CN117780775A - Hinge for aircraft and manufacturing method thereof - Google Patents

Abstract

The invention provides a hinge for an aircraft and a manufacturing method thereof, which relate to the technical field of aircraft hinges and comprise the following steps: the first rotating part and the second rotating part are rotationally connected through a plastic bearing and a pin, and the first rotating part and the second rotating part are made of fiber reinforced composite materials; the problem that the hinges commonly used in the prior art have defects is solved.

Description

Hinge for aircraft and manufacturing method thereof

Technical Field

The invention belongs to the technical field of aircraft hinges, and particularly relates to a hinge for an aircraft and a manufacturing method thereof.

Background

Hinges are an important structure on an aircraft that can be used to connect rotating control surfaces with stationary airfoils. For lightweight unmanned aerial vehicles, hinges are typically formed of a polymeric material wound wire or metal. The former has the advantages of simple structure and light weight, but has poor process consistency and difficult guarantee of precision; the latter has the advantages of good processability, but has large weight and poor corrosion resistance, and once phenomena such as local rust occur, the rotation precision of the control surface is seriously affected, thereby affecting the operability of the aircraft.

Disclosure of Invention

The invention aims to overcome the defects in the prior art, and provides a hinge for an aircraft and a manufacturing method thereof, which solve the problem that the hinges commonly used in the prior art have defects.

In order to achieve the above object, the present invention provides a hinge for an aircraft, comprising:

the first rotating part and the second rotating part are rotationally connected through plastic bearings and pins, and the materials of the first rotating part and the second rotating part are fiber reinforced composite materials.

Optionally, the first rotating part includes a first bottom plate and a first lug, the first lug is connected to one side of the first bottom plate, the second rotating part includes a second bottom plate and a second lug, and the second lug is connected to one side of the second bottom plate.

Optionally, one first tab is provided, two second tabs are provided, and a receiving groove is provided between the two second tabs, and the receiving groove can receive the first tab.

Optionally, the two sides of the first lug are provided with reinforcing ribs, and are connected with the first bottom plate through the reinforcing ribs.

Optionally, the fiber reinforced composite material comprises a matrix material and a fiber material.

Optionally, the matrix material is epoxy resin, and the fiber material is carbon fiber.

Optionally, the first lug is provided with a first through hole, the plastic bearing is arranged in the first through hole, the second lug is provided with a second through hole, a plastic bushing is arranged in the second through hole, and the pin penetrates through the plastic bushing and an inner hole of the plastic bearing.

Optionally, the plastic bearing is a deep groove ball bearing or a radial spherical plain bearing, when the plastic bearing is the deep groove ball bearing, the first rotating part and the second rotating part are rotationally connected through the deep groove ball bearing and the pin to form a single-degree-of-freedom hinge, and when the plastic bearing is the radial spherical plain bearing, the first rotating part and the second rotating part are rotationally connected through the radial spherical plain bearing and the pin to form a multi-degree-of-freedom hinge.

The invention also provides a method for manufacturing the hinge for the aircraft, which is used for manufacturing the hinge for the aircraft and comprises the following steps:

setting the model of the plastic bearing, and setting the shapes and the sizes of the first rotating part, the second rotating part and the pin;

manufacturing a first rotating part and a second rotating part by utilizing fiber reinforced composite materials, and embedding a plastic bearing into the first rotating part;

the first rotating part and the second rotating part are rotationally connected through a pin penetrating through a plastic bearing.

Optionally, manufacturing the first and second rotating parts from a fiber reinforced composite material includes:

obtaining a first mold for the first rotating portion and a second mold for the second rotating portion;

layering fiber reinforced composite prepreg in the first mold and the second mold respectively, wherein an included angle is formed between the laying directions of carbon fiber materials in the fiber reinforced composite prepreg of the adjacent layers;

and integrally curing and forming the fiber reinforced composite prepreg layered and paved in the first die and the second die.

