Low-orbit aircraft environment test tool clamp and equipment

Abstract

The utility model discloses a low orbit aircraft environment test work fixture and equipment, comprising a placing table, the center of the top of the base is fixedly connected with a motor, the output end of the motor is fixedly connected with the placing table, the outer side of the top of the placing table is fixedly connected with a plurality of electric push rods, the tail ends of the electric push rods are fixedly connected with clamping plates, and the clamping plates are fixedly connected with the clamping plates. Lifting rods are fixedly connected to the two ends of the top of the base, the top ends of the two lifting rods are fixedly connected with the same arc-shaped frame, an electric sliding rail is arranged in the middle of the arc-shaped frame, a movable frame is slidably connected to the electric sliding rail, and a fan is fixedly connected to the bottom of the movable frame. According to the utility model, by starting the motor, the placement table can be rotated, and steering adjustment can be conveniently carried out on the fixed aircraft model, so that the aircraft model can feel wind resistance in different directions, the comprehensiveness of the test is further improved, and the test is more detailed and accurate; and the rotation stability of the placement table can be ensured.

Description

Technical Field

[0001] This utility model belongs to the field of experimental tooling and fixture technology, specifically a tooling and fixture and equipment for environmental testing of low-orbit aircraft. Background Technology

[0002] Low Earth Orbit (LEO) vehicles are spacecraft that operate in low Earth orbit at an altitude of several hundred kilometers above the ground. They are mainly used to build satellite internet, such as the Starlink project, to provide high-speed and stable internet access services globally, solving network coverage problems in remote areas. They can also achieve high-resolution Earth observation for military reconnaissance, land resource surveys, urban planning, environmental protection, disaster monitoring, and other fields. They can quickly obtain detailed information about ground targets, which helps to carry out research in fields such as space physics, earth science, and astronomy, such as observing the Earth's magnetic field, atmospheric phenomena, and cosmic rays, providing important data support for scientific research. To ensure the safety of LEO vehicles, small spacecraft and experimental equipment are often used for simulation during manufacturing.

[0003] In the prior art, Chinese patent CN221936580U discloses a fixing fixture for assembling an aircraft simulator, including a side plate, a connecting column fixedly connected to the bottom of the side plate, a base fixedly connected to the bottom of the connecting column, a clamping device on the side plate, and a fitting device on the side plate; the clamping device includes a slide rod, which is fixedly connected to the left side of the side plate, a fixing block fixedly sleeved on the outer wall of the slide rod, a fixing plate fixedly connected to the back of the fixing block, and a sliding plate slidably connected to the outer wall of the slide rod. By activating a hydraulic cylinder, the output end of the hydraulic cylinder drives a telescopic rod, which drives the sliding plate to slide on the outer wall of the slide rod. When the sliding plate moves towards the fixing plate, it drives a movable rod to push a rotating block, which rotates counterclockwise. The counterclockwise rotation of the rotating block drives the sliding plate on the right side towards the fixing plate. The sliding plate drives the connecting block, which drives the clamping plate to clamp the shell.

[0004] However, the fixed fixture for assembling the aircraft simulator provided in the above technical solution still has many shortcomings in actual use. For example, after the device clamps and fixes the aircraft, it is not convenient to adjust the aircraft's direction, which makes it impossible to simulate wind resistance in different directions during simulated flight, resulting in insufficient test detail and poor practicality. Utility Model Content

[0005] The purpose of this section is to outline some aspects of embodiments of the present invention and to briefly describe some preferred embodiments. Simplifications or omissions may be made in this section, as well as in the abstract and title of this application, to avoid obscuring the purpose of these documents; however, such simplifications or omissions should not be construed as limiting the scope of the present invention.

[0006] To address the problem mentioned in the background art that the experimental fixtures and equipment, after clamping and fixing the aircraft, are not convenient for adjusting the aircraft's direction, resulting in the inability to simulate wind resistance in different directions during simulated flight, leading to insufficiently detailed tests and poor practicality, this utility model adopts the following technical solution.

