CN112284783A - Temperature gradient simulation test device and method for aerospace optical fiber cabin penetrating assembly - Google Patents

Abstract

The invention provides a temperature gradient simulation test device and method for an aerospace optical fiber penetrating component, which is used to solve the problem that controllable special equipment for penetrating the cabin component temperature gradient simulation test cannot be provided in the prior art. The temperature gradient simulation test device is based on a thermal vacuum test system. A simulated cabin is installed in the thermal vacuum container, and the thermal vacuum container is divided into a simulated space inside the cabin and a simulated space outside the cabin. The temperature control module simulates the infrared radiation when the sun is irradiated to heat the connected components, and the vacuum low temperature module simulates the vacuum cold background in space. Effects of temperature gradients on cabin components. The invention realizes the simulation of the temperature gradient effect of the piercing component in a wide temperature range, has flexible configuration, low realization cost, easy operation and control of the method, and high reliability of the test effect.

Description

Temperature gradient simulation test device and method for aerospace optical fiber penetrating module

technical field

The invention belongs to the field of aerospace equipment environmental reliability test, and in particular relates to a temperature gradient simulation test device and method for an aerospace optical fiber penetrating component.

Background technique

With the continuous improvement of spacecraft information transmission and processing rate requirements, the spacecraft transmission bus gradually develops from a cable network to an optical cable network. Extravehicular, where information is transmitted and processed outside the cabin. As an optical cable channel, the aerospace fiber optic penetrating module has one end in the spacecraft cabin and one end outside the cabin. It is an important information channel connecting the inside and outside of the spacecraft cabin, and needs to withstand the influence of the environment inside and outside the cabin at the same time.

Usually, the temperature environment in the spacecraft cabin is relatively moderate, but the outside of the cabin is affected by different sun irradiation conditions, and there will be great changes. This will cause the penetrating components fixed on the spacecraft bulkhead to bear a high temperature gradient, which will affect the working reliability and service life of the product. For example, for a low-orbit spacecraft, the highest temperature on the sunny side will reach 150°C, and when it is on the shady side, the lowest temperature will reach -150°C, and it is always in dynamic alternation, which in turn causes the aerospace fiber optic penetrating components to be constantly affected by high and low temperature changes. Under long-term operation, the temperature fatigue of the cabin components will affect the service life. Therefore, it is necessary to conduct a temperature gradient test on the aerospace optical fiber penetrating module in the ground stage to ensure the stability and reliability of the penetrating module during long-term operation in orbit.

In the prior art, the ground temperature gradient simulation test of the aerospace optical fiber penetrating component is usually carried out by the high and low temperature rapid change or temperature shock test method, and the transient temperature gradient is formed in the test piece by using the rapid temperature change process. However, the temperature gradient formed by the above method is not controllable. In addition, for simple parts, when using laser, infrared lamp irradiation and other methods to simulate radiation for heating, although rapid heating of a certain section of the test piece can form a temperature gradient, it cannot provide a cold background, and it is difficult to assess low temperature conditions.

SUMMARY OF THE INVENTION

In view of the above-mentioned defects or deficiencies in the prior art, the present invention aims to provide a temperature gradient simulation test device and method for an aerospace optical fiber penetrating module. To realize the temperature gradient simulation test of the penetration module on the ground, the test device has a simple structure, is easy to operate, and has a reliable simulation effect.

In order to achieve the above purpose, the embodiment of the present invention adopts the following technical solutions:

In a first aspect, an embodiment of the present invention provides a temperature gradient simulation test device for an aerospace optical fiber penetrating module, including a thermal vacuum container of a thermal vacuum test system, and the temperature gradient simulation test device further includes: a cooling device and a heat sink. Vacuum low temperature module, heating temperature control module, simulated cabin board with installation interface of cabin component and component performance test module; wherein,

The simulation cabin is installed in the thermal vacuum container of the thermal vacuum test system, and the thermal vacuum container is divided into a simulation space inside the spacecraft cabin and a simulation space outside the spacecraft cabin; the installation interface of the cabin component is used for fixed installation Aerospace fiber optic penetration module;

The heating temperature control module is arranged in the simulation space in the cabin, and is used to simulate the infrared radiation when the sun is irradiated to heat the connection components;

The refrigeration device of the vacuum and cryogenic module is arranged in the entire thermal vacuum container to simulate the vacuum cold background in space; the heat sink of the vacuum and cryogenic module is connected to the refrigeration device and is arranged in the simulation space outside the cabin , which is used to simulate the cold vacuum environment in which the aerospace fiber optic penetrating module extends from the cabin to the outside of the cabin when it is in orbit;

The component performance testing module is disposed outside the thermal vacuum container and has a test interface disposed in the thermal vacuum container, and is used for connecting with the cabin penetrating assembly through the test interface and testing the temperature gradient effect of the cabin penetrating assembly.

