Catapult inner trajectory simulation analysis system and method and electronic equipment

Abstract

The invention discloses a secondary combustion-considered catapult inner trajectory simulation analysis system and method and electronic equipment, and the system comprises a fuel gas generating agent thermodynamic calculation module which is used for calculating thermodynamic property parameters and combustion product components on each section in a rocket engine combustion chamber according to different charging formulas to obtain a first calculation result; a reverse design module which is used for solving the optimal charge arrangement and distribution condition to obtain a second calculation result; and a secondary combustion inner trajectory module which is used for solving a gas emitter inner rule parameter, a guide cylinder inner rule parameter and a missile motion rule parameter according to the first calculation result and the second calculation result in combination with auxiliary parameters. The performance parameters in the catapult inner trajectory fuel gas generator and the performance parameters in the guide cylinder are calculated more accurately through the catapult inner trajectory simulation system considering secondary combustion, so that the research and development period of a solid rocket engine is greatly shortened; meanwhile, the calculation precision of the related inner trajectory part is improved.

Description

technical field [0001] The invention belongs to the technical field of solid rocket motors, and in particular relates to a simulation analysis system, method and electronic equipment for an ejection internal trajectory considering secondary combustion. Background technique [0002] As an important missile launch method, ejection internal ballistic is widely used in missile launch systems. At present, there are mainly the following two technologies for the simulation calculation of the ejection interior ballistic. [0003] One is based on the classic zero-position ballistic technology, which is mainly based on thermodynamics, and solves the ordinary differential equation with the instantaneous average gas parameters to obtain the flow characteristic parameters in the high-pressure chamber and the low-pressure chamber. The biggest advantage of this technical method is the simplicity of the equation and the ease of calculation. Although this method cannot describe the flow ph...

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Problems solved by technology

However, the calculation period of this method is long and the calculation amount is huge. It usually takes hundreds of hours to complete the simulation calculation of a model. As far as the current level of computer software and hardware is concerned, it often cannot meet the progress requirements of the projectile internal ballistic engineering development.

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