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Journal articles on the topic 'Nonlinear Differential Guidance Law'

Author: Grafiati

Published: 4 June 2021

Last updated: 6 September 2023

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1

Xi, Axing, and Yuanli Cai. "A Nonlinear Finite-Time Robust Differential Game Guidance Law." Sensors 22, no. 17 (2022): 6650. http://dx.doi.org/10.3390/s22176650.

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In this paper, a robust differential game guidance law is proposed for the nonlinear zero-sum system with unknown dynamics and external disturbances. First, the continuous-time nonlinear zero-sum differential game problem is transformed into solving the nonlinear Hamilton–Jacobi–Isaacs equation, a time-varying cost function is developed to reflect the fixed terminal time, and the robust guidance law is developed to compensate for the external disturbance. Then, a novel neural network identifier is designed to approximate the unknown nonlinear dynamics with online weight tuning. Subsequently, a

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2

Bardhan, Rajarshi, and Debasish Ghose. "Nonlinear Differential Games-Based Impact-Angle-Constrained Guidance Law." Journal of Guidance, Control, and Dynamics 38, no. 3 (2015): 384–402. http://dx.doi.org/10.2514/1.g000940.

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3

Cho, Namhoon, Youdan Kim, and Sanghyuk Park. "Three-Dimensional Nonlinear Differential Geometric Path-Following Guidance Law." Journal of Guidance, Control, and Dynamics 38, no. 12 (2015): 2366–85. http://dx.doi.org/10.2514/1.g001060.

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4

Chen, Jian, Qilun Zhao, Zixuan Liang, Peng Li, Zhang Ren, and Yongjun Zheng. "Fractional Calculus Guidance Algorithm in a Hypersonic Pursuit-Evasion Game." Defence Science Journal 67, no. 6 (2017): 688. http://dx.doi.org/10.14429/dsj.67.10897.

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<p class="p1">Aiming at intercepting a hypersonic weapon in a hypersonic pursuit-evasion game, this paper presents a fractional calculus guidance algorithm based on a nonlinear proportional and differential guidance law. First, under the premise of without increasing the complexity degree of the guidance system against a hypersonic manoeuvering target, the principle that the differential signal of the line-of-sight rate is more sensitive to the target manoeuver than the line-of-sight rate is employed as the guidelines to design the guidance law. A nonlinear proportional and differential

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5

Su, Mao, Lei Liu, and Yongji Wang. "Integrated Estimation/Guidance Law against Exoatmospheric Maneuvering Targets." Complexity 2018 (December 10, 2018): 1–19. http://dx.doi.org/10.1155/2018/7470823.

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An integrated guidance integrated estimation/guidance law is designed for exoatmospheric interceptors equipped with divert thrusters and optical seekers to intercept maneuvering targets. This paper considers an angles-only guidance problem for exoatmospheric maneuvering targets. A bounded differential game-based guidance law is derived against maneuvering targets using zero-effort-miss (ZEM). Estimators based the extended Kalman filter (EKF) and the unscented Kalman filter (UKF) are designed to estimate LOS rates that are contaminated by noise and target maneuver. Furthermore, to improve the o

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6

Cho, Namhoon, Youdan Kim, and Sanghyuk Park. "Three-Dimensional Nonlinear Path-Following Guidance Law Based on Differential Geometry." IFAC Proceedings Volumes 47, no. 3 (2014): 2503–8. http://dx.doi.org/10.3182/20140824-6-za-1003.00171.

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7

He, Fan, Weiyi Chen, and Yang Bao. "Predictive Differential Game Guidance Approach for Hypersonic Target Interception Based on CQPSO." International Journal of Aerospace Engineering 2022 (May 2, 2022): 1–14. http://dx.doi.org/10.1155/2022/6050640.

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In the descent phase of the hypersonic target flight trajectory, the hypersonic speed of the target makes the reaction time shorter. Due to overload restrictions, it is challenging for the interceptor to achieve successful interception. To address this problem, a predictive differential game guidance approach based on dynamic optimization algorithm is proposed to relax the interceptor acceleration requirements. Two-dimensional kinematics and dynamics engagement mode for hypersonic target interception is formulated as a nonlinear differential control model in the presence of matched uncertainti

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8

Li, Ke-Bo, Wen-Shan Su, and Lei Chen. "Performance analysis of differential geometric guidance law against high-speed target with arbitrarily maneuvering acceleration." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 233, no. 10 (2018): 3547–63. http://dx.doi.org/10.1177/0954410018801218.

