POD for NASA/GSFC Science Instrument: Instrument Design, Fabrication, Integration, and Test

Partnership Opportunity Document (POD) for NASA's Goddard Space Flight Center Science Instrument -- Instrument Design, Fabrication, Integration, and Test dated June 2, 2018 TABLE OF CONTENTS SECTION PAGE 1.0 Introduction/Scope 3 1.1 Cost 3 1.2 Desired Mission Services 4 1.3 Proposal Support 4 2.0 Mission Overview 5 2.1 Launch Vehicle 5 2.2 Launch Readiness date 6 3.0 Technical Requirements 6 3.1 General 6 3.2 Laser Accommodation 6 3.3 Optical 6 3.4 Mechanical 7 3.5 Thermal 7 3.6 Electrical 7 3.7 Data 10 4.0 Statement of Work 10 5.0 POD Response Instructions, Format, and Selection Criteria 10 5.1 Instructions 10 5.2 Format 11 6.0 Evaluation Factors and Criteria 11 7.0 Point of Contact: 12 8.0 Final Due Date of POD Response 12 9.0 Acronyms 12 ? 1.0 INTRODUCTION/SCOPE This proposal opportunity will respond to the NASA Heliophysics 2018 Mission of Opportunity (MoO) Announcement of Opportunity (AO). The draft AO was released on 05/03/18. NASA's Goddard Space Flight Center (GSFC) is developing a mission concept to be proposed for this AO. The mission will consist of an optical / laser instrument that will be hosted on the International Space Station (ISS), specifically on the Japanese Experiment Module External Facility (JEM-EF). The partnership opportunity is issued to select a teaming partner that will develop the instrument and deliver a fully integrated and tested instrument ready for integration into the launch vehicle. The laser(s) will be fully developed and tested by GSFC and provided to the partner, as Government Furnished Equipment (GFE), for integration into the instrument. The proposed mission is currently in pre-Phase A. This phase ends with a Step 1 proposal, which is expected to be due six months after the release of the draft AO. If the proposal is selected, the next step in the proposal process is a mission concept study culminating in a Concept Study Report (CSR), which is the Step 2 proposal, and a Site Visit. The following schedule should be used as a basis for responses to this opportunity: Partnership Opportunity Document (POD) released June 2, 2018 Responses due June 15, 2018 Partner Selection announced June 29, 2018 Project Phase duration and milestones*: Phase A: 10/1/19-9/30/20 - (12 months) Phase B: 10/1/20-7/6/21 - (9.2 months) Phase C: 7/7/21-10/11/22 - (15.2 months) Phase D: 10/12/22-10/31/23 - (12.6 months) Systems Requirements Review (SRR): 8/3/2020 Preliminary Design Review (PDR): 5/27/2021 Critical Design Review (CDR): 2/21/2022 Integration & Testing (I&T): 10/12/22 - 6/15/2023 Pack & Ship: 6/16 - 6/22/2023 Launch: 09/29/2023 * Please note all the project schedule dates listed are subject to slip due to AO release dates and project award. 1.1 COST Total cost and cost fidelity are important issues for the mission trade studies. The cost cap for this AO is expected to be $55 million. This cost includes the instrument, launch site support, mission and science operations for a mission lifetime of 18 months plus commissioning, and post mission processing, as well as required contingency (25% or greater reserves). The Phase A mission concept study (Step 2 down-selection) will have a total cost cap of $400,000. There will be no exchange of funds between the teaming partners for the portion of this partnership opportunity dealing with the preparation of the initial submission (Pre-Phase A, Step 1 proposal) to the AO. Funding may be available for subsequent phases should the candidate mission concept be competitively selected for those additional phases. 1.2 DESIRED MISSION SERVICES GSFC is interested in formally establishing a partnership to provide the following for the mission: provide instrument management, systems engineering, design, fabrication, integration, and test of the science instrument, and incorporating a laser subsystem to be provided by GSFC, providing instrument support for the launch vehicle, to-ISS, and to-operations center interface support during the mission development phase. The proposer will have knowledge and experience with design and implementation of instruments for the ISS/JEM external facility. The Partner will participate in all aspects of the instrument development, from concept to launch site support, including all relevant reviews. The Partner will support the PI in the development of the Project Implementation Plan per the guidelines in the announcement of opportunity for a small Category 3 Class D project per NPR 7120.5E instrument and manage their day to day project schedule and costs as agreed to with the PI. The Partner will perform systems engineering and product assurance necessary to meet mission objectives. The expected distribution of responsibilities will be as follows: GSFC: - Principal Investigator/science team - Program Management - Laser Development (laser will be GFE to be integrated into the instrument by the POD partner - Independent Technical Authority - Mission Operations and Ground Systems (developed by