Table of Content

21 April 2023, Volume 43 Issue 2

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Research Progress on Quantum Hall Resistance of Low Magnetic Field

WANG Zhong-wei, WANG Ning, CAI Jian-zhen, LI Shuang-yu, HUANG Xiao-ding

2023, 43(2):  1-6.  doi:10.12060/j.issn.1000-7202.2023.02.01

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The establishment of resistance standard based on Quantum Hall Effect (QHE) is a cutting-edge metrology technology,which is the highest standard to define the resistance in the world.The core component is Quantum Hall Resistance(QHR) which need 10 T in traditional GaAs QHR samples.The magnet will be difficult and expensive to made.With the development of QHR,it is urgent to find methods to develop QHR samples of low magnetic field.Three schemes for reproducing QHE under low magnetic field,including GaAs,graphene and ferromagnetic topological materials are introduced.The advantages and disadvantages of three schemes are analyzed from the dimensions of magnetic field,temperature,measurement uncertainty and technology maturity,to provide theoretical reference for the development of QHR in low magnetic field for China.

Design for Sinusoidal Dynamic Torque Sensor Calibration Device Based on Braking Excitation

JIN Ran, ZHU Yong-xiao, ZHANG Wang, WU Quan, KUANG Xian-tao

2023, 43(2):  7-13.  doi:10.12060/j.issn.1000-7202.2023.02.02

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In order to solve the problem that static torque calibration cannot fully meet the use requirements at present,a sinusoidal dynamic torque sensor calibration device based on braking excitation is designed.In the system of the calibration device,the braking torque excitation part is composed of servo motor,magnetic particle brake and some connecting parts,the inertia disk is used as the load,and the angular acceleration of the inertia disk is measured with a circular grating.Through this calibration device,the dynamic torque is traced to the inertia and angular acceleration parameters.Through building simulation model and analysis,the principle of the device is explained.The developed calibration device prototype is used to carry out excitation test,and the test results show that the design scheme is feasible.

Design of Portable Intelligent Electrical Parameters Measurement and Calibration Device

DENG Xue-feng, ZHANG Yu

2023, 43(2):  14-19.  doi:10.12060/j.issn.1000-7202.2023.02.03

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Design scheme of portable intelligent verification device is proposed for the on-site measurement guarantee of special electrical parameter detection equipment supporting weapons and equipment,and the strict technical requirements for calibration environment and portable measurement standards.The automatic control of the on-site verification microenvironment,as well as the design content of the board-level high-precision electrical measurement standard source and standard meter is realized.The detection equipment display image recognition software is compiled by which the intelligent on-site verification and calibration of the equipment electrical detection equipment could be realized with the program-controlled switch trigger device,which has a good prospect of popularization and application.

Simulation of Automatic Calibration Process for Thrust of Liquid Rocket Engines

ZHAO Heng, ZHU Zi-huan

2023, 43(2):  20-26.  doi:10.12060/j.issn.1000-7202.2023.02.04

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Aiming at the requirement of high accuracy of in-situ calibration of liquid rocket engines,an automatic force loading device based on hydraulic transmission with servo motor as the execution component was introduced,and the structure and working principle of the system was expounded.The mathematical model of the system was established,the simulation model of the system was built through Matlab and AMEsim,and the fuzzy PID controller was designed on the basis of analyzing the accuracy and stability of thrust loading.The simulation results show that the designed force value loading system can complete the accurate force value loading,the (0~6) kN force value loading time is less than 30 s,and the maximum error of the loading force indication value is ±0.05%,which meets the calibration force value loading requirements.It is proved that the introduction of the fuzzy PID control algorithm into the force loading system can effectively compensate the uncertain disturbance in the system and enhance the robustness of the system.

Uncertainty Evaluation of Field Calibration and Measurement Results of Security Monitoring System’s Pressure Parameters

KOU Qiong-yue, ZHOU Jian-tong, ZHOU Rui

2023, 43(2):  27-31.  doi:10.12060/j.issn.1000-7202.2023.02.05

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The Security monitoring system’s field pressure parameter measurement system is established based on the field pressure measurement of pressure transmitter，signal conversion and transmission,and pressure terminal display.The on-line calibration method of security monitoring system’s pressure parameters is introduced.The mathematical model of measurement error is established.The source of uncertainty of the system’s pressure measurement results is analyzed.The main contribution components of the uncertainty of the field system calibration measurement results are given by the experimental verification analysis.

