Table of Content

15 April 2012, Volume 32 Issue 2

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Dynamic Calibration Method of Leading information in Integrated Following Equipment

ZHANG Xiao-fei;KOU Shu-hui;LIU Jun-song;ZHANG Xin-lei

2012, 32(2):  1-4.  doi:10.12060/j.issn.1000-7202.2012.02.01

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Azimuth of flying object must be produced by position gyroscope instead of encoder when electro-optical countermeasure system is searching and tracing objects on a moving truck. Because of temperature drift and cumulative error of gyroscope fixed on searching axis, flying object cannot be discovered by optical equipment for tracing. The temperature drift and cumulative error of position gyroscope are very hard to be corrected, because they are nonlinear with time and temperature. An indirect method to correct the guiding information is presented to solve the problem.

Research on Dynamic Angle Measurement Method of Vibration Table

ZHOU Cai-hong；YUN Peng；LIANG Ya-jun；LIU Ke

2012, 32(2):  5-8.  doi:10.12060/j.issn.1000-7202.2012.02.02

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When vibration table vibrates in high frequency, dynamic angle error is induced. This dynamic angle is not anticipated, it is considered a kind of error of the vibration. A dual-frequency laser interferometer is used to measure the dynamic yaw angle、 pitch angle and roll angle respectively when vibration table vibrates in 2 000Hz. In this dynamic angle measurement method laser interference theory is used. We find the vibration of surroundings influences the result greatly by analyzing the test result. A study direction is found to prefect the dynamic angle measurement method.

The study of the Overspeed Protection Device of the Turntable Based on MEMS Gyroscope

LIU Hua;LIU Jun-song

2012, 32(2):  9-11.  doi:10.12060/j.issn.1000-7202.2012.02.03

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The turntable as the commonly used test equipment will bring serious consequences once it can not be controlled or the overspeed is occurred.The overspeed protection device of the turntable  is put forward based on MEMS gyroscope. The serious harm of overspeed is given, the principle and components of the device are described in detail,and Matlab simulation shows the feasibility of the device.The application of the device reaches the expected results in practice.

A New Measurement and Calculation Method of Aircraft’s Primeval Posture

WANG Qing-chun;YANG Pei-yuan

2012, 32(2):  12-14.  doi:10.12060/j.issn.1000-7202.2012.02.04

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According to the specific properties of the launching stand, based on the geometric relationship in particular points, lines and faces, a simple and convenient method of measurement and calculation of aircraft’s primeval posture is concluded, providing the aircraft parameters bookbinding with reliable guarantee. The availability of this method is proved by flight tests.

A threeaxis Intersecting Degree Measurement

WANG Ming-yuan;YANG Lian-chun;YU Hai-sheng;ZHANG Xin

2012, 32(2):  15-17.  doi:10.12060/j.issn.1000-7202.2012.02.05

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A measurement method of  threeaxis turntable’s axis intersecting degree is described. The measurement method is the use of laser tracker to measure the turntable, the two fixed points on the frame (the target mirror seat position) around the rotation axis of movement of some of the space coordinates of the point where the fit of these points to construct two circles and its center, and then construct a circle by the two rotary axes. Thus, the rotation axis of the threeaxis turntable constructed after three rotary as can be calculated the distance between each, according to three rotary as the distance between any two threeaxis can be calculated intersection degree of threeaxis turntable.

Information Fusion of MEMS-gyro Based on Support Degree

ZHANG Hua-qiang;ZHAO Yan;CHEN Yu

2012, 32(2):  18-21.  doi:10.12060/j.issn.1000-7202.2012.02.06

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The MEMS inertial components have some disadvantages such as low-accuracy and big-noise, which can’t used for navigation alone because of accumulated error. In order to solve this problem, a MEMS-gyro array structure design is proposed. After the calibration of the MIMU, the information fusion algorithm based on support degree is used to deal with the data of the MEMS-gyro array. Experiment results show that this structure design and information fusion method can effectively improve the accuracy of the MIMU, which has some engineering application value.

Analysis and Calculation of Influencing Factors on Slug-Type Heat Flux Sensor

ZHANG Xiao-fei;WANG Wen-ge

2012, 32(2):  22-26.  doi:10.12060/j.issn.1000-7202.2012.02.07

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The structure and measurement principle of slugtype heat flux sensor are introduced. For a series of factors affecting the measurement results, such as the shape and size of  the sensitive component of the sensor, the thermal conductivity and thermal capacitance of the heat insulation layer and the surface emissivity of the two materials Etc., the heat transfer simulation to various models is conducted by Fluent software and the affections of different factors to the measurement results are analyzed. It can provide a reference and guidance for the development of the heat flux sensors.

