A carbon / carbon brake device for aircraft

Abstract

The present application provides a carbon / carbon brake device for aircraft, which is nested in the annular groove of the wheel assembly 19, and the brake housing 2 is a hollow cylindrical structure, the first end of the brake housing 2 is close to the main landing gear flange, and the second end is away from the main landing gear flange; the brake housing 2 is fixed on the flange of the main landing gear main shaft; the cylinder seat assembly 1 is assembled on the first end of the brake housing 2; the cylinder seat assembly 1 is a hollow annular structure, and the side of the cylinder seat assembly 1 facing the brake housing 2 is provided with N piston chambers, and an oil circuit is provided between adjacent piston chambers; a piston assembly 8 is placed in each piston chamber of the cylinder seat assembly 1; the semi-circular structure is provided, and is provided at the first end of the brake housing 2 for limiting the brake housing 2 in the axial direction; the thermal insulation ring 10, the pressure plate assembly 3, the dynamic plate assembly 4, the single-sided static plate 5, the pressure plate 6; the steel pressure plate assembly 7 are all annular structures.

Description

Technical Field

[0001] The present invention belongs to the field of aircraft wheel brakes in aviation airborne equipment, and specifically relates to a carbon / carbon brake device for aircraft. Background Art

[0002] Carbon / carbon brakes are currently a mainstream disc brake system for aircraft. They are paired with the main wheels to form a brake wheel mounted on the aircraft's main landing gear shaft. They are used for takeoff, taxiing, braking, ground parking, and engine testing. The brake system's main function is to provide braking torque to the main wheels when the aircraft lands, absorb the aircraft's kinetic energy, and dissipate it as heat. It is a key component of the aircraft's braking system.

[0003] The main components of the current mainstream aircraft brake system include cylinder seat assembly, brake housing, pressure plate assembly, dynamic plate assembly, single-sided static plate, pressure plate, steel pressure plate assembly, etc.

[0004] For example, patent CN106672218A discloses an aircraft carbon / ceramic brake system. The brake housing is mounted on a cylinder base assembly, axially restrained by two half-rings and angularly restrained by three blocks, connecting and securing various components. A piston assembly is mounted within the cylinder base assembly, converting the braking system's braking pressure into axial thrust during braking. A steel pressure plate assembly is secured to the end of the brake housing away from the cylinder base assembly with high-strength bolts to withstand braking thrust. The pressure plate assembly, dynamic plate assembly, static plate, and pressure plate are mounted on the brake housing and axially positioned by the steel pressure plate assembly. Braking force is generated through friction between the brake plates. The diameter of the pressure plate assembly is adjusted based on braking performance indicators. This invention features a simple structure, easy installation and operation, and convenient inspection and maintenance, significantly reducing maintenance workload and labor intensity.

[0005] For example, patent CN110541900 discloses a helicopter brake system comprising a brake housing, a pressure cup, a pressure plate, a static plate, a dynamic plate assembly, a pressure plate, a steel pressure ring, a cylinder seat, a piston assembly, and a thrust ring. The piston assembly is fixed in a recess in the cylinder seat. The brake housing is a cap-type structure, with the front end of the brake housing detachably connected to the cylinder seat. The steel pressure ring is fixedly connected to the pressure plate. The pressure plate and the static plate are axially slidingly connected to the brake housing. The dynamic plate assembly is rotatably connected to the brake housing. The static plate and dynamic plate assemblies are alternately arranged. The pressure plate is fixedly connected to the brake housing via a pressure cup. The pressure cup is a rotating body, with the front end of the pressure cup inserted into a hole in the pressure cup and the rear end inserted into a through-hole in the brake housing. The pressure cup is connected to the brake housing via rivets and a thrust ring. This invention solves the problem of the complex structure of existing helicopter brake systems, which greatly inconveniences the maintenance of helicopter brake systems.

