CN115002947B - Modular heating device and method for thermal environment simulation of aerospace aircraft - Google Patents

Abstract

The invention discloses a modular heating device and method for simulating the thermal environment of an aerospace plane. The device includes a heating box and a heating component arranged in the heating box; the heating component includes a plurality of heating pipes; The joints at both ends of the pipe wall; the pipe wall is Y ₂ O ₃ transparent ceramic pipe wall, YAG transparent ceramic pipe wall or ALON transparent ceramic pipe wall; the heating box is connected with an air compressor for delivering cold air into the heating box; the method includes 1. Determine the material of the tube wall; 2. Install the modular heating device; 3. Start the modular heating device; 4. Monitor the temperature of the aerospace aircraft test piece. By setting the heating box and the heating components in the heating box, the heating box can better achieve the sealing effect and improve the efficiency _of reflecting infrared radiation to the outside _; material, which improves the extreme temperature and service life of the tungsten filament radiation heating device.

Description

A modular heating device and method for thermal environment simulation of aerospace aircraft

technical field

The invention belongs to the technical field of thermal environment simulation of aerospace aircraft, and in particular relates to a modular heating device and method for thermal environment simulation of aerospace aircraft.

Background technique

Aerospace aircraft, referred to as aerospace aircraft, is becoming more and more important in the current and future aviation development. With the high development of aerospace vehicles in the world, the aerodynamic heating that appears after the hypersonic flight of aerospace vehicles The phenomenon is very serious, and the shell temperature of the aerospace vehicle will exceed 1200°C; in the face of the high temperature generated by aerodynamic heating, it will inevitably reduce the strength limit of the shell of the aerospace vehicle and the bearing capacity of the aircraft structure, causing thermal deformation and damage to the aircraft materials. The aerodynamic shape of the components does not affect the safe flight. In order to ensure the flight safety of aerospace vehicles, it is necessary to conduct ultra-high temperature simulation tests on aerospace vehicles. When performing ultra-high temperature simulation tests, tungsten halogen lamps are often used as heating elements for aerospace vehicles. The tungsten-halogen lamp heats the structure through the radiation of the tungsten filament, and there is a halogen gas in the tube of the tungsten-halogen lamp to ensure that the evaporated tungsten vapor will not condense on the outer wall of the lamp, thereby ensuring the life of the tungsten filament.

At present, when conducting ultra-high temperature simulation tests on aerospace vehicles, the heating devices generally used are large in size, which is inconvenient to install and replace the lamp tubes, and most of the heating devices used in ultra-high temperature simulation tests use quartz glass as the lamp tube. The wall and quartz glass have defects such as gradual softening when the temperature is above 1200 ° C. It is easy to form bulges or even damage at high temperatures, and cannot output high heat flow for a long time under this working condition. When quartz glass is at 1500 ℃, its service life is shortened sharply. These defects of quartz glass greatly limit the development of tungsten-halogen lamp heating devices; and because it is difficult to improve the high-temperature strength of quartz glass from aspects such as preparation technology; in addition, in the process of heating aerospace vehicles, testers often can only Implementing a single temperature control to test aerospace vehicles is not conducive to reflecting the overall heating performance of aerospace vehicles, thus affecting the thermal deformation analysis and strength limit analysis of aerospace vehicles during the heating process. Therefore, there is a need for a heating device that can not only solve the problems related to the lamp tube that occurs during the heating process, but also satisfy the performance analysis of aerospace vehicles.

Contents of the invention

The technical problem to be solved by the present invention is to provide a modular heating device for simulating the thermal environment of an aerospace aircraft in view of the above-mentioned deficiencies in the prior art. It can play a sealing effect and improve the efficiency of reflecting infrared radiation to the outside; by choosing Y ₂ O ₃ , YAG or ALON as the processing material of the tube wall, the strength and high temperature resistance of the heating tube can be better improved, and the tungsten filament can be improved. The extreme temperature and service life of the radiation heating device have created good economic benefits.

