High-precision high-low temperature box suitable for MEMS inertial navigation test system

Abstract

The utility model relates to the field of distance measurement, in particular to a high-precision high-low temperature box suitable for an MEMS (Micro Electro Mechanical System) inertial navigation test system, which comprises a high-low temperature box, a mounting cover plate is placed at the upper end of the high-low temperature box, and heating mechanisms are arranged on the left side and the right side of the inner wall of the high-low temperature box. The installation columns with the same weight are installed on the inner walls of the two internal thread cylinders which are symmetrical about the center of the support, the balance of the unmanned aerial vehicle testing mechanism is kept, the testing accuracy is improved, then the wireless control mechanism is controlled through the remote control mechanism, the unmanned aerial vehicle testing mechanism takes off, and the testing efficiency is improved. The air conditioner is started to heat or cool the temperature in the high-low temperature box, so that the problem that the MEMS inertial navigation test system in the prior art is difficult to be in the environment of the high-low temperature box, so that the MEMS inertial navigation test equipment is mounted on the fuselage of the unmanned aerial vehicle; the MEMS inertial navigation test equipment can test the performance of the unmanned aerial vehicle at different heights and different take-off weights.

Description

Technical Field

[0001] The utility model belongs to the field of distance measurement, and in particular relates to a high-precision high and low temperature box suitable for a MEMS inertial navigation test system. Background Art

[0002] The MEMS inertial navigation test system is a test platform for the inertial navigation system (INS) based on the micro-electromechanical system (MEMS) technology. The MEMS inertial navigation system mainly includes components such as gyroscopes, accelerometers, and microprocessors. The gyroscope is used to measure the angular velocity of the moving body around each axis, and the accelerometer is used to measure the acceleration and direction of the moving body. These sensor data are processed by the microprocessor to calculate the carrier's speed, position, attitude and other information. MEMS inertial navigation systems are widely used in unmanned systems such as drones, unmanned vehicles, unmanned ships, robots, as well as consumer electronic products such as mobile phones and tablets.

[0003] A high-precision high and low temperature chamber is an experimental device that can simulate extreme temperature environments. It can heat or cool the MEMS inertial navigation system under constant temperature conditions to test its performance and stability at different temperatures. However, the MEMS inertial navigation test system in the prior art is difficult to install the MEMS inertial navigation test equipment on the fuselage of the UAV in the high and low temperature chamber environment to test the performance of the test UAV at different altitudes and different take-off weights.

[0004] Therefore, a high-precision high and low temperature box suitable for MEMS inertial navigation test system is proposed. In the environment of the high and low temperature box, the MEMS inertial navigation test equipment can be installed on the fuselage of the UAV, and the MEMS inertial navigation test equipment can be used to test the performance of the test UAV at different altitudes and different take-off weights. Utility Model Content

[0005] In order to overcome the problem that the MEMS inertial navigation test system in the prior art is difficult to operate in a high and low temperature box environment, the MEMS inertial navigation test equipment can be installed on the fuselage of the UAV and the performance of the UAV can be tested by the MEMS inertial navigation test equipment at different altitudes and different take-off weights. Therefore, a high-precision high and low temperature box suitable for the MEMS inertial navigation test system is proposed.

[0006] The technical solution of the present utility model is as follows: A high-precision high and low temperature chamber applicable to a MEMS inertial navigation test system, comprising a high and low temperature chamber; an installation cover plate is placed on the upper end of the high and low temperature chamber, heating mechanisms are arranged on both the left and right sides of the inner wall of the high and low temperature chamber, a camera mechanism is arranged at the rear end of the inner wall of the high and low temperature chamber, two air conditioners are fixedly connected to the upper part of the front end of the inner wall of the high and low temperature chamber, observation slots are penetrated and opened at both the front and rear ends of the high and low temperature chamber, transparent glass plates are fixedly connected to the inner walls of the observation slots, a remote control mechanism is arranged on the side wall of the high and low temperature chamber, a first bottom block is installed at the lower end of the unmanned aerial vehicle test mechanism, a wireless control mechanism is arranged inside the first bottom block, a weight increasing mechanism is arranged at the lower end of the first bottom block, a MEMS inertial navigation test device is installed at the upper end of the unmanned aerial vehicle test mechanism, and a temperature measuring mechanism is arranged on the bottom surface of the inner wall of the high and low temperature chamber;

