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

Abstract

The invention provides a multi-physical field coupling dynamic testing device and method for an aircraft sealing strip, and belongs to the field of aviation sealing strip testing. The problem that an existing aviation sealing strip testing device lacks the dynamic interaction simulation capability of temperature, air pressure and a wind field is solved. In the multi-physical field coupling dynamic testing device for the aircraft sealing strip, a sealing tank comprises a tank body and a tank cover, the tank body is detachably connected to a sealing box, the tank cover covers the tank body, a loading plate is fixedly arranged on the tank cover and located in 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 located between the tank body and the tank cover. The temperature control assembly can control the temperature in the sealing box and the temperature in the sealing tank respectively, the pressure control assembly can control the air pressure in the sealing box and the air pressure in the sealing tank respectively, and the wind field control assembly can generate wind in any direction to be blown to the load plate. The device can test the failure mechanism of the sealing strip of the aircraft under the condition of simulating coupling of air pressure, temperature and wind field external force.

Description

Technical Field

[0001] The invention belongs to the technical field of aircraft sealing strip testing, and in particular relates to a multi-physical field coupling dynamic testing device and a testing method for aircraft sealing strips. Background Art

[0002] The failure of the sealing strip of an aircraft is a typical multi-field coupling failure problem, which mainly involves the following three failure mechanisms: First, failure caused by pressure difference. During the flight, the pressure difference between the inside and outside of the cabin causes periodic axial stress changes in the sealing strip. Long-term circulation causes fatigue damage to the sealing strip material, or sudden pressure fluctuations exceed the instantaneous bearing capacity of the sealing strip material, causing structural rupture of the sealing strip. Second, thermal failure: extreme temperature changes cause non-uniform expansion or contraction of the sealing strip material, resulting in deformation or even buckling of local areas of the sealing strip, or internal stress concentration caused by temperature gradients may cause tearing of the sealing strip material. Third, failure caused by external forces: the shear force generated by the airflow acts on the sealing lip, and the continuous action causes wear or displacement of the sealing strip material. The superposition of structural vibration and external force may cause resonance damage, reducing the reliability of the seal. Existing aviation sealing strip testing equipment cannot systematically solve the verification requirements of the above failure mechanisms. Existing aviation sealing strip testing equipment can only support single air pressure or single temperature control, cannot achieve gradient field simulation, cannot reproduce the pressure distribution changes in real flight, and lacks the ability to dynamically interact with temperature, air pressure and wind field. For example, the thermodynamic response when the air pressure changes suddenly, and cannot simulate the impact of pressures in different directions of various wind fields on the sealing contact state. For example: Patent No. CN113686519B discloses an aviation sealing component sealing detection device and detection method, and patent No. CN109580118B discloses a method for sealing metal sealing rings for aircraft engines. Both patents lack the ability to dynamically interact with temperature, air pressure and wind field, and cannot simulate the impact of pressures in different directions of various wind fields on the sealing contact state. Summary of the invention

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

[0004] To achieve the above object, the present invention adopts the following technical solutions: A multi-physics field coupling dynamic testing device for an aircraft sealing strip, comprising: Support seat; A sealing box, the sealing box is fixedly arranged above the supporting seat; A sealed can, the sealed can comprising a can body and a can cover, the can body is detachably connected to a sealed box, the can cover is arranged on the can body, and both the can body and the can cover are located in the sealed box; A load plate, the load plate is fixedly disposed on the tank cover and is located in the sealing box; The sealing strip to be tested, the tank cover is provided with a first sealing groove, the sealing strip to be tested is arranged in the first sealing groove and is located between the tank body and the tank cover; A temperature control component, wherein the temperature control component can control the temperature in the sealed box and the sealed tank respectively; A pressure control component, wherein the pressure control component can control the gas pressure in the sealed box and the sealed tank respectively; A wind field control component can generate wind in any direction to blow toward the load plate.

