A large radio telescope system constructed on-orbit and an on-orbit construction method

Abstract

The present invention relates to an on-orbit construction type large radio telescope system and an on-orbit construction method, comprising: a mother satellite, comprising a first mother satellite interface and a first mother satellite window; a sub-satellite, comprising a first sub-satellite interface and a second sub-satellite interface; a foldable payload, provided with a back frame, connected to the first mother satellite interface and / or the first sub-satellite interface through the back frame; a compressible truss, comprising a first truss end and a second truss end arranged oppositely, the first truss end being connected to the mother satellite, and the second truss end being connected to the second sub-satellite interface; before the radio telescope system is launched into orbit, the compressible truss is arranged inside the mother satellite in a compressed state, and the mother satellite and the sub-satellite are closely attached together; after the radio telescope system is launched into orbit, the compressible truss can be extended from the first mother satellite window to be in an expanded state. The present invention can improve the utilization rate of the rocket and the utilization rate of the fairing envelope space, and can conveniently construct a long baseline payload array on orbit.

Description

Technical Field

[0001] The present invention mainly relates to the field of spacecraft technology, and in particular to an on-orbit large-scale radio telescope system and an on-orbit construction method. Background Art

[0002] In the field of aerospace technology, large satellite systems, such as large radio telescope systems, have attracted much attention due to their ability to achieve higher precision and more complex functions. In order to meet these requirements, it is usually necessary to launch the various components of a large satellite system into orbit separately through a rocket, and then conduct large-scale construction in orbit.

[0003] Prior art 1 (publication number: CN105197256B) discloses a modular spacecraft that can be deployed in orbit. The mother and child modules are stacked and deployed by locking and releasing hinges. The on-orbit deployment scale is limited, and it is difficult to meet the on-orbit construction requirements of large-scale spacecraft over 20 meters. The submodules are all panel-frame structures composed of aluminum-skinned honeycomb panels. When further expanded and constructed, more submodules are required, which leads to a significant increase in the carrying mass and carrying space, and increases the cost of launch and transportation.

[0004] Prior art 2 (publication number: CN111422378B) discloses a geostationary orbit super-large assembleable satellite platform configuration and an on-orbit assembly method. In this method, the mother-and-child modules need to be launched separately, and the on-orbit construction cycle is long and the efficiency is low. In this method, the mother-and-child modules rely on large robotic arms to complete the connection, which reduces the flexibility of on-orbit operations.

[0005] Prior art 3 (publication number: CN115123582A) discloses a kilometer-class ultra-large-scale space integrated base and its on-orbit construction method. This method realizes on-orbit deployment by flying to the target position through collaborative control of the node satellite, thereby pulling open the telescopic arm, which requires strong collaborative control capabilities of the node satellite. In this method, the telescopic arm is fixedly connected to the node satellite panel, and the carrying space required for launch is larger, which reduces the utilization rate of the fairing envelope space.

[0006] Prior art 4 (publication number: CN111003211B) discloses a spacecraft configuration that can be assembled and expanded on-orbit. This method expands and installs the load through the equipment interface on the structural plate. Only one load can be installed on one surface. When more loads need to be installed, it can only be achieved by continuously connecting the first expansion module and the second expansion module, resulting in an increase in the number of platform equipment and increasing the difficulty of control. In this method, only the mother platform has a propulsion function. For large-scale spacecraft, it is difficult to achieve efficient transfer relying solely on the propulsion capability of the central mother star. To achieve distributed propulsion, other expansion modules must be expanded and installed with a propulsion cabin, and additional rockets are required to provide supply support. The truss expansion module in this method is mainly composed of truss rod connections, and each corner point is equipped with an assembly expansion joint with a low compression ratio. To achieve a long baseline truss connection in a three-dimensional shape, multiple truss expansion modules must be connected, which places high demands on the size of the launch and transportation space.

[0007] In the large-scale implementation process of large satellite systems, the existing technology has the problem of mismatch between the fairing envelope and the scale of large satellite systems, resulting in low rocket utilization and fairing envelope space utilization, making it difficult to conveniently build a long baseline payload array. Therefore, it is necessary to further optimize the on-orbit construction plan of the satellite system. Summary of the invention

[0008] The technical problem to be solved by the present application is to provide an on-orbit constructed large radio telescope system and an on-orbit construction method, which can improve the scale matching between the fairing envelope and the large radio telescope system, improve the rocket utilization rate and the fairing envelope space utilization rate, and can conveniently construct a long baseline payload array on-orbit.

[0009] The technical solution adopted by the present application to solve the above-mentioned technical problems is an in-orbit constructed large-scale radio telescope system, comprising: a mother satellite, comprising a first mother satellite interface and a first mother satellite window, the first mother satellite interface is arranged on the top surface of the mother satellite, and the first mother satellite window is arranged on the side of the mother satellite; a sub-satellite, comprising a first sub-satellite interface and a second sub-satellite interface, the first sub-satellite interface is arranged on the top surface of the sub-satellite, and the second sub-satellite interface is arranged on the side of the sub-satellite; a foldable payload, provided with a back frame, and the foldable payload is connected to the first mother satellite interface and / or the first sub-satellite interface through the back frame; a compressible truss, comprising a first truss end and a second truss end arranged oppositely, the first truss end is connected to the mother satellite, and the second truss end is connected to the second sub-satellite interface; before the large-scale radio telescope system is launched into orbit, the compressible truss is arranged in a compressed state inside the mother satellite, and the mother satellite and the sub-satellite are tightly attached together through the compressible truss; after the large-scale radio telescope system is launched into orbit, the compressible truss can be extended from the first mother satellite window and is thus in an unfolded state.

