SON_1305M224Q0264.pdf
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- Attached to
- GNSS Aided Inertial Navigation System Federal contract opportunity
- Solicitation number
- 1305M224Q0264
About this file
This document is a Statement of Need (SON) for a GNSS aided inertial navigation system required by the National Oceanic and Atmospheric Administration (NOAA) Aircraft Operations Center (AOC). The system is needed for the NOAA G550 aircraft to provide three-axis accelerometer data necessary to analyze and remove nose boom vibration velocities from scientific pressure measurements during high-altitude atmospheric research missions.
The key technical specifications for the GNSS/INS system include performance requirements for heading, pitch, roll, and angular resolution, as well as mechanical, electrical, and accelerometer requirements. The system must be small-footprint, meeting size, power, and environmental protection standards. The solicitation number is 1305M224Q0264, and the federal agency issuing the requirement is the Department of Commerce National Oceanic and Atmospheric Administration.
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Other files for this federal contract opportunity
| File | Type | Posted |
|---|---|---|
| Sol_1305M224Q0264.pdf | ||
| RFQ_1305M224Q0264.pdf |
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Text version
STATEMENT OF NEED
1305M224Q0264
PURPOSE: NOAA AOC requires a small-footprint GNSS aided inertial navigation system located inside the nose boom of the G550 aircraft. The GNSS/INS will provide three-axis accelerometer data necessary to analyze and remove nose boom vibration velocities from scientific pressure measurements.
SCOPE OR MISSION: The NOAA G550 aircraft fly high altitude atmospheric research missions and utilize varying types and quantities of scientific instrumentation.
TECHNICAL SPECIFICATIONS:
GNSS Aided INU shall meet or exceed the following criteria:
• Performance o Range (Heading/Yaw, Roll ± 180° o Range (Pitch) ± 90° o Heading (Magnetic) 2.0° RMS o Heading (INS) 0.05° to 0.1°, 1σ o Pitch/Roll (Static) 0.05° RMS o Pitch/Roll (INS) 0.015°, 1σ o Heading Mnt Misalign < 0.05°, 1σ o Pitch/Roll Mnt Misalign < 0.05°, 1σ o Angular Resolution 0.001°
• Mechanical/Electrical o Input Power 5 to 28VDC o Size No larger than 3”L x 3”W x 2”H o Package MIL-STD-810; MIL-STD-461G; DO-160G; IP 68
Rated
• Accelerometer o Range ±15 g o In-Run Bias <10ug o Noise Density (VRW) < 0.04 mg/√Hz
• Gyro o Range ±490°/s o In-Run Bias (Allan) 0.6°/hr typ.
o Noise Density (ARW) 5°/hr /√Hz
• GNSS
o Receiver Type 184 Channel o GPSL 1C/A, L2C o Galileo E1-B/C, E5b o GLONASS L10F, L20F o Beidou B1I, B2I o QZSS L1C/A, L2C o SBAS L1C/A o Time-To-First-Fix 29s o Altitude Limit 50,000 m o Velocity Limit 500 m/s
• Interface o Output Data Rate (IMU) up to 800 Hz o Output Data Rate up to 400 Hz o Primary Interface RS-422 o Auxiliary Interface RS-422 o GNSS PPS 30 ns RMS, 60 ns 99% o Input Sync-in o Output Sync-out o Message Protocols ASCII, NMEA-0183, Binary, ARINC 429
DELIVERY SCHEDULE: Within 90 days ARO.
SPECIAL REQUIREMENTS: The device will be installed on an aircraft and located in an un-pressurized, harsh, environment. Selection will include close attention to MIL spec ratings, technical and environmental specifications.
TECHNICAL POINT OF CONTACT: John Hill, john.w.hill@noaa.gov, 813-473-2216 mailto:john.w.hill@noaa.gov
File details come from the government source that posted it. Updated .