05 August 2025, Volume 24 Issue 3-4
    

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    Academician Column
  • WANG Wei, WU Zhigang
    Navigation and Control. 2025, 24(3-4): 1-12. https://doi.org/10.3969/j.issn.1674-5558.2025.h3.001
    Abstract ( ) Download PDF ( )   Knowledge map   Save
    This article reviews the current research status and development trends of multi-source information fusion and control technologies for bionic aircraft. Firstly, it provides an in-depth overview of the navigation and control mechanisms of insects and birds, elucidating how they integrate multiple sources of information, such as vision, olfaction, and geomagnetism, to achieve effective navigation. The article further analyzes their unique flight perception systems and advanced information fusion feedback control mechanisms. Subsequently, the article examines the state-of-the-art research on multi-source information fusion navigation and control technologies for bionic aircraft, encompassing multi-source information navigation technologies, dynamic modeling of bionic aircraft, motion control and navigation positioning technologies for bionic aircraft, as well as bio-inspired distributed perception-based flight control technologies. Finally, the article outlines potential future directions for the development of navigation and control technologies in bionic aircraft.
  • MEMS Inertial Technology Album
  • LIU Jun, MENG Zhijing, CAO Huiliang, TANG Jun, LI Jie, SHI Yunbo
    Navigation and Control. 2025, 24(3-4): 13-39. https://doi.org/10.3969/j.issn.1674-5558.2025.h3.002
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    Precision-guided munitions(PGMs) have become indispensable components in modern military systems due to their advantages of high strike accuracy, strong penetration capability, and extended operational range. Micro electro mechanical systems(MEMS)-based inertial guidance systems, primarily composed of MEMS accelerometers and MEMS gyroscopes, play a critical role in artillery projectile guidance. Consequently, ensuring the reliable operation of MEMS inertial devices under high-overload environments has emerged as a key research focus for academic institutions and research organizations. In this paper, the requirements and technical challenges of MEMS inertial devices in high-overload environments are systematically outlined, with emphasis on analyzing critical innovations in anti-high-overload technologies and recent advancements in high-overload testing equipment. By summarizing state-of-the-art research domestically and internationally, this paper proposes future development directions for anti-high-overload MEMS inertial devices and test equipment, providing theoretical references and practical guidance to advance this field.
  • FAN Bo, YANG Biao, BU Feng, ZHOU Ming, CHEN Fang
    Navigation and Control. 2025, 24(3-4): 40-50. https://doi.org/10.3969/j.issn.1674-5558.2025.h3.003
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    MEMS inertial sensors, which mainly include MEMS gyroscopes and MEMS accelerometers, are miniature components for navigation, positioning, and attitude measurement. However, the performance is significantly degraded by bias drift arising from structural design, packaging process, environmental fluctuations, and hardware circuits. Therefore, investigating bias drift compensation techniques holds considerable research significance. Firstly, the classification and fundamental principles of MEMS inertial sensors are introduced, and then the primary sources of bias drift are analyzed, including frequency splitting, packaging-induced stress, temperature fluctuations and phase shifts in circuits. The research status of bias drift compensation technology is summarized, mainly covering modal matching, stress compensation, temperature compensation, and phase compensation. The technical advantages and characteristics of each method are systematically discussed. The current research status and future development directions are summarized and discussed, which is of great significance for the advancement of high-precision MEMS inertial sensor technology.
  • ZHANG Chenggang, ZHAO Qiancheng, CUI Jian
    Navigation and Control. 2025, 24(3-4): 51-64. https://doi.org/10.3969/j.issn.1674-5558.2025.h3.004
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    The hermeticity of packaging directly determines the long-term stability and lifespan of MEMS inertial devices. In terms of packaging forms, wafer-level packaging(WLP) has become the mainstream packaging approach for MEMS inertial devices due to its advantages such as compact size, low cost, and high packaging yield compared to device-level packaging. In this paper, recent research progress in hermeticity reliability evaluation for wafer-level packaging of MEMS inertial devices is reviewed, covering parameter measurement and lifespan prediction methods. For key hermetic packaging parameters—including leak rate measurement, internal pressure measurement, and gas composition analysis, their current development status is elaborated in detail, followed by a comparative analysis of their strengths and weaknesses. Finally, methods for predicting the lifespan of MEMS inertial devices are discussed.
