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Journal articles on the topic 'Guidance with field-of-view constraints'

Author: Grafiati

Published: 6 September 2023

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1

Hu, Jian, Naigang Cui, Yuliang Bai, and Yunhai Geng. "Guidance law to control impact time constraining the seeker’s field of view?" Aircraft Engineering and Aerospace Technology 91, no. 1 (January 7, 2018): 20–29. http://dx.doi.org/10.1108/aeat-06-2017-0151.

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Purpose The purpose of this paper is to present a novel guidance law that is able to control the impact time while the seeker’s field of view (FOV) is constrained. Design/methodology/approach The new guidance law is derived from the framework of Lyapunov stability theory to ensure interception at the desired impact time. A time-varying guidance gain scheme is proposed based on the analysis of the convergence time of impact time error, where finite-time stability theory is used. The circular trajectory assumption is adopted for the derivation of accurate analytical estimation of time-to-go. The seeker’s FOV constraint, along with missile acceleration constraint, is considered during guidance law design, and a switching strategy to satisfy it is designed. Findings The proposed guidance law can drive missile to intercept stationary target at the desired impact time, as well as satisfies seeker’s FOV and missile acceleration constraints during engagement. Simulation results show that the proposed guidance law could provide robustness against different engagement scenarios and autopilot lag. Practical implications The presented guidance law lays a foundation for using cooperative strategies, such as simultaneous attack. Originality/value This paper presents further study on the impact time control problem considering the seeker’s FOV constraint, which conforms better to reality.

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2

Zhang, Haoqiang, Shengjing Tang, Jie Guo, and Wan Zhang. "A Two-Phased Guidance Law for Impact Angle Control with Seeker’s Field-of-View Limit." International Journal of Aerospace Engineering 2018 (2018): 1–13. http://dx.doi.org/10.1155/2018/7403639.

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A two-phased guidance problem with terminal impact angle constraints and seeker’s field-of-view limit is addressed in this paper for a missile against a nonmaneuvering incoming target. From the conventional PN guidance without any constraints, it is found that satisfying the impact angle constraint causes a more curved missile trajectory requiring a large look angle. To avoid the look angle exceeding the seeker’s physical limit, a two-phased look angle control guidance scheme with the terminal constraint is introduced. The PN-typed guidance law is designed for each guidance phase with a specific switching condition of line-of-sight. The proposed guidance law is comprised of two types of acceleration commands: the one in the initial phase which aims at controlling the missile’s look angle to reach the limit and the other for final phase which is produced by switching the navigation gain. The monotonicity of the line-of-sight angle and look angle is analyzed and proved to support the proposed method. To evaluate the specific navigation gains for both initial and final phases, the scaling coefficient between them is discussed by solving a quadratic equation with respect to the initial navigation gain. To avoid a great abrupt acceleration change at the switching instant, a minimum coefficient is chosen. Extensive simulations are performed to validate the efficiency of the proposed approach.

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3

Ma, Shuai, Zhongyuan Wang, Xugang Wang, and Qi Chen. "Three-Dimensional Impact Time Control Guidance Considering Field-of-View Constraint and Velocity Variation." Aerospace 9, no. 4 (April 9, 2022): 202. http://dx.doi.org/10.3390/aerospace9040202.

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The problem of three-dimensional impact time control guidance considering field-of-view constraints and time-varying velocity is investigated in this study. First, considering the effect of gravity and aerodynamic forces on velocity, a simplified numerical estimation algorithm of flight time with a three-dimensional proportional navigation guidance law is derived. Then, based on the structure of the biased proportional navigation guidance law, the effect of the biased term on flight time is analyzed. The biased term is then designed to achieve impact time and field-of-view constraints considering time-varying velocity. Finally, numerical simulations are performed to demonstrate the effectiveness and superiority of the proposed guidance law.

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4

Kim, Hyeong-Geun, and Jun-Yong Lee. "Generalized Guidance Formulation for Impact Angle Interception with Physical Constraints." Aerospace 8, no. 10 (October 18, 2021): 307. http://dx.doi.org/10.3390/aerospace8100307.

