SATPC0031845 Tab 04 SOW.pdf
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- Solicitation number
- 80NSSC23840228Q
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This document outlines specifications for procuring inertial navigation system components for a NASA research project. It requests two high-grade inertial measurement units with fiber optic gyroscopes having over 490 degrees per second dynamic range, 0.05 degrees per hour bias instability, and 0.005 degrees per root hertz angular random walk, as well as microelectrical mechanical accelerometers with 10g dynamic range, 0.1 milligrams bias instability, and 0.018 meters per second root hertz velocity random walk. Dimensions should be 180 by 150 by 137 millimeters. It also seeks global navigation satellite system receivers and antennas compatible with the inertial measurement units. Suppliers must deliver the components prior to the end of August 2023 or provide a written explanation and estimated delivery timeframe by the end of September 2023.
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Statement of Work:
June 12, 2023
Compiled by Michael Zanetti, MSFC ST13
Title:
Inertial Navigation System (INS) Components and Specifications for Procurement by NASA Marshall Space Flight Center.
1. Scope/Purpose
Procurement of various Inertial Measurement Units and position receiver devices for drop-in replacement of existing hardware on the Kinematic Navigation and Cartography Knapsack (KNaCK) scientific research and development test article instrument.
Devices will be to determine, with high accuracy, the orientation and relative position of the KNaCK instrument sensor platform in space and time.
2. Operational/Service Requirements
Supplier will provide devices with the mechanical requirements specified below.
Supplier will deliver these devices in a timely manner, as early as possible, but prior to the end of August 2023, or provide written explanation and estimate for delivery time frame prior to end September 2023.
3. Specifications
Inertial Measurement Orientation and Position Information (anticipate 4 different devices: high grade IMU, GNSS/INS coupling for high-grade IMU, and a separate combined IMU/GNSS unit, and antennas.
Associated cabling specific for the project will also be procured, but not included here when not proprietary).
• Technology for high-grade inertial measurement unit (IMU): Quantity 2 o Fiber optic gyroscopes with
>490°/s dynamic range 0.05°/hr bias instability Angular random walk of 0.005 °/√hz o Microelectrical mechanical accelerometers (MEMS) 10g dynamic range 0.1mg bias instability velocity random walk 0.018 °/√hz o Dimensions: 180 x 150 x 137 mm o Weight: <5.1 kg o Power +10 - +42 VDC o Cabling included
• Technology for GNSS/INS coupling: Quantity 2 o Small, low-power GNSS enclosure o SPAN GNSS+INS capability with configurable profiles o GPS consellations L1 C/A, L2C, L5 o Power: +9 - +36 VDC o Proprietary cabling for signal input/output (Quantity 4) o RS232 in/out communication port o IP67 weather protection o Dimensions:<150 x 130 x 60 mm o Weight: <550 g
• Technology for Combined IMU and GNSS/INS system: Quantity 1 o Device capable of simultaneous GPS and IMU data collection in one housing o GPS consellations L1 C/A, L2C, L5 o Appropriate Cabling o Integrated MEMS class IMU
Gyro Dynamic range: 400°/s Gyro Bias instability: 0.45°/hr Accelerometer dynamic range: 20g Accelerometer bias instability 0.075mg Dimensions: 90x60x60 mm Power: +9 - +32 VDC Antenna SMA connection
• Antenna for receiving GPS signal: Quantity 3 o GPS constellations L1, L2, L5, Capability for other signals from Glonass, Galileo.
o noise figure (typical) < 2.0dB o Weight: <~550g o Connection: TNC female o Dimensions: <180mm D x 60 mm H o Mounting: 5/8” -11 thread mount o Weather resistance: IP69K o Appropriate cabling
File details come from the government source that posted it. Updated .