Radiation heating device and method for aerospace vehicle structure thermal test

Abstract

The invention discloses an aerospace vehicle structure thermal test radiation heating device and method, and belongs to the technical field of aerospace vehicle thermal intensity tests. The device comprises quartz lamp heating assemblies, graphite heating assemblies and a controller, the quartz lamp heating assemblies and the graphite heating assemblies are arranged in a staggered mode, and the controller is electrically connected with the quartz lamp heating assemblies and the graphite heating assemblies. The controller is used for controlling the quartz lamp heating assembly to heat the aerospace vehicle structure when the temperature of the aerospace vehicle structure to be measured does not reach a first preset temperature; or the controller is used for controlling the quartz lamp heating assembly to stop working and controlling the graphite heating assembly to heat the aerospace vehicle structure when the temperature of the aerospace vehicle structure reaches the first preset temperature. Rapid heating from normal temperature to medium-high temperature can be achieved through the quartz lamp heating assembly, ultrahigh-temperature heating is achieved through the graphite heating assembly, and the rapid ultrahigh-temperature heating requirement of an aerospace vehicle thermal test is met.

Description

Technical Field

[0001] The present application relates to the technical field of radiative heating for aerospace vehicle structure thermal tests, and particularly to a radiative heating device and method for aerospace vehicle structure thermal tests. Background Art

[0002] When an aerospace vehicle re-enters the atmosphere at a hypersonic flight speed, its external structure is subjected to strong aerodynamic heating. The temperature of the vehicle structure surface rapidly rises to extremely high temperatures, and even up to 2000 °C around the stagnation point. The severe service environment poses a severe challenge to the safety of the vehicle structure. Ground thermal tests are an important means to verify the safety of the thermal structure design of aerospace vehicles.

[0003] However, most of the existing thermal test technologies use a single heating technique. Either it can only achieve rapid heating, but the high-temperature resistance performance is insufficient, or it can meet the ultra-high temperature requirements, but the heating speed is slow and the heating time is long, resulting in the test being difficult to meet the rapid and ultra-high temperature peak heating requirements of aerospace vehicles, thus affecting the accuracy of the test results. Summary of the Invention

[0004] In view of this, the present application provides a radiative heating device and method for aerospace vehicle structure thermal tests to solve the problem that the existing aerospace vehicle structure thermal tests are difficult to meet the rapid and ultra-high temperature peak heating requirements of aerospace vehicles.

[0005] To solve the above technical problems, one technical solution adopted by the present application is: to provide a radiative heating device for aerospace vehicle structure thermal tests, which includes: a quartz lamp heating component, a graphite heating component, and a controller. The quartz lamp heating component and the graphite heating component are arranged alternately, and the controller is electrically connected to the quartz lamp heating component and the graphite heating component respectively; the controller is configured to control the quartz lamp heating component to heat the aerospace vehicle structure when the temperature of the aerospace vehicle structure to be tested has not reached the first preset temperature; or, the controller is configured to control the quartz lamp heating component to stop working and control the graphite heating component to heat the aerospace vehicle structure when the temperature of the aerospace vehicle structure reaches the first preset temperature.

[0006] As a further improvement of the present application, the quartz lamp heating assembly includes a quartz lamp flow guiding element, a first electric power device, and a plurality of quartz lamp heating elements. The plurality of quartz lamp heating elements are arranged on the quartz lamp flow guiding element. The quartz lamp flow guiding element is electrically connected to the quartz lamp heating elements and the first electric power device respectively. The first electric power device is electrically connected to the controller. The graphite heating assembly includes a graphite flow guiding element, a second electric power device, and a plurality of graphite heating elements. The plurality of graphite heating elements are arranged on the graphite flow guiding element. The graphite flow guiding element is electrically connected to the graphite heating elements and the second electric power device respectively. The second electric power device is electrically connected to the controller. The plurality of quartz lamp heating elements and the plurality of graphite heating elements are arranged in an alternating manner.

