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ADRC FRACTIONAL ORDER PID CONTROLLER DESIGN OF HYPERSONIC FLIGHT VEHICLE 被引量:8
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作者 秦昌茂 齐乃明 +1 位作者 吕瑞 朱凯 《Transactions of Nanjing University of Aeronautics and Astronautics》 EI 2011年第3期240-245,共6页
Active disturbance rejection controller(ADRC)uses tracking-differentiator(TD)to solve the contradiction between the overshoot and the rapid nature.Fractional order proportion integral derivative(PID)controller i... Active disturbance rejection controller(ADRC)uses tracking-differentiator(TD)to solve the contradiction between the overshoot and the rapid nature.Fractional order proportion integral derivative(PID)controller improves the control quality and expands the stable region of the system parameters.ADRC fractional order(ADRFO)PID controller is designed by combining ADRC with the fractional order PID and applied to reentry attitude control of hypersonic vehicle.Simulation results show that ADRFO PID controller has better control effect and greater stable region for the strong nonlinear model of hypersonic flight vehicle under the influence of external disturbance,and has stronger robustness against the perturbation in system parameters. 展开更多
关键词 hypersonic flight vehicle active disturbance rejection controller(ADRC) fractional order PID D-decomposition method
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Flight Loads and Dynamics of Flexible Air Vehicles 被引量:11
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作者 吴志刚 杨超 《Chinese Journal of Aeronautics》 SCIE EI CAS CSCD 2004年第1期17-22,共6页
Based on the equations of motion of flexible air vehicles includingrigid-body modes and elastic structural modes, and applying influence coefficients of linearaerodynamics, a set of equations are derived and a method ... Based on the equations of motion of flexible air vehicles includingrigid-body modes and elastic structural modes, and applying influence coefficients of linearaerodynamics, a set of equations are derived and a method is presented for analysis of flight loadsand dynamic characteristics. The problems in the fields of flight mechanics and aeroelasticity suchas static aeroelastic divergence, trim and deformation, aerodynamic loads distribution, flutter andflight dynamics can be solved by the procedure. An airplane with high aspect ratio wings isanalyzed, and the results show that the coupling between rigid -body modes and elastic modes isdistinct and should not be overlooked. 展开更多
关键词 flexible air vehicle aeroelasticity flight dynamics flight load
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Flight Control System of Unmanned Aerial Vehicle 被引量:5
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作者 浦黄忠 甄子洋 夏曼 《Transactions of Nanjing University of Aeronautics and Astronautics》 EI CSCD 2015年第1期1-8,共8页
To date unmanned aerial system(UAS)technologies have attracted more and more attention from countries in the world.Unmanned aerial vehicles(UAVs)play an important role in reconnaissance,surveillance,and target trackin... To date unmanned aerial system(UAS)technologies have attracted more and more attention from countries in the world.Unmanned aerial vehicles(UAVs)play an important role in reconnaissance,surveillance,and target tracking within military and civil fields.Here one briefly introduces the development of UAVs,and reviews its various subsystems including autopilot,ground station,mission planning and management subsystem,navigation system and so on.Furthermore,an overview is provided for advanced design methods of UAVs control system,including the linear feedback control,adaptive and nonlinear control,and intelligent control techniques.Finally,the future of UAVs flight control techniques is forecasted. 展开更多
关键词 unmanned aerial vehicle(UAV) flight control optimal control adaptive control intelligent control
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Circular Formation Flight Control for Unmanned Aerial Vehicles With Directed Network and External Disturbance 被引量:11
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作者 Yangyang Chen Rui Yu +1 位作者 Ya Zhang Chenglin Liu 《IEEE/CAA Journal of Automatica Sinica》 EI CSCD 2020年第2期505-516,共12页
This paper proposes a new distributed formation flight protocol for unmanned aerial vehicles(UAVs)to perform coordinated circular tracking around a set of circles on a target sphere.Different from the previous results... This paper proposes a new distributed formation flight protocol for unmanned aerial vehicles(UAVs)to perform coordinated circular tracking around a set of circles on a target sphere.Different from the previous results limited in bidirectional networks and disturbance-free motions,this paper handles the circular formation flight control problem with both directed network and spatiotemporal disturbance with the knowledge of its upper bound.Distinguishing from the design of a common Lyapunov fiunction for bidirectional cases,we separately design the control for the circular tracking subsystem and the formation keeping subsystem with the circular tracking error as input.Then the whole control system is regarded as a cascade connection of these two subsystems,which is proved to be stable by input-tostate stability(ISS)theory.For the purpose of encountering the external disturbance,the backstepping technology is introduced to design the control inputs of each UAV pointing to North and Down along the special sphere(say,the circular tracking control algorithm)with the help of the switching function.Meanwhile,the distributed linear consensus protocol integrated with anther switching anti-interference item is developed to construct the control input of each UAV pointing to east along the special sphere(say,the formation keeping control law)for formation keeping.The validity of the proposed control law is proved both in the rigorous theory and through numerical simulations. 展开更多
关键词 Directed network external disturbance flight control unmanned aerial vehicles(UAVs)
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Structural Deformation Monitoring of Flight Vehicles Based on Optical Fiber Sensing Technology:A Review and Future Perspectives 被引量:7
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作者 Lianqing Zhu Guangkai Sun +3 位作者 Weimin Bao Zheng You Fanyong Meng Mingli Dong 《Engineering》 SCIE EI CAS 2022年第9期39-55,共17页
Structural deformation monitoring of flight vehicles based on optical fiber sensing(OFS)technology has been a focus of research in the field of aerospace.After nearly 30 years of research and development,Chinese and i... Structural deformation monitoring of flight vehicles based on optical fiber sensing(OFS)technology has been a focus of research in the field of aerospace.After nearly 30 years of research and development,Chinese and international researchers have made significant advances in the areas of theory and methods,technology and systems,and ground experiments and flight tests.These advances have led to the development of OFS technology from the laboratory research stage to the engineering application stage.However,a few problems encountered in practical applications limit the wider application and further development of this technology,and thus urgently require solutions.This paper reviews the history of research on the deformation monitoring of flight vehicles.It examines various aspects of OFS-based deformation monitoring including the main varieties of OFS technology,technical advantages and disadvantages,suitability in aerospace applications,deformation reconstruction algorithms,and typical applications.This paper points out the key unresolved problems and the main evolution paradigms of engineering applications.It further discusses future development directions from the perspectives of an evolution paradigm,standardization,new materials,intelligentization,and collaboration. 展开更多
关键词 Optical fiber sensing technology Deformation monitoring Structural health monitoring flight vehicle AEROSPACE
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Research on star-tracking correction technology for near-earth flight vehicles 被引量:1
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作者 Longxu Xiao Shihui Wei Hongbin Lin 《Journal of Systems Engineering and Electronics》 SCIE EI CSCD 2010年第3期485-490,共6页
By analyzing the traditional star-tracking correction technology,this paper studies the star-tracking direct correction method which is based on star sensor dynamic separation initial displacement angles and main erro... By analyzing the traditional star-tracking correction technology,this paper studies the star-tracking direct correction method which is based on star sensor dynamic separation initial displacement angles and main errors of inertial measure unit(IMU) in order to carry out automatic navigation and improve the hitting accuracy and quick reaction capability of near-earth flight vehicles.Through comprehensive application and improvement of the best correction factor method,this paper proposes the startracking comprehensive correction method which combines the two methods above-mentioned and the accelerometer dynamic error separation technology.The simulation results show that obvious effects can be achieved by using the star-tracking integrated correction method. 展开更多
关键词 near-earth flight vehicle laser SIMU/star sensor combined system star-tracking correction combined guidance.
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Micro air vehicle-motivated computational biomechanics in bio-flights:aerodynamics,flight dynamics and maneuvering stability 被引量:8
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作者 Hao Liu Toshiyuki Nakata +3 位作者 Na Gao Masateru Maeda Hikaru Aono Wei Shyy 《Acta Mechanica Sinica》 SCIE EI CAS CSCD 2010年第6期863-879,共17页
Aiming at developing an effective tool to unveil key mechanisms in bio-flight as well as to provide guidelines for bio-inspired micro air vehicles(MAVs) design,we propose a comprehensive computational framework,whic... Aiming at developing an effective tool to unveil key mechanisms in bio-flight as well as to provide guidelines for bio-inspired micro air vehicles(MAVs) design,we propose a comprehensive computational framework,which integrates aerodynamics,flight dynamics,vehicle stability and maneuverability.This framework consists of(1) a Navier-Stokes unsteady aerodynamic model;(2) a linear finite element model for structural dynamics;(3) a fluidstructure interaction(FSI) model for coupled flexible wing aerodynamics aeroelasticity;(4) a free-flying rigid body dynamic(RBD) model utilizing the Newtonian-Euler equations of 6DoF motion;and(5) flight simulator accounting for realistic wing-body morphology,flapping-wing and body kinematics,and a coupling model accounting for the nonlinear 6DoF flight dynamics and stability of insect flapping flight.Results are presented based on hovering aerodynamics with rigid and flexible wings of hawkmoth and fruitfly.The present approach can support systematic analyses of bio- and bio-inspired flight. 展开更多
