High-speed separation fluid-solid coupling simulation method for low-attitude big dynamic pressure integrated fairing

Abstract

The invention discloses a high-speed separation fluid-solid coupling simulation method for a low-attitude big dynamic pressure integrated fairing. The method comprises the following steps of S1, computing an aerodynamic coefficient of each feature point of fairing separation by using computational fluid mechanical software; S2, constructing a fairing separation aerodynamic coefficient interpolation model by using a bilinear interpolation method based on the aerodynamic coefficient acquired by computation; S3, building a fairing separation many-body dynamical model by using many-body dynamical software; S4, building a fairing separation fluid-solid coupling simulation model based on the fairing separation aerodynamic coefficient interpolation model and the many-body dynamical model; and S5, calling the aerodynamic coefficient interpolation model and the fairing separation many-body dynamical model to perform fluid-solid coupling simulation, and acquiring a simulation result. According to the method provided by the invention, strong coupling of an aerodynamic force and a fairing posture is achieved, strong fluid-solid coupling simulation is achieved, and simulation precision for separation of the fairing is greatly improved.

Description

technical field [0001] The invention relates to a design method in the aerospace field, in particular to a high-speed separation fluid-solid coupling simulation method for a low-altitude high-dynamic-pressure integral fairing. Background technique [0002] When the missile is flying in the atmosphere, the fairing is used to prevent the important equipment of the missile head from being affected by harmful environments such as aerodynamic force, aerodynamic heating and acoustic vibration, and is an important part of the missile structure. When the missile flies to a certain height, the fairing must be separated and discarded in time, so that the head equipment of the missile body can work normally and the follow-up mass of the missile can be reduced, so that the role of the missile can be effectively played. The integral fairing has good rigidity and small deformation during operation, so it is widely used in hypersonic missiles. However, the separation of the integral fairi...

AI Technical Summary

Problems solved by technology

Computational fluid dynamics directly coupled with multibody dynamics provides a solution, but the solution efficiency of computational fluid dynamics directly coupled with multibody dynamics is very low

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