Loren Data's SAM Daily™

FBO DAILY ISSUE OF JUNE 28, 2009 FBO #2771
SOURCES SOUGHT

A -- SPACECRAFT BUS AND OPERATIONS REQUEST FOR INFORMATION FOR THE CLIMATEABSOLUTE RADIANCE AND REFRACTIVITY OBSERVATORY MISSION

Notice Date

6/26/2009
 

Notice Type

Sources Sought
 

NAICS

541712 — Research and Development in the Physical, Engineering, and Life Sciences (except Biotechnology)
 

Contracting Office

NASA/Langley Research Center, Mail Stop 144, Industry Assistance Office, Hampton,VA 23681-0001
 

ZIP Code

23681-0001
 

Solicitation Number

SS-CLARREO-SC
 

Response Due

7/27/2009
 

Archive Date

6/26/2010
 

Point of Contact

Robert B. Gardner, Contracting Officer, Phone 757-864-2525, Fax 757-864-7898, Email Robert.B.Gardner@nasa.gov - Timothy P Cannella, Contracting Officer, Phone 757-864-5028, Fax 757-864-7709, Email Timothy.P.Cannella@nasa.gov<br />
 

E-Mail Address

Robert B. Gardner
(Robert.B.Gardner@nasa.gov)
 

Small Business Set-Aside

N/A
 

Description

SPACECRAFT BUS AND OPERATIONS REQUEST FOR INFORMATION (RFI) FOR THE CLIMATEABSOLUTE RADIANCE AND REFRACTIVITY OBSERVATORY (CLARREO) MISSION1. Introduction The National Aeronautics and Space Administration (NASA) is conducting a missionformulation study for the CLARREO mission. CLARREO is a climate focused mission that willbecome a key element of the climate observing system. The foundation for CLARREO is theability to produce irrefutable climate change records through the novel application ofonboard traceability and calibration techniques. CLARREO will measure spectral reflectedsolar energy, emitted infrared radiances and Global Navigation Satellite System (GNSS)Radio Occultation (RO) refractivities. These measurements will be used to detect climatechange trends and test, validate, and improve climate prediction models. The CLARREOmission will provide accurate, credible, and tested climate change records that lay thegroundwork for informed decisions on mitigation and adaptation policies that address theeffects of climate change on society. Further information is available at the following websites (Note: the data found withinthis RFI is the most current data):http://clarreo.larc.nasa.gov/docs/Decadal_Survey.pdfhttp://clarreo.larc.nasa.gov/docs/CLARREO_Data_from_Decadal_Survey.pdfhttp://www.star.nesdis.noaa.gov/star/documents/ASIC3-071218-webversfinal.pdfThis RFI including (referenced tables and figures) is posted at the CLARREO website:http://clarreo.larc.nasa.govThe purpose of this RFI is to obtain information to support a Mission Concept Review(MCR) in late 2009 and to investigate options for procuring two spacecraft buses andspacecraft bus operations for the CLARREO mission. Each integrated spacecraft bus andGovernment Furnished Equipment (GFE) payload will form an observatory. A description ofspacecraft bus development (1) and spacecraft bus operations (2) is captured below: (1) Spacecraft bus development includes:Spacecraft bus design, development and test, integration of GFE payload, full observatoryfunctional testing, performance and environmental testing, shipment to the launch site,support of launch operations, and on-orbit performance verification.(2) Spacecraft bus operations include:On-orbit spacecraft bus command and control; including the design, development,procurement, integration, testing, operational staffing, training, implementation andmaintenance to provide spacecraft bus health and attitude control. The submission of responses for either spacecraft bus development, spacecraft busoperations, or both, is acceptable. Vendors are not required to respond to both sectionsof this RFI.This RFI seeks input from vendors with experience and facilities for designing, fabricating, and integrating Earth orbiting observatories. The following capabilities aredeemed critical: Spacecraft bus management/developmentSubcontract managementQuality managementSafety managementSystems EngineeringSpacecraft bus fabrication and testInterface and Interface Control Document (ICD) developmentPayload integration and test support Observatory functional and environmental testingCoordination of observatory shipment to the launch siteLaunch vehicle integration supportLaunch and early orbit checkout operationsOn-orbit operation Sustaining engineeringFlight software maintenanceResponses to this RFI shall be commensurate with the requirements for the CLARREO missiondescribed below. The CLARREO mission is currently envisioned to consist of two duplicate observatorieseach carrying a payload of one infrared (IR) instrument suite, one reflected solarinstrument suite and a GNSS RO instrument