Three-dimensional storage and retrieval method for satellite antenna based on Archimedean spiral orbit

Abstract

The present invention relates to a three-dimensional storage and access method for satellite antennas based on Archimedean spiral tracks, wherein the three-dimensional storage for satellite antennas comprises: a storage shell, comprising a top plate, a bottom plate and a side plate, wherein the top plate, the bottom plate and the side plate together form a hollow chamber, and a hatch that can be opened and closed is arranged on the side plate; an antenna track, which is in the shape of an Archimedean spiral, and the antenna track is arranged in the hollow chamber; an antenna interface, comprising a connector and a connecting end, wherein a groove is arranged on the connecting end, and the groove is adapted to the antenna track, and the antenna interface is connected to the antenna track through the groove; a foldable satellite antenna, comprising an antenna back frame, wherein the antenna back frame is connected to the connector, and the foldable satellite antenna is vertically hoisted in the hollow chamber. The present invention can be adapted to the limited fairing space, and is convenient for launching the three-dimensional storage of satellite antennas into orbit and for accessing satellite antennas, and can avoid collisions between satellite antennas to cause damage.

Description

Technical Field

[0001] The present invention mainly relates to the technical field of satellite antenna storage, and in particular to a three-dimensional storage and access method for satellite antennas based on an Archimedean spiral track. Background Art

[0002] In the current field of satellite antenna storage, existing storage technology has many shortcomings.

[0003] Prior art 1 (Announcement No.: CN116062362B) discloses a space storage device, which is designed mainly for the storage of modular cubic satellite units. However, its internal S-shaped extension design requires the installation of a fixed interface on the side of the folded antenna, which undoubtedly increases the difficulty of antenna development. In addition, the device relies on a conveyor belt and a drive unit for movement, and this design cannot meet the vibration isolation requirements of the antenna module during transportation.

[0004] Prior art 2 (Announcement No.: CN114084553B) discloses a space storage system, which is designed mainly for storing cubic cargo and cannot meet the storage requirements of high focal diameter ratio antenna modules. The system does not consider the fixing device of the cargo in the cargo hold, which may cause the cargo to be damaged due to collision during the launch process.

[0005] Prior art 3 (publication number: CN113232890A) discloses a micro-satellite on-orbit release device, in which each group of satellite units requires a launch sleeve, which increases the mass of the storage system. The device can only realize the direction-controlled launch of satellite units and cannot cooperate with the installation robot to install the antenna module to the specified position.

[0006] Prior art 4 (Announcement No.: CN113581502B) discloses an on-orbit assembly method for a super-large space telescope based on a multi-space robot system, which is mainly used to store the disassembled optical telescope modules. However, the volume and envelope of these modules are small, and cannot meet the space requirements for storing high focal diameter ratio antenna modules. This method mainly relies on super-redundant space robots to complete the handling of modules in the shelves. The robot needs to go deep into the cargo warehouse and then move the module out. This puts a heavy burden on the robot, has low handling efficiency, and cannot operate large mass modules.

[0007] In view of the limitations of existing technologies, especially when the satellite antenna storage system needs to be launched into orbit through limited fairing space and rockets, the existing storage methods are not applicable. Therefore, it is necessary to design a three-dimensional storage system that is convenient for launching into orbit and storing and retrieving satellite antennas. Summary of the invention

[0008] The technical problem to be solved by the present application is to provide a three-dimensional storage and retrieval method for satellite antennas based on an Archimedean spiral orbit, which can be adapted to the limited fairing space, facilitate the launch of the three-dimensional satellite antenna storage into orbit and the storage and retrieval of satellite antennas, and avoid damage caused by collisions between satellite antennas.

[0009] The technical solution adopted by the present application to solve the above-mentioned technical problems is a three-dimensional storage for satellite antennas based on an Archimedean spiral track, comprising: a storage shell, comprising a top plate, a bottom plate and a side plate, the top plate, the bottom plate and the side plate together form a hollow chamber, and the side plate is provided with a switchable hatch; an antenna track, in the shape of an Archimedean spiral, the antenna track is arranged in the hollow chamber; an antenna interface, comprising a connector and a connecting end, the connecting end is provided with a groove, the groove is adapted to the antenna track, and the antenna interface is connected to the antenna track through the groove; a foldable satellite antenna, comprising an antenna back frame, the antenna back frame is connected to the connector, and the foldable satellite antenna is vertically hoisted in the hollow chamber.

