CN205644098U - Aircraft brake control system based on synthesize modularization avionics system - Google Patents
Aircraft brake control system based on synthesize modularization avionics system Download PDFInfo
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- CN205644098U CN205644098U CN201620198299.0U CN201620198299U CN205644098U CN 205644098 U CN205644098 U CN 205644098U CN 201620198299 U CN201620198299 U CN 201620198299U CN 205644098 U CN205644098 U CN 205644098U
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- interface unit
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- landing gear
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Abstract
The utility model relates to an aircraft brake control system based on synthesize modularization avionics system. This aircraft brake control system based on synthesize modularization avionics system includes: synthesize modularization avionics system bus, brake the control unit, brake the control unit are connected to and synthesize modularization avionics system bus, cockpit data interface unit, the unit connection of cockpit data interface is to synthesizing modularization avionics system bus, first main landing gear cabin data interface unit, the data interface unit connection of first main landing gear cabin is to synthesizing modularization avionics system bus, and wherein, first main landing gear cabin data interface unit integrated has the anti -skidding control logic module of brake. The utility model discloses an aircraft brake control system based on synthesize modularization avionics system can play following useful technological effect: it has solved the problem that present braking system can not combine the IMA platform, has reduced the equipment room cable and has arranged, has lightened system's weight, make full use of data bus, strengthened and the other system between the communication.
Description
Technical field
This utility model relates to aircraft brake control system based on comprehensively modularized avionics system (IMA),
Belong to aircraft system ture technology field.
Background technology
At present, the aircraft brake control system in civil aviaton applies is autonomous control system, belongs to biography
The system of system association type.
In the advanced technology of airplane design is applied, comprehensively modularized avionics system (Integrated
Modular Avionics, IMA) it is an important emerging technology, allow aircraft weight alleviate, subtract
The plurality of advantages such as few fuel oil energy consumption.
Comprehensively modularized avionics system is the real-time computer networks of airplane avionics system, this network
Contain multiple computing module and the application program of different level of security.Different application softwaries is all base
In same hardware module and operating system.Each system control unit not in use by independent control unit,
But all of sensor, actuator all with Remote-Data-Interface unit (the Remote Data of respective regions
Interface Unit, RDIU) it is connected, RDIU is led to central control computer by high speed data bus
Letter, all control softwares dwell in central control computer.
IMA, by sharing general calculating, communication and interface resource, improves resource utilization and realizes
Aircraft function, fundamentally reduces the quantity of Aerial Electronic Equipment.This not only allows aircraft weight alleviate, and reduces
Fuel oil energy consumption, cuts operating costs, and also allows the piece number of Aerial Electronic Equipment be greatly decreased, and reduces airline
Buy spare part and the cost of maintenance upgrading.And, comprehensive aircraft function system is the most, this loss of weight
The advantage of fall energy is the most obvious.
But, it is limited to signal transmission delay and can not meet the requirement of fast response time in brake control,
Brake system can not enter IMA platform as just a resident application.
Utility model content
A purpose of the present utility model is, it is provided that a kind of based on comprehensively modularized avionics system fly
Machine brake control system, which solving existing brake system can not reduce in conjunction with the problem of IMA platform
Equipment room cable is arranged, alleviates system weight, takes full advantage of data/address bus, enhances and it
Communication between his system.
Object above of the present utility model passes through a kind of aircraft brake based on comprehensively modularized avionics system
Control system realizes, and should aircraft brake control system based on comprehensively modularized avionics system include:
Comprehensively modularized avionics system bus；
Brake control unit, it is total that described brake control unit is connected to described comprehensively modularized avionics system
Line；
Driving cabin data interface unit, described driving cabin data interface unit is connected to described integration module
Change avionics system bus；
First main landing gear compartment data interface unit, described first main landing gear compartment data interface unit is even
It is connected to described comprehensively modularized avionics system bus, wherein, described first main landing gear compartment data-interface
Unit is integrated with brake anti-sliding control logic module.
According to technique scheme, aircraft brake based on comprehensively modularized avionics system of the present utility model
Control system can play following Advantageous Effects: which solving existing brake system can not be in conjunction with IMA
The problem of platform, decreases equipment room cable and arranges, alleviate system weight, take full advantage of data
Bus, enhances the communication between other system.
It is preferred that aircraft brake control system based on comprehensively modularized avionics system also includes second
Main landing gear compartment data interface unit, the second main landing gear compartment data interface unit is connected to integration module
Change avionics system bus.
It is preferred that driving cabin data interface unit is additionally coupled to brake pedal, self-actuating brake switchs,
Anti-skidding cancel switch and shutdown brake.
It is preferred that the first main landing gear compartment data interface unit is additionally coupled to wheel speed sensors, brake
Pressure transducer, brake control valve, stop valve and shutdown brake valve.