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The interception of high-speed target with an arbitrary maneuvering acceleration causes serious troubles to the guidance and control system design of airborne missile. A novel guidance law based on the classical differential geometry curve theory was proposed not long ago. Although it is believed and numerically demonstrated that this differential geometric guidance law (DGGL) is superior to the classical pure proportional navigation (PPN) in intercepting high-speed targets, its performance has not been thoroughly analyzed. In this paper, using the Lyapunov-like approach, the performance of DG

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9

Wu, Gang, and Ke Zhang. "A Novel Guidance Law for Intercepting a Highly Maneuvering Target." International Journal of Aerospace Engineering 2021 (December 10, 2021): 1–19. http://dx.doi.org/10.1155/2021/2326323.

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Given the resolution of the guidance for intercepting highly maneuvering targets, a novel finite-time convergent guidance law is proposed, which takes the following conditions into consideration, including the impact angle constraint, the guidance command input saturation constraint, and the autopilot second-order dynamic characteristics. Firstly, based on the nonsingular terminal sliding mode control theory, a finite-time convergent nonsingular terminal sliding mode surface is designed. On the back of the backstepping control method, the virtual control law appears. A nonlinear first-order fi

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10

Zhang, Dong, Xiujuan Li, and Xiao Han. "Research on Guidance and Control Method of Hypersonic UAV Capture Segment Based on Overload." Journal of Physics: Conference Series 2216, no. 1 (2022): 012042. http://dx.doi.org/10.1088/1742-6596/2216/1/012042.

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Abstract With the implementation of China’s high supersonic aircraft science and technology engineering and the key basic scientific problems of near space vehicles major research programs.In this context, China is also vigorously developing high-speed high-mobility, long range and recyclable aircraft. In view of the tracking problem of a hypersonic vehicle when it reaches the capture segment, a mathod based on overload guidance law is proposed. The relationship between force and head-on angle can be deduced from the relationship between overload and head-on angle, thus transforming the overlo

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11

Pei, Pei, and Jiang Wang. "Near-Optimal Guidance with Impact Angle and Velocity Constraints Using Sequential Convex Programming." Mathematical Problems in Engineering 2019 (October 23, 2019): 1–14. http://dx.doi.org/10.1155/2019/2065730.

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This paper proposes a near-optimal air-to-ground missile guidance law with impact angle and impact velocity constraints based on sequential convex programming. A realistic aerodynamic model is introduced into the problem formulation, such that traditional optimization theory cannot obtain an analytical solution to the optimization problem under state constraints. The original problem is considered as an optimization problem, and the angle of attack is replaced with the angle of attack rate as a new control variable to reconstruct the problem and simplify the solving process. Next, the independ

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12

Dai, Qinrui. "Two-parameter bifurcations analysis of a delayed high-temperature superconducting maglev model with guidance force." Chaos: An Interdisciplinary Journal of Nonlinear Science 32, no. 8 (2022): 083128. http://dx.doi.org/10.1063/5.0104854.

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A modified high-temperature superconducting maglev model is studied in this paper, mainly considering the influence of time delay on the dynamic properties of the system. For the original model without time delay, there are periodic equilibrium points. We investigate its stability and Hopf bifurcation and study the bifurcation properties by using the center manifold theorem and the normal form theory. For the delayed model, we mainly study the co-dimension two bifurcations (Bautin and Hopf–Hopf bifurcations) of the system. Specifically, we prove the existence of Bautin bifurcation and calculat

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13

Qiu, Bingbing, Guofeng Wang, and Yunsheng Fan. "Trajectory Linearization-Based Adaptive PLOS Path Following Control for Unmanned Surface Vehicle with Unknown Dynamics and Rudder Saturation." Applied Sciences 10, no. 10 (2020): 3538. http://dx.doi.org/10.3390/app10103538.

