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	Modeling Civil Aviation Emissions with Actual Flight Trajectories and Enhanced Aircraft Performance Model 期刊论文 OAI收割 ATMOSPHERE, 2024, 卷号: 15, 期号: 10, 页码: 1251 作者: Wang, Jinzi; Zhang, Hengcai; Yu, Jianing; Lu, Feng; Li, Yafei \| 收藏 \| 浏览/下载：6/0 \| 提交时间：2024/12/20 aviation emission emission inventory ADS-B openAP aircraft performance model uncertainty analysis
	Trajectory tacking control of a quad-rotor based on active disturbance rejection control (EI CONFERENCE) 会议论文 OAI收割 2012 IEEE International Conference on Automation and Logistics, ICAL 2012, August 15, 2012 - August 17, 2012, Zhengzhou, China Gong X.; Tian Y.; Bai Y.; Zhao C. 收藏 \| 浏览/下载：31/0 \| 提交时间：2013/03/25 The objective of this paper is to deal with a trajectory tracking of a Quad-rotor unmanned aerial vehicle (UAV). For the model uncertainty the external disturbance and the coupling factor are considered an active disturbance rejection control (ADRC) algorithm is introduced into the designing procedure. The aircraft dynamic model is proposed in this article based on which the closed-loop control system is divided into four independent channels with the coupling factor compensated by the extended state observer (ESO). The nonlinear state error feedback (NLSEF) algorithm is designed in each channel to improve the closed-loop dynamics. In this article the ADRC controller is expressed in the discrete form. And finally the simulation results show that the proposed control algorithm achieves a favourable tracking performance. 2012 IEEE.
	Aircraft flight simulation with landing gear based on multi-domain modeling technology (EI CONFERENCE) 会议论文 OAI收割 2012 2nd International Conference on Computer Application and System Modeling, ICCASM 2012, July 27, 2012 - July 29, 2012, Shenyang, China 作者: Li M. 收藏 \| 浏览/下载：16/0 \| 提交时间：2013/03/25 This paper create a full aircraft flight simulation model for accurately analyzing the performance and influence of landing gear system. The use of multi-domain modeling technology enables detailed modeling of the flight dynamic and landing gear dynamic. The simulation results show that the aircraft landing gear system mathematical model established appropriately reflects the change of force and moment in the process of taking off and landing and it is actual in the physical process. The parameter design space is easily searched by considering a number of different landing scenarios to optimize the design. the authors.
	Evaluation of the operating range for ground-based infrared imaging tracking system (EI CONFERENCE) 会议论文 OAI收割 International Symposium on Photoelectronic Detection and Imaging 2011: Advances in Infrared Imaging and Applications, May 24, 2011 - May 24, 2011, Beijing, China 作者: Zhang Z.-D. 收藏 \| 浏览/下载：48/0 \| 提交时间：2013/03/25 Ground-based infrared imaging tracking system (GIITS) is of great importance for aerial target warning and guard. The operating range is one of the key performance specifications on the other which should be calculated calculate the radiation power received on the detector in order to analysis whether the output signal meets the detection requirements or not analyzed and studied during the whole GIITS design process. The operating range is mostly influenced by a few factors without considering the effect of the background radiation. By improving of the traditional method including atmospheric attenuation a new operating range calculation model of the GIITS was established based on two requirements. One is that the image size of observed target should meet the requirement of the processor signal extraction. The number of the pixel occupied by target image should be more than 9. The other is that the signal noise ratio (SNR) of the GIITS should not be less than 5 to meet the requirements of the target detection probability and spatial frequency. The SNR calculation equation in form of energy is deduced and the radiation characteristic of the observed target and background are analyzed. When evaluate the operating range of the GIITS using the new method the performance of GIITS and feature of target and background. This paper firstly makes analysis and summarization on the definite localizations of the traditional operating range equation of the GIITS. The localizations are mainly in two aspects. On one hand we should successively calculate two operating range values according to two requirements mentioned above and choose the minimum value as the analytic result. In the end the dispersion of the image and the effect of image dispersion are not considered in the traditional method an evaluation of operating range for fighter aircraft is accomplished as an example. The influence factors in every aspect on operating range were explored by the calculated result. The new operating range calculation model provides the theoretical basis for the design and applications as well as the comprehensive evaluation of a GIITS. 2011 Copyright Society of Photo-Optical Instrumentation Engineers (SPIE).
