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2014 Vol. 40, No. 4

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Influencing depth under aircraft loads of runway
Zhang Xianmin, Xue Huaxin, Dong Qian, Sun Zhichao
2014, 40(4): 427-432. doi: 10.13700/j.bh.1001-5965.2013.0300
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In view of the current situation that the relationship among the influencing depth, the pavement structural parameters, the configuration of landing gear and take-off ground speed was not taken into consideration by the present rigid pavement, a finite element model of 45 m×15 m×10 m was built by me...
Influence of frequency mixing on vibration test of fiber optic gyroscope
Song Ningfang, Zhao Yafei, Pan Xiong, Zhang Chunsheng
2014, 40(4): 433-438. doi: 10.13700/j.bh.1001-5965.2013.0335
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Frequency mixing happening in vibration test on fiber optic gyroscope (FOG) can cause signal distortion of the output of FOG, which will influence the test result. In order to verify the consequence of frequency mixing and restrain it, a closed-loop data acquisition system which was used to get the ...
Numerical simulation analysis of steady-state properties of gas face and cylinder film seal
Ma Gang, Sun Xiaojun, Luo Xianhai, He Jun
2014, 40(4): 439-443. doi: 10.13700/j.bh.1001-5965.2013.0322
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Aimed at the special condition of fluidic dynamic seals of high speed fluid machineries such as the aero-engine, a new type of sealing form, gas face and cylinder film seal was proposed. According to the structure characteristics of the gas film seal, the mathematical analysis model of the gas face ...
Influence of laser shock peening times on microstructure and hardness of TA15 titanium alloy
Zhu Ying, Fan Bowen, Guo Wei, Kang Hui
2014, 40(4): 444-448. doi: 10.13700/j.bh.1001-5965.2013.0305
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Q-switched Nd glass laser with 20 J energy was used to shock TA15 titanium alloy in different times. Results show that laser shock peening (LSP) can produce micro plastic deformation, form dense micro pits and refine the grain size. When the number of impact times increases, the depth of the micro p...
Decoupling PI controller design for aeroengine
Gao Yahui, Zang Jun, Yao Hua, HUANG Jinquan
2014, 40(4): 449-454. doi: 10.13700/j.bh.1001-5965.2013.0312
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In discrete-time domain, the optimal PI controller design problem for aeroengine was researched. Firstly, a general coupling PI controller design method was presented. The key ideas were to construct Lyapunov function to guarantee the closed-loop stability, and the performance was optimized under th...
Loop parameters on dynamic characteristics of digital closed-loop accelerometer
Zhang Xi, Zhang Shengyan, Li Lijing, Wang Hongbo
2014, 40(4): 455-460. doi: 10.13700/j.bh.1001-5965.2013.0301
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The bandwidth of the digital closed-loop quartz-flex accelerometer was only 10 Hz under the integral controller. The servo loop parameters were adjusted to improve the system dynamic performance, and a proportional integral controller was designed to ensure that the system was no difference. The sys...
General forward kinematic algorism for three-chain parallel manipulator
Zhou Wanyong, Chen Wuyi, Liu Huadong
2014, 40(4): 461-466. doi: 10.13700/j.bh.1001-5965.2013.0337
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To solve the problem that actual geometric parameters are not equal to nominal ones in parallel manipulator, a general forward kinematic algorism, containing all of the geometric parameters, was proposed. The general 3RPS parallel manipulator, with compound spherical joints, was taken as an example....
Fighter maneuver control method of radar range tracking interrupt
Li Fei, Yu Lixin, Wang Long, Sui Yonghua
2014, 40(4): 467-472. doi: 10.13700/j.bh.1001-5965.2013.0317
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The maneuver trajectory control strategy that can interrupt the radar range tracking loop was proposed based on the system characteristic of auto range tracking system. The transfer function of auto range tracking system was developed, and the error production mechanism was researched. Taking the mi...