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This paper presents a novel robust control strategy for path following of an unmanned surface vehicle (USV) suffering from unknown dynamics and rudder saturation. The trajectory linearization control (TLC) method augmented by the neural network, linear extended state observer (LESO), and auxiliary system is used as the main control framework. The salient features of the presented strategy are as follows: in the guidance loop, a fuzzy predictor line-of-sight (FPLOS) guidance law is proposed to ensure that the USV effectively follows the given path, where the fuzzy method is introduced to adjust

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14

Niu, Kang, Xu Bai, Xi Chen, Di Yang, Jiaxun Li, and Jianqiao Yu. "A New Adaptive Control Algorithm of IGC System for Targets with Several Maneuvering Modes Based on GTSMC-DNN." Aerospace 10, no. 4 (2023): 380. http://dx.doi.org/10.3390/aerospace10040380.

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To improve the performance of intercepting a target with different maneuvering modes and changing the mode suddenly during the interception, a new adaptive control algorithm for the IGC (Integrated Guidance and Control) system is proposed, using the global terminal sliding mode control method and a DNN (Deep Neural Network). Firstly, the missile-target problem is formulated and a new strict-feedback nonlinear IGC model with mismatched uncertainties is established. Secondly, the paper divides the IGC system into four subsystems, including a guidance subsystem, overload subsystem, attitude subsy

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15

Ye, Jikun, Humin Lei, Dongfeng Xue, Jiong Li, and Lei Shao. "Nonlinear differential geometric guidance for maneuvering target." Journal of Systems Engineering and Electronics 23, no. 5 (2012): 752–60. http://dx.doi.org/10.1109/jsee.2012.00092.

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16

Kamalaskar, Mandar Bhanudas, S. Aditya Varma, and Mangal Kothari. "A nonlinear impact-angle guidance law." International Journal of Intelligent Unmanned Systems 5, no. 2/3 (2017): 46–62. http://dx.doi.org/10.1108/ijius-03-2017-0003.

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Purpose The purpose of this paper is to propose a new nonlinear guidance law to satisfy terminal impact-angle constraints against a stationary target in every possible planar surface-to-surface engagement scenario. The proposed guidance scheme is developed based on the geometry of a circular arc trajectory. The proposed guidance scheme is developed based on the geometry of circular arc trajectory. This trajectory is calculated based on the terminal impact angle and target range. The efficacy of the proposed guidance scheme is demonstrated through numerical simulations. The proposed scheme is c

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17

ZHANG, Ping, Yangwang FANG, Fengming ZHANG, Bingsong XIAO, Shiguo HU, and Shuning ZONG. "An Adaptive Weighted Differential Game Guidance Law." Chinese Journal of Aeronautics 25, no. 5 (2012): 739–46. http://dx.doi.org/10.1016/s1000-9361(11)60440-8.

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18

Peng, Shuang Chun, Liang Pan, Tian Jiang Hu, and Lin Cheng Shen. "3D Nonlinear Guidance Law for Bank-to-Turn Missile." Advanced Materials Research 317-319 (August 2011): 727–33. http://dx.doi.org/10.4028/www.scientific.net/amr.317-319.727.

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A new three-dimensional (3D) nonlinear guidance law is proposed and developed for bank-to-turn (BTT) with motion coupling. First of all, the 3D guidance model is established. In detail, the line-of-sight (LOS) rate model is established with the vector description method, and the kinematics model is divided into three terms of pitching, swerving and coupling, then by using the twist-based method, the LOS direction changing model is built for designing the guidance law with terminal angular constraints. Secondly, the 3D guidance laws are designed with Lyapunov theory, corresponding to no termina

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19

Yang, Ciann-Dong, and Hsin-Yuan Chen. "Nonlinear H Robust Guidance Law for Homing Missiles." Journal of Guidance, Control, and Dynamics 21, no. 6 (1998): 882–90. http://dx.doi.org/10.2514/2.4321.

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20

Shin, Hyo-Sang, Tae-Hun Kim, Min-Jea Tahk, and Tae-Won Hwang. "Nonlinear Formation Guidance Law with Robust Disturbance Observer." International Journal of Aeronautical and Space Sciences 10, no. 1 (2009): 30–36. http://dx.doi.org/10.5139/ijass.2009.10.1.030.

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21

Dongkyoung Chwa and Jin Young Choi. "Adaptive nonlinear guidance law considering control loop dynamics." IEEE Transactions on Aerospace and Electronic Systems 39, no. 4 (2003): 1134–43. http://dx.doi.org/10.1109/taes.2003.1261117.

