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| 1 | Fixed-time adaptive model reference sliding mode control for an air-to-ground missile显示文摘This paper addresses the fixed-time adaptive model reference sliding mode control for an air-to-ground missile associated with large speed ranges, mismatched disturbances and un-modeled dynamics. Firstly, a sliding mode surface is developed by the tracking error of the state equation and the model reference state equation with respect to the air-to-ground missile. More specifically,a novel fixed-time adaptive reaching law is presented. Subsequently, the mismatched disturbances and the un-modeled dynamics are treated as the model errors of the state equation. These model errors are estimated by means of a fixed-time disturbance observer, and they are also utilized to compensate the proposed controller. Therefore, the fixed-time controller is obtained by an adaptive reaching law and a fixed-time disturbance observer. Closed-loop stability of the proposed controller is established. Finally, simulation results including Monte Carlo simulations, nonlinear six-DegreeOf-Freedom(6-DOF) simulations and different ranges are presented to demonstrate the efficacy of the proposed control scheme. | Liang ZHANG Changzhu WEI Rong WU Naigang CUI | 2019 | Chinese Journal of Aeronautics2019，32，5： | 8 |
| 2 | A Tracking Filter in Spherical Coordinates Enhanced by De-noising of Converted Doppler Measurements显示文摘Tracking problem in spherical coordinates with range rate (Doppler) measurements, which would have errors correlated to the range measurement errors, is investigated in this paper. The converted Doppler measurements, constructed by the product of the Doppler measurements and range measurements, are used to replace the original Doppler measurements. A de-noising method based on an unbiased Kalman filter (KF) is proposed to reduce the converted Doppler measurement errors before updating the target states for the constant velocity (CV) model. The states from the de-noising filter are then combined with the Cartesian states from the converted measurement Kalman filter (CMKF) to produce final state estimates. The nonlinearity of the de-noising filter states are handled by expanding them around the Cartesian states from the CMKF in a Taylor series up to the second order term. In the mean time, the correlation between the two filters caused by the common range measurements is handled by a minimum mean squared error (MMSE) estimation-based method. These result in a new tracking filter, CMDN-EKF2. Monte Carlo simulations demonstrate that the proposed tracking filter can provide efficient and robust performance with a modest computational cost. | ZHOU Gongjian YU Changjun CUI Naigang QUAN Taifan | 2012 | Chinese Journal of Aeronautics2012，25，5： | 2 |
| 3 | Federated filter with strengthened FDIR capability for multiple sensor navigation system 显示文摘 | Rongjun Mu Siyuan Rong Naigang Cui | 2006 | IEEE Systems and Control in Aerospace and Astronautics2006，，： | 1 |
| 4 | Asynchronous filtering of discrete-time switched linear systems with average dwell time显示文摘 | Zhang Lixian Cui Naigang Liu Ming | 2011 | IEEE Transactions on Circuits and Systems2011，58，5： | 1 |
| 5 | Study on missile formation reconfiguration optimized trajectory gener- ation and control 显示文摘 | Naigang Cui Changzhu Wei Jifeng Guoea | 2010 | Journal of Applied Mechanics2010，77，5： | 1 |
| 6 | Parameters and Trajectory Overall Optimization Design of the Combined Cycle Engine Reusable Launch Vehicle显示文摘Reusable launch vehicle is an important way to realize fast,cheap and reliable space transportation.A combined cycle engine system provides a more efficient and flexible form of power.The investigation on the research status of the combined cycle engine technology,including basic principle,research programs and classification of structure is firstly discussed in this paper.Then the bilevel hierarchical and integrated parameters/trajectory overall optimization technologies are applied to improve the efficiency and effectiveness of overall vehicle design.Simulations are implemented to compare and analyze the effectiveness and adaptability of the two algorithms,in order to provide the technical reserves and beneficial references for further research on combined cycle engine reusable launch vehicles. | CUI Naigang ZHAO Lina HUANG Rong WEI Changzhu | 2016 | Aerospace China2016，17，4： | 1 |
| 7 | Trajectory optimization for hyper-sonic boost-glide missile considering aero-heating显示文摘 | Li Yu Cui Naigang | 2009 | Aircraft Engineering and Aerospace Technology2009，，1： | 1 |
| 8 | An enlarged polygon method without binary variables for obstacle avoidance trajectory optimization显示文摘In this article,an Enlarged Polygon/Polyhedron(ELP)method without binary variables is proposed to represent the Convex Polygonal/Polyhedral Obstacle Avoidance(CPOA)constraints in trajectory optimization.First,the equivalent condition of a point outside the convex set is given and proved rigorously.Then,the ELP condition describing the CPOA constraints equivalently is given without introducing binary variables,and its geometric meaning is explained.Finally,the ELP method is used to transform the CPOA trajectory optimization problem into an optimal control problem without binary variables.The effectiveness and validity of ELP method are demonstrated through simulations with both simple linear dynamic model(unmanned aerial vehicle)and complex nonlinear dynamic model(hypersonic glide vehicle).Comparison indicates the computational time of ELP method is only 1%-20%of that of the traditional Mixed-Integer Programming(MIP)method. | Rouhe ZHANG Zihan XIE Changzhu WEI Naigang CUI | 2023 | Chinese Journal of Aeronautics2023，36，8： | 0 |
| 9 | A Novel Algorithm of Error Check and Code Generation for Structured Flowchart显示文摘Structured flowchart( SFC) and Automatic code generation based on SFC( CG-SFC) have been widely used in software requirements,design and testing phases. Some CG-SFC tools such as Rhapsody have the ability to build flowchart and generate code,but they do not check whether a given flowchart is correct or structural. For unstructured error ‘goto'statements will be generated randomly. We proposed three algorithms and some error recognition criteria to solve those problems. Structure recognition algorithm can recognize Selection,While/for and do-while structures. Error recognition algorithm incorporating criteria can check all the errors. At last,we develop a CG-SFC system,and compared with existing Rhapsody,it shows that the proposed algorithms are correct and effective. | Mingcheng Qu Naigang Cui Xianghu Wu Yongchao Tao | 2017 | Journal of Harbin Institute of Technology(New Series)2017，24，4： | 0 |
| 10 | Sequence Planning for On-Orbit Assembly of Large Space Truss Structures in a Multirobot Environment显示文摘An approach to sequence planning for on-orbit assembly of large space truss structures in a multirobot environment is presented. A hierarchical representation of large space truss structures at the structural volume element level and strut level is adopted. The representation of connectivity matrix and directed graph is respectively presented at the strut level and SVE level. The multirobot environment that consists of autonomous space robots and struts is supposed. Then the multirobot serial assembly strategy,assembly states,assembly tasks and assembly sequences are described. The assembly sequence planning algorithms at the strut level and SVE level are respectively discussed. The results of the simulations show that this approach is feasible and efficient. Two extensions of this approach include more accurate assessment of the efficiency representation and improvements in planning algorithm. In the future,the assembly sequence planning of more large space truss structures and complex multirobot environments and assembly tasks will be considered. | GUO Jifeng,WANG Ping,CUI Naigang (Deptartment of Astronautic Engineering,Harbin Institute of Technology,Harbin 150001,China) | 2006 | 武汉理工大学学报2006，28，S1： | 0 |
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