[0007] As a further improvement of the present application, it further includes an air cooling system electrically connected to the controller. Air channels are provided in both the graphite flow guiding element and the graphite heating elements. The air channel inlet of the graphite flow guiding element is communicated with the air outlet of the air cooling system. The air channel outlet of the graphite flow guiding element is communicated with the air channel inlet of the graphite heating element. Air holes communicating the air channel and the external space are provided on the graphite heating element, and the air holes are facing the quartz lamp heating elements.

[0008] As a further improvement of the present application, the gas introduced into the graphite flow guiding element by the air cooling system includes one of nitrogen or inert gas.

[0009] As a further improvement of the present application, it further includes a driving device electrically connected to the controller. The quartz lamp heating assembly is arranged on the driving device. The controller is further configured to control the driving device to operate to drive the quartz lamp heating assembly away from the graphite heating assembly when controlling the graphite heating assembly to heat the aerospace vehicle structure.

[0010] As a further improvement of the present application, it further includes a water cooling system electrically connected to the controller. The cooling module of the water cooling system is arranged adjacent to the quartz lamp heating assembly and the graphite heating assembly. The controller is further configured to control the water cooling system to operate when the quartz lamp heating assembly or the graphite heating assembly is working.

[0011] To solve the above technical problems, another technical solution adopted by the present application is: to provide a method for radiative heating of an aerospace vehicle structure thermal test, which is applied to the aerospace vehicle structure thermal test radiative heating device as described above. The aerospace vehicle structure thermal test radiative heating device includes a quartz lamp heating assembly, a graphite heating assembly, and a controller. The method includes: when the temperature of the aerospace vehicle structure does not reach the first preset temperature, the controller controls the quartz lamp heating assembly to heat the aerospace vehicle structure; when the temperature of the aerospace vehicle structure reaches the first preset temperature, the controller controls the quartz lamp heating assembly to stop working and controls the graphite heating assembly to heat the aerospace vehicle structure; when a stop instruction is received, the controller controls the graphite heating assembly to stop working.

[0012] As a further improvement of the present application, the radiation heating device for the structural thermal test of the aerospace vehicle further includes an air cooling system; the controller controls the quartz lamp heating assembly to heat the aerospace vehicle structure, including: the controller controls the quartz lamp heating assembly to heat the aerospace vehicle structure and simultaneously controls the air cooling system to operate. The air cooling system introduces low-temperature gas into the air ducts of the graphite heating assembly at a first preset flow rate, and the low-temperature gas is guided to the quartz lamp heating elements through the air ducts and air holes of the graphite heating assembly; after the controller controls the graphite heating assembly to stop working, it further includes: the controller controls the air cooling system to introduce low-temperature gas into the air ducts at a second preset flow rate, and the second preset flow rate is higher than the first preset flow rate.

[0013] As a further improvement of the present application, after the controller controls the quartz lamp heating assembly to heat the aerospace vehicle structure, it further includes: when the temperature of the aerospace vehicle structure reaches a second preset temperature, the controller controls the graphite heating assembly to operate at a first preset power for preheating, and the second preset temperature is lower than the first preset temperature; the controller controls the quartz lamp heating assembly to stop working and controls the graphite heating assembly to heat the aerospace vehicle structure, including: the controller controls the quartz lamp heating assembly to gradually reduce the power based on the incremental control method until it stops working, and simultaneously controls the graphite heating assembly to gradually increase the power based on the incremental control method until it reaches the preset power.

[0014] As a further improvement of the present application, the radiation heating device for the structural thermal test of the aerospace vehicle further includes a driving device; after the controller controls the quartz lamp heating assembly to stop working, it further includes: the controller controls the driving device to operate, and the driving device drives the quartz lamp heating assembly away from the graphite heating assembly.

[0015] The beneficial effects of the present application are:

[0016] The radiation heating device for the structural thermal test of the aerospace vehicle of the present application is provided with a quartz lamp heating assembly and a graphite heating assembly. The quartz lamp heating assembly has the characteristics of fast heating efficiency but not being resistant to high temperatures, and the graphite heating assembly has the characteristic of being resistant to high temperatures. When the temperature of the aerospace vehicle structure to be tested does not reach the first preset temperature, the quartz lamp heating assembly is used to heat the aerospace vehicle structure to achieve rapid temperature rise, thereby reducing the required heating time. When the temperature of the aerospace vehicle structure reaches the first preset temperature, the graphite heating assembly is used for heating, and it can still work stably in an ultra-high temperature environment, creating the environment required for the thermal test of the aerospace vehicle, so as to meet the rapid ultra-high temperature heating requirements of the thermal test of the aerospace vehicle. Description of the Drawings

[0017] Figure 1 It is a schematic structural diagram of an embodiment of the radiation heating device for the structural thermal test of the aerospace vehicle of the present invention;

[0018] Figure 2 It is a schematic diagram of the electrical connection relationship of an embodiment of the radiation heating device for the structural thermal test of the aerospace vehicle of the present invention;

[0019] Figure 3 It is a schematic cross-sectional structure diagram of a graphite flow guiding element of an embodiment of the radiation heating device for the structural thermal test of the aerospace vehicle of the present invention;

[0020] Figure 4 It is a schematic cross-sectional structure diagram of a graphite heating element of an embodiment of the radiation heating device for the structural thermal test of the aerospace vehicle of the present invention;

[0021] Figure 5 It is a schematic flowchart of an embodiment of the radiation heating method for the structural thermal test of the aerospace vehicle of the present invention. Detailed implementation manners

[0022] Next, the technical solutions in the embodiments of the present application will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of the present application. Obviously, the described embodiments are only a part of the embodiments of the present application, rather than all the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present application.

[0023] The terms "first", "second", and "third" in the present application are only used for descriptive purposes and cannot be understood as indicating or implying relative importance or implicitly specifying the quantity of the indicated technical features. Thus, the features defined with "first", "second", and "third" may explicitly or implicitly include at least one of such features. In the description of the present application, the meaning of "a plurality" is at least two, such as two, three, etc., unless otherwise specifically and clearly defined. All directional indications (such as up, down, left, right, front, back...) in the embodiments of the present application are only used to explain the relative spatial positions and movement conditions between components in a specific posture (as shown in the drawings). If the specific posture changes, the directional indications will also change accordingly. In addition, the terms "include" and "have" and any variations thereof are intended to cover non-exclusive inclusion. For example, a process, method, device, product, or equipment that includes a series of steps or units is not limited to the listed steps or units, but optionally further includes steps or units not listed, or optionally further includes other steps or units inherent to these processes, methods, products, or equipment.

[0024] References to "embodiments" in this disclosure mean that the specific features, structures, or characteristics described in connection with the embodiments can be included in at least one embodiment of the present application. The phrase appears in various places in the specification and does not necessarily refer to the same embodiment, nor is it an independent or alternative embodiment mutually exclusive with other embodiments. Those skilled in the art will explicitly and implicitly understand that the embodiments described herein can be combined with other embodiments.

[0025] Figure 1 is a schematic structural diagram of a radiation heating device for a hypersonic vehicle structure thermal test according to an embodiment of the present invention. As Figure 1 and Figure 2 shown, the radiation heating device for a hypersonic vehicle structure thermal test includes a quartz lamp heating assembly 1, a graphite heating assembly 2, and a controller 3.

[0026] Among them, the quartz lamp heating assembly 1 and the graphite heating assembly 2 are arranged alternately. For example, the quartz lamp heating assembly 1 and the graphite heating assembly 2 form a rectangular structure, and the quartz lamp heating assembly 1 and the graphite heating assembly 2 are arranged alternately on the surface of the rectangular structure and are evenly distributed, so that the rectangular structure can uniformly heat the surface of the hypersonic vehicle structure. In addition, the quartz lamp heating assembly 1 and the graphite heating assembly 2 can also be arranged in a curved surface shape, but both need to meet the characteristics of two alternating arrangements and uniform distribution. The controller 3 is electrically connected to the quartz lamp heating assembly 1 and the graphite heating assembly 2 respectively, and is used to control the operation of the quartz lamp heating assembly 1 and the graphite heating assembly 2.

[0027] Specifically, the controller 3 is used to control the quartz lamp heating assembly 1 to heat the hypersonic vehicle structure when the temperature of the hypersonic vehicle structure to be measured has not reached the first preset temperature; or, the controller 3 is used to control the quartz lamp heating assembly 1 to stop working and control the graphite heating assembly 2 to heat the hypersonic vehicle structure when the temperature of the hypersonic vehicle structure reaches the first preset temperature. It should be understood that the quartz lamp has the characteristics of fast heating efficiency but is not resistant to high temperatures, while graphite has large thermal inertia, low heating efficiency, but is resistant to high temperatures. Therefore, the quartz lamp can achieve rapid heating in the normal temperature to medium-high temperature stage, while graphite can achieve ultra-high temperature heating, and the two complement each other, so that both rapid heating and ultra-high temperature requirements can be met.

[0028] It should be noted that the temperature of the hypersonic vehicle structure can be obtained by a pre-set temperature sensor. The first preset temperature is pre-set, and is preferably set to 1200 °C in this embodiment. Therefore, when the temperature of the hypersonic vehicle structure is in the range of normal temperature to 1200 °C, the quartz lamp heating assembly 1 is used to heat the hypersonic vehicle structure to achieve rapid heating; when the temperature is higher than 1200 °C, the graphite heating assembly 2 is used to perform ultra-high temperature heating on the hypersonic vehicle structure.

[0029] The radiation heating device for the structural thermal test of the aerospace vehicle in this embodiment is provided with a quartz lamp heating component 1 and a graphite heating component 2. The quartz lamp heating component 1 has the characteristics of fast heating efficiency but not high temperature resistance, and the graphite heating component 2 has the characteristic of high temperature resistance. When the temperature of the aerospace vehicle structure to be tested does not reach the first preset temperature, the quartz lamp heating component 1 is used to heat the aerospace vehicle structure to achieve rapid temperature rise, thereby reducing the required heating time. When the temperature of the aerospace vehicle structure reaches the first preset temperature, the graphite heating component 2 is used for heating, which can still work stably in an ultra-high temperature environment, creating the environment required for the aerospace vehicle thermal test, so as to meet the rapid ultra-high temperature heating requirements of the aerospace vehicle thermal test.

[0030] Further, as Figure 1 and Figure 2 shown, the quartz lamp heating component 1 includes a quartz lamp diversion element 11, a first electric power device 12, and a plurality of quartz lamp heating elements 13. The plurality of quartz lamp heating elements 13 are arranged on the quartz lamp diversion element 11. The quartz lamp diversion element 11 is electrically connected to the quartz lamp heating elements 13 and the first electric power device 12 respectively. The first electric power device 12 is electrically connected to the controller 3. The graphite heating component 2 includes a graphite diversion element 21, a second electric power device 22, and a plurality of graphite heating elements 23. The plurality of graphite heating elements 23 are arranged on the graphite diversion element 21. The graphite diversion element 21 is electrically connected to the graphite heating elements 23 and the second electric power device 22 respectively. The second electric power device 22 is electrically connected to the controller 3. The plurality of quartz lamp heating elements 13 and the plurality of graphite heating elements 23 are arranged in an alternating manner.

[0031] Specifically, the first electric power device 12 is electrically connected to an external power supply and is used to control the working power of the quartz lamp diversion element 11 and the quartz lamp heating elements 13. The second electric power device 22 is electrically connected to an external power supply and is used to control the working power of the graphite diversion element 21 and the graphite heating elements 23. Both the first electric power device 12 and the second electric power device 22 are electrically connected to the controller 3. The controller 3 is used to control the start and stop of the first electric power device 12 and the second electric power device 22 and the magnitude of the output power. The plurality of quartz lamp heating elements 13 and the plurality of graphite heating elements 23 are arranged in an alternating manner, thereby forming a surface for heating the aerospace vehicle structure. It should be noted that the quartz lamp heating elements 13 and the graphite heating elements 23 are insulated from each other to avoid short circuit between them.

[0032] Further, as Figure 2 shown, the radiation heating device for the structural thermal test of the aerospace vehicle further includes an air cooling system 4 electrically connected to the controller 3. Air channels 24 are provided in both the graphite diversion element 21 and the graphite heating elements 23 (please refer to Figure 3 and Figure 4), the inlet of the air passage 24 of the graphite flow guiding element 21 is communicated with the outlet of the air cooling system 4, the outlet of the air passage 24 of the graphite flow guiding element 21 is communicated with the inlet of the air passage 24 of the graphite heating element 23, and air holes 231 communicating the air passage 24 with the external space are arranged on the graphite heating element 23 (please refer to Figure 4 ), and the air holes 231 are directed at the quartz lamp heating element 13.

[0033] It should be noted that the quartz lamp heating elements 13 and the graphite heating elements 23 are arranged alternately, the side surface of the graphite heating element 23 is directed at the quartz lamp heating element 13, and the air holes 231 are arranged on the side surface of the graphite heating element 23, so that the gas ejected from the air holes 231 can effectively cool the quartz lamp heating element 13. Specifically, when the quartz lamp heating assembly 1 starts to work, the air cooling system 4 starts to work synchronously. The gas discharged from the air cooling system 4 enters the air passage 24 from the inlet of the air passage 24 of the graphite flow guiding element 21, then enters the air passage 24 of the graphite heating element 23, and finally is ejected from the air holes 231 of the graphite heating element 23 to the side wall surface of the quartz lamp heating element 13, and the side wall surface of the quartz lamp is forced to convect and cool, so as to reduce the temperature of the quartz lamp tube wall surface, thereby significantly improving the rapid heating ability of the quartz lamp heating element 13.

[0034] It should be understood that in this embodiment, by arranging the air passage 24 in the graphite flow guiding element 21 and the graphite heating element 23, it can also reduce the heat capacity of the air passage and reduce the thermal inertia of the graphite flow guiding element 21 and the graphite heating element 23.

[0035] Furthermore, the gas introduced into the graphite flow guiding element 21 by the air cooling system 4 includes one of nitrogen or inert gas.

[0036] Specifically, by using nitrogen or inert gas as the air cooling gas, its properties are stable, it is not easy to change in an ultra-high temperature environment, and it can stably cool the quartz lamp heating element 13 to prevent the temperature of the quartz lamp heating element 13 from being too high.

[0037] Furthermore, as Figure 1 and Figure 2 shown, the radiation heating device for the structure thermal test of the aerospace vehicle further includes a driving device 5 electrically connected to the controller 3. The quartz lamp heating assembly 1 is arranged on the driving device 5. The controller 3 is further used to control the driving device 5 to work to drive the quartz lamp heating assembly 1 away from the graphite heating assembly 2 when controlling the graphite heating assembly 2 to heat the aerospace vehicle structure.

[0038] Specifically, by setting the driving device 5, during the ultra-high temperature heating stage, the driving device 5 can be used to move the quartz lamp heating component 1 to a position away from the graphite heating component 2, thereby preventing the quartz lamp heating component 1 from being damaged in the ultra-high temperature environment. Moreover, after the driving device 5 moves the quartz lamp heating component 1 away, the graphite heating elements 23 and the quartz lamp heating elements 13 are no longer arranged in an interleaved manner, and the sides between the graphite heating elements 23 face each other directly. The nitrogen or inert gas ejected from the air holes 231 of the graphite heating elements 23 just creates a low-oxygen environment for the adjacent graphite heating elements 23, protecting the graphite heating elements 23 from oxidation hazards and extending the service life of the heating device.

[0039] Further, as Figure 2 shown, the radiant heating device for aerospace vehicle structural thermal tests further includes a water cooling system 6 electrically connected to the controller 3. The cooling module of the water cooling system 6 is disposed adjacent to the quartz lamp heating component 1 and the graphite heating component 2. The controller 3 is further configured to control the operation of the water cooling system 6 when the quartz lamp heating component 1 or the graphite heating component 2 is operating.

[0040] Specifically, the water cooling system 6 is used to cool down the quartz lamp heating component 1 and the graphite heating component 2.

[0041] Figure 5 Fig. shows a schematic flow chart of an embodiment of the radiant heating method for aerospace vehicle structural thermal tests according to the present invention. The radiant heating method for aerospace vehicle structural thermal tests is applied to the radiant heating device for aerospace vehicle structural thermal tests in one of the above embodiments. The radiant heating device for aerospace vehicle structural thermal tests includes a quartz lamp heating component, a graphite heating component, and a controller; as Figure 5 shown, the method includes:

[0042] Step S1: When the temperature of the aerospace vehicle structure does not reach the first preset temperature, the controller controls the quartz lamp heating component to heat the aerospace vehicle structure.

[0043] Specifically, the quartz lamp heating component includes a quartz lamp flow guiding element, a first electric power device, and a plurality of quartz lamp heating elements. The graphite heating component includes a graphite flow guiding element, a second electric power device, and a plurality of graphite heating elements. Initially, the controller controls the outputs of the first electric power device and the second electric power device to be both zero; when it is necessary to heat the aerospace vehicle structure, the controller controls the voltage across the quartz lamp heating elements through the first power device, and uses the quartz lamp heating elements to start heating the aerospace vehicle structure.

[0044] Step S2: When the temperature of the aerospace vehicle structure reaches the first preset temperature, the controller controls the quartz lamp heating component to stop operating and controls the graphite heating component to heat the aerospace vehicle structure.

[0045] Specifically, when the temperature is heated to the first preset temperature, the controller controls the quartz lamp heating element to stop heating through the first power device, and at the same time controls the voltage across the graphite heating element through the second power device, and the graphite heating element starts to heat the aerospace vehicle structure.

[0046] Step S3: When receiving the stop instruction, the controller controls the graphite heating assembly to stop working.

[0047] Specifically, when the ultra-high temperature thermal test is completed, the voltage across the graphite heating element is controlled to reduce the output power, and the temperature is gradually decreased.

[0048] The radiation heating method for the aerospace vehicle structure thermal test in this embodiment heats the aerospace vehicle structure using the quartz lamp heating assembly when the temperature of the aerospace vehicle structure to be measured has not reached the first preset temperature, achieving rapid temperature rise, thereby reducing the required heating duration. When the temperature of the aerospace vehicle structure reaches the first preset temperature, the graphite heating assembly is used for heating, which can still work stably in the ultra-high temperature environment, creating the environment required for the aerospace vehicle thermal test, thus meeting the rapid ultra-high temperature heating requirements of the aerospace vehicle thermal test.

[0049] Further, in order to protect the quartz lamp heating element and improve the heating efficiency at the same time, the radiation heating device for the aerospace vehicle structure thermal test further includes an air-cooling system. Step S1 specifically includes:

[0050] The controller controls the quartz lamp heating assembly to heat the aerospace vehicle structure, and at the same time controls the air-cooling system to work. The air-cooling system introduces low-temperature gas into the air duct of the graphite heating assembly at a first preset flow rate, and the low-temperature gas is guided to the quartz lamp heating element through the air duct and air holes of the graphite heating assembly.

[0051] Specifically, when the quartz lamp heating assembly is working, the air-cooling system is used to introduce gas into the air ducts of the graphite guiding element and the graphite heating element, and then after spraying out through the air holes, it forms a temperature-lowering effect on the quartz lamp heating element to prevent the temperature of the quartz lamp heating element from being too high.

[0052] And in order to protect the graphite heating element, after step S3, it further includes:

[0053] The controller controls the air-cooling system to introduce low-temperature gas into the air duct at a second preset flow rate, and the second preset flow rate is higher than the first preset flow rate.

[0054] Specifically, the graphite heating element has a large thermal inertia and a slow cooling efficiency. Therefore, after the graphite heating element stops heating, the controller controls the air-cooling system to introduce low-temperature gas into the air duct at a second preset flow rate, thereby increasing the flow rate of the low-temperature gas in the air duct to rapidly cool the graphite heating element.

[0055] Further, to ensure that the heating process is not affected by the switching between the quartz lamp heating component and the graphite heating component, after step S1, the following steps are also included:

[0056] When the temperature of the aerospace vehicle structure reaches the second preset temperature, the controller controls the graphite heating component to operate at the first preset power for preheating, and the second preset temperature is lower than the first preset temperature.

[0057] Step S2 specifically includes:

[0058] The controller controls the quartz lamp heating component to gradually reduce the power based on the incremental control method until it stops working, and at the same time controls the graphite heating component to gradually increase the power based on the incremental control method until it reaches the preset power.

[0059] Specifically, the graphite heating element has a large thermal inertia and is difficult to quickly achieve temperature rise. If the graphite heating element is not preheated before switching to its operation, it is difficult for the graphite heating element to quickly reach the first preset temperature, resulting in the forced interruption of the heating process. By preheating the graphite heating element in advance, the problem of the heating process being interrupted can be effectively avoided. To further ensure the smooth switching of the heating process, during the process of the controller controlling the switching of the working modes of the quartz lamp heating element and the graphite heating element, the incremental control method is used to maintain the overall heating capacity of the heating device unchanged, further ensuring the normal progress of the heating process.

[0060] Further, to avoid damage to the quartz lamp heating element in an ultra-high temperature heating environment, the aerospace vehicle structure thermal test radiation heating device further includes a driving device;

[0061] After the step where the controller controls the quartz lamp heating component to stop working, the following steps are also included:

[0062] The controller controls the driving device to operate, and the driving device drives the quartz lamp heating component away from the graphite heating component.

[0063] Specifically, after the quartz lamp heating element stops working and the graphite heating element starts to work, the controller controls the driving device to operate, and the driving device drives the quartz lamp heating element away from the graphite heating element to avoid damage in a high temperature environment.

[0064] The above is only the implementation mode of the present application, and does not limit the patent scope of the present application. Any equivalent structure or equivalent process transformation made by using the content of the specification and drawings of the present application, or directly or indirectly applied in other related technical fields, shall be equally included in the patent protection scope of the present application.

Claims

1. A radiation heating device for structural thermal tests of an aerospace vehicle, characterized in that, It includes: A quartz lamp heating component, a graphite heating component and a controller. The quartz lamp heating component and the graphite heating component are arranged in an alternating pattern. The controller is electrically connected to the quartz lamp heating component and the graphite heating component respectively; The controller is used to control the quartz lamp heating component to heat the aerospace vehicle structure when the temperature of the aerospace vehicle structure to be tested has not reached the first preset temperature; Or, The controller is used to control the quartz lamp heating component to stop working and control the graphite heating component to heat the aerospace vehicle structure when the temperature of the aerospace vehicle structure reaches the first preset temperature.

2. The radiation heating device for the structural thermal test of the aerospace vehicle according to claim 1, characterized in that, The quartz lamp heating component includes a quartz lamp flow guiding element, a first electric power device and a plurality of quartz lamp heating elements. The plurality of quartz lamp heating elements are arranged on the quartz lamp flow guiding element. The quartz lamp flow guiding element is electrically connected to the quartz lamp heating elements and the first electric power device respectively. The first electric power device is electrically connected to the controller. The graphite heating component includes a graphite flow guiding element, a second electric power device and a plurality of graphite heating elements. The plurality of graphite heating elements are arranged on the graphite flow guiding element. The graphite flow guiding element is electrically connected to the graphite heating elements and the second electric power device respectively. The second electric power device is electrically connected to the controller. The plurality of quartz lamp heating elements and the plurality of graphite heating elements are arranged in an alternating pattern.

3. The radiative heating device for the structural thermal test of the aerospace vehicle according to claim 2, wherein It further includes an air cooling system electrically connected to the controller. Air channels are provided in both the graphite flow guiding element and the graphite heating element. The air channel inlet of the graphite flow guiding element is communicated with the air outlet of the air cooling system. The air channel outlet of the graphite flow guiding element is communicated with the air channel inlet of the graphite heating element. Air holes communicating the air channel and the external space are provided on the graphite heating element, and the air holes are facing the quartz lamp heating element.

4. The radiation heating device for the structural thermal test of the aerospace vehicle according to claim 3, characterized in that The gas introduced into the graphite flow guiding element by the air cooling system includes one of nitrogen or inert gas.

5. The radiative heating device for the structural thermal test of the aerospace vehicle according to claim 4, wherein It further includes a driving device electrically connected to the controller. The quartz lamp heating component is arranged on the driving device. The controller is further used to control the driving device to work to drive the quartz lamp heating component away from the graphite heating component when controlling the graphite heating component to heat the aerospace vehicle structure.

6. The radiative heating device for the structural thermal test of the aerospace vehicle according to claim 1, wherein It further includes a water cooling system electrically connected to the controller. The cooling module of the water cooling system is arranged adjacent to the quartz lamp heating component and the graphite heating component. The controller is further used to control the water cooling system to work when the quartz lamp heating component or the graphite heating component is working.

7. A radiation heating method for the structural thermal test of an aerospace vehicle, characterized in that, It is applied to the aerospace vehicle structure thermal test radiation heating device according to any one of claims 1-6. The aerospace vehicle structure thermal test radiation heating device includes a quartz lamp heating component, a graphite heating component and a controller; The method includes: When the temperature of the aerospace vehicle structure has not reached the first preset temperature, the controller controls the quartz lamp heating component to heat the aerospace vehicle structure; When the temperature of the aerospace vehicle structure reaches the first preset temperature, the controller controls the quartz lamp heating assembly to stop working and controls the graphite heating assembly to heat the aerospace vehicle structure. When receiving a stop instruction, the controller controls the graphite heating assembly to stop working.

8. The radiative heating method for the structural thermal test of the aerospace vehicle according to claim 7, wherein The aerospace vehicle structure thermal test radiation heating device further includes an air cooling system. The controller controls the quartz lamp heating assembly to heat the aerospace vehicle structure, including: The controller controls the quartz lamp heating assembly to heat the aerospace vehicle structure and simultaneously controls the air cooling system to work. The air cooling system introduces low-temperature gas into the air duct of the graphite heating assembly at a first preset flow rate, and the low-temperature gas is guided to the quartz lamp heating element through the air duct and air holes of the graphite heating assembly. After the controller controls the graphite heating assembly to stop working, it further includes: The controller controls the air cooling system to introduce low-temperature gas into the air duct at a second preset flow rate, and the second preset flow rate is higher than the first preset flow rate.

9. The radiation heating method for the structural thermal test of the aerospace vehicle according to claim 7, wherein After the controller controls the quartz lamp heating assembly to heat the aerospace vehicle structure, it further includes: When the temperature of the aerospace vehicle structure reaches the second preset temperature, the controller controls the graphite heating assembly to work at a first preset power for preheating, and the second preset temperature is lower than the first preset temperature. The controller controls the quartz lamp heating assembly to stop working and controls the graphite heating assembly to heat the aerospace vehicle structure, including: The controller controls the quartz lamp heating assembly to gradually reduce the power based on the incremental control method until it stops working, and simultaneously controls the graphite heating assembly to gradually increase the power based on the incremental control method until it reaches the preset power.

10. The radiation heating method for the structural thermal test of the aerospace vehicle according to claim 7, characterized in that The aerospace vehicle structure thermal test radiation heating device further includes a driving device. After the controller controls the quartz lamp heating assembly to stop working, it further includes: The controller controls the driving device to work, and the driving device drives the quartz lamp heating assembly away from the graphite heating assembly.

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