CN217558848U - Carbon/carbon brake device for airplane - Google Patents

Abstract

The carbon/carbon brake device for the airplane is nested in an annular groove of an airplane wheel assembly 19, a brake shell 2 is of a hollow cylindrical structure, the first end of the brake shell 2 is close to one side of a flange of a main undercarriage, and the second end of the brake shell 2 is far away from one side of the flange of the main undercarriage; the brake shell 2 is fixed on a flange of a main shaft of the main landing gear; the cylinder block assembly 1 is assembled at a first end of the brake housing 2; the cylinder seat assembly 1 is of a hollow annular structure, N piston cavities are arranged on one side, facing the brake shell 2, of the cylinder seat assembly 1, and an oil way is arranged between every two adjacent piston cavities; one piston assembly 8 is placed in each piston cavity of the cylinder block assembly 1; the semi-clamping ring 9 is of an annular structure, is arranged at the first end of the brake shell 2 and is used for limiting the brake shell 2 in the axial direction; the heat insulation ring 10, the pressing disc component 3, the movable disc component 4, the single-sided static disc 5 and the pressure bearing disc 6; the steel pressure bearing disc assemblies 7 are all of annular structures.

Description

Carbon/carbon brake device for airplane

Technical Field

The invention belongs to the field of aircraft wheel braking in aircraft airborne equipment, and particularly relates to a carbon/carbon braking device for an aircraft.

Background

The carbon/carbon brake device is a mainstream disc brake device for an airplane at present, the brake device is matched with a main engine wheel, the main engine wheel and the main engine wheel are jointly formed into a brake wheel which is assembled on a main landing gear shaft of the airplane and is used for taking off, sliding, braking, ground parking and engine test running of the airplane, the main function of the brake device is to provide brake torque for the main engine wheel, absorb kinetic energy of the airplane and convert the kinetic energy into heat energy for dissipation when the airplane lands, and the carbon/carbon brake device is a key part of an airplane brake system.

At present, the mainstream main components of the brake device for the airplane comprise a cylinder seat assembly, a brake shell, a pressure disc assembly, a movable disc assembly, a single-sided static disc, a pressure bearing disc, a steel pressure bearing disc assembly and the like.

For example, the invention patent with the publication patent number CN106672218A discloses an aircraft carbon/ceramic brake device, wherein a brake housing of the brake device is installed on a cylinder block assembly, and is axially limited by 2 semi-snap rings and angularly limited by 3 stoppers, so as to connect and fix each component; the piston assembly is arranged in the cylinder seat assembly and converts the braking pressure of a braking system into axial thrust during braking; the steel pressure bearing plate assembly is fixed at one end of the brake shell, which is far away from the cylinder seat assembly, through a high-strength bolt and is used for bearing brake thrust; the pressing disc assembly, the movable disc assembly, the static disc and the bearing disc are arranged on the brake shell, are axially positioned by the steel bearing disc assembly, and form brake braking force through friction between the brake discs; the diameter of the brake pad is adjusted according to the brake performance index. The invention has simple structure, simple and convenient installation and operation and convenient inspection and maintenance; the maintenance workload and the labor intensity can be obviously reduced.

The invention also discloses a helicopter brake device, which comprises a brake shell, a pressure bearing cup, a pressure bearing disc, a static disc, a movable disc assembly, a compression disc, a steel compression ring, a cylinder seat, a piston assembly and an anti-thrust steel ring, wherein the piston assembly is fixed in a containing groove of the cylinder seat, the brake shell is of a cap type structure, the front end of the brake shell is detachably connected with the cylinder seat, the steel compression ring is fixedly connected with the compression disc, the compression disc and the static disc are axially connected onto the brake shell in a sliding manner, the movable disc assembly is rotatably connected onto the brake shell, the static disc and the movable disc assembly are alternately arranged, the pressure bearing disc is fixedly connected with the brake shell through the pressure bearing cup, the pressure bearing cup is a rotary body, the front end of the pressure bearing cup is embedded into a hole in the pressure bearing disc, the rear end of the pressure bearing cup is embedded into a through hole arranged on the brake shell, and the pressure bearing cup is connected with the brake shell through a rivet and the anti-thrust steel ring. The invention solves the problems that the helicopter brake device in the prior art has a complex structure and brings great inconvenience to the maintenance of the helicopter brake device.