Studies on 3D Reconstruction Camera Based on Monocular Vision

WEN Ju-ying, SHI Wei-ke, NI Yue

2023, 43(2):  32-35.  doi:10.12060/j.issn.1000-7202.2023.02.06

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In order to meet the needs of aircraft to obtain multi-dimensional space images when performing on-orbit service,the 3D reconstruction camera technology based on monocular vision was put forward,and 3D reconstruction of space objects was realized by using voxel coloring principle based on brightness method.The ground experiment was set up,and various experiments simulating circular orbit and elliptical orbit were designed.It was verified that the high-resolution 3D reconstructed image of the target could be realized in the state of accompanying flight within 200 m,and the reconstruction accuracy was 0.105 m,which laid a technical foundation for identifying the characteristic parts of the space target.

A Geometric Parameter Measurement Method of Aerospace Engine Assembly Process Based on Photogrammetry Technology

WANG Jing-long, QIANG Wei, PAN Zhao-yi, ZHANG Quan-ming, TONG Jia-wei

2023, 43(2):  36-41.  doi:10.12060/j.issn.1000-7202.2023.02.07

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At present,the measurement method of geometric parameters in the assembly process of aerospace engines in China is that professionals operate Laser Tracker System or Electronic Total System to measure point by point,which has the disadvantage of low measurement efficiency.An efficient measurement method of geometric parameters of aerospace engine assembly process based on photogrammetry technology is proposed.The measurement principle of this measurement method is introduced,and then the measurement objectives of each measurement link of this method are explained in detail.Finally,the system accuracy of industrial digital photogrammetry technology in such applications is calculated through measured data,which proves the feasibility of this measurement method.

Research on Measuring Method of Magnetic Induction Switch Based on Multi-purpose Meter

YANG Jing, WU Chun-chan, HAO Zhi-kun, MA Min, WANG Li-juan

2023, 43(2):  42-45.  doi:10.12060/j.issn.1000-7202.2023.02.08

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The working principle and electrical performance of magnetic induction switch are studied,and a method of measuring the electrical performance of magnetic induction switch based on multi-purpose meter is proposed to measure the performance index of magnetic induction switch under no-load and loading conditions.The test verification shows that the electrical performance of magnetic switch can be effectively measured based on the multi-meter method，and the uncertainty of measurement results meets the requirements of the specifications of magnetic induction switch products.

An Angle Calculation Method of Unsupported Aiming 

LI Fa-dong, SONG Xiao-yan, GAO Ming-jie, CHEN Wei

2023, 43(2):  46-50.  doi:10.12060/j.issn.1000-7202.2023.02.09

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In the process of inertial group aiming,the inertial group measuring unit and the optical tube collimation deviation angle measurement unit are completed under different measuring coordinates,and the direct synthesis of aiming angle will lead to large coupling error.Aiming at this problem,a method for solving the aiming angle of inertia group is presented,and the transformation relationship between each coordinate system is obtained by matrix method.The attitude angle of the output reference in the geographical coordinate system is obtained and the azimuth angle of the target prism is obtained by aiming calculation.

Optical Hybrid Sensor Based on EFPI-FBG Structure

LIU Dong-dong, WANG Wei, WANG Kun-peng, LIU Bin

2023, 43(2):  51-57.  doi:10.12060/j.issn.1000-7202.2023.02.10

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An EFPI-FBG fiber hybrid sensor based on an extrinsic Fabry-Perot interferometer (EFPI) and a fiber Bragg grating (FBG) structure is studied to measure pressure and temperature simultaneously.Fused silica is used as the pressure-sensitive material，and femtosecond laser welding technology is used to package the sensor head.The working principle of the sensor is analyzed，fabricated and tested in detail.The results show that the sensitivity of the sensor in the range of 0.8 MPa is about -0.729 μm/MPa，and the temperature sensitivity in the range of 50℃~200℃ is 0.009 nm/℃.The marimum permissible error of the sensor is±4.12%FS.The investigated EFPI-FBG hybrid sensor is expected to be applied in fields requiring pressure-temperature dual-parameter measurement.

Design of Linear Regulated Power Supply for Sensors with Multiple Protection

LIU Yi, GAO Bing-tao, LI Chun-yan, LU Chao

2023, 43(2):  58-63.  doi:10.12060/j.issn.1000-7202.2023.02.11

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To solve the compatibility problem of AC and DC power supply of the sensor,A linear regulated power supply suitable for the sensor is designed,which can be powered by both 24 VDC and 220 VAC.At the same time,multiple protection functions of input overvoltage protection,output overvoltage protection and output current limiting protection are possessed,which greatly improves the universality and safety of the sensor.The working principle of each part of the power supply,as well as the optimization and adjustment methods for specific parameters,are described from the aspects of theoretical design and simulation analysis.Finally,the correctness of the design is verified by experimental tests.

