CN112284783A - Temperature gradient simulation test device and method for aerospace optical fiber cabin penetrating assembly - Google Patents
Temperature gradient simulation test device and method for aerospace optical fiber cabin penetrating assembly Download PDFInfo
- Publication number
- CN112284783A CN112284783A CN202011124228.3A CN202011124228A CN112284783A CN 112284783 A CN112284783 A CN 112284783A CN 202011124228 A CN202011124228 A CN 202011124228A CN 112284783 A CN112284783 A CN 112284783A
- Authority
- CN
- China
- Prior art keywords
- cabin
- temperature
- simulation
- temperature gradient
- penetrating component
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- 238000004088 simulation Methods 0.000 title claims abstract description 132
- 230000000149 penetrating effect Effects 0.000 title claims abstract description 130
- 238000012360 testing method Methods 0.000 title claims abstract description 117
- 239000013307 optical fiber Substances 0.000 title claims description 30
- 238000000034 method Methods 0.000 title abstract description 15
- 238000010438 heat treatment Methods 0.000 claims abstract description 62
- 239000000835 fiber Substances 0.000 claims abstract description 27
- 230000000694 effects Effects 0.000 claims abstract description 19
- 230000005855 radiation Effects 0.000 claims abstract description 9
- 238000001816 cooling Methods 0.000 claims abstract description 4
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 claims description 24
- 230000035515 penetration Effects 0.000 claims description 16
- 239000007788 liquid Substances 0.000 claims description 12
- 229910052757 nitrogen Inorganic materials 0.000 claims description 12
- 238000010998 test method Methods 0.000 claims description 12
- 229910000838 Al alloy Inorganic materials 0.000 claims description 3
- 239000010453 quartz Substances 0.000 claims description 3
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N silicon dioxide Inorganic materials O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 claims description 3
- 238000012544 monitoring process Methods 0.000 claims description 2
- 238000005057 refrigeration Methods 0.000 claims 1
- 238000011056 performance test Methods 0.000 abstract description 2
- 230000003287 optical effect Effects 0.000 description 9
- 238000009434 installation Methods 0.000 description 6
- 230000008569 process Effects 0.000 description 4
- 230000005540 biological transmission Effects 0.000 description 3
- 230000008859 change Effects 0.000 description 3
- 239000000956 alloy Substances 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 230000007774 longterm Effects 0.000 description 2
- BASFCYQUMIYNBI-UHFFFAOYSA-N platinum Chemical compound [Pt] BASFCYQUMIYNBI-UHFFFAOYSA-N 0.000 description 2
- 230000009466 transformation Effects 0.000 description 2
- 238000010521 absorption reaction Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 238000011156 evaluation Methods 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 238000009863 impact test Methods 0.000 description 1
- 238000003780 insertion Methods 0.000 description 1
- 230000037431 insertion Effects 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
- 239000003973 paint Substances 0.000 description 1
- 229910052697 platinum Inorganic materials 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 238000005507 spraying Methods 0.000 description 1
- 230000001052 transient effect Effects 0.000 description 1
- 238000012795 verification Methods 0.000 description 1
Images
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M99/00—Subject matter not provided for in other groups of this subclass
- G01M99/002—Thermal testing
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E30/00—Energy generation of nuclear origin
- Y02E30/30—Nuclear fission reactors
Landscapes
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
- Testing Resistance To Weather, Investigating Materials By Mechanical Methods (AREA)
Abstract
The invention provides a device and a method for an aerospace fiber cabin penetrating component temperature gradient simulation test, which are used for solving the problem that special controllable equipment for the cabin penetrating 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 simulation cabin board is installed in a thermal vacuum container, the thermal vacuum container is divided into an cabin simulation space and an outdoor simulation space, infrared radiation generated when a heating temperature control module arranged in the cabin simulation space simulates solar irradiation is used for heating a connecting assembly, a vacuum low-temperature module is used for simulating a vacuum cooling background in space, a test interface is arranged in the thermal vacuum container through a component performance test module arranged outside the thermal vacuum container, and the temperature gradient effect of a cabin penetrating component is tested. The simulation method realizes the simulation of the temperature gradient effect of the cabin penetrating component in a wide temperature range, is flexible in configuration, low in realization cost, easy to operate and control and high in reliability of test effect.
Description
Technical Field
The invention belongs to the field of environmental reliability tests of aerospace equipment, and particularly relates to a temperature gradient simulation test device and method for an aerospace optical fiber cabin penetrating assembly.
Background
With the increasing requirement of information transmission and processing rate of the spacecraft, a spacecraft transmission bus is gradually developed from a cable network to an optical cable network, and meanwhile, an optical cable penetrates through an aerospace fiber cabin penetrating assembly arranged on the wall of a spacecraft cabin and extends from the inside of the cabin to the outside of the cabin to transmit and process information outside the cabin. An aerospace optical fiber cabin penetrating component serving as an optical cable channel is an important information channel for communicating the inside and the outside of an aerospace vehicle cabin, wherein one end of the aerospace optical fiber cabin penetrating component is positioned in the aerospace vehicle cabin, and the other end of the aerospace optical fiber cabin penetrating component is positioned outside the aerospace vehicle cabin.
