Rotor wing icing ice shape calculation method considering waving effect, storage medium and terminal

A calculation method and ice shape technology, applied in the aerospace field, can solve problems such as blade tip simulation misalignment, and achieve the effect of improving simulation accuracy

Active Publication Date: 2021-08-13
CALCULATION AERODYNAMICS INST CHINA AERODYNAMICS RES & DEV CENT
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0006] The purpose of the present invention is to overcome the problem of inaccurate simulation in the blade tip part of the existing rotor ice shape simulat...

Method used

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  • Rotor wing icing ice shape calculation method considering waving effect, storage medium and terminal
  • Rotor wing icing ice shape calculation method considering waving effect, storage medium and terminal
  • Rotor wing icing ice shape calculation method considering waving effect, storage medium and terminal

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Embodiment 1

[0038] Such as figure 1 As shown, in embodiment 1, the rotor icing ice shape calculation method considering the flapping effect specifically includes the following steps:

[0039] S1: Calculation of the three-dimensional ice shape on the surface of the rotor blade without considering the influence of flapping motion ;

[0040] S2: According to the three-dimensional ice shape on the surface of the rotor blade Calculation of icing stress at different locations on the blade ;

[0041] S3: Judging the icing stress at different positions of the blade Is it greater than the icing fracture strength threshold , if it is greater than , update the icing state of the current blade position to non-icing, otherwise, do nothing. Among them, the icing fracture intensity threshold Determined by tensile test. Specifically, if the icing stress at different positions of the blade >Icing Break Strength Threshold , that is, it is considered that the icing here is broken and shedd...

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Abstract

The invention discloses a rotor wing icing ice shape calculation method considering a flapping effect, a storage medium and a terminal, and belongs to the technical field of aerospace, and the method comprises the steps: firstly, calculating a three-dimensional ice shape of a blade without considering the flapping motion influence; and secondly, calculating icing stresses at different positions of the blade, judging whether the icing stresses at different positions of the blade are greater than an icing breaking strength threshold value or not, if so, updating the icing state of the current blade position to be non-icing, otherwise, not performing any treatment. According to the method, the breaking influence effect of the blade waving motion on the ice is fully considered, the breaking and falling judgment is performed on the ice at different positions of the blade in combination with the physical property parameters and the stress condition of the ice, the simulation precision of the ice shape of the rotor wing ice is greatly improved, and the physical reality of the blade ice is effectively restored.

Description

technical field [0001] The invention relates to the field of aerospace technology, in particular to a calculation method for rotor icing and ice shape considering the flapping effect. Background technique [0002] The rotor is a key component of the helicopter power system, and icing directly changes its shape and reduces its working efficiency; at the same time, the detached icing may damage the engine, fuel tank and weapon system, etc. These effects will lead to a decrease in the helicopter's pulling force, and in severe cases will cause damage to the rotor. Flight crash. Carrying out the evaluation research on rotor icing has important strategic and economic benefits for improving the safe flight performance of helicopters and improving the rotor anti-icing / de-icing design. [0003] At present, rotor icing evaluation methods mainly include numerical simulation, spray tower test, ice wind tunnel test and flight test, etc. Among them, numerical simulation has become an im...

Claims

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Application Information

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IPC IPC(8): G06F30/15G06F30/17G06F30/20G06F119/08G06F119/14
CPCG06F30/15G06F30/17G06F30/20G06F2119/08G06F2119/14
Inventor 李伟斌马洪林王跃军赵凡王昊王应宇
Owner CALCULATION AERODYNAMICS INST CHINA AERODYNAMICS RES & DEV CENT
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