F3X80 Three-Axis FOG IMU

 

 

 

• Mobile survey & attitude
• Unmanned systems (ground/marine/UW)
• Surveying & north-finding
• Stabilized platforms
• SATCOM-on-the-move
• Autonomous driving & munitions

 

 

Company's F3X80 is a three-axis FOG IMU purpose-built for the navigation, guidance, and attitude control systems of small missiles and guided bombs. Comprising three all-solid-state FOGs, three quartz accelerometers, and a data packaging board, it measures angular velocity and linear acceleration to support attitude and navigation control. Its all-solid-state architecture eliminates moving parts for excellent shock and vibration resistance, and RS-422 serial output enables seamless system integration in high-dynamic precision guidance and attitude measurement applications.

 

 

Company is a high-tech enterprise with full closed-loop capabilities from fiber winding equipment and coils to FOGs, fiber/MEMS inertial products, IMU circuits, software, and test equipment. End-to-end process control improves quality and reduces costs. Operating under ISO9001 with strict processes, it ensures product reliability and consistency.

 

 

Parameter	A	B	C
Fiber Optic Gyroscope
RT Bias Repeatability (run-to-run, day-to-day) ( º/ h)	≤0.5	≤0.3	≤0.20
Constant-Temp Bias Stability (°/h)	≤0.5	≤0.3	≤0.20
RT SF Repeatability (ppm)	≤50	≤30	≤20
Constant-Temp SF Asymmetry (ppm)	≤30	≤20	≤20
Constant-Temp SF Nonlinearity (ppm)	≤30	≤20	≤20
Threshold (°/h)	≤0.5
Angular Rate Range (°/s)	-500～+500
Bandwidth (Hz)	100
Dimensions (mm)	Ф80*70
Weight (g)	780±20 (with accelerometer)
Operating Temperature (°C)	-40～+65
Quartz Accelerometer
Range (g)	≥±40
SF Temp Coefficient (ppm/°C)	≤100
SF Monthly Stability (ppm)	≤100
Bias (mg)	≤±7
Bias Temp Coefficient (μg/°C)	≤100
Bias Monthly Stability (μg)	≤100
2nd-Order Nonlinearity (μg/g²)	≤20
Mounting Angle (")	≤200
Appearance	No scratches, cracks, or corrosion
Insulation	≥20 MΩ (100 V), 25°C±5°C, humidity ≤80%

 

 

 

 

Fiber optic inertial measurement unit is an inertial product developed for the navigation and guidance, attitude measurement and control system of small missiles and guided bombs, which consists of three all-solid-state fiber optic gyroscopes, three quartz accelerometers and data packing boards, etc. It measures the angular velocity and linear acceleration of the carrier's movement to provide information for the carrier's attitude and navigation control, and the measurement results are outputted through RS422 serial port.

 

1.1 Application

This instruction manual only applies to the F3X80-IMU type product, which contains performance specifications, technical conditions, external dimensions and

installation and use. Among them, the technical conditions include the product's environmental range, electrical performance, and physical characteristics.

 

1.2 Main parameters

1.2.1 The main performance index of fiber optic gyroscope:

Main Index Parameters	A	B	C
Bias Repeatability at Room Temperature (By times, by days) (º/h)	≤0.5	≤0.3	≤0.20
Bias stability at Constant Temperature (º/ h)	≤0.5	≤0.3	≤0.20
Scale Factor Repeatability at Room Temperature (ppm)	≤50	≤30	≤20
Scale Factor Asymmetry at Constant Temperature (ppm)	≤30	≤20	≤20
Scale Factor Nonlinearity at Constant Temperature (ppm)	≤30	≤20	≤20
Threshold (º/h)	≤0.5º/h
Angular Rate Range (º/s)	-500 to +500 º/s
Bandwidth (Hz)	100
Dimensions (mm)	Ф80*70
Weight (g)	780±20 (with accelerometer)
Operating Temperature (°C)	-40 to +65

 