Generally, the temperature environment in the spacecraft cabin is moderate, but the temperature outside the spacecraft cabin is greatly changed under the influence of different irradiation conditions of the sun, and the high-low temperature difference generally exceeds 200 ℃ and even reaches 300 ℃. This can result in high temperature gradients experienced by the bulkhead components attached to the spacecraft bulkhead, which can affect the operational reliability and useful life of the product. For example, for a certain low-orbit spacecraft, the sunny side can reach 150 ℃ at most, the shady side can reach-150 ℃ at least, and the space fiber penetrating component is always in dynamic alternation, so that the space fiber penetrating component is continuously influenced by high and low temperature changes, and the temperature fatigue of the penetrating component can be caused to influence the service life under the long-term operation. Therefore, the aerospace optical fiber cabin penetrating component needs to be subjected to a temperature gradient test at a ground stage, and the stability and reliability of the cabin penetrating component in the rail long-term operation are ensured.
In the prior art, a ground temperature gradient simulation test of an aerospace optical fiber cabin penetrating component is usually performed by adopting a high-low temperature rapid change or temperature impact test method, and a transient temperature gradient is formed in a test piece by utilizing a rapid temperature change process. However, the temperature gradient formed by the above method is not controllable. In addition, for simple parts, when the parts are heated by simulating radiation by adopting methods such as laser and infrared lamp irradiation, although a temperature gradient can be formed by rapidly heating a certain section of the test piece, a cold background cannot be provided, and the low-temperature condition is difficult to check.
Disclosure of Invention
In view of the above defects or shortcomings in the prior art, the invention aims to provide a temperature gradient simulation test device and method for an aerospace fiber cabin penetrating component.
In order to achieve the above purpose, the embodiment of the invention adopts the following technical scheme:
in a first aspect, an embodiment of the present invention provides an aerospace optical fiber cabin penetration assembly temperature gradient simulation test apparatus, including a thermal vacuum container of a thermal vacuum test system, where the temperature gradient simulation test apparatus further includes: the system comprises a vacuum low-temperature module with a refrigerating device and a heat sink, a heating temperature control module, a simulation cabin plate with a cabin penetrating assembly installation interface and an assembly performance test module; wherein,
the simulation cabin plate is arranged in a thermal vacuum container of the thermal vacuum test system, and the thermal vacuum container is divided into an spacecraft in-cabin simulation space and a spacecraft out-cabin simulation space; the cabin penetrating component mounting interface is used for fixedly mounting an aerospace optical fiber cabin penetrating component;
the heating temperature control module is arranged in the simulated space in the cabin and is used for simulating infrared radiation during solar irradiation to heat the connecting assembly;
the refrigerating device of the vacuum low-temperature module is arranged in the whole thermal vacuum container and is used for simulating a vacuum cooling background in space; the heat sink of the vacuum low-temperature module is connected with the refrigerating device, is arranged in the simulation space outside the cabin and is used for simulating a vacuum cold environment in which the aerospace optical fiber cabin penetrating component extends from the inside of the cabin to the outside of the cabin when in orbit;
the component performance testing module is arranged outside the thermal vacuum container, is provided with a testing interface arranged in the thermal vacuum container, and is used for connecting with the cabin penetrating component through the testing interface and testing the temperature gradient effect of the cabin penetrating component.
As a preferred embodiment of the present invention, the thermal vacuum vessel has a mounting platform inside and a flange joint assembly on the side; the heating temperature control module comprises a heating device fixing tool, a temperature sensor, a heating device, a power cable, a test cable, a direct current power supply and a temperature controller;
the simulation deck plate is arranged on the mounting platform;
the heating device fixing tool is arranged on the mounting platform and is positioned on one side of the simulation space in the cabin;
the heating device is arranged on the fixed tool, is connected with one end of the power cable, is parallel to the simulation cabin plate and is opposite to the cabin penetrating assembly mounting interface;
the direct current power supply and the temperature controller are arranged outside the thermal vacuum container;
the power cable penetrates through the flange joint assembly, and the other end of the power cable is connected with the direct-current power supply;
the test cable penetrates through the flange joint assembly, one end of the test cable is connected with a temperature sensor in the hot vacuum container, and the other end of the test cable is connected with a temperature controller outside the hot vacuum container;
the temperature sensor is used for measuring the real-time temperature of the cabin penetrating component in a simulation test;
the temperature controller is used for controlling the heating parameters of the direct current power supply to the heating device according to the real-time temperature of the cabin penetrating component fed back by the temperature sensor.
As a preferred embodiment of the invention, the heating device is an infrared quartz lamp array.
