Civilian GPS Advanced Antenna Matrix 07Nov2024.xlsx
XLSX spreadsheet 43 KB Posted
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About this file
This is an Excel spreadsheet template attached to a Request for Information (RFI) from NAWCAD and the FAA seeking information about GPS/GNSS multi-element antenna technologies with anti-jamming and anti-spoofing capabilities for civilian aircraft applications. The template requires vendors to provide detailed technical specifications for their antenna systems, including physical characteristics (size, weight, power requirements), signal capabilities (L1 C/A, L1C, WAAS, SBAS, L2, L5), interference management features, and spoofing detection capabilities.
The RFI responses are due by May 26, 2025, at 5:00 PM ET, with questions accepted through April 25, 2025. The document includes one sample entry showing a GPS anti-jamming system priced at $50,000 per unit for quantities over 40 units, with a 6-month lead time. The primary focus is on Transport and Business Jet aircraft applications, with NAWCAD planning to conduct evaluation testing of potential systems to develop updated Minimum Operational Performance Standards (MOPS) for GPS/GNSS antennas and cockpit displays. Interested vendors can submit responses through techport.center/faa-gps-antenna-rfi/.
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Other files
| File | Type | Posted |
|---|---|---|
| FAA RFI 2.19.25.jpg | JPG image | |
| FAA GPS Antenna Request for Information 1-15-2025 V1.pdf | ||
| FAA Antenna Roadmap and Questionnaire 16Feb2025.pdf |
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Cover Sheet
| NAWCAD- FAA GPS Antenna Request for Information (RFI) on |
| GNSS Multi-Element Antenna for Civil Applications |
| NAVAIR Public Release 2025-0037. Distribution Statement A – “Approved for public release; distribution is unlimited.” |
System Nomenclature
| System Nomenclature | ||||||||||||||
| Vendor Info Last Mod | System Name | Acronym | Manufacturer | Description of customer focus or application focus | Technical Readiness Level (TRL) | Year TRL 6 | Hardware available for test in 3 months | Hardware availability for Test (CY) | Current Customers | DO-178/254 Certified | DO-373 Compliant | Cost in QTY | Vendor POC, Email and Phone # | Lead Time (ARO) |
| 8/1/24 | XXX-XXX-1 | GPS AJ Technology | Vendor #1 | Air/Land/Sea | 9 | N/A | Available | 2024 | XYZ platform | N | N | $50,000 per unit for 40+ | John Smoth (abc) def-ghij | 6 months |
list each system or technology on a separate line
| Notes or brief description of unique system attributes |
| ITARrestricted, FRPA with electronics that can perform nulling and beam streering currentsly and spoofinng detection in the future. |
Antenna
| Antenna | |||||||||||
| Antenna Type attached to the system | Integrated or Federated System (antenna and electronics combined or separate) | Antenna Size L x W x H (inches) | Antenna Weight (lbs.) | Antenna Power- Volts, Amps | Antenna Power- Watts | Antenna Size L x W x H (inches) | L1 C/A, L1C, WAAS, SBAS | L2 | L5 | Signal Bandwdith | Passive or Active |
| FRPA | Federated | 3"(dia) x 2"H | 1 | 0 | 0W | 14In dia x 2in | Y | Y | N | 24Mhz | Passive |
Electronics
| Electronics | |||||
| Electronics Weight (lbs.) | Electronics Power- Volts, Amps | Electronics Power- Watts | Heatsink Size L x W x H (inches)- Additional required | Amplified Gain RF (dB) output | Interface types |
| 10 | 10-33 VDC | 25 W | N/A | 45 | RF/Power/RS-422 |
Interference
| Interference | ||||||||
| Where does the Anti-Jam HW/SW reside? | Simultanoues Nulling (L1 C/A, L1C, WAAS, SBAS, L5)? | # of Antenna Elements | Nulling Performance (dBm or dBw) vs a FRPA | Direction Finding | Jamming Detection | Jamming Situational Awareness Data Bus Interface | RF Disconnect | Null Depth dBm |
| Antenna Electronics | L1L2 | 1 | 55 dBm | N | Y | RS-422 | SMA | -33 |
Spoofing
| Spoofing, Resilency & Software Assurance Measures (RSAM) | |||||||||
| Where does the Spoofing HW/SW reside? | Spoofing Detection Capable impliments Date(L1 C/A, L1C, WAAS, SBAS Corrections/L5) (CY) | Spoofing Situational Awareness Data Bus Interface | GPS data message manipulation Detection | Repeater (meaconing) detection | SBAS Spoofing Detection | Simulated SV Detection | Spoof Mitigation | RF Disconnect | Ephemeris and Almanac Integrity Checks |
| Antenna Electronics | 2026 | N | N | N | N | N | N | N | N |
Beamforming
| Beamforming | |||||
| Where does the Beamforming HW/SW reside? | Beamforming (gain and beamwidth) | # of beams | External or Internal IMU System input of Roll, Heading, Pitch | RF Adaptation frequency | Self Antenna Manifold Calibrations |
| Anntenna electronics | 8 dBm, 15 degrees | 8 L1/8 L2 | External input | N | N |
TRL Definitions
