Liaoning General Aviation Academy

Shenyang, China

Liaoning General Aviation Academy

Shenyang, China
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Wang G.-D.,Liaoning General Aviation Academy | Wang G.-D.,Shenyang Aerospace University | Chong Q.,Liaoning General Aviation Academy | Zhou L.,Liaoning General Aviation Academy | Li N.,Liaoning General Aviation Academy
Journal of Reinforced Plastics and Composites | Year: 2017

Prediction of relative permeability is important to avoid dry spots or micro voids in the liquid composite molding process. Most of previous studies focused on plain and twill, but few are about stain and none of them provide explicit equation to calculate accurate values of unsaturated permeability. The main purpose of this work is to first propose a new model which is proposed mainly based on fractal theory and has no empirical constant in the expression, to calculate the permeability of satin fabric. And then we employ a new experimental method to calculate the unsaturated permeability. Finally, a contrast experiment of 5-harness fabric and 8-harness fabric is designed at different injection pressures, and the accurate values of permeability are obtained. The results show that unsaturated and saturated permeabilities are in the same order of magnitude; furthermore, unsaturated permeability is 77% of saturated permeability in 5-harness fabric and 73% in 8-harness fabric. © SAGE Publications.

Zhang L.,Shenyang Aerospace University | Zhang P.,Shenyang Aerospace University | Wang D.,Shenyang Aerospace University | Li Z.,Shenyang Aerospace University | Li D.,Liaoning General Aviation Academy
Progress in Steel Building Structures | Year: 2016

The 179 Ferris Wheel is 170 m in diameter and 179 m in height. It will be the world's highest ferries wheel upon completion. This ferris wheel applies the rigid spokes (rigid truss arms) combining with steel cables in the structure. The giant wheel installation is closely related to the structural design of the wheel structure. Therefore, a reasonable installation plan must be made at the structural design stage, to ensure structural safety and reliability. Rotation installation method is used to the 179 Ferris Wheel, and finite element simulation analysis on eight independent stationary states during installation is carried out. Equivalent stress, deflection and buckling analysis of the 179 Ferris Wheel are evaluated at different installation positions using ANSYS software. The analysis result indicates the whole installation process is safe and reliable. © 2016, Progress in Steel Buiding Structures All right reserved.

Huang J.,Liaoning General Aviation Academy | Huang J.,Beihang University | Yang F.,Liaoning General Aviation Academy
Hangkong Xuebao/Acta Aeronautica et Astronautica Sinica | Year: 2016

To develop green aviation is the common understanding of the society of human beings and new energy electric aircraft provides a bright technological approach to achieve a complete green aviation. The impacts of aviation on environment, applications of electricity in airplane and development history of electric aircraft have been briefly described at the beginning of this paper. The energy classification and the electric propulsion system with its overall efficiency of new energy powered electric aircraft are more deeply studied. Focusing on manned light sport aircraft, the development status, characteristics and energy demand of electric airplane are analyzed. Through researches of range and ultimate range of manned electric aircraft with energy of battery, challenges or key technologies faced by the electric aircraft, which include battery energy density upgrade and performance improvement, high lift-to-drag ratio aerodynamic aircraft design, low-cost lightweight efficient composite aircraft structure design and manufacture, high efficiency electric propulsion system design and integration, are put forward. Finally, the recommendations of striving to develop electric aircraft and future research directions in this field are provided. © 2016, Press of Chinese Journal of Aeronautics. All right reserved.

Cao Y.,Shenyang Aerospace University | Hu Z.,Shenyang Aerospace University | Zhao W.,Liaoning General Aviation Academy
Advanced Materials Research | Year: 2012

The PID control is a popularly control method that used in control systems, which is still adopted in many practical application processes.This paper is based on the oringinal navigation aircraft longitudinal channels model,and discusses the setting of navigation autopilot longitudinal channels model in the PID controller parameters, using General Aviation Aircraft Longitudinal channels of PID control parameters optimization based on Genetic Algorithm.In contrast with the simulink7.1 simulation results of the longitudinal channel model, base on the thought of genetic algorithm and use MATLAB language program to get the parameters of the controller, adjusting the parameters to achieve the optimization of PID control parameters. The result of SIMULINK simulation: The PID controller which is designed by using the genetic algorithm is more adaptability, flexibility, and can guarantee the system control effect. © (2012) Trans Tech Publications, Switzerland.

Kang G.-W.,Shenyang Aerospace University | Kang G.-W.,Liaoning General Aviation Academy | Hu Y.,Shenyang Aerospace University | Li Y.-D.,Liaoning General Aviation Academy | And 2 more authors.
Hangkong Dongli Xuebao/Journal of Aerospace Power | Year: 2013

Combined with a certain ultralight electric aircraft's design parameters, the layout of aircraft electric propulsion system, the principles and steps of the parameter matching of electric propulsion system were presented. The methods of parameter matching and performance verification of electric propulsion system were put forward. The feasibility of the system was verified from the mass of propulsion system, dynamics and economics. The maximum level flight speed of the reference aircraft is 175.5 km/h, greater than the maximum level flight speed of 170 km/h, which is design requirement, in compliance with the requirement of dynamic performance. The operation cost of electric propulsion system is RMB 6.8 yuan/h that is close to the 1/8 of the operation cost of piston engine with similar power. Compared with three electric aircrafts, the reference aircraft's power to mass ratio is still high up to 0.0842 kW/kg, which is acceptable.

