Multi-fold satellite and control method therefor, launch vehicle and computing device

Abstract

Provided are a multi-fold satellite and a control method therefor, a launch vehicle and a computing device. The multi-fold satellite comprises: a main body, which comprises a plurality of cabin modules, a deployment mechanism, and a stacking member, wherein the stacking member is arranged between adjacent cabin modules and can be locked or unlocked so as to restrict or allow rotation of the cabin modules, and the deployment mechanism is connected to each cabin module and configured to drive the cabin modules to rotate, such that the main body is in a stacked and retracted state or a flat and deployed state; and solar panels, which are connected to the cabin modules, wherein the solar panels can swing towards a space-facing side or an Earth-facing side. During the transition of the main body between the stacked and retracted state and the flat and deployed state, the deployment mechanism drives the outer cabin modules to rotate in a first direction or in a second direction. The multi-fold satellite of the present disclosure has a compact structure, achieving a high degree of miniaturization when stacked and retracted.

Description

Multi-fold satellites and their control methods, launch vehicles and computing equipment

[0001] Cross-references to related applications

[0002] This application claims priority to Chinese Patent Application No. 202510125114.7, filed on January 26, 2025, entitled "Multi-fold Satellite and Control Method Thereof, Launch Vehicle and Computing Device", the entire contents of which are incorporated herein by reference. Technical Field

[0003] This application relates to the field of aerospace technology, and specifically to a multi-fold satellite, a control method for a multi-fold satellite, a launch vehicle, a computing device, a non-transient computer-readable storage medium, and a chip system. Background Technology

[0004] The overall satellite configuration layout mainly integrates onboard units, instruments, and components effectively. It aims to provide the necessary mechanical conditions, installation space, installation location, and suitable environmental conditions for the satellite's payload and various subsystem instruments and equipment, provide support for onboard equipment, withstand the mechanical loads of ground transportation, meet the mechanical and mechanical conditions of the launch system, and ensure the strength and rigidity of the entire satellite during the active launch phase.

[0005] In recent years, the field of low-Earth orbit (LEO) internet satellites has developed rapidly, with the goal of providing global broadband internet services through the construction of large-scale satellite constellations. To achieve efficient manufacturing and rapid deployment, LEO internet satellites typically employ miniaturization and modular designs; however, current satellite designs still need improvement in structural compactness and suffer from insufficient miniaturization. Summary of the Invention

[0006] Providing a mechanism to alleviate, reduce or eliminate at least one of the above problems would be beneficial.

[0007] In a first aspect, a multi-fold satellite is provided. The multi-fold satellite includes: a main body comprising multiple cabin modules, a folding mechanism, and stacking members; the stacking members are disposed between adjacent cabin modules and are lockable or unlockable to restrict or allow rotation of the cabin modules; the folding mechanism is connected to each cabin module and is used to drive the cabin module to rotate, thereby placing the main body in a stacked, folded state or a flat, unfolded state; and solar panels are connected to the cabin modules and are oscillating towards the sky or towards the ground; wherein, during the process of the main body changing from the stacked, folded state to the flat, unfolded state: the stacking members unlock adjacent cabin modules, and the folding mechanism drives the outer cabin module to rotate along a first direction or along a second direction to unfold at least one cabin module; or during the process of the main body changing from the flat, unfolded state to the stacked, folding mechanism drives the outer cabin module to rotate along the first direction or along the second direction to stack the multiple cabin modules, and the stacking members lock adjacent cabin modules.

[0008] In a second aspect, a launch vehicle is provided. The launch vehicle includes a fairing and the aforementioned multi-fold satellites, wherein a plurality of the multi-fold satellites are interconnected and stacked within the fairing.

[0009] In a third aspect, a control method for a multi-fold satellite is provided. This control method, applied to the aforementioned multi-fold satellite, includes: in response to receiving a unfolding signal, controlling the stacking components to unlock adjacent cabin modules, and controlling the unfolding mechanism to drive the outer cabin module to rotate along a first direction or along a second direction to unfold at least one cabin module; or in response to receiving a stacking retraction signal, controlling the unfolding mechanism to drive the outer cabin module to rotate along the first direction or along the second direction to stack the plurality of cabin modules, and controlling the stacking components to lock adjacent cabin modules.

[0010] In a fourth aspect, a computing device is provided. The computing device includes: at least one processor; and at least one memory storing instructions that, when executed individually or jointly by the at least one processor, cause the computing device to perform the aforementioned control method for a multi-fold satellite.

[0011] In a fifth aspect, a chip system is provided. This chip system includes a circuit system configured to execute the aforementioned control method for multi-fold satellites.

[0012] It should be understood that the summary section is not intended to identify key or essential features of the embodiments of this application, nor is it intended to limit the scope of this application. Other features of this application will become readily apparent from the following description. Attached Figure Description

[0013] The above and other objects, features and advantages of this application will become more apparent from the more detailed description of some embodiments thereof in the accompanying drawings, wherein:

[0014] Figure 1 shows a schematic diagram of a multi-fold satellite of an embodiment of this application in a flat, unfolded state;

[0015] Figure 2 shows a schematic diagram of a multi-fold satellite according to an embodiment of this application, laid out flat and facing the sky.

[0016] Figure 3 shows a schematic diagram of a multi-fold satellite according to an embodiment of this application, laid out flat and facing the ground;

[0017] Figure 4 shows an interior schematic diagram of a multi-fold satellite according to an embodiment of this application;

[0018] Figure 5 shows a schematic diagram of a multi-fold satellite in a stacked and folded state according to an embodiment of this application;

[0019] Figure 6 shows a schematic diagram of a multi-fold satellite of another embodiment of this application in a flat, unfolded state, facing the sky.

[0020] Figure 7 shows a schematic diagram of a multi-fold satellite of another embodiment of this application in a flat, unfolded state, facing the ground;

[0021] Figure 8 shows a schematic diagram of a multi-fold satellite in a stacked and folded state according to another embodiment of this application;

[0022] Figure 9 shows a flowchart of the multi-fold satellite deployment process of this application; and

[0023] Figure 10 shows a simplified block diagram of a device suitable for implementing exemplary embodiments of this application.

