A device for thermal environment assessment and testing of aircraft components and its use method

Abstract

The present invention proposes a device for thermal environment assessment and testing of aircraft components and a method for using the device, which relates to the field of aircraft material testing technology. The device includes aircraft components, crucibles, refractory bricks, a test bench, an ablation system, a temperature measurement system, and a temperature control system. The device can provide a thermal environment higher than 1750 degrees to simulate the aerodynamic heating environment of aircraft components in service. The method for using the device includes the following steps: S1, setting up test equipment, performing heating environment pretreatment, and presetting the temperature control system; S2, maintaining the temperature control system configuration, and performing service thermal environment assessment tests; S3, measuring and recording the surface temperature distribution of aircraft components. By setting two working environments, including a heating environment and a service thermal environment, segmented heating is performed to the required test thermal environment, and the platinum-rhodium thermocouple is replaced with a smaller crystal sensor, thereby achieving synchronous online monitoring of high-temperature heating of aircraft components, non-destructive flow field, and in-situ measurement.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft material testing, and in particular to a device for thermal environment assessment testing of aircraft components and a method for using the device. Background Art

[0002] Aircraft are devices that fly within or outside the atmosphere. Aircraft are divided into three categories: aircraft, spacecraft, and rockets and missiles. Aircraft that fly within the atmosphere are called aircraft, such as balloons, airships, and airplanes. They are lifted into the air by the static buoyancy of the air or by the aerodynamic forces generated by the relative motion of the air. Spacecraft that fly in space are called spacecraft, such as artificial satellites, manned spacecraft, space probes, and the space shuttle. They gain the necessary velocity to enter space with the help of a launch vehicle, and then rely on inertia to achieve orbital motion similar to that of celestial bodies.

[0003] As human demands for aircraft performance continue to increase, aircraft speeds and ranges are also increasing, and the corresponding thermal environment is becoming more severe. Therefore, the development of ground-based high-temperature (greater than 1750°C) thermal environment testing technology for aircraft has become more critical. However, there are currently few high-temperature testing technologies that can achieve high-temperature heating of aircraft components without damaging the flow field, and simultaneously perform online monitoring and in-situ measurements. Traditional high-temperature testing technologies cannot meet the thermal environment and high-temperature measurement technology requirements of current aircraft service environments.

[0004] Chinese patent CN102879423B, "Single-Side High-Temperature Test Apparatus for Hypersonic Aircraft Materials in an 1800-Degree Aerobic Environment," discloses a single-side high-temperature test apparatus for hypersonic aircraft materials in an 1800-Degree Aerobic Environment. The apparatus replicates the thermal environment of a high-Mach number aircraft flying on its side in an aerobic environment, measures the thermal insulation parameters of hypersonic aircraft materials in extreme aerobic and high-temperature environments, and uses thermocouple temperature sensors to measure the surface temperature of the aircraft material. However, thermocouple temperature sensors are large in size and will affect the flow field on the surface of the aircraft material, resulting in insufficient simulation. Summary of the Invention

[0005] In view of this, the present invention proposes a device for thermal environment assessment and testing of aircraft components and a method of use thereof, which is used to solve the problem that traditional high-temperature testing technology cannot meet the thermal environment and high-temperature measurement technology requirements of the current aircraft service environment.

[0006] The technical solution of the present invention is achieved as follows: The present invention provides a device for thermal environment assessment and testing of aircraft components, comprising aircraft components, a crucible, refractory bricks, and a test bench;

[0007] The test bench is set on the ground and is used to carry refractory bricks;

[0008] The refractory bricks are placed on the test bench to isolate the crucible from the test bench;

[0009] The crucible is set on the refractory bricks and is used to place aircraft parts;

[0010] It is characterized by further comprising an ablation system, a temperature measurement system and a temperature control system;

[0011] The ablation system is arranged on one side above the aircraft component and is used to provide a high-temperature and high-pressure supersonic flame flow;

[0012] The temperature measurement system is provided on the other side above the aircraft component and is used to measure and record the temperature of the surface of the aircraft component;

[0013] The temperature control system is connected to the temperature measurement system signal for controlling the temperature of aircraft components.