The invention provides a hinge for an aircraft and a manufacturing method thereof, which have the beneficial effects that: the hinge for the aircraft adopts the fiber-reinforced composite material to manufacture the first rotating part and the second rotating part, realizes the rotating connection of the first rotating part and the second rotating part through the plastic bearing and the pin, further realizes the function of the hinge, has the advantages of light weight and corrosion resistance, and the selection of the fiber-reinforced composite material and the plastic bearing can also lead the bearing performance to be higher, so that the fiber-reinforced composite material can bear instantaneous impact load and avoid damage.

Additional features and advantages of the invention will be set forth in the detailed description which follows.

Drawings

The foregoing and other objects, features and advantages of the invention will be apparent from the following more particular descriptions of exemplary embodiments of the invention as illustrated in the accompanying drawings wherein like reference numbers generally represent like parts throughout the exemplary embodiments of the invention.

Fig. 1 shows a schematic overall structure of a hinge for an aircraft according to an embodiment of the invention.

Fig. 2 shows a schematic overall three-dimensional structure of a hinge for an aircraft according to one embodiment of the invention.

Fig. 3 shows a schematic structural view of a first turning part of a hinge for an aircraft according to an embodiment of the invention.

Fig. 4 shows a schematic three-dimensional structure of a first turning part of a hinge for an aircraft according to an embodiment of the invention.

Fig. 5 shows a schematic structural view of a second turning part of a hinge for an aircraft according to an embodiment of the invention.

Fig. 6 shows a schematic three-dimensional structure of a second turning part of a hinge for an aircraft according to an embodiment of the invention.

Fig. 7 shows a schematic view of an assembly of a hinge for an aircraft according to an embodiment of the invention.

Fig. 8 shows a layering structure schematic of a first turning part of a hinge for an aircraft according to an embodiment of the invention.

Fig. 9 shows a layering structure schematic of a second turning part of a hinge for an aircraft according to an embodiment of the invention.

Fig. 10 shows a flow chart of a method of manufacturing a hinge for an aircraft according to one embodiment of the invention.

Reference numerals illustrate:

1. a first rotating part; 2. a second rotating part; 3. a plastic bearing; 4. a pin; 5. a first base plate; 6. a first ear; 7. reinforcing ribs; 8. a second base plate; 9. a second tab; 10. a plastic bushing; 11. a first portion; 12. a second portion; 13. a third section; 14. a fourth section; 15. a fifth section; 16. and a sixth section.

Detailed Description

Preferred embodiments of the present invention will be described in more detail below. While the preferred embodiments of the present invention are described below, it should be understood that the present invention may be embodied in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the invention to those skilled in the art.

As shown in fig. 1 to 9, the present invention provides a hinge for an aircraft, comprising:

the first rotating part 1 and the second rotating part 2 are rotationally connected through a plastic bearing 3 and a pin 4, and the materials of the first rotating part 1 and the second rotating part 2 are fiber reinforced composite materials.

Specifically, in order to solve the problem that the hinges commonly used in the prior art have defects, the hinge for the aircraft provided by the invention adopts the fiber reinforced composite material to manufacture the first rotating part 1 and the second rotating part 2, and as shown in fig. 1 and 2, the rotating connection of the first rotating part 1 and the second rotating part 2 is realized through the plastic bearing 3 and the pin 4, so that the function of the hinge is realized, the hinge has the advantages of light weight and corrosion resistance, and the selection of the fiber reinforced composite material and the plastic bearing 3 can also enable the bearing performance to be higher, so that the hinge can bear instantaneous impact load to avoid damage.

Furthermore, the hinge for the aircraft can change the freedom degree of the hinge by changing the model of the plastic bearing 3, the hinge with single freedom degree can realize the rotation in the accurate direction, and the hinge with multiple freedom degrees can not only realize the rotation function of the control surface, but also effectively solve the problem of clamping stagnation caused by the installation error of the control surface and the deformation of the control surface; meanwhile, the fiber reinforced composite material of the connecting surface of the first rotating part 1 and the second rotating part 2 has flexible structural form, can be connected by adopting cementing or bolt components, and has wide application range.

Optionally, the first rotating part 1 includes a first base plate 5 and a first lug 6, the first lug 6 is connected to a side surface of the first base plate 5, the second rotating part 2 includes a second base plate 8 and a second lug 9, and the second lug 9 is connected to a side surface of the second base plate 8.

