Pursuer identification and time-to-go estimation using passive measurements from an evader

Li, Lin; Kirubarajan, T.; Bar‐Shalom, Yaakov

doi:10.1109/taes.2005.1413756

Cited by 27 publications

(15 citation statements)

References 16 publications

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“…In accordance with the proportional navigation law, the line of sight angles should be used to find a target interception point. Therefore the extraction of missile acceleration commands to intercept the required target [12], equations (2.8) to (2.11) will be used to compute the velocity of missile (Vmissile) and angles of acceleration.…”

Section: Missile Dynamics Modelingmentioning

confidence: 99%

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A Genetic Algorithm for Mid-Air Target Interception

Younas¹,

Aqeel²

2011

IJCA

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This paper presents a computational model that uses a modified Genetic Algorithm (GA) approach, to provide more accurate results for mid-air targets interception. The proportional navigation laws that have been practiced for many years for target interception have been deployed in this research. A revised GA is formulated to determine the optimal interception point by modifying the heuristic crossover. An interception point is computed in which the miss distance and missile flight times are minimized. The selections of proportional navigation constant (CN) and time-to-launch values are playing a key role in minimizing the interception error. The results suggest a minimized interception error with better accuracy for target interception. General TermsMissile Dynamics and Evolutionary Algorithms.

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Section: Missile Dynamics Modelingmentioning

confidence: 99%

“…The optimization with respect to the proportional navigation laws will follow the above scenario as illustrated in figure-4 [12]. The line of sight will be maintained to calculate an interception point, and for that interception point, a GA is optimizing the values of miss distance and flight time of missile.…”

Section: Modified Genetic Algorithmmentioning

confidence: 99%

A Genetic Algorithm for Mid-Air Target Interception

Younas¹,

Aqeel²

2011

IJCA

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“…Furthermore, air-to-air missile tracking brings missile trajectory and time-to-go estimation [2], which are of great benefits for pilots to make decisions.…”

Section: Introductionmentioning

confidence: 99%

“…Guidance law identification of ground-to-air missile is studied in [2] through maximum likelihood method; possibilities of different guidance laws are determined using Bayesian reasoning in [3]; guidance law identification is achieved through MMAE and IMM method in [1] and [4], respectively; research is extended in three-dimensional coordinates in [5] and saturation condition of missile controller is taken into account in [6].…”

Section: Introductionmentioning

confidence: 99%

Air-to-Air Missile Tracking and Guidance Law Identification Based on CKF

Wu¹,

Wang²,

Yang³

et al. 2018

Proceedings of the 2017 4th International Conference on Machinery, Materials and Computer (MACMC 2017)

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An air-to-air missile tracking and guidance law identification method based on CKF is proposed. A precise air-to-air missile model is constructed with drag force taken into consideration. With CKF method and preprocessing, guidance law filter is designed for missile tracking and estimation of guidance law, gravity compensation and drag constant. Simulation results indicate the rapidness and accuracy of this method.

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“…However, not much has been done on identifying/classifying the missile from the aircraft's point of view (using angle-only measurements) to infer if the missile is aimed at the aircraft (where the sensor is located) or not. The recent paper [9] considered the problem of identifying several guidance parameters of a missile aimed at an aircraft, and [14] simplified the model for the purpose of aim identification. This provides the background for the current work.…”

Section: Introductionmentioning

confidence: 99%

Aim Identification with a Minimal Parameter Set

Ravindra

Bar‐Shalom

Gottesman

2007

2007 IEEE Aerospace Conference

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This paper considers the problem of using passive (line-of-sight angle) observations of a surface to air or an air to air missile (pursuer) from an aircraft (evader), to infer whether the missile is or is not aimed at the aircraft. The observations are assumed to be made only on an initial portion of the pursuer's trajectory. The approach is to model the trajectory of the missile with a number of kinematic and guidance parameters, estimate them and use statistical tools to infer whether the missile is guided toward the aircraft or not. A mathematical model is presented for a missile under pure proportional navigation with a changing velocity (direction change as well as speed change), to intercept a nonmaneuvering aircraft. A maximum likelihood estimator (MLE) is used for estimating the missile's motion parameters and a goodness-of-fit test is formulated to test if the aircraft is the aim or not. Using measurement data from several realistic missiles aimed at an aircraft, it is shown that the proposed method can solve this problem successfully. The key to the solution, in addition to the missile model parametrization, is the use of a reliable global optimization algorithm for the MLE. The estimation/decision algorithm presented here can be used for an aircraft to decide, in a timely manner, whether appropriate countermeasures are necessary.

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Pursuer identification and time-to-go estimation using passive measurements from an evader

Cited by 27 publications

References 16 publications

A Genetic Algorithm for Mid-Air Target Interception

A Genetic Algorithm for Mid-Air Target Interception

Air-to-Air Missile Tracking and Guidance Law Identification Based on CKF

Aim Identification with a Minimal Parameter Set

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