Exploration and Prospect of Smart Rocket Data Acquisition Technology#br#

ZHANG Xia, YAN Ning, HAO Yu-xing, WANG Xiao-ding, XU Zhen-liang

2023, 43(2):  64-70.  doi:10.12060/j.issn.1000-7202.2023.02.12

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With the introduction of the concept of smart rocket，new challenges are posed to the data acquisition technology of launch vehicle.There are still problems in the launch vehicle，such as limited measurement field，low measurement accuracy and reliability，poor scalability and low tailorability.Based on the analysis of the current situation and problems of data acquisition summarizes the trend of data acquisition toward intelligence，networking，light weight and high efficiency is summarized.Combined with the trend research and judgment，the overall framework of data acquisition for a rocket is given，and the advantages，disadvantages and application scenarios of various key technologies such as structural health monitoring，fiber optic sensor network，and cable free are compared and analyzed.The application prospects of fiber grating sensor network，wireless sensor network，magnetic resonance wireless energy transmission and other technologies in smart rocket data acquisition are proposed.

Design of Evaluation System for Performance of Wireless Sensor Network#br#

LU Chao, WANG Kuo-chuan, ZHOU Ming-rui, XUE Kai-bing, XU Hui, SUN Fu-tao

2023, 43(2):  71-75.  doi:10.12060/j.issn.1000-7202.2023.02.13

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Aiming at the diversity of wireless sensor network performance evaluation indicators and the lack of unified standards,an overall evaluate system to assess the performance of wireless sensor network is designed.The system includes spectrum analysis subsystem,current acquisition subsystem and wireless sensor monitoring subsystem.The air spectrum,working current,network packet loss and throughout characteristics are acquired,counted and analyzed,and the performance evaluation of wireless sensor networks is realized.

Design of Self-test System for Batch-produced Spacecraft

YANG Tong-zhi, DANG Jian-cheng, LIU Ting-yu, AN Tian-qi, WANG Ji-ye

2023, 43(2):  76-82.  doi:10.12060/j.issn.1000-7202.2023.02.14

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Rapid integrated test，regular rapid inspection after batch storage and rapid inspection before launch have become urgent production problems for batch-produced spacecraft.The traditional spacecraft integrated test mode has the problems of low test efficiency，cumbersome test modification and deployment，high test cost，long test cycle and difficult in-depth product internal exploration，which cannot well meet the needs of rapid development and test of batch-produced spacecraft.In view of the above problems，starting from the design of spacecraft testability and self-test，the design method of spacecraft self-test function unit，self-test communication interaction mode and self-test diagnosis model based on structural model and behavior model is studied，and the construction of layered spacecraft self-test system is designed.The self-test process is quickly scheduled through bus，which improve the rapid maintenance capability to meet the needs of rapid inspection of batch-produced spacecraft.

Research on Design of Distributed Aero Vehicles’ Telemetry and Control Data Real-time Analysis System

LI Zhi, CHU Hou-bin, CAI Fei-hua, JIANG Yue, ZHANG Li-ye

2023, 43(2):  83-87.  doi:10.12060/j.issn.1000-7202.2023.02.15

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The traditional aero vehicles’ telemetry and control data analysis system cannot meet the requirements of real-time and integrity for data analysis at the same time.A distributed aero vehicles’ telemetry and control data real-time analysis system is studied.The distributed system is coupled by multiple processors,which has the advantages of resource sharing,high reliability,and high-speed parallel computing.The requirements of real-time and integrity for data analysis can be met at the same time,and verified by experiments.

Double Dimensions Polarity Checking Method and Application for Launch-vehicle Systems

DONG Yu-hong, WEI Kang, LI Mao, HUANG Hui, LIU Bing

2023, 43(2):  88-91.  doi:10.12060/j.issn.1000-7202.2023.02.16

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The design and assembly correctness of launch-vehicle’s interface polarity concern the flight success or failure.To make sure the polarity is correct during the launch-vehicle’s designing and production-manufacturing process,a method that can be used in a closed-loop double dimensions way for checking the correctness of design polarity and assembly polarity is presented.The method was used to check and confirm the new generation large scale launch-vehicle’s interface polarity in a closed-loop way,which strengthens the closed-loop management and control both of the polarity designing states and of the product’s assembly process,and which makes sure of the designing correctness and adaptability of the interface polarity.

Design and Hardware Implementation of Rocket Borne Image Acquisition System Based on Network Architecture

WANG Xu, ZHAO Zi-lun, RONG Gang, CHANG Xi, ZHANG Cong

2023, 43(2):  92-96.  doi:10.12060/j.issn.1000-7202.2023.02.17

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The image acquisition system is responsible for monitoring and recording the video information of several important points on the carrier.A general image acquisition system on board the rocket based on network architecture is introduced,which is responsible for collecting high-definition images and storing them losslessly in an image compressor.The high-definition images are compressed and transmitted to the ground through telemetry.Due to the limited bandwidth,the image information transmitted down can be switched in real time.At the same time,real-time access to image information on the rocket is supported through the network and post image data retrieval function,and guarantee for evaluating the working state of the arrow or analyzing the fault is provided.