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22

Sinha, Abhinav, and Yongcan Cao. "3-D Nonlinear Guidance Law for Target Circumnavigation." IEEE Control Systems Letters 7 (2023): 655–60. http://dx.doi.org/10.1109/lcsys.2022.3215609.

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23

Ma, Yi-Wei, Wei-Hua Zhang, and Han Long. "Intelligent guidance method based on differential geometric guidance command and fuzzy self-adaptive guidance law." Journal of Intelligent & Fuzzy Systems 29, no. 6 (2015): 2527–36. http://dx.doi.org/10.3233/ifs-151955.

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24

Chen, Hsin-Yuan, and Ciann-Dong Yang. "Three-dimensional nonlinear H∞ guidance law with maneuvering targets." IFAC Proceedings Volumes 32, no. 2 (1999): 3079–84. http://dx.doi.org/10.1016/s1474-6670(17)56525-8.

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25

Oshman, Y., and D. Arad. "Differential-game-based guidance law using target orientation observations." IEEE Transactions on Aerospace and Electronic Systems 42, no. 1 (2006): 316–26. http://dx.doi.org/10.1109/taes.2006.1603425.

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26

Shima, T., and O. M. Golan. "Bounded differential games guidance law for dual-controlled missiles." IEEE Transactions on Control Systems Technology 14, no. 4 (2006): 719–24. http://dx.doi.org/10.1109/tcst.2006.876642.

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27

Mondai, S., and R. Padhi. "Formation Flying using GENEX and Differential geometric guidance law." IFAC-PapersOnLine 48, no. 9 (2015): 19–24. http://dx.doi.org/10.1016/j.ifacol.2015.08.053.

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28

Mujumdar, Anusha, and Radhakant Padhi. "Reactive Collision Avoidance of Using Nonlinear Geometric and Differential Geometric Guidance." Journal of Guidance, Control, and Dynamics 34, no. 1 (2011): 303–11. http://dx.doi.org/10.2514/1.50923.

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29

Cho, Sungjin. "Analytic Solution for Nonlinear Impact-Angle Guidance Law with Time-Varying Thrust." Mathematics 10, no. 21 (2022): 4034. http://dx.doi.org/10.3390/math10214034.

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This paper presents an impact-angle guidance law of unmanned aerial vehicles (UAVs) with time-varying thrust in a boosting phase. Most current research on impact-angle guidance law assumes that UAV speed is constant in terms of controlled thrust. However, the UAV speed and the acceleration in a boosting phase keep changing because of time-varying thrust. Environmental factors and manufacturing process error may prohibit accurately predicting vehicle-thrust profiles. We propose a nonlinear impact-angle guidance law by analytically solving second-order error dynamics with nonlinear time-varying

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30

Liang, Haizhao, Zhi Li, Jinze Wu, Yu Zheng, Hongyu Chu, and Jianying Wang. "Optimal Guidance Laws for a Hypersonic Multiplayer Pursuit-Evasion Game Based on a Differential Game Strategy." Aerospace 9, no. 2 (2022): 97. http://dx.doi.org/10.3390/aerospace9020097.

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The guidance problem of a confrontation between an interceptor, a hypersonic vehicle, and an active defender is investigated in this paper. As a hypersonic multiplayer pursuit-evasion game, the optimal guidance scheme for each adversary in the engagement is proposed on the basis of linear-quadratic differential game strategy. In this setting, the angle of attack is designed as the output of guidance laws, in order to match up with the nonlinear dynamics of adversaries. Analytical expressions of the guidance laws are obtained by solving the Riccati differential equation derived by the closed-lo

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31

Sun, Sheng, Di Zhou, Jingyang Zhou, and Kok Lay Teo. "A generalized design method for three-dimensional guidance laws." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 231, no. 1 (2016): 47–60. http://dx.doi.org/10.1177/0954410016647076.

