Multi-physical-field coupling dynamic testing device and testing method for aircraft sealing strips

Abstract

The present invention provides a multi-physical-field coupling dynamic testing device and a testing method for aircraft sealing strips, belonging to the field of aircraft sealing strip testing. It solves the problem that existing aircraft sealing strip testing equipment lacks the ability to simulate the dynamic interaction of temperature, air pressure, and wind field. In the multi-physical-field coupling dynamic testing device for aircraft sealing strips, the sealing tank includes a tank body and a tank cover. The tank body is detachably connected to the sealing box, and the tank cover is set on the tank body. The load plate is fixedly arranged on the tank cover and is located inside the sealing box. The tank cover is provided with a first sealing groove, and the sealing strip to be tested is arranged in the sealing groove and is located between the tank body and the tank cover. The temperature control component can respectively control the temperatures inside the sealing box and the sealing tank. The pressure control component can respectively control the air pressures inside the sealing box and the sealing tank. The wind field control component can generate wind blowing in any direction towards the load plate. It can test the failure mechanism of the aircraft sealing strip under the coupling condition of simulating air pressure, temperature, and wind field external forces.

Description

Technical Field

[0001] The present invention belongs to the technical field of aircraft seal strip testing, and particularly relates to a multi-physical-field coupling dynamic testing device and a testing method for aircraft seal strips. Background Technique

[0002] The failure of aircraft seal strips is a typical multi-field coupling failure problem, mainly involving the following three failure mechanisms: One is pressure difference-induced failure. During flight, the pressure difference between the inside and outside of the cabin causes periodic axial stress changes in the seal strip. Long-term cycling leads to fatigue damage of the seal strip material, or sudden pressure fluctuations exceed the instantaneous load-bearing capacity of the seal strip material, resulting in structural rupture of the seal strip. The second is heat-induced failure: Extreme temperature changes cause non-uniform expansion or contraction of the seal strip material, resulting in local deformation or buckling of the seal strip, or internal stress concentration caused by temperature gradients may cause tearing of the seal strip material. The third is external force-induced failure: The shear force generated by the airflow acts on the sealing lip, and continuous action leads to wear or displacement of the seal strip material. The superposition of structural vibration and external force may cause resonance damage, reducing the sealing reliability. Existing aircraft seal strip testing equipment cannot systematically solve the verification requirements of the above failure mechanisms. Existing aircraft seal strip testing equipment can only support single air pressure or single temperature regulation, cannot achieve gradient field simulation, cannot reproduce the pressure distribution changes in real flight, and lacks the dynamic interaction simulation ability of temperature, air pressure and wind field, such as the thermodynamic response during sudden air pressure changes, and cannot simulate the influence of different direction pressures of various wind fields on the seal contact state. For example: The patent with the patent number CN113686519B discloses an airtightness detection device and its detection method for aircraft seals, and the patent with the patent number CN109580118B discloses a method for detecting the airtightness of a metal sealing ring for an aircraft engine. Both of these two patents lack the dynamic interaction simulation ability of temperature, air pressure and wind field, and cannot simulate the influence of different direction pressures of various wind fields on the seal contact state. Summary of the Invention

[0003] In view of this, in order to solve the problems that existing aircraft seal strip testing equipment can only support single air pressure or single temperature regulation, cannot achieve gradient field simulation, cannot reproduce the pressure distribution changes in real flight, and lacks the dynamic interaction simulation ability of temperature, air pressure and wind field, such as the thermodynamic response during sudden air pressure changes, and cannot simulate the influence of different direction pressures of various wind fields on the seal contact state, the present invention proposes a multi-physical-field coupling dynamic testing device and a testing method for aircraft seal strips.

[0004] To achieve the above object, the present invention adopts the following technical solutions:

[0005] A multi-physical-field coupling dynamic testing device for aircraft seal strips, comprising:

[0006] Support base;

[0007] Sealing box, which is fixedly arranged above the support base;

[0008] Sealing tank, which includes a tank body and a tank cover. The tank body is detachably connected to the sealing box, the tank cover is set on the tank body, and both the tank body and the tank cover are located inside the sealing box;

[0009] Load plate, which is fixedly arranged on the tank cover and is located inside the sealing box;

[0010] Tested sealing strip. The tank cover is provided with a first sealing groove, and the tested sealing strip is arranged in the first sealing groove and is located between the tank body and the tank cover;

[0011] Temperature control component, which can control the temperatures inside the sealing box and the sealing tank respectively;

[0012] Pressure control component, which can control the gas pressures inside the sealing box and the sealing tank respectively;

[0013] Wind field control component, which can generate wind blowing towards the load plate in any direction.