[0005] As a preferred solution of the multi-physical field coupled dynamic testing device for the above-mentioned aircraft sealing strip, 5 slides are provided in the sealing box, and the wind field control component includes 5 blowing structures, and the 5 blowing structures are all slidably arranged on the slides, 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, on the left and on the right of the load plate, and the blowing structure includes an adjusting structure and a fan, and the adjusting structure can adjust the distance and angle between the fan and the load plate.

[0006] As a preferred solution of the above-mentioned multi-physical field coupling dynamic testing device for the aircraft sealing strip, the adjustment structure includes a motor, a telescopic rod, a connecting plate, a connecting frame, a ball joint structure and a traction structure. The motor is slidably arranged on the slideway, one end of the telescopic rod is transmission-connected to the motor, and the other end is fixedly connected to the connecting frame, the connecting frame and the connecting plate are connected through the ball joint structure, the connecting plate is fixedly connected to the fan, the traction structure includes a traction wire, a wire pulling device, a wire lead ring and a wire locking device, the wire pulling device and the wire lead ring are spaced apart on the connecting frame, the wire locking device is arranged on the connecting plate, the traction wire passes through the wire pulling device, the wire lead ring and the wire locking device in sequence, the wire locking device can fix one end of the traction wire to the connecting plate, the wire pulling device can tighten or loosen the traction wire to drive the angle of the fan relative to the telescopic rod to change.

[0007] As a preferred solution of the multi-physical field coupled dynamic testing device for the above-mentioned aircraft sealing strip, 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 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.

[0008] As a preferred solution of the multi-physical field coupled dynamic testing device for the above-mentioned aircraft sealing strip, 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 in a one-to-one correspondence with the two air outlet nozzles, and the two air inlet nozzles and the two air outlet nozzles are provided with pressure gauges.

[0009] As a preferred solution of the above-mentioned multi-physical field coupling dynamic testing device for aircraft sealing strips, the multi-physical field coupling dynamic testing device for aircraft sealing strips also includes a plurality of piezoelectric sensors, which are arranged at intervals in the first sealing groove for real-time monitoring of the rebound characteristics of the sealing strip to be tested.

[0010] As a preferred solution of the above-mentioned multi-physical field coupled dynamic testing device for aircraft sealing strips, 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 can is detachably connected to the adapter plate.

[0011] As a preferred solution of the above-mentioned multi-physical field coupling dynamic testing device for aircraft sealing strips, the multi-physical field coupling dynamic testing device for aircraft sealing strips also 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 can.

[0012] As a preferred solution of the above-mentioned multi-physical field coupling dynamic testing device for aircraft sealing strips, a heat insulation layer is fixedly provided on the inner wall of the sealing can.

[0013] The present invention also provides a multi-physical field coupling dynamic testing method for an aircraft sealing strip, using the multi-physical field coupling dynamic testing device for an aircraft sealing strip, comprising: The sealed tank is used to simulate the environment inside the aircraft cabin and set the internal environment parameters, gas is introduced into the sealed tank through the air pressure control component to control the air pressure inside the sealed tank to reach a first set pressure, and the temperature inside the sealed tank is adjusted to reach a first set temperature through the temperature control component; The sealed box is used to simulate the external environment and set the external environment parameters, gas is introduced into the sealed box through the air pressure control component and the air pressure in the sealed box is controlled to reach a second set pressure, and the temperature in the sealed box is adjusted to reach a second set temperature through the temperature control component; Dynamic working condition simulation is performed, 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 gradually, thereby simulating the air pressure change caused by the change of 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 gradually, thereby simulating the temperature change caused by the change of the flight altitude of the aircraft; the load plate is blown at different angles by the wind field control component to simulate the flow wind field; In-situ monitoring: real-time monitoring of the air pressure in the sealing box and the sealing tank, and inversion of the leakage rate change of the sealing strip to be tested through the air pressure fluctuation curve in the sealing tank.

