Method and system for determining segmented double-combustion quick-charge explosive combustion surface of solid rocket engine

Abstract

The invention provides a method and a system for determining a segmented double-combustion-quick-charge explosive combustion surface of a solid rocket engine. The method comprises the following steps:giving an initial charging three-dimensional configuration of the engine and axial positions of high and low combustion speed interfaces of the initial charging three-dimensional configuration; meshing the cube containing the initial charge three-dimensional configuration of the whole engine, and determining the attribute of each mesh; determining high and low combustion speed initial combustionsurface node sets according to the axial positions of the high and low combustion speed interfaces; carrying out combustion surface interference judgment based on the combustion rate ratio of the high-combustion-rate charge to the low-combustion-rate charge and the minimum distance from the node at the axial position of the high-combustion-rate interface to the high-combustion-rate initial combustion surface point set and the low-combustion-rate initial combustion surface point set; and introducing a virtual combustion surface, correcting the initial combustion surface node sets of the high combustion speed and the low combustion speed, and calculating the combustion surface by adopting a minimum distance function method to respectively obtain the change rules of the charging combustion surfaces of the high combustion speed and the low combustion speed. According to the method, the calculation complexity of the combustion surface is reduced, and invalid calculation of a non-interference area is avoided.

Description

technical field [0001] The invention relates to the technical field of determining the burning surface of a solid rocket motor, in particular to a method and system for determining the burning surface of a solid rocket motor with a segmented double-burning rate charge. Background technique [0002] Determination of burning surface is used to determine the change law of the burning surface area of ​​the charge with the burning time during the burning process. The accuracy of determining the burning surface directly affects the prediction accuracy of the internal ballistic performance of the engine. It is the basis of the internal ballistic design of the engine and has always played an important role in the design of solid rocket motors. [0003] In the design process of a single-chamber dual-propulsion engine, in order to ensure the thrust ratio between the boost stage and the cruising stage, the idea of ​​matching high and low burning rates is often used to design the charge...

AI Technical Summary

Problems solved by technology

[0008] Aiming at the problem that the determination of the burning surface of the double-burning-velocity charge of the solid rocket motor in series depends on the extraction of the dynamic burning surface, which has poor versatility and a large amount of calculation, the present invention provides a method for determining the burning surface of the double-burning-velocity charge of the solid rocket motor and The system, based on the assumption of a fixed burning rate ratio, introduces a virtual initial burning surface, proposes an interface processing method, realizes the preprocessing of the double burning rate charge configuration interference process, completes the decoupling of the calculation process of different charge burning surfaces, and pushes the parallel layer The theory is applied to the calculation of high and low burning rate charges, which effectively solves the problem of determining the burning surface of single-chamber dual-thrust solid rocket motors with dual burning rates.

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