Formation parameter optimizing method and system of aircraft formation flight

A formation flight and parameter technology, which is applied in the field of aircraft formation flight, can solve the problems of low calculation accuracy of wake vortex, interference bracket, interference, etc., and achieve the goal of overcoming cave wall interference and bracket interference, improving optimization accuracy, and improving lift-drag characteristics Effect

Active Publication Date: 2017-12-19
INST OF HIGH SPEED AERODYNAMICS OF CHINA AERODYNAMICS RES & DEV CENT
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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

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  • Formation parameter optimizing method and system of aircraft formation flight
  • Formation parameter optimizing method and system of aircraft formation flight
  • Formation parameter optimizing method and system of aircraft formation flight

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Embodiment Construction

[0048] The following will clearly and completely describe the technical solutions in the embodiments of the present invention with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only some, not all, embodiments of the present invention. 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.

[0049] The object of the present invention is to provide a formation parameter optimization method and system for aircraft formation flight with high data accuracy and low cost.

[0050] In order to make the above objects, features and advantages of the present invention more comprehensible, the present invention will be further described in detail below in conjunction with the accompanying drawings and specific embodiments.

[0051] Such as figure 1 As show...

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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...

Claims

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Application Information

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IPC IPC(8): G06F17/50
CPCG06F30/20Y02T90/00
Inventor 陶洋熊能于志松林俊高荣钊王志宾王晓冰刘志勇张兆郭民彭超
Owner INST OF HIGH SPEED AERODYNAMICS OF CHINA AERODYNAMICS RES & DEV CENT
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