Vacuum thermal examination system for aircraft and simulation test method

Abstract

The invention relates to the technical field of aircraft part tests, and provides a vacuum thermal examination system for an aircraft and a simulation test method.The vacuum thermal examination system comprises a vacuum chamber, quartz glass, a water-cooling flange, a water-cooling cover and a quartz lamp, the vacuum chamber is used for containing a test piece, and a through hole is formed in the vacuum chamber; the quartz glass corresponds to the through hole; the water cooling flange is connected with the vacuum cabin and presses and fixes the quartz glass; the water cooling cover is arranged on the outer side of the quartz glass, and a cooling flow channel is formed in the water cooling cover; and the quartz lamp and the water cooling cover are relatively fixed so as to heat the test piece through radiation of the quartz glass. According to the invention, the quartz glass is arranged on the vacuum chamber, so that the quartz lamp can be arranged outside the chamber for radiation heating, and the influence of pressure change on the quartz lamp is avoided; meanwhile, the water cooling cover is arranged outside the cabin and used for installing the quartz lamp, cooling water circulates in the water cooling cover for cooling, and therefore the installation stability of the quartz lamp can be guaranteed, and meanwhile the thermal protection effect can be achieved.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft component testing, and in particular to a vacuum thermal assessment system and a simulation test method for aircraft. Background Art

[0002] As human beings increase their requirements for the speed and range of hypersonic aircraft, the extreme thermal environment caused by air stagnation compression is becoming more severe. At present, the more common method is to simulate the low-pressure and high-temperature environment of the aircraft through wind tunnel tests, but it is costly and time-consuming and cannot meet the current development needs. Therefore, there is an urgent need for a ground low-pressure, high-temperature (greater than 1600°) thermal environment assessment test system for aircraft components to solve the above problems.

[0003] The invention patent with the existing authorization announcement number CN1325898C discloses a quartz lamp array photoelectric heating device, which includes a frame and a heating chamber and a specimen chamber installed on the frame. The heating chamber is composed of an insulation shell, an infrared quartz lamp array installed in the insulation shell, and a light reflection screen installed above the infrared quartz lamp array. The specimen chamber is located below the heating chamber and is composed of a water-cooled flange and a shell. A push rod for measuring the deformation of the workpiece is provided at the center of the bottom.

[0004] As in the above technical solution, in order to meet the low-pressure environment changes corresponding to the aircraft's climbing and diving postures, setting up an adjustable pressure vacuum chamber is a feasible solution. However, the quartz lamp array in the above solution is directly set in the insulation shell. Since the quartz lamp needs to continue to work at high temperature in a variable pressure environment, it is affected by pressure and temperature changes. The reliability of the quartz lamp tube is low and there is a high risk of "tube explosion". The damage of the quartz lamp will cause the test to fail. Therefore, it is necessary to improve the existing device structure. Summary of the invention

[0005] In view of this, the present invention proposes a vacuum thermal assessment system and simulation test method for aircraft that can effectively avoid damage to quartz lamps, thereby ensuring normal testing, to solve the problem that quartz lamps in existing heating devices are prone to damage, resulting in test failures.

[0006] The technical solution of the present invention is achieved in this way:

[0007] In one aspect, the present invention provides a vacuum thermal assessment system for an aircraft, comprising a vacuum chamber, quartz glass, a water-cooling flange, a water-cooling cover and a quartz lamp, wherein:

[0008] The vacuum chamber is used to accommodate the test piece, and a through hole is provided on the vacuum chamber;

[0009] The quartz glass is provided with corresponding through holes;

[0010] The water-cooling flange is connected to the vacuum chamber and presses and fixes the quartz glass;

[0011] The water cooling cover is arranged on the outside of the quartz glass, and a cooling channel is opened inside the water cooling cover;

[0012] The quartz lamp is fixed relative to the water cooling cover to heat the test piece through quartz glass radiation.

[0013] On the basis of the above technical solution, preferably, it also includes a linear slide rail module and a water-cooled reflective plate, wherein:

[0014] Two water cooling covers are arranged opposite to each other, and a linear slide rail module is arranged on each of the opposite surfaces of the two water cooling covers;

[0015] The water-cooled reflector plate is connected to two linear slide rail modules;

[0016] The quartz lamp is set on a water-cooled reflector plate.

[0017] On the basis of the above technical solution, preferably, it also includes a fan, which is arranged between the two linear slide rail modules and corresponds to the quartz lamp.

[0018] On the basis of the above technical solution, preferably, the quartz lamp comprises an electrode plate, a lamp tube and a water-cooling tube, wherein the electrode plate is arranged opposite to the water-cooling reflecting plate, and a cooling channel is provided inside the electrode plate; the pole piece of the lamp tube is electrically connected to the electrode plate;

[0019] The water cooling pipe is connected and penetrates the electrode plate, and the water cooling pipe passes through the water cooling reflecting plate, and is fixed to the water cooling reflecting plate by fasteners.

[0020] On the basis of the above technical solution, preferably, the electrode plate includes a water cooling block and a clamping plate, wherein:

[0021] The water-cooling block has a strip-shaped structure, a cooling channel is provided inside the water-cooling block, and the cooling channel is connected with the water-cooling pipe;

[0022] A plurality of clamping plates are arranged in parallel on one side of the water cooling block, and two adjacent clamping plates clamp and fix the pole pieces of the lamp tube.

[0023] On the basis of the above technical solution, preferably, the water-cooling tube protrudes from both sides of the water-cooling reflecting plate so that the lamp tube is spaced apart from the water-cooling reflecting plate.

[0024] On the basis of the above technical solution, preferably, the semi-arc surface of the lamp tube away from the vacuum chamber is coated with a heat reflective coating, and the interior of the lamp tube is filled with a halogen gas that can undergo a cyclic protection reaction with the filament.

[0025] On the basis of the above technical solution, preferably, the vacuum chamber includes a chamber body, a chamber door, a three-axis sliding module, a pressure stabilizing valve and a pressure relief valve, wherein:

[0026] A through hole is provided on the cabin; the cabin door is connected to the cabin through a hinge;

[0027] The triaxial sliding module is arranged in the cabin to carry the test piece;

[0028] The pressure stabilizing valve and the pressure relief valve are arranged on the cabin body and are both communicated with the interior of the cabin body.

[0029] On the basis of the above technical solution, preferably, the water-cooling pipe, the water-cooling cover and the water-cooling reflecting plate are connected through a cooling pipeline.

[0030] In one aspect, the present invention provides a thermal assessment simulation test method, using the above-mentioned vacuum thermal assessment system for aircraft, comprising the following steps:

[0031] S1. Place the test piece in a vacuum chamber;

[0032] S2. Supply cooling water into the water-cooling flange and the water-cooling cover to test the sealing performance;

[0033] S3. After the sealing of the water-cooling flange and the water-cooling cover is confirmed, the cooling water is continuously circulated and supplied;

[0034] S4, setting the heating temperature of the quartz lamp and the internal pressure of the vacuum chamber;

[0035] S5, the quartz lamp heats the test piece through the quartz glass;

[0036] S6. After the heating is completed, the quartz lamp stops working and continues to supply cooling water to the water-cooling flange and the water-cooling cover to cool down to a safe temperature, while restoring the vacuum chamber to normal pressure;

[0037] S7. Open the vacuum chamber and take out the test piece.

[0038] The vacuum thermal assessment system and simulation test method for aircraft of the present invention have the following beneficial effects compared with the prior art:

[0039] (1) By placing quartz glass on the vacuum chamber, the quartz lamp can be placed outside the chamber for radiant heating, thereby avoiding the influence of pressure changes on the quartz lamp; at the same time, a water cooling cover is arranged outside the chamber for installing the quartz lamp, and cooling water flows through the water cooling cover to cool down, thereby ensuring the stability of the quartz lamp installation and achieving a thermal protection effect;

[0040] (2) By arranging two water-cooling covers opposite to each other and installing the quartz lamp on the water-cooling covers through a linear slide rail module, it is convenient to slide and adjust the distance between the quartz lamp and the vacuum chamber, thereby adjusting the heating efficiency, thereby improving the convenience of application; at the same time, the water-cooling cover can also cool the linear slide rail module to ensure the structural stability of the linear slide rail module;

[0041] (3) In the quartz lamp structure, the electrode of the lamp tube is connected to the electrode plate, and the electrode plate is connected to the water-cooled reflective plate through a water-cooling tube. In this way, the electrode connection of the quartz lamp can be cooled by water cooling to ensure the stability of the application; at the same time, the water-cooled reflective plate can achieve a reflection effect to improve the utilization rate of the infrared rays emitted by the quartz lamp tube;

[0042] (4) By arranging a fan between the two water-cooling covers, ventilation can be carried out through the fan, so that the temperature of the quartz lamp and various components can be reduced by air cooling, thereby ensuring the stability of system operation; and the layout of the water-cooling pipe makes the lamp tube of the quartz lamp and the water-cooling reflector plate separated, which increases the flow of gas and can achieve effective cooling of the quartz lamp;

[0043] (5) By coating the lamp body with a heat-reflective coating, the reflection effect can be increased, further improving the infrared utilization rate of the quartz lamp. 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 drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. 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 creative work.

[0045] Figure 1 A three-dimensional diagram of a vacuum thermal assessment system for an aircraft of the present invention;

[0046] Figure 2 It is a front view of the vacuum thermal assessment system for aircraft of the present invention;

[0047] Figure 3 A top view of the vacuum thermal assessment system for aircraft of the present invention;

[0048] Figure 4 For the present invention Figure 3 A magnified view of the structure at point A;

[0049] Figure 5 A side view of the vacuum thermal assessment system for aircraft of the present invention;

[0050] Figure 6 This is a structural diagram of the layout of the quartz lamp and fan of the vacuum thermal assessment system for aircraft of the present invention;

[0051] Figure 7 For the present invention Figure 6 A magnified view of the structure at point B;

[0052] Figure 8This is a structural diagram of the quartz lamp layout of the vacuum thermal assessment system for aircraft of the present invention;

[0053] Fig. 9 It is a structural diagram of the explosion structure of the vacuum chamber of the vacuum thermal assessment system for aircraft of the present invention;

[0054] Fig.10 For the present invention Figure 3 Middle AA section view;

[0055] like Fig.11 A cross-sectional view of a water-cooling flange of a vacuum thermal assessment system for an aircraft of the present invention;

[0056] In the figure: 1. vacuum chamber; 11. chamber body; 12. cabin door; 13. three-axis sliding module; 14. pressure regulating valve; 15. pressure relief valve; 101. through hole; 2. quartz glass; 3. water-cooling flange; 4. water-cooling cover; 5. quartz lamp; 51. electrode plate; 511. water-cooling block; 512. clamping plate; 52. lamp tube; 53. water-cooling pipe; 6. linear slide module; 7. water-cooling reflector plate; 8. fan. DETAILED DESCRIPTION

[0057] 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 described embodiments 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 creative work are within the scope of protection of the present invention.

[0058] like Figures 1 to 10 As shown, the vacuum thermal assessment system for aircraft of the present invention comprises a vacuum chamber 1, quartz glass 2, a water-cooling flange 3, a water-cooling cover 4, a quartz lamp 5, a linear slide rail module 6, a water-cooling reflection plate 7 and a fan 8.

[0059] like Figure 1 and Fig. 9 As shown, the vacuum chamber 1 is used to accommodate the test piece, and a through hole 101 is provided on the vacuum chamber 1; the quartz glass 2 is provided corresponding to the through hole 101; the water cooling flange 3 is connected to the vacuum chamber 1, and presses and fixes the quartz glass 2; the water cooling cover 4 is provided on the outside of the quartz glass 2, and a cooling flow channel is provided inside the water cooling cover 4; the quartz lamp 5 is relatively fixed to the water cooling cover 4, so as to radiate and heat the test piece through the quartz glass 2;

[0060] As in the above structure, when conducting the test, the test piece of the aircraft is placed in the vacuum chamber 1, and then the pressure in the vacuum chamber 1 is adjusted; then the quartz lamp 5 radiates and heats the test piece through the quartz glass 2. In this way, the quartz lamp 5 is arranged outside the vacuum chamber 1, which can avoid the pressure change in the chamber from affecting the quartz lamp 5 and avoid the problem of the quartz lamp 5 bursting and being damaged;

[0061] Furthermore, a water cooling cover 4 is provided outside the vacuum chamber 1 for installing the quartz lamp 5. The water cooling cover 4 circulates cooling water for cooling, thereby ensuring the stability of the structure, thereby ensuring the stability of the installation of the quartz lamp 5, and achieving a thermal protection effect;

[0062] At the same time, the quartz glass 2 is pressed and fixed by the water-cooling flange 3, so that after water flows through the water-cooling flange 3, it can be cooled to avoid high temperature affecting the fitting effect of the water-cooling flange 3 and the quartz glass 2, and at the same time, the failure of the fasteners used to fix the water-cooling flange 3 can be avoided.

[0063] Specifically, the water-cooling flange 3 is set to be rectangular, and its inner circle width is the same as the through hole 101. The side width of the water-cooling flange 3 is 50 mm, the thickness is 20 mm, and it is fixed to the vacuum chamber 1 by bolts.

[0064] Specifically, the through hole 101 is 700 mm long and 600 mm wide, and the length and width of the quartz glass 2 are 40 mm greater than the length and width of the through hole 101 .

[0065] In some embodiments, a gas sensor is provided in the vacuum chamber 1 for detecting gas components so as to facilitate regulating the content of each component as required.

[0066] like Figures 1 to 7 As shown, two water-cooling covers 4 are arranged opposite to each other, and a linear slide rail module 6 is arranged on the opposite surfaces of the two water-cooling covers 4; a water-cooling reflection plate 7 is connected to the two linear slide rail modules 6; and a quartz lamp 5 is arranged on the water-cooling reflection plate 7;

[0067] As in the above structure, two water-cooling covers 4 are arranged opposite to each other, and the middle parts of the two water-cooling covers 4 correspond to the quartz glass 2. At this time, the water-cooling reflector 7 is installed on the two water-cooling covers 4 through the linear slide rail module 6, and the quartz lamp 5 is installed on the water-cooling reflector;

[0068] During the application process, the linear slide rail module 6 can drive the quartz lamp 5 and the water-cooled reflector 7 to move synchronously, thereby adjusting the distance between the quartz lamp 5 and the test piece, thereby changing the heating power and improving the convenience of application;

[0069] Since the linear slide rail module 6 is installed on the water cooling cover 4, after the water cooling cover 4 is passed through the water cooling cover 4, the water cooling cover 4 can also cool down the linear slide rail module 6 to ensure the structural stability of the linear slide rail module 6;

[0070] The water-cooled reflective plate 7 is used to reflect the infrared rays of the quartz lamp 5 to improve the utilization rate of the infrared rays emitted by the quartz lamp 5; at the same time, cooling water flows through the water-cooled reflective plate 7 to achieve self-cooling.

[0071] Specifically, the linear slide rail module 6 uses a slide rail and a slider.

[0072] like Fig.10 As shown, there is a cooling channel in the upper end of the water-cooled reflective plate 7, with a diameter of 12 mm, which flows in from the water inlet located at the top and flows out from the water outlet located at the bottom, and the water inlet and the water outlet are arranged on both sides of the water-cooled reflective plate 7;

[0073] Specifically, the water cooling cover 4 adopts the same structural layout of the cooling channels.

[0074] like Fig.11 As shown, there is a cooling channel with a diameter of 12 mm inside the water-cooling flange 3, and the water inlet and outlet of the cooling channel are located 10 mm on both sides of the central axis of the water-cooling flange 3.

[0075] like Figures 6 to 8 As shown, the fan 8 is disposed between the two linear slide rail modules 6 and corresponds to the quartz lamp 5;

[0076] As in the above structure, by arranging a fan 8 between the two water-cooling covers 4, ventilation can be performed through the fan 8, so as to achieve cooling of the quartz lamp 5 and various components by air cooling, thereby ensuring the stability of system operation; in particular, the surface temperature of the quartz lamp 5 can be reduced, and the upper limit of the use of the quartz lamp 5 can be increased.

[0077] like Figure 7 and Figure 8 As shown, the quartz lamp 5 includes an electrode plate 51, a lamp tube 52 and a water-cooling tube 53, wherein the electrode plate 51 is arranged opposite to the water-cooling reflecting plate 7, and a cooling channel is provided inside the electrode plate 51; the electrode piece of the lamp tube 52 is electrically connected to the electrode plate 51; the water-cooling tube 53 is connected and penetrated with the electrode plate 51, and the water-cooling tube 53 penetrates the water-cooling reflecting plate 7 and is fixed to the water-cooling reflecting plate 7 by fasteners;

[0078] As shown in the above structure, the lamp tube 52 of the quartz lamp 5 is used for radiation heating, and the pole piece at the end of the lamp tube 52 is connected to the electrode plate 51, wherein the electrode plate 51 is provided with a cooling channel and is connected to the water cooling pipe 53, so that water can be supplied and discharged through the water cooling pipe 53, and the cooling water can circulate in the water cooling pipe 53 and the electrode plate 51, thereby achieving a cooling effect, so as to ensure that the quartz lamp 5 works stably and the test can be carried out normally;

[0079] Specifically, two electrode plates 51 are provided, and the two electrode plates 51 are fixed through two water-cooling pipes 53 passing through the water-cooling reflective plate 7. The outer wall of the water-cooling pipe 53 is provided with threads, and is fixed to the water-cooling reflective plate 7 with nuts.

[0080] Specifically, the quartz lamp 5 is 350 mm long, the internal wick is 310 mm long, and the distance between the two ends of the wick and the end of the lamp tube is 20 mm.

[0081] Specifically, the electrode plate 51 and the water cooling tube 53 are provided with a water cooling channel with a diameter of 8 mm.

[0082] like Figure 7 As shown, the electrode plate 51 includes a water-cooling block 511 and a clamping plate 512, wherein the water-cooling block 511 is in a strip-shaped structure, a cooling channel is provided inside the water-cooling block 511, and the cooling channel is connected to the water-cooling pipe 53; a plurality of clamping plates 512 are arranged in parallel on one side of the water-cooling block 511, and two adjacent clamping plates 512 clamp and fix the electrode piece of the lamp tube 52;

[0083] As in the above structure, the water cooling block 511 of the electrode plate 51 is provided with a cooling channel and connected to the water cooling pipe 53, and the clamping plate 512 is used to connect the end electrode of the quartz lamp 5, so that the electrode of the quartz lamp 5 can be heat-dissipated through the water cooling pipe 53;

[0084] Specifically, the water cooling block 511 and the clamping plate 512 are configured as an integrated structure.

[0085] Specifically, the pole piece of the quartz lamp 5 is also connected to a power source for power supply.

[0086] In some embodiments, an insulating cooling medium is used for circulation and cooling, the water cooling tube 53 is set to be an insulating material, and the electrode plate 51 is directly used as a conductive element to supply power to the quartz lamp 5 .

[0087] In some embodiments, an insulating cooling medium is used for circulation and cooling, the water-cooled reflective plate 7 is set to an insulating material, and the electrode plate 51 and the water-cooled tube 53 are used as conductive elements to supply power to the quartz lamp 5 .

[0088] like Figure 7 As shown, the water cooling tube 53 protrudes from both sides of the water cooling reflection plate 7 so that the lamp tube 52 is spaced apart from the water cooling reflection plate 7;

[0089] As in the above structure, the arrangement of the water-cooling tube 53 allows the lamp tube 52 of the quartz lamp 5 to be spaced apart from the water-cooling reflecting plate 7, which increases the flow rate of the gas and enables effective cooling of the quartz lamp.

[0090] Furthermore, the semi-arc surface of the lamp tube 52 away from the vacuum chamber 1 is coated with a heat-reflective coating, and the interior of the lamp tube 52 is filled with a halogen gas that can react with the filament in a cyclic protection reaction;

[0091] As in the above structure, by coating the lamp tube 52 with a heat-reflective coating, the reflection effect can be increased, and the infrared utilization rate of the quartz lamp 5 can be further improved; by injecting halogen gas into the lamp tube 52, the service life of the quartz lamp 5 can be guaranteed.

[0092] like Fig. 9The vacuum chamber 1 shown includes a chamber body 11, a chamber door 12, a three-axis sliding module 13, a pressure-stabilizing valve 14 and a pressure relief valve 15, wherein a through hole 101 is provided on the chamber body 11; the chamber door 12 is connected to the chamber body 11 by a hinge; the three-axis sliding module 13 is arranged in the chamber body 11 for carrying the test piece; the pressure-stabilizing valve 14 and the pressure relief valve 15 are arranged on the chamber body 11, and both are connected to the interior of the chamber body 11;

[0093] As in the above structure, the hatch 12 is connected to the cabin body 11 by a hinge, so that the test piece can be placed in by opening the hatch 12;

[0094] The three-axis sliding module 13 inside the cabin 11 is used to carry the test piece and adjust the position of the test piece. The three-axis sliding module 13 can be fixedly arranged in the cabin 11;

[0095] The pressure stabilizing valve 14 is used to connect to the pressure stabilizing system, and the pressure relief valve 15 is used to connect to the pressure relief system, so as to realize the pressure control in the vacuum chamber 1 and ensure the stability of the test operation.

[0096] In some embodiments, the water cooling pipe 53, the water cooling cover 4 and the water cooling reflective plate 7 are connected through a cooling pipeline;

[0097] As in the above structure, in order to improve the convenience of supplying water-cooling medium and the convenience of sealing performance detection, the water-cooling pipe 53, the water-cooling cover 4 and the water-cooling reflecting plate 7 are connected in series through pipelines, so that only one water inlet and one water outlet are required, thereby improving the convenience of supplying cooling medium and the convenience of detection.

[0098] Specifically, the three-axis sliding module 13 can adopt a screw linear module.

[0099] The thermal assessment simulation test method of the present invention uses the above-mentioned vacuum thermal assessment system for aircraft, and comprises the following steps:

[0100] S1. Place the test piece in the vacuum chamber 1;

[0101] S2, supply cooling water into the water cooling flange 3 and the water cooling cover 4 to test the sealing performance;

[0102] S3, after confirming the sealing performance of the water-cooling flange 3 and the water-cooling cover 4, continue to circulate and supply cooling water;

[0103] S4, setting the heating temperature of the quartz lamp 5 and the internal pressure of the vacuum chamber 1;

[0104] S5, the quartz lamp 5 heats the test piece through the quartz glass 2;

[0105] S6. After the heating is completed, the quartz lamp 5 stops working and continues to supply cooling water to the water-cooling flange 3 and the water-cooling cover 4 to cool down to a safe temperature, and at the same time restores the vacuum chamber 1 to normal pressure;

[0106] S7. Open the vacuum chamber 1 and take out the test piece.

[0107] 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 protection scope of the present invention.

Claims

1. A vacuum thermal assessment system for aircraft, characterized in that: It comprises a vacuum chamber (1), quartz glass (2), a water-cooling flange (3), a water-cooling cover (4) and a quartz lamp (5), wherein: The vacuum chamber (1) is used to accommodate a test piece, and a through hole (101) is provided on the vacuum chamber (1); The quartz glass (2) is arranged corresponding to the through hole (101); The water-cooling flange (3) is connected to the vacuum chamber (1) and presses and fixes the quartz glass (2); The water cooling cover (4) is arranged on the outside of the vacuum chamber (1), and a cooling flow channel is provided inside the water cooling cover (4); The quartz lamp (5) is fixed relative to the water cooling cover (4) so ​​as to heat the test piece by radiation through the quartz glass (2).

2. The vacuum thermal assessment system for aircraft according to claim 1, characterized in that: It also includes a linear slide rail module (6) and a water-cooled reflective plate (7), wherein: Two water cooling covers (4) are arranged opposite to each other, and one linear guide rail module (6) is arranged on each of the opposite surfaces of the two water cooling covers (4); The water-cooled reflective plate (7) is connected to the two linear slide rail modules (6); The quartz lamp (5) is arranged on the water-cooled reflection plate (7).

3. The vacuum thermal assessment system for aircraft according to claim 2, characterized in that: It also comprises a fan (8), which is arranged between the two water-cooling covers (4) and corresponds to the quartz lamp (5).

4. The vacuum thermal assessment system for aircraft according to claim 3, characterized in that: The quartz lamp (5) comprises an electrode plate (51), a lamp tube (52) and a water cooling tube (53), wherein: The electrode plate (51) is arranged opposite to the water-cooled reflective plate (7), and a cooling channel is provided inside the electrode plate (51); The electrode piece of the lamp tube (52) is electrically connected to the electrode plate (51); The water cooling pipe (53) is connected to and penetrates the electrode plate (51), and the water cooling pipe (53) passes through the water cooling reflection plate (7) and is fixed to the water cooling reflection plate (7) by means of fasteners.

5. The vacuum thermal assessment system for aircraft according to claim 4, characterized in that: The electrode plate (51) comprises a water cooling block (511) and a clamping plate (512), wherein: The water cooling block (511) is in a strip-shaped structure, a cooling channel is provided inside the water cooling block (511), and the cooling channel is connected to the water cooling pipe (53); A plurality of the clamping plates (512) are arranged in parallel on one side of the water cooling block (511), and two adjacent clamping plates (512) clamp and fix the pole piece of the lamp tube (52).

6. The vacuum thermal assessment system for aircraft according to claim 4, characterized in that: The water cooling tube (53) protrudes from both sides of the water cooling reflection plate (7) so that the lamp tube (52) is spaced apart from the water cooling reflection plate (7).

7. The vacuum thermal assessment system for aircraft according to claim 4, characterized in that: The semi-arc surface of the lamp tube (52) away from the vacuum chamber (1) is coated with a heat reflective coating, and the interior of the lamp tube (52) is filled with a halogen gas that can undergo a cyclic protection reaction with the filament.

8. The vacuum thermal assessment system for aircraft according to any one of claims 1 to 7, characterized in that: The vacuum chamber (1) comprises a chamber body (11), a chamber door (12), a three-axis sliding module (13), a pressure stabilizing valve (14) and a pressure relief valve (15), wherein: The through hole (101) is provided on the cabin (11); The cabin door (12) is connected to the cabin body (11) via a hinge; The three-axis sliding module (13) is arranged in the cabin (11) and is used to carry the test piece; The pressure stabilizing valve (14) and the pressure relief valve (15) are arranged on the cabin (11), and are both connected to the interior of the cabin (11).

9. The vacuum thermal assessment system for aircraft according to any one of claims 4 to 7, characterized in that: The water cooling pipe (53), the water cooling cover (4) and the water cooling reflection plate (7) are connected via a cooling pipeline.

10. A thermal assessment simulation test method, using the vacuum thermal assessment system for aircraft as claimed in claims 1 to 9, characterized in that: The following steps are involved: S1. placing a test piece in the vacuum chamber (1); S2, supplying cooling water into the water-cooling flange (3) and the water-cooling cover (4) to test the sealing performance; S3, after confirming the sealing performance of the water-cooling flange (3) and the water-cooling cover (4), continuously circulating the supply of cooling water; S4, setting the heating temperature of the quartz lamp (5) and the internal pressure of the vacuum chamber (1); S5, the quartz lamp (5) heats the test piece through the quartz glass (2); S6, after the heating is completed, the quartz lamp (5) stops working, and continues to supply cooling water to the water-cooling flange (3) and the water-cooling cover (4) to cool down to a safe temperature, and at the same time restores the vacuum chamber (1) to normal pressure; S7, opening the vacuum chamber (1) and taking out the test piece.

Images