It is preferred that the second main landing gear compartment data interface unit be additionally coupled to accumulator pressure sensor,
Brake temperature sensor and tyre pressure sensor.
It is preferred that aircraft brake control system based on comprehensively modularized avionics system also includes standby
Brake control unit, to provide standby in the case of losing efficacy at brake control unit.
It is preferred that aircraft brake control system based on comprehensively modularized avionics system also includes standby
Driving cabin data interface unit, to provide standby in the case of losing efficacy in driving cabin data interface unit.
It is preferred that aircraft brake control system based on comprehensively modularized avionics system also includes standby
First main landing gear compartment data interface unit, with lost efficacy in the first main landing gear compartment data interface unit
In the case of provide standby.
It is preferred that aircraft brake control system based on comprehensively modularized avionics system also includes standby
Second main landing gear compartment data interface unit, with lost efficacy in the second main landing gear compartment data interface unit
In the case of provide standby.
Accompanying drawing explanation
Fig. 1 is that the aircraft brake based on comprehensively modularized avionics system of this utility model one embodiment controls
The composition schematic diagram of system.
Detailed description of the invention
Below in conjunction with specific embodiments and the drawings, the utility model is described in further detail, retouches at following
Elaborate more details in stating so that fully understanding this utility model, but this utility model is obvious
Can implement with multiple this alternate manner described that is different from, those skilled in the art can not disobey
Make similar popularization according to practical situations, deduce, the most not in the case of back of the body this utility model intension
Should be with the content constraints of this specific embodiment protection domain of the present utility model.
Fig. 1 is that the aircraft brake based on comprehensively modularized avionics system of this utility model one embodiment controls
The composition schematic diagram of system.As it is shown in figure 1, according to an embodiment of the present utility model, based on comprehensive mould
The aircraft brake control system of massing avionics system includes:
Comprehensively modularized avionics system bus；
Brake control unit, brake control unit is connected to comprehensively modularized avionics system bus；
Driving cabin data interface unit, driving cabin data interface unit is connected to comprehensively modularized avionics system
System bus；
First main landing gear compartment data interface unit, the first main landing gear compartment data interface unit is connected to
Comprehensively modularized avionics system bus, wherein, the first main landing gear compartment data interface unit is integrated with stops
Car anti-sliding control logic module.
So, aircraft brake control system solution based on comprehensively modularized avionics system of the present utility model
Existing brake system of having determined can not decrease equipment room cable and arrange in conjunction with the problem of IMA platform, subtract
Light system weight, takes full advantage of data/address bus, enhances the communication between other system.
It is to say, aircraft brake control system based on comprehensively modularized avionics system of the present utility model
With the data/address bus of IMA platform as transmission channel, retain independent brake calculating and processing unit (is stopped
Car control unit), it is achieved the control of airplane brake system and supervision.This aircraft brake control system structure
Frame, both make use of IMA platform, reduces cable and arranges, alleviates weight, maintain again independent brake
Control unit, solving the signal delay that produces completely into IMA system, to be unsatisfactory for brake system quick
The problem controlling to require.
It is preferred that the first main landing gear compartment data interface unit possesses the function that simple logic processes,
The functions such as fast closed-loop can be completed.Utilize this function of the first main landing gear compartment data interface unit,
The brake anti-sliding control logic module quickly processed can will be needed integrated wherein, in order to the time of meeting prolongs
Want late.
It is preferred that aircraft brake control system based on comprehensively modularized avionics system also includes second
Main landing gear compartment data interface unit, the second main landing gear compartment data interface unit is connected to integration module
Change avionics system bus.
It is preferred that driving cabin data interface unit is additionally coupled to brake pedal, self-actuating brake switchs,
Anti-skidding cancel switch and shutdown brake.
It is preferred that the first main landing gear compartment data interface unit is additionally coupled to wheel speed sensors, brake
Pressure transducer, brake control valve, stop valve and shutdown brake valve.
It is preferred that the second main landing gear compartment data interface unit be additionally coupled to accumulator pressure sensor,
Brake temperature sensor and tyre pressure sensor.
Certainly, those skilled in the art are appreciated that on the basis of this utility model disclosure
One main landing gear compartment data interface unit is not limited to only be only connected to wheel speed sensors, brake pressure passes
Sensor, brake control valve, stop valve and shutdown brake valve, be also connected to other sensor；Second
Main landing gear compartment data interface unit is also not limited to only be only connected to accumulator pressure sensor, brake
Temperature sensor and tyre pressure sensor, be also connected to other sensor.Above-mentioned modification falls into this equally
Within the protection domain of utility model.
It is preferred that aircraft brake control system based on comprehensively modularized avionics system also includes standby
Brake control unit, to provide standby in the case of losing efficacy at brake control unit.
It is preferred that aircraft brake control system based on comprehensively modularized avionics system also includes standby
Driving cabin data interface unit, to provide standby in the case of losing efficacy in driving cabin data interface unit.
