Hot test device and test method for simulating weightlessness environment

Abstract

The application provides a simulation weightlessness environment thermal hydraulic test device and a simulation weightlessness environment thermal hydraulic test method, and relates to the technical field of heat exchange testing. The simulation weightlessness environment thermal hydraulic test device is designed to solve the problem that there is no effective simulation weightlessness environment hydraulic test method. The simulation weightlessness environment thermal hydraulic test device comprises a unmanned aerial vehicle, a falling cabin and a test cabin. The test cabin comprises a weightlessness environment thermal hydraulic test platform. The unmanned aerial vehicle is detachably connected with the weightlessness environment thermal hydraulic test platform. A parachute is arranged in the falling cabin. The simulation weightlessness environment thermal hydraulic test device can improve the economy of the simulation weightlessness environment thermal hydraulic test.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of heat exchange testing, in particular to a simulation of weightlessness environment thermal hydraulic test device and simulation of weightlessness environment thermal hydraulic test method. BACKGROUND

[0002] In recent years, the world's science and technology power pays high attention to the development of space nuclear power technology; according to the public report, China has clearly proposed in the '2017-2045 space transportation system development roadmap' that the nuclear power space shuttle technology should make a major breakthrough, and realize the revolutionary change of space transportation mode. Among them, the nuclear reactor, heat exchange equipment, propulsion device and other key technologies with the heat flow system as the core have become the key to the transformation of space nuclear power technology, and are the most original and revolutionary science and technology frontier. The boiling heat transfer process accompanied by the dynamic evolution of bubble behavior has gradually become a widely used heat design scheme due to its more observable heat transport capacity, but the complex vapor-liquid phase behavior has further increased the design difficulty of the heat flow system. In the weightlessness environment of space, the gravity and buoyancy of the cooling medium in the heat flow system are significantly attenuated, and the interfacial effect and interphase force play a leading role in the boiling heat transfer process, and the bubbles are more likely to be adsorbed on the heating surface and gathered into vapor bullets / carpet, resulting in reduced heat transfer efficiency in the vapor diffusion zone and early occurrence of boiling crisis in the vapor aggregation zone. Therefore, how to carry out fine experiment of flow boiling under simulated weightlessness environment has become the main bottleneck for the development of space nuclear power heat flow system.

[0003] Research shows that nucleate boiling heat transfer and convective evaporation heat transfer are the main two boiling heat transfer mechanisms of the heat flow system, and are significantly affected by the evolution characteristics of the vapor-liquid phase and the dynamic behavior characteristics of the near-wall bubble. In the space weightlessness environment, the volume force acting on the working medium is significantly attenuated, and the interfacial force such as surface tension and viscosity force is greatly amplified, and the behavior development of the phase interface and the bubble is obviously different from that in the gravity field environment. In the weightlessness environment, slug flow and annular flow can occur at a lower quality condition. Moreover, for pool boiling in the weightlessness environment, even if the large bubble / group has detached, it will continue to hover near the heating surface; at this time, the weak shear flow effect will also have a significant impact on the bubble behavior.

[0004] In order to simulate the weightless environment, the main test methods of boiling heat transfer research at home and abroad mainly include: international space station, aircraft parabolic flight method and drop tower method. Among them, the international space station can obtain long-term true space weightless environment, the aircraft parabolic flight method can obtain tens of seconds of simulated weightless environment, and the drop tower method can obtain seconds of simulated weightless environment, but the test facilities are quite expensive. Under the weightless environment, the boiling heat transfer mechanism of the heat flow system has been reported to be significantly different from the gravity field environment test. At this time, the near-wall bubble not only adheres to the heating surface for a long time, but even no local micro-convection effect is observed around the bubble, resulting in a significant decrease in boiling heat transfer performance. However, some scholars have found that under low flow rate and low quality conditions, the boiling heat transfer capacity of the heating surface is not significantly affected by gravity. Even some scholars have found that under high flow rate conditions, gravity does not significantly affect the boiling heat transfer capacity. Under the condition of annular flow with higher quality, convective evaporation heat transfer is the main boiling heat transfer mechanism, and the near-wall liquid film under the weightless environment is more stable than that under the gravity environment, and the boiling heat transfer performance is significantly reduced.

