Applications

  Key PointsProduct: Attitude and Heading Reference System (AHRS)Features:• Provides real-time attitude information (pitch, roll, yaw)• Uses gyroscopes, accelerometers, and magnetometers for sensor fusion• High precision and low latency for dynamic environments• Uses algorithms like Kalman filter and complementary filter for data fusion• Compact and lightweight, ideal for aerospace, marine, and autonomous applications Applications:• Aerospace: Monitors flight status and stability in aircraft and UAVs• Autonomous Vehicles: Ensures stable navigation in self-driving cars• Marine: Tracks attitude for underwater vehicles and submarines• AR/VR: Captures user head movements for immersive experiences Advantages:• High precision and reliability in real-time navigation• Reduces dependency on manual monitoring and traditional methods• Easily integrates with other navigation systems like GPS• Works in various environmental conditions (extreme temperatures, vibrations, etc.)• Low power consumption and efficient for extended use in dynamic settings   The Attitude and Heading Reference System (AHRS) is a device widely used in aerospace, unmanned vehicles, marine exploration, and other precision navigation fields. Its primary function is to provide real-time attitude information (such as pitch, roll, and yaw) by measuring the acceleration and angular velocity of the aircraft or spacecraft, enabling precise navigation and control.   1. Working Principle of AHRS The core components of AHRS typically include gyroscopes, accelerometers, and magnetometers. These sensors provide real-time data to sense the motion state of the vehicle. The gyroscope provides angular velocity information, the accelerometer measures acceleration, and the magnetometer helps calibrate the heading angle. In practical applications, AHRS needs to use sensor fusion algorithms to combine data from different sensors and provide accurate attitude estimation. Common algorithms include Kalman Filtering and Complementary Filtering. These algorithms help correct sensor errors and provide reliable heading and attitude information. 2. Attitude Estimation and Mathematical Model   One of the core tasks of AHRS is attitude estimation. Attitude refers to the orientation of an object relative to the Earth's reference coordinate system, usually represented by three angles: pitch, roll, and yaw. There is a close mathematical relationship between these angles and the output signals from inertial sensors. Let the accelerometer and angular velocity sensor outputs be represented by , and ,respectively. The estimation of attitude angles can be computed using the following formulas: (1)Relationship between Angular Velocity and Attitude AnglesThe change in attitude angles can be calculated from the angular velocity. The relationship between angular velocity and the rate of change of attitude angles is given by where represents the yaw (heading angle), pitch angle, and roll angle, and is the Jacobian matrix describing the mapping from angular velocity to attitude angles.   (2)Relationship between Acceleration and Attitude Angles For the acceleration data from the accelerometer ,the following equation combines the acceleration data with attitude angles:,whereis the rotation matrix that describes the rotation between the body frame and the world frame. This matrix allows the conversion of acceleration data from the world coordinate system to the body coordinate system. (3)Complementary Filter and Kalman Filter    In practice, AHRS systems use complementary filters or Kalman filters to fuse data from different sensors. The basic idea of complementary filtering is to leverage the low-frequency data from the accelerometer and the high-frequency data from the gyroscope to smooth the attitude estimation process and reduce noise. The formula for the complementary filter is: 1.Where   is the current estimated attitude, is the angular velocity from the gyroscope,  is the attitude estimated from the accelerometer,  is the fusion coefficient, and  is the time interval. The Kalman filter, on the other hand, uses prediction and update steps to optimize attitude estimation, providing more accurate results in dynamic environments. 3. Applications of AHRS With the continuous development of technology, the application fields of AHRS have expanded. Below are several typical applications: Aerospace: In aircraft, spacecraft, and unmanned aerial vehicles (UAVs), AHRS is one of the fundamental attitude navigation systems, used to monitor flight status in real-time and ensure the stability of the vehicle. Autonomous Vehicles: In autonomous cars, AHRS provides real-time attitude information to help the vehicle maintain stable motion, especially in complex environments where positioning and control are crucial. Marine Exploration: Submarines and underwater robots rely on AHRS to obtain attitude data for underwater navigation, ensuring proper heading and positioning. Augmented Reality and Virtual Reality: In AR/VR devices, AHRS is used to capture head movements of the user, enabling immersive experiences. 4. Future Development Trends With advancements in microelectronics, sensor technologies, and data processing capabilities, the performance and application prospects of AHRS systems continue to improve. In the future, AHRS is expected to make significant progress in the following areas: High-Precision Sensors: The next generation of high-precision, low-power sensors will further enhance the performance of AHRS, especially in harsh environments. Intelligent Algorithms: With the development of artificial intelligence, AHRS will implement more intelligent data fusion and attitude estimation algorithms, offering more precise navigation support. Multi-Sensor Fusion: In the future, AHRS will increasingly integrate with GPS, vision sensors, and other navigation technologies, forming a more comprehensive and reliable navigation system. 5. Conclusion   As a crucial component of navigation and positioning technologies, AHRS plays an increasingly important role in various fields. With the continuous advancement of technology, AHRS will provide stronger support for precise navigation, driving the development of automation and intelligence. By gaining a deeper understanding of AHRS’s working principles and its application prospects, we can better grasp the opportunities and challenges brought by this technology. A500 3 axis accelerometer+3 axis magnetometer+3 axis Gyro Digital Output RS232/485/CAN/TTL optional A5500 Imu Ahrs Ins Gnss Inertial Sensor for Agri Robot Competitive Price A5000 Tactical Grade Integrated Mems Accelerometer Gyroscope Magnetometer Altitude Heading Sensor AHRS for UAV drone    

Key Points Product: High-Performance Gyroscopes Features: Accurate rotation rate measurement with low bias Compensation for temperature and vibration errors Zero bias stability as a key performance indicator Vibration sensitivity (g-sensitivity and g2-sensitivity) impacts performance Applications: Aerospace, automotive, industrial, and consumer electronics Advantages: High precision with temperature and vibration compensation Improved stability with multiple device averaging Anti-vibration components enhance performance Limitations: Vibration sensitivity is a major error source Zero bias stability may only be achievable in ideal conditions Mechanical impacts can affect performance   Summary: When choosing a gyroscope, it is necessary to consider minimizing the maximum error source. In most applications, vibration sensitivity is the largest source of error. Other parameters can be easily improved by calibration or taking the average of multiple sensors. Zero bias stability is one of the components with a smaller error budget.   When browsing high-performance gyroscope data manuals, the first element that most system designers focus on is the zero bias stability specification. After all, it describes the lower limit of the resolution of the gyroscope and is naturally the best indicator reflecting the performance of the gyroscope! However, actual gyroscopes may experience errors due to various reasons, making it impossible for users to obtain the high zero bias stability claimed in the data manual. Indeed, such high performance may only be achieved in the laboratory. The traditional method is to use compensation to minimize the impact of these error sources to the greatest extent possible. This article will discuss various such technologies and their limitations. Finally, we will discuss another alternative paradigm - selecting gyroscopes based on their mechanical performance and how to improve their bias stability if necessary.   Environmental error All mid to low price MEMS gyroscopes have a certain time zero bias and scaling factor error, and also undergo certain changes with temperature. Therefore, temperature compensation for gyroscopes is a common practice. Generally speaking, the purpose of integrating temperature sensors into gyroscopes is for this purpose. The absolute accuracy of the temperature sensor is not important, what is important is repeatability and the close coupling between the temperature sensor and the actual temperature of the gyroscope. The temperature sensor of modern gyroscopes can almost effortlessly meet these requirements.   