In order to solve the above-mentioned technical problems, the technical solution adopted in the present invention is: a modular heating device for simulating the thermal environment of an aerospace aircraft, which is characterized in that: it includes a heating box arranged above the aerospace aircraft test piece and is arranged on the heating box. A heating assembly for heating the aerospace test piece in the box; a temperature sensor is arranged on the outer surface of the aerospace test piece, and the temperature sensor is connected to the controller;

The heating box includes a bottom plate arranged horizontally, a reflective top plate unit arranged horizontally directly above the bottom plate, and a side plate assembly vertically arranged between the bottom plate and the reflective top plate unit;

The reflective top plate unit includes a horizontally arranged reflective top plate and two reflective side baffles that are vertically arranged and symmetrically arranged on both sides of the reflective top plate, the reflective top plate and the two reflective side baffles are integrally formed, The reflective top plate and the two reflective side baffles form a door-shaped top plate, and the opening of the reflective top plate unit faces the heating assembly; the top of the reflective top plate is provided with a power interface;

The side plate assembly includes two groups of first side plate units and second side plate units that are arranged vertically and symmetrically on the bottom plate and connected with the reflective top plate;

The heating assembly includes a plurality of heating tubes arranged horizontally in the heating box, and the plurality of heating tubes are arranged along the width direction of the heating box; one end of the heating tube is clamped on the first side On the plate unit, the other end of the heating tube is clamped on the second side plate unit;

The heating tube includes a tube wall arranged horizontally and joints arranged at both ends of the tube wall, a tungsten filament is arranged inside the tube wall, and the tungsten filament is connected to the joints at both ends; the tube wall is filled with halogen gas ; The tube wall is Y ₂ O ₃ transparent ceramic tube wall, YAG transparent ceramic tube wall or ALON transparent ceramic tube wall;

The heating box is connected with an air compressor that delivers cold air into the heating box, the air compressor is connected with the first side plate unit, and the first side plate unit is provided with a The air compressor is connected to the air inlet through a cold air pipe; the second side plate unit is provided with an air outlet.

The above-mentioned modular heating device for simulating the thermal environment of an aerospace aircraft is characterized in that the bottom plate is a quartz glass plate.

The above-mentioned modular heating device for thermal environment simulation of aerospace aircraft is characterized in that: the top of the reflective top plate is provided with a through hole for the installation of the power interface, and the power interface is arranged in the center of the reflective top plate .

The above-mentioned modular heating device for simulating the thermal environment of an aerospace aircraft is characterized in that: the first side plate unit includes a first lower side baffle vertically arranged on the bottom plate and arranged on one side of the bottom plate plate and the first upper side baffle vertically arranged directly above the first lower side baffle and matched with the first lower side baffle; the bottom of the first lower side baffle and the bottom of the bottom plate The top surface is fixedly connected, the top of the first lower side baffle matches the bottom of the first upper side baffle, and the top of the first upper side baffle is connected to the reflective top plate by bolts.

The above-mentioned modular heating device for simulating the thermal environment of an aerospace aircraft is characterized in that: the top of the first lower side baffle is provided with a plurality of first lower clamping slots, and a plurality of the first lower clamping slots are provided. The slots are arranged along the length direction of the first lower side baffle; the bottom of the first upper side baffle is provided with a plurality of first upper clamping slots that cooperate with the first lower clamping slots. An upper clamping slot is arranged along the length direction of the first upper side baffle; the number of the first lower clamping slot, the number of the first upper clamping slot and the number of the heating tubes are equal and one One correspondence; the top of the first upper side baffle is provided with a first upper installation hole for the bolt installation; the air inlet is arranged on the first upper side baffle, and the air inlet is arranged on the side of the first upper mounting hole.

The above-mentioned modular heating device for simulating the thermal environment of an aerospace aircraft is characterized in that: the second side plate unit includes a second lower side vertically arranged on the bottom plate and arranged on the other side of the bottom plate The baffle and the second upper baffle vertically arranged directly above the second lower side baffle and matched with the second lower side baffle; the bottom of the second lower side baffle and the bottom plate The top surface of the second upper side baffle is fixedly connected, the top of the second lower side baffle is matched with the bottom of the second upper side baffle, and the top of the second upper side baffle is connected to the reflective top plate by bolts.

