Satellite antenna and unfolding method of satellite antenna

Abstract

The invention provides a satellite antenna and an unfolding method thereof, and relates to the technical field of spaceflight satellites. The satellite antenna is characterized in that the satellite antenna comprises a satellite loading platform, and the shape of the outer contour of the bottom of the satellite loading platform is one of a square and a rectangle; the antenna single board assembly comprises an antenna single board and a cross-board rotating part, and the antenna single board is hinged to the adjacent satellite loading platform or the antenna single board through the cross-board rotating part; the antenna single board assemblies are located in the four areas in the four quadrants, gaps are formed between the antenna single board assembly in one area and the antenna single board assemblies in the other areas, the antenna single board assemblies in the four areas can be independently folded or unfolded, and the satellite antenna has the high unfolding success rate.

Description

Technical Field

[0001] The present application relates to the field of aerospace satellite technology, and in particular to a satellite antenna and a method for deploying the satellite antenna. Background Art

[0002] With the development of space communication technology in various countries, the requirements for satellite antennas to be multifunctional, multi-band, large-capacity, high-power and high-gain are becoming increasingly higher.

[0003] The various antenna units of a satellite antenna are hingedly connected through deployment components, and all antenna units are deployed synchronously. The failure of one deployment component will cause the satellite antenna to fail to deploy successfully. This synchronous deployment method places extremely high demands on the reliability of the deployment components, resulting in a significant increase in the cost of the satellite antenna deployment components and a significant increase in the overall weight of the satellite antenna. Summary of the Invention

[0004] In view of this, the present invention provides a satellite antenna and a deployment method thereof, so as to solve the problem of improving the deployment success rate of the satellite antenna and improving the reliability of the satellite antenna.

[0005] In the first aspect, the present application provides a satellite antenna, comprising: a satellite loading platform, the bottom outer contour of the satellite loading platform is one of a square and a rectangle; an antenna single-board assembly, the antenna single-board assembly includes an antenna single board and a cross-board rotating member, the antenna single board is hinged to the adjacent satellite loading platform or antenna single board through the cross-board rotating member; the antenna single-board assembly is located in four areas within four quadrants, there is a gap between the antenna single-board assembly of one area and the antenna single-board assembly of other areas, and the antenna single-board assemblies of the four areas can be folded or unfolded independently.

[0006] Furthermore, one side of the antenna board is an antenna body, the outer contour of the antenna body is a square or a rectangle, and the outer contour side length of the antenna body is 0.4-0.5 times the outer contour side length of the base component corresponding to the satellite loading platform.

[0007] Furthermore, the cross-board rotating member is located at the edge of the antenna single board, and is used to support the folding or unfolding of the antenna single board. The rotation directions of the cross-board rotating members on different edges of the same antenna single board are opposite, and the rotation directions of the cross-board rotating members on the same edge of the same antenna single board are the same.

[0008] Furthermore, after all the antenna single-board components in the four areas of the satellite antenna are folded, the overall shape of the satellite antenna is one of a cuboid and a cube.

[0009] Furthermore, after the antenna single-board components in the four areas of the satellite antenna are all unfolded, the outer contour shape of the satellite antenna is one of central symmetry and rotational symmetry.

[0010] Furthermore, after the antenna single-board components of the four areas of the satellite antenna are fully unfolded, the outer contour shape of the satellite antenna is one of a square, a rectangle, a cross, a windmill, and a butterfly.

[0011] Furthermore, the other side surface of the antenna board opposite to the antenna body is a solar panel.

[0012] Furthermore, the cross-plate rotating member is driven by a motor or a spring.

[0013] Furthermore, when the cross-board rotating member is driven by a motor, the cross-board rotating member maintains the deployed state of the satellite antenna through a one-way transmission mechanism.

[0014] Furthermore, when the cross-plate rotating member is driven by a spring, the cross-plate rotation maintains the deployed state of the satellite antenna through a limiting mechanism.

[0015] Furthermore, the satellite antenna also includes an antenna single board locking part, which is located at the edge of the antenna single board or the satellite loading platform. After the antenna single board components in the four areas of the satellite antenna are all unfolded, the antenna single board components are locked in the unfolded state.

