阅读说明：本技术 一种直升机旋翼结构及其制造方法 (helicopter rotor structure and manufacturing method thereof ) 是由 孙海翔 古小文 周毅文 窦新国 姚雨辰 李聪 朱重庆 张航 杨宪辉 李南 王林 于 2019-09-17 设计创作，主要内容包括：本发明公开了一种直升机旋翼结构及其制造方法,该直升机旋翼结构包括旋翼蒙皮、翼尖配重盒、旋翼轴套、主梁、前缘配重丝、梳齿件和填充件。旋翼蒙皮内限定出填充腔,翼尖配重盒连接在填充腔的一端,翼尖配重盒内设有配重块,主梁的一端绕过旋翼轴套后与主梁的另一端连接在翼尖配重盒上,前缘配重丝的一端绕过旋翼轴套后与前缘配重丝的另一端连接在配重块上,梳齿件设在填充腔内,梳齿件将主梁分成多股,填充件填充在填充腔内以将旋翼轴套、主梁、前缘配重丝、旋翼轴套以及梳齿件固定在填充腔内。该直升机旋翼结构的旋翼蒙皮受力较小,降低了旋翼蒙皮开裂的可能,延长了直升机旋翼结构的寿命。(The invention discloses a helicopter rotor wing structure and a manufacturing method thereof. Inject the packing chamber in the rotor cover, the one end in packing the chamber is connected to the wingtip counter weight box, be equipped with the balancing weight in the wingtip counter weight box, the one end of girder is walked around behind the rotor axle sleeve and is connected on the wingtip counter weight box with the other end of girder, the one end of leading edge counter weight silk is walked around behind the rotor axle sleeve and is connected on the balancing weight with the other end of leading edge counter weight silk, broach spare is established at filling the intracavity, broach spare falls into the multistrand with the girder, the filling is filled in order to fix the rotor axle sleeve in the filling intracavity, the girder, the leading edge counter weight. The rotor wing skin of the helicopter rotor wing structure is low in stress, the possibility of cracking of the rotor wing skin is reduced, and the service life of the helicopter rotor wing structure is prolonged.)

1. A helicopter rotor structure, comprising:

The rotor wing skin (1) is formed by laminating multiple layers of prepregs (11), and a filling cavity is defined in the rotor wing skin (1);

the wing tip counterweight box (2) is connected to one end of the filling cavity, and a counterweight block (21) is arranged in the wing tip counterweight box (2);

the rotor shaft sleeve (3), the said rotor shaft sleeve (3) is set up in the said packing cavity;

The main beam (4) is arranged in the filling cavity, one end of the main beam (4) bypasses the rotor shaft sleeve (3) and extends out of the filling cavity together with the other end of the main beam (4), and the two ends of the main beam (4) extending out of the filling cavity are connected to the wingtip counterweight box (2);

The leading edge counterweight wire (5) is arranged in the filling cavity, one end of the leading edge counterweight wire (5) bypasses the rotor shaft sleeve (3) and then extends out of the filling cavity together with the other end of the leading edge counterweight wire (5), and the two ends of the leading edge counterweight wire (5) extending out of the filling cavity are connected to the counterweight block (21);

the comb-tooth piece (6) is arranged in the filling cavity, and the comb-tooth piece (6) divides the main beam (4) into a plurality of strands;

The filling piece (7) is filled in the filling cavity to fix the rotor shaft sleeve (3), the main beam (4), the front edge counterweight wire (5) and the comb piece (6) in the filling cavity.

2. the helicopter rotor structure according to claim 1, characterized in that said rotor bushing (3) comprises a first bushing (31) and a second bushing (32), one end of said leading edge weight wire (5) being connected to said counterweight (21) after passing around said first bushing (31); one end of one part of the main beam (4) is connected to the wing tip counterweight box (2) after bypassing the first shaft sleeve (31), and one end of the other part of the main beam (4) is connected to the wing tip counterweight box (2) after bypassing the second shaft sleeve (32); the main beam (4) and the front edge counterweight wire (5) are wound on the first shaft sleeve (31) at intervals along the axial direction of the first shaft sleeve (31).