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This paper proposes an optimal impact angle control guidance law for homing missiles with a narrow field-of-view of the seekers. As groundwork for designing a guidance law, we first present a general guidance structure that can achieve any terminal constraint of the line-of-sight rate based on the optimal control theory. We configure the desired profile of the line-of-sight rate using a saturation function whose exact form is determined to satisfy the required boundary conditions. By combining the line-of-sight rate profile with the optimal guidance structure, we develop a guidance law that achieves an impact angle interception with the field-of-view constraint. Herein, as the entire guidance structure is derived based on exact kinematics without any approximation, the proposed law ensures the accurate impact angle interception for various engagement scenarios. This precise consideration of the engagement kinematics also accurately ensures the energy optimality of preventing the excessive use of control inputs when homing. To evaluate the performance of the proposed method, numerical simulations with various engagement scenarios are conducted, and the results demonstrate that the proposed law allows missiles to accurately intercept their targets with the desired impact angles and without violating the prescribed field-of-view constraint.

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5

Shim, Sang-Wook, Seong-Min Hong, Gun-Hee Moon, and Min-Jea Tahk. "Impact Angle and Time Control Guidance Under Field-of-View Constraints and Maneuver Limits." International Journal of Aeronautical and Space Sciences 19, no. 1 (March 2018): 217–26. http://dx.doi.org/10.1007/s42405-018-0004-8.

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6

Singh, Swati, Shashi Ranjan Kumar, and Dwaipayan Mukherjee. "Barrier Lyapunov Function based Impact Time Guidance with Field-of-View and Input Constraints." IFAC-PapersOnLine 55, no. 22 (2022): 412–17. http://dx.doi.org/10.1016/j.ifacol.2023.03.069.

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7

Zhang, Youan, Xingliang Wang, and Huali Wu. "Impact time control guidance law with field of view constraint." Aerospace Science and Technology 39 (December 2014): 361–69. http://dx.doi.org/10.1016/j.ast.2014.10.002.

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8

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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9

Guo, Jing, Jun Zhou, and Bin Zhao. "Three-dimensional integrated guidance and control for strap-down missiles considering seeker’s field-of-view angle constraint." Transactions of the Institute of Measurement and Control 42, no. 6 (November 13, 2019): 1097–109. http://dx.doi.org/10.1177/0142331219883719.

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This paper investigates a novel three-dimensional (3D) integrated guidance and control (IGC) method for skid-to-turn (STT) missiles with strap-down seeker. Firstly, a nonlinear IGC model considering seeker’s field-of-view (FOV) constraint is built by employing the strap-down decoupling model, based on which the strict feedback state equation with matched and unmatched uncertainties is derived. Secondly, to handle the FOV angle and the roll angle constraints, an IGC law is proposed by combining dynamic surface control (DSC) approach with integral barrier Lyapunov function (iBLF), by which an adaptive law is employed to estimate the square of the disturbance bound. Finally, the uniform ultimately boundedness of the closed-loop system is proved strictly based on the Lyapunov stability theory, and the effectiveness and robustness of the proposed IGC scheme are illustrated with numerical simulations.

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10

Hu, Qinglei, Tuo Han, and Ming Xin. "Analytical Solution for Nonlinear Three-Dimensional Guidance With Impact Angle and Field-of-View Constraints." IEEE Transactions on Industrial Electronics 68, no. 4 (April 2021): 3423–33. http://dx.doi.org/10.1109/tie.2020.2982114.

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11

Zhao, Junmin, Cong Nie, Guannan Chang, Meibo Lyu, and Xinguo Li. "Study on project trajectory of air-to-ground missile with strapdown seeker under multi constraints." Xibei Gongye Daxue Xuebao/Journal of Northwestern Polytechnical University 39, no. 1 (February 2021): 141–47. http://dx.doi.org/10.1051/jnwpu/20213910141.

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The air-to-ground missile with strapdown seeker may have the problems, including small field of view(FOV), limited overload, and fall angle constraint. To solve the above mentioned problem, a phased guidance scheme is proposed. In this scheme, the attack trajectory is divided into the following six stages, including glided stage, fall angle constraint stage, target acquisition and adjustment stage, terminal guidance stage and blind zone stage. The glided stage is designed to increase range, the terminal fall angle is attained ahead of time at fall angle constraint stage. The aim of target acquisition and adjustment stage is to adjust the missile attitude, so that the target will fall within the FOV of the seeker. It creates good condition to capture the target for strapdown seeker. In the terminal stage, the guidance law of proportional navigation and attitude track are used to fit the needs of FOV constraint and attack accuracy. The simulation result shows that the project trajectory can solve the application of attacking moving targets for air-to-ground missile with strapdown seeker under multi constraints.

