Optimal Guidance Around Circular Trajectories for Impact-Angle Interception

Tsalik, Ronny; Shima, Tal

doi:10.2514/1.g001759

Cited by 60 publications

(18 citation statements)

References 26 publications

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“…Many researchers have developed various modern robust guidance laws based on different nonlinear control methods. 3–12 In Gao et al., 3 an adaptive guidance law was proposed for attacking a ground target in the presence of impact angle using adaptive control technique and feedback guidance strategy. In Yang et al., 4 a new integrated guidance and control law was proposed for a homing missile subject to impact angle, which can be applied for an efficient salvo attack of ground target.…”

Section: Introductionmentioning

confidence: 99%

“…In Yang et al., 4 a new integrated guidance and control law was proposed for a homing missile subject to impact angle, which can be applied for an efficient salvo attack of ground target. In Park et al., 5 Tsalik and Shima, 6 and Lee and Seo, 7 based on the optimal control theory, the optimal guidance laws were proposed. In Wang et al., 12 a retro proportional navigation was proposed for high-speed nonmaneuvering targets based on the auxiliary function and pure proportional navigation.…”

Section: Introductionmentioning

confidence: 99%

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Adaptive back-stepping sliding mode guidance laws with autopilot dynamics and acceleration saturation consideration

Geng

Zhang

Sun

2019

Proceedings of the Institution of Mechanical Engineers, Part G:

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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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Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Adaptive back-stepping sliding mode guidance laws with autopilot dynamics and acceleration saturation consideration

Geng

Zhang

Sun

2019

Proceedings of the Institution of Mechanical Engineers, Part G:

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“…Homing guidance systems that can implement fire-andforget attacks have been rapidly developed and widely applied [1,2]. In recent years, studies on homing guidance have dealt with constraints in the angle of impact [3], mostly through the employment of optimal control theory [4][5][6][7][8][9][10][11][12][13]. Moreover, constraints on the maximum acceleration command are also commonly considered [14,15].…”

Section: Introductionmentioning

confidence: 99%

“…(3) The total control cost for the first stage can be optimized by considering the term b/2 t f l t 0 u 2 t dt in equation (10).…”

mentioning

confidence: 99%

Cooperative Guidance of Seeker-Less Missiles for Precise Hit

Zhao

Xiong

2019

International Journal of Aerospace Engineering

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A novel cooperative guidance scenario is proposed that implements fire-and-forget attacks for seeker-less missiles with a cheap finder for stationary targets and without requiring real-time communication among missiles or precise position information. Within the proposed cooperative scenario, the classic leader-follower framework is utilized, and a two-stage cooperative guidance law is derived for the seeker-less missile. Linear-quadratic optimal control and biased proportional navigation guidance (PNG) are employed to develop this two-stage cooperative guidance law to minimize the control cost in the first stage and to reduce the maximum acceleration command in the second stage when the acceleration command is continuous. Simulations and comparisons are conducted that demonstrate the effectiveness and advantages of the proposed guidance law.

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“…Optimal control theory has also been applied in many studies to address the terminal impact angle constraint. By linearizing the equations of motion based on a nominal circular trajectory and treating the impact angle interception as an optimal rendezvous problem, an impact angle control guidance law was proposed by Tsalik and Shima, 9 which had better results compared with those obtained by a BPNG law. Cho et al.…”

Section: Introductionmentioning

confidence: 99%

Polynomial guidance law for impact angle control with a seeker look angle limit

Zhou

Yao

2019

Proceedings of the Institution of Mechanical Engineers, Part G:

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In this paper, the impact angle control problem is investigated by applying the polynomial shaping method. By shaping the light-of-sight angle with relative range, a guidance law called range polynomial guidance is proposed, and the coefficients are determined by boundary conditions. The range polynomial guidance law can be applied to maneuvering targets. By profiling the seeker look angle with the light-of-sight angle, a guidance law called line-of-sight polynomial guidance is developed for impact angle control under a limitation on the seeker look angle. The line-of-sight polynomial guidance law is also effective in intercepting a non-maneuvering moving target at the desired impact angle. Guidance laws with different gain sets are discussed in this paper. The proposed guidance laws take the form of proportional navigation with a time-varying navigation gain. Nonlinear simulations are performed to validate the efficacy of the proposed guidance laws in various engagement conditions. Comparison with other studies demonstrates the practicality and flexibility of the proposed guidance laws in the design of desired impact angles and maximum look angles.

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Optimal Guidance Around Circular Trajectories for Impact-Angle Interception

Cited by 60 publications

References 26 publications

Adaptive back-stepping sliding mode guidance laws with autopilot dynamics and acceleration saturation consideration

Adaptive back-stepping sliding mode guidance laws with autopilot dynamics and acceleration saturation consideration

Cooperative Guidance of Seeker-Less Missiles for Precise Hit

Polynomial guidance law for impact angle control with a seeker look angle limit

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