Mass parameter estimation method of carrier rocket

A quality parameter, launch vehicle technology, applied in the aerospace field, can solve the problems of inaccuracy and large amount of calculation

Active Publication Date: 2018-11-06
BEIHANG UNIV
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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 mass 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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  • Mass parameter estimation method of carrier rocket
  • Mass parameter estimation method of carrier rocket
  • Mass parameter estimation method of carrier rocket

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Embodiment Construction

[0073] 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 some 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.

[0074] 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 mass parameter estimation method of a carrier rocket, and belongs to the field of aerospace technology. The technical problems of large calculated amount and inaccuracy in the existing mass parameter selection are solved. The mass parameter estimation method comprises the following steps: performing task index analysis, selecting an overall scheme, and determining systemparameters; determining design variables, optimization objectives and constraint conditions, and establishing a corresponding mathematical model via a mass parameter model, wherein the mass parametermodel comprises a sequential calculation propellant mass fraction calculation module, a coefficient Ki calculation module, an inter-stage mass ratio calculation module and an overall mass calculationmodule; performing mass parameter modeling on the carrier rocket, compiling an integrated calculation program, and giving an input and output file; selecting and inputting an optimization algorithm inan optimizer, and selecting the mass parameter model to obtain a reference design scheme. By adoption of the carrier rocket mass parameter estimation method disclosed by the invention, the iterativedesign times of the carrier rocket are reduced, and the method is simple in process, small in calculated 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 mass 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 has 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 for large-scale data to know the quality parameter selection of the launch vehicle. Researchers can only compare with other types of launch vehicles of the same category, so they cannot compare Accurately narrow the range of input variables for quality parameter selection as much...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F17/50G06F17/11
CPCG06F17/11G06F30/15G06F30/20
Inventor 张晓天王鹏程王逸宁李晓刚蔡国飙
Owner BEIHANG UNIV
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