Satellite antenna pressing and unfolding device without independent locking and releasing mechanism

Abstract

The utility model relates to a pressing and unfolding device of a satellite antenna, which does not need an independent locking and releasing mechanism. Comprising the steps that a flexible antenna is arranged on the side face, facing a solar panel, of a satellite body; when the solar panel is in a locked state, the flexible antenna is bent and arranged between the satellite body and the solar panel and is in a compressed state; when the solar panel is unfolded, the flexible antenna is unfolded along with the solar panel, the compressed state is converted into the natural state, the flexible antenna is smoothly unfolded, an additional locking and releasing mechanism is not needed in the whole process, the manufacturing and maintenance cost is reduced, and the risk of task failure caused by complex mechanism faults is reduced.

Description

Technical Field

[0001] This utility model relates to the field of aerospace satellite antenna technology, and in particular to a clamping and unfolding device for satellite antennas that does not require a separate locking and releasing mechanism. Background Technology

[0002] After the satellite separates from the rocket, some of its antennas need to be deployed to function, such as tape measure antennas and flexible linear antennas. The conventional approach is to roll up the antennas before launch and secure them with a locking and releasing mechanism. After separation, the locking and releasing mechanism receives a pre-set command and unlocks, releasing and deploying the antennas.

[0003] However, the cost of the antenna itself is relatively low. For example, a tape measure antenna is simply a section of a regular tape measure cut off from the market. Adapting it with a locking and releasing mechanism increases the cost, and it requires receiving special commands to unlock, which also carries the risk of unsuccessful unlocking. Utility Model Content

[0004] Therefore, it is necessary to provide a satellite antenna clamping and unfolding device that does not require a locking and releasing mechanism and can smoothly unlock the antenna, thus addressing the aforementioned technical problems.

[0005] A pressing and unfolding device for a satellite antenna that does not require a separate locking and releasing mechanism includes a flexible antenna mounted on the side of the satellite body facing the solar panel. When the solar panel is in a locked state, the flexible antenna is bent and placed between the satellite body and the solar panel, and is in a pressed state. When the solar panel is unfolded, the flexible antenna unfolds accordingly, changing from the pressed state to a natural state.

[0006] In one embodiment, a pad is also provided on the satellite body at a location corresponding to the flexible antenna.

[0007] In one embodiment, the cross-sectional shape of the pad is adapted to the cross-sectional shape of the flexible antenna.

[0008] In one embodiment, the pad is made of a lightweight metal with a flexible material laid on its surface.

[0009] In one embodiment, the pad is made of a flexible material.

[0010] In one embodiment, a pressure strip is also provided on the solar panel at a position corresponding to the flexible antenna.

[0011] In one embodiment, the cross-sectional shape of the pressure strip is adapted to the cross-sectional shape of the flexible antenna.

[0012] In one embodiment, a protrusion is provided at the center of the pad, and the cross-sectional shape of the pressure strip is adapted to the cross-sectional shape of the protrusion.

[0013] In one embodiment, the pressure strip is made of a lightweight metal with a flexible material laid on its surface.

[0014] In one embodiment, the pressure strip is made of a flexible material.

[0015] Compared with existing technologies, the satellite antenna clamping and unfolding device provided by this utility model, which does not require a separate locking and releasing mechanism, has the following advantages:

[0016] 1. Utilizing the satellite's requirement to fold and lock before launch, a flexible antenna is installed on the satellite body. When the solar panels are locked, the flexible antenna is positioned between the satellite body and the solar panels in a compressed state. After the satellite separates, the solar panels unfold, and the flexible antenna unfolds accordingly, transitioning from the compressed state to a natural state. The antenna unlocks smoothly without the need for an additional locking and releasing mechanism. This reduces the number and complexity of components on the satellite, lowers manufacturing and maintenance costs, and reduces the risk of mission failure due to malfunctions in complex mechanisms. Simultaneously, it reduces additional control links and operational steps, improving the overall operational efficiency and reliability of the satellite system.

[0017] 2. It effectively utilizes the space between the satellite body and the solar panels, making the satellite layout more compact and improving space utilization.

[0018] 3. Since no separate locking and releasing mechanism is needed to control the clamping and unfolding of the antenna, the driving energy consumption of related mechanisms is reduced, which helps the satellite to complete its mission more efficiently under limited energy conditions.

[0019] 4. During satellite launches and other processes, the solar panels are in a locked state. At this time, the flexible antenna is pressed between the satellite body and the solar panels, which provides better protection and avoids interference and damage from the external environment, thereby improving the antenna's service life and performance. Attached Figure Description

[0020] 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.

[0021] Figure 1 This is a schematic diagram of a pressing and unfolding device for a satellite antenna that does not require a separate locking and releasing mechanism in one embodiment;

[0022] Figure 2 for Figure 1 An enlarged view of the part labeled A in the middle;

[0023] Figure 3 This is a schematic diagram of the flexible antenna being compressed in one embodiment;

[0024] Figure 4 This is a schematic diagram of the structure when the solar panel is in the locked state in one embodiment;

[0025] Figure 5 This is a schematic diagram of the structure when the solar panel is in the deployed state in one embodiment.

[0026] Explanation of reference numerals in the attached figures:

[0027] Satellite body 1, solar panel 2, flexible antenna 3, pad 4, receiving slot 41, protrusion 42, pressure strip 5.

[0028] 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

[0029] 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.

[0030] 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 specific posture. If the specific posture changes, the directional indicator will also change accordingly.

[0031] 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.

[0032] 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.

[0033] 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.

[0034] The embodiments of this utility model will now be described in detail with reference to the accompanying drawings.

[0035] like Figures 1 to 5 As shown, the satellite antenna clamping and deployment device without a separate locking and releasing mechanism provided in this embodiment includes: a flexible antenna 3 disposed on the side of the satellite body 1 facing the solar panel 2; when the solar panel 2 is in the locked state, the flexible antenna 3 is bent and placed between the satellite body 1 and the solar panel 2, and is in the clamped state; when the solar panel 2 is deployed, the flexible antenna 3 is deployed accordingly, changing from the clamped state to the natural state.

[0036] Specifically, the flexible antenna 3 can be a tape measure antenna or other flexible linear antenna. One end is fixed to the satellite body 1, and the other end is a free end facing the side of the solar panel 2. When the solar panel 2 is in the locked state, the free end of the flexible antenna 3 is bent and placed between the satellite body 1 and the solar panel 2, in a compressed state. The number of flexible antennas 3 is one or more, determined according to needs. When two or more flexible antennas 3 are set, they can simultaneously face the side of one solar panel 2, or they can face the sides of two solar panels 2, one on the left and one on the right respectively. When simultaneously facing the side of one solar panel 2, they can be set on the same vertical plane, the same horizontal plane, or cross-set on the horizontal plane. For example, when all are set facing the right side of the solar panel 2, two or more flexible antennas 3 can be vertically spaced along the front or rear side; or two or more flexible antennas 3 can be set on the front and rear sides respectively, and then located on the same horizontal plane, or cross-set. When facing the sides of two solar panels 2, the setting method is similar and will not be elaborated here. In addition, the installation and fixing of the flexible antenna 3 is done in a conventional manner, which will not be described in detail here.

[0037] Furthermore, a pad 4 is provided on the satellite body 1 at the location corresponding to the flexible antenna 3. The pad 4 is fixed by means of threads, adhesive, or snap-fit. The pad 4 is strip-shaped, with a length greater than or equal to the length of the flexible antenna 3. Its cross-sectional shape matches the cross-sectional shape of the flexible antenna 3. For example, when the cross-section of the flexible antenna 3 is arc-shaped, the cross-section of the pad 4 can also be set to be arc-shaped accordingly, and the arc-shaped dimension of the pad 4 can be just wrapped by the arc-shaped flexible antenna 3. Alternatively, as shown in this embodiment, receiving grooves 41 can be opened on the left and right sides of the pad 4, and a protrusion 42 can be provided in the middle, so that when the flexible antenna 3 is bent, its cross-section can fit well on the pad 4, reducing the shaking of the flexible antenna 3 under pressure. The pad 4 can be made of lightweight metal, such as aluminum alloy, and a flexible material can be laid on the surface of the lightweight metal. The flexible material can be silicone, PTFE, etc., thereby effectively protecting the flexible antenna 3 from damage caused by rigid contact and extending its service life. Alternatively, the pad 4 can be made of a flexible material, such as PTFE (polytetrafluoroethylene), which can effectively protect the flexible antenna 3 while reducing the overall weight of the satellite.

[0038] Furthermore, a pressure strip 5 is provided on the solar panel 3 at the location corresponding to the flexible antenna 3. The pressure strip 5 is fixed by means of thread, adhesive, or snap-fit. The pressure strip 5 is strip-shaped, and its length is greater than or equal to the length of the flexible antenna 3. The cross-sectional shape is adapted to the cross-sectional shape of the flexible antenna 3. For example, when the cross-section of the flexible antenna 3 is arc-shaped, the cross-section of the pressure strip 5 can also be set to be arc-shaped accordingly, and the arc size of the pressure strip 5 can just wrap around the arc of the flexible antenna 3 to ensure that the flexible antenna 3 has good structural stability after bending, reduce stress concentration, and reduce resonance with the satellite body 1. Alternatively, as shown in this embodiment, when the left and right sides of the pad 4 are provided with receiving grooves 41 and the middle is provided with a protrusion 42, the cross-sectional shape of the pressure strip 5 is adapted to the cross-sectional shape of the protrusion 42 to reduce the overall weight of the satellite structure. The pressure strip 5 can be made of lightweight metal, such as aluminum alloy, and a flexible material is laid on the surface of the lightweight metal. The flexible material can be silicone, PTFE, etc., thereby effectively protecting the flexible antenna 3 from damage caused by rigid contact and extending its service life. Alternatively, the pressure strip 5 can be made of a flexible material, such as PTFE (polytetrafluoroethylene), which can effectively protect the flexible antenna 3 while reducing the overall weight of the satellite.

[0039] During assembly, the flexible antenna 3 is first fixed to the satellite body 1. Then, pads 4 and pressure strips 5 are fixed at corresponding positions on the satellite body 1 and solar panel 2, respectively. Before satellite launch, the solar panel 2 is in a locked state, and the flexible antenna 3 is bent and placed between the satellite body 1 and the solar panel 2, in a compressed state. After the satellite is launched and separated, the solar panel 2 unfolds, and the flexible antenna 3, along with the unfolding of the solar panel 2, transitions from a compressed state to a natural state. The flexible antenna 3 successfully completes its unfolding without the need for additional locking and releasing mechanisms. This not only reduces manufacturing and maintenance costs but also reduces the risk of mission failure due to malfunctions of complex mechanisms.

[0040] 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.

[0041] 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 clamping and unfolding device for a satellite antenna that does not require a separate locking and releasing mechanism, characterized in that, Flexible antennas are installed on the side of the satellite facing the solar panels. When the solar panel is in the locked state, the flexible antenna is bent and placed between the satellite body and the solar panel, and is in a compressed state; When the solar panel is deployed, the flexible antenna also deploys, transitioning from a compressed state to a natural state.

2. The satellite antenna clamping and unfolding device without a separate locking and releasing mechanism according to claim 1, characterized in that, A pad is also provided on the satellite body at the location corresponding to the flexible antenna.

3. The satellite antenna clamping and unfolding device without a separate locking and releasing mechanism according to claim 2, characterized in that, The cross-sectional shape of the pad is adapted to the cross-sectional shape of the flexible antenna.

4. The satellite antenna clamping and unfolding device without a separate locking and releasing mechanism according to claim 3, characterized in that, The pad is made of lightweight metal, and the surface of the lightweight metal is covered with a flexible material.

5. The satellite antenna clamping and unfolding device without a separate locking and releasing mechanism according to claim 3, characterized in that, The pad is made of a flexible material.

6. The satellite antenna clamping and unfolding device without a separate locking and releasing mechanism according to claim 4 or 5, characterized in that, A pressure strip is also provided on the solar panel at the location corresponding to the flexible antenna.

7. The satellite antenna clamping and unfolding device without a separate locking and releasing mechanism according to claim 6, characterized in that, The cross-sectional shape of the pressure strip is adapted to the cross-sectional shape of the flexible antenna.

8. The satellite antenna clamping and unfolding device without a separate locking and releasing mechanism according to claim 6, characterized in that, The pad has receiving grooves on both sides and a protrusion in the middle. The cross-sectional shape of the pressure strip is adapted to the cross-sectional shape of the protrusion.

9. The satellite antenna clamping and unfolding device without a separate locking and releasing mechanism according to claim 7 or 8, characterized in that, The pressure strip is made of lightweight metal, and the surface of the lightweight metal is covered with a flexible material.

10. The satellite antenna clamping and unfolding device without a separate locking and releasing mechanism according to claim 7 or 8, characterized in that, The pressure strip is made of a flexible material.

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