Abstract
In order to obtain the analytical method to compute the circumferential strain on a soft pulse separation device (PSD), deformation processes of the middle section of the soft PSD, the medicine propellant grain and the case are simplified into a two-dimensional plane strain state. It is found that the main factors affecting the circumferential strain of the soft PSD are the circumferential strain of the inner surface of the propellant grain and the gap between the soft PSD and the propellant grain. In order to study the failure mechanism of the soft PSD in the double-pulse solid rocket motor (SRM), a two-dimensional axisymmetric finite element method (FEM) model of the stress process of the soft PSD is established. The variation of the strain of the soft PSD with the internal pressure load is obtained. It is found that the excessive circumferential strain is the main reason for the failure of the soft PSD. Comparing the analytical calculations with the FEM results, it can be found that the analytical method value is slightly higher than the FEM value, so the analytical method results can be used to initially estimate the circumferential strain of the soft PSD and then predict the rationality and feasibility of the design scheme. In order to further study the failure mechanism of the soft PSD, a micro-CT test of in situ stretching of the soft PSD material is carried out and the variation of porosity and elongation of the material is studied. The test results showed that when the material elongation is large, the microinterface debonding rapidly expands into a penetrating damage, and the PSD structure fails. The conclusions obtained in this paper can provide a useful reference for the design of double-pulse SRM.
Highlights
A pulse solid rocket motor (SRM) uses the pulse separation device (PSD) to divide the combustion chamber of SRM into several parts to distribute the thrust and the pulse interval time reasonably and improve the performance of various types of tactical missile systems comprehensively
In order to obtain the analytical method to compute the circumferential strain of the soft PSD, the deformation process of the intermediate section of the PSD, the propellant grain and the case are simplified into a two-dimensional plane strain state
It can be seen from formula (4) that for the double-pulse SRM, which has determined the geometry of the propellant type, the main factors affecting the circumferential strain of the soft PSD are the circumferential strain of the propellant grain inner surface and the gap between the soft PSD and the propellant grain
Summary
A pulse solid rocket motor (SRM) uses the pulse separation device (PSD) to divide the combustion chamber of SRM into several parts to distribute the thrust and the pulse interval time reasonably and improve the performance of various types of tactical missile systems comprehensively. In order to obtain the analytical method to compute the circumferential strain of the soft PSD, the deformation process of the intermediate section of the PSD, the propellant grain and the case are simplified into a two-dimensional plane strain state. This analytical method can be used as a formula basis for the design of a double-pulse SRM. The two-dimensional axisymmetric FEM model of the stress process of the soft PSD is established, and the variation of the strain of the soft PSD with the internal pressure load is obtained to verify the accuracy of the analytic method. In order to further study the failure mechanism of the soft PSD, the micro-CT test of in situ stretching of the soft PSD material is carried out, and the variation of porosity and elongation of the material is studied
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