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Suboptimal Midcourse Guidance of Interceptors for High-Speed Targets with Alignment Angle Constraint

Dwivedi, Prasiddha Nath and Bhattacharya, Abhijit and Padhi, Radhakant (2011) Suboptimal Midcourse Guidance of Interceptors for High-Speed Targets with Alignment Angle Constraint. In: Journal of Guidance, Control, and Dynamics, 34 (3). pp. 860-877.

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Using the recently developed computationally efficient model predictive static programming and a closely related model predictive spread control concept, two nonlinear suboptimal midcourse guidance laws are presented in this paper for interceptors engaging against incoming high-speed ballistic missiles. The guidance laws are primarily based on nonlinear optimal control theory, and hence imbed effective trajectory optimization concepts into the guidance laws. Apart from being energy efficient by minimizing the control usage throughout the trajectory (minimum control usage leads to minimum turning, and hence leads to minimum induced drag), both of these laws enforce desired alignment constraints in both elevation and azimuth in a hard-constraint sense. This good alignment during midcourse is expected to enhance the effectiveness of the terminal guidance substantially. Both point mass as well as six-degree-of-freedom simulation results (with a realistic inner-loop autopilot based on dynamic inversion) are presented in this paper, which clearly shows the effectiveness of the proposed guidance laws. It has also been observed that, even with different perturbations of missile parameters, the performance of guidance is satisfactory. A comparison study, with the vector explicit guidance scheme proposed earlier in the literature, also shows that the newly proposed model-predictive-static-programming-based and model-predictive-spread-control-based guidance schemes lead to lesser lateral acceleration demand and lesser velocity loss during engagement.

Item Type: Journal Article
Publication: Journal of Guidance, Control, and Dynamics
Publisher: American Institute of Aeronautics and Astronautics
Additional Information: Copyright of this article belongs to American Institute of Aeronautics and Astronautics.
Department/Centre: Division of Mechanical Sciences > Aerospace Engineering(Formerly Aeronautical Engineering)
Date Deposited: 22 Jun 2011 09:09
Last Modified: 01 Feb 2019 09:18
URI: http://eprints.iisc.ac.in/id/eprint/38412

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