As a preferred embodiment of the present invention, the vacuum low temperature module further comprises a low temperature control center; the low-temperature control center is arranged outside the hot vacuum container, is connected with the refrigerating device and is used for providing refrigerating parameters of a cold background for the refrigerating device.
In a preferred embodiment of the present invention, the refrigerating device is a liquid nitrogen pipeline installed on the upper side of the hot vacuum container near the inner wall.
As a preferred embodiment of the invention, the simulation deck plate is made of aluminum alloy materials.
In a second aspect, an embodiment of the present invention further provides an aerospace fiber penetrating component temperature gradient simulation test method, where the test method is implemented by the aerospace fiber penetrating component temperature gradient simulation test apparatus, and includes the following steps:
step S1, fixedly mounting a cabin penetrating component on the simulation cabin board through a cabin penetrating component mounting interface of the simulation cabin board, wherein one end of the cabin penetrating component faces towards the simulation space in the cabin, and the other end of the cabin penetrating component faces towards the simulation space outside the cabin;
step S2, connecting the test testing module with the cabin penetrating component;
step S3, starting and adjusting the vacuum low-temperature module and the heating temperature control module to enable one end of the cabin penetrating component facing the simulation space outside the cabin to have a temperature gradient with a preset temperature wide range;
and step S4, testing the temperature gradient effect of the cabin penetrating component in a preset temperature wide range in real time through a test testing module.
As a preferred embodiment of the present invention, in step S3, the specific process is as follows:
firstly, constructing a vacuum low-temperature cold background in a hot vacuum container through a vacuum low-temperature module; when the heating temperature control module is not started, the whole cabin penetrating assembly is in a vacuum low-temperature environment, and no temperature gradient exists; after the heating temperature control module is started, the temperature of one end of the simulation space in the cabin of the cabin penetrating assembly is increased, and one 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 penetrating assembly is continuously conducted to one end of the simulation space outside the cabin penetrating assembly to be heated; meanwhile, the low-temperature background of the simulation space outside the cabin continuously absorbs the heat conducted from one end of the simulation space outside the cabin penetrating assembly, and one end of the simulation space outside the cabin penetrating assembly is cooled; finally, the cabin penetrating component reaches dynamic balance to form a stable temperature gradient.
As a preferred embodiment of the present invention, the vacuum low temperature cold background has a vacuum degree better than 1.33X 10-3Pa, and the temperature is lower than 100K.
As a preferred embodiment of the present invention, the step S2 includes:
connecting a temperature measuring device of the heating temperature control module with the cabin penetrating assembly, and monitoring the temperature of the cabin penetrating assembly in real time;
and connecting a temperature gradient effect testing module with the cabin penetrating assembly, and testing the temperature gradient effect of the cabin penetrating assembly in real time.
The invention has the following beneficial effects:
(1) the aerospace optical fiber cabin penetrating component temperature gradient simulation test device is simple in structure, and the simulation of wide temperature range temperature gradient effect is realized through simple transformation on the existing mature thermal vacuum test system.
(2) The temperature gradient simulation test device of the aerospace optical fiber cabin penetrating component can realize flexible adjustment, realizes reliability tests of products of various specifications and models by adjusting the size of the through hole in the simulation cabin plate, and is flexible in configuration and low in realization cost.
(3) The space navigation optical fiber cabin penetrating assembly temperature gradient simulation test method is easy to operate, a vacuum low-temperature system and a heating system of the test device are separately operated, are independent of each other, do not influence each other, are easy to control, and are convenient to maintain and replace; the reliability of the test effect is high, and the stability and the service life of the aerospace optical fiber cabin penetrating component during the on-orbit operation in space are effectively ensured.
Drawings
Other features, objects and advantages of the invention will become more apparent upon reading of the detailed description of non-limiting embodiments made with reference to the following drawings:
FIG. 1 is a schematic structural diagram of an aerospace fiber cabin penetration assembly temperature gradient simulation test device according to an embodiment of the invention;
FIG. 2 is a flowchart of a simulation test method for temperature gradient of an aerospace fiber penetration assembly according to an embodiment of the present invention;
FIG. 3 is a structural diagram of a simulation test device for temperature gradient of an aerospace fiber penetrating component according to a first embodiment of the invention.
Description of reference numerals:
10-a hot vacuum vessel; 11-simulation space in the cabin; 12-extravehicular simulation space; 13-a flange joint assembly; 14-mounting a platform; 20-vacuum low temperature module; 21-liquid nitrogen pipeline; 22-a heat sink; 23-low temperature control center; 30-heating temperature control module; 31-heating device fixing tool; 32-a temperature sensor; 33-a heating device; 34-a power cable; 35-test cables; 36-a direct current power supply; 37-a temperature controller; 40-simulating a deck plate; 41-a cross cabin assembly mounting interface; 50-a component test module; 51-a component test cable; 6-cabin penetrating component.
