Energy-saving low-altitude industrial cold and hot impact test box

Abstract

The invention discloses an energy-saving low-altitude industrial cold and hot impact test box which comprises a box body, the box body is provided with a test bin, the energy-saving low-altitude industrial cold and hot impact test box further comprises a test assembly which is arranged in the box body and used for carrying out a bin separation test on a low-altitude aircraft, and the test assembly comprises a transverse partition plate fixedly connected to the inner wall of the test bin; one side of the transverse partition plate is fixedly connected with a longitudinal partition plate, the end, away from the transverse partition plate, of the longitudinal partition plate is connected with the bottom of the test bin, the side, away from the longitudinal partition plate, of the transverse partition plate is fixedly connected with a baffle, and the side, away from the transverse partition plate, of the baffle is connected with the bottom of the test bin. According to the energy-saving low-altitude industrial cold and hot impact test box disclosed by the invention, the test assembly is arranged, and the test bins in the test box are designed into three bins, so that the energy loss of a low-altitude aircraft or a part in a refrigeration environment or heating environment conversion process is reduced; and thus, the operation cost of the cold and hot impact test on the low-altitude aircraft is reduced.

Description

Technical Field

[0001] The present invention relates to the technical field of low-altitude industrial test chambers, and particularly to an energy-saving low-altitude industrial thermal shock test chamber. Background Art

[0002] Low-altitude industrial test chambers can simulate a variety of real low-altitude environments, be used to test the flight performance of unmanned aerial vehicles or small aircraft, and thus provide data support for the research and development and testing of low-altitude equipment. At present, with the booming development of the low-altitude economy, the performance reliability of various low-altitude aircraft, equipment, and related components is crucial. These products will face complex and changeable environments during actual use, especially the drastic changes in temperature, which are a great test for their performance and stability. For example, when an unmanned aerial vehicle quickly switches between high-altitude low-temperature environments and low-altitude high-temperature environments for operation, electronic components, structural materials, etc. may deform, have reduced performance, or even fail due to thermal expansion and contraction.

[0003] Existing low-altitude industrial test chambers adopt a single test chamber setting. Although it is convenient for low-altitude aircraft to conduct thermal shock tests, during the process of high-low temperature conversion, the test chamber has a large energy loss in the process of converting the refrigeration environment or heating environment due to the too high or too low initial internal temperature, thus increasing the operating cost of conducting thermal shock tests on low-altitude aircraft.

[0004] Therefore, there is an urgent need for an energy-saving low-altitude industrial thermal shock test chamber to solve the above problems. Summary of the Invention

[0005] To achieve the above object, the present invention provides the following technical solution: An energy-saving low-altitude industrial thermal shock test chamber, including a box body, the box body is provided with a test chamber, and further includes a test component arranged on the box body for conducting compartment tests on low-altitude aircraft; The test component includes a transverse partition fixedly connected to the inner wall of the test chamber. One side of the transverse partition is fixedly connected with a longitudinal partition. The end of the longitudinal partition far from the transverse partition is connected to the bottom of the test chamber. One side of the transverse partition far from the longitudinal partition is fixedly connected with a baffle. The side of the baffle far from the transverse partition is connected to the bottom of the test chamber. The test chamber is divided into a hot pressure shock chamber, a cold pressure shock chamber, and a transition chamber under the partitioning action of the transverse partition, the longitudinal partition, and the baffle. The transition chamber is provided with a switching component for switching the positions of low-altitude aircraft in different compartments, and the transverse partition is provided with an entrance component for low-altitude aircraft to enter different compartments.

[0006] The entrance component includes a through hole opened on the transverse partition. Opposite inner walls of the through hole are hinged with sealing plates through torsion shafts. Rubber protection pads are provided at opposite ends of the two sealing plates.