[0016] In a second aspect, the present application provides a method for deploying a satellite antenna, which is used for the above-mentioned satellite antenna;

[0017] Deployment methods include:

[0018] Controlling the cross-board rotating member to unfold 180 degrees along a first direction to drive the antenna single board to unfold;

[0019] The cross-board rotating member is controlled to expand 180 degrees along the second direction to drive the antenna single board to fully expand.

[0020] Compared with the prior art, the satellite antenna and deployment method provided by the present invention achieve at least the following beneficial effects:

[0021] The present application provides a satellite antenna and a method for deploying the same. By arranging antenna single-board components in four areas within four quadrants in the satellite antenna, and having gaps between the antenna single-board components in one area and the antenna single-board components in other areas, the antenna single-board components in the four areas can be folded or unfolded independently. By arranging a cross-board rotating portion in the satellite antenna that can be folded or unfolded along a first direction and a second direction, respectively, to realize the deployment of the satellite antenna in two directions, a higher folding and unfolding ratio is achieved. The higher folding and unfolding ratio enables the satellite antenna to have a larger antenna aperture in the deployed state (i.e., the working state), meeting the requirements of large capacity, high power, and high gain of the space array antenna; the higher folding and unfolding ratio also enables the satellite antenna to be in the shape of a cuboid or a cube in the folded state (i.e., the retracted state, or the launch state), which is very conducive to the layout in the rocket fairing and can support the launch of multiple satellites with one rocket.

[0022] Of course, any product implementing the present invention does not necessarily need to achieve all of the above technical effects at the same time. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and, together with the description, serve to explain the principles of the invention.

[0024] Figure 1 Shown is a schematic diagram of a satellite antenna provided in an embodiment of the present application;

[0025] Figure 2 Shown is a schematic diagram of a satellite antenna provided in an embodiment of the present application;

[0026] Figure 3 FIG2 is a schematic diagram of a process of deploying a satellite antenna along a first direction according to an embodiment of the present application;

[0027] Figure 4 FIG2 is a schematic diagram of a process of deploying a satellite antenna along a first direction according to an embodiment of the present application;

[0028] Figure 5 FIG2 is a schematic diagram of a process of deploying a satellite antenna along a first direction according to an embodiment of the present application;

[0029] Figure 6 FIG2 is a schematic diagram of a process of deploying a satellite antenna along a first direction according to an embodiment of the present application;

[0030] Figure 7 FIG2 is a schematic diagram of a process of deploying a satellite antenna along a second direction according to an embodiment of the present application;

[0031] Figure 8 FIG2 is a schematic diagram of a process of deploying a satellite antenna along a second direction according to an embodiment of the present application;

[0032] Figure 9 FIG2 is a schematic diagram of a process of deploying a satellite antenna along a second direction according to an embodiment of the present application;

[0033] Figure 10 FIG2 is a schematic diagram showing a satellite antenna provided by an embodiment of the present application divided into four areas;

[0034] Figure 11 The figure shows a schematic diagram of a satellite antenna provided by an embodiment of the present application, in which the entire shape of the satellite antenna is a cube after all four regional antenna panels are folded;

[0035] Figure 12 The figure shows a schematic diagram of a satellite antenna provided by an embodiment of the present application, in which the entire shape of the satellite antenna is a rectangular parallelepiped after all four regional antenna panels are folded;

[0036] Figure 13 The figure shows a schematic diagram of a satellite antenna provided by an embodiment of the present application, in which the outer contour of the satellite antenna is a square after all four regional antenna panels are unfolded;

[0037] Figure 14 The figure shows a schematic diagram of a satellite antenna provided by an embodiment of the present application, in which the outer contour of the satellite antenna is a rectangle after all four regional antenna panels are unfolded;

[0038] Figure 15 The figure shows a schematic diagram of a satellite antenna provided by an embodiment of the present application, in which the outer contour of the satellite antenna is a cross shape after all four regional antenna panels are unfolded;

[0039] Figure 16 The figure shows a schematic diagram of a satellite antenna provided by an embodiment of the present application, in which the outer contour of the satellite antenna is in the shape of a windmill after all four regional antenna panels are unfolded;

[0040] Figure 17 The figure shows a schematic diagram of a satellite antenna provided by an embodiment of the present application, in which the outer contour of the satellite antenna is in the shape of a butterfly after all four regional antenna panels are unfolded;

[0041] Figure 18 FIG2 is a schematic diagram showing the locked positions of the antenna panels of the satellite antenna according to an embodiment of the present application after all four regional antenna panels are unfolded;

[0042] Figure 19 Shown is a flow chart of a satellite antenna deployment method provided in an embodiment of the present application.

[0043] Description of reference numerals:

[0044] 110. Satellite loading platform;

[0045] 120. Antenna single board assembly; 121. Antenna single board; 122. Cross-board rotating member; 1211. Antenna body; 1212. Solar panel;

[0046] 130. Antenna board locking piece. DETAILED DESCRIPTION

[0047] To make the above-mentioned objects, features, and advantages of the present application more clearly understood, the specific embodiments of the present application are described in detail below with reference to the accompanying drawings. The following description sets forth many specific details to facilitate a full understanding of the present application. However, the present application can be implemented in many other ways than those described herein, and those skilled in the art can make similar improvements without violating the scope of the present application. Therefore, the present application is not limited to the specific embodiments disclosed below.

[0048] The following description of at least one exemplary embodiment is merely illustrative in nature and is in no way intended to limit the invention, its application, or uses.

[0049] Technologies, methods, and equipment known to ordinary technicians in the relevant art may not be discussed in detail, but where appropriate, the technologies, methods, and equipment should be considered part of the specification.

[0050] In all examples shown and discussed herein, any specific values ​​should be interpreted as merely exemplary and not limiting. Therefore, other examples of the exemplary embodiments may have different values.

[0051] It should be noted that like reference numerals and letters refer to like items in the following figures, and therefore, once an item is defined in one figure, it need not be further discussed in subsequent figures.

[0052] Figure 1 FIG2 is a schematic diagram of a satellite antenna provided in an embodiment of the present application. Figure 2 The figure shows a schematic diagram of a satellite antenna provided in an embodiment of the present application, referring to Figure 1 and Figure 2 , the present application provides a satellite antenna, comprising:

[0053] The satellite loading platform 110 has a bottom outer contour of a square or a rectangle;

[0054] The antenna single board assembly 120 includes an antenna single board 121 and a cross-board rotating member 122. The antenna single board 121 is hinged to the adjacent satellite loading platform 110 or the antenna single board 121 through the cross-board rotating member 122.

[0055] The antenna single board components 120 are located in four areas within four quadrants. There is a gap between the antenna single board components 120 in one area and the antenna single board components 120 in other areas. The antenna single board components 120 in the four areas can be folded or unfolded independently.

[0056] Specifically, one side of the antenna board 121 is the antenna body 1211, and the outer contour shape of the antenna body 1211 is one of a square and a rectangle. The outer contour side length L of the antenna body 1211 is 0.4-0.5 times the outer contour side length M of the base component of the corresponding satellite loading platform 110.

[0057] Specifically, the cross-board rotating member 122 is located at the edge of the antenna board 121 and is used to support the folding or unfolding of the antenna board 121. The rotation directions of the cross-board rotating members 122 on different edges of the same antenna board 121 are opposite, and the rotation directions of the cross-board rotating members 122 on the same edge of the same antenna board 121 are the same.

[0058] Specifically, after all the antenna single board components 120 in the four regions of the satellite antenna are folded, the overall shape of the satellite antenna is a rectangular parallelepiped or a cube.

[0059] Figure 3 、 Figure 4 、 Figure 5 and Figure 6 FIG2 is a schematic diagram of a process of deploying a satellite antenna along a first direction according to an embodiment of the present application, referring to FIG2. Figure 1 、 Figure 2 、 Figure 3 、 Figure 4 、 Figure 5 and Figure 6 The present application provides an optional embodiment in which when the cross-plate rotating member 122 is folded or unfolded along the first direction, the satellite antenna is folded or unfolded along the first direction.

[0060] Specifically, one end of the cross-board rotating member 122 is connected to the edge of the antenna single board 121 , and the other end is connected to the edge of another antenna single board 121 .

