Direct impact angle control guidance for passive homing missiles

Cho, Dongsoo; Kim, Seunghwan

doi:10.1177/0954410020930488

Cited by 4 publications

(6 citation statements)

References 24 publications

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“…Note that sliding mode control has been shown to be effective for various aerospace applications. [9][10][11][12][13][16][17][18]32,33,35,36 Before deriving the guidance command, we first obtain the dynamics of LOS angle and impact time using engagement kinematics (1). By using the unique relationship between the impact angle and the desired LOS angle, as shown in, 9 we aim to control the impact angle through tracking of LOS angle.…”

Section: Guidance Law Designmentioning

confidence: 99%

“…In Ref. 13, SMC-based impact angle guidance strategy was proposed for a passive seeker equipped interceptor, wherein the guidance command was composed of PN guidance with a varying navigation constant and an additional biased term. The SMC-based guidance used the constant inscribed angle geometric rule in deriving the guidance scheme developed in Ref.…”

Section: Introductionmentioning

confidence: 99%

“…The constraint of field-of-view (FOV) was also considered in Ref. 13 while designing the guidance strategy. However, the abovementioned guidance strategies do not account for impact time constraints.…”

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. 1 and 2, the guidance laws based on the state-dependent Riccati equation (SDRE) technique were designed by employing the functions of time-to-go and altitude-to-go, respectively, to satisfy the impact angle constraint.…”

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: Guidance Law Designmentioning

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:

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“…For the attack of large objects and promotion of cooperative combat capability, a concept of multiple missiles salvo attack has been dramatically developed and received significant attention from many scholars. [1][2][3][4][5][6] Clearly, the complex combat missions can be successfully realized by the cooperation of multiple missiles. Moreover, the control of impact time plays an important role in a cooperative guidance law.…”

Section: Introductionmentioning

confidence: 99%

Three-dimensional cooperative interception guidance law with impact time constraint

Yifan

Cai

2021

Proceedings of the Institution of Mechanical Engineers, Part G:

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This article proposes a new terminal cooperative guidance law with impact time constraint in three-dimensional (3D) engagement. Two parts are comprised by this guidance scheme to control the impact time and fulfill the interception. The guidance law along the line-of-sight (LOS) direction is first designed based on finite time consensus protocol to share time-to-go values among missiles and reach the consensus. Meanwhile, the guidance law on the LOS normal direction is developed based on the fast finite time control method to achieve the interception. The stability analysis of the proposed guidance law based on the Lyapunov theory is also demonstrated in detail. Moreover, the maneuvering target can be intercepted successfully under the presented control algorithm, and the guidance system can fulfill stability within finite time. Additionally, the effectiveness and applicability of the proposed guidance scheme are explicitly verified through simulation tests.

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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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Direct impact angle control guidance for passive homing missiles

Cited by 4 publications

References 24 publications

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

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

Three-dimensional cooperative interception guidance law with impact time constraint

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

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