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The true proportional navigation guidance law, the augmented proportional navigation guidance law, or the adaptive sliding-mode guidance law, is designed based on the planar target-to-missile relative motion dynamics. By a proper construction of a nonlinear Lyapunov function for the line-of-sight angular rates in the three-dimensional guidance dynamics, it is shown that the three guidance laws mentioned above are able to ensure the asymptotic convergence of the angular rates as they are directly applied to the three-dimensional guidance environment. Furthermore, considering the missile autopil

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32

Pei, Pei, and Jiang Wang. "A New Optimal Guidance Law with Impact Time and Angle Constraints Based on Sequential Convex Programming." Mathematical Problems in Engineering 2021 (January 30, 2021): 1–15. http://dx.doi.org/10.1155/2021/6618351.

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This paper proposed an optimal time-varying proportional navigation guidance law based on sequential convex programming. The guidance law can achieve the desired impact angle and impact time with look angle and lateral acceleration constraints. By treating the multiconstraints’ guidance problem as an optimization problem and changing the independent variable to linearize the problem and constraints, the original nonlinear and nonconvex problem is transformed into a series of convex optimization problem so that it can be quickly solved by sequential convex programming. Numerical simulations com

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33

Yan, Xiaodong, and Shi Lyu. "A robust hybrid nonlinear guidance law for intercepting a non-cooperative maneuvering target." Aeronautical Journal 124, no. 1273 (2019): 429–45. http://dx.doi.org/10.1017/aer.2019.121.

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ABSTRACTThis paper has proposed a new robust hybrid nonlinear guidance law, which accounts for a missile’s terminal line-of-sight (LOS) angle constraint, in order to intercept a non-cooperative maneuvering target. The proposed hybrid nonlinear guidance strategy consists of two phases; in the first phase, a guidance law named PIGL is derived from prescribed performance control and the inertial delay control method. In PIGL, a revised prescribed performance function is put forward, and a prescribed performance controller with unknown uncertainties is then derived. The controller smoothly drives

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34

She, Haoping, Shuxing Yang, Hui Ni, and Horst Baier. "A Nonlinear Optimal Guidance Law with Terminal Impact Angle Constraint." International Journal of Computational Intelligence Systems 4, no. 6 (2011): 1319. http://dx.doi.org/10.2991/ijcis.2011.4.6.24.

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35

She, Haoping, Shuxing Yang, Hui Ni, and Horst Baier. "A Nonlinear Optimal Guidance Law with Terminal Impact Angle Constraint." International Journal of Computational Intelligence Systems 4, no. 6 (2011): 1319–24. http://dx.doi.org/10.1080/18756891.2011.9727881.

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36

Cao, Jian, Xiao Ping Zhu, and Jian Feng Wu. "Research of Optimal End Guidance Law about Target-Seeking UAV under Passive Guidance." Advanced Materials Research 383-390 (November 2011): 1590–94. http://dx.doi.org/10.4028/www.scientific.net/amr.383-390.1590.

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Measuring the relative distance, relative speed and target acceleration under knowing only angular information is called a "passive track" problem to target. Because of the noise in measuring result, it is necessary to describe a "passive track" problem by nonlinear random system. This paper researches optimal end guidance law about target-seeking UAV under passive guidance. As a simulation result, optimal end guidance law attacking fixed target is superior to constant coefficient proportion guidance law.

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37

Man, Chaoyuan, Rongjie Liu та Shihua Li. "Three-dimensional suboptimal guidance law based on θ – D technique and nonlinear disturbance observer". Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 233, № 14 (2019): 5122–33. http://dx.doi.org/10.1177/0954410019837123.

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In this paper, a nonlinear suboptimal guidance system is presented for the missile targeting an unknown arbitrary target. An integrated quadratic performance index is minimized in this guidance law, and the whole design is based on the exact 3D nonlinear missile-target dynamics without any linearization. Considering that the Hamilton–Jacobi–Bellman equation of a nonlinear system is quite difficult to be solved, the [Formula: see text] method is used to obtain the approximate solution without complicated online computations. Moreover, the target accelerations are regarded as the unknown disturb

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38

Raghunathan, T., and D. Ghose. "An online-implementable differential evolution tuned all-aspect guidance law." Control Engineering Practice 18, no. 10 (2010): 1197–210. http://dx.doi.org/10.1016/j.conengprac.2010.05.013.

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39

Shima, T., and O. M. Golan. "Linear Quadratic Differential Games Guidance Law for Dual Controlled Missiles." IEEE Transactions on Aerospace and Electronic Systems 43, no. 3 (2007): 834–42. http://dx.doi.org/10.1109/taes.2007.4383577.

