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Добірка наукової літератури з теми "Singular Perturbation based guidance design"

Автор: Grafiati
Опубліковано: 6 вересня 2023

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Статті в журналах з теми "Singular Perturbation based guidance design"

1

Manickavasagam, M., A. K. Sarkar, and V. Vaithiyanathan. "A Singular Perturbation Based Midcourse Guidance Law for Realistic Air-to-Air Engagement." Defence Science Journal 67, no. 1 (December 23, 2016): 108. http://dx.doi.org/10.14429/dsj.1.9236.

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In this study, a singular perturbation based technique is used for synthesis and analysis of a near optimal midcourse guidance law for realistic air-to-air engagement. After designing the proposed midcourse guidance law using three dimensional point mass formulation it has been validated through detailed realistic six degrees of freedom simulation. During terminal phase only proportional navigation guidance have been used. The calculation of optimal altitude in present guidance law has been carried out using Newton’s method, which needs generally one iteration for convergence and suitable for real-time implementation. Extended Kalman filter based estimator has been used for obtaining evader kinetic information from both radar and seeker noisy measurements available during midcourse and terminal guidance. The data link look angle constraint due to hardware limitation which affects the performance of midcourse guidance has also been incorporated in guidance law design. Robustness of complete simulation has been carried out through Monte Carlo studies. Extension of launch boundary due to singular perturbation over proportional navigation guidance at a given altitude for a typical engagement has also been reported.<br />
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2

Yefei, Yin, Li Xu, and Li Qiaoqi. "Design of Guidance Law for Smart Missile Based on Direct Mode Configuration with Implicit Dynamic-Inverse." Journal of Physics: Conference Series 2478, no. 11 (June 1, 2023): 112036. http://dx.doi.org/10.1088/1742-6596/2478/11/112036.

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Abstract The design of guidance law for smart missile based on implicit dynamic-inverse direct mode configuration is described in this paper. The dynamic-inverse theory and direct mode algorithm are applied to the design of guidance law. The pitching acceleration and yaw acceleration are designed for the pitch channel by using the augmented proportional guidance and for the yaw channel by using the dynamic-inverse theory respectively. The attacking time parameter and the attack time error equation are introduced as the constraint criteria for the design of the dynamic-inverse. According to the singular perturbation theory, the fast and slow subsystems are designed by dynamic-inverse control, and then the required control quantities are obtained by solving the relative motion equations of the missile and the target. The simulation results showed that the guidance law can fully meet the guidance trajectory performance requirements of the smart missile.
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3

Zhao, Penglei, Wanchun Chen, and Wenbin Yu. "Optimal perturbation guidance with constraints on terminal flight-path angle and angle of attack." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 233, no. 12 (January 13, 2019): 4436–46. http://dx.doi.org/10.1177/0954410018823472.

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This paper presents the design of a singular-perturbation-based optimal guidance with constraints on terminal flight-path angle and angle of attack. By modeling the flight-control system dynamics as a first-order system, the angle of attack is introduced into the performance index as a state variable. To solve the resulting high-order optimal guidance problem analytically, the posed optimal guidance problem is divided into two sub-problems by utilizing the singular perturbation method according to two time scales: range, altitude, and flight-path angle are the slow time-scale variables while the angle of attack is the fast time-scale variable. The outer solutions are the optimal control of the slow-scale subsystem. Thereafter, by applying the stretching transformation, the fast-scale subsystem establishes the relationships between the outer solutions and acceleration command. Then, the optimal command can be obtained by solving the fast-scale subsystem also using the optimal control theory. The proposed guidance can achieve a near-zero terminal acceleration as well as a small miss distance. The superior performance of the guidance is demonstrated by adequate trajectory simulations.
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4

Fan, Yunsheng, Bowen Liu, Guofeng Wang, and Dongdong Mu. "Adaptive Fast Non-Singular Terminal Sliding Mode Path Following Control for an Underactuated Unmanned Surface Vehicle with Uncertainties and Unknown Disturbances." Sensors 21, no. 22 (November 10, 2021): 7454. http://dx.doi.org/10.3390/s21227454.