3. helicopter rotor structure according to claim 1, characterized in that said leading edge weight wire (5) is formed by winding tungsten wire or stainless steel wire with epoxy.

4. Helicopter rotor structure according to claim 1, characterized in that the main beam (4) is wound from glass fibre, carbon fibre or Kevlar impregnated resin.

5. A method of manufacturing a helicopter rotor structure, said helicopter rotor structure being a helicopter rotor structure according to any of claims 1 to 4, said method of manufacturing a helicopter rotor structure comprising the steps of:

S1: -applying a plurality of layers of said prepreg (11) to pre-form said rotor skin (1);

S2: winding the main beam (4) and the front edge counterweight wire (5), and winding the main beam (4) and the front edge counterweight wire (5) on the rotor shaft sleeve (3);

S3: laying the rotor wing skin (1) on a lower die (210) of a rotor wing die (200), and putting the main beam (4), the leading edge counterweight wire (5), the rotor wing shaft sleeve (3), the comb piece (6) and the filling piece (7) into the rotor wing die (200) and on the rotor wing skin (1);

S4: fitting the rotor shaft sleeve (3) on a pin (211) in the rotor mould (200) and keeping the main beam (4) and the leading edge counterweight wire (5) in a tensioning and straightening state;

S5: arranging the rotor wing skin (1) to enable the rotor wing skin (1) to wrap the main beam (4), the front edge counterweight wire (5), the rotor wing shaft sleeve (3), the comb-tooth piece (6) and the filling piece (7);

s6: buckling an upper die (220) of the rotor mould (200) on the lower die (210), and heating and curing;

s7: taking out the cured rotor wing skin (1) from the rotor wing mold (200), and connecting the wing tip counterweight box (2) on the rotor wing skin (1).

6. a method of manufacturing a helicopter rotor structure according to claim 5, wherein the pre-forming of said rotor skin (1) comprises the steps of:

q1: sequentially paving and pasting a plurality of layers of prepregs (11) on a skin jig (100);

Q2: covering a vacuum bag film (110) on the outer side of the plurality of layers of the prepregs (11), and adhering a sealing strip (120) between the vacuum bag film (110) and the skin jig (100);

q3; and vacuumizing the space in the vacuum bag film (110) to ensure that a plurality of layers of the skins are jointed to form the rotor wing skin (1).

7. a method of manufacturing a helicopter rotor structure according to claim 6 wherein, in step Q1, after a plurality of layers of said prepregs (11) are sequentially laid on said skin jig (100), a sheet of metal (130) is laid on the outermost prepreg (11).

8. A method of manufacturing a helicopter rotor structure according to claim 6, characterized in that said skin jig (100) is saddle-shaped.

9. A method of manufacturing a helicopter rotor structure according to claim 5, characterized in that in step S7, before installing said tip weight box (2) onto said cured rotor skin (1), said rotor skin (1) is trimmed to make the contact surface of said rotor skin (1) with said tip weight box (2) flat.

10. A method of manufacturing a helicopter rotor structure according to claim 5, characterized in that a tensioning device (300) is provided on one end of said lower mold (210) of said rotor mold (200), that in step S4, after fitting said rotor bushing (3) on said pin (211), said spar (4) and the end of said leading edge weight wire (5) remote from said rotor bushing (3) are fitted on said tensioning device (300) to achieve tensioning, and that in steps S5 and S6, said spar (4) and said leading edge weight wire (5) are kept in tension.

Technical Field

The invention relates to the technical field of flight, in particular to a helicopter rotor wing structure and a manufacturing method thereof.