system. The IR instrument will be pointed withrespect to the spacecraft bus nadir deck by an instrument internal mirror to enablenadir, off-nadir, internal calibration, and deep-space (zenith) observations. Thereflected solar instrument suite consists of three spectrometers which will beco-boresighted, combined into a single instrument suite and mounted to a two-axis gimbalto enable nadir (nominal operations), and off-nadir Lunar and Solar observations. Thetwo-axis gimbal is assumed to be part of the payload. The GNSS-RO will require a total ofthree antennas integrated on the ram, wake, and zenith faces. The zenith face antennawill be a precision orbit determination (POD) antenna. The GNSS RO system is considered ascience instrument; the spacecraft bus should provide an independent means for acquiringany required observatory position information. The instruments are currently envisionedto be integrated on a payload structure and then integrated as a payload assembly to thespacecraft bus. The only exception is the GNSS wake antenna which will need to beintegrated to the spacecraft bus (See Figure 2). The payload instruments, relatedhardware, and software elements shall be considered to be provided by others.Two possible observatory / launch vehicle configurations are currently envisioned and arebeing evaluated:Configuration A: The first configuration is a dual manifested launch with bothobservatories and a preliminary Launch Readiness Date (LRD) of December 2016. Configuration B: The second configuration consists of two separate observatorylaunches. The preliminary LRD for the first observatory is July 2016, and the preliminaryLRD for the second observatory is January 2017. The unique requirements for the CLARREO spacecraft buses are as follows:2. Mission Requirements (Both Observatories)Minimum Operational life: 3 years with consumables for 5 yearsNominal Orbit Altitude: 600 kilometersNominal Orientation: Local Vertical Local Horizontal (LVLH)Orbit: Earth orbiting, 90 degree polar inclination, 90 degree separation inlongitude of the ascending node between observatories (when looking down at the Northpole, the two orbit planes are separated by 90 degrees)Payload risk classification of C should be assumed per NASA ProceduralRequirement (NPR) 8705.4 Risk Classification for NASA PayloadsYaw flip maneuver required 2 times per year for payload thermal managementSpacecraft bus must be capable of automated fault detection and protection(failure, detection, isolation, and recovery capabilities)Spacecraft bus must be capable of reprogramming the on-board flight software toadjust for mission needs and address anomaliesSpacecraft bus must meet the NASA Procedural Requirements for Limiting OrbitalDebris (NPR 8715.6A) and NASA Process for Limiting Orbital Debris (NASA-STD-8719.14)Contamination RequirementsoNon-metallic materials shall be limited to a Total Mass Loss (TML) < 1%oNon-metallic materials shall be limited to a Collected Volatile Condensable Mass(CVCM) < 0.10%oAlthough values have not been determined, spacecraft bus will need to meet aspecific outgassing rate, including solar array(s)oAlthough values have not been determined, the spacecraft bus will need to meet,lower than typical, specific deliverable and End of Life (EOL) particle levels identifiedin Product Cleanliness Levels and Contamination Control Program (IEST-STD-1246)oObservatory integration and test operations shall be conducted, most likely, in a10K (ISO Class 7) clean roomoSpacecraft bus venting shall be preferentially directed orthogonal to the ram /wake direction. 3. Payload Description (All mass and power numbers reflect Current Best Estimate (CBE)plus contingency)Total Average Payload Power 418 Watts (334 CBE plus 25% contingency)Total Payload Mass 339 kilograms (271 CBE plus25% contingency) Payload shall not use spacecraft bus for thermal energy dissipation (adiabaticpayload/spacecraft bus interface) MIL-STD-1553B command and telemetry bus to payload instruments can be assumedSerial data interfaces sufficient to support the science data rates should beassumedInstrument descriptions are shown in Table 1. All mass and power numbers reflect CurrentBest Estimate (CBE) plus contingency4. Communications and Data Handling:Science data communication: X band at rates compatible with NASA Ground Networkin a Consultative Committee for Space Data Systems (CCSDS) standard formatCommand and spacecraft bus telemetry communication: S band at rates compatiblewith the NASA Ground Network in a CCSDS standard formatReliable CCSDS File Delivery Protocol (CFDP) Level 2 supportSpacecraft bus will downlink both X and S-Band with ground stations 6-9 times perdayNASA Near Earth Network (NEN) will be utilized for nominal, on-orbit spacecraftcommanding and data reception (ground stations will include: Poker Flats, AK; WallopsIsland, VA; and Svalbard, Norway)NASA Space Network (TDRSS) will be utilized for launch and early orbit andcontingency commanding.Connectivity with NEN and TDRSS ground stations will be accomplished via the NASAIntegrated Services Network (NISN)Data Storage: Solid State Recorder of sufficient size to meet science datavolume, expected downlink schedule, and recommended margin. 