CN202267609U - Aircraft landing gear loading system - Google Patents
Aircraft landing gear loading system Download PDFInfo
- Publication number
- CN202267609U CN202267609U CN 201120323492 CN201120323492U CN202267609U CN 202267609 U CN202267609 U CN 202267609U CN 201120323492 CN201120323492 CN 201120323492 CN 201120323492 U CN201120323492 U CN 201120323492U CN 202267609 U CN202267609 U CN 202267609U
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- loading
- loading system
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- undercarriage
- pressure fluid
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Abstract
The utility model relates to an aircraft landing gear loading system, comprising a pressure fluid source, a loading actuator used for outputting a loading load to an aircraft landing gear, a pressure fluid transportation pipeline, a valve gear and a control device, wherein the pressure fluid transportation pipeline comprises an oil supply pipeline and an oil return pipeline, one end of each of the two pipelines is respectively connected with the loading actuator, the other ends of the two pipelines are respectively connected with an oil supply opening and an oil return opening of the pressure fluid source, and the two pipelines are used for realizing transportation of a pressure fluid in a loading system; the valve gear is arranged on the pressure fluid transportation pipeline and is used for controlling transportation speed of the pressure fluid; the control device is connected to the valve gear, and the loading load output to the aircraft landing gear by the loading actuator is indirectly controlled by controlling degree of opening and closing of the valve gear; and the loading actuator comprises a swing hydraulic cylinder used for a front landing gear and a double-piston-rod hydraulic cylinder used for a left main landing gear and a right main landing gear. The aircraft landing gear loading system provided by the utility model saves an enough mounting space for mounting other parts on a test bed, does not have interference with the parts and realizes accurate simulation of a load borne by a landing gear.
Description
Technical field
The utility model relates to airplane design and makes the field, specifically, relates to a kind of undercarriage loading system, and it realizes the accurate simulation to undercarriage suffered aerodynamic loading in the folding and unfolding process in the ground simulation test of aircraft takeoffs and landings frame control system.
Background technology
In the design and manufacture process of large aircraft; Need carry out the ground simulation test of aircraft takeoffs and landings frame control system; Whether its fundamental purpose is to check the function of undercarriage control system and main performance index to meet design requirement; The work matching of inspection undercarriage control system and hydraulic energy system, and test basis is provided for the seaworthiness accordance of hydraulic energy system.For guaranteeing the accurate of test findings, need to realize aerodynamic loading suffered in the undercarriage control process is simulated.
Load (or being called passive loading) because the loading of undercarriage is belonged to motion, this type loading system is difficult to guarantee the precision that loads owing to the interference that receives carrier movement.Specifically; Because existing nose-gear loading system adopts single-piston-rod hydraulic cylinder to load; When aircraft was equipped with nose gear door on test-bed, its nose-gear loading system was not owing to can interfere with each other with hatch door for hatch door leaves enough installing spaces; Similarly, because existing main landing gear loading system adopts oil motor to load, when aircraft was equipped with wing on test-bed, its main landing gear loading system also can interfere with each other with wing.Above-mentioned reason all can cause existing undercarriage loading system can't realize accurate loading to undercarriage.
The utility model content
The problem that the utility model solves provides a kind of undercarriage loading system, is implemented in the ground simulation test of aircraft takeoffs and landings frame control system, to the accurate simulation of undercarriage suffered aerodynamic loading in the folding and unfolding process.
For addressing the above problem, the utility model provides a kind of undercarriage loading system, comprising: pressure fluid source; Load actuator, be used for to undercarriage output loaded load; The pressure fluid conveyance conduit comprises oil supply pipe and oil returning tube, and an end of two pipelines links to each other with the loading actuator respectively, and the other end links to each other with oil return opening with the oil-feed port of pressure fluid source respectively, is used to realize the conveying of pressure fluid in loading system; Valve gear is installed on the said pressure fluid conveyance conduit, is used for the transporting velocity of controlled pressure fluid; Control device is connected to said valve gear, through controlling the switching degree of said valve gear, controls the loaded load of said loading actuator to undercarriage output indirectly; Said loading actuator comprises oscillating motor that is used for nose-gear and the double piston-rod hydraulic cylinder that is used for left and right main landing gear.
