CN205632456U - Aircraft brake control system - Google Patents
Aircraft brake control system Download PDFInfo
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- CN205632456U CN205632456U CN201620512514.XU CN201620512514U CN205632456U CN 205632456 U CN205632456 U CN 205632456U CN 201620512514 U CN201620512514 U CN 201620512514U CN 205632456 U CN205632456 U CN 205632456U
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- brake
- aircraft
- braking system
- brake control
- wheel
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Abstract
The utility model discloses an aircraft brake control system relates to aircraft brake technical field. Aircraft brake control system contains automatic braking system and mechanical control braking system, automatic braking system uses braking system as the owner of aircraft, mechanical control braking system is as the supplementary braking system of aircraft. The utility model has the advantages of: aircraft brake control system contains automatic braking system and mechanical control braking system, and automatic braking system uses braking system as the owner of aircraft, and brake response time is than very fast, and the operation burden that can reduce the driver, mechanical control braking system once automatic braking system breaks down, can adopt mechanical control braking system as supplementary braking system, adopt two remaining braking system to improve aircraft braking system's reliability. Additionally, self -actuating brake control system still has antiskid brake control function.
Description
Technical field
This utility model relates to aircraft brake technical field, is specifically related to a kind of aircraft brake control system.
Background technology
Aircraft brake control system, as important airborne equipment, has relatively independent function, to aircraft
Take off, safe landing plays an important role.Foot is generally used to handle or hands during existing aircraft brake
Handling, and taking off or in landing mission, driver generally will be manually placed on engine power control arm,
On foot operating mechanism in addition to brake pedal, also pedals so that driver is logical in brake process
Often handle or error operations evening, add the manipulation burden of driver, reduce aircraft safety, particularly
During taking off sliding race, when occurring relatively major break down to need termination to take off due to other system, often
Can not apply brake within the shortest time due to the flurried of driver, miss apply to brake optimal time
Machine, and reduce aircraft utilization safety, aircraft autobrake system then can overcome disadvantages mentioned above, but self-actuating brake
Due in the course of the work, use automatic control mode completely, particularly, the control of system be by electronics,
The modes such as software realize, and accordingly, with respect to traditional mechanical handling brake system, then the operation of system can
The highest by property.Although traditional mechanical manoeuvring system is reliable, but it does not the most possess antiskid function, makes
Its handling characteristic is bad, the shortcoming of the quick-fried tire that easily occurs stopping.
Utility model content
The purpose of this utility model is to provide a kind of aircraft brake control system, to solve or at least to alleviate background
The problem at least one place in the presence of technology.
The technical solution of the utility model is: provides a kind of aircraft brake control system, comprises self-actuating brake system
System and mechanical handling brake system；Described autobrake system is as the primary brake system of aircraft, described machine
The brake system auxiliary brake system as aircraft handled by tool.
Preferably, described autobrake system comprises antiskid brake controller, antiskid brake control valve, wheel
Velocity sensor；Described antiskid brake controller is electrically connected with described antiskid brake control valve, described anti-skidding
Brake control valve is provided power by hydraulic means, is used for braking airplane wheel；Described wheel spin-up transducer is pacified
Being contained on wheel brake, described wheel spin-up transducer is electrically connected with described antiskid brake controller.
Preferably, described mechanical handling brake system comprises water brake valve, and described water brake valve is by hydraulic pressure
Device provides power, is used for braking airplane wheel.
Preferably, in described autobrake system, each airplane wheel is provided with an antiskid brake control
Valve processed, multiple described antiskid brake control valves are controlled by an antiskid brake controller.
Preferably, described autobrake system also comprises switch, described switch and described antiskid brake controller
Electrical connection.
The utility model has the advantage of: aircraft brake control system of the present utility model comprises self-actuating brake system
System and mechanical handling brake system, autobrake system is as the primary brake system of aircraft, during brake response
Between than very fast, and the operation burden of driver can be reduced；Mechanical handling brake system is as auxiliary brake system
System, once autobrake system breaks down, can use mechanical handling brake system；Use double redundant brake
System improves the reliability of airplane brake system.
Accompanying drawing explanation
Fig. 1 is the schematic diagram of the aircraft brake control system of this utility model one embodiment.
Wherein, 1-switchs, 2-antiskid brake controller, 3-antiskid brake control valve, 4-wheel velocity pick-up
Device, 5-water brake valve, 6-the first pump, 7-the second pump, 81-the first wheel, 82-the second wheel, 83-
3rd wheel, 84-the 4th wheel.
