Test system based on high-speed aircraft dynamic sealing component heat insulation performance examination

Abstract

The utility model relates to a test system based on high-speed aircraft dynamic sealing part heat insulation performance examination, which comprises an air pressure adjusting mechanism, an air heating mechanism and a sealed cabin, the air pressure adjusting mechanism comprises an air compressor, an air storage tank, a pressure reducing valve and a flow meter which are sequentially connected through a pipeline, and the flow meter is connected with the air heating mechanism. The air heating mechanism is connected with the sealed cabin, the tail end of the sealed cabin is connected with the condenser, the air pressure adjusting mechanism and the air heating mechanism are respectively connected with the measurement and control mechanism, and a heat insulation part to be measured is arranged in the sealed cabin. According to the utility model, the air heating temperature can reach 800 DEG C, the pressure difference and the flow of two sides of a tested piece are met, the device can be repeatedly used, and the heat insulation test requirements of different parts are met by replacing different test tools. The heat insulation test device for simulating the moving part of the high-speed aircraft on the ground not only can safely obtain material data, but also can save test cost and shorten the development period.

Description

Technical Field

[0001] The utility model belongs to the field of thermal insulation performance test, and in particular relates to a test system based on thermal insulation performance assessment of dynamic sealing components of high-speed aircraft. Background Art

[0002] In order to adapt to the harsh environment of high-speed flight, the structural design and material performance of aircraft face huge challenges: extremely high temperature environment, steady-state or transient local heating, ultra-high aerodynamic loads, possible severe structural vibration, acoustic loads and environmental erosion. Therefore, whether it is a cruise or taxiing aircraft, a manned spacecraft, etc., its control surfaces and opening gaps need to be insulated.

[0003] High-speed aircraft have to withstand high heat loads and oxidizing environments during flight. If no measures are taken, the low-temperature components inside the aircraft will be damaged or even fail, and in severe cases, the aircraft may be out of control. Therefore, some high-temperature gap locations need to be treated with high-temperature insulation technology to avoid the influx of high-temperature airflow, and the insulation materials used cannot affect the normal function of the aircraft. For this reason, the active thermal insulation components to be tested must have: 1) good thermal insulation performance; 2) good elasticity and wear resistance, and can maintain sealing integrity under thermal cycle loads; 3) good flexibility to meet the requirements of complex fuselage configurations. High-temperature insulation technology plays a vital role in the field of aerospace science and technology, and the corresponding dynamic thermal insulation components to be tested are also one of the key parts of high-speed aircraft.

[0004] In order to solve the problems of low reliability of thermal insulation components to be tested and easy wear of active parts of high-speed aircraft, research on high-temperature dynamic sealing process technology for rotating / translational parts of aircraft is carried out. The rationality of the process scheme is verified through high-temperature dynamic insulation test to ensure good contact between the structure and the surface, increase the number of times the thermal insulation components to be tested can be reused, and prevent structural damage caused by thermal air leakage. In order to evaluate the performance of the thermal insulation structure, it is necessary to carry out dynamic insulation tests on the materials of the thermal insulation components to be tested. Therefore, designing a set of thermal insulation test equipment that can simulate the active parts of high-speed aircraft on the ground can not only safely obtain material data, but also save test costs and shorten the development cycle. Utility Model Content

[0005] The utility model aims to overcome the deficiencies in the prior art and to provide a test system based on the thermal insulation performance assessment of dynamic sealing components of high-speed aircraft. Tests that can only be performed under high-altitude and high-speed flight conditions can be completed in a ground laboratory, which is beneficial to saving test costs and shortening the development cycle.

[0006] In order to achieve the above-mentioned purpose, the utility model is realized through the following technical scheme: a test system based on the thermal insulation performance assessment of the dynamic sealing components of high-speed aircraft, an air pressure regulating mechanism, an air heating mechanism and a sealed cabin, the air pressure regulating mechanism includes an air compressor, an air storage tank, a pressure reducing valve and a flow meter which are connected in sequence through pipelines, the flow meter is connected to the air heating mechanism, the air heating mechanism is connected to the sealed cabin, a condenser is connected to the end of the sealed cabin, the air pressure regulating mechanism and the air heating mechanism are respectively connected to the measurement and control mechanism, and the thermal insulation components to be tested are placed in the sealed cabin.

