INT-M-A02 GNSS Strapdown Aircraft Inertial Navigation System FOG INS UAV

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INT-M-A02 GNSS Strapdown Aircraft Inertial Navigation System FOG INS UAV.

Aerospace FOG INS(INT-M-A02)

Delivering exceptional navigation performance, this optical INS employs FOG/RLG gyros and quartz accelerometers in strapdown configuration. The real-time fusion center combines inertial data with GNSS, celestial and other sources.

Key advantages for UAV applications:

1) Reliable ground/air alignment;

2) Multiple alignment mode selection;

3) Scalable navigation augmentation;

4) Continuous system monitoring.

Series			Aerospace Inertial Navigation System(INS-A)
Type			INT-M-A02
Accelerometer	Months Bias Repeatability(1σ)		≤100μg
	Months Scale Factor Accuracy(1σ)		≤100ppm
Gyro	Bias Repeatability(1σ)		≤0.05°/hr
	Scale Factor Accuracy(1σ)		≤100ppm
	Random walk(1σ)		≤0.02°/√hr
Features	Position Accuracy	Pure inertia	5m/60s(Ref.),150m/300s(Ref.),CEP
		INS/GNSS combination	better than GNSS
	Speed Accuracy	Pure inertia	——
		INS/GNSS combination	≤0.2m/s,RMS
	Angular Rate		≥±400°/sec
	Angular Acceleration		100000°/sec2
	Acceleration		＞25g
	Angular Attitude		Any Orientation
	Input/output		3 RS422 full-duplex serial ports, 1 100M Ethernet port
Alignment time			＜5min
AHRS Applications Performance	Heading Accuracy	Pure inertia	≤0.5°secL+0.1°/h,RMS
		INS/GNSS combination	≤0.3°,RMS
	Pitch & Roll Accuracy	Pure inertia	≤0.1°,RMS
		INS/GNSS combination	≤0.05°,RMS
Characteristics	Power consumption		＜15W
	Dimensions		100×100×90
	Weight		＜1.35kg
	Temperature		-40℃~60℃
	Shock		15g,Half-sine wave 11ms
	Input Voltage		DC24V(±25%)
	cooling		Conduction to mounting plate
	Vibration		20~2000Hz,6.06g
	MTBF		＞20000 hours

INT

INT-M-A02 GNSS Strapdown Aircraft Inertial Navigation System FOG INS UAV

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