Many techniques can be used for temperature compensation, such as polynomial curve fitting, piecewise linear approximation, etc. As long as a sufficient number of temperature points are recorded and sufficient measures are taken during the calibration process, the specific technique used is irrelevant. For example, insufficient storage time at each temperature is a common source of error. However, no matter what technology is used or how careful, temperature hysteresis - the difference in output between cooling and heating to a specific temperature - will be the limiting factor.   The temperature hysteresis loop of gyroscope ADXRS453 is shown in Figure 1. The temperature changes from+25 ° C to+130 ° C, then to -45 ° C, and finally back to+25 ° C, while recording the zero bias measurement results of the uncompensated gyroscope. There is a slight difference in the+25 ° C zero bias output between the heating cycle and the cooling cycle (approximately 0.2 °/s in this example), which is known as temperature hysteresis. This error cannot be eliminated through compensation, as it will occur regardless of whether the gyroscope is powered on or not. In addition, the magnitude of hysteresis is proportional to the amount of temperature "excitation" applied. That is to say, the wider the temperature range applied to the device, the greater the hysteresis. Figure 1. Zero bias output of uncompensated ADXRS453 during temperature cycling (-45 ° C to+130 ° C) If the application allows resetting the zero bias at startup (i.e. starting without rotation), or zeroing the zero bias on site, this error can be ignored. Otherwise, this may be a limiting factor for zero bias stability performance, as we cannot control transportation or storage conditions.   Anti-vibration In an ideal situation, a gyroscope only measures the rotation rate and has nothing else to do with it. However, in practical applications, due to asymmetric mechanical design and/or insufficient precision in microfabrication, all gyroscopes have a certain degree of acceleration sensitivity. In fact, acceleration sensitivity has various external manifestations, and its severity varies depending on the design. The most significant sensitivity is usually the sensitivity to linear acceleration (or g-sensitivity) and the sensitivity to vibration correction (or g2 sensitivity). Due to the fact that most gyroscopes are used in devices that move and/or rotate in a 1g gravity field around the Earth, sensitivity to acceleration is often the largest source of error.   Low cost gyroscopes generally adopt extremely simple and compact mechanical system designs, and their anti vibration performance has not been optimized (it optimizes cost), so vibration may cause serious impacts. It is not surprising that the g sensitivity is above 1000 °/h/g (or 0.3 °/s/g), which is more than 10 times higher than that of high-performance gyroscopes! For this type of gyroscope, the stability of zero bias is of little significance. A slight rotation of the gyroscope in the Earth's gravity field can cause significant errors due to its sensitivity to g and g2. Generally speaking, this type of gyroscope does not specify vibration sensitivity - it defaults to very high.   Some designers attempt to use external accelerometers to compensate for g-sensitivity (usually in IMU applications where the required accelerometer already exists), which can indeed improve performance in certain situations. However, due to various reasons, g sensitivity compensation cannot achieve complete success. The g-sensitivity of most gyroscopes varies with the frequency of vibration. Figure 2 shows the response of Silicon Sensing CRG20-01 gyroscope to vibration. Note that although the sensitivity of the gyroscope is within the rated specification range (slightly exceeding at some specific frequencies, which may not be important), the rate of change from DC to 100 Hz is 12:1, so calibration cannot be simply performed by measuring the sensitivity at DC. Indeed, the compensation plan will be very complex, requiring sensitivity to be changed according to frequency. Figure 2. g-sensitivity response of Silicon Sensing CRG20-01 to different sine tones Another difficulty is to match the phase response of the compensating accelerometer and gyroscope. If the phase response of the gyroscope and compensating accelerometer is not well matched, high-frequency vibration errors may actually be amplified! From this, another conclusion can be drawn: for most gyroscopes, g-sensitivity compensation is only effective at low frequencies. Vibration calibration is often not regulated, possibly due to embarrassing differences or significant differences between different components. It is also possible that it is simply because gyroscope manufacturers are unwilling to test or regulate (to be fair, testing may be difficult). Anyway, vibration correction must be taken into consideration as it cannot be compensated by an accelerometer. Unlike the response of an accelerometer, the output error of a gyroscope will be corrected.   The most common strategy to improve the sensitivity of g2 is to add a mechanical anti vibration component, as shown in Figure 3. The picture shows a Panasonic car gyroscope partially removed from the metal cap shell package. The gyroscope component is isolated from the metal cap by a rubber anti vibration component. Anti vibration components are very difficult to design because their response is not flat over a wide frequency range (especially poor at low frequencies), and their damping characteristics vary with temperature and usage time. Like sensitivity, the vibration correction response of a gyroscope may vary with frequency. Even if anti vibration components can be successfully designed to attenuate narrowband vibrations in a known frequency spectrum, such anti vibration components are not suitable for general applications where wideband vibrations may exist. Figure 3. Typical anti vibration components The main problems caused by mechanical abuse In many applications, routine short-term abuse events may occur, which, although not causing damage to the gyroscope, can result in significant errors. Here are a few examples. Some gyroscopes can withstand rate overload without exhibiting abnormal performance. Figure 4 shows the response of the Silicon Sensing CRG20 gyroscope to rate inputs that exceed the rated range by approximately 70%. The curve on the left shows the response of CRS20 when the rotation rate changes from 0 °/s to 500 °/s and remains constant. The curve on the right shows the response of the device when the input rate decreases from 500 °/s to 0 °/s. When the input rate exceeds the rated measurement range, the output oscillates randomly between tracks. Figure 4. Response of Silicon Sensing CRG-20 to 500 °/s rate input     Some gyroscopes exhibit a tendency to 'lock' even when subjected to impacts of only a few hundred grams. For example, Figure 5 shows the response of VTI SCR1100-D04 to a 250 g 0.5 ms impact (the method of generating the impact is to drop a 5 mm steel ball from a height of 40 cm onto the PCB next to the gyroscope). The gyroscope was not damaged due to impact, but it no longer responds to rate input and needs to be turned off and powered on again to restart. This is not a rare phenomenon, as various gyroscopes exhibit similar behavior. It is wise to check whether the proposed gyroscope can withstand the impact in the application. Figure 5. Response of VTI SCR1100-D04 to 250 g, 0.5 ms impact Obviously, such errors will be astonishingly large. Therefore, it is necessary to carefully identify potential abuse situations in a given application and verify whether the gyroscope can withstand them.   Selecting a new paradigm In error budgeting, zero bias stability is one of the smallest components, so when choosing a gyroscope, a more reasonable approach is to consider minimizing the maximum error source. In most applications, vibration sensitivity is the largest source of error. However, sometimes users may still desire lower noise or better zero bias stability than the selected gyroscope. Fortunately, we have a way to solve this problem, which is to take the average.   Unlike design related environmental or vibration errors, the zero bias stability error of most gyroscopes has noise characteristics. That is to say, the zero bias stability of different devices is not correlated. Therefore, we can improve the zero bias stability performance by taking the average of multiple devices. If n devices are averaged, the expected improvement is √ n. Broadband noise can also be improved by a similar averaging method.   Conclusion For a long time, zero bias stability has been regarded as the absolute standard for gyroscope specifications, but in practical applications, vibration sensitivity is often a more serious factor limiting performance. Choosing a gyroscope based on its anti-vibration capability is reasonable, as other parameters can be easily improved through calibration or averaging multiple sensors.   Appendix: Calculation of Errors Caused by Vibration To calculate the error caused by vibration in a given application, it is necessary to understand the expected amplitude of acceleration and the frequency at which this acceleration may occur. l  Running typically produces a peak of 2 grams, accounting for approximately 4% of the time. l  The vibration of the helicopter is quite stable. Most helicopter specifications are 0.4 g wideband vibration and 100% duty cycle. l  Ships (especially small boats) on turbulent waters can tilt up to ± 30 ° (producing ± 0.5 g of vibration). The duty cycle can be assumed to be 20%. l  For construction equipment such as leveling machines and front-end loaders, as long as their blades or buckets hit stones, they will produce a high g (50 g) and brief impact. The typical duty cycle value is 1%.   When calculating the error caused by vibration, it is necessary to consider the sensitivity of g and g2. Taking helicopter application as an example, the calculation is as follows: Error=[g sensitivity error]+[g2 sensitivity error] =[0.4 g x g sensitivity x 3600 s/h x 100%]+ [(0.4 g) 2 × g2 sensitivity × 3600 s/h × 100%] If the sensitivity of g is compensated by an accelerometer, only the sensitivity of g decreases, and the decrease is the compensation coefficient.   MG502 MG-502 HIGH PRECISION MEMS SINGLE AXIS GYROSCOPES   --

Key Points Product: Fiber Optic Gyroscopes (FOGs) Features: • Highly accurate sensor for measuring angular velocity • Low bias stability (≤0.2 °/h), ensuring high measurement accuracy • Low random walk (ARW) for stable output over time (e.g., 0.001°/√h) • Scale factor accuracy (e.g., 10 ppm) with minimal deviation from actual rotation • Sensitive to temperature, vibration, and light source changes Applications: • Aviation: Provides accurate position, velocity, and attitude data for aircraft • Navigation: Assists in guidance and positioning systems • Seismic Research: Monitors rotational movement during earthquake studies • Military: Used in missile and bomb guidance systems Advantages: • High precision and stability • Low power consumption, easy installation and maintenance • Reliable in dynamic environments with minimal drift and noise • Versatile in various applications requiring precision angular velocity measurement     Fiber optic gyroscopes (FOGs) are highly accurate sensors used to measure angular velocity. They are widely used in fields such as aviation, navigation, and seismic research due to their high precision, sensitivity, and excellent stability. Its core accuracy indicators, including zero bias drift, random walk, and angle measurement error, are the key to evaluating its performance. Detailed explanation of core accuracy indicators Fiber optic gyroscope uses optical fibers as sensing elements to achieve accurate measurement of rotational angular velocity. Its accuracy performance can be comprehensively evaluated through the following three indicators:   (1)    Bias Stability (Drift Rate)   This indicator reflects the output accuracy of the gyroscope in a non rotating state, usually measured by a benchmark accuracy. The zero bias drift of fiber optic gyroscope is extremely low, generally not exceeding 0.2 °/h, ensuring high measurement accuracy.   (2)    Random Walk (Angular Random Walk, ARW)   This indicator measures the stability of the gyroscope output value over a period of time. typically measured in degrees per square root hour (°/√h). For example, the FOG has an ARW of 0.001°/√h. This means that the noise in the gyroscope's output accumulates at a rate of 0.001 degrees per square root of the operating time. (3)     Scale Factor Accuracy   The scale factor accuracy indicates how well the gyroscope's output corresponds to the actual angular velocity. It is usually expressed as a percentage error. For example, The FOG has a scale factor accuracy of 10 ppm (parts per million)**. This means that for every degree per second (°/s) of actual rotation, the gyroscope's output may deviate by up to 0.001%.   Analysis of Factors Affecting Accuracy The accuracy of fiber optic gyroscopes is influenced by various external factors: (1)    Temperature: The sensitive components of fiber optic gyroscopes are sensitive to changes in ambient temperature, which may lead to zero bias drift or increased angle measurement errors. (2)    Vibration: Environmental vibrations can have adverse effects on the accuracy of fiber optic gyroscopes, potentially leading to unstable output values. (3)   Light source: Changes in parameters such as power and wavelength of the light source may also affect the output value of the fiber optic gyroscope, thereby affecting its accuracy. Example of G-F3G70 manufactured by Micro-Magic the G-F3G70 fiber optic gyroscope inertial group is designed for medium and high precision application backgrounds. It adopts three-axis common technology and split design, with low cost and stable performance. The structure adopts optical path and circuit integrated packaging, with simple structure and easy installation. It can be used in navigation guidance, attitude measurement and control systems of small missiles and guided bombs. Main performance index of the fiber-optic gyroscope   G-F3G70-A G-F3G70-B G-F3G70-C Unit zero bias stability ≤0.050 (10s) ≤0.03 (10s ) ≤0.02 (10s) (°)/h Zero bias stability full temperature (1℃/min, 100s ) ≤0.15 ≤0.12 ≤0.10 (°)/h Zero bias repeatability ≤0.050 ≤0.03 ≤0.03 (°)/h Random walk coefficient ≤0.002 ≤0.002 ≤0.001 (º)/h1/2 Scale factor nonlinearity ≤20 ppm Scale factor asymmetry ≤20 ppm Scale factor repeatability ≤20 ppm Conclusion With its high precision advantage, fiber optic gyroscopes have been widely used in fields such as aviation, navigation, and earthquake research. For example, in aircraft, fiber optic gyroscopes can accurately determine the position, velocity, and attitude of the aircraft, ensuring stable and precise flight direction. In summary, as a high-precision measurement device, the performance of fiber optic gyroscope is affected by various factors, but it still shows great potential and value in various fields of application.       G-F3G70 Affordable price Dynamic Range 400 Deg/S Optic Fiber Gyroscopes China Leading Supplier    

Key Points Product: Tilt Angle Monitoring Sensors Features: - Monitors tilt angles for large outdoor advertisements, infrastructure, and construction. - Enables real-time data transmission via GPRS for remote monitoring. - Solar-powered for independent operation, reducing the need for external power sources. - Provides high data credibility with minimal manpower required. - Offers low cost, easy installation, and maintenance. Applications: - Outdoor Advertising: Monitors tilt of large billboards and signs to ensure optimal display angles. - Infrastructure: Tracks tilt in bridges, buildings, and dams to detect any structural issues. - Construction: Monitors the tilt of heavy machinery during operation for safety and performance evaluation. Advantages: - High precision and real-time monitoring of tilt angles. - Reduces reliance on manual inspection and traditional methods of monitoring. - Easy integration into existing monitoring systems. - Low power consumption, environmentally-friendly design with solar-powered operation. - Reliable operation in various environmental conditions, including temperature and humidity.   Inertial measurement unit (IMU) is an integrated sensor kit that combines multiple accelerometers and gyroscopes to perform three-dimensional measurements of specific force and angular velocity relative to an inertial reference frame. However, in recent years, IMU has become a general term used to describe various inertial systems, including attitude heading reference systems (AHRS) and INS. IMU itself does not provide any type of navigation solution (position, velocity, attitude) . Normally, inertial sensors can be divided into the following three performance categories:   Marine-grade and Navigation-grade inertial navigation systems :     Marine-grade inertial navigation systems are the highest level of commercial sensors used on ships, submarines, and occasionally on spacecraft. This system can provide a non assisted navigation solution with drift less than 1.8 km/day. The cost of these sensors is as high as $1 million. The performance of navigation grade inertial navigation systems is slightly lower than that of Marine-grade inertial navigation systems, and is usually used for commercial and military aircraft. Its drift is less than 1.5km/h, and its price is as high as $100000. Tactical and industrial inertial sensors: Tactical and industrial grade sensors are the most diverse among these three types of sensors, capable of addressing various performance and cost situations, and their market opportunities are enormous. This category is used for many applications that require high-performance data to be obtained at a lower cost for mass production, commonly found in automatic lawnmowers, delivery robots, drones, agricultural robots, mobile industrial robots, and autonomous ships. Consumer grade sensors: In the commercial market, these sensors are usually sold in the form of separate accelerometers or gyroscopes. Many companies have started combining multiple accelerometers and gyroscopes from different manufacturers to create independent IMU units   Choosing the appropriate inertial sensor (such as accelerometer, gyroscope, magnetometer, or combined IMU/AHRS) requires comprehensive consideration of multiple factors including application scenarios, performance parameters, environmental conditions, and costs.   1. Clarify application requirements   Dynamic range: Determine the maximum acceleration or angular velocity that the sensor needs to measure (for example, a high range gyroscope is required for high-speed maneuvering of a drone). Accuracy requirements: High precision navigation (such as autonomous driving) requires sensors with low noise and low bias. Update frequency: High frequency vibration monitoring requires a sampling rate of>1kHz, while conventional motion tracking may only require 100Hz. Power consumption limit: Wearable devices require low power consumption (such as MEMS accelerometers with ± 10mg noise), while industrial devices can be relaxed. Integration method: Do you need IMU (6-axis) or AHRS (with attitude calculation).   2. Key performance parameters   Accelerometer: Range: ±2g (inclination measurement) to ±200g (impact detection). Noise density:  < 100μg/√ Hz (high precision) vs >500 μg/√Hz (low cost). Bandwidth: It needs to cover the highest frequency of the signal (e.g. mechanical vibration may require >500Hz).   Gyroscope: Zero bias stability: < 1°/h (fiber optic gyroscope) vs 10°/h (industrial MEMS) vs 1000 °/h (consumer grade). Angle random walk (ARW): <0.1°/√h (tactical level) vs 5°/√h (consumer level). Range: ±300°/s (conventional) to ±2000 °/s (high-speed rotation).   Magnetometer: Sensitivity: 0.1μT/LSB (high-precision navigation) vs 0.5μT/LSB (universal). Orthogonal error:  <1° (reduces the influence of soft iron interference).   3. Environmental adaptability   Temperature range: Industrial grade (-40°C~85°C) vs Consumer grade (0° C~70°C). Anti vibration/impact:  For example, automotive electronics need to pass a 5g RMS vibration test. Sealing:  IP67/IP68 protection level (outdoor or humid environment).   4. Interface and power consumption   Digital interfaces: SPI/I2C (embedded systems), CAN (automotive), UART (simple communication). Power supply voltage: 3.3V (low power consumption) vs 5V (industry standard). Power consumption: < 1mA (battery device) vs unlimited (wired power supply).   Micro-Magic Inc is a high-tech company specializing in the production, manufacturing, and research and development of automotive grade and industrial grade inertial sensors. The company's inertial sensor include various series of products such as accelerometers, gyroscopes, magnetometers, inclinometers, IMUs, VRUs, AHRS, and INS+GNSS integrated navigation. Over the years, The company's products have been widely used in various application fields, including automotive, aerospace, marine vessels, industrial automation, and medical equipment. The company's products have the characteristics of high precision, low power consumption, small size, and high reliability, and are widely used in fields such as attitude control, navigation systems, motion tracking, and vibration analysis. At the same time, Micro-Magic Inc are also committed to providing customized solutions for customers to meet the specific needs of different industries U6488 MEMS High Precision Digital Output IMU Sensor U7000 High Precision MEMS IMU U300-A Digital Output High Performance MEMS IMU Sensor  

Key Points Product: Electronic Compass Principle of Calibration: - Magnetic field ellipse fitting: Collect magnetic field data in all directions while rotating the device, calculate hard iron interference and soft iron interference parameters, and apply compensation to fit the magnetic field data into a sphere for improved accuracy. Calibration Methods: 1. Plane calibration: - XY plane calibration: Rotate the device in the XY plane to find the center point of the trajectory circle projected in that plane. - XZ plane calibration: Rotate the device in the XZ plane to obtain the trajectory circle of the Earth's magnetic field and calculate the magnetic field interference vector in 3D space. 2. Stereoscopic 8-shaped calibration: - Rotate the device in various directions in the air to collect sample points that fall on the surface of a sphere. Determine the center of the circle to determine the interference value and perform calibration. Calibration Steps: 1. Preparation of testing environment: - Stay away from interference sources. - Ensure horizontal placement and stable installation. 2. Enter calibration mode: - Manually trigger calibration through key combinations or software instructions. - Auto prompt calibration when magnetic field anomalies are detected. 3. Perform calibration operation: - Horizontal rotation (2D calibration): Slowly rotate the device around the vertical axis in a horizontal position. - Three-dimensional rotation (3D calibration): Rotate the device around the X, Y, and Z axes, covering at least 360° for each axis. 4. Verify the calibration results: - Compare the device readings with a known geographic direction. - Use software tools to observe directional stability and accuracy. - Repeat calibration if deviation exceeds the nominal error of the device. Advantages of Electronic Compass: - Real-time heading and attitude measurement. - Crucial navigation tool. - Improves directional accuracy through calibration. - Various calibration methods available. - Can be used in different applications and environments.   Electronic compass is an important navigation tool that can provide real-time heading and attitude of moving objects. Calibration of an electronic compass is a crucial step in ensuring the accuracy of its directional measurement.   1. Calibration principle of electronic compass The electronic compass determines direction by measuring the components of the geomagnetic field. The calibration process is actually "magnetic field ellipse fitting": a) Collect magnetic field data  in all directions when the device rotates. b) Generate compensation parameters by calculating hard iron interference (fixed offset) and soft iron interference (scaling and cross coupling) through algorithms. c) Automatically apply compensation during subsequent measurements to fit the magnetic field data into a sphere centered at the origin, improving directional accuracy.   2. Calibration method for electronic compass The calibration methods for electronic compasses mainly include two methods: planar calibration and three-dimensional 8-shaped calibration. (1) Plane calibration method For the calibration of the XY axis, the device equipped with a magnetic sensor will rotate on its own in the XY plane, which is equivalent to rotating the Earth's magnetic field vector around the normal passing point O(γx,γy) perpendicular to the XY plane. It represents the trajectory of the magnetic field vector projected in the XY plane during the rotation process. This can find the position of the center of the circle as (Xmax+Xmin)/2, (Ymax+Ymin)/2. Similarly, rotating the device in the XZ plane can obtain the trajectory circle of the Earth's magnetic field on the XZ plane, which can calculate the magnetic field interference vector γ (γx, γy, γz) in three-dimensional space. After calibration, the electronic compass can be used normally on the horizontal plane. However, due to the angle between the compass and the horizontal plane, this angle can affect the accuracy of the heading angle and requires tilt compensation through acceleration sensors. (2) Stereoscopic 8-shaped calibration method Usually, when a device with sensors rotates in various directions in the air, the spatial geometric structure composed of measured values is actually a sphere, and all sampling points fall on the surface of this sphere, as shown in the following figure.‌                a) Aerial rotation:  Use calibrated equipment to perform an 8-shaped movement in the air, aiming for the normal direction of the equipment to point towards all 8 quadrants of space. By obtaining sufficient sample points, the center O(γx,γy,γz) is determined, which is the size and direction of the fixed magnetic field interference vector. b) Sample point collection:  When rotating the device in various directions in the air, the spatial geometric structure composed of measurement values is actually a sphere, and all sampling points fall on the surface of this sphere. By using these sample points, the center of the circle can be determined to determine the hard magnetic interference value and perform calibration.   3. Calibration steps for electronic compass (1) Preparation of testing environment Ø Stay away from interference sources: Ensure that there are no large metal objects (such as iron cabinets, vehicles), motors, speakers, or other electromagnetic equipment within 3 meters of the calibration environment. Ø Horizontal placement: Use a level or built-in sensor to adjust to a horizontal state, ensuring that the measurement is based on the horizontal component of the geomagnetic field. Ø Fixed method: Avoid wearing metal watches or rings when holding the device; If it is an embedded device (such as a drone), ensure a stable installation. (2) Enter calibration mode a) Manual triggering: Refer to the product manual, common methods include: n Key combination (such as long pressing the power and function keys for 5 seconds). n Software instructions (select 'Calibrate Compass' through the accompanying app). b) Auto prompt: Some devices automatically prompt calibration when detecting magnetic field anomalies (such as continuously displaying "low precision").   (3) Perform calibration operation a) Horizontal rotation (2D calibration): n Slowly rotate the equipment around the vertical axis (Z-axis) and keep it horizontal. n Ensure uniform rotation speed (about 10 seconds/turn), complete at least 2 turns to cover all directions. b) Three-dimensional rotation (3D calibration, suitable for high-precision equipment): n Rotate around the X (roll), Y (pitch), and Z (yaw) axes in sequence, with each axis rotating at least 360 °. n Example action: After horizontal rotation, flip the device upright and then tilt it back and forth. (4) Verify the calibration results a) Direction comparison method: Point the device towards a known geographic direction (such as using a compass to determine true north) and check if the readings match. b) Software validation: Use map apps or professional tools (such as magnetic field analysis software) to observe directional stability and accuracy. c) Repeat calibration: If the deviation exceeds the nominal error of the equipment (such as ±3°), recalibration and environmental interference inspection are required.   C9-B High Precision CAN Protocol Output 2D Electronic Compass C9-A 40° Tilt Angle Compensation CAN Protocol Output 3D Electronic Compass C9-C High Precision Digital Output 2D Electronic Compass Single Board  

