SOURCES SOUGHT
A -- SPACEFLIGHT CAPABLE VISIBLE AND INFRA-RED CAMERA SYSTEMS SUITABLE FORLONG-TERM GEOSYNCHRONOUS EARTH ORBIT
- Notice Date
- 8/26/2011
- Notice Type
- Sources Sought
- NAICS
- 541990
— All Other Professional, Scientific, and Technical Services
- Contracting Office
- NASA/Goddard Space Flight Center, Code 210.S, Greenbelt, MD 20771
- ZIP Code
- 20771
- Solicitation Number
- NNG11FA81-RFI
- Response Due
- 11/1/2011
- Archive Date
- 8/26/2012
- Point of Contact
- Claudia Canales, Contracting Officer, Phone 301-286-5990, Fax 301-286-0471, Email Claudia.Canales-1@nasa.gov - Nylsevalis Ortiz-Collazo, Contracting Officer, Phone 301-286-2387, Fax 301-286-1670, Email Nylsevalis.Ortizcollazo-1@nasa.gov
- E-Mail Address
-
Claudia Canales
(Claudia.Canales-1@nasa.gov)
- Small Business Set-Aside
- N/A
- Description
- The National Aeronautics and Space Administration (NASA) is soliciting informationthrough this Request for Information (RFI) to improve its understanding regarding thecurrent state-of-the-art of commercially available spaceflight camera systems. NASA isseeking broad information concerning previously flown camera systems, systems currentlyin development for other non-NASA missions, as well as future technologies that arerelevant to long duration spacecraft missions designed to operate in Geosynchronous EarthOrbit (GEO). In accordance with FAR 15.201(e), the information requested is for planning purposes onlyand is not intended to bind the Government.1.Background and Study Plan:NASA Goddard Space Flight Center (GSFC) has undertaken a study regarding the feasibility,practicality, and cost of operating a fleet of spacecraft for long duration missionlifetimes in Geosynchronous Earth Orbit (GEO). One particular area of this study that isof keen interest to GSFC is the availability of spaceflight capable visible and infra-redcamera systems suitable for long-term usage at GEO. Early results of our study have shownthat this spacecraft will require a wide array of camera systems to ensure missionsuccess. This RFI is the first step in identifying relevant and interested industrypartners to join GSFC in the development of these various camera systems. The main intentof this RFI is to solicit responses from industry on the current state-of-the-art inregards to spaceflight cameras. In this RFI, GSFC will describe the various types ofcamera systems it is currently investigating as well as some basic technicalspecifications. Elements described in this RFI will serve as a starting point fortechnical requirements that have yet to be defined. Responses will be assessed andconsidered based upon numerous criteria including, but not limited to, cost, TechnologyReadiness Level (TRL), spaceflight heritage, developmental lead time, delivery schedule,and applicability to the mission.2.Camera System Descriptions:There are several different types of cameras that may be utilized for our long durationGEO spacecraft: High Fidelity Machine Vision Cameras: These are visible wavelength cameras that will beused for imaging purposes over a wide range of distances. These cameras should be capableof accepting a large set of commanding options, such as gain, gamma correction, framerate, and integration time. Theses cameras must also provide telemetry for all cameraparameters and internal sensors. The machine vision cameras will have fixed pointingpositions. Mid-Fidelity Visual Inspection Cameras: These visible wavelength cameras are meant toserve a similar function as the high fidelity machine vision cameras, but to a lesserextent. Ideally these cameras would allow for real-time commanding of camera opticalsettings (aperture, focus, etc.) and have pan/tilt mounts and zoom capabilities to aid invisual inspection of the spacecraft itself. The need for real time telemetry of cameraparameters is not as crucial for these cameras.Low Fidelity Visual Inspection Cameras: These visible wavelength cameras are meant to besmall and numerous in quantity. Placed at various strategic locations on the spacecraftthey will be used mainly by ground controllers to provide an indication of thespacecrafts immediate surroundings. They will be used for specific spacecraft tasks suchas verification of solar array deployment and other deployment related activities. Thesecameras should have little to no commanding or telemetry options. In order to decreasethe number of required cameras a pan/tilt mount could be used to maximize viewing angleand minimize operational constraints. Infra-Red (IR) Camera: At geosynchronous orbit, spacecrafts are not plagued by theapproximate 90 minute sunrise/sunset cycle experienced at Low Earth Orbit (LEO).Nevertheless, there are times when lighting conditions can be poor at GEO. In thesescenarios, lighting-independent IR cameras will be extremely useful. The IR camera shallbe used as a means to gather imagery when lighting conditions are not ideal for thevisible-light cameras. Miniaturized Cameras: NASA GSFC is especially interested in unique solutions to theminiaturization of optical cameras that will be able to withstand long duration usage atGEO. These miniaturized cameras will be required to provide high quality video at veryshort focus distances. Ideally these cameras would allow for real-time commanding ofcamera optical settings (aperture, focus, etc.) and potentially have zoom capabilities toaid in