Alternatively, said loading actuator also comprises moment of torsion and the angular displacement sensor that is connected to oscillating motor, the power that is connected to the double piston-rod hydraulic cylinder and displacement transducer.
Alternatively, the two ends of said moment of torsion and angular displacement sensor are connected with nose-gear with oscillating motor respectively.
Alternatively, the two ends of said power and displacement transducer are connected with left and right main landing gear with the double piston-rod hydraulic cylinder respectively.
Alternatively, said valve gear comprises throttling valve, solenoid directional control valve, electrohydraulic servo valve and stop valve.
Alternatively, said electrohydraulic servo valve and stop valve are cascaded, and are connected between said loading actuator and the said pressure fluid source.
Alternatively, said throttling valve and solenoid directional control valve are connected between two oil pockets of said loading actuator.
Alternatively, said control device comprises the computing machine and the servo controller of series connection, is used to control the loaded load of said loading actuator to undercarriage output.
Alternatively, said loading system also comprises oil filter and the accumulator on the oil supply pipe that is installed between stop valve and the electrohydraulic servo valve.
Alternatively, said solenoid directional control valve comprises emergency button, is used for when said loading system breaks down, controlling said solenoid directional control valve through said emergency button, makes the loading system unloading.
Compared with prior art; The utlity model has following advantage: in the ground simulation test of aircraft takeoffs and landings frame control system; Adopt oscillating motor to load to the nose-gear loading system; Then adopt the double piston-rod hydraulic cylinder to load to main landing gear, even when making airplane components such as nose gear door or wing are installed on test-bed, owing to left enough installing spaces for said airplane component; So corresponding undercarriage loading system can not interfere with said airplane component yet, thereby can realize the accurate simulation to undercarriage suffered aerodynamic loading in the folding and unfolding process.In addition, the described undercarriage loading system of the utility model is safe and convenient to use, and good reliability and cost are lower.
Description of drawings
Fig. 1 is the synoptic diagram of the undercarriage loading system of the utility model.
Embodiment
Below in conjunction with specific embodiment and accompanying drawing the utility model is further described, but should limit the protection domain of the utility model with this.
Fig. 1 is the synoptic diagram of the undercarriage loading system of the utility model.With reference to Fig. 1, the undercarriage loading system that the utility model provided mainly comprises loading system that is used for nose-gear and the loading system that is respectively applied for left and right main landing gear.With the loading system that is used for nose-gear is example, and said loading system comprises like the lower part: pressure fluid source (not shown); Load actuator, comprise moment of torsion and angular displacement sensor 3 and oscillating motor 4, be used for to undercarriage output loaded load; The pressure fluid conveyance conduit comprises oil supply pipe and oil returning tube, and an end of two pipelines links to each other with the loading actuator respectively, and the other end links to each other with oil return opening 12 with the oil-feed port 11 of pressure fluid source respectively, is used to realize the conveying of pressure fluid in loading system; Valve gear comprises throttling valve 5, solenoid directional control valve 7, electrohydraulic servo valve 8 and stop valve 13, is installed on the said pressure fluid conveyance conduit, is used for the transporting velocity of controlled pressure fluid; Control device comprises computing machine 1 and servo controller 2, is connected to said valve gear, through controlling the switching degree of said valve gear, controls the loaded load of said loading actuator to undercarriage output indirectly.
In the present embodiment; The loading system of above-mentioned nose-gear also comprises the emergency button 6 that is connected with solenoid directional control valve 7 through cable; Be used for when said loading system breaks down, controlling said solenoid directional control valve, make the loading system unloading through said emergency button.
In the present embodiment, the loading system of above-mentioned nose-gear also comprises the oil filter 9 and accumulator 10 on the oil supply pipe that is installed between stop valve 13 and the electrohydraulic servo valve 8, is used to improve the efficient of loading system, reduces invalid energy loss.
In the present embodiment, the two ends of said moment of torsion and angular displacement sensor 3 mechanically are connected with nose-gear with oscillating motor 4 respectively; Electrohydraulic servo valve 8 is connected with servo controller 2 respectively through cable with angular displacement sensor 3 with moment of torsion; Throttling valve 5 and solenoid directional control valve 7 are connected between two oil pockets of said loading actuator; Electrohydraulic servo valve 8 is cascaded with stop valve 13, and is connected between said loading actuator and the said pressure fluid source; Computing machine 1 and servo controller 2 are connected through netting twine.
In the present embodiment; For the loading system that is used for left and right main landing gear; Moment of torsion in the above-mentioned nose-gear loading system and angular displacement sensor 3 are replaced by power and displacement transducer 14,25; Oscillating motor 4 in the above-mentioned nose-gear loading system is replaced by double piston-rod hydraulic cylinder 15,26, and remaining component is the same with the loading system of nose-gear.Be that the said loading system that is used for left and right main landing gear comprises like the lower part: pressure fluid source (not shown); Load actuator, comprise power and displacement transducer 14,25 and double piston-rod hydraulic cylinder 15,26, be used for to undercarriage output loaded load; The pressure fluid conveyance conduit; Comprise oil supply pipe and oil returning tube; One end of two pipelines links to each other with the loading actuator respectively, and the other end links to each other with oil return opening 23,34 with the oil-feed port 22,33 of pressure fluid source respectively, is used to realize the conveying of pressure fluid in loading system; Valve gear comprises throttling valve 16,27, solenoid directional control valve 18,29, electrohydraulic servo valve 19,30 and stop valve 24,35, is installed on the said pressure fluid conveyance conduit, is used for the transporting velocity of controlled pressure fluid; Control device comprises computing machine 1 and servo controller 2, is connected to said valve gear, through controlling the switching degree of said valve gear, controls the loaded load of said loading actuator to undercarriage output indirectly.Wherein, the loading system of left and right main landing gear and the shared control device of the loading system of above-mentioned nose-gear, i.e. computing machine 1 and servo controller 2.
In the present embodiment; The loading system of above-mentioned left and right main landing gear also comprises the emergency button 17,28 that is connected with solenoid directional control valve 18,29 through cable; Be used for when said loading system breaks down, controlling said solenoid directional control valve, make the loading system unloading through said emergency button.
In the present embodiment; The loading system of above-mentioned left and right main landing gear also comprises oil filter 20,31 and the accumulator 21,32 that is installed on stop valve 24,35 and electrohydraulic servo valve 19, the oil supply pipe between 30; Be used to improve the efficient of loading system, reduce invalid energy loss.
In the present embodiment, the two ends of said power and displacement transducer 14,25 mechanically are connected with left and right main landing gear with double piston-rod hydraulic cylinder 15,26 respectively; Electrohydraulic servo valve 19,30 is connected with servo controller 2 respectively through cable with displacement transducer 14,25 with power; Throttling valve 16,27 and solenoid directional control valve 18,29 are connected between two oil pockets of said loading actuator; Electrohydraulic servo valve 19,30 and stop valve 24,35 are cascaded, and are connected between said loading actuator and the said pressure fluid source.
The loading system of said nose-gear and the loading system three of left and right main landing gear have constituted a complete undercarriage loading system of the present invention together.
The course of work of the undercarriage loading system that the utility model provided is following:
(a) prepare to load: oil-feed port 11,22,33 connects the 20Mp fuel oil injection piping respectively, and oil return opening 12,23,34 connects return line respectively; Open stop valve 13,24,35; Loading system powers on, and the requirement according to the ground simulation test of undercarriage control system is provided with the loading curve in the undercarriage control process and downloads to servo controller 2 through computing machine 1.
(b) begin to load: solenoid directional control valve 7,18,29 disconnection that powers on; To begin load instructions through computing machine 1 and be sent to servo controller 2; Servo controller 2 is controlled electrohydraulic servo valve 8,19,30 respectively according to the feedback signal output electric signal of loading curve and moment of torsion and angular displacement sensor 3, power and displacement transducer 14,25; Electrohydraulic servo valve 8,19,30 is controlled the pressure reduction in oscillating motor 4,15,26 liang of chambeies of double piston-rod hydraulic cylinder respectively; Thereby the load of controlling nose-gear, left main, starboard main landing gear respectively and being born promptly realizes the simulation to undercarriage suffered aerodynamic loading in the folding and unfolding process.
(c) condition monitoring: servo controller 2 sends the signal of moment of torsion and angular displacement sensor 3, power and displacement transducer 14,25 feedbacks to computing machine 1 through Ethernet; When abnormal conditions occurring; Press emergency button 6,17,28 and make solenoid directional control valve 7,18,29 outages connect unloading respectively, thereby protected the safety of equipment.
(d) stop to load: solenoid directional control valve 7,18,29 outages are connected; To stop load instructions through computing machine 1 and be sent to servo controller 2, servo controller 2 stops to load; In computing machine 1, preserve data.
The utility model is in the ground simulation test of aircraft takeoffs and landings frame control system; Adopt oscillating motor to load to the nose-gear loading system; Then adopt the double piston-rod hydraulic cylinder to load to main landing gear; Even when making airplane components such as nose gear door or wing are installed on test-bed; Owing to left enough installing spaces,, thereby can realize accurate simulation to undercarriage suffered aerodynamic loading in the folding and unfolding process so the undercarriage loading system can not interfere with said airplane component yet accordingly for said airplane component.In addition, the described undercarriage loading system of the utility model is safe and convenient to use, and good reliability and cost are lower.
Though the utility model with preferred embodiment openly as above; But it is not to be used for limiting the utility model; Any those skilled in the art are in spirit that does not break away from the utility model and scope; Can make possible change and modification, so the protection domain of the utility model should be as the criterion with the scope that the utility model claim is defined.
Claims (10)
1. undercarriage loading system comprises:
Pressure fluid source;
Load actuator (3,4; 14,15; 25,26), be used for to undercarriage output loaded load;
The pressure fluid conveyance conduit comprises oil supply pipe and oil returning tube, and an end of two pipelines links to each other with the loading actuator respectively; The other end respectively with the oil-feed port (11,22,33) and the oil return opening (12 of pressure fluid source; 23,34) link to each other, be used to realize the conveying of pressure fluid in loading system;
Valve gear (5,7,8,13; 16,18,19,24; 27,29,30,35), be installed on the said pressure fluid conveyance conduit, be used for the transporting velocity of controlled pressure fluid;
Control device (1,2) is connected to said valve gear, through controlling the switching degree of said valve gear, controls the loaded load of said loading actuator to undercarriage output indirectly;
It is characterized in that said loading actuator comprises oscillating motor (4) that is used for nose-gear and the double piston-rod hydraulic cylinder (15,26) that is used for left and right main landing gear.
2. undercarriage loading system according to claim 1; It is characterized in that; Said loading actuator also comprises moment of torsion and angular displacement sensor (3), the power that is connected to double piston-rod hydraulic cylinder (15,26) and the displacement transducer (14,25) that is connected to oscillating motor (4).
3. undercarriage loading system according to claim 2 is characterized in that, the two ends of said moment of torsion and angular displacement sensor (3) are connected with nose-gear with oscillating motor (4) respectively.
4. according to claim 2 or 3 described undercarriage loading systems, it is characterized in that the two ends of said power and displacement transducer (14,25) are connected with left and right main landing gear with double piston-rod hydraulic cylinder (15,26) respectively.
5. undercarriage loading system according to claim 1 is characterized in that, said valve gear comprises throttling valve (5,16,27), solenoid directional control valve (7,18,29), electrohydraulic servo valve (8,19,30) and stop valve (13,24,35).
6. undercarriage loading system according to claim 5 is characterized in that, said electrohydraulic servo valve (8,19,30) and stop valve (13,24,35) are cascaded, and are connected between said loading actuator and the said pressure fluid source.
7. according to claim 5 or 6 described undercarriage loading systems, it is characterized in that said throttling valve (5,16,27) and solenoid directional control valve (7,18,29) are connected between two oil pockets of said loading actuator.
8. undercarriage loading system according to claim 1 is characterized in that, said control device comprises the computing machine (1) and the servo controller (2) of series connection, is used to control the loaded load of said loading actuator to undercarriage output.
9. undercarriage loading system according to claim 7 is characterized in that, said loading system also comprises and is installed on stop valve (13,24; 35) and the oil on the oil supply pipe between the electrohydraulic servo valve (8,19,30) filter (9,20; 31) and accumulator (10,21,32).