[0014] Preferably, the ablation system includes a reciprocating mechanism, a combustion chamber, a Rafale nozzle, a solenoid valve, a proportional controller, an aviation kerosene storage tank, and a liquid oxygen storage tank;

[0015] The reciprocating motion mechanism is fixedly arranged on one side above the aircraft component and is used to simulate the motion trajectory according to the size of the aircraft component;

[0016] The combustion chamber is suspended below the reciprocating mechanism and is used to burn the combustible gas;

[0017] The Rafale nozzle is connected to the combustion chamber and is located between the aircraft component and the combustion chamber, and is used to eject a high-temperature and high-pressure supersonic flame flow;

[0018] The solenoid valve is connected to the combustion chamber and is arranged on the opposite side of the Rafale nozzle to activate the ablation system;

[0019] The ratio controller is arranged on the surface of the combustion chamber and is used to adjust the ratio of aviation kerosene and oxygen;

[0020] The aviation kerosene storage tank and the liquid oxygen storage tank are connected to the combustion chamber and are located below the combustion chamber, and are used to provide aviation kerosene and oxygen.

[0021] Preferably, the temperature measurement system includes a platinum-rhodium thermocouple, a temperature measuring crystal, an infrared thermal imager and a temperature recorder;

[0022] The platinum-rhodium thermocouple is placed on the surface of the aircraft component and is used to transmit temperature data to the temperature recorder during the pre-processing stage;

[0023] The temperature measuring crystal is placed on the surface of the aircraft component and is used to transmit temperature data to the temperature recorder during the service thermal environment phase of the aircraft component;

[0024] The infrared thermal imager is arranged on the other side of the aircraft component, opposite to the Rafale nozzle, and is used to monitor the surface temperature changes of the aircraft component in real time;

[0025] The temperature recorder is arranged above the aircraft component and is used to record the temperature distribution on the surface of the aircraft component.

[0026] In another aspect, the present invention further provides a method for using a device for thermal environment assessment and testing of aircraft components, comprising the following steps:

[0027] S1, set up the test equipment, perform heating environment pretreatment, and preset the temperature control system;

[0028] S2: Maintain the temperature control system configuration and conduct service thermal environment assessment test;

[0029] S3, measuring and recording the surface temperature distribution of aircraft components.

[0030] Preferably, step S1 specifically includes:

[0031] The ratio of aviation kerosene and oxygen is adjusted through a proportional controller. The oxygen fully atomizes the aviation kerosene to form a combustible mixture that enters the combustion chamber and is ignited to generate high-temperature and high-pressure combustion gas. After ignition and combustion through the Rafale nozzle, a high-temperature and high-pressure supersonic flame flow is formed, completing the heating environment pretreatment.

[0032] More preferably, step S1 specifically includes:

[0033] Platinum-rhodium thermocouples are arranged at the main temperature measuring points of the aircraft components. The temperature control system adjusts the movement speed of the reciprocating mechanism and the opening of the solenoid valve according to the temperature signal fed back by the platinum-rhodium thermocouples, records the periodic changes in the movement speed of the reciprocating mechanism and the opening of the solenoid valve, and completes the pre-setting of the temperature control system.

[0034] Preferably, step S2 specifically includes:

[0035] When conducting service thermal environment assessment tests, the platinum-rhodium thermocouples at the main temperature measurement points are replaced with temperature measuring crystals to reduce the impact on the surface flow field of the aircraft components and reproduce the service thermal environment of the aircraft components.

[0036] More preferably, step S2 specifically includes:

[0037] The surface temperature changes of aircraft components are monitored and recorded in real time using an infrared thermal imager.

[0038] More preferably, step S2 specifically includes:

[0039] The temperature measuring crystal has no additional support or leads and can be arranged on the surface of aircraft components without affecting the original temperature field. It has a size of 0.2 mm and can measure a maximum temperature of 1800° C. with an error of less than 1.5%.