Background

The helicopter rotor wing is a 'wing' for the helicopter to fly, and the helicopter can make various flying actions through the rotation, the swinging and the shimmy of the rotor wing. The rotor wing needs to overcome the huge centrifugal force generated by rotation when the helicopter flies, and also needs to bear various torques, bending moments and vibrations generated when the helicopter does various maneuvering actions, and various impact loads in a complex environment, so the rotor wing is the part with the most severe stress condition in the helicopter structure, wherein 25% -30% of the chord length of the rotor wing is the concentrated area of the rotor wing load, and the requirements on the structural strength and the rigidity are higher. The traditional helicopter rotor structure is divided into two forms of a metal structure and a composite material structure, wherein the composite material rotor is more and more emphasized in the industry due to the advantages of good designability, higher specific strength and modulus, fatigue resistance and the like. In general, the main components of a composite rotor comprise: bushing inserts, rotor skins, girders, leading edge weights, tip weights, fillers, etc., which are co-cured or sub-cured during rotor fabrication. However, conventional composite rotors also have significant disadvantages:

1. the load generated by the counterweight components (the front edge counterweight and the wing tip counterweight) can be only transmitted to the main beam and the shaft sleeve through the rotor wing skin, and the rotor wing skin is easy to crack under large stress.

2. the bonding area between rotor covering, infill, the girder is smaller, and the shear stress level that bonding resin bore is higher, leads to easily debonding between each component, has reduced the life of rotor.

disclosure of Invention

the invention aims to provide a helicopter rotor wing structure, wherein the rotor wing skin of the helicopter rotor wing structure is relatively small in stress, and the bonding area among the rotor wing skin, a filling piece and a main beam is relatively large, so that the possibility of debonding and cracking of the rotor wing skin is reduced, and the service life of the helicopter rotor wing structure is prolonged.

another object of the present invention is to provide a method for manufacturing a helicopter rotor structure, which can reduce the probability of fatigue failure of the internal structure of the rotor and prolong the service life of the helicopter rotor.

In order to achieve the technical effects, the technical scheme of the invention is as follows:

A helicopter rotor structure comprising: the rotor wing skin is formed by laminating multiple layers of prepreg, and a filling cavity is defined in the rotor wing skin; the wing tip counterweight box is connected to one end of the filling cavity, and a counterweight block is arranged in the wing tip counterweight box; the rotor shaft sleeve is arranged in the filling cavity; the main beam is arranged in the filling cavity, one end of the main beam bypasses the rotor shaft sleeve and extends out of the filling cavity together with the other end of the main beam, and the two ends of the main beam extending out of the filling cavity are connected to the wingtip counterweight box; the leading edge counterweight wire is arranged in the filling cavity, one end of the leading edge counterweight wire rounds the rotor shaft sleeve and extends out of the filling cavity together with the other end of the leading edge counterweight wire, and the two ends of the leading edge counterweight wire extending out of the filling cavity are connected to the counterweight block; the comb-tooth piece is arranged in the filling cavity and divides the main beam into a plurality of strands; the filling piece is filled in the filling cavity so as to fix the rotor shaft sleeve, the main beam, the front edge balance weight wire and the comb tooth piece in the filling cavity.

According to the helicopter rotor wing structure, one end of the front edge counterweight wire bypasses the rotor wing shaft sleeve and the other end of the front edge counterweight wire is connected to the counterweight block, so that centrifugal load generated in the rotation process of the helicopter rotor wing structure is directly transmitted to the rotor wing shaft sleeve and the main beam, the shearing stress borne by the rotor wing skin and the filling piece is reduced, the probability of debonding and cracking of the rotor wing skin is reduced, and the service life of the helicopter rotor wing structure is prolonged. And the comb tooth part divides the main beam into a plurality of parts, so that the bonding area among the main beam, the rotor wing skin and the filling part is increased, the stress level of the bonding surface is reduced, and the damage tolerance and the service life of the rotor wing structure of the helicopter are prolonged.

in some embodiments, the rotor shaft sleeve comprises a first shaft sleeve and a second shaft sleeve, and one end of the leading edge weight wire passes around the first shaft sleeve and then is arranged on the weight block; one end of one part of the main beam is connected to the wingtip counterweight box after bypassing the first shaft sleeve, and one end of the other part of the main beam is connected to the wingtip counterweight box after bypassing the second shaft sleeve; the main beam and the front edge counterweight wire are wound on the first shaft sleeve at intervals along the axial direction of the first shaft sleeve.

In some embodiments, the leading edge weight wire is formed by winding tungsten wire or stainless steel wire and epoxy resin.