	Establishment of airplane flight model and simulation analysis of landing behavior (EI CONFERENCE) 会议论文 OAI收割 2nd Annual Conference on Electrical and Control Engineering, ICECE 2011, September 16, 2011 - September 18, 2011, Yichang, China 作者: Li L.; Li M. 收藏 \| 浏览/下载：25/0 \| 提交时间：2013/03/25 This paper create a high fidelity plant model of an aircraft landing gear to inclusion into a full aircraft flight simulation for accurately analyzing the performance and influence of landing gear system. The use of domain specific modeling software enables detailed modeling of the physics and facilitates accurate computational simulation of the flight dynamic aerodynamic landing gear dynamic and mechanical loads that occur when the landing gear are deployed and retracted during landing and take-off operations. The parameter design space is easily searched by considering a number of different landing scenarios including touching down on one wheel first to optimize the design. The simulation results show that the aircraft landing gear system mathematical model established appropriately reflects the change of force and moment in the process of taking off and landing and it is actual in the physical process. 2011 IEEE.
	Aircraft landing gear simulation using multidomain modeling technology (EI CONFERENCE) 会议论文 OAI收割 2011 International Conference on Information Technology, Computer Engineering and Management Sciences, ICM 2011, September 24, 2011 - September 25, 2011, Nanjing, Jiangsu, China 作者: Li M. 收藏 \| 浏览/下载：40/0 \| 提交时间：2013/03/25 In order to accurately analyze the performance and influence of landing gear system this paper presents a high fidelity plant model of an aircraft landing gear to inclusion into a full aircraft flight simulation. The use of domain specific modeling software enables detailed modeling of the physics and facilitates accurate computational simulation of the flight dynamic aerodynamic landing gear dynamic and mechanical loads that occur when the landing gear are deployed and retracted during landing and take-off operations. The parameter design space is easily searched by considering a number of different landing scenarios including touching down on one wheel first to optimize the design. The simulation results show that the aircraft landing gear system mathematical model established appropriately reflects the change of force and moment in the process of taking off and landing and it is improve the precision of flight simulation. 2011 IEEE.
	Modular aircraft simulation platform based on simulink (EI CONFERENCE) 会议论文 OAI收割 2010 IEEE International Conference on Mechatronics and Automation, ICMA 2010, August 4, 2010 - August 7, 2010, Xi'an, China Chen C.-Q.; Ji Y. 收藏 \| 浏览/下载：28/0 \| 提交时间：2013/03/25 Aircraft simulation platform is the most important supporting technology in the aircraft development process. This simulation platform can be used for validating the design of subsystem and also it provides the necessary data for the Aircraft design. Wind has great impact on the flight parameter. In order to accurately simulate the wind model and calculate the flight parameters a simulation modeling method for flight parameter simulation platform under wind field environment is established. Firstly the various sub-systems which affecting flight parameters are analyzed some mathematical models of the flight parameter simulation platform is established. Secondly the atmospheric wind field is studied to analyze the impact on its trajectory. Then the model is built in the Simulink toolbox in the Matlab which is based on the principles of hierarchy and modularity using C MEX S-function for the complex kinetic equations. Finally when the models have been established encapsulating models for several subsystem and assembling them for the Aircraft simulation platform based on the unified interface. The simulation tests (including the performance test of a certain gliding Aircraft the wind influence test of a certain uncontrolled aircraft) prove the simulation capability of the platform and its calculating step can reach 1 ms. Comparing simulation with field test data of a certain uncontrolled aircraft it shows that the relative deviation of range is 0.47% the relative deviation of maximal altitude is 2.1%. Taking relevant standards as a reference standard it is demonstrated the platform is reliable meets the engineering accuracy requirements. 2010 IEEE.