Requirements for equipping Tau anti-tank short-range missile with inertial guidance and navigation system

Document Type : Original Article

Authors

1 MSc. Student of Malek Ashtar University

2 Associate Professor, Malek Ashtar University

Abstract

Anti-tank missiles have been one of the most important tactical weapons on the battlefield in the past decades.Guiding, navigating and hitting the target are one of the most important issues in anti-tank missiles.The Tau missile can be named as one of the most powerful short-range anti-tank missiles used in the world, which can also be fired from a helicopter, which also plays a significant role in the military forces of the Islamic Republic of Iran.Tau missile is a three-point strategic guidance type (missile, target and tracker), in which type of guidance, if the communication wire connected to the missile is cut or the conduction laser channel is cut in the new generation Tau missiles, the missile guidance will be lost. Also, in wired or laser guidance, the helicopter from which the missile is fired must guide the missile to the end of the path until the missile hits the target (approximately "20 seconds), which is considered a very dangerous operation in terms of safety on the battlefield. Therefore, having an anti-tank guided missile with FIRE & FORGET capability in required times is necessary, so, in this research, the pre-set guidance and navigation requirements for the Tau missile are investigated and it is shown that by equipping the helicopter with a laser rangefinder to determine the target position and using a sensor with low bias error in the guidance and navigation system of the Tau missile, we can use FIRE & FORGET guidance with an acceptable accuracy for the Tau missile.

Keywords

References

[1]  ص. پایخان، «تجربه بکارگیری موشک ضدزره تاو در دوران جنگ تحمیلی بوسیله بالگرد شکاری کبرا»، درمجموعه مقالات اولین همایش سراسری موشک­های هدایت شونده ضد زره، تهران، 1379، ص 25-28.
[2] Jwo, D. J., Shih, J. H., Hsu, C. S., & Yu, K. L., “development of a strapdown inertial navigation system simulation platform”, Journal of Marine Science and Technology, Vol. 22, No. 3, pp. 381-391, 2014.
[3] Zhang, W., Ghogho, M., & Yuan, B., “Mathematical model and matlab simulation of strapdown inertial navigation system”, Hindawi Publishing Corporation, Modelling and Simulation in Engineering, Vol. 2012, Article ID 264537, pp. 1-25, 2012.
[4] Titterton, D.,  & Weston, J. “Strapdown inertial navigation technology”, (2nd Edition), Institution of Engineering and Technology, United Kigdom, 2004.
[5] Grigorie, T. L., Lungu, M., Raluca Edu, I., & Obreja, R. “Concepts for error modeling of iniatureaccelerometers used in inertial navigation systems” annals of the university of  craiova, electrical engineering _series, no. 34,; issn_ 1842-4805, 2010.
[6] Grigorie, T. L., Jula, C. C. N., & Racuciu, C. “Evaluation method of the sensors errors in an inertial navigation system”, Wseas Transactions on Circuits and Systems, issue 12, volume 7, december, issn: 1109-2734, 2008.
[7] Xu, Y., Wang, Z., & Gao, B. “Six-degree-of-freedom digital simulations for missile guidance and control” college of mechatronic engineering, north university of china, taiyuan 030051, china, received 17 march 2015; accepted 25 june, 2015.
[8] Kisabo, A. B.  Adebimpe, A. F., Okwo, O. C., & Samuel, S. O. “State-space modelling of a rocket for optimal control system design” Aliyu Bhar Kisabo et al. / journal of aircraft and spacecraft technology, 2019.
Journal of Aeronautical Engineering
Volume 23, Issue 2
December 2021
Pages 92-99

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History

  • Receive Date: 02 September 2021
  • Revise Date: 03 December 2021
  • Accept Date: 21 December 2021

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