CN203698653U - Actuation support assembly of airplane electric-brake apparatus - Google Patents
Actuation support assembly of airplane electric-brake apparatus Download PDFInfo
- Publication number
- CN203698653U CN203698653U CN201420004494.6U CN201420004494U CN203698653U CN 203698653 U CN203698653 U CN 203698653U CN 201420004494 U CN201420004494 U CN 201420004494U CN 203698653 U CN203698653 U CN 203698653U
- Authority
- CN
- China
- Prior art keywords
- connecting rod
- hole
- bush
- bearing
- mounting
- 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.)
- Expired - Lifetime
Links
- 239000003921 oil Substances 0.000 claims abstract description 16
- 239000010687 lubricating oil Substances 0.000 claims abstract description 10
- 230000000712 assembly Effects 0.000 claims abstract description 7
- 238000000429 assembly Methods 0.000 claims abstract description 7
- 238000009434 installation Methods 0.000 claims abstract description 6
- 238000003745 diagnosis Methods 0.000 abstract 1
- 239000012530 fluid Substances 0.000 description 5
- 229910000881 Cu alloy Inorganic materials 0.000 description 2
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 2
- 230000015572 biosynthetic process Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 230000009977 dual effect Effects 0.000 description 1
- 230000005662 electromechanics Effects 0.000 description 1
- 238000003912 environmental pollution Methods 0.000 description 1
- 239000010720 hydraulic oil Substances 0.000 description 1
- 230000000977 initiatory effect Effects 0.000 description 1
- 238000012856 packing Methods 0.000 description 1
- 230000002093 peripheral effect Effects 0.000 description 1
Classifications
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
Landscapes
- Braking Arrangements (AREA)
Abstract
The utility model discloses an actuation support assembly of an airplane electric-brake apparatus. Four actuator assemblies are fixed in an arc-shaped installation groove in the circumferential surface of an actuation support. A shaft bushing is arranged in the center hole of the actuation support; a connecting rod bushing is arranged on a connecting rod hole in the upper end of the actuation support. A spiral lubricating oil groove is formed in the inner surface of the shaft bushing in the center hole of the actuation support. The inner surface of the shaft bushing is matched with the outer surface of an undercarriage axle. An undercarriage connecting rod installation hole is formed in the upper end of the actuation support. A connecting rod bushing is arranged in the undercarriage connecting rod installation hole, annular lubricating oil grooves are formed in the inner surface of the connecting rod bushing and the annular lubricating oil grooves are communicated with one another. An oil filling hole communicated with the lubricating oil grooves is formed in the connecting rod bushing. According to the actuation support assembly, the composition of a brake system is simplified, the weight of the system is reduced, and the fault diagnosis capability is enhanced; besides, the actuation support assembly has the characteristics of high response speed and high brake efficiency, and achieves unmanned operation easily.
Description
Technical field
The present invention relates to a kind of aircraft brake system, specifically a kind of Electric Braking Devices Using.
Background technology
Aircraft brake system mainly contains fluid brake and Electric Braking Devices Using.Electric Braking Devices Using comprises start mounting assembly, brake housing unit and heat reservoir assembly.Electric Braking Devices Using is arranged on main landing gear, completes aircraft at take-off line brake, ground taxi and landing braking, and the stop brake of the main wheel that brakes when gear up.
At present, Domestic Aircraft brake gear all adopts fluid brake, there is the problem that causes fire because of hydraulic oil leakage in fluid brake in use, in order to solve this potential safety hazard, the present invention proposes a kind of Electric Braking Devices Using, its technical characteristics is to replace traditional hydraulic actuation system with power-actuated actuating system to brake.Traditional water brake generally provides hydraulic power source by the Centralized Hydraulic System of aircraft, on brake gear, produces needed being used as power of brake by the hydraulic piston of series connection.Different from water brake, Electric Braking Devices Using is used separate module to make electric brake actuator produce braking action power.
The patent No. is to have proposed a kind of electric brake device for vehicle in 01224755 innovation and creation, and this device relies on and on coil reaction plate, wakes uniform 8 magnet coils up and realize braking automobile function.
The patent No. is that CN101117155B has proposed an aircraft electrical brake control system architecture, has related to aircraft electromechanical actuator.
The patent No. is US2013203554(A) electromechanics that proposed three grades of decelerations sits moving device, and it is different that wherein it uses a planetary ball-screw and the design's expansion equation level Four reductor motor-driven cylinder.But there is the defect that efficiency is not high in the planetary ball-screw-transmission mode adopting.