关键词 Micro air vehicle Bio-flight Computational mechanics Integrative biomechanics
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Finite-time control of formation system for multiple flight vehicles subject to actuator saturation 被引量:1
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作者 ZHAO Enjiao ZHONG Zenan ZHENG Xin 《Journal of Systems Engineering and Electronics》 SCIE EI CSCD 2020年第5期1019-1030,共12页
This paper investigates the problem of formation tracking control for multiple flight vehicle(MFV) system considering actuator saturation constraints. First, the formation tracking control model is established. Then, ... This paper investigates the problem of formation tracking control for multiple flight vehicle(MFV) system considering actuator saturation constraints. First, the formation tracking control model is established. Then, the problem of formation control of the MFV system is converted to the convergence of a dynamical system, which is obtained by using the differential geometry theory.A class of saturation functions is introduced, and on this basis a second-order finite-time formation control protocol is developed.With the help of the homogeneous theory and Lasalle's invariance principle, it is theoretically proved that the designed formation protocol could complete the formation task in finite time, and the control inputs are shown to remain within their available actuating limits. Finally, simulations are performed to verify the effectiveness of the scheme. 展开更多
关键词 formation control multiple flight vehicle(MFV) FINITE-TIME actuator saturation
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Intelligent and Autonomous Flight Technology for Launch Vehicles 被引量:2
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作者 SONG Zhengyu 《Aerospace China》 2018年第2期3-15,共13页
This paper proposes the architecture of an intelligent flight launcher system as well as fundamental solutions to capability prediction and dynamic planning. This effort reflects the latest progress in the application... This paper proposes the architecture of an intelligent flight launcher system as well as fundamental solutions to capability prediction and dynamic planning. This effort reflects the latest progress in the applications of intelligent and autonomous technology for launcher flights. The paper first describes the characteristics and capabilities of intelligent and autonomous systems and classifies various related technologies. In the context of intelligent and autonomous technology in aerospace engineering, it then focuses on technical difficulties involved with intelligent flight and reviews developments in the field. An E^3 classification model of an intelligent flight launcher is then proposed and its application scenarios are discussed. Based on an intelligent flight system configuration of the launcher, the online trajectory planning and initial value guess are examined, and vertical landing is provided as an example to explain the effects of the implementation of computational intelligence to flight systems. 展开更多
关键词 intelligent flight launch vehicle AUTONOMOUS hierarchical model dynamic trajectory planning
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Output Feedback Dynamic Surface Controller Design for Airbreathing Hypersonic Flight Vehicle 被引量:4
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作者 Delong Hou Qing Wang Chaoyang Dong 《IEEE/CAA Journal of Automatica Sinica》 SCIE EI 2015年第2期186-197,共12页
This paper addresses issues related to nonlinear robust output feedback controller design for a nonlinear model of airbreathing hypersonic vehicle. The control objective is to realize robust tracking of velocity and a... This paper addresses issues related to nonlinear robust output feedback controller design for a nonlinear model of airbreathing hypersonic vehicle. The control objective is to realize robust tracking of velocity and altitude in the presence of immeasurable states, uncertainties and varying flight conditions. A novel reduced order fuzzy observer is proposed to estimate the immeasurable states. Based on the information of observer and the measured states, a new robust output feedback controller combining dynamic surface theory and fuzzy logic system is proposed for airbreathing hypersonic vehicle. The closedloop system is proved to be semi-globally uniformly ultimately bounded (SUUB), and the tracking error can be made small enough by choosing proper gains of the controller, filter and observer. Simulation results from the full nonlinear vehicle model illustrate the effectiveness and good performance of the proposed control scheme. © 2014 Chinese Association of Automation. 展开更多
关键词 Altitude control Feedback control Fuzzy logic Hypersonic aerodynamics Hypersonic vehicles Nonlinear feedback Robust control Tracking (position) Uncertainty analysis vehicles
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Flight Time Minimization of UAV for Cooperative Data Collection in Probabilistic LoS Channel
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作者 Yan Li Shaoyi Xu +1 位作者 Yunpu Wu Dongji Li 《China Communications》 SCIE CSCD 2024年第2期210-226,共17页
