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Light Weight Inertial Guidance System , Mems Inertial Sensors GINS300

Light Weight Inertial Guidance System , Mems Inertial Sensors GINS300

Brand Name : SkyMEMS
Model Number : GINS300
Certification : CE, FCC, ROHS
Place of Origin : Nanjing, Jiangsu
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 GINS300 Integrated Navigation System
Application : Motion Tracking and Analysis
Roll/Pitch accuracy : <0.1 degree (RMS)
Position accuracy : 1.5 m (RMS)
Speed accuracy : <0.15m / s (RMS)
Initialization time : ≤1minute
MTBF : 10000 hours
Power supply capacity : 9~36 VDC
Power consumption : ≤3W @12V DC
Electrical interface : RS232/RS422/TTL/CAN optional
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GNSS Aided Inertial Guidance System Integrated Navigation System for Motion Tracking and Analysis GINS300

Product Description

GINS300 GNSS/INS Integrated Navigation System adopts the combination of sensors, environmental compensation, and dual on-board processing with an Extended Kalman Filter (EKF), which make it perform well in a wide variety of applications that require low noise, drift, gain, and offset errors.

GINS300 enjoys smaller size, lighter weight, lower cost, and lower power consumption, faster start-up, and higher reliability, better dynamic environment adjustment, etc. It can be applied in tactical weapon, unmanned aircraft fields.

Main Features

- High precision MEMS inertial system with GPS/BD dual-mode satellite navigation system

- Multiple working modes: integrated navigation, AHRS, vertical gyro

- Supporting rapid dynamic aligning

- 100Hz data update rate

- Rich external interface:RS232/RS422/RS485/TTL/CAN

- Smaller size, lighter weight, lower cost

- Wide temperature: -40°C~+70°C

Typical Application

GINS300 Integrated Navigation System enjoys high performance and has been widely applied in the special solutions, such as:

- Mid-sized & large UAV

- Avionics

- Vessels, Ships

- Helicopters

Technical Specifications

Technical Specs
AttitudeYaw(L1/B1 single )0.15 degree (RMS)
Heading(magnetic)0.5 degree (RMS)
Roll/Pitch accuracy<0.1 degree (RMS)
PositionPosition accuracy1.5 m (RMS)
SpeedSpeed accuracy<0.15m / s (RMS)
Initialization time≤1minute
GyroscopeRange±300 (or 800)°/s
Bias stability≤4.5°/h (Allan variance)
Noise (RMS)0.3°/s
AccelerometerRange±10g (or 2g,5g, 30g)
Bias instability≤1mg
Bias repeatbility≤1mg
Non-linearity (full range)0.05%
Noise (RMS)400ug
Magnetic sensorRange6Gauss
AltimeterRate Range1100mbar
Absolute Accuracy1.5mbar
MTBF10000 hours
Electronic specsPower supply9~36 VDC
Power consumption≤3W @12V DC
Electrical interfaceRS232/RS422/TTL/CAN optional
Output rate100Hz@460,800 baud rate
Environment conditionsWorking temperature-40~+70°C
Storage temperature-55~+85°C
Vibration6g @ 20~2000 Hz
Shock30g, 11 ms, 1/2 Sine
Physical characteristicsSize65 × 65× 36mm
Weight≤500g(includ antenna)

Competitive Advantages

High Performance Integrated Navigation System

- Highly accurate, reliable and temperature stable

- Advanced, extendable, embedded Kalman Filter based sensor fusion algorithms

- State-of-the-art algorithms for different dynamic motions of Vessels, Ships, Helicopters, UAV, UUV, UGV, AGV, ROV, Gimbals and Land Vehicles

- Full temperature calibration of all sensing elements.

- Environmentally sealed (IP67), compact design

- High cost effective


What is Comparison between Loose versus Tight?

Loose and Tight integration basically differ for the type of information shared between the individual systems: processed GNSS solution is merged with INS solution in the first strategy and raw GNSS measurements are combined with INS-predicted measurements in the second.

This yields to a different structure of the two architectures, with two separate filters in the Loose coupling and only a centralized filter in the Tight.

The separate filters in the Loose have the advantage to be smaller than the corresponding centralized Tight filter, yielding faster processing times. On the other hand with separate filters in LC (if a Kalman filter is used to perform the GNSS solution), the process noise is added twice, affecting the system performance. If a Least Square estimator is used (as in this work) to obtain the GNSS solution, this problem is not present, simplifying the Loosely/Tightly comparison, which is one of the purpose of this research.

Moreover the LC approach is more robust, because INS and GNSS operate separately and so can continue to provide navigation solution also in case of failure of one system.

On the other hand LC has the great disadvantage to be unable to provide GNSS output in case of partial availability (e.g. less than four PR in GPS only mode); for this reason TC strategy is usually preferred in applications with bad visibility conditions as urban canyons.

Product Tags:

ship navigation system


ins navigation system

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