CN218330495U - Whole oil tank vibration test device - Google Patents
Whole oil tank vibration test device Download PDFInfo
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- CN218330495U CN218330495U CN202222705472.XU CN202222705472U CN218330495U CN 218330495 U CN218330495 U CN 218330495U CN 202222705472 U CN202222705472 U CN 202222705472U CN 218330495 U CN218330495 U CN 218330495U
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Abstract
The application belongs to the field of test verification of an aviation power system, and particularly relates to a vibration test device for an integral oil tank, which comprises a vibration table, wherein a test fixture is arranged at the top of the vibration table, and the vibration table is used for providing vibration for the test fixture; the test fixture is arranged at the top end of the vibration table and connected with a test piece; the high and low temperature environment box is covered on the test fixture, the lower surface of the high and low temperature environment box is supported by the bracket, the lower surface of the high and low temperature environment box is provided with a mounting hole, and the test fixture is arranged in the high and low temperature environment box through the mounting hole; an air channel device is arranged on the inner wall surface of the high-low temperature environment box, a cooling medium is introduced into the air channel device, the cooling medium is connected with a flow valve, and the temperature of the high-low temperature environment box is adjusted by adjusting the flow valve; the high-low temperature environment tank is also provided with a resistance wire, the resistance wire is used for heating the high-low temperature environment tank, and the device realizes the vibration test of the engine oil tank.
Description
Technical Field
The application belongs to the field of test verification of an aviation power system, and particularly relates to a vibration test device for an integral oil tank.
Background
The fuel tank vibration test is one of effective modes for simulating a flight environment and testing the reliability and the sealing durability of the whole fuel tank structure of an airplane, and relevant requirements on the amplitude, the frequency and the like of the airplane fuel tank vibration test are made in the section of the fuel tank test in the airworthiness standard of a certain transport airplane. Because the real service condition of oil tank is simulated during the oil tank vibration test, the test piece must be equipped with 2/3 oil tank capacity water or other suitable test liquid (such as aviation kerosene) in, to being equipped with test liquid, the oil tank test box section that size and weight are all bigger, how to accomplish the experiment smoothly on the vibration test bench, reach the sealing performance verification purpose, need the experimental apparatus of an integral oil tank, to different vibrations, the test result under the different temperatures.
SUMMERY OF THE UTILITY MODEL
In order to solve the above problem, the present application provides a whole oil tank vibration test device, includes:
the test fixture is mounted at the top of the vibration table, and the vibration table is used for providing vibration for the test fixture;
the test fixture is arranged at the top end of the vibration table and is connected with a test piece;
the high and low temperature environment box is covered on the test fixture, the lower surface of the high and low temperature environment box is supported by the bracket, the lower surface of the high and low temperature environment box is provided with a mounting hole, and the test fixture is arranged in the high and low temperature environment box through the mounting hole;
an air channel device is arranged on the inner wall surface of the high-low temperature environment box, a cooling medium is introduced into the air channel device, the cooling medium is connected with a flow valve, and the temperature of the high-low temperature environment box is adjusted by adjusting the flow valve; the high-low temperature environment box is also provided with a resistance wire which is used for heating the high-low temperature environment box.
Preferably, a plurality of acceleration sensors are arranged on the test piece and the test fixture; the acceleration sensor is connected with the vibration controller; the vibration control instrument is connected with a computer, and the computer is connected with the vibration table through a power amplifier.
Preferably, the high-low temperature environment box is provided with a temperature sensor, the temperature sensor is connected with a controller, and the controller controls the flow valve and the resistance wire through signals of the temperature sensor.
Preferably, the test fixture has two clamping plates, the test piece being clamped between the two clamping plates; the acceleration sensor is arranged on the upper wall surface and the lower wall surface of the clamping plate and is used as an input sensor; the acceleration sensor is arranged on the test piece and used as an output sensor; wherein the value of the input sensor is a theoretical analysis value, and the value of the output sensor is a test adjustment value.
Preferably, the input sensors are centered on the lower surface of the test piece and distributed along the length direction; the input sensors are arranged at one end of the upper surface of the test piece and distributed along the width direction.
Preferably, for small-sized airplanes, the whole oil tank box section is selected as a test piece, and for large-sized and medium-sized airplanes, a typical structure of the oil tank is simulated for model making.
Preferably, the test piece has a test liquid therein in a volume of 2/3 of the test piece volume.
Preferably, the test liquid comprises water or jet fuel.
The advantages of the present application include: the device has a clamp corresponding to a test piece and a sensor arranged on the test clamp, and can complete the functions of an input sensor and an output sensor, and the device has the function of temperature regulation and can complete the test result of the test piece at each required temperature; can examine oil tank seal structure smoothly through this application in flight vibration environment, have and probably appear can arousing the damage or the deformation of fuel leakage, reach the sealed reliability verification purpose of oil tank design, to the aircraft structural design who has the requirement of verification of seaworthiness, can accomplish oil tank seaworthiness conformance verification smoothly simultaneously.
Drawings
FIG. 1 is a schematic diagram of a connection form of a test piece and a test bed of the integral oil tank vibration test device.
FIG. 2 is a schematic diagram of a test control wiring frame of the integral fuel tank vibration test device.
Fig. 3 is a schematic diagram of the bonding position of an acceleration sensor of the integral fuel tank vibration testing device.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the accompanying drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all embodiments of the present application. The embodiments described below with reference to the drawings are exemplary and intended to be used for explaining the present application, and should not be construed as limiting the present application. All other embodiments obtained by a person of ordinary skill in the art without any inventive work based on the embodiments in the present application are within the scope of protection of the present application. Embodiments of the present application will be described in detail below with reference to the drawings.
The application provides a whole oil tank vibration test device, as shown in figure 1, includes:
the test fixture comprises a vibration table 3, a test fixture 2 is mounted at the top of the vibration table 3, and the vibration table 3 is used for providing vibration for the test fixture 2;
the test fixture 2 is arranged at the top end of the vibration table 3, and the test fixture 2 is connected with a test piece 1;
the high and low temperature environment box 4 is covered on the test fixture 2, the lower surface of the high and low temperature environment box 4 is supported by a bracket, the lower surface of the high and low temperature environment box 4 is provided with a mounting hole, and the test fixture 2 is arranged in the high and low temperature environment box 4 through the mounting hole;
an air channel device is arranged on the inner wall surface of the high-low temperature environment box 4, a cooling medium is introduced into the air channel device, the cooling medium is connected with a flow valve, and the temperature of the high-low temperature environment box 4 is adjusted by adjusting the flow valve; the high-low temperature environment box 4 is also provided with a resistance wire which is used for heating the high-low temperature environment box 4. The device aims to enable a vibration test to simulate the environment where an oil tank is located in the flying process more truly and effectively, the test piece 1 is placed in the high-low temperature environment box 4 for the vibration test, the temperature range of the high-low temperature environment box 4 needs to meet the normal use temperature range of an airplane, 70 ℃ is generally selected as the high-temperature environment temperature, 55 ℃ below zero is selected as the low-temperature environment temperature, the high-temperature environment temperature is heated through a resistance wire, and the low-temperature environment temperature is cooled through liquid nitrogen.
A plurality of acceleration sensors are arranged on the test piece 1 and the test fixture 2; the acceleration sensor is connected with the vibration controller; the vibration control instrument is connected with a computer, and the computer is connected with the vibration table through a power amplifier, as shown in figure 2.
Preferably, the high-low temperature environment box 4 is provided with a temperature sensor, the temperature sensor is connected with a controller, and the controller controls the flow valve and the resistance wire through signals of the temperature sensor.
Preferably, the test fixture 2 has two clamping plates, and the test piece 1 is clamped between the two clamping plates; the acceleration sensor is arranged on the upper wall surface and the lower wall surface of the clamping plate and is used as an input sensor; the acceleration sensor is arranged on the test piece 1 and used as an output sensor; the values of the input sensors are theoretical analysis values, the values of the output sensors are experimental adjustment values, as shown in fig. 3, 1# to 4# in fig. 3 are input sensors, and are places where the theoretical analysis amplitude response is maximum, as shown in fig. 3, 5# to 12# output sensors, 5# to 9# output sensors in fig. 3 are attached to the lower surface of the test piece 1, and 10# to 12# output sensors are attached to the upper surface of the test piece 1.
Preferably, the input sensors are centered on the lower surface of the test piece 1 and distributed along the length direction; the input sensors are arranged at one end of the upper surface of the test piece 1 and distributed in the width direction.
Preferably, for a small-sized airplane, the whole oil tank box section is selected as a test piece 1, for a large-sized airplane, model manufacturing is carried out on a typical structure of a simulated oil tank, the size of the test piece 1 generally selects more than two rib pitch lengths, and typical connection forms such as a real oil tank opening cover, a beam, a wall plate and ribs are simulated.
Preferably, the test piece 1 has 2/3 of the test liquid capacity of the test piece 1 therein.
Preferably, the test liquid comprises water or jet fuel.
The test method adopting the device comprises the following steps: before testing, the test piece 1 needs to be subjected to frequency sweep testing, resonance frequency generated in the testing process can be avoided through frequency sweep, the final vibration frequency is determined according to the frequency sweep result, and generally, one frequency with the largest response amplitude is selected as the critical frequency of the oil tank, namely the use frequency of the vibration testing.
Before the formal test, a touch-down test is required, the touch-down test adopts 33.3HZ and 0DB test control, the amplitude response values of the output sensors attached to different positions of the test piece 1 are observed, six positions with the maximum amplitude are selected as test monitoring points according to the test result, and the value of the input sensor is taken as the specified amplitude.
2/3 volume of water was injected into the test piece 1, and the ambient box was maintained at 70 ℃ and vibrated at a predetermined frequency and an amplitude of 0.8mm for 25 hours.
The test piece was filled with 80% by volume aviation kerosene, and the environmental chamber temperature was maintained at-55 ℃ and vibrated at a frequency of 2000 cycles/minute and an amplitude of 0.8mm for 25 hours.
In the vibration test process, due to the influence of liquid in the test oil piece 1, the amplitude measured by the output sensor at the monitoring point can drift, and in the test process, the output sensor always vibrates at the amplitude not less than the specified amplitude (0.8 mm) by adjusting the input energy, and if the vibration exceeds the specified amplitude upper limit (1.2 mm), the input energy is adjusted to be small in principle.
The integral oil tank vibration test device has a clamp corresponding to a test piece and a sensor arranged on the test clamp, and can complete the functions of an input sensor and an output sensor; can examine oil tank seal structure smoothly through this application in flight vibration environment, have and probably appear can arousing the damage or the deformation of fuel leakage, reach the sealed reliability verification purpose of oil tank design, to the aircraft structural design who has the requirement of verification of seaworthiness, can accomplish oil tank seaworthiness conformance verification smoothly simultaneously.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (8)
1. The utility model provides a whole oil tank vibration test device which characterized in that includes:
the test fixture comprises a vibrating table (3), a test fixture (2) is mounted at the top of the vibrating table (3), and the vibrating table (3) is used for providing vibration for the test fixture (2);
the test fixture (2) is arranged at the top end of the vibration table (3), and the test fixture (2) is connected with a test piece (1);
the high and low temperature environment box (4) is covered on the test fixture (2), the lower surface of the high and low temperature environment box (4) is supported by a support, the lower surface of the high and low temperature environment box (4) is provided with a mounting hole, and the test fixture (2) is arranged in the high and low temperature environment box (4) through the mounting hole;
an air channel device is arranged on the inner wall surface of the high-low temperature environment box (4), a cooling medium is introduced into the air channel device, the cooling medium is connected with a flow valve, and the temperature of the high-low temperature environment box (4) is adjusted by adjusting the flow valve; the high-low temperature environment box (4) is also provided with a resistance wire which is used for heating the high-low temperature environment box (4).
2. The integral fuel tank vibration testing device according to claim 1, wherein a plurality of acceleration sensors are mounted on the test piece (1) and the test fixture (2); the acceleration sensor is connected with the vibration controller; the vibration control instrument is connected with a computer, and the computer is connected with the vibration table through a power amplifier.
3. The integral fuel tank vibration testing device as claimed in claim 1, wherein the high-low temperature environment tank (4) is provided with a temperature sensor, the temperature sensor is connected with a controller, and the controller controls the flow valve and the resistance wire through signals of the temperature sensor.
4. The monoblock fuel tank vibration test device according to claim 2, characterized in that the test fixture (2) has two clamping plates, the test piece (1) being clamped between the two clamping plates; the acceleration sensor is arranged on the upper wall surface and the lower wall surface of the clamping plate and is used as an input sensor; the acceleration sensor is arranged on the test piece (1) and used as an output sensor; wherein the value of the input sensor is a theoretical analysis value, and the value of the output sensor is a test adjustment value.
5. The integral fuel tank vibration testing device as defined in claim 4, wherein the input sensors are centered on the lower surface of the test piece (1) and distributed along the length direction; the input sensors are arranged at one end of the upper surface of the test piece (1) and distributed along the width direction.
6. The integral fuel tank vibration test device according to claim 1, wherein the whole fuel tank box section is selected as the test piece (1) for small-sized aircraft, and the typical structure of the simulated fuel tank is modeled for medium-sized and large-sized aircraft.
7. The integral fuel tank vibration testing apparatus as set forth in claim 1, wherein the test piece (1) has a 2/3 capacity of the test piece (1) therein.
8. The monoblock tank vibration test device of claim 7, wherein the test liquid comprises water or jet fuel.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202222705472.XU CN218330495U (en) | 2022-10-12 | 2022-10-12 | Whole oil tank vibration test device |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202222705472.XU CN218330495U (en) | 2022-10-12 | 2022-10-12 | Whole oil tank vibration test device |
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| CN218330495U true CN218330495U (en) | 2023-01-17 |
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| CN202222705472.XU Active CN218330495U (en) | 2022-10-12 | 2022-10-12 | Whole oil tank vibration test device |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116222950A (en) * | 2023-05-04 | 2023-06-06 | 中国空气动力研究与发展中心高速空气动力研究所 | Dynamic test platform for verifying reliability of low-temperature model |
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2022
- 2022-10-12 CN CN202222705472.XU patent/CN218330495U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116222950A (en) * | 2023-05-04 | 2023-06-06 | 中国空气动力研究与发展中心高速空气动力研究所 | Dynamic test platform for verifying reliability of low-temperature model |
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