[0010] In one embodiment of the present application, the antenna track is arranged in multiple layers, and each layer of the antenna track is provided with a first beam and a second beam that intersect each other, and an intersection is formed between the first beam and the second beam. The multiple layers of antenna tracks are connected by connecting beams and the intersection, and the height between the multiple layers of antenna tracks is greater than or equal to the height of the foldable satellite antenna.

[0011] In one embodiment of the present application, the cross-section of the antenna track is I-shaped, the groove includes a recessed portion and a protruding portion, and the antenna interface is connected to the antenna track in a barbed manner through the groove.

[0012] In one embodiment of the present application, the antenna track is an electromagnetic track, and the antenna interface can be suspended on the antenna track and can move along the antenna track by electromagnetic suspension.

[0013] In one embodiment of the present application, the three-dimensional satellite antenna storage also includes an assembly robot. The surface of the storage shell is provided with a slide rail. The assembly robot is used to move along the slide rail to the openable and closeable cabin door to take out and / or store the foldable satellite antenna.

[0014] In one embodiment of the present application, the storage shell is cylindrical.

[0015] In one embodiment of the present application, solar cells are provided on the surface of one or more of the top plate, the bottom plate and the side plates, and the solar cells are used to provide energy for the three-dimensional storage of satellite antennas.

[0016] In one embodiment of the present application, a battery, a main control board and a temperature sensor are arranged in the hollow chamber. The battery is used to provide energy for the three-dimensional storage of satellite antennas, the main control board is used to control the movement of the antenna interface, and the temperature sensor is used to monitor the temperature in the hollow chamber.

[0017] In order to solve the above-mentioned technical problems, the present application also proposes a satellite antenna storage and access method, which is used to store and access satellite antennas using the above-mentioned satellite antenna three-dimensional storage, including: satellite antenna storage steps: Step Sa1: open the switchable cabin door; Step Sa2: connect the foldable satellite antenna and the antenna interface; Step Sa3: control the antenna interface to slide from the outside to the inside along the Archimedean spiral antenna track to drive the foldable satellite antenna to move to a preset position; Step Sa4: close the switchable cabin door; and satellite antenna removal steps: Step Sb1: open the switchable cabin door; Step Sb2: control the antenna interface to slide from the inside to the outside along the Archimedean spiral antenna track to drive the foldable satellite antenna to move to the switchable cabin door; Step Sb3: remove the foldable satellite antenna from the antenna interface; Step Sb4: close the switchable cabin door.

[0018] The technical solution of the present application can be used to store and release foldable satellite antennas in orbit. The storage shell can allow the foldable satellite antenna to adapt to thermal control and avoid micrometeorite impacts; the antenna interface can be used to firmly connect the foldable satellite antenna; by designing the antenna track as an Archimedean spiral, the number of foldable satellite antennas that can be stored can be maximized within the limited fairing space, and when taking out the antenna, it can be slid out along the spiral track from the inside to the outside, making it easy to store and retrieve the antenna; by vertically hoisting the foldable satellite antenna in the hollow chamber, it can be avoided that the antennas collide with each other and cause damage. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] In order to make the above-mentioned objects, features and advantages of the present application more obvious and easy to understand, the specific implementation methods of the present application are described in detail below with reference to the accompanying drawings, wherein:

[0020] Figure 1 is a three-dimensional diagram of a foldable satellite antenna in an unfolded state in one embodiment of the present application;

[0021] Figure 2 is a front view of a foldable satellite antenna in an unfolded state in one embodiment of the present application;

[0022] Figure 3 is a top view of a foldable satellite antenna in an unfolded state in one embodiment of the present application;

[0023] Figure 4 is a three-dimensional diagram of a foldable satellite antenna in a folded state in one embodiment of the present application;

[0024] Figure 5 This is a front view of a foldable satellite antenna in a folded state in one embodiment of the present application;

[0025] Figure 6 is a top view of a foldable satellite antenna in a folded state in one embodiment of the present application;

[0026] Figure 7 is an exemplary perspective view of a three-dimensional storage of satellite antennas according to an embodiment of the present application;

[0027] Figure 8 This is an exemplary perspective view of a three-dimensional satellite antenna storage fully loaded with antennas according to an embodiment of the present application;

[0028] Fig. 9 is a schematic diagram of an assembly robot and a storage housing in one embodiment of the present application;

[0029] Fig.10 is a top view of a storage housing in one embodiment of the present application;