Summary of the invention
For overcoming the low deficiency of driving efficiency existing in prior art, the present invention proposes a kind of start mounting assembly of Electric Brake System of Aircraft device.
The present invention includes start bearing, axle bush, 4 actuator assemblies and connecting rod bush.Wherein 4 actuator assemblies are fixed in the lip-deep arc mounting groove of start seating circumference.Axle bush is arranged in the centre hole of start bearing, and connecting rod bush is arranged in the tie rod holes of start bearing upper end.Described start bearing centre hole is evenly equipped with the bolt hole for this start mounting assembly is connected with brake housing around.In described start bearing centre hole, axle bush is installed, has helix oilway at the inside face of this axle bush.The inside face of described axle bush coordinates with the outside face of alighting gear wheel shaft.The upper end of start bearing has and alighting gear connecting rod mounting hole.In described alighting gear mounting hole, connecting rod bush is installed, has annular oilway at the inside face of this connecting rod bush, and be communicated with between each annular oilway.Described connecting rod bush is housing shape, has the oil hole being communicated with oilway on this connecting rod bush.
The profile sub-circular of described start bearing.Be distributed with the installation groove of the actuator assembly of 4 arcs at the circumferential surface of this start bearing, and angle between the line of centers of each mounting groove width is 90 degree.Upper surface and lower surface that groove both sides are installed at each actuator assembly all have the attachment face coordinating with this actuator assembly.At the projection that has of described start bearing upper end, on this projection, there is alighting gear connecting rod mounting hole.
The inwall of described axle bush radially circumferencial direction has 3 equidistant thread-shaped oilways, and inwall center has an oil hole, is used for injecting lubricating oil in oil groove, and start bearing centre hole and alighting gear shaft connection place are lubricated.
On the inwall of described connecting rod bush, have vertically 1 oil groove, radially circumferencial direction has 3 equidistant annular oil grooves, inwall center has a radially oilhole, is used for injecting lubricating oil in oilway, and start carrier link hole and alighting gear connecting rod junction are lubricated.
The line of centers of the line of centers of described alighting gear mounting hole and start bearing centre hole is parallel to each other, and in same vertical surface.
Electric Braking Devices Using relies on the electromechanical actuator on start mounting assembly to produce brake required thrust, has broken away from traditional dependence hydraulic piston and has produced brake thrust, thereby avoided because brake fluid force feed is leaked initiation fire and problem of environmental pollution.With respect to fluid brake, the present invention has simplified brake system formation, has alleviated the weight of system, has strengthened trouble diagnosibility, and has that response is faster, braking efficiency is higher and be easier to realize unmanned feature.
Accompanying drawing explanation
Fig. 1 start mounting assembly section-drawing;
Fig. 2 start mounting assembly left view;
Fig. 3 start bearing section-drawing;
Fig. 4 start bearing right elevation;
The axle figure such as Fig. 5 start bearing;
Fig. 6 axle bush cutaway view;
Fig. 7 connecting rod bush cutaway view.Wherein:
1. start bearing; 2. axle bush; 3. actuator assembly; 4. connecting rod bush.
The specific embodiment
The present embodiment is the start mounting assembly in a kind of Electric Braking Devices Using.
Described start mounting assembly comprises start bearing 1,2,4 actuator assemblies 3 of axle bush and connecting rod bush 4.Wherein 4 actuator assemblies 3 are fixed by screws in the arc mounting groove on start bearing 1 circumferential surface.Axle bush 2 is arranged in the centre hole of start bearing 1, and connecting rod bush 4 is arranged in the tie rod holes of start bearing 1 upper end.Described start bearing 1 centre hole is evenly equipped with the bolt hole for this start mounting assembly is connected with brake housing around.In described start bearing centre hole, axle bush 2 is installed, has helix oilway at the inside face of this axle bush 2.Described axle bush 2 is housing shape.The inside face of this axle bush coordinates with the outside face of alighting gear wheel shaft.
The upper end of start bearing 1 has and alighting gear connecting rod mounting hole.In described alighting gear mounting hole, connecting rod bush 4 is installed, has annular oilway at the inside face of this connecting rod bush 4, and be communicated with between each annular oilway.Described connecting rod bush 4 is housing shape, on this connecting rod bush 4, has the oil hole being communicated with oilway.
The line of centers of the line of centers of described alighting gear mounting hole and start bearing centre hole is parallel to each other, and in same vertical surface.
