CN111216380A - C-shaped beam structure composite material rotor blade positioning and assembling method - Google Patents
C-shaped beam structure composite material rotor blade positioning and assembling method Download PDFInfo
- Publication number
- CN111216380A CN111216380A CN201911116159.9A CN201911116159A CN111216380A CN 111216380 A CN111216380 A CN 111216380A CN 201911116159 A CN201911116159 A CN 201911116159A CN 111216380 A CN111216380 A CN 111216380A
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- China
- Prior art keywords
- composite material
- girder
- rotor blade
- lower die
- blade
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/40—Shaping or impregnating by compression not applied
- B29C70/42—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles
- B29C70/46—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/54—Component parts, details or accessories; Auxiliary operations, e.g. feeding or storage of prepregs or SMC after impregnation or during ageing
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29L—INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
- B29L2031/00—Other particular articles
- B29L2031/08—Blades for rotors, stators, fans, turbines or the like, e.g. screw propellers
- B29L2031/082—Blades, e.g. for helicopters
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- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Composite Materials (AREA)
- Mechanical Engineering (AREA)
- Casting Or Compression Moulding Of Plastics Or The Like (AREA)
Abstract
The invention belongs to the technical field of composite material rotor blade forming, and provides a method for positioning and assembling a C-shaped beam structure composite material rotor blade, which comprises the following steps: paving and pasting the lower die skin (2) and the upper die skin (6) on the lower die (1) and the upper die (7) respectively; firstly, a lower die girder (3) is installed on a lower die skin, and the lower die girder (3) is positioned and calibrated by using a chord-direction profile appearance template (8), so that the girder is ensured to be accurately placed and moved; after a blade foam core (4) is arranged on the lower die girder (3), an upper die girder (5) is arranged; and (4) closing the upper pressing die and the lower pressing die on which the skin is laid, and heating, pressurizing and curing. According to the invention, by arranging the chord-direction profile appearance sample plates at different positions, the precise and rapid assembly of each part in the composite material blade is realized, and the product assembly efficiency is improved. The invention improves the mould pressing quality of the C-shaped beam structure composite material rotor blade and improves the product percent of pass.
Description
Technical Field
The invention belongs to the technical field of composite material rotor blade forming, and particularly relates to a method for positioning and assembling a C-shaped beam structure composite material rotor blade.
Background
The blade girder mainly bears the centrifugal force and the flapping and shimmy bending moments of the blade and transmits the centrifugal force and the flapping and shimmy bending moments to the rotor hub, and the blade girder is an important component for providing the stretching and bending rigidity of the blade. When the composite material rotor blade is designed in China, a C-shaped beam structure is generally adopted, and high-strength and high-modulus glass fiber reinforced plastics are used as a crossbeam of the composite material rotor blade. The forming quality requirement of the blade girder is high, and the defects of folds, distortion, layering and the like cannot exist.
The crossbeam is a key bearing structure of the rotor blade made of the composite material, and the assembly quality of the pre-impregnated girder belt is of great importance to the quality and the service life of the rotor blade. The component assembly relationship in the composite material rotor blade with the C-shaped beam structure is shown in figure 1: the blade lower die skin 2 and the upper die skin 6 are coated on the upper side and the lower side of the blade lower die girder 3, the upper die girder 5 and the blade foam core 4; the lower die girder 3 and the upper die girder 5 are enclosed into a C-shaped structure and are spliced with the convex part of the foam core part; and (3) in a closed cavity formed by the lower die 1 and the upper die 7, heating and pressurizing to complete the solidification and molding of the blade. In the whole assembly process, the assembly problem of the pre-impregnated girder belt is very prominent and the difficulty is very high. The problem is mainly expressed by two points: A. when the prepreg girder belt is not cured, the prepreg girder belt is soft in texture and difficult to form a fixed appearance; B. the positioning reference of the lower die girder is difficult to determine, and the accuracy of the position of the lower die girder directly influences the assembly of the blade foam core. The existing technical scheme is that tools such as a graduated scale are used for roughly positioning the assembling position of the blade girder, and the simple positioning method can often cause the interference between the blade girder and a foam core part, so that the solidified girder has quality defects such as folds, distortion, layering and the like, and the service life of the girder and the flight safety of the composite material rotor blade are reduced.
Disclosure of Invention
The purpose of the invention is as follows: the method for positioning and assembling the rotor blade made of the composite material with the C-shaped beam structure is provided, and the product assembling efficiency is improved.
The technical scheme is as follows:
a method for positioning and assembling a rotor blade made of composite materials with a C-shaped beam structure comprises the following steps:
paving and pasting the lower die skin 2 and the upper die skin 6 on the lower die 1 and the upper die 7 respectively;
firstly, a lower die girder 3 is installed on a lower die skin, and the lower die girder 3 is positioned and calibrated by using a chord-direction profile appearance sample plate 8, so that the girder is ensured to be accurately placed and moved;
installing a blade foam core 4 on the lower die girder 3, and then installing an upper die girder 5;
and (4) closing the upper pressing die and the lower pressing die on which the skin is laid, and heating, pressurizing and curing.
And A, B points are selected on the chord-direction section profile template, and the profile of the area between A, B points is consistent with the profile of the blade foam core contacted with the crossbeam of the lower die.
And a plurality of groups of chord-direction section shape sample plates 8 are arranged along the spanwise length direction of the blade.
When the spanwise length of the blade is less than or equal to 4 meters, 1 group of chord-wise section profile sample plates 8 are arranged every 200 millimeters.
When the spanwise length of the blade is more than 4 meters, 1 group of chord-wise section profile sample plates 8 are arranged every 500 millimeters.
The chord-wise section outline template 8 is positioned in a manner that a scale line a corresponds to the boundary line of the front edge of the lower die.
The chord-wise section outline template 8 is positioned in a manner that the b scale line corresponds to the rear edge boundary line of the lower die.
The manufacturing tolerance of the external dimension of the chord-direction section external shape sample plate is controlled within +/-0.2 mm.
Has the advantages that:
according to the invention, by arranging the chord-direction profile appearance sample plates at different positions, the precise and rapid assembly of each part in the composite material blade is realized, and the product assembly efficiency is improved. The invention improves the mould pressing quality of the C-shaped beam structure composite material rotor blade and improves the product percent of pass.
Drawings
Fig. 1 is a schematic view of the assembly of parts during the molding of a composite rotor blade having a C-beam structure.
FIG. 2 is a schematic view of a chord-wise profile shape template used during assembly of a lower mold girder of a composite rotor blade.
Detailed Description
The invention aims to provide a novel method for positioning and assembling a rotor blade made of composite materials and having a C-shaped beam structure, which comprises the following steps:
1. paving and pasting the lower die skin 2 and the upper die skin 6 on the lower die 1 and the upper die 7 respectively;
2. firstly, a lower die girder 3 is installed on a lower die skin, and the lower die girder 3 is positioned and calibrated by using a chord-direction profile appearance sample plate 8, so that the girder is ensured to be accurately placed and moved;
3. installing a blade foam core 4 on the lower die girder 3, and then installing an upper die girder 5;
4. combing and compacting the composite material girder by using tools such as a rolling plate and the like;
5. and (4) closing the upper pressing die and the lower pressing die on which the skin is laid, and heating, pressurizing and curing.
Further, the contour of a blade foam core in contact with a girder of the lower die is selected from the contour of the two A, B points of the chord-wise section contour template;
furthermore, a plurality of groups of chord-direction section shape templates are arranged along the length direction of the spanwise direction of the blade, and the selected positions are selected in the areas with severe profile shape changes of the blade foam core parts;
furthermore, the chord-wise section profile template is positioned in a manner that a scale line a corresponds to a front edge boundary line of the lower die and a scale line b corresponds to a rear edge boundary line of the lower die;
further, the manufacturing tolerance of the outer dimension of the chord-direction section outer shape sample plate is controlled within +/-0.2 mm.
Claims (8)
1. A method for positioning and assembling a rotor blade made of composite materials with a C-shaped beam structure is characterized by comprising the following steps:
paving and pasting the lower die skin (2) and the upper die skin (6) on the lower die (1) and the upper die (7) respectively;
firstly, a lower die girder (3) is installed on a lower die skin, and the lower die girder (3) is positioned and calibrated by using a chord-direction profile appearance template (8), so that the girder is ensured to be accurately placed and moved;
after a blade foam core (4) is arranged on the lower die girder (3), an upper die girder (5) is arranged;
and (4) closing the upper pressing die and the lower pressing die on which the skin is laid, and heating, pressurizing and curing.
2. A method of positioning and assembling a rotor blade of composite material having a C-beam structure according to claim 1,
and A, B points are selected on the chord-direction section profile template, and the profile of the area between A, B points is consistent with the profile of the blade foam core contacted with the crossbeam of the lower die.
3. A method of positioning and assembling a rotor blade of composite material having a C-beam structure according to claim 1,
and the chord-direction section profile sample plates (8) are arranged in a plurality of groups along the spanwise length direction of the blade.
4. A method of positioning and assembling a rotor blade of composite material having a C-beam structure according to claim 3,
when the spanwise length of the blade is less than or equal to 4 meters, 1 group of chord-wise section profile sample plates (8) are arranged every 200 millimeters.
5. A method of positioning and assembling a rotor blade of composite material having a C-beam structure according to claim 3,
when the spanwise length of the blade is more than 4 meters, 1 group of chord-wise section profile sample plates (8) are arranged every 500 millimeters.
6. A method of positioning and assembling a rotor blade of composite material having a C-beam structure according to claim 1,
the chord direction section profile sample plate (8) is positioned in a way that a scale line a corresponds to the boundary line of the front edge of the lower pressing die.
7. A method of positioning and assembling a rotor blade of composite material having a C-beam structure according to claim 1,
and the chord direction section profile template (8) is positioned in a way that a scale line b corresponds to the rear edge boundary line of the lower pressing die.
8. A method of positioning and assembling a rotor blade of composite material having a C-beam structure according to claim 1,
the manufacturing tolerance of the external dimension of the chord-direction section external shape sample plate is controlled within +/-0.2 mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911116159.9A CN111216380A (en) | 2019-11-14 | 2019-11-14 | C-shaped beam structure composite material rotor blade positioning and assembling method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911116159.9A CN111216380A (en) | 2019-11-14 | 2019-11-14 | C-shaped beam structure composite material rotor blade positioning and assembling method |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN111216380A true CN111216380A (en) | 2020-06-02 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201911116159.9A Pending CN111216380A (en) | 2019-11-14 | 2019-11-14 | C-shaped beam structure composite material rotor blade positioning and assembling method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN111216380A (en) |
-
2019
- 2019-11-14 CN CN201911116159.9A patent/CN111216380A/en active Pending
Non-Patent Citations (1)
| Title |
|---|
| 戴周军 等: "先进复合材料旋翼桨叶制造技术研究", 《第八届中国航空学会青年科技论坛论文集》 * |
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| PB01 | Publication | ||
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Application publication date: 20200602 |