In:
Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering, SAGE Publications, Vol. 235, No. 2 ( 2021-02), p. 238-256
Abstract:
An impact angle control guidance law is proposed for stationary target interception considering missile's field-of-view limit and speed changes. The proposed impact angle control guidance law is structured as a biased proportional navigation with a time-varying bias. The proposed guidance law does not involve any switching logic for maintaining lock-on; hence, the guidance command is continuous during the entire engagement. Unlike the most existing studies, the proposed method guarantees that the impact angle error converges to zero before interception without the constant-speed assumption. To realize these desirable properties, the positive invariance of the bounded look angle interval and the change of independent variable are utilized. Numerical simulations are conducted to demonstrate the performance of the proposed guidance law.
Type of Medium:
Online Resource
ISSN:
0954-4100
,
2041-3025
DOI:
10.1177/0954410020942010
Language:
English
Publisher:
SAGE Publications
Publication Date:
2021
detail.hit.zdb_id:
2032759-6
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