[0007] A fixture for environmental testing of low-orbit aircraft includes a platform. A motor is fixedly connected to the top center of the platform, and the output end of the motor is fixedly connected to the platform. Multiple electric push rods are fixedly connected to the top outer side of the platform, and clamping plates are fixedly connected to the ends of the electric push rods.

[0008] Preferably, the vertical center line of the base coincides with the vertical center of the motor, the multiple electric push rods are evenly distributed in a ring about the vertical center line of the placement platform, and the horizontal center line of the clamping plate coincides with the central axis of the electric push rods.

[0009] Preferably, the top of the base is provided with an annular groove, the central axis of the annular groove coincides with the vertical center line of the placement platform, and multiple sliding rods are connected to the inner groove of the annular groove, the top of the sliding rods being fixedly connected to the bottom of the placement platform.

[0010] Preferably, the base has pads fixedly connected to the four corners of its bottom, the pads are symmetrical about the vertical center line of the base, and the sliding rods are evenly distributed in a ring about the vertical center line of the annular groove.

[0011] A low-orbit aircraft environmental testing device, wherein lifting rods are fixedly connected to both ends of the top of the base, and the top of the two lifting rods are fixedly connected to the same arc-shaped frame. An electric slide rail is provided in the middle of the arc-shaped frame, and a movable frame is slidably connected on the electric slide rail. A fan is fixedly connected to the bottom of the movable frame.

[0012] Preferably, the lifting rod is symmetrical about the vertical center line of the base, the outer side of the movable frame is in contact with the inner side of the arc-shaped frame, and the vertical center line of the arc-shaped frame coincides with the vertical center line of the placement platform.

[0013] Preferably, the base has side plates on both sides, and the side plates and the base form an integrated structure. A humidifier is threadedly connected to the top of the side plate, and the humidifier passes through the side plate. The side plate and the humidifier are symmetrical about the vertical center line of the base.

[0014] Compared with the prior art, the beneficial effects of this utility model are as follows:

[0015] This invention enables the placement platform to rotate by starting the motor, facilitating the steering adjustment of the fixed aircraft model. This allows the aircraft model to experience wind resistance in different directions, further enhancing the comprehensiveness of the experiment and making it more detailed and accurate. The combined use of the annular groove and the sliding rod ensures the stability of the placement platform's rotation. The combined use of the electric slide rail and the slider allows the movable frame to be moved, facilitating the adjustment of the fan's position and enabling airflow from different directions on the aircraft. The height of the arc-shaped frame can be adjusted via the lifting rod, facilitating the adjustment of the fan's height. Attached Figure Description

[0016] Figure 1 This is a schematic diagram of the overall three-dimensional structure of this utility model;

[0017] Figure 2 This is a partial three-dimensional structural schematic diagram of the present invention;

[0018] Figure 3 This is a schematic diagram of the bottom three-dimensional structure of this utility model;

[0019] Figure 4 This is a top view of the overall structure of this utility model;

[0020] Figure 5 This is a three-dimensional structural diagram of the base of this utility model.

[0021] The correspondence between the labels and component names in the attached figures is as follows:

[0022] 1. Base; 2. Motor; 3. Placement platform; 4. Electric push rod; 5. Clamping plate; 6. Circular groove; 7. Slide rod; 8. Foot pad; 9. Lifting rod; 10. Arc frame; 11. Electric slide rail; 12. Movable frame; 13. Fan; 14. Side plate; 15. Humidifier. Detailed Implementation

[0023] To make the above-mentioned objectives, features and advantages of this utility model more apparent and understandable, the specific embodiments of this utility model will be described in detail below with reference to the accompanying drawings.

[0024] Many specific details are set forth in the following description in order to provide a full understanding of the present invention. However, the present invention may also be implemented in other ways different from those described herein. Those skilled in the art can make similar extensions without departing from the spirit of the present invention. Therefore, the present invention is not limited to the specific embodiments disclosed below.

