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A parametric modeling method of a finite element model of a launch vehicle structure

A launch vehicle and model parameter technology, applied in the aerospace field, can solve the problems of time-consuming, labor-intensive and inefficient models

Active Publication Date: 2019-02-12
BEIJING INSTITUTE OF TECHNOLOGYGY
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Problems solved by technology

[0005] In order to solve the problem of time-consuming, labor-intensive and low-efficiency in manually establishing models when performing finite element simulation analysis on the launch vehicle structure

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  • A parametric modeling method of a finite element model of a launch vehicle structure
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  • A parametric modeling method of a finite element model of a launch vehicle structure

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Embodiment 1

[0055] A parametric modeling method for a launch vehicle structure finite element model disclosed in this embodiment, the specific implementation method is as follows:

[0056] Step 1: Define the "I-II-III-IV" rocket coordinate system.

[0057] Adopt the "I-II-III-IV" rocket coordinate system, that is, the Cartesian coordinate system of the right-hand rule, such as figure 2 shown. The positive direction of the y-axis of the coordinate system coincides with the quadrant line of the rocket coordinate system III, the positive direction of the z-axis of the coordinate system coincides with the quadrant line of the rocket coordinate system II, and the positive direction of the x-axis of the coordinate system follows the right-hand rule and points to the negative direction of the rocket arrow axis, that is, the fairing points The direction of the tail section of the rocket, the origin of the coordinate system is located at the theoretical cusp of the von Karman curve of the fairin...

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Abstract

The invention discloses a parametric modeling method of a finite element model of a launch vehicle structure, belonging to the technical field of aerospace. The realization method of the invention comprises defining a rocket coordinate system, establishing a model material database according to a model material table, and establishing a lumped mass-beam or a lumped mass-shell finite element modelof acore stage and a booster structure section according to the model data table; establishing a lumped mass-beam model fo the effective load on the basis of the core stage finite element model, through the establishment of the finite element model of the binding connection structure, connecting the finite element model of the core stage including the payload model and the finite element model ofthe booster structure to establish the finite element model of the rocket structure excluding the engine, and realizing the parametric modeling of the finite element model of the launch vehicle structure by establishing the mass center position and thrust acting point models of the core stage and the booster engine. The method of the invention contributes to the rapid design of the rocket structure and the optimization design of the structural parameters, and further solves the technical problems related to the rocket dynamics field.

Description

technical field [0001] The invention relates to a parameterized establishment method of a finite element model of a carrier rocket structure, belonging to the technical field of aerospace. Background technique [0002] The launch vehicle is the most important basic vehicle for the development of space technology of all space countries in the world, including my country. The analysis of the structural characteristics of the launch vehicle is one of the key links in its development process. With the development of the structure system of the launch vehicle toward diversification, large-scale, and complexity, the analysis of the dynamic response and dynamic characteristics of the structure system has become an indispensable part in the development process. [0003] The establishment of a structural dynamics finite element model of a launch vehicle is the basis and premise for the analysis of its structural dynamic response and dynamic characteristics. However, the traditional ...

Claims

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Application Information

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IPC IPC(8): G06F17/50
CPCG06F30/15G06F30/23Y02T90/00
Inventor 刘莉邵玉佩袁赫王强
Owner BEIJING INSTITUTE OF TECHNOLOGYGY
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