[0006] However, the existing brake device has the following problems during design: the width of the sealing ring groove at the fitting point of the bushing and the cylinder seat is too large. When the brake device is working under extreme conditions, there is a gap in the sealing groove, and part of the sealing ring body may be squeezed into the fitting point of the bushing and the cylinder seat, resulting in extrusion and distortion, which affects the sealing performance; the sealing ring groove is located at the piston orifice. During the operation of the brake device, there is excessive deformation and the fitting guide length is too short, which can easily cause excessive coaxiality between the cylinder seat and the bushing, which is not conducive to the fit between the two, resulting in eccentricity, reduced sealing performance, and a huge impact on the reliability and safety of the brake device. Summary of the Invention

[0007] The present application aims to provide a new carbon / carbon brake device for aircraft, which is used to solve the hydraulic oil leakage problem caused by the static sealing part of the piston sleeve and cylinder seat connection when the original brake device is used in the extreme low temperature environment of -55±3℃ without changing the interface relationship, brake system parameters, installation and disassembly, and operation requirements of the original brake device, thereby improving the working reliability and safety of the brake device and enhancing the convenience of field maintenance of the brake device.

[0008] The technical solution of the invention is: a carbon / carbon brake device for aircraft, which is nested in the annular groove of the wheel assembly 19, including a cylinder seat assembly 1; a brake housing 2; a pressure plate assembly 3; a dynamic plate assembly 4; a single-sided static plate 5; a pressure plate 6; a steel pressure plate assembly 7; a piston assembly 8; a half-circuit ring 9; an insulation ring 10; an indicator rod 11; a sensor transmission device 12; an automatic anti-skid transmission device 13; and a cover plate 14, wherein:

[0009] The brake housing 2 is a hollow cylindrical structure, the first end of the brake housing 2 is close to the main landing gear flange, and the second end is away from the main landing gear flange; the brake housing 2 is fixed to the flange of the main landing gear main shaft; the cylinder seat assembly 1 is assembled on the first end of the brake housing 2; the cylinder seat assembly 1 is a hollow annular structure, and the side of the cylinder seat assembly 1 facing the brake housing 2 is provided with N piston chambers, and an oil path is provided between adjacent piston chambers; a piston assembly 8 is placed in each piston chamber of the cylinder seat assembly 1; the half-circuit 9 is an annular structure, and is provided on the brake The first end of the housing 2 is used to limit the brake housing 2 in the axial direction. The thermal insulation ring 10, pressure plate assembly 3, movable plate assembly 4, single-sided static plate 5, pressure plate 6, and steel pressure plate assembly 7 are all annular structures. The thermal insulation ring 10, pressure plate assembly 3, movable plate assembly 4, single-sided static plate 5, and pressure plate 6 are arranged on the outer wall of the brake housing 2 from the first end to the second end. The indicator rod 11 is arranged on the pressure plate assembly 3. The sensor transmission device 12, automatic anti-skid transmission device 13, and cover plate 14 are all arranged on the outer end surface of the cylinder base assembly 1. A positioning block 15 is arranged on the first end of the brake housing 2 to limit the brake housing 2 in the circumferential direction.

[0010] Specifically, the single-sided static disc 5 and the dynamic disc assembly 4 are assembled at intervals. During assembly, the convex key on the inner diameter of the single-sided static disc 5 is inserted into the keyway on the inner wall of the brake housing 2, and remains relatively stationary with the brake housing 2 in the circumferential direction, and can slide along the keyway in the axial direction; the keyway on the outer diameter of the dynamic disc assembly 4 is installed on the guide rail of the wheel assembly 19, and can rotate with the wheel assembly 19 in the circumferential direction, and slide in the radial direction and along the axial direction of the guide rail.

[0011] Specifically, the brake housing 2 is made of titanium alloy material.

[0012] Specifically, the indicator rod 11 is used to check the wear degree of the brake disc and has a function of error-proofing during installation.

[0013] Specifically, the heat insulating ring 10 is installed on one end of the cylinder seat 1 close to the brake disc, and is used to block the heat radiation generated when the brake disc is working.

[0014] Specifically, the steel pressure plate assembly 7 is fixed to the end of the brake housing 2 away from the landing gear main shaft flange using high-strength bolts to withstand the axial thrust generated by the brake device.

[0015] Specifically, the steel clamp of the movable plate assembly 4 is connected by screws 17 .