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12

Zhou, Guanqun, and Qunli Xia. "A Guidance Strategy for Strapdown Seeker considering Minimum Field-of-View Angle Constraint." International Journal of Aerospace Engineering 2020 (June 19, 2020): 1–11. http://dx.doi.org/10.1155/2020/5247257.

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An off-axis strapdown seeker in missile may lead to a minimum field-of-view (FOV) angle constraint problem. The goal of this paper is to deal with the problem in guidance. Analysis of kinematics proves that on the premise of attacking stationary target, seeker look angle comes to 0 before or at the end time, and seeker will lose target finally. In order to reduce the distance of seeker losing target, a guidance strategy is proposed to sustain minimum FOV angle constraint during flight. The strategy can be applied on guidance laws with independent orders in longitudinal and lateral channels. By means of a certain rolling maneuver, it keeps the target in the seeker’s limited FOV. Moreover, a lateral guidance order compensation is utilized in the strategy to maintain seeker look angle. Simulations and comparisons are conducted to demonstrate the strategy’s effectiveness. Results show that the guidance strategy can sustain minimum FOV angle constraint longer than classical guidance method.

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13

Ma, Shuai, Xugang Wang, and Zhongyuan Wang. "Field-of-View Constrained Impact Time Control Guidance via Time-Varying Sliding Mode Control." Aerospace 8, no. 9 (September 6, 2021): 251. http://dx.doi.org/10.3390/aerospace8090251.

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The problem of impact time control guidance with field-of-view constraint is addressed based on time-varying sliding mode control. The kinematic conditions that satisfy the impact time control with field-of-view constraint are defined, and then a novel time-varying sliding surface is constructed to achieve the defined conditions. The sliding surface contains two unknown coefficients: one is tuned to achieve the global sliding surface to satisfy the impact time constraint and zero miss distance, and the other is tuned to guarantee the field-of-view constraint. The guidance law is designed to ensure the realization of the global sliding mode. On this basis, the guidance law is modified to a closed-loop structure, and the maximum detection capability of the seeker is utilized to a greater extent. Under the proposed guidance law, neither the small angle assumption nor time-to-go estimation is needed. The guidance command is continuous and converges to 0 at the desired impact time. Simulation results demonstrate the effectiveness and superiority of the proposed guidance law.

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14

Chen, Yadong, Jianan Wang, Chunyan Wang, Jiayuan Shan, and Ming Xin. "Three-Dimensional Cooperative Homing Guidance Law with Field-of-View Constraint." Journal of Guidance, Control, and Dynamics 43, no. 2 (February 2020): 389–97. http://dx.doi.org/10.2514/1.g004681.

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15

Liu, Bojun, Mingshan Hou, Ying Yu, and Zhonghua Wu. "Three-dimensional impact angle control guidance with field-of-view constraint." Aerospace Science and Technology 105 (October 2020): 106014. http://dx.doi.org/10.1016/j.ast.2020.106014.

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16

Liu, Shuangxi, Binbin Yan, Tong Zhang, Pei Dai, and Jie Yan. "Guidance Law with Desired Impact Time and FOV Constrained for Antiship Missiles Based on Equivalent Sliding Mode Control." International Journal of Aerospace Engineering 2021 (September 24, 2021): 1–15. http://dx.doi.org/10.1155/2021/9923332.

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Impact time control guidance (ITCG) is an important approach to achieve saturation attack on targets. With the increasing complexity of warfare requirements for missiles, an ITCG with field-of-view (FOV) constrained for antiship missiles is proposed based on equivalent sliding mode control. Firstly, in view of the accuracy of the calculation of remaining impact time for guidance law, the large initial lead angle is taken into consideration in the estimation of remaining flying time in which there is no need for the assumption of small angle approximation. Besides, for the sake of promoting the practical application value of the proposed guidance law, FOV is considered so that it can satisfy the actual working performance of the seeker. Then, combined with the concept of predicted interception point (PIP), the proposed guidance law is applied to attack a moving target. Numerical analysis is carried out for different initial lead angles, various impact time, different methods of estimating remaining flying time, and cooperative attack conditions. Compared with proportion navigation guidance (PNG), the feasibility and effectiveness of the guidance law are verified. Simulation results demonstrate that the proposed guidance law can guarantee the constraints of both impact time and FOV effectively.

