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Journal articles on the topic 'Terminal guidance'

Author: Grafiati

Published: 6 September 2023

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1

Takehira, Tetsuya, Nguyen X. Vinh, and Pierre T. Kabamba. "Analytical Solution of Missile Terminal Guidance." Journal of Guidance, Control, and Dynamics 21, no. 2 (March 1998): 342–48. http://dx.doi.org/10.2514/2.4241.

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2

Rusnak, Ilan. "Multiple Model-Based Terminal Guidance Law." Journal of Guidance, Control, and Dynamics 23, no. 4 (July 2000): 742–46. http://dx.doi.org/10.2514/2.4593.

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3

Yu, Wenbin, Wanchun Chen, Liang Yang, Xiaoming Liu, and Hao Zhou. "Optimal terminal guidance for exoatmospheric interception." Chinese Journal of Aeronautics 29, no. 4 (August 2016): 1052–64. http://dx.doi.org/10.1016/j.cja.2016.04.019.

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4

Liaw, Der-Cherng, Yew-Wen Liang, and Chiz-Chung Cheng. "Nonlinear Control for Missile Terminal Guidance." Journal of Dynamic Systems, Measurement, and Control 122, no. 4 (February 4, 2000): 663–68. http://dx.doi.org/10.1115/1.1316796.

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Variable Structure Control (VSC) technique is applied to the design of robust homing missile guidance laws. In the design procedure, the target’s maneuver is assumed to be unpredictable and is considered as disturbances. Guidance laws are then proposed to achieve the interception performance for both cases of longitude-axis control being available and unavailable. The proposed guidance laws are continuous which alleviate chattering drawback by classic VSC design. Results are obtained and compared with those by realistic true proportional navigation design to illustrate the benefits of the proposed design. [S0022-0434(00)00604-3]

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5

Cui, Yan Kai, Li Fu, Xiao Geng Liang, and Ling Luo. "Optimal Sliding-Mode Terminal Guidance Law Design of Airborne Boost-Phase Ballistic Missile Interception." Applied Mechanics and Materials 40-41 (November 2010): 15–20. http://dx.doi.org/10.4028/www.scientific.net/amm.40-41.15.

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Aiming at terminal guidance law design of airborne boost-phase ballistic missile interception under acceleration of target without availability, we study on optimal sliding-mode terminal guidance law design of Kinetic-Kill Vehicle. Motion characteristic and infrared characteristic of ballistic missile are analyzed basing on founding ballistic missile boost-phase motion equations. Optimal terminal guidance law of Kinetic-Kill Vehicle is designed basing on undershoot quantity least and energy minimum. Optimal guidance law and augmented proportional navigation law having the same form is proved in theory. Optimal sliding-mode terminal guidance law is designed under acceleration of target without availability, using optimal control theory and sliding-mode control theory. Simulation show that optimal sliding-mode terminal guidance law satisfies required index, reaching the aim to direct hit the target. The correctness and effectiveness of the optimal sliding-mode guidance law are proved.

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6

Guo, Zhengyu, Chaolei Wang, Hang Qian, Zhiguo Han, and Jingxian Zhang. "Cooperative Intercepting Guidance Law for Large Maneuvering Target with Impact Angle Constraint." Xibei Gongye Daxue Xuebao/Journal of Northwestern Polytechnical University 38, no. 6 (December 2020): 1257–65. http://dx.doi.org/10.1051/jnwpu/20203861257.

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A distributed multi-missile cooperative guidance law based on the finite time theory is proposed to solve the terminal guidance problem of three-dimensional multi-missiles cooperative interception of large maneuvering target. According to the finite time consistency theory, an adaptive guidance law based on the integral sliding mode is designed to ensure that all missiles can reach the target at the same time in the terminal guidance process. The longitudinal and lateral acceleration of the line of sight are based on the guidance law of the fast terminal sliding mode surface. The terminal attack angle is constrained, so that the terminal attack Angle can reach the expected value in finite time. The simulation results show that the designed guidance law can achieve the cooperative attack on the maneuvering targets.

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7

Ulybyshev, Yuri. "Terminal Guidance Law Based on Proportional Navigation." Journal of Guidance, Control, and Dynamics 28, no. 4 (July 2005): 821–24. http://dx.doi.org/10.2514/1.12545.

