中国科学院机构知识库网格系统: 检索

浏览/检索结果: 共10条，第1-10条

帮助

条数/页：排序方式：
	Research on Panel Flutter Considering the Effect of Convective Active Cooling 期刊论文 OAI收割 APPLIED SCIENCES-BASEL, 2023, 卷号: 13, 期号: 8, 页码: 4925 作者: Huang J(黄杰); Lu WS(陆维爽); Yang GW(杨国伟); Zheng GN(郑冠男) \| 收藏 \| 浏览/下载：10/0 \| 提交时间：2023/06/15 panel flutter coolant action flight stability flutter suppression
	Design of support structure for deep space detection remote sensing camera 期刊论文 OAI收割 Hongwai yu Jiguang Gongcheng/Infrared and Laser Engineering, 2018, 卷号: 47, 期号: 6 作者: Ma, Cong; Li, Wei; Zhang, Yuanqing; Li, Xiaobo; An, Mingxin \| 收藏 \| 浏览/下载：16/0 \| 提交时间：2019/09/17 Remote sensing Cameras Earth (planet) Ground supports Interplanetary flight Mirrors Optical systems Orbits Satellites Space optics Space probes Space research Thermodynamic stability
	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 \| 收藏 \| 浏览/下载：36/0 \| 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
	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：40/0 \| 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.
	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：25/0 \| 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.
	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.
	Control method research on wide flight envelope aerocraft (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: Duan Z. 收藏 \| 浏览/下载：27/0 \| 提交时间：2013/03/25 The flying qualities of aerocraft was directly effected by the autopilot for the wide flight envelope aerocraft on the basic of analyzing the typical trajectory the three loop autopilots of roll stability pitch and yaw were designed using single-mode Transient suppression method the overload due to control surface transition deflection was avoided when control parameters changing the verification was done by non-linear simulation. The result showed that: Under the action of the disturbance torque the maximum roll was less than 5 the range of the aerocraft was from 13.5km to 22.4km the max height was about 5100m the max deviation of lateral was about 42m the maximum elevator deflection was less than 6.5 the control law was applicable within the effective range. An autopilot design method of wide flight envelope aerocraft was provided. 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：20/0 \| 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.
	Valence of Precursor Compound Effects on the Stability and Composition of Cu/Cl Binary Cluster Produced by Laser Vaporization 期刊论文 OAI收割 acta physico-chimica sinica, 1997, 卷号: 13, 期号: 10, 页码: 933-937 作者: Li Haiyang; Ma Chensheng; Bai Jiling; He Guozhong 收藏 \| 浏览/下载：27/0 \| 提交时间：2015/11/12 Cluster Laser vaporization Time-of-flight mass spectrometry Magic number Stability