As a preferred embodiment of the present invention, the thermal vacuum container has a mounting platform inside and a flange joint assembly on the side; the heating temperature control module includes a heating device fixing tool, a temperature sensor, a heating device, a power cable, Test cables, DC power supplies and temperature controllers;

the simulation deck is mounted on the mounting platform;

The heating device fixing tool is installed on the installation platform and is located on one side of the simulation space in the cabin;

The heating device is installed on the fixing tool, and is connected with one end of the power cable, parallel to the simulation cabin plate and facing the installation interface of the cabin assembly;

The DC power supply and the temperature controller are arranged outside the thermal vacuum container;

The power cable passes through the flange joint assembly, and the other end is connected to the DC power supply;

The test cable runs through the flange joint assembly, one end is connected with the temperature sensor in the thermal vacuum container, and the other end is connected with the temperature controller outside the thermal vacuum container;

The temperature sensor is used to measure the real-time temperature of the penetration component in the simulation test;

The temperature controller is used for controlling the heating parameters of the heating device by the DC power supply according to the real-time temperature of the piercing assembly fed back by the temperature sensor.

As a preferred embodiment of the present invention, the heating device is an infrared quartz lamp array.

As a preferred embodiment of the present invention, the vacuum cryogenic module further includes a cryogenic control center; the cryogenic control center is arranged outside the thermal vacuum container and connected to the refrigeration device, and is used for the refrigeration device to provide a cold background. cooling parameters.

As a preferred embodiment of the present invention, the refrigeration device is a liquid nitrogen pipeline, which is installed on the upper side of the thermal vacuum container close to the inner wall.

As a preferred embodiment of the present invention, the simulation cabin is made of aluminum alloy material.

In the second aspect, the embodiment of the present invention also provides a temperature gradient simulation test method for an aerospace optical fiber penetrating assembly, and the test method is realized by the above-mentioned temperature gradient simulation test device for an aerospace optical fiber penetrating assembly, including the following steps:

In step S1, the piercing component is fixedly installed on the simulated deck through the piercing component installation interface of the simulated deck, and one end faces the simulated space in the cabin, and the other end faces the simulated space outside the cabin;

Step S2, connecting the test module and the cabin passage assembly;

Step S3, start and adjust the vacuum low temperature module and the heating temperature control module, so that the end of the cabin passage assembly facing the simulation space outside the cabin has a temperature gradient with a preset temperature range;

In step S4, the temperature gradient effect under the temperature gradient within the preset temperature width range is tested in real time by the test test module.

As a preferred embodiment of the present invention, the step S3, the specific process is as follows:

First, the vacuum low temperature cold background is constructed inside the thermal vacuum container through the vacuum low temperature module; when the heating temperature control module is not turned on, the whole cabin passage assembly is in a vacuum low temperature environment, and there is no temperature gradient; when the heating temperature control module is turned on, the cabin passage The temperature of one end of the simulation space in the cabin of the module increases, while the end of the simulation space outside the cabin is still in a low temperature environment; the heat at one end of the simulation space of the penetrating module is continuously conducted to the end of the simulation space outside the cabin of the penetrating module; The low temperature background of the space continuously absorbs the heat conducted from one end of the simulation space outside the cabin, and the end of the simulation space outside the cabin cools down; finally, the cabin achieves a dynamic balance and forms a stable temperature gradient.

As a preferred embodiment of the present invention, the vacuum low temperature cooling background, the vacuum degree is better than 1.33× ^10-3 Pa, and the temperature is lower than 100K.

As a preferred embodiment of the present invention, the step S2 includes:

Connect the temperature measuring device of the heating temperature control module to the cabin passage assembly, and monitor the temperature of the cabin passage assembly in real time;

The temperature gradient effect test module is connected to the cabin penetration assembly, and the temperature gradient effect of the cabin penetration assembly is tested in real time.