The above-mentioned modular heating device for simulating the thermal environment of an aerospace aircraft is characterized in that: the top of the second lower side baffle is provided with a plurality of second lower clamping grooves, and the plurality of second lower clamping grooves are arranged along the The length direction of the second lower side baffle is laid out; the bottom of the second upper side baffle is provided with a plurality of second upper clamping grooves that cooperate with the second lower clamping grooves, and a plurality of the second upper clamping grooves are arranged. The clamping slots are arranged along the length direction of the second upper side baffle; the number of the second lower clamping slots, the number of the second upper clamping slots and the number of the heating tubes are equal and correspond to each other The top of the second upper side baffle is provided with a second upper mounting hole for the bolt installation; the air outlet is arranged on the second upper side baffle, and the air outlet is arranged on the first Two upper mounting holes on one side.

The above-mentioned modular heating device for simulating the thermal environment of an aerospace aircraft is characterized in that: one end of the heating tube is clamped between the matching first lower clamping groove and the first upper clamping groove, The other end of the heating tube is clamped between the matched second lower clamping groove and the second upper clamping groove.

The present invention also provides a method for heating a test piece of an aerospace aircraft with a modular heating device for simulating the thermal environment of an aerospace aircraft, characterized in that the method comprises the following steps:

Step 1. Determine the material of the pipe wall: According to the thermal environment simulation test requirements of the aerospace aircraft test piece to be tested, determine the temperature target value that needs to be applied to the aerospace aircraft test piece to be tested, and select the material that meets the temperature target value according to the size of the temperature target value. Pipe wall material for temperature target value;

Step 2. Install the modular heating device: prepare the pipe wall of the heating pipe according to the pipe wall material selected in step 1, and then install the modular heating device above the aerospace aircraft test piece to be tested, so that the base plate is laid near The top of the aerospace aircraft test piece to be tested; and a temperature sensor is installed on the outer surface of the aerospace aircraft test piece, and an external power supply is connected on the power interface;

Step 3, start the modular heating device, the process is as follows:

Step 301, start the external power supply, energize the heating tube through the power interface, the heating tube radiates heat flow outward, heat the aerospace aircraft test piece, and collect the aerospace test piece through the temperature sensor temperature value;

Step 302, start the air compressor at the same time, and the air compressor sends cold air into the heating box, cools the surface of the heating pipe, and discharges it through the air outlet;

Step 4, monitoring the temperature of the aerospace aircraft test piece: according to the test temperature value that the aerospace aircraft test piece needs to reach, the temperature sensor measures the temperature of the aerospace aircraft test piece, when the temperature sensor When the measured value is equal to the test temperature value that the aerospace test piece needs to reach, the heating pipe continues to maintain the temperature to heat the aerospace test piece; when the measured value of the temperature sensor and the air When the test temperature values to be reached by the aircraft test piece are not equal, the controller adjusts the power of the tungsten filament in the heating tube to change the heat flow radiated from the heating tube until the actual measured value of the temperature sensor is equal to the air temperature. The test temperature values that the aircraft test pieces need to reach are equal.

The beneficial effect of the present invention is that by setting the heating box and the heating assembly in the heating box, the heating box can better play a sealing effect and improve the efficiency of reflecting infrared radiation to the outside; by selecting Y ₂ O ₃ , YAG or ALON as the The processing material of the tube wall can better improve the strength and high temperature resistance of the heating tube, improve the limit temperature and service life of the tungsten filament radiation heating device, and create good economic benefits; Air is conveyed in the heating box to cool the heating tubes in the heating box, effectively reducing the service temperature of the heating tubes and increasing the service life of the heating tubes.

The technical solutions of the present invention will be described in further detail below with reference to the accompanying drawings and embodiments.

Description of drawings

Figure 1 is an exploded view of the present invention.

Fig. 2 is a structural schematic diagram of the heating tube of the present invention.

Fig. 3 is a diagram of the use state of the present invention.

Fig. 4 is a schematic block diagram of the circuit of the present invention.

Fig. 5 is a flow chart of the method of the present invention.

Explanation of reference signs:

1—heating tube; 1-1—tube wall; 1-2—tungsten filament;

1-3—joint; 2—the first upper side baffle; 2-1—the first upper clamping slot;

2-2—the first upper mounting hole; 2-3—the air inlet; 3—the second upper side baffle;

3-1—the second upper clamping slot; 3-2—the second upper mounting hole; 3-3—air outlet;

4—the first lower side baffle; 4-1—the first lower clamping slot; 5—the second lower side baffle;

5-1—Second lower clamping slot; 6—Reflective top plate; 6-1—Through hole;

6-2—installation hole; 7—bottom plate; 8—power interface;

9—reflective side baffle; 10—aircraft test piece; 11—temperature sensor;

12—controller; 13—air compressor; 14—air-cooling pipe.