[0007] The switching component includes a switching board slidably connected to the transition bin. One side of the switching board close to the transverse partition is fixedly connected with a push rod motor. The output end of the push rod motor is fixedly connected with a push rod. The end of the push rod away from the switching board is fixedly connected with a placement board for placing a low-altitude aircraft. The transition bin is provided with a moving component for moving the placement board. The switching board is provided with a reflux component for refluxing the cold air or hot air overflowing during the switching of the low-altitude aircraft in the transition bin.

[0008] A sealing abutting plate is fixedly connected to the side wall of the push rod. A rubber pad is arranged on one side of the sealing abutting plate close to the transverse partition.

[0009] The moving component includes moving rods fixedly connected between two opposite inner walls of the transition bin. The two moving rods are located on the side of the switching board away from the placement board, and a first moving plate is slidably connected to the side wall. One end of the two first moving plates is connected to the switching board. A lead screw is rotatably connected between the two moving rods, and the two ends of the lead screw are respectively connected to two opposite inner walls of the transition bin. The lead screw is threadedly connected with a second moving plate. One end of the second moving plate is connected to the switching board. A motor is fixedly connected to the side wall of the box body, and the output end of the motor is connected to the lead screw.

[0010] The reflux component includes two symmetrically arranged reflux pipes arranged on one side of the switching board close to the placement board. The two reflux pipes are connected to the switching board through a telescopic component. An air inlet pipe and an air outlet pipe are fixedly connected to the side walls of the two reflux pipes. The ends of the two air outlet pipes away from the reflux pipes are respectively communicated with the hot pressing impact bin and the cold pressing impact bin. A reflux plate is slidably connected in the two reflux pipes. The transition bin is provided with a driving component for driving the two reflux plates and a one-way component arranged on the driving component for driving the reflux plate in one direction.

[0011] One-way valves are respectively arranged in the two air inlet pipes and air outlet pipes. The conduction directions of the two one-way valves are from the transition bin to the hot pressing impact bin or the cold pressing impact bin.

[0012] The driving component includes a strip-shaped plate fixedly connected to the bottom wall of the transition bin. One side of the strip-shaped plate is fixedly connected with a mounting plate. A plurality of driving blocks are fixedly connected to one side of the mounting plate close to the reflux pipe. First inclined surfaces are formed on two opposite side walls of each driving block. A driving rod is slidably connected to one side of the reflux pipe close to the driving block. The end of the driving rod close to the driving block is rounded. The other end of the driving rod is connected to the reflux plate. A first spring is fixedly connected to the side of the reflux plate away from the driving rod. The other end of the first spring is connected to the bottom wall of the reflux pipe.

[0013] The one-way component includes a one-way plate fixedly connected to one side of the mounting plate close to the driving rod. Second inclined surfaces and third inclined surfaces are respectively formed at two ends of the one-way plate close to the hot pressing impact chamber and the cold pressing impact chamber. The second inclined surfaces and the third inclined surfaces are arranged in parallel, and the driving rod is aligned with the middle positions of the second inclined surfaces and the third inclined surfaces in the initial state.

[0014] The telescopic component includes a telescopic frame fixedly connected to one side of the switching plate close to the placing plate. A U-shaped plate is slidably connected to the telescopic frame. The U-shaped plate is connected to the return pipe through a fixing ring. Two T-shaped rods are fixedly connected to the bottom wall of the telescopic frame. The U-shaped plate is slidably connected to the two T-shaped rods. Second springs are sleeved on the side walls of the two T-shaped rods, and two ends of the two second springs are respectively connected to the bottom wall of the telescopic frame and the U-shaped plate.

