A new type of aviation power supply comprehensive test bench

Abstract

The application discloses a novel aviation power supply comprehensive test bench applied to the field of vibration test, and the test bench is provided with a detection cover outside an airplane storage battery; when the airplane storage battery is deformed under extreme vibration test conditions, the air bag can detect the position where the deformation first occurs, thereby providing a reference for testers, facilitating corresponding improvement in the later period, and the infrared array temperature sensor is used to monitor the thermal runaway of the airplane storage battery in real time, and the pressure touch type color changing plate and the light type color changing ring are used to mark the first deformation position and the specific position where the thermal runaway occurs, so that researchers can obtain more detailed test data, targeted research and analysis are carried out, and in addition, the fire extinguishing cover can be used to extinguish fire when the airplane storage battery catches fire, the test bench is effectively prevented from being eroded by the flame, and the safety of the test bench is effectively protected.

Description

Technical Field

[0001] This invention relates to the field of vibration testing, and in particular to a novel integrated test bench for aviation power supplies. Background Technology

[0002] Aircraft batteries are an important component of aviation power systems, primarily used as auxiliary and emergency power sources. When the aircraft engines fail to start or the main power supply malfunctions, batteries can provide power to critical loads such as electrical mechanisms, electronic equipment, and lighting systems.

[0003] To ensure the safe and reliable operation of batteries under various extreme conditions, it is necessary to test their electrical performance by simulating real flight environments on the ground. For example, a ground simulation test system for aircraft power systems (announcement number CN220137342U) has the advantages of simulating the prime mover of the main generator under test by driving it to rotate via a drive platform; simulating the aircraft power distribution system by providing 28.5V and 115V / 400Hz power to the load through a power distribution system test model; collecting data from the drive platform and power distribution system test model through an aviation power test system; controlling and displaying the test platform through a comprehensive test management system; and supplying power to the dedicated test equipment through special power supplies and instruments.

[0004] However, the above tests lack mechanical testing of the battery. Therefore, CN213041465U discloses a battery vibration testing device that uses a clamping device with fastening bolts and clamps to easily fix batteries of different sizes onto the vibration base, ensuring stability and reliability, preventing damage to the battery casing, and preventing them from falling off during vibration. The device is located in the middle of the vibration base to prevent liquid leakage from the battery during the test, which could lead to corrosion damage to the metal platform.

[0005] Existing testing equipment mainly uses clamps to prevent liquid leakage when conducting vibration tests on batteries. However, in actual testing, in order to cope with extreme flight environments, it is necessary to test the limit test value of the battery when it is damaged. Therefore, destructive tests are also conducted. However, existing test benches cannot effectively protect the test bench after the battery is damaged and a fire occurs, and they also cannot detect the damage points accordingly. Summary of the Invention

[0006] The core of this invention lies in solving the problem of the inability to protect the test bench in existing technologies by setting up a protective device. It can also mark the specific locations where battery damage or thermal runaway occurs, facilitating research, analysis, and improvement by testing personnel.

[0007] To solve the above problems, the present invention adopts the following technical solution.

[0008] A novel integrated test bench for aviation power supplies includes a test cabinet and an aircraft battery. The test cabinet has a sealed door at its opening. Inside the test cabinet, at the bottom, is a vibration table driven by a vibration motor. The upper end of the vibration table is fixedly connected to a mounting platform. The inner wall of the test cabinet has a pair of coolers symmetrically distributed on both sides of the mounting platform. Above the mounting platform, the test cabinet is equipped with a battery integrated tester. The battery integrated tester is connected to the positive and negative terminals of the aircraft battery via two wires. A pressure controller is installed on the side wall of the test cabinet facing the sealed door. The aircraft battery is mounted on the mounting platform with fixing bolts. The mounting platform, located outside the aircraft battery, is also connected to a test cover with fixing bolts.

[0009] The detection cover includes a transparent indicator box, an airbag fixedly connected to the inside of the transparent indicator box, an air valve installed on the upper end of the airbag, and a thin-film pressure sensor fixedly embedded in the side wall of the airbag.

