CN204527621U - Aircraft electric braking device - Google Patents
Aircraft electric braking device Download PDFInfo
- Publication number
- CN204527621U CN204527621U CN201520081479.6U CN201520081479U CN204527621U CN 204527621 U CN204527621 U CN 204527621U CN 201520081479 U CN201520081479 U CN 201520081479U CN 204527621 U CN204527621 U CN 204527621U
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- Prior art keywords
- quiet dish
- support
- torque tube
- screw mandrel
- aircraft
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- 230000000712 assembly Effects 0.000 claims abstract description 19
- 238000000429 assembly Methods 0.000 claims abstract description 19
- 238000010276 construction Methods 0.000 claims 1
- 230000000694 effects Effects 0.000 description 3
- 239000012530 fluid Substances 0.000 description 3
- 239000010720 hydraulic oil Substances 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 238000011835 investigation Methods 0.000 description 1
- 239000007788 liquid Substances 0.000 description 1
- 238000010248 power generation Methods 0.000 description 1
- 238000004904 shortening Methods 0.000 description 1
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- Regulating Braking Force (AREA)
- Braking Systems And Boosters (AREA)
- Braking Arrangements (AREA)
Abstract
A kind of aircraft electric braking device, belongs to aircraft electric drag technical field.This brake gear comprises electromechanical assemblies, support, Torque tube, heat reservoir assembly and tachometric survey assembly.Electromechanical assemblies symmetry is arranged on the side of support, and Torque tube is arranged on support opposite side, and heat reservoir pieces is in Torque tube, and housing and tachometric survey assembly are arranged on the both sides of wheel respectively.Lead screw motor rotates, and drives screw mandrel and screw mandrel termination straight-line motion, quiet dish and Moving plate is compressed, and aircraft is stopped and stopped by generation brake torque.The utility model volume is little, lightweight, can be applied in and have on the small aircraft of quite strict restriction alighting gear braking device size and weight.
Description
Technical field
The utility model relates to a kind of aircraft brake brake equipment, specifically a kind of small aircraft electrical brake brake equipment and method.
Technical background
Aircraft brake device mainly contains fluid brake and electrical brake device.Quite ripe at traditional fluid brake both at home and abroad, but hydraulic actuation mechanism needs complicated high pressure liquid potential source, and hydraulic oil also has the danger of burning, and a whole set of hydraulic actuation mechanism is complicated and heavy.
Abroad bring into use on part type in electrical brake device, and this area research of domestic aspect is started late, basic investigation is less.Be propose a kind of unmanned plane brake gear in the utility model patent " a kind of unmanned plane Electric Braking Devices Using " of CN203698261U at publication number, but it is not suitable for small-sized unmanned aircraft, electromechanical actuator is comparatively complicated, and does not have pressure and tachogen.
At present, on small aircraft, particularly small-sized unmanned aircraft, because size is little, lightweight, there is quite strict restriction to the size of alighting gear braking device and weight.And small aircraft does not generally have hydraulic power source, therefore fluid brake cannot be used.For electrical brake device, on small aircraft, there is not ripe application yet.
Utility model content
The purpose of this utility model: have the strict small aircraft limited for the size to alighting gear braking device, weight, propose a kind of electrical brake device and method electric power being converted into aircraft brake braking force.
The technical solution of the utility model: this aircraft brake brake equipment comprises support and wheel shaft, support right center position is fixed with Torque tube, and described wheel shaft is relative with Torque tube fixing through the two ends, left and right of Torque tube and support.
This aircraft brake brake equipment also comprises the electromechanical assemblies group be positioned on the left of support; Be positioned at the heat reservoir assembly, wheel, the tachometric survey assembly that to be installed on successively on the right side of support on wheel shaft.
Electromechanical assemblies group is made up of along the uniform electromechanical assemblies of wheel shaft circumference some; Each electromechanical assemblies by the lead screw motor be fixed on the left of support, the screw mandrel be installed in lead screw motor, be installed on screw mandrel right-hand member screw mandrel termination, be installed on screw mandrel termination pressure sensor composition; Described support is provided with the limiting holes corresponding with screw mandrel termination; Lead screw motor can drive screw mandrel to drive screw mandrel termination and pressure sensor through described limiting holes.
