Supersonic thrust spray pipe reverse design method based on maximum thrust theory

Abstract

The invention discloses a supersonic thrust nozzle inverse design method based on a maximum thrust theory, which comprises the following steps of: presetting physical parameters of a core point, and further determining the physical parameters and a geometric position on a left-hand characteristic line passing through the core point; according to the nozzle inlet parameter distribution and the corepoint parameter, calculating by adopting a whirl characteristic line method and an iterative method to obtain an initial expansion section, and determining a nozzle inlet and expansion surface influence domain according to the inlet parameter and the initial expansion section; determining the last two characteristic lines emitted by the upper expansion surface and the lower expansion surface of the influence domain, and obtaining an intersection point which is a characteristic line intersection point; connecting the core point to the feature line intersection point; according to the law of conservation of flow, the inlet influence domain and the left-hand characteristic line passing through the core point, determining the upper wall surface profile of the thrust nozzle to be designed by adopting a spiral characteristic line method; and determining a lower wall surface profile to finish the design of the thrust nozzle. According to the invention, the performance is maximized under thecondition of meeting geometric and aerodynamic constraint conditions, and the fusion of the nozzle and the fuselage of the aircraft is better.

Description

technical field [0001] The invention belongs to the technical field of scramjet thrust nozzles, and in particular relates to a supersonic thrust nozzle reverse design method based on the maximum thrust theory. Background technique [0002] Due to its simple structure, light weight and high speed, scramjets have become the main power components of air-breathing hypersonic vehicles. Generally speaking, a scramjet is composed of key components such as an intake port, an isolation section, a combustion chamber, and a tail nozzle. Among them, the tail nozzle is an important part of the scramjet, and its performance will directly affect the overall performance of the engine and the stable operation of the engine. Relevant literature shows that when the scramjet works above Ma6, the nozzle produces more than 70% of the thrust. It can be seen that the design of the nozzle is very important for the scramjet and the combined cycle engine with the scramjet as the core. [0003] In o...

AI Technical Summary

Problems solved by technology

However, these forward design methods are greatly affected by the initial expansion section of the nozzle inlet, and repeated iterative calculations are required when using the maximum thrust theory, which increases the complexity of the design, and more importantly, it cannot optimize the performance of the nozzle

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