The present invention has the following beneficial effects:

(1) The temperature gradient simulation test device of the aerospace optical fiber penetrating module has a simple structure, and the simulation of the temperature gradient effect in a wide temperature range can be realized by simple modification on the existing mature thermal vacuum test system.

(2) The temperature gradient simulation test device of the aerospace optical fiber penetrating module can realize flexible adjustment. By adjusting the size of the through hole on the simulation cabin, the reliability test of various specifications and models can be realized, and the configuration is flexible and the realization cost is low. .

(3) The temperature gradient simulation test method of the aerospace optical fiber penetrating module is easy to operate. The vacuum and low temperature system and the heating system of the test device are operated separately, independent of each other, not affecting each other, easy to control, and convenient for maintenance and replacement; the test effect is reliable High, effectively ensure the stability and service life of the aerospace fiber optic penetrating module when it runs in orbit in space.

Description of drawings

Other features, objects and advantages of the present invention will become more apparent by reading the detailed description of non-limiting embodiments made with reference to the following drawings:

1 is a schematic structural diagram of a temperature gradient simulation test device for an aerospace optical fiber penetrating module provided by an embodiment of the present invention;

2 is a flowchart of a method for simulating a temperature gradient of an aerospace optical fiber penetrating module provided by an embodiment of the present invention;

FIG. 3 is a structural diagram of a temperature gradient simulation test device for an aerospace optical fiber penetrating module in the first embodiment of the present invention.

Description of reference numbers:

10- Thermal vacuum vessel; 11- Simulation space inside the cabin; 12- Simulation space outside the cabin; 13- Flange joint assembly; 14- Installation platform; 20- Vacuum cryogenic module; 21- Liquid nitrogen pipeline; 22- Heat sink; 23-low temperature control center; 30-heating temperature control module; 31-heating device fixing tool; 32-temperature sensor; 33-heating device; 34-power cable; 35-test cable; 36-DC power supply; 37-temperature control instrument; 40-simulation cabin; 41-installation interface of cabin components; 50-component test module; 51-component test cable; 6-passage components.

Detailed ways

The present invention will be further described in detail below in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain the related invention, but not to limit the invention. In addition, it should be noted that, for the convenience of description, only the parts related to the invention are shown in the drawings.

It should be noted that the embodiments of the present invention and the features of the embodiments may be combined with each other under the condition of no conflict. The present invention will be described in detail below with reference to the accompanying drawings and in conjunction with the embodiments.

Embodiments of the present invention provide a temperature gradient simulation test device and method for an aerospace optical fiber penetrating module. The test device is based on a thermal vacuum test system, and a simulated cabin plate is installed in a thermal vacuum container. When implementing the method, by adjusting the infrared The heating power can be used to simulate the effect of temperature gradients in different wide temperature ranges, so as to verify the reliability of the penetrating components connected to the interior and exterior environments of the spacecraft to withstand temperature gradients and temperature alternating environments. The method of the invention is simple, easy to operate in engineering, and the device is low in cost, and can be applied to the reliability verification and evaluation of optical fiber penetrating components.

FIG. 1 shows the structure of a temperature gradient simulation test device for an aerospace optical fiber penetrating module provided by an embodiment of the present invention. As shown in FIG. 1 , the temperature gradient simulation test device of the aerospace optical fiber penetrating module is based on a thermal vacuum test system, including: a thermal vacuum container 10 , a vacuum low temperature module 20 with a refrigeration device 21 and a heat sink 22 , and a heating temperature control module 30. A simulated cabin panel 40 and a component performance test module 50 having an installation interface of a cabin penetration assembly.

Wherein, the simulated cabin board 40 is installed in the thermal vacuum container 10 of the thermal vacuum test system, and the thermal vacuum container 10 is divided into a simulated space 11 inside the spacecraft cabin and a simulated space 12 outside the spacecraft cabin; The cabin assembly installation interface is used for fixed installation of the aerospace optical fiber cabin assembly; when the simulation test is performed, the aerospace optical fiber cabin assembly 6 is fixedly installed at the cabin assembly installation interface 41 on the simulated cabin board 40, and one end of the cabin assembly 6 faces The simulation space 11 in the cabin, and the other end faces the simulation space 12 outside the cabin.

