Impact time control using biased proportional navigation for missiles with varying velocity

Sun, Guoxin; Qin, Wen; Xu, Zhiqiang; Xia, Qing

doi:10.1016/j.cja.2019.11.015

Cited by 28 publications

(13 citation statements)

References 22 publications

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“…. And a coefficient that defines overall damage capabilities of this type of jets [26] . And to be able destroy all 4 ships with probability from core group we will find out that we need 8 launchers 30 missiles.…”

Section: Methodsmentioning

confidence: 99%

Simulation Model of a Missile Strike

Toshev,

Maksymov,

Kiriakidi

2024

ELTECS

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Abstract. As modern naval warfare systems and tactics continue to evolve, it is crucial to employ contemporary tools capable of assessing their potential across various combat scenarios. This study model simulates interactions between anti-ship missiles and naval forces during landing operations. Our research seeks to develop a robust method for quantitatively analyzing the impact of anti-ship missiles on naval vessels under diverse combat conditions. The model's scalability allows for the incorporation of emerging naval tactics and procedures, maintaining its relevance and utility in dynamic strategic environments. It supports enhancements in precision through statistical analysis and ongoing assessments of new weaponry and technological advancements. By simulating a broad range of missile types, naval strategies, warship classes, aircraft, reconnaissance systems, and electronic warfare capabilities, the model provides insights into the strategic utility of anti-ship missiles. Our findings aim to optimize the allocation of military resources by accurately determining the necessary missile quantities to thwart enemy naval landings, thereby enhancing the effectiveness and efficiency of defensive operations. Keywords: Anti-ship missiles, missile guidance, naval landing, simulation framework, missile damage estimation.

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Section: Methodsmentioning

confidence: 99%

Simulation Model of a Missile Strike

Toshev,

Maksymov,

Kiriakidi

2024

ELTECS

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“…The bias term b is the same as (21). In UPNG method, impact angle is constrained by bias term b and variable coefficient N defined by (27).…”

Section: Guidance Commandsmentioning

confidence: 99%

“…Erer and Ozgoren and Erer and Merttopçuoglu proposed a BPNG law without information about time-to-go or LOS distance [18,19]. By delving into the relationship between the bias integral component and the impact angle, Erer and Merttopçuoglu and Sun et al controlled the bias integral component, thereby achieving impact angle control [20,21]. Ratnoo proposed two-stage VCPNG and verified the effective control of the impact angle through numerous simulations [22].…”

Section: Introductionmentioning

confidence: 99%

A New United Proportional Navigation Guidance for Impact Angle Constraint without Measurement Distance between Vehicle and Target

Yang

Bai

et al. 2022

International Journal of Aerospace Engineering

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This paper proposed a united proportional navigation guidance (UPNG) method to alleviate the guidance command saltation with an impact angle constraint under the condition of no real-time distance between the vehicle and the target (line-of-sight (LOS) distance). Firstly, based on the biased proportional navigation guidance (BPNG), a smooth-biased proportional navigation guidance (SBPNG) method was proposed, whose bias term was designed as a trigonometric function. In SBPNG method, due to the continuous smooth change of the bias term, the guidance command would not saltus anymore, and the impact angle was controlled by the bias integral component. Secondly, biased on SBPNG method, the united proportional navigation guidance (UPNG) method combining SBPNG and variable coefficient proportional navigation guidance (VCPNG) was established. In UPNG method, because there was no LOS distance, the guidance coefficient was designed as a function of the difference between the expected impact angle and the estimated impact angle, so the closed-loop control of impact angle was realized. Finally, a lot of simulation experiments on different guidance laws were carried out without real-time LOS distance. The results verify that the UPNG method proposed in this paper solves the problem of guidance command saltation effectively and has better robustness in impact angle control.

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“…Therefore, many scholars have attempted to apply powerful nonlinear control methods to design guidance laws, aiming to improve the success rate and reduce the sensitivity of missiles to maneuvering targets, as well as reduce the fuel requirements of missiles. Biased proportional navigation guidance [4] methods incorporate the appropriate bias components to align the guidance law to meet the requirements of a specific angle of impact, thus increasing the effectiveness of the impact. In addition, there are some optimal guidance laws [5,6], especially for highspeed maneuvering targets.…”

Section: Introductionmentioning

confidence: 99%

An Improved Second-Order Sliding Mode Control for an Interception Guidance System without Angular Velocity Measurement

2023

Mathematics

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It is well-known that the successful implementation of current sliding-mode guidance laws relies on two key points: one is the prior knowledge of the upper bound of the target’s maneuver, and the other is the accurate measurement of motion information. The truth maneuver is usually difficult to acquire and can only be roughly estimated. Measurements are often affected by noise and physical limitations of the onboard sensor. This paper presents an improved second-order sliding-mode guidance law that can handle these two problems simultaneously while addressing the chattering phenomenon, which inherently exists in the sliding mode-based controller. We achieve this by using the estimation from an extended state observer (ESO) and tracking differentiator (TD). In light of the employed ESO, which is utilized to give an estimation of the external disturbance, prior knowledge of the target’s maneuver is not required. Most interestingly, we show that the motion information can be estimated efficiently from the ESO in real time. A TD filter can be further embedded to remove unwanted noise from the detected signal. A series of simulations has been conducted, clearly demonstrating that the estimation accuracy of the ESO is sufficient for the guidance law to implement accurate interception. The TD filter not only removes noise but also avoids the phase-loss problems associated with conventional filters. Moreover, the chattering phenomenon is completely eliminated in the control channel.

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Impact time control using biased proportional navigation for missiles with varying velocity

Cited by 28 publications

References 22 publications

Simulation Model of a Missile Strike

Simulation Model of a Missile Strike

A New United Proportional Navigation Guidance for Impact Angle Constraint without Measurement Distance between Vehicle and Target

An Improved Second-Order Sliding Mode Control for an Interception Guidance System without Angular Velocity Measurement

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