CN-121994862-A - High-temperature heat pipe performance testing device and method under microgravity condition

CN121994862ACN 121994862 ACN121994862 ACN 121994862ACN-121994862-A

Abstract

The invention belongs to the technical field of high-temperature heat transfer performance test of high-temperature heat pipes, and particularly relates to a device and a method for testing the performance of the high-temperature heat pipes under microgravity conditions. The invention comprises a heat pipe performance test body, a test cabin, a protection recovery system and a high-altitude carrying platform, wherein the heat pipe performance test body is arranged in the test cabin, the high-altitude carrying platform comprises a lift-off mechanism and a release mechanism, the lift-off mechanism is used for conveying the test cabin to a specified height airspace and releasing the test cabin to realize free falling of the test cabin, and the protection recovery system adopts two-stage deceleration buffering to protect the test cabin. The invention has the advantages of controllable cost, longer microgravity time and repeated use, can carry out the performance test of the heat pipe with large length-diameter ratio under the simulated space microgravity environment, accurately and comprehensively evaluates the performance of the high-temperature heat pipe under the real working condition, and is especially suitable for testing the starting characteristic, transient state and steady state characteristic and the temperature uniformity of the high-temperature heat pipe under the microgravity condition.

Inventors

JIANG SHUNLI
YUAN DEWEN
ZHANG YOUJIA
YOU ERSHENG
Cui Yinghuan
Yan Zhangrui
XU JIANJUN
Zhou Dianzhuo

Assignees

中国核动力研究设计院

Dates

Publication Date: 20260508
Application Date: 20260409

Claims (10)