[0061] The first direction unfolding process is specifically as follows: when the antenna single board 121 is in a folded state, the unfolding angle of the cross-board rotating member 122 is 0 degrees; when the antenna single board 121 is in the unfolding process, the cross-board rotating member 122 unfolds from 0 degrees to 90 degrees and 180 degrees in sequence.

[0062] Figure 6 、 Figure 7 、 Figure 8 and Figure 9 FIG2 is a schematic diagram of a process of deploying a satellite antenna along a second direction according to an embodiment of the present application, referring to FIG2. Figure 1 、 Figure 2 、 Figure 6 、 Figure 7 、 Figure 8 and Figure 9 The present application provides an optional embodiment in which when the cross-plate rotating member 122 is folded or unfolded along the second direction, the satellite antenna is folded or unfolded along the second direction.

[0063] Specifically, one end of the cross-board rotating member 122 is connected to the edge of the antenna single board 121 , and the other end is connected to the edge of another antenna single board 121 .

[0064] The second direction unfolding process is specifically as follows: when the antenna single board 121 is in a folded state, the unfolding angle of the cross-board rotating member 122 is 0 degrees; when the antenna single board 121 is in the unfolding process, the cross-board rotating member 122 unfolds from 0 degrees to 90 degrees and 180 degrees in sequence.

[0065] Reference Figures 3 to 8 After the cross-board rotating member 122 is folded or unfolded along the first direction, the cross-board rotating member 122 is folded or unfolded along the second direction; the satellite antenna can be unfolded in two directions, and the antenna diameter can be larger.

[0066] Figure 2 The figure shows a schematic diagram of a satellite antenna provided in an embodiment of the present application, referring to Figure 2 The outer contour side length L of the antenna body 1211 is 0.4-0.5 times the outer contour side length M of the base component of the corresponding satellite loading platform 110; so that the antenna single board 121 presents a 2X2 arrangement after folding, and the projection outline of the antenna single board 121 does not exceed the outer contour of the base component of the corresponding satellite loading platform 110.

[0067] Figure 10 The satellite antenna provided in the embodiment of the present application is divided into four areas. Figure 10 The satellite antenna is divided into 4 areas, and the antenna single board 121 in each area can be folded or unfolded independently; when unfolded independently, if one area fails to unfold, the remaining areas can still work normally, and at least 75% of the antenna performance can be retained.

[0068] Figure 11 The figure shows a schematic diagram of a satellite antenna provided by an embodiment of the present application, which is divided into four areas and has a cube shape after all antenna panels are folded. Figure 12 The satellite antenna provided by the embodiment of the present application is divided into 4 areas. After all the antenna panels are folded, the satellite antenna is in the shape of a rectangular parallelepiped. Figure 11 , Figure 12 The satellite antenna is divided into four areas. When the antenna single board 121 is folded, the overall shape of the satellite antenna is a rectangular parallelepiped or a cube.

[0069] The specific description is as follows: when the satellite antenna is in the folded state (i.e., the retracted state, or the launch state), the lengths of the two sides of the outer contour of the base component of the satellite loading platform 110 and the corresponding outer contour side lengths of the antenna single board 121 with four partitions folded and stacked together on the base component of the satellite loading platform 110 are basically the same length, so that the overall shape of the satellite antenna is a rectangular parallelepiped or a cube, which is very beneficial for the layout of the satellite antenna in the rocket fairing and can support the launch of multiple satellites with one rocket.

[0070] Figure 13 The satellite antenna provided by the embodiment of the present application is divided into 4 areas. When all antenna panels are unfolded, the outer contour of the satellite antenna is a square. Figure 13 The satellite antenna is divided into four areas. When the antenna single board 121 is fully unfolded, the outer contour of the satellite antenna is a square; it can support flexible and diverse beam scanning working modes and complex beam pointing requirements of the satellite antenna.

[0071] The specific details are as follows: the four partitions of the satellite antenna can be unfolded independently, and the outer contour shapes of the four partitions when unfolded independently are all square. After all four partitions are unfolded, the outer contour shape of the satellite antenna is a square; it can support the satellite antenna's flexible and diverse beam scanning working modes and complex beam pointing requirements.

