Method for positioning and assembling composite material rotor blade of C-shaped beam structure

Abstract

The invention belongs to the technical field of molding of a composite material rotor blade, and provides a method for positioning and assembling the composite material rotor blade of a C-shaped beamstructure. The method includes the steps of paving a lower mold skin (2) and an upper mold skin (6) on a lower press mold (1) and an upper press mold (7) respectively; mounting a lower mold girder (3)on the lower mold skin at first, and positioning and calibrating the lower mold girder (3) by using chordwise profile outline templates (8) to ensure that the girder is accurate in placement positionand direction; mounting a blade foam core (4) on the lower mold girder (3), and then mounting an upper mold girder (5); and assembling the upper press mold and the lower press mold which are paved with the skins, and carrying out heating, pressurizing and curing. According to the method for positioning and assembling the composite material rotor blade of the C-shaped beam structure, the chordwiseprofile outline templates at different positions are arranged, accurate and rapid assembly of parts in the composite material blade is realized, and the product assembly efficiency is improved. By means of the method for positioning and assembling the composite material rotor blade of the C-shaped beam structure, the mold pressing quality of the composite material rotor blade of the C-shaped beamstructure is improved, and the product qualification rate is improved.

Description

technical field [0001] The invention belongs to the technical field of composite material rotor blade molding, and in particular relates to a C-shaped beam structure composite material rotor blade positioning and assembling method. Background technique [0002] The blade beam mainly bears the centrifugal force, flapping and shimmy bending moment of the blade, and transmits it to the rotor hub. It is an important component that provides the tensile and bending stiffness of the blade. Domestic composite material rotor blades are generally designed with a C-beam structure, and high-strength, high-modulus FRP is used as the beam of the composite material blade. The forming quality of the propeller beam is very high, and there must be no defects such as wrinkles, twists, and layers. [0003] The girder is the key load-bearing structure of the composite rotor blade, and the assembly quality of the prepreg girder belt is crucial to the quality and life of the rotor blade. The ass...

AI Technical Summary

Problems solved by technology

The problem is mainly manifested in two points: A. When the prepreg girder belt is not cured, its texture is soft and it is difficult to form a fixed shape; B. It is difficult to determine the positioning datum of the lower mold girder, and the accuracy of its position directly affects the blade foam core assembly

The existing technical solution is to use scales and other tools to roughly locate the assembly position of the blade girder. This simple positioning method often leads to interference between the blade girder and the foam core parts, resulting in folds and wrinkles in the cured girder. Quality defects such as distortion and delamination reduce the service life of the girder and the flight safety of the composite rotor blade

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