Detailed ways

As shown in Figures 1 to 4, the present invention includes a heating box arranged above the aerospace aircraft test piece 10 and a heating assembly arranged in the heating box to heat the aerospace test piece 10; the aerospace plane A temperature sensor 11 is arranged on the outer surface of the test piece 10, and the temperature sensor 11 is connected with a controller 12;

The heating box includes a horizontally arranged bottom plate 7, a reflective top plate unit horizontally arranged directly above the bottom plate 7, and a side plate assembly vertically arranged between the bottom plate 7 and the reflective top plate unit;

The reflective top plate unit includes a horizontally arranged reflective top plate 6 and two reflective side baffles 9 arranged vertically and symmetrically on both sides of the reflective top plate 6, the reflective top plate 6 and the two reflective side baffles The plate 9 is integrally formed, the reflective top plate 6 and two reflective side baffles 9 form a door-shaped top plate, the opening of the reflective top plate unit faces the heating assembly; the top of the reflective top plate 6 is provided with a power interface 8;

The side plate assembly includes two groups of first side plate units and second side plate units that are vertically arranged and symmetrically arranged on the bottom plate 7 and connected with the reflective top plate 6;

The heating assembly includes a plurality of heating tubes 1 arranged horizontally in the heating box, and the plurality of heating tubes 1 are arranged along the width direction of the heating box; one end of the heating tube 1 is clamped on the On the first side plate unit, the other end of the heating tube 1 is clamped on the second side plate unit;

The heating tube 1 includes a tube wall 1-1 arranged horizontally and joints 1-3 arranged at both ends of the tube wall 1-1, a tungsten filament 1-2 is arranged inside the tube wall 1-1, and the tungsten The filament _1-2 is connected to the joints 1-3 at both ends; the tube wall 1-1 is filled with halogen gas; the tube wall 1-1 is _Y2O3 transparent ceramic tube wall, YAG transparent ceramic tube wall or ALON Transparent ceramic tube wall;

The heating box is connected with an air compressor 13 for delivering cold air into the heating box, the air compressor 13 is connected with the first side plate unit, and the first side plate unit is provided with a The air compressor 13 cooperates with the air inlet 2-3, and the air compressor 13 and the air inlet 2-3 are connected through a cold air pipe 14; the second side plate unit is provided with an air outlet 3-3.

In the present invention, by setting the heating box and the heating components in the heating box, the heating box can better play a sealing effect and improve the efficiency of reflecting infrared radiation to the outside; by choosing Y ₂ O ₃ , YAG or ALON as the tube wall 1- 1, can better improve the strength and high temperature resistance of the heating tube 1, improve the limit temperature and service life of the tungsten filament radiation heating device, and create good economic benefits; in addition, by setting the air compressor 13, it can Air is delivered into the heating box to cool the heating tube 1 in the heating box, effectively reducing the service temperature of the heating tube 1 and increasing the service life of the heating tube 1 .

In actual use, the first lower side baffle 4, the first upper side baffle 2, the second upper side baffle 3, the second upper side baffle 3, and the reflecting top plate unit are all made of aluminum alloy. into, used to close the heating box, and reflect infrared radiation. The tube wall 1-1 can be Y ₂ O ₃ transparent ceramic tube wall, YAG transparent ceramic tube wall or ALON transparent ceramic tube wall; wherein, the volume density of Y ₂ O ₃ transparent ceramic material is 5.03g/cm ³ The bending strength is 200MPa, the fracture toughness is 2.5MPa, the elastic modulus is 164GPa, Poisson's ratio is 0.29, the Vickers hardness is 11GPa, the thermal conductivity is 14W/mk, and the thermal expansion coefficient (25℃~1000℃) is 6×10 ^‒6 ~7×10 ^‒6 , the transmission band is 0.25μm~8μm, the maximum light transmittance is 81%, the refractive index (n@1000nm) is 1.95, the dielectric constant is 11.8, and the dielectric loss is 5×10 ^{‒ 4.} The melting point is 2430°C.

