Segmented spacecraft and ultra-large antenna on-orbit assembly method

Abstract

The invention discloses a split type spacecraft and an ultra-large antenna on-orbit assembling method.The split type spacecraft is composed of at least two main force bearing frames, a load mounting assembly and a pressing and unlocking assembly, the design of a tenon-and-mortise connection structure and a hollow supporting column is adopted, longitudinal locking-separation and transverse pressing-split separation are achieved, and the split type spacecraft can be assembled and disassembled conveniently. And the method is suitable for flexible modular transportation. The invention further discloses an ultra-large antenna on-orbit assembly method which comprises the steps that the carrier rocket transports the basic satellite and the split type spacecraft, the split type spacecraft transports the antenna module, and the assembly robot completes accurate assembly of the antenna module. The method effectively solves the problems that in the on-orbit assembling process of an existing ultra-large type modular antenna, a flexible antenna module conveying device is insufficient, and an assembling method is lacked, and has the advantages of being wide in application range, high in universality, high in expansibility and the like.

Description

Technical Field

[0001] The present application relates to the field of spacecraft technology, and in particular to an on-orbit assembly method of a petal-type spacecraft and a super-large antenna. Background Art

[0002] As a key component for obtaining information in spacecraft, space deployable antennas play a vital role in space communications, electronic reconnaissance, remote sensing and navigation. With the continuous advancement of major projects such as deep space exploration, manned space flight and space-based observation, my country's demand for large-caliber space deployable antennas is becoming increasingly urgent. Globally, 100-meter-class ultra-large space deployable antennas have become a frontier topic of concern and competition among major space powers, and on-orbit assembly technology is considered to be the most promising way to achieve this goal. Modular on-orbit assembly can not only effectively reduce manufacturing and launch costs, but also simplify the planning of assembly tasks, thus providing the possibility for the deployment of large-scale space antennas. Usually, large space payloads are sent into orbit by launch vehicles and then assembled on orbit. The transportation of large space payloads is the basis for on-orbit assembly. However, the current research on the transportation problem of large space payloads during on-orbit assembly is still insufficient and needs further exploration and improvement. Summary of the invention

[0003] The present application aims to solve at least one of the technical problems existing in the prior art. The present application provides a split-petal spacecraft and an on-orbit assembly method for a super-large antenna, which can make full use of the available space in the fairing of the launch vehicle, make the carrying efficiency higher, and solve the problem of the lack of on-orbit assembly methods for super-large antennas in the current art.

[0004] A split-petal spacecraft according to an embodiment of the first aspect of the present application includes:

[0005] At least two main load-bearing frames, each of the two lateral sides of the main load-bearing frames being provided with a first connecting member;

[0006] A load installation assembly, wherein the load installation assembly is arranged on the main load-bearing frame, and the load is installed on the main load-bearing frame through the load installation assembly;

[0007] A pressing and unlocking assembly, wherein the pressing and unlocking assembly is arranged on the main load-bearing frame;

[0008] Among them, the two main load-bearing frames are laterally connected through the first connecting member to form a petal-type spacecraft, and the two petal-type spacecraft are longitudinally unlockably connected through the clamping and unlocking assembly to form a petal-type spacecraft stack, and the clamping and unlocking assembly is used to control the longitudinal locking and separation of the petal-type spacecraft stack.

[0009] The split-petal spacecraft according to the embodiment of the present application has at least the following beneficial effects:

[0010] The split-petal spacecraft of the present application includes at least two main bearing frames, a load installation assembly and a clamping and unlocking assembly. The main bearing frame is used to carry the required load. One main bearing frame is a spacecraft petal. A first connecting member is provided on both lateral sides of the main bearing frame. The two spacecraft petals are laterally connected through the first connecting member to form a split-petal spacecraft. The load installation assembly is arranged on the main bearing frame, and is used to install the load on the main bearing frame so that each spacecraft petal can carry a load. Two adjacent split-petal spacecraft are stacked longitudinally to form a split-petal spacecraft stack. The main bearing frame is provided with a clamping and unlocking assembly. The two split-petal spacecraft are longitudinally unlockably connected through the clamping and unlocking assembly. The clamping and unlocking assembly is used to control the longitudinal locking and separation of the split-petal spacecraft stack. The load can be installed on the inner and outer sides of the main bearing frame through the load installation plate, making full use of the available space in the launch vehicle fairing, maximizing space utilization, and increasing the carrying efficiency. After the petal-type spacecraft stack reaches the preset position, the unlocking assembly is pressed to separate the petal-type spacecraft laterally from the petal-type spacecraft stack. As the two spacecraft petals in the petal-type spacecraft separate laterally, the longitudinal first connecting members are also naturally separated, so that the spacecraft can be separated naturally.

[0011] According to some embodiments of the present application, second connecting members are provided on both longitudinal sides of the main load-bearing frame, and the main load-bearing frame is also provided with a hollow pillar, and the compression and unlocking assembly is arranged in the hollow pillar. The compression and unlocking assembly and the second connecting member cooperate to control the longitudinal locking and separation of the petal-type spacecraft stack.

[0012] According to some embodiments of the present application, the main load-bearing frame includes at least three structural plates, and the main load-bearing frame is provided with a Type I main load-bearing frame and a Type II main load-bearing frame. The first side of the hollow pillar of the Type I main load-bearing frame is provided with one structural plate, and the second side of the hollow pillar of the Type I main load-bearing frame is provided with at least two structural plates, the first side of the hollow pillar of the Type II main load-bearing frame is provided with at least two structural plates, and the second side of the hollow pillar of the Type II main load-bearing frame is provided with one structural plate. The main load-bearing frames of a single split-type spacecraft are of the same type, and the main load-bearing frames of adjacent stacked split-type spacecraft are of different types. The hollow pillars of adjacent stacked split-type spacecraft are aligned and connected by the compression and unlocking components in the hollow pillars.

[0013] According to some embodiments of the present application, the first connecting member and the second connecting member are both configured as mortise and tenon connecting members, a first protrusion is provided on the first side surface of the main load-bearing frame, and a first recessed portion cooperating with the first protrusion is provided on the second side surface of the main load-bearing frame. The two main load-bearing frames are laterally connected through the cooperation of the first protrusion and the first recessed portion to form the petal-type spacecraft, a second protrusion is provided on one longitudinal side of the main load-bearing frame, and a second recessed portion cooperating with the second protrusion is provided on the other longitudinal side of the main load-bearing frame. The clamping and unlocking assembly, the second protrusion and the second recessed portion cooperate to control the longitudinal locking and separation of the two petal-type spacecraft.

[0014] According to some embodiments of the present application, the first protrusion is configured as a right-angle trapezoidal tooth, and the second protrusion is configured as an isosceles trapezoidal tooth.

[0015] According to some embodiments of the present application, the compression and unlocking assembly includes an unlockable component and a separation nut, the unlockable component is arranged on the central axis of the hollow pillar, the unlockable component is unlockably connected to the separation nut, and the two split-petal spacecraft are locked or separated by the cooperation of the unlockable component and the separation nut.

[0016] According to some embodiments of the present application, mounting holes are provided on both inner and outer sides of the main load-bearing frame, the load mounting assembly includes a load mounting plate and fasteners, the load mounting plate is fixed on the inner and outer sides of the main load-bearing frame by cooperation between the fasteners and the mounting holes, and the load is mounted on the load mounting plate.

[0017] According to the second aspect of the present application, the on-orbit assembly method of the very large antenna includes the petal-type spacecraft in the above embodiment, and includes the following steps:

[0018] S1. Obtain the data required for assembly and transportation through transportation analysis methods;

[0019] S2. assembling the split-petal spacecraft according to the data;

[0020] S3, launch of the first carrier rocket, transportation and assembly of basic satellites;

[0021] S4, the i-th launch vehicle is launched and the (i-1)-th split-type spacecraft stack is transported;

[0022] S5, the j-th layer of the (i-1)-th stack of split-petal spacecraft separates and splits;

[0023] S6. The kth antenna module of the jth layer of the (i-1)th stack is parked, unfolded, and assembled.

