SOURCES SOUGHT
A -- JPL High Specific Energy Primary Battery for Europa Lander Request for Information
- Notice Date
- 1/19/2017
- Notice Type
- Sources Sought
- NAICS
- 335912
— Primary Battery Manufacturing
- Contracting Office
- National Aeronautics and Space Administration, NASA Management Office-JPL, Business Opportunities Office, NASA Management Office, Jet Propulsion Laboratory, 4800 Oak Grove Drive, Pasadena, California, 91109, United States
- ZIP Code
- 91109
- Solicitation Number
- LS-17-02
- Point of Contact
- Mary Helen Ruiz, Phone: 8183547532, Logan Smith, Phone: 818-354-2270
- E-Mail Address
-
maryhelen.ruiz@jpl.nasa.gov, logan.smith@jpl.nasa.gov
(maryhelen.ruiz@jpl.nasa.gov, logan.smith@jpl.nasa.gov)
- Small Business Set-Aside
- N/A
- Description
- THIS IS NOT A SOLICITATION ANNOUNCEMENT. THIS IS A REQUEST FOR INFORMATION (RFI) ONLY. THE PURPOSE OF THIS RFI IS TO GAIN KNOWLEDGE OF POTENTIAL QUALIFIED SOURCES AND THEIR SIZE CLASSIFICATIONS (SMALL, SMALL DISADVANTAGED, WOMEN-OWNED, VETERAN-OWNED, SERVICE-DISABLED VETERAN-OWNED, HUBZONE OR LARGE BUSINESS) RELATIVE TO THE NAICS CODE. RESPONSES TO THIS RFI WILL BE USED BY JPL TO MAKE APPROPRIATE ACQUISITION DECISIONS. BACKGROUND The Jet Propulsion Laboratory (JPL) is an operating division of the California Institute of Technology (Caltech), staffed with Caltech employees, and is a Federally Funded Research and Development Center under the sponsorship of the National Aeronautics and Space Administration (NASA). As a member of the NASA family JPL is recognized as the agency's only FFRDC. JPL is requesting information on viable primary battery chemistries and designs to support future missions to the outer planets. There are two specific applications under consideration. APPLICATION #1: The battery must be able to provide ≥30,000 Wh of energy delivered between 36V and 24V over the course of 20 days at 0⁰C, following any required depassivation protocols. During that time, 80% of the discharge profile will occur at continuous power levels of ~40 W, with power levels rising up to ~600 W the remainder of the discharge profile. The battery will be based on cells of D, DD or an equivalent cylindrical format. Within these design limits and parameters it is anticipated individual cells will need to support discharge currents between 50 mA and 600 mA per cell. The battery will operate in a temperature range of 0 to +60⁰C, with an average operating temperature of +25⁰C. Prior to use, the battery will be stored up to 10 years at an average temperature of 0⁰C, with possible brief excursions between -40⁰C to +40⁰C. The total mass of the battery, including all cells, interconnects and packaging cannot exceed 91 kg. Designs which minimize this mass relative to the total energy required are highly encouraged. It is anticipated cells with a specific energy of >700 Wh/kg (with cell discharge evaluated at +25⁰C and 50 mA, 2V cell cut-off) would be used in the battery design. Although specific limits have not yet been established it is anticipated the battery will be required to pass a typical aerospace battery qualification process and therefore any battery packaging approach must factor in this consideration. Application #2: The battery must be able to provide a total of 1250 Wh of energy delivered between 36V and 24V over the course of 2.5 h at 0⁰C, following any required depassivation protocols. During that time, 80% of the discharge profile will occur at continuous power levels up to 900 W. The battery will be based on cells of D, DD or an equivalent cylindrical format. It is anticipated individual cells will need to support discharge currents between 4A for a D cell or 9A for a DD cell at a temperature of -10 to +10⁰C, with an average operating temperature of 0oC. Prior to use, the battery will be stored up to 10 years at an average temperature of 0oC, with possible brief excursions between -40 to +40⁰C. The total mass of the battery, including all cells, interconnects and packaging cannot exceed 8.5 kg. Designs which minimize this mass relative to the total energy required are highly encouraged. It is anticipated cells with a specific energy of >600 Wh/kg (with cell discharge evaluated at +25⁰C and 4A, 2V cell cut-off) would be used in the battery design. Although specific limits have not yet been established, it is anticipated the battery will