However, the existing brake device has the following problems in design: the width of a sealing ring groove at the matching part of the bushing and the cylinder seat is larger, when the brake device works in a limit state, a gap exists in a sealing groove, and part of a machine body of the sealing ring can be extruded into the matching part of the bushing and the cylinder seat to generate extrusion distortion to influence the sealing property; the sealing ring groove is located piston orifice department, and in brake equipment working process, there is the deflection too big, and the condition that cooperation guide length is short on the left is easily caused the axiality of cylinder block and bush too big, is unfavorable for laminating of both, leads to off-centre, reduces the leakproofness, has caused huge influence to brake equipment's reliability and security.

Disclosure of Invention

The application aims to provide a novel carbon/carbon brake device for an airplane, which is used for solving the hydraulic oil leakage phenomenon generated at the static sealing part of a piston bushing and a cylinder seat when the original brake device is used in a limit low-temperature environment of-55 +/-3 ℃ under the conditions of not changing the interface relation, brake system parameters, mounting and dismounting and operation requirements of the original brake device, improving the working reliability and safety of the brake device and also enhancing the convenience of the outfield maintenance of the brake device.

The carbon/carbon brake device for the airplane is nested in an annular groove of an airplane wheel assembly 19 and comprises a cylinder seat assembly 1; a brake housing 2; a puck assembly 3; a movable plate component 4; a single-sided static disc 5; a pressure-bearing disc 6; a steel pressure bearing disc assembly 7; a piston assembly 8; a half snap ring 9; a heat insulating ring 10; an indication lever 11; the sensor transmission 12; an automatic anti-slip transmission device 13; a cover plate, wherein:

the brake shell 2 is of a hollow cylindrical structure, the first end of the brake shell 2 is close to one side of the flange plate of the main undercarriage, and the second end of the brake shell is far away from one side of the flange plate of the main undercarriage; the brake shell 2 is fixed on a flange of a main shaft of the main landing gear; the cylinder block assembly 1 is assembled at a first end of the brake housing 2; the cylinder seat assembly 1 is of a hollow annular structure, N piston cavities are arranged on one side, facing the brake shell 2, of the cylinder seat assembly 1, and an oil way is arranged between every two adjacent piston cavities; one piston assembly 8 is placed in each piston cavity of the cylinder block assembly 1; the semi-clamping ring 9 is of an annular structure, is arranged at the first end of the brake shell 2 and is used for limiting the brake shell 2 in the axial direction; the heat insulation ring 10, the pressing disc component 3, the movable disc component 4, the single-sided static disc 5 and the pressure bearing disc 6; the steel pressure bearing plate assemblies 7 are all of annular structures; the outer wall of the brake shell 2 is sequentially provided with a heat insulation ring 10, a compact disc assembly 3, a movable disc assembly 4, a single-sided static disc 5 and a pressure bearing disc 6 from a first end to a second end; the indicating rod 11 is arranged on the pressing disc assembly 3; the sensor transmission 12, the automatic antiskid transmission 13 and the cover plate are all arranged on the outer end face of the cylinder block assembly 1. The positioning block 15 is disposed at a first end of the brake housing 2, and is used for limiting the brake housing 2 in the circumferential direction.

Specifically, the single-sided static disc 5 and the movable disc assembly 4 are assembled at intervals, and a convex key on the inner diameter of the single-sided static disc 5 is inserted into a key groove on the inner wall of the brake shell 2 during assembly, keeps relative rest with the brake shell 2 in the circumferential direction and can slide along the key groove in the axial direction; the keyways on the outer diameter of the rotor disk assembly 4 are mounted on the guide rails of the wheel assembly 19 to rotate in the circumferential direction with the wheel assembly 19, to slide in the radial direction and axially along the guide rails.

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

In particular, the indicating rod 11 is used to check the wear level of the brake disc, and has the function of error-proof indication when being installed.

Specifically, the heat insulation ring 10 is installed at one end of the cylinder block assembly 1 close to the brake disc, and is used for blocking heat radiation generated when the brake disc works.

