Basic Info.
Output Signal Type
Digital Output
Measuring Shaft Quantities
Three
Product Description
Inertial Measurement Unit IMU16488 Instruction
Integrated Navigation System GS16488 Instruction
1.Product profile
The inertial measurement unit IMU16488 is localized high-performance, small-volume, high overload-resistant inertial measurement device. The gyro bias stability is 2°/h (Allan), and the accelerometer bias stability is 50 µg (Allan). It can be used on precise navigation, precision control and dynamic measurement of weapons. This series of products uses high-precision MEMS inertial devices, with high reliability and high ruggedness, can still accurately measure the angular velocity and acceleration information of moving carriers in harsh environments.
The inertial measurement unit has a built-in GPS/BD single-frequency dual-mode satellite receiver, is equipped with a three-axis magnetic sensor, and also integrates a barometric pressure sensor to achieve altitude measurement. The working mode can be switched flexibly in the state of combined navigation, AHRS, vertical gyro, etc. It can meet the needs of various combined navigation applications, and is particularly suitable for the navigation and control of various moving objects such as drones, car navigation, and surface vehicles.
This product is equipped with a new integrated navigation fusion algorithm with independent intellectual property rights, which can realize high-sensitivity tracking and accurate positioning of open space, and can also meet the navigation applications of terrain such as cities, deep forests, and canyons. The system has been carefully designed to reduce the size of the system with excellent integrated navigation performance to an unprecedentedly compact size and minimize the quality. 2.Composition and functionThe inertial measurement unit IMU16488 has a built-in three-axis gyro and three-axis accelerometer for measuring the three-axis angular rate and three-axis acceleration of carrier. According to the agreed communication protocol through serial port, output the gyro and accelerometer data after error compensation (including temperature compensation, installation misalignment angle compensation, nonlinear compensation, etc.).
The integrated navigation system GS16488 is based on an inertial measurement unit, a three-axis magnetic sensor, a barometric pressure sensor, a satellite receiver, and a built-in integrated navigation fusion algorithm. Output the fused posture, heading, speed, altitude, position, clock and other information.
3. Product characteristics
1) Triaxial digital gyroscope:
a) ±450º/s dynamic measurement range;
b) Bias stability: 2º/h (Allan variance);
c) Random walk: 0.5º/√h.
2) Triaxial digital accelerometer:
a) ±16g dynamic measurement range;
b) Bias stability: 50ug (Allan variance);
c) Random walk: 0.02m/s√h.
3) Ability to receive externally provided GNSS information, implement inertial/satellite integrated navigation functions, and output information such as heading, pitch, roll, 3D speed, and 3D position;
4) High reliability: MTBF>20000h;
5) Guaranteed accuracy in the full temperature range (-40ºC~75ºC): Built-in high-performance temperature calibration and compensation algorithm;
6) Support UAV application: suitable for high vibration environment of UAV, when GNSS fails, the product automatically enters the vertical gyro mode, and the heading accuracy can be maintained for a long time;
7) Support surveying and mapping applications: support RTK, positioning accuracy reaches centimeter level;
8) High-precision MEMS inertial navigation, GPS/BD dual-mode, integrated navigation, AHRS, vertical gyro and other multi-working modes;
9) Support dynamic fast alignment, high bandwidth, 400Hz combination mode data update rate, support multiple external sensor combinations (odometer/DVL);
10) Support stable platform application: full parameter measurement, measurement bandwidth>200Hz;
11) The interface includes 1 SPI and 1 UART.
