CN105438453A - Aircraft static brake and protection system thereof - Google Patents
Aircraft static brake and protection system thereof Download PDFInfo
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- CN105438453A CN105438453A CN201410507995.0A CN201410507995A CN105438453A CN 105438453 A CN105438453 A CN 105438453A CN 201410507995 A CN201410507995 A CN 201410507995A CN 105438453 A CN105438453 A CN 105438453A
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Abstract
The invention relates to an aircraft static brake and a protection system thereof. The system includes a brake controller, a static brake switch, a static brake electromagnetic valve, conversion valves and wheel speed sensors. The aircraft static brake provided by the invention adopts a static brake switch to control the on-off of a static brake system, when the brake control unit detects that the aircraft meets the static brake system on-condition, the static brake switch is flipped to an on-position, the static brake electromagnetic valve can be connected, static brake oil fluid reaches brake wheels through the static brake electromagnetic valve and the conversion valves, when the brake control unit detects that the aircraft does not meet the static brake condition, the static brake switch is flipped to the on-position, the static brake switch cannot be pulled in to the on-position, and the static brake electromagnetic valve is not connected and therefore does not work at the moment. According to the invention, misoperation of the static brake system is effectively prevented, and the use safety of aircrafts is improved.
Description
Technical field
The present invention relates to airplane brake system technical field, particularly relate to the quiet brake of a kind of aircraft and protection system thereof.
Background technology
Aircraft brake control system is as important airborne equipment, and can brake system normally work and will have a strong impact on aircraft safety.At present, aircraft adopts carbon brake material mostly, a maximum characteristic for carbon brake material is exactly that its coefficient of static friction is much smaller relative to dynamic friction coefficient, for military-civil aircraft in order to reduce takeoff distance, the AB takeoff of usual employing driving engine, this just requires that wheel is stopped by aircraft before take-off and stops, therefore larger quiet brake pressure is needed, this pressure is much bigger relative to aircraft normal braking pressure, so aircraft is configured with quiet brake system, the break-make of a quiet brake of Simple switch control system is normally set at driving compartment, but this quiet brake easily occurs that misconnection is led to, particularly in aircraft landing state, once occur that misconnection is led to, quiet brake pressure can be introduced directly into brake machine wheel, there will be quick-fried tire of stopping, have a strong impact on aircraft utilization safety.
Summary of the invention
The object of the invention is: the quiet brake of a kind of aircraft and protection system thereof are provided; ensureing that aircraft needs quiet brake system to be connected during quiet brake, when not needing quiet brake, ensureing that quiet brake can not be led in misconnection; eliminate the possibility of maloperation, effectively improve the safety of aircraft.
Technical scheme of the present invention is: the quiet brake of a kind of aircraft and protection system thereof, comprise brake controller 1, quiet BK Brake Switch 2, quiet brake electric magnet valve 3, first change-over valve 41, second change-over valve 42, left wheel spin-up transducer 51, right wheel spin-up transducer 52, brake control unit 1 and quiet BK Brake Switch 2 are electrically connected, quiet brake electric magnet valve 3 oil inlet is connected with quiet brake oil sources, quiet brake electric magnet valve 3 return opening is connected with quiet brake oil return, quiet brake electric magnet valve 3 is electrically connected with brake control unit 1, quiet brake electric magnet valve 3 working hole is connected with the oil inlet of the first change-over valve 41 and the second change-over valve 42, first change-over valve 41 is connected with normal braking pressure oil port with another oil inlet of the second change-over valve 42, first change-over valve 41 working hole is connected with left wheel brake, left wheel spin-up transducer 51 is installed in left wheel wheel shaft, second change-over valve 42 working hole is connected with right wheel brake, right wheel spin-up transducer 52 is installed in right wheel wheel shaft, left, right wheel spin-up transducer 51, 52 are electrically connected with brake control unit 1.
