Rotor wing type unmanned aerial vehicle aerodynamic parallel numerical simulation method

An aerodynamic and numerical simulation technology, applied in sustainable transportation, design optimization/simulation, geometric CAD, etc., can solve problems such as complex flow field structure, complex mesh quantity of calculation grid, complex shape of UAV, etc. To achieve the effect of improving the accuracy

Pending Publication Date: 2020-01-17
SHENZHEN INST FOR INNOVATIVE DESIGN CO LTD
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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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  • Rotor wing type unmanned aerial vehicle aerodynamic parallel numerical simulation method
  • Rotor wing type unmanned aerial vehicle aerodynamic parallel numerical simulation method
  • Rotor wing type unmanned aerial vehicle aerodynamic parallel numerical simulation method

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Embodiment Construction

[0019] The technical solutions in the embodiments of the present invention will be clearly and completely described below. Obviously, the described embodiments are only some of the embodiments of the present invention, but not all of them. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without making creative efforts belong to the protection scope of the present invention.

[0020] The present invention provides a technical solution: a parallel numerical simulation method for aerodynamics of a rotor-type unmanned aerial vehicle, comprising the following steps:

[0021] (1) Use 3D CAD software to draw the calculation model. The calculation model consists of two parts: the rotor and the fuselage. The rotor is composed of three blades. The length of the blade is set to 5.2m. Here, only the helicopter is hovering. The flow field in the state is calculated, and the calculation area of ​​the outer flow field ...

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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...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F30/15G06F30/12G06F30/23
CPCY02T90/00
Inventor 赵宇波陈荣亮闫争争郭斌朱伟斌
Owner SHENZHEN INST FOR INNOVATIVE DESIGN CO LTD
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