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Iterative propulsion disturbance domain updating method for aircraft dynamic aerodynamic characteristic simulation

An update method and technology of aerodynamic characteristics, applied in special data processing applications, geometric CAD, sustainable transportation, etc., can solve problems such as large invalid calculations

Active Publication Date: 2020-10-30
BEIHANG UNIV
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0006] In view of this, the present invention provides an iterative propulsion disturbance domain update method for aircraft dynamic aerodynamic characteristics simulation to solve the problem of a large number of invalid calculations in existing aircraft dynamic aerodynamic characteristic numerical simulation methods

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  • Iterative propulsion disturbance domain updating method for aircraft dynamic aerodynamic characteristic simulation
  • Iterative propulsion disturbance domain updating method for aircraft dynamic aerodynamic characteristic simulation
  • Iterative propulsion disturbance domain updating method for aircraft dynamic aerodynamic characteristic simulation

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Embodiment 1

[0116] Embodiment 1: as figure 1 As shown, the above-mentioned iterative advancement method for updating the disturbance domain provided by the present invention specifically includes the following steps:

[0117] The first step: data read in.

[0118] The read-in data includes the grid of the aircraft flow field, the preset calculation domain, boundary conditions and calculation settings.

[0119] The second step: flow field initialization.

[0120] Flow field initialization is divided into two ways: initialization according to incoming flow conditions and initialization according to a given flow field. When initializing according to the incoming flow conditions, the conserved quantities of all grid cells in the preset computational domain are assigned as incoming flow values; when initialized according to a given flow field, the conserved quantities of all grid cells in the preset computational domain are assigned to is a given flow field value.

[0121] Step 3: Establis...

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Abstract

The invention discloses an iterative propulsion disturbance domain updating method for aircraft dynamic aerodynamic characteristic simulation. Aiming at the problem that a large amount of invalid calculation exists in an existing aircraft dynamic aerodynamic characteristic numerical simulation method, three kinds of dynamic calculation domains of unsteady, convection and viscosity are adopted, anda solving thought that only non-convergent unsteady units are solved and the viscosity effect is only considered in a local area is provided, wherein the unsteady dynamic calculation domain only comprises grid units which play a leading role in the unsteady effect at each physical moment; the convection dynamic calculation domain only comprises grid units which are disturbed in each iteration step and are not converged yet, the viscosity dynamic calculation domain only comprises grid units which play a leading role in the viscosity effect in the convection dynamic calculation domain, and thethree types of dynamic calculation domains can be updated in a self-adaptive mode in each iteration step. By avoiding invalid calculation in unsteady numerical simulation and reducing the number of iteration steps required for inner iteration to reach a convergence state, the calculation efficiency of aircraft dynamic aerodynamic characteristic numerical simulation can be remarkably improved.

Description

technical field [0001] The invention relates to the technical field of computational fluid dynamics, in particular to an iterative propulsion disturbance domain update method for aircraft dynamic aerodynamic characteristic simulation. Background technique [0002] Dynamic aerodynamic characteristics are key performance parameters in aircraft design. Thanks to the rapid development of computer hardware performance, unsteady flow numerical simulation has been widely used in the prediction of dynamic aerodynamic characteristics of various aircraft. However, due to the complexity of the flow problem, which leads to a large amount of calculation and low efficiency of the numerical simulation method, the numerical simulation of the dynamic aerodynamic characteristics of the aircraft still needs to consume a large amount of computing resources and a long solution period, and the computational efficiency of the numerical simulation is difficult to meet the increasing aerodynamic des...

Claims

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Application Information

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IPC IPC(8): G06F30/15G06F30/28
CPCG06F30/15G06F30/28Y02T90/00
Inventor 蒋崇文胡姝瑶高振勋李椿萱
Owner BEIHANG UNIV
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