Specifically, as shown in fig. 3 to 6, the first bottom plate 5 and the second bottom plate 8 are respectively used as connection surfaces of the first rotating part 1 and the second rotating part 2, and are used for being connected with a component on the aircraft, which generates relative rotation, the first bottom plate 5 can be used for being connected with a main wing stringer of the aircraft, the connection mode can be used for bonding, mechanical connection or both, when the mechanical connection is adopted, a first mounting hole is arranged on the first bottom plate 5, in the embodiment, the first bottom plate 5 is a rectangular plate, so that the first bottom plate 5 is convenient to bond with the main wing square stringer, but when the main wing adopts a circular tail beam, the first bottom plate 5 can be bonded with an arc structure matched with the main wing stringer; the second bottom plate 8 can be used for being connected with the control surface girder of the aircraft, and the connection mode can adopt the bonding, and the shape of second bottom plate 8 is decided by the shape of control surface girder, and the two phase-match, in this embodiment, second bottom plate 8 is convex structure, half parcel formula bonds in the control surface girder outside.

Optionally, one first tab 6 is provided, two second tabs 9 are provided, and a receiving groove is provided between the two second tabs 9, the receiving groove being capable of receiving the first tab 6.

Specifically, as shown in fig. 1 and 2, a first lug 6 is movably inserted between two ear light second lugs 9, and the plastic bearing 3 and the pin 4 are used for realizing rotary connection, so that the structure is more compact and stable.

Optionally, the first ear 6 is provided with a stiffener 7 on both sides and is connected to the first bottom plate 5 by the stiffener 7.

Specifically, the first lug 6 of single ear can be strengthened with the connection of first bottom plate 5 by the setting of strengthening rib 7, improves the intensity and the stability of structure.

Optionally, the fiber-reinforced composite material comprises a matrix material and a fiber material.

Specifically, the matrix material can be resin, the fiber material can be fiber with enhanced strength, and the fiber reinforced composite material formed by the resin and the fiber material has the advantages of light weight, high strength, corrosion resistance and good bonding performance.

Optionally, the matrix material is epoxy resin, and the fiber material is carbon fiber.

Specifically, the carbon fibers form fiber reinforced composite material prepreg in the matrix material, the fiber reinforced composite material prepreg is sheet-shaped, the fiber reinforced composite material prepreg is laid in a die in a layering mode, and then the fiber reinforced composite material prepreg is integrally cured and formed to form a first rotating part 1 and a second rotating part 2 of the carbon fiber composite material.

Optionally, the first lug 6 is provided with a first through hole, the plastic bearing 3 is arranged in the first through hole, the second lug 9 is provided with a second through hole, the second through hole is internally provided with a plastic bushing 10, and the pin 4 penetrates through the plastic bushing 10 and the inner hole of the plastic bearing 3.

Specifically, the plastic bearing 3 is integrally formed in the first through hole of the first lug 6, integrally connected with the first lug 6 in a pre-embedded manner, and the plastic bushing 10 is integrally formed in the second through hole of the second lug 9 and integrally connected with the second lug 9 in a pre-embedded manner; the arrangement of the plastic bushing 10 in the second lugs 9 on both sides of the first lugs 6 forms a protection for the partial carbon fiber composite material around the hole, the end of the plastic bushing 10 being in contact with the plastic bearing 3.

As shown in fig. 7, the hinge for an aircraft is provided with a plastic bearing 3 on a first lug 6 of a first rotating part 1, two second lugs 9 of a second rotating part 2 are respectively provided with a plastic bushing 10, when in assembly, the axes of the plastic bearing 3 and the plastic bushing 10 are aligned, and then a pin 4 is penetrated, so that the rotating connection of the first rotating part 1 and the second rotating part 2 can be realized, and the assembly is completed; of course, the pin 4 may be limited by using a pin 4 with a limiting structure or by using a pin with a through cotter or the like.

