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本文研究贴壁浇铸固体火箭发动机结构在燃烧室压力作用下的动态响应.固体火药药柱视为线性粘弹体,发动机外壳视为线性弹性体,利用轴对称平面应变动粘弹理论,导出动力学基本方程.它为积分微分方程形式,经过数值积分与差分技术,将方程离散化,转化为代数方程,用计算机求解.文中着重讨论固体火药与发动机壳体交界面处的径向接触应力σ_(r=b)并较为详细地研究了粘弹体剪切松弛模量G(t)对σ_(r=b)的影响,以及燃烧室压力的上升梯度及药柱与发动机外壳的物理参量与几何参量对σ_(r=b)的影响.
In this paper, the dynamic response of adherent solid rocket motor to combustion chamber pressure is studied.The solid propellants are regarded as linear viscoelasticity, the engine shell is regarded as linear elastic body, and the axial symmetry plane strain-dependent viscoelastic theory is used to derive the power Learn the basic equations.It integrates the differential equation form, through numerical integration and the difference technology, the equation discretization, transforms the algebra equation, uses the computer to solve.This article mainly discusses the radial contact stress σ_ at the interface of the solid gunpowder and the engine case (r = b). The influence of the shear relaxation modulus G (t) on σ_ (r = b) of the viscoelastic material and the increase gradient of the pressure in the combustion chamber and the physical parameters Influence of Geometric Parameters on σ_ (r = b).