MODIFICATION
A -- Deployable Solar Array Product for the Standard Bus Program
- Notice Date
- 7/27/2006
- Notice Type
- Modification
- NAICS
- 541710
— Research and Development in the Physical, Engineering, and Life Sciences
- Contracting Office
- Department of the Navy, Office of Naval Research, Naval Research Laboratory, 4555 Overlook Ave. S.W., Washington, DC, 20375
- ZIP Code
- 20375
- Solicitation Number
- N00173-06-R-TA04
- Response Due
- 8/8/2006
- Archive Date
- 7/27/2007
- Point of Contact
- Tommy Albrecht, Contract Specialist, Phone 2027673003, Fax 2027676197,
- E-Mail Address
-
tommy.albrecht@nrl.navy.mil
- Description
- The purpose of this amendment is to answer questions from prospective vendors, provide clarifications to the specifications and correct a typographical error. Question 1: Paragraph 4.2 states “The arrays shall meet the requirement of this specification during continuous exposure to any combination herein”, it follows that the requirements of 4.2.1 (modified by amendment 3) are to be used to show compliance with all performance requirements, including BOL and EOL power requirements. Is it your intent that the arrays provide the power output values of 1000 W BOL and 800 W EOL stated in 3.3.1.2 at 120 degrees Celsius? Or is there some limited set of conditions under which the array is expected to experience 120 degrees Celsius (such as the week period spent between the insertion orbit and operational orbit) and/or lower power output requirement by the bus during the 120 degrees Celsius exposure? Answer 1: The solar cells manufactured for Standard Bus shall have the beginning of life (BOL) performance characteristics listed in the following paragraphs when tested at 28 degrees Celsius, under illumination stimulating the spectrum and intensity of one sun, Air Mass Zero (AM0). All BOL and EOL calculations should be based on the environmental conditions listed above. Question 2: Paragraph 4.2.1 (modified) states “maintained at any temperature between -150 degrees Celsius and +105 degrees Celsius +120 degrees Celsius for prototype testing and on-orbit operations in the deployed configurations”. This implies that the prototype test temp is the same as the on-orbit operations temp (i.e. no margin) is this your intent? Or is the 120 degrees Celsius max temp intended to be a test temperature with margin over the on-orbit temp? Answer 2: The protoflight testing temperatures are -150 degrees Celsius and +120 degrees Celsius. The protoflight temperatures include margin from our predicted temperatures. Question 3: Para 7.2.5.5.1 states “Protoflight level tests shall consist of N cycles to a maximum temperature of +105 degrees Celsius +120 degrees Celsius and a minimum temperature of -150 degrees Celsius as shown in Figure 5 6. But Figure 6 still shows 105 degrees Celsius as the max temp. Is that intentional? Also, paragraph 7.2.5.5.1 uses the term protoflight, but paragraph 4.2.1 uses the term prototype. Are those intended to be interchangeable? Answer 3: There is an error in Figure 6. It should state a max temperature of +120 degrees Celsius. There is also a typographical error in paragraph 4.2.1. It should state protoflight instead of prototype. NOTE: THIS NOTICE WAS NOT POSTED TO FEDBIZOPPS ON THE DATE INDICATED IN THE NOTICE ITSELF (27-JUL-2006); HOWEVER, IT DID APPEAR IN THE FEDBIZOPPS FTP FEED ON THIS DATE. PLEASE CONTACT fbo.support@gsa.gov REGARDING THIS ISSUE.
- Web Link
-
Link to FedBizOpps document.
(http://www.fbo.gov/spg/DON/ONR/N00173/N00173-06-R-TA04/listing.html)
- Place of Performance
- Address: Contractor Facility
- Record
- SN01100167-F 20060729/060727224847 (fbodaily.com)
- Source
-
FedBizOpps Link to This Notice
(may not be valid after Archive Date)
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