SOLICITATION NOTICE
18 -- REQUEST FOR INFORMATION ON LONG TERM SPACE EXPOSURE CYROGENIC VALVETECHNOLOGIES
- Notice Date
- 11/6/2009
- Notice Type
- Presolicitation
- NAICS
- 336415
— Guided Missile and Space Vehicle Propulsion Unit and Propulsion Unit Parts Manufacturing
- Contracting Office
- NASA/George C. Marshall Space Flight Center, Procurement Office, Marshall SpaceFlight Center, AL 35812
- ZIP Code
- 35812
- Solicitation Number
- NNM10ZPS001L
- Response Due
- 12/4/2009
- Archive Date
- 11/6/2010
- Point of Contact
- Lizette M Kummer, Contracting Officer, Phone 256-544-3457, Fax 256-544-5028, Email Lizette.M.Kummer@nasa.gov - David A. Iosco, Contracting Officer, Phone 256-544-0387, Fax 256-544-4400, Email David.A.Iosco@nasa.gov
- E-Mail Address
-
Lizette M Kummer
(Lizette.M.Kummer@nasa.gov)
- Small Business Set-Aside
- N/A
- Description
- Background and RFI Summary:The mission of NASA is to achieve the U.S. Space Exploration Policy by implementing asustained and affordable human and robotic space program; extending human presence acrossthe solar system and beyond; and developing supporting innovative technologies,knowledge, and infrastructures. The Exploration Systems Architecture Study (ESAS)initially defined a transportation system and the study is available at:http://www.nasa.gov/mission_pages/exploration/news/ESAS_report.html.The Propulsion and Cryogenics Advanced Development Project (PCAD) within the ExplorationTechnology Development Program (ETDP) is evaluating, assessing, and advancing propulsiontechnologies for the Constellation Program. The PCAD web link is:http://spaceflightsystems.grc.nasa.gov/Advanced/Capabilities/PCAD/.This Request for Information (RFI) seeks market information for planning purposes onavailable technologies for cryogenic valves capable of long duration exposure to spaceenvironments. As NASA prepares to move beyond low earth orbit and return to a mission ofexploration, cryogenic valves need to become more robust, durable, and hardened. Themajority of space craft that are exposed to the space environments for a long durationutilize storable propellant systems. These systems typically use elastomeric materialssuch as Ethylene Propylene Diene Monomer (EPDM), Viton, or Kelrez. However, thesematerials do not work in cryogenic applications. Previous missions were limited to a fewdays and those also utilized storable propellants. NASA's experience with theInternational Space Station (ISS) shows us some of the issues resulting from long termspace exposure, and long product life cycles, while still maintaining lightweightcomponents. However, ISS components are generally not cryogenic nor propulsion related. All standard cryogenic fluid controls utilized in propulsion systems today are focused onlaunch vehicles with minutes of life, unmanned scientific satellites with longer life butnot man-rated, and a few space station applications where crew rescue or resupply ispossible within days, or weeks. Once humans settle on the moon, Mars, or other planets,such rescues or resupplies may be difficult or impossible. The crew must have robust andreliable propulsion systems that can work, and work when needed. Space craft used forthese exploration missions need the highest level of reliability, and systems that offerredundancy, without adding grossly to their weight.Specific Information Requested: The RFI seeks technologies that are at a low (2-4) Technology Readiness Level (TRL - SeeAppendix B attached) and could be applied to the standard cryogenic fluid controlsutilized in propulsion systems today to improve their performance over existingtechnologies. NASA is seeking information on candidate cryogenic valve systems that could potentiallybe used on Advanced Propulsion and Space Systems. An advanced valve development effort ison-going and this RFI will be used to identify valve technologies that may be used inflight as well as on the ground to improve the reliability, mass, and packaging of thesesystems and to provide synergies between vehicle and propulsion elements, therebyimproving the vehicle's overall performance.Specific Information on the Mission:This RFI assumes that the propulsion system will be launched in an inert state to lowearth orbit, stay on orbit for up to a month, be transported to another orbit over a fourday period, and finally enter that orbit. The system must be activated in orbit toprovide landing abort as the vehicle descends to the surface for a 6 month stay. At theend of that time the system must be activated and used to propel the crew off the surfaceand rendezvous with the orbiting vehicle. While in low earth orbit, exposure to long thermal cycles from -250 Deg F to + 250 Deg Fis typical at time frequencies of once every 90 minutes. So a total thermal cycle countof over 4000 cycles is planned and components will need to be qualified to 4 times thatduration or 16,000 thermal cycles. In transient environments there will be thermal soak temperatures as low as minus 388 DegF (-234 Deg C, no illumination) to as high as 302 Deg F (150 Deg C, direct illumination)for 4 days. On average, surface temperature cycles will vary from minus 238 Deg F (-150 Deg C) to 302Deg F (150 Deg C) over the course of 30 earth days for the 6 month stay time. Thistranslates into approximately 6 thermal cycles for a nominal mission. However, dependingon the landing location, temperature can be as low as minus 388 Deg F and remain therefor the entire duration