CN216343106U - Airplane hook load test equipment - Google Patents
Airplane hook load test equipment Download PDFInfo
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- CN216343106U CN216343106U CN202123183505.0U CN202123183505U CN216343106U CN 216343106 U CN216343106 U CN 216343106U CN 202123183505 U CN202123183505 U CN 202123183505U CN 216343106 U CN216343106 U CN 216343106U
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Abstract
The utility model provides a load test device for a plane hook, and belongs to the technical field of aviation repair equipment. The equipment comprises a hydraulic station, a pressure control system, a hydraulic gauge, a pressure numerical gauge, an electric control system, a hydraulic cylinder and a pull pressure sensor. The hydraulic system realizes the up-and-down stretching action by driving the hydraulic cylinder, simplifies the control of the load by the electric pump, transmits the load value through the tension pressure sensor, displays the load value on the digital display meter without conversion, and improves the working efficiency; the overall structural strength of the equipment meets the safety requirement of 1.5 times of rated load; the hydraulic system increases the pressurize function, can realize that the load is static, makes the test result more accurate. The utility model can be used for the tensile test of the hook of the airplane with larger load of 0-8 tons, has quick response in the test process, strong test controllability, simple structure, convenient operation, compact integral structure and small occupied area, and is used for the tensile load test of the hook of different types.
Description
Technical Field
The utility model belongs to the technical field of aviation repair equipment, and relates to a load test device for an airplane hook.
Background
When a loading test of a hook of a coach airplane is carried out, one end of the hook needs to be fixed, the other end of the hook needs to be loaded and stretched by equipment, the maximum load is 8 tons, the existing loading test equipment is continuously used for other types of equipment, a hydraulic system for driving a hydraulic cylinder to stretch up and down by a traditional hand pump is controlled, the maximum loading numerical value cannot meet the requirement, the tension value needs to be obtained by converting the pressure of a hydraulic gauge in the test process, and the working efficiency is low; the hydraulic pipeline system is complicated and laggard, is easy to damage after long-term use, and is frequently and complexly maintained; the hydraulic system is not provided with pressure maintaining, the load cannot be kept static, and the error of the test result is large; the whole system has no safety protection measures, and serious potential safety hazards exist in the test process. Based on the above, the utility model provides a load test device for an airplane hook.
SUMMERY OF THE UTILITY MODEL
In order to solve the problems, the utility model provides a load test device for an airplane hook, which takes an electro-hydraulic station as a power source and can realize a large-load tensile test; the load value is transmitted through the tension and pressure sensor and displayed on the digital display meter; the overall structural strength of the equipment meets the safety requirement of 1.5 times of rated load; after the load target value is reached, the indicating value can be made to be static by controlling the hydraulic station, so that the test result is more accurate; the safety valve is arranged in the hydraulic station, so that the hydraulic station is prevented from being damaged by overlarge pressure, and the safety performance of equipment is improved; meanwhile, a hydraulic instrument calibration interface is additionally arranged, so that the hydraulic instrument can be calibrated without disassembly, and the later calibration work is optimized.
The technical scheme of the utility model is as follows:
the utility model provides an aircraft is hung bullet hook load test equipment, includes hydraulic pressure station 1, pressure control system 2, hydraulic pressure table 3, pressure numerical value table 4, electrical system 5, pneumatic cylinder 7, draws pressure sensor 8, protection housing 9 and experimental mount 10.
The hydraulic station 1 includes a motor 11, a gear pump 12, an oil tank 13, a hydraulic line, an overflow valve 14, an electromagnetic directional valve 15, an oil filter 16, and an air cleaner 17. Wherein, the motor 11 controls the gear pump 12 to provide oil power, and the oil tank 13 provides oil; the hydraulic pipeline is used as an oil liquid circulation pipeline; the relief valve 14 regulates the oil pressure; the electromagnetic directional valve 15 controls the oil pressure direction; an oil filter 16 and an air filter 17 are provided on the tank 13 for filtering oil impurities and filtering impurities in the air entering the tank, respectively.
The pressure control system 2, the hydraulic pressure meter 3 and the electric control system 5 are all connected with the hydraulic station 1; the pressure control system 2 comprises an overflow valve and a ball valve switch and is used for controlling the pressure of the hydraulic station and keeping static pressure; the electric control system 5 comprises a power line and a change-over switch and is used for controlling a motor and an electromagnetic reversing valve in the hydraulic station; the hydraulic gauge 3 is used to measure and display the hydraulic station pressure.