Specifically, the steel pressure bearing disc assembly 7 is fixed to one end, away from the landing gear main shaft flange, of the brake housing 2 by using high-strength bolts and is used for bearing axial thrust generated by the brake device.

Specifically, the steel clips of the movable plate assembly 4 are connected by screws 17.

Specifically, the outer end face of the cylinder block assembly 1 is fixed by a stainless steel wire 18.

In summary, the present application provides a carbon/carbon brake device for an aircraft, which not only reduces the deformation of a static sealing portion during operation, but also increases the coaxiality of a cylinder block by moving the connecting portion of a bushing and the cylinder block from a hole bottom to a hole opening while moving the static sealing portion in a piston hole of the cylinder block from the hole opening to the hole bottom; the sealing size of the bushing and the cylinder seat is improved, so that the matching length of the bushing and the cylinder seat is increased; the reinforcing rib is added between the cylinder seat and the piston, so that the strength of the cylinder seat is increased, and the integral deformation of the cylinder seat during working is reduced; the one end that is close to the bearing disc on steel bearing disc internal diameter thickens to change planar structure into circular arc transition structure, when improving steel bearing disc intensity, circular arc transition structure has played the effect of guide installation again, has strengthened the convenient degree of outfield maintenance greatly.

The improved brake device has the advantages that the sealing performance is obviously improved, no matter in a high-temperature and low-temperature test of a durability test in a factory or in the process of using the brake device in an external field, the hydraulic oil leakage phenomenon does not occur, the reliability and the safety of the brake device in working are obviously improved, and the convenience degree of external field maintenance of the brake device is enhanced.

Drawings

Fig. 1 is a two-dimensional structural sectional view of a carbon/carbon brake device for an aircraft according to an embodiment of the present disclosure;

FIG. 2 is a right side view of a two-dimensional configuration of a carbon/carbon brake assembly for an aircraft according to an embodiment of the present disclosure;

FIG. 3 is a schematic diagram of a cylinder block assembly according to an embodiment of the present disclosure;

fig. 4 is a schematic structural diagram of a carbon/carbon brake device for an aircraft, which is provided in an embodiment of the present application and is matched with a wheel assembly;

fig. 5 is a schematic view of a static sealing structure of the original carbon brake device.

Fig. 6 is a schematic view of a static sealing structure of the carbon brake device provided by the present application.

FIG. 7 is a schematic diagram comparing the structure of the steel pressure bearing disc of the present invention and the original carbon brake device.

Wherein: 1. the brake comprises a cylinder seat assembly, a 2-brake shell, a 3-pressing disc assembly, a 4-movable disc assembly, a 5-single-sided static disc, a 6-pressure bearing disc, a 7-steel pressure bearing disc assembly, a 8-piston assembly, a 9-semi-clamping ring, a 10-heat insulation ring, a 11-indication rod, a 12-sensor transmission device, a 13-automatic anti-skidding transmission device, a 14-cover plate, a 15-positioning block, a 16-high-strength bolt, a 17-screw, a 18-stainless steel wire and a 19-wheel assembly.

Detailed Description

Example one

The invention provides a carbon/carbon brake device for an airplane, which mainly comprises a cylinder seat assembly 1, a brake shell 2, a pressure disc assembly 3, a movable disc assembly 4, a single-sided static disc 5, a pressure bearing disc 6, a steel pressure bearing disc assembly 7, a piston assembly 8, a semi-clamping ring 9, a heat insulation ring 10, a positioning block 15 and the like. The brake shell 2 is of a cap type structure, is assembled on a flange plate of the undercarriage and is detachably connected with the cylinder seat assembly 1, 2 half clamping rings 9 are used for limiting in the axial direction, and 3 stop blocks are used for limiting in the circumferential direction; the piston assembly 8 is assembled in a piston hole of the cylinder seat assembly 1 and mainly used for converting pressure provided by hydraulic oil into axial thrust acting on the pressing disc assembly 3 when an airplane is braked; the steel pressure bearing plate assembly 7 is connected with the brake shell 2 through a high-strength bolt 16, is assembled at one end of the brake shell 2, which is far away from the cylinder seat assembly 1, and is used for bearing the axial thrust transmitted by the piston assembly 9; the compact disc assembly 3, the movable disc assembly 4, the single-sided static disc 5 and the bearing disc 6 are assembled on the brake shell 2, are positioned through the steel bearing disc assembly 7 in the axial direction and are positioned through a key groove in the brake shell 2 and a guide rail of the airplane wheel assembly 19 in the circumferential direction, wherein the movable disc assembly 4 and the single-sided static disc 5 are assembled at intervals, and provide braking torque for a brake device through contact friction; the pressing disc component 3 is provided with an indicating rod 11 which can be used for error-proof prompt of brake disc installation and observation of a wear state; the brake disc in the whole brake device is a carbon brake disc and comprises 1 compact disc component 3, 3 movable disc components 4, 4 single-sided static discs 5 and 1 pressure-bearing disc 6; the brake device simultaneously comprises 8 piston assemblies 8 which are uniformly distributed on two sides of the axis of the brake shell 2.

The piston assembly 8 in the brake device uses an automatic gap adjusting mechanism, the brake gap can be automatically adjusted according to the abrasion degree of the brake disc, and the reliability of the brake device is improved.

As shown in fig. 5-6, fig. 5 is a static sealing structure after improvement, fig. 6 is a static sealing structure before improvement, and when the static sealing position in the piston hole of the cylinder base is moved from the hole opening to the hole bottom, the connecting position of the lining and the cylinder base is moved from the hole bottom to the hole opening, so that the deformation of the static sealing position during working is reduced, and the coaxiality of the cylinder base is increased; the sealing size of the bushing and the cylinder seat is improved, so that the matching length of the bushing and the cylinder seat is increased; and meanwhile, a reinforcing rib is added between the cylinder seat and the piston, so that the strength of the cylinder seat is increased, and the integral deformation of the cylinder seat during working is reduced.

As shown in figure 7, the end close to the bearing plate on the inner diameter of the steel bearing plate is thickened, the plane structure is changed into the arc transition structure, the arc transition structure plays a role in guiding installation while the strength of the steel bearing plate is improved, and the convenience degree of outfield maintenance is greatly enhanced

Example two

The invention is described in further detail below with reference to the drawings and the detailed description.

As shown in fig. 1-4, the present application provides an aircraft carbon/carbon brake device nested in an annular groove of a wheel assembly 19, mainly comprising a cylinder block assembly 1; a brake housing 2; a puck assembly 3; a movable plate component 4; a single-sided static disc 5; a pressure bearing disc 6; a steel pressure bearing disc assembly 7; a piston assembly 8; a half snap ring 9; a heat insulating ring 10; an indication lever 11; a sensor transmission 12; an automatic anti-slip transmission device 13; a cover plate; wherein:

the brake shell 2 is of a hollow cylindrical structure, the first end of the brake shell 2 is close to one side of the flange plate of the main landing gear, and the second end of the brake shell is far away from one side of the flange plate of the main landing gear; the brake shell 2 is fixed on a flange of a main shaft of the main landing gear; the cylinder block assembly 1 is assembled at a first end of the brake housing 2; the cylinder block assembly 1 is of a hollow annular structure, N piston cavities are arranged on one side, facing the brake shell 2, of the cylinder block assembly 1, and an oil way is arranged between every two adjacent piston cavities; one piston assembly 8 is placed in each piston cavity of the cylinder block assembly 1; the semi-clamping ring 9 is of an annular structure, is arranged at the first end of the brake shell 2 and is used for limiting the brake shell 2 in the axial direction; the heat insulation ring 10, the pressing disc component 3, the movable disc component 4, the single-sided static disc 5 and the pressure bearing disc 6; the steel pressure bearing plate assemblies 7 are all of annular structures; the outer wall of the brake shell 2 is provided with a heat insulation ring 10, a pressing disc component 3, a movable disc component 4, a single-sided static disc 5 and a pressure bearing disc 6 in sequence from a first end to a second end; the indicating rod 11 is arranged on the pressing disc assembly 3; the sensor transmission device 12, the automatic antiskid transmission device 13 and the cover plate are all arranged on the outer end face of the cylinder block component 1. The positioning block 15 is disposed at a first end of the brake housing 2 and used for limiting the brake housing 2 in the circumferential direction.

Specifically, the single-sided static disc 5 and the movable disc assembly 4 are assembled at intervals, and a convex key on the inner diameter of the single-sided static disc 5 is inserted into a key groove on the inner wall of the brake shell 2 during assembly, keeps relative static with the brake shell 2 in the circumferential direction and can slide along the key groove in the axial direction; the keyways on the outer diameter of the rotor disk assembly 4 are mounted on the guide rails of the wheel assembly 19 to rotate in the circumferential direction with the wheel assembly 19, to slide in the radial direction and axially along the guide rails.

In particular, of steel bearing disk assemblies 7

Specifically, the brake housing 2 is a housing made of a titanium alloy material.

Specifically, the brake housing 2 is connected to the flange of the main landing gear spindle by high strength bolts 16.

Specifically, the steel clips of the movable plate assembly 4 are connected by screws 17.

Specifically, the outer end face of the cylinder block assembly 1 is fixed with a stainless steel wire 18.

In particular, the indicating rod 11 is used to check the wear level of the brake disc, and has the function of error-proof indication when being installed.

Specifically, the heat insulation ring 10 is installed at one end of the cylinder block assembly 1 close to the brake disc and used for blocking heat radiation generated by the brake disc during working and improving the reliability of the brake device.

Specifically, the steel pressure bearing disc assembly 7 is fixed to one end, away from a main shaft flange of the undercarriage, of the brake housing 2 through high-strength bolts and is mainly used for bearing axial thrust generated by the brake device.

It should be noted that the high-strength bolt is fixed on a flange of a main shaft of the undercarriage, the flange is limited in the axial direction by the semi-snap ring 9, and the flange is limited in the circumferential direction by 3 blocks, and the high-strength bolt is an important force-bearing component in the brake device, bears the torque transmitted by the brake disc and the axial thrust transmitted by the piston during braking, and is provided with a sensor transmission device 12 and an automatic anti-skid transmission device 13 for acquiring brake signals on the brake shell.

The cylinder seat assembly 1 is arranged at one end, close to a flange of a main shaft of the undercarriage, of the brake shell 2, 8 piston assemblies 8 are symmetrically distributed in a piston hole of the cylinder seat assembly, the main function is to convert brake pressure provided by a brake system into axial thrust of the piston assemblies 8, compared with the previous design, the cylinder seat moves a static sealing part from a piston hole opening to the hole bottom, meanwhile, reinforcing ribs are added in the piston hole of the cylinder seat, rigidity of the cylinder seat is improved, deformation of the static sealing part is reduced, coaxiality of a lining and the cylinder seat is increased, and sealing performance of the brake device during working is greatly improved.

It should be noted that the brake disc of the brake device includes 1 pressure disc assembly 3, 3 movable disc assemblies 4, 4 single-sided static discs 5, and 1 pressure disc 6.

It should be noted that the carbon/carbon brake device for the aircraft and the wheel assembly are mounted on the main landing gear in a matching manner, the carbon/carbon brake device for the aircraft is respectively arranged on the two main landing gears of the aircraft, the mounting seats of the carbon/carbon brake device for the aircraft of the two main landing gears, the driver transmission device 12 and the automatic anti-skid transmission device 13 are symmetrical to each other in mounting position, and the rest parts are not changed.

The carbon/carbon brake device for the airplane has the following working principle: the carbon brake main engine wheel is assembled on the undercarriage by matching the brake device with the main engine wheel, when the airplane takes off and slides, the main engine wheel provided with the aircraft tire rolls on the ground, the movable disc component 4 rotates along with the main engine wheel, the brake shell 2 fixed on the flange plate of the undercarriage keeps relatively static with the undercarriage and does not rotate along with the rotation of the airplane wheel, and the gland disc component 3, the single-sided static disc 5 and the pressure bearing disc 6 also keep static with the brake shell and do not rotate along with the rotation of the airplane wheel; when the airplane brakes, hydraulic oil pressure provided by a brake system pushes the piston assembly 8 to move axially and act on the pressing disc assembly 3, and then the moving disc assembly 4 and the single-sided static disc 5 are pressed, so that brake torque is generated among the brake discs, and brake torque is generated; when the airplane stops braking, the brake is released, the pressure is released, the piston assembly 8 is restored to the original position, the pressure between the brake discs is relieved, and the braking torque disappears.

The present disclosure has been described in detail with reference to specific embodiments thereof. Any obvious modifications to the disclosure herein disclosed which do not depart from the spirit of the disclosure will become apparent to those skilled in the art to which the disclosure pertains and will bear corresponding legal responsibility.

Claims (8)

1. The utility model provides an aircraft is with carbon/carbon brake equipment, its characterized in that, aircraft is with carbon/carbon brake equipment nestification in the annular groove of wheel subassembly (19), including cylinder block subassembly (1), brake casing (2), gland plate subassembly (3), driving disk subassembly (4), single face quiet dish (5), bearing plate (6), steel bearing plate subassembly (7), piston assembly (8), semi-clasp (9), heat insulating ring (10), indicator lever (11), sensor transmission (12), automatic anti-skidding transmission (13), apron, wherein:

the brake shell (2) is of a hollow cylindrical structure, the first end of the brake shell (2) is close to one side of the flange plate of the main undercarriage, and the second end of the brake shell is far away from one side of the flange plate of the main undercarriage; the brake shell (2) is fixed on a flange of a main shaft of the main landing gear; the cylinder seat assembly (1) is assembled at the first end of the brake shell (2); the cylinder seat assembly (1) is of a hollow annular structure, N piston cavities are arranged on one side of the cylinder seat assembly (1) facing the brake shell (2), and an oil way is arranged between every two adjacent piston cavities; a piston assembly (8) is arranged in each piston cavity of the cylinder seat assembly (1); the semi-clamping ring (9) is of an annular structure, is arranged at the first end of the brake shell (2) and is used for limiting the brake shell (2) in the axial direction; the heat insulation device comprises a heat insulation ring (10), a pressing disc component (3), a movable disc component (4), a single-side static disc (5) and a pressure bearing disc (6); the steel pressure bearing disc assemblies (7) are all of an annular structure; the outer wall of the brake shell (2) is sequentially provided with a heat insulation ring (10), a pressing disc component (3), a movable disc component (4), a single-sided static disc (5) and a pressure bearing disc (6) from a first end to a second end; the indicating rod (11) is arranged on the pressing disc component (3); the sensor transmission device (12), the automatic anti-skid transmission device (13) and the cover plate are all arranged on the outer end face of the cylinder base component (1); the positioning block (15) is arranged at the first end of the brake shell (2) and used for limiting the brake shell (2) in the circumferential direction.

2. The carbon/carbon brake device for aircraft as claimed in claim 1, wherein the single-sided stationary disc (5) and the movable disc assembly (4) are assembled at intervals, and the key on the inner diameter of the single-sided stationary disc (5) is inserted into the key groove on the inner wall of the brake housing (2) during assembly, is kept stationary relative to the brake housing (2) in the circumferential direction, and is slidable along the key groove in the axial direction; the key groove on the outer diameter of the movable disc assembly (4) is arranged on the guide rail of the wheel assembly (19), can rotate along with the wheel assembly (19) in the circumferential direction, and can slide in the radial direction and along the axial direction of the guide rail.

3. Carbon/carbon brake equipment for aircraft according to claim 1, characterized in that the brake housing (2) is a housing made of titanium alloy material.

4. Carbon/carbon brake equipment for aircraft according to claim 1, characterized by the fact that the indicating lever (11) is used to check the wear of the brake disc, while having the function of error-proof indication when installed.

5. Carbon/carbon brake assembly for aircraft according to claim 1, characterized in that a heat-insulating ring (10) is mounted on the cylinder block assembly (1) at the end near the brake disc for insulating the heat radiation generated during operation of the brake disc.

6. Carbon/carbon brake assembly 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) remote from the landing gear spindle flange using high strength bolts for receiving the axial thrust generated by the brake assembly.

7. Carbon/carbon aircraft brake device according to claim 1, characterized in that the steel clips of the moving disc assembly (4) are connected by means of screws (17).

8. The carbon/carbon brake device for aircraft as claimed in claim 1, wherein the outer end surface of the cylinder block assembly (1) is fixed by a stainless steel wire (18).

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