[0014] Compared with the prior art, the multi-physical field coupling dynamic testing device and testing method for aircraft sealing strips provided by the present invention have the following beneficial effects: The present invention provides a multi-physical field coupling dynamic test device and a test method for an aircraft sealing strip. The multi-physical field coupling dynamic test device for an aircraft sealing strip comprises a sealed tank for simulating the environment in the aircraft cabin, a sealed box for simulating the external environment of the aircraft, and a sealing strip to be tested is arranged between a tank body and a tank cover of the sealed tank. The sealing performance of the sealing strip to be tested is tested in a coupled physical field of pressure, temperature and wind field. Dynamic working condition simulation can be performed by an air pressure control component, a temperature control component and a 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 gradually, 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 gradually, thereby simulating the temperature change caused by the change in the flight altitude of the aircraft; the load plate is blown at different angles by the wind field control component to simulate the flow wind field. The wind field control component can simulate a multi-directional wind field, simulating the scene of the aircraft being subjected to winds from various directions when flying. The air pressure in the sealing box and the sealing tank is monitored in real time, and the leakage rate change of the sealing strip to be tested is inverted through the air pressure fluctuation curve in the sealing tank. In addition, multiple piezoelectric sensors are arranged in the first sealing groove along the circumferential direction, 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 test device for the aircraft sealing strip can test the failure mechanism of the aircraft sealing strip under the conditions of simulating the coupling of air pressure, temperature and wind field external force. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] The accompanying drawings constituting a part of the present invention are used to provide a further understanding of the present invention. The exemplary embodiments of the present invention and their descriptions are used to explain the present invention and do not constitute an improper limitation of the present invention. In the accompanying drawings: Figure 1 is a cross-sectional view of a multi-physics field coupling dynamic testing device for an aircraft sealing strip provided by a specific embodiment of the present invention; Figure 2 It is a partial structural schematic diagram of a multi-physical field coupling dynamic testing device for an aircraft sealing strip provided by a specific embodiment of the present invention; Figure 3 It is a structural schematic diagram of a multi-physical field coupling dynamic testing device for an aircraft sealing strip provided by a specific embodiment of the present invention; Figure 4 It is a structural schematic diagram of the blowing structure of the multi-physical field coupling dynamic testing device for aircraft sealing strips provided by a specific embodiment of the present invention; Figure 5 It is a structural schematic diagram of a ball joint structure of a multi-physical field coupling dynamic testing device for an aircraft sealing strip provided by a specific embodiment of the present invention; Figure 6is a partial cross-sectional view of a multi-physics field coupling dynamic testing device for an aircraft sealing strip provided by a specific embodiment of the present invention; Figure 7 It is a structural schematic diagram of a sealing tank of a multi-physical field coupling dynamic testing device for an aircraft sealing strip provided by a specific embodiment of the present invention; Figure 8 It is a structural schematic diagram of a tank cover of a multi-physical field coupling dynamic testing device for an aircraft sealing strip provided by a specific embodiment of the present invention.

[0016] In the figure: 11. Box body; 12. Sealing plate; 13. Adapter plate; 111. Second sealing groove; 121. Third sealing groove; 131. Fourth sealing groove; 21. tank body; 22. tank cover; 221. first sealing groove; 3. Load plate; 41. first air inlet nozzle; 42. first air outlet nozzle; 43. second air inlet nozzle; 44. second air outlet nozzle; 51. First cooling module; 52. First heating module; 53. First temperature sensor; 54. Second cooling module; 55. Second heating module; 56. Second temperature sensor; 6. Blowing structure; 61. Telescopic rod; 62. Connecting frame; 63. Connecting plate; 64. Fan; 65. Wire pulling device; 66. Lead ring; 67. Wire locking device; 68. Ball head; 69. Locking ring; 7. Thermal insulation layer; 8. Piezoelectric sensor. DETAILED DESCRIPTION

[0017] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely explain the technical solutions in the embodiments of the present invention. It should be noted that the embodiments of the present invention and the features in the embodiments can be combined with each other without conflict, and the described embodiments are only part of the embodiments of the present invention, not all of the embodiments.