Experimental Research of Calculate Model on the Effective Enthalpies of Ablation of Composite

ZHOU Yan-ping;WEI Li-ping;ZHENG Hui-bao;LIU Yun-chuan;MENG Xiang-yan;WANG Xue-rong;LI Shi-cheng

2012, 32(2):  27-29.  doi:10.12060/j.issn.1000-7202.2012.02.08

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The important characteristic parameter , namely the effective enthalpies of ablation, was obtained by the research on CF/S-157PF composite under oxyacetylene flame test conditions. And using multiple linear regression, the mathematic model between the effective enthalpies of ablation, the two major factors, namely the heat flux density and ablation time is as follows:H_eff=0.016 3·q^{0.871 5}·t^{0.191 3} . Being verified, the regression model is very applicable and the forecast accuracy is much better.So the erosion properties of CF/S-157PF composite can be evaluated rapidly, effectively and accurately in the oxyacetylene flame test.

Research on Rocket-propelled Launch of UAV

TIAN Xin-feng;XUE Peng;LI Hong-quan

2012, 32(2):  30-32.  doi:10.12060/j.issn.1000-7202.2012.02.09

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UAV as a product of modern technology, can work in high-risk area and has been widely used. The risk of UAV rocketpropelled launch process is analysised. The launching is processed by the subprocessing method, and the mathematical model of each flight segment is established. An example analysis result is given to determine the safe area of launching. The result is used to provide a theoretical basis to the UAV launching. and can satisfied to engineering need of the UAV launching location. This method not only can be used to determine the launching security zone, but also has project reference to the launch security analysis for other UAVs.

Polar Coordinates Algorithm to Compute Thrust Vector of Apogee Engine

ZHANG Wei;TIAN Guo-hua;CHEN Feng;MA Jun-qiang

2012, 32(2):  33-36.  doi:10.12060/j.issn.1000-7202.2012.02.10

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The principle of Thrust Vector of Apogee Engine testing system was shortly illustrated. A linear compose method was used to compute thrust vector in previous tests. After analyzing the defaults of the linear compose method, polar coordinates algorithm was proposed and well described. A mode was given to show its computing process.

The Acceleration Effects on Crystal Oscillators and Research on Compensating Techniqu

JI Long-zhe;SHAN Qing-xiao;TANG Qian;LIN Ming

2012, 32(2):  37-42.  doi:10.12060/j.issn.1000-7202.2012.02.11

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As the reference frequency source, crystal oscillator plays a critical role in the electronic equipments. Crystal oscillator is sensitive to the acceleration, such as vibration, concussion and centrifugal force, which would influence the stability of the frequency output. How acceleration affects the frequency and phase noise of crystal oscillator is discussed, some current measures of reducing the acceleration effects are introduced. A new method based on the digital compensating system is also brought up.

Evaluation of Uncertainly for a Lubricating Oil Flow Calibration Facility Based on High-low Temperature

WANG Jun-tao;SANG Pei-yong;JIA Zheng-hong;XIN Yan-feng;CUI Chun-tao

2012, 32(2):  43-45.  doi:10.12060/j.issn.1000-7202.2012.02.12

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Lubricating oil flow calibration facility is a newly built facility, has the characters of changing temperature, mass flow, and wide-range. The range of changing temperature is:（-35～150）℃.The basic principle of this calibration facility is introduced, the verified demand and method are established. Uncertainty of the calibration facility is determined .The result of test proves that the uncertainly of the facility meets the requirement of design.

Design of Accumulator Battery Testing System Software Based on PLC

GAN Wu;ZHANG Hua-feng;ZHANG Hao

2012, 32(2):  46-49.  doi:10.12060/j.issn.1000-7202.2012.02.13

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Aiming at the characteristics and demands of accumulator battery testing system, a software working is developed in STEP 7.The theory of testing system,the flow chart of the software and how it works are described. Presently the software has been used in actual projects,it has the performance of high work efficiency,mass data processing and good practicability．

Research on Vector Characterization Measurement Method of Mixers

HAN Lu;GAO Shen-xiang;SHEN Xiao-qing

2012, 32(2):  50-53.  doi:10.12060/j.issn.1000-7202.2012.02.14

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A new technique based on reflection measurement for RF mixers measurement is presented. The technique provides accurate and repeatable measurements of mixers that reciprocal and image frequency can be filtered for input match, output match, conversion amplitude, conversion phase, and group delay. Firstly, by analyzing the measurement method, an one-port vector error model is established. Then, S-parameter matrix of the model is derived and the formulas of the mixer performance parameters are given. Finally, experimental results verify the correctness of the method.