be required to pass a typical aerospace battery qualification process and therefore any battery packaging approach must factor in this consideration. For both applications, there is interest in identifying high specific energy cell options meeting these requirements, even if respondents cannot provide information or inputs on full battery designs. These battery requirements can be used to guide inputs relative to potential cell designs that could be used in full battery designs. Required characteristics for Application 1: • Cell Format: D or DD (or equivalent cylindrical cell format) • Battery Voltage Range: 36V (maximum) to 24V (end of discharge) • Total Battery Energy: ≥30,000 Wh (delivered over 20 days) • Total Battery Mass: not to exceed 91 kg • Typical Battery Power Level: 40 W • Peak Battery Power Level: 600 W • Operating Temperature: 0oC to +60oC • Storage Temperature: -40oC to +40oC • Storage Prior to Use: up to 10 years • Storage Losses: <1% annual capacity loss at 0oC is recommended to achieve energy requirement within mass limits • Radiation Tolerance: Tolerance to 15 Mrad(Si) TID Co60 radiation, with little impact (< 5%) on long term performance is recommended Required characteristics for Application 2: • Cell Format: D or DD (or equivalent cylindrical cell format) • Battery Voltage Range: 36V (maximum) to 24V (end of discharge) • Total Battery Energy: 2550 Wh (delivered over 3 h) • Total Battery Mass: not to exceed 10 kg • Typical Battery Power Level: 900 W • Peak Battery Power: 1800 W • Operating Temperature: -10⁰C to +10⁰C • Storage Temperature: -40oC to +40oC • Storage Prior to Use: up to 10 years • Storage Losses: <1% annual capacity loss at 0⁰C is recommended to achieve energy requirement within mass limits • Radiation Tolerance: Tolerance to 15 Mrad(Si) TID Co60 radiation, with little impact (< 5%) on long term performance is recommended Desired Characteristics (not essential) for both the Applications Minimal capacity loss (<5%) after baking at 130°C for 230-hour, prior to battery assembly (for heat sterilization), to meet the bio-sterilization requirements. If this were possible, the radiation requirement may be reduced to 8Mrad. General Europa technical information can be found at: http://solarsystem.nasa.gov/europa/technical.cfm The general Europa page is: http://solarsystem.nasa.gov/europa/home.cfm The links below provide additional information provided to the science teams about the Europa Mission: http://solarsystem.nasa.gov/europa/docs/ICEE_KO_Combined_20131022_RevKAL.pdf http://solarsystem.nasa.gov/europa/iceedocs.cfm STATEMENT OF CAPABILITIES JPL requests a direct but concise response to key points regarding your company's capabilities and experiences to Application #1 and #2. JPL requests that interested parties respond in written form not to exceed fifty (50) pages in length. Please include (1) Company name; (2) NAICS Code(s); (3) Contact information, and (4) Business Size Classification. RESPONSES DUE All responses to the RFI are due no later than Thursday, February 9, 2017 to JPL, Attention: Small Business Programs Office, M/S 201-205, 4800 Oak Grove Drive, Pasadena, CA 91109-8099 or via E-Mail to: maryhelen.ruiz@jpl.nasa.gov This synopsis has been reviewed and determined no to contain export contolled technical data. DISCLAIMER It is emphasized that the requested information is for preliminary planning purposes only and does not constitute a commitment, implies or otherwise, that JPL will solicit you for such procurement in the future. Neither JPL nor the Government will be responsible for any costs incurred by you in the furnishing this information. Prospective contractors are advised that any information provided shall be deemed to be furnished with unlimited rights to JPL, with JPL assuming no liability for the disclosure, use, or reproduction of such data.
- Web Link
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FBO.gov Permalink
(https://www.fbo.gov/notices/6dd42b900b1593b3767c17d9872387a3)
- Place of Performance
- Address: California Institute of Technology, Jet Propulsion Laboratory, 4800 Oak Grove Drive, Pasadena, California, 91109, United States
- Zip Code: 91109
- Zip Code: 91109
- Record
- SN04375223-W 20170121/170119234207-6dd42b900b1593b3767c17d9872387a3 (fbodaily.com)
- Source
-
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