[0010] The test cabinet includes an environmental control unit, an alarm unit, and an emergency stop unit. The environmental control unit is connected to the vibration motor, the cooler, and the air pressure controller via a microcontroller. The alarm unit is connected to the battery comprehensive tester. The emergency stop unit is connected to the vibration motor.

[0011] Furthermore, the airbag is made of a flexible, heat-conducting material, and the airbag and the side wall of the transparent indicator box form a sealed space.

[0012] Furthermore, the sealed space is filled and released with gas via a valve, and the gas used is an inert gas.

[0013] Preferably, an infrared array temperature sensor is also fixedly embedded in the inner wall of the transparent indicator box facing the thin-film pressure sensor. The inner wall of the transparent indicator box has a cavity, and multiple arrays of fixed cylinders and magnetic telescopic cylinders perpendicular to the outer wall of the transparent indicator box are fixedly connected to the inner wall of the cavity near the airbag. The magnetic telescopic cylinder is inserted into the fixed cylinder and slidably connected to it. A tension spring is fixedly connected between the magnetic telescopic cylinder and the inner wall of the fixed cylinder. A pressure head is fixedly connected to the end of the magnetic telescopic cylinder away from the fixed cylinder. An electromagnet connected to the thin-film pressure sensor signal is installed on the inner wall of the fixed cylinder facing the magnetic telescopic cylinder. The electromagnet repels the magnetic telescopic cylinder when energized. An LED light with a ring array is fixedly connected to the side wall of the magnetic telescopic cylinder. The LED light is connected to the infrared array temperature sensor signal. Multiple arrays of pressure-sensitive color-changing plates and light-sensitive color-changing rings are fixedly embedded in the outer wall of the transparent indicator box.

[0014] Furthermore, the pressure-sensitive color-changing panel faces the pressure head, and the light-emitting color-changing ring faces the LED light. The pressure-sensitive color-changing panel uses force-sensitive color-changing material, and the light-emitting color-changing ring uses photosensitive color-changing material.

[0015] Optionally, a pair of guide plates are fixedly connected to the side wall of the test cabinet above the cooler, and the side wall of the guide plates is provided with guide grooves. A connecting frame is slidably connected in both guide grooves, and a fire extinguishing cover is fixedly connected between the two connecting frames. The lower side wall of the fire extinguishing cover is provided with a fireproof groove that matches the detection cover, and the middle of the fire extinguishing cover is provided with a through hole that matches the wire. The upper inner wall of the guide plate is provided with a groove, and an electromagnet II connected to the infrared array temperature sensor signal is installed inside the groove. A limiting block that magnetically attracts the electromagnet II is slidably connected inside the groove through a compression spring, and a limiting groove that engages with the limiting block is provided on the side wall of the connecting frame.

[0016] Furthermore, the fire extinguishing cover is initially positioned directly above the detection cover, and the fire extinguishing cover is made of flame-retardant material.

[0017] Furthermore, the inner walls on both sides of the fire extinguishing cover are provided with liquid storage chambers, and the liquid storage chambers are saturated with fire extinguishing agent. The bottom of the liquid storage chamber is connected to the fireproof tank, and a sealing membrane is fixedly connected at the connection. An elastic sling is fixedly connected to the top of the liquid storage chamber, and a spike is fixedly connected to the lower end of the elastic sling.

[0018] Compared with the prior art, the advantages of this invention are:

[0019] (1) This scheme simulates the real flight vibration environment by setting up a vibration table, simulates the temperature environment during flight by using a cooler, and simulates the air pressure environment during flight by using an air pressure controller. It effectively simulates the real flight environment, thereby effectively improving the accuracy of the test results. By adding a detection cover to the outside of the aircraft battery, when the aircraft battery deforms under extreme vibration test conditions, the airbag can be used to detect the first deformation location, thus providing a reference for the test personnel and facilitating corresponding improvements later. After the aircraft battery is deformed and damaged, the detection cover can also prevent liquid leakage and contamination of the test table.

