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	1. Modeling and Simulation of Stochastic Optimal Control for Gliding Extended Range Rocket Projectile Attitude
	Bian Wei-wei,LI Yan,XIN Zhen-fang,CHANG Si-jiang
	Aviation 30 November 2015
	Show/Hide Abstract \| Cite this paper︱Full-text: PDF (4K B)

	Abstract:An optimal control method for nonlinear stochastic systems is proposed to overcome the influence of various disturbance factors and to improve the control effect. Considering the general control principle of rocket projectile flight process, a differential form of attitude dynamics model is established. Taking the attack angle and the yaw angle as observation variables and rudder angles as control variables, the state equations, the quadratic cost function and the control law are presented. The detailed expression of the adjoint function is put forward. The optimal filter is designed based on the Riccati equation. Control parameter is designed and simulation analysis is carried out by taking gliding starting control point as the feature point. The simulation results show that the attitude controller system responds quickly and has good control quality.
	TO cite this article:Bian Wei-wei,LI Yan,XIN Zhen-fang, et al. Modeling and Simulation of Stochastic Optimal Control for Gliding Extended Range Rocket Projectile Attitude[OL].[30 November 2015] http://en.paper.edu.cn/en_releasepaper/content/4667119


	2. A robust sequence image matching algorithm for solving flight position and heading
	Ru Jiangtao,Leng Xuefei,Wu Songsen,Mao Xingyun,Gong Zhe
	Aviation 19 September 2015
	Show/Hide Abstract \| Cite this paper︱Full-text: PDF (4K B)

	Abstract:As for the transformations of translation and rotation exist between sequence images in the image matching navigation system, it is hoped that the algorithm can simultaneously solve the position and heading parameters. Therefore, an algorithm for sequence image matching based on Harris corner and modified hausdorff distance was proposed. In this method, the coordinates of the corners are described in both polar coordinates and Descartes coordinates. Considering the rotational invariance of radius set in polar coordinates, Hausdorff distance is used to match radius sets between sequence images. Then, the rotation angle and the translation distance will be calculated. Experimental analysis has been carried out for the influence of different Gauss noise and the number of Harris corner. Results show that images can still be matched with rotation angle of ${0^ circ }$, ${60^ circ }$, and ${90^ circ }$ under Gauss white noise with 0.01 variance while the position error is less than one pixel, heading error is less than 5 degrees, and matching time is about 4 seconds. The algorithm has robustness and can meet the requirements of real-time and accuracy of sequence image matching for navigation system.
	TO cite this article:Ru Jiangtao,Leng Xuefei,Wu Songsen, et al. A robust sequence image matching algorithm for solving flight position and heading[OL].[19 September 2015] http://en.paper.edu.cn/en_releasepaper/content/4654929


	3. Deep Space Quantum Communication and Navigation
	CUI Pingyuan,YU Zhengshi
	Aviation 02 April 2014
	Show/Hide Abstract \| Cite this paper︱Full-text: PDF (4K B)

	Abstract:At present, deep space navigation primarily depends on the Deep Space Network. To meet the challenges of future Solar and Galaxy explorations, this paper proposes the concept of deep space quantum communication and navigation. Such a communication and navigation network with high speed, broad bandwidth, and high accuracy will be constructed based on the quantum communication mechanism and relay communication architecture. This communication and navigation network may support the basic scheme of deep space quantum communication and navigation.
	TO cite this article:CUI Pingyuan,YU Zhengshi. Deep Space Quantum Communication and Navigation[OL].[ 2 April 2014] http://en.paper.edu.cn/en_releasepaper/content/4592155


	4. Optimal ZEM/ZEV Feedback Guidance for Mars Powered Descent Phase
	ZHOU Liuyu,,XIA Yuanqing
	Aviation 07 November 2013
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	Abstract:This paper applies the zero-effort-miss (ZEM) and zero-effort-velocity (ZEV) optimal feedback guidance algorithm to the Mars powered descent problem. Detailed descriptions have been given to this algorithm. The main advantage of this optimal guidance law is that it can not only meet the final position and velocity requirement at the same time, but also be fuel-optimal. For future Mars landing mission, the thrust-limited engine is most likely to be used. The optimal final time will be studied and determined by simulation which can minimize the fuel usage while ensuring precision landing and no-subsurface constraints. And the optimal sliding-mode guidance(OSG) which is a modification of optimal guidance law(OGL) will also be discussed and compared with the pure optimal guidance law for the Mars powered descent phase. Monte Carlos are run to test the robustness and reliability of the two algorithms which show that the two algorithms can achieve precise landing perfectly and have nearly identical performance in robustness and reliability.
	TO cite this article: ZHOU Liuyu,,XIA Yuanqing. Optimal ZEM/ZEV Feedback Guidance for Mars Powered Descent Phase[OL].[ 7 November 2013] http://en.paper.edu.cn/en_releasepaper/content/4568642


	5. Mars Entry Guidance Based on Predictor-Corrector Algorithm
	ZHOU Liuyu,XIAYuanqing,CHEN Rongfang,CUI Pingyuan
	Aviation 11 October 2013
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