[0024] According to some embodiments of the present application, it further includes a vehicle carrying analysis method, and the vehicle carrying analysis method includes:

[0025] Denote the side length of the antenna module as l, the stowed height as h, and the folding ratio as a. Therefore, the stowed diameter is l / a;

[0026] Denote the number of layers of the antenna module as m and the number of antenna modules as n. The effective aperture of the antenna plane of the m-layer antenna module is D m , and the data required for assembly and transportation is obtained through the following formula:

[0027]

[0028] Among them,

[0029] (a) Number of antenna modules: When the required effective aperture of the antenna plane is D, D ∈ (D m-1 , D m , it indicates that the required number of layers of the antenna is m. Therefore, the required number of antenna modules n = 1 + 3m(m - 1);

[0030] (b) Number of layers of the segmented spacecraft stack: Denote the effective payload diameter of the launch vehicle as D′ and the effective payload height as H′; The segmented spacecraft is set as a regular c-sided polygon, denote the side length as l″, the maximum diameter as D″, and the height as H″. Limited by the envelope, D″ < D′, then the number of layers of the segmented spacecraft stack

[0031] (c) Number of launch vehicles: The number of units that can be carried on each side of the segmented spacecraft is b, then Denote the number of antenna modules that make up the basic satellite antenna as p. Therefore, the number of launch vehicles required

[0032] According to some embodiments of the present application, the specific steps of the steps S1 to S6 are as follows:

[0033] S1-1. According to the demand for the effective aperture of the antenna satellite plane, calculate the number of layers of the antenna module m, the number of antenna modules n, the number of layers of the segmented spacecraft stack e, and the number of launch vehicles f through the vehicle carrying analysis method;

[0034] S2-1. The spacecraft segments are combined into a segmented spacecraft through the first connecting member;

[0035] S2-2. The segmented spacecrafts are stacked into a segmented spacecraft stack through the compression unlocking assembly;

[0036] S2-3. The antenna module and other functional modules are installed and fixed on the segmented spacecraft stack through the payload mounting assembly;

[0037] S2-4, the split-petal spacecraft stack is packaged at the bottom of the fairing of the launch vehicle and is pressed and fixed by pressing and unlocking the assembly;

[0038] S3-1, the first launch vehicle is launched, and basic satellites are transported and assembled;

[0039] S4-1, the i-th carrier rocket is launched and the (i-1)-th split-type spacecraft stack is transported;

[0040] S4-2, the i-th carrier rocket enters the preset orbit, the pressing and unlocking assembly of the e-th layer of the (i-1)-th split-type spacecraft stack is unlocked, and the split-type spacecraft stack is separated from the fairing of the carrier rocket;

[0041] S5-1, the pressing and unlocking assembly of the j-th layer of the split-type spacecraft in the (i-1)-th split-type spacecraft stack is unlocked, and the j-th layer of the split-type spacecraft is separated from the split-type spacecraft stack;

[0042] S5-2. As the j-th layer of split-petal spacecraft separates laterally, the split-petal spacecraft naturally separates longitudinally, and the petals separate into two spacecraft petals;

[0043] S5-3, the two spacecraft petals fly to the parking position near the base satellite;

[0044] S6-1, the (i-1)th j-th layer k-th antenna module is transported to the preset parking point;

[0045] S6-2, the detachable extendable arm of the antenna module is unfolded and the wrapping belt is released to form an antenna unfolding module;

[0046] S6-3, the assembly robot flies to the parking point and grabs the antenna deployment module;

[0047] S6-4, the detachable extension arm is unlocked and separated from the antenna deployment module;

[0048] S6-5, the assembly robot grabs the antenna deployment module and flies to the assembly position;

[0049] S6-6, the assembly robot docks and assembles the antenna deployment module to the preset position of the basic satellite antenna;

[0050] First, execute steps S1, S2 and S3, from i=2:f, j=1:e, k=1:c, loop step S4 to step S6, and when the last loop of step S6 ends, all antenna modules are assembled and the super-large satellite antenna is assembled.

[0051] The on-orbit assembly method of a super-large antenna according to the second aspect of the present application has at least the following beneficial effects:

[0052] The on-orbit assembly method of the super-large antenna of the present application includes steps S1 to S6. S1. Calculate and obtain the data required for assembly and transportation through the transportation analysis method; S2. Assembly of the petal-type spacecraft; S3. Launch of the first carrier rocket, transportation and assembly of the basic satellite; S4. Launch of the i-th carrier rocket, transportation of the (i-1)-th petal-type spacecraft stack; S5. Separation of the petals of the j-th layer of the petal-type spacecraft in the (i-1)-th stack; S6. Parking, unfolding and assembly of the k-th antenna module in the j-th layer of the (i-1)-th stack. From i=2:f, j=1:e, k=1:c, loop step S4 to step S6, and when the last cycle of step S6 ends, all antenna modules are assembled to form a super-large satellite antenna. The on-orbit assembly method of the super-large antenna of the present application makes full use of the limited space in the fairing of the carrier rocket by using the petal-type spacecraft modular transportation flexible antenna module and other functional modules, thereby greatly improving the payload rate and reducing the launch cost. At the same time, the compression unlocking assembly controls the layer-by-layer unlocking mechanism of the petal-type spacecraft stack, ensuring that the antenna modules at each layer are separated smoothly and evenly, significantly reducing the risk of mechanical shock and stress concentration, and improving safety and assembly accuracy. The petal-type spacecraft of this application has good versatility and scalability, and can flexibly adjust the number of layers and quantity of antenna modules to meet the diversified assembly requirements of 100-meter-class ultra-large antenna systems, and has significant engineering application value with high efficiency, reliability and economy. BRIEF DESCRIPTION OF THE DRAWINGS

[0053] The present application is further described below with reference to the accompanying drawings and embodiments, wherein:

[0054] Figure 1 This is a schematic structural diagram of a main load-bearing frame of a split-petal spacecraft according to an embodiment of the present application;

[0055] Figure 2 This is a structural example diagram of a split-petal spacecraft according to an embodiment of the present application;

[0056] Figure 3 This is a schematic structural diagram of an I-type main load-bearing frame of a split-petal spacecraft according to an embodiment of the present application;

[0057] Figure 4 for Figure 3 A structural schematic diagram of another angle of an embodiment;

[0058] Figure 5 This is a schematic structural diagram of a type II main load-bearing frame of a split-petal spacecraft according to an embodiment of the present application;

[0059] Figure 6 for Figure 5 A structural schematic diagram of another angle of an embodiment;

[0060] Figure 7This is a schematic structural diagram of a split-petal spacecraft stack according to an embodiment of the present application;

[0061] Figure 8 This is a schematic structural diagram of a split-petal spacecraft stack according to another embodiment of the present application;

[0062] Fig. 9 A schematic diagram of the structure of a launch vehicle according to an embodiment of the present application;

[0063] Fig.10 This is a schematic diagram of the structure of a launch vehicle carrying a split-petal spacecraft stack according to an embodiment of the present application;

[0064] Fig.11 A schematic diagram of an antenna of a split-petal spacecraft after petal deployment according to an embodiment of the present application;

[0065] Fig.12 A schematic diagram of an antenna deployment module for a grasping robot according to an embodiment of the present application;

[0066] Fig.13 A schematic diagram of a super large antenna according to an embodiment of the present application;

[0067] Fig.14 This is a flow chart of an on-orbit assembly method for a very large antenna according to an embodiment of the present application.

[0068] Reference numerals:

[0069] Main bearing frame 1; I-type main bearing frame 11; II-type main bearing frame 12; first connecting member 13; second connecting member 14; hollow pillar 15; first side 151 of hollow pillar; second side 152 of hollow pillar; mounting hole 16; first side 17; second side 18; third side 19; fourth side 20;

[0070] Load mounting plate 21;

[0071] Antenna module 31; detachable extension arm 32; other functional modules 33; antenna deployment module 34; wrapping belt 35;

[0072] Launch vehicle 4; fairing 41; fairing base 42; base connector 43; basic satellite 44; assembly robot 45;

[0073] A petal-type spacecraft stack 5; a petal-type spacecraft 51; a spacecraft petal 52. DETAILED DESCRIPTION

[0074] The embodiments of the present application are described in detail below, and examples of the embodiments are shown in the accompanying drawings, wherein the same or similar reference numerals throughout represent the same or similar elements or elements having the same or similar functions. The embodiments described below with reference to the accompanying drawings are exemplary and are only used to explain the present application, and cannot be understood as limiting the present application.

