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Nanjing Sky MEMS Technology Co.,Ltd.
Focus on MEMS Inertial Measurement Technologies and Products Aerospace Level Quality, Reliable Selection AHRS Inclinometer Fiber Optic Gyro IMU INS GNSS/INS MEMS Acc MEMS Gyro E-compass VG MRU Shock
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High Accuracy Submarine Inertial Navigation System For Aerospace IMU300

High Accuracy Submarine Inertial Navigation System For Aerospace IMU300

Brand Name : SkyMEMS
Model Number : IMU300
Certification : CE, FCC, ROHS
Place of Origin : Nanjing, Jiangsu
MOQ : 1PCS
Price : discuss personally
Payment Terms : Western Union, MoneyGram, L/C, T/T, D/A, D/P
Supply Ability : 1000PCS for month
Delivery Time : 3-5 days after payment
Packaging Details : Strong carton with PET strap for IMU300 Inertial Measurement Unit
Application : Aerospace
Enhanced MEMS sensing technology : Yes
Accelerometer Range : ±10g (custom design)
Gyro Dynamic Range : ±400°/s
Magnetic sensor range : ±6gauss
Overload resistance : 10,000g
Bandwidth : 40Hz
Output interface : 0~3V analog output
Working temperature  : -40~+85°C
acceleromenter Bias Stability : 0.005g
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High Accuracy IMU Navigation Inertial Navigation System MEMS Inertial Measurement Unit for Aerospace IMU300


Product Description

IMU300 Miniature High Overload Resistance MEMS Inertial Measurement Unit is a small, tactical grade, low weight, high performance non-GPS aided Inertial Measurement Unit (IMU), it adopts the newest MEMS technologies, it is a new type of micro inertial measurement unit which enjoys high reliability, high stability, and adjustment in harsh environment.


Main Features

High stability, high accuracy, high reliability, high survivability
Best in Class Performance
Small size, low weight and low cost
Insensitive to magnetic fields
Fully calibrated, temperature-compensated
Range: acc ±10g, gyro ±400°/s, magnetic ±6gauss (custom design)
Bias stability: acc 0.005g, gyro 80°/h
Triaxial accelerometer, gyroscope sensors and magnetic sensors achieve the best combination of measurement qualities
Overload resistance:10000g, IP67 protection
Wide temperature: -40°C~+85°C
Small size: 45*40*40mm


Typical Application

The IMU300 IMU is well suited for stabilization, guidance and navigation applications in Industrial, Aerospace and Defense markets. It is a crucial building block for inertial navigation systems in UAVs, AUVs, AGVs, UGVs and ROVs.
IMU300 is also used for camera turret stabilization.


Technical Specifications


Technical Specs
NameSpecsRemarks
Rangeacceleromenter±10gsupport custom service
gyroscope±400°/ssupport custom service
magnetic sensor±6gausssupport custom service
Resolutionacceleromenter≤0.01g
gyroscope≤0.5°/s
magnetic sensor0.001guass
Bias stabilityacceleromenter0.005g1σ standard
gyroscope80°/h1σ standard
Bias repeatabilityacceleromenter0.005g1σ standard
gyroscope80°/h1σ standard
Bandwidth40Hz
Cross coupling≤0.5%
Power supply3.3V
Output interface0~3V analog output
Weight80g
Demension45*40*40mm
Working temperature-40~+85°C
Overload resistance10,000g

Competitive Advantages

High Performance Imu Inertial Measurement Unit

- High-quality components, industrial-grade MEMS only

- Excellent for control and stabilization

- Proven and robust filter design

- Overload resistance: 10,000g

- Full tests and individual calibration from -40 to 85°C

- High cost effective


FAQ

What is True Heading?

The “true heading” performance of an IMS is always an important parameter. If the IMS contains high performance gyroscopes (drift < 0.1 deg/hr), it can perform an autonomous gyro compassing, i.e. it measures the earth rotation rate, determines the levelling by measuring the gravity vector and calculates from these data the true north (heading) beside of roll, pitch and other values.

If the IMS does not contain such high performance gyroscopes, it can obtain the true heading only from a combination of a position reference (e.g. GNSS) and the inertial sensors, assuming sufficient motion dynamics to be present.

Using only GNSS (without inertial sensors), a so-called “track over ground” can be determined, which is the secant between the obtained GNSS positions over time. Of course, this information shows only the direction of motion of the GNSS antenna over ground, but it says nothing about the heading of the vehicle! Hence with a single GNSS antenna and without additional inertial sensors it is not possible to determine the true heading.

Using a dual antenna system as stand-alone solution, true heading can be determined as long as both antennas can observe the same GNSS satellites.

If the IMS contains the inertial sensors and a single antenna GNSS receiver (standard setup), using the right signal processing it is easily possible to determine true heading, but this requires that two constraints are fulfilled:

a) The vehicle has to be under translatorial motion, and

b) The vehicle has to perform certain (“sufficient”) changes in heading to provide enough observability to the Kalman filter based data fusion to be able to estimate true heading with sufficient accuracy

Conclusion: An IMS without gyro compassing capability and without dual-antenna GNSS aiding is not able to determine true heading of its carrying vehicle, if the vehicle is moving only on a straight line without changes of direction (this feature is called as “lack of observability”). As soon as a change of heading occurs, the observability is given and the system can provide the desired information. It is very important to take this into account when selecting the right IMS/GNSS solution for the foreseen application.


Product Tags:

inertial navigation unit

      

strapdown inertial system

      
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