5. Attitude Determination and Control SystemSpacecraft bus to maintain Local Vertical Local Horizontal (LVLH) attitudethroughout the mission duration.2 yaw flip maneuvers per year required for payload thermal management3-axis stabilizationAttitude knowledge: < 0.1 degree or360 arc secondsAttitude accuracy: < 0.1 degree or 360 arc secondsAttitude jitter: < 0.01 degree or 36 arc secondsAttitude drift: < 0.01 degrees or 36 arc seconds over 0.1 seconds 6. PropulsionSpacecraft bus must carry on-board propulsion system to account for launchinjection dispersion, orbit maintenance up to 5 years within +/- 200 meters altitude and +/- 0.1 degrees inclination, momentum dumping and deorbit requirements. Spacecraft bus must meet the NASA Procedural Requirements for Limiting OrbitalDebris (NPR 8715.6A) and NASA Process for Limiting Orbital Debris (NASA-STD-8719.14).Please assume a controlled re-entry is necessary and include this in the spacecraft buspropulsion system sizing. For the dual manifest launch configuration, assume the launch vehicle inserts oneobservatory at an inclination of 90.97 degrees and the second observatory at aninclination of 89.03 degrees. Both observatories drift for approximately one year andthen assume each observatory performs a propulsive maneuver to an inclination angle of 90degrees so that both observatories are at 90 degree inclination with 90 degree separationin longitude of the ascending node between observatories. The estimated delta V for thispropulsive maneuver is approximately 128 m/s for each observatory and should be includedin the spacecraft bus propulsion system sizing. This propulsive maneuver is not requiredfor the separate launch configuration. 7. LaunchConfiguration A: Dual manifest launch configuration:oFor purposes of accommodation, please recommend a launch vehicle for the dualmanifested launch in 2016Configuration B: Separate launch configuration:oFor purposes of accommodation, please recommend a launch vehicle for the separateobservatory launches in 2016 and 2017. In both configurations, assume the launch vehicle shall be a US launch vehicleand considered Government furnished. In selecting a launch vehicle, the vendor shall maintain a minimum mass margin of30 % between the observatory mass (CBE + contingency) and the launch vehicles liftcapability to the CLARREO orbit.8. OperationsAlthough each observatory has an operational lifetime of 3 years with consumablesfor 5 years, CLARREO operations will be designed for a long-term mission (20 years ormore) with replacement observatories. RFI responses shall consider the cost of annualoperations and maintenance as well as the recurring cost to refresh the spacecraftoperations hardware (approximately every 5 years).oThe spacecraft operations system will be designed to minimize the cost and riskof operations, including minimizing the number of operators required to safely commandand control the spacecraft, and maximizing use of spacecraft and ground system faultdetection, reporting and protection tools.The CLARREO payload will be operated by other organizations separate from thespacecraft bus. Payload commands will be sent to the spacecraft bus via the spacecraftoperations center. The spacecraft operations center will verify payload commands in orderto ensure the safety of the bus, otherwise payload operations are beyond the scope ofthis RFI.The conceptual, on-orbit system architecture is shown in Figure 1. below:Spacecraft operations functions will include, but are not limited to:Command and control: The spacecraft operations center (OC) will plan and executeall commanding for both spacecraft and will verify and transmit all commanding for theinstruments. The OC will plan and execute command uploads approximately once per day perobservatory. Each observatory will likely require routine maneuvers in order to maintainproper orbit parameters and thermal control (2 yaw flips per year).Planning and scheduling: The OC will be able to perform all of