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8

Harl, Nathan, and S. N. Balakrishnan. "Reentry Terminal Guidance Through Sliding Mode Control." Journal of Guidance, Control, and Dynamics 33, no. 1 (January 2010): 186–99. http://dx.doi.org/10.2514/1.42654.

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9

Aggarwal, Romesh K., and Charles R. Moore. "Terminal Guidance Algorithm for Ramjet-Powered Missiles." Journal of Guidance, Control, and Dynamics 21, no. 6 (November 1998): 862–66. http://dx.doi.org/10.2514/2.4349.

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10

Kumar, Prem, Prasiddha N. Dwivedi, Abhijit Bhattacharyya, and Radhakant Padhi. "Terminal-Lead-Angle-Constrained Generalized Explicit Guidance." IEEE Transactions on Aerospace and Electronic Systems 53, no. 3 (June 2017): 1250–60. http://dx.doi.org/10.1109/taes.2017.2669598.

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11

Zhou, Min, Jun Zhou, and Jianguo Guo. "Terminal area guidance for reusable launch vehicles." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 230, no. 2 (July 3, 2015): 333–49. http://dx.doi.org/10.1177/0954410015591615.

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12

Liang, Zixuan, Jiateng Long, Shengying Zhu, and Rui Xu. "Entry guidance with terminal approach angle constraint." Aerospace Science and Technology 102 (July 2020): 105876. http://dx.doi.org/10.1016/j.ast.2020.105876.

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13

McInnes, Colin R. "Path shaping guidance for terminal lunar descent." Acta Astronautica 36, no. 7 (October 1995): 367–77. http://dx.doi.org/10.1016/0094-5765(95)00119-0.

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14

Wang, Xingdan, Yu Yao, Baoqing Yang, and Jian Guo. "The Sensitivity Analysis of Difference Guidance Laws for the Terminal Guidance System." Advanced Science Letters 6, no. 1 (March 15, 2012): 346–50. http://dx.doi.org/10.1166/asl.2012.2323.

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15

Cong, Mingyu, Xianghong Cheng, Zhiquan Zhao, and Zhijun Li. "Studies on Multi-Constraints Cooperative Guidance Method Based on Distributed MPC for Multi-Missiles." Applied Sciences 11, no. 22 (November 17, 2021): 10857. http://dx.doi.org/10.3390/app112210857.

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Cooperative terminal guidance with impact angle constraint is a key technology to achieve a saturation attack and improve combat effectiveness. The present study envisaged cooperative terminal guidance with impact angle constraint for multiple missiles. In this pursuit, initially, the three-dimensional cooperative terminal guidance law with multiple constraints was studied. The impact time cooperative strategy of virtual leader missile and follower missiles was designed by introducing virtual leader missiles. Subsequently, based on the distributed model prediction control combined with the particle swarm optimization algorithm, a cooperative terminal guidance algorithm was designed for multiple missiles with impact angle constraint that met the guidance accuracy. Finally, the effectiveness of the algorithm was verified using simulation experiments.

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16

Gao, C., J. Li, T. Feng, and W. Jing. "Adaptive terminal guidance law with impact-angle constraint." Aeronautical Journal 122, no. 1249 (November 29, 2017): 369–89. http://dx.doi.org/10.1017/aer.2017.124.

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ABSTRACTThis paper proposes an adaptive guidance law for attacking a ground target based on motion camouflage strategy. The coefficients of normal and bi-normal feedback guidance law are given according to the relative motion relationship under Frenet frame. Utilizing the coefficients, the motion camouflage proportional guidance law is derived. In order to improve the initial overload characteristic of the missile, an adaptive feedback coefficient is introduced. Then, the adaptive guidance law is applied to a longitudinal plane interception problem with impact-angle constraint. Finally, the validity of this guidance law for air-to-ground missiles is proved by simulations.

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17

Shi, Qingli, Hua Wang, and Hao Cheng. "Multiple Constraints-Based Adaptive Three-Dimensional Back-Stepping Sliding Mode Guidance Law against a Maneuvering Target." Aerospace 9, no. 12 (December 5, 2022): 796. http://dx.doi.org/10.3390/aerospace9120796.