The heating and temperature control module 30 is arranged in the simulation space 11 in the cabin, and is used to simulate the infrared radiation when the sun is irradiated to heat the connecting components; the refrigeration device 21 of the vacuum and low temperature module 20 is arranged in the entire thermal vacuum container , used to simulate the vacuum cold background in space; the heat sink 22 of the vacuum low temperature module 20 is connected to the refrigeration device 21 and is arranged in the simulation space outside the cabin, for simulating the aerospace fiber optic penetrating module from the orbit when the module is in orbit The vacuum cold environment in which the cabin extends to the outside. The simulation of different ambient temperature and temperature difference inside and outside the cabin is realized by the vacuum cryogenic module 20 and the heating temperature control module 30 in the thermal vacuum container.

The component performance test module 50 is disposed outside the thermal vacuum container 10 and has a test interface 51 disposed in the thermal vacuum container, for connecting with the cabin penetration assembly 6 through the test interface 51 and testing the cabin penetration assembly 6 The temperature gradient effect.

FIG. 2 shows a temperature gradient simulation test method for an aerospace optical fiber penetrating assembly provided by an embodiment of the present invention, and the test method is implemented based on the above-mentioned temperature gradient simulation test device for an aerospace optical fiber penetrating assembly. As shown in Figure 2, the temperature gradient simulation test method of the aerospace optical fiber penetrating module includes the following steps:

In step S1, the piercing component is fixedly installed on the simulated deck through the piercing component installation interface of the simulated deck, and one end faces the simulated space in the cabin, and the other end faces the simulated space outside the cabin;

Step S2, connecting the test module and the cabin passage assembly;

Step S3, start and adjust the vacuum low temperature module and the heating temperature control module, so that the end of the piercing assembly facing the simulation space outside the cabin has a temperature gradient with a preset temperature width range; wherein, the preset temperature width range is -150-150 °C;

In step S4, the temperature gradient effect of the piercing component under the temperature gradient within the preset temperature width range is tested in real time by the test test module, and the test temperature gradient, temperature gradient alternation and effect results are recorded. The temperature gradient effect includes the change of insertion loss value with temperature.

The embodiments of the present invention make full use of the mature thermal vacuum test system for partial transformation, and realize the simulation of different temperature environments inside and outside the cabin of the aerospace optical fiber penetrating component. The method is simple, the cost is low, and the simulation test effect is good.

The following will describe in detail the temperature gradient simulation test device and method of the aerospace optical fiber penetrating module according to the embodiments of the present invention through specific examples. The following examples are only used to illustrate the technical solutions of the embodiments of the present invention, and do not constitute a limitation of the present invention. .

Example

As shown in FIG. 3 , the temperature gradient simulation test device for the aerospace optical fiber penetrating module in this embodiment includes: a thermal vacuum test system including at least a thermal vacuum container 10 , and the thermal vacuum container 10 includes a flange joint assembly 13 , an installation Platform 14; vacuum low temperature module 20 composed of liquid nitrogen pipeline 21, heat sink 22, low temperature control center 23, heating device fixing tool 31, temperature sensor 32, heating device 33, power cable 34, test cable 35, A heating temperature control module 30 composed of a DC power supply 36 and a temperature controller 37 , a simulated cabin board 40 having an installation interface 41 for passing through the cabin components, and a component testing module 50 .

Wherein, the simulation cabin plate 40 is installed on the installation platform 14, and the thermal vacuum container 10 is divided into a cabin simulation space 11 and an outer cabin simulation space 12; on the installation platform in the cabin simulation space, a heating device is installed Fix the tool 31, install the heating device 33 on the fixing tool 31, the heating device 33 is connected to the DC power supply 36 outside the thermal vacuum container 10 through the power cord 34 through the flange joint assembly 13, and the temperature sensor 32 is connected through the test cable 35 Connect to the temperature controller 37 outside the thermal vacuum container 10 through the flange joint assembly 13; install the heat sink 22 on the installation platform of the simulation space 12 outside the cabin; install the liquid nitrogen pipeline in the entire space of the thermal vacuum container 10 21. The liquid nitrogen pipeline 21 is connected to the liquid nitrogen source outside the thermal vacuum container 10, and the on-off and flow rate of the liquid nitrogen pipeline is adjusted through the low temperature control center 23. The component test module 50 is arranged outside the thermal vacuum container 10, one end of the component test optical cable 51 is connected to the component test module 50, and the other end is set in the thermal vacuum container 10 through the flange joint assembly 13, and is free in the non-test state end, which is connected to the piercing assembly 6 in the test state.

