On-orbit intelligent monitoring device for cube satellite

Abstract

The embodiment of the application discloses a kind of on-orbit intelligent monitoring devices of CubeSat, it is related to satellite monitoring technical field, by utilizing the solar wing plate of existing rotation setting on the cabin plate of CubeSat, as the deployment mechanism of installation monitoring camera, without additional increase deployment mechanism, the structure of monitoring device is simplified, the control demand of deployment mechanism and the corresponding reduction of bearing use are reduced, the reliability and adaptability are relatively increased, and because the length of solar wing plate is greater than the length of connected cabin plate, when solar wing plate rotates to solar wing plate and cabin plate adhere, camera can be stored in the top end of cabin plate, avoid the overall structure of camera to protrude, affect overall stability, when solar wing plate is retracted, by the locking cooperation of first locking piece and second locking piece, so that solar wing plate and camera can be stably settled, further improve the reliability of device.

Description

Technical Field

[0001] This application relates to the field of satellite surveillance technology, specifically to an on-orbit intelligent surveillance device for a CubeSat. Background Technology

[0002] Satellites are typically designed with external cameras to monitor their own status and provide services to space users. Traditional cameras, in order to meet shooting requirements, are usually linearly related to their mass and size. To meet high-performance applications, traditional satellite space imaging devices are quite heavy and include a whole deployment mechanism. The motors, bearings, and other components of the deployment mechanism reduce the overall reliability of the device and affect its service life. Summary of the Invention

[0003] The main purpose of this application is to provide an intelligent on-orbit monitoring device for CubeSats, which aims to solve the problem of poor overall reliability of existing satellite space imaging devices.

[0004] The technical solution adopted in this application is as follows:

[0005] A CubeSat on-orbit intelligent monitoring device is used to monitor a CubeSat. Solar panels are rotatably mounted on the outer wall of the CubeSat's module. The connecting end of the solar panels is rotatably connected to the module. The movable end of the solar panels can rotate around its connecting end until the solar panels are in contact with the module. The length of the solar panels is greater than the length of the module to which they are connected. The monitoring device includes:

[0006] The camera is located at the movable end of the solar panel and on the side of the solar panel closest to the cabin panel.

[0007] The first locking element is disposed on the solar panel;

[0008] The second locking element is disposed on the deck;

[0009] When the solar panel is attached to the cabin panel, the first locking element and the second locking element work together to lock it in place.

[0010] Optionally, the first locking element is a locking plug, which is located near the movable end of the solar panel. The second locking element is an unlocker, which is mounted on the top of the cabin panel via a mounting bracket. When the solar panel is in contact with the cabin panel, the locking plug is inserted into the unlocker to engage and lock.

[0011] Optionally, two sets of mounting brackets are provided, spaced apart, so that a receiving groove is formed between the two sets of mounting brackets. When the solar panel is attached to the cabin panel, the camera is located in the receiving groove.

[0012] Optionally, a display screen is embedded in the cabin panel, and when the solar panels are deployed and perpendicular to the cabin panel, the optical axis of the camera lens is oriented towards the display screen.

[0013] Optionally, the bottom of the display screen is away from the cabin plate so that the display screen is tilted relative to the cabin plate, and a support frame is set between the display screen and the cabin plate, with glass plates embedded between the frames of the support frame.

[0014] Optionally, the camera is tilted relative to the solar panel so that the camera's lens optical axis is parallel to the display screen's axis.

[0015] Optionally, the monitoring device also includes a screen bracket, through which the display screen is mounted on the panel.

[0016] Optionally, the monitoring device also includes a monitoring controller, which is connected to the camera signal. The monitoring controller is used to receive and analyze the real-time images captured by the camera, obtain real-time satellite data, and compare the real-time satellite data with historical data to obtain the real-time status of the monitored CubeSat.

[0017] Optionally, the monitoring device also includes a camera mount, through which the camera is mounted on the solar panel.

[0018] Optionally, the monitoring device also includes a heat shield, which is positioned between the camera and the solar panel.

[0019] Compared with the prior art, the beneficial effects of this application are:

[0020] The CubeSat on-orbit intelligent monitoring device proposed in this application utilizes an existing solar panel rotatably mounted on the CubeSat's module as a deployment mechanism for mounting the monitoring camera. This eliminates the need for an additional deployment mechanism, simplifying the monitoring device's structure. The control requirements for the deployment mechanism and the use of bearings are correspondingly reduced, increasing reliability and adaptability. Furthermore, because the length of the solar panel is greater than the length of the connected module, the camera can be retracted into the top of the module when the solar panel rotates to fit against it, preventing the camera's overall structure from protruding and affecting overall stability. When the solar panel retracts, a first locking element and a second locking element lock together to ensure stable placement of the solar panel and camera, further enhancing the device's reliability. Attached Figure Description

[0021] Figure 1 A schematic diagram of the structure of the CubeSat on-orbit intelligent monitoring device provided in an embodiment of this application;

[0022] Figure 2 A side view of the CubeSat on-orbit intelligent monitoring device provided in an embodiment of this application;

[0023] Figure 3 A front view structural schematic diagram of the CubeSat on-orbit intelligent monitoring device provided in an embodiment of this application;

[0024] Figure 4 An exploded view of the CubeSat on-orbit intelligent monitoring device provided in the embodiments of this application;

[0025] Explanation of the labels in the attached drawings:

[0026] 1-Mounting bracket, 2-Bucket plate, 3-Screen bracket, 4-Bracket frame, 5-Monitoring controller, 6-Hinge, 7-Solar panel, 8-Camera bracket, 9-Camera, 10-Glass plate, 11-First locking element, 12-Receiving slot, 13-Screen bracket, 14-Second locking element, 15-Display screen. Detailed Implementation

[0027] The technical solutions of the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only a part of the embodiments of this application, and not all of the embodiments. Based on the embodiments of this application, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the scope of protection of this application.

[0028] It should be noted that all directional indicators (such as up, down, left, right, front, back, etc.) in the embodiments of this application are only used to explain the relative positional relationship and movement of each component in a certain specific posture (as shown in the figure). If the specific posture changes, the directional indicator will also change accordingly.

[0029] In this application, unless otherwise expressly specified and limited, the terms "connection," "fixed," etc., should be interpreted broadly. For example, "fixed" can mean a fixed connection, a detachable connection, or an integral part; it can mean a mechanical connection or an electrical connection; it can mean a direct connection or an indirect connection through an intermediate medium; it can mean the internal communication of two components or the interaction between two components, unless otherwise expressly limited. Those skilled in the art can understand the specific meaning of the above terms in this application according to the specific circumstances.

[0030] Furthermore, if the embodiments of this application involve descriptions such as "first" or "second," these descriptions are for descriptive purposes only and should not be construed as indicating or implying their relative importance or implicitly specifying the number of technical features indicated. Therefore, a feature defined with "first" or "second" may explicitly or implicitly include at least one of those features. Additionally, the meaning of "and / or" throughout the text includes three parallel solutions; for example, "A and / or B" includes solution A, solution B, or a solution where both A and B are satisfied simultaneously. Furthermore, the technical solutions of the various embodiments can be combined with each other, but this must be based on the ability of those skilled in the art to implement them. When the combination of technical solutions is contradictory or impossible to implement, it should be considered that such a combination of technical solutions does not exist and is not within the scope of protection claimed in this application.

[0031] Since satellites are exposed to the space environment directly after leaving the atmosphere during their on-orbit operation, many satellites are designed with external cameras to monitor their own status and provide services to space users, in order to ensure daily operation and maintenance and technical status confirmation, increase public participation in spaceflight, and improve the user experience.

[0032] Traditional satellite space surveillance (imaging) devices consist of a camera payload, controller, camera deployment mechanism, and monitored target. To meet specific imaging requirements, the mass and size of traditional cameras are typically linearly related to these requirements. To ensure a good field of view for monitoring multiple layers, cables, and structural conditions on the surface of an on-orbit satellite, a dedicated deployment mechanism is required for the imaging mission. Traditional satellite space imaging devices are bulky and contain deployment mechanisms, resulting in high costs. Furthermore, the deployment mechanism includes electrical controls and bearings, reducing overall reliability and impacting lifespan. Moreover, different satellite types require specific design and implementation of the imaging device, limiting adaptability and iterative possibilities, and leading to high project costs across different types.

[0033] Therefore, this application provides an intelligent on-orbit monitoring device for a CubeSat, as shown in the attached document. Figure 1-4 As shown, a solar panel 7 is rotatably mounted on the outer wall of the CubeSat's cabin 2 for monitoring a CubeSat. The connecting end of the solar panel 7 is rotatably connected to the cabin 2, and the movable end of the solar panel 7 can rotate around its connecting end until the solar panel 7 is in contact with the cabin 2. The length of the solar panel 7 is greater than the length of the cabin 2 to which it is connected. The monitoring device includes a camera 9, a first locking member 11, and a second locking member 14. The camera 9 is located at the movable end of the solar panel 7 and is located on the side of the solar panel 7 closest to the cabin 2. The first locking member 11 is located on the solar panel 7, and the second locking member 14 is located on the cabin 2. When the solar panel 7 is in contact with the cabin 2, the first locking member 11 and the second locking member 14 cooperate to lock it in place.

[0034] In this embodiment, the existing solar panel 7, which is rotatably mounted on the CubeSat's cabin 2, is used as the deployment mechanism for installing the surveillance camera 9. This eliminates the need for an additional deployment mechanism, simplifying the structure of the surveillance device. The control requirements for the deployment mechanism and the use of bearings are reduced accordingly, increasing the reliability and adaptability. Furthermore, since the length of the solar panel 7 is greater than the length of the connected cabin 2, the camera 9 can be stored at the top of the cabin 2 when the solar panel 7 rotates and comes into contact with the cabin 2. This prevents the overall structure of the camera 9 from protruding outwards, which would affect the overall stability. When the solar panel 7 is retracted, the first locking member 11 and the second locking member 14 lock together to ensure that the solar panel 7 and the camera 9 are stably positioned, further improving the reliability of the device.

[0035] A CubeSat is a low-cost microsatellite that adopts internationally accepted standards. It is cubic in shape and has regular panels 2. The solar panels 7 are the satellite's built-in power generation system. One end of the solar panel 7 is connected to the panels 2 (the CubeSat) via a rotating structure such as a damping shaft or hinge 6, serving as its connection end. This allows the other end of the solar panel 7 to move around it. The moving end is its movable end, capable of deployment and retraction. Essentially, one side of the solar panel 7 is its surface with the solar substrate, and the other side is its non-surface surface, the back of the solar substrate. The camera 9 needs to be positioned on the non-surface surface of the solar panel 7 to ensure safe operation and the normal functioning of the solar substrate.

[0036] The first locking element 11 and the second locking element 14 are a locking mechanism that cooperates with each other. A simpler example is a magnetic locking mechanism that locks by magnetic connection. A more stable mechanism can be the unlocker and locking plug provided in the embodiments of this application. The placement of the first locking element 11 and the second locking element 14 on their respective components is not limited, as long as they cooperate with each other when the solar panel 7 is retracted. Other settings that can form a mutual locking mechanism to assist in the stable retraction of the solar panel 7 are also acceptable. Specifically, see the attached... Figure 4 As shown, the locking mechanism in the form of an unlocker and a locking plug is as follows:

[0037] The first locking element 11 is a locking plug, located near the movable end of the solar panel 7. The second locking element 14 is an unlocker, mounted on the top of the cabin panel 2 via a mounting bracket 1. When the solar panel 7 is in contact with the cabin panel 2, the locking plug is inserted into the unlocker for locking. As described above, the rod-shaped component on the locking plug serves as a positioning component to facilitate the engagement of the two locking elements. After the unlocker is inserted, a controllable moving part on the unlocker causes the locking plug to be clamped or locked, thus achieving a stable connection. Furthermore, positioning the locking position at the movable end of the solar panel 7 improves connection stability and prevents the movable end of the solar panel 7 from being subjected to excessive force that could cause it to expand.

[0038] In one embodiment, as shown in the appendix Figure 3 , 4 Two sets of mounting brackets 1 are provided, spaced apart, to form a receiving groove 12 between them. When the solar panel 7 is attached to the cabin panel 2, the camera 9 is located within the receiving groove 12. To better protect the camera 9 when the solar panel 7 retracts and to improve the stability after the panel retracts, two sets of mounting brackets 1 are provided, corresponding to two sets of first locking members 11 and second locking members 14. When the solar panel 7 retracts, the camera 9 can be accommodated in the receiving groove 12 between the mounting brackets 1, forming effective protection and further improving the stability of the device.

[0039] In one embodiment, as shown in the appendix Figure 4 As shown, a display screen 15 is embedded in the cabin panel 2. When the solar panel 7 is deployed and perpendicular to the cabin panel 2, the optical axis of the camera 9's lens faces the display screen 15. As described above, since the display screen 15 can display the satellite's mission and results, including satellite images, scientific experimental data, or other information that needs to be displayed, the camera 9 can capture the content displayed on the display screen 15 in real time and send it to the ground terminal by aligning its lens, i.e., its optical axis, with the display screen 15.

[0040] In one embodiment, as shown in the appendix Figure 1 , 2 As shown, the bottom of the display screen 15 is far from the cabin plate 2, so that the display screen 15 is tilted relative to the cabin plate 2. A support frame 4 is set between the display screen 15 and the cabin plate 2, and a glass plate 10 is embedded in the frame of the support frame 4. In the above embodiment, the display screen 15 is installed in an embedded tilt to form a simple light-shielding structure for the display screen 15, and a support frame 4 is set in the space between the display screen 15 and the cabin plate 2. The glass plate 10 is installed through the support frame 4. The glass plate 10 can be made of high-strength glass, such as fused silica (JQS) material. At the same time, the glass plate 10 can also be coated with an anti-reflective film to reduce the hardness of glass reflection during on-orbit monitoring, ensure that the screen has a better display effect, and improve the imaging quality of the camera 9.

[0041] In one embodiment, to ensure image quality, the camera 9 is tilted relative to the solar panel 7 so that the optical axis of the camera 9's lens is parallel to the axis of the display screen 15, that is, in the attached... Figure 2 In the shown configuration, camera 9 is always directly facing display screen 15, and the tilt angles of camera 9 and display screen 15 are the same. That is, the angle between display screen 15 and the cabin panel 2 is equal to the angle between the optical axis of camera 9's lens and the solar panel 7. The size of this angle varies depending on the satellite design. Furthermore, to improve the stability of display screen 15, a screen bracket 3 is added to the monitoring device, as shown in the attached diagram. Figure 4 As shown, the display screen 15 is stably embedded in the cabin plate 2 by the screen bracket 3.

[0042] In one embodiment, as shown in the appendix Figure 1 As shown, the monitoring device also includes a camera bracket 8, through which the camera 9 is mounted on the solar panel 7. On one hand, the camera bracket 8 facilitates the installation of the camera 9 and the solar panel 7, preventing direct contact between the camera 9 and the solar panel 7. On the other hand, the camera bracket 8 allows for adjustment of the lens orientation of the camera 9. Furthermore, since the solar substrate operates at temperatures higher than room temperature, a heat insulation plate is added to the monitoring device. This heat insulation plate, made of high-temperature resistant materials such as fiberglass, is positioned between the camera 9 and the solar panel 7, ensuring heat insulation between them and improving safety.

[0043] In one embodiment, the camera 9 can be configured with a single model or multiple models, enabling it to have various shooting modes to meet different surveillance and self-portrait needs. These modes may include visible light photography mode, infrared thermal imaging mode, etc. In this way, the CubeSat can select the most suitable shooting mode according to specific needs, providing richer data and information. For example, it can detect surface damage, cracks, pollution, and other problems; using an infrared thermal imaging sensor to monitor the satellite surface can detect temperature anomalies, hotspot distribution, heat dissipation, and other issues; infrared thermal imaging technology can help discover potential thermal problems.

[0044] In one embodiment, as shown in the appendix Figure 2As shown, the monitoring device also includes a monitoring controller 5, which is signal-connected to the camera 9. The monitoring controller 5 can be installed inside the CubeSat to control the entire workflow, including camera shooting, screen driving, wing retraction and deployment, screen display, and active camera temperature control. Image processing technology can also be incorporated into the monitoring controller 5. Specifically, the monitoring controller 5 receives and analyzes real-time images captured by the camera to obtain real-time satellite data, and compares this real-time data with historical data to determine the real-time status of the monitored CubeSat. By introducing image processing technology, the monitoring device can automatically detect, identify, and analyze key features and targets in the images. Then, by using deep learning algorithms, real-time image processing and intelligent decision-making can be achieved, improving the efficiency and accuracy of monitoring self-capture and allowing the device to determine whether the monitored status is normal based on historical data.

[0045] In summary, the CubeSat on-orbit intelligent monitoring device proposed in this application utilizes existing solar panels rotatably mounted on the CubeSat's deck as the deployment mechanism for mounting the monitoring camera. This eliminates the need for an additional deployment mechanism, simplifying the monitoring device structure. The control requirements for the deployment mechanism and the use of bearings are correspondingly reduced, increasing reliability and adaptability. Furthermore, because the length of the solar panel is greater than the length of the connected deck, the camera can be retracted at the top of the deck when the solar panel rotates to contact the deck, preventing the camera's overall structure from protruding and affecting overall stability. When the solar panel retracts, a first locking element and a second locking element lock together to ensure stable placement of the solar panel and camera, further enhancing the device's reliability.

[0046] The above description is only a preferred embodiment of this application and is not intended to limit this application. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of this application should be included within the protection scope of this application.

Claims

1. A CubeSat on-orbit intelligent monitoring device, characterized in that, For monitoring a CubeSat, a solar panel is rotatably mounted on the outer wall of the CubeSat's cabin. The connecting end of the solar panel is rotatably connected to the cabin, and the movable end of the solar panel can rotate around its connecting end until the solar panel is in contact with the cabin. The length of the solar panel is greater than the length of the cabin to which it is connected. The monitoring device includes: A camera is disposed at the movable end of the solar panel and located on the side of the solar panel closest to the cabin panel; A first locking element is disposed on the solar panel; A second locking element is disposed on the cabin panel; When the solar panel is attached to the cabin panel, the first locking member and the second locking member cooperate to lock it in place. The display screen is embedded in the cabin panel. When the solar panels are deployed and perpendicular to the cabin panel, the display screen is used to display the satellite's mission and achievements. The lens optical axis of the camera is oriented towards the display screen and is used to capture the content displayed on the display screen in real time and send it to the ground terminal.

2. The CubeSat on-orbit intelligent monitoring device according to claim 1, characterized in that, The first locking component is a locking plug, which is located near the movable end of the solar panel. The second locking component is an unlocker, which is mounted on the top of the cabin panel via a mounting bracket. When the solar panel is in contact with the cabin panel, the locking plug is inserted into the unlocker to engage and lock.

3. The CubeSat on-orbit intelligent monitoring device according to claim 2, characterized in that, The mounting bracket is provided in two sets, and the two sets of mounting brackets are spaced apart to form a receiving groove between the two sets of mounting brackets. When the solar panel is attached to the cabin panel, the camera is located in the receiving groove.

4. The CubeSat on-orbit intelligent monitoring device according to claim 1, characterized in that, The bottom of the display screen is far away from the cabin plate so that the display screen is tilted relative to the cabin plate. A support frame is provided between the display screen and the cabin plate, and a glass plate is embedded between the frames of the support frame.

5. The CubeSat on-orbit intelligent monitoring device according to claim 4, characterized in that, The camera is tilted relative to the solar panel so that the optical axis of the camera lens is parallel to the axis of the display screen.

6. The CubeSat on-orbit intelligent monitoring device according to claim 1, characterized in that, The monitoring device also includes a screen bracket, through which the display screen is mounted on the cabin panel.

7. The CubeSat on-orbit intelligent monitoring device according to claim 1, characterized in that, The monitoring device also includes a monitoring controller, which is connected to the camera signal. The monitoring controller is used to receive and analyze the real-time images captured by the camera, obtain real-time satellite data, and compare the real-time satellite data with historical data to obtain the real-time status of the monitored CubeSat.

8. The CubeSat on-orbit intelligent monitoring device according to claim 1, characterized in that, The monitoring device also includes a camera bracket, through which the camera is mounted on the solar panel.

9. The CubeSat on-orbit intelligent monitoring device according to claim 1, characterized in that, The monitoring device also includes a heat insulation plate disposed between the camera and the solar panel.

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