Inertial Labs INS-U-OEM
$ 0,00
The Inertial Labs GPS-Aided Inertial Navigation System (INS-U-OEM) is OEM version of new generation, fully-integrated, combined GPS, GLONASS, GALILEO, QZSS and BEIDOU GNSS and high-performance strapdown system, that determines position, velocity and absolute orientation (Heading, Pitch and Roll) for any device on which it is mounted. Horizontal and Vertical Position, Velocity and Orientation are determined with high accuracy for both motionless and dynamic applications.
Description
The Inertial Labs INS-U-OEM utilizes advanced single antenna GNSS receiver, two barometers, magnetometers, 3-axes each of calibrated in full operational temperature range Advanced MEMS Accelerometers and Gyroscopes to provide accurate Position, Velocity, Heading, Pitch and Roll of the device under measure.
INS-U-OEM contains Inertial Labs new on-board sensors fusion filter, state-of-the-art navigation and guidance algorithms and calibration software.
KEY FEATURES, BENEFITS & FUNCTIONALITY
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Commercially exportable GPS-Aided Inertial Navigation System
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3-in-1 strapdown system: INS + AHRS + ADC (Air Data Computer)
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Embedded in-flight calibration
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UBlox ZED-F9P F9 High Precision GNSS Module
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Small size & light weight & low power
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GPS, GLONASS, GALILEO, BEIDOU, QZSS, RTK supported signals
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Total and static pressure sensors for calculating Indicated Airspeed
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Embedded or External Inertial Labs Magneto-Inductive and Mini-Fluxgate
magnetometers (compass)
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GNSS measurements and IMU raw data for post-processing
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Advanced, extendable, embedded Kalman Filter-based sensor fusion algorithms
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State-of-the-art algorithms for different dynamic motions of Helicopters, and UAV
The Inertial Navigation System (INS) – Unboxing and Connecting
Additional information
| Type of application | Air |
|---|---|
| Integrity monitoring of position input | Y |
| Horizontal Position Accuracy (RTK) [ RMS in cm ] | 1 |
| Heading [deg] | 0.3 |
| Pitch [deg] | 0.05 |
| Roll [deg] | 0.05 |
| Accelerometer bias [µ-g] | 2 |
| gyro bias [deg/hr] | 2 |
| Calibration procedure | In-fligth |
| Name | GUI Software |
| Filtering | Y |
| Adaptable filter strength | Kalman |
| Adaptable input signals | Y |
| Integrity monitoring of log input | Y |
| Hot start [ seconds ] | 30 |
| Max. number of position input signals | 10 |
| Max. number of log input signals | 10 |
| Maximum latency of log input [ms] | 3 |
| Maximum latency of position input [ms] | 3 |
| Uncertainty indicators given in output | Yes |
| Uncertainty of time stamp for output [ms] | 0.02 |
| Export restrictions | ITAR Free |
| Graphical user interface | Y |
| Typical application | Fixed-wing, VTOL UAV |
| Distinguishable features | Low cost, Air Data Computer (ADC) |
| Brand | Inertial Labs |
| Addres | Inertial Labs 39959 Catoctin Ridge Street 20129 Paeonian Springs United States |
| Horizontal Position Accuracy [ RMS in cm ] | 150 |
| Cold start [ seconds ] | 50 |
| Year of initial development | 2020 |
| Moving parts | N |
| Height [mm] | 65 |
| Width [mm] | 37.2 |
| Length [mm] | 19.9 |
| Weight [kg] | 0.1 |
| Min. Voltage (DC) | 5 |
| Max. Voltage (DC) | 32 |
| Power consumption [W] | 1 |
| Mean time between failures [hr] | 100000 |
| Type of accelerometer | MEMS |
| Type of gyro | MEMS |
| Removable from base plate | N |
| Non-operating shock tolerance [g] | 3000 |
| Update rate [ Hz ] | 200 |
| Operating shock tolerance [g] | 1500 |
| Min. operating temperature [°C] | -40 |
| Max. operating temperature [°C] | 85 |
| Max. rotation speed [deg/s] | 950 |
| NMEA formats | NMEA 0183 |
| RTCM | Y |
| Other | Binary, ASCII |
| Number of integrated GNSS receivers and antenna ports | 1 |
| No. channels p receiver | 184 |
| Tracked satellite signals | All Constellations |
| SBAS differential signals | Yes |
| RTK Network Compatibility | Yes |
| URL |
