05 April 2025, Volume 24 Issue 2

    

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Academician Column
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  Research on Biomimetic Multi-source Navigation Mechanism and Information Fusion Technology

  WANG Wei, WU Zhigang

  Navigation and Control. 2025, 24(2): 1-12. https://doi.org/10.3969/j.issn.1674-5558.2025.02.001

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  This article explores the current state of bionic multi-source navigation mechanisms and information fusion technologies, with the goal of offering fresh insights and approaches for advancing multi-source autonomous navigation technologies. At the beginning, the article examines the limitations of today's navigation systems and highlight why multi-source information fusion is essential. Next, the article focuses on how animals use multi-source information fusion for navigation, including their strategies, methods of information integration, sensory systems, and neural mechanism. Animals are remarkable in their ability to combine various sensory inputs for complex environmental awareness and precise navigation. The article also discusses bio-inspired multi-source navigation information fusion technologies, such as fusion models, algorithms, and bionic computing frameworks. The visual navigation mechanisms and strategies of insects can serve as valuable inspiration for designing efficient and intelligent autonomous navigation systems. Finally, the article anticipates future research directions and emphasizes the importance of gaining deeper insights into animal navigation mechanisms and developing bio-inspired navigation algorithms.
Summary
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  Development and Review of Foreign Inertial Technology in 2024

  SONG Lijun, GAN Shurong, SU Yan, YUE Yazhou, SHEN Yupeng, JIANG Bo

  Navigation and Control. 2025, 24(2): 13-26. https://doi.org/10.3969/j.issn.1674-5558.2025.02.002

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  Inertial technology is widely used in navigation, positioning, stable attitude and direction control of various carriers such as the sea, the land, the air, the space, and the electricity, and has become an indispensable sensitive source for dynamic autonomous perception in emerging warfare modes. By reviewing the literature of inertial technology related conferences such as the 2024 IEEE International Symposium on Inertial Sensors and Systems, DGON Inertial Sensors and Systems Symposium and IEEE 37th International Conference on Micro Electro Mechanical Systems (MEMS), as well as the dynamic information disclosed by relevant institutions in the field of inertial technology, the current development status of inertial instruments and inertial navigation systems (INS) in the market, including optical gyroscopes, MEMS gyroscopes, hemispherical resonant gyroscopes HRGs, accelerometers, and quantum inertial sensors are reviewed, summarized, and concluded. And the development trend in the field of inertial technology is analyzed and prospected.
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  A Review of Research on Underwater Biological Navigation Behaviors

  LIU Xiaochen, ZHANG Linying, WANG Xuanyi, DI Hang, LI Hanyuan, SHEN Chong, TANG Jun, LIU Jun

  Navigation and Control. 2025, 24(2): 27-47. https://doi.org/10.3969/j.issn.1674-5558.2025.02.003

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  In recent years, underwater navigation technology has garnered increasing attention for its potential applications in deep-sea exploration and underwater operations. However, traditional navigation methods face certain limitations in complex underwater environments. In contrast, marine organisms exhibit remarkable adaptability and precise navigation capabilities, showcasing unique advantages in survival and localization within such challenging conditions. In this paper, a comprehensive review of the navigation mechanisms for eight categories of underwater organisms is provided. The processes through which these organisms perceive, acquire, and process multidimensional information are thoroughly examined, including magnetic, electric, acoustic, visual, chemical, and gravitational/inertial cues, thereby uncovering the biological principles underlying their navigation behaviors. Furthermore, how these mechanisms can inspire advancements in underwater biomimetic navigation technology is explored in this paper. Finally, the limitations and challenges in current research on biological navigation behaviors are summarized and the future directions are discussed, aiming to provide theoretical foundations and technical support for the optimization and application of underwater biomimetic navigation technologies.
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  Development Status and Prospects of High-precision Quartz Resonant Accelerometer

  LI Bo, ZHAO Yulong, JIAO Jian, DONG Xinyu, LI Cun, BAI Bing

  Navigation and Control. 2025, 24(2): 48-68. https://doi.org/10.3969/j.issn.1674-5558.2025.02.004

