阅读说明：本技术 一种直升机刹车装置 (Helicopter brake device ) 是由 张天闯 郑聃 韩龙杰 刘晓华 李学强 张红松 宁国良 王岩 杨冬 于 2019-08-22 设计创作，主要内容包括：本发明公开了一种直升机刹车装置。所述直升机刹车装置包括刹车壳体、承压杯、承压盘、静盘、动盘组件、压紧盘、钢压紧环、汽缸座、活塞组件和止推钢圈,活塞组件固定在汽缸座的容置槽内,刹车壳体为帽式结构,刹车壳体前端与汽缸座可拆卸连接,钢压紧环与压紧盘固定连接,压紧盘与静盘轴向滑移连接于刹车壳体上,动盘组件转动连接于刹车壳体上,静盘与动盘组件交替设置,承压盘通过承压杯与刹车壳体固定连接,承压杯为回转体,承压杯前端嵌入承压盘上的孔内,承压杯后端嵌入刹车壳体上设置的贯穿孔内,承压杯通过铆钉、止推钢圈与刹车壳体连接。本发明解决了现有技术中的直升机刹车装置结构复杂,给直升机刹车装置检修带来了很大不便的问题。(The invention discloses a helicopter brake device. Helicopter brake equipment includes the brake housing, the pressure cup, the bearing plate, quiet dish, the driving disk subassembly, the pressure disk, the steel clamp ring, the cylinder block, piston assembly and thrust steel ring, piston assembly fixes in the storage tank of cylinder block, the brake housing is the cap structure, brake housing front end can be dismantled with the cylinder block and be connected, steel clamp ring and pressure disk fixed connection, the pressure disk slides with quiet dish axial and connects on the brake housing, the driving disk subassembly rotates and connects on the brake housing, quiet dish sets up with the driving disk subassembly in turn, the bearing plate passes through pressure cup and brake housing fixed connection, the pressure cup is the solid of revolution, downthehole on the pressure cup front end embedding bearing plate, in the through-hole that sets up on the pressure cup rear end embedding brake housing, the pressure cup passes through the rivet, the thrust steel ring is connected with the brake housing. 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.)

1. A helicopter brake assembly, comprising: the brake device comprises a brake shell (1), a pressure-bearing cup (2), a pressure-bearing disc (3), a static disc (5), a movable disc assembly (6), a compression disc (7), a steel compression ring (8), a cylinder seat (9), a piston assembly (12) and a thrust steel ring (13);

The piston assembly (12) is fixed in a containing groove of the cylinder seat (9), the brake shell (1) is of a cap type structure, the front end of the brake shell (1) is detachably connected with the cylinder seat (9), the steel compression ring (8) is fixedly connected with the compression disc (7), the compression disc (7) is axially connected with the static disc (5) in a sliding manner, the movable disc assembly (6) is rotatably connected onto the brake shell (1), the static disc (5) and the movable disc assembly (6) are alternately arranged, the pressure bearing disc (3) is fixedly connected with the brake shell (1) through the pressure bearing cup (2), the pressure bearing cup (2) is a rotary body, the front end of the pressure bearing cup (2) is embedded into a hole in the pressure bearing disc (3), the rear end of the pressure bearing cup (2) is embedded into a through hole (15) formed in the brake shell (1), the pressure bearing cup (2) is connected with the brake shell (1) through a rivet (14) and the thrust steel ring (13), and when the brake is performed, the piston assembly (12) pushes the steel compression ring (8) so that the compression disc (7) pushes the static disc (5) and extrudes the movable disc assembly (6).

2. A helicopter brake apparatus as claimed in claim 3, wherein said brake housing (1) defines a stepped surface (101) at a rear end thereof corresponding to said thrust steel ring (13), said thrust steel ring (13) abutting against said stepped surface (101).

3. A helicopter brake apparatus according to claim 2, characterized in that said piston assemblies (12) are 6 in number.

4. A helicopter brake apparatus according to claim 3, characterized in that 6 said piston assemblies (12) consist of 3 pneumatic pistons (12.1) and 3 hydraulic pistons (12.2).

5. A helicopter brake rigging according to claim 4, characterized in that it further comprises a wear indicator rod (4) fixedly connected to said cylinder block (9).

6. a helicopter brake device according to claim 5, characterized in that the materials of said pressure bearing disc (3), said static disc (5), said pressing disc (7) and said moving disc assembly (6) are all carbon ceramics.

7. A helicopter brake apparatus according to claim 6, characterized in that the material of said brake housing (1) is a titanium alloy.

Technical Field

The invention relates to the technical field of helicopter engineering, in particular to a helicopter brake device.

Background

The helicopter brake device and the main engine wheel are matched and sleeved on the main undercarriage of the helicopter for taking off, landing, sliding, braking and ground parking of the helicopter, the helicopter brake device provides brake moment for the main engine wheel and absorbs brake energy, and the helicopter brake device is an important component of a helicopter brake system.

At present, the helicopter brake equipment among the prior art compares with the tradition and does not have big change, and it includes brake housing subassembly, cylinder block subassembly, compresses tightly the dish, moves disk assembly, quiet dish and pressure-bearing dish.

For example, the invention patent with Chinese patent publication No. CN106672218A discloses an airplane carbon/ceramic brake device, wherein a brake shell (2) is arranged on a cylinder seat assembly (1), is axially limited by 2 semi-snap rings (10), and is angularly limited by 3 stoppers and used for connecting and fixing all parts and assemblies; the piston assembly (9) is arranged in the cylinder seat assembly (1) and converts the braking pressure of a braking system into axial thrust during braking; the steel pressure bearing plate assembly (7) is fixed at one end of the brake shell (2) far away from the cylinder seat assembly (1) through a high-strength bolt (16) and is used for bearing brake thrust; the compression disc component (3), the movable disc component (4), the static disc (5) and the pressure bearing disc (6) are arranged on the brake shell (2), are axially positioned by the steel pressure bearing disc component (7), and form brake braking force through friction among 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.

also for example, the invention patent with chinese patent publication No. CN108284947A discloses an aircraft brake system based on pressure accumulation and energy storage, which includes: the pressure accumulator 1, the hydraulic brake control device 2 and the normal brake device 3 of the airplane wheel; the hydraulic end of the pressure accumulator 1 is connected with the hydraulic brake control device 2 and is used for providing hydraulic oil for the hydraulic brake control device 2; the hydraulic brake control device 2 is connected with the normal brake device 3 of the wheel, and the hydraulic oil provided by the pressure accumulator 1 is used for controlling the normal brake device 3 of the wheel to brake. The invention meets the energy consumption requirements of normal braking (hydraulic pressure) and emergency braking (air pressure) of the existing airplane brake system, and is suitable for all the existing airplane main wheel brake devices.

Disclosure of Invention

The invention aims to provide a helicopter brake device, and aims to solve the problems that the helicopter brake device in the prior art is complex in structure and not beneficial to maintenance.

The helicopter brake device comprises a brake shell, a pressure bearing cup, a pressure bearing disc, a static disc, a movable disc assembly, a pressure bearing 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 structure, the front end of the brake shell is detachably connected with the cylinder seat, the steel compression ring is fixedly connected with the pressure bearing disc, the pressure bearing disc and the static disc are axially connected on the brake shell in a sliding manner, the movable disc assembly is rotatably connected on 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 revolving 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, the pressure bearing cup is connected with the brake shell through, The movable plate assembly is squeezed.

Furthermore, the rear end of the brake shell is provided with a step surface corresponding to the thrust steel ring, and the thrust steel ring abuts against the step surface.

Further, the number of the piston assemblies is 6.

Further, the 6 piston assembly is composed of 3 pneumatic pistons and 3 hydraulic pistons.

Furthermore, the helicopter brake device also comprises a wear indication rod fixedly connected with the cylinder block.

Furthermore, the pressure bearing disc, the static disc, the pressing disc and the movable disc assembly are all made of carbon pottery.

Furthermore, the material of the brake shell is titanium alloy.

Compared with the prior art, the helicopter brake device has the following remarkable advantages:

1, through designing the brake casing for cap formula structure, conduct the extrusion force for the brake casing when making the bearing cup receive the extrusion, improved the anti extrusion strength of bearing cup, improved helicopter brake equipment's life-span.

And 2, the pressing disc, the static disc and the bearing disc are connected with the brake shell in a key connection mode, so that the brake is convenient to disassemble.

3, through setting up the degree of wear that the wearing and tearing instruction pole made to compress tightly dish, quiet dish, bearing disc and driving disk assembly can in time be known to in time change.

and 4, the brake shell is connected with the cylinder seat through bolts, so that the structure is simple, and the rigidity and the strength are good.

And 5, the bearing disc, the static disc, the pressing disc and the movable disc assembly are made of carbon pottery, so that the wet braking torque attenuation rate is low, and the service life is prolonged.

And 6, the thrust steel ring is arranged, so that the pressure bearing cup is prevented from sliding towards the rear end of the brake shell when receiving the propelling force.

Drawings

FIG. 1 is a front view of a helicopter brake apparatus of the present invention;

fig. 2 is a schematic cross-sectional view taken along line a-a of fig. 1.

Shown in the figure:

1-a brake shell, 101-a step surface, 2-a pressure-bearing cup, 3-a pressure-bearing disc, 4-a wear indication rod, 5-a static disc, 6-a movable disc component, 7-a pressure-bearing disc, 8-a steel pressure ring, 9-a cylinder seat, 10-a bolt, 11-an excircle key groove, 12-a piston component, 12.1-a pneumatic piston, 12.2-a hydraulic piston, 13-a thrust steel ring, 14-a rivet and 15-a through hole.

Detailed Description

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

As shown in fig. 1 and 2, the helicopter brake apparatus of the present invention comprises a brake housing 1, a pressure-bearing cup 2, a pressure-bearing disc 3, a wear indication rod 4, a stationary disc 5, a movable disc assembly 6, a pressure-bearing disc 7, a steel compression ring 8, a cylinder block 9, an outer circular key groove 11, a piston assembly 12 and a thrust steel ring 13, wherein 6 piston assemblies 12 are respectively fixed in a containing groove (not shown) on the cylinder block 9, and the 6 piston assemblies 12 can be pushed against the steel compression ring 8 by a driving force provided by an aircraft brake system, wherein the 6 piston assemblies 12 are composed of 3 pneumatic pistons 12.1 and 3 hydraulic pistons 12.2, the 3 pneumatic pistons 12.1 and 3 hydraulic pistons 12.2 are respectively connected to the aircraft brake system, convert the hydraulic or pneumatic pressure provided by the aircraft brake system into a pressing force, the hydraulic pistons 12.2 are normally used for driving, the pneumatic pistons 12.1 are started for driving when the hydraulic pistons 12.2 fail, the brake shell 1 is of a cap type structure, the brake shell 1 and a cylinder base 9 are respectively provided with 6 through holes (not shown in the figure), 6 bolts 10 respectively penetrate through the through holes to connect the brake shell 1 with the cylinder base 9, when the helicopter brake device is overhauled, the bolts 10 are disassembled to separate the brake shell 1 from the cylinder base 9, a wear indication rod 4 is fixedly connected with the cylinder base 9 and is used for indicating the wear degree of a static disc 5 and a movable disc assembly 6, a steel compression ring 8 is fixedly connected with the compression disc 7, the brake shell 1 is provided with 8 convex keys (not shown in the figure) which are parallel to each other, key grooves (not shown in the figure) corresponding to the 8 convex keys are respectively arranged on the inner sides of the compression disc 7 and the static disc 5, wherein the key grooves can be movably matched with the convex keys so that the compression disc 7 and the static disc 5 can slide along the axial direction of the brake shell 1, an excircle key groove 11 used for being matched with a main, so that movable disk subassembly 6 rotates along with the rotation of host wheel, static dish 5 sets up with movable disk subassembly 6 in turn, bearing plate 3 passes through bearing cup 2 and brake casing 1 fixed connection, bearing cup 2 is the solid of revolution, bearing cup 2 front end embedding bearing plate 3 is downthehole, bearing cup 2 rear end embedding brake casing 1 goes up in the through hole 15 that sets up, bearing cup 2 passes through rivet 14, thrust steel ring 13 is connected with brake casing 1, when the brake, piston assembly 12 promotes steel clamp ring 8, so that clamp plate 7 promotes static dish 5, extrude movable disk subassembly 6.

Further, the rear end of the brake housing 1 is provided with a step surface 101 corresponding to the thrust steel ring 13, the thrust steel ring 13 abuts against the step surface 101 to improve the adaptability of the thrust steel ring 13 and the brake housing 1, the thrust steel ring 13 is clamped and fixed at the rear end of the pressure-bearing cup 2 through the rivet 14, when the brake is performed, the pressure-bearing cup 2 bears backward thrust, the thrust steel ring 13 is clamped and fixed at the rear end of the pressure-bearing cup 2 to abut against the pressure-bearing cup 2, and the pressure-bearing cup 2 is prevented from sliding due to the influence of the thrust.

Furthermore, the pressure bearing disc 3, the static disc 5, the pressing disc 7 and the movable disc assembly 6 are all made of carbon ceramics, and are high-temperature resistant, high in friction performance and stable.

furthermore, the material of the brake shell 1 is titanium alloy, so that the brake shell 1 has good corrosion resistance and high heat resistance.

The working principle of the helicopter brake device is as follows:

When the helicopter slides, the main wheel (not shown in the figure) rolls on the ground, at the moment, the movable disk assembly 6 rotates along with the main wheel, the compression disk 7, the static disk 5, the pressure bearing disk 3 is static relative to the movable disk assembly 6, during braking, the piston assembly 12 extrudes the steel compression ring 8 under the action of hydraulic pressure, the compression disk 7 pushes the static disk 5 and extrudes the movable disk assembly 6, the compression between the static disk 5 and the movable disk assembly 6 generates friction, the main wheel of the helicopter brakes, when the brake is loosened, the piston assembly 12 returns, the friction between the static disk 5 and the movable disk assembly 6 disappears, and the main wheel of the helicopter relieves the brake.

The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the claims of the present invention.