Solid rocket engine jet pipe material parameter sensitivity calculation method

A technology for engine nozzles and solid rockets, applied in calculation, computer-aided design, design optimization/simulation, etc., can solve the problem of few global sensitivity analysis methods, simplify the process of sensitivity analysis, reduce the amount of calculation, and improve analysis efficiency Effect

Pending Publication Date: 2022-07-12
HEFEI UNIV OF TECH
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  • Abstract
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  • Application Information

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Problems solved by technology

However, in the field of material parameter sensitivity of the solid rocket motor nozzle, the global sensitivity analysis method is rarely applied

Method used

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  • Solid rocket engine jet pipe material parameter sensitivity calculation method
  • Solid rocket engine jet pipe material parameter sensitivity calculation method
  • Solid rocket engine jet pipe material parameter sensitivity calculation method

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Embodiment Construction

[0049] The present invention will be further described below with reference to the accompanying drawings and specific analysis cases.

[0050] In this embodiment, a method for calculating the sensitivity of the material parameters of a solid rocket motor nozzle, such as figure 1 shown, including:

[0051] First, the axisymmetric section of the solid rocket motor nozzle is intercepted to build a simulation model. The model is as follows figure 2 As shown, Abaqus / Standard software is used for finite element simulation of the model. The specific operations include: setting material properties in the property module; meshing the model in the mesh module, and the selected mesh element is CAX4T; in the loading module, imposing boundary condition constraints on the model, including the model shell Perform fixed constraints and apply discrete pressure fields to the inner wall of the model; in the interaction module, apply discrete temperature fields and convective heat transfer coe...

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Abstract

The invention discloses a sensitivity calculation method for material parameters of a solid rocket engine jet pipe, which comprises the following steps of: 1, performing complete thermal coupling analysis on the engine jet pipe to obtain the temperature and stress peak moment tmax of the engine jet pipe in a working state; 2, performing random valuing on existing material parameters to generate N groups of parameter samples; 3, importing the parameter sample into the simulation model, performing complete thermal coupling analysis on the engine jet pipe, and obtaining equivalent stress and circumferential stress at a stress extreme point at a tmax moment as output response; 4, solving conditional expectations of different parameter samples and corresponding output responses through a regression fitting method; and 5, solving the sensitivity of different parameters through a variance-based global sensitivity analysis method. According to the method, the influence degree of various material parameters on the stress extreme value can be effectively quantified, so that technical support is provided for material optimization design of the rocket nozzle.

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 equivalent stress sensitivity of material parameters at their extreme stress values ​​during the working process of a solid rocket motor nozzle, and a loop of material parameters at their extreme stress values. Calculation method of directional stress sensitivity. Background technique [0002] Composite materials have the advantages of light weight, high strength and corrosion resistance, and are widely used in aerospace structures. The solid rocket motor nozzle is a key component of a solid missile or a power unit on a spacecraft, and the performance requirements for the composite materials used are more stringent, including the requirements that the materials used can withstand higher temperature burning, and withstand solid-liquid particles. High-speed flushing, etc. At present, the materials used for rocket engine nozzles...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F30/15G06F30/23G06F119/08G06F119/14
CPCG06F30/15G06F30/23G06F2119/14G06F2119/08Y02T90/00
Inventor 郑昌军许凯余志强张光喜生志斐校金友王帅
Owner HEFEI UNIV OF TECH
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