Analysis Of Solid Rocket Motor Structural Integrity Of Composite Propellant

This paper describes methods and procedures of structural analysis of compositepropellant rocket motor grains based on the use of the Finite Element analysis programMarc with its viscoelastic material modeling capability. This researches make the strengthproblems as background, which is common when the solid rocket motor is in manufactureor under pressurization on ignition loads. The result makes sense to project appliance orexperiment design.Because the solid propellant is a typical viscoelastic material, viscoelastic theory andpropellant mechanical properties are discussed fully. Since the experiential method forgrain structural integrity analysis was still widely used in history and is still being used inthe primary design stage nowadays, it is discussed properly in the paper. The paper mainlyanalyses the structural integrity of grain under thermal loads and pressurization loads byusing FEM software Marc. To chose a type of solid rocked motor as model, researches thenumerical simulation of the structure of grains which is during the cooling process, andunder internal pressurization on ignition at normal temperature, low temperature or hightemperature. Then, the effects of solid rocket motor material parameters, geometryparameters, cooling technology parameters on its structure integrity are respectivelycompared and analyzed under internal pressure and thermal loading by use of Marcsoftware. The conclusions would be useful for to the design of solid rocket motors.This research can be help for reduce economical price of repetitious experiment, andensure the solid rocket motor work reliably in the whole working condition. It should bewith important practical significance.