Co-I institution) POD partner: - Instrument Management: o Perform the instrument management and support functions, including instrument manager (IM), contracts and procurement, resources, configuration, schedules, project support and logistics. This instrument manager will report to the GSFC program manager. - Systems Engineer: o Perform the instrument systems engineer functions, including proposal development (working with the GSFC proposal team, see Sec. 1.3), requirements development, interface definitions (with GSFC laser, ISS, and launch vehicle, ground systems and operations), review preparation and presentation (all required reviews), concept design and flight and GSE hardware development, integration and test, launch and instrument commissioning support. - Safety and Quality Assurance: o Perform safety and quality assurance functions, including preparation for the required ISS safety, and, hardware quality assurance. The partner is responsible for delivery of an integrated and tested flight-ready instrument to the launch site, per the project schedule. The partner is not required to develop the following hardware/subsystems. However, the partner is responsible for ensuring the proper interfaces and making accommodations for fit/operation, and integration and testing (at instrument level) of the following: - Laser(s): Developed by GSFC, (GFE to the partner) - Optical Filters: (GFE to the partner) - PIU: Provided by the ISS, (GFE to the partner) - Launch Vehicle Mounts: Provided by ISS/Launch Vehicle Service (GFE to the partner) - ISS Installation/decommissioning tools The partner is responsible for development/procurement of all other instrument components and systems, including: - Flight structure and optical bench - Deployable mechanisms - Optics (telescope, sub-optics, and detectors) - Thermal control system (fluid cooling loops, heaters, blankets, and control electronics) - Electronics (power, command and data handling, communication, and mechanism control) - Analyses: o Structural o Thermal - GSE: All necessary GSE for processing the instrument during I&T and transportation. 1.3 ALL INTERESTED PARTIES ARE REQUIRED TO RESPOND TO THIS POD IN ACCORDANCE WITH SECTION 5 BELOW. PROPOSAL SUPPORT It is expected that the selected POD respondent will provide support using their own resources to help develop the required MoO proposal elements in response to the Step 1 Pre-Phase A NASA AO in the area of a well-defined and documented instrument, instrument-to-launch vehicle integration support, instrument-to-ISS interface support, and instrument-to-operations center interface support. The POD respondent will be expected to write or assist in the writing of portions of the proposal relevant to their responsibilities. Furthermore, the POD respondent will meet with the Principal Investigator (PI) and other proposal team members to help define the end-to-end performance requirements, including providing well-defined interfaces to the ISS and the GFE laser subsystem, to define the system architecture, to identify study topics, and to predict performance. This will include cost estimation for mission phases. The period of performance for this interval is expected to last from the award of the POD until the proposal submission date. Should the proposal be down-selected for a Phase A Mission Concept Study, the selected partner will support the Phase A effort for the 9-month to one-year concept study phase, culminating in a Mission Concept Study Report as the Step 2 proposal. The selected partner will also provide support to prepare for and execute a review panel Site Visit (location and exact date TBD). Partial funding may be provided to the partner for this Phase A mission concept study support, Mission Concept Study Report, and Site Visit. Should the mission be selected for development and launch (Phases B-F), the partner will be responsible for the design, development, integration, test, and delivery of the instrument, as well as for launch site support. The above dates and durations may change depending on selection timelines and budget allocations or phasing. The respondent to this POD shall state the timeframe that their services will be available and the extent that the respondent can meet the expected AO timeline requirements. 