A thermal radiation test platform for aviation components

Abstract

The present invention relates to a thermal radiation test platform for aviation components, which is mainly composed of a power supply system, a control system, a radiation heating device, and a cooling water tower. The control system controls the power supply system, the cooling water tower, and the radiation heating device respectively, and the control system includes a multi-channel coordinated control system and a temperature test system; the radiation heating device is composed of a lamp tube, an outer cover, a bracket, a water inlet pipe, a water outlet pipe, a thermal insulation felt, and an electrode. The lamp tube is located on the bracket, and a thermal insulation felt is arranged between the outer cover and the bracket, and the thermal insulation felt plays a role of heat insulation; at both ends of the bracket, a water inlet pipe and a water outlet pipe are respectively arranged, and the water inlet pipe and the water outlet pipe are connected to the cooling water tower. The lamp tubes of the present invention are fixed on the bracket in groups, and as a radiation light source, they are easy to install, the light source is uniform and stable, the surface of the test piece is heated evenly, and the temperature is easy to control; the present invention can be used for temperature field analysis of aircraft structural parts and guiding the design of aviation structural parts.

Description

Technical Field

[0001] The invention belongs to the technical field of aircraft design, in particular to a thermal radiation test platform for aviation components. Background Art

[0002] The performance requirements of aircraft brake materials in extreme environments are becoming more and more stringent. Traditional metal materials can no longer meet the requirements of their use temperature. The development of new high-temperature insulation materials and advanced and efficient insulation structure design directly determines the performance indicators and research and development direction of future aircraft. Studies have shown that when an aircraft is working in a temperature environment 20°C higher than its allowable temperature, the failure rate increases by 8 times. The thermal protection system plays a pivotal role in the overall design and performance of the aircraft brake structure. Therefore, the research on the thermal insulation and heat protection performance of the aircraft brake structure is imminent. According to the thermal load spectrum of the main brake wheel in operation, the transient simulation calculation of the structural thermal insulation performance is carried out, and the first ground space thermal radiation test platform in China is built to carry out thermal radiation tests to verify the rationality of the thermal structure design of the main brake wheel; shorten the product design cycle, improve the combat efficiency of the aircraft, and enhance the combat effectiveness of the aircraft, so it can produce important military benefits.

[0003] As aircraft combat technical indicators continue to upgrade, the requirements for the volume and weight of aircraft brake structures are becoming more and more stringent, and the load-bearing capacity and thermal protection indicators per unit area are becoming higher and higher, resulting in increasing difficulty in design work. The traditional trial-and-error development cycle is too long and cannot meet the current tight node and heavy task goals of military aircraft development. Therefore, early test verification is particularly important.

[0004] There is no public information on thermal radiation test platforms abroad, which leads to problems in conducting thermal radiation tests. Therefore, it is impossible to accurately predict the temperature field distribution level of aircraft structures and lack the basic ability to guide the thermal design of aircraft products. Summary of the invention

[0005] In order to overcome the existing inability to accurately predict the temperature field distribution level of aircraft structures and the lack of basic ability to guide the thermal design of aircraft products, the present invention proposes a thermal radiation test platform for aviation components.

[0006] The technical solution adopted by the present invention to solve its technical problem is:

[0007] A thermal radiation test platform for aviation components is mainly composed of a power supply system, a control system, a radiation heating device, and a cooling water tower; the control system is the central nervous system, which controls the power supply system, the cooling water tower, and the radiation heating device respectively, controls the power supply system to provide the control system, the radiation heating device, and the cooling water tower with the power they need; controls the cooling water tower to provide cooling water to the radiation heating device; and controls the radiation heating device to heat the test piece.

[0008] The control system includes a multi-channel coordinated control system and a temperature testing system; the multi-channel coordinated control system and the temperature testing system respectively control the power supply system and the cooling water tower, and the temperature testing system is used to measure the temperature of the aviation components in the radiation heating device and feed back the temperature of the aviation components to the multi-channel coordinated system.

[0009] The control system has the functions of controlling and collecting various load data. It uses the closed-loop control principle to control the aviation components according to the required heating temperature, collects the temperature of the radiation heating test device and controls it.