Explore comprehensive testing methods for fiber optic gyroscope key indicators, including zero bias stability, scale factor nonlinearity, and random walk coefficient (RWC). Learn step-by-step procedures, formulas, and equipment requirements for precision navigation and attitude control applications. Fiber optic gyroscope is based on Sagna effect and is widely used for measuring angular velocity in navigation and attitude control. Key indicators typically include zero bias stability, scaling factor, random walk, bandwidth, noise, temperature characteristics, and so on. By measuring these indicators, the performance of fiber optic gyroscopes can be comprehensively evaluated, and system design and compensation algorithms can be optimized based on these data.   1. Zero Bias Series Testing 1.1 Bias Definition： The average equivalent angular velocity output of a fiber optic gyroscope when there is no angular velocity input. Test Equipment: horizontal reference device, fiber optic gyroscope output measurement recording device. Test method: Fix the fiber optic gyroscope on a horizontal reference, with the input axis (IRA) pointing in the east-west direction. Record output data for at least 1 hour after power on, with a sampling frequency that meets the Nyquist criterion (≥ 2 times the highest frequency of the signal). Calculation formula:                 Where K is the scaling factor, is the average output value.   1.2 Bias Stability Definition: The degree of dispersion of zero bias output around the mean reflects short-term stability. Test method: Same as bias test, but requires long-term data recording (at least 1 hour). Calculation formula:                   where:  ： Zero bias stability, measured in degrees per hour (° ⁄ h) :  The single-sided amplitude output of the fiber optic gyroscope  at time .   1.3 Bias Repeatability Definition: Perform multiple power tests to ensure consistency of zero bias. Test method: Repeat the zero-bias test for more than 6 times, with power off and cooling to room temperature at intervals between each test. Calculation formula: For each test data, process it according to formula (1), calculate the zero bias, and then calculate the zero-bias repeatability of Q tests according to the following formula.                        Where,   :  Zero bias of the i-th test; :  Zero bias   1.4 Bias Temperature Sensitivity Definition: Zero bias drift caused by temperature changes. Test method: Set different temperature points (covering the working temperature range) inside the temperature control box, and maintain a constant temperature for 30 minutes at each temperature point. Measure the zero bias at each temperature point and calculate the deviation from the room temperature zero bias. Calculation formula: The test data is processed according to formula (1), and the zero bias of the fiber optic gyroscope at room temperature and each test temperature point is calculated separately. The zero bias temperature sensitivity of the fiber optic gyroscope is calculated according to the following formula:                             ：The i-th test temperature.  ：room temperature   2. Scale Factor Series Testing 2.1  Scale Factor Definition: Linear proportional relationship between output signal and input angular velocity Test equipment: high-precision rate turntable (error<1/3 of the tested gyroscope index) Test method: Select ≥ 11 angular velocity points (including the maximum input angular velocity) uniformly in both forward and reverse directions. Record the mean output of each point and fit a straight line using the least squares method. Calculation formula: Let be the average output of the fiber optic gyroscope at the jth input angular velocity, and the scaling factor calculation method is as follows:                                               The linear model for establishing the input-output relationship of fiber optic gyroscope is as follows:                     Using the least squares method to calculate K,                               Where ∅ is the rotational speed of the speed turntable, measured in degrees per second (° ⁄ s)   2.2 Scale factor nonlinearity Definition: Output the maximum deviation relative to the fitted line. Calculation formula: According to the above method, the input-output relationship of the fiber optic gyroscope is represented by fitting a straight line as follows:               Calculate the point-by-point nonlinear deviation of the output characteristics of the fiber optic gyroscope according to the following formula:                   Calculate the scaling factor linearity according to the following formula, and create the nonlinear deviation curve of the fiber optic gyroscope output (the horizontal axis represents the input angular velocity, and the vertical axis represents the nonlinear deviation)                   2.3 Scale factor temperature sensitivity Test method: Test the scaling factor at different temperature points and calculate the deviation caused by temperature changes. Calculation formula: The test data is processed according to the calculation method of scale factor, and the scale factor of the fiber optic gyroscope at room temperature and each test temperature point is calculated separately. The temperature sensitivity of the scale factor is calculated according to the following formula:                 3. Random Walk Coefficient (RWC) Definition: Integral angular velocity error caused by white noise output. Test method: Short time (tens of seconds) high-frequency sampling, analyze Allan variance. Formula for calculating Allan variance: a) There are n initial sample data of fiber optic gyroscope output values obtained at the initial sampling interval time . According to the calculation formula for gyroscope zero bias, the output angular velocity of each fiber optic gyroscope output value is calculated to obtain the initial sample data of output angular velocity, as shown in the following formula:               b) For continuous data of n initial samples, k continuous data are grouped together, and the time length of the array is set to , where τ equals , 2 ,  Calculate the average value of the array data for each time length. c) Find the average difference between two adjacent arrays:           d) Calculate the variance of a set of random variables:   …… (17) Repeat the above process with different values of, and obtain a curve in the double logarithmic coordinate system, which is called the Allan variance curve. Using the Allan variance model below, the coefficients are obtained through least squares fitting, and then the random walk coefficient RWC is calculated:                   Conclusion: The key indicator testing of fiber optic gyroscope is a bridge connecting research and development with practical applications. By quantitatively verifying performance, ensuring reliability, and meeting standard compliance, it ensures its "precision, stability, and usability" in military and civilian high-precision fields, while laying the foundation for technological innovation and cost optimization. GF2X64 Dual-Axis Low Precision Fiber Optic Gyroscope GF-60 Medium and Low Precision  Fiber Optic Gyroscope GF3G90 Tri-Axis Fiber Optic Gyroscope    

  Key Points Fiber Optic Gyroscope North Finder   Pros: High accuracy, shock resistance, low power consumption, no external reference neededCons: Requires precise calibration, sensitive to driftBest for: Harsh environments, precision navigation applications Conclusion: Ideal for determining true north in challenging conditions, offering reliable performance without requiring latitude information.   The north finder is a type of compass used to find the true north direction value of a certain location. The gyroscope north finder, also known as the gyroscope compass, is an inertial measurement system that uses the principle of gyroscope to determine the projection direction of the Earth's rotational angular velocity on the local horizontal plane (i.e. true north position). Its search for north does not require external reference.   Principle of Fiber Optic Gyroscope North Finder Fiber Optic Gyroscope (FOG) is a new type of all solid-state gyroscope based on Sagnac effect. It is an inertial measurement element without mechanical rotating parts, with advantages such as shock resistance, high sensitivity, long lifespan, low power consumption, and reliable integration. It is an ideal inertial device in the new generation of strapdown inertial navigation systems.   