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17

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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18

Ramírez, Isaac Segovia, Pedro José Bernalte Sánchez, Mayorkinos Papaelias, and Fausto Pedro García Márquez. "Autonomous Underwater Vehicles and Field of View in Underwater Operations." Journal of Marine Science and Engineering 9, no. 3 (March 4, 2021): 277. http://dx.doi.org/10.3390/jmse9030277.

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Submarine inspections and surveys require underwater vehicles to operate in deep waters efficiently, safely and reliably. Autonomous Underwater Vehicles employing advanced navigation and control systems present several advantages. Robust control algorithms and novel improvements in positioning and navigation are needed to optimize underwater operations. This paper proposes a new general formulation of this problem together with a basic approach for the management of deep underwater operations. This approach considers the field of view and the operational requirements as a fundamental input in the development of the trajectory in the autonomous guidance system. The constraints and involved variables are also defined, providing more accurate modelling compared with traditional formulations of the positioning system. Different case studies are presented based on commercial underwater cameras/sonars, analysing the influence of the main variables in the measurement process to obtain optimal resolution results. The application of this approach in autonomous underwater operations ensures suitable data acquisition processes according to the payload installed onboard.

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19

Hu, Qinglei, Ruihao Cao, Tuo Han, and Ming Xin. "Field-of-view limited guidance with impact angle constraint and feasibility analysis." Aerospace Science and Technology 114 (July 2021): 106753. http://dx.doi.org/10.1016/j.ast.2021.106753.

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20

Yang, Zhe, Hui Wang, and Defu Lin. "Time-Varying Biased Proportional Guidance with Seeker’s Field-of-View Limit." International Journal of Aerospace Engineering 2016 (2016): 1–11. http://dx.doi.org/10.1155/2016/9272019.

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Traditional guidance laws with range-to-go information or time-to-go estimation may not be implemented in passive homing missiles since passive seekers cannot measure relative range directly. A time-varying biased proportional guidance law, which only uses line-of-sight (LOS) rate and look angle information, is proposed to satisfy both impact angle constraint and seeker’s field-of-view (FOV) limit. In the proposed guidance law, two time-varying bias terms are applied to divide the trajectory into initial phase and terminal phase. The initial bias is designed as a function of LOS rate and look angle to maintain the seeker’s lock-on while the final bias eliminates the deviation between the integral value of angle control bias and the expected bias amount. A switching logic is adopted to change the biases continuously so that there is no abrupt acceleration change during the engagement. Extensive simulations considering both kinematic and realistic missile models are performed to illustrate the efficiency of the proposed method.

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21

Chen, Xiaotian, and Jinzhi Wang. "Nonsingular Sliding-Mode Control for Field-of-View Constrained Impact Time Guidance." Journal of Guidance, Control, and Dynamics 41, no. 5 (May 2018): 1214–22. http://dx.doi.org/10.2514/1.g003146.

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22

Qi, Yongqiang, and Yingmin Jia. "Field-of-view constrained guidance algorithm for -V-bar constant thrust departure." Advances in Space Research 49, no. 7 (April 2012): 1129–39. http://dx.doi.org/10.1016/j.asr.2011.12.032.

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23

Yang, Zhe, Defu Lin, and Luyao Zang. "Impact Time Control Guidance Law Considering Seeker's Field-of-View Constraint Without Time-to-Go Information." Journal of Advanced Computational Intelligence and Intelligent Informatics 20, no. 3 (May 19, 2016): 412–17. http://dx.doi.org/10.20965/jaciii.2016.p0412.

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Accurate time-to-go estimation with large heading angle error is difficult for homing guidance laws, especially for the impact time control. Considering this, a new cooperative guidance law which requires no time-to-go estimation is investigated. First, the impact time control problem is transformed to the look angle command tracking problem. The look angle command guarantees that the range-to-go error converges to zero asymptotically. Then the proposed guidance law considering the seeker's field-of-view constraint is derived using sliding mode control to track the desired look angle signal. Numerical simulations are performed to verify the effectiveness of the proposed guidance law for one-to-one and many-to-one engagement scenarios.