It is preferred that aircraft brake control system based on comprehensively modularized avionics system also includes standby
First main landing gear compartment data interface unit, with lost efficacy in the first main landing gear compartment data interface unit
In the case of provide standby.
It is preferred that aircraft brake control system based on comprehensively modularized avionics system also includes standby
Second main landing gear compartment data interface unit, with lost efficacy in the second main landing gear compartment data interface unit
In the case of provide standby.
Above detailed description of the invention of the present utility model is described, but those skilled in the art will
It will be appreciated that above-mentioned detailed description of the invention is not intended that restriction of the present utility model, people in the art
Member can carry out multiple amendment on the basis of disclosure above, and without departing from model of the present utility model
Enclose.
Claims (9)
1. an aircraft brake control system based on comprehensively modularized avionics system, it is characterised in that
Including:
Comprehensively modularized avionics system bus；
Brake control unit, it is total that described brake control unit is connected to described comprehensively modularized avionics system
Line；
Driving cabin data interface unit, described driving cabin data interface unit is connected to described integration module
Change avionics system bus；
First main landing gear compartment data interface unit, described first main landing gear compartment data interface unit is even
It is connected to described comprehensively modularized avionics system bus, wherein, described first main landing gear compartment data-interface
Unit is integrated with brake anti-sliding control logic module.
2. aircraft brake based on comprehensively modularized avionics system as claimed in claim 1 controls system
System, it is characterised in that also include that the second main landing gear compartment data interface unit, described second master are risen and fallen
Frame cabin data interface unit is connected to described comprehensively modularized avionics system bus.
3. aircraft brake based on comprehensively modularized avionics system as claimed in claim 1 controls system
System, it is characterised in that described driving cabin data interface unit is additionally coupled to brake pedal, self-actuating brake
Switch, anti-skidding cancel switch and shutdown brake.
4. aircraft brake based on comprehensively modularized avionics system as claimed in claim 1 controls system
System, it is characterised in that described first main landing gear compartment data interface unit be additionally coupled to wheel speed sensors,
Brake pressure sensor, brake control valve, stop valve and shutdown brake valve.
5. aircraft brake based on comprehensively modularized avionics system as claimed in claim 2 controls system
System, it is characterised in that described second main landing gear compartment data interface unit is additionally coupled to accumulator pressure
Sensor, brake temperature sensor and tyre pressure sensor.
6. aircraft brake based on comprehensively modularized avionics system as claimed in claim 1 controls system
System, it is characterised in that also include standby brake control unit, to lose efficacy at described brake control unit
In the case of provide standby.
7. aircraft brake based on comprehensively modularized avionics system as claimed in claim 1 controls system
System, it is characterised in that also include standby driving cabin data interface unit, with in described driving cabin data
Interface unit provided standby in the case of losing efficacy.
8. aircraft brake based on comprehensively modularized avionics system as claimed in claim 1 controls system
System, it is characterised in that also include standby first main landing gear compartment data interface unit, with described the
One main landing gear compartment data interface unit provided standby in the case of losing efficacy.
9. aircraft brake based on comprehensively modularized avionics system as claimed in claim 2 controls system
System, it is characterised in that also include standby second main landing gear compartment data interface unit, with described the
Two main landing gear compartment data interface unit provided standby in the case of losing efficacy.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620198299.0U CN205644098U (en) | 2016-03-15 | 2016-03-15 | Aircraft brake control system based on synthesize modularization avionics system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620198299.0U CN205644098U (en) | 2016-03-15 | 2016-03-15 | Aircraft brake control system based on synthesize modularization avionics system |
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| Publication Number | Publication Date |
|---|---|
| CN205644098U true CN205644098U (en) | 2016-10-12 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201620198299.0U Active CN205644098U (en) | 2016-03-15 | 2016-03-15 | Aircraft brake control system based on synthesize modularization avionics system |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107972878A (en) * | 2017-11-20 | 2018-05-01 | 中电科航空电子有限公司 | A kind of cockpit touch-screen tuning control system |
-
2016
- 2016-03-15 CN CN201620198299.0U patent/CN205644098U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107972878A (en) * | 2017-11-20 | 2018-05-01 | 中电科航空电子有限公司 | A kind of cockpit touch-screen tuning control system |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20190828 Address after: 201210 Zhang Yang Road, Shanghai, Pudong New Area, No. 25 Co-patentee after: Shanghai Aircraft Design Research Institute Co., Ltd. Patentee after: Commercial Aircraft Corporation of China, Ltd. Address before: 201210 Zhang Yang Road, Shanghai, Pudong New Area, No. 25 Co-patentee before: Commercial Aircraft Corporation of China, Ltd. Shanghai Aircraft Design Research Institute Patentee before: Commercial Aircraft Corporation of China, Ltd. |
|
| TR01 | Transfer of patent right |