1. The utility model provides a high temperature heat pipe performance testing arrangement under microgravity condition, its characterized in that includes heat pipe performance test body, test cabin, protection recovery system and high altitude carrying platform, inside the test cabin was arranged in to the heat pipe performance test body, high altitude carrying platform, including lift-off mechanism and release mechanism for send the test cabin to appointed altitude airspace and release test cabin in order to realize the test cabin free fall, protection recovery system adopts two-stage speed reduction buffering, protection test cabin.
2. The device for testing the performance of the high-temperature heat pipe under the microgravity condition according to claim 1, wherein the heat pipe performance testing body comprises a heat pipe (1), a heating component (2) and a heat preservation component, the heat pipe (1) is a stainless steel-sodium heat pipe and is divided into an evaporation section, a heat insulation section and a condensation section from bottom to top, the heating component (2) is arranged at the evaporation section, and the heat preservation component is arranged at the heat insulation section of the heating component (2) and the heat pipe (1).
3. The device for testing the performance of the high-temperature heat pipe under the microgravity condition according to claim 2, wherein the testing cabin (3) is a two-section columnar cabin body, the inner wall of the cabin body is also provided with light heat insulation materials, and the testing cabin (3) is divided into a first section testing cabin (3 a) at the lower part and a second section testing cabin (3 b) at the upper part.
4. The device for testing the performance of the high-temperature heat pipe under the microgravity condition according to claim 3, wherein the first section of testing cabin (3 a) is smaller than the heating component (2), the heating component (2) is fixed on the central axis of the bottom of the testing cabin (3), the upper end penetrates through the top of the first section of testing cabin (3 a), the penetrating part is sealed by a flange, the second section of testing cabin (3 b) is a semi-open cabin body with the height capable of being adjusted by folding so as to adapt to different heat pipe lengths, the side surface is of a folding structure and is provided with a runner groove so as to facilitate air entering the cabin body to cool the heat pipe.
5. The device for testing the performance of the high-temperature heat pipe under the microgravity condition according to claim 4, wherein a battery pack (4), a direct-current power supply (5) and a measurement and control system (6) are arranged in the first section of testing cabin (3 a), and the battery pack (4) controls the heating power of the heating assembly (2) through the direct-current power supply (5) and supplies power for the whole process of the measurement and control system (6).
6. The device for testing the performance of the high-temperature heat pipe under the microgravity condition according to claim 5, wherein the measurement and control system (6) comprises a sensor, a high-precision data acquisition module, a control module and a storage module, and is used for acquiring data and controlling action execution, and is responsible for controlling all equipment of the device to operate and storing all test data measured by the sensor.
7. The device for testing the performance of the high-temperature heat pipe under the microgravity condition according to claim 6 is characterized in that the sensor comprises a pressure sensor, a temperature sensor and an air pressure altimeter, at least 1 pressure sensor and at least 10 temperature sensors are arranged in a cabin to respectively measure the pressure and the temperature in the cabin, at least 10 temperature sensors are arranged along the axial direction of the heat pipe (1) to measure the wall temperatures of an evaporation section, an insulation section and a condensation section of the heat pipe (1), the temperature sensors adopt armoured thermocouples, the air pressure altimeter is used for judging the height of a current test cabin (3) based on the pressure of ambient air, a high-precision data acquisition module is used for recording all data in a storage module, a test program is preset by the control module, and based on the data of the acquisition module, the autonomous control of a heating assembly (2) and a protection recovery system are realized, and all components are firmly fixed at the bottom of the test cabin to avoid movement and collision in the test process.
8. The device for testing the performance of the high-temperature heat pipe under the microgravity condition according to claim 7 is characterized in that the lifting mechanism adopts a hot air balloon and can slowly and stably convey the test cabin (3) to a high altitude of 2000-3000 m, the release mechanism adopts an explosion bolt or an electromagnetic lock, and the release mechanism receives an instruction to unlock so as to separate the test cabin from the hot air balloon and start falling freely.
9. The device for testing the performance of the high-temperature heat pipe under the microgravity condition according to claim 8, wherein the two-stage deceleration buffering is adopted, the one-stage deceleration is realized by adopting a parachute (7), the parachute (7) is integrated at the top of the test cabin (3), when the free landing reaches a preset height or speed, the parachute throwing mechanism is automatically triggered to expand the parachute (7) so as to reduce the descending speed of the test cabin (3) to be within a safe range, the two-stage buffering is realized by adopting a protection air bag (8), and a plurality of high-strength nylon air bags are adopted and are arranged at the side surface and the bottom of the test cabin (3) so as to realize large-area wrapping of the test cabin (3) and absorb the impact energy of final landing.
10. The method for testing the performance of the high-temperature heat pipe under the microgravity condition is based on the device for testing the performance of the high-temperature heat pipe under the microgravity condition according to claim 9, and is characterized by comprising the following steps: S1, installing and debugging on the ground, namely installing all equipment and instruments in a test cabin, sealing a first section of test cabin (3 a), placing a heat pipe (1) to be tested in a heating component (2) and fixing the heat pipe, debugging a system in a ground laboratory, ensuring that all functions are normal, and presetting a test program, wherein the evaporation section of the heat pipe (1) is continuously heated with heating power not lower than 500W, and the conditions of releasing and opening an umbrella are set; s2, the test cabin is lifted off, namely a measurement and control system (6) is started to automatically execute a preset program and continuously record related data, the test cabin (3) is suspended below a hot air balloon hanger of the high-altitude loading platform, and after the temperature of the wall surface of the heat pipe is stable, the high-altitude loading platform is started, so that the hot air balloon carries the test cabin (3) to vertically rise to a preset height of 3000m at a speed of 3 m/S; S3, releasing the test cabin and performing microgravity test, namely after the test cabin (3) reaches a preset height of 3000m and is stable, the measurement and control system (6) sends a release instruction, the test cabin (3) and the hot air balloon are separated to start falling freely, and the moment at the moment is recorded by the separation moment measurement and control system (6) and is used as microgravity test starting time; S4, decelerating and landing and recycling, namely when the test cabin (3) descends to the preset height of 800m, the measurement and control system (6) sends out an parachute opening instruction, the parachute (7) at the top of the test cabin (3) is thrown out and unfolded, the descending speed of the test cabin (3) is reduced to below 5m/S within 3-5S, the test cabin is safely landed through the protection air bag (8), and the test cabin (3) is recycled when the test cabin goes to a landing point according to a GPS positioning signal; S5, data analysis, namely downloading complete test data in a storage module in the test cabin (3) through an interface, and acquiring and analyzing the performance transient change of the heat pipe (1) under the condition that the gravity environment is suddenly changed into microgravity and the performance under the microgravity condition; s6, checking and multiplexing the device, namely checking the states of the test cabin (3), the heat pipe (1) and all instruments, replacing the battery pack (4) or charging the battery pack (4), resetting the parachute (7), changing the program setting of the measurement and control system, and preparing for the next test task.