[0015] Compared with the prior art, the beneficial effects of the present invention are as follows: 1. In the energy-saving low-altitude industry thermal shock test chamber of the present invention, through the arrangement of the test component, by designing the test chambers in the test chamber into three chambers, the test piece can be quickly switched among the three chambers through the switching component and the moving component, so as to realize the thermal shock test on the low-altitude aircraft or components while reducing the mutual cross-mixing of different characteristic heats, thereby reducing the energy loss of the low-altitude aircraft or components during the conversion process between the refrigeration environment and the heating environment, and further reducing the operation cost of the thermal shock test on the low-altitude aircraft; 2. In the energy-saving low-altitude industry thermal shock test chamber of the present invention, through the arrangement of the return component, under the combined action of the one-way component and the driving component, the cold air or hot air overflowing in the transition chamber due to the switching of the low-altitude aircraft is continuously returned to the cold pressing impact chamber or the hot pressing impact chamber, thereby reducing the waste of hot air and cold air while reducing the probability of hot air and cold air mixing. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 is a schematic diagram of the overall structure of the present invention; Figure 2 is a schematic diagram of the experimental component structure of the present invention; Figure 3 is a schematic diagram of the switching component structure of the present invention; Figure 4 is a schematic diagram of the moving component structure of the present invention; Figure 5 is a schematic diagram of the sealing plate structure of the present invention; Figure 6 is a schematic diagram of the internal structure of the return component of the present invention; Figure 7 is a schematic diagram of the driving component and the one-way component structure of the present invention; Figure 8It is a schematic diagram of the separation structure of the test chamber.

[0017] In the figure: 1. Box body; 201. Transverse partition; 202. Longitudinal partition; 203. Baffle; 301. Through hole; 302. Sealing plate; 401. Switching plate; 402. Push rod motor; 403. Push rod; 404. Placing plate; 405. Sealing abutting plate; 501. Moving rod; 502. First moving plate; 503. Lead screw; 504. Second moving plate; 505. Motor; 601. Return pipe; 602. Intake pipe; 603. Exhaust pipe; 604. Return plate; 605. Check valve; 701. Strip plate; 702. Driving block; 703. First inclined surface; 704. Driving rod; 705. First spring; 706. Mounting plate; 801. One-way plate; 802. Second inclined surface; 803. Third inclined surface; 901. Telescopic frame; 902. U-shaped plate; 903. Fixed ring; 904. T-shaped rod; 905. Second spring. Specific implementation manners

[0018] Next, the technical solutions in the embodiments of the present invention will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present invention.

[0019] Embodiment 1: Please refer to Figures 1-8 , an energy-saving low-altitude industrial thermal shock test chamber shown in the figure, including a box body 1, the box body 1 is provided with a test chamber, and further includes a test component arranged on the box body 1 for performing sub-chamber tests on low-altitude aircraft; The test component includes a transverse partition 201 fixedly connected to the inner wall of the test chamber. One side of the transverse partition 201 is fixedly connected with a longitudinal partition 202. One end of the longitudinal partition 202 away from the transverse partition 201 is connected to the bottom of the test chamber. One side of the transverse partition 201 away from the longitudinal partition 202 is fixedly connected with a baffle 203. One side of the baffle 203 away from the transverse partition 201 is connected to the bottom of the test chamber. The test chamber forms a hot press shock chamber, a cold press shock chamber and a transition chamber under the partition action of the transverse partition 201, the longitudinal partition 202 and the baffle 203. The transition chamber is provided with a switching component for switching the positions of the low-altitude aircraft in different chambers, and the transverse partition 201 is provided with an entrance component for the low-altitude aircraft to enter different chambers; It should be noted here that: through the setting of the test components, by designing the test chamber in the test box into three chambers, the test piece can be quickly switched between the three chambers through the switching component and the moving component, so as to realize the thermal shock test on the low-altitude aircraft or components while reducing the mutual cross-mixing of heat with different characteristics, thereby reducing the energy loss during the conversion of the low-altitude aircraft or components between the refrigeration environment and the heating environment, and further reducing the operation cost of the thermal shock test on the low-altitude aircraft.

