ft (1500 m) above sea level for the NASA, government agencies, and commercial industry. Altitude Testing Six test stands at WSTF provide vacuum test capability: Engine and engine systems up to 25,000 lbf (110 kN) thrust Altitude greater than 100,000 ft (30,000 m) engine firing with steam ejectors up to 250,000 ft (76,000 m) using vacuum pumps without firing Propellants: liquid hydrogen, gaseous and liquid oxygen, hydrocarbon, hydrazine, Aerozine-50, monomethylhydrazine (MMH), nitrogen tetroxide (N2O4), gaseous and liquid methane Solid motors Helium pressurants Nitrogen pressurants Vertical or horizontal firing Temperature-conditioned propellants and test article, 40 to 120 F (4 to 49 C) Ambient Testing Three test stands at WSTF support ambient firing at 5,000 ft (1500 m) above sea level: Thrust from 25,000 to 60,000 lbf (110 to 270 kN) Vertical or horizontal firing Articulating thrust mounts Hypergolic Propellants: hydrocarbon, hydrazine, Aerozine-50, MMH, N2O4, or solid rocket propellant Propellants Propellants available for testing include liquid hydrogen, gaseous and liquid oxygen, hydrocarbon, hydrazine, Aerozine-50, monomethylhydrazine (MMH), nitrogen tetroxide (N2O4), gaseous and liquid methane and solid rocket propellants. Unique Propulsion Testing Capabilities and Expertise Combustion instability and Pogo Determination Dynamic oscillations in spacecraft engines and systems can often lead to disastrous results. Two of the more common oscillation phenomena are called combustion instability and POGO. The NASA White Sands Test Facility (WSTF) maintains the capabilities to initiate instabilities by several methods for evaluation purposes and to test for engine instability and system POGO under a wide range of conditions. Hypergolic Propellant Handling WSTF can dispatch propellant handling teams to support projects at any location. The WSTF maintains expertise with Hypergolic propellants such as hydrazine, monomethylhydrazine, nitrogen tetroxide and unsymmetrical dimethylhydrazine. Engine Testing with Saturated Propellants Spacecraft propulsion systems are often required to operate with propellants saturated with pressurant gas. This can negatively affect both engine and system performance. The NASA White Sands Test Facility (WSTF) maintains systems capable of rapid propellant saturation, verification of the gas saturation level, and capabilities for engine and system tests utilizing saturated propellants. These tests can be conducted over a wide range of conditions. Propellant Tank Pressure, Volume and Temperature Quality Gauging Due to the inherent inaccuracies of flight-type propellant gauging systems, the White Sands Test Facility (WSTF) has demonstrated the capability to determine the liquid level in a propellant tank by means of a pressure, volume, and temperature (PVT) application that uses monomethylhydrazine (MMH) as the liquid. Propellant Vapor Detection White Sands Test Facility (WSTF) has an active program in development, evaluation, and qualification of toxic vapor monitors for ground support and spaceflight. Through several on-going test programs, WSTF has developed advanced methods of producing stable toxic and/or highly reactive gas streams from the parts per billion to the percent level in a variety of carrier gases. In conjunction, the methods for quantitatively trapping and analyzing these gas streams were developed. The gold salt hydrazine detector currently used in the space station and shuttle airlocks was invented, developed, and flight qualified at WSTF. Rocket Engine Performance Measurement One of the goals of rocket engine hot-fire testing is to directly evaluate engine performance for the purpose of validating analytical design parameters or flight worthiness. Different performance parameters can be measured depending on customer requirements. The White Sands Test Facility (WSTF) performance measurement capabilities include vacuum thrust, mass flow rate, propellant pressure, and standardized performance parameter calculation for comparison to nominal engine performance. Propulsion Test Data Acquisition and Control Systems The Propulsion Test Office at White Sands Test Facility (WSTF) currently operates the second generation of automated Data Acquisition and Control Systems (DACS). These systems have proven their merit in tests of space shuttle components, including the improved auxiliary power unit, orbital maneuvering subsystem, aft reaction control subsystem, and a myriad of reaction control thrusters. Custom control and monitoring software has also been developed and implemented for such applications as safely establishing closed loop startup and shutdown profiles for a liquid propellant rocket engine with turbopump feed system. The four DACS incorporate current computing technology features for efficient and safe testing. Extensive use of both high-speed memory networks and standard network communications allows for safely automated test operations and the distribution of test results in near real-time. Graphical user interface technology provides optimum test article telemetry monitoring and control system interaction. The DACS provides customer data processing and analysis service both in real-time for test control and monitoring at WSTF, and posttest at the customers place of business. All improvements have resulted in reductions of both maintenance costs and energy usage. The Propulsion Test Office at WSTF recently procured and installed the third generation of automated DACS that is designed and built on lessons learned with the previous generations. The following information reflects this third generation system. Training WSTF can provide hands-on training to customer personnel in handling hypergolic propellants. Classes are tailored to the individual audience and can vary from intense classroom discussions of new chemical analytical techniques to field training with Level-A, totally encapsulating, protective suits. WSTF has: Developed detailed courses on hypergolic propellants that cover storage, transport, safety equipment, and emergency response for NASA Johnson Space Center, NASA Glenn Research Center, Sandia National Laboratories, and General Electric. Proven expertise in development and qualification testing. Developed adequate detection equipment and PPE for use in hypergolic propellant handling. Researched advanced methods of treating hazardous wastes including the development, construction, and validation of a unique disposal system for hydrazine-type wastes at Vandenberg Air Force Base. Experience in preparing assessment and impact statements for new projects involving hypergolic propellants. Developed procedures for saturating hypergolic propellants with inert gases to more closely simulate in-flight conditions. WSTF can provide hands-on training to customer personnel in handling hypergolics during over-the-road transport. Iron Nitrate Problems The WSTF Propulsion Office conducted studies of impact to various components and systems. Techniques such as molecular sieves were developed to reduce contamination of nitrogen tetroxide systems with solid iron nitrate. WSTF subsequently built molecular sieve units to remove iron nitrates from nitrogen tetroxide for use at WSTF, Kennedy Space Center (KSC), and other government facilities. Electrical Devices in Hazardous, Flammable, and Explosive. Environments WSTF personnel are knowledgeable in all regulatory and safety aspects for proper handling of hazardous wastes from hypergolic propellant activities, and have researched advanced methods of treating such hazardous wastes, including the development, construction, and validation of a unique disposal system for hydrazine-type wastes at Vandenberg Air Force Base. Propulsion personnel are also experienced in all aspects of the preparation of environmental assessments and impact statements for new projects involving hypergolic propellants. Bubble Point Testing WSTF Propulsion has developed and constructed units to test the propellant acquisition screens in the shuttle orbital maneuvering subsystems and reaction control subsystems for use at KSC and provided training to KSC personnel. Hydrostatic Burst Testing Testing high-pressure tubes from tube banks proved significant energy is released when tubes burst while undergoing hydrostatic testing. Since such an event could easily endanger lives, this testing has created a significant impact on industry hydrostatic test procedures. System Leak Detection Propulsion testing at WSTF has developed and applied helium mass spectrometer and ultrasonic detection techniques to large propellant systems.
- Web Link
-
FBO.gov Permalink
(https://www.fbo.gov/spg/NASA/JSC/OPDC20220/NNJ15ZBH004L/listing.html)
- Record
- SN03628239-W 20150131/150129235005-de7d041c300da475086c6fc224170595 (fbodaily.com)
- Source
-
FedBizOpps Link to This Notice
(may not be valid after Archive Date)
| FSG Index | This Issue's Index | Today's FBO Daily Index Page |