The bulk density of YAG transparent ceramic material is 4.55g/cm ³ , the bending strength at room temperature is 300MPa, the fracture toughness is 2.0MPa, the elastic modulus is 234GPa, Poisson's ratio is 0.23, the Vickers hardness is 13.4GPa, and the thermal conductivity is 12W /mk, the coefficient of thermal expansion (25℃~1000℃) is 8×10 ^‒6 , the transmission wavelength range is 0.25μm~6μm, the maximum light transmittance is 84%, the refractive index (n@1000nm) is 1.82, and the dielectric constant is 10.81MHz, the dielectric loss is 5×10 ^‒4 , and the melting point is 1950°C.

The bulk density of ALON transparent ceramic material is 3.72g/cm ³ , the bending strength at room temperature is 300MPa, the fracture toughness is 1.4MPa, the elastic modulus is 317GPa, Poisson's ratio is 0.24, the Vickers hardness is 16GPa, and the thermal conductivity is 12.6W /mk, the coefficient of thermal expansion (25℃~1000℃) is 5.83×10 ^‒6 , the transmission wavelength range is 0.25μm~5μm, the maximum light transmittance is 80.2%, the refractive index (n@1000nm) is 1.79, and the dielectric constant is 9.91MHz, the dielectric loss is less than 5×10 ^‒4 , and the melting point is 2165°C.

When the present invention is actually used, the method for simulating the thermal environment of an aerospace aircraft using a modular heating device first selects the material of the tube wall 1-1 according to the temperature achieved by the thermal environment simulation of the aerospace aircraft, and then determines the material The heating tube 1 is installed in the heating box, the heating power supply is connected to the power interface 8, the heating power supply is started, and the multiple heating tubes 1 radiate heat flow outward through the bottom plate 7, and are tested on the aerospace aircraft or the aerospace aircraft. Part 10 is subjected to a thermal environment simulation test.

In this embodiment, the bottom plate 7 is a quartz glass plate.

In actual use, the bottom plate 7 is made of quartz glass, which can be used to transmit the infrared radiation emitted by the heating tube 1 .

As shown in FIG. 1 , in this embodiment, the top of the reflective top plate 6 is provided with a through hole 6 - 1 for installing the power interface 8 , and the power interface 8 is arranged at the center of the reflective top plate 6 .

In actual use, both ends of the reflective top plate 6 are provided with installation holes 6-2 for bolt installation; the first side plate unit and the second side plate unit are respectively arranged at both ends of the reflective top plate 6 .

As shown in FIG. 1 , in this embodiment, the first side plate unit includes a first lower side baffle 4 vertically arranged on the bottom plate 7 and arranged on one side of the bottom plate 7 and a vertically arranged The first upper side baffle 2 directly above the first lower side baffle 4 and matched with the first lower side baffle 4; the bottom of the first lower side baffle 4 and the top of the bottom plate 7 The surface is fixedly connected, the top of the first lower side baffle 4 is matched with the bottom of the first upper side baffle 2, and the top of the first upper side baffle 2 is connected to the reflective top plate 6 by bolts .

As shown in Figure 1, in this embodiment, the top of the first lower side baffle 4 is provided with a plurality of first lower clamping grooves 4-1, and the plurality of first lower clamping grooves 4-1 are The length direction of the first lower side baffle 4 is arranged; the bottom of the first upper side baffle 2 is provided with a plurality of first upper clamping grooves 2-1 that cooperate with the first lower clamping grooves 4-1 , a plurality of the first upper clamping slots 2-1 are arranged along the length direction of the first upper side baffle plate 2; the number of the first lower clamping slots 4-1, the first upper clamping slots The number of slots 2-1 is equal to the number of heating tubes 1 and corresponds one by one; the top of the first upper side baffle plate 2 is provided with a first upper installation hole 2-2 for the bolt installation; The air inlet 2-3 is arranged on the first upper side baffle 2, and the air inlet 2-3 is arranged on one side of the first upper mounting hole 2-2.

As shown in Figure 1, in this embodiment, the second side plate unit includes a second lower side baffle 5 vertically arranged on the bottom plate 7 and arranged on the other side of the bottom plate 7 and a vertically arranged The second upper side baffle 3 directly above the second lower side baffle 5 and matched with the second lower side baffle 5; the bottom of the second lower side baffle 5 and the bottom of the bottom plate 7 The top surface is fixedly connected, the top of the second lower side baffle 5 is matched with the bottom of the second upper side baffle 3 , and the top of the second upper side baffle 3 is connected with the reflective top plate 6 by bolts connect.