[0072] Figure 14 The satellite antenna provided in the embodiment of the present application is divided into four areas. When all antenna panels are unfolded, the outer contour of the satellite antenna is a rectangular schematic diagram. Figure 14 The satellite antenna is divided into four areas. When the antenna single board 121 is fully unfolded, the outer contour of the satellite antenna is a rectangle.

[0073] The specific details are as follows: the four partitions of the satellite antenna can be unfolded independently, and the outer contour shapes of the four partitions when unfolded independently are all rectangular, and the long side or short side of the rectangle is at the bottom (shown in the figure) or the side (shown in the figure). When all four partitions are fully unfolded, the outer contour shape of the satellite antenna is a rectangle; it can support the satellite antenna's flexible and diverse beam scanning working modes and complex beam pointing requirements.

[0074] Figure 15 The satellite antenna provided in the embodiment of the present application is divided into four areas. When all antenna panels are unfolded, the outer contour of the satellite antenna is a cross. Figure 15 The satellite antenna is divided into four areas. When the antenna single board 121 is fully unfolded, the outer contour of the satellite antenna is a cross.

[0075] The specific details are as follows: the four partitions of the satellite antenna can be unfolded independently. The outer contour shape of the independently unfolded zone A is a square with a missing corner in the lower left corner, the outer contour shape of the independently unfolded zone B is a square with a missing corner in the upper left corner, the outer contour shape of the independently unfolded zone C is a square with a missing corner in the upper right corner, and the outer contour shape of the independently unfolded zone D is a square with a missing corner in the lower right corner. After all four partitions are unfolded, the outer contour shape of the satellite antenna is a cross; it can support the satellite antenna's flexible and diverse beam scanning working modes and complex beam pointing requirements.

[0076] Figure 16 The satellite antenna provided in the embodiment of the present application is divided into four areas. When all antenna panels are unfolded, the outer contour of the satellite antenna is in the shape of a windmill. Figure 16 The satellite antenna is divided into four areas. When the antenna single board 121 is fully unfolded, the outer contour of the satellite antenna is in the shape of a windmill.

[0077] The specific details are as follows: The four partitions of the satellite antenna can be unfolded independently. The outer contour shape of the independently unfolded area A and area C is a rectangle with the long side (pictured) at the bottom. The outer contour shape of the independently unfolded area B and area D is a rectangle with the short side (pictured) at the bottom. After all four partitions are unfolded, the outer contour shape of the satellite antenna is a windmill shape.

[0078] Figure 17 The satellite antenna provided by the embodiment of the present application is divided into 4 areas. When the antenna panels are fully unfolded, the outer contour of the satellite antenna is in the shape of a butterfly. Figure 17 The satellite antenna is divided into four areas. When the antenna single board 121 is fully unfolded, the outer contour of the satellite antenna is in the shape of a butterfly.

[0079] The specific details are as follows: The four partitions of the satellite antenna can be unfolded independently. The outer contour shape of the independently unfolded zone A is a square with a corner missing in the lower left corner, the outer contour shape of the independently unfolded zone C is a square with a corner missing in the upper right corner, and the outer contour shape of the independently unfolded zones B and D is a square. After all four partitions are unfolded, the outer contour shape of the satellite antenna is a butterfly shape.

[0080] Please refer to Figure 13 、 Figure 14 、 Figure 15 、 Figure 16 and Figure 17 The satellite antenna is divided into four areas. When the antenna single board 121 is fully unfolded, the outer contour of the satellite antenna is one of central symmetry and rotational symmetry.

[0081] The specific explanation is as follows: When the satellite antenna is in working state, attitude control is required to ensure that the surface where the antenna body 1211 on the antenna board 121 is located is always aligned with the ground; the outer contour shape of the satellite antenna is centrally symmetrical and rotationally symmetrical, which greatly reduces the control torque of active attitude control or passive attitude control, thereby reducing the cost of attitude control and improving the reliability of state control.

[0082] Please refer to Figure 13 、 Figure 14 、 Figure 15 、 Figure 16 and Figure 17 After the antenna single board 121 of the satellite antenna, which is divided into four areas, is fully unfolded, the satellite loading platform 110 is located near the geometric center of the outer contour of the satellite antenna.

[0083] The specific explanation is as follows: the satellite loading platform 110 is located near the geometric center of the outer contour of the satellite antenna, which can simplify and optimize various feeding networks and monitoring networks between the satellite loading platform and the antenna board 121. For example, in order to ensure the radiation performance of the antenna body 1211, it is necessary to connect multiple equal-length feeding networks and monitoring networks of different types between the satellite loading platform and each antenna board 121; the length of the feeding network and monitoring network between the antenna board 121 farthest from the satellite loading platform 110 and the satellite loading platform 110 determines the length of all feeding networks and monitoring networks that need to be connected with equal lengths; when the satellite loading platform 110 is located near the geometric center of the outer contour of the satellite antenna, the length of the feeding network and monitoring network between the antenna board 121 farthest from the satellite loading platform 110 and the satellite loading platform 110 is the smallest, and the sum of the lengths of all feeding networks and monitoring networks that need to be connected with equal lengths is the optimal value.

[0084] Reference Figure 2 The other side of the antenna board 121 opposite to the antenna body 1211 is a solar panel 1212 .

[0085] The specific description is as follows: On one plane of the antenna board 121, there is an antenna body 1211 that can communicate, and on the opposite plane there is a solar panel 1212 that can convert solar energy into satellite energy. This is a communication satellite that integrates the antenna body 1211 and the solar panel 1212, which is called "wing-array integration". This design makes the antenna board 121 easier to fold, and at the same time, solar energy can be used to power the TR component of the antenna body 1211 nearby, resulting in less power loss.

[0086] Optionally, the cross-plate rotating member 122 is driven by a motor or a spring.

[0087] Specifically, when the cross-plate rotating member 122 is driven by a motor, the cross-plate rotating member 122 maintains the satellite antenna in an unfolded state through a one-way transmission mechanism.

[0088] The motor drive principle is explained below: for example, when the cross-plate rotating member 122 is relatively close to the base component of the satellite loading platform 110, the bending moment borne by the cross-plate rotating member 122 may be large. In order to improve the reliability of the cross-plate rotating member 122, the cross-plate rotating member 122 can be driven by a motor. The motor is embedded in the cross-plate rotating member 122 and can be used for relative rotation of the cross-plate rotating member 122. The motor step angle is very small, and very precise rotation angle position control can be achieved; at the same time, the motor response speed is also very fast, and the rotation angle adjustment can be completed in a very short time; when the rotation angle reaches the specified angle (the specified angle can be the rotation angle that needs to be temporarily fixed during the staged deployment process, or it can be the rotation angle that needs to be fixed after the satellite antenna is fully deployed), the motor maintains the satellite antenna in the process deployment state or the fully deployed state through self-locking.

[0089] Specifically, when the cross-plate rotating member 122 is driven by a spring, the cross-plate rotating member 122 maintains the deployed state of the satellite antenna through the limiting mechanism.

[0090] The following explains the principle of spring actuation: For example, near the outer edge of the satellite antenna's antenna boards 121, to reduce the cost of connecting these antenna boards 121, the cross-board rotating members 122 connecting adjacent antenna boards 121 can be spring-driven. This spring actuation can be triggered by a release mechanism. After the cross-board rotating members 122 are deployed, a limit mechanism maintains the satellite antenna in its deployed state. This limit mechanism can have a spring pressure limiter on one end and a structural limiter on the other, or it can have structural limits on both ends.

[0091] Figure 18 The satellite antenna provided in the embodiment of the present application is divided into 4 areas. The antenna single board is fully unfolded and the antenna single board is locked in a schematic diagram. Figure 18 The satellite antenna also includes an antenna single board locking member 130, which is located at the edge of the antenna single board 121 or the base component of the satellite loading platform 110. After the satellite antenna is unfolded, the antenna single board 121 adjacent to the antenna single board locking member 130 is locked in the unfolded state.

[0092] The locking principle is explained below: For example, when the satellite antenna is fully deployed, the connection and locking between the antenna panels 121 rely solely on the cross-panel rotating member 122. The base component of the satellite loading platform 110 serves as the initial connection base, sequentially connecting the cross-panel rotating member 122 and the antenna panels 121 to form a very long series connection component, similar to a long cantilever component with a bend. When the satellite antenna is operating or changing orbits, the cross-panel rotating member 122 will be subjected to large and / or varying bending moments due to various operating conditions. Large and / or varying bending moments can cause a number of problems, such as fatigue failure of the cross-panel rotating member 122, which reduces the on-orbit lifespan of the satellite antenna. For example, deformation of the cross-panel rotating member 122 affects the surface flatness of the surface where the multiple antenna bodies 1211 of the satellite antenna are located, directly affecting the radiation performance of the satellite antenna. After the satellite antenna is deployed, in addition to maintaining the deployed state of the satellite antenna through the locking of the cross-board rotating member 122 itself, additional antenna single-board locking members 130 can be added between the base component of the satellite loading platform 110 and the adjacent antenna single board 121, as well as between adjacent antenna single boards 121. Through the locking of the antenna single-board locking member 130, it works together with the cross-board rotating member 122 to maintain the deployed state of the satellite antenna, reduce the bending moment of the cross-board rotating member 122, slow down the fatigue damage of the cross-board rotating member 122, and extend the on-orbit life of the satellite antenna.

[0093] The antenna board locking component 130 can be any component with a locking function, such as an electric locking component, a gas-controlled locking component, a mechanical locking component, a magnetic locking component, or a memory alloy locking component.

[0094] Figure 19 The figure shows a flow chart of the satellite antenna deployment method provided by the embodiment of the present application, combined with Figures 3 to 9 , and refer to Figure 19 , based on the same inventive concept, the present application also provides a method for deploying a satellite antenna, which is used for the aforementioned satellite antenna;

[0095] Deployment methods include:

[0096] Step 101: Control the cross-board rotating member 122 to expand 180 degrees along a first direction to drive the antenna board 121 to expand;

[0097] Step 102 : Control the cross-board rotating member 122 to unfold 180 degrees along the second direction to drive the antenna board 121 to fully unfold.

[0098] Specifically, the satellite antenna deployment method includes step 101. When the antenna single board 121 is in a folded state, the deployment angle of the cross-board rotating member 122 is 0 degrees; when the antenna single board 121 is in the deployment process, the cross-board rotating member 122 is deployed from 0 degrees to 90 degrees and 180 degrees in sequence.

[0099] The components involved in step 101 have the following connection and positional relationships: one end of the cross-board rotating member 122 is connected to the edge of the antenna single board 121 , and the other end is connected to the edge of another antenna single board 121 .

[0100] The satellite antenna deployment method also includes step 102, when the antenna single board 121 is in a folded state, the deployment angle of the cross-board rotating member 122 is 0 degrees; when the antenna single board 121 is in the deployment process, the cross-board rotating member 122 is deployed from 0 degrees to 90 degrees and 180 degrees in sequence.

[0101] The components involved in step 102 have the following connection and positional relationships: one end of the first cross-board rotating member 122 is connected to the edge of the base member of the satellite loading platform 110, and the other end is connected to the edge of the antenna single board 121; one end of the remaining cross-board rotating members 122 is connected to the edge of the antenna single board 121, and the other end is connected to the edge of another antenna single board 121; one end of the cross-board rotating member 122 is connected to the edge of the antenna single board 121, and the other end is connected to the edge of another antenna single board 121;

[0102] In the present application, after the cross-plate rotating member 122 is folded or unfolded along the first direction, the cross-plate rotating member 122 is folded or unfolded along the second direction; the satellite antenna can be unfolded in two directions, and the antenna diameter can be made larger.

[0103] It should be noted that the satellite antenna provided in this application can be any satellite antenna with antenna function, such as: communication satellite antenna, meteorological satellite antenna, reconnaissance satellite antenna, navigation satellite antenna, geodetic satellite antenna, earth resources satellite antenna, interceptor satellite antenna and multi-purpose satellite antenna.