During the specific connection, the bottom of the installation platform 14 is fixed on the lower bottom surface of the thermal vacuum container 10 by screws, thereby providing a stable product placement platform. Both the heating device fixing tool 31 and the simulation deck 40 are fixed on the upper surface of the product installation platform 14 by screws. The heating devices 33 are fixed on the tooling 31 in parallel by the brackets, and power lines are drawn from both ends of each heating device 33, and are finally connected to both ends of the DC power supply 36 through the flange joint assembly 13 on the thermal vacuum container 10 after collection. The flange connector assembly 13 is provided with no less than four electrical connectors and two optical connectors.

This embodiment also provides a temperature gradient simulation test of an aerospace optical fiber penetrating assembly, which is implemented by using the temperature gradient simulation test device for an aerospace optical fiber penetrating assembly in this embodiment. When the temperature gradient simulation test is performed, the following steps are specifically included:

Step S1, the cabin piercing assembly 6 is fixedly installed on the simulation cabin plate 40 through the cabin piercing assembly installation interface 41 of the simulation cabin plate, and one end faces the simulation space 11 in the cabin, and the other end faces the simulation space 12 outside the cabin;

In step S2, the free end of the component test optical cable 51 is connected to the test interface of the cabin-passing assembly 6, and the temperature sensor 32 is pasted on the surface of the cabin-passing assembly 6 simultaneously;

In step S3, the vacuum low temperature module 20 and the heating temperature control module 30 are activated, and the parameters are adjusted so that the end of the cabin piercing assembly 6 facing the simulation space 12 outside the cabin has a temperature gradient with a preset temperature range.

Specifically, during the test, a vacuum cryogenic background is first constructed for the interior of the thermal vacuum vessel 10 through the vacuum cryogenic module 20 . When the heating and temperature control module 30 is not turned on, the entire cabin assembly 6 is in a vacuum and low temperature environment, and there is no temperature gradient. When the heating temperature control module 30 is turned on, the temperature of one end of the simulated space inside the cabin of the piercing component 6 will increase, while the end of the simulated space outside the cabin will always be in a low temperature environment. Due to the heat conduction characteristics of the cabin-passing component 6 itself, the heat from one end of the simulated space inside the cabin will be continuously conducted to one end of the simulated space outside the cabin. One end of the space cools down, and finally the piercing component 6 reaches a dynamic balance, forming a stable temperature gradient. By adjusting the heating temperature control module 30 , temperature gradients in different wide temperature ranges and alternating temperature gradients can be realized. During the whole test process, the transmission performance of the penetrating module 6 is tested online by professional equipment such as insertion and return loss tester, and the function and performance status of the product are detected in real time.

Preferably, the installation direction of the cabin penetration assembly 6 is adjusted, so as to realize a comprehensive and effective assessment of the reliability of the cabin penetration assembly 6 .

In step S4 , the temperature gradient effect under the temperature gradient within the preset temperature width range is tested in real time by the test test module 50 .

In this embodiment, the thermal vacuum container 10 provides a closed space, and the vacuum degree is better than 1.33×10 ⁻³ Pa. The low temperature, cold and black environment in the closed space is created by the liquid nitrogen pipeline 21 and the heat sink 22 . The heat sink 22 adopts a pipeline + web structure to form a closed inner tank, the surface is sprayed with black paint with an absorption rate better than 0.9, and is installed on the surface of the inner bulkhead close to the thermal vacuum container 10 . The inner tube of the heat sink 22 is communicated with the liquid nitrogen pipeline 21. When liquid nitrogen flows in the heat sink 22 through the liquid nitrogen pipeline 21, the surface temperature of the heat sink 22 can be reduced to below 100K, that is, in the thermal vacuum container 10 A vacuum, low temperature, cold and dark environment is formed inside, simulating the space environment.