The cabinet door 6 surrounds the hydraulic station 1, the hydraulic cylinder 7 and the pull pressure sensor 8 in the middle; the hydraulic cylinder 7 is connected with the hydraulic station 1, and the piston rod of the hydraulic cylinder 7 is controlled to stretch and retract through the hydraulic station 1; the pull pressure sensor 8 is used for transmitting load and displaying the load on the pressure numerical table 4, one end of the pull pressure sensor is connected with a piston rod of the hydraulic cylinder 7, and the other end of the pull pressure sensor is connected with the airplane hook; the airplane hanging elastic hook is fixed on a test fixing frame 10, the test fixing frame 10 is arranged above the hydraulic cylinder 7, and a protective housing 9 is arranged on the test fixing frame.
Furthermore, the equipment comprises a hydraulic instrument checking interface connected with the hydraulic meter and used for checking; the device has the functions of safety alarm and emergency stop.
Further, a liquid level meter 18 is arranged on the oil tank 13 and used for monitoring the oil quantity of the oil tank.
Further, the cabinet door 6 is made of a Q235 iron plate and used for protecting the hydraulic station.
Further, the protective housing 9 is made of a Q235 iron plate and used for protecting the test fixing frame.
Further, the test fixing frame 10 is made of chrome manganese steel and used for fixing the airplane hook.
The utility model has the beneficial effects that: according to the airplane hook load test equipment, the hydraulic system realizes vertical stretching action by driving the hydraulic cylinder, the electric pump is used for simplifying load control, the load value is transmitted by the tension pressure sensor and displayed on the digital display meter, conversion is not needed, and the working efficiency is improved; the overall structural strength of the equipment meets the safety requirement of 1.5 times of rated load; the hydraulic system is added with a pressure maintaining function, so that the static load can be realized, and the test result is more accurate; the safety alarm and emergency stop functions are added, so that the safety performance of the equipment is improved; meanwhile, a hydraulic instrument calibration interface is additionally arranged, so that the hydraulic instrument can be calibrated without disassembly, and the later calibration work is optimized. The utility model can be used for the tensile test of the airplane hook with a large load of 0-8 tons, has the advantages of quick response in the test process, strong test controllability, simple structure, convenient operation, compact integral structure and small occupied area, and can be used for the tensile load test of the hook hooks of different types.
Drawings
Fig. 1 is a front view of the present invention.
Fig. 2 is a left side view of the present invention.
Fig. 3 is a top view of the present invention.
Fig. 4 is a structure view of the test fixture.
Fig. 5 is a hydraulic schematic of the present invention.
In the figure: 1, a hydraulic station; 2 a pressure control system; 3, a hydraulic gauge; 4 pressure value table; 5, an electric control system; 6, a cabinet door; 7, a hydraulic cylinder; 8, pulling the pressure sensor; 9, a housing; 10, testing a fixed frame; 11, a motor; 12 gear pumps; 13 an oil tank; 14 relief valves; 15 an electromagnetic directional valve; 16 oil filters; 17 an air cleaner; 18 liquid level meter.
Detailed Description
The following further explains embodiments of the present invention with reference to the examples and the drawings.
As shown in fig. 1-3, an airplane hook load test device comprises a hydraulic station 1, a pressure control system 2, a hydraulic pressure meter 3, a pressure value meter 4, an electric control system 5, a cabinet door 6, a hydraulic cylinder 7, a pull pressure sensor 8, a housing 9 and a test fixing frame 10.
The hydraulic station 1 includes a motor 11, a gear pump 12, an oil tank 13, a hydraulic line, an overflow valve 14, an electromagnetic directional valve 15, an oil filter 16, and an air cleaner 17. Wherein, the motor 11 controls the gear pump 12 to provide oil power, and the oil tank 13 provides oil; the hydraulic pipeline is used as an oil liquid circulation pipeline; the relief valve 14 regulates the oil pressure; the electromagnetic directional valve 15 controls the oil pressure direction; an oil filter 16 and an air filter 17 are provided on the tank 13 for filtering oil impurities and filtering impurities in the air entering the tank, respectively. The pressure control system 2, the hydraulic pressure meter 3 and the electric control system 5 are connected with the hydraulic station 1.
