CN201694389U - Hydraulic braking pressure supply device for airplane - Google Patents
Hydraulic braking pressure supply device for airplane Download PDFInfo
- Publication number
- CN201694389U CN201694389U CN2010292510200U CN201029251020U CN201694389U CN 201694389 U CN201694389 U CN 201694389U CN 2010292510200 U CN2010292510200 U CN 2010292510200U CN 201029251020 U CN201029251020 U CN 201029251020U CN 201694389 U CN201694389 U CN 201694389U
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- pressure
- brake
- valve
- braking
- voltage supply
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Abstract
The utility model belongs to an airplane hydraulic technology and relates to a hydraulic braking pressure supply device for an airplane. One end of an electric pump of the hydraulic braking pressure supply device is connected with an oil tank, the other end of the electric pump is connected with one end of an oil filter and a pressurizing overflow valve, the other end of the oil filter is connected with an inlet of a pressurizing electromagnetic valve, and two outlets of the pressurizing electromagnetic valve are respectively connected with a pressure supply overflow valve and one end of a one-way valve. The other end of the one-way valve is connected with a braking pressure accumulator in parallel; the braking pressure accumulator is connected with a pressure supply sensor, a pressure relay, one end of a braking valve and a pressure switch in parallel; and the other end of the braking valve is connected with a braking pressure sensor. The hydraulic braking pressure supply device adopts the electric pump to pressurize the pressure accumulator, adopts a hydraulic braking system which depends on pressure of the pressure accumulator to realize braking, is additionally provided with the pressure sensor, and can record supply pressure and braking pressure of an airplane braking system; meanwhile, the pressure relay is also provided; when the supply pressure is lower than 7MPa, the pressure relay transmits a signal to a control cabin and records the signal in a flight recorder.
Description
Technical field:
The utility model belongs to the aircraft hydraulic technique, relates to a kind of aircraft water brake voltage supply device.
Background technology
In existing aircraft water brake voltage supply device, generally adopt Hydraulic Pump directly for the brake disc voltage supply, this structural weight is heavy, complex structure, under the situation of not braking, pump idle running, by the unloader valve off-load, the Hydraulic Pump long-term work influences life-span of Hydraulic Pump.This mode has 2 drawbacks:
(1) installation site is limited: hydraulic pump shaft must link to each other with engine shaft, nonoptional leeway, the position of Hydraulic Pump, and hydraulic pump shaft and engine shaft be connected the technological requirement height.
(2) the Hydraulic Pump race time is long: when not braking, Hydraulic Pump also is in idling conditions, has influenced the efficient of driving engine and the life-span of Hydraulic Pump.
Summary of the invention
The purpose of this utility model is to propose a kind of long service life, simple in structure, aircraft water brake voltage supply device that the installation site is not limited.Technical solution of the present utility model is, water brake voltage supply device comprises brake accumulator, pressure switch, motor-drive pump, the pressurising electromagnetic valve, brake valve, brake pressure sensor, the voltage supply pressure sensor, pressure relay, the voltage supply by pass valve, the pressurising by pass valve, check valve and oil filter, motor-drive pump one end is connected with fuel tank, the other end of motor-drive pump joins with an end and the pressurising by pass valve of oil filter, the other end of oil filter is connected with the inlet of pressurising electromagnetic valve, two outlets of pressurising electromagnetic valve are connected with an end of voltage supply by pass valve and check valve respectively, the other end of check valve and brake accumulator, brake accumulator and voltage supply pressure sensor, pressure relay, one end of brake valve, the pressure switch parallel connection, the other end of brake valve links to each other with brake pressure sensor.Advantage that the utlity model has and beneficial effect, it is the pressure accumulator pressurising that the utility model has adopted motor-drive pump, hydraulic brake system by the accumulator pressure brake, and installed pressure sensor additional, can write down the voltage supply pressure and the brake pressure of airplane brake system, pressure relay has been installed simultaneously, when voltage supply pressure is lower than 7MPa, pressure relay reaches warning light in the driving compartment with low-voltage signal, and signal is recorded in the flight recorder of aircraft.