Detailed Description
The present invention will be described in further detail with reference to the accompanying drawings and examples. It is to be understood that the specific embodiments described herein are merely illustrative of the relevant invention and not restrictive of the invention. It should be noted that, for convenience of description, only the portions related to the present invention are shown in the drawings.
It should be noted that the embodiments and features of the embodiments may be combined with each other without conflict. The present invention will be described in detail below with reference to the embodiments with reference to the attached drawings.
The embodiment of the invention provides a space navigation optical fiber cabin penetrating component temperature gradient simulation test device and a space navigation optical fiber cabin penetrating component temperature gradient simulation test method. The method is simple, easy to operate in engineering, low in cost and applicable to reliability verification and evaluation of the optical fiber cabin penetrating component.
Fig. 1 shows a structure of an aerospace fiber penetration assembly temperature gradient simulation test device provided by an embodiment of the invention. As shown in fig. 1, the aerospace fiber penetrating component temperature gradient simulation test device based on a thermal vacuum test system includes: the system comprises a hot vacuum container 10, a vacuum low temperature module 20 with a refrigerating device 21 and a heat sink 22, a heating temperature control module 30, a simulation cabin plate 40 with a cabin penetrating component mounting interface and a component performance testing module 50.
The simulation cabin plate 40 is additionally arranged in a thermal vacuum container 10 of the thermal vacuum test system, and the thermal vacuum container 10 is divided into a spacecraft cabin internal simulation space 11 and a spacecraft cabin external simulation space 12; the cabin penetrating component mounting interface is used for fixedly mounting an aerospace optical fiber cabin penetrating component; when a simulation test is carried out, an aerospace optical fiber penetration assembly 6 is fixedly mounted at a penetration assembly mounting interface 41 on the simulation cabin board 40, one end of the penetration assembly 6 faces the inside-cabin simulation space 11, and the other end faces the outside-cabin simulation space 12.
The heating temperature control module 30 is arranged in the simulation space 11 in the cabin and used for simulating infrared radiation during solar irradiation to heat the connecting component; the refrigerating device 21 of the vacuum low-temperature module 20 is arranged in the whole thermal vacuum container and is used for simulating a vacuum cooling background in space; the heat sink 22 of the vacuum low-temperature module 20 is connected with the refrigerating device 21 and is arranged in the simulation space outside the cabin, and is used for simulating a vacuum cold environment in which the aerospace optical fiber penetrating component extends from the inside of the cabin to the outside of the cabin when in orbit. The simulation of different ambient temperatures and temperature differences inside and outside the cabin is realized by a vacuum low-temperature module 20 and a heating temperature control module 30 in a hot vacuum container.
The component performance testing module 50 is disposed outside the thermal vacuum container 10 and has a testing interface 51 disposed inside the thermal vacuum container, and is configured to connect with the chamber penetrating component 6 through the testing interface 51 and test a temperature gradient effect of the chamber penetrating component 6.
Fig. 2 shows a simulation test method for the temperature gradient of an aerospace optical fiber penetration assembly, which is implemented based on the simulation test device for the temperature gradient of the aerospace optical fiber penetration assembly according to an embodiment of the present invention. As shown in fig. 2, the aerospace fiber penetrating component temperature gradient simulation test method comprises the following steps:
step S1, fixedly mounting a cabin penetrating component on the simulation cabin board through a cabin penetrating component mounting interface of the simulation cabin board, wherein one end of the cabin penetrating component faces towards the simulation space in the cabin, and the other end of the cabin penetrating component faces towards the simulation space outside the cabin;
step S2, connecting the test testing module with the cabin penetrating component;
step S3, starting and adjusting the vacuum low-temperature module and the heating temperature control module to enable one end of the cabin penetrating component facing the simulation space outside the cabin to have a temperature gradient with a preset temperature wide range; wherein the preset temperature range is-150 to 150 ℃;
and step S4, testing the temperature gradient effect of the cabin penetrating component in a preset temperature wide range in real time through a test testing module, and recording test temperature gradient, temperature gradient alternation and effect results. The temperature gradient effect comprises the change of the insertion loss value with the temperature.
The embodiment of the invention fully utilizes a mature thermal vacuum test system to carry out partial transformation, realizes the simulation of different temperature environments outside the cabin of the aerospace optical fiber cabin penetrating component, and has the advantages of simple method, low cost and good simulation test effect.
The following will describe in detail the aerospace fiber penetrating component temperature gradient simulation test device and method according to the embodiments of the present invention by using specific examples, which are only used to illustrate the technical solutions of the embodiments of the present invention and do not limit the present invention.