[0010] The radiation heating device consists of a lamp tube, an outer cover, a bracket, a water inlet pipe, a water outlet pipe, a heat insulation felt and electrodes.

[0011] The lamp tube is located on the bracket, and the lamp tube and the bracket are located inside the outer cover; an insulating felt is arranged between the outer cover and the bracket, and the insulating felt plays a heat insulating role; at both ends of the bracket, a water inlet pipe and a water outlet pipe are respectively arranged, and the water inlet pipe and the water outlet pipe are connected to the cooling water tower, so that the cooling water of the cooling water tower flows into the bracket through the water inlet pipe, and flows out through the water outlet pipe and returns to the cooling water tower.

[0012] The outer cover is a structural member welded from square steel pipes, with 6 hollow rectangular faces. The structural members away from the heating area can be cooled by circulating water in the pipe to continuously provide sufficient load strength. The outer cover serves as a protective device to establish a closed test environment to ensure stable temperature during thermal radiation tests.

[0013] The cooling tower continuously provides circulating cooling water.

[0014] In the above-mentioned thermal radiation test platform, the power supply system can provide a DC voltage, and the output DC voltage can be adjusted through the control system, thereby controlling the heating radiation heating device.

[0015] In the above-mentioned thermal radiation test platform, the multi-channel coordinated control system has the control function of various load data, and sends the thermal load signal to the temperature test system to control the radiation heating test device.

[0016] The temperature testing system includes a static testing system and a temperature acquisition system, adopts a modular design, transmits data through a network, and can collect, transmit, save and display the temperature of aviation components in real time.

[0017] The static test system is a fully intelligent data acquisition system with a channel self-check function, which is used to control the power supply system and cooling water tower; it transmits, saves and displays the collected temperature of aviation components.

[0018] The temperature acquisition system is used to acquire the temperature of the aviation component and control the radiation heating device by feeding back the signal to the temperature test system.

[0019] The above-mentioned thermal radiation test platform, the lamp tube is a radiation light source, releases heat energy, has a rated voltage of 220V, a rated power of 4.3kw, and is a quartz heating lamp tube.

[0020] The positions of the lamp tubes are arranged according to the structural shape of the aviation component, and the positions and spacings can be adjusted according to the temperature required by the test piece to ensure that the temperature of each part of the test piece is consistent with its use conditions in aviation applications.

[0021] The above-mentioned thermal radiation test platform, the bracket includes a lamp tube holder, a bracket body, an electrode, and an insulating sleeve; the lamp tube holder is located on the bracket body, the lamp tube holder is used to install the lamp tube, the power line of the lamp tube is connected to the electrode along the bracket body, the electrode is arranged on the outside of the water inlet pipe and the water outlet pipe, and the insulating sleeve is arranged on the outside of the electrode, the insulating sleeve is located between the electrode and the outer cover, so that the electrode and the outer cover are insulated; the electrode, the insulating sleeve, the water inlet pipe, and the water outlet pipe pass through the outer cover; the two ends of the bracket body are respectively connected to the water inlet pipe and the water outlet pipe.

[0022] The support body is made of copper tube material. The cooling water of the cooling water tower flows through the support body made of copper tube to cool the support body, thereby preventing the support body from deformation and oxidation.

[0023] The support body is processed into a corresponding shape according to the appearance of the test piece.

[0024] The beneficial effects of the present invention are:

[0025] A thermal radiation test platform for aviation components can accurately evaluate the thermal protection performance in the early stage of product design, and can also be used to verify the thermal simulation model. The test process is accurate, simple and convenient, providing technical support for aircraft thermal protection design, while improving product reliability, it can significantly reduce weight and achieve lightweight design requirements. It can shorten the product development cycle, improve aircraft combat efficiency, enhance aircraft combat effectiveness, and is of great significance to the improvement of military combat training.

[0026] A quartz heating lamp group in a radiation heating device of a thermal radiation test platform for aviation components is fixed on a bracket. As a radiation light source, it is easy to install, the light source is uniform and stable, the product surface is heated evenly and the temperature is easy to control, and the temperature field level of aircraft components can be accurately predicted.