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This paper addresses the issue of a complex three-dimension (3-D) terminal guidance process that is used against maneuvering targets while considering both the terminal impact angle (TIA) and field-of-view (FOV) angle constraints. According to the highly coupled and nonlinear 3-D terminal guidance model, an adaptive back-stepping sliding-mode guidance law algorithm is proposed in order to guarantee the stability and robustness of the guidance system. Considering the explicit expression of the line-of-sight (LOS) angle in the kinematics and dynamics of the terminal guidance process, the TIA constraint is transformed into an LOS constraint based on their well-known relationship. In view of the challenges in obtaining the motion information of maneuvering targets, an adaptive law design is introduced in order to estimate and compensate for external disturbances caused by the maneuvering of the target and modeling uncertainty. In addition, because the FOV angle represented by the overall leading angle is not a state variable in the sliding-mode guidance system, it is decoupled into two partial leading angles based on a specific transformation relation, so the 3-D terminal guidance control problem is converted into separate tracking system control issues in the pitch and yaw planes. Then, the Lyapunov stability theory is utilized to substantiate the stability of the guidance system, where the Lyapunov functions in both of the subsystems consist of the LOS and partial FOV state error terms. Finally, a series of simulations of various motion states of maneuvering targets under different terminal cases were carried out. It was proved that the terminal guidance design based on the strategies presented above was able to obtain the desired LOS constraints with satisfying the FOV limitation, and the simulation results verified the effectiveness, universality, and significance for practical applications of the proposed guidance design method.

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18

Zhe, Luo, Li Xinsan, Wang Lixin, and Shen Qiang. "Multiconstrained Gliding Guidance Based on Optimal and Reinforcement Learning Method." Mathematical Problems in Engineering 2021 (May 26, 2021): 1–12. http://dx.doi.org/10.1155/2021/6652232.

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In order to improve the autonomy of gliding guidance for complex flight missions, this paper proposes a multiconstrained intelligent gliding guidance strategy based on optimal guidance and reinforcement learning (RL). Three-dimensional optimal guidance is introduced to meet the terminal latitude, longitude, altitude, and flight-path-angle constraints. A velocity control strategy through lateral sinusoidal maneuver is proposed, and an analytical terminal velocity prediction method considering maneuvering flight is studied. Aiming at the problem that the maneuvering amplitude in velocity control cannot be determined offline, an intelligent parameter adjustment method based on RL is studied. This method considers parameter determination as a Markov Decision Process (MDP) and designs a state space via terminal speed and an action space with maneuvering amplitude. In addition, it constructs a reward function that integrates terminal velocity error and gliding guidance tasks and uses Q-Learning to achieve the online intelligent adjustment of maneuvering amplitude. The simulation results show that the intelligent gliding guidance method can meet various terminal constraints with high accuracy and can improve the autonomous decision-making ability under complex tasks effectively.

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19

Yang, Fang, Kuanqiao Zhang, and Lei Yu. "Adaptive Super-Twisting Algorithm-Based Nonsingular Terminal Sliding Mode Guidance Law." Journal of Control Science and Engineering 2020 (July 4, 2020): 1–11. http://dx.doi.org/10.1155/2020/1058347.

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A nonsingular fast terminal sliding mode guidance law with an impact angle constraint is proposed to solve the problem of missile guidance accuracy and impact angle constraint for maneuvering targets. Aiming at the singularity problem of the terminal sliding mode, a fast terminal sliding mode surface with finite-time convergence and impact angle constraint is designed based on fixed-time convergence and piecewise sliding mode theory. To weaken chattering and suppress interference, a second-order sliding mode supertwisting algorithm is improved. By designing the parameter adaptive law, an adaptive smooth supertwisting algorithm is designed. This algorithm can effectively weaken chattering without knowing the upper bound information of interference, and it converges faster. Based on the proposed adaptive supertwisting algorithm and the sliding mode surface, a guidance law with the impact angle constraint is designed. The global finite-time convergence of the guidance law is proved by constructing the Lyapunov function. The simulation results verify the effectiveness of the proposed guidance law, and compared with the existing terminal sliding mode guidance laws, the proposed guidance law has higher guidance precision and angle constraint accuracy.

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20

Xu, X., and Y. Liang. "Biased optimal guidance law with specified velocity rendezvous angle constraint." Aeronautical Journal 119, no. 1220 (October 2015): 1287–99. http://dx.doi.org/10.1017/s0001924000011258.