The installation interface 41 on the simulated cabin board 40 is used to install and fix the cabin penetration assembly 6, and is fixed by screws. Preferably, the simulation deck 40 is made of an aluminum alloy material.

The heating device 33 is fixed on the installation platform 14 of the thermal vacuum container 10 by the fixing tool 31 and faces the in-cabin end of the optical fiber penetrating assembly 6, and is used to simulate the infrared radiation when the sun is irradiated to heat the connecting assembly. The power line 34 of the heating device 33 is connected to the outside of the thermal vacuum container 10 through the flange joint assembly 13 on the thermal vacuum container 10, and connected to the DC power supply 36, and the product temperature is finally controlled by controlling the current. Preferably, the heating device 33 adopts an infrared quartz lamp. By adjusting the input current of the heating device 33 and controlling its infrared radiation power, the radiant heat at the inner end of the cabin penetration assembly can be adjusted, thereby indirectly controlling the temperature gradient at the inner and outer ends of the cabin. When the heating device 33 is not energized, the temperature at both ends of the cabin and outside the cabin will tend to be the same. By controlling the on-off time of the heating device 33, an alternating temperature gradient can be formed on the optical fiber through the cabin assembly.

The temperature sensor 32 is adhered to the surface of the cabin passage assembly 6 for measuring the temperature of the cabin passage assembly 6. The lead wire of the temperature sensor 32 is connected to the outside of the thermal vacuum container 10 through the flange joint assembly 13 on the thermal vacuum container 10, and is connected to the outside of the thermal vacuum container 10. Enter the thermostat 37. Preferably, the temperature sensor 32 is a T-type thermocouple or platinum resistance. The temperature controller 37 generates a control signal according to the measurement signal of the temperature sensor 32, and transmits it to the DC power supply 36, so that the DC power supply 36 generates a predetermined current and voltage output, and the heating device 33 is energized, so that the heating device 33 is energized. To achieve heating of the product. The temperature of the piercing assembly 40 measured by the temperature sensor 32 is fed back to the temperature controller 37, and the temperature controller 37 outputs a control signal to the DC power supply 36 through logical operations, adjusts the current supplied to the heating device 33, and controls the heating device 33. Infrared radiation intensity, and then control the temperature of the inner end of the penetrating module, to achieve closed-loop temperature control.

The above description is only a preferred embodiment of the present invention and an illustration of the applied technical principles. Those skilled in the art should understand that the scope of the invention involved in the present invention is not limited to the technical solution formed by the specific combination of the above-mentioned technical features, and should also cover the above-mentioned technical features without departing from the inventive concept. Other technical solutions formed by any combination of its equivalent features. For example, a technical solution is formed by replacing the above features with the technical features disclosed in the present invention (but not limited to) having similar functions.

Claims (10)

1. A temperature gradient simulation test device for an aerospace fiber penetrating cabin assembly, comprising a thermal vacuum container of a thermal vacuum test system, a vacuum low-temperature module with a refrigeration device and a heat sink, it is characterized in that, the temperature gradient simulation test device also includes: A heating temperature control module, a simulated cabin board with an installation interface for the cabin penetration module, and a module performance test module; wherein, The simulation cabin is installed in the thermal vacuum container of the thermal vacuum test system, and the thermal vacuum container is divided into a simulation space inside the spacecraft cabin and a simulation space outside the spacecraft cabin; the installation interface of the cabin component is used for fixed installation Aerospace fiber optic penetration module; The heating temperature control module is arranged in the simulation space in the cabin, and is used to simulate the infrared radiation when the sun is irradiated to heat the connection components; The refrigeration device of the vacuum and cryogenic module is arranged in the entire thermal vacuum container to simulate the vacuum cold background in space; the heat sink of the vacuum and cryogenic module is connected to the refrigeration device and is arranged in the simulation space outside the cabin , which is used to simulate the cold vacuum environment in which the aerospace fiber optic penetrating module extends from the cabin to the outside of the cabin when it is in orbit; The component performance testing module is disposed outside the thermal vacuum container and has a test interface disposed in the thermal vacuum container, and is used for connecting with the cabin passage assembly through the test interface and testing the temperature gradient effect of the cabin passage assembly. 2. The temperature gradient simulation test device of the aerospace optical fiber penetration module according to claim 1, wherein the thermal vacuum container has an installation platform inside, and a flange joint assembly on the side; the heating temperature control module comprises a heating Device fixtures, temperature sensors, heating devices, power cables, test cables, DC power supplies and temperature controllers; the simulation deck is mounted on the mounting platform; The heating device fixing tool is installed on the installation platform and is located on one side of the simulation space in the cabin; The heating device is installed on the fixing tool, and is connected to one end of the power cable, parallel to the simulation cabin plate and facing the installation interface of the cabin assembly; The DC power supply and the temperature controller are arranged outside the thermal vacuum container; The power cable passes through the flange joint assembly, and the other end is connected to the DC power supply; The test cable runs through the flange joint assembly, one end is connected with the temperature sensor in the thermal vacuum container, and the other end is connected with the temperature controller outside the thermal vacuum container; The temperature sensor is used to measure the real-time temperature of the penetration component in the simulation test; The temperature controller is used for controlling the heating parameters of the heating device by the DC power supply according to the real-time temperature of the piercing assembly fed back by the temperature sensor. 3 . The temperature gradient simulation test device of the aerospace optical fiber penetrating module according to claim 2 , wherein the heating device is an infrared quartz lamp array. 4 . 4. The temperature gradient simulation test device of the aerospace optical fiber penetrating module according to any one of claims 1 to 3, wherein the vacuum low temperature module further comprises a low temperature control center; Outside the vacuum container, it is connected to the refrigeration device, and is used for the refrigeration device to provide refrigeration parameters of a cold background. 5 . The temperature gradient simulation test device of the aerospace optical fiber penetration module according to claim 4 , wherein the refrigeration device is a liquid nitrogen pipeline, which is installed on the upper side of the thermal vacuum container close to the inner wall. 6 . 6 . The temperature gradient simulation test device of the aerospace optical fiber through cabin assembly according to claim 4 , wherein the simulation cabin plate is made of an aluminum alloy material. 7 . 7. A temperature gradient simulation test method for an aerospace optical fiber penetrating module, wherein the test method is realized by the temperature gradient simulation test device for an aerospace optical fiber penetrating module according to any one of claims 1 to 6, comprising the steps of : In step S1, the piercing component is fixedly installed on the simulated deck through the piercing component installation interface of the simulated deck, and one end faces the simulated space in the cabin, and the other end faces the simulated space outside the cabin; Step S2, connecting the test test module and the cabin passage assembly; Step S3, start and adjust the vacuum low temperature module and the heating temperature control module, so that the end of the cabin passage assembly facing the simulation space outside the cabin has a temperature gradient with a preset temperature range; In step S4, the temperature gradient effect under the temperature gradient within the preset temperature width range is tested in real time by the test test module. 8. The temperature gradient simulation test method of the aerospace optical fiber penetrating module according to claim 7, is characterized in that, described step S3, concrete process is as follows: First, the vacuum low temperature cold background is constructed inside the thermal vacuum container through the vacuum low temperature module; when the heating temperature control module is not turned on, the whole cabin passage assembly is in a vacuum low temperature environment, and there is no temperature gradient; when the heating temperature control module is turned on, the cabin passage The temperature of one end of the simulation space in the cabin of the module increases, while the end of the simulation space outside the cabin is still in a low temperature environment; the heat at one end of the simulation space in the cabin of the penetrating module is continuously conducted to the end of the simulation space outside the cabin of the penetrating module. The low temperature background of the space continuously absorbs the heat conducted from one end of the simulated space outside the cabin, and the end of the simulated space outside the cabin cools down; finally, the cabin achieves a dynamic balance and forms a stable temperature gradient. 9 . The method for simulating temperature gradients of aerospace optical fiber penetrating components according to claim 8 , wherein, in the low temperature and cold background of vacuum, the degree of vacuum is better than 1.33×10 ⁻³ Pa, and the temperature is lower than 100K. 10 . 10. The method for simulating the temperature gradient of the aerospace optical fiber penetrating module according to claim 7, wherein, in the step S2, comprising: Connect the temperature measuring device of the heating temperature control module to the cabin passage assembly, and monitor the temperature of the cabin passage assembly in real time; The temperature gradient effect test module is connected to the cabin penetration assembly, and the temperature gradient effect of the cabin penetration assembly is tested in real time.

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