Advantage of the present utility model also has, and 1. aircraft water brake voltage supply device employing pressure accumulator is that pressure source is realized brake.2. pressurising control presssure switch control motor-drive pump and brake pressurising electromagnetic valve are the pressure accumulator pressurising, guarantee that pressure accumulator has enough pressure to realize brake function.3. be equipped with voltage supply pressure sensor and brake pressure sensor and survey voltage supply pressure and brake pressure respectively, the assurance chaufeur can be understood the real time information of brake gear.4. be equipped with pressure relay and can realize the low pressure alarming function.5. the installation site of this brake gear is unrestricted.
Description of drawings
Fig. 1 is a structural representation of the present utility model.
The specific embodiment
Below in conjunction with accompanying drawing the utility model is elaborated.Water brake voltage supply device comprises brake accumulator 7, pressure switch 12, motor-drive pump 2, pressurising electromagnetic valve 5, brake valve 8, brake pressure sensor 9, pressure sensor 11, pressure relay 13, voltage supply by pass valve 14, pressurising by pass valve 3, check valve 6 and oil filter 4, motor-drive pump 2 one ends are connected with fuel tank 1, the other end of motor-drive pump 2 joins with an end and the pressurising by pass valve 3 of oil filter 4, the other end of oil filter 4 is connected with the inlet of pressurising electromagnetic valve 5, two outlets of pressurising electromagnetic valve 5 are connected with an end of voltage supply by pass valve 14 and check valve 6 respectively, the other end of check valve 6 is connected with brake accumulator 7, brake accumulator 7 and voltage supply pressure sensor 11, pressure relay 13, one end of brake valve 8 and pressure switch 12 parallel connections, the other end of brake valve 8 links to each other with brake pressure sensor 9.
Water brake voltage supply device pressure is from brake accumulator 7, the pressure decay of this brake accumulator 7 is when being lower than 9MPa, 12 actions of pressurising control presssure switch, make motor-drive pump 2 and 5 energisings of brake pressurising electromagnetic valve, to pressure accumulator 7 pressurisings, when pressurising pressure reached 12MPa, pressurising control presssure switch 12 moved the pressure oil that motor-drive pump 2 produces once more by brake pressurising electromagnetic valve 5, make motor-drive pump 2 and 5 outages of brake pressurising electromagnetic valve, stop pressurising.During brake, chaufeur makes brake valve 8 conversions, and pressure oil enters pressurized strut 10 through brake valve 8, realizes brake.
Voltage supply pressure sensor 11 impression brake voltage supply pressure in the brake voltage supply device, the brake pressure sensor 9 on emergency brake valve right side is experienced the pressure of emergency brake.When emergent voltage supply pressure was lower than 7MPa, pressure relay 13 reached warning light in the driving compartment with low-voltage signal, and signal is recorded in the flight recorder of aircraft.
Voltage supply by pass valve 14 guarantees pressure accumulator 7 not overvoltages.Pressurising by pass valve 3 guarantees this not overvoltage of device in the pressurising process.Check valve 6 guarantees that the pressure oil of pressure accumulator 7 can counter-flow.Oil filter 4 guarantees the cleaning of brake voltage supply device fluid.
