CN112550691A - Helicopter rotor blade - Google Patents
Helicopter rotor blade Download PDFInfo
- Publication number
- CN112550691A CN112550691A CN202110014345.2A CN202110014345A CN112550691A CN 112550691 A CN112550691 A CN 112550691A CN 202110014345 A CN202110014345 A CN 202110014345A CN 112550691 A CN112550691 A CN 112550691A
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- CN
- China
- Prior art keywords
- blade
- foam core
- diameter
- cylinder
- carbon fiber
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 239000006260 foam Substances 0.000 claims abstract description 38
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims abstract description 33
- 229910052799 carbon Inorganic materials 0.000 claims abstract description 33
- 229920000049 Carbon (fiber) Polymers 0.000 claims abstract description 24
- 239000004917 carbon fiber Substances 0.000 claims abstract description 24
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims abstract description 24
- 239000004744 fabric Substances 0.000 claims abstract description 19
- 230000007704 transition Effects 0.000 claims abstract description 12
- 239000003365 glass fiber Substances 0.000 claims description 7
- 239000002184 metal Substances 0.000 claims description 6
- 239000002131 composite material Substances 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 230000007797 corrosion Effects 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 239000002699 waste material Substances 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/32—Rotors
- B64C27/46—Blades
- B64C27/473—Constructional features
Abstract
The invention discloses a helicopter rotor blade, wherein a blade handle is a cylinder with a larger diameter, a circular truncated cone with a smaller diameter, a cylinder with a smallest diameter, a circular truncated cone with a larger diameter, a transition cambered surface and a cylinder with a largest diameter from a head part in sequence; the cylinder with the larger diameter at the head part is provided with external threads and a key groove at one end part, and the center of the end surface at the other end is provided with a conical groove; the foam core and the blade body of the blade are same in curved shape, the blade handle end of the foam core is provided with a conical end, and the front edge end of the foam core is provided with a tip part with a V-shaped section; the conical end of the foam core is inserted in the petiole conical groove; the carbon beam is positioned at the front edge part of the blade body of the blade, and one end of the carbon beam, which is far away from the front edge, is a groove with a V-shaped section; the rear edge strip is positioned at the rear edge part of the blade body and is a thin carbon fiber belt which is formed by paving a plurality of layers of carbon fiber prepreg cloth at the rear edge end of the foam core; the skin is wrapped around all other parts except the threaded part of the blade shank. The blade of the invention has small diameter, high strength and light weight, and particularly the strength of the front edge part is very high, thus completely meeting the requirements of a helicopter.
Description
Technical Field
The invention belongs to the technical field of rotor blades, and relates to a helicopter rotor blade.
Background
The existing composite material paddle consists of a metal blade handle and a composite material wrapped inside and outside the metal blade handle. The connecting part of the petiole and the foam core is round, the connection between the foam core and the petiole is weak, the positioning is not easy, the dislocation is easy to occur during layering, the defect that the blade cannot be repaired is caused, only waste products can be made, and the rejection rate is high; the blade has low strength, and in order to meet the strength requirement, the number of layers of carbon beams needing to be paved is increased, so that the overall volume and weight of the blade are increased invisibly; in the existing blade manufacturing method, the carbon beam layers of the front edge and the rear edge of the blade are the same, and the carbon beam layers of the rear edge are also very thick to achieve the strength of the front edge, so that the weight of the whole blade is very heavy. The helicopter requires large flight power, safe and reliable structure and light weight, so the requirement for the rotor blade is light weight and high strength, especially the requirement for the strength of the front edge of the blade is very high, and the blade manufactured by the existing method can not meet the requirement of the helicopter on the rotor blade.
Disclosure of Invention
The present invention has been made to solve the above-mentioned problems occurring in the prior art, and an object of the present invention is to provide a rotor blade for a helicopter, which has a small diameter, high strength, and a light weight, and particularly, has a very high strength at the leading edge portion, and completely meets the requirements of the helicopter for the rotor blade.