10. undercarriage loading system according to claim 7 is characterized in that, said solenoid directional control valve (7,18; 29) comprise emergency button (6,17,28), be used for when said loading system breaks down; Control said solenoid directional control valve (7 through said emergency button (6,17,28); 18,29), make the loading system unloading.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201120323492 CN202267609U (en) | 2011-08-31 | 2011-08-31 | Aircraft landing gear loading system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201120323492 CN202267609U (en) | 2011-08-31 | 2011-08-31 | Aircraft landing gear loading system |
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| Publication Number | Publication Date |
|---|---|
| CN202267609U true CN202267609U (en) | 2012-06-06 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN 201120323492 Expired - Lifetime CN202267609U (en) | 2011-08-31 | 2011-08-31 | Aircraft landing gear loading system |
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| CN (1) | CN202267609U (en) |
Cited By (17)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103033380A (en) * | 2012-12-11 | 2013-04-10 | 中国飞机强度研究所 | Landing gear retractable test loading device and method |
| CN103134698A (en) * | 2012-12-11 | 2013-06-05 | 沈阳北方交通重工有限公司 | Detection device with nose landing gear protection function through detection of nose landing gear of aircraft |
| CN103604593A (en) * | 2013-11-21 | 2014-02-26 | 南京航空航天大学 | Plane type ejection launch carrier-borne aircraft front undercarriage static force test loading apparatus |
| CN103604619A (en) * | 2013-11-21 | 2014-02-26 | 南京航空航天大学 | Front undercarriage static force test loading device for frame-type catapult-assisted take-off shipboard aircraft |
| CN103983463A (en) * | 2014-04-17 | 2014-08-13 | 中国航空工业集团公司沈阳飞机设计研究所 | Method for verification test of combined loading of airframe and undercarriage |
| CN105438497A (en) * | 2015-11-26 | 2016-03-30 | 中国航空工业集团公司沈阳飞机设计研究所 | Electric driving landing gear loading device |
| CN105480431A (en) * | 2014-10-11 | 2016-04-13 | 中国航空工业集团公司西安飞机设计研究所 | Method for avoiding excessive vibration of undercarriage in overhead state |
| CN105607524A (en) * | 2016-03-16 | 2016-05-25 | 中国飞机强度研究所 | Output signal switching controller for main landing spurious wheel vertical sensor |
| CN106089820A (en) * | 2016-08-23 | 2016-11-09 | 北京航空航天大学 | A kind of based on the structural test loading actuating system along inverse load Discrete control |
| CN106428623A (en) * | 2016-08-29 | 2017-02-22 | 中国航空工业集团公司西安飞机设计研究所 | Loading method of variable stroke test for undercarriage |
| CN106932187A (en) * | 2017-03-27 | 2017-07-07 | 南京航空航天大学 | A kind of Nose Gear Fast-Extension of Carrier Based Aircraft experimental rig and test method |
| CN108757599A (en) * | 2018-04-28 | 2018-11-06 | 北京机械设备研究所 | A kind of hydraulic loading system and loading method for airplane ground test platform |
| CN109019397A (en) * | 2018-08-20 | 2018-12-18 | 中国飞机强度研究所 | load support system |
| CN110589019A (en) * | 2019-09-09 | 2019-12-20 | 中国航空工业集团公司北京长城航空测控技术研究所 | Force loading method and loading device for high-speed retraction and extension test of undercarriage |
| CN113911387A (en) * | 2021-09-13 | 2022-01-11 | 北京精密机电控制设备研究所 | Cam type airplane cabin door load simulation device and method |
| CN115556926A (en) * | 2022-11-07 | 2023-01-03 | 浙江大学 | Front wheel control swing-reducing hydraulic system of civil wide-body aircraft test prototype |
| CN115556926B (en) * | 2022-11-07 | 2024-07-09 | 浙江大学 | Front wheel control swing-reducing hydraulic system of civil wide-body airplane test prototype |
-
2011
- 2011-08-31 CN CN 201120323492 patent/CN202267609U/en not_active Expired - Lifetime
Cited By (25)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103033380B (en) * | 2012-12-11 | 2015-07-01 | 中国飞机强度研究所 | Landing gear retractable test loading method |
