A Near Optimal Midcourse Guidance Law for Air-to-Air Missile

Qing Qing Qiao; Wan Chun Chen

doi:10.4028/www.scientific.net/AMM.336-338.833

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HomeApplied Mechanics and MaterialsApplied Mechanics and Materials Vols. 336-338A Near Optimal Midcourse Guidance Law for...

A Near Optimal Midcourse Guidance Law for Air-to-Air Missile

Abstract:

Dynamic inversion and singular perturbation methods are employed for medium-range air-to-air missile to obtain a near-optimal midcourse guidance law. The midcourse guidance stage is separated into two phases. In phase 1, which the rocket engine working, a dynamic inversion guidance law is used to guide the missile flight along a nominal trajectory. In the second gliding phase, singular perturbation technique is employed to develop a guidance law which maximum terminal specific energy. A terminal correction is made to ensure the seeker intercept the target. The result obtained from numerical simulation shows that, the guidance law can conserve energy for terminal interception, and the flight path error is small enough at the end of midcourse stage.

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Periodical:

Applied Mechanics and Materials (Volumes 336-338)

Pages:

833-838

DOI:

https://doi.org/10.4028/www.scientific.net/AMM.336-338.833

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Online since:

July 2013

Authors:

Qing Qing Qiao, Wan Chun Chen

Keywords:

Dynamic Inversion, Midcourse Guidance, Singular Perturbation

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References

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