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Primary Assumptions and Guidance Laws in Wave Mechanics
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作者 Adriano Orefice Raffaele Giovanelli Domenico Ditto 《Journal of Applied Mathematics and Physics》 2018年第12期2621-2634,共14页
In an article written by Louis de Broglie in 1959 (30 years after the Nobel prize rewarding his foundation of Wave Mechanics), the most challenging problem raised by the Bohr, Heisenberg and Born Standard Quantum Mech... In an article written by Louis de Broglie in 1959 (30 years after the Nobel prize rewarding his foundation of Wave Mechanics), the most challenging problem raised by the Bohr, Heisenberg and Born Standard Quantum Mechanics (SQM) was pointed out in the renunciation to describe “a permanent localization in space, and therefore a well-defined trajectory” for any moving particle. This challenge is taken up in the present paper, showing that de Broglie’s Primary Assumption p=hk, predicting the wave-particle duality, does also allow to obtain from the energy-dependent form of the Schr&#246;dinger and/or Klein-Gordon equations the Guidance Laws piloting particles along well-defined trajectories. The energy-independent equations, on the other hand, may only give rise—both in SQM and in the Bohmian approach—to probabilistic descriptions, overshadowing the role of de Broglie’s matter waves in physical space. 展开更多
关键词 Helmholtz Equation Wave Potential Hamilton-Jacobi Equations Wave Mechanics de Broglie’s Duality Matter Waves guidance laws Schrodinger Equations Klein-Gordon Equations
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Current status and prospects of terminal guidance laws for intercepting hypersonic vehicles in near space:a review 被引量:3
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作者 Shuangxi LIU Binbin YAN +2 位作者 Wei HUANG Xu ZHANG Jie YAN 《Journal of Zhejiang University-Science A(Applied Physics & Engineering)》 SCIE EI CAS CSCD 2023年第5期387-403,共17页
The unique performance advantages of hypersonic vehicles represent a critical challenge for existing defense systems.To facilitate defensive operations against hypersonic vehicles in near space,this paper systematical... The unique performance advantages of hypersonic vehicles represent a critical challenge for existing defense systems.To facilitate defensive operations against hypersonic vehicles in near space,this paper systematically discusses both the advantages of these vehicles and the difficulties in intercepting them.Focusing on the state-of-the-art terminal guidance laws for intercepting hypersonic vehicles in near space,we examine research progress in the area of single-and multi-interceptor cooperative guidance laws and summarize their advantages and disadvantages.We also highlight future research directions for developing an effective terminal guidance law for multi-interceptor cooperative interception of hypersonic vehicles,based on four aspects:the information domain,space domain,physical domain,and effect-cost ratio.The findings provide a reference for further research into near-space interceptor terminal guidance technologies. 展开更多
关键词 Hypersonic vehicles guidance law Cooperative guidance Near space
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Closed-form guidance law for velocity maximization with impact angle constraint
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作者 ZHANG Jiahui WEN Qiuqiu 《Journal of Systems Engineering and Electronics》 SCIE CSCD 2024年第5期1295-1303,共9页
Final velocity and impact angle are critical to missile guidance.Computationally efficient guidance law with compre-hensive consideration of the two performance merits is challeng-ing yet remains less addressed.Theref... Final velocity and impact angle are critical to missile guidance.Computationally efficient guidance law with compre-hensive consideration of the two performance merits is challeng-ing yet remains less addressed.Therefore,this paper seeks to solve a type of optimal control problem that maximizes final velocity subject to equality point constraint of impact angle con-straint.It is proved that the crude problem of maximizing final velocity is equivalent to minimizing a quadratic-form cost of cur-vature.The closed-form guidance law is henceforth derived using optimal control theory.The derived analytical guidance law coincides with the widely-used optimal guidance law with impact angle constraint(OGL-IAC)with a set of navigation parameters of two and six.On this basis,the optimal emission angle is determined to further increase the final velocity.The derived optimal value depends solely on the initial line-of-sight angle and impact angle constraint,and thus practical for real-world appli-cations.The proposed guidance law is validated by numerical simulation.The results show that the OGL-IAC is superior to the benchmark guidance laws both in terms of final velocity and missing distance. 展开更多