Detailed description of the invention
Clearer, below in conjunction with this reality for the purpose making this utility model implement, technical scheme and advantage
With the accompanying drawing in new embodiment, the technical scheme in this utility model embodiment is carried out more detailed retouching
State.In the accompanying drawings, the most same or similar label represents same or similar element or has identical
Or the element of similar functions.Described embodiment is a part of embodiment of this utility model rather than all
Embodiment.The embodiment described below with reference to accompanying drawing is exemplary, it is intended to be used for explaining this practicality
Novel, and it is not intended that to restriction of the present utility model.Based on the embodiment in this utility model, ability
The every other embodiment that territory those of ordinary skill is obtained under not making creative work premise, all belongs to
Scope in this utility model protection.Below in conjunction with the accompanying drawings embodiment of the present utility model is carried out specifically
Bright.
In description of the present utility model, it is to be understood that term " " center ", " longitudinally ", " laterally ",
"front", "rear", "left", "right", " vertically ", " level ", " top ", " end " " interior ", " outward " etc. refer to
The orientation shown or position relationship, for based on orientation shown in the drawings or position relationship, are for only for ease of description originally
Utility model and simplification describe rather than indicate or imply that the device of indication or element must have specific side
Position, with specific azimuth configuration and operation, therefore it is not intended that restriction to this utility model protection domain.
As it is shown in figure 1, a kind of aircraft brake control system, comprise autobrake system and mechanical handling brake
System.Autobrake system is as the primary brake system of aircraft, and brake response time ratio is very fast and permissible
Reduce the operation burden of driver.Mechanical handling brake system is as the auxiliary brake system of aircraft.Use double
Brake system with redundance improves the reliability of airplane brake system.Wherein, autobrake system is by the first pump 6
Water brake power is provided；Mechanical handling brake system is provided water brake power by the second pump 7.
In the present embodiment, autobrake system comprise antiskid brake controller 2, antiskid brake control valve 3,
Wheel spin-up transducer 4；Antiskid brake controller 2 is electrically connected with antiskid brake control valve 3, anti-skidding stops
Car control valve 3 is provided power by hydraulic means, is used for braking airplane wheel；Wheel spin-up transducer 4 is installed
On wheel brake, wheel spin-up transducer 4 is electrically connected with antiskid brake controller 2.In this reality
Executing in example, antiskid brake control valve 3 is provided power by the first pump 6.
In the present embodiment, mechanical handling brake system comprises water brake valve 5, and water brake valve 5 is by liquid
Pressure device provides power, is used for braking airplane wheel.In the present embodiment, water brake valve 5 is by the second pump 7
Power is provided.
In the autobrake system of the present embodiment, each airplane wheel is provided with an antiskid brake control
Valve 3 processed, multiple antiskid brake control valves 3 are controlled by an antiskid brake controller 2.
In the present embodiment, autobrake system also comprises switch 1, switch 1 and antiskid brake controller 2
Electrical connection, for controlling joint and the connection of autobrake system.
Concrete, work process of the present utility model is as follows: when the tire pressure of all wheels is normal, institute
There is antiskid brake control valve 4 to work simultaneously and export identical brake weight；When having the pressure of tire less than normal
During pressure, the brake weight of antiskid brake control valve 4 output that the tire of subnormal pressure is corresponding reduces, anti-
Only wheel locking, meanwhile, with plane nose to the line of tail as symmetrical centre, the corresponding tire of opposite side
Antiskid brake control valve 4 export identical brake weight, to prevent aircraft side sliding.
As shown in Figure 1, concrete, self-actuating brake control system preferentially selected by aircraft, in the present embodiment
Wheel comprises first wheel the 81, second wheel the 82, the 3rd wheel the 83, the 4th wheel 84.Normal at aircraft
Under braking state, when operator pedal carries out skidding to aircraft, antiskid brake controller 2
Brake pressure command signal, all antiskid brake controls are sent to the antiskid brake control valve 3 that all wheels are corresponding
Valve 3 processed exports the brake weight of formed objects under the driving of hydraulic pump simultaneously, it is achieved the antiskid brake of aircraft.
When system wheel tire pressure is less than established standards value, such as, as it is shown in figure 1, work as the first wheel
When the tire pressure of 81 all shows normal less than established standards value, the tire pressure value of remaining wheel, drive
Member's operation pedal is when being braked aircraft, and antiskid brake controller 2 is to antiskid brake corresponding to all wheels
Control valve 3 sends brake pressure command signal, and all antiskid brake control valves 3 are under the driving of the first pump 6
Export brake weight simultaneously.But owing to the tire pressure of the first wheel 81 is less than standard value, its stress again smaller than
Remaining wheel, now the brake weight of antiskid brake control valve 3 output of the first wheel 81 correspondence is less, with
Time, with plane nose to the line of tail as symmetrical centre, with the 4th wheel 84 of the first wheel 81 symmetry
The brake weight of antiskid brake control valve 3 output the least, stress when braking with balance airplane, prevent from flying
Machine occurs brake to break away.