[0007] The weight increasing mechanism includes a long column, a third fixing block, a bracket, an arc-shaped block, an internally threaded cylinder and an installation column; the lower end of the first bottom block is fixedly connected with the long column, the lower end of the long column is fixedly connected with the third fixing block, the lower end of the third fixing block is fixedly connected with the bracket, the bracket is in a T shape, the lower end and the four ends of the bracket are fixedly connected with arc-shaped blocks, the inner wall of the arc-shaped block is fixedly connected with the internally threaded cylinder, and the installation column is threadedly installed in the inner wall of the internally threaded cylinder.

[0008] Preferably, during use, since the bracket is in a T shape, installation columns with the same weight can be installed on the inner walls of two internally threaded cylinders that are symmetric with respect to the center of the bracket according to the weight required for the test, which is beneficial to maintaining the balance of the unmanned aerial vehicle test mechanism and improving the accuracy of the test. Then, the wireless control mechanism is controlled through the remote control mechanism, so that the unmanned aerial vehicle test mechanism takes off. By turning on the heating mechanism in the high and low temperature chamber, the high and low temperature chamber can be quickly heated, and by turning on the air conditioner, the temperature in the high and low temperature chamber can be heated or cooled, solving the problem that in the prior art, it is difficult for the MEMS inertial navigation test system to make the MEMS inertial navigation test device installed on the fuselage of the unmanned aerial vehicle in the environment of the high and low temperature chamber, and realizing the performance test of the test unmanned aerial vehicle by the MEMS inertial navigation test device at different heights and different takeoff weights.

[0009] As a preference, the temperature measuring mechanism includes a second bottom block and a temperature detector; two second bottom blocks are fixedly connected to the bottom surface of the inner wall of the high and low temperature chamber, the two second bottom blocks are symmetric with respect to the center of the high and low temperature chamber, and temperature detectors are fixedly connected to the upper ends of the second bottom blocks in a uniformly distributed manner.

[0010] As a preference, the wireless control mechanism includes a groove body, a second fixing block, a controller, a storage battery and a wireless transceiver; a groove body is penetrated and opened on the side wall of the first bottom block, a second fixing block is fixedly connected to the inner wall of the groove body, a controller, a storage battery and a wireless transceiver are arranged inside the second fixing block, and the unmanned aerial vehicle test mechanism and the wireless control mechanism are electrically connected.

[0011] Preferably, the remote control mechanism includes a carrier board and a remote controller; the side wall of the high and low temperature chamber is fixedly connected with a carrier board, and the upper end of the carrier board is provided with a remote controller which is adapted to the wireless transceiver.

[0012] Preferably, the UAV test mechanism includes a central column, a support arm, a motor, a wing, a bearing disc, a fixing frame and a threaded column; a central column is arranged inside the high and low temperature chamber, six uniformly distributed support arms are fixedly connected to the side wall of the central column, a motor is fixedly connected to the upper end of the support arm, a wing is fixedly connected to the upper end of the output shaft of the motor, a bearing disc is fixedly connected to the upper end of the central column, a fixing frame is fixedly connected to the upper end of the bearing disc, a threaded column is threadedly installed through the side wall of the fixing frame, the side wall of the MEMS inertial navigation test device is attached to the inner wall of the fixing frame, and the threaded column is also threadedly installed in the wall layer of the MEMS inertial navigation test device.

[0013] Preferably, the camera mechanism includes a long board and a camera; a long board is fixedly connected to the middle of the rear end of the inner wall of the high and low temperature chamber, and a plurality of cameras are fixedly connected to the front end of the long board, and the cameras are uniformly distributed at the front end of the long board.