  • BAI Bing, LI Cun, SHI Yang, LI Bo, AI Jiabin, ZHI Dian, ZHAO Yulong
    Navigation and Control. 2025, 24(3-4): 65-72. https://doi.org/10.3969/j.issn.1674-5558.2025.h3.005
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    Quartz resonant accelerometers are characterized by high stability and low power consumption, and have become a hot topic of research in the field of inertial measurement. This study addresses critical performance limitations in scale factor and stability through systematic modeling and theoretical analysis, establishing a structural framework for resonant accelerometers and proposing an enhanced differential dual-opposed-pendulum configuration. Utilizing multiphysics-coupled finite element analysis for global parameter optimization, optimal chip dimensions are determined, wet-etching and precision manufacturing are implemented to develop a metal-integrated prototype. Experiment data shows that the prototype has a measurement range of ±3 g, dimensions of Φ25 mm×15 mm, a scale factor of 348.33 Hz/g, zero bias stability of 57.78 μg, and scale factor stability of 8.42 ppm. Test results indicate that this miniaturized device combines high scale factor, small measurement range, and high stability, offering a new inertial measurement solution for precision aerospace engineering applications such as deep space exploration.
  • ZHOU Lincai, FENG Lihui, ZENG Yongchao, DONG Liquan
    Navigation and Control. 2025, 24(3-4): 73-82. https://doi.org/10.3969/j.issn.1674-5558.2025.h3.006
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    Due to the limitation of materials and manufacturing process, MEMS gyroscope is susceptible to temperature, and the resulting temperature drift severely limits the measurement accuracy and further application of MEMS gyroscope. In this paper, a temperature compensation method for MEMS gyroscope based on signal decomposition and neural network is proposed. In this method, random noise is filtered by signal denoising based on interpolated complementary ensemble local mean decomposition with adaptive noise, and then a dynamic neural network model of gated recurrent unit is established to compensate for temperature drift, which can effectively reduce noise and improve the learning accuracy of temperature drift model. The verification experiment results show that, in the temperature range of -40℃ to 70℃, the proposed method reduces the bias instability of the MEMS gyroscope from 1.0406 (°)/h to 0.1228 (°)/h, and the angle random walk from 4.8309 (°)/h1/2 to 0.1587 (°)/h1/2, which improves the temperature performance of the MEMS gyroscope effectively.
  • LI Zhe, LIU Jun, LIU Xiaolan, KUANG Pengju, CHEN Kai, HUANG Yongjun
    Navigation and Control. 2025, 24(3-4): 83-91. https://doi.org/10.3969/j.issn.1674-5558.2025.h3.007
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    Micro-gyroscopes, as core sensors for angular velocity measurement, are critical for intelligent navigation and precision guidance. To address the dual problems of noise suppression improvements in traditional MEMS gyroscopes and the compatibility challenges between cavity optomechanical sensors and MEMS processes, this paper proposes a novel integrated architecture by synergistically designing a double-decoupled cavity optomechanical system and an anti-collapse ridge waveguide. Firstly, the double-decoupled structure reduces mechanical coupling between drive and sense modes, enhancing resistance to environmental vibration. Secondly, an innovative ridge waveguide is designed on a SOI substrate, where a 500 nm silicon layer is retained with 400 nm etched on each side, protecting the silica layer from collapse. The process requires only EBL and dry etching to release the proof mass, significantly simplifying the fabrication process. Finite element simulations and numerical calculations validate the performance: the cavity optomechanical system achieves an angular measurement sensitivity of 318.7 mV/[(°)/s] and an angle random walk of 0.16 (°)/h1/2, while the ridge waveguide exhibits 82.9% transmission efficiency and 46.3% end-face coupling efficiency at 1550 nm. This study provides a scalable technical pathway for high-precision micro-gyroscopes based on cavity optomechanical systems, with reduced process complexity, and showing promising potential in navigation and control applications.
  • MA Yukun, LI Haonan, LIU Yunfeng, HAN Fengtian
    Navigation and Control. 2025, 24(3-4): 92-100. https://doi.org/10.3969/j.issn.1674-5558.2025.h3.008
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    In order to improve the engineering application accuracy of the navigation-grade MEMS resonant beam accelerometer based on the glass-silicon micromachining process, this paper introduces the technical solutions for suppressing the temperature drift, nonlinearity, and vibration and shock-induced errors of the accelerometer, as well as the performance test results of the developed prototypes. The temperature drift suppression methods composing of low-temperature drift structural design, low thermal-stress packaging process, experimental modeling and compensation are described firstly. The experimental results show that the mean stabilities of the bias and scale factor are 4.3 μg and 1.4 ppm over the temperature range from -40 ℃ to 60 ℃, respectively. A refinement of the acceleration measurement with squared difference of two resonant frequencies is then introduced with a reduced scale factor nonlinearity of 25.2 ppm within the measurement range of ±20 g. Finally, an effective suppression of the first-order mode interference of the sensing structure is accomplished using active damping design, which remarkably enhances the anti-vibration and shock performance of the prototypes experimentally.
