Method for estimating size parameter of carrier rocket

A launch vehicle and size technology, applied in the field of aerospace, can solve problems such as inaccuracy and large amount of calculation

Active Publication Date: 2018-11-06
BEIHANG UNIV
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  • Abstract
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  • Application Information

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Problems solved by technology

[0004] The purpose of the present invention is to provide a method for estimating the size parameters of a launch vehicle, so as to solve the technical problems of large amount of calculation and inaccuracy in the selection of existing parameters

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  • Method for estimating size parameter of carrier rocket
  • Method for estimating size parameter of carrier rocket
  • Method for estimating size parameter of carrier rocket

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Embodiment Construction

[0070] The technical solutions of the present invention will be clearly and completely described below in conjunction with the accompanying drawings. Apparently, the described embodiments are part of the embodiments of the present invention, but not all of them. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without making creative efforts belong to the protection scope of the present invention.

[0071] In the description of the present invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer" etc. The indicated orientation or positional relationship is based on the orientation or positional relationship shown in the drawings, and is only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the referred device or element must have a specific orientation, ...

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Abstract

The invention discloses a method for estimating the size parameter of a carrier rocket, belongs to the technical field of aerospace and aims to solve the technical problem of large calculation amountand inaccuracy during conventional size parameter selection. The method for estimating the size parameter comprises the following steps of: carrying out task index analysis, selecting an overall scheme and determining each system parameter; determining design variables, an optimization target and constraint conditions and building a corresponding mathematical model on the basis of a size parametermodel, wherein the size model comprises a part size calculating module, an engine size calculating module and an overall size calculating module for sequential calculation; carrying out size parametric modeling on the carrier rocket, writing an integrated calculation program and giving input and output files; selecting an optimization algorithm, inputting to an optimizer and selecting a size parametric model to obtain a reference design scheme. The method disclosed by the invention has the advantages that the iterative design times of the carrier rocket in the overall scheme stage is reduced;and the method is simple in process, small in calculation amount and high in efficiency.

Description

technical field [0001] The invention relates to the field of aerospace technology, in particular to a method for estimating size parameters of a launch vehicle. Background technique [0002] The degree of development in the aerospace field is one of the important criteria to measure a country’s space exploration capabilities and determine whether its comprehensive national strength is strong; the multidisciplinary design and optimization of launch vehicles carried out at home and abroad currently requires a large amount of calculation, a long time, and a complex system. Before parameter selection, a benchmark design scheme needs to be given, and the products of aerospace systems cannot provide references to large-scale data to know the size parameter selection of the launch vehicle. Researchers can only compare with other types of launch vehicles of the same category, so they cannot compare Accurate, narrow as possible input variable range for size parameter selection. [0...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F17/50
CPCG06F30/15Y02T10/40
Inventor 张晓天王鹏程李萌王逸宁蔡国飙
Owner BEIHANG UNIV
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