In some embodiments, the main beam is formed by winding after glass fiber, carbon fiber or Kevlar fiber is soaked in resin.

a method of manufacturing a helicopter rotor structure, said helicopter rotor structure being a helicopter rotor structure as described above, said method of manufacturing a helicopter rotor structure comprising the steps of:

S1: laminating a plurality of layers of prepreg to pre-form the rotor wing skin;

S2: winding the main beam and the front edge counterweight wire, and winding the main beam and the front edge counterweight wire on the rotor shaft sleeve;

S3: laying the rotor wing skin on a lower die of a rotor wing die, and putting the main beam, the leading edge counterweight wires, the rotor wing shaft sleeve, the comb tooth piece and the filling piece into the rotor wing die and placing the main beam, the leading edge counterweight wires, the rotor wing shaft sleeve, the comb tooth piece and the filling piece on the rotor wing skin;

S4: fitting the rotor shaft sleeve on a pin in the rotor mold and maintaining the main beam and leading edge weight wire in a tensioned straightened state;

s5: arranging the rotor wing skin so that the rotor wing skin wraps the main beam, the leading edge counterweight wires, the rotor wing shaft sleeve, the comb-tooth piece and the filling piece;

S6: buckling an upper die of the rotor mould on the lower die, and heating and curing;

S7: and taking out the cured rotor wing skin from the rotor wing mold, and connecting the wing tip counterweight box on the rotor wing skin.

according to the helicopter rotor wing manufacturing method, the plurality of layers of prepreg are firstly laminated to be preformed to be the rotor wing skin and then placed on the lower die of the rotor wing die, so that the phenomenon of separation in the process of laying and pasting the plurality of layers of rotor wing skin is avoided; because the main beam and the front edge counterweight wire are always in a tensioning state in the curing process, the stress of the front edge counterweight wire of the main beam is more uniform, and the bearing capacity of the main beam and the front edge counterweight wire is improved; one end of the front-edge counterweight wire needs to bypass the rotor shaft sleeve and then is connected with the counterweight block at the other end in the manufacturing process, so that the shearing stress on the rotor skin and the filling piece is reduced, and the probability of cracking of the rotor skin is reduced; because the comb tooth piece is adopted to divide the main beam into a plurality of strands in the manufacturing process, the bonding area among the main beam, the rotor wing skin and the filling piece is increased, the stress level of the bonding surface is reduced, and the service life of the helicopter rotor wing structure is prolonged.

In some embodiments, the pre-forming of the rotor skin comprises the steps of:

q1: sequentially paving and pasting a plurality of layers of prepregs on a skin jig;

Q2: covering a vacuum bag film on the outer side of the plurality of layers of the prepreg, and adhering a sealing strip between the vacuum bag film and the skin jig;

q3; and vacuumizing the space in the vacuum bag film to ensure that the plurality of layers of prepregs are attached to form the rotor wing skin.

In some embodiments, in step Q1, after the multiple layers of prepregs are sequentially laid on the skin jig, a metal wrapping sheet is laid on the outermost prepreg.

in some embodiments, the skin fixture is saddle-shaped.

in some embodiments, prior to installing the tip weight box onto the cured rotor skin, the rotor skin is profile sanded to make the contact surface of the rotor skin with the tip weight box planar in step S7.

in some embodiments, a tensioning device is disposed on an end of the lower mold of the rotor mold, the spar and an end of the leading edge weight wire remote from the rotor shaft sleeve are engaged on the tensioning device to achieve tensioning after the rotor shaft sleeve is engaged on the pin in step S4, and the spar and the leading edge weight wire are maintained in tension in steps S5 and S6.

additional aspects and advantages of the invention will be set forth in part in the description which follows and, in part, will be obvious from the description, or may be learned by practice of the invention.

Drawings

Fig. 1 is a schematic structural view of a helicopter rotor structure according to an embodiment of the present invention.

Fig. 2 is a flow chart illustrating steps in a method of manufacturing a helicopter rotor structure according to an embodiment of the present invention.

Figure 3 is a schematic structural view of a rotor skin preform provided in accordance with an embodiment of the present invention.