  • REN Rui, CHEN Fang, FANG Erxi, XU Dacheng, LU Zhenghao
    Navigation and Control. 2025, 24(3-4): 101-110. https://doi.org/10.3969/j.issn.1674-5558.2025.h3.009
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    MEMS gyroscopes are crucial inertial devices used to measure the angular velocity of moving objects, particularly capacitive-sensitive MEMS gyroscopes, which are widely applied in consumer electronics and defense applications due to their small size, high precision, and high integration. To achieve high-precision angular velocity detection, an MEMS gyroscope drive circuit with self-clocking functionality is designed and implemented. Firstly, the dynamic capacitance signals from the MEMS gyroscope are converted into analog voltage signals through a capacitive readout circuit, which are then transformed into digital signals via a bandpass Σ-Δ modulator. The digital signal, after processing (including amplitude stabilization PID control), feeds back the drive voltage to the MEMS gyroscope, exciting it to resonate at a stable amplitude and frequency. The system clock is generated by a phase-locked loop using self-locking technology. The entire circuit is designed using a 0.13 μm CMOS process. Under typical simulation conditions, after the MEMS gyroscope drive circuit is closed-looped, the phase-locked loop locking time, or frequency stabilization time, is 4.32 ms, and the amplitude stabilization time of the drive circuit is 154.1 ms. The output amplitude of the capacitive readout circuit can be stabilized at different preset amplitudes according to the control word of the PID amplitude control loop.
  • WANG Shiqiu, GAO Yang, QI Yonghong, ZHANG Xiaopeng, ZHAO Minghui, ZHU Yunfei, LIU Chuang, FENG Rui, WEI Xueyong
    Navigation and Control. 2025, 24(3-4): 111-125. https://doi.org/10.3969/j.issn.1674-5558.2025.h3.010
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    Accelerometer is a key device for inertial navigation, vibration monitoring in aerospace and national defense equipment. It may face high-impact overload during its working process, resulting in functional failure. In order to meet the requirements for the impact overload resistance of MEMS accelerometers in high-impact overload scenarios, a high overload resistance capacitive accelerometer is designed in this paper, which adopts the “rigid + flexible” overload resistance structure limit scheme, with the characteristics of high rigidity, strong reliability of rigid limit structure, and flexible nonlinear limit structure is not easy to collapse, can absorb the impact energy. The structural damping and modal separation ratio are analyzed, and the key dimensions are comprehensively optimized to further improve the out-of-plane impact resistance and detection sensitivity. The performance calibration and drop hammer experiment show that the encapsulated sensitive chip has a measurement range of ±20 g, a resolution of 0.5 mg, a sensitivity amplitude linearity of 0.067%, and can resist the in-plane and out-of-plane impact acceleration of 3500 g, which is a good combination of performance and impact resistance characteristics.
  • JIA Jia, AI Shiwei, SONG Ziqi, GAO Shixuan, GAO Yang
    Navigation and Control. 2025, 24(3-4): 126-134. https://doi.org/10.3969/j.issn.1674-5558.2025.h3.011
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    As the most common rate measurement mode in micro electro mechanical system(MEMS) gyroscope applications, the nonlinearity error of scale factor significantly restricts the widening of gyroscope application scenarios. Aiming at the conventional FTR excitation method of constant DC with variable AC, which is limited by the mutual constraints of signal update rate and noise, the FTR excitation method of constant AC with variable DC is proposed. Firstly, the FTR rate measurement control loop model based on the constant DC with variable AC excitation method is constructed to analyze the phase relationship between the excitation and pickoff signals of the two operating modes for the FTR rate gyroscope, and then a 90° phase-shift circuit is designed to convert the stable amplitude signals at the pickoff end of the drive mode into the FTR excitation signals. Finally, the performance comparison of the two excitation methods is carried out. The experiment results show that compared with the traditional constant DC with variable AC excitation method, the constant AC with variable DC excitation method reduces the scale factor nonlinearity error by 82.84% and the asymmetry error by 93.93%, and the change in bias instability and angular random walking for both excitation methods is 7.32% and 17.57%, respectively.