The cabinet door 6 surrounds the hydraulic station 1, the hydraulic cylinder 7 and the pull pressure sensor 8 in the middle; wherein, the hydraulic cylinder 7 is connected with the hydraulic station 1; one end of the pull pressure sensor 8 is connected with a piston rod of the hydraulic cylinder 7, and the other end is connected with the airplane hook; the airplane hook is arranged on a test fixing frame 10, the test fixing frame 10 is arranged above the hydraulic cylinder 7, and a protective housing 9 is covered on the test fixing frame 10.
When the test device is used, one end of an airplane hook of a tested product is fixed with the test fixing frame 10, the other end of the airplane hook is fixed on a pulling pressure sensor 8 connected with the hydraulic cylinder 7, the hydraulic station 1 is started through the electric control system 5, and the hydraulic station 1 is controlled to drive the hydraulic cylinder 7 to pull the airplane hook to complete a load test action; when the pressure value table 4 shows that the required load is achieved, the hydraulic station 1 is controlled through the pressure control system 2, the load is made to be static, and the test state of the product hanging elastic hook is observed.
Claims (5)
1. The airplane hook load test equipment is characterized by comprising a hydraulic station (1), a pressure control system (2), a hydraulic pressure meter (3), a pressure numerical value meter (4), an electric control system (5), a hydraulic cylinder (7), a pull pressure sensor (8) and a test fixing frame (10);
the hydraulic station (1) comprises a motor (11), a gear pump (12), an oil tank (13), a hydraulic pipeline, an overflow valve (14) and an electromagnetic directional valve (15); wherein, the motor (11) controls the gear pump (12) to provide oil power, and the oil tank (13) provides oil; the hydraulic pipeline is used as an oil liquid circulation pipeline; the overflow valve (14) adjusts the oil pressure; the electromagnetic directional valve (15) controls the direction of oil pressure;
the pressure control system (2), the hydraulic gauge (3) and the electric control system (5) are all connected with the hydraulic station (1); the pressure control system (2) comprises an overflow valve and a ball valve switch and is used for controlling the pressure of the hydraulic station and keeping static pressure; the electric control system (5) comprises a power line and a change-over switch, and is used for controlling a motor and an electromagnetic directional valve in the hydraulic station; the hydraulic gauge (3) is used for measuring and displaying the pressure of the hydraulic station;
the cabinet door (6) surrounds the hydraulic station (1), the hydraulic cylinder (7) and the pull pressure sensor (8) in the middle; the hydraulic cylinder (7) is connected with the hydraulic station (1), and a piston rod of the hydraulic cylinder (7) is controlled to stretch and retract through the hydraulic station (1); the pull pressure sensor (8) is used for transmitting load and displaying the load on the pressure numerical value meter (4), one end of the pull pressure sensor is connected with a piston rod of the hydraulic cylinder (7), and the other end of the pull pressure sensor is connected with the airplane hook; the airplane hanging elastic hook is fixed on a test fixing frame (10), and the test fixing frame (10) is arranged above the hydraulic cylinder (7).
2. An aircraft hook latch load test device according to claim 1, wherein the device is further provided with a hydraulic instrument calibration interface connected with a hydraulic meter for calibration.
3. An aircraft hook-and-loop load testing apparatus according to claim 1 or 2, wherein said tank (13) is provided with an oil filter (16) and an air filter (17) for filtering oil contaminants and for filtering contaminants in the air entering the tank, respectively; and a liquid level meter (18) is arranged on the oil tank (13) and used for monitoring the oil quantity of the oil tank.
4. An aircraft hook-and-loop load testing device according to claim 1 or 2, characterized in that the test fixture (10) is provided with a protective cover (9) for protecting the test fixture.
5. An aircraft hook-and-loop load testing device according to claim 3, characterized in that the test holder (10) is provided with a protective cover (9) for protecting the test holder.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202123183505.0U CN216343106U (en) | 2021-12-17 | 2021-12-17 | Airplane hook load test equipment |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202123183505.0U CN216343106U (en) | 2021-12-17 | 2021-12-17 | Airplane hook load test equipment |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN216343106U true CN216343106U (en) | 2022-04-19 |
Family
ID=81165448
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202123183505.0U Active CN216343106U (en) | 2021-12-17 | 2021-12-17 | Airplane hook load test equipment |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN216343106U (en) |
-
2021
- 2021-12-17 CN CN202123183505.0U patent/CN216343106U/en active Active
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