of mission. During this whole period radiation from solarflares, exposure to unfiltered sunlight and cosmic rays are typical. Valve assemblieswill require hardening from this environment and ability to survive and provide reliableoperation. Appendix A (attached) contains a top level specification for a typical ascentmotor engine valve.The typical propellants may include cryogenic liquid oxygen and methane, but othercryogenic fuels could be utilized. Typical systems would operate in the 200 to 500 psigrange, and will require valves in the approximate 1.5 to 3 inch equivalent orifice size. Actuation should provide rapid and repeatable response in the 100 to 200 msec time frame.Actuator configuration is not defined, but position control is not typically needed.Mass, reliability, and total system impacts are prime areas of concern. The need toprovide robust designs at the minimum of weight, control, power, and maintain thatrobustness until launch at the end of this mission is critical. Preliminary Test Data and RFI Goals:NASA has undertaken a project to take a typical propulsion system valve and expose thatvalve to the environments above. The valve is a pneumatically operated ball valvedesigned for an air launched vehicle with a suborbital flight path. It was chosen as itsheritage was to the Centaur program, a well known cryogenic in-space propulsion system.The testing showed several issues. 1)The seals in the actuator leaked at over 100 SCCM as temperatures were loweredfor long periods of time (less than a day). The goal is to achieve rotary seal leakagesas low as 5-10 SCCM over this mission profile.2)The actuator and pilot valve response times increased to the point that the valvewas not operating reliably and would have adversely affected an engines ability to start.The goal is to provide at least 30% force margin to actuation loads at the end of thismission. Actuator minimum required torque is 2000 in-lbs at minimum motive power (lowestvoltage, lowest pressure, etc.) With 30% margin required at low end so 2600 in-lbsminimum required. 3)Seal friction increased and the breakaway torque requirements exceeded theactuators capability as the temperature dropped. The goal is to reduce seal frictions by25%. This can be included in actuator margin or directly as in improvement of staticfriction compared to Teflon on bare stainless steel.4)The pilot valve leakage became unacceptable (blowing leaks) as the temperaturedropped to -160 Deg F. The goal is to achieve seat and static seal leakages as low as5-10 SCCM over this mission profile.Continued testing is ongoing and data will be provided to the vendors as it becomesavailable.Vendor Information Required:NASA requests that industry provide information on potential valve designs, seals,actuators, materials, or any other relevant technologies that can be utilized to meet orimprove propulsion valve reliability, mass, and power requirements. The information provided should provide technical description of the technology, outlinethe basic assumed problem being resolved, and define how this approach will resolve theissue. Ideas for new valve technologies to be tested resulting from this RFI fall into twocategories: 1.Technologies that could be tested in the existing NASA valve must be able to beintegrated onto the existing test fixture or test valve and proven through the sametesting series currently being performed for the existing cryogenic valve. Information onthe valve and test conditions can be provided upon request. 2.For technologies that could not be easily tested in or are not applicable to theexisting NASA valve, the vendor must suggest testing that will allow NASA to provide anindependent assessment of the technology performance.Response Instructions:It is emphasized that this RFI is for information and planning purposes only. Release ofthis RFI is NOT to be construed as a commitment by the Government to enter into acontractual agreement, nor will the Government pay for the information solicited. No solicitation exists; therefore, please do not request a copy of the solicitation. If asolicitation is released, it will be synopsized in FedBizOpps and on the NASA AcquisitionInternet Service. It is your responsibility to monitor these sites for the release of anysolicitation or synopsis. Responses to this RFI should be received not later than December 4, 2009.Responses should be provided in written format.RFI responses can be submitted via e-mail to lizette.m.kummer@nasa.gov. The subject lineof the submission should be: RFI NNM10ZPS001L. Attachments should be provided inMicrosoft Word or PowerPoint, or Adobe Acrobat formats. The e-mail text must give apoint-of-contact and provide his/her name, address, telephone/fax numbers, and e-mailaddress. It is not NASA's intent to publicly disclose vendor proprietary information obtained. Tothe full extent that it is protected pursuant to the Freedom of Information Act and otherlaws and regulations, information identified by a respondent as "Proprietary orConfidential" will be kept confidential. Technical and procurement related questions or comments should be directed to:Technical: Jim Richard, james.a.richard@nasa.gov, 256-544-9452 Procurement: Lizette Kummer, lizette.m.kummer@nasa.gov, 256-544-3457 Appendix A. Functional Valve Specification. See Attachment Appendix B. NASA Technology Readiness Level (TRL) Descriptions. See Attachment
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