[0007] Furthermore, an air release valve and a dryer are provided between the air compressor and the air storage tank 4 .

[0008] Furthermore, a pressure gauge is connected between the air heating mechanism and the sealed cabin.

[0009] Furthermore, the pressure gauge is a water-cooled pressure gauge.

[0010] Furthermore, the water-cooled pressure gauge is a hollow structure, and a heat dissipation circuit is formed through a water inlet and a water outlet.

[0011] Furthermore, the condenser is connected to a muffler.

[0012] Furthermore, a water-cooled pressure gauge and flow meter are provided between the end of the sealed cabin and the condenser.

[0013] Furthermore, the sealed cabin includes a sealed cabin shell, a fixed baffle, a movable baffle and a rotating shaft. The sealed cabin shell is in the shape of a cube. The fixed baffle is composed of a horizontal plate and an angle plate to form an integral baffle with an obtuse cross-sectional shape. The fixed baffle is fixedly connected to the inner wall of the sealed cabin shell. One end of the movable baffle is connected to the rotating shaft, and the rotating shaft drives the movable baffle to swing up and down. The other end of the movable baffle overlaps with the angle plate of the movable baffle to divide the inner cavity of the sealed cabin shell into a hot cavity and a cold cavity. The rotating shaft is supported on a bracket through a bearing, and the bracket is fixedly connected to the inner wall of the sealed cabin shell. The thermal insulation components to be tested are placed around the movable baffle, and the sealed cabin shell is provided with an upper cover.

[0014] Furthermore, the angle at which the movable baffle is driven by the rotating shaft to swing up and down is the same as the movement angle of the dynamic sealing component to be simulated.

[0015] Furthermore, two groups of temperature sensors are respectively provided in the hot chamber and the cold chamber of the sealed cabin, and are connected to the measurement and control mechanism through high temperature resistant cables.

[0016] Furthermore, the air heating mechanism includes an air heater body, a heating tube and a temperature sensor. An air inlet and an air outlet are respectively provided at both ends of the air heater body. A plurality of electric heating tubes are arranged inside the air heater body, and the electric heating tubes heat the gas entering the air heater body.

[0017] Furthermore, the electric heating tube is a U-shaped electric heating tube.

[0018] Furthermore, the air heater body is coated with an asbestos protective layer on its periphery.

[0019] Beneficial effects: The air heating temperature of the utility model can reach 800℃, which meets the pressure difference and flow rate on both sides of the tested part, and can be reused. By replacing different test fixtures, it can meet the requirements of different component insulation tests. The insulation test device that simulates the active parts of high-speed aircraft on the ground can not only safely obtain material data, but also save test costs and shorten the development cycle. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Figure 1 It is a connection schematic diagram of the utility model;

[0021] Figure 2 yes Figure 1 Structural diagram of water-cooled pressure gauge;

[0022] Figure 3 yes Figure 1 Schematic diagram of the structure of the middle sealed cabin;

[0023] Figure 4 yes Figure 1 Schematic diagram of the structure of the air heater body;

[0024] Figure 5 yes Figure 1 A three-dimensional view of the middle sealed cabin.

[0025] In the figure: 1. air compressor, 2. air release valve, 3. dryer, 4. air storage tank, 5. pressure reducing valve, 6. flow meter, 7. air heater body, 7-1. U-shaped electric heating tube, 7-2. asbestos protective layer, 8. water-cooled pressure gauge, 8-1. water inlet, 8-2. water outlet, 9. sealed cabin, 9-1. sealed cabin shell, 9-2. movable baffle, 9-3. rotating shaft, 9-4. thermal insulation component to be tested, 9-5. fixed baffle, 9-6. upper cover, 10. temperature sensor, 11. condenser, 12. muffler, 13. measurement and control mechanism. DETAILED DESCRIPTION