This paper investigates the data collection in an unmanned aerial vehicle(UAV)-aided Internet of Things(IoT) network, where a UAV is dispatched to collect data from ground sensors in a practical and accurate probabili... This paper investigates the data collection in an unmanned aerial vehicle(UAV)-aided Internet of Things(IoT) network, where a UAV is dispatched to collect data from ground sensors in a practical and accurate probabilistic line-of-sight(LoS) channel. Especially, access points(APs) are introduced to collect data from some sensors in the unlicensed band to improve data collection efficiency. We formulate a mixed-integer non-convex optimization problem to minimize the UAV flight time by jointly designing the UAV 3D trajectory and sensors’ scheduling, while ensuring the required amount of data can be collected under the limited UAV energy. To solve this nonconvex problem, we recast the objective problem into a tractable form. Then, the problem is further divided into several sub-problems to solve iteratively, and the successive convex approximation(SCA) scheme is applied to solve each non-convex subproblem. Finally,the bisection search is adopted to speed up the searching for the minimum UAV flight time. Simulation results verify that the UAV flight time can be shortened by the proposed method effectively. 展开更多
关键词 data collection flight time probabilistic line-of-sight channel unlicensed band unmanned aerial vehicle
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Primary safe criterion of earth-brushing flight for flying vehicle over digital surface model
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作者 赵敏 林行刚 赵乃国 《Journal of Systems Engineering and Electronics》 SCIE EI CSCD 2004年第3期309-314,共6页
In modern terrain-following guidance it is an important index for flight vehicle to cruise about safely and normally. On the basis of a constructing method of digital surface model (DSM), the definition, classificatio... In modern terrain-following guidance it is an important index for flight vehicle to cruise about safely and normally. On the basis of a constructing method of digital surface model (DSM), the definition, classification and scale analysis of an isolated obstacle threatening flight safety of terrain-following guidance are made. When the interval of vertical-and cross-sections on DSM is 12. 5 m, the proportion of isolated obstacles to the data amount of DSM model to be loaded is optimal. The main factors influencing the lowest flying height in terrain-following guidance are analyzed, and a primary safe criterion of the lowest flying height over DSM model is proposed. According to their test errors, the lowest flying height over 1:10 000 DSM model can reach 40. 5 m^45. 0 m in terrain-following guidance. It is shown from the simulation results of a typical urban district that the proposed models and methods are reasonable and feasible. 展开更多
关键词 digital surface model terrain-following guidance flight obstacle ground feature flight vehicle.
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Flight Record of the Long March Series of Launch Vehicles
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作者 He Ying 《Aerospace China》 2012年第2期13-14,共2页
(Continued) The 75th Launch On December 30, 2003, the LM-2C/SM launch vehicle launched theTance 1 (TC-1) satellite into orbit from the Xichang Satellite Launch Center. The satellite entered a super geosynchronous orbi... (Continued) The 75th Launch On December 30, 2003, the LM-2C/SM launch vehicle launched theTance 1 (TC-1) satellite into orbit from the Xichang Satellite Launch Center. The satellite entered a super geosynchronous orbit . Launch Site: Xichang Satellite Launch Center Launch Result: Success At 03:06 Beijing time on December 30, the LM-2C/SM launch vehicle lifted off into space with TC-1 (equatorial satellite) and precisely sent the satellite into 展开更多
关键词 flight Record of the Long March Series of Launch vehicles TC LONG
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Flight Record of the Long March Series of Launch Vehicles
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作者 He Ying 《Aerospace China》 2012年第1期15-16,共2页
(Continued)The 71st Launch On October 15,2003,China's first manned spaceship,Shenzhou 5,was launched by a LM-2F launch vehicle.The first Chinese astronaut Yang Liwei stayed in space for 21 hours and landed back on... (Continued)The 71st Launch On October 15,2003,China's first manned spaceship,Shenzhou 5,was launched by a LM-2F launch vehicle.The first Chinese astronaut Yang Liwei stayed in space for 21 hours and landed back on the Earth safely on October 16。 展开更多
关键词 CBERS flight Record of the Long March Series of Launch vehicles LONG
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Unmanned Aerial Vehicles Flight Safety Improvement Using In-Flight Awareness
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作者 André L. P. Mattei Engenharia S. A. Orbital +2 位作者 Claudio F. M. Toledo Jesimar da Silva Arantes Onofre Trindade Jr. 《Intelligent Information Management》 2021年第2期97-123,共27页