[0014] As a preferred scheme of the multi - physical - field coupling dynamic test device for the aircraft sealing strip as described above, there are 5 sliding tracks inside the sealing box. The wind field control component includes 5 blowing structures. The 5 blowing structures are all slidably arranged on the sliding tracks. One of the blowing structures is located directly in front of the load plate, and the other four blowing structures are respectively located above, below, to the left and to the right of the load plate. The blowing structure includes an adjusting structure and a fan. The adjusting structure can adjust the distance and angle between the fan and the load plate.

[0015] As a preferred scheme of the multi - physical - field coupling dynamic test device for the aircraft sealing strip as described above, the adjusting structure includes a motor, a telescopic rod, a connecting plate, a connecting frame, a ball - hinge structure and a traction structure. The motor is slidably arranged on the sliding track. One end of the telescopic rod is in transmission connection with the motor, and the other end is fixedly connected to the connecting frame. The connecting frame is connected to the connecting plate through the ball - hinge structure. The connecting plate is fixedly connected to the fan. The traction structure includes a traction wire, a wire - pulling device, a lead wire ring and a wire - locking device. The wire - pulling device and the lead wire ring are arranged on the connecting frame at intervals. The wire - locking device is arranged on the connecting plate. The traction wire passes through the wire - pulling device, the lead wire ring and the wire - locking device in sequence. The wire - locking device can fix one end of the traction wire to the connecting plate, and the wire - pulling device can tighten or loosen the traction wire so as to drive the angle of the fan relative to the telescopic rod to change.

[0016] As a preferred solution of the multi-physical-field coupling dynamic test device for the aircraft sealing strip described above, the temperature control component includes two refrigeration modules, two heating modules, two temperature sensors and a PID control loop. The two refrigeration modules, the two heating modules and the two temperature sensors are all electrically connected to the PID control loop. The two refrigeration modules are respectively arranged in the sealing box and the sealing tank, the two heating modules are respectively arranged in the sealing box and the sealing tank, and the two temperature sensors are respectively arranged in the sealing box and the sealing tank.

[0017] As a preferred solution of the multi-physical-field coupling dynamic test device for the aircraft sealing strip described above, the pressure control component includes two air inlet nozzles, two air outlet nozzles and two pressure relief valves. The two air inlet nozzles are respectively arranged in the sealing box and the sealing tank, the two air outlet nozzles are respectively arranged in the sealing box and the sealing tank, the two pressure relief valves are arranged corresponding to the two air outlet nozzles one by one, and pressure gauges are arranged on the two air inlet nozzles and the two air outlet nozzles.

[0018] As a preferred solution of the multi-physical-field coupling dynamic test device for the aircraft sealing strip described above, the multi-physical-field coupling dynamic test device for the aircraft sealing strip further includes a plurality of piezoelectric sensors. The plurality of piezoelectric sensors are arranged at intervals in the first sealing groove for real-time monitoring of the rebound characteristics of the sealing strip to be tested.

[0019] As a preferred solution of the multi-physical-field coupling dynamic test device for the aircraft sealing strip described above, the sealing box includes a box body, a sealing plate and an adapter plate. The sealing plate is fixedly connected to the box body, the adapter plate is detachably connected to the sealing plate, and the sealing tank is detachably connected to the adapter plate.

[0020] As a preferred solution of the multi-physical-field coupling dynamic test device for the aircraft sealing strip described above, the multi-physical-field coupling dynamic test device for the aircraft sealing strip further includes a first sealing ring, a second sealing ring and a third sealing ring. The box body is provided with a second sealing groove, the sealing plate is provided with a third sealing groove, the adapter plate is provided with a fourth sealing groove. The first sealing ring is embedded in the second sealing groove and is located between the box body and the sealing plate, the second sealing ring is embedded in the third sealing groove and is located between the sealing plate and the adapter plate, and the third sealing ring is embedded in the fourth sealing groove and is located between the adapter plate and the sealing tank.

[0021] As a preferred solution of the multi-physical-field coupling dynamic test device for the aircraft sealing strip described above, a heat insulation layer is fixedly arranged on the inner wall of the sealing tank.

[0022] The present invention also provides a multi - physical - field coupling dynamic testing method for an aircraft seal strip, which uses the above - mentioned multi - physical - field coupling dynamic testing device for an aircraft seal strip, and includes:

[0023] Use the sealed tank to simulate the internal environment of the aircraft cabin and set the internal environment parameters. Pass gas into the sealed tank through the air pressure control component and control the air pressure in the sealed tank to reach the first set pressure, and adjust the temperature in the sealed tank to reach the first set temperature through the temperature control component;

[0024] Use the sealed box to simulate the external environment and set the external environment parameters. Pass gas into the sealed box through the air pressure control component and control the air pressure in the sealed box to reach the second set pressure, and adjust the temperature in the sealed box to reach the second set temperature through the temperature control component;

[0025] Conduct dynamic working condition simulation. Control the air pressure in the sealed box and the air pressure in the sealed tank through the air pressure control component, so that the pressure difference between the two changes in a gradient manner, thereby simulating the air pressure change caused by the change in the flight altitude of the aircraft; control the temperature in the sealed box and the temperature in the sealed tank through the temperature control component, so that the temperature difference between the two changes in a gradient manner, thereby simulating the temperature change caused by the change in the flight altitude of the aircraft; blow air at different angles to the load plate through the wind field control component to simulate the flowing wind field;

[0026] In - situ monitoring. Real - time monitor the air pressure in the sealed box and the sealed tank, and invert the change in the leakage rate of the seal strip to be tested through the air pressure fluctuation curve in the sealed tank.

[0027] Compared with the prior art, the beneficial effects of the multi - physical - field coupling dynamic testing device and testing method for an aircraft seal strip provided by the present invention are:

[0028] The present invention provides a multi-physical field coupling dynamic testing device and a testing method for an aircraft sealing strip. The multi-physical field coupling dynamic testing device for the aircraft sealing strip includes a sealed tank for simulating the environment inside the aircraft cabin, a sealed box for simulating the external environment of the aircraft, and the sealing strip to be tested is arranged between the tank body and the tank cover of the sealed tank. The sealing performance of the sealing strip to be tested is tested within the coupled physical field of pressure, temperature, and wind field. Dynamic working conditions can be simulated through a pneumatic control component, a temperature control component, and a wind field control component. The pneumatic control component controls the air pressure inside the sealed box and the air pressure inside the sealed tank to make the pressure difference between the two change in a gradient manner, so as to simulate the air pressure change caused by the change in the flight altitude of the aircraft. The temperature control component controls the temperature inside the sealed box and the temperature inside the sealed tank to make the temperature difference between the two change in a gradient manner, so as to simulate the temperature change caused by the change in the flight altitude of the aircraft. The wind field control component blows air at different angles to the load plate to simulate a flowing wind field, and the wind field control component can simulate a multi-directional wind field to simulate the scenario where the aircraft is affected by winds in various directions during flight. The air pressures inside the sealed box and the sealed tank are monitored in real time, and the leakage rate change of the sealing strip to be tested is inversely calculated through the air pressure fluctuation curve inside the sealed tank. Moreover, a plurality of piezoelectric sensors are also arranged at intervals along the circumferential direction in the first sealing groove, and the piezoelectric sensors are used to monitor the rebound characteristics of the sealing strip to be tested in real time. The multi-physical field coupling dynamic testing device for the aircraft sealing strip can test the failure mechanism of the sealing strip of the aircraft under the condition of simulating the coupling of air pressure, temperature, and wind field external forces. BRIEF DESCRIPTION OF THE DRAWINGS

[0029] The drawings constituting a part of the present invention are used to provide a further understanding of the present invention. The schematic embodiments of the present invention and their descriptions are used to explain the present invention and do not constitute an improper limitation to the present invention. In the drawings:

[0030] Figure 1 is a cross-sectional view of the multi-physical field coupling dynamic testing device for the aircraft sealing strip provided by a specific embodiment of the present invention;

[0031] Figure 2 is a partial structural schematic diagram of the multi-physical field coupling dynamic testing device for the aircraft sealing strip provided by a specific embodiment of the present invention;

[0032] Figure 3 is a structural schematic diagram of the multi-physical field coupling dynamic testing device for the aircraft sealing strip provided by a specific embodiment of the present invention;

[0033] Figure 4 is a structural schematic diagram of the blowing structure of the multi-physical field coupling dynamic testing device for the aircraft sealing strip provided by a specific embodiment of the present invention;

[0034] Figure 5It is a schematic structural diagram of the ball joint structure of the multi-physical field coupling dynamic test device for the aircraft sealing strip provided by a specific embodiment of the present invention;

[0035] Figure 6 It is a partial sectional view of the multi-physical field coupling dynamic test device for the aircraft sealing strip provided by a specific embodiment of the present invention;

[0036] Figure 7 It is a schematic structural diagram of the sealing tank of the multi-physical field coupling dynamic test device for the aircraft sealing strip provided by a specific embodiment of the present invention;

[0037] Figure 8 It is a schematic structural diagram of the tank cover of the multi-physical field coupling dynamic test device for the aircraft sealing strip provided by a specific embodiment of the present invention.