[0026] The following is a detailed description of the specific implementation method provided according to the utility model in combination with the preferred embodiment: See the accompanying drawings for details. This embodiment provides a test system based on the thermal insulation performance assessment of the dynamic sealing components of high-speed aircraft, an air pressure regulating mechanism, an air heating mechanism and a sealed cabin. The air pressure regulating mechanism includes an air compressor 1, an air storage tank 4, a pressure reducing valve 5 and a flow meter 6 connected in sequence by pipelines. The flow meter is connected to the air heating mechanism, and the air heating mechanism is connected to the sealed cabin 9. A condenser 11 is connected to the end of the sealed cabin. The air pressure regulating mechanism and the air heating mechanism are respectively connected to the measurement and control mechanism 13, and the thermal insulation component 9-4 to be tested is placed in the sealed cabin.

[0027] A preferred solution of this embodiment is that an air release valve 2 and a dryer 3 are provided between the air compressor 1 and the air storage tank 4 .

[0028] A preferred solution of this embodiment is that a pressure gauge is connected between the air heating mechanism and the sealed cabin.

[0029] A preferred solution of this embodiment is that the pressure gauge is a water-cooled pressure gauge 8 .

[0030] A preferred solution of this embodiment is that the water-cooled pressure gauge is a hollow structure, and a heat dissipation circuit is formed through the water inlet 8-1 and the water outlet 8-2.

[0031] A preferred solution of this embodiment is that the condenser is connected to a muffler 12 .

[0032] The preferred solution of this embodiment is that a water-cooled pressure gauge and a flow meter 6 are provided between the end of the sealed cabin and the condenser.

[0033] The preferred scheme of this embodiment is that the sealed cabin includes a sealed cabin shell 9-1, a fixed baffle 9-5, a movable baffle 9-2 and a rotating shaft 9-3, the sealed cabin shell is in the shape of a cube, the fixed baffle is composed of a horizontal plate and an angle plate to form an integral baffle with an obtuse cross-sectional shape, the fixed baffle is fixedly connected to the inner wall of the sealed cabin shell, one end of the movable baffle is connected to the rotating shaft, the rotating shaft drives the movable baffle to swing up and down, the other end of the movable baffle is overlapped with the angle plate of the movable baffle, dividing the inner cavity of the sealed cabin shell into a hot cavity and a cold cavity, the rotating shaft is supported on the bracket through a bearing, the bracket is fixedly connected to the inner wall of the sealed cabin shell, the heat insulation component 9-4 to be tested is placed around the movable baffle, and the sealed cabin shell is provided with an upper cover 9-6.

[0034] A preferred solution of this embodiment is that the angle at which the movable baffle is driven by the rotating shaft to swing up and down is the same as the angle of movement of the simulated dynamic sealing component.

[0035] A preferred solution of this embodiment is that two groups of temperature sensors 10 are respectively provided in the hot chamber and the cold chamber of the sealed cabin, and are connected to the measurement and control mechanism 13 through high temperature resistant cables.

[0036] The preferred solution of this embodiment is that the air heating mechanism includes an air heater body 7, a heating tube and a temperature sensor, an air inlet and an air outlet are respectively provided at both ends of the air heater body, and a plurality of electric heating tubes are arranged inside the air heater body, and the electric heating tubes heat the gas entering the air heater body.

[0037] A preferred solution of this embodiment is that the electric heating tube adopts a U-shaped electric heating tube 7-1.

[0038] A preferred solution of this embodiment is that the periphery of the air heater body is covered with an asbestos protective layer 7-2.

[0039] The working principle and working process are described in detail below in combination with the specific structure of this embodiment. Example

[0040] Taking the force-heat combined loading test device based on the performance test of thermal insulation tiles as an example, the test device includes an air compressor, a bleed valve, a dryer, an air tank, a pressure reducing valve, a flow meter, an air heater, a water-cooled pressure gauge, a sealed cabin, a temperature sensor, a condenser, a muffler, and a measurement and control system. Among them, the air pressure regulating mechanism composed of an air compressor, a bleed valve, a dryer, an air tank, a pressure reducing valve, a flow meter, a water-cooled pressure gauge, a condenser, a muffler, and a measurement and control system can achieve the test pressure and flow requirements of the tested component;

[0041] The air heating device, which consists of an air heater, a measurement and control system, and a temperature sensor, can heat normal temperature air to 800°C.

