CN117302547A - Amphibious aircraft landing gear sediment water impact verification test method - Google Patents
Amphibious aircraft landing gear sediment water impact verification test method Download PDFInfo
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- CN117302547A CN117302547A CN202311521433.7A CN202311521433A CN117302547A CN 117302547 A CN117302547 A CN 117302547A CN 202311521433 A CN202311521433 A CN 202311521433A CN 117302547 A CN117302547 A CN 117302547A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
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Abstract
The invention discloses a sediment water impact verification test method for an amphibious aircraft landing gear. Step 1, simulating the real installation state of the nose landing gear through a test fixture to install the nose landing gear, and determining the retraction state of the landing gear; step 2, checking whether the undercarriage to be tested meets test requirements, installing a sensor and a stress foil, and normally coating lubricating grease on the movable part of the undercarriage; step 3, simulating sediment-containing water in an impact test; step 4, simulating a hydraulic pressure value of an impact test; step 5, setting the water impact time of the impact test; step 6, setting the shape of the water flow of the impact test; step 7, completing an impact test under preset water pressure and water flow speed, and checking and recording in the test process; and 8, resetting the water pressure, the water flow speed and the like, repeatedly executing the step 7 until the required impact measurement points are all completed, and ending the test. The landing gear safety control method can effectively improve the safety of the landing gear under severe water environment.
Description
Technical Field
The invention belongs to the field of amphibious aircraft landing gear structural design, and particularly relates to a sediment water impact verification test method for an amphibious aircraft landing gear.
Background
Landing gear is subjected to the impact of water flow during landing gear flushing, which is carried out by an amphibious aircraft during ground sliding and launching, landing gear sliding and retraction in water, landing gear landing and the like, in order to eliminate the influence of particle impurities in water on landing gear abrasion. The quality (clean and turbid) of running water and the impact force of the running water influence the surface protection of the landing gear, the adhesion state of lubricating grease at the movable part, the installation state of a sensor on the landing gear and the cleaning degree of a gap of the landing gear, and all the influences need to be evaluated by carrying out landing gear water impact theoretical analysis and experimental research.
Disclosure of Invention
Aiming at the problems, the invention provides a test method for verifying the sediment water impact of the amphibious aircraft landing gear, which realizes the waterproof sealing of the landing gear structure and the test verification of the corrosion resistance of the retraction jack through the targeted water environment evaluation and analysis of the landing gear, and effectively improves the reliability of the amphibious aircraft landing gear structure and equipment thereof under the water impact. Through silt water impact test, the service life of the landing gear can be accurately measured.
The technical proposal is that. An amphibious aircraft landing gear sediment water impact verification test method comprises the following steps:
step 1, simulating the real installation state of the nose landing gear through a test fixture to install the nose landing gear, and determining the retraction state of the landing gear;
step 2, checking whether the undercarriage to be tested meets test requirements, installing a sensor and a stress foil, and normally coating lubricating grease on the movable part of the undercarriage;
step 3, simulating sediment-containing water in an impact test;
step 4, simulating a hydraulic pressure value of an impact test;
step 5, setting the water impact time of the impact test;
step 6, setting the shape of the water flow of the impact test;
step 7, completing an impact test under preset water pressure and water flow speed, and checking and recording in the test process;
and 8, resetting the water pressure, the water flow speed and the like, repeatedly executing the step 7 until the required impact measurement points are all completed, and ending the test.
In the amphibious aircraft landing gear sediment water impact verification test method, before the step 1 is carried out, input values of water pressure, water flow speed and impact direction to be measured are determined to simulate a real landing gear water retraction state.
In the above test method for verifying the impact of the sediment water on the landing gear of the amphibious aircraft, in the step 3, the water turbidity of the sediment water is 71.2, and the granularity D97 is 92.65.
In the above test method for verifying the sediment water impact of the amphibious aircraft landing gear, in step 4, when the impact test water pressure is simulated, the surface pressure of the landing gear is superposed with the impact pressure according to the aircraft flight speed and the water flow speed.
In the above test method for verifying the sediment water impact of the amphibious aircraft landing gear, in the step 5, the impact time is 1.5 times of the longest time from the launching of the aircraft to the retraction/lowering of the landing gear in water to the landing of the amphibious aircraft.