[0075] In the description of the present application, it should be understood that if the terms "center", "middle", "longitudinal", "lateral", "length", "width", "thickness", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", "axial", "radial", "circumferential" and the like appear, the orientation or position relationship indicated is based on the orientation or position relationship shown in the drawings, which is only for the convenience of describing the present application and simplifying the description, and does not indicate or imply that the device or element referred to must have a preset orientation, be constructed and operated in a preset orientation, and therefore cannot be understood as a limitation on the present application. In addition, the features defined as "first" and "second" may explicitly or implicitly include one or more of the features. In the description of the present application, unless otherwise specified, "multiple" means two or more.

[0076] In the description of this application, it should be noted that, unless otherwise clearly specified and limited, the terms "installed", "connected", and "connected" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in this application can be understood according to specific circumstances.

[0077] Refer to the following Figures 1 to 14 The invention describes the on-orbit assembly method of the split-petal spacecraft and the super-large antenna in the embodiments of the present application.

[0078] according to Figure 1 , Figure 2 , Figure 8 , Fig. 9 and Fig.10As shown, a split-petal spacecraft 51 of an embodiment of the present application includes at least two main load-bearing frames 1, multiple load installation components and at least two clamping and unlocking components. A single main load-bearing frame 1 is a spacecraft petal 52. The main load-bearing frame 1 is used to load various functional modules. First connecting members 13 are provided on both lateral sides of the main load-bearing frame 1. The two main load-bearing frames 1 are laterally connected by the first connecting members 13. The two spacecraft petals 52 are laterally connected by the first connecting members 13 to form a split-petal spacecraft 51. The load installation component is provided on the main load-bearing frame 1, and the load is installed on the load installation component. The load installation component is used to install the load on the main load-bearing frame 1. The pressing and unlocking assembly is arranged on the main load-bearing frame 1, two adjacent petal-type spacecraft stacks 5 are stacked to form a petal-type spacecraft stack 5, two adjacent petal-type spacecraft 51 are unlockably connected via the pressing and unlocking assembly, the pressing and unlocking assembly controls the locking or separation of the two adjacent petal-type spacecraft 51, the two adjacent petal-type spacecraft 51 are longitudinally locked and connected via the pressing and unlocking assembly to form a petal-type spacecraft stack 5, and the pressing and unlocking assembly is used to control the longitudinal locking and separation of the petal-type spacecraft stack 5.

[0079] The two main load-bearing frames 1 are connected by the first connecting member 13, and the two spacecraft petals 52 are longitudinally connected by the first connecting member 13 to form a split-petal spacecraft 51. The load installation assembly is installed on the main load-bearing frame 1, and the load is installed on the load installation assembly. The split-petal spacecraft 51 is locked and installed on the base of the fairing 41 of the launch vehicle 4 by pressing and unlocking the assembly. After the launch vehicle 4 is launched and reaches the preset position, the pressing and unlocking assembly controls the split-petal spacecraft 51 to separate from the fairing 41. As the split-petal spacecraft 51 and the fairing 41 separate laterally, the first connecting member 13 is also naturally separated, and the split-petal spacecraft 51 separates into two spacecraft petals 52.

[0080] The payload can be installed on the inner and outer sides of the main bearing frame 1 through the payload installation assembly, which can make full use of the available space in the fairing 41 of the launch vehicle 4, maximize the space utilization, and increase the carrying efficiency. Different payload modules can be loaded onto the spacecraft petal 52 through the payload installation assembly, and the antenna module 31 can be installed on the outer side of the main bearing frame 1 through the payload installation assembly, which can meet the flexibility characteristics of antenna modules 31 of various shapes and sizes and antennas. Through the setting of the payload installation assembly, other payloads such as control modules, propulsion modules, power modules, integrated electronic modules, optical payload modules, data transmission modules or some other functional modules 33 can be installed on the inner side of the main bearing frame 1. In traditional spacecraft, the control module, propulsion module and optical payload module need to be installed on the outer side of the spacecraft due to their own structural characteristics and working environment. In this application, after the split-petal spacecraft 51 is split, both sides of the spacecraft petal 52 are on the outer side, so these functional modules can be installed and fixed on the inner side of the split-petal spacecraft 51 during transportation. While improving the space utilization, the present application also greatly improves the versatility.

[0081] The connection surfaces of multiple split-petal spacecraft 51 and the connection surface of the split-petal spacecraft 51 and the fairing base 42 are transverse separation surfaces, and the separation surfaces between the spacecraft petals 52 in a single split-petal spacecraft 51 are longitudinal separation surfaces.

[0082] In some embodiments, there are six main load-bearing frames 1, and every two main load-bearing frames 1 are laterally connected by a first connecting member 13, and every two spacecraft petals 52 are longitudinally connected by a second connecting member 14 to form a petal-type spacecraft 51, thereby forming three petal-type spacecraft 51. The three petal-type spacecraft 51 are locked and connected to each other by a pressing and unlocking assembly to form a petal-type spacecraft stack 5, wherein the petal-type spacecraft 51 in contact with the fairing base 42 is also locked and connected to the fairing base 42 by a pressing and unlocking assembly. Various functional modules are installed and fixed on the main load-bearing frame 1 through a load installation assembly. After the launch vehicle 4 carrying the petal-type spacecraft stack 5 is launched and reaches the preset position, the pressing and unlocking assembly controls the petal-type spacecraft stack 5 to separate from the fairing 41, and the petal-type spacecraft stack 5 is separated from the launch vehicle 4. The pressing and unlocking components of the first layer of split spacecraft 51 in the split spacecraft stack 5 are separated, and the first layer of split spacecraft 51 is separated from the split spacecraft stack 5. As the transverse separation surface separates, the first connecting piece 13 of the longitudinal separation surface of the first layer of split spacecraft 51 is naturally separated, and the first layer of split spacecraft 51 is split into two spacecraft petals 52. Subsequently, the pressing and unlocking components of the second layer of split spacecraft 51 in the split spacecraft stack 5 are separated, and the second layer of split spacecraft 51 is separated from the split spacecraft stack 5. As the transverse separation surface separates, the first connecting piece 13 of the longitudinal separation surface of the second layer of split spacecraft 51 is naturally separated, and the second layer of split spacecraft 51 is also split into two spacecraft petals 52. Finally, the third layer of split spacecraft 51 is also separated due to the transverse separation surface, and the first connecting piece 13 of the longitudinal separation surface is naturally separated, and the split spacecraft is split into two spacecraft petals 52.

[0083] In some other embodiments, a single split-petal spacecraft 51 is composed of three, four or more main load-bearing frames 1 , that is, a single split-petal spacecraft 51 is composed of two, three, four or more spacecraft petals 52 .

[0084] In some embodiments, each main load-bearing frame 1 includes a plurality of load installation components, and one or more functional modules can be installed on each load installation component.

[0085] In some embodiments, each main load-bearing frame 1 is provided with a pressing and unlocking assembly. In some other embodiments, each main load-bearing frame 1 is provided with a plurality of pressing and unlocking assemblies.

[0086] In some embodiments, there are four, eight, ten or more main load-bearing frames 1, that is, there are four, eight, ten or more spacecraft petals 52, every two spacecraft petals 52 are horizontally connected to form a petal-type spacecraft 51, and multiple petal-type spacecraft 51 are longitudinally stacked and locked to form a petal-type spacecraft stack 5.

[0087] In some embodiments, the first connector 13 is used to prevent the spacecraft petals 52 in a single split-petal spacecraft 51 from moving relative to each other longitudinally.

[0088] according to Figure 1 , Figure 2 , Figure 8 , Fig. 9 and Fig.10 As shown, in one embodiment of the present application, second connecting members 14 are provided on both longitudinal sides of the main load-bearing frame 1, and the second connecting members 14 are used to connect two adjacent split-type spacecraft 51. The main load-bearing frame 1 is also provided with hollow pillars 15, and the hollow pillars 15 of each split-type spacecraft 51 in the split-type spacecraft stack 5 are aligned and connected, and the hollow pillars 15 are used to support the weight of all the split-type spacecraft 51 stacked above. The compression and unlocking assembly is arranged in the hollow pillars 15, and the compression and unlocking assembly is arranged in the hollow pillars 15 to better save space and make full use of the effective space in the fairing 41. The compression and unlocking assembly cooperates with the second connecting member 14 to control the lateral locking and separation of the split-type spacecraft stack 5, and the compression and unlocking assembly cooperates with the second connecting member 14 to better lock, connect and fix two adjacent lateral spacecraft stacks.

[0089] The two main load-bearing frames 1 are connected by the first connecting member 13, and the two spacecraft petals 52 are horizontally connected by the first connecting member 13 to form a petal-type spacecraft 51. According to the position of the hollow pillar 15 of each petal-type spacecraft 51, the hollow pillars 15 of two adjacent petal-type spacecraft 51 are aligned and then stacked and connected longitudinally to form a petal-type spacecraft stack 5. The two adjacent petal-type spacecraft 51 are longitudinally locked by the cooperation of the compression and unlocking components and the second connecting member 14, so as to form a petal-type spacecraft stack 5. When the petal-type spacecraft stack 5 reaches the preset position, the petal-type spacecraft 51 of the first layer to the bottom layer are separated in turn, the compression and unlocking components of the first layer of petal-type spacecraft 51 are unlocked, and the second connecting member 14 is also naturally separated, and the first layer of petal-type spacecraft 51 is separated from the second layer of petal-type spacecraft 51. As the first layer of split-petal spacecraft 51 is laterally separated from the second layer of split-petal spacecraft 51, the first connecting member 13 of the first layer of split-petal spacecraft 51 is also naturally separated, and the first layer of split-petal spacecraft 51 is split and separated to form two spacecraft petals 52. Subsequently, the second layer of split-petal spacecraft 51 to the bottom layer of split-petal spacecraft 51 are also separated in sequence. The split-petal spacecraft stack 5 can be composed of a plurality of split-petal spacecraft stacks 5 stacked and connected.

[0090] In some embodiments, the hollow pillar 15 is made of ultra-high strength material, so that it can better support all the split-type spacecraft 51 above, making the split-type spacecraft stack 5 more stable and safer.

[0091] In some embodiments, each main load-bearing frame 1 is provided with a plurality of hollow pillars 15, and a compression unlocking assembly is provided in each of the plurality of hollow pillars 15, which can strengthen the lateral locking connection between adjacent petal-type spacecrafts 51 and make the connection more stable. The provision of a plurality of hollow pillars 15 can also strengthen the supporting strength of the petal-type spacecraft 51 itself, better support the weight of the upper petal-type spacecraft 51, and be more stable.

[0092] In some embodiments, the second connecting member 14 is used to prevent two adjacent split-type spacecraft 51 from relative lateral movement, and / or to prevent the split-type spacecraft 51 and the fairing base 42 from relative lateral movement.

[0093] according to Figure 3 , Figure 4 , Figure 5 , Figure 6 , Figure 7 and Figure 8 As shown, in one embodiment of the present application, the main load-bearing frame 1 includes at least three structural plates, and the structural plates are used to bear the weight of the petal-type spacecraft 51 itself and its load. The two structural plates are connected at a certain angle, and two or more main load-bearing frames 1 are connected and closed. In the aerospace field, weight reduction is one of the key goals of aviation design. The structural plate is a hollow design and is provided with multiple cross-type trusses, which can effectively reduce the use of materials, improve the rigidity and strength while also reducing the weight, and can also improve the air flow in the petal-type spacecraft stack 5, improve the heat dissipation effect, improve the structural performance, and ensure the stable and safe operation of the spacecraft.

[0094] The main bearing frame 1 is provided with a type I main bearing frame 11 and a type II main bearing frame 12, which are divided into two types according to the position of the hollow pillar 15. The number of structural plates on both sides of the hollow pillar 15 of the type I main bearing frame 11 is opposite to the number of structural plates on both sides of the hollow pillar 15 of the type II main bearing frame 12. The first side 151 of the hollow pillar of the type I main bearing frame 11 is provided with a structural plate, and the second side 152 of the hollow pillar of the type I main bearing frame 11 is provided with at least two structural plates; the first side 151 of the hollow pillar of the type II main bearing frame 12 is provided with at least two structural plates, and the second side 152 of the hollow pillar of the type II main bearing frame 12 is provided with a structural plate. The main bearing frames 1 in a single split-flap spacecraft 51 are of the same type, that is, a single split-flap spacecraft 51 is composed of two or more type I main bearing frames 11 connected, or a single split-flap spacecraft 51 is composed of two or more type II main bearing frames 12 connected. In the split-flap spacecraft stack 5, the main load-bearing frames 1 of adjacent stacked split-flap spacecraft 51 are of different types. Taking a three-layer split-flap spacecraft stack 5 as an example, the first layer of split-flap spacecraft 51 is composed of type I main load-bearing frames 11, the second layer of split-flap spacecraft 51 is composed of type II main load-bearing frames 12, and the third layer of split-flap spacecraft 51 is composed of type I main load-bearing frames 11. Similarly, the types of the main load-bearing frames 1 of each layer of split-flap spacecraft 51 in the split-flap spacecraft stack 5 can be swapped at the same time. The multi-layer split-flap spacecraft stack 5 is arranged in the same way. The hollow pillars 15 of adjacent stacked split-flap spacecraft 51 are aligned and connected, and the main load-bearing frames 1 of adjacent stacked split-flap spacecraft 51 are of different types, so the longitudinal separation surfaces of adjacent split-flap spacecraft 51 are staggered with each other. The staggered layout can restrain the longitudinal separation surfaces from each other, making it less likely to misalign or slip during launch and transportation, thereby improving the stability of the overall structure and avoiding structural failure caused by excessive local force. When the petal-type spacecraft stack 5 reaches the preset position and the petal-type spacecraft 51 is unlocked layer by layer, the staggered longitudinal separation surfaces can gradually unlock each layer of the petal-type spacecraft 51, rather than instantly detaching as a whole, thus avoiding instant disintegration and damage of the petal-type spacecraft stack 5 due to sudden impact. The staggered arrangement of the longitudinal separation surfaces can simultaneously unlock the petal-type spacecraft 51 when the transverse separation surface separates the petal-type spacecraft 51, and the two spacecraft petals 52 can be evenly separated, thereby improving the controllability of the separation process.

[0095] In some embodiments, the main load-bearing frame 1 includes three structural plates, and the structural plates are connected at a 60-degree angle. A single split-type spacecraft stack 5 includes three layers of split-type spacecraft 51, four I-type main load-bearing frames 11 and two II-type main load-bearing frames 12. The first layer of split-type spacecraft 51 is composed of two I-type main load-bearing frames 11 connected transversely by a first connecting member 13, the second layer of split-type spacecraft 51 is composed of two II-type main load-bearing frames 12 connected transversely by a first connecting member 13, and the third layer of split-type spacecraft 51 is composed of two I-type main load-bearing frames 11 connected transversely by a first connecting member 13. The hollow pillars 15 of the first layer of split-type spacecraft 51, the second layer of split-type spacecraft 51 and the third layer of split-type spacecraft 51 are aligned and stacked longitudinally in sequence to form a split-type spacecraft stack 5, and the compression and unlocking components in the hollow pillars 15 lock the adjacent split-type spacecraft 51 longitudinally, and the second connecting member 14 assists in connecting the adjacent split-type spacecraft 51.

[0096] In some embodiments, the structural plates are connected by welding. In some other embodiments, the structural plates in the main load-bearing frame 1 are connected in an integrated manner.

[0097] according to Figure 3 , Figure 4 , Figure 5 , Figure 6 , Figure 7 and Figure 8As shown, in one embodiment of the present application, the first connecting member 13 of the main load-bearing frame 1 is set as a first mortise and tenon connecting member, and the second connecting member 14 is set as a second mortise and tenon connecting member, the first side surface 17 of the main load-bearing frame 1 is provided with a first protrusion, and the second side surface 18 of the main load-bearing frame 1 is provided with a first recessed portion, the first protrusion and the first recessed portion are detachably connected, and at least two main load-bearing frames 1 are transversely connected to form a petal-type spacecraft 51 through the cooperation of the first protrusion and the first recessed portion; the third side surface 19 of the main load-bearing frame 1 is provided with a second protrusion, and the fourth side surface 20 of the main load-bearing frame 1 is provided with a second recessed portion, the second protrusion and the second recessed portion are detachably connected, and two adjacent petal-type spacecraft 51 are longitudinally connected through the second protrusion, the second recessed portion and the clamping and unlocking assembly to form a petal-type spacecraft stack 5, and the clamping and unlocking assembly, the second protrusion and the second recessed portion cooperate with each other to control the longitudinal locking and separation of the two adjacent petal-type spacecraft 51. The first connector 13 is configured as a mortise and tenon connector, which can prevent the two main load-bearing frames 1 from longitudinally offsetting when the two main load-bearing frames 1 are laterally connected; and the second connector 14 is configured as a mortise and tenon connector and the longitudinal separation surfaces of adjacent petal spacecrafts are staggered, which can prevent the two main load-bearing frames 1 in the petal spacecraft 51 from transversely offsetting when the two petal spacecrafts 51 are longitudinally locked and connected, and then the two adjacent petal spacecrafts 51 are compressed and locked by the compression and unlocking assembly, so as to achieve the overall structure of the petal spacecraft stack 5 being fastened and stable. The first connector 13 and the second connector 14 are both configured as mortise and tenon connectors, which do not rely on metal bolts, etc., reduce additional weight, and help reduce the transportation cost of the petal spacecraft stack 5. The configuration of multiple mortise and tenon structures can also disperse stress, and while reducing weight, ensure the strength of the overall structure of the petal spacecraft stack 5, and can withstand certain vibrations during transportation.

[0098] When three layers of split-petal spacecraft 51 are stacked to form a split-petal spacecraft stack 5, two spacecraft petals 52 in each layer of split-petal spacecraft 51 are transversely connected by a first mortise and tenon joint to form a split-petal spacecraft 51, and the first mortise and tenon joint is used to prevent the two split-petal spacecraft 51 in a single split-petal spacecraft 51 from having a relative longitudinal offset. The third layer of split-petal spacecraft 51 is locked and connected with the fairing base 42 of the carrier rocket 4 by a pressing and unlocking assembly. The second recessed portion of the second layer of split-petal spacecraft 51 and the second raised portion of the third layer of split-petal spacecraft 51 are connected by mortise and tenon joints to prevent the second layer of split-petal spacecraft 51 and the third layer of split-petal spacecraft 51 from having a relative lateral offset. At the same time, the second layer of split-petal spacecraft 51 is longitudinally locked and connected with the third layer of split-petal spacecraft 51 by a pressing and unlocking assembly. The arrangement of the pressing and unlocking assembly, the first mortise and tenon joint, and the second mortise and tenon joint can tighten the structure of the entire split-petal spacecraft stack 5 while reducing weight. The second concave portion of the first layer of split spacecraft 51 and the second convex portion of the second layer of split spacecraft 51 are connected by mortise and tenon joints, and the second layer of split spacecraft 51 is longitudinally locked and connected by the compression and unlocking assembly of the first layer of split spacecraft 51, so that the split spacecraft stack 5 with three layers of split spacecraft 51 is completed. The split spacecraft stack 5 with multiple layers of split spacecraft 51 is constructed in the same way.

[0099] In some embodiments, a plurality of first mortise and tenon connectors and a plurality of second mortise and tenon connectors are provided for the main load-bearing frame 1 . The provision of a plurality of mortise and tenon connectors can make the overall structure of the petal-type spacecraft stack 5 more stable.

[0100] according to Figures 1 to 10As shown, in one embodiment of the present application, the second protrusion is set as a right-angled trapezoidal tooth, the second recessed portion is a groove matched with the right-angled trapezoidal tooth, the first protrusion is set as an isosceles trapezoidal tooth, and the first recessed portion is a groove matched with the isosceles trapezoidal tooth. The first protrusion is set as an isosceles trapezoidal tooth so that the two spacecraft petals 52 can be better and more smoothly combined and separated when they are horizontally connected or unlocked, reducing the difficulty of assembly. Since the isosceles trapezoidal teeth are symmetrical on both sides, the two spacecraft petals 52 can be evenly stressed when they are horizontally connected, reducing the imbalance caused by installation deviation. The longitudinal separation surface is connected by isosceles trapezoidal teeth, and because the adjacent longitudinal separation surfaces are staggered, the longitudinal separation surface of the split-petal spacecraft 51 is pressed and locked, and separated and relaxed as the right-angled trapezoidal teeth of the horizontal separation surface and the pressing and unlocking components are connected. As the split-petal spacecraft 51 separates on the horizontal separation surface, the isosceles trapezoidal teeth mortise and tenon joints of the longitudinal separation surface will also naturally loosen and separate, so that the two spacecraft petals 52 are naturally separated. Through the design of the mortise and tenon structure, there is no need to design a complex separation control mechanism separately, and the structure is compact, thereby reducing the overall complexity and manufacturing cost, reducing the dependence on external drive or control systems, and being less susceptible to external interference or control errors, improving the reliability and simplicity of the separation operation, and improving the success rate and safety of on-orbit separation. The second protrusion is set as a right-angled trapezoidal tooth, which can more effectively transmit and disperse the load in the vertical direction when the adjacent petal-type spacecraft stack 5 is connected, ensuring that in the stacked state, the connection of the lateral separation surface has a high compression and separation resistance, and has a strong clamping ability when subjected to force, preventing displacement and dislocation caused by vibration or impact during transportation. The right-angled trapezoidal teeth can provide rigid support to a large extent, improving the stability and safety of the overall structure.

[0101] In some embodiments, the fairing base 42 of the launch vehicle 4 is also provided with a base connector 43, which is a right-angled trapezoidal tooth and is mortise and tenon connected to the second recessed portion of the underlying split-flap spacecraft 51 to prevent relative lateral displacement between the underlying split-flap spacecraft 51 and the fairing base 42.

[0102] according to Figures 1 to 10As shown, in one embodiment of the present application, the compression unlocking assembly includes an unlockable component and a separation nut, the separation nut is arranged at the top and bottom of the split-petal spacecraft stack 5, the hollow pillar 15 is a hollow cylindrical shape, the unlockable component is arranged on the central axis of the hollow pillar 15, the unlockable component is positioned along the central axis of the hollow pillar 15 of the main load-bearing frame 1, the unlockable component and the separation nut are unlockably connected, and the unlockable component and the separation nut cooperate to control the longitudinal locking and separation of adjacent split-petal spacecraft 51. Through the cooperation of the unlockable component and the separation nut, a stable and tight mechanical connection can be formed between adjacent split-petal spacecraft 51, ensuring that there will be no accidental separation due to vibration or impact during transportation and on-orbit operation, and at the same time, the connection can be quickly and safely released during separation. The unlockable component is arranged on the central axis of the hollow pillar 15, which can make the hollow pillars 15 of adjacent split-petal spacecraft 51 stably aligned and connected, ensuring that a good connection can be maintained during locking, and enhancing the stability of the overall structure.

[0103] In some embodiments, the unlockable component can be configured as a detachable tension lock or an unlockable pull rod. The detachable tension lock or the unlockable pull rod is unlockably connected to the separation nut, and the switching between the locked state and the separated state is realized by adopting a simple mechanical unlocking cooperation, without requiring too much complicated driving mechanism, so that the petal-type spacecraft stack 5 can be designed concisely, reduce the weight of the overall structure, and provide effective protection for high load requirements.

[0104] according to Figures 1 to 10 As shown, in one embodiment of the present application, mounting holes 16 are provided on both sides of the main load-bearing frame 1, and the mounting holes 16 are evenly distributed around the structural plate. The load mounting assembly includes a load mounting plate 21 and fasteners. The load mounting plate 21 is fixedly mounted on both sides of the main load-bearing frame 1 through the fasteners and the mounting holes 16. The load is mounted on the load mounting plate 21. The load is mounted on the main load-bearing frame 1 through the load mounting plate 21, so as to achieve a stable connection between the load and the spacecraft petal 52. This not only improves the overall structural rigidity of the system, but also ensures that the load will not be displaced or loosened due to vibration or impact during the transportation and on-orbit assembly process, thereby improving safety. By fixing the load mounting plate 21 in a manner that the fasteners and the mounting holes 16 are matched, the assembly process can be simplified. Through the design of the load mounting plate 21, a universal platform can be provided for fixing the load on the spacecraft petal 52, which can be matched with functional modules of various types, sizes and weights, and the configuration can be flexibly adjusted according to mission requirements, which greatly improves the versatility and assembly efficiency of the petal-type spacecraft stack 5.

[0105] according to Figures 6 to 14As shown in the figure, the on-orbit assembly method of the ultra-large antenna in the second embodiment of the present application. The on-orbit assembly system includes a launch vehicle 4, a basic satellite 44, a split spacecraft 51, and an antenna module 31. The launch vehicle 4 is used to carry the split spacecraft 51 and the basic satellite 44. The on-orbit assembly method of the ultra-large antenna includes the following launch analysis methods:

[0106] Denote the side length of the antenna module 31 as l, the stowed height as h, and the deployment ratio as a. Therefore, the stowed diameter is l / a;

[0107] Denote the number of layers of the antenna module 31 as m, the number of antenna modules 31 as n, and the effective aperture of the antenna plane of the m-layer antenna module 31 as D m ,

[0108] where

[0109]

[0110] (a) Number of antenna modules 31: When the required effective aperture of the antenna plane is D, D ∈ (D m-1 , D m , it indicates that the required number of layers of the antenna is m. Therefore, the required number of antenna modules 31, n = 1 + 3m(m - 1);

[0111] (b) Number of layers of the split spacecraft stack 5: Denote the effective payload diameter of the launch vehicle 4 as D', and the effective payload height as H'. The split spacecraft 51 is set as a regular c-sided polygon, with the side length denoted as l'', the maximum diameter as D'', and the height as H''. Limited by the envelope, D'' < D', then the number of layers of the split spacecraft stack 5

[0112] (c) Number of launch vehicles 4: The number of units that can be carried on each side of the split spacecraft 51 is b, then Denote the number of antenna modules 31 that make up the antenna of the basic satellite 44 as p. Therefore, the number of launch vehicles 4 required

[0113] If a one-hundred-meter antenna satellite is required, that is, the required effective diameter of the antenna plane D ≥ 100 m. Set the side length of the antenna module 31, l = 15 m; the stowed height h = 4.5 m; the deployment ratio a = 40; the stowed diameter l / a = 0.375 m.

[0114] The effective aperture of the antenna plane of the 2-layer antenna module 31 (i.e., m = 2), D2 = 60 m, and the effective aperture of the antenna plane of the 3-layer antenna module 31 (i.e., m = 3), D3 ≈ 108 m. D ∈ (D2, D3]. Therefore, the required number of layers of the antenna is m = 3, and the required number of antenna modules 31 is n = 19.

[0115] The payload diameter of the launch vehicle 4 is set to D′=7m, and the payload height is recorded as H′=20m; the petal-type spacecraft 51 is set to be a hexagonal prism, that is, c=6, the side length l″=1.5m, and the height H″=6m, so the stacking number of petal-type spacecraft stack 5 is e=3, and one petal-type spacecraft stack 5 is composed of three petal-type spacecraft stacks 5.

[0116] The number of antennas that can be carried on each side of the split-petal spacecraft 51 is set to b=1, and the number of antenna modules 31 that constitute the antenna of the basic satellite 44 is p=1, so the number of launch vehicles 4 required is f=2.

[0117] Therefore, by launching the above-mentioned carrier rocket 4 at least twice, transporting 19 of the above-mentioned antenna modules 31 and 1 basic satellite 44, a 100-meter antenna satellite with a diameter of about 108m can be assembled.

[0118] according to Figures 6 to 14 As shown, in one embodiment of the present application, the super-large on-orbit assembly method includes the following steps:

[0119] S1. Obtain the data required for assembly and transportation through transportation analysis methods;

[0120] S2. assembling the split-petal spacecraft according to the data;

[0121] S3, the first carrier rocket is launched, and basic satellites are transported and assembled;

[0122] S4, the i-th launch vehicle is launched and the (i-1)-th split-type spacecraft stack is transported;

[0123] S5, the j-th layer of the (i-1)-th stack of split-petal spacecraft separates and splits;

[0124] S6. The kth antenna module of the jth layer of the (i-1)th stack is parked, unfolded, and assembled.

[0125] according to Figures 6 to 14As shown, in one embodiment of the present application, the rail assembly system also includes a detachable extension arm 32 and an assembly robot 45. The basic satellite 44 is a conventional satellite, including a satellite shell, a power system, a propulsion system, a control system, etc. The basic satellite 44 carries a common antenna composed of a small number of antenna modules 31, an antenna extension arm and an assembly robot 45. The basic satellite antenna is stored by a wrapping belt. The split-type spacecraft 51 is used to carry a large number of antenna modules 31. The antenna modules 31 are wrapped and stored by a wrapping belt 35 and are fastened to the split-type spacecraft 51. The antenna modules 31 are structural unit modules of super-large antennas. The antenna module 31 is connected to the split-type spacecraft 51 through a detachable extension arm 32. When the detachable extension arm 32 is in a locked state, the antenna module 31 is firmly fixed on the load mounting plate 21 to ensure the stability of transportation and deployment; when the antenna assembly is required, the detachable extension arm 32 is unlocked to separate the antenna module 31 from the split-type spacecraft 51, and the assembly robot 45 accurately grasps and installs it to the target position.

[0126] The specific steps of steps S1 to S5 are:

[0127] S1-1. According to the effective aperture requirement of the antenna satellite plane, the number m of antenna modules 31, the number n of antenna modules 31, the number e of layers of the petal-type spacecraft stack 5, and the number f of launch vehicles 4 are calculated by means of a carrier analysis method;

[0128] S2-1, the spacecraft petals 52 are connected transversely through the first connecting member 13 to form a split-petal spacecraft 51;

[0129] S2-2, two adjacent split-type spacecraft 51 are stacked by pressing and unlocking components to form a split-type spacecraft stack 5;

[0130] S2-3, the wrapping belt 35 stores the antenna module 31, the antenna module 31 is installed on the payload installation assembly through the separate extension arm 32, and the antenna module 31 and other functional modules 33 are installed and fixed on the petal-type spacecraft stack 5 through the payload installation assembly;

[0131] S2-4, the split-petal spacecraft stack 5 is encapsulated at the bottom of the fairing 41 of the launch vehicle 4, and is pressed and fixed by pressing and unlocking the assembly;

[0132] S3-1, the first carrier rocket 4 is launched, the basic satellite 44 is transported into orbit, the band of the basic satellite antenna is unlocked and released, the basic satellite antenna is unfolded, the antenna extension arm on the basic satellite 44 is unfolded and locked, and the p antenna modules 31 at the end of the antenna extension arm are simultaneously unfolded to form an antenna of a common caliber;

[0133] S4-1, the i-th carrier rocket 4 is launched, and the (i-1)-th split-type spacecraft stack 5 is transported;

[0134] S4-2, the i-th carrier rocket 4 enters the preset orbit, the pressing and unlocking assembly of the e-th layer of the (i-1)-th split-type spacecraft stack 5 is unlocked, so that the e-th layer of the lateral separation surface is separated, and the split-type spacecraft stack 5 is separated from the fairing 41 of the carrier rocket 4;

[0135] S5-1, the pressing and unlocking assembly of the j-th layer of the split-petal spacecraft 51 of the (i-1)-th split-petal spacecraft stack 5 is unlocked, the unlockable component is unlocked and separated from the separation nut, and the j-th layer of the split-petal spacecraft 51 is separated from the split-petal spacecraft stack 5;

[0136] S5-2, as the j-th layer of the split-petal spacecraft 51 lateral separation surface separates, the split-petal spacecraft 51 longitudinal separation surface separates naturally, and the split-petal spacecraft 51 separates into two spacecraft petals 52;

[0137] S5-3, the two spacecraft petals 52 fly to a parking position near the base satellite 44;

[0138] S6-1, the (i-1)th j-th layer k-th antenna module 31 is transported to a preset parking point;

[0139] S6-2, the wrapping band 35 of the antenna module 31 is unlocked and released, the antenna module 31 is unfolded, and the detachable extension arm of the antenna module 31 is unfolded to form an antenna unfolding module 34;

[0140] S6-3, the assembly robot 45 flies to the parking point and grabs the antenna deployment module 34;

[0141] S6-4, the detachable extension arm is unlocked and separated from the antenna deployment module 34;

[0142] S6-5, the assembly robot 45 grabs the antenna deployment module 34 and flies to the assembly position;

[0143] S6-6, the assembly robot 45 docks and assembles the antenna deployment module 34 to the preset position of the antenna of the base satellite 44;

[0144] In the on-orbit assembly method of the ultra-large antenna, steps S1, S2 and S3 are first executed, and steps S4 to S6 are looped from i=2:f, j=1:e, k=1:c. When the last loop of step S6 ends, all antenna modules 31 are assembled and the ultra-large satellite antenna is assembled.

[0145] If you need to assemble a 100-meter antenna satellite, that is, the effective diameter of the antenna plane D ≥ 100m, set the side length of the antenna module 31 to l = 15m; the folded height h = 4.5m; the folding ratio a = 40; the folded diameter l / a = 0.375m. According to the carrier analysis method, it is calculated that when the number of layers of the antenna module 31 is m = 3, D3 ≈ 108m, which meets the requirements of a 100-meter antenna satellite. Through n = 1 + 3m (m-1), the required number of antenna modules 31 is n = 19. The payload diameter of the launch vehicle 4 is D′ = 7m, and the payload height is recorded as H′ = 20m; the petal-type spacecraft 51 is set to a hexagonal prism, that is, c = 6, the side length l″ = 1.5m, and the height H″ = 6m. Through That is, the stacking number of the petal-type spacecraft stack 5 is e=3, and one petal-type spacecraft stack 5 needs to be composed of three petal-type spacecraft stacks 5. The number of antenna satellites that can be carried on each side of the petal-type spacecraft 51 is set to b=1, and the number of antenna modules 31 that constitute the basic satellite 44 antenna is p=1. That is, the number of launch vehicles 4 required is f=2, one launch vehicle 4 carries the basic satellite 44 , and the other launch vehicle 4 carries the segmented spacecraft stack 5 .

[0146] The three-layer split-flap spacecraft 51 requires four Type I main load-bearing frames 11 and two Type II main load-bearing frames 12 (or two Type I main load-bearing frames 11 and four Type II main load-bearing frames 12). The two Type I main load-bearing frames 11 are transversely connected by isosceles trapezoidal tooth mortise and tenon connectors to form the third-layer split-flap spacecraft 51, and the two Type II main load-bearing frames 12 are transversely connected by isosceles trapezoidal tooth mortise and tenon connectors to form the second-layer split-flap spacecraft 51. The hollow pillars 15 of the second-layer split-flap spacecraft 51 are aligned and connected with the hollow pillars 15 of the third-layer split-flap spacecraft 51. The second recessed portion of the second-layer split-flap spacecraft 51 and the right-angled trapezoidal tooth mortise and tenon connector of the third-layer split-flap spacecraft 51 are longitudinally mortise-tenon connected, and the compression and unlocking assembly of the second-layer split-flap spacecraft 51 longitudinally locks and compresses the second-layer split-flap spacecraft 51 and the third-layer split-flap spacecraft 51. The two I-type main bearing frames 11 are transversely connected by isosceles trapezoidal tooth mortise and tenon joints to form the first layer of split-flap spacecraft 51. The hollow pillars 15 of the first layer of split-flap spacecraft 51 are aligned and connected with the hollow pillars 15 of the second layer of split-flap spacecraft 51. The second recessed portion of the first layer of split-flap spacecraft 51 and the right-angle trapezoidal tooth mortise and tenon joints of the second layer of split-flap spacecraft 51 are longitudinally mortise and tenon connected. The first layer of split-flap spacecraft's pressing and unlocking assembly performs longitudinal locking and pressing connection on the first layer of split-flap spacecraft 51 and the second layer of split-flap spacecraft 51, thereby a split-flap spacecraft stack 5 composed of three layers of split-flap spacecraft 51 is assembled. The load mounting plate 21 is mounted on the inner and outer sides of each main bearing frame 1 by fasteners and mounting holes 16. The antenna module 31 is mounted on the load mounting plate 21 on the outer side of the main bearing frame 1, and other functional modules 33 are mounted on the load mounting plate 21 on the inner side of the main bearing frame 1. The fairing base 42 of the launch vehicle 4 is provided with a base connector 43, and the base connector 43 is connected to the second recessed portion of the third-layer split-type spacecraft 51 by mortise and tenon joints. The compression and unlocking assembly of the third-layer split-type spacecraft 51 compresses and locks the third-layer split-type spacecraft 51 and the fairing base 42 longitudinally, so that the split-type spacecraft stack 5 is encapsulated on the fairing base 42 of the launch vehicle 4.

[0147] The first carrier rocket 4 is launched, transporting the basic satellite 44 into the on-orbit assembly orbit of the super-large antenna, the strap of the basic satellite antenna is unlocked, the basic satellite antenna is unfolded, the antenna extension arm of the basic satellite 44 is unfolded and locked, and an antenna module 31 located at the end of the antenna extension arm is unfolded at the same time to form an antenna of a normal caliber. The second carrier rocket 4 is launched, transporting the split-type spacecraft stack 5, and the second carrier rocket 4 enters the preset orbit. The unlockable components of the third layer of split-type spacecraft 51 of the split-type spacecraft stack 5 are unlocked from the separation nut, the third layer of split-type spacecraft 51 is separated from the third layer of the lateral separation surface, and the split-type spacecraft stack 5 is separated from the fairing 41 of the carrier rocket 4. The compression unlocking assembly of the first layer of split-type spacecraft 51 is unlocked, and the first layer of split-type spacecraft 51 is separated from the split-type spacecraft stack 5. As the transverse separation surface of the first-layer split-type spacecraft 51 separates, the first mortise and tenon joint of the longitudinal separation surface of the split-type spacecraft 51 naturally separates, and the split-type spacecraft 51 separates into two spacecraft petals 52. The two spacecraft petals 52 fly to the parking position near the basic satellite 44. The first antenna module 31 of the first layer is transported to the preset parking point, the wrapping belt 35 of the antenna module 31 is unlocked and released, the antenna module 31 is unfolded, and the detachable extension arm of the antenna module 31 is unfolded to form an antenna deployment module 34. The assembly robot 45 flies to the parking point, and the assembly robot 45 grabs the antenna deployment module 34. The detachable extension arm is unlocked and separated from the antenna deployment module 34, and the antenna deployment module 34 is separated from the spacecraft petal 52. The assembly robot 45 grabs the antenna deployment module 34 and flies to the preset assembly position, docks the antenna deployment module 34, and assembles it to the preset position of the antenna of the basic satellite 44. The second to sixth antenna modules 31 of the first layer are unfolded, transported and assembled in sequence according to the assembly steps of the first antenna module 31 of the first layer. After the six antenna modules 31 of the first layer are assembled, the pressing and unlocking components of the second layer of the split-petal spacecraft 51 are unlocked, and the second layer of the split-petal spacecraft 51 is separated from the split-petal spacecraft stack 5. As the lateral separation surface of the second layer of the split-petal spacecraft 51 separates, the first mortise and tenon joint of the longitudinal separation surface of the split-petal spacecraft 51 is naturally separated, and the split-petal spacecraft 51 is separated into two spacecraft petals 52. The six antenna modules 31 in the two spacecraft petals 52 are assembled step by step. Finally, the third layer of the split-petal spacecraft 51 is also separated into petals, and the six antenna modules 31 of the two spacecraft petals 52 in the third layer of the split-petal spacecraft 51 are assembled step by step. Finally, all antenna modules 31 are assembled, and the assembly of the super-large satellite antenna is completed.

[0148] The present application provides a split-petal spacecraft 51 for multi-module transportation. The split-petal spacecraft 51 is mainly composed of a main load-bearing frame 1, a load installation component and a clamping and unlocking component. It can efficiently and safely transport antenna modules 31 and meet the needs of on-orbit assembly of ultra-large antennas. The split-petal spacecraft 51 not only improves the transportation efficiency of the antenna module 31, but also effectively solves the problem of the lack of multiple flexible antenna module 31 transportation devices and methods in the current on-orbit assembly of ultra-large antennas. The split-petal spacecraft 51 of the present application can be used for flexible module transportation, can be compatible with antenna modules 31 and antenna components of various sizes, and is suitable for various on-orbit assembly requirements from small antenna arrays to ultra-large antennas. The split-petal spacecraft 51 can also be used to transport other types of functional modules, such as optical remote sensing equipment, communication relay modules, energy supply units, etc., which expands the scope of application of the spacecraft and improves its versatility. With a modular design, different numbers of layers can be stacked according to mission requirements, which can form a single-layer split-petal spacecraft 51 or be stacked into a multi-layer split-petal spacecraft stack 5 to improve space utilization. A single petal-type spacecraft 51 can be further petaled into multiple independent units, making the transportation mode more flexible and adaptable to the load requirements of different sizes and structures. Using the petal-type spacecraft 51 of the present application, multiple ten-meter-class antenna modules 31 can be transported in one layer, and the carrying capacity of a single launch can be improved by stacking multiple layers. A single rocket launch can carry multiple petal-type spacecraft 51 and meet the transportation requirements of antenna modules 31 required to build a hundred-meter-class super-large antenna, greatly improving the transportation efficiency of on-orbit assembly, reducing the number of launches, and reducing the overall mission cost.

[0149] In the description of this specification, if the reference terms "one embodiment", "some examples", "some embodiments", "illustrative embodiment", "example", "specific example", or "some examples" appear, it means that the specific features, structures, materials or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the present application. In this specification, the schematic representation of the above terms does not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described may be combined in any one or more embodiments or examples in a suitable manner.

[0150] The above describes the implementation methods of the present application in detail in conjunction with the accompanying drawings, but the present application is not limited to the above implementation methods. Various changes can be made within the knowledge scope of ordinary technicians in the technical field without departing from the purpose of the present application.

Claims

1. A split-petal spacecraft, characterized in that: include At least two main load-bearing frames, each of the two lateral sides of the main load-bearing frames being provided with a first connecting member; A load installation assembly, wherein the load installation assembly is arranged on the main load-bearing frame, and the load is installed on the main load-bearing frame through the load installation assembly; A pressing and unlocking assembly, wherein the pressing and unlocking assembly is arranged on the main load-bearing frame; Among them, the two main load-bearing frames are laterally connected through the first connecting member to form a petal-type spacecraft, and the two petal-type spacecraft are longitudinally unlockably connected through the clamping and unlocking assembly to form a petal-type spacecraft stack, and the clamping and unlocking assembly is used to control the longitudinal locking and separation of the petal-type spacecraft stack.

2. The split-petal spacecraft according to claim 1, characterized in that: Second connecting pieces are provided on both longitudinal sides of the main load-bearing frame, and the main load-bearing frame is also provided with hollow pillars. The clamping and unlocking components are arranged in the hollow pillars. The clamping and unlocking components and the second connecting pieces cooperate to control the longitudinal locking and separation of the petal-type spacecraft stack.

3. The split-petal spacecraft according to claim 2, characterized in that: The main load-bearing frame includes at least three structural plates, and the main load-bearing frame is provided with a Type I main load-bearing frame and a Type II main load-bearing frame. The first side of the hollow pillar of the Type I main load-bearing frame is provided with one structural plate, and the second side of the hollow pillar of the Type I main load-bearing frame is provided with at least two structural plates, and the first side of the hollow pillar of the Type II main load-bearing frame is provided with at least two structural plates, and the second side of the hollow pillar of the Type II main load-bearing frame is provided with one structural plate. The main load-bearing frames of a single split-type spacecraft are of the same type, and the main load-bearing frames of adjacent stacked split-type spacecraft are of different types. The hollow pillars of adjacent stacked split-type spacecraft are aligned and connected by the compression and unlocking components in the hollow pillars.

4. The split-petal spacecraft according to claim 2, characterized in that: The first connecting member and the second connecting member are both configured as mortise and tenon connecting members, a first protrusion is provided on the first side surface of the main load-bearing frame, and a first recessed portion cooperating with the first protrusion is provided on the second side surface of the main load-bearing frame. The two main load-bearing frames are laterally connected through the cooperation of the first protrusion and the first recessed portion to form the petal-type spacecraft, a second protrusion is provided on one longitudinal side of the main load-bearing frame, and a second recessed portion cooperating with the second protrusion is provided on the other longitudinal side of the main load-bearing frame, and the clamping and unlocking assembly, the second protrusion and the second recessed portion cooperate to control the longitudinal locking and separation of the two petal-type spacecraft.

5. The split-petal spacecraft according to claim 4, characterized in that: The first protrusion is configured as an isosceles trapezoidal tooth, and the second protrusion is configured as a right-angled trapezoidal tooth.

6. The split-petal spacecraft according to claim 2, characterized in that: The compression and unlocking assembly includes an unlockable component and a separation nut. The unlockable component is arranged on the central axis of the hollow pillar. The unlockable component is unlockably connected to the separation nut. The two split-petal spacecraft are locked or separated by the unlockable component and the separation nut.

7. The split-petal spacecraft according to claim 1, characterized in that: The main load-bearing frame is provided with mounting holes on both sides inside and outside, and the load mounting assembly includes a load mounting plate and fasteners. The load mounting plate is fixed on the inner and outer sides of the main load-bearing frame by the cooperation of the fasteners and the mounting holes, and the load is mounted on the load mounting plate.

8. An on-orbit assembly method for a very large antenna, comprising the petal-type spacecraft according to any one of claims 1 to 7, characterized in that: The following steps are involved: S1. Obtain the data required for assembly and transportation through transportation analysis methods; S2. assembling the split-petal spacecraft according to the data; S3, the first carrier rocket is launched, and basic satellites are transported and assembled; S4, the i-th launch vehicle is launched and the (i-1)-th split-type spacecraft stack is transported; S5, the j-th layer of the (i-1)-th stack of split-petal spacecraft separates and splits; S6. The kth antenna module of the jth layer of the (i-1)th stack is parked, unfolded, and assembled.

9. The on-orbit assembly method of a very large antenna according to claim 8, characterized in that: Also included is a transport analysis method, the transport analysis method comprising: The side length of the antenna module is l, the folded height is h, and the folding ratio is set to a, so the folded diameter is l / a; Let the number of antenna module layers be m, the number of antenna modules be n, and the effective aperture of the antenna plane of the m-layer antenna module be D m , The data required for assembly and transportation are obtained through the following formula: m is an odd number, and m≠1; in, (a) Number of antenna modules: When the required antenna plane effective aperture is D, D∈(D m-1 ,D m ], it means that the number of antenna layers required is m, so the number of antenna modules required is n=1+3m(m-1); (b) Number of layers of the segmented spacecraft stack: Denote the payload diameter of the launch vehicle as D ′ , and the payload height as H ′ ; The segmented spacecraft is set as a regular c-sided polygon, with the side length denoted as l″, the maximum diameter as D″, and the height as H″. Limited by the envelope, D″ < D′, then the number of layers of the segmented spacecraft stack (c) Number of launch vehicles: The number of launch vehicles that can be carried on each side of a split-type spacecraft is b, then The number of antenna modules that make up the basic satellite antenna is p, so the number of launch vehicles required is 10. The on-orbit assembly method of a super-large antenna according to claim 9, characterized in that: The specific steps of steps S1 to S6 are: S1-1. According to the effective aperture requirement of the antenna satellite plane, the number of antenna module layers m, the number of antenna modules n, the number of layers e of the petal-type spacecraft stack, and the number of launch vehicles f are calculated by the carrier analysis method; S2-1, the spacecraft petals are connected to form a split-petal spacecraft through a first connecting member; S2-2, the petal-type spacecraft is stacked by pressing and unlocking the components to form a petal-type spacecraft stack; S2-3, antenna modules and other functional modules are installed and fixed on the split-petal spacecraft stack through the payload installation assembly; S2-4, the split-petal spacecraft stack is packaged at the bottom of the fairing of the launch vehicle and is pressed and fixed by pressing and unlocking the assembly; S3-1, the first launch vehicle is launched, and basic satellites are transported and assembled; S4-1, the i-th carrier rocket is launched and the (i-1)-th split-type spacecraft stack is transported; S4-2, the i-th carrier rocket enters the preset orbit, the pressing and unlocking assembly of the e-th layer of the (i-1)-th split-type spacecraft stack is unlocked, and the split-type spacecraft stack is separated from the fairing of the carrier rocket; S5-1, the pressing and unlocking assembly of the j-th layer of the split-type spacecraft in the (i-1)-th split-type spacecraft stack is unlocked, and the j-th layer of the split-type spacecraft is separated from the split-type spacecraft stack; S5-2. As the j-th layer of split-petal spacecraft separates laterally, the split-petal spacecraft naturally separates longitudinally, and the petals separate into two spacecraft petals; S5-3, the two spacecraft petals fly to the parking position near the base satellite; S6-1, the (i-1)th j-th layer k-th antenna module is transported to the preset parking point; S6-2, the detachable extendable arm of the antenna module is unfolded and the wrapping belt is released to form an antenna unfolding module; S6-3, the assembly robot flies to the parking point and grabs the antenna deployment module; S6-4, the detachable extension arm is unlocked and separated from the antenna deployment module; S6-5, the assembly robot grabs the antenna deployment module and flies to the assembly position; S6-6, the assembly robot docks and assembles the antenna deployment module to the preset position of the basic satellite antenna; First, execute steps S1, S2 and S3, from i=2:f, j=1:e, k=1:c, loop step S4 to step S6, and when the last loop of step S6 ends, all antenna modules are assembled and the super-large satellite antenna is assembled.

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