[0027] A thermal radiation test platform for aviation components can achieve a 95% match between the ground simulation of the product and the actual use environment, successfully solving the problem of being unable to characterize the temperature difference of different parts of the structural parts due to ignoring the heat transfer process of the structural parts themselves; it can accurately predict the temperature distribution of the product during use, provide technical support for the thermal design of the product, and avoid major accidents caused by thermal strength and thermal fatigue problems caused by insufficient consideration of the product during the design process. The maximum temperature of the structural parts calculated by finite element analysis is 516°C, and the part with the highest temperature is the part closest to the heat source; the maximum temperature tested by the test of the present invention is 526°C, and the part with the highest temperature is the part closest to the heat source. The temperature obtained by the ground space thermal radiation test platform proposed in this article for a certain type of aircraft high-temperature structure is completely consistent with the maximum temperature value and location obtained by simulation calculation. The present invention can be used for temperature field analysis of aircraft high-temperature structures and guide the design of high-temperature structures. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] The present invention is further described below in conjunction with the accompanying drawings and embodiments.

[0029] Figure 1 It is a schematic diagram of the present invention;

[0030] Figure 2 It is a schematic diagram of the structure of the radiation heating device;

[0031] In the figure, 1. lamp tube; 2. outer cover; 3. bracket; 4. water inlet pipe; 5. water outlet pipe; 6. thermal insulation felt; 7. electrode. DETAILED DESCRIPTION

[0032] Example

[0033] A thermal radiation test platform for aviation components, using aviation components as test pieces, is used to conduct ground tests on the thermal radiation performance of test pieces. It is mainly composed of a power supply system, a control system, a radiation heating device, and a cooling water tower. Figure 1 shown.

[0034] The control system is the central nervous system, which controls the power supply system, cooling water tower, and radiation heating device respectively; controls the power supply system to provide the control system, radiation heating device, and cooling water tower with the electricity they need; controls the cooling water tower to provide cooling water to the radiation heating device to reduce the temperature of the radiation heating device; and controls the radiation heating device to heat the test piece.

[0035] The power system provides electricity for the control system, radiant heating device, and cooling water tower.

[0036] The power supply system can provide a DC voltage, and the output DC voltage can be adjusted through the control system, thereby controlling the heating radiation heating device.

[0037] The control system includes a multi-channel coordinated control system and a temperature test system. The multi-channel coordinated control system and the temperature test system control the power supply system and the cooling water tower respectively. The temperature test system is used to measure the temperature of the aviation components in the radiation heating device and feed the temperature of the aviation components back to the multi-channel coordinated system.

[0038] The control system has the functions of controlling and collecting various load data, and uses the closed-loop control principle to control the required heating temperature of aviation components, collect the temperature of the radiation heating test device and control it. It has the characteristics of high precision and powerful functions.

[0039] The multi-channel coordinated control system has the control function of various load data and sends the thermal load signal to the temperature test system to control the radiation heating test device.

[0040] The temperature testing system includes a static testing system and a temperature acquisition system. It adopts a modular design and transmits data through the network. It can collect, transmit, save and display the temperature of aviation components in real time.

[0041] The static test system is a fully intelligent data acquisition system with a channel self-check function, which is used to control the power supply system and cooling water tower. It can transmit, save and display the collected temperature of aviation components.

[0042] The temperature acquisition system is used to collect the temperature of aviation components and control the radiation heating device by feeding back the signal to the temperature test system.

[0043] The radiation heating device is composed of a lamp tube 1, an outer cover 2, a bracket 3, a water inlet pipe 4, a water outlet pipe 5, a heat insulation felt 6, and an electrode 7. Figure 2 shown.