[0014] Preferably, one end of the mounting column is fixedly connected with a fixing column, the side wall of the fixing column is provided with threads, two second fixing plates are fixedly connected to the side wall of the first bottom block, and two legs are fixedly connected to the lower ends of the second fixing plates.

[0015] Preferably, the heating mechanism includes a first fixing plate, a first fixing block and an air heating pipe; the first fixing plates are fixedly connected to the left and right sides of the inner wall of the high and low temperature chamber, two first fixing blocks are fixedly connected to one end of the first fixing plate close to the center of the high and low temperature chamber, and a plurality of air heating pipes are fixedly connected to the common end of the two first fixing blocks on the same side close to each other.

[0016] The beneficial effects of the present utility model: by setting a bracket in the shape of a Chinese character 'tu', mounting columns with the same weight can be installed on the inner walls of two inner threaded cylinders symmetrical about the center of the bracket according to the weight required for the test, which is beneficial to maintaining the balance of the UAV test mechanism and improving the accuracy of the test. Then, the wireless control mechanism is controlled by the remote control mechanism to make the UAV test mechanism take off. The heating mechanism in the high and low temperature chamber can be turned on to quickly heat the high and low temperature chamber, and the air conditioner can be turned on to heat or cool the temperature in the high and low temperature chamber, solving the problem that it is difficult for the existing MEMS inertial navigation test system to install the MEMS inertial navigation test device on the fuselage of the UAV in the environment of the high and low temperature chamber and realizing the performance test of the test UAV by the MEMS inertial navigation test device at different heights and different take-off weights. Description of the Drawings

[0017] Figure 1 Shown is a three-dimensional structural schematic diagram of a high-precision high and low temperature chamber applicable to a MEMS inertial navigation test system of the present utility model;

[0018] Figure 2 What is shown is a three-dimensional structural schematic diagram of a high-precision high-low temperature box suitable for a MEMS inertial navigation test system of the utility model;

[0019] Figure 3 The three-dimensional structure schematic diagram of the heating mechanism and the camera mechanism of a high-precision high and low temperature box suitable for a MEMS inertial navigation test system of the utility model is shown;

[0020] Figure 4 What is shown is a first three-dimensional structural schematic diagram of a UAV testing mechanism of a high-precision high and low temperature box suitable for a MEMS inertial navigation test system of the utility model;

[0021] Figure 5 Shown is a second three-dimensional structural schematic diagram of a UAV test mechanism of a high-precision high and low temperature box suitable for a MEMS inertial navigation test system of the utility model;

[0022] Figure 6 What is shown is a three-dimensional structural schematic diagram of a wireless control mechanism of a high-precision high and low temperature box suitable for a MEMS inertial navigation test system of the utility model;

[0023] Figure 7 What is shown is a three-dimensional structural schematic diagram of a weighting mechanism of a high-precision high and low temperature box suitable for a MEMS inertial navigation test system according to the utility model.

[0024] The marks in the attached drawings are: 1. high and low temperature box; 2. installation cover; 3. UAV test mechanism; 301. center column; 302. support arm; 303. motor; 304. wing; 305. bearing plate; 306. fixing frame; 307. MEMS inertial navigation test equipment; 308. threaded column; 309. first bottom block; 4. bearing plate; 5. remote control; 6. air conditioner; 7. observation slot; 8. transparent glass plate; 9. first fixing plate; 10. First fixed block; 11. Air heating pipe; 12. Long board; 13. Camera; 14. Tank; 15. Second fixed block; 16. Controller; 17. Storage battery; 18. Wireless transceiver; 19. Second fixed plate; 20. Support leg; 21. Long column; 22. Third fixed block; 23. Bracket; 24. Arc block; 25. Internal threaded barrel; 26. Mounting column; 27. Fixed column; 28. Second bottom block; 29. ​​Thermometer. DETAILED DESCRIPTION

[0025] The utility model is further described below in conjunction with the accompanying drawings and embodiments.

[0026] See also Figure 1-Figure 7, the present utility model provides an embodiment: a high-precision high and low temperature chamber applicable to a MEMS inertial navigation test system, including a high and low temperature chamber 1; an installation cover plate 2 is placed on the upper end of the high and low temperature chamber 1, heating mechanisms are arranged on both the left and right sides of the inner wall of the high and low temperature chamber 1, a camera mechanism is arranged at the rear end of the inner wall of the high and low temperature chamber 1, two air conditioners 6 are fixedly connected to the upper part of the front end of the inner wall of the high and low temperature chamber 1, observation slots 7 are贯穿ly opened at both the front and rear ends of the high and low temperature chamber 1, transparent glass plates 8 are fixedly connected to the inner walls of the observation slots 7, a remote control mechanism is arranged on the side wall of the high and low temperature chamber 1, a first bottom block 309 is installed at the lower end of the unmanned aerial vehicle test mechanism 3, a wireless control mechanism is arranged inside the first bottom block 309, a weight increasing mechanism is arranged at the lower end of the first bottom block 309, a MEMS inertial navigation test device 307 is installed at the upper end of the unmanned aerial vehicle test mechanism 3, and a temperature measuring mechanism is arranged on the bottom surface of the inner wall of the high and low temperature chamber 1;

[0027] The weight increasing mechanism includes a long column 21, a third fixing block 22, a bracket 23, an arc-shaped block 24, an internal thread cylinder 25 and an installation column 26; the long column 21 is fixedly connected to the lower end of the first bottom block 309, the third fixing block 22 is fixedly connected to the lower end of the long column 21, the bracket 23 is fixedly connected to the lower end of the third fixing block 22, the bracket 23 is in a T shape, arc-shaped blocks 24 are fixedly connected to the lower end and four end parts of the bracket 23, the internal thread cylinder 25 is fixedly connected to the inner wall of the arc-shaped block 24, and the installation column 26 is threadedly installed on the inner wall of the internal thread cylinder 25.

[0028] During use, since the bracket 23 is in a T shape, installation columns 26 with the same weight can be installed on the inner walls of two internal thread cylinders 25 that are symmetrically arranged with respect to the center of the bracket 23 according to the required weight for testing, which is beneficial to maintaining the balance of the unmanned aerial vehicle test mechanism 3 and improving the accuracy of the test. Then, the wireless control mechanism is controlled through the remote control mechanism, so that the unmanned aerial vehicle test mechanism 3 takes off. The heating mechanism in the high and low temperature chamber 1 can be turned on to quickly heat the high and low temperature chamber 1, and the air conditioner 6 can be turned on to heat or cool the temperature in the high and low temperature chamber 1.

[0029] Please refer to Figure 1 and Figure 2 , in this embodiment, the temperature measuring mechanism includes a second bottom block 28 and a temperature detector 29; two second bottom blocks 28 are fixedly connected to the bottom surface of the inner wall of the high and low temperature chamber 1, the two second bottom blocks 28 are symmetrically arranged with respect to the center of the high and low temperature chamber 1, temperature detectors 29 are fixedly connected to the upper ends of the second bottom blocks 28 in a uniformly distributed manner. Turning on the temperature detectors 29 can quickly measure the temperature in different regions of the high and low temperature chamber 1, so as to conveniently test the state of the MEMS inertial navigation test device 307 when the unmanned aerial vehicle test mechanism 3 takes off at different temperatures.

[0030] Please refer to Figure 1 and Figure 6In this embodiment, the wireless control mechanism includes a slot body 14, a second fixed block 15, a controller 16, a battery 17 and a wireless transceiver 18; the side wall of the first bottom block 309 is penetrated by a slot body 14, the inner wall of the slot body 14 is fixedly connected to the second fixed block 15, and the inside of the second fixed block 15 is provided with a controller 16, a battery 17 and a wireless transceiver 18. The UAV test mechanism 3 is electrically connected to the wireless control mechanism, and the UAV test mechanism 3 can be wirelessly controlled by the controller 16, the battery 17 and the wireless transceiver 18.

