中国科学院机构知识库网格系统: 检索

Robust Flight Control Design Using Sensor-Based Backstepping Control for Unmanned Aerial Vehicles 期刊论文 OAI收割
Journal of Aerospace Engineering, 2017, 卷号: 30, 期号: 6, 页码: 04017068
作者: Cao, Lijia; Hu, Xiaoxiang; Zhang, Shengxiu; Liu, Yunfeng

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收藏 | 浏览/下载：39/0 | 提交时间：2018/11/20

Backstepping - Closed loop control systems - Closed loop systems - Control theory - Flight control systems - Flight simulators - System stability - Uncertainty analysis - Unmanned aerial vehicles (UAV) - Vehicles

Yb-doped large-mode-area aluminosilicate laser fibre fabricated by chelate precursor doping technique 期刊论文 OAI收割
electronics letters, 2016, 卷号: 52, 期号: 23, 页码: 1942-u42
作者: Peng, Kun; Wang, Zhen; Zhan, Huan; Ni, Li; Gao, Cong

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ytterbium aluminium compounds doping optical fibre fabrication optical fibre testing electron probe analysis secondary ion mass spectroscopy laser beams optical fibre amplifiers AlSiO:Yb power 1 kW efficiency 81 0 percent slope efficiency laser output two-stage master oscillator power amplifier system time-of-flight secondary ion mass spectrometry electron probe microanalysis fibre testing numerical aperture homogeneous large-core preform gas flow control system high-purity materials chelate precursor doping technique large mode area aluminosilicate laser fibre

微小型直升机姿态估计和鲁棒控制技术研究 学位论文 OAI收割
工学博士, 中国科学院自动化研究所: 中国科学院研究生院, 2012
作者: 常冠清

收藏 | 浏览/下载：61/0 | 提交时间：2015/09/02

微小型直升机姿态估计 EKF SR-UKF 自抗扰控制 Backstepping 自适应模糊系统飞控系统平台 Miniature Helicopters Attitude Estimation EKF SR-UKF ADRC Backstepping Adaptive Fuzy System Flight Control platform

Reliable attitude stability control of quad-rotor based on fault-tolerant approach (EI CONFERENCE) 会议论文 OAI收割
2012 9th IEEE International Conference on Mechatronics and Automation, ICMA 2012, August 5, 2012 - August 8, 2012, Chengdu, China
作者: Gao Q.

收藏 | 浏览/下载：46/0 | 提交时间：2013/03/25

The reliability flight property has received much attention within the aircraft control community throughout the last decades. In this paper the fault-tolerant control technique is introduced into the attitude stability control system of a quadrotor UAV in order to compensate the influence of the actuators fault of the aircraft. This control scheme is composed of two components: a robust fault detection module using the modelbased observation approach and a reconfigurable controller. Besides the designing procedure the theoretical analysis of robustness and stability of the designed FTC scheme are also contained in this article. And finally the availability of the proposed scheme is verified through numerical simulation. 2012 IEEE.

Three-loop autopilot design and simulation (EI CONFERENCE) 会议论文 OAI收割
2012 9th IEEE International Conference on Mechatronics and Automation, ICMA 2012, August 5, 2012 - August 8, 2012, Chengdu, China
作者: Zhang Y.

收藏 | 浏览/下载：49/0 | 提交时间：2013/03/25

In order to realize missile real-time change flight trajectory three-loop autopilot is setting up. The structure characteristics autopilot model and control parameters design method were researched. Firstly this paper introduced the 11th order three-loop autopilot model. With the principle of systems reduce model order the 5th order model was deduced. On that basis open-loop frequency characteristic and closed-loop frequency characteristic were analyzed. The variables of velocity ratio dynamic pressure ratio and elevator efficiency ratio were leading to correct system nonlinear. And then autopilot gains design method were induced. System flight simulations were done and result shows that autopilot gains played a good job in the flight trajectory autopilot satisfied the flight index. 2012 IEEE.

Adaptive control at launching using three loop autopilot (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
作者: Zhang Y.

收藏 | 浏览/下载：28/0 | 提交时间：2013/03/25

In order to guarantee the precise initial flight trajectory control the missile disturbance of large disturbance torque three loop adaptive autopilot was researched. The characteristics of the projectile and three loop autopilot instruction formation characteristics were analysed. From equivalent pitching angle of lateral acceleration feedback loop combined with the instruction of generalized error autopilot structure was simplified and three loop autopilot adaptive control law and stability were designed. The test data show that when disturbance torque was 600Nm the attitude angle generalized error was -4.4. In the time lasted about 15s late trajectory accuracy was within 1.0.Three loop autopilot adaptive control law was able to control the disturbance of initial trajectory and adapt to dynamic characteristics changes control system stability. It was the initial trajectory accurate solution method of flight. 2011 IEEE.

Stability control of quad-rotor based on explicit model following with inverse model feedforward method (EI CONFERENCE) 会议论文 OAI收割
2011 IEEE International Conference on Mechatronics and Automation, ICMA 2011, August 7, 2011 - August 10, 2011, Beijing, China
Bai Y.; Gong X.; Hou Z.; Tian Y.

收藏 | 浏览/下载：28/0 | 提交时间：2013/03/25

The quad-rotor is expected to carry out many different tasks. It is hoped that the quad-rotor can have different characteristics according to the different mission requirements. For this reason a flight stability augmentation control system based on explicit model following with inverse model feedforward control method is proposed in this paper. This control system is composed of an explicit model an inverse model and a feedback controller module. In order to calculate an inverse model of the coupled multivariable aircraft system a feedback linearization loop is also applied to this control system. At last simulations are performed to show the effectiveness of the designed stability augmentation control system in the presence of external disturbance and model uncertainty. The influence of explicit model to the characteristics of quad-rotor is also indicated in a contrast simulation result. 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：20/0 | 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.

小型无人直升机动力学建模、辨识及鲁棒飞行控制系统设计与优化研究 学位论文 OAI收割
工学博士, 中国科学院自动化研究所: 中国科学院研究生院, 2010
作者: 王晓东

收藏 | 浏览/下载：208/0 | 提交时间：2015/09/02

小型无人直升机数学建模预报误差法飞行控制系统 H∞回路成形多目标优化 MOGA-II small-scale unmanned helicopters mathematical modeling prediction error method flight control system H∞ loop shaping multi-objective optimizatio MOGA-II

Disc varifocal mechanism to improve efficiency of scene matching navigation system (EI CONFERENCE) 会议论文 OAI收割
2009 2nd International Conference on Future Information Technology and Management Engineering, FITME 2009, December 13, 2009 - December 14, 2009, Sanya, China
作者: Zhang C.-L.

收藏 | 浏览/下载：25/0 | 提交时间：2013/03/25

In order to meet special requests of optical imaging sensor in scene matching navigation system a disc varifocal mechanism is proposed for the flight vehicles of long flying time and range. Within small space occupied it can obtain real images with various resolutions. Moreover using plate traveling-wave Ultrasonic Motor as its driven motor can reduce energy loss improve control precision and ensure image obtaining being real-time and stable. Disc varifocal mechanism driven by plate traveling-wave Ultrasonic Motor is high-response and variation in load doesn't affect its performance parameter. Therefore applying disc varifocal mechanism in scene matching navigation system combing software and hardware can obviously improve the accuracy real-time and robust of scene matching navigation system. The experiment showed that when the weight of mechanism was 1.5kg the shortest starting was 0.6ms and the shortest shutoff was 0.5ms. 2009 IEEE.