Three-Stage Proportional Navigation for Intercepting Stationary Targets with Impact Angle Constraints

Ranjan, Alok; Hota, Sikha; Singh, Nikhil Kumar

doi:10.1109/icc47138.2019.9123163

Cited by 8 publications

(7 citation statements)

References 19 publications

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“…However, the missile must intercept the target at the desired impact angle while not exceeding the available acceleration due to the available missile acceleration limitations. Therefore, the missile's and target's position restrictions and the relative motion state conditions are vital [5][6][7]. Nevertheless, exploring the lineof-sight angle selection region under the impact-angle control guidance law helps solve the target interception failure problem at the terminal phase due to inappropriate motion conditions [8][9].…”

Section: Introductionmentioning

confidence: 99%

Analysis of Line-of-Sight Angle Characteristics for Intercepting a Non-Maneuvering Target With Impact Angle Constraints

et al. 2023

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With the widespread informationization in modern warfare, higher requirements are required for monitoring the high-value target's movement state and the corresponding attack conditions. Since the impact-angle constraint guidance law can improve the striking effect of a missile, the study of the hitting conditions and corresponding angle range of the attack angle constraint guidance law has become particularly important. This paper proposes a relationship between the missile's line-of-sight and flight-path angle under terminal conditions and defines the line-of-sight selection region. Then, we analyze the selection method of the line-of-sight restriction at the end of the missile's terminal phases. Additionally, Cauchy's inequality is used to derive the mathematical expressions for line-of-sight selection region under extreme and ideal conditions when employing the developed guidance law to intercept non-maneuvering targets. Finally, a thorough analysis and numerous simulations demonstrate that the line-of-sight angle always falls within the extreme selection region during the entire flight and before hitting the target at the expected impact angle. Compared with a head-on interception, the line-of-sight selection region of the tail-chase case is broader, and the selection region range increases with the upward trend of the acceleration limit.INDEX TERMS impact angle constraint, line-of-sight selection region, acceleration limit, tail-chase attack, head-on interception.

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Section: Introductionmentioning

confidence: 99%

Analysis of Line-of-Sight Angle Characteristics for Intercepting a Non-Maneuvering Target With Impact Angle Constraints

et al. 2023

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“…In Ref. 8, a three-stage pure proportional navigation (PPN) guidance scheme was considered, which also accounted for field-of-view constraints. In Ref.…”

Section: Introductionmentioning

confidence: 99%

“…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%

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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“…To achieve any impact angle, the lateral acceleration required in Ref. 15 is less than its requirement in Ref. 14.…”

Section: Introductionmentioning

confidence: 99%

“…More recently, in Ref. 15, any impact angle against a stationary aerial target has been achieved using a three-stage PPN guidance law in 2D accounting the FOV limit of the on-board seeker. To achieve any impact angle, the lateral acceleration required in Ref.…”

Section: Introductionmentioning

confidence: 99%

FOV constrained guidance law for nonstationary nonmaneuvering target interception with any impact angle

Singh

Hota

2021

Proceedings of the Institution of Mechanical Engineers, Part G:

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This paper presents the nonstationary nonmaneuvering target interception with all possible desired impact angles in a two-dimensional (2D) aerial engagement scenario, where the target can move in any direction. The paper also considers the field-of-view (FOV) constraint for designing the guidance law so that the target is always visible while following the missile trajectory in the entire engagement time, which makes it feasible for real world applications. The guidance law is based on the pure proportional navigation (PPN) to achieve any impact angle of the entire angular spectrum. The proposed guidance law is then simulated for intercepting a nonstationary nonmaneuvering target using a kinematic model of a missile to demonstrate the efficacy of the presented scheme. A comparison with the related work existing in the literature has also been added to establish the superiority of the present work.

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Three-Stage Proportional Navigation for Intercepting Stationary Targets with Impact Angle Constraints

Cited by 8 publications

References 19 publications

Analysis of Line-of-Sight Angle Characteristics for Intercepting a Non-Maneuvering Target With Impact Angle Constraints

Analysis of Line-of-Sight Angle Characteristics for Intercepting a Non-Maneuvering Target With Impact Angle Constraints

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

FOV constrained guidance law for nonstationary nonmaneuvering target interception with any impact angle

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