Described quiet BK Brake Switch 2 is a two-position switch, and is provided with magnet coil, the magnet coil power-off when open position pulled by switch; When control position pulled by switch, and when magnet coil is connected, switch can lock onto control position.
Described quiet brake electric magnet valve 3 adopts two-bit triplet structure, and under closed condition, working hole communicates with oil return, and under on-state, working hole communicates with oil-feed.
When aircraft will carry out quiet brake, brake control unit 1 detects left and right wheel spin-up transducer 51, the speed of 52, when both speed are all less than 20km/h, and aircraft is left, when starboard main landing gear wheel load is all in ground, aircraft possesses quiet brake condition, quiet BK Brake Switch 2 is pulled control position, brake control unit 1 is energized to the magnet coil of quiet BK Brake Switch 2, quiet BK Brake Switch 2 can be locked in control position, now brake control unit 1 controls quiet brake electric magnet valve 3 and connects, quiet brake pressure is by quiet brake electric magnet valve 3, first change-over valve 41, second change-over valve 42 carries out quiet brake to left and right brake machine wheel.
Aircraft is in aerial or high ski-running race process, for the protection preventing quiet brake from connecting is as follows, it is left when aircraft is in aerial, starboard main landing gear wheel load is all in the air, do not possess quiet brake condition, or aircraft is when high ski-running is run, left and right wheel spin-up transducer 51, the speed of 52 is all greater than 20km/h, now do not possess quiet brake condition yet, if now quiet BK Brake Switch 2 is pulled control position for maloperation by people, because brake control unit 1 detects that aircraft does not possess quiet brake condition, therefore be not energized to the magnet coil of quiet BK Brake Switch 2, quiet BK Brake Switch 2 can not be locked in control position, quiet brake electric magnet valve 3 cannot be connected, ensure that the possibility of maloperation, improve the safety of aircraft.
The advantage that the present invention has and beneficial effect are: the invention provides the quiet brake of a kind of aircraft and protection system thereof; can ensure that aircraft needs quiet brake system to be connected during quiet brake; when not needing quiet brake; ensure that quiet brake can not be led in misconnection; eliminate the possibility of maloperation, effectively improve the safety of aircraft.
Accompanying drawing explanation
Fig. 1 is structural representation of the present invention.
Detailed description of the invention
Below in conjunction with Figure of description, the present invention is illustrated.
A kind of quiet brake and protection system thereof, comprise brake controller 1, quiet BK Brake Switch 2, quiet brake electric magnet valve 3, first change-over valve 41, second change-over valve 42, left wheel spin-up transducer 51, right wheel spin-up transducer 52, brake control unit 1 and quiet BK Brake Switch 2 are electrically connected, quiet brake electric magnet valve 3 oil inlet is connected with quiet brake oil sources, quiet brake electric magnet valve 3 return opening is connected with quiet brake oil return, quiet brake electric magnet valve 3 is electrically connected with brake control unit 1, quiet brake electric magnet valve 3 working hole is connected with the oil inlet of the first change-over valve 41 and the second change-over valve 42, first change-over valve 41 is connected with normal braking pressure oil port with another oil inlet of the second change-over valve 42, first change-over valve 41 working hole is connected with left wheel brake, left wheel spin-up transducer 51 is installed in left wheel wheel shaft, second change-over valve 42 working hole is connected with right wheel brake, right wheel spin-up transducer 52 is installed in right wheel wheel shaft, left, right wheel spin-up transducer 51, 52 are electrically connected with brake control unit 1.
The signal that brake control unit 1 receives left and right wheel spin-up transducer 51,52 carries out the judgement of aircraft left and right wheel rotating speed, receive left and right main starting to fall frame wheel load signal judge its vacant lot state simultaneously, brake control unit 1 receives the disconnection of quiet BK Brake Switch 2 and goes code, and judge the break-make of magnet coil in quiet BK Brake Switch in conjunction with fall frame wheel load and aircraft left and right wheel speed signal of left and right main starting, thus the adhesive of master cock, and control according to the break-make of quiet BK Brake Switch 2 and the break-make of attracting state to quiet brake electric magnet valve 3.
