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Beijing Oriental Lianxing Technology Co., Ltd
PNS100-BGI BDS/GPS/MEMS Precision Integrated Navigation System
NegotiableUpdate on 03/25
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Overview
PNS100-BGI BDS/GPS/MEMS Precision Integrated Navigation System
Product Details
The PNS100-BGI BeiDou/GPS/MEMS precision integrated navigation system is a combination of inertial measurement units based on MEMs technology and Beidou multi-mode satellite navigation chips（OTrack-32 BeiDou/GPS/GLONASS）A small inertial device developed through the integrated design of satellite navigation receiver units using technology/Satellite combination navigation system. It has advanced performance, compact structure, convenient use, and reasonable price.
Suitable for continuous and seamless reliable navigation and precise timing of various light and small aircraft, vehicles, small ships and other motion carriers.
In addition, the combination navigation system can also add channels for obtaining information such as geomagnetic, temperature, and atmospheric pressure on the original structure according to user needs.
Technical advantages
（1）Integrated deep coupling--Adopting mature methodsMEMSInertial components and Beidou multi-mode satellite navigation chip（OTrack-32 BeiDou/GPS/GLONASS）The integrated deep coupling design not only improvesPNS100The positioning, speed measurement, attitude measurement, and timing performance of the system have the characteristics of stable performance, resistance to signal loss, and also ensurePNS100Small in size, easy to install, and weighing only330 Ke.
（2）No offline calibration required--By combining carrier motion state recognition, gravity field, and Kalman filter zero velocity constraint technology, real-time online calibration of gyroscope and accelerometer power on zero bias is achieved.
（3）Less than4 Can still work in combination mode when using satellites--Fusion processing of pseudo range obtained from inertial units and satellite navigation chips within the same processor/Pseudo range rate measurement value.
（4）Integrity monitoring--The technology of using inertial device measurement values to monitor the integrity of each channel of satellite navigation chips and eliminate gross errors has improved the reliability of satellite navigation unit operation.
（5）Quickly assist in finding the north--By using magnetic sensors, embedded with a global magnetic declination database and fast search and calibration technology, fast magnetic sensor assisted north finding can be achieved under stable magnetic field conditions.
（6）hardware synchronization--Utilize satellite navigation internallyPPSThe second pulse signal achieves hardware synchronization, improving the accuracy and execution efficiency of data fusion between inertial measurement and satellite navigation measurement.
（2）No offline calibration required--By combining carrier motion state recognition, gravity field, and Kalman filter zero velocity constraint technology, real-time online calibration of gyroscope and accelerometer power on zero bias is achieved.
（3）Less than4 Can still work in combination mode when using satellites--Fusion processing of pseudo range obtained from inertial units and satellite navigation chips within the same processor/Pseudo range rate measurement value.
（4）Integrity monitoring--The technology of using inertial device measurement values to monitor the integrity of each channel of satellite navigation chips and eliminate gross errors has improved the reliability of satellite navigation unit operation.
（5）Quickly assist in finding the north--By using magnetic sensors, embedded with a global magnetic declination database and fast search and calibration technology, fast magnetic sensor assisted north finding can be achieved under stable magnetic field conditions.
（6）hardware synchronization--Utilize satellite navigation internallyPPSThe second pulse signal achieves hardware synchronization, improving the accuracy and execution efficiency of data fusion between inertial measurement and satellite navigation measurement.
Performance indicators of PNS100
| positioning accuracy (1σ) | Horizontal position accuracy | 5.0m（The interruption time of satellite signals shall not exceed10s） 80mThe interruption time of satellite signals shall not exceed2minThe statistical results of in vehicle testing show that the sample size is greater than20） | |
| Speed measurement accuracy (1σ) | Uniform speed measurement accuracy | 0.05m/s | |
| Variable speed measurement accuracy | 0.10m/s | ||
| time accuracy | 1PPS | ±100ns | |
| Attitude accuracy (1σ) | Pitch angle | 0.3°(Satellite signal is valid) | |
| Roll angle | 0.3°(Satellite signal is valid) | ||
| Heading angle | 0.6°(Satellite signal is valid) | ||
| Start Time | Satellite re capture | <> | |
| Satellite hot start | 1s | ||
| Satellite cold start | 35s | ||
| Combination startup | +30sThe speed of the carrier's movement is greater than1m/s） | ||
| output data | navigation data | Specialized binary format (position, velocity, attitude, time) | |
| raw data | Satellite raw channel data, inertial sensor raw data | ||
| interface | input/output | RS232/RS422 | |
| Positioning update rate | 50Hz | ||
| Effective bandwidth | 100Hz | ||
| data interface | IP50-14 | ||
| Connector | SMA | ||
| INPUT VOLTAGE | 9V~36VDC | ||
| physical property | volume | 106.5mm×83.5mm×57.5mm | |
| weight | 340g | ||
| power consumption | 3W@24VDC | ||
| operation temperature | -40℃~ +85℃ | ||
| Impact resistance | 1000g（10ms） | ||
| Anti vibration | 8g（20 Hz~2000 Hz） | ||
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