Mass estimation method and its application for horizontal takeoff horizontal landing two stage to orbit system
Jiang Yazhong, Jiang Chongwen, Gao Zhenxun, Lee Chunhian
2014, 40(4): 473-478. doi: 10.13700/j.bh.1001-5965.2013.0299
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Aiming at transportation missions to low global orbit, a mass estimation method was proposed for horizontal takeoff horizontal landing two stage to orbit (TSTO) transportation systems considering thrust-drag characteristics in different flight stages and specific impulse variations in different engi...
Attitude dynamics and control of spacecraft with fluidic ring actuator based on the refined model
Guan Hong, Xu Shijie
2014, 40(4): 479-485. doi: 10.13700/j.bh.1001-5965.2013.0316
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The influence of nonlinear disturbances to model's precision and control accuracy were studied after considering the viscous of the flow flied and the friction in the pump control system. For the former, the momentum loss caused by the viscous of flow was studied. The equivalent momentum loss depth ...
Nonlinear leakage model of rotary vane actuator
Wang Zeng, Jiao Zongxia, Wang Chengwen, Shang Yaoxing
2014, 40(4): 486-493. doi: 10.13700/j.bh.1001-5965.2013.0584
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Rotary vane actuator is a high-precision actuating mechanism. Internal structure of seals is more complex than the other actuators. Nonlinear leakage model of rotary vane actuator was put forward based on the analysis of the character of seals of rotary vane actuator. Rotary vane actuator's total le...
Spacecraft attitude estimation based on attitude-weighted kernel regression
Zhang Haopeng, Jiang Zhiguo
2014, 40(4): 494-499. doi: 10.13700/j.bh.1001-5965.2013.0298
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An attitude estimation method for monocular vision imaging systems was proposed to solve relative attitude estimation problem of spacecrafts. On the basis of the original kernel regression model, the similarity of training data in the attitude space was used to weight kernel functions of the origina...
Stiffness characteristics distribution of 3 PRS/UPS parallel manipulator with actuation redundancy
Guo Jiangzhen, Wang Dan, Fan Rui, Chen Wuyi
2014, 40(4): 500-506. doi: 10.13700/j.bh.1001-5965.2013.0304
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A three degree of freedom (DOF) 3PRS/UPS parallel manipulator with actuation redundancy was designed and investigated. The architectural model was constructed and the kinematic analysis was presented based on screw theory. The overall Jacobian matrix including redundant actuation was derived through...
Tipping calibration method for K-band hyperspectral microwave radiometer
Xie Yan, Chen Jingxiong, Miao Jungang
2014, 40(4): 507-511. doi: 10.13700/j.bh.1001-5965.2013.0315
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The K band ground based hyperspectral microwave radiometer can be applied in the atmospheric sounding field, and it can improve the profile error and the vertical resolution of the moisture profiling from Earth's surface to the atmospheric troposphere. For the purpose of reducing the fluctuations of...
Robust optimization of coupled structural-acoustic systems based on sensitivity analysis
Wang Chong, Qiu Zhiping, Wang Xiaojun, Wu Di
2014, 40(4): 512-516. doi: 10.13700/j.bh.1001-5965.2013.0328
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An interval finite element method and an interval robust optimization model were proposed for the coupled structural-acoustic field prediction and structural design with uncertainties both in the inherent parameters and external load. Based on the central difference method, the response sensitivity ...
State space theory and NR-LMS algorithm based method for structural dynamics parameter identification
Wang Yunfeng, Cheng Wei, Chen Jiangpan
2014, 40(4): 517-522. doi: 10.13700/j.bh.1001-5965.2013.0285
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A parameter identification method for structural dynamics system based on state space (SS) theory and normalized robust least mean square (NR-LMS) algorithm was proposed. By using this method, the identified dynamic system's input and output data were used to build its Hankel-Toeplitz model based on...
Precise configuration of mixed message sets’ transmission mode in network partition
Tu Xiaojie, He Feng, Wu Qing, Xiong Huagang
2014, 40(4): 523-528. doi: 10.13700/j.bh.1001-5965.2013.0286
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It was indicated that configuration of message transmission mode among network partition method in distributed integrated modular avionics was uncertain. Through formal description the problem was transferred into an optimal problem with constrains including real-time, bandwidth and buffer. Then the...