In this embodiment, as shown in fig. 8, the layering of the fiber reinforced composite prepreg of the first rotating part 1 is divided into three parts, the first bottom plate 5 is a first part 11, two single-lug outer layers are both L-shaped and are a second part 12, the two parts are symmetrically arranged to form a first lug 6, the reinforcing rib 7 is a third part 13, the thickness of the first part 11 is 0.8-1.5mm, the thickness of the second part 12 is determined according to the size of the plastic bearing 3, so that the plastic bearing 3 can be pre-embedded into the second part 12, the thickness of the third part 13 is 1.5-2mm, wherein the first part 11, the second part 12 and the third part 13 can be formed by sequentially layering the fiber reinforced composite prepreg in a first mold for multiple times, and are integrally cured and formed, and the third part 13 and the second part 12 can also share the same fiber reinforced composite prepreg layering; as shown in fig. 9, the lay-up of the fiber reinforced composite prepreg of the second rotating part 2 is also divided into three parts, the second bottom plate 8 is a fourth part 14, two binaural outer layers are L-shaped, and are a fifth part 15, one binaural inner layer is U-shaped, and is a sixth part 16, the two binaural outer layers are connected with the one binaural inner layer to form two second lugs 9, the thickness of the fourth part 14 is 0.8-1.5mm, and the thicknesses of the fourth part 14 and the fifth part 15 are 1.5-2mm.

Optionally, the plastic bearing 3 is a deep groove ball bearing or a radial spherical plain bearing, when the plastic bearing 3 is a deep groove ball bearing, the first rotating part 1 and the second rotating part 2 are rotationally connected through the deep groove ball bearing and the pin 4 to form a single-degree-of-freedom hinge, and when the plastic bearing 3 is a radial spherical plain bearing, the first rotating part 1 and the second rotating part 2 are rotationally connected through the radial spherical plain bearing and the pin 4 to form a multi-degree-of-freedom hinge.

Specifically, the plastic bearing 3 adopts a standard goods shelf product, has low cost and high precision, and can be replaced according to different freedom degree requirements, for example, when the hinge requirement is single freedom degree, the combination of the first rotating part 1 and the second rotating part 2 with the deep groove ball bearing can be used, when the hinge requirement is multiple freedom degrees, the combination of the first rotating part 1 and the second rotating part 2 with the centripetal joint bearing can be used, and the switching of different freedom degrees of the hinge can be realized only by replacing the first rotating part with different plastic bearings 3.

As shown in fig. 10, the present invention further provides a method for manufacturing a hinge for an aircraft, for manufacturing the hinge for an aircraft, including:

setting the model of the plastic bearing 3, and setting the shapes and sizes of the first rotating part 1, the second rotating part 2 and the pin 4;

manufacturing a first rotating part 1 and a second rotating part 2 by using fiber reinforced composite materials, and embedding a plastic bearing 3 into the first rotating part 1;

the first rotary part 1 and the second rotary part 2 are rotatably connected by a pin 4 through a plastic bearing 3.

Optionally, manufacturing the first rotating part 1 and the second rotating part 2 from a fiber reinforced composite material comprises:

obtaining a first mold for the first rotating portion 1 and a second mold for the second rotating portion 2;

layering fiber reinforced composite prepreg in the first mold and the second mold respectively, wherein an included angle is formed between the laying directions of carbon fiber materials in the fiber reinforced composite prepreg of the adjacent layers;

and integrally curing and forming the fiber reinforced composite prepreg layered and paved in the first die and the second die.

In this embodiment, a plastic bearing 3 is pre-buried in the first rotating portion 1, and a plastic bushing 10 is pre-buried in the second rotating portion 2.