[0038] In the figure:

[0039] 11. Box body; 12. Sealing plate; 13. Adapter plate; 111. Second sealing groove; 121. Third sealing groove; 131. Fourth sealing groove;

[0040] 21. Tank body; 22. Tank cover; 221. First sealing groove;

[0041] 3. Load plate;

[0042] 41. First intake nozzle; 42. First exhaust nozzle; 43. Second intake nozzle; 44. Second exhaust nozzle;

[0043] 51. First refrigeration module; 52. First heating module; 53. First temperature sensor; 54. Second refrigeration module; 55. Second heating module; 56. Second temperature sensor;

[0044] 6. Blowing structure; 61. Telescopic rod; 62. Connecting frame; 63. Connecting plate; 64. Fan; 65. Cable pulling device; 66. Lead ring; 67. Wire locking device; 68. Ball head; 69. Locking ring;

[0045] 7. Heat insulation layer;

[0046] 8. Piezoelectric sensor. Detailed implementation manners

[0047] Next, the technical solutions in the embodiments of the present invention will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of the present invention. It should be noted that, without conflict, the embodiments and features in the embodiments of the present invention can be combined with each other. The described embodiments are only some of the embodiments of the present invention, rather than all of the embodiments.

[0048] In the description of the present invention, unless otherwise clearly defined and limited, the terms "connected", "connected to", and "fixed" shall be understood in a broad sense. For example, it may be a fixed connection, a detachable connection, or integrated; it may be a mechanical connection or an electrical connection; it may be directly connected or indirectly connected through an intermediate medium, and it may be the communication inside two components or the interaction relationship between two components. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to specific situations.

[0049] In the present invention, unless otherwise clearly defined and limited, the first feature being "above" or "below" the second feature may include the direct contact between the first and second features, or may include the situation where the first and second features are not in direct contact but in contact through other features therebetween. Moreover, the first feature being "above", "over", and "on top of" the second feature includes the first feature being directly above and obliquely above the second feature, or simply indicating that the horizontal height of the first feature is higher than that of the second feature. The first feature being "below", "under", and "beneath" the second feature includes the first feature being directly below and obliquely below the second feature, or simply indicating that the horizontal height of the first feature is lower than that of the second feature.

[0050] In the description of this embodiment, the orientation or positional relationships such as "above", "below", "right" are based on the orientation or positional relationships shown in the drawings. It is only for the convenience of description and simplifying the operation, rather than indicating or implying that the device or component referred to must have a specific orientation, be constructed and operated in a specific orientation, so it cannot be understood as a limitation to the present invention. In addition, the terms "first" and "second" are only used for distinction in description and have no special meanings.

[0051] See Figure 1-8 Describing this embodiment, the present invention provides a multi-physical-field coupling dynamic testing device and a testing method for an aircraft sealing strip. The multi-physical-field coupling dynamic testing device for the aircraft sealing strip includes a support base, a sealing box, a sealing tank, a load plate 3, a sealing strip to be tested, a temperature control component, a pressure control component, and a wind field control component. The sealing box is fixedly arranged above the support base. The sealing tank includes a tank body 21 and a tank cover 22. The tank body 21 is detachably connected to the sealing box, and the tank cover 22 is covered on the tank body 21. Both the tank body 21 and the tank cover 22 are located inside the sealing box. The load plate 3 is fixedly arranged on the tank cover 22 and is located inside the sealing box. The tank cover 22 is provided with a first sealing groove 221. The sealing strip to be tested is arranged in the sealing groove and is located between the tank body 21 and the tank cover 22. The temperature control component can respectively control the temperatures inside the sealing box and the sealing tank. The pressure control component can respectively control the gas pressures inside the sealing box and the sealing tank. The wind field control component can generate wind blowing in any direction towards the load plate 3.