[0024] Explanation of reference numerals in the accompanying drawings of the specific embodiments: 10. Satellite; 11. Main body; 12. Cabin module; 121. First panel; 122. Second panel; 1231. First side; 1232. Second side; 124. Phased array antenna; 1251. Star sensor; 1252. Solar array; 1253. Magnetometer; 1254. Gyroscope; 1255. Sun sensor; 1256. Integrated electronic system; 1257. Power controller; 1258. Routing device; 1259. Power distributor; 1260. Thruster; 13. Stacked components; 1301. First stacked section; 1302. Second stacked section; 131. First stacked component; 132. Second stacked component; 133. Third stacked component; 134. Fourth stacked component; 14. Solar panel; D1. First direction; D2. Second direction. Detailed Implementation

[0025] The principles of this application will now be described with reference to some embodiments. It should be understood that these embodiments are described for illustrative purposes only and to help those skilled in the art to understand and implement this application, and do not impose any limitation on the scope of this application. The disclosure described herein may be implemented in ways other than those described below.

[0026] In the following description and claims, unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this application pertains.

[0027] References to "an embodiment," "embodiment," "exemplary embodiment," etc., in this application indicate that the described embodiment may include specific features, structures, or characteristics, but not every embodiment needs to include specific features, structures, or characteristics. Furthermore, such phrases do not necessarily refer to the same embodiment. Moreover, when a specific feature, structure, or characteristic is described in conjunction with an exemplary embodiment, whether explicitly described or not, those skilled in the art will recognize that such a feature, structure, or characteristic affects its association with other embodiments.

[0028] It should be understood that while the terms “first” and “second”, etc., may be used herein to describe various elements, these elements should not be limited by these terms. These terms are used only to distinguish one element from another. For example, without departing from the scope of the exemplary embodiments, a first element may be referred to as a second element, and similarly, a second element may be referred to as a first element. The term “and / or” as used herein includes any and all combinations of one or more of the listed terms.

[0029] The terminology used herein is for the purpose of describing particular embodiments only and is not intended to limit the exemplary embodiments. The singular forms “a,” “an,” and “the” used herein also include the plural forms unless the context clearly indicates otherwise. The terms “a group of elements” or “a collection of elements” as used herein are intended to include one or more elements. It should also be understood that the terms “comprising,” “including,” “having,” “possessing,” “including,” and / or “comprising,” when used herein, specify the presence of the stated features, elements, and / or components, but do not exclude the presence or addition of one or more other features, elements, components, and / or combinations thereof.

[0030] As used in this application, the term "circuit" may refer to one or more of the following:

[0031] (a) Implemented only in hardware circuitry (e.g., implemented only in analog and / or digital circuitry)

[0032] (b) A combination of hardware circuitry and software, such as (if applicable):

[0033] (i) a combination of analog and / or digital hardware circuitry with software / firmware; and

[0034] (ii) Any part of a hardware processor (including a digital signal processor), software, and memory that work together to enable a device such as a mobile phone or server to perform various functions, and

[0035] (c) Hardware circuitry and / or processors, such as microprocessors or a portion thereof, which require software (e.g., firmware) to operate, but may be absent when the software is not required to operate.

[0036] The definition of "circuit" applies to all uses of the term in this application, including in any claim. As another example, as used herein, the term "circuit" also includes implementations of hardware circuitry or processors (or processors in general) or a portion thereof and their accompanying software and / or firmware. The term "circuit" also includes, for example, baseband integrated circuits or processor integrated circuits for mobile devices, or similar integrated circuits in servers, cellular network devices, or other computing network devices, if applicable to a particular claim element.

[0037] As used herein, the term "communication network" refers to a network that conforms to any suitable communication standard, such as Long Term Evolution (LTE), LTE-Advanced (LTE-A), Wideband Code Division Multiple Access (WCDMA), High-Speed ​​Packet Access (HSPA), Narrowband Internet of Things (NB-IoT), New Radio (NR), Non-Terrestrial Network (NTN), etc. Furthermore, communication between terminal devices and network devices in a communication network can be performed according to any suitable generation of communication protocol, including but not limited to first-generation (1G), second-generation (2G), 2.5G, 2.75G, third-generation (3G), fourth-generation (4G), 4.5G, fifth-generation (5G), and future sixth-generation (6G) communication protocols, and / or any other currently known or to be developed in the future. Embodiments of this application can be applied to satellite communication systems. Given the rapid development in communications, future types of communication technologies and systems will naturally exist, and this application can be implemented using these technologies and systems. It should not be considered that the scope of this application is limited to the aforementioned systems.

[0038] The term "terminal device" refers to any terminal device capable of wireless communication. As an example and not a limitation, a terminal device may also be referred to as a communication device, user equipment (UE), subscriber station (SS), portable subscriber station, mobile station (MS), or access terminal (AT). This terminal device may include, but is not limited to, mobile phones (such as cell phones), cellular phones, smartphones, Voice over IP (VoIP) phones, wireless local loop phones, tablets, wearable terminal devices, personal digital assistants (PDAs), portable computers, desktop computers, image capture terminal devices such as digital cameras, gaming terminal devices, music storage and playback devices, in-vehicle wireless terminal devices, wireless endpoints, mobile stations, laptop embedded devices (LEEs), laptop installed devices (LMEs), USB dongles, smart devices, wireless subscriber equipment (CPEs), Internet of Things (IoT) devices, watches or other wearable devices, head-mounted displays (HMDs), vehicles, drones, medical devices and applications (e.g., remote surgery), industrial devices and applications (e.g., robots and / or other wireless devices operating in the context of industrial and / or automated processing chains), consumer electronics devices, relay nodes, devices operating on commercial and / or industrial wireless networks, etc. The mobile terminal (MT) portion of an IAB node can perform the functions of a "terminal device" and therefore can operate as a terminal device. In the following description, the terms "terminal device," "communication device," "terminal," "user equipment," and "UE" are used interchangeably.

