Missile guidance with constrained intercept body angle

Ilan Rusnak; Haim Weiss; Rei Eliav; Tal Shima

doi:https://doi.org/10.1109/TAES.2014.120100

Missile guidance with constrained intercept body angle

Ilan Rusnak, Haim Weiss, Rei Eliav, Tal Shima

Technion - Israel Institute of Technology

Research output: Contribution to journal › Article › peer-review

Abstract

A linear quadratic based missile guidance law is presented that imposes a predetermined terminal body angle. Solutions are provided for arbitrary order autopilot dynamics, with explicit analytical expressions given for first-order and zero-lag dynamics. Performance is demonstrated through simulation in a planar interception scenario.

Original language	English
Article number	6850166
Pages (from-to)	1445-1453
Number of pages	9
Journal	IEEE Transactions on Aerospace and Electronic Systems
Volume	50
Issue number	2
DOIs	https://doi.org/10.1109/TAES.2014.120100
State	Published - Apr 2014

All Science Journal Classification (ASJC) codes

Aerospace Engineering
Electrical and Electronic Engineering

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https://doi.org/10.1109/TAES.2014.120100

Cite this

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title = "Missile guidance with constrained intercept body angle",

abstract = "A linear quadratic based missile guidance law is presented that imposes a predetermined terminal body angle. Solutions are provided for arbitrary order autopilot dynamics, with explicit analytical expressions given for first-order and zero-lag dynamics. Performance is demonstrated through simulation in a planar interception scenario.",

author = "Ilan Rusnak and Haim Weiss and Rei Eliav and Tal Shima",

year = "2014",

month = apr,

doi = "https://doi.org/10.1109/TAES.2014.120100",

language = "الإنجليزيّة",

volume = "50",

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T1 - Missile guidance with constrained intercept body angle

AU - Rusnak, Ilan

AU - Weiss, Haim

AU - Eliav, Rei

AU - Shima, Tal

PY - 2014/4

Y1 - 2014/4

N2 - A linear quadratic based missile guidance law is presented that imposes a predetermined terminal body angle. Solutions are provided for arbitrary order autopilot dynamics, with explicit analytical expressions given for first-order and zero-lag dynamics. Performance is demonstrated through simulation in a planar interception scenario.

AB - A linear quadratic based missile guidance law is presented that imposes a predetermined terminal body angle. Solutions are provided for arbitrary order autopilot dynamics, with explicit analytical expressions given for first-order and zero-lag dynamics. Performance is demonstrated through simulation in a planar interception scenario.

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U2 - https://doi.org/10.1109/TAES.2014.120100

DO - https://doi.org/10.1109/TAES.2014.120100

M3 - مقالة

SN - 0018-9251

VL - 50

SP - 1445

EP - 1453

JO - IEEE Transactions on Aerospace and Electronic Systems

JF - IEEE Transactions on Aerospace and Electronic Systems

IS - 2

M1 - 6850166

ER -

Missile guidance with constrained intercept body angle

Abstract

All Science Journal Classification (ASJC) codes

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