[0031] See also Figure 1 and Figure 6 In this embodiment, the remote control mechanism includes a carrying plate 4 and a remote control 5; the side wall of the high and low temperature box 1 is fixedly connected with the carrying plate 4, and the upper end of the carrying plate 4 is placed with the remote control 5 and the wireless transceiver 18. The remote control 5 and the wireless transceiver 18 can be paired, and the remote control 5 can be used to remotely control the UAV test mechanism 3 to take off, and various data of the UAV test mechanism 3 when taking off can be tested.

[0032] See also Figure 1 , Figure 4 and Figure 5 In this embodiment, the UAV test mechanism 3 includes a central column 301, an arm 302, a motor 303, a wing 304, a bearing plate 305, a fixing frame 306 and a threaded column 308; the high and low temperature box 1 is provided with a central column 301 inside, the side wall of the central column 301 is fixedly connected with six evenly distributed arms 302, the upper end of the arm 302 is fixedly connected with the motor 303, the upper end of the output shaft of the motor 303 is fixedly connected with the wing 304, the upper end of the central column 301 is fixedly connected with the bearing plate 305, the upper end of the bearing plate 305 is fixedly connected with the fixing frame 306, and the side wall of the fixing frame 306 is penetrated The through-thread installation has a threaded column 308, the side wall of the MEMS inertial navigation test device 307 and the inner wall of the fixed frame 306 are fitted, and the threaded column 308 is also threadedly installed in the wall layer of the MEMS inertial navigation test device 307. The MEMS inertial navigation test device 307 is placed on the inner wall of the fixed frame 306, and then the threaded column 308 is threadedly installed in the wall layer of the fixed frame 306 and the MEMS inertial navigation test device 307. The MEMS inertial navigation test device 307 can be fixed on the inner wall of the fixed frame 306, thereby facilitating the rapid installation and fixation of the MEMS inertial navigation test device 307.

[0033] See also Figure 1-Figure 3 In this embodiment, the camera mechanism includes a long board 12 and a camera 13; the long board 12 is fixedly connected to the middle of the rear end of the inner wall of the high and low temperature box 1, and a plurality of cameras 13 are fixedly connected to the front end of the long board 12. The cameras 13 are evenly distributed at the front end of the long board 12. By turning on a plurality of cameras 13, it is convenient to shoot and record the flight path of the UAV test mechanism 3.

[0034] Please refer to Figure 1 、 Figure 6 and Figure 7 In this embodiment, one end of the mounting post 26 is fixedly connected to a fixing post 27. The side wall of the fixing post 27 is provided with threads. Two second fixing plates 19 are fixedly connected to the side wall of the first bottom block 309. Two legs 20 are fixedly connected to the lower ends of the second fixing plates 19. By providing the fixing post 27, it is convenient to manually rotate the fixing post 27 to remove the mounting post 26 from the inner wall of the internal thread cylinder 25 during use, facilitating the quick disassembly and assembly of the mounting post 26.

[0035] Please refer to Figure 1 and Figure 3 In this embodiment, the heating mechanism includes a first fixing plate 9, a first fixing block 10, and an air heating tube 11. Both the left and right sides of the inner wall of the high and low temperature box 1 are fixedly connected to the first fixing plate 9. Two first fixing blocks 10 are fixedly connected to the end of the first fixing plate 9 close to the center of the high and low temperature box 1. A plurality of air heating tubes 11 are fixedly connected together at the ends of the two first fixing blocks 10 on the same side that are close to each other. When it is necessary to accelerate the temperature rise, turning on the air heating tube 11 can increase the speed of temperature rise inside the high and low temperature box 1.