[0039] While the functions described herein may be implemented in fixed and / or wireless network nodes in various exemplary embodiments, in other exemplary embodiments, they may be implemented in user equipment devices (such as cellular phones, tablet computers, laptop computers, desktop computers, mobile IoT devices, or fixed IoT devices). For example, the user equipment device may suitably have the corresponding capabilities described in relation to fixed and / or wireless network nodes. The user equipment device may be user equipment and / or control devices, such as chipsets or processors, configured to control the user equipment when it is installed therein. Examples of these functions include boot server functions and / or home subscriber servers, which may be implemented in the user equipment device by providing the user equipment device with software configured to cause the user equipment device to perform from the perspective of these functions / nodes.

[0040] This section will first introduce the technical means related to satellites, as well as the technical concept of this application.

[0041] Low-Earth orbit (LEO) satellite communication technology primarily achieves global coverage through satellite antennas, such as phased array antennas. Flat-panel satellites typically employ small phased array antennas, a design that makes the satellite structure simple, easy to launch, and easy to deploy. Although this allows for the deployment of large-scale satellite constellations, the relatively small area of ​​the phased array antenna primarily serves users who need to install ground terminals and cannot directly support communication with ordinary mobile phones. While its low-cost deployment model and efficient mass launch have gained market recognition, providing seamless direct mobile phone connectivity services to ordinary users globally still faces technological bottlenecks.

[0042] Furthermore, the smaller antenna area also affects the selection of communication frequencies and signal strength, limiting communication bandwidth and coverage efficiency. To address communication coverage and performance issues, some satellites have adopted larger phased array antennas (estimated to be close to 25 square meters), potentially enabling direct mobile phone communication. However, this design does not incorporate a folding and unfolding mechanism in its structure; the antenna remains in its full-size state at launch. This results in a very large overall satellite envelope, far exceeding traditional launch payload specifications, placing extremely high demands on the space available in the launch vehicle fairing.

[0043] Currently, only a very small number of launch vehicles worldwide can meet the launch requirements of large-sized satellites. Other traditional launch vehicles cannot accommodate such large satellites due to insufficient fairing space, which greatly limits the satellite launch options and cost control, and restricts the flexibility of their commercial applications.

[0044] Furthermore, some satellites employ a complex, in-orbit deployable integrated wing-array mechanical structure design. This allows for the deployment of ultra-large-area phased array antennas (approximately 64 square meters) through multiple deployments, enabling direct mobile phone communication. A small number of large-area antenna satellites can be used to build a global communication network through the extensive coverage of each satellite. However, the deployment process of this integrated wing-array mechanical structure satellite is complex, involving numerous mechanical components and posing a high risk of mechanical failure.

[0045] Furthermore, the integrated wing array design generates significant heat, making satellite thermal management difficult and potentially leading to overheating issues during long-term operation, thus affecting communication quality and satellite lifespan. Additionally, the compact arrangement of this large-area antenna structure hinders the integration of inter-satellite laser communication equipment, a crucial means for achieving high-speed communication and data exchange in low-Earth orbit internet constellations, thus limiting future technological scalability.

[0046] Based on the analysis of current technical solutions, in order to overcome the shortcomings of direct communication with terminal devices such as mobile phones, this application presents a new type of foldable low-Earth orbit communication satellite with an overall configuration and layout design. It combines multi-wing solar panels and cabin module stacking design to solve problems such as insufficient onboard antenna area, excessively large launch envelope size, high mechanical deployment complexity, insufficient mechanical deployment reliability, difficulty in attitude control, and insufficient inter-satellite laser communication capability in the current overall design of low-Earth orbit internet communication satellites.

[0047] This application's multi-fold satellite utilizes inter-satellite stacking components to fold multiple cabin modules, resulting in a compact structure and high miniaturization after stacking, facilitating launch from a rocket. After launch into orbit, the satellite can be released and separated in a timely manner to avoid collisions. When unfolded, the multi-fold satellite can directly connect to mobile phones, improving communication efficiency for ground users.

[0048] The principles and implementation of this application will be described in detail below. It should be noted that some of the accompanying drawings of this application show a configuration of three cabin modules and four solar panels (i.e., four wings), but this application does not limit the number of cabin modules and solar panels, and they can be freely selected in practical applications.

[0049] Figure 1 shows a schematic diagram 100 of a multi-fold satellite according to an embodiment of the present application in a flat, unfolded state, and Figure 5 shows a schematic diagram 500 of a multi-fold satellite according to an embodiment of the present application in a stacked, folded state. Referring to Figures 1 and 5, the multi-fold satellite 10 includes: a main body 11, including multiple cabin modules 12, a folding mechanism (not shown in the figures), and stacking members 13; the stacking members 13 are disposed between adjacent cabin modules 12, and the stacking members 13 can be locked or unlocked to restrict or allow the cabin modules 12 to rotate; the folding mechanism is connected to each cabin module 12, and the folding mechanism is used to drive the cabin module 12 to rotate so that the main body 11 is in a stacked, folded state or a flat, unfolded state; a solar panel 14 is connected to the cabin module 12, and the solar panel 14 can swing towards the sky or towards the ground.

[0050] For example, Figure 1 shows a configuration of three cabin modules 12 and four solar panels 14, where the solar panels 14 may be solar cell array panels. In some embodiments, during the process of the main body 11 changing from a stacked and folded state (as shown in Figure 5) to a flat and unfolded state (as shown in Figure 1): the stacking member 13 unlocks the adjacent cabin modules 12, and the unfolding mechanism drives the outer cabin module 12 to rotate along a first direction D1 or along a second direction D2, thereby unfolding at least one cabin module 12.

[0051] In some embodiments, during the process of the main body 11 changing from a flat unfolded state (as shown in FIG1) to a stacked folded state (as shown in FIG5): the unfolding mechanism drives the outer cabin module 12 to rotate along the first direction D1 or along the second direction D2 to stack multiple cabin modules 12, and the stacking member 13 locks the adjacent cabin modules 12.

[0052] For example, in the embodiment shown in Figure 1, during the unfolding or stacking process of the main body 11, the left and right cabin modules rotate around the middle cabin module. The cabin module 12 of this application is equivalent to a satellite platform. Under the premise of the same total solar panel area, compared with the single-wing configuration or wing-array integrated configuration of traditional satellites, the solar panel 14 of this application has the characteristics of single-axis oscillation, small surface-to-mass ratio, reduced inertia and inertial product, and strong thermal control capability, which can provide efficient energy and attitude control.

[0053] The multi-fold satellite 10 of this application achieves flexible space deployment. In the stacked and folded state, the stacking component 13 locks the cabin module 12 to ensure that the modules remain compact, optimizing the launch envelope of the satellite 10. After the stacking component 13 is unlocked, the unfolding mechanism can drive the cabin module 12 to rotate in different directions, allowing the main body 11 to switch between stacked and unfolded states. The solar panel 14 can adjust the orientation of the satellite 10, optimizing energy harvesting. The multi-fold satellite 10 of this application can unfold to its maximum area during mission execution, enabling large-area deployment of phased array antennas on the satellite 10, thereby increasing antenna power and enabling the satellite 10 to provide direct mobile phone connectivity.

[0054] Referring to Figures 1 and 5, in some embodiments, the stacking member 13 is a stacking column, which includes a first stacking portion 1301 and a second stacking portion 1302, which are respectively disposed on adjacent cabin modules 12; wherein, when the stacking member 13 unlocks the adjacent cabin module 12, the first stacking portion 1301 and the second stacking portion 1302 are separated; or when the stacking member 13 locks the adjacent cabin module 12, the first stacking portion 1301 and the second stacking portion 1302 are connected.

[0055] For example, the first stacking portion 1301 and the second stacking portion 1302 can be configured as a snap-fit ​​structure. When the first stacking portion 1301 and the second stacking portion 1302 are separated, the cabin module 12 is allowed to rotate relative to each other; when the first stacking portion 1301 and the second stacking portion 1302 are connected, the cabin module 12 can be locked. This application can flexibly and reliably control the stacking and deployment states of multiple cabin modules 12.

[0056] Figure 2 shows a schematic diagram 200 of a multi-fold satellite according to an embodiment of the present application, which is laid out flat and facing the sky. Figure 3 shows a schematic diagram 300 of a multi-fold satellite according to an embodiment of the present application, which is laid out flat and facing the ground. Figure 4 shows a schematic diagram 400 of the interior of a multi-fold satellite according to an embodiment of the present application.

[0057] Referring to Figures 1 to 4, in some embodiments, the cabin module 12 is a flat-panel cabin module. The cabin module 12 includes a first panel 121 (as shown in Figures 1 and 2), a second panel 122 (as shown in Figure 3), and a support assembly (not shown in the figures). The support assembly is connected to the first panel 121 and the second panel 122 respectively. The first panel 121 and the second panel 122 are arranged opposite to each other. The first panel 121 is used to face the sky, and the second panel 122 is used to face the ground. The solar panel 14 is connected to the support assembly. Exemplarily, the support assembly can be installed inside the cabin as shown in Figure 4. Specifically, the support assembly can be a metal main structural frame, which is connected to the first panel 121 and the second panel 122 respectively.

[0058] For example, the flat-panel satellite 10 of this application can be efficiently stacked in a rocket. By folding the satellite 10, this application greatly reduces the envelope size of the satellite 10 in the launch state, thereby adapting to the envelope requirements of various rocket fairing sizes, improving the space utilization of the fairing, and allowing more satellites 10 to be launched each time. The support components securely connect to other celestial components, enhancing the stability of the cabin module 12, optimizing the layout of the solar panels 14, and enabling the satellite 10 to flexibly and agilely adjust its attitude, maximizing the utilization of solar energy resources.

[0059] Referring to Figure 3, in some embodiments, a phased array antenna 124 is provided on the second panel 122 of all cabin modules 12; or a phased array antenna 124 is provided on the second panel 122 of at least one cabin module 12. Exemplarily, this application achieves large-area phased array antenna deployment through the deployment of the satellite, which can be used for direct communication with terrestrial mobile phones. It can achieve efficient communication coverage based on optimized transmission envelope, and can also adjust the communication direction and coverage area as needed. This application is applicable to large-scale satellite networking in low-Earth orbit constellations.

[0060] Referring to Figure 2, in some embodiments, at least one of the following components, or any combination thereof, is provided on the first panel 121 of the cabin module 12: a star sensor 1251, a laser communication device (not shown), a telemetry and control antenna (not shown), a solar array 1252, a magnetometer 1253, a gyroscope 1254, and a sun sensor 1255. Exemplarily, this application improves the attitude control accuracy, communication capability, energy self-sufficiency level, and space environment monitoring capability of the satellite 10 by providing onboard components on the first panel 121 of the cabin module 12, providing a foundation for the efficient operation and multifunctional applications of the satellite 10. In practical applications, different types of onboard components can be freely arranged on the first panel 121 as needed; this application does not impose any restrictions.

[0061] Referring to Figures 1 and 5, in some embodiments, the solar panel 14 is a roll-up flexible solar panel. The solar panel 14 is equipped with a drive shaft (not shown) and a deployment mechanism (not shown). When the solar panel 14 is in a rolled-up state (as shown in Figure 5), the solar panel 14 unfolds into a flat plate shape via the deployment mechanism (as shown in Figure 1), and is oscillated towards the sky and the ground via the drive shaft. Exemplarily, this application optimizes the storage volume of the solar panel 14, improves the deployment efficiency and stability of the solar panel 14, thereby effectively enhancing the operational flexibility of the satellite 10.

[0062] Figure 6 shows a schematic diagram 600 of a multi-fold satellite of another embodiment of the present application in a flat, unfolded state facing the sky, and Figure 7 shows a schematic diagram 700 of a multi-fold satellite of another embodiment of the present application in a flat, unfolded state facing the ground. Referring to Figures 1, 6, and 7, in some embodiments, the number of solar panels 14 is N, where N is an even number and greater than or equal to four; at least four solar panels 14 are respectively disposed on the outer cabin module 12, and two solar panels 14 located on the same cabin module 12 are disposed opposite to each other.

[0063] For example, the embodiment shown in Figure 1 includes four solar panels 14, while the embodiments shown in Figures 6 and 7 include six solar panels 14. In practical applications, the number of solar panels 14 can also be set to eight, ten, or even more; this application does not limit the number of solar panels 14. This application optimizes the solar panel layout, ensuring the stability and balance of the solar panels 14 during deployment, storage, and operation, thereby improving the operational reliability of the satellite 10.

[0064] Referring to Figure 1, in some embodiments, the number of cabin modules 12 is at least three, and the stacking components 13 include: a first stacking component 131, a second stacking component 132, and a third stacking component 133. Each cabin module 12 includes a first side 1231 and a second side 1232 opposite to each other. On the same cabin module 12, the first stacking component 131 is disposed in the middle of the first side 1231, and the second stacking component 132 and the third stacking component 133 are respectively disposed at both ends of the second side 1232. Exemplarily, this configuration achieves flexibility and stability in the connection and unlocking of the cabin modules 12, facilitating both tight stacking of modules and rapid deployment when needed, thus improving the reliability of the satellite structure.

[0065] Figure 8 shows a schematic diagram 800 of a multi-fold satellite in a stacked and folded state according to another embodiment of this application. Referring to Figures 6 to 8, in some embodiments, the number of cabin modules 12 is at least three, and the stacking members 13 include: a first stacking member 131, a second stacking member 132, a third stacking member 133, and a fourth stacking member 134; the cabin module 12 includes a first side 1231 and a second side 1232 opposite to each other. On the same cabin module 12, the first stacking member 131 and the second stacking member 132 are respectively disposed at both ends of the first side 1231, and the third stacking member 133 and the fourth stacking member 134 are respectively disposed at both ends of the second side 1232.

[0066] For example, Figures 6 and 7 show three large cabin modules 12. In practical applications, multiple smaller cabin modules can also be used. For instance, Figure 6 can be considered to include five cabin modules 12, with the two smaller cabin modules on the left forming one large cabin module and the two smaller cabin modules on the right forming another large cabin module. In practical applications, the number of cabin modules 12 can be three, four, five, six, or even more. This application does not limit the number of cabin modules 12.

[0067] For example, by setting multiple stacking components 13 between the cabin modules 12, this application achieves flexibility in connecting and unlocking the cabin modules 12, enhances the stability and reliability of the satellite 10 structure, and facilitates the tight stacking or unfolding of modules as needed during launch, transportation and on-orbit operation, thereby improving the overall performance of the satellite 10.

[0068] Referring to Figure 4, in some embodiments, at least one of the following components, or any combination thereof, is provided on the support assembly of the cabin module 12: an integrated electronic system 1256, a battery (not shown), a power controller 1257, a reaction flywheel (not shown), a payload electronic system (not shown), a thruster 1260, a routing device 1258, and a power distributor 1259. Exemplarily, this configuration enhances the functionality and self-sufficiency of the satellite 10, optimizes the system layout, improves resource utilization efficiency, and ensures the stable operation and efficient mission execution of the satellite 10 in complex space environments. In practical applications, different types of onboard components can be freely configured on the support assembly as needed; this application does not impose any restrictions.

[0069] The multi-fold satellite 10 of this application is illustrated here with an embodiment. In this embodiment, the multi-fold satellite 10 is designed as a three-fold satellite with four-wing sails.

[0070] 1. Foldable structure design.

[0071] The main body 11 of satellite 10 consists of three flat-panel cabin modules 12. Each flat-panel cabin module 12 consists of an upper panel (i.e., the first panel 121), a lower panel (i.e., the second panel 122), and a middle main structural frame. The upper and lower panels are made of aluminum alloy or sandwich composite materials (e.g., aluminum skin honeycomb panels), and the middle main structural frame is made of aluminum alloy or magnesium-aluminum alloy.

[0072] The outer side of the upper panel is mainly equipped with star sensor 1251, inter-satellite laser communication equipment, telemetry and control antennas, etc. In particular, the upper panel of the cabin is mainly equipped with perovskite battery arrays, which are used to obtain energy after the star separates from the rocket and before the satellite 10 is deployed.

[0073] The outer side of the lower panel is mainly equipped with phased array antennas 124, while the inner side of the lower panel is mainly equipped with satellite-mounted individual equipment, such as integrated electronics, battery packs, power controllers 1257, reaction flywheels, and payload electronics.

[0074] The middle main structural frame is the main load-bearing structure. The cabin and the outer frame mainly house the four-wing roll-type flexible solar array structure and mechanism, as well as eight thrusters 1260.

[0075] When launching Satellite 10, the three flat-panel cabins are compactly stacked in a folded state through a folding mechanism to reduce the envelope size during launch, thereby reducing the space requirements of the rocket fairing. The three flat-panel cabins are clamped and locked together using shape memory alloys or pyrotechnics to improve the rigidity of the entire satellite and ensure that the base frequency meets the requirements of the launch vehicle.

[0076] After Satellite 10 enters orbit, its three flat-panel cabins unfold to full size using drive motors or mechanical devices, with an automatic locking structure ensuring structural rigidity after unfolding. The three phased array antennas 124 on the ground are then assembled in orbit into a large-area phased array antenna surface (area greater than 10m²). 2 The deployed antenna area can meet the needs of direct mobile phone communication, eliminating reliance on ground terminal equipment. Phased array technology can dynamically adjust the beam direction according to the location of the ground user, improving communication efficiency and stability. After satellite 10 is deployed in orbit, the locking structure can be unlocked, allowing satellite 10 to be retracted back into its stacked state.

[0077] For example, in practical applications, the multi-fold satellite 10 can be configured with three-fold, four-fold, or five-fold modules.

[0078] 2. Four-wing sailboard design.

[0079] This application addresses a series of problems inherent in traditional flat-panel single-wing and bi-wing solar panel designs through a four-wing solar panel layout. Deploying the roll-up flexible solar panels via a single-axis oscillation simplifies the deployment process of the original bi-axis solar panels, reduces mechanical complexity, and increases system reliability. Since the four-wing solar panels oscillate only along a single axis in the ±Z direction (i.e., towards the sky and towards the ground), combined with the flight direction of Satellite 10, the surface-to-mass ratio is small. Furthermore, with the same panel area, the four-wing solar panel design effectively reduces the overall satellite's moment of inertia and inertial product compared to bi-wing solar panels. The reduced inertial product makes Satellite 10 more responsive during attitude adjustments, requiring less torque or angular momentum. This significantly improves the control efficiency and accuracy of attitude control systems such as reaction wheels.

[0080] 3. Stacking design and timing separation mechanism.

[0081] In this application, satellite 10 adopts a stacked design. Multiple satellites 10 are arranged in the rocket fairing and launched by tightly stacking them in an inter-satellite stacking column. The number of inter-satellite stacking columns can be set to three or four, etc. With the timing separation method and claw-type separation and release mechanism, the satellites 10 can separate one by one in a predetermined sequence after entering orbit in a diagonal manner. This design ensures that each satellite 10 can safely deploy its antenna and enter the working state after separation, avoiding the risk of inter-satellite collision during separation.

[0082] The deployment process of the multi-fold satellite of this application is illustrated here with an example.

[0083] Figure 9 shows a flowchart 900 of the multi-fold satellite deployment process of this application. Referring to Figure 9, data acquisition is performed in step S910; in step S920, it is determined whether the launch vehicle attitude parameters meet the requirements. If the determination is negative, proceed to step S910; if the determination is positive, proceed to step S930; in step S930, the inter-satellite timing separation procedure is executed; in step S940, the chuck-type separation mechanism operates; in step S950, it is determined whether the inter-satellite separation signal meets the requirements. If the determination is negative, proceed to step S940; if the determination is positive, proceed to step S960; in step S960, it is determined whether the satellite attitude parameters meet the requirements. If the determination is negative, proceed to step S950; if the determination is positive, proceed to step S970.

[0084] Referring to Figure 9, in step S970, the inter-cabin locking device is unlocked and the cabin is deployed; in step S980, it is determined whether the cabin locking signal meets the requirements. If the determination is no, proceed to step S970; if the determination is yes, proceed to step S990; in step S990, it is determined whether the satellite attitude parameters meet the requirements. If the determination is no, proceed to step S980; if the determination is yes, proceed to step S911.

[0085] For example, the beneficial effects that this application can produce are as follows.

[0086] 1. Strong Communication Capabilities: The multi-fold configuration design of this application significantly increases the area of ​​the phased array antenna of the satellite after deployment, thereby significantly improving signal reception and transmission capabilities. Compared to the small phased array antennas installed in existing satellites, this application can support direct communication with ordinary mobile phones, expanding coverage, improving signal strength, and reducing communication blind spots. The large-area phased array antenna enables the satellite to communicate directly with ground users, eliminating reliance on ground base stations or special terminal equipment. Users only need to use ordinary mobile phones to connect to the satellite, greatly simplifying the user process and improving the user experience.

[0087] 2. Compact Envelope Design: The multi-fold design effectively reduces the satellite's envelope size during launch, lowering the space requirements for the launch vehicle fairing. This allows the satellite to be launched in conjunction with more types of rockets, improving launch flexibility and reducing launch costs.

[0088] 3. Improved launch and deployment efficiency: Through a stacking design, multiple multi-fold satellites can be launched by tightly stacking them together, making full use of the rocket's payload space and maximizing launch efficiency. This significantly improves the deployment speed of satellite constellations, helping to quickly cover global network needs. The timing separation method and mechanism ensure the safe deployment of multiple satellites.

[0089] 4. Improved Reliability and Stability: Compared to the complex integrated wing-array mechanical structure design of existing satellites, the multi-fold configuration and solar panel design of this application adopt a folding and deployment mechanism, reducing the number of mechanical components. Fewer mechanical components mean fewer potential failure points, thereby reducing the risk of failure during on-orbit deployment and improving the on-orbit operational reliability of the satellite. The single-axis oscillating design of the solar panels simplifies the deployment and attitude adjustment of the panels and significantly reduces the satellite's moment of inertia and inertial product, improving the efficiency of the satellite's attitude control system.

[0090] 5. Spatial Layout Supporting Inter-Satellite Laser Communication: Even after deployment, the multi-fold satellite configuration of this application still provides sufficient installation space for laser communication equipment between satellites. Compared to the integrated wing array design and small phased array antenna area of ​​existing satellites, this application can simultaneously meet the dual requirements of direct mobile phone communication and high-speed inter-satellite data transmission. This makes the configuration suitable not only for low-bandwidth direct mobile phone services but also for the high-speed communication and data transmission needs of large-scale low-Earth orbit satellite networks.

[0091] This application also proposes a launch vehicle comprising: a fairing and the aforementioned multi-fold satellites, wherein multiple multi-fold satellites are interconnected and stacked within the fairing. Exemplarily, this arrangement enables efficient stacking of satellites within the rocket, improving the space utilization of the fairing and allowing for the launch of more satellites per launch.

[0092] This application also proposes a control method for multi-fold satellites, applied to the aforementioned multi-fold satellites, including:

[0093] In response to receiving a unfolding signal, the stacked components are controlled to unlock adjacent cabin modules, and the unfolding mechanism is controlled to drive the outer cabin module to rotate in a first direction or in a second direction to unfold at least one cabin module.

[0094] In response to receiving a stacking signal, the folding mechanism is controlled to drive the outer cabin module to rotate in a first direction or in a second direction to stack multiple cabin modules, and the stacking components are controlled to lock adjacent cabin modules.

[0095] The proposed multi-fold satellite overall configuration design for direct mobile phone connectivity utilizes novel technologies such as a folded satellite configuration, multi-wing roll-up flexible solar panels, stacking design, and timing separation mechanism. This design addresses issues in existing technologies, including insufficient phased array antenna area, excessively large satellite envelope size, complex deployment process with low reliability, and lack of support for inter-satellite laser communication. This application offers significant advantages in optimizing the transmission envelope, improving satellite reliability, and supporting direct mobile phone connectivity and inter-satellite laser communication, making it suitable for the construction and operation of future large-scale low-Earth orbit internet satellite constellations.

[0096] This application also proposes a computing device, comprising: at least one processor; and at least one memory storing instructions thereon, which, when executed individually or jointly by the at least one processor, cause the computing device to perform the above-described control method for a multi-fold satellite.

[0097] Figure 10 shows a simplified block diagram of a device 1000 suitable for implementing exemplary embodiments of the present application. For example, a computing device may be implemented by device 1000. As shown, device 1000 includes one or more processors 1010, one or more memories 1020 coupled to processors 1010, and one or more communication modules 1040 coupled to processors 1010.

[0098] The communication module 1040 is used for bidirectional communication. The communication module 1040 has at least one antenna to facilitate communication. The communication interface can represent any interface necessary for communication with other network elements.

[0099] Processor 1010 can be of any type suitable for a local technology network, and as a non-limiting example, can include one or more of the following: general-purpose computer, special-purpose computer, microprocessor, digital signal processor (DSP), and processor based on a multi-core processor architecture. Device 1000 can have multiple processors, such as application-specific integrated circuit (ASIC) chips, which are timely driven to a clock that synchronizes with the main processor.

[0100] Memory 1020 may include one or more non-volatile memories and one or more volatile memories. Examples of non-volatile memories include, but are not limited to, read-only memory (ROM) 1024, electrically programmable read-only memory (EPROM), flash memory, hard disk, optical disc (CD), digital video disc (DVD), and other magnetic and / or optical storage. Examples of volatile memories include, but are not limited to, random access memory (RAM) 1022 and other volatile memories that do not persist during power-off periods.

[0101] Computer program 1030 includes computer-executable instructions that are executed by the associated processor 1010. Program 1030 may be stored in ROM 1024. Processor 1010 may perform any appropriate actions and processes by loading program 1030 into RAM 1022.

[0102] Embodiments of this application can be implemented via program 1030, enabling device 1000 to execute any of the disclosed processes discussed with reference to FIG9. Embodiments of this application can also be implemented via hardware or a combination of software and hardware.

[0103] In some embodiments, program 1030 may be tangibly contained in a computer-readable medium, which may be contained in device 1000 (e.g., memory 1020) or other storage device accessible to device 1000. Device 1000 may load program 1030 from the computer-readable medium into RAM 1022 for execution. The computer-readable medium may include any type of tangible non-volatile memory, such as ROM, EPROM, flash memory, hard disk, CD, DVD, etc. Program 1030 is stored on the computer-readable medium.

[0104] This application also proposes a non-transitory computer-readable storage medium storing machine-executable instructions, which, when executed individually or jointly by one or more processors of the machine, cause the machine to perform the aforementioned multi-fold satellite control method.

[0105] This application also proposes a chip system, including a circuit system configured to perform the above-described control method for multi-fold satellites.

[0106] Generally, the various embodiments of this application can be implemented in hardware or dedicated circuitry, software, logic, or any combination thereof. Some aspects may be implemented in hardware, while others may be implemented in firmware or software, which may be executed by a controller, microprocessor, or other computing device. Although various aspects of the embodiments of this application are shown and described as block diagrams, flowcharts, or other graphical representations, it should be understood that, as non-limiting examples, the blocks, devices, systems, techniques, or methods described herein may be implemented in hardware, software, firmware, dedicated circuitry or logic, general-purpose hardware or controllers or other computing devices, or some combination thereof.

[0107] This application also provides at least one computer program product tangibly stored on a non-transitory computer-readable storage medium. The computer program product includes computer-executable instructions, such as instructions included in program modules, which execute in a device on a target real or virtual processor to perform the flow described above with reference to FIG9. Typically, program modules include routines, programs, libraries, objects, classes, components, data structures, etc., that perform specific tasks or implement specific abstract data types. In various embodiments, the functionality of program modules can be combined or separated as needed. The machine-executable instructions for the program modules can execute within a local or distributed device. In a distributed device, the program modules can reside in both local and remote storage media.

[0108] The program code used to perform the methods of this application can be written in any combination of one or more programming languages. This program code can be provided to a processor or controller of a general-purpose computer, a special-purpose computer, or other programmable data processing device, such that when the program code is executed by the processor or controller, the functions / operations specified in the flowcharts and / or block diagrams are implemented. The program code can be executed entirely on a machine, partially on a machine, partially on a remote machine, partially on a remote machine, or entirely on a remote machine or server as a standalone software package.

[0109] In the context of this application, computer program code or related data may be carried by any suitable carrier to enable a device, apparatus, or processor to perform the various processes and operations described above. Examples of carriers include signals, computer-readable media, etc.

[0110] Computer-readable media can be computer-readable signal media or computer-readable storage media. Computer-readable media can include, but is not limited to, electronic, magnetic, optical, electromagnetic, infrared, or semiconductor systems, devices, or apparatuses, or any suitable combination thereof. More specific examples of computer-readable storage media include electrical connections having one or more wires, portable computer floppy disks, hard disks, random access memory (RAM), read-only memory (ROM), erasable programmable read-only memory (EPROM or flash memory), optical fibers, portable optical disc read-only memory (CD-ROM), optical storage devices, magnetic storage devices, or any suitable combination thereof.

[0111] Furthermore, although the operations are described in a specific order, this should not be construed as requiring that these operations be performed in the specific order or sequence shown, or that all of the operations shown be performed to obtain the desired result. In some cases, multitasking and parallel processing may be advantageous. Similarly, while several specific implementation details are included in the foregoing discussion, these details should not be construed as limiting the scope of this application, but rather as descriptions of features specific to particular embodiments. Certain features described in the context of a single embodiment may also be implemented in combination in a single embodiment. Conversely, various features described in the context of a single embodiment may also be implemented individually or in any suitable sub-combination in multiple embodiments.

[0112] Although this application has been described in language specific to structural features and / or methodological behavior, it should be understood that the application as defined in the appended claims is not necessarily limited to the specific features or behaviors described above. Rather, the specific features and actions described above are disclosed as exemplary forms for implementing the claims.

[0113] It should be fully understood that the use of personally identifiable information should comply with privacy policies and practices generally considered to meet or exceed industry or governmental requirements for protecting user privacy. In particular, personally identifiable information data should be managed and processed to minimize the risk of unintentional or unauthorized access or use, and the nature of authorized use should be clearly indicated to the user.

Claims

1. A multi-fold satellite, comprising: The main body includes multiple cabin modules, folding mechanisms, and stacking components; The stacking components are arranged between adjacent cabin modules, and the stacking components can be locked or unlocked to restrict or allow the cabin modules to rotate; The folding mechanism is connected to each cabin module, and the folding mechanism is used to drive the cabin module to rotate so that the main body is in a stacked and folded state or a flat and unfolded state. A solar panel, connected to the cabin module, is capable of swinging towards either the sky or the ground; wherein... During the process of the main body changing from the stacked and folded state to the flat and unfolded state: the stacked parts unlock the adjacent cabin modules, and the unfolding mechanism drives the outer cabin module to rotate in the first direction or in the second direction to unfold at least one cabin module. or During the process of the main body changing from the unfolded state to the stacked state: the unfolding mechanism drives the outer cabin module to rotate along the first direction or along the second direction to stack the multiple cabin modules, and the stacking component locks the adjacent cabin modules.

2. The multi-fold satellite as described in claim 1, wherein, The stacking component is a stacking column, which includes a first stacking section and a second stacking section, respectively disposed on the adjacent cabin modules; wherein, When the stacked components unlock adjacent cabin modules, the first stacked portion and the second stacked portion separate; or When the stacked components lock adjacent cabin modules, the first stacked portion and the second stacked portion are connected.

3. The multi-fold satellite as described in claim 1 or 2, wherein, The cabin module is a flat-panel cabin module, which includes a first panel, a second panel, and a support assembly. The support assembly is connected to the first panel and the second panel respectively. The first panel and the second panel are arranged opposite to each other. The first panel is used to face the sky, and the second panel is used to face the ground. The solar panel is connected to the support assembly.

4. The multi-fold satellite as described in claim 3, wherein, All cabin modules have a phased array antenna on their second panel; or at least one cabin module has a phased array antenna on its second panel.

5. The multi-fold satellite as described in claim 3, wherein, At least one of the following is provided on the first panel of the cabin module: a star sensor, a laser communication device, a telemetry and control antenna, a solar array, a magnetometer, a gyroscope, and a sun sensor, or any combination thereof.

6. The multi-fold satellite as described in claim 1, wherein, The solar panel is a roll-type flexible solar panel. The solar panel is equipped with a drive shaft and a deployment mechanism. When the solar panel is in a rolled-up state, the solar panel is deployed into a flat plate shape by the deployment mechanism and swings towards the sky and the ground by the drive shaft.

7. The multi-fold satellite as described in claim 1 or 6, wherein, The number of solar panels is N, where N is an even number and greater than or equal to four; at least four solar panels are respectively installed on the outer cabin module, and two solar panels located on the same cabin module are arranged opposite each other.

8. The multi-fold satellite as described in claim 1, wherein, The number of cabin modules is at least three, and the stacking components include: a first stacking component, a second stacking component, and a third stacking component; the cabin module includes a first side and a second side opposite to each other, and on the same cabin module, the first stacking component is disposed in the middle of the first side, and the second stacking component and the third stacking component are respectively disposed at both ends of the second side.

9. The multi-fold satellite as described in claim 1, wherein, The number of cabin modules is at least three, and the stacking components include: a first stacking component, a second stacking component, a third stacking component, and a fourth stacking component; the cabin module includes a first side and a second side opposite to each other, and on the same cabin module, the first stacking component and the second stacking component are respectively disposed at both ends of the first side, and the third stacking component and the fourth stacking component are respectively disposed at both ends of the second side.

10. The multi-fold satellite as described in claim 3, wherein, At least one of the following components is provided on the support assembly of the cabin module: an integrated electronic system, a battery, a power controller, a reaction flywheel, a load electronic system, a thruster, a routing device, and a power distribution unit, or any combination thereof.

11. A launch vehicle, comprising: The fairing and the multi-fold satellite of any one of claims 1-10, wherein a plurality of said multi-fold satellites are interconnected and stacked within the fairing.

12. A control method for a multi-fold satellite, applied to a multi-fold satellite according to any one of claims 1-10, comprising: In response to receiving a unfolding signal, the stacked components are controlled to unlock adjacent cabin modules, and the unfolding mechanism is controlled to drive the outer cabin module to rotate in a first direction or in a second direction to unfold at least one cabin module. or In response to receiving a stacking signal, the folding mechanism is controlled to drive the outer cabin module to rotate along the first direction or along the second direction to stack multiple cabin modules, and the stacking component is controlled to lock adjacent cabin modules.

13. A computing device, comprising: At least one processor; as well as At least one memory storing instructions that, when executed individually or jointly by the at least one processor, cause the computing device to perform the method according to claim 12.

14. A non-transitory computer-readable storage medium storing machine-executable instructions, which, when executed individually or jointly by one or more processors of a machine, cause the machine to perform the method of claim 12.

15. A chip system comprising a circuit system configured to perform the method of claim 12.

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