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2003 Vol. 29, No. 12

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Design of longitudinal automatic landing control law of transport aircraft with μ synthesis
Wang Hui, Li Shaoyan, Chen Zongji
2003, 29(12): 1059-1063.
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The process and characteristic of landing of transport aircraft was analyzed. The synthesis method based on structured singular value was adopted to design the automatic landing control system to accurately follow the slide path of landing. The robust performance of the landing system was analyzed. The simulation results showed that the designed control law satisfied the requirements of automatic landing of transport aircraft when there are uncertainties of transport aircraft model, measurement noises and gust disturbances.
Experimental investigations of improving AO-resistant characteristics of glass fiber/epoxy resin composite filled with superfine cenospheres
Wang Mingzhu, Zhao Xiaohu, Shen Zhigang, Ma Shulin
2003, 29(12): 1064-1067.
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A new technology was adopted to improve AO-resistant characteristics of spacecraft composites. The superfine cenospheres, which were stable in AO environment, were filled in the epoxy matrix in order to produce the AO-resistant glass fiber/epoxy resin composite. Cenospheres/glass fiber/epoxy resin composites were prepared and the AO exposure test was conducted in ground-based AO effects simulation facility. It was found that the filling of cenospheres effectually protected the glass fiber/epoxy resin against AO erosion. After the AO exposure test of 60 h, the erosion yield of the composite with cenosphere fillers can decrease to 11% of the composite without cenosphere fillers.
Development of fly-by-light control system
Li Kun, Wang Shaoping
2003, 29(12): 1068-1072.
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An overview was given to the development of fly-by-light (FBL) control system. The achievements in every period of the international research work about FBL were illustrated. The key problem that restrict the development of FBL was the FBL hardware. The way how to select optical components which were suitable for aviation environment was discussed. Considering the present status of technology and the level of researches on FBL in our country, the research steps and direction of FBL were provided.
Concurrent design of environmental control systems for aircraft
Wang Xiaowen, Wang Jun
2003, 29(12): 1073-1076.
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Based on the development of the environmental control systems for aircraft, the arrangement for the structure of systems design was analyzed. To recur information technology, designing technology, imitating technology, an concurrent engineering frame was proposed based on management-structure design-imitate. Design system runs through the whole life of the design period of the environmental control systems for aircraft.
Development of flight control with aircraft
Zhang Rulin
2003, 29(12): 1077-1083.
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The flight control technology development and effects on aircraft were discussed. It was briefly reviewed that history from Wright brothers to 1960s'. The emergence of active control technology and fly-by-wire control system had tremendous influences on aircraft design. The main technique connotation and approaches of new integrated adaptive flight control system were introduced.
Second-order sliding mode control of cross beam experiment system
Gu Wenjin, Yu Hongyun, Yang Zhiyong
2003, 29(12): 1084-1086.
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To reduce the chattering produced by traditional sliding mode controller on the cross beam experimental system, a second-order sliding mode controller based on the idea of high-order sliding mode control for output tracking the cross beam system which was a higher order and MIMO nonlinear system was designed. This method achieved the application of high-order sliding mode control on MIMO system. The simulation shows that second-order sliding mode control can reduce the chattering effectively.
Aeroelastic analysis of flexible large aspect ratio wing
Xie Changchuan, Wu Zhigang, Yang Chao
2003, 29(12): 1087-1090.
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Aeroelastic phenomena are significant for high-altitude long-endurance aircrafts for the large aspect ratio wing. The effect of structural geometric-nonlinear on wing dynamic characteristics and the changes of unsteady aerodynamics due to the large static deformation of wing were studied. The wing flutter was carried out based on the result of large deflected wing vibration analysis using quasi-linear method and its unsteady aerodynamics by strip theory. Through the calculation of the wing, it can be concluded that the flutter speed decreases significantly under large deformation.
Competence-based workflow task organizing
Wan Liangjun, Huai Jinpeng
2003, 29(12): 1091-1096.
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To solve the problem on coupling of activities and cooperators in classical workflow model, and improve the task distribution flexibility and adaptability, the competence concept for workflow activity and cooperator was presented. The competence ontology model and competence-based task organizing principles were described. A process meta-model was constructed based on the three-layer architecture of activity/competence/cooperator. A series formal description of competence matchmaking policy was put forward. These concepts and methodologies are implemented and verified in an open workflow system-ABCflow.
Calculation of reliability index based on mission completion probability for UAV system
Zhang Wenjin, Kang Rui, Zeng Shengkui
2003, 29(12): 1097-1100.
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In order to solve the problem of the reliability index determination of the UAV (unmanned aerial vehicle) system, the function of the modern UAV system was described. And a practical calculating method for the mission completion probability of UAV system was presented, in which the modes and the field statistics data of the UAV system were considered to build the reliability block diagram of the system. Finally, the UAV system's MTBCF (mission time between critical failure) and MTBF (mean time between failure) were calculated and analyzed.
Design and analysis of novel airborne integrated electro-hydrostatic actuator
Li Jun, Fu Yongling, Wang Zhanlin, Gao Bo
2003, 29(12): 1101-1104.