In the test method for verifying sediment water impact of the amphibious aircraft landing gear, in the step 6, the landing gear is impacted by columnar water flow at the position below the aircraft waterline and is impacted by mist water flow at the position above the aircraft waterline.
In the above-mentioned amphibious aircraft landing gear silt water impact verification test method, in step 7, the checking and recording includes:
1) Checking and recording the falling time and state of the lubricating grease in the test process;
2) The landing gear surface wear is checked and recorded after the test is finished;
3) Checking and recording the blocking or blocking condition of mud and sand penetrating into cracks, pores, bearings, joints and the like after the test is finished;
4) After the test is finished, the sensor is electrified to check the function condition;
5) And (5) checking the retraction function condition of the landing gear after the test is ended.
In the amphibious aircraft landing gear sediment water impact verification test method, landing gear water impact test programs and methods are formed through landing gear water impact tests, evaluation and calculation are carried out through sensor and deformation sheet measurement, and waterproof sealing of the structure and test verification of corrosion resistance of a retracting mechanism are achieved.
In the amphibious aircraft landing gear sediment water impact verification test method, the evaluation and calculation comprises the following steps:
1) Evaluating the influence of landing gear water impact on landing gear surface protection, movable part lubricating grease and sensors;
2) Evaluating the surface protection and sealing tolerance of the landing gear device under the impact of silt water;
3) And evaluating the blocking or blocking condition of sediment infiltration into cracks, pores, bearings, joints and the like.
The beneficial effects are that: the landing gear to be tested completely simulates the real installation state and the water impact state of the water flying landing gear, and forms a landing gear water impact test program and a landing gear water impact test method. According to the test method, parameters such as landing gear state, water gun outlet pressure, water flow, water gun and landing gear distance, impact direction, impact time, water turbidity of impact water flow, granularity and the like in a landing gear water impact test are determined to form a landing gear water impact test program and method, so that a sediment-containing water impact test of the landing gear of the amphibious aircraft is simulated, and the following effects can be evaluated according to a water impact test recording result: 1) The impact of landing gear water impact on landing gear surface protection, movable part lubricating grease and sensors; 2) The landing gear device has the capability of protecting and sealing the surface under the impact of silt water; 3) Silt permeates cracks, pores, bearings, joints and other blocked or plugged conditions; and further verifies the waterproof sealing of the landing gear structure and the corrosion resistance of the retracting mechanism under the water flow impact environment. According to the invention, the waterproof sealing of the structure and the corrosion resistance test verification of the retracting mechanism are realized through the landing gear structure water impact test, so that the safety of the landing gear under severe water environment can be effectively improved, and the support is provided for the verification and identification of the water environment applicability of the landing gear system and equipment thereof.
In conclusion, through targeted landing gear water environment evaluation and analysis, the invention realizes the waterproof sealing of the landing gear structure and the test verification of the corrosion resistance of the retraction jack, and effectively improves the reliability of the amphibious aircraft landing gear structure and equipment thereof under the impact of water flow. Through silt water impact test, the service life of the landing gear can be accurately measured.
Drawings
FIG. 1 is a schematic layout of a water impact test.
Detailed Description
Referring to fig. 1, a complete landing gear water impact test program and method are formed to simulate an amphibious aircraft landing gear sediment-containing water impact test, and the landing gear reliability performance is evaluated and verified through the test, wherein the specific test is carried out according to the following steps:
before step 1, a plurality of input values such as water pressure, water flow speed, impact direction and the like which need to be measured are determined to simulate the real water retraction state of the landing gear, and the landing gear is ensured to be retracted and extended under the allowable most severe water flow speed, so that the reliability of test results is ensured. The water parameter test and investigation are carried out on three water areas such as a Jinmen-Zhanghe airport, an Shanghai-Jinshan airport, a Qingdao-Tuo island airport and the like to obtain the silt water parameter value so as to ensure the accuracy of experimental results.