the activitiesand functions required to maintain the health and attitude of both observatories;including planning all contacts with the observatory, integration of flight dynamicsdata, coordination/scheduling with the NASA Near Earth Network (and Space Network asrequired), and building, transmitting, and verifying command loads. The observatory willdownlink with earth stations as discussed in Section 4: Communications and Data Handlingabove.Trending and analysis: The OC will have tools to automatically select, store,trend, display, and report spacecraft engineering data.Anomaly resolution: The OC will be capable of quickly responding to andcorrecting anomalies with either the observatories or the ground system.Flight dynamics: The OC will be capable of generating flight dynamic productsfrom onboard GPS data and ground network tracking data. The response to the RFI shouldindicate if the OC will need to interface with and utilize products from external sourcesduring launch and early orbit or contingency response (such as the Flight DynamicsFacility (FDF) at Goddard Space Flight Center).On-board data storage management: The OC will be capable of tracking and managingthe storage space for science data onboard the observatory.Integration and testing: The OC and mission ops team will support integration andtesting of the payload and the spacecraft bus.The OC software and tools will beutilized for spacecraft I&T.Mission simulations: The OC will utilize mission simulations andspacecraft/instrument simulators in order to verify command uploads and to supporttraining of operational personnel.GUIDE FOR RFI RESPONSESVENDOR PROPOSAL CONTENT INSTRUCTIONSResponses to this RFI will support a Mission Concept Review (MCR) preliminarily scheduledfor late 2009. Please provide information on the spacecraft bus that meets the aboverequirements and accommodates the payload. The requested information is documented in thefollowing sections.Spacecraft Bus Development:Section 1- Description of proposed spacecraft bus including spacecraft configuration,hardware capabilities, redundancies, payload accommodation, accommodation in launchvehicle, deployments, fields of view description, alignments and calibration, attitudecontrol methodology, command and data flow. Please include discussion and presentationon accommodation of the payload and fields of view. Payload CAD models (in STEP (.STP)format) providing notional representations of the payload will be provided upon request.Section 2 Description of the reliability of the proposed bus including: all margins andredundancies, fault detection and protection, potential risks and mitigations, any newdesigns and associated risks. In addition, please identify any payload requirements thatcontribute to the spacecraft bus design and development risks.Section 3 Identification of requirements that are drivers for spacecraft bus andaccommodation in the launch vehicle. Please suggest changes in requirements that willresult in substantial cost reductions. In addition, suggest accommodation approaches thatwill meet the requirements but would require changes in the payload design.Section 4 Description of the proposed spacecraft bus heritage. If the proposed bus issubstantially different from a heritage bus, then propose suggestions in payload designor payload requirements that would enable use of a heritage bus.Section 5- Description of the observatory mass and power breakdowns by subsystem. Include the current best estimate (CBE) for mass and power and recommended contingenciesfor each subsystem. Any additional margins in the spacecraft bus design beyond thestated contingencies should be identified. The payload mass and power numbers in this RFIare current best estimates with contingency included. In selecting a launch vehicle thevendor shall maintain a minimum mass margin of 30% between the observatory mass (CBE +contingency) and the launch vehicles lift capability to the CLARREO orbit.Section 6 Description of the assembly, integration, test and launch operations approachfor the spacecraft bus and observatory levels. Any differences from the contractorsnormal test flow should be identified and described.Section 7- ROM price estimates, including required funding profile, and schedule,including reserves for: spacecraft buses and full mission observatory implementationconsistent with the above characteristics and capabilities (including spacecraft busmanagement/development, subcontract management, quality management, safety management,systems engineering, spacecraft bus fabrication and test, interface and ICD development,payload