机构

• 沈阳自动化研究所 [5]
• 长春光学精密机械与物... [4]
• 武汉物理与数学研究所 [3]
• 大连化学物理研究所 [1]
• 长春应用化学研究所 [1]

采集方式

• OAI收割 [14]

内容类型

• 期刊论文 [8]
• 会议论文 [6]

发表日期

• 2018 [1]
• 2017 [2]
• 2016 [1]
• 2014 [1]
• 2012 [1]
• 2011 [3]
• 更多

学科主题

筛选

浏览/检索结果: 共14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 Attitude Calculation Method Based on CPF-EKF for Large Load Plant Protection UAV 期刊论文  OAI收割 Nongye Jixie Xuebao/Transactions of the Chinese Society for Agricultural Machinery, 2018, 卷号: 49, 期号: 6, 页码: 24-31 and 77 作者:  Wu, Helong;  Bai, Yue;  Pei, Xinbiao;  Ma, Ping;  Peng, Cheng   |  收藏  |  浏览/下载：16/0  |  提交时间：2019/09/17 Extended Kalman filters  Antennas  Flight dynamics  Pesticides  Unmanned aerial vehicles (UAV)   Excited-state dynamics of m-dichlorobezene in ultrashort laser pulses 期刊论文  OAI收割 ACTA PHYSICA SINICA, 2017, 卷号: 66, 期号: 15 作者:  Shen Huan;  Hu Chun-Long;  Deng Xu-Lan   |  收藏  |  浏览/下载：29/0  |  提交时间：2017/12/06 Femtosecond Time-resolved  Time-of-flight Mass Spectroscopy  M-dichlorobenzene  Excitedstate Dynamics   Control techniques of tilt rotor unmanned aerial vehicle systems: A review 期刊论文  OAI收割 Chinese Journal of Aeronautics, 2017, 卷号: 30, 期号: 1, 页码: 135-148 作者:  Liu Z(刘重);  He YQ(何玉庆);  Yang LY(杨丽英);  Han JD(韩建达) 收藏  |  浏览/下载：22/0  |  提交时间：2017/02/05 Aircraft structures  Dynamics modeling  Flight control  Tilt rotors  Unmanned aerial vehicle (UAV)   Dynamics modelling and predictive control for 6-DOF rotorcraft aerial manipulator system 期刊论文  OAI收割 International Journal of Modelling, Identification and Control, 2016, 卷号: 26, 期号: 3, 页码: 227-237 作者:  Song DL(宋大雷);  Qi JT(齐俊桐)   |  收藏  |  浏览/下载：26/0  |  提交时间：2017/12/11 rotorcraft unmanned aerial vehicle  RUAV  aerial manipulator  dynamics modelling  predictive control  flight simulation   Modeling and control for unmanned helicopter based aerial manipulator 会议论文  OAI收割 6th International Conference on Modelling, Identification and Control, ICMIC 2014, Melbourne, VIC, Australia, December 3-5, 2014 作者:  Song DL(宋大雷);  Qi JT(齐俊桐) 收藏  |  浏览/下载：32/0  |  提交时间：2015/03/30 RUA V  Aerial Manipulator  Dynamics Modeling  Predictive Control  Flight Simulation   Ultrafast Predissociation Dynamics of Excited State of Acrylic Acid 期刊论文  OAI收割 ACTA PHYSICO-CHIMICA SINICA, 2012, 卷号: 28, 期号: 3, 页码: 522-527 作者:  Zhang Rong-Rong;  Qin Chao-Chao;  Long Jin-You;  Yang Ming-Hui;  Zhang Bing 收藏  |  浏览/下载：17/0  |  提交时间：2015/06/25 Time-resolved mass spectrum  Ultrafast dynamics  Pump-probe  Time-of-flight mass spectroscopy  Internal conversion   Reentry guidance based on feedback linearization (EI CONFERENCE) 会议论文  OAI收割 2011 International Conference on Electronics, Communications and Control, ICECC 2011, September 9, 2011 - September 11, 2011, Ningbo, China Li D.-W. 收藏  |  浏览/下载：30/0  |  提交时间：2013/03/25 This paper presents a new reentry guidance algorithm for RLV (Reusable Launching Vehicle). The algorithm consists of two integrated components: trajectory planning algorithm and tracking algorithm. The most striking feature of algorithm here lies in that both planning and tracking are executed directly in height-velocity space  which is different from the methodology of configuration of drag in traditional shuttle guidance. In the session of trajectory planning  all trajectory constraints can be expressed with upper bound and lower bound in height-velocity space  then a linear interpolation is carried to search the nominal trajectory satisfying the requirement of downrange and target constraints. Then the tracking algorithm uses feedback linearization method to track this nominal profile and meet all constraints. Another typical feature of this algorithm is the strategy of downrange extension using FPA (flight path angle) controller to fulfill the requirement of large downrange. Proper combination of planning-tracking algorithm and FPA controller can bring great flexibility and adaptability to reentry guidance. The algorithm is proved to be robust enough to accommodate the model error and noises in the dynamics. 