[0020] (2) The infrared array temperature sensor is used to monitor the thermal runaway of the aircraft battery in real time, and the pressure-sensitive color-changing plate and the light-sensitive color-changing ring are used to mark the first deformation position and the specific location of thermal runaway, which helps researchers obtain more detailed test data for targeted research and analysis. In addition, when the aircraft battery catches fire, the fire can be extinguished by the fire extinguishing cover, which effectively prevents the test bench from being eroded by the flame and effectively protects the safety of the test bench. Attached Figure Description

[0021] Figure 1 This is a perspective view of the test bench of the present invention;

[0022] Figure 2 This is a diagram showing the sequence of installing the battery and the detection cover in this invention;

[0023] Figure 3 This is a diagram showing the state of the fire extinguishing cover of the present invention during fire extinguishing;

[0024] Figure 4 This is a perspective view of the detection cover of the present invention;

[0025] Figure 5 This is a side cross-sectional view of the detection cover of the present invention;

[0026] Figure 6 for Figure 5 Enlarged view of the structure at point A in the middle;

[0027] Figure 7 This is a state diagram of the contact head of the present invention when indicating the deformation position and thermal runaway position of the battery;

[0028] Figure 8 This is a structural diagram showing the distribution of the pressure-sensitive color-changing plate and the light-emitting color-changing ring of the present invention;

[0029] Figure 9 This is a diagram showing the state of the fire extinguishing cover of the battery before it catches fire, according to the present invention.

[0030] Figure 10 This is a diagram showing the state of the fire extinguishing cover of the battery of the present invention after a fire.

[0031] Explanation of the labels in the diagram:

[0032] 1. Test cabinet, 2. Sealed cabinet door, 3. Vibration table, 4. Mounting platform, 5. Refrigerator, 6. Battery comprehensive tester, 7. Air pressure controller, 8. Detection cover, 801. Transparent indicator box, 8011. Pressure-sensitive color-changing plate, 8012. Illuminated color-changing ring, 802. Airbag, 803. Air valve, 804. Thin-film pressure sensor, 805. Infrared array temperature sensor, 9. Aircraft battery, 10. Fixed cylinder, 11. Magnetic telescopic cylinder, 12. Contact head, 13. Electromagnet I, 14. LED light, 15. Fire extinguishing cover, 1501. Fireproof groove, 16. Guide plate, 1601. Guide groove, 17. Connecting frame, 1701. Limiting groove, 18. Electromagnet II, 19. Limiting block, 20. Sealing membrane, 21. Elastic sling, 22. Spike. Detailed Implementation

[0033] The technical solutions will now be clearly and completely described with reference to the accompanying drawings in the embodiments of the present invention.

[0034] First implementation method:

