NASA Solicitation: Electromagnetic Radiation-Based Ranging Systems Suitable for Long-Term Geosynchronous Earth Orbit
Synopsis – May 08, 2012
General Information
Solicitation Number: NNG12FA84-RFI
Posted Date: May 08, 2012
FedBizOpps Posted Date: May 08, 2012
Recovery and Reinvestment Act Action: No
Original Response Date: Jun 06, 2012
Current Response Date: Jun 06, 2012
Classification Code: A — Research and Development
NAICS Code: 541990
Contracting Office Address
NASA/Goddard Space Flight Center, Code 210.S, Greenbelt, MD 20771
Description
The National Aeronautics and Space Administration (NASA) is soliciting information to conduct market research to improve its understanding of the current state-of-the-art in commercially-available space-rated ranging systems. NASA is seeking broad information about systems previously flown, systems currently in development–including for other non-NASA missions–and future technologies that are relevant to long-duration spacecraft missions 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 only and is not intended to bind the Government.
1. Background and Study Plan:
NASA’s Satellite Servicing Capabilities Office (SSCO) is currently studying the feasibility, practicality, and cost of operating a long-duration autonomous rendezvous, proximity operations, and capture mission in GSO. One particular area of interest is the availability of space-rated electromagnetic radiation-based relative ranging systems (laser range finders, lidars, and radars) suitable for the GSO environment. Early results of our study show that availability of direct range measurements between a chaser and target spacecraft is critical to mission success.
Through this request for information (RFI), SSCO wants to survey the current state-of-the-art of available ranging systems and seeks relevant and interested industry partners to develop an appropriate system. At this time, GSFC does not have a preferred ranging technique–laser range finder, flash or scanning lidar, radar, etc.–nor preferred output measurement type–calibrated point clouds or voxels, range/bearing estimate, or six degree relative position and orientation. The system’s performance, Technology Readiness Level (TRL), spaceflight heritage, developmental lead-time, cost, delivery schedule, and applicability 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, without the use of active or passive targeting aides on the target vehicle. Most missions requiring rendezvous and proximity operations (RPO) completed in recent years have relied on 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 that some ranging devices used for these missions can also be used non-cooperatively. Furthermore, some RPO demonstrations have been recently completed where non-cooperative devices and algorithms have been used. Information on these ranging systems is of particular interest to GSFC.
2. Ranging System Descriptions:
There are several different types of direct ranging systems that could be utilized for a geosynchronous satellite-servicing vehicle.
– Laser Range Finder: A system consisting of a photon source (such as a laser), a photon detector, and a timing circuit. The distance to a target is derived from the time of flight (TOF) between when a photon (in many cases, multiple photons) is emitted from the source and when the detector senses the same photon(s). The TOF is divided by the speed of light to produce measured range. These types of systems produce a range measurement only. Most often, transmit and receive optics are used to focus the outgoing and incoming photons, respectively.
– Flash Lidar: A system consisting of a wide-angle photon source and a one- or two-dimensional focal plane array of multiple photon detectors. These systems typically operate under the same TOF principle of a laser range finder, but instead give a one- or two-dimensional range image, where each range measurement is acquired simultaneously. Some flash lidar systems determine range though phase shift detection of a modulated continuous 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, and the range image is recorded on the detector array.
– Scanning Lidar: These systems are similar to a laser range finder except the direction of the laser beam can be steered with respect to a stationary measurement frame. The scanning 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 systems provide 3D measurements: range, azimuth, and elevation. Each range and bearing measurement must be tagged individually with a time of measurement. Scanning lidars can measure range using multiple techniques, e.g., through TOF principles or triangulation geometry.
– Radio/Microwave Radar: These systems are similar to flash lidar systems except the laser source and detector are replaced by transmit and receive antennas and electronics. These radar systems offer many ways to detect range such as using the time of flight principle or through detecting phase shifts in a modulated continuous wave signal. Many such systems 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 could output one of many data output types.
– Range Only: This measurement is self-explanatory. The ranging device will provide a single (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 the FOV, a notification is sent to the user.
– Range/Bearing triplets: This measurement adds directional information to the basic range measurement. The assumption here is that the device is giving one range and bearing measurement for each distinct object in the effective FOV (or, on simpler systems, one measurement for all objects). Range and bearing is only one of many parameterizations possible for LOS information.
– Voxel Sets: This type is also a three-dimensional measurement but is distinctly different from the range/bearing measurement given above. Here, multiple measurements for a single target are given instead of just a single estimate. It is assumed that each voxel triplet is measured at different times and no constraint is placed on the structure or spacing of the bearing portion of the measurement.
– Point Clouds: Closely related to a voxel group, a point cloud also provides multiple three-dimensional measurements for a single target but it is assumed that all measurements are taken simultaneously. Most of the time, the spacing of the bearing portion of the measurement is fixed and rectilinear.
– 6DOF Pose: This measurement type provides a full estimate of a target’s position and attitude relative to the sensor. Obviously this is the most processed form of measurement and the most directly useable to a spacecraft navigation system. Most systems providing this 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 systems mentioned above except where noted otherwise.
– Availability: GSFC is interested in flying ranging systems that are already in development or have a successful flight heritage, however, we expect some development will be required to fill gaps between our mission requirements and the as-built specifications of off-the-shelf units.
– Development/Flight Units: -Emulator(s): Input/output emulators are required. Such emulators shall mimic the operation of flight software as well as mimic the flight hardware command and telemetry interfaces.
-Engineering Development Unit(EDU): A high fidelity EDU of the ranging system is required. Such an EDU shall use electronic parts of similar form, fit, and function as the flight unit. The embedded software in the EDU shall be flight-like.