In fiber optic gyroscope based north finding applications, the majority of methods used involve FOG rotation at a fixed angle and calculating the angle relative to the north direction by determining the offset. In order to accurately point north, it is also necessary to eliminate the drift of FOG. Generally, a rotating platform as shown in Figure 1 is used to place the fiber optic gyroscope on a moving base, with the plane of the moving base parallel to the horizontal plane and the sensitive axis of the fiber optic gyroscope parallel to the plane of the moving base. When starting to search north, the gyroscope is in position 1, and its sensitive axis is parallel to the carrier. Assuming that the angle between the initial direction of the sensitive axis of the fiber optic gyroscope and the true north direction is α. The output value of the gyroscope at position 1 is ω1; Then rotate the base 90° and measure the output value of the gyroscope at position 2 as ω2. Rotate 90° twice in sequence, turning to positions 3 and 4 respectively, to obtain angular velocities ω3 and ω4.    Assuming the latitude of the measurement point is φ，The Earth's rotation is  , The angular velocity measured at position 1 is: Where  is the zero drift of the gyroscope output. Similarly, it can be concluded that: In a short period of time, assuming that the drift of the fiber optic gyroscope is a constant, that is: , Then:   By using this method for measurement, the zero bias of the gyroscope can be eliminated, and there is no need to know the latitude value of the measurement location. If the latitude of the measurement location is a known value, then only measuring positions 1 and 3 (or 2 and 4) can determine the heading angle.   Conclusion The fiber optic gyroscope north finder has a simple structure and excellent performance, especially able to resist impacts and various harsh environments. When the turntable is horizontal, it can provide the angle between the carrier and true north direction without inputting latitude values. In the case where the turntable is not strictly horizontal, the Earth's angular velocity measured by fiber optic gyroscope and the angle between the gyroscope and the horizontal plane measured by accelerometer are also used to calculate the angle between the baseline of the carrier and the true north direction through computer calculation. At the same time, the accelerometer can also measure the attitude angle of the north finder.   NF2000 inertial navigation system High Precision FOG North Seeker   NF3000 Inertial Navigation System High Performance Dynamic Fog North Seeker  

Key Points Quartz Accelerometer Pros: High accuracy, stable, wide range, robust Cons: Larger, expensive, high power Best for: Precision applications (e.g., aerospace) MEMS Accelerometer Pros: Compact, low cost, low power Cons: Lower accuracy, limited range Best for: Consumer electronics, portable devices Conclusion Quartz: For high precision MEMS: For cost-effective, compact solutions Choosing between a quartz flexible accelerometer and a MEMS accelerometer depends on specific application requirements. Here are some key factors to consider:   1.       Quartz Flexible Accelerometer Advantages: 1)      High Accuracy and Stability: Quartz accelerometers are known for their high precision and long-term stability, making them suitable for applications requiring precise measurements over extended periods. 2)      Wide Dynamic Range: They can measure a wide range of accelerations, from very low to very high. 3)      Robustness: They are generally robust and can operate in harsh environments, including high temperatures and high vibration conditions. 4)      Low Noise: They typically have low noise levels, which is crucial for sensitive measurements.   Disadvantages: 1)      Size and Weight: Quartz accelerometers are generally larger and heavier compared to MEMS accelerometers. 2)      Cost: They are usually more expensive due to the complex manufacturing process and high-quality materials. 3)      Power Consumption: They tend to consume more power, which might be a concern for battery-operated devices.   2.       MEMS Accelerometer Advantages: 1)      Compact Size: MEMS accelerometers are small and lightweight, making them ideal for applications where space and weight are critical, such as in consumer electronics and portable devices. 2)      Low Cost: They are generally less expensive to produce, making them cost-effective for high-volume applications. 3)      Low Power Consumption: MEMS accelerometers consume less power, which is beneficial for battery-powered devices. 4)      Integration: They can be easily integrated with other electronic components on a single chip, enabling multifunctional devices.   Disadvantages: 1)      Lower Accuracy: MEMS accelerometers may have lower accuracy and stability compared to quartz accelerometers, especially over long periods. 2)      Limited Dynamic Range: They may not perform as well in measuring very high or very low accelerations. 3)      Environmental Sensitivity: They can be more sensitive to environmental factors such as temperature and vibration, which might affect performance.   3.       Application Considerations Ø  High-Precision Applications: If your application requires high precision, stability, and wide dynamic range (e.g., aerospace, defense, or seismic monitoring), a quartz flexible accelerometer might be the better choice. Ø  Consumer Electronics: For applications where size, weight, cost, and power consumption are critical (e.g., smartphones, wearables, IoT devices), a MEMS accelerometer is likely more suitable.   4.       Performance comparison Micro-Magic Inc provides a series of high-precision quartz accelerometers and a series of MEMS accelerometers. Taking quartz accelerometer AC-5B and MEMS accelerometer ACM-300-8 as examples, some typical parameter comparisons are as follows: Parameters AC-5 ACM-300 Measuring range ±50 g ±8 g Resolution <5μg <5 mg Bias <7 mg <50 mg Bias thermal coefficient < ±30μg/℃ 0.5 mg/℃ Scale factor thermal coefficient <50 ppm/℃ 100 ppm/℃ Bandwidth >300Hz 0~400 Hz   5.       Conclusion   Choose Quartz Flexible Accelerometer for high-precision, high-stability applications where size, weight, and cost are less critical. Choose MEMS Accelerometer for compact, cost-effective, low-power applications where high precision is not the primary concern. ACM-300 High Performance Industry Current type MEMS Accelerometer Sensor Factory   AC-5 Large Measurement Range 50g Quartz Pendulum Accelerometer Quartz Flex Accelerometer    

Key Points Product: Fiber Optic Gyroscope (FOG) Key Features: Components: Solid-state sensor using optical fiber for precise inertial measurements. Function: Leverages the SAGNAC effect for accurate angular rate sensing without moving parts. Applications: Suitable for IMUs, INS, missile seekers, UAVs, and robotics. Data Fusion: Combines FOG data with external references to enhance accuracy and stability. Conclusion: FOGs provide high precision and reliability in navigation tasks, with promising future developments across various sectors. Like ring laser gyro, fiber optic gyro has the advantages of no mechanical moving parts, no preheating time, insensitive acceleration, wide dynamic range, digital output and small size. In addition, fiber optic gyro also overcomes the fatal shortcomings of ring laser gyro such as high cost and blocking phenomenon. Fiber optic gyro is a kind of optical fiber sensor used in inertial navigation.Because it has no moving parts – high-speed rotor, called solid state gyroscope. This new all-solid gyroscope will become the leading product in the future and has a wide range of development prospects and application prospects. 1. Fiber optic gyro classification According to the working principle, fiber optic gyroscope can be divided into interferometric fiber optic gyro (I-FOG), resonant fiber optic gyro (R-FOG) and stimulated Brillouin scattering fiber optic gyroscope (B-FOG). At present, the most mature fiber optic gyro is the interferometric fiber optic gyroscope (that is, the first generation of fiber optic gyroscope), which is the most widely used. It uses multi-turn optical fiber coil to enhance SAGNAC effect. A double-beam ring interferometer composed of multi-turn single-mode optical fiber coil can provide high accuracy, but also will inevitably make the overall structure more complicated.Fiber optic gyros are divided into open ring fiber optic gyroscopes and closed loop fiber optic gyros according to the type of loop. Open-loop fiber optic gyro without feedback, directly detect the optical output, save many complex optical and circuit structure, has the advantages of simple structure, cheap price, high reliability, low power consumption, the disadvantage is the input-output linearity is poor, small dynamic range, mainly used as an Angle sensor. The basic structure of an open-loop interferometric fiber optic gyro is a ring dual-beam interferometer. It is mainly used for occasions where the accuracy is not high and the volume is small. 2. Status and future of fiber optic gyroscope With the rapid development of fiber optic gyro, many large companies, especially military equipment companies, have invested huge financial resources to study it. The main research companies for the United States, Japan, Germany, France, Italy, Russia, low and medium precision gyroscope has completed the industrialization, and the United States has maintained a leading position in this area of research.The development of fiber optic gyroscope is still at a relatively backward level in our country. According to the level of development, the gyro development is divided into three echelons: the first echelon is the United States, the United Kingdom, France, they have all the gyro and inertial navigation research and development capabilities; The second tier is mainly Japan, Germany, Russia; China is currently in the third tier. The research of fiber optic gyro in China started relatively late, but with the efforts of the majority of scientific researchers, it has gradually narrowed the gap between us and the developed countries.At present, China’s fiber optic gyro industry chain is complete, and manufacturers can be found upstream and downstream of the industry chain, and the development accuracy of fiber optic gyro has reached the requirements of middle and low accuracy of inertial navigation system. Although the performance is relatively poor, it will not bottleneck like the chip.The future development of fiber optic gyro will focus on the following aspects:(1) High precision. Higher precision is an inevitable requirement for fiber optic gyro to replace laser gyro in advanced navigation. At present, the high precision fiber optic gyro technology is not fully mature.(2) High stability and anti-interference. Long-term high stability is also one of the development directions of fiber optic gyroscope, which can maintain navigation accuracy for a long time under harsh environment is the requirement of inertial navigation system for gyroscope. For example, in the case of high temperature, strong earthquake, strong magnetic field, etc., the fiber optic gyro must also have sufficient accuracy to meet the requirements of users.(3) Product diversification. It is necessary to develop products with different precision and different needs. Different users have different requirements for navigation accuracy, and the structure of the fiber optic gyro is simple, and only the length and diameter of the coil need to be adjusted when changing the accuracy. In this respect, it has the advantage of surpassing mechanical gyro and laser gyro, and its different precision products are easier to achieve, which is the inevitable requirement of the practical application of fiber optic gyro.(4) Production scale. The reduction of cost is also one of the preconditions for fiber optic gyro to be accepted by users. The production scale of various components can effectively promote the reduction of production costs, especially for middle and low precision fiber optic gyro. 3.Summary The zero bias stability of the fiber optic gyroscope F50 is 0.1~0.3º/h, and the zero bias stability of the F60 is 0.05~0.2º/h. Their application fields are basically the same, and can be used in small IMU, INS, missile seeker servo tracking, photoelectric pod, UAV and other application fields. If you want more technical data, please feel free to contact us. GF50 Single-Axis Medium Accuracy Military Standard Fiber Optic Gyroscope   GF60 Single Axis Fiber Gyro Low Power Fiber Optic Gyro Imu Angular Rate for Navigation  

Key Points Product: I3500 GNSS-Aided MEMS INS Key Features: Components: Cost-efficient MEMS IMU, dual-antenna satellite positioning module, magnetometers, and barometer. Function: Provides high-precision navigation data, maintaining performance during GNSS outages. Applications: Suitable for drones, autonomous navigation, surveying, and motion analysis. Inertial Navigation: Combines inertial measurements for position, velocity, and attitude calculation. Conclusion: The I3500 exemplifies the integration of MEMS INS and GNSS, enhancing navigation reliability and accuracy across various sectors.   MINS/GNSS integrated navigation, refers to the fusion of information from both MINS (MEMS INS) and GNSS (Global Navigation Satellite System). This integration combines the strengths of both systems to complement each other and achieve accurate PVA (Position, Velocity, Attitude) results. Classification of MEMS Inertial Navigation Systems After more than 30 years of development, MEMS inertial technology has advanced rapidly and seen wide application. Various practical MEMS inertial devices and MEMS INS have emerged, finding extensive use in fields such as aerospace, maritime, and automotive industries. Tactical-grade MEMS gyroscopes (with bias stability of 0.1°/h to 10°/h, 1σ) and high-precision MEMS accelerometers (with bias stability of 10⁻⁵g to 10⁻⁶g, 1σ) have marked the entry of tactical-grade MEMS INS into the model application stage. Generally, MEMS inertial systems can be classified into three levels: Inertial Sensors Assembly (ISA), Inertial Measurement Unit (IMU), and Inertial Navigation System (INS), as illustrated in Figure 1. Fig.1 Three Levels Of Mems Ins (2) MEMS ISA: Comprised solely of three MEMS gyroscopes and three MEMS accelerometers, it lacks the capability to operate independently. MEMS IMU: Builds on the MEMS ISA by adding A/D converters, mathematical processing chips, and specific programs, enabling it to independently collect and process inertial information. MEMS INS: Further expands on the MEMS IMU by incorporating coordinate transformation, filtering processes, and auxiliary modules, which typically include magnetometers and GNSS receiver boards. Auxiliary sensors like magnetometers are particularly significant in aiding MEMS INS alignment and enhancing performance. The three newly launched MEMS INS (Micro-Magic Inc-Mechanical System Inertial Navigation System) models by Ericco, shown in the image below, are suitable for applications in drones, flight recorders, intelligent unmanned vehicles, roadbed positioning and orientation, channel detection, unmanned surface vehicles, and underwater vehicles. Fig.2 The Three Newly Launched Mems Ins Models By Ericco How GNSS-Aided MEMS INS Works GNSS provides users with all-weather, high-precision absolute position and time information, while inertial navigation systems (INS) offer high short-term resolution and strong autonomy. Their complementary characteristics enhance overall performance: INS can leverage its high short-term accuracy to provide GNSS with more continuous and complete navigation information, while GNSS can help estimate INS error parameters like bias, thus obtaining more precise observations and reducing INS drift. Fig.3 Three Levels Of Mems Ins Specifically, GNSS uses signals from orbiting satellites to calculate position, time, and velocity. As long as the antenna has a line-of-sight connection with at least four satellites, GNSS navigation achieves excellent accuracy. When satellite visibility is obstructed by obstacles like trees or buildings, navigation becomes unreliable or impossible. INS calculates relative position changes over time using angular rate and acceleration information from the inertial measurement unit (IMU). The IMU comprises six complementary sensors arranged on three orthogonal axes. Each axis has an accelerometer and a gyroscope. Accelerometers measure linear acceleration, while gyroscopes measure rotational rate. With these sensors, the IMU can accurately measure its relative motion in 3D space. INS uses these measurements to compute position and velocity. Another advantage of IMU measurements is that they provide angular solutions about the three axes. INS converts these angular solutions into local attitudes (roll, pitch, and yaw), providing this data along with position and velocity. Fig.4 The Inertial Measurement Unit Body Coordinate System Real-Time Kinematic (RTK) is a mature high-precision positioning algorithm of GNSS, capable of achieving centimeter-level accuracy in open environments. However, in complex urban environments, signal obstructions and interferences reduce the ambiguity fixing rate, leading to decreased positioning capability. Therefore, researching GNSS RTK and INS integrated positioning systems is crucial for fields such as autonomous navigation, surveying and mapping, and motion analysis. I3500 newly launched by Micro-Magic Inc is a Cost-efficient GNSS aided MEMS INS with a highly reliable MEMS IMU and a dual-antenna full-system full-band positioning and directional satellite module. It also integrates magnetometers and a barometer, which can calculate the size of the attitude Angle and help the drone navigate to the desired altitude. Conclusion Integrating MEMS Inertial Navigation Systems (INS) with GNSS technology significantly enhances navigation accuracy by combining their strengths. MEMS INS, with its rapid advancement, is now widely used in aerospace, maritime, and automotive industries. GNSS provides precise positioning, while MEMS INS ensures continuous navigation, even during GNSS outages. The I3500 by Micro-Magic Inc exemplifies this integration, offering high-precision navigation data, ideal for autonomous navigation, surveying, and motion analysis. In summary, GNSS and MEMS INS integration revolutionizes navigation by improving accuracy, reliability, and versatility across various applications.   I3500 High Accuracy 3-Axis Mems Gyro I3500 Inertial Navigation System    

Key Points Product: North Finder Inertial Navigation System Key Features: Components: Uses gyroscopes and accelerometers to provide precise inertial measurements for north-seeking functionality. Function: Quickly and accurately determines the north direction in all-weather conditions, independent of external signals. Applications: Suitable for both military and civilian uses requiring autonomous, interference-resistant orientation. Data Processing: Features advanced software for sensor data collection, processing, and attitude error correction. Modularity: Software is modular for ease of development, testing, and maintenance, allowing for flexible system upgrades. The appearance of north finder is an important achievement in the development of inertial navigation technology. It is widely used in military and civilian fields by configuring inertial sensors to form a precision inertial measurement system, which can accurately sense the relevant position parameters of the carrier, and provide various information resources such as coordinate position, orientation and attitude of the carrier with other equipment. North finder is an inertial instrument, it has the general advantages of inertial instruments, that is, the use of inertia working principle, does not rely on external information when working, does not radiate energy to the outside, will not be subjected to enemy interference in the work, will not be subjected to magnetic field substances and other environmental interference, good environmental resistance, in the high and low temperature environment performance superior, is an autonomous orientation indicating system. It can quickly and accurately determine the north in an all-weather environment. In the hardware of north finder, the sensor signal output of gyroscope and accelerometer is filtered, gated and amplified, and the analog signal is converted into digital signal by A/D converter to the control computer of the north seeking system for calculation and processing. The software of the north finder can be said to be the soul of the system, without the control of the software, the hardware in the system is virtually useless and can not play its performance. The software part controls the hardware of the whole system, sets the initial value, collects data regularly, human-computer interaction interface, and provides serial interface and network communication interface to realize the exchange of data with the outside world. The main content of the north finder software includes two parts: one is the management software, which makes the hardware work according to the predetermined program, such as the initialization of each part, the interrupt management in the running process, the communication management between the system and the external connection; The second is the data processing software, which samples the information of each sensor and processes the sampled data to prevent the output of the north finding result. Its main tasks are: 1. System initialization: including the initial position selection of the system, the feedback closing judgment of the gyro, A/D sampling initialization and so on. 2. System transfer control: the software controls the motor to rotate according to the predetermined position. 3. Data processing: A/D sampling and data preprocessing; Attitude matrix calculation and error correction; Display and output, etc. These tasks are intertwined in time and rely on interrupt management to coordinate them. In the design of north finder, we follow the basic principle of modularity, the program is divided into several modules, each module sets a function, and then these modules together to form a whole can complete the specified function. The advantages of developing modules with independent functions and without too much interaction between modules are mainly shown in: first, the software of modular implementation is relatively easy to develop. Second, independent modules are easy to test and maintain, and can be easily modified, replaced or inserted into new modules when needed. Micro-Magic Inc company in the north finder manufacturing has mastered the skilled technology, in the navigation system internal software and hardware, Micro-Magic Inc selection are cost-effective, high-performance inertial components, currently has a new type of north finder different from the traditional north seeker, is our NF2000, if you are interested in this, welcome to communicate with our professional staff.   NF2000 Inertial Navigation System High Precision Fog North Seeker    

Key Points Product: NF1000 Gyro North Finder Key Features: Components: Utilizes a gyroscope and quartz flexible accelerometer in a strap-down system for precise azimuth measurement. Function: Provides real-time, all-weather north seeking and orientation, calculating the azimuth and inclination angle for applications such as directional drilling. Applications: Ideal for military operations, oil and gas exploration, and engineering projects in confined spaces. Compact Design: Size: Φ31.8 x 85 mm, Weight: 400g, offering enhanced portability and adaptability. Performance: Advanced features like inclination compensation and self-alignment ensure accurate, reliable orientation in difficult environments. Conclusion: The NF1000 delivers fast, precise north seeking and orientation, making it a valuable tool for directional drilling, military navigation, and other engineering applications. In military and civilian orientation, north finder is widely used. It can determine the north in static all-weather, all-round, fast and real-time, so as to determine the carrier azimuth, that is, the angle between a reference axis of the carrier and the true north direction, which is used as the azimuth reference for observation, target aiming and navigation system reset. It can also be used as a bearing reference for underground operations such as tunnels and mines in military applications, especially requiring the gyro north finder to achieve fast and accurate orientation in a short time. 1.Basic principles of north finding The north finder uses the gyroscope to calculate the angle between the carrier and the true north direction. This system uses a gyroscope and a quartz flexible accelerometer to form a strap-down system. The sensitive axis of an accelerometer is parallel to the sensitive axis of the gyroscope. The other is along the horizontal plane orthogonal gyro and accelerometer to form an inertial assembly relative to the installation base around the vertical axis according to the command of the control system rotation of the assembly around the vertical axis rotation two positions can be solved to measure the azimuth acceleration of the inertial assembly to compensate for the vertical component of the earth rotation angular velocity. 2.Oil drilling technology Oil drilling and development is a high-investment, high-risk, high-return, technology-intensive, capital-intensive industry, decision-making or operational mistakes will cause huge economic and social losses. With the improvement of the exploration level of oil and gas on land and sea, the types of oil and gas reservoirs have become complicated and diversified, the proportion of low and ultra-low permeability oil and gas reservoirs has increased year by year, and the well depth has developed from shallow and medium deep to deep and even ultra-deep. The types of oil and gas reservoirs are extended from conventional to unconventional. The sedimentary type expanded from continental to Marine. Exploration and development work has entered the stage of low, deep and difficult, which poses new challenges to oil and gas exploitation. In this case, the continuous use of vertical well technology will not meet the needs of modern drilling, so the directional drilling technology came into being. Directional drilling has always been considered “the process and science of deflecting a well in a specific direction in order to drill to a predetermined underground target.” As shown by the drilling directional north finder, azimuth angle and inclination angle are two key parameters for drilling hole positioning. The key performance indexes of gyroscope and accelerometer can be tested and calibrated automatically by using the built gyro north finder software. During drilling construction, the drilling rig arrives at the designated drilling site. According to the designed azimuth and inclination angle, the operator roughly predetermined the orientation and inclination Angle of the drilling rig, and then placed the north finding instrument at the horizontal place near the drilling site for north seeking operation; After the north finding is completed, the north seeker is placed on the guide rail of the rig to display the current rig attitude information (inclination angle and azimuth angle), and then the rig attitude is adjusted until the rig reaches the design angle. According to the problems we encountered in the drilling survey process, we launched a new shaped north finder NF1000, specially for petroleum mining, directional drilling and other engineering applications, it not only achieved a breakthrough in appearance, but also from the volume and weight have been greatly improved, its size is only mm Φ31.8 x85 mm, The weight is 400g, which has achieved a great breakthrough in the traditional inertial products of the North finder series. Its emergence allows more engineers to face more difficult, more limited space monitoring environment. 3.Summary Micro-Magic Inc north seeker uses a strap-down system. For the zero deviation drift and random error of the north finder, Micro-Magic Inc company has carried out many product technical reforms. At present, the latest north seeker NF1000 not only carries out inclination compensation and self-alignment functions, but also can be used in the probe. More limited monitoring space is facilitated. If you are interested in this product, please discuss it with us.   NF1000 Inertial Navigation System High Performance Dynamic MEMS North Seeker