[0030] Fig.11 is a front view of a storage housing in one embodiment of the present application;

[0031] Fig.12 is a schematic diagram of an antenna track in an embodiment of the present application;

[0032] Fig.13 is a top view of an antenna track in an embodiment of the present application;

[0033] Fig.14 is a bottom view of an antenna track in one embodiment of the present application;

[0034] Fig.15 is a schematic diagram of a multi-layer antenna track connected in series in one embodiment of the present application;

[0035] Fig.16 is a front view of a multi-layer antenna track connected in series in one embodiment of the present application;

[0036] Fig.17 is a schematic diagram of an antenna interface in an embodiment of the present application;

[0037] Fig.18 is a front view of an antenna interface in an embodiment of the present application;

[0038] Fig.19 is a side view of an antenna interface in an embodiment of the present application;

[0039] Fig. 20 is a top view of an antenna interface in an embodiment of the present application;

[0040] Fig.21 is a schematic diagram of the connection between a foldable satellite antenna and an antenna track in one embodiment of the present application;

[0041] Fig. 22 is along Fig.21 The cross-sectional structural diagram of the AA' line shown in FIG.

[0042] Fig.23is a top view of an antenna track with a preset antenna storage position in an embodiment of the present application;

[0043] Fig.24 is a top view of an antenna track fully loaded with antennas in one embodiment of the present application;

[0044] Fig.25 is a side view of the connection between a foldable satellite antenna and an antenna track in one embodiment of the present application;

[0045] Fig.26 is an exemplary flow chart of sliding out foldable satellite antennas one by one from the antenna track in a step-by-step manner in one embodiment of the present application;

[0046] Fig. 27 is a schematic diagram of a single-layer antenna track fully loaded with antennas in one embodiment of the present application;

[0047] Fig.28 is a schematic diagram of a multi-layer antenna track fully loaded with antennas in one embodiment of the present application;

[0048] Fig.29 is a schematic diagram of an embodiment of the present application when all antenna tracks are fully loaded with antennas;

[0049] Fig.30 It is an exemplary flow chart of a satellite antenna access method according to an embodiment of the present application.

[0050] Description of the accompanying drawings in the specific implementation manner:

[0051] 100. Three-dimensional storage for satellite antennas; 101. Storage shell; 1011. Top plate; 1012. Bottom plate; 1013. Side plate; 10131. Solar cell panel; 1014. Openable hatch; 1015. Hollow chamber; 10151. Storage battery; 10152. Main control board; 10153. Temperature sensor; 1016. Slide rail; 102. Antenna track; 1021. First crossbeam; 1022. Second crossbeam; 1023. Intersection; 1024. Connecting beam; 103. Antenna interface; 1031. Connector; 1032. Connecting end; 1033. Groove; 1034. Recessed portion; 1035. Protrusion; 104. Foldable satellite antenna; 1041. Antenna back frame; 105. Assembly robot. DETAILED DESCRIPTION

[0052] In order to make the above-mentioned objects, features and advantages of the present application more obvious and easy to understand, the specific implementation methods of the present application are described in detail below with reference to the accompanying drawings.

[0053] In the following description, many specific details are set forth to facilitate a full understanding of the present application, but the present application may also be implemented in other ways different from those described herein, and therefore the present application is not limited to the specific embodiments disclosed below.

[0054] As shown in this application and claims, unless the context clearly indicates an exception, the words "a", "an", "an" and / or "the" do not refer to the singular and may also include the plural. Generally speaking, the terms "include" and "comprise" only indicate the inclusion of the steps and elements that have been clearly identified, and these steps and elements do not constitute an exclusive list. The method or device may also include other steps or elements.

[0055] Flowcharts are used in the present application to illustrate the operations performed by the system according to the embodiments of the present application. It should be understood that the preceding or following operations are not necessarily performed accurately in order. On the contrary, various steps may be processed in reverse order or simultaneously. At the same time, other operations may be added to these processes, or one or more operations may be removed from these processes.

[0056] The present application proposes a three-dimensional satellite antenna storage based on an Archimedean spiral orbit, which can be used in application scenarios where it is necessary to adapt the fairing space and launch the three-dimensional satellite antenna storage into orbit, as well as to store and retrieve satellite antennas in orbit.