[0005] In summary, the boiling heat transfer mechanism under the weightless environment is still in the exploratory stage, many basic problems have not been clarified, and some research conclusions are even contradictory, and it is urgent to establish an effective and economic simulation of weightless environment thermal hydraulic test method. SUMMARY

[0006] The first object of the present application is to provide a simulation of weightless environment thermal hydraulic test device to solve the technical problem that there is no effective and economic simulation of weightless environment hydraulic test method.

[0007] The simulation of weightless environment thermal hydraulic test device provided by the present application comprises an unmanned aerial vehicle, a falling cabin and a test cabin, the test cabin comprises a weightless environment thermal hydraulic test platform, the unmanned aerial vehicle is detachably connected with the weightless environment thermal hydraulic test platform, and a parachute is arranged in the falling cabin.

[0008] The simulation of weightless environment thermal hydraulic test device provided by the present application has the beneficial effects that:

[0009] The falling cabin and the test cabin are driven to a certain height by the unmanned aerial vehicle, and then the falling cabin and the test cabin are released, and the falling cabin and the test cabin are free falling, and after falling a set distance, the parachute in the falling cabin is opened, so that the test cabin and the weightless environment thermal hydraulic test platform in the test cabin can stably land. In the process of free falling, a simulated weightless environment with sufficient time can be provided for the thermal hydraulic test. Moreover, the test cabin can be connected with the unmanned aerial vehicle and the falling cabin again, and the test under the same parameters or different parameters can be carried out again, which obviously improves the economy.

[0010] Preferably, the weightless environment thermal hydraulic test platform comprises a frame, a boiling flow channel is installed in the frame, a thermocouple is arranged in the boiling flow channel, the boiling flow channel is communicated with a preheater, the preheater is communicated with a water pump and a pressure stabilizer, the pressure stabilizer is communicated with a condenser, and the condenser is communicated with the boiling flow channel.

[0011] Preferably, the weightless environment thermal hydraulic test platform comprises an electromagnetic flowmeter.

[0012] Preferably, pressure transmitters are arranged between the electromagnetic flowmeter and the preheater and between the electromagnetic flowmeter and the thermocouple.

[0013] Preferably, an electromagnetic valve and an adjusting valve are arranged between the electromagnetic flowmeter and the preheater.

[0014] Preferably, the weightless environment thermal hydraulic test platform further comprises ITO conductive glass, a laser emitter and an infrared camera, a hydrophilic / hydrophobic coating is arranged on the ITO conductive glass, the laser emitter is directed to the ITO conductive glass through a first beam splitter, and the infrared camera is directed to the ITO conductive glass.

[0015] Preferably, the weightless environment thermal hydraulic test platform further comprises a second beam splitter, a first high-speed camera and a second high-speed camera, the first beam splitter is optically connected with the first high-speed camera through the second beam splitter and is optically connected with the second high-speed camera through the second beam splitter and a mirror.

[0016] Preferably, the weightless environment thermal hydraulic test platform further comprises a navigation module and an accelerometer.

[0017] The second object of the present application is to provide a method for simulating a weightless environment thermal hydraulic test, so as to solve the technical problem that there is no effective and economical method for simulating a weightless environment hydraulic test.

[0018] The method for simulating a weightless environment thermal hydraulic test provided by the present application uses the simulation device, and the test method comprises the following steps: the unmanned aerial vehicle carries the falling cabin and the test cabin to ascend to a preset height; the falling cabin connecting mechanism connected with the unmanned aerial vehicle and the falling cabin is automatically disconnected; and the weightless environment thermal hydraulic test is observed in the process of free falling of the falling cabin.

[0019] The method for simulating a weightless environment thermal hydraulic test provided by the present application uses the simulation device, and the test method comprises the following steps: the unmanned aerial vehicle carries the falling cabin and the test cabin to ascend to a preset height; the falling cabin connecting mechanism connected with the unmanned aerial vehicle and the falling cabin is automatically disconnected; and the weightless environment thermal hydraulic test is observed in the process of free falling of the falling cabin.

[0020] In the preferred technical solution, at least one of the unmanned aerial vehicle inclination, the preheater heating power, the coolant flow, the coolant pressure, the heating surface temperature absolute value, the heating surface temperature change gradient and the altimeter height is obtained, and if at least one of the unmanned aerial vehicle inclination, the preheater heating power, the coolant flow, the coolant pressure, the heating surface temperature absolute value, the heating surface temperature change gradient and the altimeter height exceeds a safety value, the power supply of the preheater and the power supply of the measuring device are cut off. BRIEF DESCRIPTION OF DRAWINGS

[0021] In order to more clearly illustrate the technical solutions in the embodiments of the present application or the background art, the drawings needed to be used in the embodiments or background art description will be briefly introduced as follows. Obviously, the drawings in the following description are only embodiments of the present application, and other drawings can also be obtained by those skilled in the art without any creative effort on the basis of the provided drawings.

[0022] Figure 1 The structural schematic diagram of the thermal-hydraulic test device for simulating weightlessness environment provided by the embodiment one of the present application is shown in the figure.

[0023] Figure 2 The schematic diagram of the thermal-hydraulic test method for simulating weightlessness environment provided by the embodiment one of the present application is shown in the figure.

[0024] Explanation of reference signs:

[0025] 100 - unmanned aerial vehicle; 200 - falling cabin; 210 - falling cabin connecting mechanism; 300 - test cabin; 310 - frame; 320 - boiling flow channel; 321 - thermocouple; 330 - preheater; 331 - first heater; 332 - first heat exchanger; 340 - pressure stabilizer; 341 - second heater; 342 - second heat exchanger; 350 - water pump; 360 - condenser; 371 - electromagnetic flowmeter; 372 - pressure transmitter; 373 - differential pressure transmitter; 374 - electromagnetic valve; 375 - regulating valve; 381 - ITO conductive glass; 382 - laser emitter; 383 - infrared camera; 384 - first beam splitter; 385 - second beam splitter; 386 - first high-speed camera; 387 - second high-speed camera; 388 - reflector; 391 - navigation module; 392 - accelerometer; 393 - mobile power supply; 394 - notebook computer; 399 - test cabin suspension mechanism. DETAILED DESCRIPTION

[0026] In order to make the above-mentioned purposes, features and advantages of the present application more obvious and easy to understand, the specific embodiments of the present application will be described in detail below with reference to the drawings. It should be understood that the specific embodiments described herein are only used to explain the present application and do not limit the present application.

[0027] Example 1:

[0028] Figure 1 This is a schematic diagram of the structure of the simulated weightlessness environment thermo-hydraulic test device provided in Embodiment 1 of the present invention; as shown. Figure 1 As shown, the simulated weightless environment thermal-hydraulic test device provided in Embodiment 1 of the present invention includes a drone 100, a drop chamber 200 and a test chamber 300. The test chamber 300 includes a weightless environment thermal-hydraulic test platform. The drone 100 is detachably connected to the weightless environment thermal-hydraulic test platform. A parachute is provided in the drop chamber 200.

[0029] The drone 100 lifts the drop capsule 200 and test chamber 300 to a certain altitude, then releases them. The drop capsule 200 and test chamber 300 will then freefall. After falling a predetermined distance, the parachute in the drop capsule 200 deploys, allowing the test chamber 300 and its weightless environment thermal-hydraulic test platform to land stably. During freefall, a sufficient period of simulated weightlessness is generated for conducting thermal-hydraulic experiments. Furthermore, the test chamber 300 can later be connected to the drone 100 and drop capsule 200 to conduct experiments with the same or different parameters, significantly improving economic efficiency.