[0040] The device for thermal environment assessment and testing of aircraft components and the method for using the device of the present invention have the following beneficial effects compared with the prior art:

[0041] (1) By using a high-temperature heating device with a heating temperature of over 1750 degrees, the aerodynamic heating environment of the aircraft components in service is simulated, and the operating speed of the reciprocating motion mechanism is adjusted to simulate the motion trajectory according to the size of the aircraft components;

[0042] (2) Two working environments were set up. First, the temperature control system was pre-set by heating environment pretreatment. Then, the configuration of the temperature control system was kept unchanged, and the platinum-rhodium thermocouple was replaced with a temperature measuring crystal. The service thermal environment assessment test was started, and the flow field was not damaged during high-temperature heating and in-situ measurement was achieved.

[0043] (3) In conjunction with an infrared thermal imager, the temperature distribution on the surface of aircraft components is measured and recorded using a temperature recorder, which facilitates personnel to precisely control the heating environment and service thermal environment, thus achieving synchronous online monitoring. BRIEF DESCRIPTION OF THE DRAWINGS

[0044] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the embodiments or the description of the prior art. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0045] Figure 1 This is a schematic structural diagram of a device for thermal environment assessment and testing of aircraft components according to the present invention;

[0046] Figure 2 This is a flow chart of a method for using a device for thermal environment assessment and testing of aircraft components according to the present invention;

[0047] Figure 3 This is a diagram showing the composition of an assessment and testing system for an apparatus for thermal environment assessment and testing of aircraft components according to the present invention;

[0048] Figure 4 This is a diagram showing the composition of a pre-set heating environment test system for a device for thermal environment assessment and testing of aircraft components according to the present invention;

[0049] Figure 5 This is a composition diagram of a formal service thermal environment test system of a device for thermal environment assessment and testing of aircraft components according to the present invention. DETAILED DESCRIPTION

[0050] The following will be combined with the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the embodiments described are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of the present invention.

[0051] Example 1

[0052] Provide a device for thermal environment assessment and testing of aircraft components, such as Figure 1 As shown, it includes an aircraft component 1, a crucible 2, refractory bricks 3, and a test bench 4;

[0053] The test bench 4 is set on the ground and is used to carry the refractory bricks 3;

[0054] The refractory bricks 3 are placed on the test bench 4 to isolate the crucible 2 from the test bench 4;

[0055] The crucible 2 is arranged on the refractory bricks 3 and is used to place the aircraft component 1;

[0056] It also includes an ablation system 5, a temperature measurement system 6 and a temperature control system 7;

[0057] The ablation system 5 is arranged on one side above the aircraft component 1 and is used to provide a high-temperature and high-pressure supersonic flame flow;

[0058] The temperature measurement system 6 is provided on the other side above the aircraft component 1 and is used to measure and record the temperature of the surface of the aircraft component 1;

[0059] The temperature control system 7 is connected to the temperature measurement system 6 by signal, and is used for temperature control of the aircraft component 1 .

[0060] The device for thermal environment assessment and testing of aircraft components can provide a thermal environment higher than 1750 degrees, simulating the aerodynamic heating environment of aircraft components in service. Before the thermal environment test, the above-mentioned device is placed in accordance with Figure 1 Settings shown.

[0061] The ablation system 5 includes a reciprocating mechanism 51, a combustion chamber 52, a Rafale nozzle 53, a solenoid valve 54, a proportional controller 55, an aviation kerosene storage tank 56 and a liquid oxygen storage tank 57;

[0062] The reciprocating motion mechanism 51 is fixedly arranged on one side above the aircraft component 1 and is used to simulate the motion trajectory according to the size of the aircraft component 1;

[0063] The combustion chamber 52 is suspended below the reciprocating mechanism 51 and is used to burn the combustible gas;

[0064] The Rafale nozzle 53 is connected to the combustion chamber 52 and is located between the aircraft component 1 and the combustion chamber 52, and is used to eject a high-temperature and high-pressure supersonic flame flow;

[0065] The solenoid valve 54 is connected to the combustion chamber 52 and is arranged on the opposite side of the Rafale nozzle 53 to start the ablation system 5;

[0066] The ratio controller 55 is provided on the surface of the combustion chamber 52 and is used to adjust the ratio of aviation kerosene and oxygen;

[0067] The aviation kerosene storage tank 56 and the liquid oxygen storage tank 57 are connected to the combustion chamber 52 and are located below it, and are used to provide aviation kerosene and oxygen.

