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Method for determining interference magnitude of numerical model of composite material rotor blade foam process

A technology for rotor blades and composite materials, which is applied in the field of determining the digital-analog interference of rotor blade foam technology, can solve problems such as poor applicability, blade white spots, and wrinkles, and achieves strong applicability, improved surface quality, and uniformity. The effect of internal pressure

Active Publication Date: 2020-06-02
CHANGHE AIRCRAFT INDUSTRIES CORPORATION
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Problems solved by technology

Such a determination method is relatively poor in applicability, and the molded blades are prone to quality defects such as white spots and wrinkles on the skin surface

Method used

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  • Method for determining interference magnitude of numerical model of composite material rotor blade foam process

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Experimental program
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Effect test

Embodiment

[0020] Embodiment: A certain model propeller adopts domestic PMI foam material A52, a is taken as a coefficient of 0.01, and b is taken as a constant of 0.65mm. The thickness dimension of a section of the foam core part is 10.497, which can be calculated by substituting the formula, and the range of the digital-analog interference of the foam at this section is: 0.75497±0.1mm.

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Abstract

The invention belongs to the technical field of molding of a composite material rotor blade, and improves the product qualification rate. According to the technical scheme, the foam core interferencemagnitude (3) is set in the blade thickness direction of a foam core part theoretical numerical model (4), and is recorded as [delta]m, double-sided amplification is carried out, the interference magnitude is a non-fixed value, and no foam interference magnitude is set in two directions of the span length and the chordwise width of the blade. According to the method for determining the interference magnitude of the numerical model of the composite material rotor blade foam process, different foam core interference magnitudes can be respectively set for foam core parts in different thickness sizes, so that the applicability is higher. By means of the method for determining the interference magnitude of the numerical model of the composite material rotor blade foam process, more uniform internal pressure can be provided during mold pressing of the composite material rotor blade, the area of white spot regions and wrinkle defect regions of skin of the composite material rotor blade is reduced, the molding performance of the blade is good, the surface quality is improved, and the product qualification rate is improved.

Description

technical field [0001] The invention belongs to the technical field of forming composite material rotor blades, and in particular relates to a method for determining the digital-to-analog interference of a rotor blade foam process. Background technique [0002] The rotor blade is the main lifting surface and control surface of the helicopter, and its quality directly affects the performance, flight quality, reliability, maintainability and safety of the helicopter. Composite rotor blades generally adopt a closed mold thermocompression curing molding process. Closed mold forming ensures that the shape of the composite blade can strictly conform to the mold cavity surface, so that the key shape parameters such as the twist angle of the blade, the precision of the airfoil profile and the surface roughness meet the design requirements. [0003] When the rotor blade is formed, in order to avoid problems such as pores and white spots caused by uneven curing pressure, the gas in t...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B29C70/54B29L31/08G06F30/15
CPCB29C70/54B29L2031/082
Inventor 戴周军周阳富谈健彭广棚许漂徐凌波李江钰
Owner CHANGHE AIRCRAFT INDUSTRIES CORPORATION
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