[0010] In one embodiment of the present application, the large radio telescope system also includes an assembly robot and a payload replenishment package, the payload replenishment package is provided with a payload storage portion and a replenishment package interface, at least one foldable payload is arranged in the payload storage portion, and the mother satellite also includes a second mother satellite interface, and the second mother satellite interface is arranged on the bottom surface of the mother satellite; after the assembly robot and the payload replenishment package are launched into orbit, the payload replenishment package and the mother satellite are connected via the replenishment package interface and the second mother satellite interface, and the assembly robot is used to connect at least one foldable payload to the back frame.

[0011] In one embodiment of the present application, the assembly robot includes a sliding portion and a robotic arm. The assembly robot is connected to the compressible truss through the sliding portion, and the robotic arm is used to grasp and unfold at least one foldable load.

[0012] In one embodiment of the present application, the large radio telescope system further includes a turntable, which is disposed on the first mother satellite interface and is used to rotate to adjust the position of the foldable payload.

[0013] In one embodiment of the present application, the mother satellite also includes a load-bearing part, a top plate, a bottom plate, a first side plate and a second side plate. The top plate, the bottom plate, the first side plate and the second side plate together form a hollow cavity. The load-bearing part is arranged at the center position of the hollow cavity. A first mother satellite window is arranged on the first side plate, a third mother satellite interface is arranged on the second side plate, and the first side plate and the second side plate are arranged alternately.

[0014] In one embodiment of the present application, the load-bearing portion is connected to the first truss end, and before the large radio telescope system is launched into orbit, the compressible truss is placed in a compressed state within the hollow cavity.

[0015] In one embodiment of the present application, a first electromechanical digital interface is provided on the first truss end, and the first electromechanical digital interface is connected to the mother satellite through a first locking piece; a second electromechanical digital interface is provided on the second truss end, and the second electromechanical digital interface is connected to the second sub-satellite interface through a second locking piece; the first electromechanical digital interface and the second electromechanical digital interface are used to enable communication between the mother satellite and the sub-satellite.

[0016] In order to solve the above-mentioned technical problems, the present application also proposes an on-orbit construction method for constructing the above-mentioned large radio telescope system, comprising: step S1: before the large radio telescope system is launched into orbit, the locking mechanism is locked so that the compressible truss is in a compressed state and is located inside the mother satellite, thereby folding the foldable payload; step S2: after the large radio telescope system is launched into orbit, the locking mechanism is unlocked, and the sub-satellite pulls the compressible truss to extend from the first mother satellite window to a preset unfolded state; step S3: unfolding the foldable payload.

[0017] In one embodiment of the present application, after step S3, it also includes: step S4: after the assembly robot and the payload replenishment package are launched into orbit, the payload replenishment package and the mother satellite are connected through the replenishment package interface and the second mother satellite interface; step S5: controlling the assembly robot to fly to the compressible truss; step S6: the assembly robot grabs a foldable payload from the payload replenishment package and unfolds the foldable payload; step S7: the assembly robot connects the grabbed foldable payload to the back frame of the foldable payload already on the mother satellite; step S8: rotating the turntable to a preset angle to adjust the position of the foldable payload; step S9: determining whether the number of foldable payloads connected to the mother satellite is greater than or equal to the preset number, if it is determined to be no, repeating steps S6 to S8; if it is determined to be yes, ending the construction of the large radio telescope system.

[0018] The technical solution of the present application can greatly increase the capacity for accommodating foldable payloads and other components within the limited space of a radio telescope system by reserving space inside the mother satellite, and setting a mother satellite interface and a mother satellite window on the mother satellite, and setting a sub-satellite interface on the sub-satellite, thereby improving the utilization rate of the launch vehicle; through the high folding and aspect ratio design of the foldable payload and the compressible truss, the fairing envelope space can be maximized, and the long baseline payload array can be conveniently carried and quickly constructed in orbit, which greatly reduces the difficulty of in-orbit construction of large radio telescope systems; the sub-satellite can carry a small controller, and through the distributed layout and coordinated control of the sub-satellite and the mother satellite, the requirements for torque and thrust of the control unit of the large radio telescope system can be reduced, and the cost is lower than that of centralized control of the central main satellite. BRIEF DESCRIPTION OF THE DRAWINGS

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

[0020] Figure 1 is a schematic diagram of a large radio telescope system according to an embodiment of the present application;

[0021] Figure 2 is a schematic diagram of an assembly robot and a payload supplement package in an embodiment of the present application;

[0022] Figure 3 is a front view of a large radio telescope system according to an embodiment of the present application;

