CN110541900A - Helicopter brake device - Google Patents
Helicopter brake device Download PDFInfo
- Publication number
- CN110541900A CN110541900A CN201910780322.5A CN201910780322A CN110541900A CN 110541900 A CN110541900 A CN 110541900A CN 201910780322 A CN201910780322 A CN 201910780322A CN 110541900 A CN110541900 A CN 110541900A
- Authority
- CN
- China
- Prior art keywords
- brake
- disc
- helicopter
- pressure
- assembly
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 229910000831 Steel Inorganic materials 0.000 claims abstract description 33
- 239000010959 steel Substances 0.000 claims abstract description 33
- 230000003068 static effect Effects 0.000 claims description 24
- 230000006835 compression Effects 0.000 claims description 20
- 238000007906 compression Methods 0.000 claims description 20
- 230000000712 assembly Effects 0.000 claims description 7
- 238000000429 assembly Methods 0.000 claims description 7
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims description 5
- 229910052799 carbon Inorganic materials 0.000 claims description 5
- 239000000463 material Substances 0.000 claims description 4
- 229910001069 Ti alloy Inorganic materials 0.000 claims description 3
- 239000000919 ceramic Substances 0.000 claims description 3
- 238000012423 maintenance Methods 0.000 abstract description 6
- 239000007787 solid Substances 0.000 abstract description 2
- 230000009286 beneficial effect Effects 0.000 description 3
- 238000001125 extrusion Methods 0.000 description 3
- 230000008859 change Effects 0.000 description 2
- 239000010720 hydraulic oil Substances 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 238000009825 accumulation Methods 0.000 description 1
- 230000009471 action Effects 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- 230000007797 corrosion Effects 0.000 description 1
- 238000005265 energy consumption Methods 0.000 description 1
- 238000004146 energy storage Methods 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 238000007689 inspection Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 230000002035 prolonged effect Effects 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface
- B64C25/42—Arrangement or adaptation of brakes
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16D—COUPLINGS FOR TRANSMITTING ROTATION; CLUTCHES; BRAKES
- F16D55/00—Brakes with substantially-radial braking surfaces pressed together in axial direction, e.g. disc brakes
- F16D55/24—Brakes with substantially-radial braking surfaces pressed together in axial direction, e.g. disc brakes with a plurality of axially-movable discs, lamellae, or pads, pressed from one side towards an axially-located member
- F16D55/26—Brakes with substantially-radial braking surfaces pressed together in axial direction, e.g. disc brakes with a plurality of axially-movable discs, lamellae, or pads, pressed from one side towards an axially-located member without self-tightening action
- F16D55/36—Brakes with a plurality of rotating discs all lying side by side
- F16D55/40—Brakes with a plurality of rotating discs all lying side by side actuated by a fluid-pressure device arranged in or one the brake
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16D—COUPLINGS FOR TRANSMITTING ROTATION; CLUTCHES; BRAKES
- F16D65/00—Parts or details
- F16D65/02—Braking members; Mounting thereof
- F16D65/04—Bands, shoes or pads; Pivots or supporting members therefor
- F16D65/092—Bands, shoes or pads; Pivots or supporting members therefor for axially-engaging brakes, e.g. disc brakes
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16D—COUPLINGS FOR TRANSMITTING ROTATION; CLUTCHES; BRAKES
- F16D65/00—Parts or details
- F16D65/14—Actuating mechanisms for brakes; Means for initiating operation at a predetermined position
- F16D65/16—Actuating mechanisms for brakes; Means for initiating operation at a predetermined position arranged in or on the brake
- F16D65/18—Actuating mechanisms for brakes; Means for initiating operation at a predetermined position arranged in or on the brake adapted for drawing members together, e.g. for disc brakes
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16D—COUPLINGS FOR TRANSMITTING ROTATION; CLUTCHES; BRAKES
- F16D66/00—Arrangements for monitoring working conditions, e.g. wear, temperature
- F16D66/02—Apparatus for indicating wear
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16D—COUPLINGS FOR TRANSMITTING ROTATION; CLUTCHES; BRAKES
- F16D2121/00—Type of actuator operation force
- F16D2121/02—Fluid pressure
- F16D2121/04—Fluid pressure acting on a piston-type actuator, e.g. for liquid pressure
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Braking Arrangements (AREA)
Abstract
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.
Description
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.
The prior art has at least the following problems:
The helicopter brake device in the prior art is complex in structure and not beneficial to maintenance.
The helicopter brake device aims at the problems that a helicopter brake device in the prior art is complex in structure and not beneficial to maintenance, and an effective solution is not provided at present.
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.
