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	Sliding Mode Guidance Law Considering Missile Dynamic Characteristics and Impact Angle Constraints 期刊论文 OAI收割 International Journal of Automation and Computing, 2018, 卷号: 15, 期号: 2, 页码: 218-227 作者: Hui-Bo Zhou; Jun-Hong Song; Shen-Min Song \| 收藏 \| 浏览/下载：19/0 \| 提交时间：2021/02/23 Autopilot impact angle nonsingular terminal sliding mode finite-time convergent guidance.
	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.
	The aircraft autopilot design of parameters changing in a wide range (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 Zhen D.; Yue Z. 收藏 \| 浏览/下载：30/0 \| 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%
	The research on test scheme of the digital Electromechanical Actuator based on CAN Bus (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 J.; Zhang J. 收藏 \| 浏览/下载：34/0 \| 提交时间：2013/03/25 In order to realize the digital of Electromechanical Actuator(EMA) control system the CAN Bus which has efficient reliable performance and flexible network modes works as data interface.The EMA test scheme is designed based on the CAN Bus.First of all the microcontroller DSP with the CAN Bus works as the core of the EMA control system circuit boards.Then the CAN Bus test network is established with the EMA Ground Test System and Autopilot computer.The function and self-check of the EMA canbe conveniently tested by the network and the result of the test canbe easily displayed in the PC.Finally the CAN Bus test network is established with the EMA the Frequency Characteristics Scanner and etc.The purpose is to test the performance of the EMA.The result of the test can be intuitively showed on the Frequency Characteristics Scanner.In a word the application of the CAN bus provides a new method to test the EMA and reference to engineering the digital EMA which has vital significance. 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：31/0 \| 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.
	基于虚拟航向的智能自动舵控制方法研究学位论文 OAI收割工学硕士, 中国科学院自动化研究所: 中国科学院研究生院, 2007 卢雄辉收藏 \| 浏览/下载：73/0 \| 提交时间：2015/09/02 船自动舵虚拟航向模糊控制遗传算法跟踪 ship autopilot virtual course fuzzy logic genetic algorithm tracking