4. Applications
1) Drone 2) Smart bomb 3) Surveying and mapping
4) Stable platform 5) Seeker 6) Rocket
5.Main technical indicators
Parameter | Test Condition | Min | Typical Value | Max | Unit |
Gyroscope | Measuring range | | ±400 | ±450 | - | deg/s |
Bias stability | Allan variance | - | 2 | - | deg /h |
Random walk | | - | 0.1 | - | deg /√h |
Bias repeatability | Full temperature range ?40°C ≤ TA ≤ +85°C | | 0.1 | 0.2 | deg/s |
Scale factor repeatability | Full temperature range ?40°C ≤ TA ≤ +85°C | | 0.2 | 1 | % |
Scale factor nonlinearity | FS=450 º/s | | 0.1 | 0.2 | %FS |
Bandwidth | | | | 400 | Hz |
Accelerometer | range | | | ±6 | ±18 | g |
Bias stability | | | 0.1 | | mg |
Random walk | | | 0.02 | 0.02 | m/s/√h |
Bias repeatability | Full temperature range ?40°C ≤ TA ≤ +85°C | | ±5 | | mg |
Scale factor repeatability | Full temperature range ?40°C ≤ TA ≤ +85°C | | 0.5 | 1 | % |
Scale factor nonlinearity | | | 0.1 FS=6g | 0.2 FS=18g | %FS |
Bandwidth | | | | 200 | Hz 3dB |
Magnetometer | Dynamic measurement range | | ±2.5 | | | gauss |
Resolution | | | 120 | | uGauss |
Noise density | | | 50 | | uGauss |
Bandwidth | | | 200 | | Hz |
Barometer | Pressure range | | 450 | | 1100 | mbar |
Resolution | | | 0.1 | | mbar |
Absolute measurement accuracy | | | 1.5 | | mbar |
Based External GNSS Inertial satellite Navigation Accuracy | Heading accuracy | Single GNSS, maneuver required, RMS | | 1.0 | | º |
Pitch and roll accuracy | GNSS is effective, RMS | | 0.3 | | º |
GNSS is invalid, unlimited time, RMS | | 2 | | º |
Position accuracy | GNSS effective, single point L1/L2,RMS | | 1.5 | | m |
Speed accuracy | GNSS is effective, single point L1/L2,RMS | | 0.15 | | m/s |
Communication interface | 1 SPI | baud rate | | | 15 | MHz |
1 UART | baud rate | 9.6 | 230.4 | 921.6 | Kbps |
Electrical characteristics | Voltage | | 3.0 | 3.3 | 3.6 | V |
Power consumption | | | | 1.5 | W |
Ripple | P-P | | | 100 | mV |
Structural characteristics | Dimensions | | | 44×47×14 | | mm |
Weight | | | | | g |
Operating environment | Operating temperature | | -40 | | 75 | ºC |
Storage temperature | | -45 | | 85 | ºC |
Vibration | | | 10~2000Hz, 3g | | |
Shock | | | 30g,11ms | | |
| Overload | (Half-sine 0.5msec) | | 1000 | | |
Reliability | MTBF | | | 20000 | | h |
Continuous working time | | | 120 | | h |
Address:
No 5, Fenghui South Rd, Xi′an, Shaanxi, China
Business Type:
Manufacturer/Factory
Business Range:
Auto, Motorcycle Parts & Accessories, Electrical & Electronics, Industrial Equipment & Components, Manufacturing & Processing Machinery, Tools & Hardware
Management System Certification:
ISO 9001
Company Introduction:
Xi′an SenNav Electronic Technology Co. Ltd is one of the top inertial sensor manufacturers in China, which specializes in manufacturing and marketing quartz flex accelerometer and fiber optic gyroscope, also we have GNSS simulator for navigation signal trajectory simulation.
SenNav focus on producing quartz flex accelerometer for 10+ years, executing China military standard and company standard, inertial sensor warranty is 3 years, simulator warranty is 1 year. We provide you with high-quality products and VIP service.
SenNav teams provide supports at any time. Our staff is with strong team-work spirit, young, experienced, passionate, helpful. When cooperating with us, just be assured, we will satisfy you.
At present, our major customers from all over the world, especially from Europe, Middle East, Asia. Providing high price/performance ratio products to our customers, assisting them to gain competitive advantages are our major focus.