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	Missile guidance with assisted deep reinforcement learning for head-on interception of maneuvering target 期刊论文 OAI收割 COMPLEX & INTELLIGENT SYSTEMS, 2021, 页码: 12 作者: Li, Weifan; Zhu, Yuanheng; Zhao, Dongbin \| 收藏 \| 浏览/下载：37/0 \| 提交时间：2021/12/28 Reinforcement learning Missile guidance Auxiliary learning Self-imitation learning
	The ship-borne infrared searching and tracking system based on the inertial platform (EI CONFERENCE) 会议论文 OAI收割 International Symposium on Photoelectronic Detection and Imaging 2011: Advances in Infrared Imaging and Applications, May 24, 2011 - May 24, 2011, Beijing, China 作者: Li Y.; Zhang H. 收藏 \| 浏览/下载：38/0 \| 提交时间：2013/03/25 As a result of the radar system got interferenced or in the state of half silent it can cause the guided precision drop badly In the modern electronic warfare therefore it can lead to the equipment depended on electronic guidance cannot strike the incoming goals exactly. It will need to rely on optoelectronic devices to make up for its shortcomings but when interference is in the process of radar leading especially the electro-optical equipment is influenced by the roll pitch and yaw rotation it can affect the target appear outside of the field of optoelectronic devices for a long time so the infrared optoelectronic equipment can not exert the superiority and also it cannot get across weapon-control system "reverse bring" missile against incoming goals. So the conventional ship-borne infrared system unable to track the target of incoming quickly the ability of optoelectronic rivalry declines heavily.Here we provide a brand new controlling algorithm for the semi-automatic searching and infrared tracking based on inertial navigation platform. Now it is applying well in our XX infrared optoelectronic searching and tracking system. The algorithm is mainly divided into two steps: The artificial mode turns into auto-searching when the deviation of guide exceeds the current scene under the course of leading for radar.When the threshold value of the image picked-up is satisfied by the contrast of the target in the searching scene the speed computed by using the CA model Least Square Method feeds back to the speed loop. And then combine the infrared information to accomplish the closed-loop control of the infrared optoelectronic system tracking. The algorithm is verified via experiment. Target capturing distance is 22.3 kilometers on the great lead deviation by using the algorithm. But without using the algorithm the capturing distance declines 12 kilometers. The algorithm advances the ability of infrared optoelectronic rivalry and declines the target capturing time by using semi-automatic searching and reliable capturing-tracking when the lead deviation of the radar is great. 2011 Copyright Society of Photo-Optical Instrumentation Engineers (SPIE).
	LOS rate reconstruction and application of roll-pitch seeker (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 Yang C.; Zhang N.; Jia H. 收藏 \| 浏览/下载：22/0 \| 提交时间：2013/03/25 Frame motion form of roll-pitch seeker is introduced in this paper. There is corresponding relationship between the frame angle of the roll-pitch seeker and the traditional yaw-pitch seeker. The discrepancy of line-of-sight (LOS) rate of the two seekers is caused by the different frame motion forms. LOS rate reconstruction method of roll-pitch seeker is deduced. Compared to the pure proportional navigation guidance law the true proportional navigation guidance law is more suitable for the roll-pitch seeker missile guidance. 2011 IEEE.
	The design of missile's dome that fits both optical and aerodynamic needs (EI CONFERENCE) 会议论文 OAI收割 5th International Symposium on Advanced Optical Manufacturing and Testing Technologies: Smart Structures and Materials in Manufacturing and Testing, April 26, 2010 - April 29, 2010, Dalian, China 作者: Zhang X.; Zhang X.; Zhang X. 收藏 \| 浏览/下载：14/0 \| 提交时间：2013/03/25 Optical guidance missiles requires a dome which fits both optical and aerodynamic needs when they attack at 3 Ma. In this study ellipse is the figure chosen to be the dome's shape. The ellipticity is the main variable should to be decided. The optimized function was built by optical and aerodynamic performance function multiply by their weights. The optical and aerodynamic functions were all obtained by computational fluid dynamic (CFD) simulation's results after normalization. In this study the optical and aerodynamic performances have equal weights after optimzing the ellipticity is 2 for the missile. 2010 SPIE.