CN114509248A - Aircraft undercarriage pressurized strut test system - Google Patents
Aircraft undercarriage pressurized strut test system Download PDFInfo
- Publication number
- CN114509248A CN114509248A CN202111662938.6A CN202111662938A CN114509248A CN 114509248 A CN114509248 A CN 114509248A CN 202111662938 A CN202111662938 A CN 202111662938A CN 114509248 A CN114509248 A CN 114509248A
- Authority
- CN
- China
- Prior art keywords
- servo valve
- oil
- actuator
- temperature
- test
- Prior art date
- 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.)
- Pending
Links
- 238000012360 testing method Methods 0.000 title claims abstract description 135
- 239000003921 oil Substances 0.000 claims abstract description 51
- 239000010720 hydraulic oil Substances 0.000 claims abstract description 33
- 238000006073 displacement reaction Methods 0.000 claims abstract description 32
- 238000002955 isolation Methods 0.000 claims abstract description 11
- 238000009413 insulation Methods 0.000 claims description 19
- 239000010687 lubricating oil Substances 0.000 claims description 15
- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical compound [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 claims description 6
- 229910052742 iron Inorganic materials 0.000 claims description 3
- 238000012827 research and development Methods 0.000 abstract description 2
- 238000004088 simulation Methods 0.000 abstract description 2
- 230000005540 biological transmission Effects 0.000 description 2
- 238000013461 design Methods 0.000 description 2
- 230000007613 environmental effect Effects 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 238000001228 spectrum Methods 0.000 description 2
- WYTGDNHDOZPMIW-RCBQFDQVSA-N alstonine Natural products C1=CC2=C3C=CC=CC3=NC2=C2N1C[C@H]1[C@H](C)OC=C(C(=O)OC)[C@H]1C2 WYTGDNHDOZPMIW-RCBQFDQVSA-N 0.000 description 1
- 230000004075 alteration Effects 0.000 description 1
- 238000004458 analytical method Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000004364 calculation method Methods 0.000 description 1
- 239000002131 composite material Substances 0.000 description 1
- 238000012669 compression test Methods 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 238000001514 detection method Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000009661 fatigue test Methods 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 229910052751 metal Inorganic materials 0.000 description 1
- 238000003908 quality control method Methods 0.000 description 1
- 238000011084 recovery Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 238000009864 tensile test Methods 0.000 description 1
- 238000010998 test method Methods 0.000 description 1
- 238000012546 transfer Methods 0.000 description 1
Images
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M13/00—Testing of machine parts
Landscapes
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
Abstract
The utility model provides an aircraft undercarriage actuator test system, including loading actuator, loading oil source, the actuator test piece, high-pressure oil station, test box No. 1, hydraulic oil temperature controller, temperature sensor II, MOOG controller, servo valve I, servo valve II, force sensor, displacement sensor and test fixture, loading oil source oil-out is connected with I oil inlet of servo valve, I oil-out of servo valve is connected with the loading actuator, the high-pressure oil station oil-out is connected with II oil inlets of servo valve, II two way oil-outs of servo valve are connected with the heater respectively through the isolation cylinder respectively, heater and actuator test piece are connected, MOOG controller respectively with servo valve I, servo valve II, force sensor and displacement sensor are connected, servo valve I and force sensor are connected with the loading actuator respectively, servo valve II and displacement sensor are connected with the actuator test piece. Provides a more real simulation environment for the research and development of the products such as the actuating cylinder.
Description
Technical Field
The invention relates to a test system, in particular to a test system for an aircraft landing gear actuator cylinder, and belongs to the technical field of tests.
Background
Landing gear is an important component of an aircraft, and is mainly applied to take-off, landing, ground sliding and parking and the like of the aircraft, and various energies generated during landing and ground movement of the aircraft are absorbed and dissipated. The undercarriage retractable actuator cylinder can simultaneously receive the effects of external force, ambient temperature, hydraulic system medium temperature and the like during working. At present, fatigue tests of actuator cylinder products generally use normal-temperature hydraulic oil to perform simple tensile and compression tests in a normal-temperature environment; however, this method cannot simulate the high temperature environment generated after the aircraft flies at high speed and the state that the temperature of the working medium exceeds the ambient temperature due to the high temperature environment and the work, and it is difficult to realize the complex working condition that different strokes of the actuator cylinder correspond to different loads.
