CN203111498U - Directly driving type aircraft FBW (fly-by-wire) braking system - Google Patents
Directly driving type aircraft FBW (fly-by-wire) braking system Download PDFInfo
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- CN203111498U CN203111498U CN 201320049328 CN201320049328U CN203111498U CN 203111498 U CN203111498 U CN 203111498U CN 201320049328 CN201320049328 CN 201320049328 CN 201320049328 U CN201320049328 U CN 201320049328U CN 203111498 U CN203111498 U CN 203111498U
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- brake
- brake control
- valve
- sensor
- pressure
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Abstract
The utility model relates to a directly driving type aircraft FBW braking system. A brake instruction sensor (1) converts driver pedal input into an electrical signal and inputs the signal into a brake control box (2), the brake control box (2) controls unlocking and locking of an electromagnetic hydraulic lock (3) according to the fact that the brake instruction sensor (1) and an airplane wheel velocity sensor (6) measure the rotation speed signal of the airplane wheel, and controls the input of a brake control valve (4), and pressure sensor (5) measures the brake pressure of the system and feeds a measurement signal back to the brake control box (2). The directly driving type FBW braking system provided by the utility model has the advantages that on the basis of the traditional FBW braking system, a directly driving pressure control valve is adopted to serve as the brake control valve, so that the directly driving valve can be used, hydraulic regulation is not needed to perform on the static characteristic of the valve, the control accuracy is good, and the influence of the temperature and pressure change is small.
Description
Technical field
The utility model relates to the aircraft brake technical field, particularly relates to a kind of direct drive type airplane fax brake system.
Background technology
The aircraft brake control system is as important airborne equipment, can brake system normal operation will have a strong impact on aircraft safety, at present, aircraft fax brake system, brake control valve adopts conventional nozzle baffle type electro-hydraulic pressure servovalve mostly, there is the static response dead band in it, temperature and pressure changes generation zero drift, shortcomings such as spillage is big, make in brake process because the system leak amount is big, cause the brake system inefficiency, can not use the storage type energy resource system to carry out the fax brake, because there is not the spool position feedback in system, causes the brake system control accuracy lower.
Summary of the invention
The objective of the invention is: a kind of direct drive type airplane fax brake system is provided, improves the control accuracy of fax brake system, reduced the oil liquid leakage amount of system works, improved the work efficiency of system.
Technical scheme of the present invention is: a kind of direct drive type airplane fax brake system comprises brake instruction sensor 1, brake control capsule 2, electromagnetic hydraulic pressure lock 3, brake control valve 4, pressure sensor 5 and wheel spin-up transducer 6; Wherein, described brake instruction sensor 1 is converted into electric signal with the input of chaufeur pedal and is input in the brake control capsule 2, brake control capsule 2 is controlled unblanking and locking of electromagnetic hydraulic pressure lock 3 according to the tach signal of brake instruction sensor 1 and wheel spin-up transducer 6 measurement wheels, and control brake control valve 4 input sizes; The brake pressure of pressure sensor 5 measuring systems and with measurement signal feed back to the brake control capsule 2.
Advantage and beneficial effect that the present invention has are: the utility model can improve the control accuracy of fax brake system, has reduced the oil liquid leakage amount of system works, has improved the work efficiency of system.The advantage of this novel direct drive-type fax brake system is on the basis of traditional fax brake system, adopt direct driving pressure control cock as brake control valve, can utilize direct driving valve to need not the static response of valve is carried out the hydraulic pressure adjustment like this, control accuracy is good, the temperature and pressure variable effect is little, spillage is little, has characteristics such as position feedback, improves the control accuracy of fax brake system, reduce the oil liquid leakage amount of system works, improved the work efficiency of system
Description of drawings
Fig. 1 is the utility model structural representation.
The specific embodiment
A kind of direct drive type airplane fax brake system comprises brake instruction sensor 1, brake control capsule 2, electromagnetic hydraulic pressure lock 3, brake control valve 4, pressure sensor 5 and wheel spin-up transducer 6; Wherein, described brake instruction sensor 1 is converted into electric signal with the input of chaufeur pedal and is input in the brake control capsule 2, brake control capsule 2 is controlled unblanking and locking of electromagnetic hydraulic pressure lock 3 according to the tach signal of brake instruction sensor 1 and wheel spin-up transducer 6 measurement wheels, and control brake control valve 4 input sizes; The brake pressure of pressure sensor 5 measuring systems and with measurement signal feed back to the brake control capsule 2.
Concrete implementation process is as follows:
Brake instruction sensor 1 is installed under the driving compartment brake pedal, brake instruction sensor 1 and brake control capsule 2 are by being electrically connected, brake control capsule 2 and electromagnetic hydraulic pressure lock 3 and brake control valve 4 are by being electrically connected, the oil-feed of brake system enters electromagnetic hydraulic pressure lock 3, the outlet of electromagnetic hydraulic pressure lock 3 is connected with brake control valve 4, the outlet of brake control valve 4 is connected with the brake disc of brake wheel, brake control valve 4 and brake disc between hydraulic tubing on setting pressure sensor 5, the electric signal of pressure sensor 5 is given brake control capsule 2, wheel shaft at the brake wheel is installed wheel spin-up transducer 6, and the electric signal of wheel spin-up transducer 6 is given brake control capsule 2.
The chaufeur pin pedal that touches on the brake in brake process, the brake instruction sensor of installing on the brake pedal 1 is sent to brake control capsule 2 with the brake command signal of chaufeur, brake control capsule 2 is according to the switching of brake command signal control electromagnetic hydraulic pressure lock 3 and the size of brake control valve 4 delivery pressures, brake control capsule 2 receives wheel spin-up transducer 6 and judges whether the brake wheel is in slipping state under the current state, thus the size of control brake control valve 4 delivery pressures; Pressure sensor 5 feeds back to brake control capsule 2 with the brake pressure on the wheel, brake control valve 4 with its valve body built-in motor signal feedback to the control capsule 2 that brakes, thereby the control accuracy of brake control capsule 2 pairs of brake control valves 4 is improved.The advantage of native system is on the basis of traditional fax brake system, adopt direct driving pressure control cock as brake control valve, can utilize direct driving valve to need not the static response of valve is carried out the hydraulic pressure adjustment like this, control accuracy is good, the temperature and pressure variable effect is little, spillage is little, has characteristics such as position feedback, improves the control accuracy of fax brake system, reduce the oil liquid leakage amount of system works, improved the work efficiency of system.
Claims (2)
1. direct drive type airplane fax brake system, it is characterized in that native system comprises brake instruction sensor (1), brake control capsule (2), electromagnetic hydraulic pressure lock (3), brake control valve (4), pressure sensor (5) and wheel spin-up transducer (6); Wherein, described brake instruction sensor (1) is converted into electric signal with the input of chaufeur pedal and is input in the brake control capsule (2), brake control capsule (2) is controlled unblanking and locking of electromagnetic hydraulic pressure lock (3) according to the tach signal of brake instruction sensor (1) and wheel spin-up transducer (6) measurement wheel, and control brake control valve (4) input size; The brake pressure of pressure sensor (5) measuring system and with measurement signal feed back to the brake control capsule (2).
2. a kind of direct drive type airplane fax brake system as claimed in claim 1, it is characterized in that, described brake control valve (4) adopts direct drive-type pressure servo valve, be provided with an energy in its valve body and give brake control capsule (2) with the signal feedback of electrical motor in the direct driving valve, to judge brake control valve (4) spool position bit position sensor.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201320049328 CN203111498U (en) | 2013-01-29 | 2013-01-29 | Directly driving type aircraft FBW (fly-by-wire) braking system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201320049328 CN203111498U (en) | 2013-01-29 | 2013-01-29 | Directly driving type aircraft FBW (fly-by-wire) braking system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203111498U true CN203111498U (en) | 2013-08-07 |
Family
ID=48891868
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201320049328 Expired - Lifetime CN203111498U (en) | 2013-01-29 | 2013-01-29 | Directly driving type aircraft FBW (fly-by-wire) braking system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203111498U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103821846A (en) * | 2014-03-04 | 2014-05-28 | 北京航空航天大学 | Small aircraft braking system |
| CN104890863A (en) * | 2015-06-03 | 2015-09-09 | 西安航空制动科技有限公司 | Brake valve with non-decompression direct supply capacity |
| CN109533300A (en) * | 2018-11-19 | 2019-03-29 | 西安航空制动科技有限公司 | Improve the aircraft brake-by-wire system and control method of take-off line braking ability |
-
2013
- 2013-01-29 CN CN 201320049328 patent/CN203111498U/en not_active Expired - Lifetime
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103821846A (en) * | 2014-03-04 | 2014-05-28 | 北京航空航天大学 | Small aircraft braking system |
| CN103821846B (en) * | 2014-03-04 | 2015-12-30 | 北京航空航天大学 | A kind of braking system of baby plane |
| CN104890863A (en) * | 2015-06-03 | 2015-09-09 | 西安航空制动科技有限公司 | Brake valve with non-decompression direct supply capacity |
| CN109533300A (en) * | 2018-11-19 | 2019-03-29 | 西安航空制动科技有限公司 | Improve the aircraft brake-by-wire system and control method of take-off line braking ability |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CX01 | Expiry of patent term |
Granted publication date: 20130807 |
|
| CX01 | Expiry of patent term |