| CN103134698A (en) * | 2012-12-11 | 2013-06-05 | 沈阳北方交通重工有限公司 | Detection device with nose landing gear protection function through detection of nose landing gear of aircraft |
| CN103033380A (en) * | 2012-12-11 | 2013-04-10 | 中国飞机强度研究所 | Landing gear retractable test loading device and method |
| CN103604619B (en) * | 2013-11-21 | 2016-01-20 | 南京航空航天大学 | Frame-type catapult-assisted take-off carrier-borne aircraft nose-gear slow test charger |
| CN103604619A (en) * | 2013-11-21 | 2014-02-26 | 南京航空航天大学 | Front undercarriage static force test loading device for frame-type catapult-assisted take-off shipboard aircraft |
| CN103604593B (en) * | 2013-11-21 | 2016-03-02 | 南京航空航天大学 | Plane type ejection launch carrier-borne aircraft front undercarriage static force test charger |
| CN103604593A (en) * | 2013-11-21 | 2014-02-26 | 南京航空航天大学 | Plane type ejection launch carrier-borne aircraft front undercarriage static force test loading apparatus |
| CN103983463A (en) * | 2014-04-17 | 2014-08-13 | 中国航空工业集团公司沈阳飞机设计研究所 | Method for verification test of combined loading of airframe and undercarriage |
| CN103983463B (en) * | 2014-04-17 | 2016-08-24 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of airframe and the checking test method of undercarriage combination loading |
| CN105480431A (en) * | 2014-10-11 | 2016-04-13 | 中国航空工业集团公司西安飞机设计研究所 | Method for avoiding excessive vibration of undercarriage in overhead state |
| CN105438497A (en) * | 2015-11-26 | 2016-03-30 | 中国航空工业集团公司沈阳飞机设计研究所 | Electric driving landing gear loading device |
| CN105607524B (en) * | 2016-03-16 | 2018-04-13 | 中国飞机强度研究所 | One kind has led the vertical sensor output switch method of remote signal device of false wheel |
| CN105607524A (en) * | 2016-03-16 | 2016-05-25 | 中国飞机强度研究所 | Output signal switching controller for main landing spurious wheel vertical sensor |
| CN106089820A (en) * | 2016-08-23 | 2016-11-09 | 北京航空航天大学 | A kind of based on the structural test loading actuating system along inverse load Discrete control |
| CN106089820B (en) * | 2016-08-23 | 2018-05-25 | 北京航空航天大学 | A kind of structural test based on along inverse load Discrete control loads actuating system |
| CN106428623A (en) * | 2016-08-29 | 2017-02-22 | 中国航空工业集团公司西安飞机设计研究所 | Loading method of variable stroke test for undercarriage |
| CN106932187A (en) * | 2017-03-27 | 2017-07-07 | 南京航空航天大学 | A kind of Nose Gear Fast-Extension of Carrier Based Aircraft experimental rig and test method |
| CN106932187B (en) * | 2017-03-27 | 2023-05-26 | 南京航空航天大学 | Device and method for testing protruding of nose landing gear of carrier-based aircraft |
| CN108757599A (en) * | 2018-04-28 | 2018-11-06 | 北京机械设备研究所 | A kind of hydraulic loading system and loading method for airplane ground test platform |
| CN109019397A (en) * | 2018-08-20 | 2018-12-18 | 中国飞机强度研究所 | load support system |
| CN110589019A (en) * | 2019-09-09 | 2019-12-20 | 中国航空工业集团公司北京长城航空测控技术研究所 | Force loading method and loading device for high-speed retraction and extension test of undercarriage |
| CN113911387A (en) * | 2021-09-13 | 2022-01-11 | 北京精密机电控制设备研究所 | Cam type airplane cabin door load simulation device and method |
| CN113911387B (en) * | 2021-09-13 | 2023-09-29 | 北京精密机电控制设备研究所 | Cam type aircraft cabin door load simulation device and simulation method |
| CN115556926A (en) * | 2022-11-07 | 2023-01-03 | 浙江大学 | Front wheel control swing-reducing hydraulic system of civil wide-body aircraft test prototype |
| CN115556926B (en) * | 2022-11-07 | 2024-07-09 | 浙江大学 | Front wheel control swing-reducing hydraulic system of civil wide-body airplane test prototype |
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| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
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Granted publication date: 20120606 |
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| CX01 | Expiry of patent term |