As shown in Figure 1, in this embodiment, the top of the second lower side baffle 5 is provided with a plurality of second lower fitting grooves 5-1, and the plurality of second lower fitting grooves 5-1 are arranged along the The length direction of the second lower side baffle 5 is laid out; the bottom of the second upper side baffle 3 is provided with a plurality of second upper clamping grooves 3-1 which cooperate with the second lower clamping grooves 5-1, and The second upper clamping slots 3-1 are arranged along the length direction of the second upper side baffle plate 3; the number of the second lower clamping slots 5-1, the second upper clamping slots 3 The number of -1 is equal to the number of the heating tubes 1 and corresponds one by one; the top of the second upper side baffle plate 3 is provided with a second upper mounting hole 3-2 for the bolt installation; the air outlet 3-3 is arranged on the second upper side baffle 3, and the air outlet 3-3 is arranged on one side of the second upper mounting hole 3-2.

As shown in Figure 1, in this embodiment, one end of the heating tube 1 is clamped between the matched first lower clamping groove 4-1 and the first upper clamping groove 2-1, the The other end of the heating tube 1 is clamped between the matched second lower clamping groove 5-1 and the second upper clamping groove 3-1.

As shown in Figures 1 to 5, a method for heating an aerospace aircraft test piece with a modular heating device for simulating the thermal environment of an aerospace aircraft, the method comprises the following steps:

Step 1, determine the pipe wall material: according to the thermal environment simulation test requirements of the aerospace aircraft test piece 10 to be tested, determine the temperature target value that needs to be applied to the aerospace plane test piece 10 to be tested, and select according to the size of the temperature target value Pipe wall material that meets the temperature target value;

Step 2, install the modular heating device: prepare the pipe wall 1-1 of the heating pipe 1 according to the pipe wall material selected in the step 1, and then install the modular heating device on the top of the aerospace aircraft test piece 10 to be tested, so that all The bottom plate 7 is arranged near the top of the aerospace aircraft test piece 10 to be tested; and a temperature sensor 11 is installed on the outer surface of the aerospace aircraft test piece 10, and an external power supply is connected on the power interface 8;

Step 3, start the modular heating device, the process is as follows:

Step 301, start the external power supply, energize the heating tube 1 through the power supply interface 8, the heating tube 1 radiates heat flow outward, heat the aerospace aircraft test piece 10, and collect the temperature sensor 11 The temperature value of the aerospace aircraft test piece 10;

Step 302, start the air compressor 13 at the same time, and the air compressor 13 sends cold air into the heating box, cools the surface of the heating tube 1, and discharges it through the air outlet 3-3;

Step 4, monitoring the temperature of the aerospace test piece: according to the test temperature value that the aerospace test piece 10 needs to reach, the temperature sensor 11 measures the temperature of the aerospace test piece 10, when the When the measured value of the temperature sensor 11 is equal to the test temperature value that the aerospace test piece 10 needs to reach, the heating pipe 1 continues to maintain the temperature to heat the aerospace test piece 10; when the temperature sensor When the measured value of 11 is not equal to the test temperature value that the aerospace aircraft test piece 10 needs to reach, the power of the tungsten filament 1-2 in the heating tube 1 is adjusted by the controller 12, and the outward direction of the heating tube 1 is changed. The radiated heat flow until the measured value of the temperature sensor 11 is equal to the test temperature value that the aerospace test piece 10 needs to reach.

By adjusting the power of the tungsten filament 1-2 in the heating tube 1, the present invention can precisely adjust the radiant heat flow of the lamp tube, so as to facilitate the heating of the aerospace test piece 10. The distance between the aerospace test piece 10 and the modular heating device is preferably 5 cm. As shown in FIG. 3 , it is a diagram of the use state of the modular heating device and the aerospace aircraft test piece 10 when no external power supply is connected.

The above are only preferred embodiments of the present invention, and do not limit the present invention in any way. All simple modifications, changes and equivalent structural changes made to the above embodiments according to the technical essence of the present invention still belong to the technical aspects of the present invention. within the scope of protection of the scheme.