[0023] Figure 4 is a left side view of a large radio telescope system according to an embodiment of the present application;

[0024] Figure 5 is a top view of a large radio telescope system and fairing envelope in one embodiment of the present application;

[0025] Figure 6 is a bottom view of a large radio telescope system and fairing envelope in one embodiment of the present application;

[0026] Figure 7 is a schematic diagram of a mother satellite in an embodiment of the present application;

[0027] Figure 8 is an exploded diagram of a mother satellite in one embodiment of the present application;

[0028] Fig. 9 is a schematic diagram of a compressible truss in a compressed state in one embodiment of the present application;

[0029] Fig.10 is a schematic diagram of a compressible truss in an expanded state in one embodiment of the present application;

[0030] Fig.11 is a schematic diagram of a neutron satellite in one embodiment of the present application;

[0031] Fig.12 is a schematic diagram of a foldable load in a folded state in an embodiment of the present application;

[0032] Fig.13 is a schematic diagram of a foldable load in an expanded state in an embodiment of the present application;

[0033] Fig.14 is a schematic diagram of an assembly robot in one embodiment of the present application;

[0034] Fig.15 is a schematic diagram of an assembly robot grasping a foldable load in a folded state in one embodiment of the present application;

[0035] Fig.16 is a schematic diagram of an assembly robot unfolding a foldable payload in one embodiment of the present application;

[0036] Fig.17 is a schematic diagram of an interface between an assembly robot and a backpack in one embodiment of the present application;

[0037] Fig.18 is an exemplary flow chart of an on-orbit construction method according to an embodiment of the present application;

[0038] Fig.19 is an exemplary flow chart of the on-orbit deployment process of a large radio telescope system in one embodiment of the present application;

[0039] Fig. 20 It is an exemplary flow chart of the on-orbit expansion process of a large radio telescope system in one embodiment of the present application.

[0040] Description of the accompanying drawings in the specific implementation manner:

[0041] 100. Large radio telescope system; 101. Mother satellite; 1011. First mother satellite interface; 1012. Third mother satellite interface; 10111. Turntable; 1013. First mother satellite window; 1014. Load-bearing part; 1015. Top plate; 1016. Bottom plate; 1017. First side plate; 1018. Second side plate; 1019. Hollow cavity; 102. Sub-satellite; 1021. First sub-satellite interface; 1022. Second sub-satellite interface; 1023. Attitude control module; 1024. Propulsion module; 103. Deployable payload; 103 1. Reflector antenna; 1032. Back frame; 10321. Support beam; 104. Compressible truss; 1041. First truss end; 1042. Second truss end; 1043. Second electromechanical digital interface; 1044. Folding unit; 105. Assembly robot; 1051. Slide; 1052. Robotic arm; 1053. Measurement sensor system; 1054. Thruster; 1055. Installation interface; 10551. Recessed portion; 106. Payload replenishment package; 1061. Payload storage; 1062. Replenishment package interface; 107. Fairing envelope. DETAILED DESCRIPTION

[0042] In order to make the above-mentioned objects, features and advantages of the present application more obvious and easy to understand, the specific implementation methods of the present application are described in detail below with reference to the accompanying drawings.

[0043] In the following description, many specific details are set forth to facilitate a full understanding of the present application, but the present application may also be implemented in other ways different from those described herein, and therefore the present application is not limited to the specific embodiments disclosed below.

[0044] As shown in this application and claims, unless the context clearly indicates an exception, the words "a", "an", "an" and / or "the" do not refer to the singular and may also include the plural. Generally speaking, the terms "include" and "comprise" only indicate the inclusion of the steps and elements that have been clearly identified, and these steps and elements do not constitute an exclusive list. The method or device may also include other steps or elements.

[0045] Flowcharts are used in the present application to illustrate the operations performed by the system according to the embodiments of the present application. It should be understood that the preceding or following operations are not necessarily performed accurately in order. On the contrary, various steps may be processed in reverse order or simultaneously. At the same time, other operations may be added to these processes, or one or more operations may be removed from these processes.

[0046] The present application proposes a large radio telescope system constructed on orbit, which can be applied to application scenarios where it is necessary to improve the utilization rate of rockets and the utilization rate of fairing envelope space, and to conveniently construct a long baseline payload array on orbit. The large radio telescope system of the present application can be a large satellite system such as tens of meters, hundreds of meters, and thousands of meters. The foldable payload of the present application is a key component of the radio telescope system.

[0047] Figure 1 is a schematic diagram of a large radio telescope system according to an embodiment of the present application, Figure 3 is a front view of a large radio telescope system according to an embodiment of the present application, Figure 4 is a left side view of a large radio telescope system according to an embodiment of the present application, Figure 7 Schematic diagram of a mother satellite in an embodiment of the present application. Figure 1 , Figure 3 , Figure 4 , Figure 7 As shown, the on-orbit large radio telescope system 100 of this embodiment includes: a mother satellite 101, including a first mother satellite interface 1011 and a first mother satellite window 1013, the first mother satellite interface 1011 is arranged on the top surface of the mother satellite 101, and the first mother satellite window 1013 is arranged on the side of the mother satellite 101; a sub-satellite 102, including a first sub-satellite interface 1021 and a second sub-satellite interface 1022, the first sub-satellite interface 1021 is arranged on the top surface of the sub-satellite 102, and the second sub-satellite interface 1022 is arranged on the side of the sub-satellite 102; a foldable payload 103 is provided with a back frame 1032, and the foldable payload 103 is connected to the first mother satellite interface 1011 and / or the first sub-satellite interface 1021 through the back frame 1032.