Heat reservoir assembly comprises the housing of left side opening, and above-mentioned Torque tube extend in housing by this opening; This heat reservoir assembly also comprises the first quiet dish be installed on successively from left to right in Torque tube, dynamic/quiet dish group, whole quiet dish wherein in the first quiet dish, dynamic/quiet dish group all adopts axial keyway mode coordinate and do not contact with case inside with Torque tube, and the quiet dish in the first quiet dish, dynamic/quiet dish group can not be rotated by relative torque forces pipe; Housing side also has fluting, and the Moving plate in dynamic/quiet dish group has the convex key with this slotted engagement, and the Moving plate in dynamic/quiet dish group does not contact with Torque tube, and Moving plate can be rotated together with housing; This heat reservoir assembly also comprises the bearing disc of the right-hand end being fixed on Torque tube.
Wheel is arranged on wheel shaft by bearing, fixes on the right side of the housing of heat reservoir assembly with on the left of wheel.
Aircraft lands, wheel drives housing and Moving plate to rotate around wheel shaft, when needing to brake, brake controller is to lead screw motor signal, lead screw motor rotates, drive screw mandrel and screw mandrel termination straight-line motion in support limiting holes, by pressure sensor by the first quiet dish and dynamic/quiet dish group axial compression, brake pressure Real-time Feedback to brake controller, is rotated by adjustment lead screw motor and makes actual brake pressure consistent with brake controller demand pressure by pressure sensor; First quiet dish and dynamic/quiet dish group contact friction, the kinetic energy that aircraft advances is dissipated with the form of heat energy, thus wheel is slowed down, wheel rotating speed Real-time Feedback is constantly used for antiskid brake to brake controller by tachogen, and aircraft can be stopped and stop under high efficiency braking effect.
The beneficial effects of the utility model:
A () this brake gear relies on the brake weight required for electric power generation, no longer need heavy hydraulic efficiency gear, alleviate aircraft weight.Do not re-use hydraulic oil, reduce the danger of hydraulic oil burning, improve safety.The speed of response of electric actuator, far above hydraulic actuation mechanism, shortens response time, improves braking efficiency.
B () this brake gear volume is little, lightweight, can be applied in and have on the small aircraft of quite strict restriction alighting gear braking device size and weight.
C () this brake gear tachometric survey assembly is composed as follows: comprise tachogen, and tachogen is installed in erecting frame, and erecting frame is fixed on wheel shaft, and the hollow shaft portion of tachogen is fixed by coupler and described wheel.The actual brake pressure that pressure sensor Real-time Feedback electromechanical assemblies applies, completes accurate pressure and applies; Tachogen provides real-time wheel speed feedback, improves antiskid brake performance, and shortening stops stops distance, improves the service life of tire and brake gear.
Accompanying drawing explanation
Accompanying drawing 1 aircraft brake brake device structure schematic diagram;
Accompanying drawing 2 electromechanical assemblies and support installing schematic diagram;
Accompanying drawing 3 tachometric survey assembly scheme of installation;
Accompanying drawing 4 aircraft brake brake equipment section-drawings;
Number in the figure title: 1, lead screw motor, 2, screw mandrel, 3, screw mandrel termination, 4, pressure sensor, the 5, first quiet dish, 6, Moving plate, 7, bearing disc, 8, housing, 9, support, 10, Torque tube, 11, wheel, 12, coupler, 13, tachogen, 14, erecting frame, 15, wheel shaft.
detailed description of the invention:
This aircraft brake brake equipment comprises electromechanical assemblies, support 9, Torque tube 10, heat reservoir assembly and tachometric survey assembly.
Electromechanical assemblies comprises lead screw motor 1, screw mandrel 2, screw mandrel termination 3 and pressure sensor 4, and screw mandrel termination 3 is arranged on screw mandrel 2 one end near support 9 by holding screw, moves linearly vertically in support 9 limiting holes with screw mandrel 2.
Support 9 is major support members, and electromechanical assemblies, Torque tube 10 and alighting gear are installed in its effect, and bear being used as power of electromechanical assemblies.Lead screw motor 1 and Torque tube 10 are installed respectively by screw in support both sides.The knock hole of two installation alighting gears is had above support 9.Support 9 has the limiting holes coordinated with screw mandrel termination 3, and restriction screw mandrel termination 3, this hole, along the rotation in support 9 plane, only allows the rectilinear movement perpendicular to support 9 plane.
Pressure sensor 4 is arranged on screw mandrel termination 3 by screw, between screw mandrel termination 3 and the first quiet dish 5, can obtain the brake pressure that electromechanical assemblies is applied to the first quiet dish 5 in real time.
Torque tube 10 is arranged on support 9 center, is delivered on support 9, is also delivered to the friction moment on quiet dish 5 on support 9 by the brake pressure of bearing disc 7.
Heat reservoir assembly comprises the first quiet dish 5, dynamic/quiet dish group, bearing disc 7 and housing 8.First quiet dish 5 is placed in Torque tube 10, coordinates with the convex key in Torque tube 10.Bearing disc 7 is arranged on the side of Torque tube 10 near wheel 11 by screw, limits the movement of quiet dish 5 and dynamic/quiet dish group, and electromechanical assemblies is applied to quiet dish 5 dynamic/brake pressure of quiet dish group is delivered in Torque tube 10.Quiet dish 5 Moving plate 6 conventional approach is alternately placed in Torque tube 10, is wrapped up wherein by housing 8, the convex key on Moving plate 6 and the fit depressions of housing 8.Housing 8 is arranged on the side of wheel 11 by bolt, rotates together under the drive of wheel 11.Aircraft kinetic energy dissipates with the form of heat energy by heat reservoir assembly.
Tachogen 13 is hollow shaft sensor, and its hollow shaft is connected with wheel 11 by coupler 12, rotates together under the drive of wheel 11.Tachogen 13 outside face is connected by erecting frame 14 and wheel shaft 15, does not rotate with wheel together with hollow shaft.
Wheel shaft 15, through the center of tachogen 13, wheel 11, bearing disc 7, Torque tube 10, support 9, has in support 9 electromechanical assemblies side the mounting head be connected with alighting gear.
During aircraft lands, wheel 11 drives housing 8 and Moving plate 6 to rotate around wheel shaft 15, when needing to brake, brake controller is to lead screw motor 1 signal, lead screw motor 1 rotor rotates, drive screw mandrel 2 and screw mandrel termination 3 straight-line motion vertically in support 9, compressed with Moving plate 6 by quiet dish 5 by pressure sensor 4, brake pressure Real-time Feedback to brake controller, is rotated by adjustment lead screw motor 1 rotor and makes true brake pressure consistent with brake controller demand pressure by pressure sensor 4; Quiet dish 5 and Moving plate 6 contact friction, the kinetic energy that aircraft advances is dissipated with the form of heat energy, thus making aircraft down, wheel rotating speed Real-time Feedback is constantly used for antiskid brake to brake controller by tachogen 13, and aircraft can be stopped and stop under high efficiency braking effect.