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Abstract In order to increase the effectiveness of interceptor missile, velocity rendezvous angle control is required in the terminal phase. The purpose of this paper is to obtain an optimal guidance law which can achieve specified velocity rendezvous angle as well as zero terminal miss distance. A biased optimal guidance law based on a simplified mathematical model is deduced for interceptors engaging against invasion aircraft. Different from previous literatures on this issue, the presented guidance law suitable for intercepting high-speed maneuvering target. Another advantage is, under centimeter level miss distance setting, the guidance law needs smaller guidance command near the terminal time, which can successfully avoid command saturation. Simulation results demonstrate the effectiveness of the presented guidance law.

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21

Liu, JH, JY Shan, and Q. Liu. "Optimal pulsed guidance law with terminal impact angle constraint." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 231, no. 11 (August 28, 2016): 1993–2005. http://dx.doi.org/10.1177/0954410016664918.

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An optimal pulsed guidance law with a time-varying weighted quadratic cost function that enables imposing a predetermined intercept angle is presented. Due to the characteristic of impulse force, admissible variance of control is redefined. The optimal pulsed guidance law is deduced via extended maximum principle. The optimal pulsed guidance law is eventually transformed to solve the two-point boundary value problem. To decide a shooting point, an efficient algorithm is proposed by combining particle swarm optimization and Kriging surrogate model method. The optimal pulsed guidance law is implemented in several representative engagements. From simulation results, it can be seen that the proposed guidance law can achieve small miss distance with terminal impact angle constraint under different conditions. Moreover, the performance of the proposed guidance law is satisfactory with the comparison of sliding-mode pulsed guidance law.

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22

Xie, Dao Cheng, and Zhong Wei Wang. "Optimal Guidance Law Design for Reentry Vehicles with Terminal Velocity and Angle Constraints." Advanced Materials Research 459 (January 2012): 505–9. http://dx.doi.org/10.4028/www.scientific.net/amr.459.505.

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To achieve better impact effect, impact point error is of first importance, terminal velocity and angle of reentry vehicle are also needed to satisfy the expected value. This paper investigates the optimal guidance law for reentry vehicle. Guidance equation is expressed in longitudinal and lateral plane respectively, needed guidance command of angle of attack and sideslip angle is generated. Guidance command of angle of attack and sideslip angle is appended when considering reentry velocity. Synthesized guidance command is the sum of needed guidance command and appended guidance command. Effect of attitude control for reentry vehicle is analyzed using optimal guidance; the attitude of vehicle is stable and is guided to target point precisely. Trendline of landing error, reentry velocity and terminal angle varying with reentry time are analyzed, simulation results show that optimal guidance law is proper and satisfies the demand of impact point error, terminal velocity and angle.

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23

Zhou, Hao, Tawfiqur Rahman, and Wanchun Chen. "Neural Network Assisted Inverse Dynamic Guidance for Terminally Constrained Entry Flight." Scientific World Journal 2014 (2014): 1–12. http://dx.doi.org/10.1155/2014/686040.

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This paper presents a neural network assisted entry guidance law that is designed by applying Bézier approximation. It is shown that a fully constrained approximation of a reference trajectory can be made by using the Bézier curve. Applying this approximation, an inverse dynamic system for an entry flight is solved to generate guidance command. The guidance solution thus gotten ensures terminal constraints for position, flight path, and azimuth angle. In order to ensure terminal velocity constraint, a prediction of the terminal velocity is required, based on which, the approximated Bézier curve is adjusted. An artificial neural network is used for this prediction of the terminal velocity. The method enables faster implementation in achieving fully constrained entry flight. Results from simulations indicate improved performance of the neural network assisted method. The scheme is expected to have prospect for further research on automated onboard control of terminal velocity for both reentry and terminal guidance laws.

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24

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 terminal constraints and terminal constraints, respectively. And finally, the simulation results show that the proposed guidance law can effectively satisfy the guidance precision requirements of BTT missile.

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25

Wang, Hui, Jiang Wang, and Defu Lin. "Generalized optimal impact-angle-control guidance with terminal acceleration response constraint." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 231, no. 14 (September 11, 2017): 2515–36. http://dx.doi.org/10.1177/0954410017730250.

