Composite impact vector control based on Apollo descent guidance

Date

2022-01-01

Author

ERER, Koray S.
TEKIN, Raziye
Özgören, Mustafa Kemal

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© 2021 Chinese Society of Aeronautics and AstronauticsA new three-dimensional missile guidance law to control the impact vector against a stationary target is proposed. The composite guidance law has two well-known components: Apollo descent guidance and trajectory shaping guidance. These respectively linear and planar guidance laws are combined to achieve a specified impact direction. The main idea is to define an impact plane and to steer the missile onto this plane using Apollo descent guidance while concurrently performing trajectory shaping with reference to the impact plane. The resulting guidance law is expressed by a single equation in vector form, which is straightforward to implement. Because it originates from an optimal formulation, the performance of the proposed technique is expected to be satisfactory. This is confirmed by comparative simulation runs, which also involve the method known as generalized explicit guidance.

Subject Keywords

Impact angle, Impact plane, Impact vector, Three-dimensional missile guidance, Trajectory shaping

URI

https://www.scopus.com/inward/record.uri?partnerID=HzOxMe3b&scp=85125463495&origin=inward
https://hdl.handle.net/11511/97503

Journal

Chinese Journal of Aeronautics

DOI

https://doi.org/10.1016/j.cja.2021.07.009

Collections

Department of Mechanical Engineering, Article

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Citation Formats

K. S. ERER, R. TEKIN, and M. K. Özgören, “Composite impact vector control based on Apollo descent guidance,” Chinese Journal of Aeronautics, pp. 0–0, 2022, Accessed: 00, 2022. [Online]. Available: https://www.scopus.com/inward/record.uri?partnerID=HzOxMe3b&scp=85125463495&origin=inward.