The Inverted Flight Optimization of the Genetic Algorithm to Hyper boost Vehicle Trajectory

International Journal of Electrical and Electronics Engineering

© 2019 by SSRG - IJEEE Journal

Volume 6 Issue 10

Year of Publication : 2019

Authors : Umakant Bhaskarrao Gohatre, Dr. C. Ram Singla

10.14445/23488379/IJEEE-V6I10P102

How to Cite?

Umakant Bhaskarrao Gohatre, Dr. C. Ram Singla, "The Inverted Flight Optimization of the Genetic Algorithm to Hyper boost Vehicle Trajectory," SSRG International Journal of Electrical and Electronics Engineering, vol. 6,  no. 10, pp. 1-8, 2019. Crossref, https://doi.org/10.14445/23488379/IJEEE-V6I10P102

Abstract:

Hypersonic interception in close space is a major challenge because of the unpredictable trajectory of the target, requiring trajectory cluster interceptors to cover the forecast area and the optimum ability to modify the trajectory in order to update the predicted midcourse impact location (PIP) consistently. Based on the next optimum theory of control is proposed a new mid-course optimum trajectory cluster generation and trajectory modification algorithm. Firstly, the problem of optimizing the midcourse trajectory; the conditions necessary to optimize control and the constraints on transversely are given. Secondly, with the description of the Nearby Optimum Trajectory Existence (NOTET), An inverted flight management approach is implemented to identify the best way in which a hypersonic missile dive can be entered. This article examines the fighting scene in which the hypersonic missile attacks the target. In particular, the hypersonic missile is a maneuvering form known as inverted flight. An optimal path is designed to minimize the attachment time with regard to angle, dynamic pressure, heat transfer speed and normal overload. In addition, inverted flight in contrast simulation is better performed than normal flight.

Keywords:

Aircraft Control, Optimal Control, Optimisation Position Control, Trajectory control, Mathematical Model, Prediction

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