[0018] In the description of the present invention, unless otherwise clearly specified and limited, the terms "connected", "connected", and "fixed" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium, it can be the internal connection of two elements or the interaction relationship between two elements. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0019] In the present invention, unless otherwise clearly specified and limited, a first feature being "above" or "below" a second feature may include that the first and second features are in direct contact, or may include that the first and second features are not in direct contact but are in contact through another feature between them. Moreover, a first feature being "above", "above" and "above" a second feature includes that the first feature is directly above and obliquely above the second feature, or simply indicates that the first feature is higher in level than the second feature. A first feature being "below", "below" and "below" a second feature includes that the first feature is directly below and obliquely below the second feature, or simply indicates that the first feature is lower in level than the second feature.

[0020] In the description of this embodiment, the terms "upper", "lower", "right" and other directions or positional relationships are based on the directions or positional relationships shown in the drawings, and are only for the convenience of description and simplified operation, rather than indicating or implying that the device or element referred to must have a specific direction, be constructed and operated in a specific direction, and therefore cannot be understood as limiting the present invention. In addition, the terms "first" and "second" are only used to distinguish in the description and have no special meaning.

[0021] See also Figure 1-8 To describe this embodiment, the present invention provides a multi-physical field coupling dynamic testing device and a testing method for an aircraft sealing strip, wherein the multi-physical field coupling dynamic testing device for an aircraft sealing strip comprises a support seat, 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, wherein the sealing box is fixedly arranged above the support seat, the sealing tank comprises a tank body 21 and a tank cover 22, the tank body 21 is detachably connected to the sealing box, the tank cover 22 is covered on the tank body 21, the tank body 21 and the tank cover 22 are both located in the sealing box, the load plate 3 is fixedly arranged on the tank cover 22 and is located in 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 temperature in the sealing box and the sealing tank, the pressure control component can respectively control the gas pressure in the sealing box and the sealing tank, and the wind field control component can generate wind in any direction to blow toward the load plate 3.

[0022] The multi-physical field coupling dynamic test device for the aircraft sealing strip, the sealed tank is used to simulate the aircraft cabin environment, the sealed box is used to simulate the aircraft external environment, 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. The dynamic working condition simulation can be performed by 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 gradually, thereby simulating the air pressure change caused by the change of the aircraft flight altitude; 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 gradually, thereby simulating the temperature change caused by the change of the aircraft flight altitude; the wind field control component is used to blow air at different angles on the load plate 3 to simulate the flow wind field, and the wind field control component can simulate a multi-directional wind field, simulating the scene of the aircraft being subjected to wind from various directions when flying. The air pressure in the sealed box and the sealed tank is monitored in real time, and the leakage rate change of the sealing strip to be tested is inverted through the air pressure fluctuation curve in the sealed tank. The multi-physics field coupled dynamic testing device for the aircraft sealing strip can test the failure mechanism of the aircraft sealing strip under the coupled working conditions of simulating air pressure, temperature and wind field external force.

[0023] It is understandable that the wind force blown by the wind field control assembly toward the load plate 3 will be transmitted to the tank cover 22 through the load plate 3, thereby affecting the sealing strip to be tested.

[0024] In this embodiment, the support seat adopts a heavy alloy support seat, which can ensure the structural stability of the sealing box under extreme working conditions.

[0025] Optionally, the sealed box is provided with 5 slideways, the wind field control assembly includes 5 blowing structures 6, the 5 blowing structures 6 are all slidably arranged on the slideways, one blowing structure 6 is located directly in front of the load plate 3, and the other four blowing structures 6 are respectively located above, below, on the left and on 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. Each blowing structure 6 can blow air alone, or any number of blowing structures 6 can cooperate to blow air.