[0044] The lamp tube 1 is located on the bracket 3, and the lamp tube 1 and the bracket 3 are located inside the outer cover 2; a heat insulation felt 6 is arranged between the outer cover 2 and the bracket 3, and the heat insulation felt 6 plays a role of heat insulation; at both ends of the bracket 3, a water inlet pipe 4 and a water outlet pipe 5 are respectively arranged, and the water inlet pipe 4 and the water outlet pipe 5 are connected to the cooling water tower, so that the cooling water of the cooling water tower flows into the bracket 3 through the water inlet pipe 4, and flows out through the water outlet pipe 5 and returns to the cooling water tower;

[0045] The lamp tube 1 is a radiation light source, releases heat energy, has a rated voltage of 220V, a rated power of 4.3kw, and is a quartz heating lamp tube.

[0046] The position of the lamp tube 1 is arranged according to the structural shape of the aviation component, and the position and spacing can be adjusted according to the temperature required by the test piece to ensure that the temperature of each part of the test piece is consistent with its use conditions in aviation applications.

[0047] The bracket 3 includes a lamp holder, a bracket body, an electrode 7, and an insulating sleeve. The lamp holder is located on the bracket body and is used to install the lamp. The power cord of the lamp is connected to the electrode 7 along the bracket body. The electrode 7 is arranged on the outside of the water inlet pipe 4 and the water outlet pipe 5. An insulating sleeve is arranged on the outside of the electrode 7. The insulating sleeve is located between the electrode 7 and the outer cover 2 to insulate the electrode 7 from the outer cover 2. The electrode 7, the insulating sleeve, the water inlet pipe 4, and the water outlet pipe 5 pass through the outer cover 2. The two ends of the bracket body are respectively connected to the water inlet pipe 4 and the water outlet pipe 5.

[0048] The bracket body is made of copper tube material. The cooling water of the cooling tower flows through the bracket body made of copper tube to cool the bracket body, preventing the bracket body from deformation and oxidation, thereby overcoming the defect that the contact resistance of the lamp tube increases due to deformation and oxidation of the bracket body made of copper tube, resulting in burning or bursting damage.

[0049] The outer cover 2 is a structural member welded from a square steel pipe, with 6 hollow rectangular parallelepiped faces. The structural members away from the heating area can be cooled by water circulation in the pipe to continuously provide sufficient load strength; the outer cover is used as a protective device to establish a closed test environment, ensure the stability of the thermal radiation test temperature, and ensure the safety of the test personnel.

[0050] The cooling water tower continuously provides circulating cooling water for reducing the temperature in the support body in the radiation heating device.

[0051] The main body of the bracket is made of 2 Φ10mm copper tubes processed into corresponding shapes according to the appearance of the test piece. The copper tube is cooled by circulating water provided by a cooling water tower to prevent the copper tube from deforming and oxidizing, which may cause the lamp to burn out or burst.

[0052] The test process of a thermal radiation test platform for aviation components is as follows:

[0053] Step 1: Cooling water is passed through the bracket body of the radiation heating device

[0054] Before the test, cooling water is passed through the radiation heating device for pre-load debugging to ensure that the cooling circulating water can work normally in the bracket of the copper tube.

[0055] Step 2: Test piece installation

[0056] The temperature acquisition system is fixed at the corresponding measuring points on the inner and outer surfaces of the test piece, and the test piece is transported to the heating area of ​​the radiation heating device to complete the installation of the test piece.

[0057] Step 3: Control system installation

[0058] The control system controls the radiation heating device to apply temperature loading to the aircraft components. By adjusting the DC voltage value at both ends of the lamp tube, the temperature loading is achieved so that the surface temperature of the test piece reaches the set value.

[0059] Step 4: Experimental test temperature monitoring

[0060] The temperature acquisition system is used to monitor the surface temperature changes of aviation components in real time, and the test results are fed back to the multi-channel coordinated test system, which in turn serves as the basis for the temperature setting of the radiation heating device and the structural thermal design.

[0061] At this point, the testing process of the thermal radiation test platform is completed.