Claims (1)
1. aircraft water brake voltage supply device, it is characterized in that, water brake voltage supply device comprises brake accumulator (7), pressure switch (12), motor-drive pump (2), pressurising electromagnetic valve (5), brake valve (8), brake pressure sensor (9), voltage supply pressure sensor (11), pressure relay (13), voltage supply by pass valve (14), pressurising by pass valve (3), check valve (6) and oil filter (4), motor-drive pump (2) one ends are connected with fuel tank (1), the other end of motor-drive pump (2) joins with an end and the pressurising by pass valve (3) of oil filter (4), the other end of oil filter (4) is connected with the inlet of pressurising electromagnetic valve (5), two outlets of pressurising electromagnetic valve (5) are connected with the end of voltage supply by pass valve (14) with check valve (6) respectively, the other end of check valve (6) is connected with brake accumulator (7), brake accumulator (7) and voltage supply pressure sensor (11), pressure relay (13), one end of brake valve (8) and pressure switch (12) parallel connection, the other end of brake valve (8) links to each other with brake pressure sensor (9).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010292510200U CN201694389U (en) | 2010-02-08 | 2010-02-08 | Hydraulic braking pressure supply device for airplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010292510200U CN201694389U (en) | 2010-02-08 | 2010-02-08 | Hydraulic braking pressure supply device for airplane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN201694389U true CN201694389U (en) | 2011-01-05 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2010292510200U Expired - Fee Related CN201694389U (en) | 2010-02-08 | 2010-02-08 | Hydraulic braking pressure supply device for airplane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN201694389U (en) |
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102092472A (en) * | 2011-01-20 | 2011-06-15 | 北京航空航天大学 | Self-energy feeding type brake device for airplanes |
| CN102442430A (en) * | 2011-11-01 | 2012-05-09 | 哈尔滨飞机工业集团有限责任公司 | Aircraft hydraulic anti-skid braking pressure supply device |
| CN103818546A (en) * | 2012-11-16 | 2014-05-28 | 哈尔滨飞机工业集团有限责任公司 | Operating power steering system for airplane hydraulic control |
| CN105090143A (en) * | 2015-07-22 | 2015-11-25 | 南京梅山冶金发展有限公司 | Control system and control method for pitch oil cylinder of stacker-reclaimer |
| CN103979101B (en) * | 2014-04-25 | 2016-02-24 | 哈尔滨飞机工业集团有限责任公司 | Steering engine for unmanned plane hydraulic actuated work-saving device |
| CN106321530A (en) * | 2015-06-19 | 2017-01-11 | 北京强度环境研究所 | Graded loading low-overshoot braking recovery system and recovery method thereof |
| CN106801688A (en) * | 2015-11-26 | 2017-06-06 | 衡阳市利美电瓶车制造有限责任公司 | A kind of railless electric flatcar hydraulic power unit |
| CN107351823A (en) * | 2017-06-29 | 2017-11-17 | 西安航空制动科技有限公司 | A kind of more train brake system and its control method |
| CN108284947A (en) * | 2017-12-13 | 2018-07-17 | 中国航空工业集团公司成都飞机设计研究所 | A kind of airplane brake system based on pressure accumulation energy storage |
| CN110550195A (en) * | 2019-09-03 | 2019-12-10 | 中国航空工业集团公司西安飞机设计研究所 | brake system |
-
2010
- 2010-02-08 CN CN2010292510200U patent/CN201694389U/en not_active Expired - Fee Related
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102092472A (en) * | 2011-01-20 | 2011-06-15 | 北京航空航天大学 | Self-energy feeding type brake device for airplanes |
| CN102442430A (en) * | 2011-11-01 | 2012-05-09 | 哈尔滨飞机工业集团有限责任公司 | Aircraft hydraulic anti-skid braking pressure supply device |
| CN103818546A (en) * | 2012-11-16 | 2014-05-28 | 哈尔滨飞机工业集团有限责任公司 | Operating power steering system for airplane hydraulic control |
| CN103979101B (en) * | 2014-04-25 | 2016-02-24 | 哈尔滨飞机工业集团有限责任公司 | Steering engine for unmanned plane hydraulic actuated work-saving device |
| CN106321530A (en) * | 2015-06-19 | 2017-01-11 | 北京强度环境研究所 | Graded loading low-overshoot braking recovery system and recovery method thereof |
| CN106321530B (en) * | 2015-06-19 | 2018-03-16 | 北京强度环境研究所 | The low overshoot brake recovery system and its recovery method of a kind of hierarchical loading |
| CN105090143A (en) * | 2015-07-22 | 2015-11-25 | 南京梅山冶金发展有限公司 | Control system and control method for pitch oil cylinder of stacker-reclaimer |
| CN106801688A (en) * | 2015-11-26 | 2017-06-06 | 衡阳市利美电瓶车制造有限责任公司 | A kind of railless electric flatcar hydraulic power unit |
| CN107351823A (en) * | 2017-06-29 | 2017-11-17 | 西安航空制动科技有限公司 | A kind of more train brake system and its control method |
| CN108284947A (en) * | 2017-12-13 | 2018-07-17 | 中国航空工业集团公司成都飞机设计研究所 | A kind of airplane brake system based on pressure accumulation energy storage |
| CN110550195A (en) * | 2019-09-03 | 2019-12-10 | 中国航空工业集团公司西安飞机设计研究所 | brake system |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20110105 Termination date: 20150208 |
|
| EXPY | Termination of patent right or utility model |