CN102442430A - Aircraft hydraulic anti-skid braking pressure supply device - Google Patents
Aircraft hydraulic anti-skid braking pressure supply device Download PDFInfo
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- CN102442430A CN102442430A CN2011103402332A CN201110340233A CN102442430A CN 102442430 A CN102442430 A CN 102442430A CN 2011103402332 A CN2011103402332 A CN 2011103402332A CN 201110340233 A CN201110340233 A CN 201110340233A CN 102442430 A CN102442430 A CN 102442430A
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Abstract
The invention belongs to the aircraft hydraulic technology and especially relates to an aircraft hydraulic anti-skid braking pressure supply device, which contains a baking pressure reservoir (7), a pressure switch (12), an electric pump (2), a pressurizing solenoid valve (5), an antiskid braking valve (8), braking pressure transducer (9), a pressure supply pressure transducer (11), a pressure relay (13), a pressure supply overflow valve (14), a pressurizing overflow valve (3), a non-return valve (6), an oil filter (4), a speed transmitter and a control box (15). According to the invention, the pressure reservoir is used as a pressure source to realize braking; the pressurizing control pressure switch controls the electric pump and the brake pressurizing solenoid valve to pressurize the pressure reservoir and guarantee there is enough pressure in the pressure reservoir for realizing the brake function; the pressure supply pressure transducer and the braking pressure transducer are installed to respectively detect the pressure-supply pressure and the braking pressure so as to ensure a driver understands real-time information of the braking device; and the pressure relay on the braking device has a low-pressure alarm function. The installation position of the invention is not limited.
Description
Technical field
The invention belongs to the aircraft hydraulic technique, particularly relate to a kind of aircraft hydraulic pressure antiskid brake voltage supply device.
Background technology
In the existing aircraft water brake voltage supply device, generally adopt Hydraulic Pump directly to be the brake disc voltage supply, this structural weight is heavy; Complex structure, under the situation of not braking, pump idle running; Through the unloader valve off-load, the Hydraulic Pump long-term work influences life-span of Hydraulic Pump; And can't control brake pressure simply accurately, cause tyre explosion when brake pressure is excessive.This mode has 3 drawbacks:
The 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 to be connected technological requirement high.
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.
Can not mediate to brake pressure, possibly cause tyre explosion.
Summary of the invention
The object of the invention: provide a kind of long service life, simple in structure, the installation site is not limited, and can prevent the aircraft hydraulic pressure antiskid brake voltage supply device of tyre explosion
Technical scheme of the present invention is: a kind of aircraft hydraulic pressure antiskid brake voltage supply device; It is characterized in that; Comprise brake accumulator 7, pressure switch 12, motor-drive pump 2, pressurising electromagnetic valve 5, antiskid 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, speed sensor and control capsule 15;
Said motor-drive pump 2 one ends are connected with fuel tank 1; The other end 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 check valve 6 with oil filter 4 respectively, and the other end of check valve 6 is connected with brake accumulator 7, and brake accumulator 7 is parallelly connected with an end of pressure relay 13, pressure switch 12, voltage supply pressure sensor 11 and brake valve 8; The other end of brake valve 8 links to each other with brake pressure sensor 9, and speed sensor and control capsule 15 are experienced the wheel rotating speed and controlled the electromagnetic conversion of antiskid brake valve 8.
The invention has the beneficial effects as follows: it is that pressure source is realized brake that the present invention adopts pressure accumulator; Pressurising control presssure switch control motor-drive pump is the pressure accumulator pressurising with brake pressurising electromagnetic valve; Guarantee that pressure accumulator has enough pressure to realize brake function; And 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, and the pressure relay on the device has the low pressure alarming function.Installation site of the present invention is unrestricted.
Description of drawings:
Fig. 1 is a structural representation of the present invention.
Wherein, 1 fuel tank, 2 motor-drive pumpes, 3 pressurising by pass valves, 4 oil filters, 5 pressurising electromagnetic valves, 6 check valves, 7 brake accumulators, 8 brake valves, 9 brake pressure sensors, 10 pressurized struts, 11 pressure sensors, 12 pressure switches, 13 pressure relayes, 14 voltage supply by pass valves, 15 speed sensors and control capsule, 16 wheels.
The specific embodiment
A kind of aircraft hydraulic pressure antiskid brake voltage supply device; It is characterized in that; Comprise brake accumulator 7, pressure switch 12, motor-drive pump 2, pressurising electromagnetic valve 5, antiskid 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, speed sensor and control capsule 15;
Said motor-drive pump 2 one ends are connected with fuel tank 1; The other end 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 check valve 6 with oil filter 4 respectively, and the other end of check valve 6 is connected with brake accumulator 7, and brake accumulator 7 is parallelly connected with an end of pressure relay 13, pressure switch 12, voltage supply pressure sensor 11 and brake valve 8; The other end of brake valve 8 links to each other with brake pressure sensor 9, and speed sensor and control capsule 15 are experienced the wheel rotating speed and controlled the electromagnetic conversion of antiskid brake valve 8.
Water brake voltage supply device pressure is from brake accumulator 7, the pressure decay of this brake accumulator 7 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 through 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 gets into 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 hydraulic pressure antiskid brake voltage supply device; It is characterized in that; Comprise brake accumulator [7], pressure switch [12], motor-drive pump [2], pressurising electromagnetic valve [5], antiskid 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], speed sensor and control capsule [15];
Said motor-drive pump [2] one ends are connected with fuel tank [1]; The other end 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 oil filter [4] and check valve [6] respectively, and the other end of check valve [6] is connected with brake accumulator [7], and brake accumulator [7] is parallelly connected with an end of pressure relay [13], pressure switch [12], voltage supply pressure sensor [11] and brake valve [8]; The other end of brake valve [8] links to each other with brake pressure sensor [9], and speed sensor and control capsule [15] are experienced the wheel rotating speed and controlled the electromagnetic conversion of antiskid brake valve [8].
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011103402332A CN102442430A (en) | 2011-11-01 | 2011-11-01 | Aircraft hydraulic anti-skid braking pressure supply device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011103402332A CN102442430A (en) | 2011-11-01 | 2011-11-01 | Aircraft hydraulic anti-skid braking pressure supply device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN102442430A true CN102442430A (en) | 2012-05-09 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
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| CN2011103402332A Pending CN102442430A (en) | 2011-11-01 | 2011-11-01 | Aircraft hydraulic anti-skid braking pressure supply device |
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| CN (1) | CN102442430A (en) |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103552685A (en) * | 2013-11-20 | 2014-02-05 | 渭南高新区晨星专利技术咨询有限公司 | Aircraft anti-skid brake control method |
| 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 |
| CN103818549A (en) * | 2012-11-16 | 2014-05-28 | 哈尔滨飞机工业集团有限责任公司 | Automatic hydraulic braking pressure supply device for unmanned aerial vehicle |
| CN104760692A (en) * | 2015-04-01 | 2015-07-08 | 西安航空制动科技有限公司 | Normal aircraft brake system |
| 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 |
| CN110203379A (en) * | 2019-07-08 | 2019-09-06 | 西安航空制动科技有限公司 | Airplane brake system and control method with aerial overbottom pressure warning function |
| CN110316361A (en) * | 2019-07-19 | 2019-10-11 | 赵海荣 | A kind of braking system of aircraft |
| CN112173088A (en) * | 2020-09-25 | 2021-01-05 | 中国直升机设计研究所 | Combined pressure accumulator with flow rate control function and hydraulic brake system |
Citations (5)
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| CN1198389A (en) * | 1997-05-02 | 1998-11-11 | 海德尔罗－艾尔公司 | System and method for adaptive brake application and initial skid detection |
| CN101224740A (en) * | 2008-01-31 | 2008-07-23 | 赵西安 | Anti-lock method |
| US20100274457A1 (en) * | 2009-04-24 | 2010-10-28 | Cahill Eric D | Deceleration controlled braking |
| US20100286881A1 (en) * | 2009-05-05 | 2010-11-11 | Goodrich Corporation | Brake wear control system |
| CN201694389U (en) * | 2010-02-08 | 2011-01-05 | 哈尔滨飞机工业集团有限责任公司 | Hydraulic braking pressure supply device for airplane |
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2011
- 2011-11-01 CN CN2011103402332A patent/CN102442430A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1198389A (en) * | 1997-05-02 | 1998-11-11 | 海德尔罗－艾尔公司 | System and method for adaptive brake application and initial skid detection |
| CN101224740A (en) * | 2008-01-31 | 2008-07-23 | 赵西安 | Anti-lock method |
| US20100274457A1 (en) * | 2009-04-24 | 2010-10-28 | Cahill Eric D | Deceleration controlled braking |
| US20100286881A1 (en) * | 2009-05-05 | 2010-11-11 | Goodrich Corporation | Brake wear control system |
| CN201694389U (en) * | 2010-02-08 | 2011-01-05 | 哈尔滨飞机工业集团有限责任公司 | Hydraulic braking pressure supply device for airplane |
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN103818549A (en) * | 2012-11-16 | 2014-05-28 | 哈尔滨飞机工业集团有限责任公司 | Automatic hydraulic braking pressure supply device for unmanned aerial vehicle |
| CN103552685A (en) * | 2013-11-20 | 2014-02-05 | 渭南高新区晨星专利技术咨询有限公司 | Aircraft anti-skid brake control method |
| CN104760692A (en) * | 2015-04-01 | 2015-07-08 | 西安航空制动科技有限公司 | Normal aircraft brake system |
| 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 |
| CN110203379A (en) * | 2019-07-08 | 2019-09-06 | 西安航空制动科技有限公司 | Airplane brake system and control method with aerial overbottom pressure warning function |
| CN110203379B (en) * | 2019-07-08 | 2024-02-02 | 西安航空制动科技有限公司 | Aircraft brake system with air residual pressure warning function and control method |
| CN110316361A (en) * | 2019-07-19 | 2019-10-11 | 赵海荣 | A kind of braking system of aircraft |
| CN112173088A (en) * | 2020-09-25 | 2021-01-05 | 中国直升机设计研究所 | Combined pressure accumulator with flow rate control function and hydraulic brake system |
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Application publication date: 20120509 |