Lead Angle Constrained Optimal Midcourse Guidance

Dwivedi, PN and Kumar , P and Bhattacharya, A and Padhi, R (2013) Lead Angle Constrained Optimal Midcourse Guidance. In: AIAA Guidance, Navigation, and Control (GNC) Conference, Guidance, Navigation, and Control and Co-located Conferences, (AIAA 2013-4533), August 19-22, 2013, Boston, Massachusetts.

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Abstract

A lead angle constrained optimal mid course guidance in this paper, which is quite important for missions with missiles with limited sen sor capability to detect and monitor the target. This guidance law not only achieves the minimum control effort, but also generates the desired optimal terminal angl es (in both pitch and yaw planes) that can lead to proper trajectory shaping to assure the desired lead angle during the midcourse. If both plane terminal lead angles are free, then this guidance will generate the desired terminal lead angles suc h that control effort can be minimized. If total lead angle is specified, then this guid ance law solves the constraint optimal problem to find the lead angles in both plane optimally. In a case where both lead angles are specified, this guidance law will achieves this with minimum control effort. For all the three cases close form solutions for the lateral acceleration command has been obtained. Simulation results for all three cases are quite very promising. Robustness and generalized nature of this guidance law have also been demonstrated through extensive simulations in this paper

Item Type:	Conference Proceedings
Series.:	AIAA Guidance, Navigation, and Control (GNC) Conference
Publisher:	American Institute of Aeronautics and Astronautics
Additional Information:	Copy right for this article belongs to the American Institute of Aeronautics and Astronautics
Department/Centre:	Division of Mechanical Sciences > Aerospace Engineering(Formerly Aeronautical Engineering)
Date Deposited:	25 Aug 2016 10:38
Last Modified:	25 Aug 2016 10:38
URI:	http://eprints.iisc.ac.in/id/eprint/54602

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