Nonlinear Robust Inscribed Angle Guidance for Stationary Targets

Kumar, Shashi Ranjan; Tsalik, Ronny; Shima, Tal

doi:10.2514/1.g002461

Cited by 15 publications

(16 citation statements)

References 23 publications

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“…The SMC-based guidance used the constant inscribed angle geometric rule in deriving the guidance scheme developed in Ref. 12 to enforce the desired impact angle. The constraint of field-of-view (FOV) was also considered in Ref.…”

Section: Introductionmentioning

confidence: 99%

“…There are a few works in the literature which used SMC for simultaneous control of the impact angle and time, for instance, Refs. 12, 32, and 33. The line-of-sight (LOS) shaping-based guidance strategy was designed in Ref.…”

Section: Introductionmentioning

confidence: 99%

“…The guidance scheme based on switching between the SMC-based impact time guidance and an optimal impact angle guidance was developed in Ref. 12 for the interceptor to intercept the target at a desired impact time and impact angle. Another SMC-based impact angle and time control guidance law was derived in Ref.…”

Section: Introductionmentioning

confidence: 99%

“…The continuous switching between these two dynamics avoids a switching behavior, unlike two-stage–based strategies such as the one in Ref. 12, while at the same time demanding smooth lateral acceleration profiles. It is also proved using the Lyapunov stability theory 34 that occurrence of the sliding mode on the defined hierarchical sliding surface enforces sliding mode on the individual sliding surfaces corresponding to the impact time and the impact angle.…”

Section: Introductionmentioning

confidence: 99%

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Sliding mode–based simultaneous control of impact angle and impact time

Majumder¹,

Kumar²

2021

Proceedings of the Institution of Mechanical Engineers, Part G:

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In this article, a sliding mode control–based nonlinear guidance scheme for controlling both impact angle and impact time simultaneously is proposed. The problem of impact angle control is first transformed to that of controlling line-of-sight angle and its rate, while the requirement of impact time is achieved by tracking the desired time-to-go. The chosen time-to-go estimate accounts for the curvature required to meet the impact angle requirements toward the target interception. In order to satisfy both of these terminal constraints, the sliding surface is defined as a combination of impact time error and the variable pertaining to the errors in line-of-sight angle and its rate, with appropriate gains assigned to them. The interceptor first performs necessary maneuvers to meet the impact time requirements and then steers its course to achieve the target interception at a desired impact angle. The guidance law is initially derived using nonlinear engagement kinematics against stationary targets and then extended to cater to constant velocity targets using the concept of predicted interception point. Numerical simulations are performed to validate the efficacy of the proposed guidance scheme for various initial engagement geometries. The performance of the proposed guidance scheme is also compared with those of the existing guidance laws and shown to be superior.

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Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

Sliding mode–based simultaneous control of impact angle and impact time

Majumder¹,

Kumar²

2021

Proceedings of the Institution of Mechanical Engineers, Part G:

Self Cite

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“…The exact estimation of time-to-go can be obtained if the missile follows a trajectory with a special algebraic structure (Snyder et al, 2015;Tekin et al, 2016). Recently, a trajectory-shaping guidance concept named inscribed angle guidance is proposed by Shima (2015, 2016;Kumar et al 2017), where the nominal trajectory is a specific circular. Because of the merits of circular trajectory, such as simple form, easy calculation and easy realization, the circular trajectory assumption is adopted in this paper, which is valid according to the study of Erer and Tekin (2016).…”

Section: Introductionmentioning

confidence: 99%

Guidance law to control impact time constraining the seeker’s field of view?

Cui

Bai

et al. 2018

AEAT

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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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Finite-time Convergent Impact Angle Constrained Sliding Mode Guidance

Majumder

Kumar

2020

IFAC-PapersOnLine

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Nonlinear Robust Inscribed Angle Guidance for Stationary Targets

Cited by 15 publications

References 23 publications

Sliding mode–based simultaneous control of impact angle and impact time

Sliding mode–based simultaneous control of impact angle and impact time

Guidance law to control impact time constraining the seeker’s field of view?

Finite-time Convergent Impact Angle Constrained Sliding Mode Guidance

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