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Nanjing Sky MEMS Technology Co.,Ltd.
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Advanced Integrated Navigation System / Commercial Navigation System 7~30VDC

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

Advanced Integrated Navigation System / Commercial Navigation System 7~30VDC

Brand Name : SkyMEMS
Model Number : GINS200
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 : Unmanned Aircraft Applications
Roll/Pitch accuracy : <0.3 degree (RMS)
Position accuracy : 5m (RMS)
Speed accuracy : <0.15m / s (RMS)
Receiver Working mode : BD2 B1/GPSL1
MTBF : 10000 hours
Power supply capacity : 7~30VDC
Power consumption : ≤2.5W
Electrical interface : RS232/RS422
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INS Navigation GNSS INS Integrated Navigation System for Unmanned Aircraft Applications GINS200


Product Description

GINS200 GNSS/INS Integrated Navigation System adopts high precision MEMS inertial components and integrates GPS/BD single frequency dual-mode satellite navigation system. It has built-in magnetic heading measurement system and has the height measurement solution. GINS200 has speical SkyMEMS new integrated navigation fusion algorithm, which can realize high sensitivity tracking and accurate positioning in open space, and it also can realize navigation application in the city, forest, canyon terrain, etc.


Main Features

- Low Cost Compact MEMS inertial system with GPS/BD dual-mode satellite navigation system

- High Reliability, strong vibration proof

- High performance, position accuracy <5m, speed accuracy<0.15m/s, attitude accuracy: 0.3° (rms)

- Rich external interface:RS232/RS422, protocol optional

- Smaller size, lighter weight, lower cost

- Wide temperature: -40°C~+60°C


Typical Application

GINS200 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
NameValue
AttitudeRoll/Pitch accuracy<0.3 degree (RMS)
PositionPosition accuracy5m (RMS)
SpeedSpeed accuracy<0.15m / s (RMS)
GyroscopeRange±400 °/s
Scale factor Non-linearity1000ppm
Zero Bias stability≤50°/h
Zero Bias repeatability≤200°/h
Bandwidth50~200Hz
AccelerometerRange±2~ ±10g
Bias≤3mg
Bias instability≤8mg (Allan variance)
Non-linearity (full range)0.05%
In Band Noise0.5°/s
ReceiverWorking modeBD2 B1/GPSL1
MTBF10000 hours
Electronic specsPower supply7~30VDC
Power consumption≤2.5W
Electrical interfaceRS232/RS422
Output rate100~400Hz
Environment conditionsWorking temperature-40~+60°C
Storage temperature-55~+85°C
Vibration6g @ 20~2000 Hz
Shock9g/11 ms, 1000g/1ms
Physical characteristicsSize58 × 45× 30mm
Weight≤100g

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


FAQ

What is Kalman Filter and navigation?

KF is an extremely effective and versatile procedure for combining noisy sensor outputs to estimate the state of a system with uncertain dynamics. Noisy sensor outputs include outputs from the GPS and INS; state of the system may include position, velocity,

attitude and attitude rate of a vehicle or an aircraft; and uncertain dynamics includes unpredictable disturbances in the sensor parameters or disturbances caused by a human operator or a medium (like wind).

The KF is used to estimate the errors introduced into the unaided INS system due to the gyros and accelerometers. These errors form the state vector ^xk and the measured values of the state vector from the GPS forms the measurement vector z. Once the errors are modelled, the KF loop, is implemented after giving the initial estimates of the state vector and its covariance matrix at time t = 0. This is the GPS-aided INS system configuration, and the errors are either compensated by the feedforward or the feedback mechanism.


Product Tags:

ins navigation system

      

mems inertial sensors

      
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