integration and test support, observatory functional and environmental testing,coordination of observatory shipment to the launch site, launch vehicle integrationsupport, on-orbit checkout, sustaining engineering, and deliverable documentation). Section 8- Description of key technical, schedule and price drivers and options tomitigate and/or trade against price reductions. Information on technical, schedule and price drivers associated with developingtwo spacecraft buses for both launch configurations (A and B) is of interest. Pleasedescribe the optimum spacecraft bus development approach for both launch scenarios.Given that the CLARREO mission is envisioned to be a long term mission (20 yearsor more), information on developing a spacecraft bus where costs savings can be realizedbased on multiple units being built and procured, including the option of adjusting thespacecraft bus lifetime and subsequent launch spacing is of interest. Cost differencesbetween the 1st and 2nd unit as well as between the 2nd and 3rd units for follow onmissions is desired. Section 9 - ROM price estimate and description of a spacecraft bus interface emulator tobe used to test interfaces with the payload/instruments. Current plans include test andverification of the power and data hardware and protocol interfaces between thespacecraft bus and payload/instruments before system level integration and testactivities. Spacecraft Operations:Section 10- Description of spacecraft operations to include: The recommended choice of operational software tools (indicate if these areCOTS/GOTS/or mission specific), operations center hardware, and simulators.The staffing required for development and operations, the phasing of requiredmanpower, and the level, description, timing of operational training.The level and descriptions of autonomous flight operations.Maintenance concepts for operations center software and hardware, with anemphasis on supporting a long-term mission.Mission unique test provisions.Flight Software MaintenanceDiagrams of data flow and operational processes.Section 11- ROM price estimates, including required funding profile, and schedule foroperations center design, development, procurement, integration, testing, staffing,training, implementation, and maintenance. Include recommended contract types andoptions (e.g., fixed price versus cost, options for hardware refresh)Section 12- Description of key technical, schedule and price drivers and options tomitigate and/or trade against price reductions. Please suggest changes in requirements orconcepts that will result in substantial cost reductions. Information on technical, schedule and price drivers associated with developing aspacecraft operations capability for both launch configurations (A and B) is of interest.Information on technical, schedule and price drivers for designing, implementing,staffing, and maintaining a highly automated operations center is of interest.Vendor Capabilities:Section 13- Description of company capabilities and past experience performing spacecraftbus management/development, observatory I&T, launch support, and mission operationssimilar to this missionFigures 2-4 show multiple views of the CLARREO observatory and the FOR requirements. This RFI is issued by the NASA/LaRC to solicit responses from interested parties. ThisRFI is not to be construed as a commitment by the Government, nor will the Government payfor the information submitted in response. Respondents will not be notified of theresults.Technical questions should be directed to Craig Jones (for spacecraft) atcraig.d.jones@nasa.gov and Steve Hall (for operations) at stephen.r.hall@nasa.gov. Allother questions should be directed to Brad Gardner at robert.b.gardner@nasa.gov or TimCannella at timoth.p.cannella@nasa.gov.Responses are not page limited and should be emailed to the four individuals cited above.Hardcopy can be mailed to Brad Gardner at NASA Langley Research Center, Mail Sop 126,Hampton, Va 23681-0001. In all communications, reference SS-CLARREO-SC. An ombudsman has been appointed -- See NASA Specific Note "B".The Internet site, or URL, for the NASA/LaRC Business Opportunities home page ishttp://prod.nais.nasa.gov/cgi-bin/eps/bizops.cgi?gr=D&pin=23 Any referenced notes may be viewed at the following URLs linked below.
 

Web Link

FBO.gov Permalink
(https://www.fbo.gov/spg/NASA/LaRC/OPDC20220/SS-CLARREO-SC/listing.html)
 

Record

SN01859045-W 20090628/090627002042-2576b370f7dde0aafdd2bba09b4528c7 (fbodaily.com)
 

Source

FedBizOpps Link to This Notice
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