Rotor wing type unmanned aerial vehicle aerodynamic parallel numerical simulation method

Abstract

The invention discloses a rotor wing type unmanned aerial vehicle aerodynamic parallel numerical simulation method. The method comprises the following steps of (1) drawing a calculation model throughthree-dimensional CAD software, the calculation model is composed of a rotor wing and a helicopter body, the rotor wing is composed of three blades, the length of each blade is set to be 5.2 m, and only a flow field of the helicopter in a hovering state is calculated at the position; (2) setting a calculation area; according to the rotor wing type unmanned aerial vehicle aerodynamic parallel numerical simulation method, through model construction, a calculation area is set to perform grid division, simulating the relative movement of a rotor wing and a fuselage by moving a grid of a rotating area by using a moving grid technology at each time step, adding proper conditions at an interface to exchange information of a flow field, and then performing solving in a full coupling form to quickly obtain a numerical calculation result with high fidelity.

Description

technical field [0001] The invention relates to the technical field of high-fidelity numerical simulation of the full flow field of a rotor-type unmanned aerial vehicle, in particular to a parallel numerical simulation method for the aerodynamics of a rotor-type unmanned aerial vehicle. Background technique [0002] High-fidelity numerical simulation of the full flow field of rotor-shaped UAV is a very challenging and important research direction in the field of computational fluid dynamics. Compared with traditional non-rotor aircraft aerodynamic analysis problems, the challenges of this type of problem are mainly reflected in the following aspects: (1) The relative motion between the rotor and the fuselage involves moving grids, relative motion simulation, multi- Coupling of various methods such as high-precision interpolation of physical quantities; (2) The complex shape of the UAV leads to a very complex calculation grid and a huge amount of grid; (3) The interaction bet...

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Problems solved by technology

Compared with traditional non-rotor aircraft aerodynamic analysis problems, the challenges of this type of problem are mainly reflected in the following aspects: (1) The relative motion between the rotor and the fuselage involves moving grids, relative motion simulation, multi- Coupling of various methods such as high-precision interpolation of physical quantities; (2) The complex shape of the UAV leads to a very complex calculation grid and a huge amount of grid; (3) The interaction between the rotor and the fuselage leads to the flow field structure extremely complicated

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