[0020] Please refer to Figure 2 and Figure 3 , in the illustrated inlet component, a through hole 301 is opened in the transverse partition 201. Sealing plates 302 are hinged to the two opposite inner walls of the through hole 301 through torsion shafts, and rubber protective pads are provided at one end of the two sealing plates 302 facing each other. It should be noted here that: through the setting of the inlet component, it is used to provide an inlet for the low-altitude aircraft or components to enter the hot press shock chamber or the cold press shock chamber.

[0021] Please refer to Figure 3 , Figure 4 and Figure 5 , in the illustrated switching component, a switching plate 401 is slidably connected to the transition chamber. A push rod motor 402 is fixedly connected to one side of the switching plate 401 close to the transverse partition 201. A push rod 403 is fixedly connected to the output end of the push rod motor 402. A placement plate 404 for placing the low-altitude aircraft is fixedly connected to one end of the push rod 403 away from the switching plate 401. A moving component for moving the placement plate 404 is provided in the transition chamber, and a reflux component for refluxing the cold air or hot air overflowing during the switching process of the low-altitude aircraft in the transition chamber is provided on the switching plate 401. It should be noted here that: through the setting of the switching component, it is used to switch the position of the low-altitude aircraft or components in different test chambers, so as to realize the thermal and cold press tests.

[0022] Please refer to Figure Figure 5 , a sealing abutting plate 405 is fixedly connected to the side wall of the illustrated push rod 403, and a rubber pad is provided on one side of the sealing abutting plate 405 close to the transverse partition 201. It should be noted here that: through the setting of the sealing abutting plate 405, it is used to seal the through hole 301, thereby reducing the risk of hot air or cold air overflowing.

[0023] Please refer to Figure 4 and Figure 5, the moving components in the illustration include a moving rod 501 fixedly connected between two opposite inner walls of the transition bin. The two moving rods 501 are located on the side of the switching plate 401 away from the placement plate 404, and a first moving plate 502 is slidably connected to the side wall. One end of each of the two first moving plates 502 is connected to the switching plate 401. A lead screw 503 is rotatably connected between the two moving rods 501, and both ends of the lead screw 503 are respectively connected to two opposite inner walls of the transition bin. The lead screw 503 is threadedly connected to a second moving plate 504, and one end of the second moving plate 504 is connected to the switching plate 401. A motor 505 is fixedly connected to the side wall of the box body 1, and the output end of the motor 505 is connected to the lead screw 503; It should be noted here that: through the setting of the moving components, it is used to drive the switching plate 401 to move.

[0024] Working principle: When using the test chamber to conduct a thermal shock test on a low-altitude aircraft, when first conducting the thermal compression shock test on the low-altitude aircraft, first start the motor 505 to drive the lead screw 503 to rotate. Under the action of the threaded meshing drive between the lead screw 503 and the second moving plate 504 and the guiding action of the two moving rods 501 and the first moving plate 502, drive the placement plate 404 on one side of the switching plate 401 to move. When the placement plate 404 is opposite to the through hole 301 of the transverse partition 201, start the push rod motor 402, and then push the placement plate 404 to move closer to the transverse partition 201. As the placement plate 404 continues to move, under the action of the driving force, push the two sealing plates 302 at the through hole 301 to rotate away from each other. When the placement plate 404 moves into the thermal compression shock chamber, the sealing abutting plate 405 on the side wall of the push rod 403 will abut against the side wall of the transverse partition 201, thereby sealing the through hole 301. At this time, the cabinet door of the box body 1 can be opened to place the low-altitude aircraft or components on the placement plate 404 and fix them; Moreover, more optimally, an operation hole can be opened at the cabinet door of the box body 1, and the operation hole is opposite to the baffle 203. Therefore, by installing and disassembling the baffle 203, the placement of the low-altitude aircraft or components and the replacement operation of different test objects can be completed; After placing the low-altitude aircraft or components on the placement plate 404 and entering the thermal compression shock chamber, the thermal compression shock chamber can be heated by a heater (not shown here), thereby conducting a thermal compression shock test on the low-altitude aircraft or components; After the hot pressing impact test on the low-altitude aircraft or components is completed, the push rod motor 402 can be started again to drive the placement plate 404 to retract into the transition bin. At this time, the two sealing plates 302 will be reset under the elastic action of the torsion shaft, so as to block the through hole 301. After the placement plate 404 is completely retracted into the transition bin, the placement plate 404 is moved by the moving component to align with the through hole 301 at the cold pressing impact bin, and then the placement plate 404 is pushed into the cold pressing impact bin by the push rod motor 402. Thus, a refrigerator (not shown here) can be used to conduct the hot and cold pressing impact test on the low-altitude aircraft or components on the placement plate 404. Therefore, by designing the test bins in the test chamber into three bins, the test piece can be quickly switched among the three bins through the switching component and the moving component. While realizing the thermal shock test on the low-altitude aircraft or components, the mutual cross-mixing of different characteristic heats is reduced, thereby reducing the energy loss of the low-altitude aircraft or components during the conversion process between the refrigeration environment and the heating environment, and further reducing the operation cost of the thermal shock test on the low-altitude aircraft.