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  Inertial navigation technology relies on the inertial measurement device in the inertial navigation system to determine the spatial position and attitude of the carrier, which can provide reliable navigation accuracy in the satellite rejection environment. As the key core device of the inertial navigation system, the performance accuracy of the accelerometer directly affects the positioning and guidance accuracy of the inertial navigation system. The resonant accelerometer based on the force-frequency principle of quartz resonator has the characteristics of high-precision, small-size, low-cost and frequency signal output, which has attracted the attention of relevant research institutions at home and abroad. In this paper, the latest research progress of quartz resonant accelerometer is reviewed, the development status of quartz resonant accelerometer is summarized, and its future development trend is prospected.
Navigation and Guidance
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  A Method to Improve the Accuracy of Inertial Guidance Based on Error Feedback Correction

  WEI Zongkang, ZHONG Huimin, WANG Erwei

  Navigation and Control. 2025, 24(2): 69-75. https://doi.org/10.3969/j.issn.1674-5558.2025.02.005

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  The error equation under the earth coordinate system of the launch point is a nonlinear multivariate cross-chain equation, and a simplified scheme is adopted to solve the error coefficients of the guidance tool in engineering. In this paper, for the problem of mismatch between the velocity environment function and the telemetry velocity error caused by the approximate linearization of the simplified error model, a method to improve the accuracy of inertial guidance based on error feedback correction is proposed. Firstly, a high-order error model of inertial measurement system is established, in which there are 60 error coefficients in the error model of gyroscope and accelerometer, and then the attitude, velocity and position error equations based on the earth coordinate system of the launching point are given, and the simplified ambient function is derived according to the linear model and the computation method of its problems is summarized. Secondly, the attitude, velocity and position error feedback is utilized to correct and compensate the velocity error, and a new velocity environment function is obtained. Finally, the least squares method is used to solve the error coefficients of the guidance tool and set the insignificant terms to zero to compensate the inertial guidance telemetry observations, and the telemetry velocity error compensated by using the environment function based on the error feedback correction has a smaller mean and standard deviation than that compensated by using the simplified environment function calculation, which shows that the method proposed in this paper has some application value.
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  A Spacecraft Navigation Algorithm Based on the Shadow Edges of Solar Array

  GUO Jinrong, ZHU Dongyue, ZHANG Yongxing, FANG Chuanxin, WEN Kangkang, LIU Qi

  Navigation and Control. 2025, 24(2): 76-84. https://doi.org/10.3969/j.issn.1674-5558.2025.02.006

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  During the landing process of spacecraft for asteroid exploration, due to solar array power generation or to avoid image navigation difficulties, the small solar incidence angle results in the spacecraft’s shadow appearing in the navigation images, affecting navigation accuracy. To address this issue, a navigation algorithm based on the shadow edge features of the solar array for spacecraft is proposed. Firstly, the shadow edge features are extracted, and equations are constructed using the geometric relationship between the shadow shape and size and the spacecraft’s attitude and altitude to calculate the spacecraft’s attitude and altitude. Secondly, the obtained attitude and altitude are used to calculate the inter-frame rotation matrix and scaling factor, the current image is rotated, scaled, and interpolated to obtain the image to be matched, and the horizontal component of the spacecraft’s translation is calculated through template matching. Finally, a simulation platform is built using Unity3D for simulation verification. The results show that under the possible influence of noise, as the spacecraft’s altitude decreases, the position error and attitude error continuously decrease, with the final position error within 0.5 m and the attitude error within 0.2°.
Sensors and Actuators
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  Research and Implementation of Parallel Acquisition System for Sensor Array

  JIANG Haomiao, CHEN Du, BAI Haile, LI Gang, LUO Xiaoliang, WEN Guangjun, HUANG Yongjun

  Navigation and Control. 2025, 24(2): 85-93. https://doi.org/10.3969/j.issn.1674-5558.2025.02.007

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  The efficacy of the inertial sensor array is contingent upon the correlation between the sensors. The asynchronous acquisition time between the sensors represents a significant limiting factor in the accuracy of the measurements. To enhance the precision of measurements obtained from a consumer inertial sensor array, a parallel transmission bus data acquisition system is devised. This system employs a shared clock and data line to minimize the discrepancy in acquisition time between sensors. The impact of varying designs on the performance of inertial sensor arrays is evaluated, employing precision indexes such as zero bias stability and Allan variance. The experimental results demonstrate that the sensor array is capable of reducing random errors, such as zero bias stability and angle random walk. Furthermore, the parallel bus mode has been shown to enhance the zero bias stability of the sensor by approximately 28% and the angle random walk by approximately 10%. The parallel bus design offers a viable approach to augmenting the number of sensors in the array, thereby enhancing the practical utility of the inertial sensor array.
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  Design of SiP Circuit for Navigation Signal Processing

