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	Nonsingular Terminal Sliding Mode Control With Ultra-Local Model and Single Input Interval Type-2 Fuzzy Logic Control for Pitch Control of Wind Turbines 期刊论文 OAI收割 IEEE/CAA Journal of Automatica Sinica, 2021, 卷号: 8, 期号: 3, 页码: 690-700 作者: Saber Abrazeh; Ahmad Parvaresh; Saeid-Reza Mohseni; Meisam Jahanshahi Zeitouni; Meysam Gheisarnejad \| 收藏 \| 浏览/下载：34/0 \| 提交时间：2021/04/09 Interval type-2 (IT2) fuzzy logic control model-independent nonsingular terminal sliding-mode control (MINTSMC) pitch angle control real-time software-in-the-loop (RT-SiL)
	Sea-Whale 2000: A Long-range Hybrid Autonomous Underwater Vehicle for Ocean Observation 会议论文 OAI收割 Marseille, France, June 17-20, 2019 作者: Huang Y(黄琰); Qiao JN(乔佳楠); Yu JC(俞建成); Wang ZY(王振宇); Xie ZB(谢宗伯) \| 收藏 \| 浏览/下载：62/0 \| 提交时间：2019/12/23 AUV long-range hybrid driven pitch angle control fuzzy PI
	Longitudinal control law design and simulation of fixed-wing UAV (EI CONFERENCE) 会议论文 OAI收割 2012 International Conference on Measurement, Instrumentation and Automation, ICMIA 2012, September 15, 2012 - September 16, 2012, Guangzhou, China 作者: Duan Z. 收藏 \| 浏览/下载：27/0 \| 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.
	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：28/0 \| 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%
	Analysis of zenith pass problem in a roll-pitch optics seeker (EI CONFERENCE) 会议论文 OAI收割 2011 International Conference on Electronics and Optoelectronics, ICEOE 2011, July 29, 2011 - July 31, 2011, Dalian, China 作者: Jiang H. 收藏 \| 浏览/下载：30/0 \| 提交时间：2013/03/25 There are mainly two kind of structures for a missile two-axes seeker which is always mentioned as elevate-azimuth and roll-pitch. The elevate-azimuth structured seeker has been studied for a long time and it is applied in all sort of missiles. Not only structure design but also control algorithm of the elevate-azimuth seeker are deeply developed. But for elevate-azimuth seeker there are several disadvantages such as big size and large abaxial angle blind. So the elevate-azimuth seeker gimbal angle is designed up to 65 according to relative references. In modern air war it is important for a missile to have the ability of "first recognize" and "first attack". That means the air to air missile seeker is required to be a system with large gimbal angle and large abaxial launch angle. With the mentioned requirement roll-pitch seeker with its advantages smart size and large gimbal angle is studied widely and deeply. The pitch angle of roll-pitch is up to 90 while its roll angle up to n 360. But there are also some disadvantages for the roll-pitch seeker the most troublesome one is the zenith pass problem. The zenith pass problem is brought about from the gimbal kinematics it is said that when target moves in the center of image plane roll servo command gotten from the kinematics algorithm will go to infinite. Math model of zenith pass problem is proposed in this paper and two ways to solve the problem are brought forward. 2011 IEEE.