2.0 MISSION OVERVIEW The mission consists of an earth-pointing lidar instrument mounted on the ISS JEM-EF. The mission uses two lasers to send pulses into the earth's atmosphere and a receiver telescope to collect the photons returned from the atmosphere. Photon-counting detectors transmit photon data to the instrument electronics, which perform minimal onboard processing before transmitting the data across the ISS data interface for transmission to the ground, and ultimately to the science operations center (SOC) at GSFC. Boresight alignment mechanisms will be operated as necessary to maintain alignment between the transmitted lasers and the receiver telescope field of view. Heat dissipated by the lasers and electronics is transported away from the instrument by the instrument liquid cooling loop which will be connected to the JEM-EF liquid cooling loop. The instrument must meet JEM-EF accommodation requirements for volume, mass and power, and must adhere to specific electronic, data, and physical interface requirements, including interfaces for the launch vehicle and for the ISS robotic arm that will remove the instrument from the launch vehicle and install it on the JEM-EF, and will un-install the instrument from the JEM-EF and install it in the return vehicle, at the end of the mission. GSFC 420-01-09, EXTERNAL PAYLOADS PROPOSER'S GUIDE to the International Space Station, and, NASDA-ESPC-2900B, JEM Payload Accommodation Handbook, are examples of sources for the JEM requirements for hosted payloads. 2.1 LAUNCH VEHICLE The launch vehicle and launch services are provided by NASA's ISS program. The likely launch vehicle is a Space-X Falcon 9 with a dragon capsule. The dragon capsule has an instrument transport compartment, the "trunk", which has specific instrument interfaces. The instrument will be delivered to the Space-X processing facility and, after minimal instrument team launch site operations, will be turned over to the Space-X launch site team for integration to the dragon capsule. 2.2 LAUNCH READINESS DATE The vendor must commit to meeting the launch readiness date specified in the Mission of Opportunity AO. This date is currently expected to be 09/29/2023. SRR: 8/3/2020 PDR: 5/27/2021 CDR: 2/21/2022 I&T: 10/12/22 - 6/15/2023 Pack & Ship: 6/16 - 6/22/2023 Launch: 09/29/2023 Note: All above dates are approximate 3.0 TECHNICAL REQUIREMENTS 3.1 GENERAL The mission will be a small Category 3 Class D project per NPR 7120.5E, with an 18 month lifetime that is consistent with the EHPD Mission Assurance Requirements (EHPD-RQMT-0003) Unless otherwise noted, the provider is expected to deliver one flight unit for each component listed. Mass: <320 kg, total instrument (including GFE lasers) (excluding PIU and launch vehicle mounts) Power: <440 W, total instrument (including lasers power = 246 W) Communication: ISS/JEM 1553 3.2 LASER ACCOMMODATION Quantity: 2 each Envelope: 87 x 204 x 305 mm (each laser) Mass: 17 kg total (both lasers) Wavelength: 589 nm Laser Power: 123 W each, 246 W total (included in the instrument total) 3.3 OPTICAL Telescope: - 0.6 m primary aperture - Beryllium substrate and metering structure - Optimized for ?=589 nm (>90% reflectance) - Mass < 22.5 kg - Volume: o Diameter < 612 mm o Length < 500 mm Detectors: - 8 each, Perkin Elmer Silicon Avalanche Photo Diode (APD) - Model: SPCM-AQR-IX Aft optics: - Full development: o Including: optical elements, mounts, and detector fiber optics o Excluding: GFE filters (e.g. etalon). 3.4 MECHANICAL Instrument Enclosure: - Instrument structure, including all internal (instrument components) and external mounting and interfaces with the ISS JEM and its associated robotics. Instrument Optical Bench Analysis: - Structural design and analysis for all instrument subsystems Aperture Cover Mechanism: - Deployable door, command deployable, launch lock, capable of stowing via command and ISS robotics operations. Bore-sight Alignment Mechanism: - 2 each, (one per laser), to provide rotation for GFE Risley prism pairs. - Each mechanism provides 2 DOF (angular) control over the laser pointing/alignment. Laser Aperture Cover Mechanism: - 2 each, (one per laser), operations via command 3.5 THERMAL Analysis: - Thermal subsystem design and analysis of all instrument systems Fluid Cooling Loop: - Develop fluid loop to interface with the ISS JEM, including the cold plates, accumulator(s), lines, and flow control orifices Heaters: - Design and specification of the heater circuits, implementation of all operational and survival heater circuits and elements into the instrument Thermal blankets: - Design and development of all thermal control blankets 3.6 ELECTRICAL Main Electronics (ME) general requirements - The main electronics shall interface to ISS 1553B communications - The main electronics shall interface to ISS power service - The main electronics shall interface with the laser electronics units Main Electronics (ME) Requirements 1. ME should encompass three main functions which could be physically allocated into one or more electronics modules: Power Conversion, Laser Control, and Instrument Avionics. Each module may contain an appropriate number of electronics cards to perform the three required functions subject to the instrument mass, volume, and power requirements. a. Power Conversion 1. Provide ISS 120 Volts Direct Current (VDC) power conversion down to 28 VDC for the overall instrument. 2. Provide 28 VDC power for two Laser Electronics Units (LEUs.) b. Laser Control 1. Interfaces to two Lasers. 2. Provides an interlaced 300 Hz differential master clock for each of two LEUs. 3. Provides command, communications, control, and telemetry services to the LEUs. 4. Each Laser command and control shall be performed via two serial RS422 links. 