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To study the optimal impact-angle-control guidance problem with multiple terminal constraints, a generalized optimal impact-angle-control guidance law with terminal acceleration response constraint (GOIACGL-TARC) is proposed. In the deriving, a time-to-go − nth power weighted object function is adopted to derived the GOIACGL-TARC and a general expression of GOIACGL-TARC is presented. Based on the general expression of GOIACGL-TARC, three guidance laws, GOIACGL-TARC1/TACC0/TACC1 are proposed and the inheritance relationship between GOIACGL-TACC0/TACC1/TARC1 and the conventional optimal guidance law with impact angle constraint is demonstrated. Performance analysis of the proposed guidance laws shows that in the case of GOIACGL-TACC0, the terminal acceleration is not zero at n = 0 and only as n > 0, the terminal acceleration converges to zero; in the case of GOIACGL-TACC1 and GOIACGL-TARC1, GOIACGL-TARC1 can guarantee the acceleration response to reach the exactly zero value but GOIACGL-TACC1 cannot, which can only guarantee the acceleration command to reach the exactly zero value. It is pointed out that compared with the biased proportional navigation guidance law, GOIACGL-TARC1 has an outstanding guidance performance in acceleration response, miss distance, and terminal impact angle error.

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26

Qiao, Qing Qing, and Wan Chun Chen. "A Near Optimal Midcourse Guidance Law for Air-to-Air Missile." Applied Mechanics and Materials 336-338 (July 2013): 833–38. http://dx.doi.org/10.4028/www.scientific.net/amm.336-338.833.

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Dynamic inversion and singular perturbation methods are employed for medium-range air-to-air missile to obtain a near-optimal midcourse guidance law. The midcourse guidance stage is separated into two phases. In phase 1, which the rocket engine working, a dynamic inversion guidance law is used to guide the missile flight along a nominal trajectory. In the second gliding phase, singular perturbation technique is employed to develop a guidance law which maximum terminal specific energy. A terminal correction is made to ensure the seeker intercept the target. The result obtained from numerical simulation shows that, the guidance law can conserve energy for terminal interception, and the flight path error is small enough at the end of midcourse stage.

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27

Li, E., and A. Fomichev. "Accuracy Analysis of Lunar Lander Terminal Guidance Algorithm." Science and Education of the Bauman MSTU 17, no. 04 (April 3, 2017): 113–28. http://dx.doi.org/10.7463/0417.0000957.

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28

Rogers, Jonathan, and Nathan Slegers. "Robust Parafoil Terminal Guidance Using Massively Parallel Processing." Journal of Guidance, Control, and Dynamics 36, no. 5 (September 2013): 1336–45. http://dx.doi.org/10.2514/1.59782.

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29

Ryoo, Chang-Kyung, Hangju Cho, and Min-Jea Tahk. "Optimal Guidance Laws with Terminal Impact Angle Constraint." Journal of Guidance, Control, and Dynamics 28, no. 4 (July 2005): 724–32. http://dx.doi.org/10.2514/1.8392.

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30

Fowler, Lee, and Jonathan Rogers. "Bézier Curve Path Planning for Parafoil Terminal Guidance." Journal of Aerospace Information Systems 11, no. 5 (May 2014): 300–315. http://dx.doi.org/10.2514/1.i010124.

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31

Fomichev, A. V., and E. K. Li. "Analytical 3D Terminal Guidance Algorithm for Lunar Landing." MEHATRONIKA, AVTOMATIZACIA, UPRAVLENIE 18, no. 6 (June 15, 2017): 423–31. http://dx.doi.org/10.17587/mau.18.423-431.

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32

Liang, Zixuan, Qingdong Li, and Zhang Ren. "Virtual Terminal–Based Adaptive Predictor–Corrector Entry Guidance." Journal of Aerospace Engineering 30, no. 4 (July 2017): 04017013. http://dx.doi.org/10.1061/(asce)as.1943-5525.0000716.

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33

XIANG, Shengwen, Tiancheng LI, Wei CHEN, Hongqi FAN, and Qiang FU. "Maximal admissible mode decision delay in terminal guidance." Chinese Journal of Aeronautics 32, no. 8 (August 2019): 1959–66. http://dx.doi.org/10.1016/j.cja.2019.02.011.

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34

Fariz, A., and R. A. Sasongko. "Missile Initial Engagement Determination and Terminal Phase Guidance." IFAC-PapersOnLine 52, no. 12 (2019): 19–24. http://dx.doi.org/10.1016/j.ifacol.2019.11.063.