[0042] The sealed cabin, which is composed of a sealed cabin shell, a fixed baffle, a movable baffle, and a heat-insulating component, can simulate the motion / stationary state of the dynamic sealing components of a high-speed aircraft. The design and construction of this test device can achieve an air heating temperature of up to 800°C, a pressure difference of up to 200Kpa before and after the test piece, and can be reused. By replacing different test fixtures, different test requirements can be met. The measurement and control mechanism is the LMS Test.Lab integrated system of Siemens Industry, which can collect and control temperature, pressure, and flow data. Among them, the air pressure regulating mechanism applies a specified air pressure load to the sealed cabin through an air compressor, a vent valve, a dryer, an air storage tank, a pressure reducing valve, a flow meter, a water-cooled pressure gauge, a condenser, and a muffler. All components are connected by a metal pipe with an inner diameter of Φ50. The water-cooled pressure gauge is a hollow structure, and a heat dissipation circuit can be formed through the water inlet and outlet to protect the pressure gauge and ensure the accuracy of the value. At the same time, the air heating mechanism forms a hot air loading circuit through the air heater body, the measurement and control mechanism, and the temperature sensor to apply a temperature load to the sealed cabin. The air heater body contains multiple U-shaped electric heating tubes to quickly heat the air temperature. There is an asbestos protective layer on the outside to reduce heat loss. The sealed cabin is mainly composed of a sealed cabin shell, a movable baffle, and a thermal insulation component to be tested. During the loading process of air pressure load and temperature load, the movable baffle drives the rotation of the shaft (9-3) through the rotation of the stepper motor, which can simulate the movement angle of the dynamic sealing component of the high-speed aircraft. A layer of the thermal insulation component to be tested is covered around the moving component, which has the effect of thermal insulation and sealing. Figure 3 , 5 As shown in the figure, the working process of the sealed cabin: the entire sealed cabin has a rectangular hollow structure, and the cabin body is divided into two parts by a fixed baffle and a movable baffle. When the motor drives the shaft to rotate, the movable baffle contacts the fixed baffle, which is the working state 1-sealed state. When the movable baffle separates from the fixed baffle, it is the working state 2-unblocked state.

[0043] Working process:

[0044] 1) During the implementation of the test, the test device based on the thermal insulation performance assessment of the dynamic sealing components of high-speed aircraft shall be inspected before the test to ensure the normal operation of the test device without leakage, interference, etc.;

[0045] 2) Perform visual inspection on the dynamic heat seal verification part of the air inlet adjustment plate and take photos for record;

[0046] 3) Open the air pressure regulating mechanism, open the pressure reducing valve, and adjust the pressure to the specified value according to the specified pressure;

[0047] 4) After the system pressure stabilizes, record the values ​​of the pressure sensor, flow sensor and temperature sensor;

[0048] 5) Turn on the test system, turn on the air heater body, set the temperature to 800℃, open the pressure reducing valve, adjust the pressure to the specified value according to the specified flow rate, monitor the system temperature, and when the temperature stabilizes to 800℃, record the current time, inlet and outlet temperature, inlet and outlet pressure and flow rate. Repeat the above test values ​​every 5 minutes;

[0049] 6) After the system is stable for 30 seconds, the movable baffle completes all opening and closing states through the movement of the shaft in accordance with the prescribed requirements for the action of the air intake components, and the current time, inlet and outlet temperatures, inlet and outlet pressures and flow rates are recorded in real time;

[0050] 7) After all required actions are completed, turn off the heating system;

[0051] 8) After the temperature drops, turn off the gas supply system, check the appearance of the test sample and take photos for record;

[0052] 9) Repeat this step three times to complete all thermal insulation performance tests.

[0053] The above-mentioned reference embodiment provides a detailed description of a test system for evaluating the thermal insulation performance of dynamic sealing components of high-speed aircraft. It is illustrative rather than restrictive, and several embodiments can be listed according to the limited scope. Therefore, changes and modifications without departing from the overall concept of the present invention should fall within the scope of protection of the present invention.