[0035] Please see Figure 1 , 2 and Figure 3A novel integrated test bench for aviation power supplies includes a test cabinet 1 and an aircraft battery 9. The test cabinet 1 has a sealed door 2 at its opening. Inside the test cabinet 1, at its bottom, is a vibration table 3 driven by a vibration motor (the specific model is selected based on actual requirements and will not be described in detail here). The upper end of the vibration table 3 is fixedly connected to a mounting platform 4. A pair of coolers 5 (the specific model is selected based on actual requirements and will not be described in detail here) symmetrically distributed on both sides of the mounting platform 4 are installed on the inner wall of the test cabinet 1. Above the mounting platform 4, the test cabinet 1 is equipped with a battery integrated tester 6 (the specific model is selected based on actual requirements and will not be described in detail here). The battery integrated tester 6 is connected to the positive terminal of the aircraft battery 9 via two wires. The positive and negative terminals are connected. A pressure controller 7 (the specific model is selected according to actual needs and will not be described in detail here) is installed on the side wall of the test cabinet 1 opposite the sealed cabinet door 2. The aircraft battery 9 is mounted on the mounting platform 4 with fixing bolts, and the mounting platform 4 is located outside the aircraft battery 9 and is also connected to a test cover 8 with fixing bolts. The test cabinet 1 includes an environmental control unit, an alarm unit, and an emergency stop unit. The environmental control unit is connected to the vibration motor, the cooler 5, and the pressure controller 7 via a microprocessor. The alarm unit is connected to the battery comprehensive tester 6, and the emergency stop unit is connected to the vibration motor (the specific control logic of this part is well-known technology to those skilled in the art and will not be described in detail here). Before testing, first... The aircraft battery 9 is mounted on the mounting platform 4 using fixing bolts. Then, the test cover 8 is placed over the aircraft battery 9 and secured with fixing bolts. Next, the test cover 8 is inflated using external inflation equipment. After inflation, the test cover 8 expands and encloses the aircraft battery 9. The battery comprehensive tester 6 is connected to the positive and negative terminals of the aircraft battery 9 using wires. Finally, the sealed cabinet door 2 is locked to begin testing. Once testing begins, the vibration motor is started to vibrate the aircraft battery 9, simulating the vibration environment during flight. The cooler 5 is started to cool the inside of the test cabinet 1, simulating the low-temperature environment during flight. The pressure controller 7 is started to reduce the air pressure inside the test cabinet 1, simulating the low-pressure environment during flight. Finally, the battery comprehensive tester 6 is started to perform the test. The electrical performance of aircraft battery 9, including voltage, capacity, internal resistance, and charge / discharge status, is measured and the test data is sent to a backend computer. During the test, the vibration frequency and amplitude of the vibration motor, the temperature value and temperature fluctuation range of the cooler 5, and the air pressure value and air pressure fluctuation range of the air pressure controller 7 are dynamically adjusted by the environmental control unit to simulate a near-realistic flight environment, making the test more accurate. During the test, if the battery comprehensive tester 6 detects that the electrical performance of aircraft battery 9 exceeds the set safety threshold, the alarm unit is triggered to issue an alarm, and the emergency stop unit is triggered to stop the vibration motor, thus promptly interrupting the test to prevent further damage to aircraft battery 9 and potential fire.The vibration motor, cooler 5, and pressure controller 7 work together to create a near-real flight environment for the aircraft battery 9. Compared to existing technologies that only perform vibration testing at normal temperature and pressure on the ground, this embodiment can detect the electrical performance of the aircraft battery 9 in a near-real flight environment, resulting in highly reliable test data.

[0036] Please see Figure 4 and Figure 5 The detection cover 8 includes a transparent indicator box 801, an airbag 802 fixedly connected to the inside of the transparent indicator box 801, an air valve 803 installed on the upper end of the airbag 802, and a thin-film pressure sensor 804 (the specific model is selected according to actual needs and will not be described in detail here) fixedly embedded in the side wall of the airbag 802. The airbag 802 is made of flexible thermally conductive material (rubber is preferred, but other materials can also be selected according to actual needs). The airbag 802 and the side wall of the transparent indicator box 801 form a sealed space. The sealed space is inflated and deflated by the air valve 803, and the gas used is an inert gas. The detection cover 8 is then placed over the airbag. After the aircraft battery 9 is placed outside, inert gas is injected into the airbag 802 through the air valve 803 using an inflation device. After the airbag 802 is inflated, it expands and wraps around the aircraft battery 9. The thin-film pressure sensor 804 is tightly attached to the outer surface of the aircraft battery 9. The initial value is the detection value of the thin-film pressure sensor 804 before the test begins. After the test begins, if the aircraft battery 9 deforms under vibration, low temperature, and low pressure, the thin-film pressure sensor 804 can detect the location of the deformation of the aircraft battery 9 in a timely manner according to the change of pressure value, thereby providing the testers with accurate test data for later research and analysis.

[0037] This embodiment simulates the real flight vibration environment by setting up a vibration table 3, simulating the temperature environment during flight by using a cooler 5, and simulating the air pressure environment during flight by using an air pressure controller 7. This effectively simulates the real flight environment and thus improves the accuracy of the test results. By adding a detection cover 8 to the outside of the aircraft battery 9, when the aircraft battery 9 deforms under extreme vibration test conditions, the airbag 802 can detect the location where the deformation first occurs, thus providing a reference for the testers and facilitating corresponding improvements later. After the aircraft battery 9 is deformed and damaged, the detection cover 8 can also prevent liquid leakage and contamination of the test table.

[0038] Second implementation method:

[0039] In the first embodiment, the deformation of the aircraft battery 9 is detected by relying solely on the thin-film pressure sensor 804. However, such deformation is merely an external change such as bulging or shell cracking. Under vibration, the aircraft battery 9 will also experience internal structural damage and diaphragm rupture. These changes will inevitably cause short circuits and lead to thermal runaway. Therefore, this embodiment uses an infrared array temperature sensor 805 to monitor the temperature change of the aircraft battery 9 to indirectly know the internal condition of the aircraft battery 9.