Step 1, simulating the real installation state of the nose landing gear through a test fixture to install the nose landing gear, and enabling the landing gear to be in a down locking position;
step 2, checking that the undercarriage to be tested is complete in structure and normal in retraction function, installing a front wheel steering hydraulic pipeline, a steering angle sensor and other typical position sensors, and normally coating lubricating grease on a movable position;
step 3, simulating impact test to obtain sediment-containing water, wherein the turbidity of the water is 71.2, and the granularity D97 is 92.65;
step 4, simulating impact test water pressure, wherein the surface pressure of the undercarriage is characterized by superposing impact pressure according to the flight speed (18 km/h) of the aircraft and the water flow speed (1 section of maximum ocean current) through a pressure sensor on a buffering strut of the undercarriage;
step 5, calculating the water impact time of an impact test, wherein the impact time is 1.5 times of the maximum time (1.5×15 min=22.5 min) when the aircraft is launched into the landing gear water to be retracted or the landing gear water to be launched off the water;
step 6, simulating the water flow shape of an impact test, wherein the landing gear is impacted by columnar water flow (corresponding to a direct-current water gun) at a position below the water line of the aircraft, and is impacted by mist water flow (corresponding to a mist water gun) above the water line of the aircraft;
step 7, completing an impact test under a certain water pressure and water flow speed, and checking and recording in the test process;
and 8, re-determining the water pressure, the water flow speed, the impact direction and the like, and repeatedly executing the step 7 until the required impact measurement points are all completed, and ending the test.
Preferably, the checking and recording in the test procedure in step 7 mainly includes the following:
1) Checking and recording the falling time and state of the lubricating grease in the test process;
2) The landing gear surface wear is checked and recorded after the test is finished;
3) Checking and recording the blocking or blocking condition of mud and sand penetrating into cracks, pores, bearings, joints and the like after the test is finished;
4) After the test is finished, the sensor is electrified to check the function condition;
5) And (5) checking the retraction function condition of the landing gear after the test is ended.
The landing gear water impact test program and method are formed through the landing gear water impact test, and under the preferred mode, the water-proof sealing of the structure and the corrosion-resistant test verification of the retracting mechanism are realized through evaluation and calculation by the measurement of the sensor, the deformation sheet and the like. The verification method evaluation mainly comprises the following steps:
1) Evaluating the influence of landing gear water impact on landing gear surface protection, movable part lubricating grease and sensors;
2) Evaluating the surface protection and sealing tolerance of the landing gear device under the impact of silt water;
3) And evaluating the blocking or blocking condition of sediment infiltration into cracks, pores, bearings, joints and the like.
The foregoing is only a preferred embodiment of the present invention, but the scope of the present invention is not limited thereto, and any person skilled in the art, who is within the scope of the present invention, should be covered by the protection scope of the present invention by making equivalents and modifications to the technical solution and the inventive concept thereof.
Claims (9)
1. The method for verifying and testing the sediment water impact of the landing gear of the amphibious aircraft is characterized by comprising the following steps of:
step 1, simulating the real installation state of the nose landing gear through a test fixture to install the nose landing gear, and determining the retraction state of the landing gear;
step 2, checking whether the undercarriage to be tested meets test requirements, installing a sensor and a stress foil, and normally coating lubricating grease on the movable part of the undercarriage;
step 3, simulating sediment-containing water in an impact test;
step 4, simulating a hydraulic pressure value of an impact test;
step 5, setting the water impact time of the impact test;
step 6, setting the shape of the water flow of the impact test;
step 7, completing an impact test under preset water pressure and water flow speed, and checking and recording in the test process;
and 8, resetting the water pressure, the water flow speed and the like, repeatedly executing the step 7 until the required impact measurement points are all completed, and ending the test.
2. The amphibious aircraft landing gear silt water impact test method according to claim 1, wherein before step 1 is carried out, input values of water pressure, water flow speed and impact direction to be measured are determined to simulate a real landing gear water retraction state.
3. The amphibious aircraft landing gear silt water impact test method according to claim 1, wherein in the step 3, the water turbidity of silt water is 71.2, and the granularity D97 is 92.65.
4. The amphibious aircraft landing gear silt water impact test method according to claim 1, wherein in the step 4, when the impact test water pressure is simulated, the landing gear surface pressure superimposes the impact pressure according to the aircraft flight speed and the water flow speed.
5. An amphibious aircraft landing gear silt water impact test method according to claim 1, wherein in step 5, the impact time is 1.5 times the longest time for the aircraft to launch into the landing gear water to stow/drop down and then to land off the water.
6. The amphibious aircraft landing gear sediment water impact verification test method according to claim 1, wherein in step 6, the landing gear is impacted by columnar water flow at a position below an aircraft waterline and impacted by mist water flow at a position above the aircraft waterline.
7. A method of testing for the impact of silt and water on landing gear of an amphibious aircraft according to claim 1, wherein in step 7, the checking and recording comprises:
1) Checking and recording the falling time and state of the lubricating grease in the test process;
2) The landing gear surface wear is checked and recorded after the test is finished;
3) Checking and recording the blocking or blocking condition of mud and sand penetrating into cracks, pores, bearings, joints and the like after the test is finished;
4) After the test is finished, the sensor is electrified to check the function condition;
5) And (5) checking the retraction function condition of the landing gear after the test is ended.
8. The amphibious aircraft landing gear silt water impact verification test method according to claim 1, wherein landing gear water impact test procedures and methods are formed through landing gear water impact tests, evaluation and calculation are carried out through sensor and deformation sheet measurement, and test verification of waterproof sealing of the structure and corrosion resistance of a retraction jack is achieved.
9. The amphibious aircraft landing gear silt and water impact test method according to claim 8, wherein the evaluation and calculation comprises:
1) Evaluating the influence of landing gear water impact on landing gear surface protection, movable part lubricating grease and sensors;
2) Evaluating the surface protection and sealing tolerance of the landing gear device under the impact of silt water;
3) And evaluating the blocking or blocking condition of sediment infiltration into cracks, pores, bearings, joints and the like.
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| CN202311521433.7A CN117302547A (en) | 2023-11-15 | 2023-11-15 | Amphibious aircraft landing gear sediment water impact verification test method |
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| CN202311521433.7A CN117302547A (en) | 2023-11-15 | 2023-11-15 | Amphibious aircraft landing gear sediment water impact verification test method |
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20090006056A1 (en) * | 2007-06-26 | 2009-01-01 | Horner Darrell W | Closed-loop cabin pressure control system test method with actual pressure feedback |
| KR20140040510A (en) * | 2012-09-26 | 2014-04-03 | 한국항공우주산업 주식회사 | Aircraft waterproofness test system |
| US20160363505A1 (en) * | 2015-06-12 | 2016-12-15 | The Boeing Company | Wind tunnel for erosion testing |
| RU2678540C1 (en) * | 2017-12-27 | 2019-01-29 | Федеральное государственное унитарное предприятие "Государственный научно-исследовательский институт авиационных систем" (ФГУП "ГосНИИАС") | Aircraft airframe and the landing gear technical condition monitoring method and device and device for its implementation |
| CN113932976A (en) * | 2021-12-17 | 2022-01-14 | 中国飞机强度研究所 | Airplane rain test control system and control method |
-
2023
- 2023-11-15 CN CN202311521433.7A patent/CN117302547A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20090006056A1 (en) * | 2007-06-26 | 2009-01-01 | Horner Darrell W | Closed-loop cabin pressure control system test method with actual pressure feedback |
| KR20140040510A (en) * | 2012-09-26 | 2014-04-03 | 한국항공우주산업 주식회사 | Aircraft waterproofness test system |
| US20160363505A1 (en) * | 2015-06-12 | 2016-12-15 | The Boeing Company | Wind tunnel for erosion testing |
| RU2678540C1 (en) * | 2017-12-27 | 2019-01-29 | Федеральное государственное унитарное предприятие "Государственный научно-исследовательский институт авиационных систем" (ФГУП "ГосНИИАС") | Aircraft airframe and the landing gear technical condition monitoring method and device and device for its implementation |
| CN113932976A (en) * | 2021-12-17 | 2022-01-14 | 中国飞机强度研究所 | Airplane rain test control system and control method |
Non-Patent Citations (1)
| Title |
|---|
| 罗琳胤等: "水陆两栖飞机起落架水环境适应性验证要求与方法", 装备环境工程, vol. 20, no. 1, 31 January 2023 (2023-01-31), pages 37 * |
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