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1. Research on multi-UAV focused area cooperative search based on MTSP | |||
Xu Jianfeng,Zhuang Yufeng | |||
Aviation 17 March 2022 | |||
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Abstract:This paper takes the multi-UAV area search problem as the background, addresses the multi-UAV collaborative search track planning task assignment problem in which the target location is known in the environment but the number of targets is large and the target location is randomly dispersed, combines the multi-traveler MTSP problem, establishes a multi-UAV focused collaborative search track planning task assignment model, and designs a GA algorithm based on the target location coding multi-crossing operator multivariable operator and an improved SA algorithm for multi-UAV collaborative focused search track planning, both algorithms have better solution effects, and the SA algorithm has better optimized solution effects than the GA algorithm. | |||
TO cite this article:Xu Jianfeng,Zhuang Yufeng. Research on multi-UAV focused area cooperative search based on MTSP[OL].[17 March 2022] http://en.paper.edu.cn/en_releasepaper/content/4757044 |
2. 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 | |||
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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 |
3. 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 | |||
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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 |
4. Deep Space Quantum Communication and Navigation | |||
CUI Pingyuan,YU Zhengshi | |||
Aviation 02 April 2014 | |||
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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 |
5. 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 |
6. Mars Entry Guidance Based on Predictor-Corrector Algorithm | |||
ZHOU Liuyu,XIAYuanqing,CHEN Rongfang,CUI Pingyuan | |||
Aviation 11 October 2013 | |||
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Abstract:This paper addresses the development and evaluation of the numerical predictor-corrector algorithm for the Mars entry guidance.The requirement of future Mars missions is to enable pinpoint and high elevation Mars landing.There are two main entry guidance algorithms: guidance using a reference trajectory and guidance using predictor-corrector.Guidance algorithm that tracks the reference trajectory during entry, has some degree of model-independence and does not require fast on-board computation, but it is sensitive to initial conditions.However, the predictor-corrector algorithm can be less sensitive to initial dispersions, but needs fast on-board computation.Detailed descriptions of predictor-corrector algorithm, lateral control logic and heading alignment are given and an improved predictor-corrector algorithm is provided to shorten the on-board computational time. Simulation results show that this entry guidance algorithm demonstrates reliable and robust performance in situations with high uncertainties. | |||
TO cite this article:ZHOU Liuyu,XIAYuanqing,CHEN Rongfang, et al. Mars Entry Guidance Based on Predictor-Corrector Algorithm[OL].[11 October 2013] http://en.paper.edu.cn/en_releasepaper/content/4563676 |
7. Adaptive Back-Stepping Sliding Mode Attitude Tracking of Rigid Spacecraft with disturbances}%uthorCHN{张三丰ffil{1},李四ffil{2} | |||
LU Kunfeng,XIA Yuanqing | |||
Aviation 23 December 2012 | |||
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Abstract:The attitude tracking control problem for rigid spacecraft is investigated in thispaper. A novel adaptive approach is proposed with the utilization of sliding mode control(SMC) and backstepping techniques (BT) to not only achieve accurate attitude tracking control forspacecraft system, but also be robust against the inertia uncertainties and external disturbances. The proposed controller including the merits of SMC, BT and adaptive technique to provide fast response and accurate attitude tracking. The proposed controller is continuous, then it is chattering-free. What's more, the proposed controller does not include any information of unknown inertial matrix, then it can be used widely in practical application. Finally, simulation results are presented to illustrate effectiveness of the control strategies. | |||
TO cite this article:LU Kunfeng,XIA Yuanqing. Adaptive Back-Stepping Sliding Mode Attitude Tracking of Rigid Spacecraft with disturbances}%uthorCHN{张三丰ffil{1},李四ffil{2}[OL].[23 December 2012] http://en.paper.edu.cn/en_releasepaper/content/4502987 |
8. NTSM based finite-time control for 6DOF spacecraft formation flying system | |||
Lan Qixun,Li Shihua | |||
Aviation 13 December 2012 | |||
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Abstract:This paper considers the finite-timecontrol (FTC) problem of 6DOF spacecraft formation flying (SFF)system in the presence of externaldisturbances. Firstly, a nonsingularterminal sliding mode (NTSM) technique a finite time controller is proposed for 6DOF SFF system.Secondly, a finite-time disturbance observer (FTDOB) is introducedto estimate the disturbances , then acomposite controller which consists of a feedback controller basedon NTSM method and feed-forward compensation term based on FTDOBtechnique is obtained to ensure that the 6DOF spacecraft canreach the desired formation in finite time. The merit of theproposed method is that chattering is substantially reduced sincethe switching gain of the controller is only requiredto be greater than the bound of disturbance estimation error ratherthan that of disturbance. Finally,the effectiveness of the proposed methods are shown bysimulation results. | |||
TO cite this article:Lan Qixun,Li Shihua . NTSM based finite-time control for 6DOF spacecraft formation flying system[OL].[13 December 2012] http://en.paper.edu.cn/en_releasepaper/content/4501134 |
9. Research on Sliding Mode Control of Folding-Wing Missile’s Lateral Overload | |||
Yang Liang,Yang Jianying | |||
Aviation 23 February 2009 | |||
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Abstract:Considering that the folding-wing missile deploys its wings in short time, and such a transient but complicated process has a strong influence on its math model, we simplify the process into model\ | |||
TO cite this article:Yang Liang,Yang Jianying. Research on Sliding Mode Control of Folding-Wing Missile’s Lateral Overload[OL].[23 February 2009] http://en.paper.edu.cn/en_releasepaper/content/29503 |
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