[0052] The multi-physical-field coupling dynamic testing device for the aircraft sealing strip. The sealed tank is used to simulate the environment inside the aircraft cabin, and the sealed box is used to simulate the external environment of the aircraft. The sealing strip to be tested is arranged between the tank body 21 and the tank cover 22 of the sealed tank, and the sealing performance of the sealing strip to be tested is tested in the coupled physical field of pressure, temperature and wind field. Dynamic working condition simulation can be carried out through the air pressure control component, the temperature control component and the wind field control component. The air pressure in the sealed box and the air pressure in the sealed tank are controlled by the air pressure control component, so that the pressure difference between the two changes in a gradient manner, thereby simulating the air pressure change caused by the change in the flight altitude of the aircraft; the temperature in the sealed box and the temperature in the sealed tank are controlled by the temperature control component, so that the temperature difference between the two changes in a gradient manner, thereby simulating the temperature change caused by the change in the flight altitude of the aircraft; the load plate 3 is blown at different angles by the wind field control component to simulate the flowing wind field, and the wind field control component can simulate a multi-directional wind field to simulate the scenario of the aircraft being affected by winds in various directions during flight. The air pressures in the sealed box and the sealed tank are monitored in real time, and the leakage rate change of the sealing strip to be tested is inversed through the air pressure fluctuation curve in the sealed tank. The multi-physical-field coupling dynamic testing device for the aircraft sealing strip can test the failure mechanism of the aircraft sealing strip under the condition of simulating the coupling of air pressure, temperature and external wind force.

[0053] It can be understood that the wind force blown by the wind field control component towards the load plate 3 will be transmitted to the tank cover 22 through the load plate 3, thus affecting the sealing strip to be tested.

[0054] In this embodiment, the support seat adopts a heavy alloy support seat, which can ensure the structural stability of the sealed box under extreme working conditions.

[0055] Optionally, 5 slideways are provided in the sealed box, and the wind field control component includes 5 blowing structures 6. The 5 blowing structures 6 are all slidably arranged on the slideways. One of the blowing structures 6 is located directly in front of the load plate 3, and the other four blowing structures 6 are respectively located above, below, to the left and to the right of the load plate 3. The blowing structure 6 includes an adjusting structure and a fan 64. The adjusting structure can adjust the distance and angle between the fan 64 and the load plate 3. Each blowing structure 6 can blow air independently, or any number of blowing structures 6 can cooperate to blow air.

[0056] In this embodiment, the slideways located above and below the load plate 3 extend in the horizontal direction, and the slideways located in front of, to the left and to the right of the load plate 3 extend in the vertical direction.

[0057] Specifically, the adjustment structure includes a motor, a telescopic rod 61, a connecting plate 63, a connecting frame 62, a ball joint structure, and a traction structure. The motor is slidably disposed on the slideway. One end of the telescopic rod 61 is drivingly connected to the motor, and the other end is fixedly connected to the connecting frame 62. The connecting frame 62 is connected to the connecting plate 63 through the ball joint structure. The connecting plate 63 is fixedly connected to the fan 64. The traction structure includes a traction wire, a wire pulling device 65, a wire guiding ring 66, and a wire locking device 67. The wire pulling device 65 and the wire guiding ring 66 are spaced apart on the connecting frame 62. The wire locking device 67 is disposed on the connecting plate 63. The traction wire passes through the wire pulling device 65, the wire guiding ring 66, and the wire locking device 67 in sequence. The wire locking device 67 can fix one end of the traction wire to the connecting plate 63. The wire pulling device 65 can tighten or loosen the traction wire to drive the angle of the fan 64 relative to the telescopic rod 61 to change. The motor can drive the telescopic rod 61 to extend and retract. The telescopic rod 61 drives the connecting frame 62, the connecting plate 63, the fan 64, and the traction structure to move together, so as to adjust the distance between the fan 64 and the load plate 3. The traction structure is used to adjust the angle of the fan 64, so as to realize the universal adjustment of the fan 64. In this embodiment, the number of the traction structures is four, which are respectively arranged on the four sides of the connecting plate 63, and can control the fan 64 to deflect in four directions and can adjust the deflection angle.

[0058] In this embodiment, the specific structure of the wire pulling device 65 is prior art and will not be elaborated herein.

[0059] Specifically, the ball joint structure includes a ball head 68, a locking ring 69, and a ball groove. The ball groove is disposed on the connecting plate 63. The ball head 68 is embedded in the ball groove. The ball groove is semi-circular. The ball head 68 passes through the locking ring 69. The upper half of the ball head 68 abuts against the inner ring of the locking ring 69. The locking ring 69 is fixedly connected to the connecting plate 63.

[0060] Optionally, the temperature control component includes two refrigeration modules, two heating modules, two temperature sensors, and a PID control loop. The two refrigeration modules, the two heating modules, and the two temperature sensors are all electrically connected to the PID control loop. The two refrigeration modules are respectively disposed in the sealed box and the sealed tank. The two heating modules are respectively disposed in the sealed box and the sealed tank. The two temperature sensors are respectively disposed in the sealed box and the sealed tank. In this embodiment, the refrigeration module located in the sealed box is the first refrigeration module 51, the heating module located in the sealed box is the first heating module 52, the temperature sensor located in the sealed box is the first temperature sensor 53, the temperature sensor located in the sealed tank is the second temperature sensor 56, the refrigeration module located in the sealed tank is the second refrigeration module 54, and the heating module located in the sealed tank is the second heating module 55.

