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GINS100 GNSS INS Integrated Navigation System 10000g Overload Resistance

Nanjing Sky MEMS Technology Co.,Ltd.
Nanjing Sky MEMS Technology Co.,Ltd.
City: Nanjing
Province/State: Jiangsu
Country/Region: China
Tel: +86-25-83356968
Contact Person:Mr David zhu

GINS100 GNSS INS Integrated Navigation System 10000g Overload Resistance

Brand Name : SkyMEMS
Model Number : GINS100
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 GINS100 Integrated Navigation System
Application : UGV
Accelerometer Range : <100m (Within 100s)
Power supply : DC +7V~+15VDC
Attitude angle error : ≤2°
Output interface : RS232
Data refresh frequency : 200Hz (Adjustable)
Data storage capacity : 8GB
Weight : 10,000g
Overload resistance : 10,000g
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Compact Inertial Navigation Best Navigation System GNSS INS Integrated Navigation System GINS100


Product Description

GINS100 GNSS/INS integrated navigation system is composed of 3-axis MEMS accelerometers, 3-axis MEMS gyroscopes and GNSS satellite navigation system, it adopts real-time operating system and has special data fusion filtering algorithm in the high-performance information processing CPU, the system can have good response and provide reliable and accurate attitude parameters in the static, dynamic and shock environment.

The system 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.

GINS100 GNSS INS Integrated Navigation System.pdf


Main Features

- High Performance Integrated Navigation Systems

- High stability, high reliability, high survivability in harsh environment, fully calibrated INS

- Provide accurately real-time 3D position, speed, acceleration, attitude angle, angular rate, etc.

- Position accuracy of pure inertial navigation: 100m (100s)

- Attitude angle error: 2°, data refresh frequency: 200Hz

- Overload resistance:10000g, IP67 protection

- Wide temperature: -40°C~+85°C

- Small size: 60*60*60mm


Typical Application

GINS100 Integrated Navigation System can measures the complete motion. And it enjoys high overload resistance up to 10000g, GINS100 has been widely applied in the special solutions, such as:

- Mid-sized & large UAV

- Avionics

- Unmanned Ground Vehicle

- Motion monitoring

- AUV, ROV

- Weapon


Technical Specifications

Technical Specs
NameTechnical specsRemarks
Position accuracy of pure inertial navigation<100mWithin 100s
Attitude angle error≤2°
Power supplyDC +7V~+15VDC
Output interfaceRS232
Data refresh frequency200HzAdjustable
Data storage capacity8GB
Weight400±20g
Dimension60*60*60mm
Working Temperature-40~85°C
Overload resistance10,000g

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

- Overload resistance: 10,000g

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

- High cost effective


FAQ

What is GPS System?

Global Positioning System (GPS) is a worldwide, all-weather positioning system able to provide tri-dimensional position and time synchronization to UTC scale.

GPS positioning is based on the one-way ranging technique: the time of travel of a signal transmitted by satellites is measured and scaled by speed of light to obtain the satellite-user distance.

To measure the time of travel of the signal both satellite and receiver are equipped with clocks and a ranging signal is broadcast by satellite; the ranging signal is a particular code in which is embedded a timing information that enables the receiver to compute when the signal left the satellite according to the satellite clock.

In ideal conditions satellite and receiver clocks are synchronized and the time of travel, multiplied by light speed, provides the true range satellite-receiver; in this case the user position would belong to the spherical surface centered in the satellite position (at the transmission epoch) and with radius equal to the true range. Thus three simultaneous range measurements define three spherical surfaces, whose intersection would allow coordinates determination.

Actually satellites and receiver clock are not synchronized, generating errors in the measured distances (also other error sources affect the measurements, but they are negligible with respect to the error due to non-synchronization); so the measured range is not equal to the true range and is denoted as pseudorange.

At least four simultaneous measurements are necessary to compute user position, because a further unknown, representing the receiver clock bias, has to be included.


Product Tags:

ship navigation system

      

mems inertial sensors

      
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