CN105438453B - A kind of quiet brake of aircraft and its protection system - Google Patents
A kind of quiet brake of aircraft and its protection system Download PDFInfo
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- CN105438453B CN105438453B CN201410507995.0A CN201410507995A CN105438453B CN 105438453 B CN105438453 B CN 105438453B CN 201410507995 A CN201410507995 A CN 201410507995A CN 105438453 B CN105438453 B CN 105438453B
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Abstract
The present invention relates to a kind of quiet brake of aircraft and its protection system, system includes brake controller, quiet brake switch, quiet brake magnetic valve, switching valve and wheel spin-up transducer, the present invention is controlled using quiet brake switch to switching on and off for quiet brake system, when brake control unit, which detects aircraft, meets quiet brake system on-condition, quiet brake switch is pulled to on-position, quiet brake magnetic valve is connected, quiet brake fluid passes through quiet brake magnetic valve, switching valve is to brake machine wheel, when brake control unit, which detects aircraft, is unsatisfactory for quiet brake condition, quiet brake switch is pulled to on-position, quiet brake switch can not be pull-in on on-position, quiet brake magnetic valve is not turned on, now quiet brake does not work, it effectively prevent the maloperation of quiet brake system, improve the safety in utilization of aircraft.
Description
Technical field
The present invention relates to airplane brake system technical field, more particularly to a kind of quiet brake of aircraft and its protection system.
Background technology
Aircraft brake control system as important airborne equipment, brake system can normal work will have a strong impact on aircraft
Safety.At present, carbon brake material is used mostly on aircraft, a maximum characteristic for carbon brake material is exactly its static friction system
The relative coefficient of kinetic friction of number is much smaller, for military-civil aircraft in order to reduce takeoff distance, generally using engine reinforcing
Take off, this requires aircraft before take-off stops wheel to stop, it is therefore desirable to larger quiet brake pressure, this pressure is with respect to aircraft just
Normal brake pressure is much greater, is typically to set a Simple switch in driving cabin so being configured with quiet brake system on aircraft
The break-make of the quiet brake of control system, but easily there is misconnection and leads in this quiet brake, particularly in aircraft landing state, once occur
Misconnection is led to, and quiet brake pressure can be introduced directly into brake machine wheel, it may appear that quick-fried tire of stopping, and has a strong impact on aircraft utilization safety.
The content of the invention
The purpose of the present invention is：A kind of quiet brake of aircraft and its protection system are provided, when can guarantee that aircraft needs quiet brake
Quiet brake system is connected, when not needing quiet brake, it is ensured that quiet brake will not misconnection lead to, eliminate the possibility of maloperation, have
Effect improves the security of aircraft.
The technical scheme is that:A kind of quiet brake of aircraft and its protection system, including brake controller 1, quiet brake
Switch 2, quiet brake magnetic valve 3, the first switching valve 41, the second switching valve 42, left wheel spin-up transducer 51, right wheel speed are passed
Sensor 52；Brake controller 1 is electrically connected with quiet brake switch 2, and the quiet brake oil inlet of magnetic valve 3 is connected with quiet brake oil sources,
The quiet brake oil return opening of magnetic valve 3 is connected with quiet brake oil return, and quiet brake magnetic valve 3 is electrically connected with brake controller 1, quiet brake
The working hole of magnetic valve 3 is connected with the oil inlet of the first switching valve 41 and the second switching valve 42, the first switching valve 41 and the second conversion
Another oil inlet of valve 42 is connected with normal braking pressure oil port, and the working hole of the first switching valve 41 connects with left wheel brake
Connect, left wheel spin-up transducer 51 is installed in left wheel wheel shaft, the working hole of the second switching valve 42 connects with right wheel brake
Connect, right wheel spin-up transducer 52 is installed in right wheel wheel shaft, left and right wheel spin-up transducer 51,52 and brake controller 1
Electrical connection.
Described quiet brake switch 2 is a two-position switch, and is provided with magnet coil, when switch pulls open position
Magnet coil is powered off；When switch pulls on-position, and during solenoid ON, switch can be locked to on-position.
Described quiet brake magnetic valve 3 uses working hole under two-bit triplet structure, closed mode to be communicated with oil return, connects shape
Working hole is communicated with oil-feed under state.
When aircraft will carry out quiet brake, brake controller 1 detects the speed of left and right wheel spin-up transducer 51,52, when
Both speed are respectively less than 20km/h, and aircraft left and right main starting, when falling frame wheel load and being in ground, aircraft possesses quiet brake condition,
Quiet brake switch 2 is pulled into on-position, brake controller 1 is powered to the magnet coil of quiet brake switch 2, quiet brake switch
2 can be locked in on-position, and now brake controller 1 controls quiet brake magnetic valve 3 to connect, and quiet brake pressure passes through quiet brake electricity
Magnet valve 3, the first switching valve 41, the second switching valve 42 carry out quiet brake to left and right brake machine wheel.
Aircraft is in during aerial or high ski-running race, to prevent the protection that quiet brake is connected as follows, when aircraft is in sky
Left and right main starting falls frame wheel load and is in the air, not possessing quiet brake condition when middle, or aircraft is when high ski-running is run, left and right machine
The speed of wheel speed sensor 51,52 is all higher than 20km/h, does not also possess quiet brake condition now, if now artificial maloperation
Quiet brake switch 2 is pulled into on-position, does not possess quiet brake condition because brake controller 1 detects aircraft, therefore not
To the magnet coil energization to quiet brake switch 2, quiet brake switch 2 can not be locked in on-position, and quiet brake magnetic valve 3 can not
Connect, it is ensured that the possibility of maloperation, improve the security of aircraft.
The present invention is had the advantage that with beneficial effect：The present invention provides a kind of quiet brake of aircraft and its protection system, energy
Ensure aircraft need quiet brake when quiet brake system is connected, when not needing quiet brake, it is ensured that quiet brake will not misconnection lead to, disappear
Except the possibility of maloperation, the security of aircraft is effectively improved.
Brief description of the drawings
Fig. 1 is schematic structural view of the invention.
Embodiment
The present invention is illustrated with reference to Figure of description.
A kind of quiet brake and its protection system, including brake controller 1, quiet brake switch 2, quiet brake magnetic valve 3, first
Switching valve 41, the second switching valve 42, left wheel spin-up transducer 51, right wheel spin-up transducer 52；Brake controller 1 is stopped with quiet
Stopping switch 2 is electrically connected, and the quiet brake oil inlet of magnetic valve 3 is connected with quiet brake oil sources, and the quiet brake oil return opening of magnetic valve 3 is stopped with quiet
Car oil return is connected, and quiet brake magnetic valve 3 is electrically connected with brake controller 1, quiet the brake working hole of magnetic valve 3 and the first switching valve
41 and second switching valve 42 oil inlet connection, another oil inlet and normal braking of the first switching valve 41 and the second switching valve 42
Pressure oil port is connected, and the working hole of the first switching valve 41 is connected with left wheel brake, and left wheel spin-up transducer 51 is installed on
In left wheel wheel shaft, the working hole of the second switching valve 42 is connected with right wheel brake, and right wheel spin-up transducer 52 is installed on
In right wheel wheel shaft, left and right wheel spin-up transducer 51,52 is electrically connected with brake controller 1.
The signal that brake controller 1 receives left and right wheel spin-up transducer 51,52 carries out sentencing for aircraft or so wheel rotating speed
It is disconnected, fall frame wheel load signal while receiving left and right main starting and judge its vacant lot state, brake controller 1 receives quiet brake switch 2
Off and on is instructed, and combination left and right main starting falls frame wheel load and the left and right wheel rate signal of aircraft is judged on quiet brake switch
The break-make of magnet coil, so that the adhesive of controlling switch, and it is electric to quiet brake according to the break-make and attracting state of quiet brake switch 2
The break-make of magnet valve 3 is controlled.