Claims

1. A test system for evaluating the thermal insulation performance of dynamic sealing components of high-speed aircraft, characterized by: air pressure The air pressure regulating mechanism comprises an air compressor, an air storage tank, a pressure reducing valve and a flow meter which are connected in sequence through pipelines. The flow meter is connected to the air heating mechanism, which is connected to the sealed cabin. A condenser is connected to the end of the sealed cabin. The air pressure regulating mechanism and the air heating mechanism are respectively connected to the measurement and control mechanism. The thermal insulation component to be measured is placed in the sealed cabin.

2. The test system for evaluating the thermal insulation performance of dynamic sealing components of high-speed aircraft according to claim 1 is characterized by: An air release valve and a dryer are provided between the air compressor and the air storage tank.

3. The test system for evaluating the thermal insulation performance of dynamic sealing components of high-speed aircraft according to claim 1 is characterized by: A pressure gauge is connected between the air heating mechanism and the sealed cabin.

4. The test system for evaluating the thermal insulation performance of dynamic sealing components of high-speed aircraft according to claim 3 is characterized by: The pressure gauge is a water-cooled pressure gauge.

5. The test system for evaluating the thermal insulation performance of dynamic sealing components of high-speed aircraft according to claim 4 is characterized by: The water-cooled pressure gauge is a hollow structure, and a heat dissipation circuit is formed through a water inlet and a water outlet.

6. The test system for evaluating the thermal insulation performance of dynamic sealing components of high-speed aircraft according to claim 1 is characterized by: The condenser is connected with a muffler.

7. The test system for evaluating the thermal insulation performance of dynamic sealing components of high-speed aircraft according to claim 1 is characterized by: A water-cooled pressure gauge and a flow meter are provided between the end of the sealed cabin and the condenser.

8. The test system for evaluating the thermal insulation performance of dynamic sealing components of high-speed aircraft according to claim 1 or 7, characterized in that: The sealed cabin includes a sealed cabin shell, a fixed baffle, a movable baffle and a rotating shaft. The sealed cabin shell is in the shape of a cube. The fixed baffle is composed of a horizontal plate and an angle plate to form an integral baffle with an obtuse cross-sectional shape. The fixed baffle is fixedly connected to the inner wall of the sealed cabin shell. One end of the movable baffle is connected to the rotating shaft, and the rotating shaft drives the movable baffle to swing up and down. The other end of the movable baffle overlaps with the angle plate of the movable baffle to divide the inner cavity of the sealed cabin shell into a hot cavity and a cold cavity. The rotating shaft is supported on a bracket through a bearing, and the bracket is fixedly connected to the inner wall of the sealed cabin shell. The heat insulation components to be tested are placed around the movable baffle, and the sealed cabin shell is provided with an upper cover.

9. The test system for evaluating the thermal insulation performance of dynamic sealing components of high-speed aircraft according to claim 8 is characterized by: The angle at which the movable baffle is driven to swing up and down by the rotating shaft is the same as the movement angle of the dynamic sealing component to be simulated.

10. The test system for evaluating the thermal insulation performance of dynamic sealing components of high-speed aircraft according to claim 8, characterized in that: Two groups of temperature sensors are respectively arranged in the hot cavity and the cold cavity of the sealed cabin, and are connected to the measurement and control mechanism through high temperature resistant cables.

11. The test system for evaluating the thermal insulation performance of dynamic sealing components of high-speed aircraft according to claim 1 is characterized by: The air heating mechanism includes an air heater body, a heating tube and a temperature sensor. An air inlet and an air outlet are respectively arranged at both ends of the air heater body. A plurality of electric heating tubes are arranged inside the air heater body to heat the gas entering the air heater body.

12. The test system for evaluating the thermal insulation performance of dynamic sealing components of high-speed aircraft according to claim 11, characterized in that: The electric heating tube is a U-shaped electric heating tube.

13. The test system for evaluating the thermal insulation performance of dynamic sealing components of high-speed aircraft according to claim 11, characterized in that: The periphery of the air heater body is covered with an asbestos protective layer.

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