CN202171468U - Airplane brake sensor testing stand capable of carrying out heavy load test - Google Patents
Airplane brake sensor testing stand capable of carrying out heavy load test Download PDFInfo
- Publication number
- CN202171468U CN202171468U CN2011202229591U CN201120222959U CN202171468U CN 202171468 U CN202171468 U CN 202171468U CN 2011202229591 U CN2011202229591 U CN 2011202229591U CN 201120222959 U CN201120222959 U CN 201120222959U CN 202171468 U CN202171468 U CN 202171468U
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- brake sensor
- hydraulic
- loading
- testing stand
- hydraulic system
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Abstract
The utility model discloses an airplane brake sensor testing stand capable of carrying out heavy load tests, belonging to the field of aviation accessory maintenance. The testing stand comprises a hydraulic system, a loading support provided with a brake sensor and a loading pull bar which loads load via the hydraulic system, wherein the hydraulic system comprises a hydraulic oil cylinder, an oil tank, a hydraulic pump, a solenoid valve and an overflow valve used for adjusting loading load, a piston of the hydraulic oil cylinder is fixed with the loading pull bar, an inlet of the overflow valve is connected with an outlet of the hydraulic pump, and an oil return opening of the solenoid valve is respectively connected with a pressure transducer and a pressure gauge. The testing stand is reasonable in design, convenient in installation, safe and reliable, fully satisfies test requirements for brake sensor assemblies prescribed in a maintenance manual, saves maintenance cost and shortens maintenance period.
Description
Technical field
The utility model relates to a kind of aviation annex maintenance of equipment, relates in particular to a kind of aircraft brake sensor testing table that carries out the heavy load test.
Background technology
Along with present development of aviation; Service quality and maintenance efficiency to the maintenance of aircarrier aircraft annex are also increasingly high; Brake sensor belongs to the brake torque restriction system of aircraft main undercarriage unit, is used for the size of responsive aircraft brake gear output damping force when braking state, and transmits the size of brake torque in real time to brake system control device (BSCU); In case braking moment is excessive, cause the destruction of aircaft configuration.Stipulate in the servicing manual of these parts, need carry out the environment of heavy load when braking when this product is tested with simulated aircraft.But China does not also have a heavy load testing apparatus that can satisfy this part test, and airline must it deliver to state's exogenesis producer place under repair and verification, and not only the cost of repairs is high, and the repair cycle is long.
The utility model content
Goal of the invention: in order to overcome the deficiency that exists in the prior art, the utility model provides a kind of aircraft brake sensor testing table that carries out the heavy load test.
Technical scheme: for realizing above-mentioned purpose; The aircraft brake sensor testing table of the carried out heavy load test of the utility model comprises hydraulic system, the loading support of brake sensor is installed; And the loading pull bar that passes through the hydraulic system load; Said hydraulic system comprises hydraulic jack, and the piston of hydraulic jack is fixed with the loading pull bar.
Said hydraulic system also comprises fuel tank, hydraulic pump, solenoid valve and the surplus valve that is used to regulate load; The inlet of said surplus valve is connected the outlet oil sump tank of surplus valve with the hydraulic pump outlet; Said solenoid valve oil return opening is connected with pressure transducer and tensimeter respectively.
Wherein, said surplus valve is used for the pressure size of regulator solution pressing system, thereby the regulator solution compressing cylinder is carried in by the capable load of examination brake sensor.Said hydraulic jack is a double rod cylinder, and said solenoid valve is a three-position four-way valve, and the oil-in of this three-position four-way valve is communicated with the oil return opening oil sump tank with the hydraulic pump outlet.
Wherein, said pressure transducer and tensimeter are used to measure the oil liquid pressure at solenoid valve oil return opening place, and the pressure display that detection is obtained is on the display panel of testing table.This pressure is exactly the load of being tried brake sensor.
As the further optimization of the utility model, between solenoid valve and hydraulic pump, also be provided with a retaining valve, in retaining valve outlet also and connect a safety valve, the outlet oil sump tank of this safety valve is used to prevent the excessive measuring accuracy that influences of charge oil pressure.
