Structural response analysis of a solid rocket motor with HTPB propellant grain under vertical storage condition

Abstract

Aiming at the structural response characteristics of solid rocket motor (SRM) under vertical storage conditions, the creep tests of HTPB propellant under different stress levels were carried out, and the creep constitutive model of the propellant was fitted. Then the creep model of the HTPB propellant was used to analyze the structural response of a solid rocket motor with HTPB propellant grain. At the same time, a two-week vertical storage experiment was conducted for the SRM with HTPB propellant grain, and the creep displacement of the front and rear end of the propellant grain was measured and compared with the simulation results. The results show that the creep model of the HTPB propellant can well simulate the structural response of the propellant grain under vertical storage condition. During the storage process, the position near the root of the front artificial relief flaps is the high stress area of propellant grain. After 1 year of vertical storage, the axial sinking displacement at the rear end face of propellant grain is about 1.38 mm.

Effect of Annealing on the Interface and Properties of Pd/Al Composite Wires

“…As the rate of Pd/Al diffusion increases, a large number of intermetallic compounds are generated at the interface, and an immediate exothermic reaction occurs, generating high temperatures that can directly detonate the explosive or ignite the solid fuel. Because of its short reaction time, the availability of a constant current to control the reaction process and the high heat release during the reaction (about 1368.19 J/g), it can directly meet the requirements of short ignition response time, small ignition peaks and easy control of the ignition time for solid rocket motors [ 9 , 10 , 11 , 12 ]. It has the characteristics of having less substance discharged during the reaction, heat transferred mainly by conduction, the reaction does not need oxygen, and it can react under vacuum and inert gas.…”

Study on the constitutive model of NEPE propellant based on indentation creep

“…Composite solid propellant is a typical viscoelastic material with obvious relaxation and creep, and creep is one of the main mechanical properties of solid propellant materials [1]. Due to the residual stress caused by hardening and cooling of solid rocket motor and its own gravity, the creep effect of grain will change the geometric and ballistic characteristics of the column, affect the structural response characteristics of grain and interface, and even affect the reliability of the engine [1b]. Therefore, the influence of creep of propellant grain should be considered in the design, pouring, service and storage stages.…”