Position Calculation for Front Fin of Rocket Forebody Using Variable Step Scheme

• Published in: Aerospace 2024-08, Vol.11 (8), p.617
• Main Authors: Zhou, Zeyang, Huang, Jun
• Format: Article
• Language: English
• Subjects: aerodynamic analysis; Aerodynamic forces; Aerodynamics; Algorithms; Artificial satellites; computational fluid; Computational fluid dynamics; Design; Design and construction; Fins; Flow characteristics; Fluid dynamics; Fluid flow; Forebodies; Genetic algorithms; Hydrodynamics; hypersonic; Mach number; Mathematical optimization; Meteorological satellites; Optimization; Position indicators; rocket forebody fin; Rockets; Rockets (Aeronautics); Search algorithms; Shear stress; Simulation; Turbulence models; Vehicles; Weight
• ISSN: 2226-4310; 2226-4310
• DOI: 10.3390/aerospace11080617

In order to determine the installation position of the front fin on the example rocket forebody, an optimized method based on a comprehensive evaluation indicator and variable step search is presented. The comprehensive indicator consists of four weight coefficients, two lateral aerodynamic forces and two aerodynamic moments. The computational fluid dynamics method based on a shear stress transport turbulence model is established to analyze the flow field characteristics of the forebody. The results indicate that under equal weight coefficients, the presented search algorithm can provide an optimized solution for the front fin to achieve the minimum value of the comprehensive evaluation indicator. When the range of the current wing movement changes or the weight coefficient distribution changes, this search algorithm can still provide the optimal solution and some feasible solutions. Under the given conditions, there is a difference between the optimal solution of the aerodynamic force priority and that of the aerodynamic moment priority. For the case of the aerodynamic moment priority, the mean level of the pressure coefficient corresponding to the optimal solution on the given observation plane is low. The presented method is effective in learning the appropriate installation position of the rocket’s front fins.