Examples
As shown in fig. 3, the aerospace fiber cabin penetration assembly temperature gradient simulation test apparatus according to this embodiment includes: the thermal vacuum test system at least comprises a thermal vacuum container 10, wherein the thermal vacuum container 10 comprises a flange joint assembly 13 and a mounting platform 14; the vacuum low-temperature module 20 comprises a liquid nitrogen pipeline 21, a heat sink 22 and a low-temperature control center 23, a heating temperature control module 30 comprises a heating device fixing tool 31, a temperature sensor 32, a heating device 33, a power supply cable 34, a test cable 35, a direct-current power supply 36 and a temperature controller 37, a simulation cabin plate 40 with a cabin penetrating component mounting interface 41 and a component test module 50.
Wherein the simulation cabin plate 40 is installed on the installation platform 14, and divides the thermal vacuum container 10 into an indoor simulation space 11 and an outdoor simulation space 12; a heating device fixing tool 31 is arranged on an installation platform in the simulation space in the cabin, a heating device 33 is arranged on the fixing tool 31, the heating device 33 penetrates through the flange joint assembly 13 through a power line 34 to be connected with a direct current power supply 36 outside the thermal vacuum container 10, and a temperature sensor 32 penetrates through the flange joint assembly 13 through a test cable 35 to be connected with a temperature controller 37 outside the thermal vacuum container 10; on the installation platform of the outboard simulation space 12, a heat sink 22 is installed; a liquid nitrogen pipeline 21 and a liquid nitrogen pipeline 21 are arranged in the whole space of the thermal vacuum container 10, a liquid nitrogen source communicated with the outside of the thermal vacuum container 10 is arranged, and the on-off and the flow of the liquid nitrogen pipeline are adjusted through a low-temperature control center 23. The component testing module 50 is arranged outside the thermal vacuum container 10, one end of the component testing optical cable 51 is connected with the component testing module 50, the other end of the component testing optical cable passes through the flange joint assembly 13 and is arranged in the thermal vacuum container 10, the other end of the component testing optical cable is a free end in a non-testing state, and the component testing optical cable is connected with the cabin penetrating assembly 6 in a testing state.
Specifically attached, the bottom of the mounting platform 14 is bolted to the bottom of the hot vacuum vessel 10, thereby providing a stable product placement platform. The heating device fixing tool 31 and the simulation cabin plate 40 are both fixed on the upper surface of the product mounting platform 14 through screws. The heating devices 33 are fixed on the tool 31 in parallel through a support, power lines are led out from two ends of each heating device 33, and the power lines are collected and finally connected to two ends of a direct current power supply 36 through the flange joint assembly 13 on the thermal vacuum container 10. The flange joint assembly 13 is provided with not less than four electrical joints and two optical joints.
The embodiment also provides an aerospace fiber cabin penetrating component temperature gradient simulation test, which is realized by adopting the aerospace fiber cabin penetrating component temperature gradient simulation test device of the embodiment, and when the temperature gradient simulation test is carried out, the aerospace fiber cabin penetrating component temperature gradient simulation test device specifically comprises the following steps:
step S1, fixedly installing the cabin penetrating component 6 on the simulation cabin board 40 through a cabin penetrating component installation interface 41 of the simulation cabin board, wherein one end of the cabin penetrating component faces the simulation space 11 in the cabin, and the other end of the cabin penetrating component faces the simulation space 12 outside the cabin;
step S2, connecting the free end of the component test optical cable 51 to the test interface of the cabin penetrating component 6, and simultaneously adhering the temperature sensor 32 to the surface of the cabin penetrating component 6;
step S3, the vacuum low-temperature module 20 and the heating temperature control module 30 are started, and parameters are adjusted to make one end of the cabin penetration assembly 6 facing the simulation space 12 outside the cabin have a temperature gradient within a preset temperature wide range.
Specifically, in the experiment, a vacuum low temperature cold background is first constructed on the inside of the hot vacuum container 10 by the vacuum low temperature module 20. When the heating temperature control module 30 is not started, the whole cabin penetrating assembly 6 is in a vacuum low-temperature environment, and no temperature gradient exists. When the heating temperature control module 30 is turned on, the temperature of one end of the simulation space inside the cabin of the cabin penetration assembly 6 is increased, and the other end of the simulation space outside the cabin is always in a low-temperature environment. Because of the heat conduction characteristic of the cabin penetrating component 6, the heat at one end of the simulation space in the cabin is continuously conducted to one end of the simulation space outside the cabin, but the low-temperature background of the simulation space outside the cabin continuously absorbs the conducted heat, so that one end of the simulation space outside the cabin of the component is cooled, and finally the cabin penetrating component 6 reaches dynamic balance to form a stable temperature gradient. By adjusting the heating temperature control module 30, temperature gradients and temperature gradient alternation in different wide temperature ranges can be realized. In the whole test process, the transmission performance of the cabin penetrating assembly 6 is tested on line through professional equipment such as a plug-in return loss tester, and the product function and performance state are detected in real time.
Preferably, the installation direction of the cabin penetrating component 6 is adjusted, so that the reliability of the cabin penetrating component 6 is comprehensively and effectively checked.
