CN203111499U - Aeroplane failure-safety braking control system - Google Patents
Aeroplane failure-safety braking control system Download PDFInfo
- Publication number
- CN203111499U CN203111499U CN 201320049409 CN201320049409U CN203111499U CN 203111499 U CN203111499 U CN 203111499U CN 201320049409 CN201320049409 CN 201320049409 CN 201320049409 U CN201320049409 U CN 201320049409U CN 203111499 U CN203111499 U CN 203111499U
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- electromagnetic hydraulic
- hydraulic pressure
- braking
- braking control
- pressure lock
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Abstract
The utility model relates to an aeroplane failure-safety braking control system comprising a braking controller, electromagnetic hydraulic locks, a shuttle-shaped valve and braking control valves. The aeroplane failure-safety braking control system adopts a single hydraulic source to supply pressure, the two electromagnetic hydraulic locks are connected to positions behind the hydraulic source; two inlets of the shuttle-shaped valve are connected to positions in back of the two electromagnetic hydraulic locks; the working port of the shuttle-shaped valve is connected with the two braking control valves; one aeroplane wheel braking device is connected to a position in back of each braking control valve; when any one electromagnetic hydraulic lock is closed, the hydraulic source can reach the shuttle-shaped valve via the other electromagnetic hydraulic lock and then reaches the braking control valves; braking pressure acts on the a braked wheel via the regulation of the braking control valves; when the valve cores of the braking control valves are in a state of clamping stagnation, the electromagnetic hydraulic locks are in closed positions, oil fed to the braking control valves can return an oil tank via the electromagnetic hydraulic locks, and a braking system is in a state of demulcent braking, as a result, tyre burst of an aeroplane, which is caused during the braking, landing and skidding, can be prevented.
Description
Technical field
The utility model relates to the airplane brake system technical field, particularly relates to a kind of airplane fault-safety shut-down control 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, the aircraft brake control system, adopt a cover hydraulic power source voltage supply mostly, at the left and right sides wheel brake control valve is set respectively, at the control cock front end electromagnetic hydraulic pressure lock is set respectively, in case the spool clamping stagnation appears in brake control valve, the electromagnetic hydraulic pressure lock can not be got back to fuel tank with the brake system oil-feed, system will belt brake lands and drags tire, aircraft the danger of stopping quick-fried tire can occur, has a strong impact on aircraft utilization safety.
Utility model patent " airplane brake system hydraulic pressure remaining control setup ", numbering ZL200620118140.X, the electromagnetic hydraulic pressure lock adopts the 2/2-way mode, in case clamping stagnation appears in pressure servo valve, system's brake pressure can't discharge, and can cause the belt brake landing and drag tire.
Summary of the invention
The objective of the invention is: a kind of airplane fault-safety shut-down control system is provided, in the time of guaranteeing that the clamping stagnation fault appears in the brake control valve spool, makes brake system be in the pine state of stopping, in case the locking system belt brake lands and drag tire to cause the aircraft quick-fried tire of stopping.
This utility model can guarantee that system is in a safe condition when spool clamping stagnation fault appears in brake control valve, improves the landing safety of aircraft.
Technical scheme of the present invention is: a kind of airplane fault-safety shut-down control system, comprise brake controller 1, the first electromagnetic hydraulic pressure lock 21, second electromagnetic hydraulic pressure lock 22, fusiformis valve 3, left side brake control valve 41, right brake control valve 42, left and right sides wheel brake 51,52; Wherein, first electromagnetic hydraulic pressure lock, 21, second electromagnetic hydraulic pressure lock 22 is electrically connected with brake controller 1 respectively, 22 outlets are connected with two entrances of fusiformis valve 3 respectively 21 outlets of first electromagnetic hydraulic pressure lock with second electromagnetic hydraulic pressure lock, the working hole of fusiformis valve 3 links to each other with the import of left brake control valve 41 and right brake control valve 42, the working hole of left side brake control valve 41 links to each other with left wheel brake 51, and the working hole of right brake control valve 42 links to each other with right wheel brake 52.
Described first electromagnetic hydraulic pressure lock, 21, second electromagnetic hydraulic pressure lock 22 adopts the two-bit triplet structure, and working hole communicates with oil return under the closed condition, and working hole communicates with oil-feed under the on-state.
During normal braking, the system liquid potential source arrives fusiformis valve 3 by first electromagnetic hydraulic pressure lock, 21 and second electromagnetic hydraulic pressure lock 22, and then enters left and right sides wheel brake 51 and 52 by left brake control valve 41 and right brake control valve 42, carries out aircraft brake.Behind arbitrary et out of order in first electromagnetic hydraulic pressure lock, 21 and second electromagnetic hydraulic pressure lock 22, the system liquid potential source enters fusiformis valve 3 by normal electromagnetic hydraulic pressure lock and carries out normal braking then.
When the spool clamping stagnation appears in arbitrary brake control valve; the electromagnetic hydraulic pressure lock is in the closed position; the oil-feed of brake control valve can be got back to fuel tank by the electromagnetic hydraulic pressure lock; brake system is in the pine state of stopping; can anti-locking system belt brake land and drag tire to cause the aircraft quick-fried tire of stopping, play the fail safe protective effect.
Advantage and beneficial effect that the present invention has are: when the utility model can guarantee that the clamping stagnation fault appears in the brake control valve spool, make brake system be in the pine state of stopping, in case the locking system belt brake lands and drag tire to cause the aircraft quick-fried tire of stopping.Improved the landing safety of aircraft.
Description of drawings
Fig. 1 is the utility model structural representation.
The specific embodiment
Below in conjunction with Figure of description the utility model is specified.
A kind of airplane fault-safety shut-down control system comprises brake controller 1, the first electromagnetic hydraulic pressure lock 21, second electromagnetic hydraulic pressure lock 22, fusiformis valve 3, left brake control valve 41, right brake control valve 42, left and right sides wheel brake 51,52; First electromagnetic hydraulic pressure lock, 21, second electromagnetic hydraulic pressure lock 22 is electrically connected with brake controller 1 respectively, 22 outlets are connected with two entrances of fusiformis valve 3 respectively 21 outlets of first electromagnetic hydraulic pressure lock with second electromagnetic hydraulic pressure lock, the working hole of fusiformis valve 3 links to each other with the import of left brake control valve 41 and right brake control valve 42, the working hole of left side brake control valve 41 links to each other with left wheel brake 51, and the working hole of right brake control valve 42 links to each other with right wheel brake 52.
During normal braking, the system liquid potential source arrives fusiformis valve 3 by first electromagnetic hydraulic pressure lock, 21 and second electromagnetic hydraulic pressure lock 22, and then enters left and right sides wheel brake 51 and 52 by left brake control valve 41 and right brake control valve 42, carries out aircraft brake.Behind arbitrary et out of order in first electromagnetic hydraulic pressure lock, 21 and second electromagnetic hydraulic pressure lock 22, the system liquid potential source enters fusiformis valve 3 by normal electromagnetic hydraulic pressure lock and carries out normal braking then.
When arbitrary when the spool clamping stagnation occurring in left brake control valve 41 and the right brake control valve 42; first electromagnetic hydraulic pressure lock, 21 and second electromagnetic hydraulic pressure lock 22 cuts out; the system liquid potential source can not enter fusiformis valve 3; the import fluid of left side brake control valve 41 and right brake control valve 42 is by fusiformis valve 3; and then lock 22 by first electromagnetic hydraulic pressure lock, 21 and second electromagnetic hydraulic pressure and get back to fuel tank; make the import of left brake control valve 41 and right brake control valve 42 not have pressure; system is in the pine state of stopping, and plays the fail safe protective effect.
When the utility model can guarantee that the clamping stagnation fault appears in the brake control valve spool, make brake system be in the pine state of stopping, in case the locking system belt brake lands and drag tire to cause the aircraft quick-fried tire of stopping.Improved the landing safety of aircraft.
Claims (2)
1. airplane fault-safety shut-down control system, native system comprises brake controller (1), first electromagnetic hydraulic pressure lock (21) and two electromagnetic hydraulic pressures locks (22), it is characterized in that, native system also comprises fusiformis valve (3), left brake control valve (41), right brake control valve (42) and left and right wheel brake (51), (52); First electromagnetic hydraulic pressure lock (21), second electromagnetic hydraulic pressure lock (22) are electrically connected with brake controller (1) respectively, outlet is connected with two entrances of fusiformis valve (3) respectively with second electromagnetic hydraulic pressure lock (22) in first electromagnetic hydraulic pressure lock (21) outlet, the working hole of fusiformis valve (3) links to each other with the import of left brake control valve (41) with right brake control valve (42), the working hole of left side brake control valve (41) links to each other with left wheel brake (51), and the working hole of right brake control valve (42) links to each other with right wheel brake (52).
2. a kind of airplane fault as claimed in claim 1-safety shut-down control system, it is characterized in that, first electromagnetic hydraulic pressure lock (21), second electromagnetic hydraulic pressure lock (22) adopt the two-bit triplet structure, and working hole communicates with oil return under the closed condition, and working hole communicates with oil-feed under the on-state.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201320049409 CN203111499U (en) | 2013-01-29 | 2013-01-29 | Aeroplane failure-safety braking control system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201320049409 CN203111499U (en) | 2013-01-29 | 2013-01-29 | Aeroplane failure-safety braking control system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203111499U true CN203111499U (en) | 2013-08-07 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201320049409 Expired - Lifetime CN203111499U (en) | 2013-01-29 | 2013-01-29 | Aeroplane failure-safety braking control system |
Country Status (1)
| Country | Link |
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| CN (1) | CN203111499U (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2015109779A1 (en) * | 2014-01-26 | 2015-07-30 | 北京航空航天大学 | Multi-wheel aeroplane braking system based on self-energy-regenerative braking device and controlling method therefor |
| CN105000173A (en) * | 2015-08-11 | 2015-10-28 | 中国航空工业集团公司西安飞机设计研究所 | Ground protection system and method for airplane brake |
| CN105523178A (en) * | 2014-09-28 | 2016-04-27 | 中国航空工业集团公司西安飞机设计研究所 | Aircraft double-redundancy anti-skid control system |
| CN110529449A (en) * | 2019-09-24 | 2019-12-03 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of hydraulic efficiency servo-valve high reliability pressure relief device and method |
| CN111963587A (en) * | 2020-09-03 | 2020-11-20 | 合肥中辰轻工机械有限公司 | Pneumatic control system and method of clutch |
| CN118062228A (en) * | 2024-04-24 | 2024-05-24 | 成都飞机工业（集团）有限责任公司 | Anti-skid brake system, control method, residual pressure fault warning method and disposal method |
-
2013
- 2013-01-29 CN CN 201320049409 patent/CN203111499U/en not_active Expired - Lifetime
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2015109779A1 (en) * | 2014-01-26 | 2015-07-30 | 北京航空航天大学 | Multi-wheel aeroplane braking system based on self-energy-regenerative braking device and controlling method therefor |
| US10093288B2 (en) | 2014-01-26 | 2018-10-09 | Beihang University | Multi-wheel aeroplane braking system based on self-energy-regenerative braking device and controlling method therefor |
| CN105523178A (en) * | 2014-09-28 | 2016-04-27 | 中国航空工业集团公司西安飞机设计研究所 | Aircraft double-redundancy anti-skid control system |
| CN105000173A (en) * | 2015-08-11 | 2015-10-28 | 中国航空工业集团公司西安飞机设计研究所 | Ground protection system and method for airplane brake |
| CN110529449A (en) * | 2019-09-24 | 2019-12-03 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of hydraulic efficiency servo-valve high reliability pressure relief device and method |
| CN110529449B (en) * | 2019-09-24 | 2021-03-09 | 中国航空工业集团公司沈阳飞机设计研究所 | High-reliability pressure relief device and method for hydraulic servo valve |
| CN111963587A (en) * | 2020-09-03 | 2020-11-20 | 合肥中辰轻工机械有限公司 | Pneumatic control system and method of clutch |
| CN111963587B (en) * | 2020-09-03 | 2021-12-07 | 合肥中辰轻工机械有限公司 | Pneumatic control system and method of clutch |
| CN118062228A (en) * | 2024-04-24 | 2024-05-24 | 成都飞机工业（集团）有限责任公司 | Anti-skid brake system, control method, residual pressure fault warning method and disposal method |
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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 |