SOURCES SOUGHT
A -- Plankton, Aerosol, Cloud, ocean Ecosystem (PACE) Star Sensor System
- Notice Date
- 1/17/2018
- Notice Type
- Sources Sought
- NAICS
- 334511
— Search, Detection, Navigation, Guidance, Aeronautical, and Nautical System and Instrument Manufacturing
- Contracting Office
- NASA/Goddard Space Flight Center, Code 210.Y, Greenbelt, Maryland, 20771, United States
- ZIP Code
- 20771
- Solicitation Number
- RFI-2017-PACE-StarSensorSystem
- Point of Contact
- Elizabeth D. Abraham, Phone: 3016146996
- E-Mail Address
-
elizabeth.d.abraham@nasa.gov
(elizabeth.d.abraham@nasa.gov)
- Small Business Set-Aside
- N/A
- Description
- The National Aeronautics and Space Administration (NASA), Goddard Space Flight Center (GSFC) is seeking capability statements from all interested parties, including Small, Small Disadvantaged (SDB), 8(a), Woman-owned (WOSB), Veteran Owned (VOSB), Service Disabled Veteran Owned (SD-VOSB), Historically Underutilized Business Zone (HUBZone) businesses, and Historically Black Colleges and Universities (HBCU)/Minority Institutions (MI) for the purposes of determining the appropriate level of competition and/or small business subcontracting goals for an anticipated Firm Fixed Price (FFP) contract on a Star Sensor system in order to incorporate this information into the PACE Spacecraft conceptual design and to obtain answers to several questions, listed below. The Government reserves the right to consider a Small, 8(a), Woman-owned (WOSB), Service Disabled Veteran (SD-VOSB), or HUBZone business set-aside based on responses hereto. The PACE Project, which is managed by the NASA Goddard Space Flight Center, is investigating vendors who can provide quaternion output star sensor systems, appropriate sun shades, ground support equipment, and pertinent life test data to the PACE Attitude Control Subsystem (ACS), for an orbiting spacecraft in a circular sun-synchronous polar orbit at 676.5 km altitude with an inclination of 98 deg, and a 1 pm local ascending node crossing time. PACE is currently targeted to launch in the 2022-2023 timeframe. The purpose of this RFI is to survey vendor capabilities to meet the PACE mission requirements. This request is for information and planning purposes and feasibility of the requirements. Responses should include written and illustrated concepts, specification sheets, basic design information, and descriptions of capabilities for any available star sensor system that may meet the requirements described below. Responses are requested to identify potential areas of non-compliance. Where there is non-compliance, please state current capability and if a Non Recurrent Effort (NRE) could be pursued to achieve compliance on that particular requirement (and associated cost). The main science instrument for PACE resides upon a tilting platform that is attached to the spacecraft bus. This tilt platform alternates from +20 deg to -20 deg twice per orbit. As a result, the star sensor systems will be pointing in the two corresponding orientations. The PACE mission requires 1 to 2 star sensors to be mounted (a) upon the tilting platform in order to provide attitude orientation knowledge of the platform for the post-processing of the science data, and (b) 1 to 2 star sensors upon the spacecraft bus in order to provide attitude pointing and optional attitude rate information for the purposes of spacecraft attitude control. The platform star sensor system is only required to meet knowledge requirements at the two final tilt orientations. The star sensor system shall consist of the processing electronics, optical heads with star sensors (2-to-4), optical head baffles for bright object protection, required operational power and signal cabling between processing electronics and optical heads, and test optical EGSE for ground stimulation of star sensors. 