Thermal intensity testing device for spaceflight pipeline

Abstract

The invention relates to the technical field of pipeline heat intensity testing, in particular to a spaceflight pipeline heat intensity testing device which comprises a spaceflight pipeline, a cold bath tank, a heat load applying device and a data acquisition module. One end of the spaceflight pipeline is fixed to the fixed end mounting base, the other end of the spaceflight pipeline is fixed to the movable end mounting base, and the movable end mounting base is used for fixing the end of the spaceflight pipeline and moving in the length direction of the spaceflight pipeline; cooling liquid is contained in the cold bath tank, the fixed end installation base and the movable end installation base are both arranged in the cold bath tank, and the cold bath tank is connected with the medium circulation cooling device. The thermal load applying device is located above the spaceflight pipeline and used for applying thermal load to the spaceflight pipeline. The temperature, displacement and strain of the spaceflight pipeline can be monitored, the thermal strength performance of the spaceflight pipeline under deformation in the length direction can be tested, meanwhile, the adapter mounting seats at the two ends of the pipeline are cooled in a cold bath supply mode, and normal operation of the test process is guaranteed.

Description

Technical Field

[0001] The present invention relates to the technical field of pipeline thermal strength testing, and in particular to a thermal strength testing device for aerospace pipelines. Background Art

[0002] Thermal strength test is an important part of structural test, which is mainly used to evaluate the mechanical properties and anti-destruction ability of aircraft structures or components in thermal environment. In the thermal strength test of aerospace pipeline, one end of the aerospace pipeline is stretched to a preset length (i.e. deformation displacement length) along the direction of the straight line connecting the center points of the mounting seats at both ends of the aerospace pipeline in a preset high temperature environment, and then the thermal stress (i.e. thermal installation stress) generated by the aerospace pipeline is measured. At present, during the thermal strength test of aerospace pipeline, the mounting seats at both ends of the aerospace pipeline are easily affected by high temperature, and usually spraying is used for cooling, which has limited cooling effect. Summary of the Invention

[0003] In view of the above problems, the purpose of the present invention is to provide a thermal strength test device for aerospace pipelines. The present invention adopts the following technical solutions:

[0004] The present invention provides a thermal strength test device for aerospace pipelines, comprising:

[0005] An aerospace pipeline, one end of which is fixed to a fixed end mounting seat, which is used to fix and limit one end of the aerospace pipeline, and the other end of which is fixed to a movable end mounting seat, which is used to fix the end of the aerospace pipeline and move it along its length direction;

[0006] A cold bath tank containing a coolant, wherein the fixed end mounting seat and the movable end mounting seat are both arranged in the cold bath tank, and the cold bath tank is connected to a medium circulation cooling device;

[0007] a heat load applying device, the heat load applying device being located above the aerospace pipeline and being used to apply a heat load to the aerospace pipeline;

[0008] A data acquisition module includes a high-temperature resistant resistance strain gauge, a first temperature sensor, and a displacement sensor. The resistance strain gauge is attached to the aerospace pipeline to collect strain data generated by the aerospace pipeline. The first temperature sensor is used to collect the temperature of the aerospace pipeline. The displacement sensor is used to collect the displacement of the movable end mounting seat. The resistance strain gauge, the first temperature sensor, and the displacement sensor are all connected to a processor, and the processor is connected to a display.

[0009] Preferably, the fixed end mounting seat includes a fixed end base plate, a fixed end adapter seat is provided on the top of the fixed end base plate, a pipeline pressurization channel is provided in the fixed end adapter seat, the outlet of the pipeline pressurization channel is located at the top of the fixed end adapter seat, the inlet of the pipeline pressurization channel is located on the side of the fixed end adapter seat, and the pipeline pressurization channel.

[0010] Preferably, the movable end mounting seat includes a movable end bottom plate, a guide rail is provided on the top of the movable end bottom plate, and a movable end adapter seat is slidably connected to the guide rail.

[0011] Preferably, it further comprises a tensile load applying device, wherein the tensile load applying device is used to pull the movable end mounting seat to move.

[0012] Preferably, the tensile load applying device includes a telescopic driving member, the telescopic end of the telescopic driving member is provided with a first hook arm, the front end of the first hook arm is provided with a first hook head, the rear part of the first hook head is provided with a second hook head, the second hook head is fixed to the second hook arm, and the second hook arm is fixed to the movable end adapter;

[0013] A force sensor is provided between the first hook head and the second hook head. The force sensor is electrically connected to the processor and is fixed on the first hook head.

[0014] Preferably, the heat load applying device comprises a lampshade, a quartz lamp tube is arranged below the lampshade, the lampshade is fixed on a lifting device, and the lifting device is arranged on the test bench.

[0015] Preferably, there are two cold bath tanks, and the fixed end mounting seat and the movable end mounting seat are respectively placed on the corresponding cold bath tanks.

[0016] Preferably, a heat insulation plate is provided between the two cold bath tanks, and the heat insulation plate is located below the aerospace pipeline.

[0017] Preferably, the medium circulation cooling device includes a circulation pump, a filter and a heat exchanger connected together, the inlet of the circulation pump is connected to the cold bath tank through a pipeline, and the outlet of the heat exchanger is connected to the cold bath tank through a pipeline.

[0018] Preferably, a second temperature sensor is provided in the cold bath.

[0019] Compared with the prior art, the present invention has the following beneficial technical effects:

[0020] The present invention can monitor the temperature, displacement and strain of aerospace pipelines, which is beneficial for testing the thermal strength performance of aerospace pipelines under deformation in the longitudinal direction. At the same time, the adapter mounting seats at both ends of the pipeline adopt a cold bath method to cool down, ensuring the normal operation of the test process. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] The present invention will be further described below with reference to the accompanying drawings.

[0022] Figure 1 This is a schematic diagram of the thermal strength test device system for aerospace pipelines according to the present invention;

[0023] Figure 2 This is a structural diagram of the thermal strength test device for aerospace pipelines of the present invention;

[0024] Figure 3 This is a structural diagram of the fixed end mounting base of the present invention;

[0025] Figure 4 This is a structural diagram of the movable end mounting seat of the present invention;

[0026] Figure 5 This is a structural diagram of the medium circulation cooling device of the present invention.

[0027] Explanation of reference numerals: 1. aerospace pipeline; 2. fixed end mounting seat; 201. fixed end base plate; 202. fixed end adapter seat; 203. pipeline pressurization channel; 3. movable end mounting seat; 301. movable end base plate; 302. guide rail; 303. movable end adapter seat; 4. cold bath; 5. medium circulation cooling device; 501. circulation pump; 502. filter; 503. heat exchanger; 504. second temperature sensor; 505. refrigerant compressor; 6. heat load application Device; 601, lampshade; 602, quartz lamp tube; 603, lifting device; 7, processor; 701, resistance strain gauge; 702, first temperature sensor; 703, displacement sensor; 8, display; 9, tensile load applying device; 901, telescopic drive member; 902, first hook arm; 903, first hook head; 904, second hook head; 905, second hook arm; 906, force sensor; 10, test bench; 11, thermal insulation board; 12, pipeline gasification and pressurization system. DETAILED DESCRIPTION

[0028] In order to make the technical problems, technical solutions and beneficial effects to be solved by the present invention more clearly understood, the present invention is further described in detail below with reference to the accompanying drawings and embodiments.

[0029] like Figure 1 and 2As shown, this embodiment discloses a thermal strength test device for a space pipeline, including a space pipeline 1, which is a thermal expansion tube. One end of the aerospace pipeline 1 is fixed to a fixed end mounting seat 2, which is used to fix and limit one end of the aerospace pipeline 1. The other end of the aerospace pipeline 1 is fixed to a movable end mounting seat 3, which is used to fix the end of the aerospace pipeline 1 and move it along its length.

[0030] The fixed end mounting seat 2 and the movable end mounting seat 3 are both arranged in the cold bath tank 4. The height of the fixed end mounting seat 2 and the movable end mounting seat 3 is higher than the liquid level of the coolant in the cold bath tank 4. The cold bath tank 4 contains coolant, and the coolant is circulated and cooled through the medium circulation cooling device 5. The fixed end mounting seat 2 and the movable end mounting seat 3 are cooled by the coolant.

[0031] A thermal load application device 6 is disposed above the aerospace pipeline 1 and is used to apply a thermal load to the aerospace pipeline 1. A high-temperature-resistant resistance strain gauge 701 and a first temperature sensor 702 are disposed on the aerospace pipeline 1. The resistance strain gauge 701 is attached to the aerospace pipeline 1 to collect strain data generated by the aerospace pipeline 1. The first temperature sensor 702 is used to collect the temperature of the aerospace pipeline 1. The first temperature sensor 702 can specifically be a thermocouple sensor, which can be fixed to the aerospace pipeline 1 by adhesive.

[0032] A displacement sensor 703 is arranged on one side of the movable end mounting base 3. The displacement sensor 703 is used to collect the displacement of the movable end mounting base 3. The resistance strain gauge 701, the first temperature sensor 702, and the displacement sensor 703 together constitute a data acquisition module. The resistance strain gauge 701, the first temperature sensor 702, and the displacement sensor 703 are all electrically connected to the processor 7, and the processor 7 is electrically connected to the display 8. The processor 7 can be a programmable controller PLC, a central processing unit CPU, or a single-chip microcomputer MCU.

[0033] like Figure 3 As shown, in this embodiment, the fixed end mounting seat 2 includes a fixed end base plate 201, which is fixed in the cold bath 4 by bolts. A fixed end adapter seat 202 is provided on the top of the fixed end base plate 201, which is fixed to the fixed end base plate 201 by bolts. A mounting hole connected to the aerospace pipeline 1 is provided on the top of the fixed end adapter seat 202. A flange is usually arranged at the end of the aerospace pipeline 1, and the flange at the end of the aerospace pipeline 1 is fixed to the fixed end adapter seat 202 by bolts.

[0034] A pipeline pressurization channel 203 is provided in the fixed end adapter 202. The outlet of the pipeline pressurization channel 203 is located at the top of the fixed end adapter 202, and the inlet of the pipeline pressurization channel 203 is located on the side of the fixed end adapter 202. The pipeline pressurization channel 203 is connected to the external pipeline gas pressurization system 12. Through the oil-ventilation and gas pressurization structure, it can truly simulate the state of the aerospace pipeline in actual use and the internal pressure it is subjected to.

[0035] like Figure 4 As shown, in this embodiment, the movable end mounting seat 3 includes a movable end base plate 301, a guide rail 302 is provided on the top of the movable end base plate 301, and a movable end adapter seat 303 is slidably connected to the guide rail 302. The end of the aerospace pipeline 1 is usually arranged with a flange, and the flange at the end of the aerospace pipeline 1 is fixed to the movable end adapter seat 303 by bolts.

[0036] The movable end mounting seat 3 is also provided with a tensile load applying device 9, which is used to pull the movable end mounting seat 3 to move. The tensile load applying device 9 includes a telescopic drive member 901. The telescopic end of the telescopic drive member 901 is provided with a first hook arm 902. The front end of the first hook arm 902 is provided with a first hook head 903. The rear end of the first hook head 903 is provided with a second hook head 904. The second hook head 904 is fixed to a second hook arm 905, which is fixed to the movable end adapter 303. A force sensor 906 is provided between the first hook head 903 and the second hook head 904. The force sensor 906 is electrically connected to the processor 7 and is fixed to the first hook head 903. During the retraction of the telescopic drive member 901, the first hook head 903 pulls the second hook head 904, thereby achieving tension on the aerospace pipeline 1. The force sensor 906 is located between the first hook head 903 and the second hook head 904 and feeds back a pressure signal to the processor 7.

[0037] In this embodiment, the thermal load applying device 6 includes a lampshade 601, below which is disposed a quartz lamp 602. The lampshade 601 is fixed to a lifting device 603, which is disposed on the test bench 10. The lifting device 603 can be in the form of a hydraulic cylinder. The lifting device 603 drives the quartz lamp 602 upward or downward to adjust the thermal load exerted by the quartz lamp 602 on the aerospace pipeline 1.

[0038] In this embodiment, there are two cold baths 4, with the fixed-end mounting base 2 and the movable-end mounting base 3 placed on corresponding cold baths 4. A heat shield 11 is positioned between the two cold baths 4 and is located below the aerospace pipeline 1. Heat shield 11 is secured to a test bench 10.

[0039] like Figure 5As shown, each cold bath 4 is correspondingly provided with a medium circulation cooling device 5, and the medium circulation cooling device 5 can be arranged in the test bench 10. The medium circulation cooling device 5 includes a circulation pump 501, a filter 502 and a heat exchanger 503 connected together. The inlet of the circulation pump 501 is connected to the cold bath 4 through a pipe, and the outlet of the heat exchanger 503 is connected to the cold bath 4 through a pipe. A second temperature sensor 504 is provided in the cold bath 4. Among them, one group of interfaces of the heat exchanger 503 is connected in series to the pipe connected to the cold bath 4, and another group of interfaces of the heat exchanger 503 is connected to the refrigerant compressor 505. The second temperature sensor 504 is electrically connected to the processor 7, and the processor 7 controls the refrigerant compressor 505 to work after detecting the electrical signal based on the second temperature sensor 504.

[0040] In addition, both the fixed end mounting seat 2 and the movable end mounting seat 3 may be provided with channels for the cooling medium to pass through, so that the cooling medium in the cold bath 4 can cool the fixed end mounting seat 2 and the movable end mounting seat 3 .

[0041] The present invention can be used in two situations: (1) the first hook 903 of the tensile load applying device 9 is disconnected from the second hook 904, and the strain, temperature, and expansion displacement data of the aerospace pipeline 1 are monitored only under the action of the thermal load applying device 6. (2) the first hook 903 is in contact with the second hook 904, and the strain, temperature, and tensile displacement data of the aerospace pipeline 1 are detected under the simultaneous action of the thermal load applying device 6 and the tensile load applying device 9.