  • ZHANG Xin, LIU Wei, WANG Lei, LI Chong
    Navigation and Control. 2025, 24(3-4): 135-143. https://doi.org/10.3969/j.issn.1674-5558.2025.h3.012
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    With the increase of gyroscope quality factor, the bandwidth performance of MEMS gyroscope restricts its development in high-precision and high-dynamic fields. This paper focuses on the ultra-low bandwidth issue of ultra-high Q MEMS gyro. Firstly, modeling of the MEMS gyroscope is done. Then, a bandwidth extension algorithm is designed based on the traditional force-rebalance control loop, and the noise model of the system after bandwidth extension is established. The main noise source is analyzed and optimized. Test results show that the designed algorithm and optimization are suitable for ultra-high Q MEMS gyroscope with a Q-factor of 416k. Compared with the traditional PI control scheme, the method can increase the bandwidth from 1.5 Hz to 40 Hz while maintaining the same level of bias instability, and the bias instability is 0.4832 (°)/h. This method achieves bandwidth expansion and resolves the mutual restriction between bandwidth and noise performance.
  • HAO Zhiwen, WANG Lei, CUI Wanxin, FU Qiang, YIN Liang
    Navigation and Control. 2025, 24(3-4): 144-151. https://doi.org/10.3969/j.issn.1674-5558.2025.h3.013
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    The MEMS accelerometer is an inertial sensor based on silicon micromachining technology, which is used to measure acceleration information. The temperature characteristics of its interface circuit determine the performance of the entire sensor. In this paper, three temperature characteristic optimization schemes for the zero output drift and hysteresis characteristics of the MEMS accelerometer interface ASIC chip under full temperature conditions are proposed. Firstly, an array capacitor compensation scheme is proposed to solve the temperature characteristic problems caused by operational amplifier offset and capacitor mismatch leading to zero offset. Secondly, a low-temperature-drift bandgap reference source is designed to provide carrier level and common mode level. Finally, a third-order fitting digital temperature compensation scheme is designed to further improve the output accuracy. The chip is tested, and the final measured results show that within the temperature range of -45℃ to 85℃, the peak-to-peak drift of the three axes analog output for the MEMS accelerometer is 8 mg, 12 mg, and 11 mg respectively, which can be reduced to within 2.8 mg after compensation, and the temperature hysteresis error is within 2.5 mg. The peak-to-peak drift of the three axes digital output is 50 mg, 22 mg, and 18 mg respectively, which can be reduced to within 6 mg after compensation, and the temperature hysteresis error is within 0.5 mg. This paper provides technical support and theoretical basis for the design of low-temperature-drift accelerometers.
  • LU Yue, LI Zhaohan, LU Hongbin, WANG Jiaqi, CHANG Yuchun
    Navigation and Control. 2025, 24(3-4): 152-159. https://doi.org/10.3969/j.issn.1674-5558.2025.h3.014
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    The readout circuit, serving as the front-end module of a sensor system, is a critical component that determines the overall performance of the system. To meet the low-noise readout requirements of MEMS capacitive gyroscopes, an integrated readout circuit incorporating a drive loop and a detection circuit was designed in 180 nm CMOS process. Based on the actual structure of the gyroscope, a gyroscope sensor model for co-simulation with CMOS readout circuits is constructed using Verilog-A. Leveraging chopper technology, a low-noise capacitive readout circuit is designed, achieving adjustable gain while reducing low-frequency noise. An integrated design approach is applied to the demodulation and filtering modules of the detection circuit, achieving a streamlined architecture. Simulation results demonstrate that at a chopping frequency of 250 kHz, the output noise of the readout circuit is 50.5 μV, with a minimum detectable capacitance of 20 aF and a dynamic range of 94 dB.
  • XU Xiaoyun, ZHOU Yi, YU Zhuolin, ZHOU Tong
    Navigation and Control. 2025, 24(3-4): 160-166. https://doi.org/10.3969/j.issn.1674-5558.2025.h3.015
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    MEMS gyroscopes exhibit significant temperature-dependent performance variations due to their micro-mechanical structures and the thermally sensitive characteristics of silicon-based materials. To address this issue, a temperature compensation method based on Bayesian-optimized adaptive segmentation polynomial fitting is proposed. Overcoming the limitations of conventional polynomial fitting in temperature interval partitioning and parameter optimization, the proposed approach incorporates three key technical innovations. An adaptive, data-driven temperature range segmentation using K-means clustering; the simultaneous optimization of optimal polynomial order and regularization coefficients within each temperature interval through Bayesian optimization; and the integration of L2 regularization to effectively suppress model overfitting while enhancing generalization capability. Experimental results demonstrate substantial performance improvement for the MEMS gyroscope across a wide temperature range (-40 ℃ to 60 ℃), with bias stability enhanced from 1.2 (°)/s to 0.047 (°)/s and bias instability reduced from 0.0023 (°)/s to 0.0016 (°)/s.