Hexahedral mesh generation method for geometric features
Chen Ruizhi, Xi Ping, Wang Shuai
2014, 40(4): 529-535. doi: 10.13700/j.bh.1001-5965.2013.0296
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In order to guarantee self-adaptability of geometric features and coordination between meshes of geometric features and overall structure, a hexahedral mesh generation method for geometric features was proposed which focuses on generating high-quality hexahedral meshes for local complex features hav...
Method optimization of optimum measurement point selection in experiential modal analysis
Rong Shuanglong, Li Chuanri, Xu Fei, Ma Tian
2014, 40(4): 536-543. doi: 10.13700/j.bh.1001-5965.2013.0292
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As an important basis of the validation of the finite element model, the result of experimental modal analysis is influenced by various aspects, one significant aspect is the measurement point selection. A new optimal measurement point selection method, namely effective independent-coefficient varia...
Adaptive recovery algorithm for compressive sensing based on Fourier basis
Lü Fangxu, Zhang Jincheng, Wang Quan, Wang Yu
2014, 40(4): 544-550. doi: 10.13700/j.bh.1001-5965.2013.0332
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In order to improve the recovery accuracy of compressive sampling, an algorithm of modified sparsity adaptive matching pursuit based on discrete Fourier transform (MSAMP-DFT) was proposed. In the course of reconstruction, not only the correlation, but also the conjugate symmetry on discrete Fourier ...
Oblique flying wing supersonic airliner aerodynamic configuration parameters selection method
Hu Shuyao, Jiang Chongwen, Gao Zhenxun, Lee Chunhian
2014, 40(4): 551-557. doi: 10.13700/j.bh.1001-5965.2013.0291
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The method is capable of providing the basic geometry of the flying wing simply by given certain bulk parameters, such as the passenger number, range, cruise velocity and height. Discussions were paid to the selection of the appropriate symmetry plane chord, the constraint of the wing span caused by...
Camera calibration from geometric feature of spheres
Zhao Yuntao, Sun Junhua, Chen Xu, Gong Zheng
2014, 40(4): 558-563. doi: 10.13700/j.bh.1001-5965.2013.0293
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Camera calibration with spheres has little demand on image number, camera shooting angle and high adaptivity to occlusion, which has an obvious advantage in applications. A novel camera calibration method was proposed based on geometric feature of sphere projection model. This algorithm used two pro...
Anti-coking performance of nozzle materials’ surface chemical modification
Li Fan, Zhu Yuelin, Huang Yanfei, Liu Yajie
2014, 40(4): 564-568. doi: 10.13700/j.bh.1001-5965.2013.0326
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Based on the problem of technical performance and service life of the aero-engine with a mass of coking on nozzles, steady rich chromium oxide layer was prepared on the aircraft engine nozzle materials' surface through the chemical oxidation-cathodic reduction method. The sample surface was characte...
Probabilistic flutter analysis with uncertainties in structural stiffness
Tang Jian, Wu Zhigang, Yang Chao
2014, 40(4): 569-574. doi: 10.13700/j.bh.1001-5965.2013.0336
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A probabilistic flutter analysis method was proposed to evaluate the structural stability and flutter risk of the rudder, which was subject to uncertainties in structural parameters with stochastic distribution. Monte Carlo simulation (MCS) and non-intrusive polynomials chaos (NIPC) method were used...
Calculation and selection of sequentially truncated test scheme
Yu Chuang, Wang Xiaohong, Li Qiuxi
2014, 40(4): 575-578. doi: 10.13700/j.bh.1001-5965.2013.0295
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The method for calculating the two types of risk's real value under sequential test scheme was researched, and software for calculating the truncation scheme of test was programed. Then test scheme was analyzed and the relationship between truncated sequential test and fixed number test was studied....

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