CN204775196U - Aircraft rear deck emergency brake system - Google Patents
Aircraft rear deck emergency brake system Download PDFInfo
- Publication number
- CN204775196U CN204775196U CN201520509717.9U CN201520509717U CN204775196U CN 204775196 U CN204775196 U CN 204775196U CN 201520509717 U CN201520509717 U CN 201520509717U CN 204775196 U CN204775196 U CN 204775196U
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- CN
- China
- Prior art keywords
- emergency brake
- arm
- valve
- erection support
- swivel arm
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- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Abstract
The utility model discloses an aircraft rear deck emergency brake system, including the brake lever, the pull rod, the cable wire, the erection support bent in both ends, the emergency brake relief pressure valve with set up the valve compression pole in emergency brake relief pressure valve one side, the erection support lower part is located to the emergency brake relief pressure valve, the lower part of the erection support department of bending of valve compression pole one side is equipped with rocker arm mechanism and limit stop, rocker arm mechanism includes rocking arm and fixed bolster, the rocking arm includes the upper and lower rotor arms that two slopes set up, the link of two rotor arms forms the main part and is connected with the central rotation of fixed bolster, the top one side of going up the rotor arm is equipped with stop screw, and the cable wire is passed through to the lower part of lower rotor arm and the pull rod is connected with the brake lever, during the pulling brake lever, goes up rotor arm and the contact of valve compression pole, drives the compression of valve compression pole, and stop screw and limit stop compress spacingly to last rotor arm jointly. The utility model discloses an adopt rocker arm mechanism to guarantee, the increase of moment has reduced to control power, has reduced the maintenance work volume.
Description
Technical field
The utility model belongs to airplane design technical field, specifically relates to aircraft rear deck emergency brake system.
Background technology
Aircraft Emergency System many employings mechanical structure, for Aircraft Emergency System design, first will ensure aircraft safety, its system reliability requires very high.
With the mechanical valve class of compression link, need mechanical transmission mechanism during work, driving valve compression link works, thus the break-make of pilot piping, but the fixed installation form of this valve class, and the design of transmission driver train, be the key of system works stability, system maintenance.Although if adopt Electromechanical Control mode accuracy-control system to export, can promote whole system complexity, increase design difficulty and safeguard manufacturing cost, system reliability is difficult to ensure.
According to above design background, for ensureing the control overflow of aircraft rear deck emergency brake system, design and installation emergency brake reducing valve on aircraft mouth frame beam, ensure the requirement of aircraft emergency brake, towing brake.Because this emergency brake system input pressure is 13MPa, delivery pressure is 5MPa ~ 5.7MPa, therefore this design and installation not only will ensure that passenger cabin manipulation can be moved by driving valve compression link, and the valve compression link limit of sports record after installing should be limited in very among a small circle to ensure the decompression delivery pressure of valve, the passenger cabin actuating force of mounting design should meet the maximum restriction requirement of actuating force of operator simultaneously.
Utility model content
The purpose of this utility model is to provide a kind of aircraft rear deck emergency brake system.
The utility model is achieved in that a kind of aircraft rear deck emergency brake system, comprise brake handle, pull bar, cable wire, the erection support of two ends bending, emergency brake reducing valve and the valve compression link being arranged on emergency brake reducing valve side, emergency brake reducing valve is located at erection support bottom, the bottom of the erection support bending part of valve compression link side is provided with rocker arm body and positive stop, and rocker arm body comprises rocking arm and fixed support
Described rocking arm comprise two be obliquely installed rotate up and down arm, the coupling end of two swivel arms forms main body and is connected with fixed support center rotating;
The side, top of described upper swivel arm is provided with stop screw,
The bottom of described lower swivel arm is connected with brake handle by cable wire and pull bar,
When pulling brake handle, upper swivel arm contacts with valve compression link, and drive the compression of valve compression link, stop screw and positive stop compress spacing to upper swivel arm jointly.
The bottom of emergency brake reducing valve is provided with banking stop, is provided with retracing spring between rocking arm and fixed support, and when rocking arm resets, banking stop resets spacing to lower swivel arm.
The radius of gyration of described lower swivel arm is four times of the upper swivel arm radius of gyration.
The beneficial effects of the utility model are:
The accurate debugging of valve has been tested before dress, and on machine, Installation and Debugging only need to carry out for system; Rocker arm body ensure that, the increase of moment, reduces actuating force; System debug and flight-line service, to the adjustment of valve delivery pressure, only need the position adjusting stop screw to ensure, reduce maintenance workload; The combined driving mechanism of cable wire and pull bar both ensure that the transmission of power was smooth and easy, rocker shaft vertical direction can also do low-angle adjustment again, ensure that the technological requirement of assembling.
Accompanying drawing explanation
Fig. 1, the utility model structural representation.
In figure: emergency brake reducing valve 1, erection support 2, banking stop 3, valve compression link 4, Rocker arm 5, cable wire 6, positive stop 7, stop screw 8, rocking arm fixed support 9.
Detailed description of the invention
Embodiment: see Fig. 1.