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35

Vittal, R. Vijaya, and M. Seetharama Bhat. "Optimal explicit terminal guidance for a launch vehicle." Acta Astronautica 29, no. 4 (April 1993): 249–62. http://dx.doi.org/10.1016/0094-5765(93)90138-m.

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36

Shieh, C. S. "Nonlinear rule-based controller for missile terminal guidance." IEE Proceedings - Control Theory and Applications 150, no. 1 (January 1, 2003): 45–48. http://dx.doi.org/10.1049/ip-cta:20030007.

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37

Fan, Shijie, Hongqi Fan, Huaitie Xiao, Jianpeng Fan, and Qiang Fu. "Observability analysis of feature aided terminal guidance systems." Journal of Systems Engineering and Electronics 26, no. 1 (February 2015): 127–33. http://dx.doi.org/10.1109/jsee.2015.00017.

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38

Long, Jiateng, Ai Gao, Pingyuan Cui, and Yang Liu. "Mars atmospheric entry guidance for optimal terminal altitude." Acta Astronautica 155 (February 2019): 274–86. http://dx.doi.org/10.1016/j.actaastro.2018.12.001.

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39

Ratnoo, Ashwini. "A Non-Switching Guidance Law with Terminal Constraints." IFAC-PapersOnLine 49, no. 1 (2016): 7–11. http://dx.doi.org/10.1016/j.ifacol.2016.03.020.

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40

Jiang, C. W., G. F. Zhou, B. Yang, C. S. Gao, and W. X. Jing. "Novel guidance model and its application for optimal re-entry guidance." Aeronautical Journal 122, no. 1257 (October 2, 2018): 1811–25. http://dx.doi.org/10.1017/aer.2018.94.

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ABSTRACTAiming at three-dimensional (3D) terminal guidance problem, a novel guidance model is established in this paper, in which line-of-sight (LOS) range is treated as an independent variable, describing the relative motion between the vehicle and the target. The guidance model includes two differential equations that describe LOS’s pitch and yaw motions in which the pitch motion is separately decoupled. This model avoids the inaccuracy of simplified two-dimensional (2D) guidance model and the complexity of 3D coupled guidance model, which not only maintains the accuracy but also simplifies the guidance law design. The application of this guidance model is studied for optimal re-entry guidance law with impact angle constraint, which is presented in the form of normal overload. Compared with optimal guidance laws based on traditional guidance model, the proposed one based on novel guidance model is implemented with the LOS range instead of time-to-go, which avoids the problem of the time-to-go estimation of traditional optimal guidance laws. Finally, the correctness and validity of the guidance model and guidance law are verified by numerical simulation. The guidance model and guidance law proposed in this paper provide a new way for the design of terminal guidance.

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41

Wu, Zhenglong, Zhenyu Guan, Chengwei Yang, and Jie Li. "Terminal Guidance Law for UAV Based on Receding Horizon Control Strategy." Complexity 2017 (2017): 1–19. http://dx.doi.org/10.1155/2017/2750172.

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Terminal guidance law against the maneuvering target is always the focal point. Most of the literatures focus on estimating the acceleration of target and time to go in guidance law, which are difficult to acquire. This paper presents a terminal guidance law based on receding horizon control strategy. The proposed guidance law adopts the basic framework of receding horizon control, and the guidance process is divided into several finite time horizons. Then, optimal control theory and target motion prediction model are used to derive guidance law for minimum time index function with continuous renewal of original conditions at the initial time of each horizon. Finally, guidance law performs repeated iteration until intercepting the target. The guidance law is of subprime optimal type, requiring less guidance information, and does not need to estimate the acceleration of target and time to go. Numerical simulation has verified that the proposed guidance law is more effective than traditional methods on constant and sinusoidal target with bounded acceleration.

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42

Zhang, Jing. "Research on Classroom Teaching Evaluation and Instruction System Based on GIS Mobile Terminal." Mobile Information Systems 2021 (July 15, 2021): 1–11. http://dx.doi.org/10.1155/2021/9790766.

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With the development of mobile terminal technology, GIS has begun to be applied in all walks of life. With its powerful spatial indexing, positioning, query, analysis, and graphics processing capabilities, it has become the evaluation and guidance analysis of domestic and foreign scholars. As an essential tool to improve the quality of teaching in our country’s primary and secondary schools and universities and to understand the status quo of education and teaching levels, appropriate teaching evaluation and guidance are essential. In order to adopt a better method to carry out teaching work, this research uses GIS mobile terminal to analyze the classroom teaching evaluation and guidance system, and through the research on teaching evaluation, the teaching work is made more effective. This paper uses questionnaire survey method, index weighted evaluation method, and fuzzy analytic hierarchy process as research methods. In the experimental part, a classroom teaching evaluation and guidance system based on GIS mobile terminal is designed. In the analysis part, a comprehensive analysis of teaching evaluation and guidance is carried out, including the analysis of teacher teaching evaluation, the analysis of teaching evaluation system, and the analysis of teachers and students’ understanding of teaching evaluation. Among them, after adopting the teaching evaluation system of GIS mobile terminal, the number of students who thought the teaching evaluation system was useless dropped from 4.6% to 1.8%. Students tend to emphasize the teacher’s effectiveness in teaching (57.2%) and interesting teaching content in the classroom (56.9%). This analysis has a certain significance for teaching evaluation, and it occupies a relatively important proportion in the improvement of the evaluation system. In general, the teaching evaluation system using GIS mobile terminals can improve the communication and teaching diagnosis between teachers and students and help further improve teaching.

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43

Li, Bin, Defu Lin, Jiang Wang, and Song Tian. "Guidance law to control impact angle and time based on optimality of error dynamics." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 233, no. 10 (September 24, 2018): 3577–88. http://dx.doi.org/10.1177/0954410018801226.

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In this work, a new guidance law with a meaningful performance index is designed to satisfy terminal impact angle and impact time constraints based on optimal error dynamics, which can be used for salvo attacks or cooperative missions of multi-missile. The analytical solution of the proposed guidance law is a combination of trajectory shaping guidance law and an additional impact time error feedback term that is proportional to the difference between the desired and the true impact times. Trajectory shaping guidance law aims to achieve the desired terminal impact angle and zero miss distance, whereas the extra term aims to meet the desired impact time. The minimum and maximum feasible impact times that consider the seeker's field-of-view limit, terminal impact angle constraint, and missile's maneuvering acceleration limit are calculated to provide the feasible boundary range of the desired impact time. Numerical simulations of several engagement situations demonstrate the effectiveness of the proposed guidance law in the accuracy of terminal impact angle and impact time.

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Li, Bin, Pan Tang, Haotian Xu, and Duo Zheng. "Terminal Impact Angle Control Guidance Law Considering Target Observability." Aerospace 9, no. 4 (April 3, 2022): 193. http://dx.doi.org/10.3390/aerospace9040193.

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The problem of the terminal impact angle control guidance law, considering the target observability for passive guidance with bearing-only measurement, is investigated in this paper. Modified line-of-sight (LOS) angle error dynamics and their closed-loop analytical solution are developed to enhance the target observability, and then their characteristics are studied, which makes the LOS angular rate oscillate in the early stage. The terminal impact angle control guidance law with the global sliding mode is designed to eliminate the approaching stage of sliding mode control, which makes the system robust throughout the entire process of control. Finally, numerical simulations are presented to demonstrate the performance of the proposed guidance law under various conditions, which achieves the desired results.

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Geng, Sheng-Tao, Jie Zhang, and Jing-Guang Sun. "Adaptive back-stepping sliding mode guidance laws with autopilot dynamics and acceleration saturation consideration." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 233, no. 13 (March 19, 2019): 4853–63. http://dx.doi.org/10.1177/0954410019835728.

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This paper studies the guidance scheme for the terminal guidance problem subject to input constraints, attack angle constraints, and second-order dynamics of missile autopilot. Firstly, the guidance system model with the above multi-constraint model is given. Secondly, an anti-saturation back-stepping guidance law which makes use of the low-pass filter to avoid the differential of the virtual control signals is designed based on the terminal sliding mode method, auxiliary system, and adaptive technique. Finally, Lyapunov theory and numerical simulations are utilized to prove that the states of the system under the proposed guidance law are uniformly ultimately bounded.

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Kumar, G. N., and A. K. Sarkar. "CMAC Trained Optimum Mid course Guidance for Tactical Flight Vehicle." Defence Science Journal 71, no. 6 (October 22, 2021): 826–35. http://dx.doi.org/10.14429/dsj.71.16295.