[0048] Figure 6 is a bottom view of a large radio telescope system and a fairing envelope in one embodiment of the present application, Figure 6 The base plate 1016 of the mother satellite 101 is removed. Figure 1 and Figure 6 As shown, the large radio telescope system 100 also includes a compressible truss 104, including a first truss end 1041 and a second truss end 1042 that are relatively arranged, the first truss end 1041 is connected to the mother satellite 101, and the second truss end 1042 is connected to the second sub-satellite interface 1022; before the large radio telescope system 100 is launched into orbit, the compressible truss 104 is in a compressed state and is arranged inside the mother satellite 101, and the mother satellite 101 and the sub-satellite 102 are tightly attached together through the compressible truss 104; after the large radio telescope system 100 is launched into orbit, the compressible truss 104 can be extended from the first mother satellite window 1013 and is thus in an expanded state.

[0049] Exemplarily, the first mother satellite interface 1011, the first sub-satellite interface 1021, the second sub-satellite interface 1022 and other interfaces mentioned in the present application can be used as standard interfaces, and these standard interfaces can be configured to be connected to other components by magnetic attraction. Figure 1 1 mother satellite 101 and 3 sub-satellites 102 are shown in the figure. In other embodiments, the number of sub-satellites 102 can be set to 1, 2, 4, etc. Figure 1 The mother satellite 101 shown in the figure is a regular hexagon when viewed from a top view. In other embodiments, the shape of the mother satellite 101 can be set to other polygons. The present application does not limit the number of mother satellites 101 and sub-satellites 102, and the shape of the mother satellite 101.

[0050] Fig.11 is a schematic diagram of a neutron satellite in an embodiment of the present application, with reference to Fig.11 As shown, the outer surface of the sub-satellite 102 is provided with a plurality of interfaces, which are respectively a first sub-satellite interface 1021 and a second sub-satellite interface 1022. The interface on the surface of the sub-satellite 102 can be used as a standard extension interface for installing a foldable payload 103 or a compressible truss 104 so as to further expand the configuration of the large radio telescope system 100. The sub-satellite 102 is provided with a propulsion module 1024 and an attitude control module 1023. The sub-satellite 102 can actively stretch the compressible truss 104 respectively, so as to realize the long baseline deployment of the large radio telescope system 100.

[0051] Fig.12 is a schematic diagram of a foldable load in a folded state in an embodiment of the present application, Fig.13 Schematic diagram of a foldable load in an embodiment of the present application in an unfolded state. Fig.12 and Fig.13 As shown, the foldable payload 103 of the present application can be set as a radio payload. The foldable payload 103 includes a foldable reflector antenna 1031 and a foldable antenna back frame 1032. The antenna back frame 1032 is used to provide antenna installation, splicing, energy supply and other functions.

[0052] Fig. 9 is a schematic diagram of a compressible truss in a compressed state in one embodiment of the present application, Fig.10 Schematic diagram of a compressible truss in an expanded state in one embodiment of the present application. Fig. 9 As shown, when the compressible truss 104 is in a compressed state, each folding unit 1044 is tightly attached together; Fig.10 As shown, when the compressible truss 104 is in a fully expanded state, there is a certain distance between each folding unit 1044 .

[0053] Figure 5is a top view of a large radio telescope system and fairing envelope in one embodiment of the present application, with reference to Figure 5 and Figure 6 As shown, the scale matching between the fairing envelope 107 and the large radio telescope system 100 is relatively high. Figure 5 and Figure 6 In the illustrated embodiment, the present application constructs a large radio telescope system 100 in the form of a one-to-three mother-and-child satellite (i.e., one mother satellite 101 is connected to three child satellites 102); both the mother satellite 101 and the child satellite 102 can be installed with a foldable payload 103 through a standard surface interface; the mother and child satellites 101 are connected by a compressible truss 104, and are tightly attached together when launched into orbit, which can greatly improve the utilization rate of the rocket's carrying space; after launching into orbit, the compressible truss 104 can be unfolded to achieve convenient deployment and expansion of the antenna array.

[0054] The technical solution of the present application can significantly increase the capacity for accommodating components such as the foldable payload 103 within the limited space of the large radio telescope system 100 by reserving space inside the mother satellite 101, setting a mother satellite interface and a mother satellite window on the mother satellite 101, and setting a sub-satellite interface on the sub-satellite 102, thereby improving the utilization rate of the launch vehicle; through the high folding and aspect ratio design of the foldable payload 103 and the compressible truss 104, the space of the fairing envelope 107 can be maximized, and the long baseline payload array can be conveniently carried and quickly constructed in orbit, which greatly reduces the difficulty of in-orbit construction of the large radio telescope system 100; the sub-satellite 102 can carry a small controller, and through the distributed layout and coordinated control of the sub-satellite 102 and the mother satellite 101, the requirements of the control unit of the large radio telescope system 100 on torque and thrust can be reduced, and the cost is lower than that of centralized control of the central main satellite.

