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A Parametric Design Method for Small Launch Vehicle Structure

A technology for launch vehicles and structural parameters, applied in computer-aided design, calculation, electrical digital data processing, etc., can solve rare problems, and achieve the effect of stable program, high modeling efficiency and clear process

Active Publication Date: 2019-07-09
NAT UNIV OF DEFENSE TECH
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  • Description
  • Claims
  • Application Information

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Problems solved by technology

If the parametric design of the small launch vehicle structure can be realized, the design efficiency will be greatly improved. At present, there are not many researches on the parametric design method of the rocket structure at home and abroad.

Method used

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  • A Parametric Design Method for Small Launch Vehicle Structure
  • A Parametric Design Method for Small Launch Vehicle Structure
  • A Parametric Design Method for Small Launch Vehicle Structure

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Embodiment Construction

[0046] The specific implementation manner of the present invention will be further described below in conjunction with the accompanying drawings.

[0047] A kind of parametric design method of small launch vehicle structure of the present invention, comprises the following steps:

[0048] Step 1: Analyze the components of the rocket, including the structural features of the fairing, cabin, and wings, extract characteristic parameters, determine the modeling ideas, and establish parametric models of the fairing, cabin, and wings respectively.

[0049] Step 2: Make the user interface of rocket parametric design in UG software, including menus and dialog boxes, such as figure 1 shown. Then the dialog box C++ template file is automatically generated.

[0050]Step 3: Create the NX Open project in Visual Studio 2010, and open the C++ template file generated in the second step. Add the modeling procedure in the C++ template file.

[0051] Step 4: Compile and run to obtain the dyn...

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Abstract

The invention provides a structure parametric design method of a small-size launch vehicle, including the following steps: firstly, extracting characteristic parameters, determining a modeling approach and building parametric models of a fairing, a body tube section and a fin separately; secondly, making a user interface and generating a dialog box C++ template file automatically; thirdly, creating an NX Open Project in Visual Studio 2010 and writing a modeling program; fourthly, compiling and running to acquire a dynamic link library file; fifthly, performing parameter input on the user interface, and clicking "ok" to acquire a corresponding structure model; sixthly, creating an NX Open Project in Visual Studio 2010 and adding an automatic assembly program in a C++ source file; seventhly, compiling and running to acquire a dynamic link library file; and eighthly, executing the dynamic link library file in UG to acquire an automatic assembly model. The invention has the advantage of significantly improving efficiency of the structure design of the small-size launch vehicle, and the method adopted can be extended to parametric design researches of other rockets or aircrafts.

Description

technical field [0001] The invention belongs to the field of rocket overall structure design, and in particular relates to a parametric design method of rocket structure. Background technique [0002] Today, rockets are the most effective and important vehicle for human beings to enter space, whether it is for high-altitude scientific experiments or space-oriented commercial development. With the help of rockets with a rich spectrum, people can send various payloads with different functions to the predetermined location to carry out tasks. In recent years, small launch vehicles have become a hot spot in the launch market of various countries due to their characteristics of fast response, low cost, and dual-use for military and civilian use. Facing many different missions also diversifies the design of small launch vehicles. In the scheme stage of rocket design, the overall structure design of the rocket is a work of great significance in the rocket research and development...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G06F17/50
CPCG06F30/15G06F2113/28
Inventor 江振宇王晓伟杨枝山孙乐园黄振新
Owner NAT UNIV OF DEFENSE TECH
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