Description

High-temperature heat pipe performance testing device and method under microgravity condition Technical Field The invention belongs to the technical field of high-temperature heat transfer performance test of high-temperature heat pipes, and particularly relates to a device and a method for testing the performance of the high-temperature heat pipes under microgravity conditions. Background The heat pipe is a heat transfer element which conducts heat transfer by means of working medium phase change, has important application value in aspects of solid state reactors, spacecraft thermal control and the like, and a typical application scene faces a space microgravity environment, and the operation characteristics and the heat transfer performance of the heat pipe under the space microgravity environment are obviously different from those of the ground gravity environment. The main methods of simulating microgravity environment on the ground currently comprise tower falling (short time and high cost), airplane (extremely high cost), space station or satellite in-orbit experiment (rare opportunity, long period and strict limitation on the size of a test piece). For long-time start-up and steady-state performance testing of heat pipes, especially large aspect ratio heat pipes (greater than 1 meter in length), the existing methods have limitations. Therefore, there is a need for a floor test device that provides a stable, repeatable microgravity environment for a long period of time (10 s or more) and accommodates a large test piece. Disclosure of Invention The invention solves the technical problems of providing the high-temperature heat pipe performance testing device and the high-temperature heat pipe performance testing method under the microgravity condition, which have the advantages of controllable cost, longer microgravity time and repeated use, can carry out the performance test of the heat pipe with large length-diameter ratio under the simulated space microgravity environment, accurately and comprehensively evaluate the performance of the high-temperature heat pipe under the real working condition, and are particularly suitable for the starting characteristic, transient state and steady state characteristic and the temperature uniformity test of the high-temperature heat pipe under the microgravity condition. The invention adopts the technical scheme that: The utility model provides a high temperature heat pipe performance testing arrangement under microgravity condition, includes heat pipe performance test body, test cabin, protection recovery system and high altitude carry-on platform, the test cabin is inside to be arranged in to the heat pipe performance test body, high altitude carry-on platform, including lift-off mechanism and release mechanism for send the test cabin to appointed altitude airspace and release the test cabin in order to realize the test cabin free fall, protection recovery system adopts two-stage deceleration buffering, protection test cabin. The heat pipe performance test body comprises a heat pipe, a heating component and a heat preservation component, wherein the heat pipe is an alkali metal heat pipe and is divided into an evaporation section, a heat insulation section and a condensation section from bottom to top, the heating component is arranged at the evaporation section, and the heat preservation component is arranged at the heat insulation section of the heating component and the heat pipe. The test cabin is a two-section columnar cabin body, light heat insulation materials are arranged on the inner wall of the cabin body, and the test cabin is divided into a first section of test cabin at the lower part and a second section of test cabin at the upper part. The first section test cabin is smaller than the length of the heating component, the heating component is fixed on the central axis of the bottom of the test cabin, the upper end penetrates through the top of the first section test cabin, the penetrating part is sealed by a flange, the second section test cabin is a semi-open cabin body with the height capable of being adjusted by folding so as to adapt to different heat pipe lengths, the side face of the second section test cabin is of a folding structure and is provided with a flow channel groove so that air enters the cabin body to cool the heat pipe. The battery pack, the direct current power supply and the measurement and control system are arranged in the first section of test cabin, and the battery pack controls the heating power of the heating assembly through the direct current power supply and supplies power to the measurement and control system in the whole process. The measurement and control system comprises a sensor, a high-precision data acquisition module, a control module and a storage module, and is used for acquiring data and controlling action execution, and is responsible for controlling all equipment of the device to run and storing all test dat