[0055] Figure 2 is a schematic diagram of assembling a robot and a payload supplement pack in one embodiment of the present application, with reference to Figure 2As shown, in some embodiments, the large radio telescope system 100 further includes an assembly robot 105 and a payload supplement package 106, the payload supplement package 106 is provided with a payload storage unit 1061 and a supplement package interface 1062, at least one foldable payload 103 is provided in the payload storage unit 1061, and the mother satellite 101 further includes a second mother satellite interface (not shown), and the second mother satellite interface is provided on the bottom surface of the mother satellite 101; after the assembly robot 105 and the payload supplement package 106 are launched into orbit, the payload supplement package 106 is connected to the mother satellite 101 through the supplement package interface 1062 and the second mother satellite interface, and the assembly robot 105 is used to connect at least one foldable payload 103 to the back frame 1032. Exemplarily, the payload supplement package 106 is used to provide a foldable payload 103 (such as a radio payload) for subsequent expansion and installation, and can be flexibly separated and docked with the bottom of the mother satellite 101 through the supplement package interface 1062.

[0056] Fig.14 is a schematic diagram of an assembly robot in one embodiment of the present application; Fig.15 is a schematic diagram of an assembly robot grasping a foldable load in a folded state in one embodiment of the present application, Fig.15 , the assembly robot 105 is shown with a single arm grasping the foldable load 103 in a folded state; Fig.16 is a schematic diagram of an assembly robot unfolding a foldable payload in one embodiment of the present application, Fig.16 FIG. 1 shows an assembly robot 105 with its arms extended to fold the deployable payload 103. Figures 14 to 16 As shown, in some embodiments, the assembly robot 105 includes a slide portion 1051 and a robotic arm 1052 . The assembly robot 105 is connected to the compressible truss 104 via the slide portion 1051 . The robotic arm 1052 is used to grab and unfold at least one foldable load 103 .

[0057] Exemplarily, the sliding part 1051 of the assembly robot 105 can be configured as a sliding leg, and the sliding part 1051 and the compressible truss 104 can be connected via a slide rail. The assembly robot 105 can slide on the compressible truss 104 and complete the grasping, unfolding and installation of the foldable load 103. Fig.16 The assembly robot 105 shown in the figure is provided with two seven-degree-of-freedom mechanical arms. The ends of the mechanical arms 1052 can be connected to the antenna back frame 1032 of the foldable payload 103 through a mechanical interface. The single arm of the assembly robot 105 can complete the grasping of the foldable payload 103, and the two arms can realize the deployment of the foldable payload 103 by grasping different interfaces of the antenna back frame 1032 at the ends. The head of the assembly robot 105 is provided with a measurement sensor system 1053 to assist in the splicing and installation of the foldable payload 103. The assembly robot 105 can also carry a thruster 1054, so as to realize the functions of leaping, taking off, and posture adjustment in complex environments.

[0058] Fig.17 is a schematic diagram of an interface between an assembly robot and a back frame in one embodiment of the present application, with reference to Fig.17 As shown, a recessed portion 10551 is provided on the installation interface 1055 between the assembly robot 105 and the antenna back frame 1032, and the recessed portion 10551 is adapted to the support beam 10321 on the back frame 1032 of the foldable load 103. The engagement of the recessed portion 10551 and the support beam 10321 can realize a stable connection between the robot arm 1052 and the foldable load 103.

[0059] Figure 8 is an exploded diagram of a mother satellite in an embodiment of the present application, refer to Figure 7 and Figure 8 As shown, in some embodiments, the large radio telescope system 100 further includes a turntable 10111, which is disposed on the first mother satellite interface 1011, and the turntable 10111 is used to rotate to adjust the position of the foldable payload 103. Exemplarily, the foldable payload 103 can be connected to the mother satellite 101 by snapping the turntable 10111. The supplementary payload can be deployed to the mother satellite 101 by the assembly robot 105, and the turntable 10111 on the top of the mother satellite 101 can realize the extended installation of more payloads by rotating.

[0060] refer to Figure 8 As shown, in some embodiments, the mother satellite 101 also includes a load-bearing portion 1014, a top plate 1015, a bottom plate 1016, a first side plate 1017 and a second side plate 1018. The top plate 1015, the bottom plate 1016, the first side plate 1017 and the second side plate 1018 together form a hollow cavity 1019. The load-bearing portion 1014 is arranged at a central position in the hollow cavity 1019. The first side plate 1017 is provided with a first mother satellite window 1013. The second side plate 1018 is provided with a third mother satellite interface 1012. The first side plate 1017 and the second side plate 1018 are alternately arranged.