[0104] It can be seen from the above embodiments that the satellite antenna and deployment method thereof provided by the present invention achieve at least the following beneficial effects:

[0105] Most or all of the following technical effects are achieved simultaneously: the satellite antenna supports bidirectional deployment; in the deployed state (i.e., working state), it has a larger antenna aperture; a simple deployment mechanism; a higher folding / expansion ratio; in the folded state (i.e., retracted state, or called launching state), the shape is a rectangular parallelepiped or cube-shaped; in the deployed state (i.e., working state), the antenna cross-sectional shape is diversified; in the deployed state (i.e., working state), the satellite loading platform is located near the geometric center of the space array antenna.

[0106] Although some specific embodiments of the present invention have been described in detail by way of examples, it should be understood by those skilled in the art that the above examples are for illustration only and are not intended to limit the scope of the present invention. It should be understood by those skilled in the art that modifications may be made to the above embodiments without departing from the scope and spirit of the present invention. The scope of the present invention is defined by the appended claims.

Claims

1. A satellite antenna, characterized in that: include: A satellite loading platform (110), wherein the bottom outer contour of the satellite loading platform (110) is in the shape of a square or a rectangle; An antenna single board assembly (120), the antenna single board assembly (120) comprising an antenna single board (121) and a cross-board rotating member (122), the antenna single board (121) being hinged to an adjacent satellite loading platform (110) or antenna single board (121) via the cross-board rotating member (122); The antenna single board components (120) are located in four areas within four quadrants, with gaps between the antenna single board components (120) in one area and the antenna single board components (120) in other areas, and the antenna single board components (120) in the four areas can be folded or unfolded independently.

2. The satellite antenna according to claim 1, wherein: One side surface of the antenna single plate (121) is an antenna body (1211), the outer contour of the antenna body (1211) is a square or a rectangle, and the outer contour side length of the antenna body (1211) is 0.4-0.5 times the outer contour side length of the base component corresponding to the satellite loading platform (110).

3. The satellite antenna according to claim 1, wherein: The cross-board rotating member (122) is located at the edge of the antenna single board (121) and is used to support the folding or unfolding of the antenna single board (121); the cross-board rotating members (122) at different edges of the same antenna single board (121) rotate in opposite directions, while the cross-board rotating members (122) at the same edge of the same antenna single board (121) rotate in the same direction.

4. The satellite antenna according to claim 1, wherein: After the antenna single-board components (120) in the four areas of the satellite antenna are all folded, the overall shape of the satellite antenna is one of a cuboid and a cube.

5. The satellite antenna according to claim 1, wherein: After the antenna single-board components (120) in the four regions of the satellite antenna are fully unfolded, the outer contour shape of the satellite antenna is one of central symmetry and rotational symmetry.

6. The satellite antenna according to claim 5, characterized in that When the antenna single-board components (120) in the four regions of the satellite antenna are fully unfolded, the outer contour of the satellite antenna is in the shape of a square, a rectangle, a cross, a windmill, or a butterfly.

7. The satellite antenna according to claim 2, wherein: The other side surface of the antenna single board (121) opposite to the antenna body (1211) is a solar panel (1212).

8. The satellite antenna according to claim 1, wherein: The cross-plate rotating member (122) is driven by a motor or a spring.

9. The satellite antenna according to claim 8, characterized in that When the cross-board rotating member (122) is driven by a motor, the cross-board rotating member (122) maintains the unfolded state of the satellite antenna through a one-way transmission mechanism.

10. The satellite antenna according to claim 8, characterized in that When the cross-plate rotating member (122) is driven by a spring, the cross-plate rotating member (122) maintains the unfolded state of the satellite antenna through a limiting mechanism.

11. The satellite antenna according to claim 1, wherein: The satellite antenna further comprises an antenna single board locking member (130), wherein the antenna single board locking member (130) is located at the edge of the antenna single board (121) or the satellite loading platform (110), and locks the antenna single board assembly (120) in the unfolded state after the antenna single board assembly (120) in the four areas of the satellite antenna are fully unfolded.

12. A method for deploying a satellite antenna, characterized in that: A satellite antenna as claimed in any one of claims 1 to 11; The expansion method includes: Controlling the cross-board rotating member to unfold 180 degrees along a first direction to drive the antenna single board to unfold; The cross-board rotating member is controlled to expand 180 degrees along the second direction to drive the antenna single board to fully expand.

Images