Ballistic performance calculation method in thrust termination pressure relief process of solid rocket engine

Abstract

The invention discloses a ballistic performance calculation method in a thrust termination pressure relief process of a solid rocket engine. The ballistic performance calculation method comprises thefollowing steps: establishing a solid engine physical model containing reverse spray pipe thrust termination; according to the solid engine physical model containing reverse spraying pipe thrust termination, solving and obtaining resultant thrust generated by the engine under given pressure intensity; and according to an engine gas generation and exhaust conservation equation, adopting a Runge-Kutta method to determine the pressure intensity of an engine combustion chamber and the change condition of the resultant thrust generated by the engine along with time. According to the method, the characteristics of the molded surface of the thrust termination reverse spraying pipe of the engine are combined, the ballistic performance in the thrust termination pressure relief process of the solidrocket engine is calculated according to the pneumatic parameter relation and the flow conservation equation, and the contradiction problem between the calculation precision and the complexity in theprior art is solved.

Description

technical field [0001] The invention belongs to the technical field of solid rocket motors, and in particular relates to a method for calculating the ballistic performance of a solid rocket motor in the process of thrust termination and pressure relief. Background technique [0002] The solid rocket motor has the advantages of simple structure, convenient use and maintenance, and is the most widely used power device in the field of tactical weapons. According to the energy management requirements of the overall use of missile weapons, it is necessary to use the anti-nozzle pressure relief device to achieve engine thrust termination in specific cases. After the engine thrust termination mechanism is opened, the change process of the internal ballistic performance of the engine has an important impact on the overall separation design of the missile, and is an important parameter in the overall design process. [0003] For the calculation of the internal ballistic performance ...

AI Technical Summary

Problems solved by technology

[0004] The technical solution of the present invention: the present invention combines the characteristics of the engine thrust termination reverse nozzle profile, according to the aerodynamic parameter relationship and the flow conservation equation, and based on theoretical analysis, establishes a calculation method for the internal ballistic performance of the solid rocket motor thrust termination pressure relief process, Solve the contradiction between calculation accuracy and complexity existing in the prior art

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