A Prediction Method of Internal Ballistic Performance of Solid Rocket Motor

Abstract

This application provides a method for predicting the internal ballistic performance of a solid rocket motor. The method includes the following steps: establishing a parameterized charge structure model; simulating the combustion process of the charge structure model, and outputting the relationship between the thickness of the burned meat and the burning surface curve and the relationship curve between the thickness of the burned flesh and the exposed area of ​​the thermal insulation layer; calculate the propellant mass flow rate corresponding to different time points according to the relationship curve between the thickness of the burned flesh and the exposed area of ​​the thermal insulation layer; The ablation mass flow rate of the adiabatic layer corresponding to different time points, the mass flow rate of the propellant and the ablation mass flow rate of the adiabatic layer corresponding to the same time point are added together, and the relationship between the time and the mass flow rate of the combustion product is output; according to the combustion time and The internal ballistic performance curve is obtained from the combustion product mass flow rate relationship curve. The application obviously improves the prediction accuracy of the internal ballistic performance of the solid rocket motor before the ignition test, optimizes the performance of the solid rocket motor, and reduces the development time and cost.

Description

technical field [0001] The present application relates to the technical field of dynamic ablation of thermal insulation layers of solid rocket motors, in particular to a method for predicting internal ballistic performance of solid rocket motors. Background technique [0002] During the working process of the solid rocket motor, the combustion of the charge produces a large amount of high-temperature and high-pressure gas, which is accelerated by the expansion of the nozzle to form a supersonic gas flow and is ejected. According to the conservation of mass, in the state of pressure balance in the engine room, if the insulation layer and other components are not considered The mass flow rate of the nozzle inlet is equal to the propellant combustion mass flow rate. [0003] Before the ground ignition experiment, there are usually two options for predicting the internal ballistic performance of solid rocket motors: [0004] The first one does not consider the influence of the ...

AI Technical Summary

Problems solved by technology

[0004] The first one does not consider the effect of ablation of the thermal insulation layer on the internal ballistic performance

This scheme is suitable for engines with short working hours, low combustion chamber pressure, and good ablation resistance of the heat insulation layer, and the engine has no strict requirements on the accuracy of internal ballistic prediction. Low, only suitable for small and medium solid rocket motors

The defect of this scheme is that it is impossible to explain the difference between the prediction results of the internal ballistic performance of the engine that has not undergone the ignition test and the measured internal ballistic performance, and multiple ground ignition tests will inevitably increase the development time and development cost

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