Disclosure of Invention
The invention aims to solve the problems in the prior art and provide an aircraft landing gear actuator cylinder test system.
In order to achieve the purpose, the technical solution of the invention is as follows: a test system for an aircraft landing gear actuator cylinder comprises a loading actuator, a loading oil source, an actuator cylinder test piece, a high-pressure oil station, a test box No. 1, a hydraulic oil temperature controller, a temperature sensor II, an MOOG controller, a servo valve I, a servo valve II, a force sensor, a displacement sensor and a test fixture, wherein the loading actuator and an actuator cylinder test piece are respectively fixed on the test fixture, an oil outlet of the loading oil source is connected with an oil inlet of the servo valve I through a hydraulic pipeline, an oil outlet of the servo valve I is connected with the loading actuator through a hydraulic pipeline, an oil outlet of the high-pressure oil station is connected with an oil inlet of the servo valve II through a hydraulic pipeline, two oil outlets of the servo valve II are respectively connected with isolation cylinders through hydraulic pipelines, the two isolation cylinders are respectively connected with a hydraulic oil heater through hydraulic pipelines, and the hydraulic oil heater is connected with the actuator cylinder test piece through a hydraulic pipeline, the hydraulic oil temperature controller is connected with a hydraulic oil heater, a No. 1 test box and a temperature sensor II through signal lines respectively, the temperature sensor II is arranged at a lubricating oil inlet of the actuating cylinder test piece, the MOOG controller is connected with a servo valve I, a servo valve II, a force sensor and a displacement sensor through signal lines respectively, the servo valve I and the force sensor are connected with a loading actuator respectively, and the servo valve II and the displacement sensor are connected with the actuating cylinder test piece.
Still including No. 2 temperature test case, draught fan, temperature sensor I and insulation can, No. 2 temperature test case pass through the tuber pipe and be connected with the draught fan, the draught fan pass through the tuber pipe and be connected with the insulation can, No. 2 temperature test case pass through the signal line and be connected with temperature sensor I, temperature sensor I set up in the insulation can.
The test fixture comprises a universal base, a linear bearing and two lugs, the loading actuator is connected with the actuator cylinder test piece through the linear bearing, the actuator cylinder test piece and the loading actuator are connected with the two lugs through iron tips, the force sensor is installed at the top end of the loading actuator and connected with the left end of a middle circular shaft of the linear bearing, the displacement sensor is installed on a shell of the actuator cylinder test piece through a support, and a pull wire of the displacement sensor is installed at the right end of the middle circular shaft of the linear bearing.
And the hydraulic pipeline connecting the hydraulic oil heater and the actuator cylinder test piece passes through the No. 1 test box.
Compared with the prior art, the invention has the beneficial effects that:
the invention can simulate the actual working environment of the actuating cylinder products and provides a more real simulation environment for the research and development of the actuating cylinder products; the test system is economic and safe, is convenient to implement, can provide more accurate detection results for the actuating cylinder products, optimizes quality control by utilizing effective investment in the test method, and helps enterprises to balance manufacturing economy and quality safety.
Drawings
Fig. 1 is a schematic diagram of the structure of the present invention.
In the figure: the hydraulic oil heating device comprises a hydraulic oil heater 1, a test box 2 No. 1, a servo valve I3, a test fixture 4, a loading actuator 5, a force sensor 6, a linear bearing 7, a heat insulation box 8, a displacement sensor 9, an actuator cylinder test piece 10, a temperature sensor I11, a temperature sensor II 12, an air pipe 13, an induced draft fan 14, a test box 15 No. 2, a hydraulic oil temperature controller 16, an isolation cylinder 17, a servo valve II 18, a high-pressure oil station 19, a loading oil source 20 and an MOOG controller 21.
Detailed Description
The invention is described in further detail below with reference to the following description of the drawings and the detailed description.
Referring to fig. 1, the aircraft landing gear actuator cylinder test system comprises a loading actuator 5, a loading oil source 20, an actuator cylinder test piece 10, a high-pressure oil station 19, a test box No. 12, a hydraulic oil temperature controller 16, a temperature sensor II 12, an MOOG controller 21, a servo valve I3, a servo valve II 18, a force sensor 6, a displacement sensor 9 and a test fixture 4, wherein the loading actuator 5 and the actuator cylinder test piece 10 are respectively fixed on the test fixture 4.