[0036] Working principle: First, place the MEMS inertial navigation test device 307 on the inner wall of the fixing frame 306, and then thread the threaded column 308 into the wall layers of the fixing frame 306 and the MEMS inertial navigation test device 307, so that the MEMS inertial navigation test device 307 can be fixed on the inner wall of the fixing frame 306, thus facilitating the quick installation and fixation of the MEMS inertial navigation test device 307.

[0037] Since the bracket 23 is in a T shape, mounting posts 26 with the same weight can be installed on the inner walls of two internal thread cylinders 25 that are symmetric about the center of the bracket 23 according to the weight required for the test, which helps to maintain the balance of the UAV test mechanism 3 and improves the accuracy of the test. During the test, select a mounting post 26 with an appropriate weight according to the requirements and install it on the inner wall of the internal thread cylinder 25.

[0038] Then, the remote control mechanism is used to control the wireless control mechanism to make the UAV test mechanism 3 take off. Specifically, pair the remote control 5 with the wireless transceiver 18, and then the UAV test mechanism 3 can be remotely controlled to take off through the remote control 5, and various data during the takeoff of the UAV test mechanism 3 can be tested.

[0039] Turning on the heating mechanism inside the high and low temperature box 1 can quickly heat the inside of the high and low temperature box 1. When it is necessary to accelerate the temperature rise, turning on the air heating tube 11 can increase the speed of temperature rise inside the high and low temperature box 1. Turning on the air conditioner 6 can heat or cool the temperature inside the high and low temperature box 1.

[0040] Turning on the temperature detector 29 can quickly measure the temperature of different areas in the high and low temperature box 1, so as to facilitate testing the state of the MEMS inertial navigation test equipment 307 when the drone test mechanism 3 takes off at different temperatures;

[0041] By turning on multiple cameras 13, the distance of the UAV test mechanism 3 during flight can be measured, thereby facilitating the filming and recording of the flight path of the UAV test mechanism 3.

[0042] The embodiments of the present invention are described in detail above in conjunction with the accompanying drawings, but the present invention is not limited to the above embodiments, and various changes can be made within the knowledge scope of those skilled in the art without departing from the purpose of the present invention.

Claims

1. A high-precision high-low temperature box suitable for a MEMS inertial navigation test system, comprising a high-low temperature box (1); characterized in that: An installation cover plate (2) is placed on the upper end of the high and low temperature chamber (1). Heating mechanisms are arranged on both the left and right sides of the inner wall of the high and low temperature chamber (1). A camera mechanism is provided at the rear end of the inner wall of the high and low temperature chamber (1). Two air conditioners (6) are fixedly connected to the upper part of the front end of the inner wall of the high and low temperature chamber (1). Observation slots (7) are贯穿 opened at both the front and rear ends of the high and low temperature chamber (1). A transparent glass plate (8) is fixedly connected to the inner wall of the observation slot (7). A remote control mechanism is arranged on the side wall of the high and low temperature chamber (1). A first bottom block (309) is installed at the lower end of the unmanned aerial vehicle testing mechanism (3). A wireless control mechanism is arranged inside the first bottom block (309). A weight adding mechanism is arranged at the lower end of the first bottom block (309). A MEMS inertial navigation testing device (307) is installed at the upper end of the unmanned aerial vehicle testing mechanism (3). A temperature measuring mechanism is arranged on the bottom surface of the inner wall of the high and low temperature chamber (1). The weight adding mechanism includes a long column (21), a third fixing block (22), a bracket (23), an arc-shaped block (24), an internally threaded cylinder (25), and a mounting column (26). The long column (21) is fixedly connected to the lower end of the first bottom block (309). The third fixing block (22) is fixedly connected to the lower end of the long column (21). The bracket (23) is fixedly connected to the lower end of the third fixing block (22). The bracket (23) is in the shape of a Chinese character 'tu'. The lower end and four ends of the bracket (23) are fixedly connected with arc-shaped blocks (24). The internally threaded cylinder (25) is fixedly connected to the inner wall of the arc-shaped block (24). The mounting column (26) is threadedly installed on the inner wall of the internally threaded cylinder (25).