  • ZHANG Lemin, XU Jie, HE Yandong, WANG Jianpeng, GAO Naikun, LIU Guowen, LIU Fumin
    Navigation and Control. 2025, 24(3-4): 167-176. https://doi.org/10.3969/j.issn.1674-5558.2025.h3.016
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    Quadrature coupling is a key factor affecting the output of gyroscopes. During the startup of dual closed-loop MEMS gyroscopes, loop control parameters significantly impact the output stabilization time. Experiments show that increasing the quadrature loop integration parameter KIQ and aligning the detection demodulation phase with the actual phase of the sense axis enables the gyroscope to achieve zero bias stabilization within 30 ms after startup. However, under high and low temperatures, variations in the sensing modal quality(Q) factor cause the detection demodulation phase to deviate from the optimal value, prolonging the startup stabilization time. To tackle this, a control method combining a fixed quadrature stiffness correction configuration with a real-time closed-loop is proposed. This method configures a fixed quadrature correction bias to counteract inherent quadrature coupling, reducing the quadrature coupling deviation at the initial startup moment and significantly shortening the closed-loop stabilization time. As a result, the gyroscope can startup rapidly and reach a stable output state within 30 ms, even when the KIQ parameter is relatively small or the detection demodulation phase error is large, over a temperature range of -45℃ to 85℃, with markedly improved startup characteristics.
  • ZHANG Qiukun, WANG Lei, JIANG Likun, YIN Liang, FU Qiang
    Navigation and Control. 2025, 24(3-4): 177-184. https://doi.org/10.3969/j.issn.1674-5558.2025.h3.017
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    Resonant accelerometer is a new type of acceleration sensor, which has the advantages of small size, low power consumption and high accuracy. In this paper, the closed-loop self-excited driving technology of resonant accelerometer is studied, and the establishment and simulation of the electrical model for the sensitive structure is completed by analyzing the working principle of resonant accelerometer. On the basis of completing the design for the front-stage transimpedance detection unit and automatic gain control unit including low-noise operational amplifier and nonlinear multiplier, the closed-loop self-excited driving circuit is constructed and verified by simulation. The simulation results show that the closed-loop self-excited driving circuit completes the establishment of the driving signal within 100 ms, and the PI controller output has an average value of 3.076 V and a fluctuation amplitude of 209.2 μV. This technology provides support for the integrated design of resonant accelerometer driving circuit.
  • LYU Bing, LI Zhaohan, LU Hongbin, WANG Jiaqi, CHANG Yuchun
    Navigation and Control. 2025, 24(3-4): 185-192. https://doi.org/10.3969/j.issn.1674-5558.2025.h3.018
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    In this paper, an open-loop detection circuit for a capacitive MEMS accelerometer based on chopping technology is designed. The circuit is intended to convert the acceleration signal sensed by the accelerometer into an electrical signal that can be processed by subsequent circuits. Utilizing a fully differential architecture, the circuit enhances common-mode interference rejection capability, while effectively suppressing circuit noise through the application of the chopping technology. This open-loop detection circuit works in coordination with the sensitive mechanical structure of the capacitive MEMS accelerometer. Through simulation under the 0.18 μm BCD process, an acceleration detection range of ±6 g is achieved, with a sensitivity reaching 0.54 V/g and a bandwidth of 1.35 kHz. In the frequency range of 1 kHz~1.35 kHz, the circuit output noise is 10.59 μV, the equivalent output resolution is 19.61 μg, the output dynamic range is 109.71 dB, and the total power consumption of the circuit is 2.94 mW.
