Applications

Key Points Product: Pure Inertial Navigation System (INS) Based on IMU Key Features: Components: Uses MEMS accelerometers and gyroscopes for real-time measurement of acceleration and angular velocity. Function: Integrates initial position and attitude data with IMU measurements to calculate real-time position and attitude. Applications: Ideal for indoor navigation, aerospace, autonomous systems, and robotics. Challenges: Addresses sensor errors, cumulative drift, and dynamic environment impacts with calibration and filtering methods. Conclusion: Provides precise positioning in challenging environments, with robust performance when combined with auxiliary positioning systems like GPS.   Pure inertial data (IMU) position calculation is a common positioning technology. It calculates the target object in real time by using the acceleration and angular velocity information obtained by the Inertial Measurement Unit (IMU), combined with the initial position and attitude information. s position. This article will introduce the principles, application scenarios and some related technical challenges of pure inertial navigation data position calculation. 1. Principle of position calculation based on pure inertial navigation data Pure inertial navigation data position calculation is a positioning method based on the principle of inertial measurement. IMU is a sensor that integrates an accelerometer and a gyroscope. By measuring the acceleration and angular velocity of the target object in three directions, the position and attitude information of the target object can be derived. In pure inertial navigation data position calculation, it is first necessary to obtain the initial position and attitude information of the target object. This can be achieved by introducing other sensors (such as GPS, compass, etc.) or manual calibration. The initial position and attitude information play an important role in the solution process. They provide a starting point so that the acceleration and angular velocity data measured by the IMU can be converted into the actual displacement and attitude changes of the target object. Then, based on the acceleration and angular velocity data measured by the IMU, combined with the initial position and attitude information, numerical integration or filtering algorithms can be used to calculate the position of the target object in real time. The numerical integration method obtains the speed and displacement of the target object by discretizing and integrating the acceleration and angular velocity data. The filtering algorithm uses methods such as Kalman filtering or extended Kalman filtering to filter the data measured by the IMU to obtain the position and attitude estimation of the target object. 2. Application scenarios of pure inertial navigation data position calculation Position calculation based on pure inertial navigation data is widely used in many fields. Among them, indoor navigation is one of the typical application scenarios for pure inertial navigation data position calculation. In indoor environments, GPS signals are usually unable to reach, and pure inertial navigation data position calculation can use the data measured by IMU to achieve accurate positioning of target objects indoors. This is of great significance in fields such as autonomous driving and indoor navigation robots. Pure inertial navigation data position calculation can also be used in the aerospace field. In aircraft, since the GPS signal may be interfered at high altitudes or far from the ground, pure inertial navigation data position calculation can be used as a backup positioning method. It can calculate the position and attitude of the aircraft in real time through the data measured by the IMU, and provide it to the flight control system for attitude stabilization and flight path planning. 3. Challenges of position calculation using pure inertial navigation data Position calculation based on pure inertial navigation data still faces some challenges in practical applications. First of all, the IMU sensor itself has errors and noise, which will affect positioning accuracy. In order to improve the solution accuracy, the IMU sensor needs to be calibrated and error compensated, and an appropriate filtering algorithm is used to reduce the error. Position calculation based on pure inertial navigation data is prone to cumulative errors during long-term movements. Due to the characteristics of the integration operation, even if the measurement accuracy of the IMU sensor is high, long-term integration will lead to the accumulation of positioning errors. In order to solve this problem, other positioning means (such as GPS, visual sensors, etc.) can be introduced for auxiliary positioning, or a tightly coupled inertial navigation method can be used. Position calculation based on pure inertial navigation data also needs to consider the impact of the dynamic environment. In a dynamic environment, the target object may be affected by external forces, causing deviations in the data measured by the IMU. In order to improve the robustness of the solution, the effects of dynamic environments can be compensated through methods such as motion estimation and dynamic calibration. Summarize Pure inertial data position calculation is a positioning method based on IMU measurement. By acquiring acceleration and angular velocity data, combined with initial position and attitude information, the position and attitude of the target object are calculated in real time. It has wide applications in indoor navigation, aerospace and other fields. However, pure inertial navigation data position calculation also faces challenges such as calibration error, cumulative error and dynamic environment. In order to improve the solution accuracy and robustness, appropriate calibration methods, filtering algorithms and auxiliary positioning methods need to be adopted. The MEMS IMU independently developed by Micro-Magic Inc has relatively high accuracy, such as UF300A and UF300B, which have higher accuracy and are navigation-grade products. If you want to know more about IMU, please contact our professional technicians as soon as possible.   UF300 High-precision Miniaturized Inertial Measurement Unit Fiber Optic Inertial Measurement Unit   -

Key Points Product: Integrated Optical Chip-Based Fiber Optic Gyroscope Key Features: Components: Uses an integrated optical chip combining functions like luminescence, beam splitting, modulation, and detection on a lithium niobate thin film (LNOI) platform. Function: Achieves “multi-in-one” integration of non-sensitive optical path functions, reducing size and production costs while enhancing polarization and phase modulation for accurate gyroscope performance. Applications: Suited for positioning, navigation, attitude control, and oil well inclination measurement. Optimization: Further improvements in polarization extinction ratio, emission power, and coupling efficiency can enhance stability and accuracy. Conclusion: This integrated design paves the way for miniaturized, low-cost fiber optic gyroscopes, meeting the growing demand for compact and reliable inertial navigation solutions. With the advantages of all-solid state, high performance and flexible design, fiber optic gyroscope has become the mainstream inertial gyroscope, which is widely used in many fields such as positioning and navigation, attitude control and oil well inclination measurement. Under the new situation, the new generation of inertial navigation system is developing towards miniaturization and low cost, which puts forward higher and higher requirements for the comprehensive performance of gyroscope such as volume, accuracy and cost. In recent years, hemispherical resonator gyro and MEMS gyro have developed rapidly with the advantage of small size, which has a certain impact on the fiber optic gyro market. The main challenge of traditional optical gyro volume reduction is the reduction of optical path volume. In the traditional scheme, the optical route of fiber optic gyro is composed of several discrete optical devices, each of which is realized based on different principles and processes and has independent packaging and pigtail. As a result, the device volume under the prior art is close to the reduction limit, and it is difficult to support the further reduction of the volume of fiber optic gyro. Therefore, it is urgent to explore new technical solutions to realize the effective integration of different functions of the optical path, greatly reduce the volume of the gyro optical path, improve the process compatibility, and reduce the production cost of the device. With the development of semiconductor integrated circuit technology, integrated optical technology has gradually achieved breakthroughs, and the feature size has been continuously reduced, and it has entered the micro and nano level, which has greatly promoted the technical development of integrated optical chips, and has been applied in optical communication, optical computing, optical sensing and other fields. The integrated optical technology provides a new and promising technical solution for the miniaturization and low cost of fiber optic gyro optical path. 1 Integrated optical chip scheme design 1.1 Overall Design The traditional optical routing light source (SLD or ASE), fiber taper coupler (referred to as “coupler”), Y branch waveguide phase modulator (referred to as “Y waveguide modulator”), detector, sensitive ring (fiber ring). Among them, the sensitive ring is the core unit of the sensitive Angle rate, and its volume size directly affects the precision of the gyro.We propose a hybrid integrated chip, which consists of a light source component, a multifunctional component and a detection component through hybrid integration. Among them, the light source part is an independent component, which is composed of SLD chip, isolation collimation component and peripheral components such as heat sink and semiconductor cooler. The detection module consists of a detection chip and a transresistance amplifier chip. The multifunctional module is the main body of hybrid integrated chip, which is realized based on lithium niobate thin film (LNOI) chip, and mainly includes optical waveguide, mode-spot conversion, polarizer, beam splitter, mode attenuator, modulator and other on-chip structures. The beam emitted by the SLD chip is transmitted into the LNOI waveguide after isolation and collimation.The polarizer deflects the input light, and the mode attenuator attenuates the non-working mode. After the beam splitter splits the beam and modulator modulates the phase, the output chip enters the sensitive ring and the sensitive angular rate. The light intensity is captured by the detector chip, and the generated photoelectric output flows through the transresistance amplifier chip to the demodulation circuit.The hybrid integrated optical chip has the functions of luminescence, beam splitting, beam combining, deflection, modulation, detection, etc. It realizes the “multi-in-one” integration of non-sensitive functions of gyro optical path. Fiber optic gyroscopes depend on the sensitive Angle rate of coherent beam with high degree of polarization, and the polarization performance directly affects the precision of gyroscopes. The traditional Y-waveguide modulator itself is an integrated device, which has the functions of deflection, beam splitting, beam combining and modulation. Thanks to material modification methods such as proton exchange or titanium diffusion, Y-waveguide modulators have extremely high deflection ability. However, thin film materials need to take into account the requirements of size, integration and deflection ability, which can not be met by material modification methods. On the other hand, the mode field of thin film optical waveguide is much smaller than that of bulk material optical waveguide, resulting in changes in electrostatic field distribution and electrorefractive index parameters, and the electrode structure needs to be redesigned. Therefore, the polarizer and modulator are the core design points of the “all-in-one” chip. 1.2 Specific Design The polarization characteristics are obtained by structural bias, and an on-chip polarizer is designed, which consists of curved waveguide and straight waveguideAgreed. The curved waveguide can limit the difference between the transmission mode and the non-transmission mode, and achieve the effect of mode bias. The transmission loss of the transmission mode is reduced by setting the offset.The transmission characteristics of optical waveguide are mainly affected by scattering loss, mode leakage, radiation loss and mode mismatch loss. Theoretically, the scattering loss and mode leakage of small curved waveguides are small, which are mainly limited by the late process. However, the radiation loss of curved waveguides is inherent and has different effects on different modes. The transmission characteristics of the curved waveguide are mainly affected by the mode mismatch loss, and there is mode overlap at the junction of the straight waveguide and the curved waveguide, resulting in a sharp increase in mode scattering. When the light wave is transmitted into the polarized waveguide, due to the existence of curvature, the effective refractive index of the light wave mode is different in the vertical direction and the parallel direction, and the mode restriction is different, which results in different attenuation effects for TE and TM modes.Therefore, it is necessary to design the bending waveguide parameters to achieve the deflection performance. Among them, bending radius is the key parameter of bending waveguide. The transmission loss under different bending radius and the loss comparison between different modes are calculated by FDTD eigenmode solver. The calculated results show that the loss of the waveguide decreases with the increase of the radius at small bending radius. On this basis, the relationship between polarization property (ratio of TE mode to TM mode) and bending radius is calculated, and the polarization property is inversely proportional to bending radius. The determination of the bending radius of the on-chip polarizer should consider the theoretical calculation, the simulation results, the technological capability and the actual demand.The finite difference Time domain (FDTD) is used to simulate the transmitted light field of the on-chip polarizer. The TE mode can pass through the waveguide structure with low loss, while the TM mode can produce obvious mode attenuation, so as to obtain polarized light with high extinction ratio. By increasing the number of cascaded waveguides, the extinction ratio of the polarization-extinction ratio can be further improved, and better than -35dB polarization extinction ratio performance can be obtained on the micron scale. At the same time, the structure of the waveguide on chip is simple, and it is easy to realize the low-cost fabrication of the device. 2 Integrated optical chip performance verification The LNOI main chip of the integrated optical chip is an unsliced sample engraved with multiple chip structures, and the size of a single LNOI main chip is 11mm×3mm. The performance test of integrated optical chip mainly includes the measurement of spectral ratio, polarization extinction ratio and half-wave voltage.Based on the integrated optical chip, a gyroscope prototype is built, and the performance test of the integrated optical chip is carried out. Static zero bias performance of a gyro prototype based on integrated optical chip in a non-vibration isolated foundation at room temperature. set-basedThe gyroscope formed into optical chip has a long time drift in the start-up segment, which is mainly caused by the start-up characteristic of light source and the large loss of optical link. In the 90min test, the zero bias stability of the gyroscope is 0.17°/h (10s). Compared with the gyroscope based on traditional discrete devices, the zero bias stability index deteriorates by an order of magnitude, indicating that the integrated optical chip needs to be further optimized. Main optimization directions: improve the polarization extinction ratio of the chip, improve the luminous power of the light-emitting chip, improve the end-coupling efficiency of the chip, and reduce the overall loss of the integrated chip. 3 Summary We propose an integrated optical chip based on LNOI, which can realize the integration of non-sensitive functions such as luminescence, beam splitting, beam combining, deflection, modulation and detection. The zero bias stability of the gyro prototype based on the integrated optical chip is 0.17°/h. Compared with the traditional discrete devices, the performance of the chip still has a certain gap, which needs to be further optimized and improved. We preliminarily explore the feasibility of fully integrated optical path functions except ring, which can maximize the application value of integrated optical chip in gyro, and meet the development needs of miniaturization and low cost of fiber optic gyro. 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: MEMS Gyroscope Borehole North Finding System Key Features: Components: Employs MEMS gyroscopes for north-seeking, featuring compact size, low cost, and high shock resistance. Function: Uses an improved two-position method (90° and 270°) and real-time attitude correction for precise north determination. Applications: Optimized for downhole drilling systems in complex underground environments. Data Fusion: Combines gyroscope data with local magnetic declination corrections for true north calculation, ensuring accurate navigation during drilling. Conclusion: Delivers precise, reliable, and independent north-finding capabilities, ideal for borehole and similar applications. The new MEMS gyroscope is a kind of inertial gyro with simple structure, which has the advantages of low cost, small size and resistance to high shock vibration. The inertial north seeking gyroscope can complete the independent north seeking all weather without external restrictions, and can achieve fast, high efficiency, high precision and continuous work. Based on the advantages of MEMS gyro, MEMS gyro is very suitable for downhole north finding system. This paper describes the segmented fusion research of MEMS gyro borehole north finding system. The following will introduce the improved two-position north finding, the scheme of MEMS gyro borehole fusion north finding and the determination of north finding value. Improved two-position north finding The static two-position north seeking scheme generally selects 0° and 180° as the initial and end positions of north seeking. After repeated experiments, the gyro output angular velocity is collected, and the final north seeking Angle is obtained by combining the local latitude. The experiment adopted the two-position method every 10°, collected 360° of the turntable, and a total of 36 sets of data were collected. After averaging each set of data, the measured solution values were shown in Figure 1 below. Figure 1 Fitting curve of gyroscope output from 0 to 360° As can be seen from Figure 1, the output fitting curve is a cosine curve, but the experimental data and angles are still small, and the experimental results lack accuracy. Repeated experiments were conducted, and the Angle of acquisition was extended to 0~660°, and the two-position method was conducted every 10° from 0°, and the data results were shown in Figure 2. The trend of the image is cosine curve, and there are obvious differences in data distribution. At the crest and trough of the cosine curve, the distribution of data points is scattered and the degree of fit to the curve is low, while at the place with the highest slope of the curve, the fit of data points to the curve is more obvious. Figure 2 Fitting curve of gyroscope output at two positions 0~660° Combined with the relationship between azimuth and gyro output amplitude in Figure 3, it can be concluded that the data fit is better when the two-position north finding is adopted at 90° and 270°, indicating that it is easier and more accurate to detect the north Angle in the east-west direction. Therefore, 90°, 270°, instead of 0° and 180°, are used in this paper as the two-position north seeking gyro output acquisition positions. Figure 3 Relation between azimuth and gyro output amplitude MEMS gyroscope borehole fusion northfinding When MEMS gyro is used in borehole north finding system, it is faced with complex environment, and there will be variable attitude Angle with drill bit drilling, so the solution of north Angle becomes much more complicated. In this section, based on the improvement of the two-position north finding scheme in the previous section, a method is proposed to obtain the attitude Angle by controlling rotation according to the output data information, and the included Angle with the north is obtained. The specific flow chart is shown in Figure 4. The MEMS gyroscope is transmitted to the upper computer through RS232 data interface. As shown in Figure 4, after the initial north Angle is obtained by searching north at the two positions, the next step of drilling while drilling is carried out. After receiving the north seeking instruction, the drilling work stops. The attitude Angle output by MEMS gyro is collected and transmitted to the upper computer. The rotation of the borehole north seeking system is controlled by the attitude Angle information, and the roll Angle and pitch Angle are adjusted to 0. The heading Angle at this moment is the Angle between the sensitive axis and the magnetic north direction. In this scheme, the Angle between MEMS gyroscope and true north direction can be obtained in real time by collecting attitude Angle information. Figure 4 Fusion north finding flow chart The north seeking value is determined In the fusion north finding scheme, the improved two-position north finding was performed on the MEMS gyroscope. After the north finding was completed, the initial north position was obtained, the heading Angle θ was recorded, and the initial attitude state was (0,0,θ), as shown in Figure 5(a). When the bit is drilling, the attitude Angle of the gyroscope changes, and the roll Angle and pitch Angle are regulated by the rotary table, as shown in Figure 5(b). As shown in Figure 5(b), when drilling the bit, the system receives the attitude Angle information of the attitude instrument, and needs to judge the sizes of roll Angle γ ‘and pitch Angle β’, and rotate them through the rotation control system to make them turn to 0. At this time, the output heading Angle data is the Angle between the sensitive axis and the magnetic north direction. The Angle between the sensitive axis and the true north direction should be obtained according to the relationship between the magnetic north and the true north direction, and the true north Angle should be obtained by combining the local magnetic declination Angle. The solution is as follows: θ’=Φ-∆φ In the above formula, θ ‘drill bit and the true north direction Angle, ∆φ is the local magnetic declination Angle, Φ is the drill bit and magnetic north Angle. Figure 5 Change of initial and drilling attitude Angle The north seeking value is determined In this chapter, the north finding scheme of MEMS gyroscope underground north finding system is studied. Based on the two-position north finding scheme, an improved two-position north finding scheme with 90° and 270° as starting positions is proposed. With the continuous progress of MEMS gyroscope, MEMS north-seeking gyroscope can achieve independent north finding, such as MG2-101, its dynamic measurement range is 100°/s, can work in the environment of -40 ° C ~+85 ° C, its bias instability is 0.1°/hr, and the angular velocity random walk is 0.005°/√hr. I hope you can understand the north finding scheme of MEMS gyroscope through this article, and look forward to discussing professional issues with you.   MG502 MEMS Gyroscope MG502    

Key Points Product: Pure Inertial Navigation System (INS) Based on IMU Key Features: Components: Uses MEMS accelerometers and gyroscopes for real-time measurement of acceleration and angular velocity. Function: Integrates initial position and attitude data with IMU measurements to calculate real-time position and attitude. Applications: Ideal for indoor navigation, aerospace, autonomous systems, and robotics. Challenges: Addresses sensor errors, cumulative drift, and dynamic environment impacts with calibration and filtering methods. Conclusion: Provides precise positioning in challenging environments, with robust performance when combined with auxiliary positioning systems like GPS.   The law of instrument constant drift with temperature of a gyro theodolite is a complex phenomenon, which involves the interaction of multiple components and systems within the instrument. Instrument constant refers to the measurement reference value of the gyro-theodolite under specific conditions. It is crucial to ensure measurement accuracy and stability. Temperature changes will cause the drift of instrument constants, mainly because the differences in thermal expansion coefficients of materials cause changes in the instrument structure, and the performance of electronic components changes with temperature changes. This drift pattern is often nonlinear because different materials and components respond differently to temperature. In order to study the drift of the instrument constants of a gyro theodolite with temperature, a series of experiments and data analysis are usually required. This includes calibrating and measuring the instrument at different temperatures, recording changes in instrument constants, and analyzing the relationship between temperature and instrument constants. Through the analysis of experimental data, the trend of instrument constants changing with temperature can be found, and an attempt can be made to establish a mathematical model to describe this relationship. Such models can be based on linear regression, polynomial fitting, or other statistical methods and are used to predict and compensate for drift in instrument constants at different temperatures. Understanding the drift of the instrument constants of a gyro theodolite with temperature is very important to improve measurement accuracy and stability. By taking corresponding compensation measures, such as temperature control, calibration and data processing, the impact of temperature on instrument constants can be reduced, thereby improving the measurement performance of the gyro theodolite. It should be noted that the specific drift rules and compensation methods may vary depending on different gyro theodolite models and application scenarios. Therefore, in practical applications, corresponding measures need to be studied and implemented according to specific situations. The study of the drift pattern of instrument constants of gyro theodolite with temperature usually involves monitoring and analyzing the performance of the instrument under different temperature conditions. The purpose of such research is to understand how changes in temperature affect the instrument constants of a gyro theodolite and possibly find a way to compensate or correct for this temperature effect. Instrumental constants generally refer to the inherent properties of an instrument under specific conditions, such as standard temperature. For gyro theodolite, instrument constants may be related to its measurement accuracy, stability, etc. When the ambient temperature changes, the material properties, mechanical structure, etc. inside the instrument may