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This paper discusses design and validation of neural network based mid-course guidance law of a surface to air flight vehicle. In present study, initially different optimal trajectories have been generated off-line of different pursuer-evader engagements by ensuring minimum flight time, maximum terminal velocity and favorable handing over conditions for seeker based terminal guidance. These optimal trajectories have been evolved by nonlinear programming based direct method of optimisation. The kinematic information of both pursuer and evader, generated based on these trajectories have been used to train cerebellar model articulate controller (CMAC) neural network. Later for a given engagement scenario an on-line near optimal mid-course guidance law has been evolved based on output of trained network. Training has been carried out by CMAC type supervisory neural network. The tested engagement condition is within input/output training space of neural network. Seeker based homing guidance has been used for terminal phase. Complete methodology has been validated along pitch plane of pursuer-evader engagement. During mid-course phase, the guidance demand has been tracked by attitude hold autopilot and during terminal phase, the guidance demanded lateral acceleration has been tracked by acceleration autopilot. System robustness has been studied in presence of plant parameter variations and sensor noise under Monte Carlo Platform.

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Zhai, Qing Lin, Da Wei Lu, and Jun Zhang. "A Novel Decoupled LOS Rate Estimator for Terminal Guidance." Applied Mechanics and Materials 519-520 (February 2014): 1032–39. http://dx.doi.org/10.4028/www.scientific.net/amm.519-520.1032.

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An novel decoupled estimation algorithm based on kalman filter is presented to solve the line-of-sight (LOS) rate estimation problem in terminal guidance of air-to-air combat. The measurements of target azimuth and elevation are obtained by missile-borne active radar seeker which use a monopulse doppler radar. As it cant be directly measured by this kind of radar, the LOS rate which is needed as the input of guidance law should be estimated from these angle measurements. The close-loop simulation of LOS rate estimation in typical terminal guidance scenario that an air-to-air missile seeks a military fighter validates the presented algorithm.

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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 (April 19, 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 compared with existing guidance schemes and relevant analysis is provided. Design/methodology/approach The paper develops 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. This guidance scheme is further extended to moving targets. Findings The proposed guidance intercepts a stationary target with a smooth lateral acceleration command, which is desirable for realistic implementation. The efficacy of the approach is demonstrated through numerical simulation. A comparative study with the existing algorithm is presented and it is shown that the proposed algorithm is better on many counts. Originality/value There are many approach exists in the literature for impact-angle guidance laws. The paper proposes a computationally efficient guidance law using geometric and kinematic properties. As the approach produces smooth command, it has a practical relevance. A comparative study shows superiority on some counts (miss distance, flight time, smoothness).

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Zhang, Haoqiang, Shengjing Tang, and Jie Guo. "Cooperative near-space interceptor mid-course guidance law with terminal handover constraints." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 233, no. 6 (May 3, 2018): 1960–76. http://dx.doi.org/10.1177/0954410018769182.

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A cooperative problem in mid-course guidance phase is addressed in this paper. For providing suitable initial conditions of successful terminal salvo attack, a novel finite-time cooperative mid-course guidance law with terminal handover constraints is proposed. Firstly, a three-dimensional guidance model of mid-course is decoupled in a planar line-of-sight frame as a two-point boundary value problem. The terminal handover constraints which can guarantee an ideal zero effort terminal engagement are proposed and analyzed. Secondly, the design of the cooperative mid-course guidance law is separated into two stages. The acceleration commands along the line-of-sight direction are developed based on the finite-time average-consensus protocol and super-twisting algorithm in the first stage. In the second stage, the model predictive static programming method is adopted to solve the two-point boundary value problem in line-of-sight frame with a known final time from first stage. Furthermore, sliding mode control theory is used in combination with model predictive static programming method to satisfy terminal handover constraints with bounded perturbation. Finally, numerical simulations of two four-interceptor cooperative scenario are carried out to verify the validity of the proposed cooperative guidance law. The simulation results reflect that all the four interceptors can reach their own predictive interception points with specific approach angles simultaneously.

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de Celis, Raúl, Pablo Solano López, and Luis Cadarso. "Sensor hybridization using neural networks for rocket terminal guidance." Aerospace Science and Technology 111 (April 2021): 106527. http://dx.doi.org/10.1016/j.ast.2021.106527.

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