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Strong Shock Vibration Inertial Measurement Unit Sensor for Aerospace Defense RS-422 Output

Strong Shock Vibration Inertial Measurement Unit Sensor for Aerospace Defense RS-422 Output

Brand Name:	Firepower
Model Number:	IMU6-1
MOQ:	1
Price:	2000$
Payment Terms:	L/C,D/A,D/P,T/T,Western Union
Supply Ability:	500/month

Detail Information

Product Description

Detail Information

Place of Origin:

China

Gyro Measuring Range:

±400°/s

Bias Stability:

0.3°/h

Angular Random Walk:

0.15º/√h

Bias Repeatability (1σ ):

1°/h

Scale Factor Repeatability (1σ ):

150ppm

3 DB Bandwidth:

250Hz

Accelerometer Bias Stability:

0.02mg

Weight:

55g

Misalignment:

±0.05°

Power Consumption:

Packaging Details:

BOX+Sponge

Supply Ability:

500/month

Highlight:

Aerospace Defense Inertial Measurement Unit

Strong Shock Inertial Measurement Unit

RS-422 Inertial Measurement Unit

Product Description

Strong Shock Vibration Inertial Measurement Unit Sensor for Aerospace Defense RS-422 Output

Key Specifications

Attribute	Value
Gyro Measuring range	±400°/s
Bias Stability	0.3°/h
Angular Random Walk	0.15º/√h
Bias repeatability (1σ)	1°/h
Scale Factor Repeatability (1σ)	150ppm
3 dB Bandwidth	250Hz
Accelerometer bias stability	0.02mg
Weight	55g
Misalignment	±0.05°
Power consumption	2W

Product Overview

The IMU6 MEMS Inertial Measurement Unit is a highly integrated sensing system designed for aerospace and defense applications with RS-422 output.

System Components

Three-axis gyroscope
Three-axis accelerometer
Three-axis inclination angle sensor
Temperature sensor
Signal processing board
Mechanical housing
Accompanying software

Designed to measure three-axis angular rate, linear acceleration, and inclination angle of moving platforms, the system features comprehensive error compensation including temperature compensation, installation misalignment correction, and nonlinear compensation. Outputs high-accuracy data via standard RS-422 serial interface following predefined communication protocol.

Gyroscope Specifications

Parameter	Unit	IMU6-1	IMU6-1A	IMU6-1B	IMU6-1C
Measuring range (customizable)	°/s	±400	±400	±400	±2000
In-Run Bias Stability(@ Allan variance)	°/h	0.3	0.1	0.05	1
Bias stability @10s (10s smooth, 1σ, room temperature)	°/h	3	1	0.5	6
Bias stability in full temperature	°/h	10	3	2	18
Angular Random Walk	°/√h	0.15	0.1	0.02	0.3
Bias repeatability (1σ)	°/h	1	0.5	0.3	2
Bias acceleration sensitivity	°/h/g	1	1	1	2
Scale Factor Non-Linearity(1σ)	ppm	150	150	150	300
Scale Factor Repeatability (1σ)	ppm	20	20	20	100
Misalignment	°	±0.05	±0.05	±0.05	±0.05
3 dB Bandwidth	Hz	250	200	150	250

Accelerometer Technical Indicators

Parameter	Unit	IMU6-1y-1	IMU6-1y-2	IMU6-1y-3	IMU6-1y-4
Measuring range (customizable)	g	±10	±30	±50	±80
In-Run Bias Stability (Allan Variance @ 25 ℃)	mg	0.02	0.05	0.1	0.2
Bias stability @10s	mg	0.05	0.2	0.5	1
Bias stability in full temperature	mg	1	3	5	15
Angular Random Walk	m/s/√h	0.001	0.002	0.005	0.01
Bias repeatability(1σ)	mg	0.1	0.5	1	2
Scale Factor Repeatability (1σ)	ppm	200	200	200	200
Scale Factor Non-Linearity(1σ)	ppm	50	100	200	300
Misalignment	°	±0.05	±0.05	±0.05	±0.05
3 dB Bandwidth	Hz	100	100	100	100

Electrical Characteristics

Parameter	Unit	Value
Voltage	V	5
Power consumption	W	2
Ripple	mV	100

Environmental Adaptability

Parameter	Unit	Value
Operating temperature	℃	-45~85
Storage temperature	℃	-55~105
Vibration	--	10~2000Hz,6.06g
Impact	--	1000g,0.1ms
Weight	g	55±5

Outline Structure

Tags:

Accelerometer Gyro Sensor

IMU Accelerometer Gyro

Quartz Flexure Accelerometer

Fiber Optic Gyro

Inertial Navigation System

3 Axis Turntable

Gyro North Finder

Accelerometer Test Equipment

Magnetometer Sensor

1 Axis Turntable

2 Axis Turntable

Accelerometer Gyro Sensor

IMU Accelerometer Gyro

Quartz Flexure Accelerometer

Fiber Optic Gyro

Inertial Navigation System

3 Axis Turntable

Gyro North Finder

Accelerometer Test Equipment

Magnetometer Sensor

1 Axis Turntable

2 Axis Turntable

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Strong Shock Vibration Inertial Measurement Unit Sensor for Aerospace Defense RS-422 Output

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