1) PACE Star Sensor System Requirements • The star sensor system shall provide time-tagged attitude quaternion output telemetry. • The star sensor system shall provide quaternion solutions using (commandable) 1 to 4 optical heads. • The star sensor system attitude quaternion shall meet or exceed the following accuracy (using 1 to 2 bus mounted optical heads): o 10 arcsec (3 sigma) per axis with a 4 arcsec (3 sigma) Noise Equivalent Angle for the platform. o 10 arcsec (3 sigma) per axis with a 4 arcsec (3 sigma) Noise Equivalent Angle for the spacecraft. • The star sensor system shall support a command and data handling interface. This interface may be RS-422, MIL-STD-1553B, or ECSS-E-ST-50-12A (Spacewire). • The star sensor system shall have an autonomous attitude acquisition capability that operates up to a maximum rate of 4 deg/sec. • The star sensor system shall maintain performance accuracy up to a maximum rate of 2 deg/sec, and an acceleration of 1 deg/sec2. • The star sensor system shall support an update rate of up to 5 Hz at maximum rate and acceleration. • The star sensor system shall provide attitude quaternions with the required accuracy with the moon in the Field of View (FOV). • The star sensor system shall provide attitude quaternions with the required accuracy with the sun off of the optical head boresight greater than or equal to 40 degrees Half-cone angle (HCA), or provide details on relevant baffle options. • The star sensor system shall recover full accuracy within 10 seconds of the sun exiting a 40 degree HCA of an optical head boresight. • The star sensor system shall provide synchronization capability with the spacecraft time reference to within 100 microseconds. 2) Ground Support Equipment (GSE) a) The vendor shall provide optical EGSE to stimulate each of the optical heads with simulated star fields. b) The vendor shall provide non-flight baffle covers. 3) Radiation Environment: The star sensor system shall be designed to operate without degradation due to the radiation environment of a circular 676 km polar, sun-synchronous Low Earth Orbit. It is expected that the star sensor system design will comply with the following requirements: a) EEE parts and materials shall be selected for a total ionizing dose (TID) of 10 krad-SI (including 2x margin), behind 100 mils of equivalent Aluminum shielding and a 3-year mission life; b) EEE parts shall not be susceptible to destructive single-event latchups (SELs); c) The design shall avoid or tolerate errors due to non-destructive Single Event Upsets (SEUs) 4) Design Lifetime: The star sensor system shall meet the required mission lifetime of 38 months with a pre-launch life of at least 2 years. 5) NASA Standards: The star sensor system shall adhere to NASA flight system standards (e.g., mission assurance requirements, NASA-STD-1000: GOLD Rules, GSFC-STD-6016: Materials and Processes, NASA-STD-5001: Structural Design And Test Factors Of Safety, GSFC-STD-7000: Environmental Verification). 6) Deliverables: Along with the hardware, the respondent should also cost providing the following deliverables • Kick-off Meeting • Design Conformance Review (DCR) and presentation • Pre-Environmental Review (PER) and presentation • Pre-Ship Review (PSR) and presentation • Structural Analysis Report • Structural Finite Element Model (MSC-NASTRAN format) • CAD Model - CREO preferred • Mass Properties Report • Electrical Interface Control Document (ICD) • Thermal Analysis Report • Thermal Model & Documentation • Anomaly/Failure Reports • Verification Test Report(s) • Class I Configuration Management (CM) Changes • Trended Parameters List • Limited Life Items List • As-Built Parts List • As-Built Materials List • List of Critical Fasteners • Radiation Test Reports • GIDEP Alert Disposition and Preparation Furthermore, NASA/GSFC requests the following information (# 7 - 16 below) for the requirements above: 7) Physical Characteristics: Provide the following estimated characteristics: a) Mass of each star sensor system component b) Dimensions of each star sensor system component (volume) c) Electrical Interface Type and Locations d) Mounting Interface 8) Thermal: a) Define thermal temperature ranges for survival and operating conditions. b) Define thermal power dissipation of each component of the star sensor system. c) Define the minimum temperature for star sensor power on. d) Does the star sensor have a thermal electric cooler? i) If yes, what accommodations from the spacecraft are required? 9) Power: The observatory will supply switched power from +27V to +35V. Provide the peak and steady-state power estimate for the star sensor system. 10) Reliability: Provide reliability estimates for both single-string and single-fault tolerant star sensor systems. 11) Vibration and Shock Levels: Please provide vibration and shock levels that the unit has been tested to. 12) Rate Measurement: If component has rate measurement capability, provide time-tagged rate measurement performance and accuracy. 