关键词 MISSILE guidance law proportional-navigation guidance impact angle
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Computational intelligence interception guidance law using online off-policy integral reinforcement learning
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作者 WANG Qi LIAO Zhizhong 《Journal of Systems Engineering and Electronics》 SCIE CSCD 2024年第4期1042-1052,共11页
Missile interception problem can be regarded as a two-person zero-sum differential games problem,which depends on the solution of Hamilton-Jacobi-Isaacs(HJI)equa-tion.It has been proved impossible to obtain a closed-f... Missile interception problem can be regarded as a two-person zero-sum differential games problem,which depends on the solution of Hamilton-Jacobi-Isaacs(HJI)equa-tion.It has been proved impossible to obtain a closed-form solu-tion due to the nonlinearity of HJI equation,and many iterative algorithms are proposed to solve the HJI equation.Simultane-ous policy updating algorithm(SPUA)is an effective algorithm for solving HJI equation,but it is an on-policy integral reinforce-ment learning(IRL).For online implementation of SPUA,the dis-turbance signals need to be adjustable,which is unrealistic.In this paper,an off-policy IRL algorithm based on SPUA is pro-posed without making use of any knowledge of the systems dynamics.Then,a neural-network based online adaptive critic implementation scheme of the off-policy IRL algorithm is pre-sented.Based on the online off-policy IRL method,a computa-tional intelligence interception guidance(CIIG)law is developed for intercepting high-maneuvering target.As a model-free method,intercepting targets can be achieved through measur-ing system data online.The effectiveness of the CIIG is verified through two missile and target engagement scenarios. 展开更多
关键词 two-person zero-sum differential games Hamilton–Jacobi–Isaacs(HJI)equation off-policy integral reinforcement learning(IRL) online learning computational intelligence inter-ception guidance(CIIG)law
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Design and Analysis of Terminal Guidance Law for Kinetic Interceptors based on Pulse Engine
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作者 Shixin Li Jia Ma Shuai Yue 《Journal of Electronic Research and Application》 2024年第5期95-108,共14页
A new terminal guidance law is proposed based on a solid propellant pulse engine and an improved proportional navigation method to address the terminal guidance issue for kinetic interceptors.On this basis,the start-s... A new terminal guidance law is proposed based on a solid propellant pulse engine and an improved proportional navigation method to address the terminal guidance issue for kinetic interceptors.On this basis,the start-stop curve of the pulse motor during the terminal guidance process is designed,along with its start-up logic.The effectiveness of the proposed guidance strategy is verified through simulation. 展开更多
关键词 Pulse engine Terminal guidance law Kinetic interceptor Proportional navigation method
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Three-dimensional pursuer convoy by using guidance laws 被引量:1
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作者 Shulin FENG Wei WANG Huanshui ZHANG 《控制理论与应用(英文版)》 EI CSCD 2013年第3期442-453,共12页
This paper investigates the problem of modeling and controlling pursuer convoy in three-dimensional space. The guidance laws applied for convoy, the velocity pursuit, the deviated pursuit and the proportional navigati... This paper investigates the problem of modeling and controlling pursuer convoy in three-dimensional space. The guidance laws applied for convoy, the velocity pursuit, the deviated pursuit and the proportional navigation, steer the pursuer using the rate of line-of-sight (LOS) between successive pursuers. On the basis of the differential equations for the range, the pitch angle of LOS and the yaw angle of LOS between successive pursuers, the guidance laws are proposed to derive decentralized control strategy for pursuer convoy. The results concerning the pursuer convoy are rigorously proven. Simulations are conducted to demonstrate the feasibility and effectiveness of the proposed control strategy. 展开更多
关键词 Pursuer convoy Three-dimensional space guidance laws LOS
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The stochastic sliding mode variable structure guidance laws based on optimal control theory 被引量:7
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作者 Hongqiang WANG Daiqiang CAO Xudong WANG 《控制理论与应用(英文版)》 EI CSCD 2013年第1期86-91,共6页