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40

Ding, Hao, Kui Ping Liu, and Wen Li You. "Study on a New Nonlinear H_∞ Guidance Law for Autonomous Underwater Vehicle." Advanced Materials Research 219-220 (March 2011): 362–65. http://dx.doi.org/10.4028/www.scientific.net/amr.219-220.362.

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The key for Autonomous Underwater Vehicle (AUV) to implement target pursuit is to design high performance guidance law. The globose reference frame is adopted, and equations for 3-D relative motion between AUV and the target are built. Then the H∞ theory is used, and a new AUV nonlinear H∞ guidance law is obtained by solving Hamilton-Jacobi inequation. Simulation is taken on to verify the performance of H∞ guidance law. And the results show that the H∞ guidance law can help AUV overtake the target in less time, and the azimuth and pitching angle of the target line of sight are always staying a

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Kalra, Arti, Sreenatha Anavatti, and Radhakant Padhi. "Aggressive Formation Flying of Fixed-Wing UAVs with Differential Geometric Guidance." Unmanned Systems 05, no. 02 (2017): 97–113. http://dx.doi.org/10.1142/s2301385017500078.

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A nonlinear differential geometric guidance scheme is presented in this paper for aggressive autonomous formation flying of fixed-wing unmanned aerial vehicles (UAVs) in the leader-follower framework. It is assumed that the desired location of the followers are known in the velocity frame of the leader. It is also assumed that the followers can also access the position, velocity and acceleration parameters of the leader as necessary auxiliary information. By utilizing this information and manipulating their own dynamics, the proposed logic autonomously guides the followers to their respective

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42

Li, Zhi Ping, Jun Zhou, and Jian Guo Guo. "Study on Autopilot Dynamics with Robust Guidance Law and Terminal Constraint in Mechanical Engineering." Advanced Materials Research 644 (January 2013): 77–80. http://dx.doi.org/10.4028/www.scientific.net/amr.644.77.

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A new nonlinear robust guidance law was proposed by considering autopilot dynamics. Firstly, the mathematic model was built according to relationship between target and missile in vertical plane, by introducing the one-order dynamics of autopilot in Mechanical Engineering. Secondly, the nonlinear terminal guidance was obtained by applying the H∞ control theory under the performance index of minimizing the terminal angular constraint tracking error and control energy, and the asymptotic stability of guidance system was strictly proven by Lyapunov stability theory avoiding the estimation of the

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43

Gai, Wendong, Ning Zhang, Jing Zhang, and Yuxia Li. "A constant guidance law-based collision avoidance for unmanned aerial vehicles." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 233, no. 4 (2018): 1204–16. http://dx.doi.org/10.1177/0954410017751325.

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A method of automatic collision avoidance based on constant guidance law is proposed to solve the problem that the collision avoidance time is difficult to be estimated accurately during the collision avoidance process. The guidance command of the collision avoidance method is constant, and the lower bound of the constant guidance command satisfying the safe collision avoidance requirement is given by geometric method. Then, a collision avoidance time estimation method based on particle swarm optimization is proposed. In addition, the attitude control loop adopts the nonlinear proportional-int

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44

Li, Xiangxiang, Wanchun Chen, Zhongyuan Chen, Ting Wang, and Heng Shi. "Fixed-Time Circular Impact-Time Guidance with Look Angle Constraint." Aerospace 9, no. 7 (2022): 356. http://dx.doi.org/10.3390/aerospace9070356.

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A fixed-time nonlinear circular guidance law that satisfies the impact time constraint is proposed. By utilizing the geometric principle that the length of a circular arc connecting the missile and the target can be analytically calculated, the exact expression of time-to-go is obtained. Thus, the impact time error can be shaped to zero, and the missile can intercept the target at the desired time, which is crucial in a salvo attack. The settling time of the impact time error is proved to be bounded by a fixed time, which does not depend on initial conditions, but is only determined by two gui

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45

Liu, Xiang, Xutuo Ding, Yunlong Wang, Yahui Li, and Yukai Wang. "Adaptive Super-Twisting Sliding Mode Forward Tracking Guidance Law Considering Missile Body Characteristics." Journal of Physics: Conference Series 2569, no. 1 (2023): 012057. http://dx.doi.org/10.1088/1742-6596/2569/1/012057.