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24

He, Shaoming, and Defu Lin. "A robust impact angle constraint guidance law with seeker’s field-of-view limit." Transactions of the Institute of Measurement and Control 37, no. 3 (June 23, 2014): 317–28. http://dx.doi.org/10.1177/0142331214538278.

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25

Liu, Bojun, Mingshan Hou, and Dan Feng. "Nonlinear mapping based impact angle control guidance with seeker's field-of-view constraint." Aerospace Science and Technology 86 (March 2019): 724–36. http://dx.doi.org/10.1016/j.ast.2019.02.009.

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26

Fu, Shengnan, Guanqun Zhou, and Qunli Xia. "A trajectory shaping guidance law with field-of-view angle constraint and terminal limits." Journal of Systems Engineering and Electronics 33, no. 2 (April 2022): 426–37. http://dx.doi.org/10.23919/jsee.2022.000043.

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27

Tian, Jiayi, Haifeng Chen, Xuancen Liu, Huabo Yang, and Shifeng Zhang. "Integrated Strapdown Missile Guidance and Control With Field-of-View Constraint and Actuator Saturation." IEEE Access 8 (2020): 123623–38. http://dx.doi.org/10.1109/access.2020.3006128.

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28

Wen, Qiuqiu, Qunli Xia, and Su Weixia. "A parameter design strategy for seeker’s field-of-view constraint in impact angle guidance." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 229, no. 13 (March 13, 2015): 2389–96. http://dx.doi.org/10.1177/0954410015576237.

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29

Zhang, Youan, Xingliang Wang, and Huali Wu. "Impact time control guidance with field-of-view constraint accounting for uncertain system lag." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 230, no. 3 (July 22, 2015): 515–29. http://dx.doi.org/10.1177/0954410015594401.

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30

Han, Tuo, Qinglei Hu, and Ming Xin. "Analytical solution of field-of-view limited guidance with constrained impact and capturability analysis." Aerospace Science and Technology 97 (February 2020): 105586. http://dx.doi.org/10.1016/j.ast.2019.105586.

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31

Yang, Linghui, Yuanlin Pan, Jiarui Lin, Yang Liu, Yue Shang, Shuo Yang, and Hanwen Cao. "Automatic Guidance Method for Laser Tracker Based on Rotary-Laser Scanning Angle Measurement." Sensors 20, no. 15 (July 27, 2020): 4168. http://dx.doi.org/10.3390/s20154168.

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Laser-tracking measurement systems (laser tracker) have been playing a critical role in large-scale 3D high-precision coordinate measurement. However, the existing visual guidance of laser trackers is still limited by the disadvantages of operator-dependence, small-angle view field, time-consuming laser-guided process. This paper presents an automatic guidance method for laser trackers based on the rotary-laser scanning angle measurement technology. In this method, a special target consisting of six photoelectric receivers and a retroreflector is integrated into the rotary-laser scanning transmitter’ coordinate systems. Real-time constraints calculated by the proposed method would provide the coordinates of the target in a laser tracker coordinates system for guidance. Finally, the experimental results verified the automatic re-establish of sightline can be realized in horizontal 360° angle field within tens of arc-seconds, and this method is robust against the fast movement of the target.

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32

Ni, Dejing, AYC Nee, SK Ong, Huijun Li, Chengcheng Zhu, and Aiguo Song. "Point cloud augmented virtual reality environment with haptic constraints for teleoperation." Transactions of the Institute of Measurement and Control 40, no. 15 (February 14, 2018): 4091–104. http://dx.doi.org/10.1177/0142331217739953.

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Remote manipulation of a robot without assistance in an unstructured environment is a challenging task for operators. In this paper, a novel methodology for haptic constraints in a point cloud augmented virtual reality environment is proposed to address this human operation limitation. The proposed method generates haptic constraints in real time for an unstructured environment, including regional constraints and guidance constraints. A modified implicit surface method is applied for regional constraint generation for the entire point cloud. Additionally, the isosurface derived from the implicit surface is proposed for real-time three-dimensional artificial force field estimation. For guidance constraint generation, a new incremental prediction and local artificial force field generation method based on the modified sigmoid model is proposed in an unstructured point cloud virtual reality environment. With the generated haptic constraints, the operator can control the robot to realize obstacle avoidance and easily reach the target tasks. System evaluation is conducted, and the result demonstrates the effectiveness of the proposed method. In addition, a 10-participant study with users who control the robot to three specific targets shows that the system can enhance human operation efficiency and reduce time costs by at least 59% compared with no-haptic-constraint operations. Additionally, the designed questionnaire also demonstrates that the proposed methodology can reduce the workload during human operations.

