Lead Angle based Three-Dimensional Guidance for Angle Constrained Interception

Nanavati, Rohit V.; Kumar, Shashi Ranjan; Maity, Arnab

doi:10.2514/6.2021-1460

Cited by 2 publications

(3 citation statements)

References 29 publications

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“…There have been a significant volume of works in the development of interceptor guidance considering the impact angle constraint, using various techniques, such as the optimal control, [1][2][3][4][5] the variants of proportional navigation (PN) guidance, [6][7][8] and the sliding mode control (SMC). [9][10][11][12][13] In Refs.…”

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%

“…In Ref. 3, a three-dimensional guidance strategy was proposed using SDRE without decoupling the engagement kinematics to achieve the desired impact angle. In Ref.…”

Section: Introductionmentioning

confidence: 99%

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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“…Shi et al proposed a predictive guidance law [24], the virtual target is the predictive intercept point, which is based on the target's velocity and the time to go, and the missile pursues the virtual target by PNG law. A suboptimal IACG law based on finite-time state-dependent Riccati equation was proposed for an interceptor to pursue an aerial vehicle in a 3D engagement [25]. Kim et al proposed a IACG law [26] for nose-dive missile which can maximize its terminal velocity, but the assumption that the initial angle is close to vertical is unreasonable.…”

Section: Introductionmentioning

confidence: 99%

Impact Angle Control Guidance to Intercept Moving Targets by Virtual Target Technique

Hou

Zhu

Kuang

et al. 2021

International Journal of Aerospace Engineering

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To solve the problem regarding the impact angle of the missile, this paper proposes a novel guidance law, which can control the missile to hit the target at the desired angle. The key of the guidance law is selecting a moving point on the collision line as the virtual target, and the tactical requirements can be fulfilled by the missile directly pursuing the virtual target. The Lyapunov stable theory is used to prove the convergence of the proposed guidance law. The guidance command is generated by a PID controller to make the missile towards the virtual target. The proposed guidance law makes the lateral acceleration of the missile converge to zero, which leads the angle of attack to zero, and it theoretically guarantees the flight path angle equals the attitude angle. Numerical simulations demonstrate this impact angle control guidance law is very accurate and robust. Regardless of whether the initial heading error is large or small, the missile which employs the proposed guidance law can always hit the target from the preset direction and the guidance process is smooth.

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Lead Angle based Three-Dimensional Guidance for Angle Constrained Interception

Cited by 2 publications

References 29 publications

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

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

Impact Angle Control Guidance to Intercept Moving Targets by Virtual Target Technique

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