This paper presents a novel onboard system called In-Flight Awareness Augmentation System (IFA<sup>2</sup>S) to improve flight safety. IFA<sup>2</sup>S is designed to semi-automatically (with h... This paper presents a novel onboard system called In-Flight Awareness Augmentation System (IFA<sup>2</sup>S) to improve flight safety. IFA<sup>2</sup>S is designed to semi-automatically (with human supervision) avoid hazards and accidents due to either internal or external causal factors. The requirements were defined in an innovative way using Systems-Theoretic Process Analysis (STPA) method and applied next to model the system. IFA<sup>2</sup>S increases aircraft awareness regarding both itself and its environment and, at the same time, recognizes platform and operational constraints to act in accordance to predefined decision algorithms. Results are presented through simulations and flight tests using state machines designed to allow the adoption of appropriate actions for the identified hazards. The different decision algorithms are evaluated over as many as possible hazard situations by simulations conducted with software Labview and XPlane flight simulator. Flight tests are performed in a small fixed wing aircraft and make use of a limited version IFA<sup>2</sup>S, partially attending identified requirements. Results support the conclusion that IFA<sup>2</sup>S is capable of improving flight safety. 展开更多
关键词 Unmanned Aerial vehicles Air Safety Systems-Theoretic Process Analysis In-flight Awareness
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Flight Record of the Long March Series of Launch Vehicles
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作者 He Ying 《Aerospace China》 2011年第2期12-13,共2页
(Continued)THE 67TH LAUNCHOn May 15, 2002, a LM-4B launch vehicle lifted off with FY-1D meteorological satellite and HY-1A oceanic satellite from Tai-yuan Satellite Launch Center and
关键词 flight Record of the Long March Series of Launch vehicles LONG
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Flight Record of the Long March Series of Launch Vehicles
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作者 He Ying 《Aerospace China》 2011年第1期18-19,共2页
(Continued) THE 59TH LAUNCH On November 20,1999,a LM-2F launch vehicle lifted off with China’s indigenous Shenzhou 1 experimental spaceship from Jiuquan Satellite Launch Center.Shenzhou 1 returned to Earth on Novembe... (Continued) THE 59TH LAUNCH On November 20,1999,a LM-2F launch vehicle lifted off with China’s indigenous Shenzhou 1 experimental spaceship from Jiuquan Satellite Launch Center.Shenzhou 1 returned to Earth on November 21 after 21 hours of in-orbit operation and circling the Earth 14 times. 展开更多
关键词 flight Record of the Long March Series of Launch vehicles LONG
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Flight Record of the Long March Series of Launch Vehicles
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作者 He Ying 《Aerospace China》 2011年第3期9-10,共2页
(Continued)THE 67TH LAUNCHOn May 15, 2002, a LM-4B launch vehicle lifted off with FY-1D meteorological satellite and HY-1A oceanic satellite from Tai-yuan Satellite Launch Center and
关键词 flight Record of the Long March Series of Launch vehicles LONG
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Flight Record of the Long March Series of Launch Vehicles
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作者 He Ying 《Aerospace China》 2012年第4期12-13,共2页
(Continued) The 79th Launch On September 9, 2004, a LM-4B launch vehicle launched two satellites, SJ-6A and SJ-6B, into space both for space environment exploration from the Taiyuan Satellite Launch Center. The two sa... (Continued) The 79th Launch On September 9, 2004, a LM-4B launch vehicle launched two satellites, SJ-6A and SJ-6B, into space both for space environment exploration from the Taiyuan Satellite Launch Center. The two satellites entered their preset sun synchronous orbits. Launch Site: Taiyuan Satellite Launch Center Launch Result: Success At 07:14 Beijing time on September 9, the LM-4B launch vehicle was launched into space with SJ-6A and SJ-6B on board. 展开更多
关键词 flight Record of the Long March Series of Launch vehicles
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Adaptive augmentation of gain-scheduled controller for aerospace vehicles 被引量:8
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作者 Xiyuan Huang Qing Wang +2 位作者 Yali Wang Yanze Hou Chaoyang Dong 《Journal of Systems Engineering and Electronics》 SCIE EI CSCD 2013年第2期272-280,共9页
This paper proposes an adaptive augmentation control design approach of the gain-scheduled controller.This extension is motivated by the need for augmentation of the baseline gainscheduled controller.The proposed appr... This paper proposes an adaptive augmentation control design approach of the gain-scheduled controller.This extension is motivated by the need for augmentation of the baseline gainscheduled controller.The proposed approach can be utilized to design flight control systems for advanced aerospace vehicles with a large parameter variation.The flight dynamics within the flight envelope is described by a switched nonlinear system,which is essentially a switched polytopic system with uncertainties.The flight control system consists of a baseline gain-scheduled controller and a model reference adaptive augmentation controller,while the latter can recover the nominal performance of the gainscheduled controlled system under large uncertainties.By the multiple Lyapunov functions method,it is proved that the switched nonlinear system is uniformly ultimately bounded.To validate the effectiveness of the proposed approach,this approach is applied to a generic hypersonic vehicle,and the simulation results show that the system output tracks the command signal well even when large uncertainties exist. 展开更多
关键词 adaptive control gain-scheduled control flight envelope aerospace vehicle
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