In summary, when the hinge for the aircraft is manufactured, taking application to the unmanned aerial vehicle as an example, the model of the plastic bearing 3 is determined according to the maximum instantaneous impact load and the requirement of the freedom degree of the hinge, which can occur to the unmanned aerial vehicle; the shape and basic dimensions of the first rotating part 1, the second rotating part 2 and the pin 4 are designed according to the shape of the main wing and the control surface, the relative positions of the main wing and the control surface and the dimension of the plastic bearing 3; when the first rotating part 1 is molded, the plastic bearing 3 is embedded into the first lug 6, and is integrally cured and molded; when the second rotating part 2 is molded, 4 plastic bushings 10 are embedded into the second lug 9, and are integrally cured and molded; the 4 plastic bushings 10 are positioned at the two side edges of the two second lugs 9 and used for protecting the two second lugs 9 of the carbon fiber composite material and increasing the wear resistance of the carbon fiber composite material; the first rotating part 1 and the second rotating part 2 are manufactured in a mode that fiber reinforced composite material prepregs are paved in a die for multiple times, and the included angle between the paving directions of carbon fiber materials in the fiber reinforced composite material prepregs of adjacent layers is 45 degrees, so that the structural strength is improved; after the first rotating part 1 and the second rotating part 2 are respectively paved and solidified, the assembly is completed according to the relative positions. When the hinge for the aircraft is used, the product is only required to be respectively bonded or screwed with the main wing stringers and the control surface main beams according to the design positions; if the degree of freedom of the hinge needs to be replaced, the model of the plastic bearing 3 embedded in the first rotating part 1 is changed, namely the first rotating part 1 with the corresponding plastic bearing 3 is replaced.

The foregoing description of embodiments of the invention has been presented for purposes of illustration and description, and is not intended to be exhaustive or limited to the embodiments disclosed. Many modifications and variations will be apparent to those of ordinary skill in the art without departing from the scope and spirit of the various embodiments described.

Claims (10)

1. A hinge for an aircraft, comprising:

the first rotating part and the second rotating part are rotationally connected through plastic bearings and pins, and the materials of the first rotating part and the second rotating part are fiber reinforced composite materials.

2. The hinge for an aircraft according to claim 1, wherein the first rotating portion includes a first base plate and a first tab, the first tab being connected to one side of the first base plate, and the second rotating portion includes a second base plate and a second tab, the second tab being connected to one side of the second base plate.

3. The hinge for an aircraft according to claim 2, wherein one of the first tabs is provided, two of the second tabs are provided, and a receiving groove is provided between the two second tabs, the receiving groove being capable of receiving the first tab.

4. A hinge for an aircraft according to claim 3, wherein the first tab is provided with a stiffener on both sides and is connected to the first floor by the stiffener.

5. The hinge for an aircraft of claim 1, wherein the fiber-reinforced composite material comprises a matrix material and a fiber material.

6. The hinge for an aircraft according to claim 5, wherein the base material is epoxy resin and the fiber material is carbon fiber.

7. A hinge for an aircraft according to claim 3, wherein the first tab is provided with a first through hole, the plastic bearing is provided in the first through hole, the second tab is provided with a second through hole, a plastic bushing is provided in the second through hole, and the pin penetrates through the plastic bushing and the inner hole of the plastic bearing.

8. The hinge for an aircraft according to claim 7, wherein the plastic bearing is a deep groove ball bearing or a radial spherical joint bearing, and when the plastic bearing is the deep groove ball bearing, the first rotating portion and the second rotating portion are rotatably connected through the deep groove ball bearing and the pin to form a single degree of freedom hinge, and when the plastic bearing is a radial spherical joint bearing, the first rotating portion and the second rotating portion are rotatably connected through the radial spherical joint bearing and the pin to form a multiple degree of freedom hinge.

9. A method of manufacturing a hinge for an aircraft, for manufacturing a hinge for an aircraft according to any one of claims 1 to 8, comprising:

setting the model of the plastic bearing, and setting the shapes and the sizes of the first rotating part, the second rotating part and the pin;

manufacturing a first rotating part and a second rotating part by utilizing fiber reinforced composite materials, and embedding a plastic bearing into the first rotating part;

the first rotating part and the second rotating part are rotationally connected through a pin penetrating through a plastic bearing.

10. The method of manufacturing a hinge for an aircraft according to claim 9, wherein manufacturing the first and second rotating parts from a fiber-reinforced composite material comprises:

obtaining a first mold for the first rotating portion and a second mold for the second rotating portion;

layering fiber reinforced composite prepreg in the first mold and the second mold respectively, wherein an included angle is formed between the laying directions of carbon fiber materials in the fiber reinforced composite prepreg of the adjacent layers;

and integrally curing and forming the fiber reinforced composite prepreg layered and paved in the first die and the second die.