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Shenzhen Fire Power Control Technology Co., LTD

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City:shenzhen

Province/State:guangdong

Country/Region:china

Contact Person:Caine

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China Micro-nano Integrated Fiber Optic Gyroscope GNSS/INS Integrated Inertial Navigation System wholesale

Micro-nano Integrated Fiber Optic Gyroscope GNSS/INS Integrated Inertial Navigation System

Name: Micronano Integrated Fiber Optic Gyroscope GNSSINS Integrated Inertial Navigation System
Brand: Firepower
Price: 2 USD

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Brand Name :Firepower

Model Number :INS100

Certification :CE

Place of Origin :Shenzhen, China

MOQ :1 pcs

Price :US$2,000.00~3,000.00

Payment Terms :T/T

Supply Ability :100 pcs per month

Delivery Time :2 weeks for sample

Packaging Details :Sponge and box

Material :Stainless steel

Size :68mm*71mm*60mm

Power :9-36V

Gyro range :±300°/s

Gyro Zero Bias Stability :≤1.0°/h

Acc Range :±50g

Acc Zero Bias Stability :≤100ug

Self-north-seeking heading accuracy :≤1.5°/cosL

Azimuth measurement accuracy :≤0.2°

Vibration :20~2000Hz

Communication Interface :CAN/RS422/Network

Weight :≤0.51kg

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Product Description

INS-100 is a high-precision integrated navigation system. It is equipped with three self-developed 40 fiber optic gyroscopes,three-self MEMS accelerometers and GNSS modules, and realizes high-precision positioning and navigation in complex environments through multi-sensor fusion and integrated navigation algorithm. The product has high reliability and strong environmental adaptability. The products can be widely used in intelligent driving, UAV, surveying and mapping, marine compass, stable platform, photoelectric pod, underwater vehicle and other fields.
 
 Main functions of the integrated navigation system are as follows: 1. The initial alignment function is completed by using the output of the inertial device, and the shaking base alignment and the moving alignment can be carried out;
2. The GPS information received from outside can be used to complete the integrated navigation function and output information such as angle, speed and position. 
3. After the satellite signal is lost, the inertial device output and the odometer input can be used to continue the navigation calculation;
 4. It can output high performance and high sampling rate gyro raw output and add raw data for stable platform control.
 5. The program and configuration parameters can be upgraded online through the serial port.

Technical Parameter

Gyro technology

Project		Indicators	Remark
Gyro	Measuring range	-300°/s ~+300°/s
	Resolution	≤0.5°/h
	Bias residual	-1.0°/h ~+1.0°/h
	Random walk	0.05 o / h
	Bias stability at room temperature	≤0.3°/h(1σ)	10 seconds smoothing, 1h test result
	Bias stability at full temperature	≤0.5°/h(1σ)	10 seconds smoothing, 1h test result
	Normal-temperature Bias repeatability	≤0.3°/h(1σ)	Statistics of 6 test data
	Bias repeatability at full temperature	≤0.5°/h(1σ)	Take 2 Biasdata at full temperature, high temperature, low temperature and normal temperature respectively
	Scale factor nonlinearity	≤200ppm	Full temperature and constant temperature
	Scale factor repeatability	≤200ppm(1σ)	Full temperature and constant temperature
	Gyro start time	≤5s
	Gyro bandwidth	300Hz	Design assurance, batch testing
	Installation error residual of three-axis gyroscope	≤30"

Accelerometer technical indicators

Project		Indicators	Remark
Acceleration	Measuring range	-50g ~ +50g	Design and selection guarantee
	Scale factor nonlinearity	≤200ppm	Design and selection guarantee
	Bias stability at full temperature	≤100ug(1σ)	10 seconds smoothing, 1H test result
	Bias repeatability at full temperature	≤100ug(1σ)	Take 2 Biasdata at full temperature, high temperature, low temperature and normal temperature respectively
	Scale factor repeatability	≤100ppm(1σ)	Design and selection guarantee
	Random walk	≤0.02m/s/h1/2
	Add up the starting time	≤5s
	Triaxial addition installation error residual	≤30"

Alignment accuracy

Project		Indicators	Remark
Alignment accuracy	North seeking time	≤5min	Generally, the standard is 3min or 5min.
	Heading Angle Alignment Repeatability	≤1°/cosL	1σ
	Pitch Alignment Repeatability	≤0.05°	1σ
	Roll Angle Alignment Repeatability	≤0.05°	1σ
	North-seeking mode	Optional	It can realize swaying base alignment, GPS auxiliary alignment during travel, odometer auxiliary alignment during travel and main inertial navigation transfer alignment.

Integrated navigation accuracy (satellite effective)

Project		Indicators	Remark
Alignment accuracy	North seeking time	≤5min	Generally, the standard is 3min or 5min.
	Heading Angle Alignment Repeatability	≤1°/cosL	1σ
	Pitch Alignment Repeatability	≤0.05°	1σ
	Roll Angle Alignment Repeatability	≤0.05°	1σ
	North-seeking mode	Optional	It can realize swaying base alignment, GPS auxiliary alignment during travel, odometer auxiliary alignment during travel and main inertial navigation transfer alignment.

Inertial navigation accuracy (invalid satellite)

Project		Indicators	Remark
Inertial navigation accuracy	Accuracy of course angle maintenance	≤2°/h
	Pitch Angle Holding Accuracy	≤0.2°/h
	Accuracy of roll angle maintenance	≤0.2°/h
	Pure inertial positioning accuracy	≤20m(100s)	CEP, without external information assistance
	Position positioning accuracy of odometer integrated navigation	≤ 0.2% (mileage greater than 3 km)
	Position positioning accuracy of odometer integrated navigation	≤1m(50s)

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