[0026] In this embodiment, the slideways located above and below the loading plate 3 extend in the horizontal direction, and the slideways located in front of, on the left side and on the right side of the loading plate 3 extend in the vertical direction.

[0027] 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 arranged on the slideway. One end of the telescopic rod 61 is transmission 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 a ball joint structure. The connecting plate 63 is fixedly connected to the fan 64. The traction structure includes a traction line, a wire pulling device 65, a lead ring 66 and a locking wire device 67. The wire pulling device 65 and the lead ring 66 are arranged at intervals on the connecting frame 62. The locking wire device 67 is arranged on the connecting plate 63. The traction line passes through the wire pulling device 65, the lead ring 66 and the locking wire device 67 in sequence. The locking wire device 67 can fix one end of the traction line to the connecting plate 63. The wire pulling device 65 can tighten or loosen the traction line to drive the fan 64 to change its angle relative to the telescopic rod 61. The motor can drive the telescopic rod 61 to extend and retract, and the telescopic rod 61 drives the connecting frame 62, the connecting plate 63, the fan 64 and the traction structure to move together, thereby adjusting the distance between the fan 64 and the load plate 3. The traction structure is used to adjust the angle of the fan 64, thereby realizing the universal adjustment of the fan 64. In this embodiment, there are four traction structures, 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 adjust the deflection angle.

[0028] In this embodiment, the specific structure of the wire pulling device 65 is prior art and will not be described in detail here.

[0029] Specifically, the ball joint structure includes a ball head 68, a locking ring 69 and a ball groove. The ball groove is arranged on the connecting plate 63, and the ball head 68 is embedded in the ball groove. The ball groove is semicircular. The ball head 68 is passed through the locking ring 69. The upper hemisphere of the ball head 68 abuts against the inner ring of the locking ring 69, and the locking ring 69 is fixedly connected to the connecting plate 63.

[0030] 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 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. In this embodiment, the refrigeration module located in the sealed box is a first refrigeration module 51, the heating module located in the sealed box is a first heating module 52, the temperature sensor located in the sealed box is a first temperature sensor 53, the temperature sensor located in the sealed tank is a second temperature sensor 56, the refrigeration module located in the sealed tank is a second refrigeration module 54, and the heating module located in the sealed tank is a second heating module 55.

[0031] Optionally, the pressure control assembly includes two air inlet nozzles, two air outlet nozzles and two pressure relief valves, the two air inlet nozzles are respectively arranged in the sealed box and the sealed tank, the two air outlet nozzles are respectively arranged in the sealed box and the sealed tank, the two pressure relief valves are arranged in one-to-one correspondence with the two air outlet nozzles, and the two air inlet nozzles and the two air outlet nozzles are provided with pressure gauges. Both the air inlet nozzle and the air outlet nozzle adopt airtight nozzles. The air inlet nozzle and the air outlet nozzle can realize two-way air flow balance regulation. In this embodiment, the air inlet nozzle arranged in the sealed box is the first air inlet nozzle 41, the air outlet nozzle arranged in the sealed box is the first air outlet nozzle 42, the air inlet nozzle arranged in the sealed tank is the second air inlet nozzle 43, and the air outlet nozzle arranged in the sealed tank is the second air outlet nozzle 44. The sealed box is inflated through the first air inlet nozzle 41, the sealed box is deflated through the first air outlet nozzle 42, and the air pressure in the sealed box is adjusted through the first air inlet nozzle 41 and the first air outlet nozzle 42. The sealed can is inflated through the second air inlet nozzle 43 , and the sealed can is deflated through the second air outlet nozzle 44 . The air pressure in the sealed can is adjusted through the second air inlet nozzle 43 and the second air outlet nozzle 44 .

[0032] In this embodiment, both the air inlet nozzle and the air outlet nozzle are connected to a pressure gauge, so that the air pressure change can be monitored in real time during the test.

[0033] In this embodiment, the air inlet nozzle and the air outlet nozzle are both configured with independent air pressure buffer structures, and a pressure relief valve is also provided at the air outlet nozzle to ensure pressure stability.