Fig. 4 is a schematic structural view of a rotor mold according to an embodiment of the present invention.

Fig. 5 is a schematic structural view of a tensioner in accordance with an embodiment of the present invention.

Reference numerals:

1. a rotor wing skin; 11. covering a skin; 2. a wingtip weight box; 21. a balancing weight; 3. a rotor shaft sleeve; 31. a first bushing; 32 a second bushing; 4. a main beam; 5. leading edge counterweight wires; 6. comb tooth member 7, filler

100. A skin tool; 110. vacuum bag film; 120. a sealing strip; 130. a metal clad sheet;

200. A rotor mould; 210. a lower die; 211. a pin; 220, 220; an upper die;

300. A tensioning device; 310. a support; 320. tensioning the spring; 330. tensioning the adjusting screw.

Detailed Description

in order to make the technical problems solved, the technical solutions adopted and the technical effects achieved by the present invention clearer, the technical solutions of the present invention are further described below by way of specific embodiments with reference to the accompanying drawings.

in the description of the present invention, it is to be understood that the terms "central," "longitudinal," "lateral," "length," "width," "thickness," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," "clockwise," "counterclockwise," "axial," "radial," "circumferential," and the like are used in the orientations and positional relationships indicated in the drawings for convenience in describing the invention and to simplify the description, and are not intended to indicate or imply that the referenced device or element must have a particular orientation, be constructed and operated in a particular orientation, and are not to be considered limiting of the invention.

furthermore, features defined as "first" and "second" may explicitly or implicitly include one or more of the features for distinguishing between descriptive features, non-sequential, non-trivial and non-trivial. In the description of the present invention, "a plurality" means two or more unless otherwise specified.

In the description of the present invention, it should be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.

A specific structure of a helicopter rotor structure according to an embodiment of the present invention will be described below with reference to fig. 1.

As shown in fig. 1, the helicopter rotor structure of the embodiment of the present invention includes a rotor skin 1, a tip weight box 2, a rotor shaft sleeve 3, a main beam 4, a leading edge weight wire 5, a comb member 6, and a filler member 7. The rotor wing skin 1 is formed by laminating multiple layers of prepreg 11, a filling cavity is defined in the rotor wing skin 1, a wing tip counterweight box 2 is connected at one end of the filling cavity, counterweight blocks 21 are fixed in the counterweight box 2 through bolts, a rotor wing shaft sleeve 3 is arranged in the filling cavity, a girder 4 is arranged in the filling cavity, one end of the girder 4 extends out of the filling cavity together with the other end of the girder 4 after bypassing the rotor wing shaft sleeve 3, two ends of the girder 4 extending out of the filling cavity are connected to the wing tip counterweight box 2, a front edge counterweight wire 5 is arranged in the filling cavity, one end of the front edge counterweight wire 5 extends out of the filling cavity together with the other end of the front edge counterweight wire 5 after bypassing the rotor wing shaft sleeve 3, two ends of the front edge counterweight wire 5 extending out of the filling cavity are connected to the counterweight blocks 21, a comb tooth piece 6 is arranged in the filling cavity, the girder 4 is divided into multiple strands by the, The leading edge weight wire 5 and the comb teeth 6 are fixed in the filling cavity.

It can be understood that, in the invention, one end of the front edge counterweight wire 5 winds the back of the back rotor shaft sleeve 3 and the other end is connected to the counterweight 21, which not only plays a role of adjusting the gravity center of the helicopter rotor structure, but also can independently bear the centrifugal force of the rotor, namely, the centrifugal load of the counterweight 21 is directly transmitted to the rotor shaft sleeve 3 and the main beam 4 when the helicopter rotor structure rotates, thereby reducing the shear stress on the rotor skin 1 and the filling piece 7, further reducing the probability of cracking the rotor skin 1 and prolonging the service life of the helicopter rotor structure.