[0025] Secondly, the term "an embodiment" or "embodiment" as used herein refers to a specific feature, structure, or characteristic that may be included in at least one implementation of the present invention. The phrase "in one embodiment" appearing in different places in this specification does not necessarily refer to the same embodiment, nor is it a single or selective embodiment that excludes other embodiments. The present invention provides the following embodiments.

[0026] Please see Figure 1-5 One embodiment of this utility model is a low-orbit aircraft environmental testing fixture, which includes a base 1. The four corners of the bottom of the base 1 are fixedly connected with pads 8. The pads 8 are symmetrical about the vertical center line of the base 1. The sliding rods 7 are evenly distributed in a ring about the vertical center line of the annular groove 6. The pads 8 can support the device on the external horizontal surface and prevent wear between the bottom surface of the base 1 and the external horizontal surface.

[0027] In this embodiment, a motor 2 is fixedly connected to the top center of the base 1, and a placement platform 3 is fixedly connected to the output end of the motor 2. Multiple electric push rods 4 are fixedly connected to the top outer side of the placement platform 3, and a clamping plate 5 is fixedly connected to the end of the electric push rods 4. The vertical center line of the base 1 coincides with the vertical center of the motor 2. The multiple electric push rods 4 are evenly distributed in a ring about the vertical center line of the placement platform 3. The horizontal center line of the clamping plate 5 coincides with the central axis of the electric push rods 4. The test aircraft model can be placed on the placement platform 3. The electric push rods 4 are used to make the clamping plate 5 abut against the aircraft on the placement platform 3. The placement platform 3 is equipped with multiple electric push rods 4 and clamping plates 5, which can clamp and fix the aircraft model, making it convenient to conduct experiments on the aircraft model.

[0028] A low-orbit aircraft environmental testing device includes a base 1 with lifting rods 9 fixedly connected to both ends of the top. The top ends of the two lifting rods 9 are fixedly connected to the same arc-shaped frame 10. An electric slide rail 11 is set in the middle of the arc-shaped frame 10, and a movable frame 12 is slidably connected to the electric slide rail 11. A fan 13 is fixedly connected to the bottom of the movable frame 12. Side plates 14 are set on both sides of the base 1, and the side plates 14 and the base 1 form an integrated structure. A humidifier 15 is threadedly connected to the top of the side plate 14 and passes through the side plate 14. The side plate 14 and the humidifier 15 are symmetrical about the vertical center line of the base 1. The fan 13 can blow air on the aircraft model to measure the wind resistance. The humidifier 15 can adjust the air humidity around the placement platform 3, making the test more comprehensive and detailed. Rotating the humidifier 15 can separate the humidifier 15 from the side plate 14 for easy replacement.

[0029] In this embodiment, the top of the base 1 is provided with an annular groove 6, the central axis of the annular groove 6 coincides with the vertical center line of the placement platform 3, and multiple sliding rods 7 are connected to the internal sliding groove of the annular groove 6. The top of the sliding rods 7 is fixedly connected to the bottom of the placement platform 3. By starting the motor 2, the placement platform 3 can be rotated, which facilitates the steering adjustment of the fixed aircraft model, so that the aircraft model can feel the wind resistance in different directions, further improving the comprehensiveness of the test and making the test more detailed and accurate. The combined use of the annular groove 6 and the sliding rods 7 can ensure the stability of the rotation of the placement platform 3.

[0030] In this embodiment, the lifting rod 9 is symmetrical about the vertical center line of the base 1. The outer side of the movable frame 12 is in contact with the inner side of the arc frame 10. The vertical center line of the arc frame 10 coincides with the vertical center line of the placement platform 3. By using the electric slide rail 11 and the slider, the movable frame 12 can be moved, which facilitates the adjustment of the position of the fan 13 and enables air to blow in different directions of the aircraft. The height of the arc frame 10 can be adjusted by the lifting rod 9, which facilitates the adjustment of the height of the fan 13.