| SYSTEM/HW TRL | Description |
| 1. Basic principles observed & reported. | Lowest level of technology readiness. Scientific research begins to be translated into applied R&D. Examples might include paper studies of a technology's basic properties. |
| 2. Technology concept and/or application formulated. | Invention begins. Once basic principles are observed, practical applications can be invented. Applications are speculative & there may be no proof or detailed analysis to support the assumptions. Examples are limited to analytic studies. |
| 3. Analytical & experimental critical function and/or characteristic proof of concept. | Active R&D is initiated. This includes analytical studies & lab studies to physically validate analytical predictions of separate elements of the technology. Examples include components that are not yet integrated or representative. |
| 4. Component and/or breadboard validation in lab environment. | Basic technological components are integrated to establish that they will work together. This is relatively "low fidelity" compared to the eventual system. Examples include integration of "ad hoc" HW in the lab. |
| 5. Component and/or breadboard validation in relevant environment. | Fidelity of breadboard technology increases significantly. The basic technological components are integrated with reasonably realistic supporting elements so it can be tested in a simulated environment. Examples include "high fidelity" lab integration of components. |
| 6. System/subsystem model or prototype demo in a relevant environment. | Representative model or prototype system, which is well beyond that of TRL 5, is tested in a relevant environment. Represents a major step up in a technology's demonstrated readiness. Examples include testing a prototype in a high-fidelity lab environment or in simulated operational environment. |
| 7. System prototype demo in an operational environment. | Prototype near, or at, planned operational system. Represents a major step up from TRL 6, requiring demo of an actual system prototype in an operational environment such as an A/C, vehicle, or space. Examples include testing the prototype in a test bed A/C. |
| 8. Actual system completed & qualified through test & demo. | Technology has been proven to work in its final form & under expected conditions. In almost all cases, this TRL represents the end of true system development. Examples include developmental T&E of the system in its intended weapon system to determine if it meets design specs. |
| 9. Actual system proven through successful mission operations. | Actual application of the technology in its final form & under mission conditions, such as those encountered in operational T&E. Examples include using the system under operational mission conditions. |
| Term | Definition |
| Breadboard | Integrated components that provide a representation of a system/subsystem and that can be used to determine concept feasibility and to develop technical data. Typically configured for laboratory use to demonstrate the technical principles of immediate interest. May resemble final system/subsystem in function only. |
| High | |
| Fidelity | Addresses form, fit and function. A high-fidelity laboratory environment would involve testing with equipment that can simulate and validate all system specifications within a laboratory setting. |
| Low | |
| Fidelity | A representative of the component or system that has limited ability to provide anything but first-order information about the end item product. Low-fidelity assessments are used to provide trend analysis. |
| Model | A functional form of a system generally reduced in scale, near or at operational specification. Models will be sufficiently hardened to allow demonstration of the technical and operational capabilities required of the final system. |
| Operational Environment | Environment that addresses all the operational requirements and specifications required of the final system to include platform/packaging. |
| Prototype | A physical or virtual model used to evaluate the technical or manufacturing feasibility or military utility of a particular technology or process, concept, end item, or system. |
| Relevant | |
| Environment | Testing environment that simulates the key aspects of the operational environment. |
| Simulated | |
| Operational Environment | Either (1) a real environment that can simulate all the operational requirements and specifications required of the final system or (2) a simulated environment that allows for testing of a virtual prototype. Used in either case to determine whether a developmental system meets the operational requirements and specifications of the final system. |
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