F3X70 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 F3X70 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) (°/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)		±1000
Bandwidth (Hz)		200
Dimensions (mm)		70*70*45
Weight (g)		400±50
Operating Temperature (°C)		-40～+65
Quartz Accelerometer
Specifications	Min.		Typ.		Max.		Unit
Measurement Range	-20		-		+20		g
Bias Instability	-		30		-		μg
Velocity Random Walk	-		0.02		-		m/s/√h
Resolution	-		0.02		-		mg
Nonlinearity Accuracy	-		0.1		-		%FS
Bandwidth	-		200		-		Hz

 

 

 

 

This fiber optic IMU is an inertial product developed for navigation, guidance, attitude measurement, and control systems of small missiles and guided bombs. It consists of three all-solid-state FOGs, three quartz accelerometers, and a data packaging board, measuring angular velocity and linear acceleration to provide attitude and navigation control information. Measurement results are output via RS-422 serial interface.

 

1.1 Scope of Application

This manual applies only to the F3X70 product and includes performance specifications, technical conditions, dimensions, and installation/usage. Technical conditions cover environmental range, electrical performance, and physical characteristics.

1.2 Main Specifications

1.2.1 FOG Main Performance Specifications:

Fiber OpticGyroscopeMainPerformanceSpecifications	Parameter	A	B	C
	RT Bias Repeat. (run-to-run, day-to-day) ( º/ h)	≤0.5	≤0.3	≤0.20
	Const-Temp Bias Stability ( º/ h)	≤0.5	≤0.3	≤0.20
	RT SF Repeatability ( ppm)	≤50	≤30	≤20
	Const-Temp SF Asymmetry ( ppm)	≤30	≤20	≤20
	Const-Temp SF Nonlinearity ( ppm)	≤30	≤20	≤20
	Threshold ( º/ h)	≤0.5º/ h
	Angular Rate Range( º/s)	±1000
	Bandwidth ( Hz)	200
	Dimensions ( mm)	70*70*45
	Weight (g)	400±50
	Operating Temp. (°C)	-40～+65

 

Table 1 Product Main Performance Specifications

Parameter		Min.	Typ.	Max.	Unit
Accelerometer Specifications	Range	-20		+20	g
	Bias Instability		30		μg
	Velocity Random Walk		0.02		m/s/√h
	Resolution		0.02		mg
	Nonlinearity Accuracy		0.1		%FS
	Bandwidth		200		Hz

 

1.2.2 Mechanical Testing

1.2.2.1 Sine Sweep Vibration

Mount the gyro on the vibration table by axis direction using fixtures. Perform sine sweep in three directions: X, Y, and Z axes. Procedure: energize vibration table, power on gyro, warm up for a period (gyro start-up time), measure gyro output for approx. 5 min, then apply sine vibration. Conditions: 20 Hz-2000 Hz, sweep time 5 min, amplitude 4.2 g. Record gyro output during vibration.

Random Vibration

Frequency: 20 Hz-2000 Hz

Duration: 5 min per axis

Direction: X, Y, Z axes

Spectrum: See Attachment 1 ttachment 1: Vibration Spectrum

Requirements:

FOG exhibits no resonance during sine sweep from 20 Hz to 2000 Hz;

Random vibration: absolute difference between in-vibration bias and pre/post average bias shall be <0.3°/h.

 

1.2.2.2 Mechanical shock per Table 2.

Table 2 Shock Test Conditions

Peak Acceleration (g)	30
Duration (ms)	10
Shock Count	per direction3times
Waveform	Half-sine
Direction	X,Y,Z
	Note: Interval between shocks ≥1.5s

 

The product shall remain powered during shock testing and function normally afterward. Bias change before/after shock shall be <0.3°/h.

Appendix A:

Baud rate: 460800, no parity, 1 stop bit

Output frequency: 400 Hz

Output data protocol:

Byte	Name	Unit	Value	Conversion	Type
0	Frame Header1		0xAA		uchar
1	Frame Header2		0xAA		uchar
2	Tx Counter		1~200		uchar
3	Self-test Byte		255		uchar
4~7	XAxis Gyro		32bitLSB first		signed int32
8~11	YAxis Gyro		32bitLSB first		signed int32
12~15	ZAxis Gyro		32bitLSB first		signed int32
16~19	XAxis Accel		32bitLSB first		signed int32
20~23	YAxis Accel		32bitLSB first		signed int32
24~27	ZAxis Accel		32bitLSB first		signed int32
28,29	XAxis Gyro Temp		16bitLSB first	1/16	signed int16
30	Checksum		4~29 Byte XOR sum		uchar
31	Frame Tail		0xBB		uchar

 

3. Wiring Definition

The FOG uses a J30-15ZKP receptacle. Pinout defined in Table 1.

Table 1 FOG Output Connector Electrical Characteristics

Pin	Definition	Label	Color
1	TXD+	TX+	Yellow
2	TXD-	TX-	Orange
3	RXD+	RX+	Blue
4	RXD-	RX-	Green
5, 13	+5 V Power	+5V	Red
6, 7	GND	GND	Black

 

 

F3X70 Dimensional Drawing

 

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