[0068] The working principle of the ablation system 5 is as follows: the solenoid valve 54 is opened, and the ratio of aviation kerosene and oxygen provided by the aviation kerosene storage tank 56 and the liquid oxygen storage tank 57 is adjusted through the proportional controller 55. The oxygen fully atomizes the aviation kerosene through the atomizing nozzle to form a combustible mixture that enters the combustion chamber 52. The ignition system ignites it to generate high-temperature and high-pressure combustion gas. The reciprocating motion mechanism 51 simulates the motion trajectory of the aircraft component 1. After ignition and combustion through the Rafale nozzle 53, a high-temperature and high-pressure supersonic flame flow is formed.

[0069] The temperature measurement system 6 includes a platinum-rhodium thermocouple 61, a temperature measuring crystal 62, an infrared thermal imager 63 and a temperature recorder 64;

[0070] The platinum-rhodium thermocouple 61 is placed on the surface of the aircraft component 1 and is used to transmit temperature data to the temperature recorder 64 during the pre-processing stage;

[0071] The temperature measuring crystal 62 is placed on the surface of the aircraft component 1 and is used to transmit temperature data to the temperature recorder 64 during the service thermal environment phase of the aircraft component 1;

[0072] The infrared thermal imager 63 is provided on the other side of the aircraft component 1, opposite to the Rafale nozzle 53, and is used to monitor the surface temperature change of the aircraft component 1 in real time;

[0073] The temperature recorder 64 is disposed above the aircraft component 1 and is used to record the temperature distribution on the surface of the aircraft component 1 .

[0074] The temperature measurement system 6 can program 12 sets of process curves. Different service thermal environments can be preset for different aircraft components 1 as needed. The platinum-rhodium thermocouple can measure temperatures up to 1800°C with an accuracy of ±0.25%. The temperature measuring crystal is a crystal sensor with a size of approximately 0.2mm. It can measure temperatures up to 1800°C with an error of less than 1.5%.

[0075] Example 2

[0076] Provided is a method for using a device for thermal environment assessment testing of aircraft components, such as Figure 2 As shown, the following steps are included:

[0077] S1, set up the test equipment, perform heating environment pretreatment, and preset the temperature control system;

[0078] S2: Maintain the temperature control system configuration and conduct service thermal environment assessment test;

[0079] S3, measuring and recording the surface temperature distribution of aircraft components.

[0080] By setting up two working environments, first presetting the heating environment and then reproducing the service thermal environment of the aircraft components, in-situ measurement and non-destructive commutation field temperature measurement are achieved.

[0081] Step S1 specifically includes:

[0082] The ratio of aviation kerosene and oxygen is adjusted through a proportional controller. The oxygen fully atomizes the aviation kerosene to form a combustible mixture that enters the combustion chamber and is ignited to generate high-temperature and high-pressure combustion gas. After ignition and combustion through the Rafale nozzle, a high-temperature and high-pressure supersonic flame flow is formed, completing the heating environment pretreatment.

[0083] Platinum-rhodium thermocouples are arranged at the main temperature measuring points of the aircraft components. The temperature control system adjusts the movement speed of the reciprocating mechanism and the opening of the solenoid valve according to the temperature signal fed back by the platinum-rhodium thermocouples, records the periodic changes in the movement speed of the reciprocating mechanism and the opening of the solenoid valve, and completes the pre-setting of the temperature control system.

[0084] Set up the test equipment as Figure 1 As shown, according to the size of the aircraft components and the service thermal environment, the heating environment pretreatment is performed first to complete the preset of the temperature control system. The supersonic flame flow can reach a temperature of more than 2000°C and a speed of more than 2000m / s.