[0040] Please see Figure 6 , 7 and Figure 8An infrared array temperature sensor 805 (the specific model is selected according to actual needs and will not be described in detail here) is also fixedly embedded in the inner wall of the transparent indicator box 801 opposite to the thin film pressure sensor 804. A cavity is formed in the inner wall of the transparent indicator box 801, and multiple arrays of fixed cylinders 10 and magnetic telescopic cylinders 11 perpendicular to the outer wall of the transparent indicator box 801 are fixedly connected to the cavity near the inner wall of the airbag 802. The magnetic telescopic cylinder 11 is inserted into the fixed cylinder 10 and slidably connected to it. A tension spring is fixedly connected between the magnetic telescopic cylinder 11 and the inner wall of the fixed cylinder 10. A pressure head 12 is fixedly connected to the end of the magnetic telescopic cylinder 11 away from the fixed cylinder 10. A device for the thin film pressure sensor is installed on the inner wall of the fixed cylinder 10 opposite to the magnetic telescopic cylinder 11. Electromagnet 13 (specific model selected according to actual needs, not described in detail here) is connected to the signal of device 804. Electromagnet 13 repels the magnetic telescopic cylinder 11 when energized. A ring array of LED lights 14 is fixedly connected to the side wall of the magnetic telescopic cylinder 11, and the LED lights 14 are connected to the infrared array temperature sensor 805. Multiple sets of arrayed pressure-sensitive color-changing plates 8011 and light-sensitive color-changing rings 8012 are fixedly embedded in the outer wall of the transparent indicator box 801. The pressure-sensitive color-changing plate 8011 faces the pressure head 12, and the light-sensitive color-changing ring 8012 faces the LED lights 14 (specific models selected according to actual needs, not described in detail here). The pressure-sensitive color-changing plate 8011 uses a force-sensitive color-changing material, and the light-sensitive color-changing ring... The ring 8012 uses photochromic material. When the internal structure of the aircraft battery 9 is damaged, causing a short circuit, a large amount of heat is generated. The infrared array temperature sensor 805 monitors the temperature change of the aircraft battery 9 in real time. When a short circuit occurs at a certain point inside the aircraft battery 9, the heat is transferred to the outer surface of the aircraft battery 9, and then to the airbag 802. Finally, it is detected by the infrared array temperature sensor 805. The infrared array temperature sensor 805 activates the corresponding LED light 14 based on the detected temperature change. The light emitted by the LED light 14 shines on the photochromic ring 8012, and the photochromic ring 8012 changes color under the light. Testers can determine the location of the color change by observing the position of the color change from the outside. The approximate location of the internal damage to the aircraft battery 9 is indicated, facilitating later analysis and research. Additionally, when the membrane pressure sensor 804 detects deformation of the aircraft battery 9, it activates the corresponding electromagnet 13. When energized, the electromagnet 13 repels the magnetic telescopic cylinder 11, causing the magnetic telescopic cylinder 11 to drive the pressure head 12 to press against the pressure-sensitive color-changing plate 8011. The pressure-sensitive color-changing plate 8011 changes color upon compression, marking the location of the deformation in the aircraft battery 9. Together, the pressure-sensitive color-changing plate 8011 and the light-sensitive color-changing ring 8012 visually mark the locations of internal and external damage to the aircraft battery 9. This provides reliable experimental data for later research and improvement, contributing to the refinement of the aircraft battery 9.

[0041] This embodiment also uses an infrared array temperature sensor 805 to monitor the thermal runaway of the aircraft battery 9 in real time, and uses a pressure-sensitive color-changing plate 8011 and an illumination-sensitive color-changing ring 8012 to mark the location of the first deformation and the specific location of the thermal runaway, helping researchers to obtain more detailed test data for targeted research and analysis.

[0042] The third implementation method:

[0043] In the second embodiment, the huge heat generated by the internal short circuit of the aircraft battery 9 will cause thermal runaway of the battery, which will eventually lead to a fire. In order to prevent the test bench from being damaged, a fire extinguishing cover 15 is added for protection.

