GG1320AN Digital Ring Laser Gyroscope
Overview
Gyroscopes are critical rotation sensing elements used in navigation systems (inertial navigation systems (INS), attitude and heading reference systems (AHRS) or inertial measurement units (IMUs) for manned and unmanned aircraft, spacecraft, marine vehicles and surface vehicles.In addition, gyroscopes are important elements in platform stabilization systems (i.e. antenna stabilization) and where accurate pointing and/or targeting is required.Honeywell gyro technologies include:The principle of operation of a RLG is two counter-propagating laser beams have different frequencies with the difference dependent on rotation rate. Measurement of this difference provides the rotation angle or rotation rate about the RLG's sensitive axis. Honeywell's GG1320 RLG has demonstrated capability of measuring an arc-second of rotation.
- Spinning mass mechanical gyros
- Fiber-optic gyros (FOGS)
- Micro-electro-mechanical (MEMS) gyros
- Ring laser gyros (RLG)
Specifications
Dimensions
Weight
- 1 lb. (454 grams)
Size
- Diameter 3.45 in (8.8 cm) millimetre
- Height 1.77 in (4.5 cm) millimetre
Performance Data
Operating & Non-Operating Shock
- 22 g, half sine, 11 millisecond
Non-operating Temperature Range
- -65°F to +200°F (Non-Operating) -54°C to 93.3°C
Operating Magnetic Environment
- 0.002°/hr/gauss
Angular Random Walk (ARW)
- 0.0035 deg/root-hour (typical)
Scale Factor - Corrected
- 1,164,352 ±18 pulses/rev.
Operating Temperature
- -65°F to +185°F (Operating) -54°C to 85°C
Operating Attitude
- -20,000 ft. to +80,000 ft
- -610 m to +21,336 m
Sample Frequency
- 2,000 Hz (typical use) 5,000 Hz (maximum)
Bias Stability
- 0.0035 deg/hr (typical)
Start-Up Time
- 1 second (typical)
Applications
- Manned and Unmanned Aircraft
- Marine Vehicles
- Spacecraft
- Surface Vehicles
Rate Input
- 900 deg/ sec (maximum)
Interface
- RS-422, 25 pin micro D Asynchronous, 1 MHz, 8 Bit
Latency
- 168 micro-seconds
Power
- 15 Vdc, 1.6 Watts nominal Watt
- 5 Vdc, 0.375 Watts nominal Watt