Claims (7)
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.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CN201910780322.5A CN110541900A (en) | 2019-08-22 | 2019-08-22 | Helicopter brake device |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CN201910780322.5A CN110541900A (en) | 2019-08-22 | 2019-08-22 | Helicopter brake device |
Publications (1)
Publication Number | Publication Date |
---|---|
CN110541900A true CN110541900A (en) | 2019-12-06 |
Family
ID=68711889
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
CN201910780322.5A Pending CN110541900A (en) | 2019-08-22 | 2019-08-22 | Helicopter brake device |
Country Status (1)
Country | Link |
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CN (1) | CN110541900A (en) |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN111824399A (en) * | 2020-06-05 | 2020-10-27 | 贵州新安航空机械有限责任公司 | Synchronous locking mechanism about aircraft is with wheel |
CN115773318A (en) * | 2022-12-05 | 2023-03-10 | 北京少仕科技有限公司 | Vehicle braking device |
Citations (14)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5540305A (en) * | 1993-11-05 | 1996-07-30 | Dunlop Limited | Multi-disc brake |
US5588507A (en) * | 1995-09-15 | 1996-12-31 | Alliedsignal, Inc. | Aircraft brake assembly providing additional wearable friction material |
CN1259194A (en) * | 1997-06-06 | 2000-07-05 | 联合讯号公司 | Method of converting aircraft brake assemblies |
US6532637B1 (en) * | 1997-06-06 | 2003-03-18 | Honeywell International Inc. | Method of converting an aircraft brake assembly and a convertible aircraft brake assembly |
CN203246585U (en) * | 2013-04-03 | 2013-10-23 | 北京北摩高科摩擦材料有限责任公司 | Brake casing of airplane wheel brake device in large transport airplane |
CN203698261U (en) * | 2014-01-03 | 2014-07-09 | 西安航空制动科技有限公司 | Electric brake device for unmanned aerial vehicle |
CN204415719U (en) * | 2015-02-05 | 2015-06-24 | 北京北摩高科摩擦材料有限责任公司 | A kind of brake shell assembly of airplane wheel brake device |
CN105156516A (en) * | 2015-09-29 | 2015-12-16 | 西安航空制动科技有限公司 | Steel pressure-bearing disc assembly for brake device |
CN205801503U (en) * | 2016-06-30 | 2016-12-14 | 北京北摩高科摩擦材料有限责任公司 | A kind of brake shell assembly of main airplane wheel |
CN205801504U (en) * | 2016-06-30 | 2016-12-14 | 北京北摩高科摩擦材料有限责任公司 | A kind of main airplane wheel brake gear |
CN106672218A (en) * | 2016-12-22 | 2017-05-17 | 西安航空制动科技有限公司 | Carbon/ceramic brake device for airplane |
CN207292394U (en) * | 2017-09-30 | 2018-05-01 | 北京北摩高科摩擦材料股份有限公司 | A kind of aircraft brake system |
CN208842618U (en) * | 2018-08-22 | 2019-05-10 | 北京北摩高科摩擦材料股份有限公司 | A kind of brake main wheel of helicopter |
CN211371094U (en) * | 2019-08-22 | 2020-08-28 | 北京北摩高科摩擦材料股份有限公司 | Helicopter brake device |
-
2019
- 2019-08-22 CN CN201910780322.5A patent/CN110541900A/en active Pending
Patent Citations (14)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5540305A (en) * | 1993-11-05 | 1996-07-30 | Dunlop Limited | Multi-disc brake |
US5588507A (en) * | 1995-09-15 | 1996-12-31 | Alliedsignal, Inc. | Aircraft brake assembly providing additional wearable friction material |
CN1259194A (en) * | 1997-06-06 | 2000-07-05 | 联合讯号公司 | Method of converting aircraft brake assemblies |
US6532637B1 (en) * | 1997-06-06 | 2003-03-18 | Honeywell International Inc. | Method of converting an aircraft brake assembly and a convertible aircraft brake assembly |
CN203246585U (en) * | 2013-04-03 | 2013-10-23 | 北京北摩高科摩擦材料有限责任公司 | Brake casing of airplane wheel brake device in large transport airplane |
CN203698261U (en) * | 2014-01-03 | 2014-07-09 | 西安航空制动科技有限公司 | Electric brake device for unmanned aerial vehicle |
CN204415719U (en) * | 2015-02-05 | 2015-06-24 | 北京北摩高科摩擦材料有限责任公司 | A kind of brake shell assembly of airplane wheel brake device |
CN105156516A (en) * | 2015-09-29 | 2015-12-16 | 西安航空制动科技有限公司 | Steel pressure-bearing disc assembly for brake device |
CN205801503U (en) * | 2016-06-30 | 2016-12-14 | 北京北摩高科摩擦材料有限责任公司 | A kind of brake shell assembly of main airplane wheel |
CN205801504U (en) * | 2016-06-30 | 2016-12-14 | 北京北摩高科摩擦材料有限责任公司 | A kind of main airplane wheel brake gear |
CN106672218A (en) * | 2016-12-22 | 2017-05-17 | 西安航空制动科技有限公司 | Carbon/ceramic brake device for airplane |
CN207292394U (en) * | 2017-09-30 | 2018-05-01 | 北京北摩高科摩擦材料股份有限公司 | A kind of aircraft brake system |
CN208842618U (en) * | 2018-08-22 | 2019-05-10 | 北京北摩高科摩擦材料股份有限公司 | A kind of brake main wheel of helicopter |
CN211371094U (en) * | 2019-08-22 | 2020-08-28 | 北京北摩高科摩擦材料股份有限公司 | Helicopter brake device |
Cited By (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN111824399A (en) * | 2020-06-05 | 2020-10-27 | 贵州新安航空机械有限责任公司 | Synchronous locking mechanism about aircraft is with wheel |
CN111824399B (en) * | 2020-06-05 | 2023-06-13 | 贵州新安航空机械有限责任公司 | Synchronous locking mechanism about aviation is with wheel |
CN115773318A (en) * | 2022-12-05 | 2023-03-10 | 北京少仕科技有限公司 | Vehicle braking device |
CN115773318B (en) * | 2022-12-05 | 2024-02-02 | 北京少仕科技有限公司 | Vehicle braking device |
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