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• 会议论文 [9]
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浏览/检索结果: 共13条，第1-10条 帮助 条数/页： 5101520253035404550556065707580859095100 排序方式： 请选择题名升序题名降序提交时间升序提交时间降序作者升序作者降序发表日期升序发表日期降序 Online Adaptive Dynamic Programming for Optimal Self-Learning Control of VTOL Aircraft Systems With Disturbances 期刊论文  OAI收割 IEEE TRANSACTIONS ON AUTOMATION SCIENCE AND ENGINEERING, 2024, 卷号: 21, 期号: 1, 页码: 343-352 作者:  Wei, Qinglai;  Yang, Zesheng;  Su, Huaizhong;  Wang, Lijian   |  收藏  |  浏览/下载：20/0  |  提交时间：2024/07/03 Adaptive dynamic programming (ADP)  VTOL aircraft system  policy iteration  neural network (NN)  optimal control  iterative errors   Design, modeling, and control of morphing aircraft: A review 期刊论文  OAI收割 Chinese Journal of Aeronautics, 2022, 页码: 1-27 作者:  Chu LL(禇玲玲);  Li Q(李琦);  Gu F(谷丰);  Du XT(杜心田);  He YQ(何玉庆)   |  收藏  |  浏览/下载：42/0  |  提交时间：2021/12/31 Aircraft design  Dynamic modeling  Fault tolerance  Flight control  Intelligent material  Morphing aircraft  Unmanned Aerial Vehicles (UAV)   Vibration Characteristics of Unsaturated Runways Under Moving Aircraft Loads 期刊论文  OAI收割 INTERNATIONAL JOURNAL OF STRUCTURAL STABILITY AND DYNAMICS, 2021, 卷号: 21, 期号: 05, 页码: 19 作者:  Tang, Chuxuan;  Lu, Zheng;  Yao, Hailin;  Guo, Shuan;  Han, Yukun   |  收藏  |  浏览/下载：41/0  |  提交时间：2021/06/18 Dynamic response  unsaturated ground  Fourier transform  aircraft loads  critical speed   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：48/0  |  提交时间：2020/08/26 Flight dynamic simulation  Multi-time scale  Elastomeric aircraft  Reduced order models  Store separation   Monitoring Target Through Satellite Images By Using Deep Convolutional NetworksCNN Based Aircraft Dynamic Monitoring through Remote Sensing Images 会议论文  OAI收割 ICDIP2017, 中国香港, 2017-5 作者:  Sui XD(随旭东);  Hu XH(胡晓惠);  Zhang JF(张金芳) 收藏  |  浏览/下载：26/0  |  提交时间：2017/07/08 Aircraft Dynamic  Monitoring Method  Priori Model  CNN   A conceptual design of next generation hypersonic air-breathing airplanes with dual waveriders forebody 会议论文  OAI收割 20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference, 2015, Glasgow, United kingdom, July 6, 2015 - July 9, 2015 作者:  Cui K(崔凯);  Hu SC(胡守超);  Li GL;  Xiao Y(肖尧);  Situ M 收藏  |  浏览/下载：32/0  |  提交时间：2017/05/05 Aero  dynamic performance  Aerodynamic performance predictions  Design Methodology  Flight altitudes  Numerical results  Propulsion system  Turbulent models  Wing body aircraft   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.   Analysis on the influence of random vibration on MEMS gyro precision and error compensation (EI CONFERENCE) 会议论文  OAI收割 2011 3rd International Conference on Mechanical and Electronics Engineering, ICMEE 2011, September 23, 2011 - September 25, 2011, Hefei, China 作者:  Li M. 收藏  |  浏览/下载：24/0  |  提交时间：2013/03/25 In order to improve its precision in dynamic environment  a Kalman filter was designed. Firstly  two sets of random drift data of MEMS gyro were respectively analysed  and it was found that the variance of random drift under random vibration significantly increased and its mean also changed. Then calculation results show that attitude angle error under random vibration is 2.6  while in the static test it is 0.25. Analysis on the characteristics of random drift was carried out  and it is found that it can be treated as stable  normally distributed random signal. Finally  a corresponding Kalman filter was designed. The results indicated that after filtering the variance of random drift is reduced to 0.0282  26.4% of pre-filtering and the attitude angle error is reduced to 1.5  57.7% of pre-filtering. The above method can effectively compensate for the attitude angle error of MEMS gyro caused by random vibration. This study can be a reference to the application of low-cost MEMS gyro in aircraft navigation. (2012) Trans Tech Publications  Switzerland.   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.   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.