MODIFICATION
99 -- LO2/ETHANOL VACUUM JACKETED TANK AND FEEDSYSTEM
- Notice Date
- 1/23/2003
- Notice Type
- Modification
- Contracting Office
- NASA/Lyndon B. Johnson Space Center, Houston Texas, 77058-3696, Mail Code: BH
- ZIP Code
- 00000
- Solicitation Number
- 9-BH13-67-03-04P
- Response Due
- 2/10/2003
- Archive Date
- 1/23/2004
- Point of Contact
- Mary F. Thomas, Contract Specialist, Phone (281) 483-8828, Fax (281) 244-5337, Email mary.f.thomas1@jsc.nasa.gov - Krystine O. Bui, Contracting Officer, Phone (281) 483-4186, Fax (281) 244-5331, Email krystine.o.bui1@jsc.nasa.gov
- E-Mail Address
-
Email your questions to Mary F. Thomas
(mary.f.thomas1@jsc.nasa.gov)
- Description
- THIS NOTICE CONSTITUTES AMENDMENT NO. 1 TO THE COMBINED SYNOPSIS/RFQ FOR LO2/ETHANOL VACUUM JACKETED TANK AND FEEDSYSTEM. Companies shall acknowledge all amendment(s) in their quote. This notice serves as the official amendment to subject synopsis/RFQ and a written amendment will not be issued. The purpose of this amendment is to (1) add the detailed drawings for tank SNL24-100266; (2) add line item 2 to the Request for Quote for pricing of the spare tank parts; and (3) to provide answers to questions submitted. Q1: Where are the detailed drawings of the tank, SLN24-100266? A1: The drawings are attached. The dimensions are approximate and are to be supplied by the vendor. Q2: Where is the detailed drawings of the LO2 accumulator, SMN24-100268? A2: Drawing number SMN24-100268 was inadvertently mis-numbered. The correct drawing number is SMN24-100269. This drawing was provided in the initial solicitation. Q3: There are 4 High Point Bleed/RV Ports in Figure 2 but only two apparent in drawing number SLN24-100270. Where are the other two ports? A3: The location of the other two ports is to be detemined by the offeror. The final drawings will be updated at contract start. Q4: The SOW requires two identical units. Does this mean jacketed systems for both the LOX and Ethanol? A4: Yes. Both sides are vacuum jacketed in the current approach and design. This was determined to have some advantages 1) in cost by avoiding two different design and manufacturing steps, 2) in the thermal conditioning of the ethanol, and 3) in simulating a flight feedline. The ethanol lines in space will be in a vacuum and have MLI. Heaters are being avoided for ethanol systems. Q5: The SOW states that the LOX system be designed for Helium service. Please clarify what this means. A5: Commercial vacuum jacketed lines and components typically have more insulation (30 layers MLI versus 15) and lower heat leak when designed for Liquid Helium service. This requirement was intended for those proposing commercial components. Q6: What specific style of bayonet is required? Male? Female? Air Force? Vendor Specific? A6: The details of the bayonet can be negotiated within the requirements for heat leak and pipe sizes and then finalized at the CDR. Q7: Are performance requirements for acceptance testing available? A7: The SOW lists the required acceptance tests. The specified values (proof pressure, cleanliness, heat leak, etc) for these tests are in the specification. The vendor shall be responsible for defining how these are to be verified for acceptance. Q8: When is anticipated ATP? A8: The anticipated ATP is March 2003. Q9: What aspects of a flight tank are to be simulated? A9: There are currently minimal primary objectives to simulate a flight tank, other than 1) the tank is sized to provide approximate capacity of RCS type systems, and 2) the tank is insulated to provide a relatively stable liquid oxygen and ethanol supply temperature over the intended test period of 7 days. Q10: What are the termination requirements for the instrumentation interface and control wiring? (i.e. connectors, J-box terminations). A10: The specific connectors, terminations, etc are to be detailed and agreed to by the CDR. Q11: What is the class of leakage required for the valves? A11: Internal leakage of all valve components shall be bubble tight using Gaseous helium. Q12: Are valve position indicators visual or electronic? A12: The indicators are electronic. Q13: Any supply pressure limitations for pneumatic actuators? A13: There are no limitations. Q14: Who provides pressure transducers and relief valves throughout each system? A14: Test facility will provide the pressure transducers and relief valves. Q15: Are specific piping elbows required to be mitered as shown in envelope drawing? A15: The piping elbows are not required to be mitered as shown. The internal piping is a radius bend. Q16: On drawings SLN24-100270 and SDN24-100274, multiple two and three place decimal dimensions are called out. Is this tolerance required? A16: The two and three decimal tolerances are inadvertent. Requirement 3.2.3 states that the lengths of individual line segments between valves shall be within +/- 1 inch. There is substantial flexibility in the dimensional tolerance. The dimensional tolerances are to be established by the vendor for the end item as required for manufacturability. The tolerances for the accumulator SMN24-100269 are TBD, but it will meet those required by vendor to install the component. These tolerances will be agreed to prior to CDR. Q17: Do you have preferred material compatibility reference documents? Drawings SLN24-100266 and SMN24-100268 are referenced in the end item spec, and are not included in the package. A17: LO2 fluid systems and components shall be designed and operated according to NSS 1740.15 (Jan 1996) or an equivalent ASME standard. Drawing SLN24-100266 is provided in the amendment #1. The drawing SMN24-100268 should be deleted from SOW and specification, as it has no necessary information. Q18. In the SOW, Section "3.0 End Item Specification," paragraph 3.1.15 states, "The propellant tank pressure vessel shall be SPHERICAL." In the diagram, "End Item: Tank, Feedsystem, Valves, and Structures," page "17" of the SOW, the Tank is CYLINDRICAL. A18: The drawings show the outer vacuum jacket and the pressure (inner) vessel is spherical. Q19. If all other specifications are met (e.g., heat leak, capacity, pressure rating, etc.), will a cylindrical propellant tank pressure vessel be acceptable? A19: The inner pressure vessel was specified as spherical to reduce heat leak by reducing surface area and to also reduce chill-down mass. Q20. What are the concerns about a cylindrical tank that would need to be addressed for it to be considered equal in performance to a spherical tank? A20: The cylindrical tank would need to have the same or less chill-down mass then a spherical, and the same or better heat transfer. Q21. If a cylindrical tank is acceptable but a spherical is preferred, can we submit two proposals with two different prices, one for a cylindrical and one for spherical? A21: Yes. Two proposals, with a justification, can be submitted. Q22. Are "GLOBE" valves a requirement? A22. Globe valves are not a requirement. Q23. What are the concerns about non-globe valves that would need to be addressed for it to be considered equal in performance to GLOBES? A23. There are no concerns with other valves as long as they meet the requirements such as heat leak and pressure drop. The due date for receipt of offers is not extended. Companies shall provide the information stated in the synopsis/RFQ posted on the NASA Acquisition Internet Service (NAIS) on February 10, 2003. Documents related to this procurement are available over the Internet and are in Microsoft Office 97 format and reside on the World Wide Web (WWW) server which may be accessed using a WWW browser application. The Internet site, or URL, for the NASA/JSC Business Opportunities home page is http://prod.nais.nasa.gov/cgi-bin/eps/bizops.cgi?gr=CL&pin=73
- Web Link
-
Click here for the latest information about this notice
(http://prod.nais.nasa.gov/cgi-bin/eps/bizops.cgi?gr=D&pin=73#103822)
- Record
- SN00245705-W 20030125/030123213747 (fbodaily.com)
- Source
-
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