Method for acquiring aerodynamic coefficients of guided missile

Abstract

The invention relates to a method for acquiring the aerodynamic coefficients of a guided missile. The method solves the problem that a polar coordinate system aerodynamic coefficient can not be used under a rectangular coordinate system. The method includes the steps that firstly, after the step of acquiring the aerodynamic coefficient under the polar coordinate system of the guided missile through a wind tunnel test, guided missile ballistic parameters are acquired, and guided missile aerodynamic parameters are obtained through resolving according to the guided missile ballistic parameters, wherein the guided missile ballistic parameters include the flight speed with the symbol shown in the description and the flight attitude angle, and the guided missile aerodynamic parameters include the flight attack angle alpha and the flight sideslip angle beta; then, the total attack angle alpha sigma and the roll angle phi under the polar coordinate system are obtained according to the flight attack angle alpha, the flight sideslip angle beta and a conversion formula; then, the interpolation polar coordinate aerodynamic coefficient is obtained through interpolation according to the total attack angle alpha sigma and the roll angle phi; then, the rectangular coordinate system aerodynamic coefficient is obtained according to the interpolation polar coordinate aerodynamic coefficient and a conversion formula; accordingly, the acceleration and the angular acceleration of the guided missile are obtained; finally, the ballistic parameters including the flight speed with the symbol shown in the description and the flight attitude angle of the guided missile at the next moment are obtained.

Description

technical field [0001] The invention belongs to the field of aerospace wind tunnel test data processing, and in particular relates to a method for acquiring missile aerodynamic coefficients. Background technique [0002] According to the geometric angle relationship between the projectile body and the airflow space, the aerodynamic coefficients used in missile design are divided into two systems: Cartesian coordinate system and polar coordinate system. The aerodynamic coefficient of the Cartesian coordinate system varies with the two-dimensional change of the angle of attack α and the angle of sideslip β, and the data points present a matrix distribution in space. The aerodynamic coefficient in the polar coordinate system varies with the total angle of attack α Σ and the roll angle Φ change in two dimensions, the data points are distributed in a circle in space, the data near the center of the circle is denser, and the data far away from the center of the circle is sparse. ...

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Problems solved by technology

[0004] Purpose of the present invention: the main purpose of the present invention is, find out a kind of acquisition method of missile aerodynamic coefficient or obtain the test method of missile aerodynamic coefficient in other words, solve the problem that the polar coordinate system aerodynamic coefficient cannot be used under the Cartesian coordinate system

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