[0030] Specifically, in this embodiment, the UAV 100 is connected to the landing cabin 200 via the landing cabin connection mechanism 210, and the landing cabin 200 is connected to the test cabin 300 via the test cabin suspension mechanism 399. A large-payload UAV 100 with a maximum payload capacity of 100kg and a maximum flight altitude of 2000m can be selected to carry the test cabin 300 and the landing cabin 200 to an altitude of approximately 400m. The connection between the UAV 100 and the landing cabin 200 is released via the landing cabin connection mechanism 210, and the landing cabin 200 and the test cabin 300 begin freefall. The freefall distance is approximately 40m, and the parachute distance is approximately 360m, achieving a weightlessness environment simulation of ≥2s, where the gravitational acceleration under weightlessness conditions is ≤10. -2 g.

[0031] like Figure 1 As shown, preferably, the weightless environment thermal-hydraulic test platform includes a frame 310, a boiling channel 320 installed in the frame 310, a thermocouple installed in the boiling channel 320, the boiling channel 320 being connected to a preheater 330, the preheater 330 being connected to a water pump 350 and a pressure regulator 340, the pressure regulator 340 being connected to a condenser 360, and the condenser 360 being connected to the boiling channel 320.

[0032] Specifically, the frame 310 can be a light frame made of aluminum alloy profile, and the frame 310 is fixed in the test cabin 300. The preheater 330 includes a first heater 331 for heating the liquid in the preheater 330 and a first heat exchanger 332 for adjusting the temperature of the liquid in the preheater 330 to a suitable temperature. The liquid passing through the preheater 330 will flow into the boiling flow channel 320 to maintain the temperature stability required for the reaction. The outlet of the boiling flow channel 320 is connected to the condenser 360, which is used to cool the liquid passing through the boiling flow channel 320. The liquid cooled by the condenser 360 enters the pressure stabilizer 340, which is filled with liquid and gas, and the second heat exchanger 342 and the second heater 341 are arranged in the pressure stabilizer 340 to control the temperature and pressure in the pressure stabilizer 340, thereby controlling the pressure in the overall loop. The liquid stabilized by the pressure stabilizer 340 is pumped out by the water pump 350 and sent into the preheater 330, and then into the boiling flow channel 320, thereby forming a stable water environment.

[0033] As shown in Figure 1 , preferably, the weightless environment thermal hydraulic test platform includes an electromagnetic flowmeter 371.

[0034] By arranging the electromagnetic flowmeter 371, the liquid flow in the loop can be measured to accurately control the liquid flow, so that the heating power, the condensing power and the flow are matched to maintain the stability of the pressure and temperature at the bubble generation position.

[0035] As shown in Figure 1 , preferably, the electromagnetic flowmeter 371 is provided with a pressure transmitter 372 between the electromagnetic flowmeter 371 and the preheater 330 and between the electromagnetic flowmeter 371 and the thermocouple.

[0036] By arranging the pressure transmitter 372, the pressure in the loop can be obtained to accurately control the pressure in the boiling flow channel 320, so that the bubble generation in the boiling flow channel 320 is in a stable pressure range, and the test precision is improved. In addition, a differential pressure transmitter 373 can also be arranged at both ends of the boiling flow channel 320.

[0037] As shown in Figure 1 , preferably, the electromagnetic flowmeter 371 is provided with an electromagnetic valve 374 and an adjusting valve 375 between the electromagnetic flowmeter 371 and the preheater 330.

[0038] By arranging the electromagnetic valve 374 and the adjusting valve 375, not only the on-off of the loop can be controlled, but also the flow of the loop can be adjusted by the adjusting valve 375, thereby simulating the bubble generation under different flows.

[0039] As shown in Figure 1As shown, preferably, the weightless thermal hydraulic test platform further comprises ITO conductive glass 381, laser emitter 382 and infrared camera 383, the ITO conductive glass 381 is provided with a hydrophilic / hydrophobic coating, the laser emitter 382 is directed to the ITO conductive glass 381 through the first beam splitter 384, and the infrared camera 383 is directed to the ITO conductive glass 381.

[0040] Specifically, the ITO conductive glass 381 is used to realize a transparent heating surface for the optical subsystem to shoot, the transmittance of the ITO conductive glass 381 is greater than or equal to 85%, the sheet resistance is less than or equal to 5Ω, and the size is 1mm*10mm*100mm. The ITO conductive glass 381 can be prepared by sputtering an ITO (Indium-Tin Oxide) conductive film on a tempered quartz glass, and then sputtering an Al2O3 protective layer and a hydrophilic / hydrophobic coating on the ITO conductive film in sequence, so that the transmittance of the finally prepared heating body is not less than 80%. The ITO conductive glass 381 is arranged in the boiling flow channel 320, the boiling flow channel 320 is prepared by using PC transparent material, the boiling flow channel 320 is in communication with the electromagnetic flowmeter 371 and the condenser 360, and deionized water is introduced into the boiling flow channel 320.

[0041] The laser emitter 382 can provide a light source for the bubble generation area, the ITO conductive glass 381 transmits the laser, and the bubble generation area can be observed by using the infrared camera 383 to record the heating wall temperature distribution and obtain the bubble bottom heating surface temperature distribution, so that the bubble growth process in the weightless environment can be simulated and observed.

[0042] As shown in Figure 1 Preferably, the weightless thermal hydraulic test platform further comprises a second beam splitter 385, a first high-speed camera 386 and a second high-speed camera 387, the first beam splitter 384 is connected with the first high-speed camera 386 in an optical path through the second beam splitter 385, and is connected with the second high-speed camera 387 in an optical path through the second beam splitter 385 and a mirror 388.

[0043] The laser interference imaging can be observed by using the first high-speed camera 386, the light and dark alternating ring-shaped stripes obtained by the laser interference imaging can be used to calculate the micro-liquid film thickness, and the three-phase contact line local liquid temperature can be obtained by using the laser-induced fluorescence imaging method by using the second high-speed camera 387.

[0044] As shown in Figure 1 Preferably, the weightless thermal hydraulic test platform further comprises a navigation module 391 and an accelerometer 392.

[0045] By setting the navigation module 391, the test cabin 300 can be confirmed in time after landing, and the corresponding positioning can be provided for the test personnel to recover. By setting the accelerometer 392, the acceleration of the unmanned aerial vehicle 100 can be detected, and then the position and inclination angle of the unmanned aerial vehicle 100 can be obtained.

[0046] In summary, the simulated weightless environment thermal hydraulic test device comprises a UAV 100, the UAV 100 has a maximum load of 100 kg, and a built-in power supply, the flight time of the maximum load is 0.5 h. The test device further comprises: a self-starting parachute with a weight of 1 kg and a maximum power demand of 2 W; a weightless environment thermal hydraulic test platform, the frame 310 of the weightless environment thermal hydraulic test platform weighs 2.5 kg; a falling cabin 200 and a falling cabin connecting mechanism 210, weighing 20 kg, with a maximum power demand of 0.5 W, a test cabin 300 and a test cabin suspension mechanism 399, weighing 2.5 kg, with a maximum power demand of 0.5 W; a lightweight shock-absorbing frame, weighing 1 kg; a thin-walled stainless steel pipeline, weighing 2.5 kg; a set of mobile power supply 393, weighing 10 kg, with a maximum capacity of 1 kWh, a maximum output power of 2500 W, supporting 24 V DC output and 220 V AC output; a data acquisition system, weighing 0.25 W, with a maximum power demand of 2 W, which can be powered by a computer USB interface; a first high-speed camera 386 and a second high-speed camera 387, each weighing 1.5 kg, each with a maximum power demand of 60 W, which can be powered by 220 V AC power, with a maximum shooting rate of 20000 fps; an infrared thermal imager, weighing 6 kg, with a maximum power demand of 80 W, powered by 220 V AC power, with a maximum shooting rate of 10000 fps; a laser source, weighing 1 kg, with a maximum power demand of 1 W, powered by 24 V DC power; a water pump 350, weighing 1.5 kg, with a maximum power demand of 60 W, a maximum lift of 15 m, a maximum flow of 10 L / min, and a maximum flow of 1.8 L / min that can be used in the test; an electromagnetic valve 374, weighing 0.5 kg, with a maximum power demand of 10 W; a manual regulating valve 375, weighing 0.5 kg; two sets of pressure transmitters 372, each weighing 1 kg, each with a maximum power demand of 1 W; a differential pressure transmitter 373, weighing 1 kg, with a maximum power demand of 2 W; an accelerometer 392, weighing 0.25 kg, with a maximum power demand of 1 W; a navigation module 391 with a built-in gyroscope, weighing 0.25 kg, with a maximum power demand of 1 W; a notebook computer 394 for receiving and processing data, weighing 2 kg, with a built-in power supply; a test body including an ITO conductive glass 381 and a boiling flow channel 320, weighing 1 kg, with a maximum power demand of 1850 W; a voltage stabilizer 340, which can hold 8 L of water, weighs 11 kg, with a maximum power demand of 100 W; a preheater 330, weighing 1.5 kg, with a maximum power demand of 100 W; a condenser 360, weighing 1.5 kg. The total weight of each of the above components is about 72 kg-73 kg, and the total maximum power demand is 2334 W. The total weight is less than the maximum load of the UAV 100, and the mobile power supply 393 can also meet the maximum power demand of the test device.

[0047] Example Two

[0048] As Figure 2 shown, the simulation of weightlessness environment thermal hydraulic test method provided by the second embodiment of the present application uses the simulation of weightlessness environment thermal hydraulic test device described above, and the test method comprises: the unmanned aerial vehicle 100 carries the falling cabin 200 and the test cabin 300 to rise to a preset height; the falling cabin connecting mechanism 210 connected with the unmanned aerial vehicle 100 and the falling cabin 200 is automatically disconnected; in the process of free fall of the falling cabin 200, the weightlessness environment thermal hydraulic test is observed.

[0049] In the embodiment, the preset height can be 400 m, and the rising speed is 2.0 m / s, and the rising process takes about 200 s. After reaching the preset height, the falling cabin connecting mechanism 210 is disconnected, the test cabin 300, the falling cabin 200 and the test cabin suspension mechanism 399 are free-falling by 40 m, and the test platform can generate a weightlessness time of at least 2 s. When the falling distance reaches 40 m, the parachute in the falling cabin 200 is opened, and the parachute travel is started, and the parachute travel can be 360 m. This is sufficient to ensure the safe landing of the falling cabin 200 for further test.

[0050] Preferably, at least one of the unmanned aerial vehicle inclination, the preheater heating power, the coolant flow, the coolant pressure, the heating surface temperature absolute value, the heating surface temperature change gradient and the altimeter height is obtained, and if at least one of the unmanned aerial vehicle inclination, the preheater heating power, the coolant flow, the coolant pressure, the heating surface temperature absolute value, the heating surface temperature change gradient and the altimeter height exceeds a safety value, the power supply of the preheater 330 and the power supply of the measuring device are cut off.

[0051] When any of the above parameters exceeds the safety value, the test conditions deviate from the expected conditions, or the safety of the test equipment or the unmanned aerial vehicle 100 is endangered, so when the above parameters exceed the safety value, the power supply of the measuring device and the power supply of the heating device are cut off, and the continuation of the test can be terminated, and the possibility of danger can be reduced.

[0052] Although the present application is disclosed as above, the present application is not limited thereto. Any person skilled in the art can make various changes and modifications without departing from the spirit and scope of the present application, and therefore the protection scope of the present application should be subject to the scope defined by the claims.

[0053] Finally, it should be noted that, in this document, the term "only" is not used as a transition, but rather to limit the scope of a claim to the features recited. Also, the terminology used herein for the purpose of describing particular embodiments should not be read as indicating that the invention is limited to only these described embodiments. For example, unless otherwise defined, all terms (including technical and scientific terms) used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this invention belongs. The terminology used herein should not be interpreted to have the same meaning as those used in any prior art document unless otherwise specifically defined. In addition, it should be noted that the use of "a" or "an", that can be preceded by the terms "comprising", "containing", "having", "including", "containing", "carrying" or "with", does not, unless otherwise noted, exclude other

[0054] In the above embodiments, the orientation terms such as "upper", "lower", etc. are based on the figures shown.

[0055] The above description of disclosed embodiments provides examples, and is not intended to be limiting. Numerous modifications of these embodiments can be apparent to those of skill in the art, and the present application includes all such modifications that do not depart from the spirit and scope of the claims. It should further be noted that various claims can be drawn to cover any combination of the generic and specific features recited in any of the claims.

[0056] Accordingly, the present application is not intended to be limited to the embodiments shown herein but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.

Claims

1. A thermo-hydraulic test device for simulating weightlessness, characterized in that, The simulation weightless environment thermal hydraulic test device comprises a UAV (100), a falling cabin (200) and a test cabin (300), the test cabin (300) comprises a weightless environment thermal hydraulic test platform, the UAV (100) is detachably connected with the weightless environment thermal hydraulic test platform, and a parachute is arranged in the falling cabin (200). The weightless environment thermal hydraulic test platform comprises ITO conductive glass (381), a laser emitter (382), an infrared camera (383), a second beam splitter (385), a first high-speed camera (386) and a second high-speed camera (387), the ITO conductive glass (381) is provided with a hydrophilic / hydrophobic coating, the laser emitter (382) is directed to the ITO conductive glass (381) through a first beam splitter (384), and the infrared camera (383) is directed to the ITO conductive glass (381); the ITO conductive glass (381) is arranged in a boiling flow channel (320). The first beam splitter (384) is connected with the first high-speed camera (386) in an optical path through the second beam splitter (385) and is connected with the second high-speed camera (387) in an optical path through the second beam splitter (385) and a reflector (388); the first high-speed camera (386) is used for obtaining a light-and-dark alternating ring-shaped stripe through laser interference imaging to calculate a micro-liquid film thickness, and the second high-speed camera (387) is used for obtaining a three-phase contact line local liquid temperature through a laser-induced fluorescence imaging method.

2. The thermal-hydraulic test apparatus for simulating a weightless environment according to Claim 1, wherein The weightless environment thermal hydraulic test platform comprises a frame (310), the boiling flow channel (320) is arranged in the frame (310), a thermocouple (321) is arranged in the boiling flow channel (320), the boiling flow channel (320) is communicated with a preheater (330), the preheater (330) is communicated with a water pump (350) and a pressure stabilizer (340), the pressure stabilizer (340) is communicated with a condenser (360), and the condenser (360) is communicated with the boiling flow channel (320).

3. The thermal-hydraulic test apparatus for simulating a weightless environment according to Claim 2, wherein The weightless environment thermal hydraulic test platform comprises an electromagnetic flowmeter (371).

4. The thermal-hydraulic test apparatus for simulating a weightless environment according to Claim 3, wherein Pressure transmitters (372) are arranged between the electromagnetic flowmeter (371) and the preheater (330) and between the electromagnetic flowmeter (371) and the thermocouple (321).

5. The thermal-hydraulic test apparatus for simulating a weightless environment according to Claim 3, wherein An electromagnetic valve (374) and an adjusting valve (375) are arranged between the electromagnetic flowmeter (371) and the preheater (330).

6. The thermal-hydraulic test apparatus for simulating a weightless environment according to any one of claims 1 to 5, wherein The weightless environment thermal hydraulic test platform further comprises a navigation module (391) and an accelerometer (392).

7. A method for simulating a thermal-hydraulic test in a weightless environment, characterized by, The simulation weightless environment thermal hydraulic test device according to any one of claims 2-5, the test method comprising: the UAV (100) carrying the falling cabin (200) and the test cabin (300) rising to a preset height, automatically disconnecting a falling cabin connecting mechanism (210) connecting the UAV (100) and the falling cabin (200); in the process of free falling of the falling cabin (200), a weightless environment thermal hydraulic test is observed.

8. The thermal-hydraulic test method simulating a weightless environment according to claim 7, wherein At least one of a drone tilt angle, a preheater heating power, a coolant flow rate, a coolant pressure, a heating surface temperature absolute value, a heating surface temperature change gradient, and an altimeter height is obtained, and if at least one of the drone tilt angle, the preheater heating power, the coolant flow rate, the coolant pressure, the heating surface temperature absolute value, the heating surface temperature change gradient, and the altimeter height exceeds a safety value, power supply to the preheater (330) and a measuring device is cut off.

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