An iterative propulsion disturbance domain update method for the simulation of dynamic aerodynamic characteristics of aircraft

An update method and aerodynamic characteristics technology, applied in special data processing applications, geometric CAD, design optimization/simulation, etc., can solve problems such as large invalid calculations, achieve the effect of reducing memory requirements and improving computing efficiency

Active Publication Date: 2022-04-22
BEIHANG UNIV
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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

Method used

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  • An iterative propulsion disturbance domain update method for the simulation of dynamic aerodynamic characteristics of aircraft
  • An iterative propulsion disturbance domain update method for the simulation of dynamic aerodynamic characteristics of aircraft
  • An iterative propulsion disturbance domain update method for the simulation of dynamic aerodynamic characteristics of aircraft

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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 update method for the simulation of the dynamic aerodynamic characteristics of an aircraft. Aiming at the problems of a large number of invalid calculations in the existing numerical simulation methods of the dynamic aerodynamic characteristics of the aircraft, three types of dynamic calculation domains, namely unsteady, convective and viscous, are adopted. A solution idea that only solves the unconverged unsteady element and only considers the viscous effect in the local area is proposed. The unsteady dynamic calculation domain only includes the grid units whose unsteady effect plays a leading role at each physical moment, the convective dynamic calculation domain only includes the grid units that are disturbed in each iteration step and the solution has not yet converged, and the viscous dynamic calculation domain only includes Containing grid cells that dominate the viscous effects in the flow dynamic computational domain, the three types of dynamic computational domains are adaptively updated at each iteration step. By avoiding invalid calculation in unsteady numerical simulation and reducing the number of iteration steps needed for internal iteration to reach a convergent state, the invention can significantly improve the calculation efficiency of the numerical simulation of the dynamic aerodynamic characteristics of the aircraft.

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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Patent Type & Authority Patents(China)
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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