SOURCES SOUGHT
A -- ELECTROMAGNETIC RADIATION-BASED RANGING SYSTEMS SUITABLE FOR LONG-TERMGEOSYNCHRONOUS EARTH ORBIT
- Notice Date
- 5/8/2012
- 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
- NNG12FA84-RFI
- Response Due
- 6/6/2012
- Archive Date
- 5/8/2013
- Point of Contact
- Claudia Canales, Contracting Officer, Phone 301-286-5990, Fax 301-286-1670, Email Claudia.Canales-1@nasa.gov - Dean S Patterson, Procurement Manager, Phone 301-286-8085, Fax 301-286-1670, Email Dean.S.Patterson@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 informationto conduct market research to improve its understanding of the current state-of-the-artin commercially-available space-rated ranging systems. NASA is seeking broad informationabout systems previously flown, systems currently in developmentincluding for othernon-NASA missionsand future technologies that are relevant to long-duration spacecraftmissions designed to operate in both low-Earth orbit (LEO) and geosynchronous orbit(GSO).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:NASAs Satellite Servicing Capabilities Office (SSCO) is currently studying thefeasibility, practicality, and cost of operating a long-duration autonomous rendezvous,proximity operations, and capture mission in GSO. One particular area of interest is theavailability of space-rated electromagnetic radiation-based relative ranging systems(laser range finders, lidars, and radars) suitable for the GSO environment. Early resultsof our study show that availability of direct range measurements between a chaser andtarget spacecraft is critical to mission success. Through this request for information (RFI), SSCO wants to survey the currentstate-of-the-art of available ranging systems and seeks relevant and interested industrypartners to develop an appropriate system. At this time, GSFC does not have a preferredranging techniquelaser range finder, flash or scanning lidar, radar, etc.nor preferredoutput measurement typecalibrated point clouds or voxels, range/bearing estimate, or sixdegree relative position and orientation. The systems performance, Technology ReadinessLevel (TRL), spaceflight heritage, developmental lead-time, cost, delivery schedule, andapplicability to the mission are the most important specifications at this point in time.Of sole interest are ranging systems that can be used non-cooperatively, that is, withoutthe use of active or passive targeting aides on the target vehicle. Most missionsrequiring rendezvous and proximity operations (RPO) completed in recent years have reliedon target aides like laser retro-reflectors or a bi-directional communications link.Shuttle, ATV, and HTV rendezvous to ISS all fit this cooperative paradigm. We expect thatsome ranging devices used for these missions can also be used non-cooperatively.Furthermore, some RPO demonstrations have been recently completed where non-cooperativedevices and algorithms have been used. Information on these ranging systems is ofparticular interest to GSFC. 2. Ranging System Descriptions:There are several different types of direct ranging systems that could be utilized for ageosynchronous satellite-servicing vehicle.Laser Range Finder: A system consisting of a photon source (such as a laser), a photondetector, and a timing circuit. The distance to a target is derived from the time offlight (TOF) between when a photon (in many cases, multiple photons) is emitted from thesource and when the detector senses the same photon(s). The TOF is divided by the speedof light to produce measured range. These types of systems produce a range measurementonly. Most often, transmit and receive optics are used to focus the outgoing and incomingphotons, respectively. Flash Lidar: A system consisting of a wide-angle photon source and a one- ortwo-dimensional focal plane array of multiple photon detectors. These systems typicallyoperate under the same TOF principle of a laser range finder, but instead give a one- ortwo-dimensional range image, where each range measurement is acquired simultaneously.Some flash lidar systems determine range though phase shift detection of a modulatedcontinuous wave signal. The focal plane array may also return a laser intensity image.The operational concept is similar to a flash camera: the laser flashes the scene, andthe range image is recorded on the detector array.Scanning Lidar: These systems are similar to a laser range finder except the directionof the laser beam can be steered with respect to a stationary measurement frame. Thescanning mechanism can be a pan ilt mechanism, a pair of high-speed steering mirrors,an electronically steered beam, etc. Because of the scanning capability, these systemsprovide 3D measurements: range, azimuth, and elevation. Each range and bearingmeasurement must be tagged individually with a time of measurement. Scanning lidars canmeasure range using multiple techniques, e.g., through TOF principles or triangulationgeometry. Radio/Microwave Radar: These systems are similar to flash lidar systems except the lasersource and detector are replaced by transmit and receive antennas and electronics. Theseradar systems offer many ways to detect range such as using the time of flight principleor through detecting phase shifts in a modulated continuous wave signal. Many suchsystems also provide a range-rate measurement. Some systems can provide line of sight (LOS) information through gimbaled antennae or phased-array antenna systems. 3. Measurement Types:In addition to the numerous ranging technologies listed above, a ranging system couldoutput one of many data output types. Range Only: This measurement is self-explanatory. The ranging device will provide asingle (or multiple) range measurement for all objects in the effective field of view(FOV) of the system. When the system times out, indicating that no objects are in theFOV, a notification is sent to the user.Range/Bearing triplets: This measurement adds directional information to the basic rangemeasurement. The assumption here is that the device is giving one range and bearingmeasurement for each distinct object in the effective FOV (or, on simpler systems, onemeasurement for all objects). Range and bearing is only one of many parameterizationspossible for LOS information.Voxel Sets: This type is also a three-dimensional measurement but is distinctlydifferent from the range/bearing measurement given above. Here, multiple measurements fora single target are given instead of just a single estimate. It is assumed that eachvoxel triplet is measured at different times and no constraint is placed on the structureor spacing of the bearing portion of the measurement.Point Clouds: Closely related to a voxel group, a point cloud also provides multiplethree-dimensional measurements for a single target but it is assumed that allmeasurements are taken simultaneously. Most of the time, the spacing of the bearingportion of the measurement is fixed and rectilinear. 6DOF Pose: This measurement type provides a full estimate of a targets position andattitude relative to the sensor. Obviously this is the most processed form of measurementand the most directly useable to a spacecraft navigation system. Most systems providingthis type of measurement require information on the target vehicle. 4. General Specifications:The following general specifications are to be considered for all of the ranging systemsmentioned above except where noted otherwise.Availability: GSFC is interested in flying ranging systems that are already indevelopment or have a successful flight heritage, however, we expect some developmentwill be required to fill gaps between our mission requirements and the as-builtspecifications of off-the-shelf units. Development/Flight Units: -Emulator(s): Input/output emulators are required. Suchemulators shall mimic theoperation of flight software as well as mimic the flight hardware command and telemetryinterfaces. -Engineering Development Unit(EDU): A high fidelity EDU of the ranging system isrequired. Such an EDU shall use electronic parts of similar form, fit, and function asthe flight unit. The embedded software in the EDU shall be flight-like.-Engineering Test Unit(ETU): New hardware developed under this effort shallrequire an ETU to verify survivability in the space environment. Such an ETU shall useflight-qualified electrical and mechanical parts in all areas. Any electrical,electronic, and electromechanical (EEE) parts used would be qualified for flight butflight screening is optional.-Flight Unit(s): Final version of the hardware that will be used in the spaceenvironment. All parts, materials, and processes would be flight qualified. Operational Lifespan: 5 years. Radiation: GSFC has not chosen a specific radiation model, but many models exist in theliterature, such as the AE-9/AP-9 radiation specification model, to provide a startingpoint for the GSO environment. Respondents should assume an inclination of +/-7 degrees.System designers should take steps to ensure the survivability of the optics, detectors,lasers and accompanying electronics in a typical radiation environment for the missionlifespan. Other potential client orbits are also being investigated so respondents shouldreport on their systems applicability in other altitude regimes as well.Survival Temperatures: Thermal limitations will depend directly on the inclination ofthe spacecraft orbit and structure surrounding the ranging system. Internal componentsare likely to set the survivability temperatures for the units themselves. If certaincomponents within the ranging system are temperature sensitive, the system shouldregulate those temperatures through heaters or coolers. Power used for such devices mustbe included in worst-case maximum power numbers. Thermal blanketing may also be useddepending on the final temperature limitations of the hardware. Launch Loads: To be determined by launch vehicle. Standard GSFC General EnvironmentalVerification Specification (GEVS) for a generic expendable launch vehicle shall apply.5. Disclaimer:It 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. The Government shall not beheld liable for any damages incurred if proprietary information is not properlyidentified. It is emphasized that this RFI is NOT a Request for Proposal, Quotation, or Invitationfor Bid. This RFI is for information and planning purposes only and is subject to FARClause 52.215-3 entitled Solicitation for Information or Planning Purposes. This RFI isNOT to be construed as a commitment by the Government to enter into a contractualagreement, nor will the Government 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. It is the potential offerors responsibility to monitor these sites forthe release of any solicitation or synopsis. The Government reserves the right toconsider a small business or 8(a) set-aside based on responses hereto. All questions mustbe submitted in writing via e-mail to both points of contact as outlined under the Pointof Contact section. As part of its assessment of industry capabilities, NASA GSFC maycontact respondents to this RFI, if clarifications or further information is needed.Respondents will not be notified of the results of the evaluation. All submissions willbe retained by the Government and will not be returned.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=516. Instructions to Respondents:Respondents may submit separate responses to any number of these items. Respondents arenot required to respond with information for all ranging system types. NASA appreciatesresponses from all capable and qualified sources including, but not limited to, NASACenters, universities, university affiliated research centers, federally funded researchand development centers, private or public companies, and government researchlaboratories.Respondents are required to include the following technical specifications for theirrespective ranging systems:Summary of the ranging system and how it could be used in a system/mission context.Mass of unitBounding box dimensions (length, width, height)Nominal and peak power draw (with and without thermal self-regulation)Power on in-rush currentCommand, telemetry and raw output (where applicable) interfaceMaximum commanding bandwidth (where applicable)Maximum telemetry bandwidth (where applicable)Maximum raw output bandwidth (where applicable)Time synchronization and timestamp capabilitiesData latencyOperational and survivability temperature rangesEmission source. Include power output, emission spread (beam width), wavelength, and anyhuman safety concerns (eye safety, radiation safety, etc.)Detector type:-Array-based systems: pixel resolution, pixel size, S/N ratio, and maximum fullframe rate-Scanning-based systems: S/N ratio, sample rateRange (time) accuracy as a function of range, temperature, etcBearing accuracy (where applicable)Pose accuracy (where applicable)Other data output types where applicableAvailability of current flight or prototype units for near-term laboratory testingRespondents 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 ranging systems. Relevant flight heritage within theorganization and individual component flight history is extremely relevant.Business size standard: large or small. If small business state whether smalldisadvantaged, 8(a), HUBZone, Service Disabled Veteran Owned Small Business (SD-VOSB),Veteran Owned Small Business (VOSB) and/or Women-OwnedResponses must have classified and proprietary information properly marked.Respondents must specify the ability to conduct functional acceptance testing of unitsprior to delivery. This includes both functional performance testing and environmentalqualification tests such as thermal vacuum and vibration testing. Relevant test plans,procedures, and the results of theses tests must be provided to GSFC at the time of theflight unit(s) delivery.Respondents must specify the ability to provide relevant system specification documentsincluding, but not limited to, system drawings, parts lists, electrical, optical, andsoftware Interface Control Documents (ICDs). This documentation is needed for partsanalysis as well the development of high fidelity synthetic image simulations.Responses must include a Rough Order of Magnitude (ROM) cost estimate for eachindividual system. Please include estimates on any potential non-recurring expensesanticipated for the requirements listed.Respondents must specify a target delivery date of the various hardware deliverables(emulators, EDUs, flight) from the date of any potential contract award.7. How to Respond:Submit by June 6th 2012, 11:59 p.m. Eastern Daylight Time(EDT)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: NNG12FA84-RFI, GSO Ranging Systems.
- Web Link
-
FBO.gov Permalink
(https://www.fbo.gov/spg/NASA/GSFC/OPDC20220/NNG12FA84-RFI/listing.html)
- Record
- SN02741611-W 20120510/120508234659-c92e36f940070327072e7cf3e0d21a02 (fbodaily.com)
- Source
-
FedBizOpps Link to This Notice
(may not be valid after Archive Date)
| FSG Index | This Issue's Index | Today's FBO Daily Index Page |