[0034] Optionally, the multi-physical field coupled dynamic testing device for the aircraft sealing strip further comprises a plurality of piezoelectric sensors 8, which are arranged in the first sealing groove 221 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.

[0035] The sealing strip to be tested is subjected to different loads, and its sealing effect is also different. When a circle of the sealing strip to be tested is subjected to uneven loads, the sealing effects at different positions are different. Therefore, a plurality of piezoelectric sensors 8 are provided 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 uneven load, thereby monitoring the rebound characteristics of each position of the sealing strip to be tested in real time.

[0036] 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 can is detachably connected to the adapter plate 13. The adapter plate 13 can be replaced according to the size of the sealed can, so that the sealed box can be connected to sealed cans of different sizes.

[0037] Optionally, the multi-physics field coupling dynamic test device for the aircraft sealing strip further comprises 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, 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 sealing tank. The first sealing ring, the second sealing ring and the third sealing ring can achieve sealing between the sealing box and the outside world.

[0038] Optionally, the inner wall of the sealed can is fixedly provided with a heat insulation layer 7. The heat insulation layer 7 isolates the ambient temperature inside and outside the sealed can.

[0039] In this embodiment, the sealed can is a pressure-resistant sealed can.

[0040] The present invention also provides a multi-physical field coupling dynamic testing method for an aircraft sealing strip, using the multi-physical field coupling dynamic testing device for an aircraft sealing strip, specifically comprising: A sealed tank is used to simulate the environment inside the aircraft cabin and set the internal environment parameters. Gas is introduced into the sealed tank through the air pressure control component to control the air pressure inside the sealed tank to reach the first set pressure, and the temperature control component is used to adjust the temperature inside the sealed tank to reach the first set temperature. If the pressure changes after adjusting the temperature, the pressure can be fine-tuned.

[0041] A sealed box is used to simulate the external environment and set the external environment parameters. Gas is introduced into the sealed box through the air pressure control component to control the air pressure in the sealed box to reach the second set pressure, and the temperature control component is used to adjust the temperature in the sealed box to reach the second set temperature. If the pressure changes after adjusting the temperature, the pressure can be fine-tuned.

[0042] Dynamic working condition simulation is performed, and 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 gradually, thereby simulating the air pressure change caused by the change of the aircraft's flight altitude; 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 gradually, thereby simulating the temperature change caused by the change of the aircraft's flight altitude; the load plate 3 is blown at different angles by the wind field control component to simulate the flow wind field.

[0043] The test condition can be established by the curve of temperature and air pressure changing with the aircraft's altitude increase, or the test condition 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, and the load plate 3 is blown at different angles and different wind speeds at the required temperature and pressure for testing, thereby constructing a coupled physical field of temperature, air pressure and wind field external force.

[0044] In-situ monitoring, real-time monitoring of the air pressure in the sealing box and the sealing tank, inversion of the leakage rate change of the sealing strip to be tested through the air pressure fluctuation curve in the sealing tank, and real-time monitoring of the rebound characteristics of the sealing strip to be tested through the piezoelectric sensor 8.

[0045] Obviously, the embodiments of the present invention disclosed above are only used to help illustrate 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. This specification selects and specifically describes these embodiments in order to better explain the principles and practical applications of the present invention, so that those skilled in the art can understand and use the present invention well. It is not necessary and impossible to exhaustively list all the embodiments here.

Claims

1. A multi-physics field coupling dynamic testing device for aircraft sealing strips, characterized in that: include: Support seat; A sealing box, which is fixedly arranged above the supporting seat; A sealed can, comprising a can body (21) and a can cover (22), wherein the can body (21) is detachably connected to a sealed box, the can cover (22) is disposed on the can body (21), and both the can body (21) and the can cover (22) are located in the sealed box; A load plate (3), the load plate (3) is fixedly arranged on the tank cover (22) and is located in the sealed box; The sealing strip to be tested, the can cover (22) is provided with a first sealing groove (221), the sealing strip to be tested is arranged in the first sealing groove (221) and is located between the can body (21) and the can cover (22); A temperature control component, which can control the temperature in the sealed box and the sealed tank respectively; A pressure control component, which can control the gas pressure in the sealed box and the sealed tank respectively; A wind field control component can generate wind in any direction to blow toward the load plate (3).