[0057] Figure 4 is a three-dimensional diagram of a foldable satellite antenna in a folded state in one embodiment of the present application, Figure 7 is an exemplary perspective view of a three-dimensional storage of satellite antennas according to an embodiment of the present application. Fig.17 is a schematic diagram of an antenna interface in an embodiment of the present application, Fig.21 It is a schematic diagram of the connection between a foldable satellite antenna and an antenna track in one embodiment of the present application.

[0058] refer to Figure 4 , Figure 7 , Fig.17 , Fig.21 As shown, the three-dimensional satellite antenna storage 100 based on the Archimedean spiral track of this embodiment includes: a storage shell 101 (such as Figure 7 As shown in FIG. 1 ), the antenna includes a top plate 1011, a bottom plate 1012 and a side plate 1013, wherein the top plate 1011, the bottom plate 1012 and the side plate 1013 together form a hollow chamber 1015, and a hatch 1014 that can be opened and closed is provided on the side plate 1013; an antenna track 102, which is in the shape of an Archimedean spiral, is provided in the hollow chamber 1015; an antenna interface 103 (as shown in FIG. Fig.17), including a connector 1031 and a connector end 1032, a groove 1033 is provided on the connector end 1032, the groove 1033 is adapted to the antenna track 102, and the antenna interface 103 is connected to the antenna track 102 through the groove 1033; the foldable satellite antenna 104 (as shown Figure 4 ), including an antenna back frame 1041, the antenna back frame 1041 is connected to the connecting member 1031, and the foldable satellite antenna 104 is vertically hoisted in the hollow chamber 1015 (as shown in FIG. Fig.21 shown).

[0059] Fig.10 is a top view of a storage housing in one embodiment of the present application, Fig.11 2 is a front view of a storage shell in one embodiment of the present application. Figure 7 , Fig.10 and Fig.11 As shown, in some embodiments, the storage housing 101 is cylindrical. For example, the switchable hatch 1014 on the side panel 1013 of the storage housing 101 can be configured to be opened or closed by a hinge, such as Fig.10 The state of the foldable hatch 1014 being opened is shown in FIG. The present application can make the foldable satellite antenna 104 in the hollow chamber 1015 adapt to thermal control and avoid micro-meteorite impact by providing the storage shell 101.

[0060] Fig.12 is a schematic diagram of an antenna track in an embodiment of the present application, Fig.13 is a top view of an antenna track in an embodiment of the present application, Fig.14 is a bottom view of the antenna track in one embodiment of the present application. Figure 12 to Figure 14 As shown, the Archimedean spiral antenna track 102 is a spiral structure as a whole. The present application sets the antenna track 102 in the Archimedean spiral shape, which can be matched with the cylindrical storage shell 101. This configuration enables the satellite antenna three-dimensional storage 100 to be adapted to the circular fairing space (not shown), thereby maximizing the utilization efficiency of the fairing space and facilitating the launch of the satellite antenna three-dimensional storage 100 into orbit.

[0061] Fig.18 is a front view of an antenna interface in an embodiment of the present application, Fig.19 is a side view of an antenna interface in an embodiment of the present application, Fig. 20 is a top view of an antenna interface in one embodiment of the present application. Figures 17 to 20As shown, the antenna interface 103 of the present application is equivalent to the installation interface of the antenna, and the connector 1031 on the antenna interface 103 can fix the foldable satellite antenna 104. By setting the connector 1031 to a disc shape, it can better adapt to the state of the folded foldable satellite antenna 104, and the number of foldable satellite antennas 104 mounted on the antenna track 102 can be maximized under the load weight constraint. In actual applications, the connector 1031 can be set to other shapes, and this application does not limit it.

[0062] Fig.23 is a top view of an antenna track with a preset antenna storage position in an embodiment of the present application, Fig.24 is a top view of an antenna track fully loaded with antennas in one embodiment of the present application, Fig.25 1 is a side view of the connection between the foldable satellite antenna and the antenna track in one embodiment of the present application. Figure 23 to Figure 25 As shown, multiple disc-shaped antenna interfaces 103 in a top view cover the entire antenna track 102 .