Quartz Accelerometer Parameters

No.	Item	Technical Requirement
1	Range (g)	≥±40
2	Scale Factor Temperature Coefficient (ppm /°C)	≤100
3	Scale Factor Monthly Stability (ppm)	≤100
4	Bias (mg)	≤±7
5	Bias Temperature Coefficient (μg /°C)	≤100
6	Bias Monthly Stability (μg)	≤100
7	Second-order Nonlinear Coefficient (μg /g2)	≤20
8	Mounting angle (")	≤200
9	Outlook	No scratches, cracks, or corrosion
10	Isolate	≥20MΩ; (100V),25℃±5℃, humidity≤80%

 

1.2.2 Mechanical Testing

1.2.2.1 Sinusoidal Scanning Vibration

The gyro is fixed on the vibration table through the fixture according to the direction of vibration, and the gyroscope carries out sinusoidal scanning in 3 directions, corresponding to the X-axis, Y-axis, and Z-axis directions, respectively. Vibration steps; vibration table plus excitation, to the gyroscope power, after a certain period of warm-up (gyro start-up time), test the output value of the gyroscope, about 5min; sinusoidal vibration. Vibration conditions: 20Hz-2000Hz, scanning time 5min, amplitude 4.2g. vibration process, record the gyroscope output.

Random Vibration

Vibration Frequency: 20Hz~2000Hz

Vibration Time: 5min for each axis

Vibration Direction: X, Y, Z axis

Vibration Spectrum: see Figure 1

 

 

Index requirements:

Fiber optic gyro shall be no resonance with sinusoidal scanning in the range of 20 HZ to 2000 Hz;

Random vibration: the absolute value of the bias in the vibration and the average bias before and after the vibration shall be less than 1º/h.

 

1.2.2.2 Mechanical impacts are as required by Table 2.

Table 2 Impact Conditions

Peak Acceleration (g)	30
Duration (ms)	10
Times of Impacts	3 times in each direction
Waveform	half-sine wave
Directions	X, Y, Z
	Note: The interval between two impacts is not less than 1.5s.

Impact process, the product should be able to work normally after mechanical impacts in the state of electricity, the bias should be less than 1º/h before and after the impact.

 

2 Communication protocols

2.1 IMU Data Transmission Protocol

Baud rate: 460800, no parity bit, 1 stop bit

Transmission frequency: 400Hz

Send Data Protocol:

Bits	Name	Value	Conversion	Type
0	Frame header byte 1	0xAA		uchar
1	Frame header byte 2	0xAA		uchar
2	Data Transmission Count	1~200		uchar
3	self-checking byte	255		uchar
4~7	X-axis gyro	32bit low in front and high in back		signed int32
8~11	Y-axis gyro	32bit low in front and high in back		signed int32
12~15	Z-axis gyro	32bit low in front and high in back		signed int32
16~19	X-axis plus table	32bit low in front and high in back		signed int32
20~23	Y-axis plus table	32bit low in front and high in back		signed int32
24~27	Z-axis plus table	32bit low in front and high in back		signed int32
28,29	X-axis gyro temperature	16bit low in front high in back	1/16	signed int16
30	checksum	4~29-byte dissimilarity and		uchar
31	end of frame	0xBB		uchar

 

3 Connecting Definition

The gyroscope electrical interface uses a J30-15ZK connector, and the nodes are defined in Table 4.

F3X80-IMU/INS output definition
J30J-15ZK	Definition	Note
5, 13	Power +24V	IMU Power Supply
6, 7	Power +24V (ground)
1	Serial Port Transmit 3+	IMU Serial Port
2	Serial Port Transmit 3-
3	Serial Port Receive 3+
4	Serial Port Receive 3-
11	Serial Port Transmit 2+	IMU Data Output Serial Port
12	Serial Port Transmit 2-
14	Serial Port Transmit 1+	Debugging Serial Port
15	Serial Port Transmit 1-
9	Serial Port Receive 1+
10	Serial Port Receive 1-

 

 

Figure 2 F3X80-IMU Dimension

 

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