[0025] Embodiment 2: Please refer to Figure 6 , this embodiment further describes Embodiment 1. The reflux component in the figure includes two symmetrically arranged reflux pipes 601 provided on the side of the switching plate 401 close to the placement plate 404. The two reflux pipes 601 are connected to the switching plate 401 through the telescopic component. An air inlet pipe 602 and an air outlet pipe 603 are fixedly connected to the side walls of the two reflux pipes 601. The ends of the two air outlet pipes 603 away from the reflux pipes 601 are respectively communicated with the hot pressing impact bin and the cold pressing impact bin. A reflux plate 604 is slidably connected in the two reflux pipes 601. The transition bin is provided with a driving component for driving the two reflux plates 604 and a one-way component provided on the driving component for driving the reflux plate 604 in one direction. One-way valves 605 are respectively provided in the two air inlet pipes 602 and the air outlet pipes 603, and the conduction directions of the two one-way valves 605 are from the transition bin to the hot pressing impact bin or the cold pressing impact bin; It should be noted here that: through the setting of the reflux component, the cold air or hot air overflowing in the transition bin due to the switching of the low-altitude aircraft is continuously refluxed to the cold pressing impact bin or the hot pressing impact bin, thereby reducing the waste of hot air and cold air while reducing the probability of mixing of hot air and cold air.

[0026] Please refer to Figure 6 and Figure 7, in the illustrated driving assembly, it includes a strip plate 701 fixedly connected to the bottom wall of the transition bin. One side of the strip plate 701 is fixedly connected with a mounting plate 706. On the side of the mounting plate 706 close to the return pipe 601, a plurality of driving blocks 702 are fixedly connected. On the two opposite side walls of each driving block 702, a first inclined surface 703 is provided. On the side of the return pipe 601 close to the driving block 702, a driving rod 704 is slidably connected. One end of the driving rod 704 close to the driving block 702 is rounded. The other end of the driving rod 704 is connected to the return plate 604. On the side of the return plate 604 away from the driving rod 704, a first spring 705 is fixedly connected. The other end of the first spring 705 is connected to the bottom wall of the return pipe 601; It should be noted here that: through the setting of the driving assembly, it is used to reciprocally push the return plate 604 at one end of the driving rod 704.