In like manner, if the pressure of the second wheel 82 is less than established standards value, when braking the most accordingly, second
The brake weight of wheel 82 and the 3rd wheel 83 is less than the brake weight of other wheel, thus balance airplane brakes
Time stress, prevent aircraft occur brake break away.
If the first wheel 81 in the case of wheel tire burst, such as, as shown in Figure 1
Tire burst, tire pressure is zero, and now the antiskid brake control valve 3 of the first wheel 81 correspondence is not
Output brake pressure, meanwhile, with plane nose to the line of tail as symmetrical centre, with the first wheel 81
The antiskid brake control valve 3 of the 4th symmetrical wheel 84 does not the most export brake pressure, brakes with balance airplane
Time stress, prevent aircraft occur brake break away.
In like manner, if the tire burst of the second wheel 82, when braking the most accordingly, the second wheel 82
Brake weight is not the most exported with the corresponding antiskid brake control valve 3 of the 3rd wheel 83；Thus balance airplane brake
Time stress, prevent aircraft occur brake break away.
When above autobrake system controls aircraft brake, no matter under which kind of situation, if self-actuating brake
System malfunctions, then have operator switch 1, close autobrake system, meanwhile, driver's hands
Dynamic manipulation mechanical handling brake system, the second pump 7 provides power to water brake valve 5, enters all wheels
Row braking.
Last it is noted that above example is only in order to illustrate the technical solution of the utility model, rather than
It is limited.Although this utility model being described in detail with reference to previous embodiment, this area general
Lead to and skilled artisans appreciate that the technical scheme described in foregoing embodiments still can be repaiied by it
Change, or wherein portion of techniques feature is carried out equivalent；And these amendments or replacement, do not make phase
The essence answering technical scheme departs from the spirit and scope of this utility model each embodiment technical scheme.
Claims (5)
1. an aircraft brake control system, it is characterised in that: comprise autobrake system and mechanical handling
Brake system；Described autobrake system as the primary brake system of aircraft, the brake of described mechanical handling is
System is as the auxiliary brake system of aircraft.
2. aircraft brake control system as claimed in claim 1, it is characterised in that: described self-actuating brake
System comprises antiskid brake controller (2), antiskid brake control valve (3), wheel spin-up transducer (4)；
Described antiskid brake controller (2) and described antiskid brake control valve (3) are electrically connected, and described anti-skidding stop
Car control valve (3) is provided power by hydraulic means, is used for braking airplane wheel；Described wheel velocity pick-up
Device (4) is arranged on wheel brake, described wheel spin-up transducer (4) and described antiskid brake control
Device processed (2) is electrically connected.
3. aircraft brake control system as claimed in claim 1, it is characterised in that: described mechanical handling
Brake system comprises water brake valve (5), and described water brake valve (5) is provided power by hydraulic means,
For braking airplane wheel.
4. aircraft brake control system as claimed in claim 2, it is characterised in that: described self-actuating brake
In system, each airplane wheel is provided with an antiskid brake control valve (3), multiple described anti-skidding
Brake control valve (3) is controlled by an antiskid brake controller (2).
5. aircraft brake control system as claimed in claim 4, it is characterised in that: described self-actuating brake
System also comprises switch (1), and described switch (1) is electrically connected with described antiskid brake controller (2).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620512514.XU CN205632456U (en) | 2016-05-31 | 2016-05-31 | Aircraft brake control system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620512514.XU CN205632456U (en) | 2016-05-31 | 2016-05-31 | Aircraft brake control system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205632456U true CN205632456U (en) | 2016-10-12 |
Family
ID=57050921
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201620512514.XU Active CN205632456U (en) | 2016-05-31 | 2016-05-31 | Aircraft brake control system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205632456U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108099874A (en) * | 2017-12-06 | 2018-06-01 | 西安航空制动科技有限公司 | The aircraft autobrake system directly controlled by self-actuating brake switch |
| 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 |
-
2016
- 2016-05-31 CN CN201620512514.XU patent/CN205632456U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108099874A (en) * | 2017-12-06 | 2018-06-01 | 西安航空制动科技有限公司 | The aircraft autobrake system directly controlled by self-actuating brake switch |
| CN108099874B (en) * | 2017-12-06 | 2020-04-28 | 西安航空制动科技有限公司 | Airplane automatic braking system directly controlled by automatic brake switch |
| 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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|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant |