Competitive Price GNSS INS Integrated Navigation System for Avionics Applications GINS200
GINS200 GNSS/INS Integrated Navigation System adopts high precision
MEMS inertial components and integrates GPS/BD single frequency
dual-mode satellite navigation system. It has built-in magnetic
heading measurement system and has the height measurement solution.
GINS200 has speical SkyMEMS new integrated navigation fusion
algorithm, which can realize high sensitivity tracking and accurate
positioning in open space, and it also can realize navigation
application in the city, forest, canyon terrain, etc.
- Low Cost Compact MEMS inertial system with GPS/BD dual-mode
satellite navigation system
- High Reliability, strong vibration proof
- High performance, position accuracy <5m, speed
accuracy<0.15m/s, attitude accuracy: 0.3° (rms)
- Rich external interface:RS232/RS422, protocol optional
- Smaller size, lighter weight, lower cost
- Wide temperature: -40°C～+60°C
GINS200 Integrated Navigation System enjoys high performance and
has been widely applied in the special solutions, such as:
- Mid-sized & large UAV
- Vessels, Ships
|Attitude||Roll/Pitch accuracy||<0.3 degree (RMS)|
|Position||Position accuracy||5m (RMS)|
|Speed||Speed accuracy||<0.15m / s (RMS)|
|Scale factor Non-linearity||1000ppm|
|Zero Bias stability||≤50°/h|
|Zero Bias repeatability||≤200°/h|
|Bias instability||≤8mg (Allan variance)|
|Non-linearity (full range)||0.05%|
|In Band Noise||0.5°/s|
|Receiver||Working mode||BD2 B1/GPSL1|
|Electronic specs||Power supply||7~30VDC|
|Environment conditions||Working temperature||-40~+60°C|
|Vibration||6g @ 20~2000 Hz|
|Shock||9g/11 ms, 1000g/1ms|
|Physical characteristics||Size||58 × 45× 30mm|
High Performance Integrated Navigation System
- Highly accurate, reliable and temperature stable
- Advanced, extendable, embedded Kalman Filter based sensor fusion
- State-of-the-art algorithms for different dynamic motions of
Vessels, Ships, Helicopters, UAV, UUV, UGV, AGV, ROV, Gimbals and
- Full temperature calibration of all sensing elements.
- Environmentally sealed (IP67), compact design
- High cost effective
What is Inertial Navigation Systems?
The INS consists of 3-axis gyroscopes which give the system
computer the roll,pitch and yaw rates about the body axes. It also
has 3-axis accelerometers which give the accelerations along the
three body axes. There are two basic inertial mechanisms which are
used to derive the Euler angles from the rate gyros, viz. stable
platform and strap-down INS. We would be concerned with the
strap-down INS where the gyros and accelerometers are strapped-down
to the aircraft body frame. The acceleration values from the
accelerometers are then corrected for rotation of the earth and
gravity to give the velocity and position of the aircraft.
What is Errors in the INS?
Most INS errors are attributed to the inertial sensors (instrument
errors). These are the residual errors exhibited by the installed
gyros and accelerometers following calibration of the INS. The
dominant error sources are as follows:
Alignment errors: roll, pitch and heading errors
Accelerometer bias or offset: a constant offset in the
accelerometer output that changes randomly after each turn-on.
Accelerometer scale factor error: results in an acceleration error
proportional to sensed acceleration.
Nonorthogonality of gyros and accelerometers: the axes of
accelerometer and gyro uncertainty and misalignment.
Gyro drift or bias(due to temperature changes) : a constant gyro
output without angular rate presence.
Gyro scale factor error: results in an angular rate error
proportional to the sensed angular rate
Random noise: random noise in measurement