2. The high-precision high and low temperature box suitable for MEMS inertial navigation test system according to claim 1, characterized in that: The temperature measuring mechanism includes a second bottom block (28) and a temperature detector (29). Two second bottom blocks (28) are fixedly connected to the bottom surface of the inner wall of the high and low temperature chamber (1). The two second bottom blocks (28) are symmetric with respect to the center of the high and low temperature chamber (1). The temperature detectors (29) are fixedly connected to the upper ends of the second bottom blocks (28) in a uniformly distributed manner.

3. The high-precision high and low temperature box suitable for MEMS inertial navigation test system according to claim 1, characterized in that: The wireless control mechanism includes a groove body (14), a second fixing block (15), a controller (16), a storage battery (17), and a wireless transceiver (18). A groove body (14) is贯穿 opened on the side wall of the first bottom block (309). The second fixing block (15) is fixedly connected to the inner wall of the groove body (14). The controller (16), the storage battery (17), and the wireless transceiver (18) are arranged inside the second fixing block (15). The unmanned aerial vehicle testing mechanism (3) is electrically connected to the wireless control mechanism.

4. The high-precision high and low temperature box suitable for MEMS inertial navigation test system according to claim 1, characterized in that: The remote control mechanism includes a carrier plate (4) and a remote controller (5). The carrier plate (4) is fixedly connected to the side wall of the high and low temperature chamber (1). The remote controller (5) is placed on the upper end of the carrier plate (4). The remote controller (5) is adapted to the wireless transceiver (18).

5. The high-precision high and low temperature box suitable for MEMS inertial navigation test system according to claim 1, characterized in that: The unmanned aerial vehicle testing mechanism (3) comprises a central column (301), a support arm (302), a motor (303), a wing (304), a bearing plate (305), a fixing frame (306) and a threaded column (308); the interior of the high and low temperature box (1) is provided with a central column (301), the side wall of the central column (301) is fixedly connected to six evenly distributed support arms (302), the upper end of the support arm (302) is fixedly connected to the motor (303), and the output shaft of the motor (303) is The upper end of the central column (301) is fixedly connected to a wing (304), the upper end of the central column (301) is fixedly connected to a carrier plate (305), the upper end of the carrier plate (305) is fixedly connected to a fixed frame (306), a threaded column (308) is threadedly installed on the side wall of the fixed frame (306), the side wall of the MEMS inertial navigation test equipment (307) is fitted with the inner wall of the fixed frame (306), and the threaded column (308) is also threadedly installed in the wall layer of the MEMS inertial navigation test equipment (307).

6. The high-precision high and low temperature box suitable for MEMS inertial navigation test system according to claim 1, characterized in that: The camera mechanism comprises a long plate (12) and a camera (13); the long plate (12) is fixedly connected to the middle of the rear end of the inner wall of the high and low temperature box (1), and a plurality of cameras (13) are fixedly connected to the front end of the long plate (12); the cameras (13) are evenly distributed at the front end of the long plate (12).

7. The high-precision high and low temperature box suitable for MEMS inertial navigation test system according to claim 6, characterized in that: One end of the mounting column (26) is fixedly connected to a fixing column (27), the side wall of the fixing column (27) is provided with patterns, the side wall of the first bottom block (309) is fixedly connected to two second fixing plates (19), and the lower end of the second fixing plate (19) is fixedly connected to two legs (20).

8. The high-precision high and low temperature box suitable for MEMS inertial navigation test system according to claim 1, characterized in that: The heating mechanism comprises a first fixing plate (9), a first fixing block (10) and an air heating pipe (11); the first fixing plates (9) are fixedly connected to both left and right sides of the inner wall of the high and low temperature box (1); one end of the first fixing plate (9) close to the center of the high and low temperature box (1) is fixedly connected to two first fixing blocks (10); and the ends of the two first fixing blocks (10) on the same side close to each other are commonly fixedly connected to a plurality of air heating pipes (11).

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