5. Each Laser shall generate a T0 timing signal that verifies continued Laser firing. NOTE 1: The two LEUs are GFE. The Main Electronics (ME) does not include the LEUs. c. Instrument Avionics (IA) 1. Provides single-channel 1553B Remote Terminals (RT) bidirectional communications to the ISS 1553 BBC. 2. Provides ISS command parsing and command response. 3. Generates and distributes two interleaved 300 Hz clock signals to the two LEUs. 4. Receives Laser photon count science data collected by eight Single Photon Counting Modules (SPCMs). 5. The Instrument Avionics (IA) shall ingest the SPCM maximum photon count of 20 Mcps/SPCM x 8 SPCMs. Therefore, the total maximum science input photon count rate is 160 Mega counts per second (Mcps). 6. The 8 SPCMs bin counts are captured and summed by the IA for each time bin. 7. The IA shall create photon count bins from the SPCMs Transistor-Transistor Logic (TTL) signals as follows: - A 240 bin data set is captured for each pulse. - A data set for each laser wavelength is transmitted to the ISS twice per second. 8. The IA shall collect and transmit housekeeping telemetry data from the instrument. 9. The IA provides mechanism control for all instrument mechanisms. 10. The IA provides thermal monitoring and control loops for: 4 pump diodes, 1 Etalon, The telescope primary, secondary, and overall structure. 11. The IA ingests the ISS 1 Pulse Per Second (PPS) Broadcast Ancillary Data (BAD) data for real-time ISS location and current time extraction. 12. The IA performs science data time binning, Consultative Committee for Space Data Systems (CCSDS) data packetization, Coordinated Universal Time (UTC) packet time stamping, and populates each data packet with real-time ISS coordinate positions obtained from (xi.) above. 13. The IA implements a two-fault tolerant Laser Fire Inhibit Safety requirement. This is required by the Johnson Space Center's (JSC) Computer-Based Control System (CBCS). 14. The ME supplier shall provide and deliver all Electrical Ground Support Equipment (EGSE) required for the instrument integration and test, including launch site instrument checkout. 15. The IA shall receive each Laser's T0 timing signal to properly synchronize its time binning function and monitor the Laser operation. 16. The IA shall implement a 1553B loss of signal (LOS) watch dog timer (WDT). 17. Harness: Design and develop all harness (flight and GSE) required by the instrument for flight operations and ground testing. Deliverables 1. One Engineering Model (EM) ME system. 2. One Flight Model (FM) ME system. 3. One EM EGSE monitoring and control system capable of interfacing to the I&T ASIST and/or TReK software. The EGSE shall interchangeably work with both, the EM ME and the FM ME hardware. 4. Design, test, and acceptance documentation for the ME EM and FM systems. 5. ME firmware code (no flight software) and test documentation. 6. ME User's Manual. 7. EGSE User's Manual. 8. Technical support. 9. Training for Government users and operators of the ME and EGSE hardware. 10. Complete parts list for every module of the ME and EGSE. 11. Space flight heritage, if available. Describe any previous space flight mission in which the ME hardware has previously flown. 3.7 DATA Data Rate: <16 kbps 4.0 STATEMENT OF WORK During the proposal preparation period, the partner will participate as part of the mission proposal team. Statements of Work (SOWs) are not required to be submitted with the Step 1 proposal. However, they are required before the Phase A (Step 2 proposal) work can begin. Therefore, the partner shall provide a draft statement of work during the Step 1 proposal effort that defines what the partner is proposing to provide to the mission. SOWs will include the requirement for a Phase A CSR as well as general task statements for Phases B through F. SOWs will include the following as a minimum: Scope of Work, Deliverables, and Government Responsibilities (as applicable). SOWs need not be more than a few pages in length. 5.0 POD RESPONSE INSTRUCTIONS, FORMAT, AND SELECTION CRITERIA 5.1 INSTRUCTIONS The respondent shall: - Provide demonstrated prior institutional experience and flight heritage of developing and delivering low-earth orbit instruments. - Provide demonstrated flight heritage, either within the respondent's own organization, or from proposed sub-contractors, designing and implementing mechanical, thermal, electrical, and data interfaces with the launch vehicle, and the ISS. - Demonstrate understanding and quantified experience in the design, fabrication, integration, and testing of spaceflight instruments. The response shall describe how the respondent proposes to meet the requirements given in Section 3. - Describe the instrument to the ISS JEM/EF mechanical, thermal, and electrical interfaces. Provide information on the maturity of these interfaces and indicate if the configuration has flight heritage and demonstrated on-orbit performance. - Describe the approach for instrument integration and test, including the location for these activities. This will include