Simplified Design of  CAMAC Bus Control Unit Based on General I/O Interface

LI Xiao-jian;ZHANG Xia;YU Wei-rong;WU Jin-cai;ZHAO Liang-qing

2012, 32(2):  54-57.  doi:10.12060/j.issn.1000-7202.2012.02.15

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In order to decrease the cost and reduce dimension, the standard signals of CAMAC bus are analyzed. 6 type bus signals are produced by adopting TTL logic circuit. Hence the simplified design of CAMAC bus control unit is realized.Electro circuit principle and subprogram is introduced in detail. In this control unit, the Bus Control right can be obtained via operating the general I/O interface. Its stability and reliability are proved by application and can be used in module testing and system miniaturizing too.

〗Investigation on the Radiation Effect of Rubidium Atomic Clock by Low Dose Rate

WANG Shi-wei;ZHANG Jun;YANG Shi-yu;YANG Wei;ZHAI Hao

2012, 32(2):  58-61.  doi:10.12060/j.issn.1000-7202.2012.02.16

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The physics part is the frequency discriminator for the rubidium atomic clock, which determines its stability specifications including the short term and long term stability specifications(above 1 second). In physics part, the rubidium metal, glass and ferronickel are adopted, and some bipolar transistors and operational amplifiers are also adopted, the kernel componentrubidium bulb, was especially manufactured by a special vacuum technology. So the low dose rate sensitivity for these materials, devices and technology is essential to be estimated. The radiation experiment by low dose rate was advanced for the physics part of the rubidium atomic clock and the rubidium bulb used in it. The radiation source is Co⁶⁰ γ, the dose rate is 0.01rad(Si)/s, and the total dose is 50krad(Si). This work realistically simulates the ionization damage for these products, and the results will be referenced for the rubidium atomic clocks in the orbit and be useful to the radiation harden design for the later rubidium atomic clocks.

Research on Real-time Estimation Mathod for Range and Cruise Duration of UAV

CONG Shu-quan;WANG Cheng-jun;JIANG yang

2012, 32(2):  62-65.  doi:10.12060/j.issn.1000-7202.2012.02.17

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The range and cruise duration of UAV are the key tactical and technical characteristics to identify successful mission.That affectted the range and cruise duration are so many when UAV flying.According to the aerodynamics principle and the kinematics principle,real-time estimation method and application of the range and cruise duration of UAV are explored.

Research and Design of Satellite’s Thermal Control Voltage Measurement Module

SONG Bo；JI Qi-zheng；JIANG Fang-liang

2012, 32(2):  66-69.  doi:10.12060/j.issn.1000-7202.2012.02.18

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Measurement for satellite’s thermal control voltage is an important part to guarantee satellite’s reliability and security. Because the particularity of the measurement, it needs to research and design a voltage measurement module which is fit for the whole satellite’s thermal control system. Signals isolation and input protection are used to guarantee the safety of measurement, and techniques of advanced data collection, quantity conversion and automatic calibration are used for reliability of measurement. The measurement process is controlled by microprocessor, and the computer’s data transfer and communication control are realized by LAN interface, the efficiency of measurement is improved a lot.

The Design of Interface Circuit of Wide-Band Power Source Based on ARM9

FENG Rong-wei；JI Qi-zheng

2012, 32(2):  70-74.  doi:10.12060/j.issn.1000-7202.2012.02.19

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A method of interface circuit design and software development of wide-band power source based on ARM9 are introduced, according to the actual development work. The design of the circuit is given, functions and design ideas of various circuit modules are introduced. On the basis of discussion the framework of the VxWorks operating system, the detailed application development process is stated.

Research About Validating GUM Uncertainty Evaluation Using MCM

CAO Yun；CHEN Huai-yan；HAN Jie

2012, 32(2):  75-78.  doi:10.12060/j.issn.1000-7202.2012.02.20

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The basic method of uncertainty evaluation is GUM uncertainty framework(GUM) at present. On some conditions, GUM can be applied correctly. But when the model is complicated, all the applying condition can’t be ensured to meet. Compared to GUM, the validity range of MCM is larger, we can use MCM to validate GUM uncertainty evaluation with appropriate software. It’s suggested that the results can be compared which are obtained by GUM and MCM. If the results are satisfied, the GUM is applied correctly. Otherwise, MCM or other replacement must be considered. Concerning the example of mass calibration, the two methods are introduced to validate GUM uncertainty evaluation using MCM.