[0061] For example, Figure 7 and Figure 8In the illustrated embodiment, the mother satellite 101 is a central load-bearing cylindrical configuration, with an overall regular hexagonal prism shape, and the load-bearing portion 1014 is set as a cylindrical structure. The turntable 10111 on the mother satellite 101 can provide a load installation position and can splice multiple loads by rotation, which is convenient for the expansion and installation of the load. The load-bearing portion 1014 can provide an installation reference and support for the entire large radio telescope system 100, and the interior of the load-bearing portion 1014 can include a propulsion module. The top plate 1015 and the bottom plate 1016 are hexagonal, and the surfaces of the top plate 1015 and the bottom plate 1016 reserve standard installation interfaces for components, which can provide mechanical connection while transmitting energy and information. The first side plate 1017 has a window for forming a first mother satellite window 1013, and the first mother satellite window 1013 is used to bury the truss rod of the compressible truss 104. The second side plate 1018 is rectangular, and its surface reserves a third mother satellite interface 1012 for connecting other components. The empty space enclosed by the side panels and the load-bearing part 1014 can be used to arrange other components, such as payloads with different functions, attitude control modules, onboard computing modules, power modules, etc.

[0062] refer to Figure 6 As shown, in some embodiments, the load-bearing portion 1014 is connected to the first truss end 1041 , and before the large radio telescope system 100 is launched into orbit, the compressible truss 104 is in a compressed state and is disposed in the hollow cavity 1019 .

[0063] refer to Figure 6 and Fig. 9 As shown, in some embodiments, a first electromechanical digital interface (not shown) is provided on the first truss end 1041, and the first electromechanical digital interface is connected to the mother satellite 101 through a first locking member (not shown); a second electromechanical digital interface 1043 is provided on the second truss end 1042, and the second electromechanical digital interface 1043 is connected to the second sub-satellite interface 1022 through a second locking member (not shown); the first electromechanical digital interface and the second electromechanical digital interface have built-in power supply and data interface, which are used to enable communication between the mother satellite 101 and the sub-satellite 102. Exemplarily, the first locking member and the second locking member can be configured to automatically snap, and the locking with the docking member is achieved by automatic snap. The mother satellite 101 and the sub-satellite 102 are connected by the compressible truss 104, and the function of lengthening the whole satellite baseline and maintaining the configuration can be played in the process of unfolding the compressible truss 104. The whole satellite baseline can be understood as the distance between the mother satellite 101 and the sub-satellite 102 after the compressible truss 104 is unfolded.

[0064] The present application also proposes an on-orbit construction method for constructing the large radio telescope system 100 as described above. The on-orbit construction method can be run in the satellite computer of the large radio telescope system, and can also be run on the ground side. When the on-orbit construction method is run on the ground side, the data of the ground side and the data of the satellite computer are interacted through a wireless network. The present application does not limit the operating environment of the on-orbit construction method.

[0065] Fig.18 is an exemplary flow chart of an on-orbit construction method according to an embodiment of the present application, with reference to Fig.18 As shown, the on-orbit construction method of this embodiment includes the following steps:

[0066] Step S1: Before the large radio telescope system is launched into orbit, the locking mechanism is locked so that the compressible truss is in a compressed state and located inside the mother satellite, thereby folding the foldable load.

[0067] Step S2: After the large radio telescope system is launched into orbit, the locking mechanism is unlocked, and the sub-satellite pulls the compressible truss to extend from the first mother satellite window to a preset unfolded state.

[0068] Step S3: unfold the expandable load.

[0069] Exemplarily, the above steps S1 to S3 are equivalent to the process of on-orbit deployment of a large radio telescope system, and the process is described below using an embodiment.

[0070] Fig.19 is an exemplary flow chart of the on-orbit deployment process of a large radio telescope system in one embodiment of the present application, with reference to Fig.19 As shown, in step S1910, when the large radio telescope system is launched into orbit, the compressible trusses are folded and placed inside the mother satellite, the foldable payload is folded and placed on the sub-satellite and the mother satellite, and the entire large radio telescope system is placed in the fairing; in step S1920, after the large radio telescope system is launched into orbit, it separates from the fairing and is deployed in a designated orbit; in step S1930, the locking mechanism is released, and the sub-satellite pulls the three compressible trusses to unfold; in step S1940, the compressible trusses are fully unfolded; in step S1950, the back frame locking mechanism on the sub-satellite and the mother satellite is released, and the back frame of the foldable payload is unfolded; in step S1960, the reflecting surface locking mechanism of the foldable payload is released, and the antenna is automatically unfolded.

[0071] In some embodiments, after step S3, the method further includes:

[0072] Step S4: After the assembly robot and the payload supplement package are launched into orbit, the payload supplement package is connected to the mother satellite through the supplement package interface and the second mother satellite interface;

[0073] Step S5: controlling the assembly robot to fly onto the compressible truss;

[0074] Step S6: the assembly robot grabs a foldable payload from the payload supplement package and unfolds the foldable payload;

[0075] Step S7: the assembly robot connects the grasped foldable payload to the existing foldable payload back frame on the mother satellite;

[0076] Step S8: rotating the turntable to a preset angle to adjust the position of the foldable load;

[0077] Step S9: Determine whether the number of foldable payloads connected to the mother satellite is greater than or equal to a preset number. If it is not, repeat steps S6 to S8; if it is yes, end the construction of the large radio telescope system.