change, thus affecting the instrument constants. To study this drift pattern, the following steps are usually required: Select a range of different temperature points to cover the operating environments a gyroscopic theodolite may encounter.Take multiple directional measurements at each temperature point to obtain sufficient data samples.Analyze the data and observe the trend of instrument constants as a function of temperature.Try to build a mathematical model to describe this relationship, such as linear regression, polynomial fitting, etc.Use this model to predict instrument constants at different temperatures and possibly develop methods to compensate for temperature effects. A mathematical model might look like this: K(T) = a + b × T + c × T^2 + … Among them, K(T) is the instrument constant at temperature T, and a, b, c, etc. are the coefficients to be fitted. This kind of research is of great significance for improving the performance of gyro theodolite under different environmental conditions. It should be noted that specific research methods and mathematical models may vary depending on specific instrument models and application scenarios. Summarize The law of instrument constant drift with temperature of a gyro theodolite is a complex phenomenon, which involves the interaction of multiple components and systems within the instrument. Instrument constant refers to the measurement reference value of the gyro-theodolite under specific conditions. It is crucial to ensure measurement accuracy and stability. Temperature changes will cause the drift of instrument constants, mainly because the differences in thermal expansion coefficients of materials cause changes in the instrument structure, and the performance of electronic components changes with temperature changes. This drift pattern is often nonlinear because different materials and components respond differently to temperature. In order to study the drift of the instrument constants of a gyro theodolite with temperature, a series of experiments and data analysis are usually required. This includes calibrating and measuring the instrument at different temperatures, recording changes in instrument constants, and analyzing the relationship between temperature and instrument constants. Through the analysis of experimental data, the trend of instrument constants changing with temperature can be found, and an attempt can be made to establish a mathematical model to describe this relationship. Such models can be based on linear regression, polynomial fitting, or other statistical methods and are used to predict and compensate for drift in instrument constants at different temperatures. Understanding the drift of the instrument constants of a gyro theodolite with temperature is very important to improve measurement accuracy and stability. By taking corresponding compensation measures, such as temperature control, calibration and data processing, the impact of temperature on instrument constants can be reduced, thereby improving the measurement performance of the gyro theodolite. It should be noted that the specific drift rules and compensation methods may vary depending on different gyro theodolite models and application scenarios. Therefore, in practical applications, corresponding measures need to be studied and implemented according to specific situations. The study of the drift pattern of instrument constants of gyro theodolite with temperature usually involves monitoring and analyzing the performance of the instrument under different temperature conditions. The purpose of such research is to understand how changes in temperature affect the instrument constants of a gyro theodolite and possibly find a way to compensate or correct for this temperature effect. Instrumental constants generally refer to the inherent properties of an instrument under specific conditions, such as standard temperature. For gyro theodolite, instrument constants may be related to its measurement accuracy, stability, etc. When the ambient temperature changes, the material properties, mechanical structure, etc. inside the instrument may change, thus affecting the instrument constants. To study this drift pattern, the following steps are usually required: Select a range of different temperature points to cover the operating environments a gyroscopic theodolite may encounter.Take multiple directional measurements at each temperature point to obtain sufficient data samples.Analyze the data and observe the trend of instrument constants as a function of temperature.Try to build a mathematical model to describe this relationship, such as linear regression, polynomial fitting, etc.Use this model to predict instrument constants at different temperatures and possibly develop methods to compensate for temperature effects. A mathematical model might look like this: K(T) = a + b × T + c × T^2 + … Among them, K(T) is the instrument constant at temperature T, and a, b, c, etc. are the coefficients to be fitted. This kind of research is of great significance for improving the performance of gyro theodolite under different environmental conditions. It should be noted that specific research methods and mathematical models may vary depending on specific instrument models and application scenarios.   MG502 MEMS Gyroscope MG502    

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    

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: 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: 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