Multi-objective optimization of the aerodynamic shape of the front fuselage of a controlled flying aircraft by parameter space investigation


Tran Manh Tuan, Nguyen Phu Thang, Nguyen Ngoc Dien


Academy of Military Science and Technology, Ha Noi City, Vietnam

Le Quy Don Technical University, Ha Noi City, Vietnam

Corresponding Author Email: bauman252@lqdtu.edu.vn

This is an open access article distributed under the Creative Commons Attribution License, which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.

This paper presents a method to multi-objectively optimize aerodynamic profile for the front fuselage of a single-channel controlled aircraft using Parameter Space Investigation (PSI). The input parameters are the design options of the profile layout, taken according to the LPτ series in the parameter space. The solution method is based on the results of calculating the set of aerodynamic coefficients using Missile Datcom and simulating flight dynamics with Matlab Simulink. The objective function selected for optimization is the static stability reserve and the controllability of the aircraft in automatic control according to the three-point guidance method. This method has some advantages, it can be applied to all kinds of optimization problems with different types of objective functions and constraints. The number of calculations is limited not to be too large even when the number of design variables is large. This method has many advantages when solving multi-objective optimization problems thanks to its ability to analyze computational data. The optimization algorithm is based on human intervention and automatic computer programming allows appropriate adjustments when necessary, so the problem always has a solution.