When carrying out the load test of brake sensor, brake sensor is fixed on the loading support and loads on the pull bar energized through pin; Pulling force requirement according to the brake sensor servicing manual; Regulate surplus valve and confirm the pressure of system, primer fluid press pump then is through observing the demonstration of display panel upward pressure table numerical value; Make the setting that reaches servicing manual that meets that is carried in by on the examination brake sensor, and the record test value.
Beneficial effect: the aircraft brake sensor test platform structure of the carried out heavy load test of the utility model is reasonable in design, easy for installation, safe and reliable; Satisfy in the servicing manual test request fully to the brake sensor assembly; Practice thrift maintenance cost, shortened maintenance cycle.
Description of drawings
Fig. 1 is the structural representation of the utility model;
Fig. 2 is the utility model hydraulic schematic diagram.
Embodiment
Below in conjunction with accompanying drawing the utility model is done explanation further.
160U0100-11 brake sensor assembly on the present embodiment employing B747-400 aircraft main landing gear is as explanation.The pulling force of this assembly on servicing manual loads and require is 17.9 ~ 18.4 tons.
As shown in Figure 1, this testing table is provided with loading support 2 and loads pull bar 3, loads support 1 and is provided with the chassis, is used for quilt examination brake sensor 1 is fixed on loading support 2 through pin.Fixed with the piston of hydraulic jack 4 through loading pull bar 3 by the other end of examination brake sensor 1.Testing table is through the pressure of display panel 12 display systems, and the loading current that is tried brake sensor 1.
Hydraulic system is as shown in Figure 2, is connected to hydraulic jack 3 through retaining valve 12, four position three-way valves 7 successively from fuel tank 5, hydraulic pump 6, and this hydraulic jack 3 is a double rod cylinder.The oil return opening oil sump tank 5 of four position three-way valves 7 also is provided with pressure transducer 9 and tensimeter 10 at oil return opening, is used for detection system pressure and shows at display panel.Be provided with surplus valve 8 in the exit of hydraulic pump 6, be provided with safety valve 11 in the exit of retaining valve.
The above only is the preferred implementation of the utility model; Be noted that for those skilled in the art; Under the prerequisite that does not break away from the utility model principle; Can also make some improvement and retouching, these improvement and retouching also should be regarded as the protection domain of the utility model.
Claims (3)
1. one kind can be carried out the aircraft brake sensor testing table that heavy load is tested; It is characterized in that: this testing table comprises hydraulic system, the loading support (2) of brake sensor (1) is installed; And the loading pull bar (3) that passes through the hydraulic system load; Said hydraulic system comprises hydraulic jack (4), and the piston of said hydraulic jack (4) is fixing with loading pull bar (3).
2. the aircraft brake sensor testing table that carries out the heavy load test according to claim 1, it is characterized in that: said hydraulic system also comprises fuel tank (5), hydraulic pump (6), solenoid valve (7) and the surplus valve (8) that is used to regulate load; The inlet of said surplus valve (8) is connected with hydraulic pump (6) outlet; Said solenoid valve (7) oil return opening is connected with pressure transducer (9) and tensimeter (10) respectively.
3. the aircraft brake sensor testing table that carries out the heavy load test according to claim 2, it is characterized in that: said hydraulic jack (4) is a double rod cylinder; Said solenoid valve (7) is a three-position four-way valve.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011202229591U CN202171468U (en) | 2011-06-29 | 2011-06-29 | Airplane brake sensor testing stand capable of carrying out heavy load test |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011202229591U CN202171468U (en) | 2011-06-29 | 2011-06-29 | Airplane brake sensor testing stand capable of carrying out heavy load test |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN202171468U true CN202171468U (en) | 2012-03-21 |
Family
ID=45829663
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2011202229591U Expired - Fee Related CN202171468U (en) | 2011-06-29 | 2011-06-29 | Airplane brake sensor testing stand capable of carrying out heavy load test |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN202171468U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106933216A (en) * | 2017-03-13 | 2017-07-07 | 北京航空航天大学 | A kind of test device for aircraft brake controller |
-
2011
- 2011-06-29 CN CN2011202229591U patent/CN202171468U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106933216A (en) * | 2017-03-13 | 2017-07-07 | 北京航空航天大学 | A kind of test device for aircraft brake controller |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20120321 Termination date: 20160629 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |