Modular satellites and spacecraft

Abstract

The application relates to a modular satellite and spacecraft. The modular satellite comprises a main structure, at least one power module and at least one storage tank module, the storage tank module comprising at least one storage tank module; at least one platform module detachably connected with the main structure; and at least one observation load detachably connected with the main structure. The application can improve the universality of the satellite, modularly assemble and expand the performance on demand, reduce the production cost of the satellite, and adapt to multiple task scenarios.

Description

Technical Field

[0001] This application relates primarily to the field of artificial satellite technology, and more specifically to a modular satellite and spacecraft. Background Technology

[0002] With the rapid development of the commercial space industry, the demand for low-cost, universal, and scalable micro-nano satellite platforms continues to increase. Current micro-nano satellites typically employ an integrated frame structure, which suffers from poor versatility and high costs associated with iterative modifications. Summary of the Invention

[0003] The technical problem to be solved by this application is to provide a modular satellite and spacecraft that can improve the versatility of the satellite, allow for modular assembly and performance expansion as needed, reduce the production cost of the satellite, and adapt to multiple mission scenarios.

[0004] The technical solution adopted in this application to solve the above-mentioned technical problems is a modular satellite, comprising: a main structure, including a tank module and at least one power module, wherein the tank module includes at least one tank module; at least one platform module, detachably connected to the main structure; and at least one observation payload, detachably connected to the main structure.

[0005] In one embodiment of this application, the main structure includes at least two power modules, which are respectively disposed at opposite ends of the tank module, and the tank module and the axis center of the at least two power modules coincide.

[0006] In one embodiment of this application, the platform module includes one or any combination of an integrated electronic module, an energy module, a measurement and control attitude determination module, and a windsurfing module.

[0007] In one embodiment of this application, a receiving groove is formed on one side of the integrated electronic module and / or one side of the energy module, and the inner contour dimension of the receiving groove matches the outer contour dimension of the storage tank module, so that the integrated electronic module and / or the energy module can be spliced ​​and combined with the storage tank module.

[0008] In one embodiment of this application, the integrated electronic module and the energy module are respectively disposed on both sides of the tank module. The receiving slot of the integrated electronic module is in contact with the first side of the tank module, and the receiving slot of the energy module is in contact with the second side of the tank module. The integrated electronic module, the tank module and the energy module together constitute a combination with a rectangular cross-section.

[0009] In one embodiment of this application, the axial height of the integrated electronic module and the axial height of the energy module are consistent with the axial height of the tank module, so that the assembly can be sandwiched between the at least two power modules to form a sandwich structure.

[0010] In one embodiment of this application, the measurement and control attitude determination module is disposed on the outer end face of one of the power modules, and the cross-sectional outer envelope dimension of the measurement and control attitude determination module is consistent with the cross-sectional outer envelope dimension of the power module.

[0011] In one embodiment of this application, the solar panel module is disposed on the end face of the telemetry and attitude determination module away from the power module, and the solar panel module can be deployed or retracted to the side of the satellite.

[0012] In one embodiment of this application, the solar panel module includes: at least one first base plate, at least two second base plates, a deployment device, and a clamping and releasing device; wherein, the at least one first base plate is connected to the telemetry and attitude determination module, the at least two second base plates are connected to adjacent first base plates through the deployment device, and the clamping and releasing device can lock the second base plates to the side of the satellite.

[0013] In one embodiment of this application, the observation load is disposed on the outer end face of one of the power modules.

[0014] In one embodiment of this application, the tank module includes a tank frame and a fuel tank, wherein the fuel tank is disposed inside the tank frame.

[0015] In one embodiment of this application, the tank module further includes a tank valve group switch, which is connected to the fuel tank and is capable of sealing off the fuel added to the fuel tank.

[0016] In one embodiment of this application, each power module includes: a protective frame, at least one satellite thruster, and a propulsion pipeline, wherein the at least one satellite thruster is disposed outside the protective frame, and the propulsion pipeline is disposed inside the protective frame.

[0017] To address the aforementioned technical problems, this application also proposes a spacecraft comprising a modular satellite as described above.

[0018] The technical solution of this application forms a modular and scalable reconfigurable satellite structure by disassembling the satellite into a main structure for load-bearing, a detachable platform module, and a detachable observation payload. Each module can be designed and manufactured independently, and the number of power modules and the selection of platform modules and observation payloads with different functions can be flexibly adjusted according to the needs of different orbits and different observation missions. There is no need to redesign the overall satellite structure, which reduces the overall R&D, production and modification costs of the satellite and improves the satellite's versatility. Attached Figure Description

[0019] To make the above-mentioned objectives, features and advantages of this application more apparent and understandable, the specific embodiments of this application will be described in detail below with reference to the accompanying drawings, wherein: Figure 1 This is a schematic diagram of an existing integrated frame micro / nano satellite; Figure 2 This is a schematic diagram of an existing panel-type micro / nano satellite; Figure 3 This is a schematic diagram of an existing panel-type micro / nano satellite with the panel opened. Figure 4 This is a schematic diagram of a modular satellite according to an embodiment of this application; Figure 5 This is an exploded view of a modular satellite according to an embodiment of this application; Figure 6 This is a schematic diagram of the main structure in one embodiment of this application; Figure 7 This is a schematic diagram of the main structure in another embodiment of this application; Figure 8 This is an exploded view of a modular satellite according to another embodiment of this application; Figure 9 This is a schematic diagram of a modular satellite according to another embodiment of this application; Figure 10 This is a schematic diagram of a modular satellite retractable solar panel module according to another embodiment of this application; Figure 11 This is a schematic diagram of a modular satellite according to yet another embodiment of this application.

[0020] Explanation of reference numerals in the accompanying drawings for specific embodiments: 101. Thrust; 102. Integrated electronic and energy single-unit systems; 103. Integrated frame; 104. Onboard optical camera payload; 105. Propel the storage tank; 201. Panel; 300. Satellite; 301. Observation payload; 302. Power module; 3021. Protection Frame; 3022. Satellite thruster; 303. Energy Module; 304. Measurement and control attitude determination module; 305. Integrated electronic module; 306. Storage tank module; 3061. Storage tank module; 3062. Storage tank frame; 3063. Fuel tank; 307. Sailboard Module; 3071. First substrate; 3072. Second substrate; 3073. Deployment device; 801. Phased array antenna. Detailed Implementation

[0021] To make the above-mentioned objectives, features and advantages of this application more apparent and understandable, the specific embodiments of this application will be described in detail below with reference to the accompanying drawings.

[0022] Many specific details are set forth in the following description in order to provide a full understanding of this application. However, this application may also be implemented in other ways different from those described herein, and therefore this application is not limited to the specific embodiments disclosed below.

[0023] As illustrated in this application, unless the context clearly indicates otherwise, the words "a," "an," "an," and / or "the" do not specifically refer to the singular and may also include the plural. Generally speaking, the terms "comprising" and "including" only indicate the inclusion of explicitly identified steps and elements, which do not constitute an exclusive list, and the method or apparatus may also include other steps or elements.

[0024] In the description of this application, it should be understood that the orientation or positional relationship indicated by directional terms such as "front, back, up, down, left, right", "horizontal, vertical, horizontal" and "top, bottom" is usually based on the orientation or positional relationship shown in the accompanying drawings, and is only for the convenience of describing this application and simplifying the description. Unless otherwise stated, these directional terms do not indicate or imply that the device or element referred to must have a specific orientation or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation on the scope of protection of this application; the directional terms "inner" and "outer" refer to the inner and outer contours relative to the outline of each component itself.

[0025] For ease of description, spatial relative terms such as "above," "on top of," "on the upper surface of," "above," etc., are used herein to describe the spatial positional relationship of a device or feature as shown in the figures to other devices or features. It should be understood that spatial relative terms are intended to encompass different orientations in use or operation beyond the orientation of the device as described in the figures. For example, if the device in the figures were inverted, a device described as "above" or "on top of" other devices or structures would subsequently be positioned as "below" or "under" other devices or structures. Thus, the exemplary term "above" can include both "above" and "below." The device may also be positioned in other different ways (rotated 90 degrees or in other orientations), and the spatial relative descriptions used herein will be interpreted accordingly.

[0026] Furthermore, it should be noted that the use of terms such as "first" and "second" to define components is merely for the purpose of distinguishing the corresponding components. Unless otherwise stated, these terms have no special meaning and therefore should not be construed as limiting the scope of protection of this application. In addition, although the terminology used in this application is selected from commonly known and used terms, some terms mentioned in this application's specification may have been chosen by the applicant according to his or her judgment, and their detailed meanings are explained in the relevant sections of this description. Moreover, this application should be understood not only through the actual terms used, but also through the meaning implied by each term.

[0027] The embodiments of this application are described below based on the accompanying drawings. However, the embodiments shown below are examples of modular satellites and spacecraft used to embody the technical concept of this application, and the modular satellites and spacecraft of this application are not specifically defined as follows. This application is by no means intended to limit the scope of this application to the dimensions, materials, shapes, and relative arrangements of the constituent components described in the embodiments. In particular, unless otherwise specified, it is not intended to limit the scope of this application to these aspects, but merely to provide illustrative examples.

[0028] However, the dimensions or positional relationships of the components shown in the accompanying drawings are sometimes exaggerated for clarity. Therefore, in the following description, detailed descriptions of the same names and symbols representing the same or homogeneous components are appropriately omitted. Furthermore, the elements constituting this application may be multiple elements composed of the same components, thus allowing one component to function as multiple elements; conversely, multiple components may share the function of one component. Additionally, the content described in some embodiments and implementations can be applied to other embodiments and implementations. Furthermore, in this specification, "upper" is not limited to the case of being formed in contact with an upper surface, but also includes the case of being formed separately on top, and also includes the meaning of an intermediate layer between layers.

[0029] Figure 1 This is a schematic diagram of an existing integrated frame micro / nano satellite. (Example) Figure 1 As shown, the main structure of this integrated frame micro / nano satellite is an integrated frame 103, which serves as the load-bearing structure of the satellite body. The propulsion tank 105 is installed inside the frame, while the exposed thrusters 101 are arranged outside. One end of the integrated frame 103 houses the onboard optical camera payload 104, and the other end houses the integrated electronics and power unit 102. For frame-structured micro / nano satellites, the integrated frame 103 is designed and manufactured specifically for the dimensions of the satellite platform's individual units and payloads (such as the onboard optical camera payload 104), which has the drawback of requiring separate frame designs for each model. Furthermore, to meet the mission requirements of different orbits and on-orbit maneuvers, the fuel capacity of the propulsion tank 105 and the thrusters 101 need to be expanded. However, the already manufactured integrated frame 103 is incompatible, requiring redesign and reproduction, increasing the satellite design and production cycle and cost.

[0030] Figure 2 This is a schematic diagram of an existing panel-type micro / nano satellite. Figure 3 This is a schematic diagram of an existing panel-type micro / nano satellite with the panel opened. (Example:) Figure 2 and Figure 3 As shown, this microsatellite adopts a panel-type structure design, with its main structure composed of multiple panels 201 spliced ​​together. Compared to Figure 1 The integrated frame 103 shown is Figure 2 The panel-type structure shown has a relatively lower manufacturing cycle and cost, but it still cannot meet the requirements for universal satellite support and platform capability expansion. For example, to accommodate the increased size of the propulsion tank 105, the panel 201 needs to be redesigned and manufactured. Therefore, the current micro-nano satellite configuration cannot meet the requirements of low cost, universality, and scalability.

[0031] To address the shortcomings of the aforementioned satellite configurations, this application proposes a modular satellite that can be applied in scenarios requiring enhanced satellite versatility and on-demand modular assembly and performance expansion. This modular satellite can serve as a component of a spacecraft or as equipment suitable for integration into space launch vehicles.

[0032] Figure 4 This is a schematic diagram of a modular satellite according to an embodiment of this application. Figure 5 This is an exploded view of a modular satellite according to an embodiment of this application. (Reference) Figure 4 and Figure 5 As shown, the modular satellite 300 of this embodiment includes a main structure, at least one platform module, and at least one observation payload 301. The main structure includes a tank module 306 and at least one power module 302, and the tank module 306 includes at least one tank module 3061. At least one platform module is detachably connected to the main structure. At least one observation payload 301 is detachably connected to the main structure.

[0033] Figure 6 This is a schematic diagram of the main structure in one embodiment of this application. Figure 7 This is a schematic diagram of the main structure in another embodiment of this application. For example, see reference... Figures 5 to 7 As shown, the tank module 306 is the core unit, and the tank module 306 includes a tank frame 3062 and a fuel tank 3063. A tank module 3061 may include a tank frame 3062 and a fuel tank 3063. Depending on actual expansion needs, the tank module 306 may be composed of one or more tank modules 3061. Figure 5 and Figure 6 The basic configuration of a tank module 3061 is shown. Figure 7 An extended configuration of two tank modules 3061 connected in series is shown. If multiple tank modules 3061 are used to form a tank module 306, the fuel tanks 3063 within the multiple tank modules 3061 can be connected to form a large fuel tank. The tank module 306 can also consist of multiple standard-height tank frames 3062 and a complete fuel tank 3063 adapted to their height.

[0034] In practical applications, if the capacity of the fuel tank module 306 cannot meet the fuel consumption requirements of the satellite 300 during flight maneuvers, it can be expanded according to the tank volume. For example, a 2Kg (Kg represents kilogram) fuel tank 3063 can be replaced with a 4Kg fuel tank 3063, and simultaneously combined with multiple (e.g., two) tank frames 3062 to form a configuration such as... Figure 7The tank module 306 shown can enhance the capabilities of the satellite propulsion system, enabling the satellite 300 to perform maneuvers and maintain its orbit for longer periods. The tank frame 3062 and fuel tank 3063 will be further explained later.

[0035] The number of power modules 302 can be set to one, two, or more than three depending on the task requirements. For example, if there is one power module 302, it can be placed above or below the tank module 306; if there are two power modules 302, they can be placed above and below the tank module 306 respectively; if there are three power modules 302, one power module 302 can be placed above the tank module 306 and two power modules 302 can be placed below it; multiple power modules 302 can also be placed on one side of the tank module 306 simultaneously. This application does not limit the number of tank modules 3061 and power modules 302, or the arrangement of the power modules 302. The platform module and observation payload 301 of this application can be assembled with the main structure using standard mechanical interfaces, facilitating assembly and disassembly.

[0036] This application achieves a modular assembly design for the entire satellite at the physical structure level by dividing the functions of each subsystem. By disassembling the satellite into multiple sets of detachable standardized modules, when facing different mission requirements and design specifications, some modules can be replaced or upgraded to higher-performance modules of the same type without modifying other modules. This application changes the traditional customized design approach of "one type, one satellite" for integrated satellites, reducing the development and design costs of satellites.

[0037] refer to Figure 5 and Figure 6 As shown, in some embodiments, the main structure includes at least two power modules 302, which are respectively disposed at opposite ends of the tank module 306, and the tank module 306 coincides with the axial center (not shown in the figure) of the at least two power modules 302.

[0038] For example, the main structure of satellite 300 can be assembled from two power modules 302 (upper and lower) and a storage tank module 306. The two power modules 302 are respectively installed at opposite ends of the storage tank module 306, with their axes coinciding. The power modules 302 and the storage tank module 306 can be screwed together to form a whole, becoming the main structure of satellite 300. This application improves the rigidity of the overall structure by arranging multiple power modules 302 coaxially and symmetrically. The power modules 302, with their two-end layout, can each be equipped with different functional units, optimizing the overall satellite spatial layout.

[0039] refer to Figure 4 and Figure 5As shown, in some embodiments, the platform module includes one or any combination of an integrated electronics module 305, an energy module 303, a telemetry, tracking, and attitude determination module 304, and a solar panel module 307. For example, the integrated electronics module 305 includes a satellite mission computer, capable of controlling the satellite platform and planning and executing missions. The energy module 303 includes a battery pack and a corresponding integrated power controller. The battery pack provides power to individual satellite platform units and stores the electrical energy generated by the solar panel module 307; the power controller distributes the energy output from the battery, enabling modulation of the operating voltage and current of different satellite units. The telemetry, tracking, and attitude determination module 304 includes a telemetry and control board, a star sensor, a fiber optic gyroscope, and a small momentum wheel. The solar panel module 307 includes a solar panel base plate, a deployment hinge, a clamping and releasing device, and solar cells.

[0040] In practical applications, some modules can be selectively configured based on the mission complexity of different satellites. For example, satellites performing simple missions can be configured with integrated electronic module 305 and energy module 303; satellites performing complex missions can be configured with all platform modules. The platform modules in this application are not limited to the module types mentioned above. Depending on the specific satellite model and constellation requirements, the platform modules may also include onboard stand-alone modules (such as intelligent processing modules and mission planning modules). Platform modules can be expanded and interchanged as long as their mechanical interfaces and size envelopes are consistent. By dividing the satellite platform functions into multiple functional modules, this application can adapt to various mission scenarios of different satellites, improving the scenario adaptability and versatility of the satellite platform.

[0041] refer to Figure 5 As shown, in some embodiments, a receiving groove (such as) is formed on one side of the integrated electronic module 305 and / or one side of the energy module 303. Figure 5 The diagram shows that the overall outer dimensions of the integrated electronic module 305 and the energy module 303 are U-shaped. The inner contour dimensions of the receiving slot match the outer contour dimensions of the storage tank module 306, so that the integrated electronic module 305 and / or the energy module 303 can be spliced ​​and combined with the storage tank module 306.

[0042] Exemplarily, the overall outer dimension envelope of the integrated electronic module 305 and the energy module 303 is designed with a structure having a receiving groove on one side. The integrated electronic module 305 or the energy module 303 can be used alone to be spliced with the tank module 306, or the integrated electronic module 305 and the energy module 303 can be assembled simultaneously. The integrated electronic module 305 and the energy module 303 are in direct contact with the frame surface of the tank module 306 through their respective receiving grooves, and the generated heat can be conducted to the tank module 306. Through the structural design of splicing by the receiving groove in this application, the space utilization rate is improved. By the contact of the integrated electronic module 305, the energy module 303 and the tank module 306, heat can be conducted to provide passive thermal insulation for the fuel tank, realizing the integrated design of structural thermal control coupling and lightweighting.

[0043] Reference Figure 4 and Figure 5 As shown, in some embodiments, the integrated electronic module 305 and the energy module 303 are respectively disposed on both sides of the tank module 306. The receiving groove of the integrated electronic module 305 is in contact with the first side surface of the tank module 306, and the receiving groove of the energy module 303 is in contact with the second side surface of the tank module 306. The integrated electronic module 305, the tank module 306 and the energy module 303 together form a combined body with a rectangular cross-section (such as in an approximate cube state).

[0044] Exemplarily, the outer dimension envelopes of the integrated electronic module 305 and the energy module 303 are the same (for example, the sizes are exactly equal or approximately close). The two are symmetrically arranged on the left and right sides of the tank module 306. After the three are spliced, the overall outer contour is a regular rectangle (such as a combined body structure similar to a "hui" character shape), that is, the energy module 303 and the integrated electronic module 305 centrally wrap the tank module 306. This combination method enables the tank module 306 to be comprehensively wrapped, improves the heat conduction effect and the thermal insulation effect, optimizes the thermal control performance, reduces the thermal control resource requirements of the satellite platform, and realizes the lightweight design of the satellite. By forming a rectangular combined body through bilateral symmetric splicing, the centroid distribution of the whole satellite can be balanced, the stability of the on-orbit attitude of the satellite 300 is improved, and the regular rectangular contour is convenient for assembling with the power module 302.

[0045] Figure 8 is an exploded view of a modular satellite according to another embodiment of the present application. Reference Figure 5 and Figure 8 As shown, in some embodiments, the axial height of the integrated electronic module 305 and the axial height of the energy module 303 are the same as the axial height of the tank module 306, so that the combined body of the three can be clamped between at least two power modules 302 to form a sandwich structure.

[0046] Exemplarily, the axial direction mentioned in this application can be Figure 5 and Figure 8 the direction A shown in. Figure 8 The diagram shows a large integrated electronic module 305 composed of two small integrated electronic modules, and a large energy module 303 composed of two small energy modules. The integrated electronic module 305, energy module 303, and tank module 306 have completely equal or approximately similar axial heights. The rectangular assembly formed by these three modules can be embedded between the upper and lower power modules 302 to form a sandwich structure. This sandwich structure relies on the power modules 302 at both ends for axial restraint and fastening. In practical applications, the frame height of the central tank module 306 can be further expanded according to satellite operational requirements. For example, the tank module 306 can be composed of more tank frames 3062 and fuel tanks 3063 of different capacities, correspondingly increasing the height of the integrated electronic module 305 and energy module 303. This can significantly improve and expand the satellite platform's performance indicators, particularly computing power and battery capacity. If the tank module 306 adopts N (N is a positive integer) standard height tank frames 3062, 2N platform modules located on the outside of the frame can be added accordingly, such as integrated electronic module 305, energy module 303, intelligent computing module, etc. This application does not limit the combination type and combination quantity of each module.

[0047] This application utilizes a sandwich structure formed by the cooperation of various modules, ensuring uniform axial stress on each module and improving the overall structural strength of the satellite. The modular sandwich layout simplifies assembly and facilitates rapid integration, disassembly, and maintenance. Through the high degree of expansion of the storage tank module 306 and related cooperating modules, a step-by-step improvement in satellite platform performance is achieved.

[0048] refer to Figure 4 and Figure 5 As shown, in some embodiments, the telemetry, control, and attitude determination module 304 is disposed on the outer end face of one of the power modules 302, and the outer envelope dimension of the cross-section of the telemetry, control, and attitude determination module 304 is consistent with the outer envelope dimension of the cross-section of the power module 302 (e.g., the dimensions are completely equal or approximately equal). For example, the telemetry, control, and attitude determination module 304 can be installed on the outer end face of the upper power module 302. Through the design of consistent outer envelope dimensions, the power module 302 can achieve maximum load-bearing capacity as the main structure of the satellite, effectively utilizing the load-bearing space of the power module 302 and improving structural utilization.

[0049] The telemetry, control, and attitude determination module 304 can integrate attitude control-related individual components such as a telemetry and control board, a star sensor, a fiber optic gyroscope, a small momentum wheel, and a reaction flywheel. The telemetry and control board is used to implement the satellite-to-ground telemetry, control, and communication functions of satellite 300. The star sensor enables on-orbit attitude determination and pointing confirmation of satellite 300. The fiber optic gyroscope enables on-orbit attitude confirmation of satellite 300. The small momentum wheel enables attitude control and stabilization of satellite 300. The telemetry, control, and attitude determination module 304 can be extended in height according to the number of individual units and size requirements.

[0050] Figure 9 This is a schematic diagram of a modular satellite according to another embodiment of this application. Figure 10 This is a schematic diagram of a modular satellite retractable solar panel module according to another embodiment of this application. (See reference) Figure 4 and Figure 5 ,as well as Figures 8 to 10 As shown, in some embodiments, the windsurf module 307 is disposed on the end face of the measurement and control attitude determination module 304 away from the power module 302, and the windsurf module 307 can be deployed (e.g. Figure 9 (as shown) or folded up to the side of satellite 300 (as shown) Figure 10 (As shown).

[0051] For example, the solar panel module 307 can be installed on the upper part of the telemetry, tracking, and command (TT&C) module 304. Before the launch of the launch vehicle carrying the satellite 300, the solar panels located at the edges of the solar panel module 307 can be folded and retracted to the sides of the energy module 303 and the integrated electronics module 305 to meet the envelope requirements of the launch vehicle. After the satellite 300 enters orbit, it is unlocked by an unlocking device, such as by unfolding and locking via a rotating hinge. After unfolding, the solar panel module 307 is oriented towards the sun to achieve satellite energy harvesting. This application, through the retractable and unfoldable structural design of the solar panel module 307, can balance the envelope constraints during the launch phase of the launch vehicle with the operational requirements of the satellite 300 during its on-orbit phase. The area of ​​the solar panels in the solar panel module 307 can be expanded as needed to further enhance the overall satellite energy harvesting capability.

[0052] refer to Figure 4 and Figure 9 As shown, in some embodiments, the sailboard module 307 includes: at least one first substrate 3071, at least two second substrates 3072, a deployment device 3073, and a clamping and releasing device (not shown in the figure). At least one first substrate 3071 is connected to the measurement and control attitude determination module 304, and at least two second substrates 3072 are connected to adjacent first substrates 3071 via the deployment device 3073. When the sailboard module 307 is in a retracted state (e.g., ...), Figure 10 As shown), the clamping release device can lock the second substrate 3072 to the side of the satellite 300.

[0053] For example, Figure 4The diagram shows that the sailboard module 307 includes a first substrate 3071 and two second substrates 3072; Figure 9 The diagram shows a windsurf module 307 comprising a first substrate 3071 and four second substrates 3072. The first substrate 3071 serves as the intermediate substrate, and the second substrates 3072 are located on the sides of the first substrate 3071. The first substrate 3071 can be mounted to the upper end of the measurement and control attitude determination module 304 by means of screws or the like. The second substrates 3072 are connected to the intermediate first substrate 3071 via a deployment device 3073 (e.g., a deployment hinge). The deployment hinge allows the windsurf substrate to rotate around its axis, thereby enabling the folding and unfolding of the side windsurf substrates. This application does not limit the number of first substrates 3071 and second substrates 3072.

[0054] The clamping and releasing device can employ shape memory alloys, pyrotechnics, or hot knives to lock the side-folding solar panel substrate to the side of the satellite platform. After the satellite enters orbit, heating the shape memory alloy unlocks the substrate, allowing the second substrate 3072 to unfold under the drive of a hinge. Solar cells can be attached to the surface of the solar panel substrate, enabling the satellite 300 to generate electricity using solar power during its orbital flight to ensure energy supply. The surface of the solar panel module 307 can be equipped with communication antennas such as telemetry and control antennas and GNSS (Global Navigation Satellite System) antennas to achieve satellite telemetry and control, further improving space utilization.

[0055] This application, through the combination of a base plate, hinge, and clamping release device, enables reliable folding and automatic on-orbit deployment of the solar panels. The structure is simple, the operation is stable, and it is suitable for the lightweight design requirements of micro and nano satellites.

[0056] Figure 11 This is a schematic diagram of a modular satellite according to yet another embodiment of this application. (Reference) Figure 4 and Figure 11 As shown, in some embodiments, the observation payload 301 is disposed on the outer end face of one of the power modules 302. Exemplarily, the observation payload 301 can be mounted on the outer end face of the lower power module 302, and the mechanical interface of the observation payload 301 conforms to the cross-sectional dimensions of the power module 302. The observation payload 301 can be an Earth observation camera or other Earth remote sensing observation payloads, such as a SAR (Synthetic Aperture Radar) antenna. Figure 4 The image shows that the observation payload 301 is an optical remote sensing camera for Earth. After satellite 300 enters orbit, it can point to the Earth to perform optical imaging work and obtain ground remote sensing optical images. Figure 11 The image shows that the observation payload 301 is an active phased array antenna 801, which can realize radar remote sensing imaging of the ground.

[0057] This application achieves physical partitioning between the observation payload 301 and the platform module by arranging the observation payload 301 on the outer end face of the power module 302, thus avoiding mutual interference. A standardized interface facilitates rapid replacement of the observation payload 301, and the same satellite platform can be expanded to carry different types of observation payloads 301, achieving wide adaptability of the satellite platform.

[0058] refer to Figure 6 As shown, in some embodiments, the tank module 306 includes a tank frame 3062 and a fuel tank 3063, with the fuel tank 3063 disposed inside the tank frame 3062. Exemplarily, the propellant types that can be filled in the fuel tank 3063 include, but are not limited to, non-toxic fuel AND (Ammonium Dinitramide), anhydrous hydrazine, and chilled gas. This application improves the overall structural rigidity of the tank module 306 by utilizing a machined tank frame 3062, and also achieves integrated protection for the fuel tank 3063, thereby enhancing the structural reliability of the tank module 306.

[0059] In some embodiments, the tank module 306 further includes a tank valve group switch (not shown in the figure), which is connected to the fuel tank 3063 and can seal the fuel added to the fuel tank 3063. For example, the tank valve group switch is equivalent to a fuel filler / discharge port. After the tank module 3061 has completed assembly and leak testing, fuel can be added to the fuel tank 3063, and the fuel tank 3063 can be sealed by the tank valve group switch. After all production and inspection work of the tank module 3061 is completed, it can be used for assembly or shelf storage.

[0060] This application enables fuel loading and sealing through an integrated tank valve group switch, allowing the tank module 3061 to be pre-packaged and loaded independently. After mass production and acceptance, it becomes a shelf-ready product, readily available for use. This design eliminates the need for on-site chemical propellant loading at the launch site, shortening the assembly and integration cycle of satellite 300 and enabling rapid launch response in emergency situations.

[0061] Continue to refer to Figure 6 As shown, in some embodiments, each power module 302 includes: a protective frame 3021, at least one satellite thruster 3022 and a propulsion pipeline (not shown in the figure), with at least one satellite thruster 3022 disposed outside the protective frame 3021 and the propulsion pipeline disposed inside the protective frame 3021.

[0062] For example, the protective frame 3021 is equivalent to the power module frame. Components such as pressure sensors can also be installed within the protective frame 3021. The protective frame 3021 can be machined as a single unit, employing topology optimization and hollowing-out design for weight reduction while ensuring overall structural rigidity. The sides of the protective frame 3021 are also designed with screw mounting interfaces for unlocking and releasing devices between the launch vehicle and the spacecraft, enabling on-orbit unlocking and release of the satellite 300 and completing its orbital deployment.

[0063] Figure 6 The diagram shows four satellite thrusters 3022 mounted at the four corners of the protective frame 3021. In practical applications, a single propulsion module 302 can use four 1N (N represents Newton) main thrusters and three 0.25N lateral attitude control engines, with the four main thrusters facing the same direction and the three lateral attitude control engines mounted on three sides of the propulsion module 302. Combining two propulsion modules 302 results in the satellite 300 having a total of eight main thrusters and six attitude control engines, enabling flexible maneuvering and orbit changes in orbit, and improving the satellite 300's imaging and detection efficiency for key targets. This application utilizes a pre-machined, topology-optimized, hollowed-out protective frame 3021 to balance structural rigidity and lightweight design. The propulsion piping is integrated within the protective frame 3021, preventing damage from exposed piping and improving the operational reliability of the satellite propulsion system.

[0064] This application can produce the following beneficial effects: 1. The satellite structure proposed in this application changes the traditional customized design approach of "one type, one satellite" for micro-nano satellites. The satellite configuration of this application integrates and divides the various individual units within Satellite 300 according to their functions, creating physically independent modular products. When facing different mission requirements and design specifications, some modules can be replaced or upgraded to higher-performance modules of the same type without modifying other modules, reducing the satellite's development and design costs. Simultaneously, it gives Satellite 300 the characteristic of versatility in module replacement.

[0065] 2. The tank module 306 of this application can be combined with the propulsion module 302 using tank modules 3061 of different volumes (e.g., composed of fuel tanks 3063 of different volumes and different numbers of tank frames 3062 of the same type) according to mission requirements, thus alleviating the situation where a traditional satellite has a single propulsion system, which is inconvenient for replacement and upgrades. With other module designs remaining unchanged, the satellite 300 can carry more fuel, enabling it to achieve higher maneuverability requirements and orbital maintenance lifespan requirements.

[0066] 3. The tank module 306 of this application is equipped with a valve group switch, which allows for pre-filling and packaging of the completed tank module 3061 with fuel. After mass production, it can be inspected and stored as a shelf product, realizing the on-demand and ready-to-use operation of the propulsion system. Compared with traditional satellites, there is no need to carry out chemical propellant fuel filling at the launch site, shortening the satellite assembly and integration cycle and enabling rapid response launch of satellites in emergency situations.

[0067] 4. The integrated electronic module 305 and energy module 303 of this application are heat-generating modules during on-orbit flight, and the fuel in the propellant tank module 306 requires thermal insulation during on-orbit flight. This application achieves an integrated design of structural and thermal control coupling through the combined layout of modules. By surrounding and enclosing the heat-generating modules in the propellant tank module 306 that requires insulation, the fuel can be kept warm. Compared with the discrete design of traditional satellite structures that require independent heating and temperature control of the propellant tank fuel and additional heat dissipation for the heat-generating modules, this application achieves a closed-loop design of the thermal environment, reduces the demand for thermal control resources of the satellite platform, effectively utilizes the onboard heat-generating and heat-absorbing modules, and achieves a lightweight design for the satellite.

[0068] 5. The integrated electronic module 305 and energy module 303 of this application are designed with a unified envelope size, i.e., consistent external dimensions. The frame height of the storage tank module 306 at the center position can be expanded. For example, one or two storage tank modules 3061 can be set before expanding the frame height, and three or four or even more storage tank modules 3061 can be set after expanding the frame height. This allows for the expansion of a larger number of integrated electronic modules 305, energy modules 303, or other types of modules, enabling a significant increase in the performance indicators of the satellite platform, particularly in computing power and battery capacity.

[0069] The embodiments of this application also disclose a spacecraft (not shown in the figures), including a modular satellite 300 as described above. Exemplarily, the spacecraft of this application can be a space launch vehicle carrying the modular satellite 300, or an interplanetary spacecraft, etc., and the spacecraft can be flexibly configured with satellite payloads of different functions and performance.

