Introduction
TDMS-300 MEMS integrated navigation system is a highly reliable and cost-effective six-axis MEMS inertial/satellite integrated navigation system, which can be widely used in navigation, control and measurement fields represented by missile-borne and highly dynamic unmanned aerial vehicles (UAVS). TDMS-300 is mainly composed of three-axis MEMS gyroscope, three-axis MEMS accelerometer, information processing circuit, navigation software, structural components, test cable, test software, GNSS receiver (built-in).
The TDMS-300 MEMS series integrated navigation system integrates high-performance MEMS gyroscopes and MEMS accelerometers in a separate structure. The gyroscopes and accelerometers selected for the system represent the leading level of MEMS inertial devices. The zero bias of all temperature parameters, scale factor, non-orthogonal error and acceleration related terms are compensated in the system, which can maintain high measurement accuracy for a long time. At the same time, adaptive attitude algorithm is integrated in the system, which can ensure the measurement accuracy of attitude for a long time.
The following outputs are provided by default: 3D angular velocity, 3D acceleration, gyro temperature, accelerometer temperature, 3D attitude, INS/GNSS position, INS/GNSS speed.
Features
● high precision integrated navigation
● Built-in high dynamic missile-borne receiver
● Small size, low weight, low power consumption
● -40℃ to +80℃ full temperature scale compensation
● 1KHz high speed sampling
● Built-in adaptive Kalman filtering algorithm
● Resistant to harsh mechanical environment
● Online software upgrade function
● Inertial /GNSS integrated navigation function
Application fields
● Medium and long endurance UAVs
● Vehicle positioning and orientation
● Radar/infrared antenna stabilization platform
● Patrol Smart Munition
● Port measurement system
● mobile communication
● UAV/Vehicle/ship/boat attitude reference
● Attitude control
● photoelectric pod
● steady control and sight equipment
Specification
MEMS Gyroscope |
|
Measurement range(°/s) |
400 |
Full temperature bias(°/h) |
15 |
Bias stability(°/h,10s smooth) |
3 |
Bias repeatability(°/h) |
3 |
Non-linearity of scale factor(ppm) |
100 |
Bandwidth(Hz) |
100 |
MEMS Accelerometer |
|
Measurement range(g) |
30 |
Full temperature bias(mg) |
2 |
Bias stability(μg) |
100 |
Bias repeatability(μg) |
100 |
Non-linearity of scale factor(ppm) |
500 |
Bandwidth(Hz) |
100 |
Attitude accuracy |
|
Pitch(°,RMS) |
0.05(GNSS aided) |
Roll(°,RMS) |
0.05(GNSS aided) |
Heading(°,RMS,GNSS aided,dynamic condition) |
0.2 |
Electrical/Mechanical Interface |
|
Power supply (V) |
9V~36V |
Power consumption(W) |
5 |
Start-up time(s) |
2 |
Communication port |
2 x RS-422,1 x RS-232 |
Updating rate(Hz) |
200Hz |
Size(mm×mm×mm) |
96mm×75mm×39mm |
Weight(g) |
≤200 |
Environmental conditions |
|
Working temperature(℃) |
-40~80 |
Storage temperature(℃) |
-55~85 |
Pin definition
Pin No. |
Definition |
1 |
28V_SYS+: Power + |
2 |
28V_SYS+: Power + |
3 |
GD_RSS422_A: Navigation communication A |
4 |
GD_RS422_B: Navigation communication B |
6 |
IMU_RS422_A: IMU communication A |
7 |
IMU_RS422_B: IMU communication B |
8 |
IMU_RS422_Y: IMU communication Y |
9 |
IMU_RS422_Z: IMU communication Z |
10 |
RS4SS_GND: Communication ground |
12 |
28V_SYS-: Power - |
13 |
28V_SYS-: Power - |
14 |
GD_RS422_Y: Navigation communication Y |
15 |
GD_RS422_Z: Navigation communication Z |
16 |
RS232_RX |
17 |
RS232_TX |
18 |
RS232_GND |
21 |
SHIELD: Shield ground |
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