中国开放科研知识云: 检索

Speed control for K mirror of 2 m telescope based on adaptive active disturbance rejection-controller 期刊论文
Hongwai yu Jiguang Gongcheng/Infrared and Laser Engineering, 2018, 卷号: 47, 期号: 7
作者: Xia, Peipei; Wang, Zhiqian; Li, Hongwen; Deng, Yongting; Wang, Xianjun

收藏 | 浏览/下载：14/0 | 提交时间：2019/09/17

Adaptive control systems Controllers Disturbance rejection Mirrors Regression analysis Scattering parameters Servomechanisms Speed Speed control Speed regulators Step response Telescopes

Reentry guidance based on parametric optimization (EI CONFERENCE) 会议论文
2012 International Conference on Mechatronics and Control Engineering, ICMCE 2012, November 29, 2012 - November 30, 2012, Guangzhou, China
Li D.

收藏 | 浏览/下载：147/0 | 提交时间：2013/03/25

This paper presents a parametric optimization approach to solve reentry guidance. Due to the various constraints imposed on the trajectory original guidance problem can be converted into an optimal control problem with a merit function to be minimized. Direct implementation of method of variation and is too complex to get a reasonable result while a numerical parametric optimization approach is feasible and efficient if we choose appropriate control variables as the optimization parameters and effective optimization algorithm. A simulation of the approach is performed to show its validity on reentry guidance problem: as the value of merit function converges to acceptable threshold all constraints are hold. (2013) Trans Tech Publications Switzerland.

Longitudinal control law design and simulation of fixed-wing UAV (EI CONFERENCE) 会议论文
2012 International Conference on Measurement, Instrumentation and Automation, ICMIA 2012, September 15, 2012 - September 16, 2012, Guangzhou, China
Duan Z.

收藏 | 浏览/下载：19/0 | 提交时间：2013/03/25

Taken some fixed-wing UAV as the study object the aircraft movement was broken down into the longitudinal movement and lateral movement according to the linearized small perturbation principle the longitudinal control law design method was discussed using root locus which belonged to classical control theory. The six degrees of freedom nonlinear model simulation result shows that: the control parameters designed are reasonable the simulation profile is fully consistent with the setting profile the control effect of pitch angle loop and altitude loop meets with the indices requirements the method is mature and reliable easy to realize in engineering. (2013) Trans Tech Publications Switzerland.

Trajectory tracking control of a quad-rotor UAV based on command filtered backstepping (EI CONFERENCE) 会议论文
2012 3rd International Conference on Intelligent Control and Information Processing, ICICIP 2012, July 15, 2012 - July 17, 2012, Dalian, China
Gong X.; Bai Y.; Peng C.; Zhao C.; Tian Y.

收藏 | 浏览/下载：23/0 | 提交时间：2013/03/25

A quad-rotor unmanned aerial vehicle is an under-actuated strong coupled nonlinear system with parameters uncertainty and unknown external aerodynamic disturbance. The trajectory tracking control system with a nested double-loops structure is designed in this paper according to the coupling characteristic between the attitude angles and translational position. A PD control algorithm is proposed in the translational outer-loop to export the desired attitude signals to the attitude inner-loop. An adaptive backstepping control algorithm is designed in the inner-loop with respect to the uncertain rotational inertia and un-modeled disturbance while in order to reduce the computational complexity the command filtered approach is introduced into the designing procedure. And finally the numerical simulation results are presented for the trajectory tracking stabilization of a Quad-rotor which demonstrates the excellent performance of the proposed control system and illustrate its robustness in face of disturbance and uncertain parameters. 2012 IEEE.

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

收藏 | 浏览/下载：39/0 | 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.

The sequence measurement system of the IR camera (EI CONFERENCE) 会议论文
International Symposium on Photoelectronic Detection and Imaging 2011: Advances in Infrared Imaging and Applications, May 24, 2011 - May 24, 2011, Beijing, China
Geng A.-H.; Han H.-X.; Zhang H.-B.