A stochastic sliding-mode variable structure guidance law involving optimal control theory is presented for the missile target intercept model, in which state noise, uncertain system parameters, target movement and me... A stochastic sliding-mode variable structure guidance law involving optimal control theory is presented for the missile target intercept model, in which state noise, uncertain system parameters, target movement and measured noise are considered. This guidance law synthesizes the merits of optimal guidance law with line-of-sight rate convergence and sliding-mode guidance law with strong robustness. Through theoretic analysis, it is proved that the sliding mode hyperplane is sub-achievable in the closed loop system. The numerical results show the effectiveness of the proposed control algorithm. 展开更多
关键词 Stochastic system Variable structure control Optimal control guidance law ROBUST
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Three-dimensional Large Landing Angle Guidance Based on Two-dimensional Guidance Laws 被引量:3
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作者 DOU Lei DOU Jiao 《Chinese Journal of Aeronautics》 SCIE EI CAS CSCD 2011年第6期756-761,共6页
Both the design process and form of the three-dimensional (3D) suboptimal guidance law (3DSGL) are very complex. Therefore, we propose the use of two-dimensional (2D) guidance laws to meet the guidance requireme... Both the design process and form of the three-dimensional (3D) suboptimal guidance law (3DSGL) are very complex. Therefore, we propose the use of two-dimensional (2D) guidance laws to meet the guidance requirements of 3D space. By analyzing the relationship between the flight-path angle and its projections on OXY and OXZ planes, we obtain the ideal design requirements of the guidance laws. Based on the requirements, we design a 2D suboptimal guidance law used in the horizontal plane; combining the 2D vertical suboptimal guidance law, we create a whole ballistic simulation of six degree-of-freedom. The results are compared with those using other three guidance modes in the case of large windage of the initial azimuth angle. When the proportional navigation guidance (PNG) law is used in the horizontal planes, the landing angle will obviously decrease. With the proposed guidance mode, the large landing angle can be realized and meet the guidance precision requirements. Moreover, the required overload can decrease to meet the control requirement. The effects of the proposed guidance mode are close to that of 3DSGL despite its very simple form. 展开更多
关键词 optimal control guidance law THREE-DIMENSIONAL MULTI-CONSTRAINTS landing angle satellite-guided
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Guidance Laws Based on H_∞ Observer Considering Measurement Noises
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作者 LIAO Fei JI Haibo 《Journal of Systems Science & Complexity》 SCIE EI CSCD 2016年第3期642-656,共15页
Since in practice the line-of-sight(LOS)rate is difficult for a pursuer to measure accurately,the robust nonlinear H∞observer is applied to estimate it using LOS azimuths without any priori information of target mane... Since in practice the line-of-sight(LOS)rate is difficult for a pursuer to measure accurately,the robust nonlinear H∞observer is applied to estimate it using LOS azimuths without any priori information of target maneuvers or its estimate in the presence of measurement noise.A threedimensional guidance law is implemented by replacing the LOS rate with their estimates using only relative range,speed,and LOS azimuths.The stability analyses and performed simulations results show that the presented approach is effective. 展开更多
关键词 guidance law H∞ observer measurement noise.
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EVOLUTIONARY FUZZY GUIDANCE LAW WITH SELF-ADAPTIVE REGION 被引量:3
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作者 邹庆元 姜长生 吴柢 《Transactions of Nanjing University of Aeronautics and Astronautics》 EI 2004年第3期234-240,共7页
Effective guidance is one of the most important tasks to the performance of air-to-air missile. The fuzzy logic controller is able to perform effectively even in situations where the information about the plant is ina... Effective guidance is one of the most important tasks to the performance of air-to-air missile. The fuzzy logic controller is able to perform effectively even in situations where the information about the plant is inaccurate and the operating conditions are uncertain. Based on the proportional navigation, the fuzzy logic and the genetic algorithm are combined to develop an evolutionary fuzzy navigation law with self-adapt region for the air-to-air missile guidance. The line of sight (LOS) rate and the closing speed between the missile and the target are inputs of the fuzzy controller. The output of the fuzzy controller is the commanded acceleration. Then a nonlinear function based on the conventional fuzzy logic control is imported to change the region. This nonlinear function can be changed with the input variables. So the dynamic change of the fuzzy variable region is achieved. The guidance law is optimized by the genetic algorithm. Simulation results of air-to-air missile attack using MATLAB show that the method needs less acceleration and shorter flying time, and its realization is simple.[KH*3/4D] 展开更多
关键词 guidance law fuzzy logic genetic algorithm self-adaptive region
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Head Pursuit Variable Structure Guidance Law for Three-dimensional Space Interception 被引量:10
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作者 葛连正 沈毅 +1 位作者 高云峰 赵立军 《Chinese Journal of Aeronautics》 SCIE EI CAS CSCD 2008年第3期247-251,共5页
This article aims to develop a head pursuit (HP) guidance law for three-dimensional hypervelocity interception, so that the effect of the perturbation induced by seeker detection can be reduced. On the basis of a no... This article aims to develop a head pursuit (HP) guidance law for three-dimensional hypervelocity interception, so that the effect of the perturbation induced by seeker detection can be reduced. On the basis of a novel HP three-dimensional guidance model, a nonlinear variable structure guidance law is presented by using Lyapunov stability theory. The guidance law positions the interceptor ahead of the target on its tlight trajectory, and the speed of the interceptor is required to be lower than that of the target, A numerical example of maneuvering ballistic target interception verifies the rightness of the guidance model and the effectiveness of the proposed method. 展开更多
关键词 head pursuit three-dimensional guidance model nonlinear variable structure Lyapunov stability theory guidance law
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Variable structure guidance law for attacking surface maneuver targets 被引量:16
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作者 Han Yanhua Xu Bo 《Journal of Systems Engineering and Electronics》 SCIE EI CSCD 2008年第2期337-341,共5页
The characteristics of surface maneuver targets are analyzed and a 3-D relative motion model for missiles and targets is established. A variable structure guidance law is designed considering the characteristics of ta... The characteristics of surface maneuver targets are analyzed and a 3-D relative motion model for missiles and targets is established. A variable structure guidance law is designed considering the characteristics of targets. In the guidance law, the distance between missiles and targets as well as the missile-target relative velocity are all substituted by estimation values. The estimation errors, the target's velocity, and the maneuver acceleration are all treated as bounded disturbance. The guidance law proposed can be implemented conveniently in engineering with little target information. The performance of the guidance system is analyzed theoretically and the numerical simulation result shows the effectiveness of the guidance law. 展开更多
关键词 air-to-surface missile guidance law variable structure control surface maneuver target.
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Extended optimal guidance law with impact angle and acceleration constriants 被引量:8
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作者 Ran Li Qunli Xia Qiuqiu Wen 《Journal of Systems Engineering and Electronics》 SCIE EI CSCD 2014年第5期868-876,共9页
The extended optima straints of miss distance and Schwartz inequality. To reduce guidance law with terminal conmpact angle is derived by the terminal acceleration and eliminate gravity disturbance absolutely, the obje... The extended optima straints of miss distance and Schwartz inequality. To reduce guidance law with terminal conmpact angle is derived by the terminal acceleration and eliminate gravity disturbance absolutely, the object function, which designs the weight of control command to be the power function of time-to-go's reciprocal, is given. And the gravity is considered when building the state equation. Based on the parsing express of the guidance command change with varying time and adjoint system analysis method, the command characteristics and the non-dimensional miss distance of the guidance law are analyzed, a design principle of guidance order coefficients is discussed. Finally, based on the requirement of engineering, the method to calculate the guidance condition and maximal required acceleration of the guidance law is given. The simulation demonstrates that not only the guidance law can satisfy the terminal position and impact angle constraints, but also the terminal acceleration can be converged toward zero, which will support a good situation for the terminal angle of attacking control. 展开更多
关键词 impact angle constraint optimal guidance law accel- eration command guidance order.
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Impact angle control over composite guidance law based on feedback linearization and finite time control 被引量:7
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作者 ZHANG Xiaojian LIU Mingyong +1 位作者 LI Yang ZHANG Feihu 《Journal of Systems Engineering and Electronics》 SCIE EI CSCD 2018年第5期1036-1045,共10页
The impact angle control over guidance(IACG) law against stationary targets is proposed by using feedback linearization control(FLC) and finite time control(FTC). First, this paper transforms the kinematics equation o... The impact angle control over guidance(IACG) law against stationary targets is proposed by using feedback linearization control(FLC) and finite time control(FTC). First, this paper transforms the kinematics equation of guidance systems into the feedbackable linearization model, in which the guidance law is obtained without considering the impact angle via FLC. For the purpose of the line of sight(LOS) angle and its rate converging to the desired values, the second-order LOS angle is considered as a double-integral system. Then, this paper utilizes FTC to design a controller which can guarantee the states of the double-integral system converging to the desired values. Numerical simulation illustrates the performance of the IACG, in contrast to the existing guidance law. 展开更多
关键词 guidance law impact angle feedback linearization finite time control global stabilization
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Three-dimensional impact angle constrained distributed cooperative guidance law for anti-ship missiles 被引量:7
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作者 LI Wei WEN Qiuqiu +1 位作者 HE Lei XIA Qunli 《Journal of Systems Engineering and Electronics》 SCIE EI CSCD 2021年第2期447-459,共13页
This paper investigates the problem of distributed cooperative guidance law design for multiple anti-ship missiles in the three-dimensional(3-D)space hitting simultaneously the same target with considering the desired... This paper investigates the problem of distributed cooperative guidance law design for multiple anti-ship missiles in the three-dimensional(3-D)space hitting simultaneously the same target with considering the desired terminal impact angle constraint.To address this issue,the problem formulation including 3-D nonlinear mathematical model description,and communication topology are built firstly.Then the consensus variable is constructed using the available information and can reach consensus under the proposed acceleration command along the line-of-sight(LOS)which satisfies the impact time constraint.However,the normal accelerations are designed to guarantee the convergence of the LOS angular rate.Furthermore,consider the terminal impact angle constraints,a nonsingular terminal sliding mode(NTSM)control is introduced,and a finite time convergent control law of normal acceleration is proposed.The convergence of the proposed guidance law is proved by using the second Lyapunov stability method,and numerical simulations are also conducted to verify its effectiveness.The results indicate that the proposed cooperative guidance law can regulate the impact time error and impact angle error in finite time if the connecting time of the communication topology is longer than the required convergent time. 展开更多
关键词 distributed cooperative guidance law impact angle constraint communication topology nonsingular terminal sliding mode(NTSM)control finite time convergent
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Adaptive weighting impact angle optimal guidance law considering seeker's FOV angle constraints 被引量:7
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作者 LI Ran WEN Qiuqiu +1 位作者 TAN Wangchun ZHANG Yijie 《Journal of Systems Engineering and Electronics》 SCIE EI CSCD 2018年第1期142-151,共10页
In this paper, a new adaptive optimal guidance law with impact angle and seeker’s field-of-view(FOV) angle constraints is proposed. To this end, the generalized optimal guidance law is derived first. A changeable imp... In this paper, a new adaptive optimal guidance law with impact angle and seeker’s field-of-view(FOV) angle constraints is proposed. To this end, the generalized optimal guidance law is derived first. A changeable impact angle weighting(IAW) coefficient is introduced and used to modify the guidance law to make it adaptive for all guidance constraints. After integrating the closed-form solution of the guidance command with linearized engagement kinematics, the analytic predictive models of impact angle and FOV angle are built, and the available range of IAW corresponding to constraints is certain. Next, a calculation scheme is presented to acquire the real-time value of IAW during the entire guidance process. When applying the proposed guidance law, the IAW will keep small to avoid a trajectory climbing up to limit FOV angle at an initial time but will increase with the closing target to improve impact position and angle accuracy, thereby ensuring that the guidance law can juggle orders of guidance accuracy and constraints control. 展开更多
关键词 optimal guidance law impact angle constraint fieldof-view(FOV) angle constraint weighting coefficient
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Multiconstraint adaptive three-dimensional guidance law using convex optimization 被引量:6
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作者 FU Shengnan LIU Xiaodong +1 位作者 ZHANG Wenjie XIA Qunli 《Journal of Systems Engineering and Electronics》 SCIE EI CSCD 2020年第4期791-803,共13页
The traditional guidance law only guarantees the accuracy of attacking a target. However, the look angle and acceleration constraints are indispensable in applications. A new adaptive three-dimensional proportional na... The traditional guidance law only guarantees the accuracy of attacking a target. However, the look angle and acceleration constraints are indispensable in applications. A new adaptive three-dimensional proportional navigation(PN) guidance law is proposed based on convex optimization. Decomposition of the three-dimensional space is carried out to establish threedimensional kinematic engagements. The constraints and the performance index are disposed by using the convex optimization method. PN guidance gains can be obtained by solving the optimization problem. This solution is more rapid and programmatic than the traditional method and provides a foundation for future online guidance methods, which is of great value for engineering applications. 展开更多
关键词 proportional navigation(PN) adaptive guidance law three-dimensional space second-order cone programming(SOCP) convex optimal control
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Sliding mode control and Lyapunov based guidance law with impact time constraints 被引量:4
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作者 Xiaojian Zhang Mingyong Liu Yang Li 《Journal of Systems Engineering and Electronics》 SCIE EI CSCD 2017年第6期1186-1192,共7页
This paper analyses the issue of impact time control of super-cavitation weapons impact fixed targets which mainly refer to the ships or submarines who lost power, but still have combat capability. Control over impact... This paper analyses the issue of impact time control of super-cavitation weapons impact fixed targets which mainly refer to the ships or submarines who lost power, but still have combat capability. Control over impact time constraints of guidance law(ITCG) is derived by using sliding mode control(SMC) and Lyapunov stability theorem. The expected impact time is realized by using the notion of attack process and estimated time-to-go to design sliding mode surface(SMS). ITCG contains equivalent and discontinuous guidance laws, once state variables arrive at SMS,the equivalent guidance law keeps the state variables on SMS,then the discontinuous guidance law enforces state variables to move and reach SMS. The singularity problem of ITCG is also analyzed. Theoretical analysis and numerical simulation results are given to test the effectiveness of ITCG designed in this paper. 展开更多
关键词 Lyapunov stability sliding mode control impact time salvo attack TIME-TO-GO guidance law
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Observer-based Guidance Law Accounting for Second-order Dynamics of Missile Autopilots 被引量:5
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作者 Ping-Ping Qu Di Zhou 《Journal of Harbin Institute of Technology(New Series)》 EI CAS 2013年第1期17-22,共6页
Accounting for the missile autopilot as second-order dynamics, an observer-based guidance law is designed based on the dynamic surface control method. Some first-order low-pass filters are introduced into the design p... Accounting for the missile autopilot as second-order dynamics, an observer-based guidance law is designed based on the dynamic surface control method. Some first-order low-pass filters are introduced into the design process to avoid the occurrence of high-order derivatives of the line of sight angle in the expression of guidance law such that it can be implemented in practical applications. The proposed guidance law is effective in compensating the bad influence of the autopilot lag on guidance accuracy. In the simulations of intercepting non maneuvering targets, targets with step acceleration, and targets with sinusoidal acceleration respectively, the guidance law is compared with the adaptive sliding mode guidance law in the presence of missile autopilot lag. The simulation results show that the proposed guidance law is able to guide a missile to accurately intercept a maneuvering target, even if it escapes in a great and fast maneuver and the autopilot has a relatively large lag. 展开更多
关键词 MISSILE guidance law dynamic surface control AUTOPILOT OBSERVER
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Extended differential geometric guidance law for intercepting maneuvering targets 被引量:4
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作者 HUANG Jingshuai ZHANG Hongbo +1 位作者 TANG Guojian BAO Weimin 《Journal of Systems Engineering and Electronics》 SCIE EI CSCD 2018年第5期1046-1057,共12页
Without assumptions made on motion states of missile and target, an extended differential geometric guidance law is derived. Through introducing a line of sight rotation coordinate system, the derivation is simplified... Without assumptions made on motion states of missile and target, an extended differential geometric guidance law is derived. Through introducing a line of sight rotation coordinate system, the derivation is simplified and has more explicit physical significances. The extended law is theoretically applicable to any engagement scenarios. Then, on basis of the extended law, a modified one is designed without the requirement of target acceleration and an approach is proposed to determining the applied direction of commanded missile acceleration. Qualitative analysis is carried out to study the capture performance and a criterion for capture is given. Simulation results indicate the two laws are effective and make up the deficiency that pure proportional navigation suitable for endoatmospheric interceptions cannot deal with high-speed maneuvering targets. Furthermore, the correctness of the criterion is validated. 展开更多
关键词 missile guidance maneuvering target extended differential geometric guidance law capture performance proportional navigation
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