a discussion of what capabilities the respondent has in their own facilities, and what capabilities will need to be procured from outside the respondent's organization. This will include a description of the instrument safety and mission assurance process. - Describe the approach for supporting the AO Step 1 proposal, the mission concept Phase A study (Step 2 proposal), Step 2 Phase A Site Visit, and mission development, including the level of support that the partner plans to make available for each activity. - Demonstrate the ability to work closely with the PI and his team members at GSFC in Greenbelt, MD. Describe how the respondent will carry out day-to-day interactions with the project office at GSFC and the laser development team at GSFC. - Provide a brief statement of work defining participation in the AO Step 1 proposal. - Provide an itemized cost estimate from initial selection (Phase A) onward for all activities, including instrument design, integration and testing, and launch site support. The AO proposal process limits cost changes between the Step 1 proposal and the Step 2 proposal to no more than 20% total. The response shall include a brief discussion of the uncertainty in the cost estimate. 5.2 FORMAT The response to this partnership opportunity is limited to 15 pages in not less than 12-point font. Excluded from the page count are the cover letter, title pages, table of contents, and acronym list. Partners may attach additional appendices that further describe their capabilities, although GSFC is under no obligation to include the contents of such appendices in the evaluation of the offer package. The entire offer package, including any cover letter, title pages, and other supporting material, shall be formatted as a Portable Document Format (PDF) file delivered to the E-mail address below. 6.0 EVALUATION FACTORS AND CRITERIA The evaluation team will use the following factors in selection and award: 1. Technical (35%). Offerors will be evaluated on their ability to: a. Provide technical input during the step one proposal development. b. Provide design and development support during phase A. c. Meet the instrument technical requirements as stated in Section 3. d. Demonstrate heritage and Technology Readiness Level (TRL) of the proposed solution. e. Provide personnel, (with the experience, skills and past performance) (partner, or its sub-contractors), capable of completing the required project support, systems engineering, design, analyses, preparation and presentations at reviews, hardware development, integration, and test. f. Demonstrate capability to provide facility (at the partner, or its sub-contractors locations) that meets the instrument requirements through all its development phases from formulation to pack and ship to launch site. 2. Cost (30%). Offerors will be evaluated on their overall cost and on the reasonableness of cost and schedule estimates. 3. Relevant Experience and Past Performance (35%). Special emphasis will be given to demonstrated experience with similar missions, particularly with regards to laser and lidar instruments and to ISS-hosted payloads, and relevant reviews. 7.0 POINT OF CONTACT: Questions about this POD should be directed to Rosa E. Acevedo, at rosa.e.acevedo@nasa.gov, or (301) 286-7152. 8.0 FINAL DUE DATE OF POD RESPONSE The response to the POD is due no later than 5 p.m. EDT on June 15, 2018. The electronic PDF document shall be sent to Rosa.E.Acevedo@nasa.gov It is the responsibility of potential respondents to monitor the following site: http://fbo.gov for information concerning this POD. 9.0 ACRONYMS AO Announcement of Opportunity APD Avalanche Photo Diode ASIST Advanced Spacecraft Integration & System Test BAD Broadcast Ancillary Data CBCS Computer-Based Control System CCSDS Consultative Committee for Space Data Systems CDR Critical Design Review CSR Concept Study Report DC Direct Current DOF Degrees Of Freedom EGSE Electrical Ground Support Equipment EM Engineering Model FM Flight Model GFE Government Furnished Equipment GSFC Goddard Space Flight Center Hz Hertz IA Instrument Avionics I & T Integration & Test ICD Interface Control Document ISS International Space Station JEM-EF Japanese Experiment Module-External Facility JSC Johnson Space Center kbps kilo bits per second kg kilogram LEU Laser Electronics Unit LOS Loss Of Signal Mcps Mega counts per second ME Main Electronics mm millimeter MoO Mission of Opportunity NLT No Later Than nm nanometer NPR NASA Procedural Requirements PDF Portable Document Format PDR Preliminary Design Review PI Principal Investigator POD Partnership Opportunity Document PIU Payload Interface Unit PPS Pulse Per Second ROM Rough Order of Magnitude RT Remote Terminal SOW Statement Of Work SPCM Single Photon Counting Modules SRR Systems Requirements Review TBD To Be Determined TReK Telescience Resource Kit TRL Technology Readiness Level TTL Transistor-Transistor Logic U.S.A United States of America UTC Coordinated Universal Time VDC Volts Direct Current W Watt WDT Watch Dog Timer