[0044] Please see Figure 9 and Figure 10 A pair of guide plates 16 are fixedly connected to the side wall of the test cabinet 1 above the cooler 5. The side walls of the guide plates 16 have guide grooves 1601. Connecting brackets 17 are slidably connected within each of the two guide grooves 1601, and a fire extinguishing cover 15 is fixedly connected between the two connecting brackets 17. The fire extinguishing cover 15 is initially positioned directly above the detection cover 8. The fire extinguishing cover 15 is made of flame-retardant material. A fireproof groove 1501 matching the detection cover 8 is opened on the lower side wall of the fire extinguishing cover 15, and a through-hole matching the wire is opened in the middle of the fire extinguishing cover 15. A groove is opened on the upper inner wall of the guide plates 16, and an electromagnet 2 18 (specific model depends on actual requirements) is installed inside the groove, which is connected to the infrared array temperature sensor 805 signal. (Selection will not be described in detail here). Inside the groove, a limiting block 19 is slidably connected to the electromagnet 18 via a compression spring. The side wall of the connecting frame 17 is provided with a limiting groove 1701 that engages with the limiting block 19. When the infrared array temperature sensor 805 detects a temperature change in the aircraft battery 9, the electromagnet 18 is immediately activated. The electromagnet 18 is energized and magnetically attracts the limiting block 19. The limiting block 19 disengages from the limiting groove 1701, and the fire extinguishing cover 15 falls freely under the action of gravity. After the fire extinguishing cover 15 falls, it seals the opening at the top of the detection cover 8 to prevent the aircraft battery 9 from igniting the device inside the test cabinet 1 after it catches fire. The fire is controlled within the detection cover 8, effectively protecting the test bench.

[0045] Please see Figure 9 and Figure 10The fire extinguishing cover 15 has liquid storage chambers on both sides of the through-hole, and the liquid storage chambers are saturated with fire extinguishing agent. The bottom of the liquid storage chamber is connected to the fireproof tank 1501, and a sealing membrane 20 is fixedly connected at the connection. An elastic sling 21 is fixedly connected to the top of the liquid storage chamber, and a spike 22 is fixedly connected to the lower end of the elastic sling 21. After the aircraft battery 9 catches fire, in order to extinguish the fire in time, the fire extinguishing cover 15 is pre-filled with fire extinguishing agent. After the flame burns through the sealing membrane 20, the fire extinguishing agent can be released. In order to ensure that the fire extinguishing agent can be released smoothly, after the fire extinguishing cover 15 falls, the inertia generated by the fall causes the spike 22 to continue to move downward. The downward movement of the spike 22 punctures the sealing membrane 20, ensuring that the fire extinguishing agent is released smoothly.

[0046] The above are merely preferred embodiments of the present invention; they encompass all the protection scope of the present invention. Any equivalent substitutions or modifications made by those skilled in the art within the technical scope disclosed in the present invention, based on the technical solutions and improved concepts of the present invention, should be covered within the protection scope of the present invention.