[0027] Please refer to Figure 6 and Figure 7 , in the illustrated one-way assembly, it includes a one-way plate 801 fixedly connected to the side of the mounting plate 706 close to the driving rod 704. At both ends of the one-way plate 801 close to the hot pressing impact bin and the cold pressing impact bin, a second inclined surface 802 and a third inclined surface 803 are respectively provided. The second inclined surface 802 and the third inclined surface 803 are arranged in parallel. In the initial state, the driving rod 704 is aligned with the middle positions of the second inclined surface 802 and the third inclined surface 803; It should be noted here that: through the setting of the one-way assembly, when the low-altitude aircraft switches from the hot pressing impact bin to the cold pressing impact bin, the airflow in the transition bin flows back into the hot pressing impact bin, and when the low-altitude aircraft switches from the cold pressing impact bin to the hot pressing impact bin, the airflow in the transition bin flows back into the cold pressing impact bin, so as to facilitate the targeted return operation of the airflow according to the switching situation of the low-altitude aircraft, and further reduce the probability of mixing of hot air and cold air.

[0028] Working principle: During the process of the moving component driving the switching board 401 to move, the driving rod 704 at one end of the return pipe 601 will be driven to move synchronously. During the movement of the driving rod 704, when the driving rod 704 abuts against the driving block 702 on the mounting plate 706, under the mutual acting force of the first inclined surface 703, the return plate 604 at one end of the driving rod 704 will be pushed to slide in the return pipe 601. Then, under the action of air pressure change and the one-way blocking effect of the one-way valve 605, the gas in the return pipe 601 is transported from the air outlet pipe 603 to the hot pressing impact chamber or the cold pressing impact chamber. When the driving rod 704 passes over the driving block 702, under the elastic action of the first spring 705, the return plate 604 at one end of the driving rod 704 will be driven to slide in the opposite direction in the return pipe 601. Then, under the action of air pressure change and the one-way blocking effect of the one-way valve 605, the gas in the transition chamber will enter the return pipe 601 from the air inlet pipe 602. Therefore, during the process of the moving component driving the driving rod 704 to move continuously, it will continuously abut against the driving block 702 reciprocally, and then push the return plate 604 to move reciprocally in the return pipe 601, thereby continuously returning the cold air or hot air overflowing due to the switching of the low-altitude aircraft in the transition chamber to the cold pressing impact chamber or the hot pressing impact chamber. Thus, while reducing the waste of hot air and cold air, the probability of hot air and cold air mixing is reduced; And during the process of the moving component driving the two return pipes 601 to move, when the low-altitude aircraft switches from the hot press impact chamber to the cold press impact chamber, the driving rod 704 on the return pipe 601 at the end connected to the hot press impact chamber will first abut against the second inclined surface 802 on the one-way plate 801. Then, under the action of the interaction force and the guiding action of the telescopic component, the driving rod 704 is pushed to move above the one-way plate 801, so that the driving rod 704 can reciprocally abut against each driving block 702, facilitating the return of the hot air in the transition chamber to the hot press impact chamber. At the same time, the driving rod 704 on the return pipe 601 at the end connected to the cold press impact chamber of the air outlet pipe 603 will first abut against the third inclined surface 803 on the one-way plate 801. Then, under the action of the interaction force and the guiding action of the telescopic component, the driving rod 704 is pushed to move below the one-way plate 801, so that the driving rod 704 will not reciprocally abut against each driving block 702, thus preventing the hot air in the transition chamber from flowing back into the cold press impact chamber. Similarly, when the low-altitude aircraft switches from the cold press impact chamber to the hot press impact chamber, the two driving rods 704 move in the opposite direction, which will not be elaborated here specifically. Therefore, through the setting of the one-way component, when the low-altitude aircraft switches from the hot press impact chamber to the cold press impact chamber, the air flow in the transition chamber flows back into the hot press impact chamber, and when the low-altitude aircraft switches from the cold press impact chamber to the hot press impact chamber, the air flow in the transition chamber flows back into the cold press impact chamber, facilitating the targeted return operation of the air flow according to the switching situation of the low-altitude aircraft, and thus reducing the probability of mixing of hot air and cold air.