Wang G.-D.,Liaoning General Aviation Academy | Yang Y.,Shenyang Aerospace University | Wang W.,Liaoning General Aviation Academy | Si-Chao L.V.,Shenyang Aerospace University
International Journal of Advanced Manufacturing Technology | Year: 2015

In order to improve product quality and enhance economic returns, the research about tolerance allocation under multi-constraints including assembly and manufacturing accuracy is done. On the basis of cost-tolerance relationship, this paper introduces variable coefficients reciprocal squared model (VCRSM) into tolerance allocation process and thus constructs the tolerance allocation optimization objective model. Aiming at resolving multi-constraints problem within allocation process, the penalty items are added into allocation optimization objective model, and an analytic equation based on multi-constraints is proposed. The equation is solved using the Newton iteration method in consideration of the assembly and manufacturing accuracy constraints. Finally, a tolerance allocation instance about aircraft door component assembly is given. The numerical results show the method can achieve optimal tolerance allocation and the VCRSM is more suitable than other cost-tolerance models in multi-constraints tolerance allocation. © 2015 Springer-Verlag London

Xiang S.,Shenyang Aerospace University | Xiang S.,Liaoning General Aviation Academy | Li G.-C.,Shenyang Aerospace University | Zhang W.,Shenyang Aerospace University | Yang M.-S.,Shenyang Aerospace University
Applied Mathematics and Mechanics (English Edition) | Year: 2012

Love's first approximation theory is used to analyze the natural frequencies of rotating functionally graded cylindrical shells. To verify the validity of the present method, the natural frequencies of the simply supported non-rotating isotropic cylindrical shell and the functionally graded cylindrical shell are compared with available published results. Good agreement is obtained. The effects of the power law index, the wave numbers along the x- and θ-directions, and the thickness-to-radius ratio on the natural frequencies of the simply supported rotating functionally graded cylindrical shell are investigated by several numerical examples. It is found that the fundamental frequencies of the backward waves increase with the increasing rotating speed, the fundamental frequencies of the forward waves decrease with the increasing rotating speed, and the forward and backward waves frequencies increase with the increasing thickness-to-radius ratio. © 2012 Shanghai University and Springer-Verlag Berlin Heidelberg.

Xiang S.,Shenyang Aerospace University | Xiang S.,Liaoning General Aviation Academy | Chen Y.-T.,Shenyang Aerospace University
Gongcheng Lixue/Engineering Mechanics | Year: 2013

Three-dimensional governing differential equations are derived based on the linear elasticity theory and the equations are discretized using the meshless collocation method based on the inverse multiquadrics radial basis function. Through the numerical examples, the convergence characteristics and the choice of shape parameter are studied. It is found that the natural frequencies computed with shape parameter c=0.5/√Nx (Nx is the number of node at the x side) converge most rapidly. The natural frequencies of orthotropic and isotropic plates under different boundary conditions are calculated by the proposed method. The proposed results are in good agreement with the available published results.

Lin F.,Shenyang Aerospace University | Li H.,Shenyang Aerospace University | Zhang X.,Shenyang Aerospace University | Zhang X.,Liaoning General Aviation Academy
International Conference on Signal Processing Proceedings, ICSP | Year: 2015

A model of solar radiation intensity is established which can help analysis the issue better, because the UAV has a tall order in weight control and yet it consumes much electricity. By using MATLAB, the mode can simulate the solar cell's output power during the daylight well and in this way proved that the solar panel can give sufficient power for the testing UAV. To ensure the UAV can work without faults, a monitoring system is developed to monitor the power supplied by solar panel and the built-in battery. The following test also shows that the system can work properly and have a satisfying accuracy. The energy monitoring system measures and displays for energy system data, and provides the first data when a small solar unmanned demonstrator flies in the test process. © 2014 IEEE.

Shuli W.,Shenyang Aerospace University | Shuli W.,Liaoning General Aviation Academy | Kang G.,Shenyang Aerospace University | Kang G.,Liaoning General Aviation Academy | Jun M.,AVIC Shenyang Xinghua Aerospace Electrical Appliance CO.
Proceedings of the 2015 27th Chinese Control and Decision Conference, CCDC 2015 | Year: 2015

Electric propulsion system of two seat electric aircraft used permanent magnet synchronous motor as the main drive, combined with vector control system. The aircraft is suffered impact of airflow with a certain chaotic characteristics while the vector control system ignores the chaotic characteristics of airflow impact force. Permanent magnet synchronous motor according to the two seat electric aircraft was established by chaos mathematical model. The use of the method of time delayed feedback chaos anti control are a reflection of the permanent magnet synchronous motor. The system is simulated using Simulink, and the lyapunov value and simulation image are given. Validity of the control algorithm is proved, On the basis of chaos anti control provides the theory of PMSM used for electric two seat aircraft. © 2015 IEEE.

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