收藏 | 浏览/下载：28/0 | 提交时间：2013/03/25

Design of thermostat system based on Proteus simulation software (EI CONFERENCE) 会议论文
2011 International Conference on Electronic and Mechanical Engineering and Information Technology, EMEIT 2011, August 12, 2011 - August 14, 2011, Harbin, China
Han Z.; Song K.

收藏 | 浏览/下载：33/0 | 提交时间：2013/03/25

In order to solve the problem of precise temperature control the thermoelectric cooler (TEC) principle widely used is analyzed for the design of the whole control process and selection of control parameters and then accurate simulation model of the TEC is established in Proteus simulation software. Moreover combined with the traditional circuit simulation model the temperature control loop is designed and the response characteristics of the system are tested using an input signal similar to the unit-step function to achieve the precise temperature control. Simulation results show that the proposed control circuits can precisely convert error signal to output voltage sent to TEC model and TEC model behaves approximately like a two-pole system. The first pole starts at 20mHz and a second pole at 1Hz. 2011 IEEE.

Study on the servo system of large telescope based on the internal model pid control strategy (EI CONFERENCE) 会议论文
IEEE 2011 10th International Conference on Electronic Measurement and Instruments, ICEMI 2011, August 16, 2011 - August 18, 2011, Chengdu, China
Li H.

收藏 | 浏览/下载：15/0 | 提交时间：2013/03/25

This paper developed the internal model PID control for large telescope control system considerations in more parameters adjustment in servo control loop at present. The large electro-optic telescope system belongs to a big inertia system. This simplifies the debug process the feasibility and robustability are also verified by the analyses and simulation results that satisfy the high precision demand. The practicability of this algorithm is verified in an actual project that only two parameters need adjusted. The application shows that this system runs stably with high accuracy. The technology and methods adopted in the system are practical and worthy of using abroad. 2011 IEEE.

The aircraft autopilot design of parameters changing in a wide range (EI CONFERENCE) 会议论文
2011 International Conference on Electric Information and Control Engineering, ICEICE 2011, April 15, 2011 - April 17, 2011, Wuhan, China
Zhen D.; Yue Z.

收藏 | 浏览/下载：19/0 | 提交时间：2013/03/25

Autopilot is an important part of aircraft Under the action of the disturbance torque for the flight parameters of aircraft Changing in a wide range the range was about 16km on the basic of analyzing the typical trajectory the max height was about 5100m the trajectory of feature points were selected the deviation of lateral was about 12m taking pitch control loop for example the maximum angle of attack was about 3.6 a sub- PID autopilot was designed using classical control theory the maximum elevator deflection was less than 5 using single-mode Transient suppression method the maximum aileron deflection was less than 2 the overload due to control surface transition deflection was avoided when control parameters changing the maximum roll was less than 5 the verification was done by non-linear simulation. The result showed that: the phase margin of autopilot was greater than 30 the response of overload can accurately track the given overload instruction. An autopilot design method of aircraft of parameter changes in a wide range was provided. 2011 IEEE. the bandwidth was more than 14rad / s the settling time was less than 0.7s the maximum overshoot was 23.3%

A fuzzy control method based on information integration for double inverted pendulum (EI CONFERENCE) 会议论文
2011 2nd International Conference on Digital Manufacturing and Automation, ICDMA 2011, August 5, 2011 - August 7, 2011, Zhangjiajie, Hunan, China
Fan Y.; Sang Y.; Liu B.

收藏 | 浏览/下载：52/0 | 提交时间：2013/03/25

This article proposes a new fuzzy controller based on information integration. The mathematical model of Linear double inverted pendulum has been studied and estabLished with dynamics analytical method and LQR theory is used to design the optimal Linear inverted pendulum controller then the integration technology is used to design the variable parameters self-tuning fuzzy controller. Thereby the fuzzy controller input variable dimension and the number of fuzzy control rules have been extremely reduced. Two controllers are designed for inverted pendulum system control and the comparison simulation experiments have been done. The results show that the controllers can both reaLize good control and the fuzzy controller has higher precision faster response better stabiLity and robustness. 2011 IEEE.

在结果中检索

相关链接

CORC

联系我们