Referring to fig. 1, in the test system, an MOOG controller 21, a servo valve I3, a servo valve II 18, a force sensor 6, a displacement sensor 9 and a test fixture 4 form a control system; the MOOG controller 21 is respectively connected with the servo valve I3, the servo valve II 18, the force sensor 6 and the displacement sensor 9 through signal lines, the servo valve I3 and the force sensor 6 are respectively connected with the loading actuator 5, and the servo valve II 18 and the displacement sensor 9 are connected with the actuator cylinder test piece 10. The control system carries out follow-up control according to signals fed back by the force sensor 6 and the displacement sensor 9, and the purpose that the displacement of the actuator cylinder test piece 10 and the external force load applied to the actuator cylinder test piece meet test conditions is achieved.
Referring to fig. 1, a loading oil source 20 and a loading actuator 5 in the test system form a loading system, an oil outlet of the loading oil source 20 is connected with an oil inlet of a servo valve i 3 through a hydraulic pipeline, and an oil outlet of the servo valve i 3 is connected with the loading actuator 5 through a hydraulic pipeline; the loading system is mainly used for applying external force load to the actuator cylinder test piece 10 according to control signals sent by the control system.
Referring to fig. 1, in the test system, a high-pressure oil station 19, an isolation cylinder 17, a hydraulic oil heater 1, a test box No. 12, a hydraulic oil temperature controller 16 and a temperature sensor ii 12 form a hydraulic oil temperature control system. An oil outlet of the high-pressure oil station 19 is connected with an oil inlet of a servo valve II 18 through a hydraulic pipeline, two oil outlets of the servo valve II 18 are respectively connected with an isolation cylinder 17 through the hydraulic pipeline, and the two isolation cylinders 17 are respectively connected with a hydraulic oil heater 1 through the hydraulic pipeline; the hydraulic oil heater 1 is connected with the actuator cylinder test piece 10 through a hydraulic pipeline. The hydraulic oil temperature controller 16 is respectively connected with the hydraulic oil heater 1, the No. 1 test box 2 and the temperature sensor II 12 through signal lines, and the temperature sensor II 12 is arranged at a lubricating oil inlet of the actuator cylinder test piece 10. The high-pressure oil station 19 provides high-pressure lubricating oil according to a control signal sent by a control system, and the isolation cylinder 17 is mainly used for physically isolating a high-pressure lubricating oil loop in the high-pressure oil station from a high-temperature/low-temperature aviation lubricating oil loop flowing through the actuator cylinder test piece 10 and realizing real-time transmission of hydraulic pressure; the hydraulic oil heater 1 heats the aviation oil circuit of high/low temperature flowing through the actuator cylinder test piece 10. The test box No. 1 mainly provides a low-temperature environment, a section of serpentine pipeline in the aviation lubricating oil loop is placed in the test box No. 1, and the aviation lubricating oil is cooled through heat exchange; the temperature sensor II 12 measures the temperature of the lubricating oil and feeds the temperature back to the hydraulic oil temperature controller 16 to realize closed-loop control so as to meet the temperature condition of a medium (lubricating oil) of the actuator cylinder test piece.
Referring to fig. 1, the system further comprises a temperature test box No. 2 15, an induced draft fan 14, a temperature sensor I11 and an insulation box 8, wherein the temperature test box No. 2, the induced draft fan 14, the temperature sensor I11 and the insulation box 8 form a high-low temperature environment system. No. 2 temperature test case 15 pass through tuber pipe 13 and be connected with draught fan 14, draught fan 14 pass through tuber pipe 13 and be connected with insulation can 8, No. 2 temperature test case 15 pass through the signal line and be connected with temperature sensor I11, temperature sensor I11 set up in insulation can 8. During the test, the actuator cylinder test piece 10 is placed in the heat insulation box 8, and high-temperature/low-temperature air is generated in the No. 2 temperature test box 15 and is transported into the heat insulation box 8 through the air pipe 13 under the action of the induced draft fan 14. A temperature sensor I11 in the heat insulation box 8 collects real-time temperature in the heat insulation box 8 and feeds the real-time temperature back to a No. 2 temperature test box 15, and the No. 2 temperature test box 15 adjusts the temperature of air in the box according to temperature feedback to realize closed-loop control of the ambient temperature in the heat insulation box 8 so as to meet the ambient temperature condition of the actuator cylinder test piece.
