A Time-Parallel Disturbance Domain Update Method for Simulation of Aircraft Dynamic Characteristics

A technology of dynamic characteristics and updating methods, which is applied in the directions of instruments, geometric CAD, design optimization/simulation, etc., can solve problems such as acceleration, achieve the effect of improving computing efficiency and avoiding invalid calculations

Active Publication Date: 2022-06-17
BEIHANG UNIV
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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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  • A Time-Parallel Disturbance Domain Update Method for Simulation of Aircraft Dynamic Characteristics
  • A Time-Parallel Disturbance Domain Update Method for Simulation of Aircraft Dynamic Characteristics
  • A Time-Parallel Disturbance Domain Update Method for Simulation of Aircraft Dynamic Characteristics

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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 It 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. t 0 to t n must be solved in order, 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 fields of multiple physical moments simultaneously in one iteration. t 0 to t n can be solved simultaneously, such as Figure 2b shown.

[0157] image 3 It is the evolution process diagram of the transient flow field and the dynamic calculation domain for solving the unsteady flow around the transonic airfoil by using 24 threads in parallel...

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Abstract

The invention relates to the technical field of computational fluid dynamics, and provides a time-parallel disturbance domain update method for aircraft dynamic characteristic simulation. The method includes: reading in data; obtaining the Chebyshev transformation matrix components; initializing the flow field; establishing a dynamic calculation domain; solving the flow control equations of all time layers in parallel in the dynamic calculation domain; updating the dynamic calculation domain; judging whether the parallel solution in the current time period converges, Whether the calculation is completed, if it converges, jump to the dynamic calculation domain to solve all time layers in parallel, and enter the next iterative step of the parallel solution in the current time period; if the solution at the current moment has converged and the calculation is not completed, then jump to flow field initialization , enter the solution of the next time period; otherwise, output the result. The invention avoids the invalid calculation caused by adopting the static calculation field, solves the problem of acceleration bottleneck limited by the time dimension sequential advance solution requirement, and significantly improves the calculation efficiency.

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 the simulation of dynamic characteristics of an aircraft. 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 exceeding those expected in steady state, and even endanger flight safety. Therefore, accurate prediction of aircraft dynamic characteristics is indispensable for the design of aircraft aerodynamics, control and other systems. [0003] The numerical simulation of computational fluid dynamics based on the second-order backward differential double time-step method is currently the mainstream method for predicting the dynamic characteristics of aircraft. This method is a class of numerical metho...

Claims

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Application Information

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Patent Type & Authority Patents(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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