2. The multi-physical field coupling dynamic testing device for aircraft sealing strips according to claim 1, characterized in that: Five slideways are arranged in the sealed box, and the wind field control component includes five blowing structures (6), and the five 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, on the left and on the right of the load plate (3), and 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).

3. The multi-physical field coupling dynamic testing device for aircraft sealing strips according to claim 2, characterized in that: The adjustment structure comprises 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 arranged on the slideway. One end of the telescopic rod (61) is transmission-connected to the motor, and the other end is fixedly connected to the connecting frame (62). The connecting frame (62) and the connecting plate (63) are connected via the ball joint structure. The connecting plate (63) and the fan (64) are fixedly connected. The traction structure comprises a traction line, a wire pulling device (65), a wire lead ring (66) and A wire locking device (67), a wire pulling device (65) and a wire lead 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 lead 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 fan (64) to change its angle relative to the telescopic rod (61).

4. The multi-physics field coupling dynamic testing device for aircraft sealing strips according to claim 1, characterized in that: 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 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.

5. The multi-physics field coupling dynamic testing device for aircraft sealing strips according to claim 1, characterized in that: 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 sealed box and the sealed tank, and the two air outlet nozzles are respectively arranged in the sealed box and the sealed tank. The two pressure relief valves are arranged in a one-to-one correspondence with the two air outlet nozzles, and the two air inlet nozzles and the two air outlet nozzles are all provided with pressure gauges.

6. The multi-physics field coupling dynamic testing device for aircraft sealing strips according to claim 1, characterized in that: It also comprises a plurality of piezoelectric sensors (8), which are arranged at intervals in the first sealing groove (221) along the circumferential direction of the first sealing groove (221) and are used to monitor the rebound characteristics of the sealing strip to be tested in real time.

7. The multi-physics field coupling dynamic testing device for aircraft sealing strips according to claim 1, characterized in that: The sealed box comprises 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).

8. The multi-physics field coupling dynamic testing device for aircraft sealing strips according to claim 7, characterized in that: The invention also comprises a first sealing ring, a second sealing ring and a third sealing ring, wherein the box body (11) is provided with a second sealing groove (111), the sealing plate (12) is provided with a third sealing groove (121), 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 sealing tank.

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

10. A multi-physics field coupling dynamic testing method for an aircraft sealing strip, characterized in that: The multi-physics field coupling dynamic testing device for an aircraft sealing strip according to any one of claims 1 to 9 comprises: A sealed tank is used to simulate the environment inside the aircraft cabin and set the internal environment parameters, gas is introduced into the sealed tank through the air pressure control component and the air pressure in the sealed tank is controlled to reach a first set pressure, and the temperature in the sealed tank is adjusted to reach a first set temperature through the temperature control component; A sealed box is used to simulate the external environment and set the external environment parameters, gas is introduced into the sealed box through the air pressure control component and the air pressure in the sealed box is controlled to reach a second set pressure, and the temperature in the sealed box is adjusted to reach a second set temperature through the temperature control component; Dynamic working condition simulation is performed, 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 gradually, thereby simulating the air pressure change caused by the change of 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 gradually, thereby simulating the temperature change caused by the change of the flight altitude of the aircraft; the load plate (3) is blown at different angles by the wind field control component to simulate the flow wind field; In-situ monitoring: real-time monitoring of the air pressure in the sealed box and sealed tank, and inversion of the leakage rate change of the tested sealing strip through the air pressure fluctuation curve in the sealed tank.

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