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Ring Laser Gyroscope Strapdown Inertial Navigation System
JIO-D50A Ring Laser Gyroscope Strapdown Inertial Navigation System is an inertial navigation system based on ring laser gyroscope and quartz flexible accelerometer. Can be combined with altimeter, GNSS, airspeed meter and other auxiliary equipment, can provide air carrier, ground carrier and other navigation information, such as speed, position and attitude.
Model:JIO-D50A
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Product Description
D50A series of inertial navigation systems can be widely used in tanks, all kinds of armored vehicles, self-propelled artillery, rockets, all kinds of unmanned aerial vehicles, aircraft, ships, automobiles, high-speed rail, unmanned vehicles, mobile satellite communication systems, drilling and other carrying platforms. Flight control, attitude stabilization, weapon stabilization platform, positioning and positioning, etc.
Ring Laser Gyroscope Strapdown Inertial Navigation System Technical features
Cost-effective ring laser gyro and quartz accelerometer
Optional static or moving base self-alignment
Error parameters calibration and compensation in full temperature range
Optional diverse input interfaces for GNSS/Odometer/DVL
Configurable navigation modes
Excellent environmental suitability
Military standards
Optional static or moving base self-alignment
Error parameters calibration and compensation in full temperature range
Optional diverse input interfaces for GNSS/Odometer/DVL
Configurable navigation modes
Excellent environmental suitability
Military standards
Typical application scenarios
Sea vehicle navigation
Under-water vehicle navigation and positioning
Positioning and north-finding for land vehicle
Stabilization and control for moving carrier
Attitude measurement for demanding applications
Under-water vehicle navigation and positioning
Positioning and north-finding for land vehicle
Stabilization and control for moving carrier
Attitude measurement for demanding applications
Main functions of the system
It has the function of outputting information such as carrier position, heading, attitude angle, angular rate and speed in real time;
It has working modes such as pure inertial navigation and INS/GNSS (including Beidou) integrated navigation;
Possess the function of receiving satellite navigation information provided by external time system frequency standard equipment;
It has the function of ground self-alignment and supports the function of air alignment;
It has functions such as power-on self-test, periodic self-test, status report, installation error compensation, and non-volatile storage.
It has working modes such as pure inertial navigation and INS/GNSS (including Beidou) integrated navigation;
Possess the function of receiving satellite navigation information provided by external time system frequency standard equipment;
It has the function of ground self-alignment and supports the function of air alignment;
It has functions such as power-on self-test, periodic self-test, status report, installation error compensation, and non-volatile storage.
System composition and dimensions
The whole system is composed of two parts: the inertial navigation main instrument and the inertial navigation main instrument bracket.
Among them, the external dimensions of the main instrument are as follows:
Main technical indicators of the system
|
System accuracy System Accuracy |
Pure Inertial Navigation/Pure Inertial Navigation | 0.8 nmile/1h, CEP | |
| Integrated Navigation/Navigation with GNSS | ≤5m , 1σ _ | ||
| Heading angle /Heading | 0.05°, RMS | ||
|
Horizontal attitude (roll and pitch ) Horizontal Attitude (roll & pitch) |
0.01°, RMS | ||
| Pure Inertial Velocity | 1 .5 m/s , RMS | ||
| GNSS Integrated navigation Velocity | 0. 1 m/s , RMS | ||
|
Indicators of inertial devices Gyro and Accelerometer Parameters |
laser gyroscope _ Gyroscope |
Range/Range | ± 6 00 deg/s |
| Bias Stability | ≤0.01 deg/h, 1σ | ||
|
Zero bias repeatability Bias Repeatability |
≤0.01 deg/h, 1σ | ||
| Scale Factor non-linearity | 10 ppm | ||
|
Accelerometer Accelerometer |
Range/Range | ± 15g _ | |
| Bias Stability | ≤10μg , 1σ | ||
|
Zero bias repeatability Bias Repeatability |
≤10μg , 1σ | ||
| Scale Factor non-linearity | 15 ppm | ||
|
align time Alignment Time |
Cold Start | ≤ 8 min | |
| Re-Start | ≤ 5min _ | ||
| Air/In-Flight Start | ≤10min | ||
|
Working hours Operation Time |
Continuous working time/Operation Time | more than 10h | |
|
Interface Features interface |
Supply voltage/Voltage | 18~36VDC | |
| Power Consumption | ≤ 40W @ 24VDC | ||
| Electrical interface/Electrical |
RS232 × 2 RS422 × 3 CAN × 2 Ethernet × 1 1pps × 1 |
||
| Data Update Rate (configurable) | 200Hz@115.2kbps _ _ _ | ||
|
Use environment Environmental |
Operating Temperature | -40°C~+65°C | |
| Storage temperature/Storage Temperature | -55°C~+85°C | ||
| Use Altitude/Altitude | 20000m | ||
| Humidity | 95% (+25°C) | ||
| Vibration/Vibration | 5g @ 20~2000Hz | ||
| Shock/Shock | 40 g, 11 ms, 1/2 Sine | ||
|
Physical properties Physical |
Dimensions/ Size (L*W*H) | 240 x202x 169 mm _ | |
| Weight/ Weight | 9 kg | ||
Note: The structure can be customized according to the user's requirements.
Hot Tags: Ring Laser Gyroscope Strapdown Inertial Navigation System, Manufacturers, Suppliers, Factory, China, Made in China, Customized, High Quality
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