Nonlinear receding horizon sub-optimal guidance law for the minimum interception time problem

Alamir, Mazen

doi:10.1016/s0967-0661(00)00085-x

Cited by 8 publications

(3 citation statements)

References 11 publications

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“…From the simulation results, it was observed that the performance of the proposed formulation of SMC+IDC guidance law in driving the LOS rate to zero is uniformly superior in comparison to the other guidance laws while maintaining practicable commanded acceleration profiles. For the case of data of [39], it is observed that the performance of all the other guidance laws become unstable for the case 4 of target acceleration profile whereas the performance of the proposed formulation remains satisfactory. The performance of the SBPN was found unstable for the same target acceleration profile in simulation cases of data taken from [37] and [38].…”

Section: B Simulations With Varying Missile Velocitymentioning

confidence: 97%

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Sliding Mode and Inertial Delay Control Based Missile Guidance

Phadke

Talole

2012

IEEE Trans. Aerosp. Electron. Syst.

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A novel formulation of sliding mode control (SMC) based proportional navigation (PN) guidance law is presented. Unlike conventional SMC-based guidance laws, the law presented here does not need any knowledge of bounds of target acceleration. The target acceleration is estimated using the so-called inertial delay control (IDC). Closed-loop stability for the guidance loop is established. Simulations are carried out by considering highly-maneuvering targets and constant as well as varying missile velocity and the results are presented to demonstrate the effectiveness of the proposed formulation.

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Section: B Simulations With Varying Missile Velocitymentioning

confidence: 97%

“…Next we take a more realistic approach [31][32][33][34][35][36][37][38][39] by considering the effect of thrust and drag when the propulsion system is on and only drag otherwise. To this end, the equations (1) are augmented by…”

Section: B Simulations With Varying Missile Velocitymentioning

confidence: 99%

Sliding Mode and Inertial Delay Control Based Missile Guidance

Phadke

Talole

2012

IEEE Trans. Aerosp. Electron. Syst.

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“…The last category includes the guidance laws that guide the missile into the predicted engagement course (Alamir, 2001;Cho, Ryoo et al Tahk, 1999;Gurfil, 2001; Ben Asher and Ben Yaesh, 1997). The performance of the guidance laws in this category is greatly affected by the time to go estimation and the update rules of engagement.…”

Section: Introductionmentioning

confidence: 99%

A Full Missile Homing System Design Based on Proportional Navigation Guidance Law and Electro-Optical Tracking System

Al-Ashtari

2008

jcoeng

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Generally, the homing systems are majorly constructing from three components: the guidance law, the target tracking system, and the missile flight control system. Therefore, in this paper, we construct our homing system from the following components: the proportional navigation guidance law which is considered as the guidance scheme for most homing missile systems, the electro-optical tracking system, and a tail controlled missile. And subsequently complete mathematical derivations and the demand transfer function formulations of all these three components have been introduced. The proposed homing system is capable to pursuit and hit any target just by specifying the required missile flight time. A SIMULINK software program has been built mainly from four subsystems to simulate the operation of this homing system, and the simulation results show clearly the efficient performance of the proposed homing system under any probable disturbance

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