Claims

1. A thermal radiation test platform for aviation components, characterized in that: It is mainly composed of power supply system, control system, radiation heating device and cooling water tower; the control system is the central nervous system, which controls the power supply system, cooling water tower and radiation heating device respectively; controls the power supply system to provide the control system, radiation heating device and cooling water tower with the required electricity; controls the cooling water tower to provide cooling water to the radiation heating device; controls the radiation heating device to heat the test piece; The control system includes a multi-channel coordinated control system and a temperature test system; the multi-channel coordinated control system and the temperature test system respectively control the power supply system and the cooling water tower, and the temperature test system is used to measure the temperature of the aviation components in the radiation heating device and feed back the temperature of the aviation components to the multi-channel coordinated system; The control system has the functions of controlling and collecting various load data. It uses the closed-loop control principle to control the aviation components according to the required heating temperature, collect the temperature of the radiation heating test device and control it. The radiation heating device is composed of a lamp tube (1), an outer cover (2), a bracket (3), a water inlet pipe (4), a water outlet pipe (5), a heat insulation felt (6), and an electrode (7); The lamp tube (1) is located on the bracket (3), and the lamp tube (1) and the bracket (3) are located inside the outer cover (2); a heat insulation felt (6) is arranged between the outer cover (2) and the bracket (3), and the heat insulation felt (6) plays a heat insulation role; a water inlet pipe (4) and a water outlet pipe (5) are respectively arranged at both ends of the bracket (3), and the water inlet pipe (4) and the water outlet pipe (5) are connected to a cooling water tower, so that cooling water from the cooling water tower flows into the bracket (3) through the water inlet pipe (4), and flows out through the water outlet pipe (5) and returns to the cooling water tower; The outer cover (2) is a structural member formed by welding square steel pipes, and has six hollow rectangular parallelepiped faces. The structural member away from the heating area can be cooled by water circulation in the pipe, and continuously provide sufficient load strength. The outer cover serves as a protective device. Used to establish a closed test environment to ensure stable temperature for thermal radiation tests; The cooling tower continuously provides circulating cooling water.

2. The thermal radiation test platform for aviation components according to claim 1, characterized in that: The power supply system can provide a DC voltage, and the output DC voltage can be adjusted through the control system, thereby controlling the heating radiation heating device.

3. The thermal radiation test platform for aviation components according to claim 1, characterized in that: The multi-channel coordinated control system has the control function of various load data, and sends the thermal load signal to the temperature test system to control the radiation heating test device; The temperature testing system includes a static testing system and a temperature acquisition system, which adopts a modular design and transmits data through a network, and can collect, transmit, save and display the temperature of aviation components in real time; The static test system is a fully intelligent data acquisition system with a channel self-check function, which is used to control the power supply system and cooling water tower; Transmit, save and display the collected temperature of aviation components; The temperature acquisition system is used to acquire the temperature of the aviation component and control the radiation heating device by feeding back the signal to the temperature test system.

4. The thermal radiation test platform for aviation components according to claim 1, characterized in that: The lamp tube (1) is a radiation light source, releases heat energy, has a rated voltage of 220V, a rated power of 4.3kw, and is a quartz heating lamp tube; The positions of the lamp tubes (1) are arranged according to the structural shape of the aviation component, and the positions and spacings can be adjusted according to the temperature required by the test piece, so as to ensure that the temperature of each part of the test piece is consistent with its use conditions in aviation applications.

5. The thermal radiation test platform for aviation components according to claim 1, characterized in that: The support (3) comprises a lamp holder, a support body, an electrode (7), and an insulating sleeve; the lamp holder is located on the support body, the lamp holder is used to install the lamp, the power line of the lamp is connected to the electrode (7) along the support body, the electrode (7) is arranged on the outside of the water inlet pipe (4) and the water outlet pipe (5), and an insulating sleeve is arranged on the outside of the electrode (7), the insulating sleeve is located between the electrode (7) and the outer cover (2), so that the electrode (7) and the outer cover (2) are insulated; the electrode (7), the insulating sleeve, the water inlet pipe (4), and the water outlet pipe (5) pass through the outer cover (2); the two ends of the support body are respectively connected to the water inlet pipe (4) and the water outlet pipe (5); The support body is made of copper tube material, and the cooling water of the cooling water tower flows through the support body made of copper tube to cool the support body, thereby preventing the support body from deformation and oxidation; The support body is processed into a corresponding shape according to the appearance of the test piece.

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