  • ZHANG Jingwu, ZHOU Yi, YU Zhuolin, ZHOU Tong
    Navigation and Control. 2025, 24(3-4): 193-201. https://doi.org/10.3969/j.issn.1674-5558.2025.h3.019
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    With the development of MEMS gyroscope-related error technologies, phase error has become a significant factor limiting their performance as high-precision, high-stability inertial devices. To address issues such as quadrature error coupling into angular rate output caused by phase error, the phase error in control circuits is mathematically modeled and derived. Subsequently, a parabolic interpolation method is proposed to identify and compensate for phase error by continuously updating the search interval through iteration to locate the minimum drive voltage amplitude, thereby achieving identification and compensation objectives. Compared with traditional methods, the approach proposed is more efficient and well-adapted to the closed-loop control of gyroscopes. Experimental results demonstrate that after phase error compensation, the drive amplitude is minimized, the quadrature coupling error in angular rate output is eliminated, and the scale factor performance is improved. While the angle random walk remains unchanged, bias instability is reduced significantly from 0.762 (°)/h to 0.117 (°)/h. This method effectively resolves the issues of slow identification and insufficient compensation accuracy for phase errors.
  • Others
  • ZHU Mengqi, MA Jie, ZHANG Peizhe, SHANG Lunyan, YU Wenkai, ZHANG Anning
    Navigation and Control. 2025, 24(3-4): 202-219. https://doi.org/10.3969/j.issn.1674-5558.2025.h3.020
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    Coded aperture snapshot spectral imaging (CASSI) technology enables efficient synergistic acquisition of spatial and spectral information through single-shot compressive imaging. It overcomes the limitations of traditional spectral imaging techniques, which rely on scanning mechanisms and incur high costs on data storage and transmission. This paper systematically reviews the research progress in CASSI technology, focusing on its hardware architecture, theoretical models, and reconstruction algorithms. The hardware design section explores the iterative optimization of system architecture and the impact of coded aperture design on imaging performance. The theoretical model section analyzes the physical modeling methods of single dispersion CASSI and summarizes optimization paths for the theoretical models, highlighting the importance of optical error correction in improving reconstruction accuracy. The reconstruction algorithms section talks about the performance bottlenecks of traditional algorithms introducing recent breakthroughs in deep-learning based reconstruction methods. While deep learning has demonstrated significant advantages in complex scene reconstruction and computational efficiency, challenges related to interpretability, data dependency, and hardware compatibility remain to be addressed. Finally, the paper discusses the future development trends of CASSI technology across multiple dimensions, including system architecture, hardware innovations, algorithm frameworks, and embedded terminal development, aiming to promote its widespread applications in fields such as aerospace remote sensing, biomedicine, deep space exploration, and real-time navigation.
  • PEI Ziyan, LI Yong, YANG Bo, WANG Qiwei
    Navigation and Control. 2025, 24(3-4): 220-227. https://doi.org/10.3969/j.issn.1674-5558.2025.h3.021
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    Frequency modulated continuous wave(FMCW) laser ranging technology has great potential for application in the fields of satellite formation flight, spacecraft rendezvous and docking, with its high-precision ranging and speed measuring capability. However, the inherent nonlinearity of the laser leads to the broadening of the signal spectrum, which restricts the improvement of measurement accuracy. In order to solve this problem, a nonlinear correction technology and device based on semiconductor butterfly laser are proposed, which generates specific phase points as sampling trigger clock by beating the auxiliary interference optical path to realize resampling of the measurement signal, thus suppressing the signal spectrum broadening and realizing the nonlinear correction of the laser. The nonlinear correction technology is verified experimentally by setting up optical device, and the repeated measurement accuracy is less than 20 cm within 100 m measurement range. The experiment results show that this technology can effectively restrain the signal spectrum broadening caused by nonlinearity on the basis of system miniaturization, and improve the stability of distance measurement.
  • ZHANG Zhongqi, WANG Tianshun, ZHANG Tianyu, AN Hualiang, DENG Yicheng, WANG Xuefeng
    Navigation and Control. 2025, 24(3-4): 228-234. https://doi.org/10.3969/j.issn.1674-5558.2025.h3.022
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    The relaxation time of atomic vapor cell is a key parameter for the performance of NMRG, and the long relaxation time is crucial for the enhancement of NMRG precision. Aiming at the problem of relaxation time measurement in NMRG, based on the BLOCH equation, a formula is derived to describe the relationship between the phase difference of nuclear spin advance signal and the driving magnetic field, as well as the transverse relaxation time of atomic vapor cell. A new approach through the orthogonal phase detection method is proposed to measure the transverse relaxation time measurement, and finally the feasibility is experimentally verified, which provides a new method for the measurement of transverse relaxation time of atomic vapor cell, and lays a technological foundation for the evaluation of the performance of atomic vapor cell.