  DUAN Yuhe, ZHENG Lihua, WANG Lu, LI Lei

  Navigation and Control. 2025, 24(2): 94-102. https://doi.org/10.3969/j.issn.1674-5558.2025.02.008

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  Navigation signal processing system is an important part of navigation system, which not only needs to have fast signal processing ability and high stability, but also to realize miniaturization and lightweight to meet the needs of sea, land, air and space equipment. In response to the various requirements, the navigation signal processing microsystem circuit based on SiP technology is developed by using high-density integration process and advanced system in packaging (SiP) technology. The internal integration of high capacity storage resource packaging (including FPGA, NOR Flash and multiple DDR3 chips) is realized by adopting fully domestic components. The size is reduced to 26.15 mm×18.45 mm, which is only 7% of the original board area; and the weight is 7.5 g, which is 45% of discrete devices. The top is covered with a high thermal conductivity shaped heat dissipation cover, which improves the mechanical performance of the circuit and heat dissipation capacity. When used with various kinds of data collection front-ends, the circuits can realize rapid coding and decoding of navigation signals, algorithm acceleration, high-speed signal type conversion, comprehensive information processing, high-speed communication and other functions, and meet the needs of miniaturization and lightweight.
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  Polarization Stability of Circular Polarization Maintaining Fiber for Resonant Fiber Optic Gyroscope

  LI Suolan, YANG Zhendong, ZHANG Yiran, DOU Yufei, DONG Hao

  Navigation and Control. 2025, 24(2): 103-110. https://doi.org/10.3969/j.issn.1674-5558.2025.02.009

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  In recent years, much research attention has been paid on resonant fiber optic gyroscope(RFOG). As an important inertial navigation sensor, RFOG has advantages of lightweight and high stability. However, the optical effects in the fiber ring resonator(FRR), including scattering and polarization mode crosstalk, limit the development of RFOG and become a core and urgent problem for researchers to solve. In this paper, the polarization stability of the fiber optic resonator has been researched in depth both theoretically and experimentally. Firstly, theoretical analysis has been made on the polarization noise in RFOG and the suppression effect of polarization noise by circular polarization maintaining fiber. Then, the temperature stability of circular polarization maintaining fiber resonators and polarization maintaining fiber(PMF) resonators are compared, and the drift of the intrinsic polarization phase differences for PMF and circular polarization maintaining fiber under temperature changes are simulated. Finally, a phase change acquisition experiment of the resonator with temperature is designed, which experimental results show that the resonant cavity of the circular polarization maintaining fiber is 5.496 rad, and the resonant cavity of the PMF is 663.65 rad. Compared to the PMF resonant cavity, the polarization stability of the resonant cavity using a circular fiber under the same conditions has been improved by 121.79 times. A new approach of solving the polarization noise problem in RFOG is provided in this paper, which lays an important foundation for the practical application of circular polarization maintaining fiber in RFOG.
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  Research on the Technology of Interferometric Fiber Optic Gyroscope Employing Multifunctional Integrated Optical Chip

  SUO Xinxin, YU Haicheng, FENG Wenshuai, FAN Tao, WANG Teng

  Navigation and Control. 2025, 24(2): 111-118. https://doi.org/10.3969/j.issn.1674-5558.2025.02.010

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  A novel interferometric fiber optic gyroscope (I-FOG) based on a “four-in-one” multifunctional integrated optical chip and micro polarization-maintaining photonic-crystal fiber (PM-PCF) coil is proposed. The “four-in-one” multifunctional integrated optical chip integrates super-luminescent diode light source, couplers, thin-film lithium niobate (TFLN) modulator and photodiode detector employing a hybrid integration technology. To obtain a high sensitivity effect and minimize the I-FOG as much as possible, a type of 60 μm/100 μm ultra-thin diameter PM-PCF is customized to wind the interference ring, and a high-accuracy integrated I-FOG prototype with the volume of Φ30 mm is achieved. It experimentally demonstrates a smooth bias stability of 0.23 (°)/h(1σ)at the integration time of 10 s, with an angle random walk (ARW) of 0.012 (°)/h^1/2 and a scale factor nonlinearity of 2.83×10^-5 over the range of ±100 (°)/s at room temperature. It also shows a smooth bias stability of 0.51 (°)/h (1σ) at the integration time of 10 s over the temperature range from -30~60 ℃. Compared with conventional I-FOG with discrete photo-electric devices, the I-FOG proposed has both small volume and high accuracy, which has unique advantages for application in the field of new-type tactical weapons, unmanned systems and other fields.