DOAJ Open Access 2025

A Guidance Method for Impact Time and Angle Control Based on Trajectory Tracking

Gang Lei He Wang Shaopeng Li

Abstrak

To attack a stationary target with both impact time and angle constraints, a guidance method is proposed based on trajectory tracking. According to the constraints of each stage of missile flight, a polynomial missile trajectory satisfying the impact time and angle is introduced, and the discrete kinematics equation of the missile flight process is established. In order to improve the tracking efficiency of the linear quadratic regulator, curvature feedback term and error feedback term are introduced into the weight matrix. The Savitzky–Golay filter is added to the output end, which weakens the chattering of guidance commands. Numerical simulation proves the effectiveness of the proposed guidance method.

Topik & Kata Kunci

Motor vehicles. Aeronautics. Astronautics

Penulis (3)

Gang Lei

He Wang

Shaopeng Li

Format Sitasi

APA MLA BibTeX

Lei, G., Wang, H., Li, S. (2025). A Guidance Method for Impact Time and Angle Control Based on Trajectory Tracking. https://doi.org/10.1155/ijae/5533692

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Informasi Jurnal

Tahun Terbit: 2025
Sumber Database: DOAJ
DOI: 10.1155/ijae/5533692
Akses: Open Access ✓