Composite material blade with replaceable blade tip
A technology of composite materials and propeller tips, which is applied in the direction of aircraft component testing, rotorcraft, aircraft parts, etc., can solve the problems of material and resource loss, long test cycle, mold scrapping, etc., and achieve reduced manufacturing cycle, simple structure, easy disassembly and assembly convenient effect
Pending Publication Date: 2022-01-18
CHINA HELICOPTER RES & DEV INST
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Problems solved by technology
[0003] When performing aerodynamic noise verification tests, a large number of model blades required for verification are usually manufactured according to the shape of the blade tip. Repeated mold opening and production lead to
Method used
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[0031] The present invention will be further described below by means of specific embodiments:
[0032] see figure 1 and figure 2 , the present invention provides a blade tip replaceable structure, which can realize the replacement of the blade tip of the composite material blade, thereby changing the shape of the blade. The joint section is arranged at the section where the thickness of the blade airfoil is relatively large, and the space at this location is relatively large, which is convenient for structural arrangement. At the same time, the joint section is arranged on the extension line of the girder laying, and the force transmission effect is the best. The upper and lower airfoils of the airfoil joint section are wrapped with metal covers. With this structure, the good ductility of the metal can be used to ensure the shape of the partial section of the blade, and it can also provide a supporting surface for the connecting bolts and prevent water seepage.
[0033] se...
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The invention belongs to the field of blade structure design and rotor dynamics design, and discloses a composite material blade with a replaceable blade tip, which comprises a blade body section and a blade tip section, one end of the blade body section close to the blade tip is a blade body joint section; one end of the blade tip section far away from the blade tip is a blade tip joint section; a blade body joint is a single lug and is arranged in a blade body skin, and the single lug is further provided with a plurality of first bolt holes penetrating through the upper surface and the lower surface of the single lug; the blade tip joint section comprises a blade tip skin, a blade tip joint and a blade tip filling block; the blade tip joint is a double-lug matched with the single lug and is arranged in the blade tip skin; second bolt holes matched with the first bolt holes are formed in the double lugs; the blade body joint and the blade tip joint are fixed through a bolt after being inserted; and the space between the blade tip joint and the blade tip skin is filled with the blade tip filling block. Openings for containing bolts are formed in the upper surface and the lower surface of the area, corresponding to the first bolt holes, of the blade body skin, and an upper airfoil covering cap and a lower airfoil covering cap cover the openings of the blade body skin so as to maintain the aerodynamic shape of the blade.
Description
technical field [0001] The invention belongs to the fields of blade structure design and rotor dynamics design, and discloses a composite material blade with a replaceable blade tip. Background technique [0002] Rotor noise is the main source of helicopter noise, and the tip shape of the blade has a great influence on the noise of the helicopter rotor. In order to verify the influence of different tip shapes on the noise of the helicopter rotor, a large number of model blades have been invested at home and abroad for verification. At present, the vast majority of rotor blades are made of composite material blades, and a set of corresponding production molds is required to produce a blade with a shape. Therefore, the production cost of composite material blades is high and the production cycle is long. [0003] When performing aerodynamic noise verification tests, a large number of model blades required for verification are usually manufactured according to the shape of the ...
Claims
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Login to View More IPC IPC(8): B64C27/473B64F5/00B64F5/60
CPCB64C27/473B64F5/00B64F5/60
Inventor 袁翔吴灵伟李伟熊绍海喻国瑞江嘉吉孙立达
Owner CHINA HELICOPTER RES & DEV INST