spacecraft operations. Novel concepts for miniaturized cameras that providearticulating views of the spacecraft (pan/tilt mounts, fiberscope, videoscope, borescope,etc.) are of particular interest.Additionally, there are scenarios where multiple views of the same area of the spacecraftmay be required. Methods to provide multiple views of a particular spacecraft inspectionsite are also a special area of interest to GSFC (stereo pair, orthogonal views,stitching multiple camera views together, etc.).For these miniaturized cameras, keeping the package in the smallest possible volume isimportant for both launch storage configuration and also while fully deployed in anoperational state. Packaging and miniaturization solutions that reduce the bulk of thecamera itself is another special area of interest to GSFC. For example, a camera headunit may consist of only the detector and lens assembly while the image processorelectronics could be located elsewhere on the spacecraft. This would allow the imaginingportion of the camera to retain the minimum amount of mass and volume while the bulkierelectronics and power supply could be located elsewhere on the spacecraft bus.Finally, poor lighting conditions are a known problem for these short focal length,miniaturized cameras. Packaging solutions that incorporate lighting sources into thecameras themselves are encouraged for these miniaturized cameras.3. Technical Specifications:The following general specifications are to be considered for all of the camerasmentioned above except where noted otherwise.Availability: General: GSFC is interested in flying camera systems that are already in development orhave a successful flight heritage. No significant development time is available for thisparticular application. Accessibility of inexpensive Commercial Off The Shelf (COTS)laboratory demonstration units will be seen as a plus.Camera Emulator(s): Availability required 6 months After Receipt of Order (ARO). Engineering Development Units (EDU): Availability required 12 months ARO. Flight Unit(s): Availability required 24 months ARO.Operational Lifespan: 5 to 10 years in Geosynchronous Earth Orbit.Optics: General: GSFC is interested in both fixed focal length and zoom capable cameras forall of the various camera systems listed above. All non-zoom cameras shall incorporate afixed aperture lens with a fixed focus setting. For Zoom capable cameras, both varifocaland parfocal lens designs will be considered, although a varifocal lens must incorporatea motorized focusing mechanism. Both fixed aperture and motorized aperture will beconsidered. Cameras with auto-aperture capabilities are another area of interest to GSFC. Materials: Lens materials must not be susceptible to significant radiation damage overthe operational lifespan. Radiation hardened glass may be necessary or radiationmitigation techniques must be employed. Working Range (Depth of Field): The high fidelity machine vision cameras shall have alarge depth of field ranging from 100 Km+ (infinite focus) to less than 1 meter. This canbe accomplished in a number of ways. Multiple cameras can be considered using a varietyof fixed focal lengths that yield cameras specialized for imaging at various distances(i.e. a long range vs. short range camera). Additionally, a single camera with a zoomlens can also be utilized.The low fidelity visual inspection and infrared camera lenses will all be focused atinfinity. These cameras shall have a minimum focus distance of at least 2 feet.The mid-fidelity and miniaturized cameras will be extreme short range cameras. Thenominal working distances shall be between 2 and 12 inches for the mid-fidelity camerasand between 4 inches and 2 feet for the miniaturized cameras. Field of View (FOV): For the high fidelity machine vision cameras, a wide range FOVs isdesired. A wide FOV (> 55) is desired for use at short ranges while a narrowFOV (10 - 15) is desired for long range imaging. This can be accomplishedvia multiple cameras or a single zoom capable camera.There are no specifications at this time for the FOV of the other camera systems.Environmental: Radiation: The specific radiation environment for these cameras has yet to bedetermined since the radiation will be orbit specific. GSFC has yet to choose a specificradiation model, but many models exist in the literature to provide a starting point forthe GEO environment. Design considerations must be taken to ensure the survivability ofthe optics, optical coatings, detectors, and accompanying electronics in this radiationenvironment for the orbital lifespan. GSFC is interested in radiation mitigationtechniques such as retractable camera covers and shielding to protect sensitive optics inthe event customized rad-hard lenses are not available. Survival Temperatures: Thermal limitations have yet to be determined as they willdepend on the final orbit of the spacecraft. Internal camera components are likely to setthe survivability temperatures for the cameras themselves. Temperature limits for bothsurvival and operation shall be held by internal cameras heaters if deemed necessary.Thermal blanketing may also be used depending on the final temperature limitations of thehardware. Power used for internal heaters in a cold environment must be included inworst-case maximum power numbers. Launch Loads: To be determined by launch vehicle. Standard GSFC