The profile sub-circular of described start bearing 1.Be distributed with the installation groove of the actuator assembly 3 of 4 arcs at the circumferential surface of this start bearing 1, and angle between the line of centers of each mounting groove width is 90 degree.Upper surface and lower surface that groove both sides are installed at each actuator assembly all have the attachment face coordinating with this actuator assembly.At the projection that has of described start bearing 1 upper end, on this projection, there is alighting gear connecting rod mounting hole.
It is disclosed actuator assembly in 201310656428.7 innovation and creation that described actuator assembly is selected application number.In described 201310656428.7 claim 1～7, the technical characterictic of this actuator assembly is disclosed in detail:
This invention comprises housing, end cap, motor, ball-screw assembly, power sensor, needle bearing, reduction gear component, pilot bar, piston, heat insulating mattress, signal processor and plug-assembly.Reduction gear component is arranged between upper shell and middle shell; One end of described ball-screw assembly is arranged between upper shell and middle shell, and the other end is positioned at lower house.Described reduction gear component is dual gear, comprises the first gear and the second gear, and the second wherein said gear engages with the ball screw component gear in ball-screw assembly, and the first described gear engages with the output shaft of motor.Motor is arranged in middle shell; Plug-assembly is arranged in middle shell, for the wire of the wire of described motor and signal processor mouth is drawn.Described signal processor is placed in the signal processor mounting groove of middle shell upper surface; The data-in port UNICOM of the data line of power sensor and signal processor.Piston packing is arranged in described middle shell and lower house.Ball-screw assembly is arranged in described piston.The top of described ball-screw is positioned at upper shell.Ball-screw is positioned at ball nut intermeshing.Pilot bar is positioned at upper shell, and packs in the endoporus of ball-screw; The endoporus bearing fit of described pilot bar and ball-screw.Heat insulating mattress is positioned at outside lower house, and one end, through the via hole on described lower house, packs the inner chamber of ball-screw into.Power sensor sleeve is contained in the external peripheral surface of ball nut.Needle bearing is arranged on the bearing attachment face on the excircle of ball-screw assembly, and fits tightly with the lower surface of power sensor.
Actuator assembly 3 is brake gear parts for generation of braking action power.When work, in electromechanical actuator, the output torque of motor is delivered on ball-screw assembly after amplifying by gear reduction, and ball-screw promotes piston forward and moves, and circular movement is converted to and is moved axially.
Axle bush 2 is a copper alloy thin wall cylinder, its inwall radially circumferencial direction has 3 equidistant thread-shaped oilways, inwall center has an oil hole, for injecting lubricating oil to oil groove, start bearing centre hole and alighting gear shaft connection place is lubricated.
Connecting rod bush 4 is a copper alloy thin wall cylinder, on inwall, have vertically 1 oil groove, radially circumferencial direction has 3 equidistant annular oil grooves, inwall center has a radially oilhole, be used for injecting lubricating oil in oilway, start carrier link hole and alighting gear connecting rod junction are lubricated.
Claims (5)
1. a start mounting assembly for Electric Brake System of Aircraft device, is characterized in that, described start mounting assembly comprises start bearing, axle bush, 4 actuator assemblies and connecting rod bush; Wherein 4 actuator assemblies are fixed in the lip-deep arc mounting groove of start seating circumference; Axle bush is arranged in the centre hole of start bearing, and connecting rod bush is arranged in the tie rod holes of start bearing upper end; Described start bearing centre hole is evenly equipped with the bolt hole for this start mounting assembly is connected with brake housing around; In described start bearing centre hole, axle bush is installed, has helix oilway at the inside face of this axle bush; The inside face of described axle bush coordinates with the outside face of alighting gear wheel shaft; The upper end of start bearing has and alighting gear connecting rod mounting hole; In described alighting gear mounting hole, connecting rod bush is installed, has annular oilway at the inside face of this connecting rod bush, and be communicated with between each annular oilway; Described connecting rod bush is housing shape, has the oil hole being communicated with oilway on this connecting rod bush.
2. the start mounting assembly of Electric Brake System of Aircraft device as claimed in claim 1, is characterized in that the profile sub-circular of described start bearing; Be distributed with the installation groove of the actuator assembly of 4 arcs at the circumferential surface of this start bearing, and angle between the line of centers of each mounting groove width is 90 degree; Upper surface and lower surface that groove both sides are installed at each actuator assembly all have the attachment face coordinating with this actuator assembly; At the projection that has of described start bearing upper end, on this projection, there is alighting gear connecting rod mounting hole.