[0016] Specifically, the outer end surface of the cylinder base assembly 1 is fixed by using a stainless steel wire 18 .

[0017] In summary, the present application provides a carbon / carbon brake device for aircraft, which not only reduces the deformation of the static sealing part during operation but also increases the coaxiality of the cylinder seat by moving the static sealing part in the piston hole of the cylinder seat from the hole mouth to the hole bottom, but also increases the coaxiality of the cylinder seat; improves the sealing dimensions of the sleeve and the cylinder seat, so that the fitting length of the sleeve and the cylinder seat seal is increased; adds reinforcing ribs between the cylinder seat and the piston, increases the strength of the cylinder seat, and reduces the overall deformation of the cylinder seat during operation; thickens the inner diameter of the steel pressure plate close to the end of the pressure plate, and changes the plane structure into an arc transition structure. While improving the strength of the steel pressure plate, the arc transition structure also plays a role in guiding installation, greatly enhancing the convenience of field maintenance.

[0018] The improved brake device has significantly improved its sealing performance. No hydraulic oil leakage has occurred during high and low temperature durability tests in the factory or during field use. This has significantly improved the reliability and safety of the brake device during operation and enhanced the convenience of field maintenance of the brake device. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] Figure 1 This is a two-dimensional structural cross-sectional view of a carbon / carbon brake device for an aircraft provided in an embodiment of the present application;

[0020] Figure 2 This is a right view of the two-dimensional structure of a carbon / carbon brake device for aircraft provided in an embodiment of the present application;

[0021] Figure 3 This is a structural schematic diagram of a cylinder base assembly provided in an embodiment of the present application;

[0022] Figure 4 This is a schematic structural diagram of a carbon / carbon brake device for an aircraft and a wheel assembly provided in an embodiment of the present application;

[0023] Figure 5 This is a schematic diagram of the static seal structure of the original carbon brake device.

[0024] Figure 6 This is a schematic diagram of the static seal structure of the carbon brake device provided in this application.

[0025] Figure 7 It is a schematic diagram comparing the structure of the steel pressure plate of the present invention and the original carbon brake device.

[0026] Among them: 1. Cylinder seat assembly, 2-brake housing, 3-pressure plate assembly, 4-dynamic plate assembly, 5-single-sided static plate, 6-pressure plate, 7-steel pressure plate assembly, 8-piston assembly, 9-half retaining ring, 10-thermal insulation ring, 11-indicator rod, 12-sensor transmission device, 13-automatic anti-skid transmission device, 14-cover plate, 15-positioning block, 16-high-strength bolts, 17-screws, 18-stainless steel wire, 19-wheel assembly. DETAILED DESCRIPTION

[0027] Example 1

[0028] The invention provides a carbon / carbon brake device for aircraft, the main structure of which includes a cylinder seat assembly 1, a brake housing 2, a pressure plate assembly 3, a dynamic plate assembly 4, a single-sided static plate 5, a pressure plate 6, a steel pressure plate assembly 7, a piston assembly 8, a half-circuit breaker 9, a heat-insulating ring 10, a positioning block 15, etc. The brake housing 2 is a cap-type structure, which is assembled on the landing gear flange and is detachably connected to the cylinder seat assembly 1. It is limited in the axial direction by two half-circuit breaker rings 9 and in the circumferential direction by three blocks; the piston assembly 8 is assembled in the piston hole of the cylinder seat assembly 1, and its main function is to convert the pressure provided by the hydraulic oil into an axial thrust acting on the pressure plate assembly 3 when the aircraft brakes; the steel pressure plate assembly 7 is connected to the brake housing 2 by a high-strength bolt 16, and is assembled on the end of the brake housing 2 away from the cylinder seat assembly 1 to withstand the axial thrust transmitted by the piston assembly 9; the pressure plate assembly 3, the dynamic plate assembly 4, the single-sided static plate 5, and the pressure plate 6 are assembled On the brake housing 2, it is positioned in the axial direction by the steel pressure plate assembly 7, and in the circumferential direction by the keyway on the brake housing 2 and the guide rail of the wheel assembly 19, wherein the dynamic plate assembly 4 and the single-sided static plate 5 are assembled at intervals and provide braking torque for the brake device through contact friction; the pressure plate assembly 3 is equipped with an indicator rod 11, which can be used for error-proof prompts for brake disc installation and observation of wear status; the brake discs in the entire brake device are all carbon brake discs, including 1 pressure plate assembly 3, 3 dynamic plate assemblies 4, 4 single-sided static plates 5, and 1 pressure plate 6; the brake device also includes 8 piston assemblies 8, evenly distributed on both sides of the axis of the brake housing 2.