[0070] While the foregoing disclosure has discussed various embodiments that are currently considered useful, it should be understood that such details are for illustrative purposes only, and this application is not limited to the disclosed embodiments. Rather, this application is intended to cover all modifications and equivalent combinations that conform to the spirit and scope of the embodiments of this application. For example, although the system components described above can be implemented by hardware devices, they can also be implemented solely by software solutions, such as installing the described system on existing servers or mobile devices.

[0071] Similarly, it should be noted that, in order to simplify the description of the present application and thus aid in the understanding of one or more embodiments, the foregoing description of the embodiments of the present application sometimes combines multiple features into a single embodiment, drawing, or description thereof. However, this disclosure method does not imply that the subject matter of the present application requires more features than those mentioned foregoing. In fact, the embodiments have fewer features than all the features of the single embodiments disclosed above.

[0072] In some embodiments, numbers describing the quantity of components and attributes are used. It should be understood that such numbers used to describe embodiments are sometimes modified by the terms "approximately," "approximately," or "generally." Unless otherwise stated, "approximately," "approximately," or "generally" indicates that the numbers are allowed to vary by ±20%. Accordingly, in some embodiments, the numerical parameters used in this application are approximate values, which may be changed depending on the characteristics required by individual embodiments. In some embodiments, numerical parameters should take into account specified significant digits and employ a general method of digit reservation. Although the numerical ranges and parameters used to confirm their breadth of range in some embodiments of this application are approximate values, in specific embodiments, such values ​​are set as precisely as feasible.

[0073] Although this application has been described with reference to specific embodiments, those skilled in the art should recognize that the above embodiments are only used to illustrate this application, and various equivalent changes or substitutions can be made without departing from the spirit of this application. Therefore, any changes or modifications to the above embodiments within the scope of the essential spirit of this application will fall within the scope of this application.

Claims

1. A modular satellite, characterized in that, include: The main structure includes a tank module and at least one power module, wherein the tank module includes at least one tank module; At least one platform module is detachably connected to the main structure; and At least one observation load is detachably connected to the main structure.

2. The modular satellite as described in claim 1, characterized in that, The main structure includes at least two power modules, which are respectively disposed at opposite ends of the tank module, and the tank module and the at least two power modules have their axial centers coincident.

3. The modular satellite as described in claim 1, characterized in that, The platform modules include one or any combination of the following: integrated electronic module, energy module, measurement and control attitude determination module, and windsurfing module.

4. The modular satellite as described in claim 3, characterized in that, A receiving groove is formed on one side of the integrated electronic module and / or one side of the energy module. The inner contour dimension of the receiving groove matches the outer contour dimension of the storage tank module, so that the integrated electronic module and / or the energy module can be spliced ​​and combined with the storage tank module.

5. The modular satellite as described in claim 4, characterized in that, The integrated electronic module and the energy module are respectively disposed on both sides of the storage tank module. The receiving slot of the integrated electronic module is in contact with the first side of the storage tank module, and the receiving slot of the energy module is in contact with the second side of the storage tank module. The integrated electronic module, the storage tank module and the energy module together constitute a combination with a rectangular cross-section.

6. The modular satellite as described in claim 5, characterized in that, The axial height of the integrated electronic module and the axial height of the energy module are consistent with the axial height of the tank module, so that the assembly can be sandwiched between the at least two power modules to form a sandwich structure.

7. The modular satellite as described in claim 3, characterized in that, The measurement and control attitude determination module is disposed on the outer end face of one of the power modules, and the outer envelope dimension of the cross-section of the measurement and control attitude determination module is consistent with the outer envelope dimension of the cross-section of the power module.

8. The modular satellite as described in claim 7, characterized in that, The solar panel module is located on the end face of the telemetry, control and attitude determination module away from the power module, and the solar panel module can be deployed or retracted to the side of the satellite.

9. The modular satellite as described in claim 8, characterized in that, The solar panel module includes: at least one first base plate, at least two second base plates, a deployment device, and a clamping and releasing device; wherein, the at least one first base plate is connected to the telemetry and attitude determination module, the at least two second base plates are connected to adjacent first base plates through the deployment device, and the clamping and releasing device can lock the second base plates to the side of the satellite.

10. The modular satellite as described in claim 1 or 2, characterized in that, The observation payload is set on the outer end face of one of the power modules.

11. The modular satellite as described in claim 1, characterized in that, The tank module includes a tank frame and a fuel tank, with the fuel tank disposed inside the tank frame.

12. The modular satellite as described in claim 11, characterized in that, The tank module also includes a tank valve group switch, which is connected to the fuel tank and can shut off the fuel added to the fuel tank.

13. The modular satellite as described in claim 1, characterized in that, Each power module includes: a protective frame, at least one satellite thruster, and a propulsion pipeline, wherein the at least one satellite thruster is disposed outside the protective frame, and the propulsion pipeline is disposed inside the protective frame.

14. A spacecraft, characterized in that, Including modular satellites as described in any one of claims 1-13.

Images