Referring to fig. 1, the test fixture 4 includes a linear bearing 7, the loading actuator 5 is connected with the actuator cylinder test piece 10 through the linear bearing 7, and the linear bearing 7 can ensure that the travel paths of the actuator cylinder test piece 10 and the loading actuator 5 are coaxial again, so as to avoid damage to the loading actuator 5 and the actuator cylinder test piece 10 caused by eccentricity of the two. The force sensor 6 is arranged at the top end of the loading actuator 5, and the force sensor 6 is connected with the left end of the middle circular shaft of the linear bearing 7 on a force transmission path. The displacement sensor 9 is arranged on the shell of the actuator cylinder test piece 10 by using a bracket, and a pull wire of the displacement sensor 9 is arranged at the right end of a middle circular shaft of the linear bearing 7 by using the bracket; therefore, the change length of the pull wire is the change length of the piston rod of the actuator cylinder test piece 10, and therefore the displacement of the piston rod of the actuator cylinder test piece 10 is measured.
Referring to fig. 1, the test fixture 4 further includes a universal base and two lugs, and the actuator cylinder test piece 10 and the loading actuator 5 are connected with the two lugs through iron tips. Test requirements of test pieces with different sizes can be met by replacing double lugs with different specifications, and the whole set of test fixture 4 is subjected to calculation analysis during design, so that the strength of the test fixture 4 under strong load is ensured.
Referring to fig. 1, the hydraulic line connecting the hydraulic oil heater 1 and the ram test piece 10 passes through a test chamber No. 1 2. No. 1 proof box 2 mainly provides an environment, and the hydraulic pressure pipeline of connecting hydraulic oil heater 1 and pressurized cylinder test piece 10 passes from No. 1 proof box 2, passes partial pipeline and is the tubular metal resonator, when being low temperature environment in No. 1 proof box 2, can realize the cooling to fluid in the hydraulic pressure pipe through the heat transfer.
Referring to fig. 1, the pressure of a loading oil source 20 in the system is adjustable from 0Mpa to 21Mpa, and the force load adjustment of 0-1000KN can be realized by matching with the control of a loading actuator 5 with specifications of 10KN, 30KN, 50KN, 100KN, 500KN and 1000KN and a servo valve I3. The pressure of the high-pressure oil station 19 is adjustable from 0Mpa to 35Mpa, and the force value between the actuator cylinder test piece 10 and the loading actuator 5 can be in follow-up balance when the displacement is used as a control signal by matching with the control of the servo valve II 18. The isolation cylinder 17 can insulate temperature and not insulate pressure, and can avoid high-temperature hydraulic oil from flowing back to the oil source while pressure is normally transmitted, so that the oil source is ensured to work at normal temperature, and the requirement on high temperature resistance of the oil source is lowered. The force sensor 6 is provided with an A-B bridge, and the consistency of the axes of the loading actuator 5 and the actuator cylinder test piece 10 can be judged by observing the consistency of the force values of the A bridge and the B bridge. The hydraulic oil heater 1 can adjust the temperature of the lubricating oil from normal temperature to 200 ℃ under the flow of the lubricating oil of 10L/min, can compensate the heat loss in the process of conveying the hydraulic oil pipe, and enables the temperature of the lubricating oil of the actuating cylinder test piece 10 to meet the temperature requirement. The temperature in the effective space of the No. 1 test box 2 is adjustable from minus 70 ℃ to 150 ℃, and is adjusted through the feedback of the temperature sensor I11, so that the insulation box where the actuator cylinder test piece 10 is located reaches the environmental temperature condition. The induced draft fan 14 can be 240m3The high-temperature/low-temperature air in the warm and humid cabinet is introduced into the heat insulation cabinet 8 at the speed of/h, so that the actuator cylinder test piece 10 does not need to be integrally placed in the heat insulation cabinet, and real-time observation and operation are facilitated. The displacement and the external force load of the actuator cylinder test piece 10 can be changed according to actual needs so as to meet different working condition requirements of different products.
