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Simulation method of aerodynamic parameters of canard configuration aircraft and terminal equipment

A technology of aerodynamic parameters and simulation methods, applied in the field of aircraft, can solve the problems of high cost and long cycle of wind tunnel experiments, and achieve the effect of short cycle and reduced cost

Active Publication Date: 2017-12-08
PEOPLES LIBERATION ARMY ORDNANCE ENG COLLEGE
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Problems solved by technology

[0003] Compared with the unguided rocket, the change of the canard and the tail will cause a large change in its aerodynamic characteristics. In order to accurately obtain the aerodynamic characteristics of the canard-guided rocket, the existing method for calculating the aerodynamic characteristics of the rocket is usually Wind tunnel experiments are used, but wind tunnel experiments are expensive and take a long time

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  • Simulation method of aerodynamic parameters of canard configuration aircraft and terminal equipment

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Embodiment Construction

[0030] In the following description, specific details such as specific system structures and technologies are presented for the purpose of illustration rather than limitation, so as to thoroughly understand the embodiments of the present invention. It will be apparent, however, to one skilled in the art that the invention may be practiced in other embodiments without these specific details. In other instances, detailed descriptions of well-known systems, devices, circuits, and methods are omitted so as not to obscure the description of the present invention with unnecessary detail.

[0031] It should be understood that when used in this specification and the appended claims, the term "comprising" indicates the presence of described features, integers, steps, operations, elements and / or components, but does not exclude one or more other features. , whole, step, operation, element, component and / or the presence or addition of a collection thereof.

[0032] It should also be und...

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Abstract

The invention belongs to the technical field of aircrafts, and provides a simulation method of aerodynamic parameters of a canard configuration aircraft and terminal equipment. The method includes the steps that a three-dimensional model of the canard configuration aircraft is established; meshing is conducted on the surface of the three-dimensional model of the canard configuration aircraft and a flow field domain corresponding to the three-dimensional model of the canard configuration aircraft, and the volume mesh of the flow field domain is obtained according to the mesh of the surface of the three-dimensional model and the mesh of the outer surface of the flow field domain; a k-epsilon turbulent mathematic model for simulating air flow in the volume mesh is established; simulation solving is conducted on the aerodynamic parameters of the canard configuration aircraft through the k-epsilon turbulent mathematic model. According to the scheme, the three-dimensional model of the canard configuration aircraft is established, then the volume mesh of the corresponding flow field domain is obtained according to the three-dimensional model of the aircraft, and air in the volume mesh around the aircraft is simulated through the turbulent mathematic model to obtain the aerodynamic parameters of the aircraft. The simulation method is short in cycle, low in cost and precise.

Description

technical field [0001] The invention belongs to the technical field of aircraft, and in particular relates to a method for simulating aerodynamic parameters of an aircraft with a canard layout and a terminal device. Background technique [0002] With the development of ballistic information acquisition technology and ballistic deviation elimination technology, rockets have gradually developed from no control or simple control to full ballistic guidance control. At the same time, the strike accuracy of rockets has also gradually improved. The prerequisite for rockets to achieve precise strikes is to have a good aerodynamic shape. Among the existing guided rockets, the more widely used aerodynamic shape is to add canards to the front of the projectile and use a straight tail at the tail of the projectile. [0003] Compared with the unguided rocket, the change of the canard and the tail will cause a large change in its aerodynamic characteristics. In order to accurately obtain ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F17/50
CPCG06F30/15G06F30/17G06F30/20Y02T90/00
Inventor 方丹陈永超高敏王毅陶贵明徐帅张宽桥
Owner PEOPLES LIBERATION ARMY ORDNANCE ENG COLLEGE
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