-Engineering Test Unit(ETU): New hardware developed under this effort shall require an ETU to verify survivability in the space environment. Such an ETU shall use flight-qualified electrical and mechanical parts in all areas. Any electrical, electronic, and electromechanical (EEE) parts used would be qualified for flight but flight screening is optional.
-Flight Unit(s): Final version of the hardware that will be used in the space environment. 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 the literature, such as the AE-9/AP-9 radiation specification model, to provide a starting point 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 mission lifespan. Other potential client orbits are also being investigated so respondents should report on their system’s applicability in other altitude regimes as well.
– Survival Temperatures: Thermal limitations will depend directly on the inclination of the spacecraft orbit and structure surrounding the ranging system. Internal components are likely to set the survivability temperatures for the units themselves. If certain components within the ranging system are temperature sensitive, the system should regulate those temperatures through heaters or coolers. Power used for such devices must be included in worst-case maximum power numbers. Thermal blanketing may also be used depending on the final temperature limitations of the hardware.
– Launch Loads: To be determined by launch vehicle. Standard GSFC General Environmental Verification Specification (GEVS) for a generic expendable launch vehicle shall apply.
5. Disclaimer:
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. The Government shall not be held liable for any damages incurred if proprietary information is not properly identified.
It is emphasized that this RFI is NOT a Request for Proposal, Quotation, or Invitation for Bid. This RFI is for information and planning purposes only and is subject to FAR Clause 52.215-3 entitled “Solicitation for Information or Planning Purposes”. This RFI is NOT to be construed as a commitment by the Government to enter into a contractual agreement, 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 a solicitation is released it will be synopsized in FedBizOpps and on the NASA Acquisition Internet Service. It is the potential offeror’s responsibility to monitor these sites for the release of any solicitation or synopsis. The Government reserves the right to consider a small business or 8(a) set-aside based on responses hereto. All questions must be submitted in writing via e-mail to both points of contact as outlined under the Point of Contact section. As part of its assessment of industry capabilities, NASA GSFC may contact respondents to this RFI, if clarifications or further information is needed. Respondents will not be notified of the results of the evaluation. All submissions will be retained by the Government and will not be returned.
The solicitation and any documents related to this procurement will be available over the Internet. These documents will reside on a World Wide Web (WWW) server, which may be accessed using a WWW browser application. The Internet site, or URL, for the NASA/GSFC Business Opportunities home page is http://prod.nais.nasa.gov/cgi-bin/eps/bizops.cgi?gr=D&pin=51
6. Instructions to Respondents:
Respondents may submit separate responses to any number of these items. Respondents are not required to respond with information for all ranging system types. NASA appreciates responses from all capable and qualified sources including, but not limited to, NASA Centers, universities, university affiliated research centers, federally funded research and development centers, private or public companies, and government research laboratories.
Respondents are required to include the following technical specifications for their respective ranging systems:
– Summary of the ranging system and how it could be used in a system/mission context.
– Mass of unit
– Bounding box dimensions (length, width, height)
– Nominal and peak power draw (with and without thermal self-regulation)
– Power on in-rush current
– Command, telemetry and raw output (where applicable) interface
– Maximum commanding bandwidth (where applicable)
– Maximum telemetry bandwidth (where applicable)
– Maximum raw output bandwidth (where applicable)
– Time synchronization and timestamp capabilities
– Data latency
– Operational and survivability temperature ranges
– Emission source. Include power output, emission spread (beam width), wavelength, and any human safety concerns (eye safety, radiation safety, etc.)
– Detector type: -Array-based systems: pixel resolution, pixel size, S/N ratio, and maximum full frame rate -Scanning-based systems: S/N ratio, sample rate
– Range (time) accuracy as a function of range, temperature, etc
– Bearing accuracy (where applicable)
– Pose accuracy (where applicable)
– Other data output types where applicable
– Availability of current flight or prototype units for near-term laboratory testing
Respondents are also required to address the following programmatic items:
– Name of corporate point of contact, telephone number, full mailing address, and e-mail address.
– Corporate competencies and past performance experience with regard to the development and production of similar ranging systems. Relevant flight heritage within the organization and individual component flight history is extremely relevant.
– Business size standard: large or small. If small business state whether small disadvantaged, 8(a), HUBZone, Service Disabled Veteran Owned Small Business (SD-VOSB), Veteran Owned Small Business (VOSB) and/or Women-Owned
– Responses must have classified and proprietary information properly marked.
– Respondents must specify the ability to conduct functional acceptance testing of units prior to delivery. This includes both functional performance testing and environmental qualification 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 the flight unit(s) delivery.
– Respondents must specify the ability to provide relevant system specification documents including, but not limited to, system drawings, parts lists, electrical, optical, and software Interface Control Documents (ICDs). This documentation is needed for parts analysis as well the development of high fidelity synthetic image simulations.
– Responses must include a Rough Order of Magnitude (ROM) cost estimate for each individual system. Please include estimates on any potential non-recurring expenses anticipated 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. No limit on supporting documentation.
– Format: Microsoft Word (.doc) or Portable Document Format (.pdf)
– Mark all responses: NNG12FA84-RFI, GSO Ranging Systems.
Point of Contact
Name: Claudia Canales
Title: Contracting Officer
Phone: 301-286-5990
Fax: 301-286-1670
Email: Claudia.Canales-1@nasa.gov
Name: Dean S Patterson
Title: Procurement Manager
Phone: 301-286-8085
Fax: 301-286-1670
Email: Dean.S.Patterson@nasa.gov