Referring to fig. 1, before the test, the tool is designed and processed according to the installation characteristics of the test piece, and the pressures of the actuator 5, the loading oil source 20 and the high-pressure oil station 19 are properly loaded according to the matching range of the design load of the product; adjusting the positions of a linear bearing 7 and two lugs at two ends of a test fixture 4 to enable a loading actuator 5 and an actuator cylinder test piece 10 to be on the same axis; the loading actuator 5 is preloaded to see if the A, B bridge values of the force sensor 6 are substantially identical, thereby verifying signal correctness. And (3) starting the hydraulic oil heater 1 and the test box No. 12, and setting the test temperature to ensure that the temperature of the lubricating oil passing through the actuator cylinder test piece 10 reaches the test requirement and is stable. The No. 2 test box 15 is set to the designated temperature, the induced draft fan 14 is started to introduce the high-temperature/low-temperature air in the warm box 15 into the warm box 8, and the environment temperature in the warm box 8 reaches the test requirement and is stable. And opening the loading oil source 20 and the high-pressure oil station 19, setting a loading curve, and performing combined debugging on the whole test system to ensure that the test system is reliably connected and moving parts smoothly run.
Referring to fig. 1, during formal test, the MOOG controller 21 issues a control signal to the servo valve i 3 according to a force-time spectrum, and by feedback of the force sensor 6, closed-loop control of the loading force is realized, and meanwhile, force value protection is set. The MOOG controller 21 sends a control signal to the servo valve II 18 according to a displacement-time spectrum, closed-loop control over displacement of the actuator cylinder test piece 10 is achieved through feedback of the displacement sensor 9, and meanwhile displacement protection is well set; and adjusting the PID value to enable the deviation of the force and the displacement to be within a tolerance range, so that the actuator cylinder test piece reaches a displacement and force follow-up balance state. At this point, four stress conditions of the actuator cylinder test piece 10, namely the environmental temperature, the medium temperature, the external force load and the piston displacement, are simultaneously achieved, and the specified times of extension-recovery cycles are carried out under the conditions to examine the fatigue resistance of the test piece. Therefore, the system can realize the composite durability test under four stress conditions of the environment temperature of the aircraft landing gear actuator cylinder, the medium (lubricating oil) temperature, the external force load and the piston displacement.
The foregoing is a more detailed description of the invention in connection with specific preferred embodiments and it is not intended that the invention be limited to these specific details. For those skilled in the art to which the invention relates, numerous changes, substitutions and alterations may be made without departing from the spirit of the invention, and the above described structures are deemed to be within the scope of the invention.
Claims (5)
1. An aircraft landing gear actuator cylinder test system, characterized in that: the device comprises a loading actuator (5), a loading oil source (20), an actuating cylinder test piece (10), a high-pressure oil station (19), a test box No. 1 (2), a hydraulic oil temperature controller (16), a temperature sensor II (12), an MOOG controller (21), a servo valve I (3), a servo valve II (18), a force sensor (6), a displacement sensor (9) and a test fixture (4), wherein the loading actuator (5) and the actuating cylinder test piece (10) are respectively fixed on the test fixture (4), an oil outlet of the loading oil source (20) is connected with an oil inlet of the servo valve I (3) through a hydraulic pipeline, an oil outlet of the servo valve I (3) is connected with the loading actuator (5) through a hydraulic pipeline, an oil outlet of the high-pressure oil station (19) is connected with a servo valve II (18) through a hydraulic pipeline, two oil outlets of the servo valve II (18) are respectively connected with an isolation cylinder (17) through hydraulic pipelines, the two isolation cylinders (17) are respectively connected with a hydraulic oil heater (1) through hydraulic pipelines, the hydraulic oil heater (1) is connected with the actuating cylinder test piece (10) through a hydraulic pipeline, the hydraulic oil temperature controller (16) is respectively connected with the hydraulic oil heater (1), the No. 1 test box (2) and the temperature sensor II (12) through signal lines, the temperature sensor II (12) is arranged at a lubricating oil inlet of the actuating cylinder test piece (10), the MOOG controller (21) is respectively connected with the servo valve I (3), the servo valve II (18), the force sensor (6) and the displacement sensor (9) through signal lines, the servo valve I (3) and the force sensor (6) are respectively connected with the loading actuator (5), and the servo valve II (18) and the displacement sensor (9) are connected with the actuator cylinder test piece (10).
2. An aircraft landing gear actuator test system according to claim 1, wherein: still including No. 2 temperature test case (15), draught fan (14), temperature sensor I (11) and insulation can (8), No. 2 temperature test case (15) be connected with draught fan (14) through tuber pipe (13), draught fan (14) be connected with insulation can (8) through tuber pipe (13), No. 2 temperature test case (15) passing signal line be connected with temperature sensor I (11), temperature sensor I (11) set up in insulation can (8).
3. An aircraft landing gear actuator test system according to claim 1, wherein: the test fixture (4) comprises a linear bearing (7), the loading actuator (5) and the actuating cylinder test piece (10) are connected through the linear bearing (7), the force sensor (6) is installed at the top end of the loading actuator (5), the force sensor (6) is connected with the left end of a middle circular shaft of the linear bearing (7), the displacement sensor (9) is installed on the actuating cylinder test piece (10), and a pull wire of the displacement sensor (9) is installed at the right end of the middle circular shaft of the linear bearing (7).
4. An aircraft landing gear actuator test system according to claim 3, wherein: the test fixture (4) further comprises a universal base and two lugs, and the actuating cylinder test piece (10) and the loading actuator (5) are connected with the two lugs through iron tips.
5. An aircraft landing gear actuator test system according to claim 1, wherein: and the hydraulic pipeline connecting the hydraulic oil heater (1) and the actuator cylinder test piece (10) passes through the No. 1 test box (2).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111662938.6A CN114509248A (en) | 2021-12-31 | 2021-12-31 | Aircraft undercarriage pressurized strut test system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111662938.6A CN114509248A (en) | 2021-12-31 | 2021-12-31 | Aircraft undercarriage pressurized strut test system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN114509248A true CN114509248A (en) | 2022-05-17 |
Family
ID=81547955
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111662938.6A Pending CN114509248A (en) | 2021-12-31 | 2021-12-31 | Aircraft undercarriage pressurized strut test system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114509248A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115493825A (en) * | 2022-09-23 | 2022-12-20 | 沈阳黎明航空零部件制造有限公司 | Test device and method for simulating low-temperature environment work of actuating cylinder |
| CN117387894A (en) * | 2023-12-13 | 2024-01-12 | 天津航天瑞莱科技有限公司 | Catapult-assisted take-off and arresting impact test device |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN204422209U (en) * | 2015-02-10 | 2015-06-24 | 吉林大学 | Thrust hydrodynamic journal liquid polymers reliability test bench |
| EP3109487A1 (en) * | 2015-06-26 | 2016-12-28 | SPP Canada Aircraft, Inc. | Dual locking hydraulic actuator for structural brace |
| CN107401534A (en) * | 2017-07-13 | 2017-11-28 | 江西洪都航空工业集团有限责任公司 | With the load combined fatigue experimental device of pressurized strut heat of normal temperature fluid driving |
| CN109869377A (en) * | 2017-12-01 | 2019-06-11 | 中国飞机强度研究所 | A kind of controllable uninstalling system |
| CN110985462A (en) * | 2019-12-12 | 2020-04-10 | 四川凌峰航空液压机械有限公司 | Hydraulic system for eliminating pulse test actuating cylinder and pipeline gas thereof |
| CN112834196A (en) * | 2021-02-24 | 2021-05-25 | 陕西理工大学 | Intelligent testing system for actuating cylinder |
| CN112945541A (en) * | 2021-04-08 | 2021-06-11 | 西安旭彤电子科技股份有限公司 | Special device for airplane undercarriage turning endurance test and detection method |
| CN216695547U (en) * | 2021-12-31 | 2022-06-07 | 天津航天瑞莱科技有限公司 | Aircraft undercarriage actuator cylinder test system |
-
2021
- 2021-12-31 CN CN202111662938.6A patent/CN114509248A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN204422209U (en) * | 2015-02-10 | 2015-06-24 | 吉林大学 | Thrust hydrodynamic journal liquid polymers reliability test bench |