Step S4, the temperature gradient effect of the cabin penetrating component 6 under the temperature gradient within the preset temperature wide range is tested in real time by the test testing module 50.
In this embodiment, the thermal vacuum container 10 provides a closed space with a vacuum degree better than 1.33 × 10-3Pa, the low-temperature cold black environment in the closed space is constructed by a liquid nitrogen pipeline 21 and a heat sink 22. The heat sink 22 adopts a pipeline and web structure to form a closed inner container, and the surface spraying absorption rate is better than 0The black paint of claim 9, mounted on the inner bulkhead surface adjacent to the hot vacuum vessel 10. The inner container pipeline 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 be below 100K, namely a vacuum low-temperature cold black environment is formed in the thermal vacuum container 10, and the space environment is simulated.
The mounting interface 41 on the simulation cabin plate 40 is used for mounting and fixing the cabin penetrating component 6, and a screw fixing mode is adopted. Preferably, the dummy deck 40 is made of an aluminum alloy material.
The heating device 33 is fixed on the mounting platform 14 of the thermal vacuum container 10 through the fixing tool 31, faces towards the inner end of the cabin of the optical fiber cabin penetrating assembly 6, and is used for simulating infrared radiation during solar irradiation 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 is connected to the direct current power supply 36, and the control of the product temperature is finally realized through the control of the current. Preferably, the heating device 33 employs an infrared quartz lamp. By adjusting the input current of the heating device 33 and controlling the infrared radiation power thereof, the radiation heat at the inner end of the cabin penetrating assembly can be adjusted, thereby indirectly controlling the temperature gradients at the inner end and the outer end of the cabin. When the heating device 33 is not electrified, the temperatures of the two ends inside and outside the cabin tend to be consistent, and an alternating temperature gradient can be formed on the optical fiber cabin penetrating component by controlling the power-on and power-off time of the heating device 33.
The temperature sensor 32 is adhered on the surface of the chamber-penetrating component 6 and used for measuring the temperature of the chamber-penetrating component 6, and the lead of the temperature sensor 32 is connected to the outside of the thermal vacuum container 10 through the flange joint component 13 on the thermal vacuum container 10 and connected into the temperature controller 37. Preferably, the temperature sensor 32 is a T-thermocouple or platinum resistor. The temperature controller 37 generates a control signal according to the measurement signal of the temperature sensor 32, and transmits the control signal 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, thereby heating the product in the thermal vacuum container 10. The temperature of the cabin penetrating component 40 measured by the temperature sensor 32 is fed back to the temperature controller 37, the temperature controller 37 outputs a control signal to the direct current power supply 36 through logical operation, the current supplied to the heating device 33 is adjusted, the infrared radiation intensity of the heating device 33 is controlled, the temperature of the inner end of the cabin penetrating component is further controlled, and closed-loop temperature control is achieved.
The foregoing description is only exemplary of the preferred embodiments of the invention and is illustrative of the principles of the technology employed. It will be appreciated by those skilled in the art that the scope of the invention herein disclosed is not limited to the particular combination of features described above, but also encompasses other arrangements formed by any combination of the above features or their equivalents without departing from the spirit of the invention. For example, the above features and (but not limited to) features having similar functions disclosed in the present invention are mutually replaced to form the technical solution.
Claims (10)
1. The utility model provides an aerospace optic fibre cross cabin subassembly temperature gradient analogue test device, includes the hot vacuum vessel of hot vacuum test system, has the vacuum low temperature module of refrigerating plant and heat sink, its characterized in that, temperature gradient analogue test device still includes: the device comprises a heating temperature control module, a simulation cabin plate with a cabin penetrating component mounting interface and a component performance testing module; wherein,
the simulation cabin plate is arranged in a thermal vacuum container of the thermal vacuum test system, and the thermal vacuum container is divided into an spacecraft in-cabin simulation space and a spacecraft out-cabin simulation space; the cabin penetrating component mounting interface is used for fixedly mounting an aerospace optical fiber cabin penetrating component;
the heating temperature control module is arranged in the simulated space in the cabin and is used for simulating infrared radiation during solar irradiation to heat the connecting assembly;
the refrigerating device of the vacuum low-temperature module is arranged in the whole thermal vacuum container and is used for simulating a vacuum cooling background in space; the heat sink of the vacuum low-temperature module is connected with the refrigerating device, is arranged in the simulation space outside the cabin and is used for simulating a vacuum cold environment in which the aerospace optical fiber cabin penetrating component extends from the inside of the cabin to the outside of the cabin when in orbit;
the component performance testing module is arranged outside the thermal vacuum container, is provided with a testing interface arranged in the thermal vacuum container, and is used for connecting with the cabin penetrating component through the testing interface and testing the temperature gradient effect of the cabin penetrating component.
