Analytical analysis of lock-on range of infrared heat seeker missile

Mohd Syuhaimi Ab Rahman, Mazen R. Hassan

Research output: Contribution to journalArticle

2 Citations (Scopus)

Abstract

The lock-on range, R, of infrared (IR) heat seeker missile has been studied in details. An analytical expression form of R has been derived in term of target (assumed as aircraft hot metal tailpipe), atmosphere and infrared (IR) detector parameters. The R is represented in term of "Lambert W function" and as a function of target temperature, T, and atmosphere extinction coefficient, á, and also the noise equivalent irradiance (NEI) of the detector. Assuming clear sky background, the simulation results show that a high value of R can be achieved when the temperature of aircraft engine is high especially in takeoff case where the engine thrust is large. The R can be decreased by (1) increasing the attenuation coefficient of the propagation medium, i. e. by cooling the aircraft hot engine or any other obscurants that absorb or scatter the IR radiation (2) or by decreasing emissivity, å, of the target surface which depends on the applied coatings / paintings. However, the R of can be increased by reducing the NEI of the IR detector.

Original languageEnglish
Pages (from-to)3703-3713
Number of pages11
JournalAustralian Journal of Basic and Applied Sciences
Volume3
Issue number4
Publication statusPublished - Oct 2009

Fingerprint

homing devices
missiles
infrared detectors
irradiance
heat
aircraft
engines
aircraft engines
atmospheres
takeoff
infrared radiation
attenuation coefficients
emissivity
thrust
sky
extinction
cooling
coatings
temperature
propagation

Keywords

  • Heat seeker missile
  • Infrared
  • Lock-on range

ASJC Scopus subject areas

  • General

Cite this

Analytical analysis of lock-on range of infrared heat seeker missile. / Ab Rahman, Mohd Syuhaimi; Hassan, Mazen R.

In: Australian Journal of Basic and Applied Sciences, Vol. 3, No. 4, 10.2009, p. 3703-3713.

Research output: Contribution to journalArticle

@article{c1ff32cfa6f1474088b5af5697d96cab,
title = "Analytical analysis of lock-on range of infrared heat seeker missile",
abstract = "The lock-on range, R, of infrared (IR) heat seeker missile has been studied in details. An analytical expression form of R has been derived in term of target (assumed as aircraft hot metal tailpipe), atmosphere and infrared (IR) detector parameters. The R is represented in term of {"}Lambert W function{"} and as a function of target temperature, T, and atmosphere extinction coefficient, {\'a}, and also the noise equivalent irradiance (NEI) of the detector. Assuming clear sky background, the simulation results show that a high value of R can be achieved when the temperature of aircraft engine is high especially in takeoff case where the engine thrust is large. The R can be decreased by (1) increasing the attenuation coefficient of the propagation medium, i. e. by cooling the aircraft hot engine or any other obscurants that absorb or scatter the IR radiation (2) or by decreasing emissivity, {\aa}, of the target surface which depends on the applied coatings / paintings. However, the R of can be increased by reducing the NEI of the IR detector.",
keywords = "Heat seeker missile, Infrared, Lock-on range",
author = "{Ab Rahman}, {Mohd Syuhaimi} and Hassan, {Mazen R.}",
year = "2009",
month = "10",
language = "English",
volume = "3",
pages = "3703--3713",
journal = "Australian Journal of Basic and Applied Sciences",
issn = "1991-8178",
publisher = "INSInet Publications",
number = "4",

}

TY - JOUR

T1 - Analytical analysis of lock-on range of infrared heat seeker missile

AU - Ab Rahman, Mohd Syuhaimi

AU - Hassan, Mazen R.

PY - 2009/10

Y1 - 2009/10

N2 - The lock-on range, R, of infrared (IR) heat seeker missile has been studied in details. An analytical expression form of R has been derived in term of target (assumed as aircraft hot metal tailpipe), atmosphere and infrared (IR) detector parameters. The R is represented in term of "Lambert W function" and as a function of target temperature, T, and atmosphere extinction coefficient, á, and also the noise equivalent irradiance (NEI) of the detector. Assuming clear sky background, the simulation results show that a high value of R can be achieved when the temperature of aircraft engine is high especially in takeoff case where the engine thrust is large. The R can be decreased by (1) increasing the attenuation coefficient of the propagation medium, i. e. by cooling the aircraft hot engine or any other obscurants that absorb or scatter the IR radiation (2) or by decreasing emissivity, å, of the target surface which depends on the applied coatings / paintings. However, the R of can be increased by reducing the NEI of the IR detector.

AB - The lock-on range, R, of infrared (IR) heat seeker missile has been studied in details. An analytical expression form of R has been derived in term of target (assumed as aircraft hot metal tailpipe), atmosphere and infrared (IR) detector parameters. The R is represented in term of "Lambert W function" and as a function of target temperature, T, and atmosphere extinction coefficient, á, and also the noise equivalent irradiance (NEI) of the detector. Assuming clear sky background, the simulation results show that a high value of R can be achieved when the temperature of aircraft engine is high especially in takeoff case where the engine thrust is large. The R can be decreased by (1) increasing the attenuation coefficient of the propagation medium, i. e. by cooling the aircraft hot engine or any other obscurants that absorb or scatter the IR radiation (2) or by decreasing emissivity, å, of the target surface which depends on the applied coatings / paintings. However, the R of can be increased by reducing the NEI of the IR detector.

KW - Heat seeker missile

KW - Infrared

KW - Lock-on range

UR - http://www.scopus.com/inward/record.url?scp=77953490377&partnerID=8YFLogxK

UR - http://www.scopus.com/inward/citedby.url?scp=77953490377&partnerID=8YFLogxK

M3 - Article

AN - SCOPUS:77953490377

VL - 3

SP - 3703

EP - 3713

JO - Australian Journal of Basic and Applied Sciences

JF - Australian Journal of Basic and Applied Sciences

SN - 1991-8178

IS - 4

ER -