[0085] Step S2 specifically includes:

[0086] When conducting service thermal environment assessment tests, the platinum-rhodium thermocouples at the main temperature measurement points are replaced with temperature measuring crystals to reduce the impact on the surface flow field of the aircraft components and reproduce the service thermal environment of the aircraft components.

[0087] The surface temperature changes of aircraft components are monitored and recorded in real time using an infrared thermal imager.

[0088] The temperature measuring crystal has no additional support or leads and can be placed on the surface of aircraft components without affecting the original temperature field. It has a size of about 0.2 mm and can measure a maximum temperature of 1800°C with an error of less than 1.5%.

[0089] The implementation method of high-temperature measurement technology that does not damage the flow field and synchronizes online monitoring and in-situ measurement: During the temperature field test, the platinum-rhodium thermocouples at the main temperature measurement points are replaced with crystal sensors to reduce the impact on the flow field on the surface of the aircraft components and at the same time achieve the reproduction of the service thermal environment of the aircraft components. Infrared thermal imagers are used to monitor the surface temperature changes of the aircraft components in real time.

[0090] Example 3

[0091] Simulate the aerodynamic heating thermal environment of aircraft components in service. The aircraft component thermal environment assessment and testing device can heat to a temperature of over 1750 degrees. The aircraft component thermal environment assessment and testing device can achieve high-temperature heating without damaging the flow field, synchronous online monitoring and in-situ measurement. The aircraft component thermal environment assessment and testing system consists of the following components: Figure 3 As shown, it includes a temperature measurement system, an ablation system and a temperature control system;

[0092] The aircraft component thermal environment assessment test device has two working links. First, with the cooperation of platinum-rhodium thermocouple and temperature recorder, the temperature control system is preset, and then the opening of the solenoid valve of the burner and the running speed of the reciprocating motion mechanism are regulated to ensure the accuracy of the applied thermal environment. The preset heating environment test system is composed of the following: Figure 4 As shown;

[0093] Then, keep the configuration of the temperature control system unchanged, remove the platinum-rhodium thermocouple, install the temperature measuring crystal at the main temperature measuring point, and cooperate with the infrared imager to start the service thermal environment assessment test and temperature measurement. The service thermal environment formal test system consists of the following: Figure 5 As shown; the temperature recorder is used to record the temperature distribution on the surface of the aircraft components, and at the same time facilitates personnel to accurately control the service thermal environment.

[0094] In the aircraft component thermal environment assessment and testing device, the ratio of aviation kerosene and liquid oxygen needs to be adjusted in advance through a proportional controller; in the preset stage of the temperature control system, temperature measuring crystals are not deployed, but are deployed in the formal service thermal environment test stage. At the same time, platinum-rhodium thermocouples are removed to ensure that the surface flow field of the aircraft components is not affected.

[0095] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention should be included in the scope of protection of the present invention.

Claims

1. A device for thermal environment assessment and testing of aircraft components, comprising an aircraft component (1), a crucible (2), refractory bricks (3), and a test bench (4); The test bench (4) is arranged on the ground and is used to carry the refractory bricks (3); The refractory bricks (3) are arranged on the test bench (4) and are used to isolate the crucible (2) and the test bench (4); The crucible (2) is arranged on a refractory brick (3) and is used to place the aircraft component (1); It is characterized by: Also includes an ablation system (5), a temperature measurement system (6) and a temperature control system (7); The ablation system (5) is arranged on one side above the aircraft component (1) and is used to provide a high-temperature and high-pressure supersonic flame flow; The temperature measurement system (6) is arranged on the other side above the aircraft component (1) and is used to measure and record the temperature of the surface of the aircraft component (1); The temperature control system (7) is connected to the temperature measurement system (6) via a signal and is used for temperature control of the aircraft component (1); The ablation system (5) includes a reciprocating mechanism (51), a combustion chamber (52), a Laval nozzle (53), a solenoid valve (54), a proportional controller (55), an aviation kerosene storage tank (56), and a liquid oxygen storage tank (57); The reciprocating motion mechanism (51) is fixedly arranged on one side above the aircraft component (1) and is used to simulate a motion trajectory according to the size of the aircraft component (1); The combustion chamber (52) is suspended below the reciprocating mechanism (51) and is used to burn combustible gas; The Rafale nozzle (53) is connected to the combustion chamber (52), is located between the aircraft component (1) and the combustion chamber (52), and is used to eject a high-temperature and high-pressure supersonic flame flow; The solenoid valve (54) is connected to the combustion chamber (52) and is arranged on the opposite side of the Rafale nozzle (53) to open the ablation system (5); The ratio controller (55) is arranged on the surface of the combustion chamber (52) and is used to adjust the ratio of aviation kerosene and oxygen; The aviation kerosene storage tank (56) and the liquid oxygen storage tank (57) are connected to the combustion chamber (52) and are located below it, and are used to provide aviation kerosene and oxygen.

2. The device for thermal environment assessment and testing of aircraft components according to claim 1, characterized in that: The temperature measurement system (6) includes a platinum-rhodium thermocouple (61), a temperature measuring crystal (62), an infrared thermal imager (63) and a temperature recorder (64); The platinum-rhodium thermocouple (61) is placed on the surface of the aircraft component (1) and is used to transmit temperature data to the temperature recorder (64) during the pre-processing stage; The temperature measuring crystal (62) is placed on the surface of the aircraft component (1) and is used to transmit temperature data to the temperature recorder (64) during the service thermal environment phase of the aircraft component (1); The infrared thermal imager (63) is arranged on the other side of the aircraft component (1), opposite to the Rafale nozzle (53), and is used to monitor the surface temperature change of the aircraft component (1) in real time; The temperature recorder (64) is arranged above the aircraft component (1) and is used to record the temperature distribution on the surface of the aircraft component (1).

3. A method for using a device for thermal environment assessment and testing of aircraft components, characterized in that: The device for thermal environment assessment and testing of aircraft components according to any one of claims 1 to 2 is implemented, comprising the following steps: S1, set up the test equipment, perform heating environment pretreatment, and preset the temperature control system; S2: Maintain the temperature control system configuration and conduct service thermal environment assessment test; S3, measuring and recording the surface temperature distribution of aircraft components.

4. The method for using the device for thermal environment assessment and testing of aircraft components according to claim 3, characterized in that: The step S1 specifically includes: The ratio of aviation kerosene and oxygen is adjusted through a proportional controller. The oxygen fully atomizes the aviation kerosene to form a combustible mixture that enters the combustion chamber and is ignited to generate high-temperature and high-pressure combustion gas. After ignition and combustion through the Rafale nozzle, a high-temperature and high-pressure supersonic flame flow is formed, completing the heating environment pretreatment.

5. The method for using the device for thermal environment assessment and testing of aircraft components according to claim 4, characterized in that: The step S1 specifically includes: Platinum-rhodium thermocouples are arranged at the main temperature measuring points of the aircraft components. The temperature control system adjusts the movement speed of the reciprocating mechanism and the opening of the solenoid valve according to the temperature signal fed back by the platinum-rhodium thermocouples, records the periodic changes in the movement speed of the reciprocating mechanism and the opening of the solenoid valve, and completes the pre-setting of the temperature control system.

6. The method for using the device for thermal environment assessment and testing of aircraft components according to claim 5, characterized in that: The step S2 specifically includes: When conducting service thermal environment assessment tests, the platinum-rhodium thermocouples at the main temperature measurement points are replaced with temperature measuring crystals to reduce the impact on the surface flow field of the aircraft components and reproduce the service thermal environment of the aircraft components.

7. The method for using the device for thermal environment assessment and testing of aircraft components according to claim 6, characterized in that: The step S2 specifically includes: The surface temperature changes of aircraft components are monitored and recorded in real time using an infrared thermal imager.

8. The method for using the device for thermal environment assessment and testing of aircraft components according to claim 7, characterized in that: The step S2 specifically includes: The temperature measuring crystal has no additional supports or leads and can be placed on the surface of aircraft components without affecting the original temperature field. It has a size of 0.2 mm and can measure a maximum temperature of 1800°C with an error of less than 1.5%.

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