[0029] The piston assembly 8 in the brake device uses an automatic clearance adjustment mechanism, which can automatically adjust the brake clearance according to the degree of wear of the brake disc, thereby improving the reliability of the brake device.

[0030] like Figure 5-Figure 6 As shown, Figure 5 For the improved static sealing structure, Figure 6In order to improve the previous static sealing structure, the static sealing part in the piston hole of the cylinder seat is moved from the hole mouth to the hole bottom, and the connection part between the bushing and the cylinder seat is moved from the hole bottom to the hole mouth. This not only reduces the deformation of the static sealing part during operation, but also increases the coaxiality of the cylinder seat; the sealing dimensions of the bushing and the cylinder seat are improved, so that the fitting length of the bushing and the cylinder seat seal is increased; at the same time, reinforcing ribs are added between the cylinder seat and the piston to increase the strength of the cylinder seat and reduce the overall deformation of the cylinder seat during operation.

[0031] like Figure 7 As shown in the figure, the inner diameter of the steel pressure plate is thickened at one end close to the pressure plate, and the plane structure is changed to an arc transition structure. While improving the strength of the steel pressure plate, the arc transition structure also plays a role in guiding installation, greatly enhancing the convenience of field maintenance.

[0032] Example 2

[0033] The present invention will be described in further detail below with reference to the accompanying drawings and specific implementation methods.

[0034] like Figure 1-Figure 4 As shown, the present application provides a carbon / carbon brake device for aircraft, which is nested in the annular groove of the wheel assembly 19 and mainly includes a cylinder seat assembly 1; a brake housing 2; a pressure plate assembly 3; a dynamic plate assembly 4; a single-sided static plate 5; a pressure plate 6; a steel pressure plate assembly 7; a piston assembly 8; a half-circuit ring 9; an insulation ring 10; an indicator rod 11; a sensor transmission device 12; an automatic anti-skid transmission device 13; and a cover plate 14.

[0035] The brake housing 2 is a hollow cylindrical structure, the first end of the brake housing 2 is close to the main landing gear flange, and the second end is away from the main landing gear flange; the brake housing 2 is fixed to the flange of the main landing gear main shaft; the cylinder seat assembly 1 is assembled on the first end of the brake housing 2; the cylinder seat assembly 1 is a hollow annular structure, and the side of the cylinder seat assembly 1 facing the brake housing 2 is provided with N piston chambers, and an oil path is provided between adjacent piston chambers; a piston assembly 8 is placed in each piston chamber of the cylinder seat assembly 1; the half-circuit 9 is an annular structure, and is provided on the brake The first end of the housing 2 is used to limit the brake housing 2 in the axial direction. The thermal insulation ring 10, pressure plate assembly 3, movable plate assembly 4, single-sided static plate 5, pressure plate 6, and steel pressure plate assembly 7 are all annular structures. The thermal insulation ring 10, pressure plate assembly 3, movable plate assembly 4, single-sided static plate 5, and pressure plate 6 are arranged on the outer wall of the brake housing 2 from the first end to the second end. The indicator rod 11 is arranged on the pressure plate assembly 3. The sensor transmission device 12, automatic anti-skid transmission device 13, and cover plate 14 are all arranged on the outer end surface of the cylinder base assembly 1. A positioning block 15 is arranged on the first end of the brake housing 2 to limit the brake housing 2 in the circumferential direction.

[0036] Specifically, the single-sided static disc 5 and the dynamic disc assembly 4 are assembled at intervals. During assembly, the convex key on the inner diameter of the single-sided static disc 5 is inserted into the keyway on the inner wall of the brake housing 2, and remains relatively stationary with the brake housing 2 in the circumferential direction, and can slide along the keyway in the axial direction; the keyway on the outer diameter of the dynamic disc assembly 4 is installed on the guide rail of the wheel assembly 19, and can rotate with the wheel assembly 19 in the circumferential direction, and slide in the radial direction and along the axial direction of the guide rail.

[0037] Specifically, the steel pressure plate assembly 7

[0038] Specifically, the brake housing 2 is made of titanium alloy material.

[0039] Specifically, the brake housing 2 is connected to the flange of the main landing gear main shaft by using high-strength bolts 16 .

[0040] Specifically, the steel clamp of the movable plate assembly 4 is connected by screws 17 .

[0041] Specifically, the outer end surface of the cylinder base assembly 1 is fixed by using a stainless steel wire 18 .

[0042] Specifically, the indicator rod 11 is used to check the wear degree of the brake disc and has a function of error-proofing during installation.

[0043] Specifically, the heat insulating ring 10 is installed on one end of the cylinder seat 1 close to the brake disc, and is used to block the heat radiation generated when the brake disc is working, thereby improving the reliability of the brake device.

[0044] Specifically, the steel pressure plate assembly 7 is fixed to the end of the brake housing 2 away from the landing gear main shaft flange using high-strength bolts, and is mainly used to withstand the axial thrust generated by the brake device.

[0045] It should be noted that it is fixed to the flange of the landing gear main shaft by high-strength bolts, and is limited in the axial direction by a half retaining ring 9 and in the circumferential direction by three blocks. It is an important load-bearing component in the brake device. During braking, it withstands the torque transmitted by the brake disc and the axial thrust transmitted by the piston. A sensor transmission device 12 and an automatic anti-skid transmission device 13 for brake signal acquisition are installed on the brake housing.

[0046] The above-mentioned cylinder seat assembly 1 is installed at one end of the flange of the brake housing 2 close to the landing gear main shaft. There are 8 piston assemblies 8 symmetrically distributed in the piston hole of the cylinder seat assembly. The main function is to convert the brake pressure provided by the brake system into the axial thrust of the piston assembly 8. Compared with the previous design, the above-mentioned cylinder seat moves the static sealing part from the piston hole mouth to the bottom of the hole. At the same time, reinforcing ribs are added at the piston hole of the cylinder seat, which increases the stiffness of the cylinder seat, reduces the deformation of the static sealing part, and increases the coaxiality of the bushing and the cylinder seat, greatly enhancing the sealing performance of the brake device during operation.

[0047] It should be noted that the brake disc of the brake device includes a pressure disc assembly 3, three dynamic disc assemblies 4, four single-sided static discs 5, and a pressure disc 6.

[0048] It should be noted that the aircraft carbon / carbon brake device is installed on the main landing gear in combination with the wheel assembly. The two main landing gears of the aircraft are respectively provided with an aircraft carbon / carbon brake device. The mounting seats of the aircraft carbon / carbon brake devices, the transmission device 12 and the automatic anti-skid transmission device 13 of the two main landing gears are symmetrical to each other, and the rest of the parts remain unchanged.

[0049] The working principle of the carbon / carbon brake device for aircraft described in the present invention is as follows: the brake device is matched with the main engine wheel to form a carbon brake, and the main engine wheel is assembled on the landing gear. When the aircraft takes off and taxis, the main engine wheel equipped with aviation tires rolls on the ground, and the dynamic disc assembly 4 rotates with the main engine wheel. The brake housing 2 fixed on the landing gear flange remains relatively stationary with the landing gear and does not rotate with the rotation of the random wheel, and the pressure disc assembly 3, the single-sided static disc 5 and the pressure disc 6 also remain stationary with the brake housing and do not rotate with the rotation of the random wheel; when the aircraft brakes, the hydraulic oil pressure provided by the brake system pushes the piston assembly 8 to move axially and act on the pressure disc assembly 3, and then compresses the dynamic disc assembly 4 and the single-sided static disc 5, so that a braking torque is generated between the brake discs, thereby generating a braking torque; when the aircraft stops braking, the brake is released, the pressure is released, the piston assembly 8 returns to its original position, the pressure between the brake discs is released, and the braking torque disappears.

[0050] The specific embodiments of the present invention have been described in detail. For those skilled in the art, any obvious changes made to the present invention without departing from the spirit of the present invention will constitute infringement of the patent of the present invention and will be subject to corresponding legal liability.

Claims

1. A carbon / carbon brake device for aircraft, characterized in that: The carbon / carbon brake device for an aircraft is nested in an annular groove of a wheel assembly (19), and comprises a cylinder seat assembly (1), a brake housing (2), a pressure plate assembly (3), a dynamic plate assembly (4), a single-sided static plate (5), a pressure plate (6), a steel pressure plate assembly (7), a piston assembly (8), a half-circlip (9), an insulation ring (10), an indicator rod (11), a sensor transmission device (12), an automatic anti-skid transmission device (13), and a cover plate (14), wherein: The brake housing (2) is a hollow cylindrical structure, the first end of the brake housing (2) is close to the main landing gear flange, and the second end is away from the main landing gear flange; the brake housing (2) is fixed on the flange of the main landing gear main shaft; the cylinder seat assembly (1) is assembled on the first end of the brake housing (2); the cylinder seat assembly (1) is a hollow annular structure, and the side of the cylinder seat assembly (1) facing the brake housing (2) is provided with N piston chambers, and an oil path is provided between adjacent piston chambers; a piston assembly (8) is placed in each piston chamber of the cylinder seat assembly (1); the half-circuit ring (9) is an annular structure, which is provided at the first end of the brake housing (2) and is used to limit the brake housing (2) in the axial direction; the heat insulation ring (10), the pressure plate assembly (3), the dynamic plate assembly (4), the single-sided static plate (5), the pressure plate (6); the steel pressure plate assembly (7) are all annular structures; on the outer wall of the brake housing (2), heat insulation rings are provided in sequence from the first end to the second end. (10), a pressure plate assembly (3), a dynamic plate assembly (4), a single-sided static plate (5), and a pressure plate (6); an indicator rod (11) is arranged on the pressure plate assembly (3); a sensor transmission device (12), an automatic anti-skid transmission device (13) and a cover plate (14) are all arranged on the outer end surface of the cylinder seat assembly (1); a positioning block (15) is arranged at the first end of the brake housing (2) for limiting the brake housing (2) in the circumferential direction; the single-sided static plate (5) and the dynamic plate assembly (4) are assembled at intervals, and when assembled, the convex key on the inner diameter of the single-sided static plate (5) is inserted into the keyway on the inner wall of the brake housing (2), and remains relatively stationary with the brake housing (2) in the circumferential direction, and can slide along the keyway in the axial direction; the keyway on the outer diameter of the dynamic plate assembly (4) is installed on the guide rail of the wheel assembly (19), and can rotate with the wheel assembly (19) in the circumferential direction, and slide in the radial direction and along the axial direction of the guide rail; the brake housing (2) is a housing made of titanium alloy material.

2. The carbon / carbon brake device for aircraft according to claim 1, characterized in that: The indicator rod (11) is used to check the wear degree of the brake disc and has the function of error prevention during installation.

3. The carbon / carbon brake device for aircraft according to claim 1, characterized in that: The heat insulating ring (10) is mounted on one end of the cylinder seat assembly (1) close to the brake disc and is used to block the heat radiation generated when the brake disc is working.

4. The carbon / carbon brake device for aircraft according to claim 1, characterized in that: The steel pressure plate assembly (7) is fixed to the end of the brake housing (2) away from the landing gear main shaft flange using high-strength bolts, and is used to withstand the axial thrust generated by the brake device.

5. The carbon / carbon brake device for aircraft according to claim 1, characterized in that: The steel clamp of the moving plate assembly (4) is connected using screws (17).

6. The carbon / carbon brake device for aircraft according to claim 1, characterized in that: The outer end surface of the cylinder base assembly (1) is fixed by using a stainless steel wire (18).

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