Display load folding and unfolding device on cubesat

Abstract

The utility model relates to a folding and unfolding device for displaying load on a cubesat. The load is displayed; one end of the display load is a hinged end, and the other end is a free end; the hinge end is provided with a hinge piece, and the display load is mounted on a non-sailboard surface of the cubesat through the hinge piece, so that the free end has a stroke for rotating around the hinge end; when the free end rotates to be parallel to the non-sailboard surface, the display load completes folding, and the hinge piece is in a pre-tightening state; when the free end rotates to be perpendicular to the non-sailboard face, the display load is unfolded completely, and the hinge piece is in a natural state. The display load can be folded, so that in the non-display stage of spacecraft launching and in-orbit operation, space can be effectively saved, overall layout and design of a cubesat are facilitated, and the space utilization rate is high.

Description

Technical Field

[0001] This utility model relates to the field of satellite technology, and in particular to a folding and unfolding device for display payloads on a CubeSat. Background Technology

[0002] With the development of aerospace technology and the expansion of application scenarios, the demand for CubeSats in space visualization missions is increasing. For example, scenarios such as dynamic advertising and emergency information broadcasting require CubeSats to carry large-size external display payloads to achieve information display visible on the ground through optical effects, thereby meeting diverse needs for space information dissemination.

[0003] Currently, traditional fixed external display panels cannot be folded due to their structural characteristics, creating a fundamental contradiction between size constraints and functional requirements when applied to CubeSats. If large, rigid screens are directly mounted externally, the protruding display panel structures will far exceed the standard size of CubeSats, potentially preventing them from being enveloped by the fairing during launch or causing resonance risks. If a compromise is made by using small display units, the brightness and resolution for ground observation will be significantly insufficient, rendering them impractical. Utility Model Content

[0004] Therefore, it is necessary to provide a CubeSat display payload folding and unfolding device that can fold the display payload to maximize the compression of the overall size of the CubeSat, in order to address the above-mentioned technical problems.

[0005] A device for folding and unfolding a display payload on a CubeSat includes a display payload; one end of the display payload is a hinged end, and the other end is a free end; the hinged end is provided with a hinge member, through which the display payload is mounted on the non-sail surface of the CubeSat, allowing the free end to have a stroke for rotational movement around the hinged end; when the free end rotates to be parallel to the non-sail surface, the display payload is folded, and the hinge member is in a pre-tensioned state; when the free end rotates to be perpendicular to the non-sail surface, the display payload is unfolded, and the hinge member is in a natural state.

[0006] In one embodiment, the display payload is mounted on a non-sail surface on the side of the CubeSat with a slide rail; as the CubeSat slides into the deployer, the display payload slides into the deployer together with it based on the movement of the hinged end.

[0007] In one embodiment, a guide is provided at the free end of the display payload; when the display payload slides into the deployer along with the cubesat, it is guided by the guide; and when the display payload is fully folded, the guide abuts against the inner wall of the deployer.

[0008] In one embodiment, a guide is provided on the side of the display payload facing the deployer entrance; the display payload is guided by the guide as it slides into the deployer along with the CubeSat; and the guide abuts against the inner wall of the deployer when the display payload is fully folded.

[0009] In one embodiment, the guide is a detachable connection.

[0010] In one embodiment, a locking element is provided at the hinge end, which self-locks when the free end rotates to be perpendicular to the non-sailboard surface.

[0011] In one embodiment, the hinge and the locking element are integrated into one unit.

[0012] In one embodiment, a limiting member is provided on the non-sail surface of the CubeSat; when the display load is folded, the side facing the CubeSat abuts against the limiting member.

[0013] In one embodiment, the limiting member is made of a soft, high- and low-temperature resistant material.

[0014] In one embodiment, the hinge is a detachable connection.

[0015] Compared with existing technologies, the CubeSat display payload folding and unfolding device provided by this utility model has the following advantages:

[0016] 1. The display payload can be folded parallel to the non-sail surface of the CubeSat using hinges. This effectively saves space during the non-display phase of spacecraft launch and on-orbit operation, facilitating the overall layout and design of the CubeSat and resulting in high space utilization.

[0017] 2. The display payload in its folded state can be placed together with the CubeSat in the deployer, and the display payload in its folded state can be placed as close to the CubeSat as possible, which can reduce vibration during the launch phase and effectively protect the display payload.

[0018] 3. The hinge is in a pre-tightened state when folded. When the cube star is ejected, the pre-tightened state automatically switches to the natural state, thereby driving the display load to unfold automatically. The structure is simple, easy to control, meets the requirements of lightweight design, and can adapt to various mission requirements. Attached Figure Description

[0019] To more clearly illustrate the technical solutions in the embodiments of this utility model or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this utility model. For those skilled in the art, other drawings can be obtained based on the structures shown in these drawings without creative effort.

[0020] Figure 1 This is a schematic diagram of the payload folding and unfolding device structure on a CubeSat in one embodiment;

[0021] Figure 2 This is a front view showing the load and the connection between the hinge in one embodiment;

[0022] Figure 3 This is a first-view illustration showing the load connected to the hinge in one embodiment;

[0023] Figure 4 This is a second front view showing the connection between the load and the hinge in one embodiment;

[0024] Figure 5 This is a second view showing the load connected to the hinge in one embodiment;

[0025] Figure 6 This is a perspective view of the cubesat's storage state in one embodiment;

[0026] Figure 7 This is a front view of the cubesat in its stored state in one embodiment;

[0027] Figure 8 for Figure 7 The diagram shows an enlarged representation of part A.

[0028] Figure 9 This is a schematic diagram of the cubesat and the deployer in a semi-separated state in one embodiment.

[0029] Figure 10 This is a schematic diagram of a cubesat and deployer completely separated in one embodiment.

[0030] Explanation of reference numerals in the attached figures:

[0031] Display load 1, display screen 101, monitoring camera 102, hinge end 11, free end 12, cube star 2, sail surface 21, non-sail surface 22, slide rail 23, deployer 3, hinge 4, guide 5, limit 6.

[0032] The purpose, features, and advantages of this utility model will be further explained in conjunction with the embodiments and with reference to the accompanying drawings. Detailed Implementation

[0033] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the protection scope of the present utility model.

[0034] It should be noted that all directional indicators (such as up, down, left, right, front, back, etc.) in this utility model embodiment 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.

[0035] Furthermore, in this utility model, the use of terms such as "first," "second," etc., is 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 as "first" or "second" may explicitly or implicitly include at least one of that feature. In the description of this utility model, "multiple" means at least two, such as two, three, etc., unless otherwise explicitly specified.

[0036] In this utility model, unless otherwise explicitly 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, an electrical connection, a physical connection, or a wireless communication connection; it can mean a direct connection or an indirect connection through an intermediate medium; it can mean the internal connection of two components or the interaction between two components, unless otherwise explicitly limited. Those skilled in the art can understand the specific meaning of the above terms in this utility model according to the specific circumstances.

[0037] It is understood that the technical solutions of the various embodiments of this utility model can be combined with each other, but this must be based on the ability of a person skilled in the art to implement them. When the combination of technical solutions is contradictory or cannot be implemented, it should be considered that such combination of technical solutions does not exist and is not within the protection scope claimed by this utility model.

[0038] The embodiments of this utility model will now be described in detail with reference to the accompanying drawings.

[0039] like Figures 1 to 10As shown, the CubeSat display load folding and unfolding device provided in this embodiment includes a display load 1; one end of the display load 1 is a hinged end 11, and the other end is a free end 12; the hinged end 11 is provided with a hinge member 4, and the display load 1 is mounted on the non-sail surface 22 of the CubeSat 2 through the hinge member 4, so that the free end 12 has a stroke for rotation around the hinged end 11; when the free end 12 rotates to be parallel to the non-sail surface 22, the display load 1 is folded and the hinge member 4 is in a pre-tightened state; when the free end 12 rotates to be perpendicular to the non-sail surface 22, the display load 1 is unfolded and the hinge member 4 is in a natural state.

[0040] Specifically, the display payload 1 includes, but is not limited to, devices such as a display screen 101 and a monitoring camera 102 used for visualization tasks. The CubeSat 2 has a solar panel surface 21 and a non-solar panel surface 22. Solar panels are provided on the solar panel surface 21. Therefore, the display payload 1 is mainly installed on the non-solar panel surface 22 of the CubeSat 2. More preferably, it is installed on the non-solar panel surface 22 on the side of the CubeSat 2 with the slide rail 23. When the CubeSat 2 slides into the deployer 3, the display payload 1 slides into the deployer 3 together with it based on the movement of the hinge end 11.

[0041] It is understandable that the display payload 1 is preferably mounted on the non-sail surface 22 on the side of CubeSat 2 with the slide rail 23. This minimizes the overall size of CubeSat 2, thereby allowing for the minimization of the size of the deployer 3 during design to meet the rocket's carrying space requirements. Furthermore, a screen of appropriate size can be selected based on the size of the non-sail surface 22 to achieve the best display effect and maximize the functionality of the display payload 1.

[0042] The placement of display load 1 is determined based on the optimal viewing angle, such as placing it near the end or middle. When multiple display loads 1 are set, they can be placed on the same non-sail surface 22 or on opposite non-sail surfaces 22. When placed on the same non-sail surface 22, the specific spacing parameters between the display loads 1 are determined according to usage requirements.

[0043] The hinge 4 is preferably positioned on the right side of the display load 1. This conforms to the movement pattern of the cube star 2 being pushed into the deployer 3, and also reduces the risk of collision or friction with surrounding structures, thus improving the reliability and stability of the entire system. Furthermore, the hinge 4 is pre-tightened to the right when folded. When the cube star 2 pops out, the pre-tightening force of the hinge 4 is released to the left, allowing the display load 1 to unfold smoothly and avoiding risks associated with energy and drive control.

[0044] The hinge 4 can be set as one or two. If it is set as one, it is set in the middle of the hinge end 11 of the display load 1; if it is set as two, it is set symmetrically along the vertical axis of the display load 1.

[0045] Hinged component 4 consists of two components hinged together with torque. One component is detachably mounted on the display load 1, and the other component is detachably mounted on the cube star 2. It is worth noting that detachable connections include, but are not limited to, snap-fit ​​connections, threaded connections, pin connections, magnetic connections, and plug-in connections, which can be selected adaptively according to the situation. In this embodiment, a threaded connection is preferred. Furthermore, subsequent detachable connection methods mentioned in this embodiment have the same meaning and will not be elaborated further.

[0046] A guide member 5 is also provided on the display load 1. There are two ways to set it. One is to set the guide member 5 on the free end 12 as provided in this embodiment. There are two guide members 5. As can be seen from the figure, the guide members 5 are set on the left side of the free end 12, located at the two corners and extending outward to expose the guide wheel. This is because when the display load 1 slides into the deployer 3 with the cube star 2, as the thrust acts on the cube star 2, the free end 12 of the display load 1 moves to the right around the hinge 4. Setting the guide member 5 on the left side of the free end 12 can cooperate with the inner wall of the deployer 3 during the sliding process, guide the free end 12 to slide in accurately along a specific trajectory, ensure that the display load 1 enters the deployer 3 in the correct posture, and improve the accuracy of the sliding.

[0047] Another option is to install guide members 5 on the side of the display load 1 facing the entrance of the deployer 3. That is, guide members 5 are installed on the left side of the display load 1 as needed, and the number is determined according to requirements. For example, they can be set at the four corners or four sides of the left side, or they can be set on the surface. The specific setting is aimed at ensuring the accuracy and stability of the display load 1 during the sliding process.

[0048] When the display payload 1 slides into the deployer 3 along with the CubeSat 2, it is guided by the guide member 5, which reduces the friction between the display payload 1 and the inner wall of the deployer 3 during movement, improving the accuracy and reliability of the sliding. When the display payload 1 is fully folded, the guide member 5 abuts against the inner wall of the deployer 3, ensuring the stability of the display payload 1 and preventing deviation or shaking during handling or launch. The guide member 5 is preferably a guide wheel and is detachably connected to the display payload 1.

[0049] A locking element is provided at the hinge end 11. When the free end 12 rotates to be perpendicular to the non-sail surface 22, it self-locks via the locking element. The locking element and the hinge element 4 can be separately provided or integrated into a single design. When the locking element and the hinge element 4 are separately provided, the locking element can adopt a structure such as a spring plunger or a wedge lock. The number is determined according to the number of hinge elements 4. When there is one hinge element 4 and it is located in the middle, there are two locking elements, which are symmetrically arranged with the hinge element 4 as the center. When there are two hinge elements 4, there is one locking element, which is located between the two hinge elements 4. When the locking element and the hinge element 4 are integrated into a single design, as shown in this embodiment, the hinge element 4 is a self-locking hinge with torque. A self-locking plate extends upward from the part connected to the cube star 2. When the free end 12 rotates, the self-locking plate limits the further movement of the display load 1, thereby ensuring that the display load 1 unfolds smoothly to be perpendicular to the non-sail surface 22.

[0050] Furthermore, a limiting member 6 is provided on the non-sail surface 22 of the cubesat 2; when the display load 1 is folded, the side facing the cubesat 2 abuts against the limiting member 6. The main purpose of the limiting member 6 is to dampen and limit the display load 1, and its shape, setting position, and quantity are designed according to the setting position of the display load 1. In this embodiment, the limiting member 6 for the display screen 101 is two smaller rectangular blocks, symmetrically arranged inside the slide rail 23, and its position corresponds to the position near the free end 12 of the display screen 101 after folding. The limiting member 6 for the monitoring camera 102 is a larger irregular shape, set on the non-sail surface 22 on the right side, and its position corresponds to the position of the bottom surface of the monitoring camera 102. The limiting member 6 is made of a soft, high and low temperature resistant material.

[0051] The folding and unfolding device for the display payload on the CubeSat provided in this embodiment can fold the display payload 1 to the maximum extent, thereby compressing the overall size of the CubeSat to accommodate it in the CubeSat deployer. Under the premise of meeting the CubeSat launch conditions, the overall size of the CubeSat is minimized, thereby compressing the size of the CubeSat deployer to the maximum extent, so as to meet the high utilization of the rocket's payload space and reduce the launch cost of the CubeSat. At the same time, an appropriate screen size is selected according to the foldable space to present the best display effect and maximize the function of the display payload.

[0052] The technical features of the above embodiments can be combined in any way. For the sake of brevity, not all possible combinations of the technical features in the above embodiments are described. However, as long as there is no contradiction in the combination of these technical features, they should be considered to be within the scope of this specification.

[0053] The embodiments described above are merely illustrative of several implementations of this utility model, and while the descriptions are relatively specific and detailed, they should not be construed as limiting the scope of the utility model. It should be noted that those skilled in the art can make various modifications and improvements without departing from the concept of this utility model, and these all fall within the protection scope of this utility model. Therefore, the protection scope of this utility model should be determined by the appended claims.

Claims

1. A device for folding and unfolding a display payload on a CubeSat, characterized by, The display load comprises a hinged end and a free end; The hinged end is provided with a hinge, which is used to install the display load on a non-sail panel of the cubic star, so that the free end has a stroke of rotating movement around the hinged end; When the free end is rotated to be parallel to the non-sail panel, the display load is folded, and the hinge is in a pre-tightening state; When the free end is rotated to be perpendicular to the non-sail panel, the display load is unfolded, and the hinge is in a natural state.

2. The folding and unfolding device of a display payload on a CubeSat according to claim 1, characterized in that, The display load is installed on the non-sail panel of the cubic star on the side with a slide rail; When the cubic star slides into a deployer, the display load slides into the deployer together based on the movement of the hinged end.

3. The folding and unfolding device of a display payload on a CubeSat according to claim 2, characterized in that, A guide is arranged on the free end of the display load; When the display load slides into the deployer together with the cubic star, the guide is used for guiding; and when the display load is completely folded, the guide abuts against an inner wall surface of the deployer.

4. The folding and unfolding device of a display payload on a CubeSat according to claim 2, characterized in that, A guide is arranged on a side of the display load facing the entrance of the deployer; When the display load slides into the deployer together with the cubic star, the guide is used for guiding; and when the display load is completely folded, the guide abuts against an inner wall surface of the deployer.

5. The device according to claim 3 or 4, characterized in that The guide is detachably connected.

6. The folding and unfolding device of a display payload on a CubeSat according to any one of claims 1 to 3, characterized in that, A locking member is arranged on the hinged end, which is used for self-locking when the free end is rotated to be perpendicular to the non-sail panel.

7. The folding and unfolding device of a display payload on a CubeSat according to claim 6, characterized in that, The hinge and the locking member are integrally designed.

8. The device according to any one of claims 1 to 3, wherein A limiting member is arranged on the non-sail panel of the cubic star; When the display load is folded, a side of the display load facing the cubic star abuts against the limiting member.

9. The device according to claim 8, wherein The limiting member is made of soft high-temperature-resistant material.

10. The folding and unfolding device of a display payload on a CubeSat according to any one of claims 1 to 3, characterized in that, The hinge is detachably connected.

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