Method for predicting internal ballistic performance of solid rocket engine

Abstract

The invention provides a method for predicting internal ballistic performance of a solid rocket engine. The method comprises the following steps of: establishing a parameterized charging structure model; carrying out analogue simulation on the combustion process of the charging structure model, and outputting a relation curve between combusted thickness and a combustion surface and a relation curve between the combusted thickness and the exposed area of a heat insulation layer; calculating propellant mass flow rates corresponding to different time points according to the relation curve of thecombusted thickness and the area of the combustion surface, calculating the ablation mass flow rates of the heat insulation layer corresponding to the different time points according to the relation curve of the combusted thickness and the exposure area of the heat insulation layer, adding the propellant mass flow rate and the ablation mass flow rate of the heat insulation layer corresponding to the same time point, and outputting the relation curve of time and combustion product mass flow rates; and obtaining an internal ballistic performance curve according to the relation curve of the combustion time and the combustion product mass flow rates. The method obviously improves the prediction precision of the internal ballistic performance in of solid rocket engine before a ignition test, optimizes the performance of the solid rocket engine, and reduces the development time and development 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 ...

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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 suitab

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