Title: A Note on the Singularity of Modified Proportional Navigation Guidance
Abstract: It is well known that the Proportional Navigation Guidance (PN) is used as a terminal guidance law for missiles. It is also famous that PN is an optimal guidance under some conditions, but in the real world, PN is not always the ’optimal’ guidance especially when the missile accelerates. For the accelerating missiles, Modified Proportional Navigation Guidance (MPN) was proposed, although the axial acceleration of the missile was considered as constant. In fact, the missile will be accelerated non-linearly, thus the Modified Proportional Navigation Guidance (MPN) is revisited and we proposed a new method in order to improve MPN. In our method, a missile and a target are considered as point masses. We assume that it is a shortrange air-to-air missile with a solid rocket motor and its acceleration is nonlinear. To maintain as high missile speed as possible at the end of the engagement (near the collision), the missile lift coefficient should be as small as possible. We, however, found some singular points in the guidance law and propose some changes in this paper. Under new formulation, numerical analyses are performed. As a result, we succeeded to bring the missile guidance more reliable and the trajectories are closer to those of optimal solutions than those of the former MPN’s.
Publication Year: 2022
Publication Date: 2022-01-03
Language: en
Type: article
Indexed In: ['crossref']
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