Meanwhile, the comb piece 6 can divide the main beam 4 into a plurality of strands, so that the bonding area between the main beam 4 and the rotor wing skin 1 and between the main beam 4 and the filling piece 7 is increased, and the stress level of a bonding surface is reduced, so that the debonding probability of the main beam 4 and the rotor wing skin 1 and between the main beam 4 and the filling piece 7 is reduced, and the service life of the helicopter rotor wing structure is prolonged.

according to the helicopter rotor wing structure, one end of the front edge counterweight wire 5 bypasses the rotor wing shaft sleeve 3 and the other end is connected to the counterweight 21, so that centrifugal load generated in the rotation process of the helicopter rotor wing structure is directly transmitted to the rotor wing shaft sleeve 3 and the main beam 4, the shearing stress on the rotor wing skin 1 and the filling piece 7 is reduced, the probability of debonding and cracking of the rotor wing skin 1 is reduced, and the service life of the helicopter rotor wing structure is prolonged. And the comb tooth piece 6 divides the main beam 4 into a plurality of, has increased the bonding area between main beam 4, rotor skin 1 and the filler 7, has reduced the stress level of bonding surface, has prolonged the life of helicopter rotor structure.

in some embodiments, the rotor hub 3 includes a first hub 31 and a second hub 32, and one end of the leading-edge weight wire 5 is connected to the weight 21 after passing around the first hub 31. One end of one part of the main beam 4 is connected to the wingtip counterweight box 2 together with the other end after bypassing the first shaft sleeve 31, one end of the other part of the main beam 4 is connected to the wingtip counterweight box 2 together with the other end after bypassing the second shaft sleeve 32, and the position of the main beam 4 wound on the first shaft sleeve 31 and the position of the front edge counterweight wire 5 wound on the first shaft sleeve 31 are arranged at intervals along the axial direction of the first shaft sleeve 31. Therefore, the strength of the helicopter rotor structure can be better ensured. The position of the main beam 4 wound on the first shaft sleeve 31 and the position of the leading edge counterweight wire 5 wound on the first shaft sleeve 31 are arranged at intervals along the axial direction of the first shaft sleeve 31, so that the main beam 4 and the leading edge counterweight wire 5 can be prevented from being wound together, and the force transmission function of the main beam 4 and the leading edge counterweight wire 5 can be prevented from being influenced.

In some embodiments, the leading edge weight wire 5 is formed by winding tungsten wire or stainless steel wire with epoxy resin. It can be understood that the tungsten wire or the stainless steel wire is used as the leading edge counterweight wire 5, so that the mechanical property of the leading edge counterweight wire 5 can be ensured, and the centering function of the leading edge counterweight wire 5 and the force transmission function of the leading edge counterweight wire 5 can be better realized. In addition, the leading edge weight wire 5 further comprises epoxy resin, so that in the production process of the helicopter rotor structure, after heating and curing, the leading edge weight wire 5 can be well connected with the filling piece 7 and the rotor skin 1, the rigidity of the leading edge weight wire 5 is improved, and the possibility of deformation of the leading edge weight wire 5 is reduced. Advantageously, the tungsten wire or stainless steel wire has a diameter of 0.1mm to 0.5 mm.

Of course, in other embodiments of the present invention, the leading edge weighting wire 5 may be formed by winding other metal wires and resin materials, and is not limited to the tungsten wire, the stainless steel wire and the surrounding resin in this embodiment.

In some embodiments, the main beams 4 are formed by winding glass fiber, carbon fiber or Kevlar fiber after being soaked in resin. It can be understood that the main beam 4 comprises glass fiber, carbon fiber or kevlar fiber, which guarantees the mechanical property of the main beam 4 on the premise of ensuring the light weight of the main beam 4, thereby guaranteeing the mechanical property of the whole helicopter rotor structure. In addition, the main beam 4 is formed by winding the fiber-impregnated resin, so that the main beam 4 can be well connected with the filler 7 and the rotor skin 1 after being heated and cured in the production process of the helicopter rotor structure, the rigidity of the main beam 4 is improved, and the possibility of deformation of the main beam 4 is reduced. Of course, in other embodiments of the present invention, the main beam 4 may be formed by winding other fibers after being impregnated with resin, and is not limited to the glass fiber, the carbon fiber, or the kevlar fiber of the present invention.