A kind of aircraft rear deck emergency brake system, comprise the cable wire 6, pull bar, the brake handle that are linked in sequence, the erection support 2 of two ends bending, erection support 2 is installed on fastening aircraft mouth frame beam by four bolts, emergency brake reducing valve 1 and the valve compression link 4 being arranged on emergency brake reducing valve 1 side, emergency brake reducing valve 1 is located at the bottom of erection support 2 bending part, and erection support 2 bottom of valve compression link 4 side is provided with rocker arm body and positive stop 7; rocker arm body comprises Rocker arm 5 and fixed support 9
Described Rocker arm 5 comprise two be obliquely installed rotate up and down arm, the coupling end of two swivel arms forms main body and fixed support 9 carriage center is rotationally connected;
The side, top of described upper swivel arm is provided with stop screw 8,
The bottom of described lower swivel arm is connected with brake handle by cable wire 6 and pull bar,
When pulling brake handle, upper swivel arm contacts with valve compression link 4, and drive valve compression link 4 to compress, stop screw 8 and positive stop 7 compress spacing to upper swivel arm jointly.
The bottom of emergency brake reducing valve 1 is provided with banking stop 3, is provided with retracing spring between Rocker arm 5 and fixed support 9, and when Rocker arm 5 resets, banking stop 3 resets spacing to lower swivel arm.
The radius of gyration of lower swivel arm is four times of the upper swivel arm radius of gyration, increase effectively moment, reduces actuating force.
Principle of work: operator pulls brake handle, by pull bar and cable wire power transmission, drive Rocker arm 5 around the holder pivots of bearing 2; rocker shaft top is used for driving valve compression link 4 and compresses; when rocking arm turns to end position; stop screw 8 is withstood by screw positive stop 7, rocking arm cannot rotate again, then valve port output system rated pressure air pressure; Releasing of brake handle, valve compression link 4 resets under the effect of valve contained spring, and Rocker arm 5 is then reset to the limit under action of reset spring, i.e. rocking arm close contact banking stop 3, and emergency brake reducing valve 1 discharges mouth pressure,
The installation of the main pile-up valve of aircraft rear deck emergency brake system, spacing, transmission control mechanism; The accurate debugging of valve has been tested before dress, and on machine, Installation and Debugging only need to carry out for system; Rocker arm body ensure that, the increase of moment, reduces actuating force; System debug and flight-line service, to the adjustment of valve delivery pressure, only need the position adjusting stop screw to ensure, reduce maintenance workload; The combined driving mechanism of cable wire and pull bar both ensure that the transmission of power was smooth and easy, rocker shaft vertical direction can also do low-angle adjustment again, ensure that the technological requirement of assembling.
The assembling of this aircraft rear deck emergency brake system and debugging are carried out between dress front truck, general assembly only carries out bug check to system, line is that the stop screw namely by adjusting rock arm lower end carries out fine adjustment to system delivery pressure, safeguards easy to use without the need to dismounting.
Claims (3)
1. an aircraft rear deck emergency brake system, comprise brake handle, pull bar, cable wire (6), the erection support (2) of two ends bending, emergency brake reducing valve (1) and be arranged on the valve compression link (4) of emergency brake reducing valve (1) side, emergency brake reducing valve (1) is located at erection support (2) bottom, it is characterized in that, the bottom of erection support (2) bending part of valve compression link (4) side is provided with rocker arm body and positive stop (7); rocker arm body comprises rocking arm (5) and fixed support (9)
Described rocking arm (5) comprise two be obliquely installed rotate up and down arm, the coupling end of two swivel arms forms main body and is connected with fixed support (9) center rotating;
The side, top of described upper swivel arm is provided with stop screw (8),
The bottom of described lower swivel arm is connected with brake handle by cable wire (6) and pull bar,
When pulling brake handle, upper swivel arm contacts with valve compression link (4), and drive valve compression link (4) compression, stop screw (8) and positive stop (7) compress spacing to upper swivel arm jointly.
2. aircraft rear deck emergency brake system according to claim 1, it is characterized in that, the bottom of emergency brake reducing valve (1) is provided with banking stop (3); be provided with retracing spring between rocking arm (5) and fixed support (9); when rocking arm (5) resets, and banking stop (3) resets spacing to lower swivel arm.
3. aircraft rear deck emergency brake system according to claim 1 and 2, is characterized in that, the radius of gyration of described lower swivel arm is four times of the upper swivel arm radius of gyration.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520509717.9U CN204775196U (en) | 2015-07-15 | 2015-07-15 | Aircraft rear deck emergency brake system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520509717.9U CN204775196U (en) | 2015-07-15 | 2015-07-15 | Aircraft rear deck emergency brake system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204775196U true CN204775196U (en) | 2015-11-18 |
Family
ID=54515307
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520509717.9U Active CN204775196U (en) | 2015-07-15 | 2015-07-15 | Aircraft rear deck emergency brake system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN204775196U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109367527A (en) * | 2018-10-17 | 2019-02-22 | 江西洪都航空工业集团有限责任公司 | A kind of aircraft shutdown brake stopper mechanism |
| CN110654567A (en) * | 2019-09-23 | 2020-01-07 | 刘金营 | Early education-6 airplane brake efficiency measuring device |
-
2015
- 2015-07-15 CN CN201520509717.9U patent/CN204775196U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109367527A (en) * | 2018-10-17 | 2019-02-22 | 江西洪都航空工业集团有限责任公司 | A kind of aircraft shutdown brake stopper mechanism |
| CN110654567A (en) * | 2019-09-23 | 2020-01-07 | 刘金营 | Early education-6 airplane brake efficiency measuring device |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant |