Satellite structure

Abstract

The embodiment of the application provides a satellite structure, and relates to the technical field of spaceflight equipment. The satellite structure comprises: a main frame; a cabin plate; and a connecting assembly arranged between the main frame and the cabin plate. The cabin plate is movably arranged on the main frame through the connecting assembly and is fixed to any position after movement through the connecting assembly. The satellite structure can improve the test efficiency of electronic equipment during ground heat dissipation test.

Description

Technical Field

[0001] This application relates to the field of aerospace equipment technology, and in particular to a satellite structure. Background Technology

[0002] A satellite is an artificial celestial body that operates in space, primarily used for tasks such as communication, navigation, meteorological observation, Earth resource exploration, and scientific research. By carrying various electronic devices, satellites utilize their position in their orbit to accomplish various tasks.

[0003] In related technologies, the satellite structure includes a main frame and a compartment. Multiple electronic devices are installed inside the main frame, and the compartment is located on one side of the main frame for opening and closing the main frame. When conducting heat dissipation tests on the multiple electronic devices inside the main frame on the ground, fans are usually used to assist in heat dissipation. By placing the fan inside the main frame, the fan can carry away the heat generated by the electronic devices through air convection, thereby reducing the temperature of the devices.

[0004] However, in order to achieve air circulation within the main frame, the compartment panel needs to be removed from the main frame for each test. When electronic equipment is installed on the compartment panel, the connecting cable between the electronic equipment on the compartment panel and the electronic equipment in the main frame will be insufficient in length, and the test cable needs to be replaced. This process reduces the testing efficiency. Utility Model Content

[0005] This application provides a satellite structure to solve the technical problem that satellite structures in related technologies require the removal of the cabin panel during testing, resulting in insufficient cable length for connecting electronic devices on the cabin panel to electronic devices in the main frame, thus reducing testing efficiency.

[0006] This application provides a satellite structure, including:

[0007] Main framework;

[0008] hatch;

[0009] A connecting component is disposed between the main frame and the cabin panel. The cabin panel is movably mounted on the main frame via the connecting component and fixed to any movable position via the connecting component.

[0010] In some embodiments, the connecting assembly includes a hinge and a fastener, both of which are disposed between the main frame and the cabin panel. The cabin panel is hinged to one side of the main frame via the hinge, and the fastener is used to fix the cabin panel to any position after rotation.

[0011] In some embodiments, the hinge includes a first plate and a second plate, the first plate being disposed on the main frame and the second plate being disposed on the cabin plate, the first plate and the second plate being hinged to each other.

[0012] In some embodiments, both the first plate and the second plate are provided with grooves, which are used to accommodate a portion of the main frame and a portion of the cabin plate.

[0013] In some embodiments, the fastener includes at least one fastening rope and a fastening part. One end of the fastening rope is disposed on the main frame, and the other end of the fastening rope passes through the cabin plate. The fastening part is disposed on the cabin plate and is used to fix the fastening rope at any position so that the fastening rope tightens the cabin plate.

[0014] In some embodiments, the fixing part includes two clamping plates and a clamping section, a fixing space is formed between the two clamping plates, the fixing space is used to accommodate at least one fixing rope, the clamping section is disposed on the clamping plates, and the clamping section is used to drive the two clamping plates to move closer to each other so that the two clamping plates clamp the fixing rope.

[0015] In some embodiments, it also includes:

[0016] An installation component is disposed on the connecting component, and the installation component is used to detachably connect the connecting component to the main frame and the cabin plate.

[0017] In some embodiments, the mounting assembly includes a through-hole member, with at least one through-hole member provided on both the first plate and the second plate. The through-hole member is used to pass through or detach from the first plate and the second plate to abut or detach from the inner wall of the groove.

[0018] The mounting assembly also includes a connecting piece disposed within the groove. The through-feed member is used to drive the connecting piece to abut against the main frame and the cabin plate, thereby abutting the main frame and the cabin plate against the inner wall of the groove.

[0019] In some embodiments, the mounting assembly further includes a clamping seat detachably connected to the main frame, one end of the fixing rope being disposed within the clamping seat, and the fixing rope being disposed on the main frame via the clamping seat.

[0020] In some embodiments, the system further includes a cylinder that passes through the cabin plate, and a fixing rope that passes through the cylinder and passes through the cabin plate.

[0021] This application provides a satellite structure that, through the use of connecting components, allows the cabin panel to move relative to the main frame. This enables the cabin panel to open the main frame, facilitating heat dissipation testing of electronic devices within the main frame via fans. Furthermore, the cabin panel can be fixed to any moved position via the connecting components, allowing for easy adjustment of the opening degree. This prevents electronic devices on the cabin panel from being too far removed from those within the main frame, eliminating the need to replace test cables between the two systems, thus improving testing efficiency. It is also applicable to cables of varying lengths between the cabin panel and the main frame, enhancing versatility. Using the original cables for heat dissipation testing indirectly improves test accuracy. Moreover, each heat dissipation test of electronic devices does not require repeated installation and removal of the cabin panel, further improving testing efficiency. Attached Figure Description

[0022] The accompanying drawings, which are incorporated in and form part of this specification, illustrate embodiments consistent with this application and, together with the description, serve to explain the principles of this application.

[0023] Figure 1 A structural diagram of the satellite structure provided in this application;

[0024] Figure 2 for Figure 1 A structural diagram from another angle;

[0025] Figure 3 for Figure 2 Schematic diagram of the hinged connector;

[0026] Figure 4 for Figure 2 Schematic diagram of the middle fixing part;

[0027] Figure 5 for Figure 2 Schematic diagram of the structure of the intermediate pressure seat;

[0028] Figure 6 for Figure 2 A schematic diagram of the middle cylinder.

[0029] Explanation of reference numerals in the attached figures:

[0030] 100. Main framework;

[0031] 200. Hatch plate;

[0032] 300. Connecting assembly; 310. Hinge; 311. First plate; 312. Second plate; 313. Hinge block; 314. Hinge shaft; 320. Fixing component; 321. Fixing rope; 322. Fixing part; 323. Clamping plate; 324. Fixing space; 325. Flanged edge; 326. Clamping section; 330. Groove;

[0033] 400. Mounting component; 410. Insert; 420. Connecting piece; 430. Clamping seat;

[0034] 500. Cylinder body; 510. Through-running part; 520. Protective part.

[0035] The accompanying drawings illustrate specific embodiments of this application, which will be described in more detail below. These drawings and descriptions are not intended to limit the scope of the concept in any way, but rather to illustrate the concept of this application to those skilled in the art through reference to particular embodiments. Detailed Implementation

[0036] Exemplary embodiments will now be described in detail, examples of which are illustrated in the accompanying drawings. When the following description relates to the drawings, unless otherwise indicated, the same numbers in different drawings denote the same or similar elements. The embodiments described in the following exemplary embodiments do not represent all embodiments consistent with this application. Rather, they are merely examples of apparatuses and methods consistent with some aspects of this application as detailed in the appended claims.

[0037] In related technologies, a satellite structure includes a main frame, a hatch, and a heat sink. The main frame is the core structure of the satellite, housing numerous electronic devices that generate heat during operation. The hatch is installed on one side of the main frame and is used to open or close the main frame for the installation, maintenance, and testing of equipment. The heat sink is located on the main frame. In the space environment, the satellite is in a vacuum, and heat cannot be dissipated through air convection. Therefore, the satellite employs a special heat dissipation mechanism: heat is conducted to the heat sink through components such as heat pipes and heat conduction strips, and then the heat sink dissipates the heat into space in the form of infrared radiation. This heat dissipation method is very effective in the vacuum environment of space, but it faces challenges during ground testing. When conducting heat dissipation tests on the electronic equipment inside the main frame on the ground, fans are usually used to assist in heat dissipation. The fans carry away the heat generated by the electronic equipment through air convection, thereby reducing the temperature of the equipment and ensuring that the equipment is not damaged by overheating during testing.

[0038] However, during ground testing, in order to achieve air circulation within the main frame, the cabin panel needs to be removed from the main frame for each test. When electronic equipment is installed on the cabin panel, the length of the connecting cable between the electronic equipment on the cabin panel and the electronic equipment in the main frame may be insufficient. In this case, in order to ensure normal connection and communication between the devices, the test cable needs to be replaced. This frequent disassembly and cable replacement operation significantly reduces testing efficiency and brings many inconveniences to the ground testing of the satellite.

[0039] The technical solution of this application and how the technical solution of this application solves the above-mentioned technical problems are described in detail below with specific embodiments. These specific embodiments can be combined with each other, and the same or similar concepts or processes may not be described again in some embodiments. The embodiments of this application will be described below with reference to the accompanying drawings.

[0040] Combination Figures 1 to 6 This application provides a satellite structure, including:

[0041] Main framework 100;

[0042] 200 hatch panels;

[0043] A connecting component 300 is disposed between the main frame 100 and the cabin plate 200. The cabin plate 200 is movably disposed on the main frame 100 via the connecting component 300 and is fixed to any movable position via the connecting component 300.

[0044] In this application, by employing the connecting component 300, the compartment 200 can move relative to the main frame 100, thereby allowing the compartment 200 to open the main frame 100. This facilitates heat dissipation testing of the electronic devices within the main frame 100 via a fan. Furthermore, the compartment 200 can be fixed to any movable position via the connecting component 300, allowing for easy adjustment of the opening degree. This prevents the electronic devices on the compartment 200 from being too far from the electronic devices within the main frame 100, eliminating the need to replace test cables between the electronic devices on the compartment 200 and those within the main frame 100, thus improving testing efficiency. It is also applicable to cables of different lengths between the compartment 200 and the main frame 100, improving applicability. Using the original cables for heat dissipation testing indirectly improves testing accuracy. Moreover, by eliminating the need for repeated installation and removal of the compartment 200 each time heat dissipation testing is performed on the electronic devices, testing efficiency is further improved.

[0045] In this embodiment, the main frame 100 is generally rectangular, and the hatch 200 is located at one end of the length direction of the rectangular main frame 100. The hatch 200 is used to open and close one end of the rectangular main frame 100 along its length. In other embodiments, the main frame 100 can also be set as a cube or a sphere. When the main frame 100 is spherical, the hatch 200 for opening and closing the main frame 100 can also be set at any position of the spherical main frame 100.

[0046] The connecting assembly 300 includes a hinge 310 and a fastener 320. Both the hinge 310 and the fastener 320 are disposed between the main frame 100 and the cabin plate 200. The cabin plate 200 is hinged to one side of the main frame 100 by the hinge 310, and the fastener 320 is used to fix the cabin plate 200 to any position after rotation.

[0047] In this application, by employing a hinge 310, the compartment 200 is hinged to one side of the main frame 100. When the main frame 100 needs to be opened, the compartment 200 is driven to rotate, allowing gaps to be formed between the three adjacent sides of the compartment 200 and the main frame 100, thus facilitating heat dissipation testing. By hinged one side of the compartment 200 to the main frame 100, the main frame 100 can support the compartment 200, indirectly improving the strength of the compartment 200 when opened. By employing a fastener 320, the fastener 320 can fix the compartment 200 to any rotated position, thus facilitating the use of cables of different lengths.

[0048] In this embodiment, the bottom of the cabin panel 200 is hinged to the bottom of the main frame 100 via a hinge 310. In other embodiments, the hinge position of the cabin panel 200 and the main frame 100 can be adjusted according to adaptability, for example, the hinge position of the cabin panel 200 and the main frame 100 can be set at the upper part or side of the cabin panel 200.

[0049] In other embodiments, the movable arrangement also includes sliding the entire compartment 200 along the direction of approaching or moving away from the main frame 100 on the main frame 100. For example, slide rails are provided at the four corners of the main frame 100, and sliders are provided on the compartment 200 that are slidably connected to the slide rails. When the main frame 100 needs to be opened, the compartment 200 is driven away from the main frame 100, so that gaps can be formed between the compartment 200 and the main frame 100 on all four sides, thereby achieving better heat dissipation efficiency. The fixing member 320 can be an electric cylinder provided on the main frame 100. By providing the driving end of the electric cylinder on the compartment 200, the electric cylinder can drive the compartment 200 to move, so that the compartment 200 can be fixed to any moved position.

[0050] In other embodiments, the movable arrangement also includes rotatably mounting the compartment 200 on the main frame 100. For example, a rotating shaft is provided on the compartment 200 and rotatably connected to the main frame 100. The rotating shaft is perpendicular to the compartment 200. By driving the rotating shaft to rotate, the rotating shaft can drive the compartment 200 to rotate, so that a gap is formed between the compartment 200 and the main frame 100, thereby achieving better heat dissipation efficiency. The fixing member 320 can be a worm gear drive assembly provided on the main frame 100. By sleeved on the worm gear and fixedly connected to the rotating shaft, the worm gear is meshed with the worm gear. The worm gear is driven to rotate by a motor, so that the worm gear drives the worm gear to rotate, so that the worm gear drives the rotating shaft to rotate, so that the rotating shaft drives the compartment 200 to rotate, so that the compartment 200 can be fixed in any rotated position.

[0051] In this embodiment, two hinge members 310 are provided, and the two hinge members 310 are respectively provided on both sides of the edge of the cabin plate 200; in other embodiments, the number of hinge members 310 can be adjusted as needed, for example, four hinge members 310 are provided, and the four hinge members 310 are evenly distributed along the edge of the cabin plate 200.

[0052] The hinge 310 includes a first plate 311 and a second plate 312. The first plate 311 is disposed on the main frame 100, and the second plate 312 is disposed on the cabin plate 200. The first plate 311 and the second plate 312 are hinged to each other.

[0053] In this application, by employing a first plate 311 and a second plate 312 and hinged the first plate 311 and the second plate 312 together, the first plate 311 and the second plate 312 can drive the main frame 100 and the cabin plate 200 to be hinged together, which simplifies the structure and reduces the structural complexity of the hinge component 310.

[0054] In this embodiment, both the first plate 311 and the second plate 312 are provided with hinge blocks 313 extending in the direction of mutual approach. A hinge shaft 314 is passed through and rotatably connected to the two hinge blocks 313. The first plate 311 and the second plate 312 are hinged to each other through the hinge blocks 313 and the hinge shaft 314. The hinge shaft 314 can be a bolt or a combination of bolt and nut, thereby facilitating the installation and disassembly of the first plate 311 and the second plate 312.

[0055] Both the first plate 311 and the second plate 312 are provided with grooves 330, which are used to accommodate part of the main frame 100 and part of the cabin plate 200.

[0056] In this embodiment, the groove 330 is U-shaped. The groove 330 of the first plate 311 is used to accommodate the edge of the main frame 100, and the groove 330 of the second plate 312 is used to accommodate the edge of the cabin plate 200.

[0057] In other embodiments, the shape of the groove 330 can be adapted as needed, for example, the groove 330 can be set to a dovetail shape or a "T" shape.

[0058] In this application, by adopting the groove 330, the contact area between the first plate 311 and the main frame 100, and between the second plate 312 and the cabin plate 200 can be indirectly increased, thereby indirectly improving the fixing strength between the first plate 311 and the main frame 100, and between the second plate 312 and the cabin plate 200, preventing the first plate 311 and the second plate 312 from breaking, and indirectly improving the hinge strength between the first plate 311 and the second plate 312 driving the main frame 100 and the cabin plate 200.

[0059] The fastener 320 includes at least one fastening rope 321 and a fastening part 322. One end of the fastening rope 321 is disposed on the main frame 100, and the other end of the fastening rope 321 is passed through the cabin plate 200. The fastening part 322 is disposed on the cabin plate 200 and is used to fix it to any position of the fastening rope 321 so that the fastening rope 321 pulls the cabin plate 200 taut.

[0060] In this application, when it is necessary to fix the deck 200, the fixing rope 321 is moved on the deck 200 so that the fixing rope 321 passes through the deck 200 to a suitable length. At this time, the fixing part 322 fixes the fixing rope 321, so that the fixing rope 321 can tighten the deck 200, thereby fixing the deck 200 to the rotated position. By using the fixing rope 321, the structure is simple and does not occupy a large space of the main frame 100 and the deck 200, thereby indirectly improving the fixing effect of the deck 200. Furthermore, by controlling the length of the fixing rope 321, the fixing rope 321 can fix the deck 200 to different rotated positions, further improving the fixing effect of the deck 200.

[0061] In this embodiment, the fixing rope 321 is a steel wire rope. By using steel wire rope, it has high strength and can withstand greater tension and load. At the same time, steel wire rope has good flexibility, can be bent and wound. In addition, steel wire rope is wear-resistant, corrosion-resistant, and has a long service life. Its structure is compact and its weight is relatively light, making it easy to transport and install. Steel wire rope also has good fatigue resistance, can withstand repeated bending and stretching, and is not easy to break.

[0062] In other embodiments, the fixing rope 321 may also be a titanium alloy rope, a synthetic fiber rope, a phosphated steel wire rope, or a galvanized steel wire rope.

[0063] In this embodiment, two fixing ropes 321 are provided. One end of the two fixing ropes 321 is set on the top edge of the main frame 100 and located on both sides of the top edge of the main frame 100. The other end of the two fixing ropes 321 is set on the cabin plate 200 and located on both sides of the cabin plate 200. By using two fixing ropes 321, the fixing ropes 321 are prevented from breaking, and the fixing strength of the fixing ropes 321 to the cabin plate 200 is further improved. In other embodiments, the number of fixing ropes 321 can be adjusted as needed. For example, four fixing ropes 321 can be set and the four fixing ropes 321 can be evenly distributed around the circumference of the edge of the main frame 100.

[0064] The fixing part 322 includes two clamping plates 323 and a clamping section 326. A fixing space 324 is formed between the two clamping plates 323. The fixing space 324 is used to accommodate at least one fixing rope 321. The clamping section 326 is disposed on the clamping plates 323. The clamping section 326 is used to drive the two clamping plates 323 to move closer to each other so that the two clamping plates 323 clamp the fixing rope 321.

[0065] In this application, when it is necessary to fix the fixing rope 321, by passing the two fixing ropes 321 through the fixing space 324 between the two clamping plates 323 at the same time, adjusting the position of the fixing ropes 321 that need to be clamped by the two clamping plates 323, and driving the two clamping plates 323 to move closer through the clamping section 326, so that the two clamping plates 323 clamp the two fixing ropes 321 at the same time, thereby enabling the clamping plates 323 to fix the fixing ropes 321. At this time, the clamping plates 323 can abut against the cabin plate 200, so that the two fixing ropes 321 fix the cabin plate 200 in the rotated position.

[0066] In this embodiment, two clamping plates 323 are disposed on the side of the cabin plate 200 away from the main frame 100, and the two clamping plates 323 are located between the two fixing ropes 321. The clamping plates 323 are not connected to the cabin plate 200. The clamping plates 323 simultaneously fix the two fixing ropes 321. When the clamping plates 323 fix the two fixing ropes 321, the two fixing ropes 321 can drive the clamping plates 323 to abut against the cabin plate 200, so that the clamping plates 323 do not need to be connected to the cabin plate 200 to achieve the fixation of the cabin plate 200.

[0067] In other embodiments, one of the clamps 323 can be fixed to the cabin plate 200, and the other clamp 323 can be slidably disposed on the clamp 323 of the cabin plate 200 in a direction close to or away from the cabin plate 200, so that the two clamps 323 can also fix the fixing rope 321.

[0068] In this embodiment, both clamps 323 are wavy in shape. One clamp 323 has flanges 325 on opposite sides, and the other clamp 323 is slidably disposed between the flanges 325 on both sides. By setting the clamps 323 to be wavy and using flanges 325, the two clamps 323 can be prevented from separating in a direction parallel to the plane where the clamps 323 are located, thereby further improving the fixing strength of the two clamps 323 to the fixing rope 321.

[0069] In other embodiments, the shape of the clamp 323 can be adapted as needed, for example, the clamp 323 can be set to an arc shape or other shapes.

[0070] In this embodiment, the fixing section is the first bolt, and there are two first bolts. The two first bolts are respectively set on both sides of the clamping plate 323. The shank of the first bolt is used to pass through one of the clamping plates 323 and pass through and threadedly connected to the other clamping plate 323, so that the first bolt can drive the two clamping plates 323 to move closer, so that the two clamping plates 323 clamp the two fixing ropes 321.

[0071] In other embodiments, the fixing segment can also be a clamp, which clamps the two clamping plates 323, thus clamping the fixing rope 321.

[0072] The satellite structure also includes:

[0073] Mounting component 400 is disposed on connecting component 300 and is used to detachably connect connecting component 300 to main frame 100 and compartment 200.

[0074] In this application, by adopting the installation component 400, the installation and disassembly of the connection component 300 are facilitated, and the connection component 300 can be reused on multiple satellite structures, thereby indirectly improving the reusability of the connection component 300.

[0075] The mounting assembly 400 includes a through-hole member 410. At least one through-hole member 410 is provided on both the first plate 311 and the second plate 312. The through-hole member 410 is used to pass through or detach from the first plate 311 and the second plate 312 to abut or detach from the inner wall of the groove 330.

[0076] In this application, by employing a through-hole member 410, which is inserted through the first plate 311, the through-hole member 410 can abut against the main frame 100, allowing the main frame 100 to be pressed against the inner wall of the groove 330. The first plate 311 and the main frame 100 are fixed together by the friction between the main frame 100 and the inner wall of the groove 330. This method of fixing the first plate 311 and the main frame 100 is convenient and simple, improving the operator's control over the first plate 311 and the main frame 100. The efficiency of installing and disassembling the body frame 100 is improved. By inserting the through member 410 into the second plate 312, the through member 410 can abut against the hatch plate 200, and the through member 410 can abut against the inner wall of the groove 330. The second plate 312 and the hatch plate 200 are fixed by the friction between the hatch plate 200 and the inner wall of the groove 330. The fixing method between the second plate 312 and the hatch plate 200 is convenient and simple, which improves the efficiency of the operator in installing and disassembling the second plate 312 and the hatch plate 200.

[0077] In this embodiment, two through-hole members 410 are provided on the first plate 311 and two through-hole members 410 are provided on the second plate 312. By providing two through-hole members 410 on the first plate 311 and the second plate 312 respectively, the abutment force between the main frame 100 and the inner wall of the groove 330 and the cabin plate 200 and the inner wall of the groove 330 is indirectly improved, thereby further improving the fixing strength between the first plate 311 and the main frame 100 and between the second plate 312 and the cabin plate 200.

[0078] In this embodiment, the through-bolt 410 is a second bolt. The second bolt passes through and is threadedly connected to the first plate 311 and the second plate 312. The shank of the second bolt can abut against the main frame 100 and the cabin plate 200, thereby abutting the main frame 100 and the cabin plate 200 against the inner wall of the groove 330, realizing the fixation of the first plate 311 and the main frame 100, as well as the second plate 312 and the cabin plate 200. The second bolt can be fixed in any moved position, thereby further improving the fixation strength of the first plate 311 and the main frame 100, as well as the second plate 312 and the cabin plate 200.

[0079] In other embodiments, the insert 410 may include a rod and a spring. The rod is inserted through and slidably connected to the first plate 311 and the second plate 312. The spring is sleeved on the rod, with one end of the spring connected to the rod and the other end connected to the first plate 311 and the second plate 312. This allows the insert 410 to abut against the main frame 100 and the cabin plate 200 by the elastic force of the spring, thus eliminating the need to rotate the insert 410 on the first plate 311 and the second plate 312, making it easier to fix the first plate 311 and the second plate 312.

[0080] The mounting assembly 400 also includes a connecting piece 420 disposed in the groove 330. The through piece 410 is used to drive the connecting piece 420 to abut against the main frame 100 and the cabin plate 200, so as to abut against the inner wall of the groove 330.

[0081] In this application, by adopting the connecting piece 420, when the second bolt abuts against the connecting piece 420, the connecting piece 420 can be driven to abut against the main frame 100 and the cabin plate 200, thereby indirectly increasing the contact area between the second bolt and the main frame 100 and the cabin plate 200, and further improving the fixing strength between the first plate 311 and the main frame 100 and the second plate 312 and the cabin plate 200.

[0082] In this embodiment, the connecting piece 420 can be a rubber sheet, thereby further increasing the friction between it and the main frame 100 and the cabin plate 200. Alternatively, multiple protrusions can be provided on the connecting piece 420 for abutting against the main frame 100 and the cabin plate 200, thereby also increasing the friction between it and the main frame 100 and the cabin plate 200. Each groove 330 is provided with a connecting piece 420, which abuts against one side of the main frame 100 and the cabin plate 200. The number of connecting pieces 420 in the groove 330 can also be set to two, etc.

[0083] The mounting assembly 400 also includes a clamping seat 430, which is detachably connected to the main frame 100. One end of the fixing rope 321 is disposed inside the clamping seat 430, and the fixing rope 321 is disposed on the main frame 100 through the clamping seat 430.

[0084] In this application, by adopting the clamping seat 430, one end of the fixing rope 321 can be detachably connected to the main frame 100 through the clamping seat 430, which facilitates the installation and replacement of the fixing rope 321, and also facilitates the installation of the fixing rope 321 on other satellite structures for reuse.

[0085] In this embodiment, the outer wall of the clamping seat 430 is provided with a threaded portion, and the clamping seat 430 is detachably connected to the main frame 100 through the threaded portion. By adopting the threaded portion, the strength of the clamping seat 430 fixed on the main frame 100 is improved, and the clamping seat 430 is easy to install and remove. In other embodiments, a buckle can also be provided on the outer wall of the clamping seat 430, so that the clamping seat 430 is detachably connected to the main frame 100 through the buckle.

[0086] In this embodiment, there are two clamping seats 430, and the two clamping seats 430 correspond one-to-one with the two fixing ropes 321.

[0087] The satellite structure also includes a cylinder 500, which is mounted on the panel 200. A fixing rope 321 is mounted inside the cylinder 500 and passes through the cylinder 500 onto the panel 200.

[0088] In this application, by adopting the configuration of the cylinder 500, when the fixing rope 321 moves inside the cylinder 500, it can prevent the fixing rope 321 from being damaged due to friction between it and the hatch plate 200, thus preventing damage to the hatch plate 200 from affecting subsequent use and indirectly extending the service life of the fixing rope 321 and the hatch plate 200.

[0089] In this embodiment, the cylinder 500 includes a through portion 510 and a protective portion 520. The through portion 510 passes through the compartment plate 200 and is fixed to the compartment plate 200 by friction. The protective portion 520 is located at the end of the through portion 510 away from the main frame 100. The protective portion 520 is circular and its area is larger than that of the through portion 510, thereby increasing the contact area between the protective portion 520 and the fixing rope 321, thus providing better protection for the fixing rope 321.

[0090] The satellite structure provided in this application, when requiring heat dissipation testing of electronic equipment within the main frame 100, rotates the cabin panel 200. The cabin panel 200 then rotates the second plate 312 on top of the first plate 311. By rotating the cabin panel 200 to a suitable angle, the fixing ropes 321 move along the cabin panel 200, passing through the fixing space 324. The fixing section moves one clamping plate 323 towards the other clamping plate 323, causing the two clamping plates 323 to clamp the two fixing ropes 321, thus fixing the cabin panel 200 in position. After the cabin panel 200 is opened, it facilitates heat dissipation testing of the electronic equipment within the main frame 100 via a fan. Adjusting the opening degree of the compartment 200 facilitates the adjustment of the distance between the electronic devices on the compartment 200 and the electronic devices inside the main frame 100 when electronic devices are installed on the compartment 200. This prevents the electronic devices on the compartment 200 from being too far apart from the electronic devices inside the main frame 100, thus eliminating the need to replace test cables between the electronic devices on the compartment 200 and the electronic devices inside the main frame 100, thereby improving testing efficiency. By using the original cables for heat dissipation testing, the accuracy of the test is indirectly improved. Furthermore, the compartment 200 does not need to be repeatedly installed and disassembled, indirectly improving testing efficiency. It also eliminates the need to use a ground lift vehicle to support the compartment 200 when disassembling the compartment 200, reducing the space occupied by the electronic devices during heat dissipation testing.

[0091] Finally, it should be noted that other embodiments of this utility model will readily occur to those skilled in the art upon consideration of the specification and practice of the utility model disclosed herein. This utility model is intended to cover any variations, uses, or adaptations of this utility model that follow the general principles of this utility model and include common knowledge or customary techniques in the art not disclosed herein, and is not limited to the precise structures described above and shown in the accompanying drawings, and various modifications and changes can be made without departing from its scope. The scope of this utility model is limited only by the appended claims.

Claims

1. A satellite structure, characterized in that, include: Main framework (100); Hatch plate (200); A connecting component (300) is disposed between the main frame (100) and the cabin plate (200). The cabin plate (200) is movably disposed on the main frame (100) via the connecting component (300) and fixed to any movable position via the connecting component (300).

2. The satellite structure according to claim 1, characterized in that, The connecting assembly (300) includes a hinge (310) and a fixing member (320). Both the hinge (310) and the fixing member (320) are disposed between the main frame (100) and the cabin plate (200). The cabin plate (200) is hinged to one side of the main frame (100) through the hinge (310), and the fixing member (320) is used to fix the cabin plate (200) to any position after rotation.

3. The satellite structure according to claim 2, characterized in that, The hinge (310) includes a first plate (311) and a second plate (312). The first plate (311) is disposed on the main frame (100), and the second plate (312) is disposed on the cabin plate (200). The first plate (311) and the second plate (312) are hinged to each other.

4. The satellite structure according to claim 3, characterized in that, Both the first plate (311) and the second plate (312) are provided with grooves (330), which are used to accommodate part of the main frame (100) and part of the cabin plate (200).

5. The satellite structure according to claim 4, characterized in that, The fastener (320) includes at least one fastening rope (321) and a fastening part (322). One end of the fastening rope (321) is disposed on the main frame (100), and the other end of the fastening rope (321) is passed through the cabin plate (200). The fastening part (322) is disposed on the cabin plate (200) and is used to fix the fastening rope (321) at any position so that the fastening rope (321) pulls the cabin plate (200) taut.

6. The satellite structure according to claim 5, characterized in that, The fixing part (322) includes two clamping plates (323) and a clamping section (326). A fixing space (324) is formed between the two clamping plates (323) for accommodating at least one fixing rope (321). The clamping section (326) is disposed on the clamping plates (323) and is used to drive the two clamping plates (323) to move closer to each other so that the two clamping plates (323) clamp the fixing rope (321).

7. The satellite structure according to claim 5 or 6, characterized in that, Also includes: An installation assembly (400) is disposed on the connection assembly (300) for detachably connecting the connection assembly (300) to the main frame (100) and the compartment plate (200).

8. The satellite structure according to claim 7, characterized in that, The mounting assembly (400) includes a through-hole member (410), and at least one through-hole member (410) is provided on both the first plate (311) and the second plate (312). The through-hole member (410) is used to pass through or detach from the first plate (311) and the second plate (312) to abut or detach from the inner wall of the groove (330) of the main frame (100) and the cabin plate (200).

9. The satellite structure according to claim 8, characterized in that, The mounting assembly (400) further includes a connecting piece (420) disposed within the groove (330). The through-piece (410) is used to drive the connecting piece (420) to abut against the main frame (100) and the cabin plate (200), so as to abut against the inner wall of the groove (330) of the main frame (100) and the cabin plate (200).

10. The satellite structure according to claim 7, characterized in that, The mounting assembly (400) also includes a clamping seat (430), which is detachably connected to the main frame (100). One end of the fixing rope (321) is disposed inside the clamping seat (430), and the fixing rope (321) is disposed on the main frame (100) through the clamping seat (430).

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