Augmented Polynomial Guidance With Impact Time and Angle Constraints

In this paper, a new impact time and impact angle control guidance law for homing missiles against a stationary target is proposed. To derive a state feedback command for the proposed law with terminal constraints on the impact time and angle, we introduce a polynomial function of the guidance comma...

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Bibliographic Details
Published inIEEE transactions on aerospace and electronic systems Vol. 49; no. 4; pp. 2806 - 2817
Main Authors Kim, Tae-Hun, Lee, Chang-Hun, Jeon, In-Soo, Tahk, Min-Jea
Format Journal Article
LanguageEnglish
Published IEEE 01.10.2013
Subjects
Boundary conditions
Missiles
Polynomials
State feedback
Time factors
Trajectory
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Summary:In this paper, a new impact time and impact angle control guidance law for homing missiles against a stationary target is proposed. To derive a state feedback command for the proposed law with terminal constraints on the impact time and angle, we introduce a polynomial function of the guidance command with three unknown coefficients, one of which is determined to achieve the impact time requirement. The others are determined to satisfy the terminal impact angle constraint, as well as the zero miss distance. Because the proposed guidance law has arbitrary guidance gains, it is possible to shape the intercept trajectory and acceleration command profile by choosing proper gains in relation to the missile's capability, operational conditions, and so on.
ISSN:0018-9251
1557-9603
DOI:10.1109/TAES.2013.6621856