Formation parameter optimizing method and system of aircraft formation flight

Abstract

The invention discloses a formation parameter optimizing method and system of aircraft formation flight. The method includes the steps of obtaining a numerical value response face model of a wing aircraft aerodynamic force coefficient through a numerical value simulating calculation method, obtaining part of sample points in the numerical value simulating calculation method, conducting a formation flight wind tunnel test with the part of sample points as the test sample points to obtain test data, establishing a test response face model of the wing aircraft aerodynamic force coefficient according to the test data, establishing a hybrid response face model according to the numerical value response face model and the test response face model, conducting the formation parameter optimizing of aircraft formation flight on the hybrid response face model through an efficient global optimizing algorithm to obtain optimal aircraft formation position parameters. The numerical value simulating calculation method and the wind tunnel test method are combined, the data precision of the optimizing process is improved, and cost is reduced.

Description

technical field [0001] The invention relates to the technical field of aircraft formation flight, in particular to a formation parameter optimization method and system for aircraft formation flight. Background technique [0002] Increasing lift and reducing drag is the eternal pursuit of fluid mechanics researchers and aircraft designers, and drag reduction is also consistent with today's pursuit of environmental protection, fuel economy and other flight goals. Drag directly affects the load capacity and fuel carrying capacity of the aircraft, thus affecting the performance and economy of the aircraft. [0003] A pair of counter-rotating wake vortices will also appear at the wingtips during the flight of the aircraft. The wake vortex of an aircraft has been considered for a long time to have adverse effects on the aircraft and the aircraft following it. In fact, the wake vortex of the aircraft will form an upwash on the airflow in a certain area behind, such as image 3 As...

AI Technical Summary

Problems solved by technology

For the problem of formation flight, the advantages of numerical calculation are low cost and a large amount of data can be obtained, but the calculation accuracy of wake vortex is not high due to numerical dissipation and other reasons

The advantage of the wind tunnel test is that the data accuracy is high, but the cost is relatively high, a large amount of data cannot be obtained, and there are factors such as the interference of the wall and the support

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