| EP3109487A1 (en) * | 2015-06-26 | 2016-12-28 | SPP Canada Aircraft, Inc. | Dual locking hydraulic actuator for structural brace |
| CN107401534A (en) * | 2017-07-13 | 2017-11-28 | 江西洪都航空工业集团有限责任公司 | With the load combined fatigue experimental device of pressurized strut heat of normal temperature fluid driving |
| CN109869377A (en) * | 2017-12-01 | 2019-06-11 | 中国飞机强度研究所 | A kind of controllable uninstalling system |
| CN110985462A (en) * | 2019-12-12 | 2020-04-10 | 四川凌峰航空液压机械有限公司 | Hydraulic system for eliminating pulse test actuating cylinder and pipeline gas thereof |
| CN112834196A (en) * | 2021-02-24 | 2021-05-25 | 陕西理工大学 | Intelligent testing system for actuating cylinder |
| CN112945541A (en) * | 2021-04-08 | 2021-06-11 | 西安旭彤电子科技股份有限公司 | Special device for airplane undercarriage turning endurance test and detection method |
| CN216695547U (en) * | 2021-12-31 | 2022-06-07 | 天津航天瑞莱科技有限公司 | Aircraft undercarriage actuator cylinder test system |
Non-Patent Citations (1)
| Title |
|---|
| 刘春 等: "飞机起落架作动筒检测试验台的设计原理", 《航空制造技术》, 31 December 2016 (2016-12-31), pages 81 - 83 * |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115493825A (en) * | 2022-09-23 | 2022-12-20 | 沈阳黎明航空零部件制造有限公司 | Test device and method for simulating low-temperature environment work of actuating cylinder |
| CN117387894A (en) * | 2023-12-13 | 2024-01-12 | 天津航天瑞莱科技有限公司 | Catapult-assisted take-off and arresting impact test device |
| CN117387894B (en) * | 2023-12-13 | 2024-02-09 | 天津航天瑞莱科技有限公司 | Catapult-assisted take-off and arresting impact test device |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN216695547U (en) | Aircraft undercarriage actuator cylinder test system | |
| CN114509248A (en) | Aircraft undercarriage pressurized strut test system | |
| CN104535438B (en) | A kind of all Combined Fatigue Crack Propagation pilot systems of testpieces high temperature height and measuring method | |
| CN107764673B (en) | A kind of biaxial stress fatigue experimental device and test method | |
| CN101995354B (en) | Water pressure testing machine pressure balancing device and control method thereof | |
| CN213068195U (en) | Ship-borne main shaft bearing impact test equipment | |
| CN109580228B (en) | Cold test run test system for solid rocket engine | |
| CN113504048B (en) | Military turbofan engine ball bearing tester with service environment and maneuvering load simulation | |
| CN113173263A (en) | Undercarriage folding and unfolding actuator test bed | |
| CN102507164B (en) | Comprehensive quickly-disassembled clamping hoop test system | |
| CN109655346B (en) | Tunnel segment longitudinal force simulation application device and method | |
| CN107328588B (en) | Mud testing machine for front axle knuckle bearing of automobile | |
| RU2701473C1 (en) | Mechanical thermal compensator test bench | |
| CN110173472B (en) | Hydraulic system of wind power gear box flexible pin shaft test bench and control method thereof | |
| CN105651639A (en) | Inverted type piston thermal fatigue testing device | |
| CN113588473B (en) | High-temperature high-pressure water environment fretting wear test device and test method | |
| CN109060578B (en) | Thermal fatigue testing device for cylinder cover of diesel engine | |
| CN115144128A (en) | Measurement and control system and method for leakage characteristic evaluation of spacecraft porous sealing material | |
| CN102157101B (en) | Multifunctional thermodynamic analogue experimental machine | |
| CN205280391U (en) | Auto -lock swing hydraulic press performance testing platform | |
| CN114858450A (en) | Device and method for testing service life of joint bearing loaded by air pressure | |
| CN110589019B (en) | Force loading method and loading device for high-speed retraction and extension test of undercarriage | |
| CN112903276A (en) | Open turbine blade test equipment | |
| Yin | High Speed Pneumatic Theory and Technology Volume I: Servo System | |
| CN106153318A (en) | Precise bushing valve couple performance test measurement apparatus |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination |