CN206579838U - A kind of distributed aircraft brake control system - Google Patents
A kind of distributed aircraft brake control system Download PDFInfo
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- CN206579838U CN206579838U CN201720147471.4U CN201720147471U CN206579838U CN 206579838 U CN206579838 U CN 206579838U CN 201720147471 U CN201720147471 U CN 201720147471U CN 206579838 U CN206579838 U CN 206579838U
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Abstract
A kind of distributed aircraft brake control system of the utility model, is made up of the first wheel braking and the second wheel braking, wherein the first wheel braking is made up of first brake instruction sensor component, the first wheel spin-up transducer component, the first water brake component.Second wheel braking of distributed brake system is made up of the second brake instruction transducer component, the second wheel spin-up transducer component, the second water brake component.The problem of system work failure rate is high caused by being transmitted it solves existing airplane hydraulic pressure brake system because of sensor with control signal using analog quantity.
Description
Technical field
This patent is related to a kind of distributed airplane hydraulic pressure brake system, and specifically a kind of each wheel braking of aircraft is completely only
Vertical brake-by-wire system.
Background technology
Brake instruction transducer, wheel spin-up transducer and the water brake pressure of current aircraft fax hydraulic brake system
The output signal of the sensors such as sensor is transmitted using analog quantity by cable, by a set of brake control unit (BCU)
Carry out concentrated collection.And BCU is computed exporting the brake electric current to hydraulic efficiency servo-valve according to the various sensor signals received
Signal, the control signal of magnetic valve are also to be transmitted by the voltage and current signal of analog quantity.Because BCU is apart from above-mentioned sensing
Device, hydraulic package are distant, and transmission cable is longer, cause the poor anti jamming capability and precision of the analog signal of sensor output
Low problem is than more serious, the phenomenon that output signal decays by the long presence of cable.
The centerized fusion structure of the use of current aircraft fax hydraulic brake system, causes BCU's whether normal direct
The landing safety of aircraft is influenceed, is that this BCU generally uses double redundancy design modes, to improve the functional reliability of brake system,
But thus produced problem is exactly that BCU indoor designs are more complicated, and the basic reliability of product is relatively low, false-alarm phenomenon occupies height not
Under, the airplane conditions of more than two brake machine wheel are particularly acute.Problem above makes current fax hydraulic brake system in use
Fault rate it is higher.
The content of the invention
To solve to be caused by existing airplane hydraulic pressure brake system is transmitted because of sensor with control signal using analog quantity
The problem of work failure rate of uniting is high, the present invention proposes a kind of distribution of the bus transfer of difference 422 based on strong antijamming capability
Formula fax hydraulic brake system.
A kind of distributed aircraft brake control system, is made up of the first wheel braking and the second wheel braking, wherein first
Wheel braking is made up of first brake instruction sensor component, the first wheel spin-up transducer component, the first water brake component.
Second wheel braking of distributed brake system is by the second brake instruction transducer component, the second wheel velocity pick-up
Device assembly, the second water brake component composition.
The 422 buses output of first brake instruction sensor component and the one 422 bus of the first water brake component are defeated
Enter connection, the 422 buses input of first brake instruction sensor component and the one 422 bus of the first water brake component are exported
Connection.The 422 buses output of first wheel spin-up transducer component connects with the 2nd 422 bus input of the first water brake component
Connect, the 422 buses input of the first wheel spin-up transducer component connects with the 2nd 422 bus output of the first water brake component
Connect.The hydraulic pressure output of first water brake component is connected with the wheel of aircraft first.
The 422 buses output of second brake instruction transducer component and the one 422 bus of the second water brake component are defeated
Enter connection, the 422 buses input of the second brake instruction transducer component and the one 422 bus of the second water brake component are exported
Connection.The 422 buses output of second wheel spin-up transducer component connects with the 2nd 422 bus input of the second water brake component
Connect, the 422 buses input of the second wheel spin-up transducer component connects with the 2nd 422 bus output of the second water brake component
Connect.The hydraulic pressure output of second water brake component is connected with the wheel of aircraft second.
First brake instruction sensor component is identical with the electrically composition of the second brake instruction transducer component, mainly by electricity
Source processing unit, linear movement pick-up unit, command signal conditioning unit, CPU processing units and 422 communication units are constituted.Group
In part power supply processing unit input be connected with aircraft 28V power supplys, power supply processing unit export respectively with linear movement pick-up unit,
Command signal conditioning unit, CPU processing units, the connection of 422 communication unit power inputs, the output of linear movement pick-up unit is with referring to
Signal condition unit input connection is made, the output of command signal conditioning unit is connected with the input of CPU processing units, CPU processing units
It is connected with 422 communication units.
First wheel spin-up transducer component is identical with the electrically composition of the second wheel spin-up transducer component, mainly by electricity
Source processing unit, wheel speed sensors unit, rate signal conditioning unit, CPU processing units and 422 communication units are constituted.Component
The input of middle power supply processing unit is connected with aircraft 28V power supplys, power supply processing unit export respectively with wheel speed sensors unit, speed
Signal condition unit, CPU processing units, the connection of 422 communication unit power inputs, wheel speed sensor unit output are believed with instruction
The input connection of number conditioning unit, the output of rate signal conditioning unit is inputted with CPU processing units to be connected, CPU processing units and 422
Communication unit is connected.
First water brake component is identical with the electric of the second water brake component, hydraulic pressure composition, and electric component is by power supply
Processing unit, the one 422 communication unit, the 2nd 422 communication unit, CPU processing units, servo valve control unit, magnetic valve control
Unit processed, brake pressure sensor unit composition, hydraulic package are made up of magnetic valve with servo valve.Power supply is handled in electric component
Unit input be connected with aircraft 28V power supplys, power supply processing unit respectively with CPU processing units, servo valve control unit, magnetic valve
Control unit, the one 422 communication unit, the 2nd 422 communication unit, the connection of brake pressure sensor unit power input, first
422 communication units, the 2nd 422 communication unit are connected with CPU processing units, brake pressure sensor unit and CPU processing units
Connect, CPU processing units are connected with servo valve control unit, CPU processing units are connected with control unit of electromagnetic valve, servo valve control
Unit processed is connected with servo valve coil, and control unit of electromagnetic valve is connected with electromagnetic valve coil.The oil-feed of magnetic valve in hydraulic package
It is connected with airplane hydraulic pressure source, magnetic valve brake is connected with the oil inlet of servo valve, servo valve brake and airplane wheel oil inlet phase
Even, servo valve is connected with electromagnetic valve oil return with airplane hydraulic pressure source oil return opening.
Brief description of the drawings
Fig. 1 distribution brake system theory diagrams
Fig. 2 instruction sensor component electrical principle block diagrams
Fig. 3 speed sensor assembly electrical principle block diagrams
Fig. 4 water brake assembly principle block diagrams
Embodiment
First wheel braking of distributed brake system is by first brake instruction sensor component, the first wheel velocity pick-up
Device assembly, the first water brake component composition.
Second wheel braking of distributed brake system is by the second brake instruction transducer component, the second wheel velocity pick-up
Device assembly, the second water brake component composition.
The 422 buses output of first brake instruction sensor component and the one 422 bus of the first water brake component are defeated
Enter connection, the 422 buses input of first brake instruction sensor component and the one 422 bus of the first water brake component are exported
Connection.The 422 buses output of first wheel spin-up transducer component connects with the 2nd 422 bus input of the first water brake component
Connect, the 422 buses input of the first wheel spin-up transducer component connects with the 2nd 422 bus output of the first water brake component
Connect.The hydraulic pressure output of first water brake component is connected with the wheel of aircraft first.
The 422 buses output of second brake instruction transducer component and the one 422 bus of the second water brake component are defeated
Enter connection, the 422 buses input of the second brake instruction transducer component and the one 422 bus of the second water brake component are exported
Connection.The 422 buses output of second wheel spin-up transducer component connects with the 2nd 422 bus input of the second water brake component
Connect, the 422 buses input of the second wheel spin-up transducer component connects with the 2nd 422 bus output of the second water brake component
Connect.The hydraulic pressure output of second water brake component is connected with the wheel of aircraft second.
First brake instruction sensor component is identical with the electrically composition of the second brake instruction transducer component, mainly by electricity
Source processing unit, linear movement pick-up unit, command signal conditioning unit, CPU processing units and 422 communication units are constituted.Group
In part power supply processing unit input be connected with aircraft 28V power supplys, power supply processing unit export respectively with linear movement pick-up unit,
Command signal conditioning unit, CPU processing units, the connection of 422 communication unit power inputs, the output of linear movement pick-up unit is with referring to
Signal condition unit input connection is made, the output of command signal conditioning unit is connected with the input of CPU processing units, CPU processing units
It is connected with 422 communication units.
First wheel spin-up transducer component is identical with the electrically composition of the second wheel spin-up transducer component, mainly by electricity
Source processing unit, wheel speed sensors unit, rate signal conditioning unit, CPU processing units and 422 communication units are constituted.Component
The input of middle power supply processing unit is connected with aircraft 28V power supplys, power supply processing unit export respectively with wheel speed sensors unit, speed
Signal condition unit, CPU processing units, the connection of 422 communication unit power inputs, wheel speed sensor unit output are believed with instruction
The input connection of number conditioning unit, the output of rate signal conditioning unit is inputted with CPU processing units to be connected, CPU processing units and 422
Communication unit is connected.
First water brake component is identical with the electric of the second water brake component, hydraulic pressure composition, and electric component is by power supply
Processing unit, the one 422 communication unit, the 2nd 422 communication unit, CPU processing units, servo valve control unit, magnetic valve control
Unit processed, brake pressure sensor unit composition, hydraulic package are made up of magnetic valve with servo valve.Power supply is handled in electric component
Unit input be connected with aircraft 28V power supplys, power supply processing unit respectively with CPU processing units, servo valve control unit, magnetic valve
Control unit, the one 422 communication unit, the 2nd 422 communication unit, the connection of brake pressure sensor unit power input, first
422 communication units, the 2nd 422 communication unit are connected with CPU processing units, brake pressure sensor unit and CPU processing units
Connect, CPU processing units are connected with servo valve control unit, CPU processing units are connected with control unit of electromagnetic valve, servo valve control
Unit processed is connected with servo valve coil, and control unit of electromagnetic valve is connected with electromagnetic valve coil.The oil-feed of magnetic valve in hydraulic package
It is connected with airplane hydraulic pressure source, magnetic valve brake is connected with the oil inlet of servo valve, servo valve brake and airplane wheel oil inlet phase
Even, servo valve is connected with electromagnetic valve oil return with airplane hydraulic pressure source oil return opening.
Claims (4)
1. a kind of distributed aircraft brake control system, it is characterised in that control system is by the first wheel braking and the second wheel
Brake composition, wherein the first wheel braking is by first brake instruction sensor component, the first wheel spin-up transducer component, first
Water brake component is constituted；Second wheel braking of distributed brake system is by the second brake instruction transducer component, the second machine
Wheel speed sensor cluster, the second water brake component composition；
The 422 buses output of first brake instruction sensor component connects with the one 422 bus input of the first water brake component
Connect, the 422 buses input of first brake instruction sensor component connects with the one 422 bus output of the first water brake component
Connect；The 422 buses output of first wheel spin-up transducer component connects with the 2nd 422 bus input of the first water brake component
Connect, the 422 buses input of the first wheel spin-up transducer component connects with the 2nd 422 bus output of the first water brake component
Connect；The hydraulic pressure output of first water brake component is connected with the wheel of aircraft first；
The 422 buses output of second brake instruction transducer component connects with the one 422 bus input of the second water brake component
Connect, the 422 buses input of the second brake instruction transducer component connects with the one 422 bus output of the second water brake component
Connect；The 422 buses output of second wheel spin-up transducer component connects with the 2nd 422 bus input of the second water brake component
Connect, the 422 buses input of the second wheel spin-up transducer component connects with the 2nd 422 bus output of the second water brake component
Connect；The hydraulic pressure output of second water brake component is connected with the wheel of aircraft second.
2. distribution aircraft brake control system as claimed in claim 1, it is characterised in that first brake instruction sensor group
Part is identical with the electrically composition of the second brake instruction transducer component, mainly by power supply processing unit, linear movement pick-up unit,
Command signal conditioning unit, CPU processing units and 422 communication units are constituted；The input of power supply processing unit and aircraft 28V in component
Power supply connect, power supply processing unit output respectively with linear movement pick-up unit, command signal conditioning unit, CPU processing units,
422 communication unit power inputs are connected, and the output of linear movement pick-up unit is connected with the input of command signal conditioning unit, instruction letter
The output of number conditioning unit is inputted with CPU processing units to be connected, and CPU processing units are connected with 422 communication units.
3. distribution aircraft brake control system as claimed in claim 1, it is characterised in that the first wheel spin-up transducer group
Part is identical with the electrically composition of the second wheel spin-up transducer component, mainly by power supply processing unit, wheel speed sensors unit, speed
Signal condition unit, CPU processing units and 422 communication units are spent to constitute；The input of power supply processing unit and aircraft 28V electricity in component
Source connect, power supply processing unit output respectively with wheel speed sensors unit, rate signal conditioning unit, CPU processing units, 422
Communication unit power input is connected, and the output of wheel speed sensor unit is connected with the input of command signal conditioning unit, rate signal
Conditioning unit is exported to be connected with the input of CPU processing units, and CPU processing units are connected with 422 communication units.
4. distribution aircraft brake control system as claimed in claim 1, it is characterised in that the first water brake component and the
The electric of two water brake components, hydraulic pressure composition are identical, and electric component is by power supply processing unit, the one 422 communication unit, second
422 communication units, CPU processing units, servo valve control unit, control unit of electromagnetic valve, brake pressure sensor unit composition,
Hydraulic package is made up of magnetic valve with servo valve；The input of power supply processing unit is connected with aircraft 28V power supplys in electric component, power supply
Processing unit respectively with CPU processing units, servo valve control unit, control unit of electromagnetic valve, the one 422 communication unit, second
422 communication units, brake pressure sensor unit power input connection, the one 422 communication unit, the 2nd 422 communication unit with
CPU processing units are connected, brake pressure sensor unit is connected with CPU processing units, CPU processing units and servo valve control list
Member connection, CPU processing units are connected with control unit of electromagnetic valve, and servo valve control unit is connected with servo valve coil, magnetic valve
Control unit is connected with electromagnetic valve coil；The oil-feed of magnetic valve is connected with airplane hydraulic pressure source in hydraulic package, magnetic valve brake with
The oil inlet of servo valve is connected, and servo valve brake is connected with airplane wheel oil inlet, servo valve and electromagnetic valve oil return and aircraft liquid
Potential source oil return opening is connected.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720147471.4U CN206579838U (en) | 2017-02-17 | 2017-02-17 | A kind of distributed aircraft brake control system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720147471.4U CN206579838U (en) | 2017-02-17 | 2017-02-17 | A kind of distributed aircraft brake control system |
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| CN206579838U true CN206579838U (en) | 2017-10-24 |
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| CN201720147471.4U Active CN206579838U (en) | 2017-02-17 | 2017-02-17 | A kind of distributed aircraft brake control system |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP4353588A1 (en) * | 2022-10-12 | 2024-04-17 | Airbus Operations Limited | An aircraft braking system |
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2017
- 2017-02-17 CN CN201720147471.4U patent/CN206579838U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP4353588A1 (en) * | 2022-10-12 | 2024-04-17 | Airbus Operations Limited | An aircraft braking system |
| GB2623334A (en) * | 2022-10-12 | 2024-04-17 | Airbus Operations Ltd | An aircraft braking system |
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