[0031] Working principle: When using this device, the pads 8 first support the device on a horizontal surface to prevent wear between the bottom of the base 1 and the horizontal surface. The test aircraft model can be placed on the platform 3. The electric push rods 4 make the clamping plate 5 abut against the aircraft on the platform 3. The platform 3 is equipped with multiple electric push rods 4 and clamping plates 5 to hold and fix the aircraft model, which is convenient for conducting experiments on the aircraft model. The fan 13 blows air on the aircraft model to measure wind resistance. The humidifier 15 can adjust the air humidity around the platform 3 to make the experiment more comprehensive and detailed. Rotating the humidifier 15 can separate the humidifier 15 from the side plate 14 for easy replacement of the humidifier 15.

[0032] By starting motor 2, the placement platform 3 can be rotated, which facilitates the steering adjustment of the fixed aircraft model. This allows the aircraft model to experience wind resistance in different directions, further improving the comprehensiveness of the test and making the test more detailed and accurate. The combined use of annular groove 6 and slide bar 7 can ensure the stability of the rotation of placement platform 3. The combined use of electric slide rail 11 and slider can move movable frame 12, which facilitates the adjustment of the position of fan 13 and can blow air in different directions on the aircraft. The height of arc frame 10 can be adjusted by lifting rod 9, which facilitates the adjustment of the height of fan 13.

[0033] The above description, in conjunction with specific embodiments, provides a further detailed explanation of the present utility model. It should not be construed that the specific implementation of the present utility model is limited to these descriptions. For those skilled in the art, several simple deductions or substitutions can be made without departing from the concept of the present utility model, and all such deductions or substitutions should be considered to fall within the scope of protection defined by the claims submitted by the present utility model.

Claims

1. A low orbit aircraft environmental test fixture clamp comprising a base (1) characterised in that: A motor (2) is fixedly connected to the top center of the base (1), and a placement platform (3) is fixedly connected to the output end of the motor (2). Multiple electric push rods (4) are fixedly connected to the top outer side of the placement platform (3), and a clamping plate (5) is fixedly connected to the end of the electric push rod (4).

2. The low earth orbit vehicle environmental test fixture clamp of claim 1, wherein: The vertical center line of the base (1) coincides with the vertical center of the motor (2), and the multiple electric push rods (4) are evenly distributed in a ring about the vertical center line of the placement platform (3). The horizontal center line of the clamp (5) coincides with the central axis of the electric push rods (4).

3. The low earth orbit vehicle environmental test fixture clamp of claim 2, wherein: The base (1) has an annular groove (6) on its top. The central axis of the annular groove (6) coincides with the vertical center line of the placement platform (3). Multiple sliding rods (7) are connected to the internal sliding groove of the annular groove (6). The top of the sliding rod (7) is fixedly connected to the bottom of the placement platform (3).

4. The low earth orbit vehicle environmental test fixture clamp of claim 3, wherein: The base (1) has four fixed feet (8) at its bottom corners. The feet (8) are symmetrical about the vertical center line of the base (1), and the sliding rods (7) are evenly distributed in a ring about the vertical center line of the annular groove (6).

5. A low-orbit aircraft environmental test device applied to the low-orbit aircraft environmental test tooling fixture of any one of claims 1-4, characterized in that: The base (1) has lifting rods (9) fixedly connected to both ends of the top. The top ends of the two lifting rods (9) are fixedly connected to the same arc frame (10). An electric slide rail (11) is provided in the middle of the arc frame (10). A movable frame (12) is slidably connected on the electric slide rail (11). A fan (13) is fixedly connected to the bottom of the movable frame (12).

6. The low earth orbit vehicle environmental test apparatus of claim 5, wherein: The lifting rod (9) is symmetrical about the vertical center line of the base (1), the outer side of the movable frame (12) is in contact with the inner side of the arc frame (10), and the vertical center line of the arc frame (10) coincides with the vertical center line of the placement platform (3).

7. The low earth orbit vehicle environmental test apparatus of claim 6, wherein: Both sides of the base (1) are provided with side plates (14), and the side plates (14) and the base (1) form an integrated structure. A humidifier (15) is threadedly connected to the top of the side plate (14), and the humidifier (15) passes through the side plate (14). The side plate (14) and the humidifier (15) are symmetrical about the vertical center line of the base (1).

Images