13) Harness Length: Please provide a maximum harness length between the star sensors system and the spacecraft command and data handling electronics. 14) Occultation of FOV: Please provide accuracy associated with 10%, 25% and 50% dark Earth occultation. 15) Cost and Schedule: a) Please provide a cost estimate and schedule for the delivery of one (1) single-string flight star sensor system and associated deliverables. b) Please provide a cost estimate and schedule for the delivery of one (1) single-fault tolerant flight star sensor system and associated deliverables. c) Please provide a separate cost to borrow a star sensor engineering test unit for a period of six-months (starting on a date after May 2019). 16) Heritage and Capabilities: a) Describe any spaceflight heritage designs or similar star sensor systems to the one being proposed in response to this RFI and indicate any future planned missions. b) Provide a brief summary of your fabrication and test facilities that demonstrate the ability of your company to support the PACE requirements. The North American Industry Classification System (NAICS) code for this procurement is 334511 - Search, Detection, Navigation, Guidance, Aeronautical, and Nautical System and Instrument Manufacturing with a size standard of 1,250 employees. No solicitation exists; therefore, do not request a copy of the solicitation. If a solicitation is released, it will be synopsized in FedBizOpps. It is the potential offeror's responsibility to monitor this site for the release of any solicitation or synopsis. Estimated award date for this contract is December, 2018. Responses must include the following: name and address of firm, size of business; average annual revenue for past 3 years and number of employees; ownership; whether they are large, small, small disadvantaged, 8(a), Woman-owned, Veteran Owned, Service Disabled Veteran Owned, Historically Underutilized Business Zone and Historically Black Colleges and Universities)/Minority Institutions; number of years in business; affiliate information: parent company, joint venture partners, potential teaming partners, prime contractor (if potential sub) or subcontractors (if potential prime); list of customers covering the past five years (highlight relevant work performed, contract numbers, contract type, dollar value of each procurement; and point of contact - address and phone number). In addition, please let the contacts below know if you are interested in responding to this RFI prior to the deadline. Notification of interest will allow us to provide updated/revised information to the requirements and questions below. Procurement related questions should be directed to: Elizabeth Abraham Contract Specialist NASA/Goddard Space Flight Center 8800 Greenbelt Road Greenbelt, MD 20771 Phone: (301) 614-6996 E-mail: elizabeth.d.abraham@nasa.gov Technical questions should be directed to: Linh Nguyen Components and Hardware Systems Branch NASA/GSFC Code 596 Greenbelt, MD 20771 Phone: (301) 286-3419 Fax: (301) 286-3823 Email: linh.nguyen-1@nasa.gov This requirement is not considered a commercial item. While our intent may be to team with an industry partner(s), we are not bound by this RFI to do so. This is not a Request for Proposal, nor a Request for Quotation, nor an Invitation to Bid. Therefore, this RFI is not to be construed as a commitment by the Government to enter into a contract nor will the Government pay for information provided in response to this RFI. It is not NASA's intent to publicly disclose vendor proprietary information obtained during this solicitation. To the full extent that it is protected pursuant to the Freedom of Information Act and other laws and regulations, information identified by a respondent as "Proprietary or Confidential" will be kept confidential. Comments and suggestions for improving the requirements documents are always encouraged and solicited. All responses shall be submitted to Elizabeth Abraham via electronic mail (in either Microsoft Word or ADOBE PDF format) to the e-mail address above no later than February 13, 2018 at 4:00 PM EDT. Please reference 2018-ST-GSFC-NASA in any response.
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FBO.gov Permalink
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- Record
- SN04791939-W 20180119/180117231323-5482e673e0fbe4faaa7adb607526808c (fbodaily.com)
- Source
-
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