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	Longitudinal Control for Balloon-Borne Launched Solar Powered UAVs in Near-Space 期刊论文 OAI收割 JOURNAL OF SYSTEMS SCIENCE & COMPLEXITY, 2022, 卷号: 35, 期号: 3, 页码: 802-819 作者: Hu Yanpeng; Guo Jin; Meng Wenyue; Liu Guanyu; Xue Wenchao \| 收藏 \| 浏览/下载：20/0 \| 提交时间：2023/02/07 Aeroelastic model balloon-borne flight test flight dynamic model longitudinal control numerical simulation solar powered UAV
	A multi-time scale solution strategy for an elastomeric aircraft 期刊论文 OAI收割 AEROSPACE SCIENCE AND TECHNOLOGY, 2020, 卷号: 103, 页码: 13 作者: Yang L(杨磊); Sun QH(孙泉华) \| 收藏 \| 浏览/下载：47/0 \| 提交时间：2020/08/26 Flight dynamic simulation Multi-time scale Elastomeric aircraft Reduced order models Store separation
	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.
	A strong coupled CFD-CSD method on computational aeroelastity (EI CONFERENCE) 会议论文 OAI收割 2011 2nd International Conference on Mechanic Automation and Control Engineering, MACE 2011, July 15, 2011 - July 17, 2011, Inner Mongolia, China Xi R.; Jia H. 收藏 \| 浏览/下载：67/0 \| 提交时间：2013/03/25 In this paper a strong coupled CFD-CSD method is developed to simulate the aeroelastic phenomena. The CFD solver is based on the finite-volume algorithm for the Navier-Stokes equations on unstructured grid. The CSD solver solves the aeroelastic governing equations in the modal space. Their coupling is realized by a dual-time method. The spring-based smoothing method is adopted to deform and regenerate the aerodynamic grid. Two test cases are selected to validate the authors' method for static and dynamic aeroelastity .The results of the simulation for the static aeroelastic problems of a missile wing show that the Lift Coefficient and Drag Coefficient are severally 7% and 5% lower than those don't consider the elasticity of the wing. The results for the flutter boundary prediction of the AGARD 445.6 wing have been proved much closer to the experiment than using the DLM. This method can describe the effects of fluid viscosity more exactly for highly nonlinear transonic flight conditions. The calculation has proved reliable in the subsonic regime but not accurate enough in the supersonic regime. 2011 IEEE.
	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.
	Application research of intelligent algorithm in electric-driven flight simulation turntable (EI CONFERENCE) 会议论文 OAI收割 ISECS International Colloquium on Computing, Communication, Control, and Management, CCCM 2008, August 3, 2008 - August 4, 2008, Guangzhou, China Xie M.-J.; Wang Z.-Q.; Wang L.-M. 收藏 \| 浏览/下载：39/0 \| 提交时间：2013/03/25 Application Research of Intelligent Algorithm in Electric-driven Flight Simulation Turntable is discussed in this paper. Fuzzy control is used to solve the problem of fast tracking and overshoot since its essence belongs to PD control In order to improve the performance of system in low speed a method named variance-gain adaptive algorithm is introduced in this paper. It defines the amplifier gain as a function whose independent variable is speed so the amplifier gain can automatically be adjusted with the change of speed. When the turntable runs at low speed it has a big amplifier gain a good rigidity and high tracking accuracy. When the turntable runs at high speed the method can control the amplifier gain and ensure the system dynamic performance. Design and implementation of these algorithms is introduced in detail. Experiment results show that the Flight Simulation Turntable has achieved the required performance through using fuzzy control algorithm and variance-gain adaptive algorithm. 2008 IEEE.