[0078] Exemplarily, the above steps S4 to S9 are equivalent to the process of on-orbit expansion of a large radio telescope system, and the process is described below using an embodiment.

[0079] Fig. 20 is an exemplary flow chart of the on-orbit expansion process of a large radio telescope system in one embodiment of the present application, with reference to Fig. 20 As shown, in step S2010, after the assembly robot and the payload replenishment package are launched into orbit, they are connected through the interface at the bottom of the mother satellite and the replenishment package interface; in step S2020, the assembly robot flies into the truss, grabs the foldable payload from the payload replenishment package and unfolds it; in step S2030, the assembly robot docks the antenna backpack of the foldable payload with the antenna backpack of the foldable payload already on the top of the mother satellite; in step S2040, the turntable on the top of the mother satellite rotates 60° to reserve a position for the installation of the next foldable payload; in step S2050, the assembly robot grabs the next foldable payload from the payload replenishment package and unfolds it, and after completing the installation of the foldable payload on the mother satellite, the turntable of the mother satellite continues to rotate 60°; in step S2060, the above grabbing and installation steps are repeated until all the foldable payloads are installed.

[0080] The present application also includes a computer-readable medium storing a computer program code, which, when executed by a processor, implements the on-orbit construction method described above.

[0081] When the on-orbit construction method is implemented as a computer program, it can also be stored in a computer-readable storage medium as a product. For example, a computer-readable storage medium may include, but is not limited to, a magnetic storage device (e.g., a hard disk, a floppy disk, a magnetic strip), an optical disk (e.g., a compact disk (CD), a digital versatile disk (DVD)), a smart card, and a flash memory device (e.g., an electrically erasable programmable read-only memory (EPROM), a card, a stick, a key drive). In addition, the various storage media described herein can represent one or more devices and / or other machine-readable media for storing information. The term "machine-readable medium" may include, but is not limited to, wireless channels and various other media (and / or storage media) that can store, contain and / or carry code and / or instructions and / or data.

[0082] It should be understood that the embodiments described above are only illustrative. The embodiments described herein may be implemented in hardware, software, firmware, middleware, microcode, or any combination thereof. For hardware implementation, the processor may be implemented in one or more application specific integrated circuits (ASICs), digital signal processors (DSPs), digital signal processing devices (DSPDs), programmable logic devices (PLDs), field programmable gate arrays (FPGAs), processors, controllers, microcontrollers, microprocessors, and / or other electronic units designed to perform the functions described herein, or a combination thereof.

[0083] Some aspects of the present application may be performed entirely by hardware, entirely by software (including firmware, resident software, microcode, etc.), or by a combination of hardware and software. The above hardware or software may be referred to as "data blocks", "modules", "engines", "units", "components" or "systems". The processor may be one or more application specific integrated circuits (ASICs), digital signal processors (DSPs), digital signal processing devices (DAPDs), programmable logic devices (PLDs), field programmable gate arrays (FPGAs), processors, controllers, microcontrollers, microprocessors, or combinations thereof. In addition, various aspects of the present application may be expressed as computer products located in one or more computer-readable media, which include computer-readable program codes. For example, computer-readable media may include, but are not limited to, magnetic storage devices (e.g., hard disks, floppy disks, tapes ...), optical disks (e.g., compact disks CDs, digital versatile disks DVDs ...), smart cards, and flash memory devices (e.g., cards, sticks, key drives ...).

[0084] A computer-readable medium may include a propagated data signal containing computer program code, such as in baseband or as part of a carrier wave. The propagated signal may have a variety of manifestations, including electromagnetic, optical, etc., or a suitable combination. A computer-readable medium may be any computer-readable medium other than a computer-readable storage medium, which may be connected to an instruction execution system, device or apparatus to communicate, propagate or transmit a program for use. The program code on the computer-readable medium may be propagated via any suitable medium, including radio, cable, fiber optic cable, radio frequency signal, or similar medium, or any combination of the above mediums.

[0085] The basic concepts have been described above. Obviously, for those skilled in the art, the above application disclosure is only an example and does not constitute a limitation of the present application. Although not explicitly stated herein, those skilled in the art may make various modifications, improvements and amendments to the present application. Such modifications, improvements and amendments are suggested in the present application, so such modifications, improvements and amendments still belong to the spirit and scope of the exemplary embodiments of the present application.

[0086] At the same time, the present application uses specific words to describe the embodiments of the present application. For example, "one embodiment", "an embodiment", and / or "some embodiments" refer to a certain feature, structure or characteristic related to at least one embodiment of the present application. Therefore, it should be emphasized and noted that "one embodiment" or "an embodiment" or "an alternative embodiment" mentioned twice or more in different positions in this specification does not necessarily refer to the same embodiment. In addition, some features, structures or characteristics in one or more embodiments of the present application can be appropriately combined.