Claims

1. A novel integrated test bench for aviation power supplies, comprising a test cabinet (1) and an aircraft battery (9), characterized in that: The test cabinet (1) has a sealed cabinet door (2) installed at the opening. The test cabinet (1) has a vibration table (3) driven by a vibration motor installed at the bottom inside. The upper end of the vibration table (3) is fixedly connected to a mounting platform (4). The inner wall of the test cabinet (1) has a pair of coolers (5) symmetrically distributed on both sides of the mounting platform (4). The test cabinet (1) is located above the mounting platform (4) and has a battery comprehensive tester (6). The battery comprehensive tester (6) is connected to the positive and negative terminals of the aircraft battery (9) through two wires. The test cabinet (1) has a pressure controller (7) installed on the side wall facing the sealed cabinet door (2). The aircraft battery (9) is installed on the mounting platform (4) by fixing bolts. The mounting platform (4) is located outside the aircraft battery (9) and is also connected to a test cover (8) by fixing bolts. The detection cover (8) includes a transparent indicator box (801), an airbag (802) fixedly connected to the inside of the transparent indicator box (801), an air valve (803) installed on the upper end of the airbag (802), and a thin film pressure sensor (804) fixedly embedded in the side wall of the airbag (802). The test cabinet (1) includes an environmental control unit, an alarm unit and an emergency stop unit. The environmental control unit is connected to the vibration motor, the cooler (5) and the air pressure controller (7) via a microcontroller. The alarm unit is connected to the battery comprehensive tester (6) via a signal. The emergency stop unit is connected to the vibration motor via a signal. An infrared array temperature sensor (805) is also fixedly embedded in the inner wall of the transparent indicator box (801) facing the thin film pressure sensor (804). The inner wall of the transparent indicator box (801) has a cavity, and multiple sets of arrayed fixed cylinders (10) and magnetic telescopic cylinders (11) perpendicular to the outer wall of the transparent indicator box (801) are fixedly connected to the inner wall of the airbag (802). The magnetic telescopic cylinder (11) is inserted into the fixed cylinder (10) and slidably connected to it. A tension spring is fixedly connected between the magnetic telescopic cylinder (11) and the inner wall of the fixed cylinder (10). A pressure head (12) is fixedly connected to the end of the magnetic telescopic cylinder (11) away from the fixed cylinder (10). The inner wall of the fixed cylinder (10) facing the magnetic telescopic cylinder (11) is equipped with a contact head (12) for the thin film. The pressure sensor (804) is connected to an electromagnet (13), and the electromagnet (13) repels the magnetic telescopic cylinder (11) after being energized. The side wall of the magnetic telescopic cylinder (11) is fixedly connected to an LED lamp (14) arranged in a ring array, and the LED lamp (14) is connected to an infrared array temperature sensor (805). The outer side wall of the transparent indicator box (801) is fixedly inlaid with multiple sets of array-arranged pressure-sensitive color-changing plates (8011) and light-sensitive color-changing rings (8012). The pressure-sensitive color-changing plate (8011) faces the pressure head (12), and the light-sensitive color-changing ring (8012) faces the LED lamp (14). The pressure-sensitive color-changing plate (8011) is made of force-sensitive color-changing material, and the light-sensitive color-changing ring (8012) is made of photosensitive color-changing material. The test cabinet (1) is fixedly connected to a pair of guide plates (16) on the side wall above the cooler (5), and the side wall of the guide plate (16) is provided with a guide groove (1601). A connecting frame (17) is slidably connected in both guide grooves (1601), and a fire extinguishing cover (15) is fixedly connected between the two connecting frames (17). The lower side wall of the fire extinguishing cover (15) is provided with a fireproof groove (1501) that matches the detection cover (8), and the middle part of the fire extinguishing cover (15) is provided with a through hole that matches the wire. The upper inner wall of the guide plate (16) is provided with a groove, and an electromagnet (18) connected to the infrared array temperature sensor (805) is installed inside the groove. A limiting block (19) that magnetically attracts the electromagnet (18) is slidably connected inside the groove by a compression spring, and a limiting groove (1701) that engages with the limiting block (19) is provided on the side wall of the connecting frame (17).

2. The novel integrated test bench for aviation power supplies according to claim 1, characterized in that: The airbag (802) is made of a flexible thermally conductive material, and the airbag (802) and the side wall of the transparent indicator box (801) form a sealed space.

3. The novel integrated test bench for aviation power supplies according to claim 2, characterized in that: The sealed space is filled and released by a gas valve (803), and the gas used is an inert gas.

4. The novel integrated test bench for aviation power supplies according to claim 1, characterized in that: The fire extinguishing cover (15) is located directly above the detection cover (8) in the initial state, and the fire extinguishing cover (15) is made of flame-retardant material.

5. A novel integrated test bench for aviation power supplies according to claim 1, characterized in that: The fire extinguishing cover (15) has a liquid storage chamber on the inner wall on both sides of the through opening, and the liquid storage chamber is saturated with fire extinguishing agent. The bottom of the liquid storage chamber is connected to the fireproof tank (1501), and a sealing membrane (20) is fixedly connected at the connection. An elastic sling (21) is fixedly connected to the top of the liquid storage chamber, and a spike (22) is fixedly connected to the lower end of the elastic sling (21).

Images