When aircraft will carry out quiet brake, brake control unit 1 detects left and right wheel spin-up transducer 51, the speed of 52, when both speed are all less than 20km/h, and aircraft is left, when starboard main landing gear wheel load is all in ground, aircraft possesses quiet brake condition, quiet BK Brake Switch 2 is pulled control position, brake control unit 1 is energized to the magnet coil of quiet BK Brake Switch 2, quiet BK Brake Switch 2 can be locked in control position, now brake control unit 1 controls quiet brake electric magnet valve 3 and connects, quiet brake pressure is by quiet brake electric magnet valve 3, first change-over valve 41, second change-over valve 42 carries out quiet brake to left and right brake machine wheel.
Aircraft is in aerial or high ski-running race process, for the protection preventing quiet brake from connecting is as follows, it is left when aircraft is in aerial, starboard main landing gear wheel load is all in the air, do not possess quiet brake condition, or aircraft is when high ski-running is run, left and right wheel spin-up transducer 51, the speed of 52 is all greater than 20km/h, now do not possess quiet brake condition yet, if now quiet BK Brake Switch 2 is pulled control position for maloperation by people, because brake control unit 1 detects that aircraft does not possess quiet brake condition, therefore be not energized to the magnet coil of quiet BK Brake Switch 2, quiet BK Brake Switch 2 can not be locked in control position, quiet brake electric magnet valve 3 cannot be connected, ensure that the possibility of maloperation, improve the safety of aircraft.
Claims (4)
1. the quiet brake of aircraft and protection system thereof, it is characterized in that, native system comprises brake controller (1), quiet BK Brake Switch (2), quiet brake electric magnet valve (3), first change-over valve (41), the second change-over valve (42), left wheel spin-up transducer (51), right wheel spin-up transducer (52), brake control unit (1) and quiet BK Brake Switch (2) are electrically connected, quiet brake electric magnet valve (3) oil inlet is connected with quiet brake oil sources, quiet brake electric magnet valve (3) return opening is connected with quiet brake oil return, (30 are electrically connected with brake control unit (1) quiet brake electric magnet valve, quiet brake electric magnet valve (3) working hole is connected with the oil inlet of the first change-over valve (41) and the second change-over valve (42), first change-over valve (41) is connected with normal braking pressure oil port with another oil inlet of the second change-over valve (42), first change-over valve (41) working hole is connected with left wheel brake, left wheel spin-up transducer (51) is installed in left wheel wheel shaft, second change-over valve (42) working hole is connected with right wheel brake, right wheel spin-up transducer (52) is installed in right wheel wheel shaft, left, right wheel spin-up transducer (51), (52) be electrically connected with brake control unit (1).
2. the quiet brake of a kind of aircraft and protection system thereof as claimed in claim 1, it is characterized in that, quiet BK Brake Switch (2) is a two-position switch, and is provided with magnet coil, the magnet coil power-off when open position pulled by switch; When control position pulled by switch, and when magnet coil is connected, switch can lock onto control position.
3. the quiet brake of a kind of aircraft and protection system thereof as claimed in claim 1, is characterized in that, quiet brake electric magnet valve (3) adopts two-bit triplet structure, and under closed condition, working hole communicates with oil return, and under on-state, working hole communicates with oil-feed.
4. a kind of quiet brake protection system as described in one of claim 1-3; it is characterized in that; brake control unit (1) detects the speed of left and right wheel spin-up transducer (51), (52); when both speed are all less than 20km/h; when and aircraft left and right main starting falls, frame wheel load is all in ground; quiet BK Brake Switch (2) is pulled control position; brake control unit (1) is energized to the magnet coil of quiet BK Brake Switch (2); quiet BK Brake Switch (2) can be locked in control position, otherwise quiet BK Brake Switch (2) cannot be locked in control position.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410507995.0A CN105438453B (en) | 2014-09-28 | 2014-09-28 | A kind of quiet brake of aircraft and its protection system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410507995.0A CN105438453B (en) | 2014-09-28 | 2014-09-28 | A kind of quiet brake of aircraft and its protection system |
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| Publication Number | Publication Date |
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| CN105438453A true CN105438453A (en) | 2016-03-30 |
| CN105438453B CN105438453B (en) | 2017-10-31 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201410507995.0A Active CN105438453B (en) | 2014-09-28 | 2014-09-28 | A kind of quiet brake of aircraft and its protection system |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107352020A (en) * | 2017-06-29 | 2017-11-17 | 西安航空制动科技有限公司 | A kind of airplane brake system and the control method of quiet brake protection |
| CN110510111A (en) * | 2019-09-09 | 2019-11-29 | 西安航空制动科技有限公司 | Quiet brake protection circuit and its design method with anti-interference ability |
| CN110562475A (en) * | 2019-09-06 | 2019-12-13 | 中国航空工业集团公司西安飞机设计研究所 | control system of plane ejection traction rod |
| CN110816820A (en) * | 2019-10-30 | 2020-02-21 | 中国航空工业集团公司沈阳飞机设计研究所 | Brake deceleration control system |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN102300755A (en) * | 2009-01-29 | 2011-12-28 | 海卓-艾尔公司 | Taxi brake inhibit system |
| EP2591961A1 (en) * | 2011-11-09 | 2013-05-15 | The Boeing Company | System and method for controlling an electronic brake |
| EP2641791A1 (en) * | 2012-03-21 | 2013-09-25 | Messier-Bugatti-Dowty | An electromechanical braking system for an aircraft. |
| CN104002784A (en) * | 2014-05-14 | 2014-08-27 | 西安航空制动科技有限公司 | Brake control system of multi-wheel-train brake machine wheel |
| EP2777998A2 (en) * | 2013-03-14 | 2014-09-17 | The Boeing Company | Method and apparatus to monitor components of an aircraft landing system |
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2014
- 2014-09-28 CN CN201410507995.0A patent/CN105438453B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102300755A (en) * | 2009-01-29 | 2011-12-28 | 海卓-艾尔公司 | Taxi brake inhibit system |
| EP2591961A1 (en) * | 2011-11-09 | 2013-05-15 | The Boeing Company | System and method for controlling an electronic brake |
| EP2641791A1 (en) * | 2012-03-21 | 2013-09-25 | Messier-Bugatti-Dowty | An electromechanical braking system for an aircraft. |
| EP2777998A2 (en) * | 2013-03-14 | 2014-09-17 | The Boeing Company | Method and apparatus to monitor components of an aircraft landing system |
| CN104002784A (en) * | 2014-05-14 | 2014-08-27 | 西安航空制动科技有限公司 | Brake control system of multi-wheel-train brake machine wheel |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107352020A (en) * | 2017-06-29 | 2017-11-17 | 西安航空制动科技有限公司 | A kind of airplane brake system and the control method of quiet brake protection |
| CN107352020B (en) * | 2017-06-29 | 2019-11-22 | 西安航空制动科技有限公司 | A kind of airplane brake system and the control method of quiet brake protection |
| CN110562475A (en) * | 2019-09-06 | 2019-12-13 | 中国航空工业集团公司西安飞机设计研究所 | control system of plane ejection traction rod |
| CN110510111A (en) * | 2019-09-09 | 2019-11-29 | 西安航空制动科技有限公司 | Quiet brake protection circuit and its design method with anti-interference ability |
| CN110510111B (en) * | 2019-09-09 | 2024-01-30 | 西安航空制动科技有限公司 | Static brake protection circuit with anti-interference capability and design method thereof |
| CN110816820A (en) * | 2019-10-30 | 2020-02-21 | 中国航空工业集团公司沈阳飞机设计研究所 | Brake deceleration control system |
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| Publication number | Publication date |
|---|---|
| CN105438453B (en) | 2017-10-31 |
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