Hostname: page-component-78c5997874-fbnjt Total loading time: 0 Render date: 2024-11-18T17:20:36.085Z Has data issue: false hasContentIssue false
  • English
  • Français

Biased optimal guidance law with specified velocity rendezvous angle constraint

Published online by Cambridge University Press:  27 January 2016

X. Xu  and
Y. Liang
X. Xu*
Affiliation:
Information Engineering School, Henan University of Science and Technology, Luoyang, China China Airborne Missile Academy, Luoyang, China Department of Automatic Control, Xi’an Jiao Tong University, Xi’an, China
Y. Liang
Affiliation:
Information Engineering School, Henan University of Science and Technology, Luoyang, China
*
xuxingyuan2003@126.com
Get access Rights & Permissions [Opens in a new window]

Abstract

In order to increase the effectiveness of interceptor missile, velocity rendezvous angle control is required in the terminal phase. The purpose of this paper is to obtain an optimal guidance law which can achieve specified velocity rendezvous angle as well as zero terminal miss distance. A biased optimal guidance law based on a simplified mathematical model is deduced for interceptors engaging against invasion aircraft. Different from previous literatures on this issue, the presented guidance law suitable for intercepting high-speed maneuvering target. Another advantage is, under centimeter level miss distance setting, the guidance law needs smaller guidance command near the terminal time, which can successfully avoid command saturation. Simulation results demonstrate the effectiveness of the presented guidance law.

Type
Research Article
Information
The Aeronautical Journal , Volume 119 , Issue 1220 , October 2015 , pp. 1287 - 1299
Copyright
Copyright © Royal Aeronautical Society 2015

Access options

Get access to the full version of this content by using one of the access options below. (Log in options will check for institutional or personal access. Content may require purchase if you do not have access.)

References

1.Zarchan, P.Tactical And Strategic Missile Guidance, 5th ed (Progress in Astronautics and Aeronautics), AIAA, 5th ed, 2007.Google Scholar
2.Siouris, G.M.Missile Guidance and Control Systems, Springer, New York, US, 2003.Google Scholar
3.Kim, B.S., Lee, J.G. and Han, S.H.Biased PNG law for impact with angular constraint, IEEE Transactions on Aerospace and Electronic Systems, 1998, 34, (1), pp 277–288.Google Scholar
4.Ratnoo, A and Ghose, D.Impact angle constrained interception of stationary targets, J Guidance, Control and Dynamics, 2008, 31, (6), pp 1816–1821.Google Scholar
5.Ratnoo, A and Ghose, D.Impact angle constrained guidance against nonstationary non-maneuvering targets, J Guidance, Control and Dynamics, 2010, 33, (1), pp 269–275.Google Scholar
6.Erer, K.S. and Merttopçuo, L.O.Indirect impact-angle-control against stationary targets using biased pure proportional navigation, J Guidance, Control and Dynamic, 2012, 35, (2), Pp 700–703.Google Scholar
7.Sang, D., Min, B.M. and Tahk, M.J.Impact angle control guidance law using Lyapunov function and PSO method, Proc. of the SICE annual conference, Takamatsu, JP, 2007.Google Scholar
8.Jeong, S.K., Cho, S.J. and Kim, E.G.Angle constraint biased PNG, Proc of the 5th asian control conference, Melbourne, Victoria, Australia, 2004.Google Scholar
9.Kim, M and Grider, K.V.Terminal guidance for impact attitude angle constrained flight trajectories, IEEE Transactions on Aerospace and Electronic Systems, 1973, AES-9, (6), pp 852–859.Google Scholar
10.Taub, I.Interceptor angle guidance under time varying speed, AIAA guidance, navigation, and control conference, 5-9 January, Kissimmee, Florida, US, 2015.Google Scholar
11.Taub, I and Shima, T.Interceptor angle guidance under time varying acceleration bounds, J Guidance, Control and Dynamic, 2013, 36, (3), pp 686–699.Google Scholar
12.Ryoo, C.K., Cho, H and Tahk, M.J.Optimal guidance laws with terminal impact angle constraint, J Guidance, Control and Dynamics, 2005, 28, (4), pp 724–732.Google Scholar
13.Ryoo, C.K., Cho, H and Tahk, M.J.Time-to-go weighted optimal guidance with impact angle constraints, IEEE Transactions of Control Systems, 2006, 14, (3), Pp 483–492.Google Scholar
14.Shaferman, V and Shima, T.Linear quadratic guidance laws for imposing a terminal intercept angle, J Guidance, Control and Dynamic, 2008, 31, (5), pp 1400–1412.Google Scholar
15.Ben-Asher, J.Z. and Yaesh, I.Advances in missile guidance theory, Progress in Astronautics and Aeronautics, AIAA, Reston, VA, US, 1998, (180), pp 25–90.Google Scholar
16.Martinez-Val, R. and Perez, E.Aeronautics and astronautics: recent progress and future trends, Proc. IMechE, Part C: Journal of Mechanical Engineering Science, 2009, 223, (C12), pp 2767–2820.Google Scholar