Time parallel disturbance domain updating method for aircraft dynamic characteristic simulation

A technology of dynamic characteristics and update methods, applied in the fields of instruments, electrical digital data processing, geometric CAD, etc., can solve problems such as acceleration, achieve the effect of improving computing efficiency and avoiding invalid computing

Active Publication Date: 2022-04-12
BEIHANG UNIV
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  • Claims
  • Application Information

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Problems solved by technology

[0005] In view of this, the present invention provides a time-parallel disturbance domain update method for aircraft dynamics simulation, to solve the problem that the traditional method of aircraft dynamics prediction is limited by the time-dimensional sequential advance solution requirements and has an acceleration bottleneck

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  • Time parallel disturbance domain updating method for aircraft dynamic characteristic simulation
  • Time parallel disturbance domain updating method for aircraft dynamic characteristic simulation
  • Time parallel disturbance domain updating method for aircraft dynamic characteristic simulation

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Embodiment 1

[0155] Figure 2a is a schematic diagram of the traditional time sequence advancing method provided by the present invention; Figure 2b is a schematic diagram of the time parallel method provided by the present invention.

[0156] In the traditional method, parallel computing can only divide the calculation amount according to the grid, and one iteration can only calculate the flow field at one physical moment, and the physical moment t 0 to t n The solution of must be solved sequentially, such as Figure 2a shown. In the method of the present invention, the parallel calculation can not only divide the calculation amount according to the grid, but also solve the flow field at multiple physical moments in one iteration at the same time. t 0 to t n can be solved simultaneously, such as Figure 2b shown.

[0157] image 3 It is an evolution process diagram of the transient flow field and the dynamic calculation domain for solving the unsteady flow around a transonic ...

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Abstract

The invention relates to the technical field of computational fluid mechanics, and provides a time parallel disturbance domain updating method for aircraft dynamic characteristic simulation. The method comprises the following steps: reading in data; a Chebyshev conversion matrix component is obtained; initializing a flow field; establishing a dynamic computational domain; solving flow control equations of all time layers in parallel in a dynamic calculation domain; updating the dynamic computing domain; judging whether the parallel solution in the current time period converges or not and whether the calculation is completed or not, if yes, skipping to the dynamic calculation domain to solve all time layers in parallel, and entering the next iteration step of the parallel solution in the current time period; if the solution at the current moment is converged and the calculation is not completed, jumping to flow field initialization, and entering the solution of the next time period; otherwise, outputting a result. According to the method, invalid calculation caused by the adoption of a static calculation domain is avoided, the problem that acceleration bottleneck exists due to limitation of time dimension sequential propulsion solving requirements is solved, and the calculation efficiency is remarkably improved.

Description

technical field [0001] The invention relates to the technical field of computational fluid dynamics, in particular to a time-parallel disturbance domain update method for aircraft dynamic characteristic simulation. Background technique [0002] High speed and high maneuverability have always been the performance characteristics pursued by modern aircraft research and development. During high-speed maneuvering flight, complex flow phenomena lead to aerodynamic effects far beyond those expected in a steady state, and even endanger flight safety. Therefore, accurate prediction of aircraft dynamic characteristics is indispensable for the design of aircraft aerodynamics and control systems. [0003] Computational fluid dynamics numerical simulation based on the second-order backward difference dual-time step method is currently the mainstream method for predicting the dynamic characteristics of aircraft. This method is a class of numerical methods that must advance the solution...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F30/15G06F30/23G06F113/08
CPCG06F30/15G06F30/23G06F2113/08
Inventor 蒋崇文胡姝瑶高振勋许晨豪李椿萱
Owner BEIHANG UNIV
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