General EnvironmentalVerification Specification (GEVS) for a generic expendable launch vehicle shall apply.4. DisclaimerIt is not NASAs intent to publicly disclose vendor proprietary information obtainedduring this solicitation. To the full extent that it is protected pursuant to the Freedomof Information Act and other laws and regulations, information identified by a respondentas Proprietary or Confidential will be kept confidential. It is emphasized that thisRFI is NOT a Request for Proposal, Quotation, or Invitation for Bid. This RFI is forinformation and planning purposes only, subject to FAR Clause 52.215-3 titledSolicitation for Information or Planning Purposes, and is NOT to be construed as acommitment by the Government to enter into a contractual agreement, nor will theGovernment pay for information submitted in response to this RFI. No solicitation exists; therefore, do not request a copy of the solicitation. If asolicitation is released it will be synopsized in FedBizOpps and on the NASA AcquisitionInternet Service (NAIS). It is the potential offerors responsibility to monitor thesesites for the release of any solicitation or synopsis. The Government reserves the rightto consider a small business or 8(a) set-aside based on responses hereto. All nontechnical questions must be submitted in writing to the primary Contracting Officer underpoints of contact. As part of its assessment of industry capabilities, the NASA-GSFC maycontact respondents to this Request for Information (RFI), if clarifications or furtherinformation is needed. Respondents will not be notified of the results of the evaluation.An ombudsman has been appointed -- See NASA Specific Note 'B'.Questions sent via email are welcomed.For technical related questions please contactMr. Ross Henry at Ross.M.Henry@nasa.gov. For other non-technical questions pleasecontact the primary Contracting Officer for this action.The solicitation and any documents related to this procurement will be available over theInternet. These documents will reside on a World Wide Web (WWW) server, which may beaccessed using a WWW browser application. The Internet site, or URL, for the NASA/GSFCBusiness Opportunities home page ishttp://prod.nais.nasa.gov/cgi-bin/eps/bizops.cgi?gr=D&pin=515. Instructions to Respondents:Respondents may submit separate responses to any number of these items. Respondents arenot required to respond with information for all camera types. NASA appreciates responsesfrom all capable and qualified sources including, but not limited to, NASA Centers,universities, university affiliated research centers, federally funded research anddevelopment centers, private or public companies, and government research laboratories.Respondents are required to include the following technical specifications for theirrespective camera systems:Summary of the camera system and how it could be used in a system/missioncontext.Mass of unit.Bounding box dimensions (length, width, height).Nominal and peak power draw.Power on in-rush current.Command, telemetry and video interface.Maximum commanding bandwidth (where applicable).Maximum telemetry bandwidth (where applicable).Maximum video bandwidth.Operational & survivability temperature ranges.Detector Type, pixel resolution, pixel size, optical format, S/N ratio, maximumfull frame rate and Region Of Interest (ROI) capabilities (where applicable).Optics description & specifications (lens effective focal length, f/#, focusdistance, FOV, DOF, geometric distortion, lens mount type).Respondents are also required to address the following programmatic items: Name of corporate point of contact, telephone number, full mailing address, and e-mailaddress. Corporate competencies and past performance experience with regard to the developmentand production of similar camera systems. Relevant flight heritage/history is extremelyimportant. Responses must have classified and proprietary information properly marked. Respondents must specify the ability to conduct functional acceptance testing of cameraunits prior to delivery. This includes both functional performance testing andenvironmental qualification tests such as thermal vacuum and vibration testing. Relevanttest plans, procedures and the results of theses tests must be provided to GSFC at thetime of the flight unit(s) delivery. Respondents must specify the ability to provide relevant camera system specificationdocuments including, but not limited to, system drawings, parts lists, electrical,optical, and software Interface Control Documents (ICDs). This documentation is neededfor parts analysis as well the development of high fidelity simulations for cameracontrol algorithm development and testing. Responses must include a Rough Order of Magnitude (ROM) cost estimate for eachindividual camera system. Respondents must specify a target delivery period of the various camera hardwaredeliverables (emulators, EDUs, flight) from the date of any potential ARO.6. How to Respond: Submit via email in PDF or Word format by 11/01/2011, 11:59 p.m. Eastern Standard Time(EST) to BOTH points of contact outlined below. Less than five (5) page executive summary, 12-point font size, one inch margins. Nolimit on supporting documentation. Format: Microsoft Word (.doc) or Portable Document Format (.pdf). Mark all responses: RFI, GEO Cameras
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