When aircraft will carry out quiet brake, brake controller 1 detects the speed of left and right wheel spin-up transducer 51,52, when
Both speed are respectively less than 20km/h, and aircraft left and right main starting, when falling frame wheel load and being in ground, aircraft possesses quiet brake condition,
Quiet brake switch 2 is pulled into on-position, brake controller 1 is powered to the magnet coil of quiet brake switch 2, quiet brake switch
2 can be locked in on-position, and now brake controller 1 controls quiet brake magnetic valve 3 to connect, and quiet brake pressure passes through quiet brake electricity
Magnet valve 3, the first switching valve 41, the second switching valve 42 carry out quiet brake to left and right brake machine wheel.
Aircraft is in during aerial or high ski-running race, to prevent the protection that quiet brake is connected as follows, when aircraft is in sky
Left and right main starting falls frame wheel load and is in the air, not possessing quiet brake condition when middle, or aircraft is when high ski-running is run, left and right machine
The speed of wheel speed sensor 51,52 is all higher than 20km/h, does not also possess quiet brake condition now, if now artificial maloperation
Quiet brake switch 2 is pulled into on-position, does not possess quiet brake condition because brake controller 1 detects aircraft, therefore not
To the magnet coil energization to quiet brake switch 2, quiet brake switch 2 can not be locked in on-position, and quiet brake magnetic valve 3 can not
Connect, eliminate the possibility of maloperation, improve the security of aircraft.
Claims (4)
1. a kind of quiet brake of aircraft and its protection system, it is characterized in that, the system includes brake controller (1), quiet brake switch
(2), quiet brake magnetic valve (3), the first switching valve (41), the second switching valve (42), left wheel spin-up transducer (51), right wheel
Velocity sensor (52)；Brake control unit (1) and quiet brake switch (2) are electrically connected, quiet brake magnetic valve (3) oil inlet with
Quiet brake oil sources connection, quiet brake magnetic valve (3) oil return opening is connected with quiet brake oil return, and (30 control quiet brake magnetic valve with brake
Unit (1) electrical connection processed, the oil-feed of quiet brake magnetic valve (3) working hole and the first switching valve (41) and the second switching valve (42)
Another oil inlet of mouth connection, the first switching valve (41) and the second switching valve (42) is connected with normal braking pressure oil port, and first
Switching valve (41) working hole is connected with left wheel brake, and left wheel spin-up transducer (51) is installed in left wheel wheel shaft,
Second switching valve (42) working hole is connected with right wheel brake, and right wheel spin-up transducer (52) is installed on right wheel wheel shaft
Interior, left and right wheel spin-up transducer (51), (52) and brake control unit (1) are electrically connected.
Braked and its protection system 2. a kind of aircraft is quiet as claimed in claim 1, it is characterized in that, quiet brake switch (2) is one or two
Bit switch, and magnet coil is installed, when switch pulls open position, magnet coil is powered off；When switch pulls connection position
Put, and during solenoid ON, switch can be locked to on-position.
Braked and its protection system 3. a kind of aircraft is quiet as claimed in claim 1, it is characterized in that, quiet brake magnetic valve (3) uses
Working hole is communicated with oil return under two-bit triplet structure, closed mode, and working hole is communicated with oil-feed under on-state.
4. a kind of quiet brake of aircraft and its protection system as described in one of claim 1-3, it is characterized in that, brake control unit
(1) speed of detection left and right wheel spin-up transducer (51,52), when both speed are respectively less than 20km/h, and aircraft left and right main starting
When falling frame wheel load and being in ground, quiet brake switch (2) is pulled into on-position, brake control unit (1) is opened to quiet brake
The magnet coil for closing (2) is powered, and quiet brake switch (2) can be locked in on-position, and otherwise quiet brake switch (2) can not be locked in
On-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 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105438453A CN105438453A (en) | 2016-03-30 |
| CN105438453B true CN105438453B (en) | 2017-10-31 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| 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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| Country | Link |
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Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| 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 |
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. |
| 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 |
-
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 |
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| Publication number | Publication date |
|---|---|
| CN105438453A (en) | 2016-03-30 |
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