2. The aerospace fiber penetrating component temperature gradient simulation test device of claim 1, wherein the thermal vacuum vessel has a mounting platform inside and a flange joint component on a side; the heating temperature control module comprises a heating device fixing tool, a temperature sensor, a heating device, a power cable, a test cable, a direct current power supply and a temperature controller;
the simulation deck plate is arranged on the mounting platform;
the heating device fixing tool is arranged on the mounting platform and is positioned on one side of the simulation space in the cabin;
the heating device is arranged on the fixed tool, is connected with one end of the power cable, is parallel to the simulation cabin plate and is opposite to the cabin penetrating assembly mounting interface;
the direct current power supply and the temperature controller are arranged outside the thermal vacuum container;
the power cable penetrates through the flange joint assembly, and the other end of the power cable is connected with the direct-current power supply;
the test cable penetrates through the flange joint assembly, one end of the test cable is connected with a temperature sensor in the hot vacuum container, and the other end of the test cable is connected with a temperature controller outside the hot vacuum container;
the temperature sensor is used for measuring the real-time temperature of the cabin penetrating component in a simulation test;
the temperature controller is used for controlling the heating parameters of the direct current power supply to the heating device according to the real-time temperature of the cabin penetrating component fed back by the temperature sensor.
3. The aerospace fiber penetrating component temperature gradient simulation test device of claim 2, wherein the heating device is an infrared quartz lamp array.
4. The aerospace fiber penetrating component temperature gradient simulation test device of any one of claims 1 to 3, wherein the vacuum cryogenic module further comprises a cryogenic control center; the low-temperature control center is arranged outside the hot vacuum container, is connected with the refrigerating device and is used for providing refrigerating parameters of a cold background for the refrigerating device.
5. The aerospace fiber penetrating component temperature gradient simulation test device of claim 4, wherein the refrigeration device is a liquid nitrogen pipeline and is arranged on the upper side of the hot vacuum container close to the inner wall.
6. The aerospace fiber penetrating component temperature gradient simulation test device of claim 4, wherein the simulation deck plate is made of aluminum alloy.
7. An aerospace optical fiber penetration assembly temperature gradient simulation test method, which is characterized in that the test method is realized by the aerospace optical fiber penetration assembly temperature gradient simulation test device of any one of claims 1 to 6, and comprises the following steps:
step S1, fixedly mounting a cabin penetrating component on the simulation cabin board through a cabin penetrating component mounting interface of the simulation cabin board, wherein one end of the cabin penetrating component faces towards the simulation space in the cabin, and the other end of the cabin penetrating component faces towards the simulation space outside the cabin;
step S2, connecting the test testing module with the cabin penetrating component;
step S3, starting and adjusting the vacuum low-temperature module and the heating temperature control module to enable one end of the cabin penetrating component facing the simulation space outside the cabin to have a temperature gradient with a preset temperature wide range;
and step S4, testing the temperature gradient effect of the cabin penetrating component in a preset temperature wide range in real time through a test testing module.
8. The aerospace fiber penetration assembly temperature gradient simulation test method according to claim 7, wherein the step S3 is as follows:
firstly, constructing a vacuum low-temperature cold background in a hot vacuum container through a vacuum low-temperature module; when the heating temperature control module is not started, the whole cabin penetrating assembly is in a vacuum low-temperature environment, and no temperature gradient exists; after the heating temperature control module is started, the temperature of one end of the simulation space in the cabin of the cabin penetrating assembly is increased, and one 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 penetrating assembly is continuously conducted to one end of the simulation space outside the cabin penetrating assembly to be heated; meanwhile, the low-temperature background of the simulation space outside the cabin continuously absorbs the heat conducted from one end of the simulation space outside the cabin penetrating assembly, and one end of the simulation space outside the cabin penetrating assembly is cooled; finally, the cabin penetrating component reaches dynamic balance to form a stable temperature gradient.
9. The aerospace fiber penetrating component temperature gradient simulation test method of claim 8, wherein the vacuum low temperature cold background and vacuum degree are better than 1.33 x 10-3Pa, and the temperature is lower than 100K.
10. The aerospace fiber penetration assembly temperature gradient simulation test method according to claim 7, wherein the step S2 comprises:
connecting a temperature measuring device of the heating temperature control module with the cabin penetrating assembly, and monitoring the temperature of the cabin penetrating assembly in real time;
and connecting a temperature gradient effect testing module with the cabin penetrating assembly, and testing the temperature gradient effect of the cabin penetrating assembly in real time.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011124228.3A CN112284783B (en) | 2020-10-20 | 2020-10-20 | Temperature gradient simulation test device and method for aerospace optical fiber cabin penetrating assembly |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011124228.3A CN112284783B (en) | 2020-10-20 | 2020-10-20 | Temperature gradient simulation test device and method for aerospace optical fiber cabin penetrating assembly |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN112284783A true CN112284783A (en) | 2021-01-29 |
| CN112284783B CN112284783B (en) | 2023-03-14 |
Family
ID=74423392
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011124228.3A Active CN112284783B (en) | 2020-10-20 | 2020-10-20 | Temperature gradient simulation test device and method for aerospace optical fiber cabin penetrating assembly |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN112284783B (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113532855A (en) * | 2021-07-23 | 2021-10-22 | 北京卫星环境工程研究所 | Ground comprehensive test system for verifying joint life of aerospace mechanical arm |
| CN113916403A (en) * | 2021-10-15 | 2022-01-11 | 北京卫星环境工程研究所 | Dual-channel temperature detection device for thermal vacuum test |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101008651A (en) * | 2006-12-08 | 2007-08-01 | 北京航空航天大学 | Test apparatus of large-scaled environment simulation |
| CN106467174A (en) * | 2015-08-10 | 2017-03-01 | 北京卫星环境工程研究所 | Large Spacecraft mechanism normal pressure thermograde pilot system |
| CN108168878A (en) * | 2017-12-15 | 2018-06-15 | 北京卫星环境工程研究所 | Spatial rotational mechanism floor synthetic verification test system based on the moment of reaction |
| CN109799421A (en) * | 2019-03-12 | 2019-05-24 | 北京卫星环境工程研究所 | The combined environment test of aerospace optical connector studies system |
-
2020
- 2020-10-20 CN CN202011124228.3A patent/CN112284783B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101008651A (en) * | 2006-12-08 | 2007-08-01 | 北京航空航天大学 | Test apparatus of large-scaled environment simulation |
| CN106467174A (en) * | 2015-08-10 | 2017-03-01 | 北京卫星环境工程研究所 | Large Spacecraft mechanism normal pressure thermograde pilot system |
| CN108168878A (en) * | 2017-12-15 | 2018-06-15 | 北京卫星环境工程研究所 | Spatial rotational mechanism floor synthetic verification test system based on the moment of reaction |
| CN109799421A (en) * | 2019-03-12 | 2019-05-24 | 北京卫星环境工程研究所 | The combined environment test of aerospace optical connector studies system |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113532855A (en) * | 2021-07-23 | 2021-10-22 | 北京卫星环境工程研究所 | Ground comprehensive test system for verifying joint life of aerospace mechanical arm |
| CN113532855B (en) * | 2021-07-23 | 2024-03-12 | 北京卫星环境工程研究所 | Ground comprehensive test system for verifying joint life of aerospace mechanical arm |
| CN113916403A (en) * | 2021-10-15 | 2022-01-11 | 北京卫星环境工程研究所 | Dual-channel temperature detection device for thermal vacuum test |
Also Published As
| Publication number | Publication date |
|---|---|
| CN112284783B (en) | 2023-03-14 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN112284783B (en) | Temperature gradient simulation test device and method for aerospace optical fiber cabin penetrating assembly | |
| US20100046575A1 (en) | Flexible Thermal Cycle Test Equipment for Concentrator Solar Cells | |
| CN109799421B (en) | Comprehensive environment experiment research system of aerospace optical cable connector | |
| CN106467174B (en) | Large Spacecraft mechanism normal pressure temperature gradient pilot system | |
| US7129732B1 (en) | Substrate test apparatus and method of testing substrates | |
| CN106950249B (en) | The analysis experimental provision of rock thermal conductivity is tested under a kind of simulation different pressures | |
| CN109932599A (en) | A kind of quiet dynamic driving characteristic integrated tester of automatically controlled shape-memory alloy wire | |
| CN111405687B (en) | Temperature control device and method for optical window of space environment simulator | |
| KR20150069138A (en) | Life test apparatus for optical communication module | |
| CN104596781B (en) | A kind of flame heating hot noise compound environmental tester | |
| CN112706943A (en) | Aircraft internal and external heat source coupling test device and test method | |
| CN104215659A (en) | Infrared lamp single-lamp radiation characteristic test system under vacuum thermal environment | |
| CN219224426U (en) | Mechanical load testing device for photovoltaic module | |
| CN112710699A (en) | Test system and method for simulating thermal deformation of composite material rod piece in space environment | |
| CN112051032B (en) | Infrared lamp array heat flow calibration method and device in satellite heat balance test | |
| CN218330495U (en) | Whole oil tank vibration test device | |
| CN116952715A (en) | Stratospheric airship capsule material testing system and testing method | |
| CN112340070A (en) | Design method of ground test system of high-stability temperature measurement and control system | |
| Konrath | Flow field measurements by PIV at high Reynolds numbers | |
| KR100907926B1 (en) | Satellite surface contamination measuring device | |
| CN111323052A (en) | Navigation sensor heat balance test device used in complex thermal environment | |
| Davis et al. | James Webb Space Telescope Thermal Pathfinder Test Results | |
| CN110466810A (en) | The space-environment simulator and its installation method of a kind of roll type boom mechanism | |
| CN112113688A (en) | Portable temperature controller unit calibration equipment | |
| CN220270982U (en) | Constant temperature test box device for loosening performance of steel strand |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |