Robust stochastic controller for a missile guidance system

Rizk, Mohamed R. M.; Rahim, Mohammad Akmal Baharain Abdul

doi:10.1109/icecs.2000.912996

Cited by 1 publication

(1 citation statement)

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“…Utilizing this method, it is possible to determine the shape of trajectories and the necessary manoeuvrability of the missile under the assumption that the missile velocity is a known function of time (which is determined from Kalman tracker) [8]. The position of the missile w.r.t target is determined in the polar coordinate system by radius vector D , as shown in Fig 1. The principle law of motion of a self-guidance missile in the vector form is given by [9], centre of gravity motion are [8]:…”

Section: General Kinematic Equations Of Missile Target Engagementmentioning

confidence: 99%

Target tracking enhancement using a Kalman filter in the presence of interference

Elgamel

Soraghan

2009

2009 IEEE International Geoscience and Remote Sensing Symposium

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In this paper we present a new target tracking enhancement system that uses a Kalman filter in the presence of interference. If the radar (seeker) is affected by different types of interference, this will affect the missile trajectory towards the target and may cause inaccurate tracking. In the new system a six-state Kalman filter is utilized to perform the tracking task and to carry out smoothing to the corrupted trajectory. This also provides good information about the target velocity in three dimensions which is very important information about the target. A three dimensional scenario between target (with high manoeuvre) and missile is used to illustrate the performance of the system in the case when (i) no interference is present and (ii) interference is present. The performance of the filtered trajectory using the Kalman tracker will be assessed for different guidance methods: including (i) proportional navigation (ii) pure pursuit and (iii) constant bearing. The Kalman improvement for the tacking for the three guidance method will be analysed.

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Section: General Kinematic Equations Of Missile Target Engagementmentioning

confidence: 99%