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本文简要介绍了一种计算亚声速飞机外挂物气动载荷和分离轨迹的工程方法。本方法分别采用源汇模型和涡格模型模拟母机的体积效应和法向力效应,采用迭代方法计及母机-外挂物之间的二阶干扰。在气动中心高速所研制的战术导弹气动特性工程计算方法的基础上,以迎角沿弹身轴线和翼片变化的流动条件代替该方法中的均匀来流条件,而建立了非均匀流场中外挂物气动载荷的计算方法。最后采用四阶的 Adams 数值积分方法求解六自由度运动方程而得到外挂物的分离轨迹。与国内外其它计算方法相比,本方法具有适用范围广、迅速、方便、实用等特点。本方法对一系列算例进行了计算,其结果与风洞实验数据具有令人满意的一致性。
This article briefly introduces an engineering method for calculating aerodynamic loads and separation trajectories of subsonic aerosols. In this method, the volume effect and the normal force effect of the master are simulated by the model of source and sink and the model of the vortex grid respectively. The second order interference between the master and the attached object is taken into account by the iterative method. Based on the calculation method of aerodynamic characteristics of tactical missile developed at high speed aerodynamic center, the uniform flow conditions in the method are replaced by the flow conditions of the attack angle along the axis of the projectile and the variation of the fins, so that the non-uniform flow field The calculation method of pneumatic load of external objects. Finally, the fourth-order Adams numerical integration method is used to solve the equations of motion of six degrees of freedom to get the separation trajectory of the external object. Compared with other calculation methods at home and abroad, this method has the characteristics of wide range of application, rapid, convenient and practical. This method calculates a series of examples and the results are in good agreement with wind tunnel experimental data.