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An Optimal Missile Autopilot Design Model

An Optimal Missile Autopilot Design Model
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Author(s): Yong-chao Chen (Electronic Engineering Department, Shijiazhuang Mechanical Engineering College, Shijiazhuang, China), Xin-bao Gao (Electronic Engineering Department, Shijiazhuang Mechanical Engineering College, Shijiazhuang, China), Min Gao (Electronic Engineering Department, Shijiazhuang Mechanical Engineering College, Shijiazhuang, China) and Dan Fang (Electronic Engineering Department, Shijiazhuang Mechanical Engineering College, Shijiazhuang, China)
Copyright: 2018
Volume: 14
Issue: 1
Pages: 7
Source title: International Journal of Enterprise Information Systems (IJEIS)
Editor(s)-in-Chief: Gianluigi Viscusi (Imperial College Business School, United Kingdom)
DOI: 10.4018/IJEIS.2018010106

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Abstract

This article describes how one optimal design method is given to the design of missile autopilots. This method profits from an exhaustive method. By this method, the design process of a missile autopilot is simplified, and the design efficiency is improved. In the design process of this method, the performance indexes of autopilot are translated into constraint conditions, and the response speed is translated to an objective function. Thus, the optimal design of missile autopilot is translated into the optimal design of a nonlinear system with multiple constraints. The optimization algorithm is found to be out of controller parameter combinations which can satisfy constrained conditions. Firstly, calculations of the corresponding objective function values. Second, by the extract the optimal combination which has the minimal objective function value.

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