[0029] Embodiment 3: Please refer to Figure 6 , this embodiment further explains other embodiments. In the illustrated telescopic component, it includes a telescopic frame 901 fixedly connected to the side of the switching plate 401 close to the placement plate 404. A U-shaped plate 902 is slidably connected to the telescopic frame 901. The U-shaped plate 902 is connected to the return pipe 601 through a fixing ring 903. Two T-shaped rods 904 are fixedly connected to the bottom wall of the telescopic frame 901. The U-shaped plate 902 is slidably connected to the two T-shaped rods 904. Second springs 905 are sleeved on the side walls of the two T-shaped rods 904. The two ends of the two second springs 905 are respectively connected to the bottom wall of the telescopic frame 901 and the U-shaped plate 902; It should be noted here that: through the setting of the telescopic component, while the fixing ring 903 is used to install and fix the return pipe 601, under the elastic action of the T-shaped rods 904 and the second springs 905, a guiding and resetting effect for the movement of the return pipe 601 is provided.

[0030] It is obvious to those skilled in the art that the present invention is not limited to the details of the above-described exemplary embodiments, and that the present invention can be implemented in other specific forms without departing from the spirit or essential characteristics of the present invention. Therefore, in any respect, the embodiments should be regarded as exemplary and non-limiting. The scope of the present invention is defined by the appended claims rather than the above description. Accordingly, all changes that fall within the meaning and scope of the equivalent elements of the claims are intended to be embraced within the present invention. Any reference signs in the claims should not be construed as limiting the claims involved.

Claims

1. An energy-saving low-altitude industry thermal shock test chamber, comprising: A box body (1), the box body (1) is provided with a test chamber; It is characterized in that it further comprises: A test component arranged in the box body (1) for conducting compartment tests on low-altitude aircraft; The test component includes a transverse partition (201) fixedly connected to the inner wall of the test chamber. One side of the transverse partition (201) is fixedly connected to a longitudinal partition (202). The end of the longitudinal partition (202) away from the transverse partition (201) is connected to the bottom of the test chamber. One side of the transverse partition (201) away from the longitudinal partition (202) is fixedly connected to a baffle (203). The side of the baffle (203) away from the transverse partition (201) is connected to the bottom of the test chamber. The test chamber forms a hot press shock chamber, a cold press shock chamber and a transition chamber under the partitioning action of the transverse partition (201), the longitudinal partition (202) and the baffle (203). The transition chamber is provided with a switching component for switching the positions of the low-altitude aircraft in different compartments, and the transverse partition (201) is provided with an entrance component for the low-altitude aircraft to enter different compartments.

2. The energy-saving low-altitude industrial thermal shock test chamber according to claim 1, wherein: The entrance component includes a through hole (301) opened in the transverse partition (201). Sealing plates (302) are hinged to the opposite two inner walls of the through hole (301) through torsion shafts. Rubber protection pads are provided at the opposite ends of the two sealing plates (302).

3. An energy-saving low-altitude industrial thermal shock test chamber according to claim 2, characterized in that: The switching component includes a switching plate (401) slidably connected to the transition chamber. A push rod motor (402) is fixedly connected to one side of the switching plate (401) close to the transverse partition (201). The output end of the push rod motor (402) is fixedly connected to a push rod (403). The end of the push rod (403) away from the switching plate (401) is fixedly connected to a placement plate (404) for placing the low-altitude aircraft. The transition chamber is provided with a moving component for moving the placement plate (404). The switching plate (401) is provided with a reflux component for refluxing the cold air or hot air overflowing during the switching process of the low-altitude aircraft in the transition chamber.

4. An energy-saving low-altitude industrial thermal shock test chamber according to claim 3, characterized in that: A sealing abutting plate (405) is fixedly connected to the side wall of the push rod (403). A rubber pad is provided on the side of the sealing abutting plate (405) close to the transverse partition (201).

