Angular acceleration compensation guidance law for passive homing missiles-Reference-Cited by-同舟云学术

Angular acceleration compensation guidance law for passive homing missiles

Published:2022-01-01 Issue:1 Volume:31 Page:287-299
ISSN:2543-6376
Container-title:Open Astronomy
language:en
Short-container-title:

Author:

Li Jixin¹,Liang Xiaogeng¹,Xia Keqiang²,You Yilin³

Affiliation:

1. China Airborne Missile Academy , Luoyang , Henan Province, 471009 , China

2. State Key Laboratory of Astronautic Dynamics , Xi’an , Shaanxi Province, 720043 , China

3. School of Information Science & Engineering, Yunnan University , Kunming , Yunnan Province, 650091 , China

Abstract

Abstract Proportional navigation guidance law (PNG) is widely used for passive homing missiles. But PNG often suffers from inaccurate tracking of target or even failure when the target is maneuvering quickly or releasing artificial decoys. In order to solve this problem, the angular acceleration compensation guidance law (AACG) is constructed by using line of sight (LOS) angular velocity and LOS angular acceleration. The stability analysis with Lyapunov stability theory shows that AACG system is asymptotically stable on a large scale under certain stability constraint conditions. AACG command is designed to be perpendicular to the LOS and optimized by gravity compensation. AACG is neither dependent on target acceleration nor the distance between the missile and the target. The numerical simulation results indicate that AACG has good guidance performance on air-to-air missiles when the target maneuvers violently or releases artificial decoys in the endgame term.

Publisher

Walter de Gruyter GmbH

Subject

Space and Planetary Science,Astronomy and Astrophysics

Link

https://www.degruyter.com/document/doi/10.1515/astro-2022-0039/pdf

Reference22 articles.

1. Vermeulen A, Maes G. 2009. Missile avoidance maneuvres with simultaneous decoy deployment. AIAA Guidance, Navigation and Control Conference; Chicago (IL), USA: American Institute of Aeronautic and Astronautics, 2009. p. 10–13.

2. Cao YL, Zhang JP. 2020. Study on the new algorithm for fast correction of guidance large loop against high maneuvering target. Aero Weapon. 27(6):103–107.

3. Fei J, Liu P. 2006. System application of staring infrared imaging terminal guidance. Infrared Laser Eng. 3:253–257.

4. Feng KQ. 2019. Research on some key technologies of MEMS-INS/GNSS integrated navigation system with the application to guidance munition. Taiyuan: North University of China. p. 12–45.

5. Gao SY, Liu H, Zhu MC, Zhang X, Bai Y. 2015. Analysis and optimization of angle measurement accuracy of strap-down laser semi-active guidance seeker. Infrared Laser Eng. 44(7):2169–2174.