Automatic balancing method for numerical simulation of three-dimensional full machine

Abstract

The invention discloses an automatic balancing method for numerical simulation of a three-dimensional full machine. The method comprises the following steps: S1, generating an original calculation grid of the three-dimensional full machine, wherein the original calculation grid comprises splicing grid blocks; s2, reading space point coordinates and boundary conditions of an original calculation grid, and performing numerical simulation on the spliced grid blocks according to the read space point coordinates and boundary conditions to obtain a pitching moment coefficient under a current elevator surface deflection angle; s3, judging whether the elevator surface reaches a balancing state or not according to the pitching moment coefficient under the current elevator surface deflection angle,if the elevator surface does not reach the balancing state, adjusting the deflection angle of the elevator surface, and repeatedly executing the steps S2 to S3 until the elevator surface reaches the balancing state. According to the method, numerical simulation is carried out on the spliced grid blocks of the three-dimensional whole aircraft, automatic balancing of the deflection angle of the elevator surface is achieved, manual intervention is not needed in the whole process, and convenience and rapidness are achieved.

Description

technical field [0001] The invention relates to the field of surface and space grid generation in computational fluid dynamics, in particular to an automatic balancing method for three-dimensional full-machine numerical simulation. Background technique [0002] At present, in CFD (Computational Fluid Dynamics), in order to meet the needs of the design unit, it is often necessary to obtain the aerodynamic characteristics of the whole machine shape in a trim state (pitching moment is zero) at different Mach numbers and different angles of attack. The shape of the whole machine can keep the pitching moment of the whole machine at zero through the deflection of the elevator rudder surface on the horizontal tail. However, under different Mach numbers and different angles of attack, the deflection angle of the elevator rudder surface that satisfies the trim state of the whole machine is different. It needs to be calculated in CFD. determined during the iterative process. This req...

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Problems solved by technology

For the mainstream structural grid method, due to the inherent geometric properties of the structural grid itself that are difficult to automatically generate, there is no related full-machine automatic trimming technology in the CFD field.

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