[0063] Figure 1 is a three-dimensional diagram of a foldable satellite antenna in an unfolded state in one embodiment of the present application, Figure 2 is a front view of a foldable satellite antenna in an unfolded state in one embodiment of the present application, Figure 3 is a top view of a foldable satellite antenna in an unfolded state in one embodiment of the present application, Figure 5 This is a front view of a foldable satellite antenna in a folded state in one embodiment of the present application. Figure 6 FIG. 1 is a top view of a foldable satellite antenna in a folded state in an embodiment of the present application. Figures 1 to 6 As shown, the foldable satellite antenna 104 shown in the present application is umbrella-shaped when in the unfolded state, and is rod-shaped when in the folded state. The present application takes into account the fragility of the foldable satellite antenna 104. After the umbrella-shaped antenna is folded, only the antenna end can be fixed, and the remaining parts cannot be in contact with each other by stacking or the like. At the same time, considering the longitudinal acceleration of the rocket when it is launched into orbit, the present application sets the foldable satellite antenna 104 to be vertically hoisted in the hollow chamber 1015. This setting can realize efficient storage of high focal diameter ratio antenna modules and avoid collision between antennas to cause damage.

[0064] The technical solution of the present application can be used to store and release the foldable satellite antenna 104 in orbit. The storage shell 101 can allow the foldable satellite antenna 104 to adapt to thermal control and avoid micrometeorite impact; the antenna interface 103 can firmly connect the foldable satellite antenna 104; by designing the antenna track 102 as an Archimedean spiral, the number of foldable satellite antennas 104 that can be stored can be maximized within the limited fairing space, and when taking out the antenna, it can be slid out along the spiral track from the inside to the outside, which is convenient for storing and accessing the antenna; by vertically hoisting the foldable satellite antenna 104 in the hollow chamber 1015, it can be avoided that the antennas collide with each other and cause damage.

[0065] Fig.15 is a schematic diagram of multiple layers of antenna tracks connected in series in one embodiment of the present application, Fig.16 is a front view of a multi-layer antenna track connected in series in one embodiment of the present application. Figures 12 to 16 As shown, in some embodiments, the antenna track 102 is arranged in multiple layers, and each layer of the antenna track 102 is provided with a first beam 1021 and a second beam 1022 that intersect each other, and a cross section 1023 is formed between the first beam 1021 and the second beam 1022. The multiple layers of antenna tracks 102 are connected by connecting beams 1024 and the cross section 1023, and the height H between the multiple layers of antenna tracks 102 is greater than or equal to the height of the foldable satellite antenna 104 (not shown).

[0066] For example, by providing a connecting beam 1024 to connect multiple layers of antenna tracks 102 in series, the stability between all antenna tracks 102 can be increased. In practical applications, the diameter of the spiral antenna track 102, the height between the antenna tracks 102, and the number of layers of the antenna track 102 can be adjusted according to the size of the rocket fairing, and this application does not impose any restrictions. Figure 7 In the embodiment shown, the present application is equivalent to a three-dimensional storage design for satellite antennas based on multi-layer Archimedean spiral tracks.

[0067] Figure 8 This is an exemplary perspective view of a three-dimensional satellite antenna storage fully loaded with antennas according to an embodiment of the present application. Fig. 27 is a schematic diagram of a single-layer antenna track fully loaded with antennas in one embodiment of the present application, Fig.28 is a schematic diagram of a multi-layer antenna track fully loaded with antennas in one embodiment of the present application, Fig.29 Schematic diagram of an embodiment of the present application when all antenna tracks are fully loaded with antennas. Figure 8 and Fig.29 All the layers of antenna tracks 102 are fully loaded with foldable satellite antennas 104. Fig. 27 One of the antenna tracks 102 is fully loaded with foldable satellite antennas 104. Fig.28 Three layers of antenna tracks 102 are fully loaded with foldable satellite antennas 104 .

[0068] Fig. 22 is along Fig.21 The cross-sectional structure diagram of the AA' line shown in FIG. Fig.17 , Fig.18 , Fig. 27 As shown, in some embodiments, the cross section of the antenna track 102 is in an I-shape, the groove 1033 includes a recessed portion 1034 and a protruding portion 1035, and the antenna interface 103 is connected to the antenna track 102 in a barb manner through the groove 1033. Exemplarily, the present application sets the cross section of the antenna track 102 to be in an I-shape, so that the antenna interface 103 and the antenna track 102 can be better engaged and connected, thereby improving the stability of the antenna interface 103. The connector 1031 on the antenna interface 103 and the foldable satellite antenna 104 can be connected by an automatic lock (not shown) or other mechanical connection methods, which is not limited in the present application.

[0069] In some embodiments, the antenna track 102 is an electromagnetic track, and the antenna interface 103 can be suspended on the antenna track 102 and can move along the antenna track 102 by electromagnetic suspension. For example, considering the strong vibration and easy damage to the antenna during the rocket launch, the present application sets the antenna track 102 as an electromagnetic track, and uses electromagnetic suspension to fix the antenna interface 103 and the antenna track 102 with magnetic repulsion, which can effectively isolate vibration during the rocket launch to avoid damage to the antenna. After the satellite antenna stereo storage 100 is launched into orbit, the antenna interface 103 can be moved along the antenna track 102 to the switchable hatch 1014 at the track exit by electromagnetic suspension, so as to facilitate the subsequent removal of the foldable satellite antenna 104.

[0070] Fig. 9 Schematic diagram of assembling a robot and a storage housing in one embodiment of the present application. Fig. 9 As shown, in some embodiments, the three-dimensional satellite antenna storage 100 based on the Archimedean spiral track also includes an assembly robot 105. The surface of the storage shell 101 is provided with a slide rail 1016. The assembly robot 105 is used to move along the slide rail 1016 to the switchable hatch 1014 to take out and / or store the foldable satellite antenna 104.

[0071] Exemplarily, the closable hatch 1014 is arranged at the end of the antenna track 102, and a slide rail 1016 is arranged outside the closable hatch 1014 from top to bottom, and the assembly robot 105 can slide along the slide rail 1016 to the end position of each layer of the antenna track 102 to take out or store the foldable satellite antenna 104. The slide rail 1016 and the Archimedean spiral antenna track 102 design can maximize the space utilization efficiency in the circular fairing space. By adopting the Archimedean spiral track and the magnetic levitation mobile antenna interface 103, the present application can move all antennas in the storage shell 101 to the exit, and then hand them over to the assembly robot 105 for operation, which is more efficient.

[0072] refer to Figure 7 As shown, in some embodiments, a solar cell sheet 10131 is disposed on the surface of one or more of the top plate 1011, the bottom plate 1012, and the side plate 1013, and the solar cell sheet 10131 is used to provide energy for the satellite antenna three-dimensional storage 100. Exemplarily, the solar cell sheet 10131 can be disposed on the top plate 1011, the bottom plate 1012, and the side plate 1013 in a pasting manner, or the solar cell sheet 10131 can be pasted only on the side plate 1013, and this application does not limit this.

[0073] In some embodiments, a battery 10151, a main control board 10152, and a temperature sensor 10153 are provided in the hollow chamber 1015. The battery 10151 is used to provide energy for the satellite antenna stereo storage 100, the main control board 10152 is used to control the movement of the antenna interface 103, and the temperature sensor 10153 is used to monitor the temperature in the hollow chamber 1015. Exemplarily, by providing the temperature sensor 10153, the temperature in the hollow chamber 1015 can be controlled within a suitable range to better store the foldable satellite antenna 104. By providing the battery 10151 and the main control board 10152, power and control can be provided for the magnetic suspension and sliding out of the antenna.

[0074] The present application also proposes a method for accessing a satellite antenna, which is used to access a satellite antenna using the satellite antenna stereo storage 100 as described above. The satellite antenna access method of the present application can be run in a controller in the satellite antenna stereo storage, and can also be run on the ground end. When the satellite antenna access method is run on the ground end, the data on the ground end interacts with the data in the satellite antenna stereo storage through a wireless network. The present application does not limit the operating environment of the satellite antenna access method.

[0075] Fig.30 is an exemplary flow chart of a satellite antenna access method according to an embodiment of the present application. Fig.30 As shown, the satellite antenna access method of this embodiment includes the following steps:

[0076] To store the satellite dish:

[0077] Step Sa1: Open the hatch;

[0078] Step Sa2: Connect the foldable satellite antenna to the antenna interface;

[0079] Step Sa3: Control the antenna interface to slide along the Archimedean spiral antenna track from outside to inside, thereby driving the foldable satellite antenna to move to a preset position;

[0080] Step Sa4: Close the switchable hatch.

[0081] Steps to remove the satellite antenna:

[0082] Step Sb1: Open the switchable hatch;

[0083] Step Sb2: Control the antenna interface to slide out from the inside to the outside along the Archimedean spiral antenna track, thereby driving the foldable satellite antenna to move to the hatch that can be opened and closed;

[0084] Step Sb3: Remove the foldable satellite antenna from the antenna interface;

[0085] Step Sb4: Close the switchable hatch.

[0086] The following is an example of an embodiment to illustrate step Sb2 and step Sb3 in the above-mentioned steps of removing the satellite antenna.

[0087] Fig.26 This is an exemplary flow chart of sliding out the foldable satellite antennas one by one from the antenna track in a step-by-step manner in one embodiment of the present application. Fig.26 As shown, exemplarily, in this embodiment, the antenna interface is fixed by grids in a magnetic suspension manner, and spirally slides out one by one in a step-by-step manner to achieve the removal of all foldable satellite antennas one by one. In step S2610, the command controls all antennas; in step S2620, the first antenna is taken out; in step S2630, the second antenna is controlled to step by one grid; in step S2640, the third antenna is controlled to step by one grid; until step S2650, the penultimate antenna is controlled to step by one grid; in step S2660, the last antenna is controlled to step by one grid; in steps S2670 and S2680, all antennas are taken out one by one; in step S2690, the last antenna is taken out.

[0088] The present application also includes a computer-readable medium storing a computer program code, which implements the satellite antenna access method described above when executed by a processor.

[0089] When the satellite antenna access method is implemented as a computer program, it can also be stored in a computer-readable storage medium as a product. For example, a computer-readable storage medium may include, but is not limited to, a magnetic storage device (e.g., a hard disk, a floppy disk, a magnetic strip), an optical disk (e.g., a compact disk (CD), a digital versatile disk (DVD)), a smart card, and a flash memory device (e.g., an electrically erasable programmable read-only memory (EPROM), a card, a stick, a key drive). In addition, the various storage media described herein can represent one or more devices and / or other machine-readable media for storing information. The term "machine-readable medium" may include, but is not limited to, wireless channels and various other media (and / or storage media) that can store, contain and / or carry code and / or instructions and / or data.

[0090] It should be understood that the embodiments described above are only illustrative. The embodiments described herein may be implemented in hardware, software, firmware, middleware, microcode, or any combination thereof. For hardware implementation, the processor may be implemented in one or more application specific integrated circuits (ASICs), digital signal processors (DSPs), digital signal processing devices (DSPDs), programmable logic devices (PLDs), field programmable gate arrays (FPGAs), processors, controllers, microcontrollers, microprocessors, and / or other electronic units designed to perform the functions described herein, or a combination thereof.

[0091] Some aspects of the present application may be performed entirely by hardware, entirely by software (including firmware, resident software, microcode, etc.), or by a combination of hardware and software. The above hardware or software may be referred to as "data blocks", "modules", "engines", "units", "components" or "systems". The processor may be one or more application specific integrated circuits (ASICs), digital signal processors (DSPs), digital signal processing devices (DAPDs), programmable logic devices (PLDs), field programmable gate arrays (FPGAs), processors, controllers, microcontrollers, microprocessors, or combinations thereof. In addition, various aspects of the present application may be expressed as computer products located in one or more computer-readable media, which include computer-readable program codes. For example, computer-readable media may include, but are not limited to, magnetic storage devices (e.g., hard disks, floppy disks, tapes ...), optical disks (e.g., compact disks CDs, digital versatile disks DVDs ...), smart cards, and flash memory devices (e.g., cards, sticks, key drives ...).

[0092] A computer-readable medium may include a propagated data signal containing computer program code, such as in baseband or as part of a carrier wave. The propagated signal may have a variety of manifestations, including electromagnetic, optical, etc., or a suitable combination. A computer-readable medium may be any computer-readable medium other than a computer-readable storage medium, which may be connected to an instruction execution system, device or apparatus to communicate, propagate or transmit a program for use. The program code on the computer-readable medium may be propagated via any suitable medium, including radio, cable, fiber optic cable, radio frequency signal, or similar medium, or any combination of the above mediums.

[0093] The basic concepts have been described above. Obviously, for those skilled in the art, the above application disclosure is only an example and does not constitute a limitation of the present application. Although not explicitly stated herein, those skilled in the art may make various modifications, improvements and amendments to the present application. Such modifications, improvements and amendments are suggested in the present application, so such modifications, improvements and amendments still belong to the spirit and scope of the exemplary embodiments of the present application.

[0094] At the same time, the present application uses specific words to describe the embodiments of the present application. For example, "one embodiment", "an embodiment", and / or "some embodiments" refer to a certain feature, structure or characteristic related to at least one embodiment of the present application. Therefore, it should be emphasized and noted that "one embodiment" or "an embodiment" or "an alternative embodiment" mentioned twice or more in different positions in this specification does not necessarily refer to the same embodiment. In addition, some features, structures or characteristics in one or more embodiments of the present application can be appropriately combined.

[0095] In some embodiments, numbers describing the number of components and attributes are used. It should be understood that such numbers used in the description of the embodiments are modified by the modifiers "about", "approximately" or "substantially" in some examples. Unless otherwise specified, "about", "approximately" or "substantially" indicate that the numbers are allowed to vary by ±20%. Accordingly, in some embodiments, the numerical parameters used in the specification and claims are approximate values, which may change according to the required features of individual embodiments. In some embodiments, the numerical parameters should take into account the specified significant digits and adopt the general method of retaining digits. Although the numerical domains and parameters used to confirm the breadth of their range in some embodiments of the present application are approximate values, in specific embodiments, the setting of such numerical values ​​is as accurate as possible within the feasible range.

Claims

1. A three-dimensional storage system for satellite antennas based on Archimedean spiral orbit, characterized in that: include: The storage shell comprises a top plate, a bottom plate and side plates, wherein the top plate, the bottom plate and the side plates together form a hollow chamber, and the side plates are provided with a hatch that can be opened and closed; An antenna track is in the shape of an Archimedean spiral, and the antenna track is arranged in the hollow chamber; The antenna interface comprises a connector and a connector end, wherein the connector end is provided with a groove, the groove is adapted to the antenna track, and the antenna interface is connected to the antenna track via the groove; The foldable satellite antenna comprises an antenna back frame, the antenna back frame is connected to the connecting piece, and the foldable satellite antenna is vertically hoisted in the hollow chamber.

2. The three-dimensional storage of satellite antennas based on Archimedean spiral orbit as claimed in claim 1, characterized in that: The antenna track is arranged in multiple layers, and each layer of the antenna track is provided with a first crossbeam and a second crossbeam that intersect each other, and an intersection is formed between the first crossbeam and the second crossbeam. The multiple layers of antenna tracks are connected by connecting beams and the intersection, and the height between the multiple layers of antenna tracks is greater than or equal to the height of the foldable satellite antenna.

3. The three-dimensional storage of satellite antennas based on Archimedean spiral orbit as claimed in claim 1, characterized in that: The cross section of the antenna track is in an I-shape, the groove includes a recessed portion and a protruding portion, and the antenna interface is connected to the antenna track in a barbed manner through the groove.

4. The three-dimensional storage of satellite antennas based on Archimedean spiral orbit as claimed in claim 1 or 3, characterized in that: The antenna track is an electromagnetic track, and the antenna interface can be suspended on the antenna track and can move along the antenna track by electromagnetic suspension.

5. The three-dimensional storage of satellite antennas based on Archimedean spiral orbit as claimed in claim 1, characterized in that: It also includes an assembly robot. The surface of the storage shell is provided with a slide rail. The assembly robot is used to move along the slide rail to the switchable cabin door to take out and / or store the foldable satellite antenna.

6. The three-dimensional storage of satellite antennas based on Archimedean spiral orbit as claimed in claim 1, characterized in that: The storage shell is cylindrical.

7. The three-dimensional storage of satellite antennas based on Archimedean spiral orbit as claimed in claim 1, characterized in that: Solar cells are arranged on the surface of one or more of the top plate, the bottom plate and the side plates, and the solar cells are used to provide energy for the three-dimensional satellite antenna storage.

8. The three-dimensional storage of satellite antennas based on Archimedean spiral orbit as claimed in claim 1, characterized in that: A battery, a main control board and a temperature sensor are arranged in the hollow chamber. The battery is used to provide energy for the three-dimensional storage of the satellite antenna, the main control board is used to control the movement of the antenna interface, and the temperature sensor is used to monitor the temperature in the hollow chamber.

9. A method for accessing a satellite antenna, characterized in that: Used to store and access satellite antennas using the satellite antenna stereo storage as described in any one of claims 1 to 8, comprising: To store the satellite dish: Step Sa1: Open the hatch; Step Sa2: Connect the foldable satellite antenna to the antenna interface; Step Sa3: Control the antenna interface to slide along the Archimedean spiral antenna track from outside to inside, thereby driving the foldable satellite antenna to move to a preset position; Step Sa4: closing the closable door; and Steps to remove the satellite antenna: Step Sb1: opening the closable door; Step Sb2: Control the antenna interface to slide out from the inside to the outside along the Archimedean spiral antenna track, thereby driving the foldable satellite antenna to move to the closable door; Step Sb3: removing the foldable satellite antenna from the antenna interface; Step Sb4: Close the switchable hatch.

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