Lock-on range of infrared heat seeker missile

Mohd Syuhaimi Ab Rahman, Mazen R. Hassan

Research output: Chapter in Book/Report/Conference proceedingConference contribution

5 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. Assuming clear sky background, the simulation results show: firstly, R increases as the target temperature increases. High value of R is achieved when the temperature of aircraft engine is high especially in takeoff case where the engine thrust is large. Secondly, 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. The decreasing of R will increase the probability of aircraft survivability assuming effective aircraft early warning system where the detecting range of the latter should be larger than the missile lock-on range.

Original languageEnglish
Title of host publicationProceedings of the 2009 International Conference on Electrical Engineering and Informatics, ICEEI 2009
Pages472-477
Number of pages6
Volume2
DOIs
Publication statusPublished - 2009
Event2009 International Conference on Electrical Engineering and Informatics, ICEEI 2009 - Selangor
Duration: 5 Aug 20097 Aug 2009

Other

Other2009 International Conference on Electrical Engineering and Informatics, ICEEI 2009
CitySelangor
Period5/8/097/8/09

Fingerprint

Missiles
Aircraft
Infrared radiation
Engines
Aircraft engines
Infrared detectors
Alarm systems
Takeoff
Painting
Temperature
Cooling
Coatings
Hot Temperature
Metals

Keywords

  • Heat seeker missile
  • Infrared
  • Lock-on range

ASJC Scopus subject areas

  • Information Systems
  • Software
  • Energy Engineering and Power Technology
  • Electrical and Electronic Engineering

Cite this

Ab Rahman, M. S., & Hassan, M. R. (2009). Lock-on range of infrared heat seeker missile. In Proceedings of the 2009 International Conference on Electrical Engineering and Informatics, ICEEI 2009 (Vol. 2, pp. 472-477). [5254691] https://doi.org/10.1109/ICEEI.2009.5254691

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

Proceedings of the 2009 International Conference on Electrical Engineering and Informatics, ICEEI 2009. Vol. 2 2009. p. 472-477 5254691.

Research output: Chapter in Book/Report/Conference proceedingConference contribution

Ab Rahman, MS & Hassan, MR 2009, Lock-on range of infrared heat seeker missile. in Proceedings of the 2009 International Conference on Electrical Engineering and Informatics, ICEEI 2009. vol. 2, 5254691, pp. 472-477, 2009 International Conference on Electrical Engineering and Informatics, ICEEI 2009, Selangor, 5/8/09. https://doi.org/10.1109/ICEEI.2009.5254691
Ab Rahman MS, Hassan MR. Lock-on range of infrared heat seeker missile. In Proceedings of the 2009 International Conference on Electrical Engineering and Informatics, ICEEI 2009. Vol. 2. 2009. p. 472-477. 5254691 https://doi.org/10.1109/ICEEI.2009.5254691
Ab Rahman, Mohd Syuhaimi ; Hassan, Mazen R. / Lock-on range of infrared heat seeker missile. Proceedings of the 2009 International Conference on Electrical Engineering and Informatics, ICEEI 2009. Vol. 2 2009. pp. 472-477
@inproceedings{72240a52c97f4ba1ba299c244080737f,
title = "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}. Assuming clear sky background, the simulation results show: firstly, R increases as the target temperature increases. High value of R is achieved when the temperature of aircraft engine is high especially in takeoff case where the engine thrust is large. Secondly, 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. The decreasing of R will increase the probability of aircraft survivability assuming effective aircraft early warning system where the detecting range of the latter should be larger than the missile lock-on range.",
keywords = "Heat seeker missile, Infrared, Lock-on range",
author = "{Ab Rahman}, {Mohd Syuhaimi} and Hassan, {Mazen R.}",
year = "2009",
doi = "10.1109/ICEEI.2009.5254691",
language = "English",
isbn = "9781424449132",
volume = "2",
pages = "472--477",
booktitle = "Proceedings of the 2009 International Conference on Electrical Engineering and Informatics, ICEEI 2009",

}

TY - GEN

T1 - Lock-on range of infrared heat seeker missile

AU - Ab Rahman, Mohd Syuhaimi

AU - Hassan, Mazen R.

PY - 2009

Y1 - 2009

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. Assuming clear sky background, the simulation results show: firstly, R increases as the target temperature increases. High value of R is achieved when the temperature of aircraft engine is high especially in takeoff case where the engine thrust is large. Secondly, 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. The decreasing of R will increase the probability of aircraft survivability assuming effective aircraft early warning system where the detecting range of the latter should be larger than the missile lock-on range.

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. Assuming clear sky background, the simulation results show: firstly, R increases as the target temperature increases. High value of R is achieved when the temperature of aircraft engine is high especially in takeoff case where the engine thrust is large. Secondly, 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. The decreasing of R will increase the probability of aircraft survivability assuming effective aircraft early warning system where the detecting range of the latter should be larger than the missile lock-on range.

KW - Heat seeker missile

KW - Infrared

KW - Lock-on range

UR - http://www.scopus.com/inward/record.url?scp=70449686409&partnerID=8YFLogxK

UR - http://www.scopus.com/inward/citedby.url?scp=70449686409&partnerID=8YFLogxK

U2 - 10.1109/ICEEI.2009.5254691

DO - 10.1109/ICEEI.2009.5254691

M3 - Conference contribution

SN - 9781424449132

VL - 2

SP - 472

EP - 477

BT - Proceedings of the 2009 International Conference on Electrical Engineering and Informatics, ICEEI 2009

ER -