[0087] In some embodiments, numbers describing the number of components and attributes are used. It should be understood that such numbers used in the description of the embodiments are modified by the modifiers "about", "approximately" or "substantially" in some examples. Unless otherwise specified, "about", "approximately" or "substantially" indicate that the numbers are allowed to vary by ±20%. Accordingly, in some embodiments, the numerical parameters used in the specification and claims are approximate values, which may change according to the required features of individual embodiments. In some embodiments, the numerical parameters should take into account the specified significant digits and adopt the general method of retaining digits. Although the numerical domains and parameters used to confirm the breadth of their range in some embodiments of the present application are approximate values, in specific embodiments, the setting of such numerical values ​​is as accurate as possible within the feasible range.

Claims

1. A large radio telescope system constructed on orbit, characterized in that: include: A mother satellite, comprising a first mother satellite interface and a first mother satellite window, wherein the first mother satellite interface is arranged on a top surface of the mother satellite, and the first mother satellite window is arranged on a side surface of the mother satellite; A sub-satellite, comprising a first sub-satellite interface and a second sub-satellite interface, wherein the first sub-satellite interface is arranged on a top surface of the sub-satellite, and the second sub-satellite interface is arranged on a side surface of the sub-satellite; A foldable payload is provided with a back frame, and the foldable payload is connected to the first mother satellite interface and / or the first child satellite interface through the back frame; A compressible truss comprises a first truss end and a second truss end which are arranged opposite to each other, wherein the first truss end is connected to the mother satellite, and the second truss end is connected to the interface of the second sub-satellite; before the large radio telescope system is launched into orbit, the compressible truss is arranged inside the mother satellite in a compressed state, and the mother satellite and the sub-satellite are tightly attached together through the compressible truss; after the large radio telescope system is launched into orbit, the compressible truss can be extended from the window of the first mother satellite to be in an expanded state.

2. The large radio telescope system constructed on orbit as claimed in claim 1, characterized in that: It also includes an assembly robot and a payload replenishment package, the payload replenishment package is provided with a payload storage part and a replenishment package interface, at least one foldable payload is arranged in the payload storage part, and the mother satellite also includes a second mother satellite interface, and the second mother satellite interface is arranged on the bottom surface of the mother satellite; after the assembly robot and the payload replenishment package are launched into orbit, the payload replenishment package and the mother satellite are connected via the replenishment package interface and the second mother satellite interface, and the assembly robot is used to connect the at least one foldable payload to the back frame.

3. The large radio telescope system constructed on orbit as claimed in claim 2, characterized in that: The assembly robot comprises a sliding part and a mechanical arm, wherein the assembly robot is connected to the compressible truss via the sliding part, and the mechanical arm is used to grasp and unfold the at least one foldable load.

4. The large radio telescope system constructed on orbit as claimed in claim 1, characterized in that: It also includes a turntable, which is arranged on the first mother satellite interface and is used to rotate to adjust the position of the foldable payload.

5. The large radio telescope system constructed on orbit as claimed in claim 1, characterized in that: The mother satellite also includes a load-bearing part, a top plate, a bottom plate, a first side plate and a second side plate. The top plate, the bottom plate, the first side plate and the second side plate together form a hollow cavity. The load-bearing part is arranged at a central position in the hollow cavity. The first side plate is provided with the first mother satellite window, the second side plate is provided with a third mother satellite interface, and the first side plate and the second side plate are alternately arranged.

6. The large radio telescope system constructed on orbit as claimed in claim 5, characterized in that: The load-bearing portion is connected to the first truss end. Before the large radio telescope system is launched into orbit, the compressible truss is in a compressed state and is arranged in the hollow cavity.

7. The large radio telescope system constructed on orbit as claimed in claim 1, characterized in that: A first electromechanical digital interface is provided on the first truss end, and the first electromechanical digital interface is connected to the mother satellite through a first locking piece; a second electromechanical digital interface is provided on the second truss end, and the second electromechanical digital interface is connected to the second sub-satellite interface through a second locking piece; the first electromechanical digital interface and the second electromechanical digital interface are used to enable communication between the mother satellite and the sub-satellite.

8. An on-orbit construction method, characterized in that: Used to construct a large radio telescope system as claimed in any one of claims 1 to 7, comprising: Step S1: before the large radio telescope system is launched into orbit, the locking mechanism is locked so that the compressible truss is in a compressed state and located inside the mother satellite, and the foldable load is folded; Step S2: After the large radio telescope system is launched into orbit, the locking mechanism is unlocked, and the sub-satellite pulls the compressible truss to extend from the first mother satellite window to a preset unfolded state; Step S3: unfolding the foldable load; Step S4: After the assembly robot and the payload supplement package are launched into orbit, the payload supplement package is connected to the mother satellite through the supplement package interface and the second mother satellite interface; Step S5: controlling the assembly robot to fly onto the compressible truss; Step S6: the assembly robot grabs a foldable payload from the payload supplement package and unfolds the foldable payload; Step S7: the assembly robot connects the grasped foldable payload to the existing foldable payload back frame on the mother satellite; Step S8: rotating the turntable to a preset angle to adjust the position of the foldable load; Step S9: Determine whether the number of foldable payloads connected to the mother satellite is greater than or equal to a preset number. If it is not, repeat steps S6 to S8; if it is yes, then finish constructing the large radio telescope system.

Images