Multi-disciplinary integrated design optimization method and system for carrier rocket

Abstract

The invention provides a multi-disciplinary integrated design optimization system for a carrier rocket. The multi-disciplinary integrated design optimization system comprises a system analysis module, an optimization model module and an optimization solving module, wherein the three modules are carried out according to a sequence in a multi-disciplinary integrated design optimization process of the carrier rocket, namely the system analysis module is firstly executed, then the optimization model module is executed and the optimization solving module is lastly executed. A multi-disciplinary integrated design optimization method for the carrier rocket comprises the following three steps: step 1, establishing the system analysis module of the carrier rocket; step 2, establishing a multi-disciplinary optimization model of the carrier rocket; step 3, optimizing and solving. According to the multi-disciplinary integrated design optimization system and method for the carrier rocket, synergistic effects generated by mutual effects of various disciplines are utilized sufficiently to obtain the whole optimal solution of a carrier rocket system; the design period is shortened and the cost is reduced.

Description

technical field [0001] The invention relates to a multidisciplinary comprehensive design optimization method and system for a carrier rocket, which can quickly and effectively realize the overall design of the carrier rocket, and belongs to the technical field of aerospace. Background technique [0002] A country's ability to enter space largely determines its space activity capabilities and the level of space application development. The world's major aerospace powers measure their space technology level by their ability to enter space. The development scale and technical level of the launch vehicle support the ability to enter space. [0003] A launch vehicle is a complex engineering system involving multiple disciplines, such as geometric master model, power, aerodynamics, space flight mechanics, heat transfer / thermal protection system, structure, control, load, ballistic, etc., and each discipline is coupled and influenced by each other. In the traditional overall desig...

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Problems solved by technology

[0005] The purpose of the present invention is to provide a method and system for multidisciplinary comprehensive design optimization of launch vehicles, so as to overcome the shortcomings of traditional launch vehicle design methods such as low design efficiency, long cycle, error-prone, and failure to obtain global optimal solutions;

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