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33

Kim, Hyeong-Geun, and H. Jin Kim. "Field-of-View Constrained Guidance Law for a Maneuvering Target With Impact Angle Control." IEEE Transactions on Aerospace and Electronic Systems 56, no. 6 (December 2020): 4974–83. http://dx.doi.org/10.1109/taes.2020.2996306.

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34

Surve, Prajakta, Arnab Maity, and Shashi Ranjan Kumar. "Polynomial Shaping-based Field-of-View Constrained Impact Time Guidance against Non-maneuvering Targets." IFAC-PapersOnLine 55, no. 22 (2022): 406–11. http://dx.doi.org/10.1016/j.ifacol.2023.03.068.

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35

Wang, Xingliang, Youan Zhang, and Huali Wu. "Sliding mode control based impact angle control guidance considering the seeker׳s field-of-view constraint." ISA Transactions 61 (March 2016): 49–59. http://dx.doi.org/10.1016/j.isatra.2015.12.018.

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36

Song, Jia, Xiaowei Xu, Xindi Tong, and Kai Zhao. "A Time Cooperation Guidance for Multi-Hypersonic Vehicles Based on LSTM Network and Improved Artificial Potential Field Method." Aerospace 9, no. 10 (September 28, 2022): 562. http://dx.doi.org/10.3390/aerospace9100562.

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Time cooperation guidance is a key technology which can greatly increase the success rate of flight missions. However, it is difficult to satisfy all the strict constraints when designing the guidance system for multiple hypersonic vehicles. To solve these problems, a time cooperation framework is proposed. In this paper, the longitudinal predictor–corrector guidance law is firstly applied to meet the terminal and path constraints simultaneously. To settle the inaccurate estimation problem of residual flight time, a long short-term memory network (LSTM network) is trained and adopted in a time decision module, whose inputs are selected as six-dimensional feature vectors combined with the features of the sequential ballistics. In the time control module, the traditional artificial potential field method is modified to handle the no-fly zone constraints problem. Furthermore, the time potential field as a new type of potential field is added to indirectly control the flight time of hypersonic vehicles. The final simulation results show that the novel time potential field is compatible with the traditional potential field, which can satisfy the no-fly zone and flight time constraints at the same time. Meanwhile, compared with other time cooperative guidance, the algorithm proposed in this paper performs better in terms of time adjustable range.

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37

Liu, Bojun, Mingshan Hou, and Yajun Li. "Field-of-View and Impact Angle Constrained Guidance Law for Missiles With Time-Varying Velocities." IEEE Access 7 (2019): 61717–27. http://dx.doi.org/10.1109/access.2019.2916798.

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38

Singh, Netra, and Manoranjan Sinha. "Suboptimal Guidance and Control Design for a Missile with Onboard Strapdown Seeker." Applied Mechanics and Materials 110-116 (October 2011): 2513–20. http://dx.doi.org/10.4028/www.scientific.net/amm.110-116.2513.

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Dynamic inversion control in conjunction with nonlinear suboptimal three dimensional (3-D) guidance law, in terminal phase, is implemented in both the pitch and yaw plane for a short range surface to surface missile with onboard active strapdown seeker. The implemented guidance and control laws intercept the target with a minimum miss distance in addition to meeting the various constraints such as line of sight, seeker field-of-view (FOV), and impact angle. This is achieved using approximate solution to Hamilton-Jacobi-Bellman (HJB) equation [1]. Dynamic inversion control is implemented in two time scales for the inner loop body rate and outer loop angles. Various nonlinearities including that due to the coupling effect between pitch and yaw channels are accounted for in the six-degree-of-freedom (6-DOF) formulation.

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Mokrane, Adel, Abdelaziz Benallegue, Amal Choukchou-Braham, Abdelhafid El Hadri, and Brahim Cherki. "Guidance, Navigation and Control for Autonomous Quadrotor Flight in an Agricultural Field: The Case of Vineyards." Sensors 22, no. 22 (November 16, 2022): 8865. http://dx.doi.org/10.3390/s22228865.

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In this paper, we present a complete and efficient solution of guidance, navigation and control for a quadrotor platform to accomplish 3D coverage flight missions in mapped vineyard terrains. Firstly, an occupancy grid map of the terrain is used to generate a safe guiding coverage path using an Iterative Structured Orientation planning algorithm. Secondly, way-points are extracted from the generated path and added to them trajectory’s velocities and accelerations constraints. The constrained way-points are fed into a Linear Quadratic Regulator algorithm so as to generate global minimum snap optimal trajectory while satisfying both the pointing and the corridor constraints. Then, when facing unexpected obstacles, the quadrotor tends to re-plan its path in real-time locally using an Improved Artificial Potential Field algorithm. Finally, a geometric trajectory tracking controller is developed on the Special Euclidean group SE(3). The aim of this controller is to track the generated trajectory while pointing towards predetermined direction using the vector measurements provided by the inertial unit. The performance of the proposed method is demonstrated through several simulation results. In particular, safe guiding paths are achieved. Obstacle-free optimal trajectories that satisfy the way-point position, the pointing direction, and the corridor constraints, are successfully generated with optimized platform snap. Besides, the implemented geometric controller can achieve higher trajectory tracking accuracy with an absolute value of the maximum error in the order of 10−3 m.

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Hirwani, Vijay, and Ashwini Ratnoo. "Field-of-view Constrained Polynomial Guidance Law for Interception of Moving Target using Dual-Seeker Interceptors." IFAC-PapersOnLine 51, no. 1 (2018): 377–82. http://dx.doi.org/10.1016/j.ifacol.2018.05.054.

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Lee, Seokwon, Namhoon Cho, and Youdan Kim. "Impact-Time-Control Guidance Strategy with a Composite Structure Considering the Seeker’s Field-of-View Constraint." Journal of Guidance, Control, and Dynamics 43, no. 8 (August 2020): 1566–74. http://dx.doi.org/10.2514/1.g005063.

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Kim, Hyeong-Geun, Jun-Yong Lee, Hyoun Jin Kim, Hyuck-Hoon Kwon, and Jang-Seong Park. "Look-Angle-Shaping Guidance Law for Impact Angle and Time Control With Field-of-View Constraint." IEEE Transactions on Aerospace and Electronic Systems 56, no. 2 (April 2020): 1602–12. http://dx.doi.org/10.1109/taes.2019.2924175.

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M. Johnson, Christa. "The Intrapersonal Paradox of Deontology." Journal of Moral Philosophy 16, no. 3 (June 12, 2019): 279–301. http://dx.doi.org/10.1163/17455243-20182527.

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In response to the so-called “paradox of deontology,” many have argued that the agent-relativity of deontological constraints accounts for why an agent may not kill one in order to prevent five others from being killed. Constraints provide reasons for particular agents not to kill, not reasons to minimize overall killings. In this paper, I tease out the significance of an underappreciated aspect of this agent-relative position, i.e. it provides no guidance as to what an agent ought to do when faced with the prospect of killing one in order to prevent herself from killing five. After rejecting mere agent-relativity, the view that agents are morally permitted to violate constraints in order to minimize their overall violations, I offer a view that this is both agent- and time-relative, and show how this view exemplifies the underlying motivations for deontological constraints while successfully responding to both the inter- and intra-personal paradoxes of deontology.

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Li, Zhibing, Quanlin Dong, Xiaoyue Zhang, Huanrui Zhang, and Feng Zhang. "Field-To-View Constrained Integrated Guidance and Control for Hypersonic Homing Missiles Intercepting Supersonic Maneuvering Targets." Aerospace 9, no. 11 (October 24, 2022): 640. http://dx.doi.org/10.3390/aerospace9110640.

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An integrated guidance and control (IGC) scheme considering the field-of-view (FOV) constraint is proposed in this paper for hypersonic skid-to-turn (STT) missiles with a strapdown seeker intercepting a high-speed maneuvering target, which is based on the backstepping control (BC), barrier Lyapunov function (BLF), sliding mode control (SMC), dynamic surface control (DSC), and reduced-order extended state observer (ESO). First, a fifth-order strict feedback IGC model considering the rudder delay dynamics is derived, which also considers the drag effect on the axial velocity. Second, the missile guidance control system based on the BC consists of seeker, guidance, angle-of-attack, attitude, and rudder subsystems. The seeker subsystem was designed based on the BLF, and the other four subsystems were designed based on the SMC. The system-lumped disturbances, including unknown target maneuvers, unmodeled parts, perturbations caused by aerodynamic parameter variations, and external disturbances, were estimated and compensated for using the reduced-order ESO. The DSC prevented the “differential explosion” caused by virtual control commands introduced by the BC. Subsequently, the stability of the closed-loop system was strictly proven using the Lyapunov theory, and the boundedness of the FOV angle was strictly derived. Finally, the simulation results demonstrated the effectiveness and robustness of the proposed IGC scheme.

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Wang, Tianning, Shengjing Tang, Jie Guo, and Haoqiang Zhang. "Two-Phase Optimal Guidance Law considering Impact Angle Constraint with Bearings-Only Measurements." International Journal of Aerospace Engineering 2017 (2017): 1–12. http://dx.doi.org/10.1155/2017/1380531.

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The implementation of advanced guidance laws with bearings-only measurements requires estimation of the range information. To improve estimation accuracy and satisfy the impact angle constraint, this paper proposes a two-phase optimal guidance law consisting of an observing phase and an attacking phase. In the observing phase, the determinant of Fisher information matrix is maximized to achieve the optimal observability and a suboptimal solution expressed by leading angle is derived analytically. Then, a terminal sliding-mode guidance law is designed to track the desired leading angle. In the followed attacking phase, an optimal guidance law is integrated with a switching term to satisfy both the impact angle constraint and the field-of-view constraint. Finally, comparison studies of the proposed guidance law and a traditional optimal guidance law are conducted on stationary targets and maneuvering targets cases. Simulation results demonstrate that the proposed guidance law is able to improve the range observability and achieve better terminal performances including impact angle accuracy and miss distance.

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Ku, Ching-Heng, and Wen-Hsiang Tsai. "Robust Trajectory Planning for Target Following Vision-based Autonomous Land Vehicle Guidance." Journal of Navigation 57, no. 1 (January 2004): 103–16. http://dx.doi.org/10.1017/s0373463303002509.

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We propose a robust trajectory planning method for vision-based autonomous land vehicle (ALV) guidance by target following using a visual field model. The proposed trajectory planning method aims to guide the ALV to achieve the goal that the targeted person will always appear in the image. It is found in this study that the goal can be achieved if three visual contact constraints in the visual field model are satisfied. The first constraint postulates that the target has appeared in the image. The second constraint asks that the vehicle head at the next position points straight towards to the target's current position. The third constraint sets bounds between the next position of the ALV and the current position of the target. A formula for the trajectory of the vehicle that satisfies the second visual contact constraint is derived. The steps for generating a speed and a turn angle of the ALV for real-time navigation are described as a trajectory-planning algorithm. Finally, the approach is tested on a real ALV and successful navigation sessions confirm the feasibility and the robustness of the approach.

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Lee, Seokwon, Namhoon Cho, and Youdan Kim. "Correction: Impact-Time-Control Guidance Strategy with a Composite Structure Considering the Seeker’s Field-of-View Constraint." Journal of Guidance, Control, and Dynamics 43, no. 10 (October 2020): 1983. http://dx.doi.org/10.2514/1.g005063.c1.

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Tian, Jiayi, Xibin Bai, Huabo Yang, and Shifeng Zhang. "Time-Varying Asymmetric Barrier Lyapunov Function-Based Impact Angle Control Guidance Law With Field-of-View Constraint." IEEE Access 8 (2020): 185346–59. http://dx.doi.org/10.1109/access.2020.3030158.

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Zhou, Shou, Cheng Hu, Pan Wu, and Shifeng Zhang. "Impact Angle Control Guidance Law Considering the Seeker’s Field-of-View Constraint Applied to Variable Speed Missiles." IEEE Access 8 (2020): 100608–19. http://dx.doi.org/10.1109/access.2020.2997805.

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Zhou, Shou, Shifeng Zhang, and Donghui Wang. "Impact Angle Control Guidance Law With Seeker’s Field-of-View Constraint Based on Logarithm Barrier Lyapunov Function." IEEE Access 8 (2020): 68268–79. http://dx.doi.org/10.1109/access.2020.2986355.

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