3. the start mounting assembly of Electric Brake System of Aircraft device as claimed in claim 1, it is characterized in that, the inwall of axle bush radially circumferencial direction has 3 equidistant thread-shaped oilways, inwall center has an oil hole, be used for injecting lubricating oil in oil groove, start bearing centre hole and alighting gear shaft connection place are lubricated.
4. the start mounting assembly of Electric Brake System of Aircraft device as claimed in claim 1, it is characterized in that, on the inwall of connecting rod bush, have vertically 1 oil groove, radially circumferencial direction has 3 equidistant annular oil grooves, inwall center has a radially oilhole, be used for injecting lubricating oil in oilway, start carrier link hole and alighting gear connecting rod junction are lubricated.
5. the start mounting assembly of Electric Brake System of Aircraft device as claimed in claim 1, is characterized in that, the line of centers of the line of centers of described alighting gear mounting hole and start bearing centre hole is parallel to each other, and in same vertical surface.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420004494.6U CN203698653U (en) | 2014-01-03 | 2014-01-03 | Actuation support assembly of airplane electric-brake apparatus |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420004494.6U CN203698653U (en) | 2014-01-03 | 2014-01-03 | Actuation support assembly of airplane electric-brake apparatus |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203698653U true CN203698653U (en) | 2014-07-09 |
Family
ID=51049128
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420004494.6U Expired - Lifetime CN203698653U (en) | 2014-01-03 | 2014-01-03 | Actuation support assembly of airplane electric-brake apparatus |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203698653U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105697619A (en) * | 2016-03-16 | 2016-06-22 | 西安航空制动科技有限公司 | Piston assembly in electric braking actuator |
| CN109322759A (en) * | 2018-12-10 | 2019-02-12 | 中国航发四川燃气涡轮研究院 | A kind of pressurized strut seat structure |
-
2014
- 2014-01-03 CN CN201420004494.6U patent/CN203698653U/en not_active Expired - Lifetime
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105697619A (en) * | 2016-03-16 | 2016-06-22 | 西安航空制动科技有限公司 | Piston assembly in electric braking actuator |
| CN105697619B (en) * | 2016-03-16 | 2017-12-12 | 西安航空制动科技有限公司 | Piston component in electric brake actuator |
| CN109322759A (en) * | 2018-12-10 | 2019-02-12 | 中国航发四川燃气涡轮研究院 | A kind of pressurized strut seat structure |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN104442784B (en) | Integrated electric control master cylinder drive system | |
| CN104641149B (en) | Combined vehicle brake | |
| CN201262205Y (en) | Actuating mechanism of electronic-mechanical braking system | |
| CN104071142B (en) | A kind of electric motor car line control brake system | |
| CN102966686B (en) | A kind of brake caliper assembly of vehicle electronic parking braking system | |
| CN205578558U (en) | Automotive electronics mechanical brake with clearance adjustment function | |
| CN104670482A (en) | Electric worm-gear airplane braking system and method for operating braking system | |
| CN204284259U (en) | Vehicle wheel side speed reducer and wet type brake assembly | |
| CN104691747A (en) | Air vehicle full-electric braking device and method thereof | |
| CN103953667A (en) | High-efficiency magneto-rheological braking device | |
| CN103711819A (en) | Electric brake actuator comprising signal conditioning module | |
| CN203698653U (en) | Actuation support assembly of airplane electric-brake apparatus | |
| CN106704312A (en) | Digital hydraulic cylinder with novel feedback mechanism | |
| CN103407436B (en) | Electromagnetic control type device for eliminating air loss energy consumption and improving low-speed performance of hydrodynamic retarder | |
| CN109305339B (en) | Three-redundancy full-electric brake actuating system | |
| CN205292617U (en) | Electronic and mechanical braking system | |
| CN203651807U (en) | Spring braking totally-closed wet-type parking brake | |
| CN203836032U (en) | High-efficient magneto-rheological braking device | |
| CN103486164A (en) | Engine oil medium type hydraulic retarder | |
| CN203500340U (en) | Engine oil medium type hydraulic retarder | |
| CN203698261U (en) | Electric brake device for unmanned aerial vehicle | |
| CN203463527U (en) | Vehicle electronic mechanical brake actuator | |
| CN202992122U (en) | Heavy-duty car axle hub reductor structure | |
| CN202418309U (en) | Driving device of automatic clutch for vehicle | |
| CN202742989U (en) | Driving axle with parking brake |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CX01 | Expiry of patent term |
Granted publication date: 20140709 |
|
| CX01 | Expiry of patent term |