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To meet the development of aircraft actuating systems in the future, a novel airborne electro-hydrostatic actuator (EHA) which is integrated for power-by-wire (PBW) is designed. The paper describes the principle of work and features of EHA, models its components and the system, and simulates it with Matlab/Simulink. The EHA closed-loop system's simulation obtained the perfect dynamic performances; verify the correctness of the design with its control strategy. It will be used as a part of airborne PBW actuating system.
Reusable space vehicle flight control
Zhang Ziyan
2003, 29(12): 1105-1109.
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It was analyzed about the problems of space vehicle flight control, the development of space vehicles, the design aim and main characteristic of flight control systems of varied space vehicles, the main design requirement of flight control system of reusable space vehicles, the key technology which have to be resolved in flying control law design and flight control system design.
Flight test of modern fighter
Zhou Ziquan
2003, 29(12): 1110-1114.
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Based on the engineering practice of flight test recently for the new type of fighter, referred to the foreign experience, the flight test characteristics of modern fighters was described,including sorties and period,aboard acquisition system,ground data acquisition system,ground support facilities, flight with other types of aircraft, organization and management ;The flight test technologies which should be emphasized in term of the fly-by-wire,including stability margin of flight control system, flutter and aero-servo-elasticity,pilot in-the loop flying qualities and high angle of attack technologies .Some problem in F/T was discussed.
Shape adaptive embedded wavelet image code
Bao Yongsheng, Wang Qi, Guo Lei
2003, 29(12): 1115-1118.
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It can code arbitrarily shaped object not only preserving visual texture information but also introducing no redundancy. Transforming arbitrarily shaped object will bring a little change because of the variety of sequence's length and subsample location, which was resolved by the method that arbitrarily shaped mask images were transformed through lazy wavelet and shape adaptive wavelet transform was resolved by lift-based wavelet of 9-7 filter banks. Finally arbitrarily shaped object texture was coded and compressed using the modified shape adaptive SPIHT. Comparison with origin algorithm shows the gain of 0.2 dB.
LQ optimal simulation for aircraft anti-skid brake control system
Huang You
2003, 29(12): 1119-1122.
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Linear-Quadratic optimal control technique, Matlab optimal toolbox and Simulink were applied for aircraft anti-skid brake control system, according to aircraft body,tyre,ground and brake device. The dynamic model was given by modern state-space method, optimal state-feedback gain was calculated and the robust controller of aircraft anti-skid brake system was designed.
Study on effectiveness evaluation of integrated control system with laser guided bomb
Xie Zhenpeng, Shen Gongzhang
2003, 29(12): 1123-1126.
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The effectiveness evaluation of LGB integrated flight/fire/propulsion control (IFFPC) system was composed of performance evaluation and combat effectiveness evaluation, according to the general rules of weapon systems effectiveness evaluation and the characteristic of the IFFPC system. For evaluating its performance, the IFFPC system was divided into three strata hierarchical control system on the large scale system control theory. The combat effectiveness was evaluated by comparing the combat aim with the combat result.
Design of fuzzy flight control system based on LMI
Wang Yueping
2003, 29(12): 1127-1129.
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A fuzzy flight control system model was established. Through using linear matrix inequality, a design method was gained which guarantees the fuzzy system is global asymptotic stability and the poles were assigned to anticipant areas. The numerical simulations of a fuzzy flight control system designed by this method show the system possesses not only satisfactory performances but also strong robustness.
Helicopter pitch fly-by-wire control law design based on fuzzy control
Huang Ying
2003, 29(12): 1130-1132.
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Because of the nonlinear properties of the helicopters, such as multivariable, strong couple, the conventional control methods can hardly provide the perfect manipulability for advanced helicopter. Fuzzy control is an effect control method, which deals with the control problems through the way similar to human problems solving, so it can control some uncertain systems by imitating the fuzzy concepts of human thoughts. Fuzzy control method was applied to designing the pitch ACAH control law of hovering for a helicopter. The effectiveness of the proposed method was provided by simulation.
Dynamic reverse and fuzzy integrated control of unmanned helicopters
Shen Yi, Yu Xiaomin, Li Aijun
2003, 29(12): 1133-1135.
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To nonlinear system, the approximate reverse of the system was extracted using its approximate linearized model and the fuzzy control was employed to restrain the effect the error produces on the system so as to guarantee the terminal performance of the system, thus constituting a plan of dynamic reverse and fuzzy integrated control. This method was applied to the attitude control of unmanned helicopters and it can, in accordance with the simulation results, remove uncertain effects unmanned helicopters bring about, being provided with better robustness.
Recursive damped least square and its application in INS/DS integrated system
Zhao Long, Liu Zhun, Chen Zhe
2003, 29(12): 1136-1138.
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The filtering performance is unsatisfactory while INS/DS (Double-star) integrated navigation system is implemented using Kalman filtering technology, because the model error of double-star system is unknown and the stability is not good, either. As an alternative, the least square(LS)scheme is widely used in practical engineering application. But LS scheme is easy to bring about the problem of parameter burst-off. Therefore, a modified LS scheme based on multi-input-multi-output system, i. e. recursive damped least square (RDLS) scheme, was developed, and be applied to INS/DS integrated navigation system. Simulation results show that the RDLS scheme has the same estimation precision as the recursive least square (RLS) scheme, and furthermore, the parameter burst-off is obviously restricted.

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