2011 IEEE.   Research on model reference sliding mode control in roll stabilization of aerocraft (EI CONFERENCE) 会议论文  OAI收割 2011 International Conference on Electric Information and Control Engineering, ICEICE 2011, April 15, 2011 - April 17, 2011, Wuhan, China Chu H.-R. 收藏  |  浏览/下载：40/0  |  提交时间：2013/03/25 Aimed at aerospace roll stabilization  control arithmetic based on model reference sliding mode variable structure theory and chattering reduction arithmetic are formulated. Correctness and validity of arithmetic are analyzed. With flight dynamics  the roll-loop mathematic model and reference model are established. Sliding hyperplane is deduced based on model reference sliding mode variable structure theory. Combing with reaching law  control law is derived  and stability of roll-loop is analyzed. Chattering of aileron instructions is alleviate by using boundary layer approach. Digital flying simulation result shows that variable structure control arithmetic realized roll stabilization control  the roll angle is less than 5.3 under powered flight  and that of unpowered flight is less than 0.5  respectively. The command fin angle is less than 1.5. High frequency chattering of fin command nearby the minimum velocity was trailed off by chattering reduction arithmetic. The sliding mode control arithmetic show good performance when aerodynamic coefficients varies 20%. The control arithmetic is easy to be implemented for its simplicity. 2011 IEEE.   Dynamic coupling analysis and modeling for stabilized platform of rolling-pitching seeker (EI CONFERENCE) 会议论文  OAI收割 2011 International Conference on Electric Information and Control Engineering, ICEICE 2011, April 15, 2011 - April 17, 2011, Wuhan, China 作者:  Liu H.;  Liu H.;  Liu H. 收藏  |  浏览/下载：12/0  |  提交时间：2013/03/25 Missile's attitude change will be delivered to visual axis through stabilized platform during maneuvering flight  and the missile vibration will be an interference source to visual axis stabilization. In order to solve this problem  the coupling relationship between missile attitude and visual axis is obtained by Coordinate transformation. When the seeker stably tracks a target  the angular velocity of visual axis in inertial space is zero  so the relative angular velocity of roll axis and pitch axis can be derived for servo control. According to Oura dynamics equation  the dynamic models of roll axis and pitch axis were established and kinetic equations of two axises were obtained. The dynamic models can provide theoretical basis to developing research of servo control system and structural optimization design of stabilized platform. Finally  some measures could reduce the dynamic coupling between the framework was given. 2011 IEEE.   Active modeling based model predictive control for yaw-heave coupling dynamics of unmanned helicopters in full flight envelope 会议论文  OAI收割 AUVSI Unmanned Systems North America Conference 2009, Washington, DC, United states, August 10-13, 2009 作者:  Song DL(宋大雷);  Qi JT(齐俊桐);  Han JD(韩建达) 收藏  |  浏览/下载：25/0  |  提交时间：2012/06/06 Actuators  Controllers  Dynamics  Flight envelopes  Helicopters  Predictive control systems  Robust control