[0061] Optionally, the pressure control component includes two intake nozzles, two outlet nozzles and two pressure relief valves. The two intake nozzles are respectively arranged on the sealed box and the sealed tank, the two outlet nozzles are respectively arranged on the sealed box and the sealed tank, the two pressure relief valves are arranged in one-to-one correspondence with the two outlet nozzles, and pressure gauges are provided on both the two intake nozzles and the two outlet nozzles. Both the intake nozzles and the outlet nozzles are airtight nozzles. The arrangement of the intake nozzles and the outlet nozzles can achieve two-way air flow balance regulation. In this embodiment, the intake nozzle arranged on the sealed box is the first intake nozzle 41, the outlet nozzle arranged on the sealed box is the first outlet nozzle 42, the intake nozzle arranged on the sealed tank is the second intake nozzle 43, and the outlet nozzle arranged on the sealed tank is the second outlet nozzle 44. The sealed box is inflated through the first intake nozzle 41, the sealed box is deflated through the first outlet nozzle 42, and the air pressure in the sealed box is adjusted through the first intake nozzle 41 and the first outlet nozzle 42. The sealed tank is inflated through the second intake nozzle 43, the sealed tank is deflated through the second outlet nozzle 44, and the air pressure in the sealed tank is adjusted through the second intake nozzle 43 and the second outlet nozzle 44.

[0062] In this embodiment, pressure gauges are connected to both the intake nozzles and the outlet nozzles, which can real-time monitor the air pressure changes during the test.

[0063] In this embodiment, both the intake nozzles and the outlet nozzles are configured with independent air pressure buffer structures, and pressure relief valves are also provided at the outlet nozzles to ensure pressure stability.

[0064] Optionally, the multi-physical-field coupling dynamic testing device for the aircraft sealing strip further includes a plurality of piezoelectric sensors 8. The plurality of piezoelectric sensors 8 are arranged at intervals along the circumferential direction of the first sealing groove 221 for real-time monitoring of the rebound characteristics of the sealing strip to be tested.

[0065] The load received by the sealing strip to be tested is different, and its sealing effect is also different. When the sealing strip to be tested is subjected to uneven loads around its circumference, the sealing effects at its various positions are different. Therefore, a plurality of piezoelectric sensors 8 are arranged at intervals along the circumferential direction of the first sealing groove 221. The circumferential distribution of the plurality of piezoelectric sensors 8 can measure the uneven pressure caused by the non-uniform load, so as to real-time monitor the rebound characteristics of each position of the sealing strip to be tested.

[0066] Optionally, the sealed box includes a box body 11, a sealing plate 12 and an adapter plate 13. The sealing plate 12 is fixedly connected to the box body 11, the adapter plate 13 is detachably connected to the sealing plate 12, and the sealed tank is detachably connected to the adapter plate 13. The adapter plate 13 can be replaced according to the size of the sealed tank, so that the sealed box can be connected to sealed tanks of different sizes.

[0067] Optionally, the multi-physical-field coupling dynamic testing device for the aircraft sealing strip further includes a first sealing ring, a second sealing ring, and a third sealing ring. The box body 11 is provided with a second sealing groove 111, the sealing plate 12 is provided with a third sealing groove 121, and the adapter plate 13 is provided with a fourth sealing groove 131. The first sealing ring is embedded in the second sealing groove 111 and is located between the box body 11 and the sealing plate 12. The second sealing ring is embedded in the third sealing groove 121 and is located between the sealing plate 12 and the adapter plate 13. The third sealing ring is embedded in the fourth sealing groove 131 and is located between the adapter plate 13 and the sealing tank. The first sealing ring, the second sealing ring, and the third sealing ring can achieve the sealing between the sealed box and the outside world.

[0068] Optionally, a heat insulation layer 7 is fixedly provided on the inner wall of the sealing tank. The heat insulation layer 7 isolates the temperature of the environment inside and outside the sealing tank.

[0069] In this embodiment, the sealing tank is a pressure-resistant sealing tank.

