Online integrated aircraft aerodynamic modeling system

Abstract

The invention discloses an online integrated aircraft aerodynamic modeling system, and relates to the technical field of aircraft modeling. The system comprises: a source data module provided with a data supplement port for supplementing data in a multi-source data set; a data accounting module used for obtaining an aircraft prototype application data set; a cube construction module used for constructing a complete data cube of the aircraft; a model construction module used for constructing an aircraft aerodynamic force model after cutting, meshing data, incremental calculation and incrementalfitting are carried out on the complete data cube of the aircraft; and a data storage and online visualization module used for storing and displaying the data. The system can meet accounting requirements under aircraft coupling characteristics under the limitation of test equipment, solves the problem that modeling cannot be performed due to complex, repeated and missing data under multi-source data, and meets related requirements and difficulties of automatic modeling, traceability, comparable analysis and the like of an integrated aircraft along with a research period.

Description

technical field [0001] The invention relates to the technical field of aircraft system modeling, in particular to an online integrated aircraft aerodynamic modeling system. Background technique [0002] Integrated aircraft refers to airframe / propulsion integrated aircraft powered by air-breathing scramjet technology. The body-propulsion coupling of an integrated aircraft brings a series of challenges to performance evaluation and control modeling. The literature "He Yuanyuan, Ni Hongli, Le Jialing. Aerodynamic-propulsion performance evaluation of integrated hypersonic vehicle [J]. Experimental Fluid Mechanics, 2007, (02): 63-67." Introduces a combination of CFD and wind tunnel test evaluation Approximation methods and procedures for aerodynamic-propulsion performance of integrated aircraft. The paper "Wu Yingchuan, He Yuanyuan, He Wei, et al. Research progress of air-breathing hypersonic vehicle airframe propulsion integration technology [J]. Acta Aeronautics Sinica, 2015,...

AI Technical Summary

Problems solved by technology

[0005] (1) Modeling relies on a complete aerodynamic data set, but the data set increases with the entire long-term period of aircraft research, and the data at different stages of the research may come from multiple sources at multiple levels such as engineering estimation, CFD simulation, wind tunnel test, and flight test Data, the aerodynamic data set has the problem of complex, repetitive and missing data that cannot be modeled

[0006] (2) The integrated aircraft is faced with multi-coupling problems, and at the same time, it is difficult to meet the calculation needs of aerodynamic forces due to the limitations of equipment and test conditions

[0007] (3) The data source, process, and results of the modeling change with the change of the data set, facing difficulties in storage, traceability, and comparative analysis

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