Claims (2)
1. an aircraft brake brake equipment, is characterized in that:
This aircraft brake brake equipment comprises support (9) and wheel shaft (15), and support right center position is fixed with Torque tube (10), and described wheel shaft (15) is relative fixing with Torque tube (10) through the two ends, left and right of Torque tube (10) and support (9);
This aircraft brake brake equipment also comprises the electromechanical assemblies group being positioned at support (9) left side; Be positioned at support (9) right side and be installed on heat reservoir assembly, wheel (11), tachometric survey assembly on wheel shaft (15) successively;
Above-mentioned electromechanical assemblies group is made up of along the uniform electromechanical assemblies of wheel shaft (15) circumference some; Each electromechanical assemblies is by being fixed on the lead screw motor (1) in support (9) left side, the screw mandrel (2) be installed in lead screw motor (1), being installed on the screw mandrel termination (3) of screw mandrel (2) right-hand member, being installed on pressure sensor (4) composition of screw mandrel termination (3); Described support (9) is provided with the limiting holes corresponding with screw mandrel termination (3) position, size; Lead screw motor (1) can drive screw mandrel (2) to drive screw mandrel termination (3) and pressure sensor (4) through described limiting holes;
Above-mentioned heat reservoir assembly comprises the housing (8) of left side opening, and above-mentioned Torque tube (10) extend in housing (8) by this opening; This heat reservoir assembly also comprises the first quiet dish (5) be installed on successively from left to right in Torque tube (10), dynamic/quiet dish group, whole quiet dish wherein in the first quiet dish (5), dynamic/quiet dish group all adopts axial keyway mode to coordinate with Torque tube (10) and does not contact with housing (8) inner side, and the quiet dish in the first quiet dish (5), dynamic/quiet dish group can not be rotated by relative torque forces pipe (10); Housing (8) side also has fluting, and the Moving plate in dynamic/quiet dish group has the convex key with this slotted engagement, and the Moving plate (6) in dynamic/quiet dish group does not contact with Torque tube (10), and Moving plate (6) can be rotated together with housing (8); This heat reservoir assembly also comprises the bearing disc (7) of the right-hand end being fixed on Torque tube (10);
Above-mentioned wheel (11) is arranged on wheel shaft (15) by bearing, and housing (8) right side of above-mentioned heat reservoir assembly fixes with wheel (11) left side.
2. aircraft brake brake equipment according to claim 1, it is characterized in that above-mentioned tachometric survey unit construction is as follows: comprise tachogen (13), tachogen (13) is installed in erecting frame (14), erecting frame (14) is fixed on wheel shaft (15), and the hollow shaft portion of tachogen (13) is fixed by coupler (12) and described wheel (11).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520081479.6U CN204527621U (en) | 2015-02-05 | 2015-02-05 | Aircraft electric braking device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520081479.6U CN204527621U (en) | 2015-02-05 | 2015-02-05 | Aircraft electric braking device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204527621U true CN204527621U (en) | 2015-08-05 |
Family
ID=53741649
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520081479.6U Withdrawn - After Issue CN204527621U (en) | 2015-02-05 | 2015-02-05 | Aircraft electric braking device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN204527621U (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104691747A (en) * | 2015-02-05 | 2015-06-10 | 南京航空航天大学 | Air vehicle full-electric braking device and method thereof |
| CN108488266A (en) * | 2018-06-12 | 2018-09-04 | 北京航空航天大学 | A kind of disc-type brake gear suitable for miniature unmanned vehicle wheel |
| CN110435882A (en) * | 2019-07-11 | 2019-11-12 | 南京航空航天大学 | Aircraft brake brake apparatus based on Piezoelectric Driving flexibility displacement amplifying mechanism |
| CN111824400A (en) * | 2020-06-05 | 2020-10-27 | 贵州新安航空机械有限责任公司 | Electromechanical actuating brake device |
-
2015
- 2015-02-05 CN CN201520081479.6U patent/CN204527621U/en not_active Withdrawn - After Issue
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104691747A (en) * | 2015-02-05 | 2015-06-10 | 南京航空航天大学 | Air vehicle full-electric braking device and method thereof |
| CN104691747B (en) * | 2015-02-05 | 2016-08-24 | 南京航空航天大学 | Aircraft electric braking device and method |
| CN108488266A (en) * | 2018-06-12 | 2018-09-04 | 北京航空航天大学 | A kind of disc-type brake gear suitable for miniature unmanned vehicle wheel |
| CN110435882A (en) * | 2019-07-11 | 2019-11-12 | 南京航空航天大学 | Aircraft brake brake apparatus based on Piezoelectric Driving flexibility displacement amplifying mechanism |
| CN110435882B (en) * | 2019-07-11 | 2022-04-22 | 南京航空航天大学 | Aircraft brake device based on piezoelectric drive flexible displacement amplification mechanism |
| CN111824400A (en) * | 2020-06-05 | 2020-10-27 | 贵州新安航空机械有限责任公司 | Electromechanical actuating brake device |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20150805 Effective date of abandoning: 20160824 |
|
| C25 | Abandonment of patent right or utility model to avoid double patenting |