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Abstract Aiming at the problem of forward tracking guidance munitions with missile body characteristics intercepting maneuvering targets, and to improve the hit accuracy of forward tracking guidance system, this paper proposes an adaptive super-twisting sliding mode forward tracking guidance algorithm considering the impact of first-order overload characteristics of missile body and input saturation limitation. Firstly, the nonlinear model of the guidance system is made by the kinematic relation for projectile-target, the principle for the forward tracking interception, the overload characteri

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46

Cao, Jian, Cong Yan, and Li Liu. "Research of Integrated Design about Guidance and Control of Homing UAV." Applied Mechanics and Materials 373-375 (August 2013): 1428–31. http://dx.doi.org/10.4028/www.scientific.net/amm.373-375.1428.

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Integrated design about guidance and control of homing unmanned aerial vehicle (UAV) is proposed. Firstly, an integrated guidance and control model with uncertainties can be described. Secondly, a nonlinear observer is designed for the integrated guidance and control model. Finally, the simulation results show that the nonlinear adaptive guidance law using the proposed integrated design model can perform better than the one designed separately.

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47

Chen, Feng, Guangjun He, and Qifang He. "A finite-time-convergent composite guidance law with strong fault-tolerant performance." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 233, no. 9 (2018): 3120–30. http://dx.doi.org/10.1177/0954410018793280.

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To improve the performance of tracking and intercepting the low-altitude target, a nonlinear integral sliding mode guidance law is designed firstly, which can guarantee that the line-of-sight angle converges to a desired tracking angle and the line-of-sight angular rate converges to zero in finite time. Meanwhile, to solve the chattering problem caused by the high gain coefficient of the sign function in the guidance law, a sliding mode disturbance observer is designed to estimate the maneuvering acceleration of the target. Moreover, a composite nonlinear integral sliding mode guidance law is

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Sun, Qilong, Minghui Shen, Xiaolong Gu, Kang Hou, and Naiming Qi. "Evasion-Pursuit Strategy against Defended Aircraft Based on Differential Game Theory." International Journal of Aerospace Engineering 2019 (March 12, 2019): 1–12. http://dx.doi.org/10.1155/2019/7980379.

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The active defense scenario in which the attacker evades from the defender and pursues the target is investigated. In this scenario, the target evades from the attacker, and the defender intercepts the attacker by using the optimal strategies. The evasion and the pursuit boundaries are investigated for the attacker when the three players use the one-to-one optimal guidance laws, which are derived based on differential game theory. It is difficult for the attacker to accomplish the task by using the one-to-one optimal guidance law; thus, a new guidance law is derived. Unlike other papers, in th

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Qin, Xuesheng, Kebo Li, Yangang Liang, and Yuanhe Liu. "Minimum-Effort Waypoint-Following Differential Geometric Guidance Law Design for Endo-Atmospheric Flight Vehicles." Drones 7, no. 6 (2023): 369. http://dx.doi.org/10.3390/drones7060369.

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To improve the autonomous flight capability of endo-atmospheric flight vehicles, such as cruise missiles, drones, and other small, low-cost unmanned aerial vehicles (UAVs), a novel minimum-effort waypoint-following differential geometric guidance law (MEWFDGGL) is proposed in this paper. Using the classical differential geometry curve theory, the optimal guidance problem of endo-atmospheric flight vehicles is transformed into an optimal space curve design problem, where the guidance command is the curvature. On the one hand, the change in speed of the flight vehicle is decoupled from the guida

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Qian, Yu, Xiao Jun Xiang, and Jun Li Yang. "Design and Simulation of Guidance Law for a Kind of Flight Test Missile." Advanced Materials Research 538-541 (June 2012): 2887–91. http://dx.doi.org/10.4028/www.scientific.net/amr.538-541.2887.

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To reduce the miss distance of flight test missile, the midcourse guidance law is studied in this paper. The nonlinear projectile dynamic model is developed at first, and then designed the midcourse guidance law with the impact point prediction information. The guidance law was designed using the difference between predicting impact point and target point. To improve the guidance law’s performance, this research inducted the predicted impact point’s velocity information and integral term into guidance law command. At the end, the simulation was developed. The results of simulation show that th

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