Claims (8)

1. A modularized heating method for simulating the thermal environment of an aerospace plane is characterized by comprising the following steps: the test device comprises a heating box arranged above a test piece (10) of the aerospace plane and a heating assembly arranged in the heating box and used for heating the test piece (10) of the aerospace plane; a temperature sensor (11) is arranged on the outer surface of the aerospace plane test piece (10), and the temperature sensor (11) is connected with a controller (12);

the heating box comprises a bottom plate (7) which is horizontally arranged, a reflective top plate unit which is horizontally arranged right above the bottom plate (7) and a side plate assembly which is vertically arranged between the bottom plate (7) and the reflective top plate unit;

the reflecting top plate unit comprises a horizontally arranged reflecting top plate (6) and two reflecting side baffle plates (9) which are vertically arranged and symmetrically arranged on two sides of the reflecting top plate (6), the reflecting top plate (6) and the two reflecting side baffle plates (9) are integrally formed, the reflecting top plate (6) and the two reflecting side baffle plates (9) enclose a door-shaped top plate part, and an opening of the reflecting top plate unit faces the heating assembly; the top of the reflecting top plate (6) is provided with a power interface (8);

the side plate assembly comprises a first side plate unit and a second side plate unit which are vertically arranged and symmetrically distributed on the bottom plate (7) and connected with the reflection top plate (6);

the heating assembly comprises a plurality of heating pipes (1) which are horizontally arranged in the heating box, and the plurality of heating pipes (1) are distributed along the width direction of the heating box; one end of the heating pipe (1) is clamped on the first side plate unit, and the other end of the heating pipe (1) is clamped on the second side plate unit;

the heating pipe (1) comprises a pipe wall (1-1) which is horizontally arranged and joints (1-3) which are arranged at two ends of the pipe wall (1-1), a tungsten filament (1-2) is arranged in the pipe wall (1-1), and the tungsten filament (1-2) is connected with the joints (1-3) at two ends; halogen gas is filled in the pipe wall (1-1); the pipe wall (1-1) is Y ₂ O ₃ A transparent ceramic tube wall, a YAG transparent ceramic tube wall or an ALON transparent ceramic tube wall;

an air compressor (13) for conveying cold air into the heating box is connected to the heating box, the air compressor (13) is connected to the first side plate unit, an air inlet (2-3) matched with the air compressor (13) is formed in the first side plate unit, and the air compressor (13) and the air inlet (2-3) are connected through a cold air pipe (14); the second side plate unit is provided with an air outlet (3-3);

the method comprises the following steps:

step one, determining the material of a pipe wall: according to the thermal environment simulation test requirement of the aerospace plane test piece (10) to be tested, determining a temperature target value to be applied to the aerospace plane test piece (10) to be tested, and selecting a pipe wall material meeting the temperature target value according to the temperature target value;

step two, installing a modularized heating device: preparing a pipe wall (1-1) of the heating pipe (1) according to the pipe wall material selected in the step one, and then installing a modular heating device above the aerospace plane test piece (10) to be tested to enable the bottom plate (7) to be arranged at the position close to the top of the aerospace plane test piece (10) to be tested; a temperature sensor (11) is arranged on the outer surface of the aerospace plane test piece (10), and an external power supply is connected to the power supply interface (8);

step three, starting the modularized heating device, and the process is as follows:

301, starting an external power supply, electrifying the heating pipe (1) through the power supply interface (8), radiating heat flow outwards by the heating pipe (1), heating the aerospace plane test piece (10), and acquiring a temperature value of the aerospace plane test piece (10) through the temperature sensor (11);

step 302, simultaneously starting an air compressor (13), wherein the air compressor (13) conveys cold air into the heating box, cools the surface of the heating pipe (1), and discharges the cold air through the air outlet (3-3);

step four, monitoring the temperature of the aerospace plane test piece: according to the test temperature value which needs to be reached by the aerospace plane test piece (10), the temperature sensor (11) measures the temperature of the aerospace plane test piece (10), and when the measured value of the temperature sensor (11) is equal to the test temperature value which needs to be reached by the aerospace plane test piece (10), the heating pipe (1) continuously maintains the temperature and heats the aerospace plane test piece (10); when the measured value of the temperature sensor (11) is not equal to the test temperature value required to be reached by the aerospace plane test piece (10), the power of a tungsten filament (1-2) in the heating pipe (1) is adjusted through a controller (12), and the heat flow radiated outwards by the heating pipe (1) is changed until the measured value of the temperature sensor (11) is equal to the test temperature value required to be reached by the aerospace plane test piece (10).

2. The modular heating method for simulating the thermal environment of the aerospace plane as claimed in claim 1, wherein: the bottom plate (7) is a quartz glass plate.

3. The modular heating method for simulating the thermal environment of the aerospace plane as claimed in claim 1, wherein: the top of the reflection top plate (6) is provided with a through hole (6-1) for installing the power interface (8), and the power interface (8) is arranged at the center of the reflection top plate (6).

4. The modularized heating method for simulating the thermal environment of the aerospace plane as claimed in claim 1, wherein: the first side plate unit comprises a first lower baffle (4) which is vertically arranged on the bottom plate (7) and is arranged on one side of the bottom plate (7) and a first upper baffle (2) which is vertically arranged right above the first lower baffle (4) and is matched with the first lower baffle (4); the bottom of the first lower baffle (4) is fixedly connected with the top surface of the bottom plate (7), the top of the first lower baffle (4) is matched with the bottom of the first upper baffle (2), and the top of the first upper baffle (2) is connected with the reflection top plate (6) through bolts.

5. The modularized heating method for simulating the thermal environment of the aerospace plane as claimed in claim 4, wherein: the top of the first lower baffle (4) is provided with a plurality of first lower clamping grooves (4-1), and the first lower clamping grooves (4-1) are distributed along the length direction of the first lower baffle (4); the bottom of the first upper side baffle (2) is provided with a plurality of first upper clamping grooves (2-1) matched with the first lower clamping grooves (4-1), and the plurality of first upper clamping grooves (2-1) are distributed along the length direction of the first upper side baffle (2); the number of the first lower clamping grooves (4-1), the number of the first upper clamping grooves (2-1) and the number of the heating pipes (1) are equal and are in one-to-one correspondence; the top of the first upper side baffle (2) is provided with a first upper mounting hole (2-2) for mounting the bolt; the air inlets (2-3) are arranged on the first upper side baffle (2), and the air inlets (2-3) are arranged on one side of the first upper mounting hole (2-2).

6. The modularized heating method for simulating the thermal environment of the aerospace plane as claimed in claim 5, wherein: the second side plate unit comprises a second lower side baffle (5) which is vertically arranged on the bottom plate (7) and is arranged on the other side of the bottom plate (7) and a second upper side baffle (3) which is vertically arranged right above the second lower side baffle (5) and is matched with the second lower side baffle (5); the bottom of the second lower side baffle (5) is fixedly connected with the top surface of the bottom plate (7), the top of the second lower side baffle (5) is matched with the bottom of the second upper side baffle (3), and the top of the second upper side baffle (3) is connected with the reflection top plate (6) through bolts.

7. The modular heating method for simulating the thermal environment of the aerospace plane as claimed in claim 6, wherein: the top of the second lower side baffle (5) is provided with a plurality of second lower clamping grooves (5-1), and the plurality of second lower clamping grooves (5-1) are distributed along the length direction of the second lower side baffle (5); the bottom of the second upper side baffle (3) is provided with a plurality of second upper clamping grooves (3-1) matched with the second lower clamping grooves (5-1), and the second upper clamping grooves (3-1) are distributed along the length direction of the second upper side baffle (3); the number of the second lower clamping grooves (5-1), the number of the second upper clamping grooves (3-1) and the number of the heating pipes (1) are equal and are in one-to-one correspondence; a second upper mounting hole (3-2) for mounting the bolt is formed in the top of the second upper side baffle (3); the air outlet (3-3) is arranged on the second upper side baffle (3), and the air outlet (3-3) is arranged on one side of the second upper mounting hole (3-2).

8. The modular heating method for simulating the thermal environment of the aerospace plane as claimed in claim 7, wherein: one end of the heating pipe (1) is clamped between the first lower clamping groove (4-1) and the first upper clamping groove (2-1) which are matched with each other, and the other end of the heating pipe (1) is clamped between the second lower clamping groove (5-1) and the second upper clamping groove (3-1) which are matched with each other.

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