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This paper focuses on an issue involving robust adaptive path following for the uncertain underactuated unmanned surface vehicle with time-varying large sideslips angle and actuator saturation. An improved line-of-sight guidance law based on a reduced-order extended state observer is proposed to address the large sideslip angle that occurs in practical navigation. Next, the finite-time disturbances observer is designed by considering the perturbations parameter of the model and the unknown disturbances of the external environment as the lumped disturbances. Then, an adaptive term is introduced into Fast Non-singular Terminal Sliding Mode Control to design the path following controllers. Finally, considering the saturation of actuator, an auxiliary dynamic system is introduced. By selecting the appropriate design parameters, all the signals of the whole path following a closed-loop system can be ultimately bounded. Real-time control of path following can be achieved by transferring data from shipborne sensors such as GPS, combined inertial guidance and anemoclinograph to the Fast Non-singular Terminal Sliding Mode controller. Two examples as comparisons were carried out to demonstrate the validity of the proposed control approach.
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5

Ha, Cheol-Keun, and Hyoung-Sik Choi. "Design of Autolanding Guidance and Control Algorithm Using Singular Perturbation." Journal of Control, Automation and Systems Engineering 11, no. 8 (August 1, 2005): 726–32. http://dx.doi.org/10.5302/j.icros.2005.11.8.726.

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6

Annam, Chandrakanth, Ashwini Ratnoo, and Debasish Ghose. "Singular-Perturbation-Based Guidance of Pulse Motor Interceptors with Look Angle Constraints." Journal of Guidance, Control, and Dynamics 44, no. 7 (July 2021): 1356–70. http://dx.doi.org/10.2514/1.g005508.

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7

Landolsi, F., and F. H. Ghorbel. "Design and singular perturbation control of a piezotube-based nanomanipulator." Nonlinear Dynamics 83, no. 1-2 (September 8, 2015): 971–81. http://dx.doi.org/10.1007/s11071-015-2381-x.

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8

Song, Seong Ho, Chang Seop Kim, and Jeom Keun Kim. "Stability Analysis of Internal Model Based Gain Control System for Three-Level EDFA Model." Applied Mechanics and Materials 339 (July 2013): 33–37. http://dx.doi.org/10.4028/www.scientific.net/amm.339.33.

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In this paper, stability analysis of an optical fiber amplifier gain controller is presented. The mathematical model of an EDFA (Eribium-Doped Fiber Amplifier) control system is described by two-time scaled system and thus singular perturbation approach can be applied to the design and analysis of the control system. In order to handle the channel variations such as add/drop, we adopt an internal model. The performance of the control system is theoretically analyzed based on a novel singular-perturbation-like approach.
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9

Wardi, Mohamed Lazhar, Messaoud Amairi, and Mohamed Naceur Abdelkrim. "Fractional PID controller design for nonlinear systems based on singular perturbation technique." International Journal of Digital Signals and Smart Systems 2, no. 2 (2018): 95. http://dx.doi.org/10.1504/ijdsss.2018.093172.

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10

Wardi, Mohamed Lazhar, Mohamed Naceur Abdelkrim, and Messaoud Amairi. "Fractional PID controller design for nonlinear systems based on singular perturbation technique." International Journal of Digital Signals and Smart Systems 2, no. 2 (2018): 95. http://dx.doi.org/10.1504/ijdsss.2018.10014373.

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Дисертації з теми "Singular Perturbation based guidance design"

1

Wu, Chia-Pin, and 吳佳斌. "Using Singular Perturbation Methods in Observer-based Controller Design." Thesis, 2012. http://ndltd.ncl.edu.tw/handle/88637893484414157491.

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Анотація:
博士
國立臺灣科技大學
電機工程系
100
The thesis is mainly to design the controller by applying the theory of singular perturbation. First of all, using the singular perturbation technique to design the output feedback controller of mechanic systems, it is similar to the design of a proportional-derivative control law. We can precede the speed control by only measuring the displacement. The controller algorithm is the rule of low-order dynamic output feedback control. It is simple and easily accomplished. Besides, when the mechanical system contains uncertain items, this thesis presents robust stability of the closed-loop system. It also offers the analysis of Lyapunov theory by solving a Riccati algebra equation and a linear matrix inequality. Furthermore, for the mismatched parameter uncertainties and matched nonlinear perturbations in a linear MIMO system, the thesis proposes a disturbance-observer based controller in which the input disturbance can be effectively estimated by using a high-gain integration observer. Finally, it is verified the practicability by numerical examples.
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2

Chang, Yuan-Jen, and 張元震. "Application of the Singular Perturbation Method in the Design of Real-Time Guidance Law for an Air-to-Surface Missile." Thesis, 1998. http://ndltd.ncl.edu.tw/handle/66639207625545361372.

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Анотація:
碩士
國立成功大學
航空太空工程學系
86
How a missile flying along the optimal trajectory which leads to a hit to a target in the minimum time is a major topic for the investigation of the design of guidance law. This is essentially a two-point boundary value problem. In the past, however, the optimal trajectories obtained by using the rigorous optimal control theory associated with the gradient method for numerical computations are too difficult to be implemented as the procedure of computation is so complicated that the iterations often do not converge. The purpose of this thesis is to investigate a real-time guidance law by using the singular perturbation method(SPM). As a result, the trajectory of the missile is near optimal but not rigorously optimal. In the beginning, the altitude is much lower than the optimal value, the guidance law derived by using the SPM is employed. When the missile climbs to the near optimal altitude, the guidance law derived by using the classical control theory is used to accomplish the mission. According to the results of computer simulations, the guidance law designed can indeed guide the missile to fly a near optimal trajectory which characterize the essential part of the rigorous optimal trajectory, and is, therefore, very practical.
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Тези доповідей конференцій з теми "Singular Perturbation based guidance design"

1

Zheng, Tianyu, Fenghua He, Yu Yao, Hongsheng Qi, and Xiaoming Hu. "A singular perturbation-based design for the integrated guidance and control." In 2016 American Control Conference (ACC). IEEE, 2016. http://dx.doi.org/10.1109/acc.2016.7525596.

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2

Chen, Yuanyan, and J. Jim Zhu. "Car-Like Ground Vehicle Trajectory Tracking by Using Trajectory Linearization Control." In ASME 2017 Dynamic Systems and Control Conference. American Society of Mechanical Engineers, 2017. http://dx.doi.org/10.1115/dscc2017-5372.

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This paper focuses on trajectory tracking control for an under-actuated car-like ground vehicle. We consider the 3 degree-of-freedom nonlinear vehicle rigid-body dynamics with nonlinear tire traction force, nonlinear drag forces and actuator dynamics. The control structure employs multi-loop Trajectory Linearization Control (TLC) based on singular perturbation (time-scale separation) theory for exponential stability. The designed controller controls the longitudinal velocity and steering angle simultaneously to follow a feasible guidance trajectory. The paper presents the modeling and design approach with computer simulation results on a scaled-down model car.
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3

YOO, S., and T. BULLOCK. "Missile guidance based on weight adjusted singular perturbation." In Guidance, Navigation and Control Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1989. http://dx.doi.org/10.2514/6.1989-3482.

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4

Park, S., and G. Nagati. "Singular perturbation method in the design of decoupling flight control systems with output feedback." In Guidance, Navigation, and Control Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1995. http://dx.doi.org/10.2514/6.1995-3261.

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5

Zhu, J., Brad Banker, and Charles Hall. "X-33 ascent flight control design by trajectory linearization - A singular perturbation approach." In AIAA Guidance, Navigation, and Control Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2000. http://dx.doi.org/10.2514/6.2000-4159.

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6

SMITH, P., D. HOPPER, and A. BRADSHAW. "Comparison of eigenstructure assignment and the Salford singular perturbation methods in VSTOL aircraft control law design." In Guidance, Navigation and Control Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1989. http://dx.doi.org/10.2514/6.1989-3451.

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7

Xiao, Jiaping, and Zuojun Shen. "Stability analysis of Trajectory Tracking Entry Guidance based on singular perturbation theory." In 2016 35th Chinese Control Conference (CCC). IEEE, 2016. http://dx.doi.org/10.1109/chicc.2016.7553323.

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8

Manhartsgruber, Bernhard. "Singular Perturbation Analysis of an Electrohydraulic Servo-Drive With Discontinuous Reduced Dynamics." In ASME 1999 Design Engineering Technical Conferences. American Society of Mechanical Engineers, 1999. http://dx.doi.org/10.1115/detc99/vib-8178.

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Abstract This paper deals with the position control of a hydraulic servo-drive for translatory motion. The application of a nonlinear composite feedback control based on singular perturbation methods (Kokotovic, Khalil & O’Reilly 1986) is described. A comparison with linear output and state feedback shows the benefits of nonlinear control. The nonlinear design uses feedback linearization for the reduced system and simple proportional feedback for the control of the pressure difference (fast system). The feedback linearization results in a standard second order behavior of the reduced system with cutoff frequency and damping as decoupled design parameters. The proposed method is especially suitable for oscillation drives. Experimental results are given for step responses and sine tracking.
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9

Fakharian, A., F. Jamshidi, and M. Taghi Hamidi Beheshti. "Logic based switching H2/H∞ controller design for linear singular perturbation systems: A fuzzy supervisor approach." In 2010 8th IEEE International Conference on Control and Automation (ICCA 2010). IEEE, 2010. http://dx.doi.org/10.1109/icca.2010.5524299.

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10

Aksenov, Efim A., and Valery D. Yurkevich. "Control system design based on sliding mode control and singular perturbation technique for a Cuk converter." In 2016 13th International Scientific-Technical Conference on Actual Problems of Electronics Instrument Engineering (APEIE). IEEE, 2016. http://dx.doi.org/10.1109/apeie.2016.7806933.

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