[0042] The embodiments described above are merely descriptions of preferred embodiments of the present invention and are not intended to limit the scope of the present invention. Without departing from the spirit of the present invention, various modifications and improvements made to the technical solutions of the present invention by persons skilled in the art should fall within the scope of protection defined by the claims of the present invention.

Claims

1. A thermal strength test device for aerospace pipelines, characterized in that: include: A space pipeline (1), one end of the space pipeline (1) is fixed to a fixed end mounting seat (2), the fixed end mounting seat (2) is used to fix and limit one end of the space pipeline (1), and the other end of the space pipeline (1) is fixed to a movable end mounting seat (3), the movable end mounting seat (3) is used to fix the end of the space pipeline (1) and move it along its length direction; A cold bath tank (4), wherein the cold bath tank (4) contains a coolant, the fixed end mounting seat (2) and the movable end mounting seat (3) are both arranged in the cold bath tank (4), and the cold bath tank (4) is connected to a medium circulation cooling device (5); a heat load applying device (6), the heat load applying device (6) being located above the aerospace pipeline (1) and being used to apply a heat load to the aerospace pipeline (1); A data acquisition module, comprising a high-temperature resistant strain gauge (701), a first temperature sensor (702), and a displacement sensor (703); the strain gauge (701) is attached to the aerospace pipeline (1) and is used to collect strain data generated by the aerospace pipeline (1); the first temperature sensor (702) is used to collect the temperature of the aerospace pipeline (1); the displacement sensor (703) is used to collect the displacement of the movable end mounting seat (3); the strain gauge (701), the first temperature sensor (702), and the displacement sensor (703) are all connected to a processor (7); and the processor (7) is connected to a display (8).

2. The thermal strength testing device for aerospace pipelines according to claim 1, characterized in that: The fixed end mounting seat (2) comprises a fixed end base plate (201), a fixed end adapter seat (202) is provided on the top of the fixed end base plate (201), a pipeline pressurization channel (203) is provided in the fixed end adapter seat (202), an outlet of the pipeline pressurization channel (203) is located at the top of the fixed end adapter seat (202), an inlet of the pipeline pressurization channel (203) is located at the side of the fixed end adapter seat (202), and the pipeline pressurization channel (203) is provided in the fixed end adapter seat (202).

3. The thermal strength testing device for aerospace pipelines according to claim 1, characterized in that: The movable end mounting seat (3) comprises a movable end base plate (301), a guide rail (302) is provided on the top of the movable end base plate (301), and a movable end adapter seat (303) is slidably connected to the guide rail (302).

4. The thermal strength testing device for aerospace pipelines according to claim 1, characterized in that: It also includes a tensile load applying device (9), which is used to pull the movable end mounting seat (3) to move.

5. The thermal strength testing device for aerospace pipelines according to claim 4, characterized in that: The tensile load applying device (9) comprises a telescopic driving member (901), the telescopic end of the telescopic driving member (901) is provided with a first hook arm (902), the front end of the first hook arm (902) is provided with a first hook head (903), the rear part of the first hook head (903) is provided with a second hook head (904), the second hook head (904) is fixed on the second hook arm (905), and the second hook arm (905) is fixed on the movable end adapter (303); A force sensor (906) is provided between the first hook head (903) and the second hook head (904), the force sensor (906) is electrically connected to the processor (8), and the force sensor (906) is fixed on the first hook head (903).

6. The thermal strength testing device for aerospace pipelines according to claim 1, characterized in that: The heat load applying device (6) comprises a lampshade (601), a quartz lamp tube (602) is arranged below the lampshade (601), and the lampshade (601) is fixed on a lifting device (603), and the lifting device (603) is arranged on a test bench (10).

7. The thermal strength testing device for aerospace pipelines according to claim 1, characterized in that: There are two cold bath tanks (4), and the fixed end mounting seat (2) and the movable end mounting seat (3) are respectively placed on the corresponding cold bath tanks (4).

8. The thermal strength testing device for aerospace pipelines according to claim 1, characterized in that: A heat insulation board (11) is provided between the two cold bath tanks (4), and the heat insulation board (11) is located below the aerospace pipeline (1).

9. The thermal strength testing device for aerospace pipelines according to claim 1, characterized in that: The medium circulation cooling device (5) comprises a circulation pump (501), a filter (502) and a heat exchanger (503) connected together, the inlet of the circulation pump (501) is connected to the cold bath tank (4) through a pipeline, and the outlet of the heat exchanger (503) is connected to the cold bath tank (4) through a pipeline.

10. The thermal strength testing device for aerospace pipelines according to claim 9, characterized in that: A second temperature sensor (504) is provided in the cold bath tank (4).

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