[0070] The present invention also provides a multi-physical-field coupling dynamic testing method for an aircraft sealing strip, which uses the above-mentioned multi-physical-field coupling dynamic testing device for an aircraft sealing strip, and specifically includes:

[0071] Using the sealing tank to simulate the aircraft cabin environment and set the internal environment parameters, introducing gas into the sealing tank through the air pressure control component and controlling the air pressure in the sealing tank to reach the first set pressure, and adjusting the temperature in the sealing tank to reach the first set temperature through the temperature control component. If the pressure changes after adjusting the temperature, pressure fine-tuning can be performed again.

[0072] Using the sealed box to simulate the external environment and set the external environment parameters, introducing gas into the sealed box through the air pressure control component and controlling the air pressure in the sealed box to reach the second set pressure, and adjusting the temperature in the sealed box to reach the second set temperature through the temperature control component. If the pressure changes after adjusting the temperature, pressure fine-tuning can be performed again.

[0073] Performing dynamic working condition simulation, controlling the air pressure in the sealed box and the air pressure in the sealing tank through the air pressure control component, so that the pressure difference between the two changes in a gradient manner, thereby simulating the air pressure change caused by the change in the flight altitude of the aircraft; controlling the temperature in the sealed box and the temperature in the sealing tank through the temperature control component, so that the temperature difference between the two changes in a gradient manner, thereby simulating the temperature change caused by the change in the flight altitude of the aircraft; blowing air at different angles to the load plate 3 through the wind field control component to simulate the flowing wind field.

[0074] The test conditions can be established based on the change curves of temperature and air pressure with the increase in the altitude of the aircraft, or the test conditions can be carried out according to constant temperature and constant air pressure, variable temperature and constant air pressure, and constant temperature and variable air pressure. The wind field is established independently. At the required temperature and pressure, the load plate 3 is blown at different angles and different wind speeds for testing, so as to construct a coupled physical field of temperature, air pressure and external wind field forces.

[0075] In-situ monitoring, real-time monitoring of the air pressure inside the sealed box and the sealed tank, and the leakage rate change of the seal strip to be tested is inversed through the air pressure fluctuation curve inside the sealed tank. And the rebound characteristics of the seal strip to be tested are real-time monitored through the piezoelectric sensor 8.

[0076] Obviously, the embodiments of the present invention disclosed above are only used to help explain the present invention. The embodiments do not describe all the details in detail, nor do they limit the invention to the specific embodiments described. According to the content of this specification, many modifications and changes can be made. These embodiments are selected and specifically described in this specification in order to better explain the principle and practical application of the present invention, so that those skilled in the relevant technical field can well understand and utilize the present invention. It is not necessary and impossible to enumerate all the embodiments here.

Claims

1. A multi-physical-field coupling dynamic testing device for an aircraft sealing strip, characterized in that Comprising: Support base; Sealed box, which is fixedly arranged above the support base; Sealed tank, the sealed tank includes a tank body (21) and a tank cover (22), the tank body (21) is detachably connected to the sealed box, the tank cover (22) covers the tank body (21), and both the tank body (21) and the tank cover (22) are located inside the sealed box; Load plate (3), the load plate (3) is fixedly arranged on the tank cover (22) and is located inside the sealed box; Test sealing strip, the tank cover (22) is provided with a first sealing groove (221), and the test sealing strip is arranged in the first sealing groove (221) and is located between the tank body (21) and the tank cover (22); Temperature control component, which can respectively control the temperatures inside the sealed box and the sealed tank; Pressure control component, which can respectively control the gas pressures inside the sealed box and the sealed tank; Wind field control component, which can generate winds blowing in any direction towards the load plate (3); There are 5 sliding tracks inside the sealed box, the wind field control component includes 5 blowing structures (6), the 5 blowing structures (6) are all slidably arranged on the sliding tracks, one of the blowing structures (6) is located directly in front of the load plate (3), and the other four blowing structures (6) are respectively located above, below, to the left and to the right of the load plate (3). The blowing structure (6) includes an adjustment structure and a fan (64), and the adjustment structure can adjust the distance and angle between the fan (64) and the load plate (3); The adjustment structure includes a motor, a telescopic rod (61), a connecting plate (63), a connecting frame (62), a ball hinge structure and a traction structure. The motor is slidably arranged on the sliding track, one end of the telescopic rod (61) is in transmission connection with the motor, and the other end is fixedly connected to the connecting frame (62). The connecting frame (62) is connected to the connecting plate (63) through the ball hinge structure, and the connecting plate (63) is fixedly connected to the fan (64). The traction structure includes a traction wire, a wire pulling device (65), a wire leading ring (66) and a wire locking device (67). The wire pulling device (65) and the wire leading ring (66) are arranged at intervals on the connecting frame (62), the wire locking device (67) is arranged on the connecting plate (63), the traction wire passes through the wire pulling device (65), the wire leading ring (66) and the wire locking device (67) in sequence, the wire locking device (67) can fix one end of the traction wire to the connecting plate (63), and the wire pulling device (65) can tighten or loosen the traction wire to drive the angle of the fan (64) relative to the telescopic rod (61) to change.