5. The energy-saving low-altitude industrial thermal shock test chamber according to claim 4, wherein: The moving component includes moving rods (501) fixedly connected between the opposite two inner walls of the transition chamber. The two moving rods (501) are located on the side of the switching plate (401) away from the placement plate (404), and a first moving plate (502) is slidably connected to the side wall. One end of the two first moving plates (502) is connected to the switching plate (401). A lead screw (503) is rotatably connected between the two moving rods (501), and the two ends of the lead screw (503) are respectively connected to the opposite two inner walls of the transition chamber. A second moving plate (504) is threadedly connected to the lead screw (503). One end of the second moving plate (504) is connected to the switching plate (401). A motor (505) is fixedly connected to the side wall of the box body (1), and the output end of the motor (505) is connected to the lead screw (503).

6. The energy-saving low-altitude industrial thermal shock test chamber according to claim 5, wherein: The reflux assembly includes two symmetrically arranged reflux pipes (601) provided on the side of the switching board (401) close to the placement board (404). The two reflux pipes (601) are connected to the switching board (401) through a telescopic assembly. An air inlet pipe (602) and an air outlet pipe (603) are fixedly connected to the side walls of the two reflux pipes (601). One ends of the two air outlet pipes (603) far from the reflux pipes (601) are respectively communicated with a hot pressing impact chamber and a cold pressing impact chamber. A reflux plate (604) is slidably connected in the two reflux pipes (601). The transition chamber is provided with a driving assembly for driving the two reflux plates (604) and a one-way assembly provided on the driving assembly for driving the reflux plate (604) unidirectionally.

7. An energy-saving low-altitude industrial thermal shock test chamber according to claim 6, characterized in that: One-way valves (605) are respectively provided in the two air inlet pipes (602) and the air outlet pipes (603). The conduction directions of the two one-way valves (605) are from the transition chamber to the hot pressing impact chamber or the cold pressing impact chamber.

8. An energy-saving low-altitude industrial thermal shock test chamber according to claim 7, characterized in that: The driving assembly includes a strip-shaped plate (701) fixedly connected to the bottom wall of the transition chamber. One side of the strip-shaped plate (701) is fixedly connected with a mounting plate (706). A plurality of driving blocks (702) are fixedly connected to the side of the mounting plate (706) close to the reflux pipe (601). First inclined surfaces (703) are provided on two opposite side walls of each driving block (702). A driving rod (704) is slidably connected to the side of the reflux pipe (601) close to the driving block (702). One end of the driving rod (704) close to the driving block (702) is rounded. The other end of the driving rod (704) is connected to the reflux plate (604). A first spring (705) is fixedly connected to the side of the reflux plate (604) far from the driving rod (704). The other end of the first spring (705) is connected to the bottom wall of the reflux pipe (601).

9. The energy-saving low-altitude industrial thermal shock test chamber according to claim 8, characterized in that: The one-way assembly includes a one-way plate (801) fixedly connected to the side of the mounting plate (706) close to the driving rod (704). Second inclined surfaces (802) and third inclined surfaces (803) are respectively provided at two ends of the one-way plate (801) close to the hot pressing impact chamber and the cold pressing impact chamber. The second inclined surfaces (802) and the third inclined surfaces (803) are arranged in parallel. The driving rod (704) is aligned with the middle positions of the second inclined surfaces (802) and the third inclined surfaces (803) in the initial state.

10. An energy-saving low-altitude industrial thermal shock test chamber according to claim 9, characterized in that: The telescopic assembly includes a telescopic frame (901) fixedly connected to the side of the switching board (401) close to the placement board (404). A U-shaped plate (902) is slidably connected to the telescopic frame (901). The U-shaped plate (902) is connected to the reflux pipe (601) through a fixing ring (903). Two T-shaped rods (904) are fixedly connected to the bottom wall of the telescopic frame (901). The U-shaped plate (902) is slidably connected to the two T-shaped rods (904). Second springs (905) are sleeved on the side walls of the two T-shaped rods (904). Two ends of the two second springs (905) are respectively connected to the bottom wall of the telescopic frame (901) and the U-shaped plate (902).

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