In order to realize the purpose of the invention, the technical solution of the invention is as follows: a helicopter rotor blade comprising a shank, a foam core, a carbon beam, a trailing edge strip, and a skin; the blade handle is an integral metal piece, one end of the head part is a cylinder with a larger diameter, then a section of circular truncated cone with a reduced diameter, then a section of cylinder with a minimum diameter, then a section of circular truncated cone with an enlarged diameter, and finally a section of cylinder with a maximum diameter, wherein a transition arc surface is arranged between the circular truncated cone with the enlarged diameter and the cylinder with the maximum diameter; the cylinder with the larger diameter at the head part is provided with external threads and a key groove at one end part, and the center of the end surface at the other end is provided with a conical groove; a connecting through hole is formed in the diameter-enlarged circular truncated cone along the radial direction of the blade shank; the foam core and the blade body of the blade are same in curved shape, the blade shank end of the foam core is provided with a conical end head which is completely matched with the blade shank conical groove, and the front edge end of the foam core is provided with a convex tip part with a V-shaped section; the conical end of the foam core is inserted in the petiole conical groove, and the rest part of the foam core deflects to the rear edge part of the blade; the carbon beam is positioned at the front edge of the blade body, one end of the carbon beam, which is far away from the front edge, is a groove with a V-shaped section and is completely matched with the V-shaped tip of the foam core, the carbon beam is made by paving a plurality of layers of carbon fiber prepreg cloth on the V-shaped tip of the foam core, the blade stem end of the carbon beam is paved to the part with only the left blade stem thread, and the other end of the carbon beam is paved to the blade tail; the rear edge strip is positioned at the rear edge part of the blade body and is a thin carbon fiber belt which is formed by paving a plurality of layers of carbon fiber prepreg cloth at the rear edge end of the foam core, the petiole end of the thin carbon fiber belt is paved to the position where only the threaded part of the petiole is left, and the other end of the thin carbon fiber belt reaches the tail of the blade; the skin is wrapped on all other parts except the threaded part of the blade handle; the same through connecting holes which are communicated with each other are reserved on the foam core, the carbon beam, the rear edge strip and the skin which correspond to the connecting holes of the blade handle to form bolt connecting holes for connecting the blade and the blade hoop.
Further preferably, the diameter of the transition arc surface of the petiole is 50mm, and the length of the cylinder with the largest diameter is 5 mm.
Further preferably, a transition arc surface a is arranged between the cylinder with the smallest diameter of the blade handle and the round table with the larger diameter.
Further preferably, the carbon beam area, as seen in a cross-sectional area of the blade body perpendicular to the blade axis, is 25-40% of the total cross-sectional area. The carbon beam area can ensure the strength of the paddle and can also ensure that the paddle has light weight.
Further preferably, the skin is composed of 3-10 layers of carbon fiber prepreg cloth and glass fiber prepreg cloth. The glass fiber prepreg is arranged on the outer layer and can be one layer or a plurality of layers, the more the number of the layers is, the stronger the corrosion resistance is, but the higher the cost is.
The metal blade handle of the paddle root is only provided with the tapered groove on the rear end face, the structure is simple, the strength is high, the diameter which can be manufactured is smaller, the foam core is connected in the tapered groove, the connection reliability is high, the transition cambered surface arranged at the rear end part enables the carbon beam, the rear edge strip and the skin which are paved and fixed outside to be good in fixing stability and not easy to fall off, and particularly the carbon beam, the rear edge strip and the skin of which the front end is also provided with the transition cambered surface A are better in fixing stability. Because the blade shank head has external screw thread and keyway, and the paddle has the bolted connection hole with the oar hoop link, can make the paddle rotationally fix simple structure on the propeller hub, and the spare part of adoption is few, and the connection reliability is high, and joint strength is high, has correspondingly reduced the volume and the weight of propeller hub. The carbon beam is only supported at the thicker front edge part of the paddle, the carbon beam has high supporting force, the requirement of the paddle on the strength of the front edge can be met, the foam core is deviated from the rear edge of the paddle, the thin rear edge part is only supported by the rear edge strip of the thin carbon fiber band, and the rear edge strip can meet the strength requirement due to the low requirement of the paddle on the rear edge, so that the weight of the paddle can be greatly reduced under the condition of meeting the strength requirement of the paddle.
In a word, the blade of the invention has small diameter, high strength and light weight, and particularly the strength of the front edge part is very high, thus completely meeting the requirements of large flying power, safe and reliable structure and light weight of the rotor blade of the helicopter.
Drawings
FIG. 1 is a front view of the present invention;
FIG. 2 is a cross-sectional view AA of FIG. 1;
FIG. 3 is a cross-sectional view of BB of FIG. 1;
FIG. 4 is a front view of a petiole according to the present invention;
FIG. 5 is an enlarged front view of a petiole according to the present invention;
FIG. 6 is a front view of a foam core of the present invention;
FIG. 7 is a front view of a carbon beam according to the present invention;
FIG. 8 is a front view of the trailing edge strip of the present invention.
Detailed Description
The invention is further described with reference to the following figures and specific embodiments.
As shown in fig. 1-8, this embodiment includes a petiole 1, a foam core 8, a carbon beam 7, a trailing edge strip 9, and a skin 6. The petiole 1 is an integral metal piece, one end of the head is a cylinder 18 with a larger diameter, a circular truncated cone 12 with a reduced diameter is arranged next to the cylinder 13 with a minimum diameter, a circular truncated cone 14 with an enlarged diameter is arranged next to the cylinder 17 with a maximum diameter, and a transition arc surface 16 is arranged between the circular truncated cone 14 with the enlarged diameter and the cylinder 17 with the maximum diameter. The cylinder 18 with larger diameter at the head part is provided with an external thread 11 and a key groove 10 at one end part, and the center of the end surface at the other end part is provided with a tapered groove 15. The round table 14 with the enlarged diameter is provided with a connecting through hole along the radial direction of the petiole 7. The foam core 8 and the blade body 2 are same in curved shape, the end of the blade shank 1 is provided with a conical end 19 which is completely matched with the conical groove 15 of the blade shank, and the end of the front edge 3 is provided with a convex tip 21 with a V-shaped section. The conical end 19 of the foam core 8 is inserted in the petiole conical groove 15, and the rest part of the foam core is deflected to the rear edge 4 of the blade. The carbon beam 7 is positioned at the front edge 3 of the blade body 2, one end of the carbon beam, which is far away from the front edge 3, is a groove 20 with a V-shaped section, which is completely matched with the V-shaped tip part 21 of the foam core 8, the groove is formed by paving a plurality of layers of carbon fiber prepreg cloth on the V-shaped tip part 21 of the foam core, the blade shank end of the groove is paved to the part with only the left blade shank thread, and the other end of the groove is paved to the blade tail 5. The rear edge strip 9 is positioned at the rear edge 4 of the blade body 2 and is a thin carbon fiber belt which is formed by paving a plurality of layers of carbon fiber prepreg cloth at the rear edge 4 end of the foam core 8, the petiole end of the thin carbon fiber belt is paved to the part with only the remaining petiole threads, and the other end of the thin carbon fiber belt is paved to the petiole tail 5. The skin 6 is wrapped around all but the threaded portion of the shank. The same through connecting holes are reserved on the foam core 8, the carbon beam 7, the rear edge strip 9 and the skin 6 corresponding to the connecting holes of the blade handle 1 to form bolt connecting holes for connecting the blade and the blade hoop.
Preferably, the transition arc 16 of the petiole 1 has a diameter of 50mm and the cylinder 17 of its largest diameter is 5mm long. Preferably, a transition arc surface A23 is arranged between the cylinder 13 with the smallest diameter and the round platform 14 with the larger diameter of the petiole 1.
Preferably, the carbon beam 7 has an area, as seen in a cross-sectional area of the blade body 2 perpendicular to the blade axis, of 25-40% of the total cross-sectional area.
Preferably, the skin 9 is composed of 3-10 layers of carbon fiber prepreg cloth and the outside of glass fiber prepreg cloth.
There are, of course, many other embodiments of the invention and modifications and variations of this invention that will be obvious to those skilled in the art may be made without departing from the spirit and scope of the invention, but it is intended to cover all such modifications and variations as fall within the true spirit and scope of the invention.
Claims (9)
1. A helicopter rotor blade characterized by: comprises a petiole, a foam core, a carbon beam, a trailing edge strip and a skin; the blade handle is an integral metal piece, one end of the head part is a cylinder with a larger diameter, then a section of circular truncated cone with a reduced diameter, then a section of cylinder with a minimum diameter, then a section of circular truncated cone with an enlarged diameter, and finally a section of cylinder with a maximum diameter, wherein a transition arc surface is arranged between the circular truncated cone with the enlarged diameter and the cylinder with the maximum diameter; the cylinder with the larger diameter at the head part is provided with external threads and a key groove at one end part, and the center of the end surface at the other end is provided with a conical groove; a connecting through hole is formed in the diameter-enlarged circular truncated cone along the radial direction of the blade shank; the foam core and the blade body of the blade are same in curved shape, the blade shank end of the foam core is provided with a conical end head which is completely matched with the blade shank conical groove, and the front edge end of the foam core is provided with a convex tip part with a V-shaped section; the conical end of the foam core is inserted in the petiole conical groove, and the rest part of the foam core deflects to the rear edge part of the blade; the carbon beam is positioned at the front edge of the blade body, one end of the carbon beam, which is far away from the front edge, is a groove with a V-shaped section and is completely matched with the V-shaped tip of the foam core, the carbon beam is made by paving a plurality of layers of carbon fiber prepreg cloth on the V-shaped tip of the foam core, the blade stem end of the carbon beam is paved to the part with only the left blade stem thread, and the other end of the carbon beam is paved to the blade tail; the rear edge strip is positioned at the rear edge part of the blade body and is a thin carbon fiber belt which is formed by paving a plurality of layers of carbon fiber prepreg cloth at the rear edge end of the foam core, the petiole end of the thin carbon fiber belt is paved to the position where only the threaded part of the petiole is left, and the other end of the thin carbon fiber belt reaches the tail of the blade; the skin is wrapped on all other parts except the threaded part of the blade handle; the same through connecting holes which are communicated with each other are reserved on the foam core, the carbon beam, the rear edge strip and the skin which correspond to the connecting holes of the blade handle to form bolt connecting holes for connecting the blade and the blade hoop.
2. A helicopter rotor blade according to claim 1, wherein: the diameter of the transition cambered surface of the petiole is 50mm, and the length of the cylinder with the largest diameter is 5 mm.
3. A helicopter rotor blade according to claim 1 or claim 2, wherein: a transition arc surface A is arranged between the cylinder with the smallest diameter of the blade handle and the round table with the larger diameter.
4. A helicopter rotor blade according to claim 3, wherein: the carbon beam area, as seen in the cross-sectional area of the blade body perpendicular to the blade axis, accounts for 25-40% of the total cross-sectional area.
5. A helicopter rotor blade according to claim 4, wherein: the skin is composed of 3-10 layers of carbon fiber prepreg cloth and the outside of glass fiber prepreg cloth.
6. A helicopter rotor blade according to claim 1 or claim 2, wherein: the carbon beam area, as seen in the cross-sectional area of the blade body perpendicular to the blade axis, accounts for 25-40% of the total cross-sectional area.
7. A helicopter rotor blade according to claim 6, wherein: the skin is composed of 3-10 layers of carbon fiber prepreg cloth and the outside of glass fiber prepreg cloth.
8. A helicopter rotor blade according to claim 3, wherein: the skin is composed of 3-10 layers of carbon fiber prepreg cloth and the outside of glass fiber prepreg cloth.
9. A helicopter rotor blade according to claim 1 or claim 2, wherein: the skin is composed of 3-10 layers of carbon fiber prepreg cloth and the outside of glass fiber prepreg cloth.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110014345.2A CN112550691A (en) | 2021-01-06 | 2021-01-06 | Helicopter rotor blade |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110014345.2A CN112550691A (en) | 2021-01-06 | 2021-01-06 | Helicopter rotor blade |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN112550691A true CN112550691A (en) | 2021-03-26 |
Family
ID=75035276
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110014345.2A Pending CN112550691A (en) | 2021-01-06 | 2021-01-06 | Helicopter rotor blade |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN112550691A (en) |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN86104001A (en) * | 1986-06-13 | 1987-03-25 | 齐大中 | Fixed-moment air propeller |
| CN101428686A (en) * | 2008-12-23 | 2009-05-13 | 北京航空航天大学 | Method for structural design of coaxal helicopter composite material blade |
| US20130287585A1 (en) * | 2012-04-30 | 2013-10-31 | Ratier-Figeac Sas | Propeller blade with lightweight insert |
| CN204956918U (en) * | 2015-09-29 | 2016-01-13 | 深圳聚科精密机电有限公司 | Unmanned aerial vehicle bispin wing structure |
| CN206278269U (en) * | 2016-11-30 | 2017-06-27 | 中国直升机设计研究所 | A kind of new configuration of propeller shank |
| CN108045559A (en) * | 2017-12-15 | 2018-05-18 | 惠阳航空螺旋桨有限责任公司 | A kind of composite material blade blade root fastenings structure |
| US20190315451A1 (en) * | 2018-04-17 | 2019-10-17 | Ratier-Figeac Sas | Propeller blade spar |
-
2021
- 2021-01-06 CN CN202110014345.2A patent/CN112550691A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN86104001A (en) * | 1986-06-13 | 1987-03-25 | 齐大中 | Fixed-moment air propeller |
| CN101428686A (en) * | 2008-12-23 | 2009-05-13 | 北京航空航天大学 | Method for structural design of coaxal helicopter composite material blade |
| US20130287585A1 (en) * | 2012-04-30 | 2013-10-31 | Ratier-Figeac Sas | Propeller blade with lightweight insert |
| CN204956918U (en) * | 2015-09-29 | 2016-01-13 | 深圳聚科精密机电有限公司 | Unmanned aerial vehicle bispin wing structure |
| CN206278269U (en) * | 2016-11-30 | 2017-06-27 | 中国直升机设计研究所 | A kind of new configuration of propeller shank |
| CN108045559A (en) * | 2017-12-15 | 2018-05-18 | 惠阳航空螺旋桨有限责任公司 | A kind of composite material blade blade root fastenings structure |
| US20190315451A1 (en) * | 2018-04-17 | 2019-10-17 | Ratier-Figeac Sas | Propeller blade spar |
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| PB01 | Publication | ||
| PB01 | Publication | ||
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Application publication date: 20210326 |