2. The multi-physical-field coupling dynamic test device for the aircraft sealing strip according to claim 1, wherein: The temperature control component includes two refrigeration modules, two heating modules, two temperature sensors and a PID control loop. The two refrigeration modules, the two heating modules and the two temperature sensors are all electrically connected to the PID control loop. The two refrigeration modules are respectively arranged in the sealed box and the sealed tank, the two heating modules are respectively arranged in the sealed box and the sealed tank, and the two temperature sensors are respectively arranged in the sealed box and the sealed tank.

3. The multi-physical-field coupling dynamic testing device for the aircraft seal strip according to claim 1, wherein: The pressure control component includes two intake nozzles, two outlet nozzles and two pressure relief valves. The two intake nozzles are respectively arranged on the sealed box and the sealed tank, the two outlet nozzles are respectively arranged on the sealed box and the sealed tank, the two pressure relief valves are arranged in one-to-one correspondence with the two outlet nozzles, and pressure gauges are provided on both the two intake nozzles and the two outlet nozzles.

4. The multi-physical field coupling dynamic testing device for the aircraft sealing strip according to claim 1, characterized in that: It further includes a plurality of piezoelectric sensors (8). The plurality of piezoelectric sensors (8) are arranged at intervals along the circumferential direction of the first sealing groove (221) in the first sealing groove (221) for real-time monitoring of the rebound characteristics of the seal strip to be measured.

5. The multi-physical-field coupling dynamic testing device for the aircraft sealing strip according to claim 1, characterized in that: The sealed box includes a box body (11), a sealing plate (12) and an adapter plate (13). The sealing plate (12) is fixedly connected to the box body (11), the adapter plate (13) is detachably connected to the sealing plate (12), and the sealed tank is detachably connected to the adapter plate (13).

6. The multi-physical-field coupling dynamic testing device for the aircraft sealing strip according to claim 5, wherein: It further includes a first sealing ring, a second sealing ring and a third sealing ring. The box body (11) is provided with a second sealing groove (111), the sealing plate (12) is provided with a third sealing groove (121), and the adapter plate (13) is provided with a fourth sealing groove (131). The first sealing ring is embedded in the second sealing groove (111) and is located between the box body (11) and the sealing plate (12), the second sealing ring is embedded in the third sealing groove (121) and is located between the sealing plate (12) and the adapter plate (13), and the third sealing ring is embedded in the fourth sealing groove (131) and is located between the adapter plate (13) and the sealed tank.

7. The multi-physical field coupling dynamic test device for the aircraft sealing strip according to claim 1, characterized in that: A heat insulation layer (7) is fixedly provided on the inner wall of the sealed tank.

8. A multi-physical field coupling dynamic testing method for an aircraft sealing strip, characterized in that: The multi-physical field coupling dynamic test device for aircraft seal strips according to any one of claims 1-7, comprising: Using the sealed tank to simulate the aircraft cabin environment and set the internal environment parameters, introducing gas into the sealed tank through the air pressure control component and controlling the air pressure in the sealed tank to reach the first set pressure, and adjusting the temperature in the sealed tank to reach the first set temperature through the temperature control component; Using the sealed box to simulate the external environment and set the external environment parameters, introducing gas into the sealed box through the air pressure control component and controlling the air pressure in the sealed box to reach the second set pressure, and adjusting the temperature in the sealed box to reach the second set temperature through the temperature control component; Conducting dynamic working condition simulation, controlling the air pressure in the sealed box and the air pressure in the sealed tank through the air pressure control component so that the pressure difference between the two changes in a gradient manner, thereby simulating the air pressure change caused by the change in the flight altitude of the aircraft; controlling the temperature in the sealed box and the temperature in the sealed tank through the temperature control component so that the temperature difference between the two changes in a gradient manner, thereby simulating the temperature change caused by the change in the flight altitude of the aircraft; blowing air on the load plate (3) at different angles through the wind field control component to simulate the flowing wind field; In-situ monitoring, real-time monitoring of the air pressure in the sealed box and the sealed tank, and inversely calculating the change in the leakage rate of the seal strip to be measured through the air pressure fluctuation curve in the sealed tank.

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