Concealed parent-child star structure and child star separation control method

Abstract

The application provides a concealed parent-child satellite structure and a parent-child satellite separation control method, wherein the parent-child satellite structure comprises a parent satellite and a child satellite assembly (200), the parent satellite comprises a platform cabin (100) and a load cabin (300), the platform cabin (100) is connected with the load cabin (300) in a top-down manner, and the child satellite assembly (200) is arranged in the load cabin (300); the load cabin (300) has two states of being closed and not being closed, and when a top plate (302) of the load cabin is in an unfolded state, the child satellite assembly (200) arranged in the load cabin (300) can be exposed; the child satellite assembly (200) comprises a child satellite (201) and a separation mechanism (202), and the child satellite (201) is arranged in the load cabin (300) through the separation mechanism (202). The application can provide a good temperature environment and an anti-radiation environment for the child satellite (201) before separation, and the child satellite (201) is hidden in the load cabin (300) before separation, so that the actual use of the child satellite (201) is not easy to be observed and found.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of satellite security technology, in particular to a concealed mother-daughter satellite structure and a daughter satellite separation control method. BACKGROUND

[0002] Satellites are often launched in different ways due to different payloads and task backgrounds. Common satellite launch methods include one satellite per rocket, multiple satellites in series per rocket, and multiple satellites in parallel per rocket. The mother-daughter satellite launch method, in which one mother satellite carries multiple daughter satellites, is relatively rare. The mother-daughter satellite launch method places high demands on the structural design of the mother satellite. The structural design of the mother satellite must not only reasonably support the daughter satellites and create a good force, thermal, and radiation environment for the daughter satellites, but also must avoid the structural design of the daughter satellites and the mother satellite being too bulky and cumbersome, which would result in high launch costs.

[0003] In existing mother-daughter satellite structures, the mother satellite usually carries only one or two daughter satellites, and the daughter satellites are directly exposed on the outside of the mother satellite. Through observation by an enemy on-orbit camera, the function and purpose of the mother-daughter satellite can be easily identified based on the structure of the daughter satellites, the structure of the mother satellite, and the supporting payload style, which lacks concealment. The daughter satellites are directly exposed on the outside of the mother satellite, which requires overcoming a relatively harsh on-orbit temperature alternating environment and radiation environment, placing higher demands on the design of the daughter satellites, or requiring greater costs to enable the daughter satellites to meet the corresponding functional, performance, and life requirements. Meanwhile, most mother-daughter satellites have the characteristics that the mother satellite performs a conventional on-orbit task before the daughter satellites separate, with low energy demand, and the mother satellite performs a special on-orbit task after the daughter satellites separate, with increased energy demand. How to ensure sufficient energy during different task stages is also a problem that needs to be solved. SUMMARY

[0004] The technical problem to be solved by the present application is to provide a concealed mother-daughter satellite structure and a daughter satellite separation control method, which can provide a good temperature environment and anti-radiation environment before the daughter satellites separate, and the daughter satellites are hidden in the payload cabin before the daughter satellites separate, so that their actual purpose is not easily detected and discovered.

[0005] To solve the above technical problems, in a first aspect, the present application provides a concealed mother-daughter satellite structure, comprising: a mother satellite and a daughter satellite assembly, wherein the mother satellite comprises a platform cabin and a payload cabin, the platform cabin is connected to the payload cabin above, and the payload cabin is provided with the daughter satellite assembly; the payload cabin has two states of being closed and not being closed, and when the top plate of the payload cabin is in an unfolded state, the daughter satellite assembly placed in the payload cabin can be exposed; the daughter satellite assembly comprises a daughter satellite and a separation mechanism, and the daughter satellite is arranged in the payload cabin through the separation mechanism.

[0006] Optionally, the bottom of the load cabin is a platform cabin top plate, the side is a load cabin side plate, and the top is a load cabin top plate; wherein the platform cabin top plate and the load cabin side plate are fixed plates, and the load cabin top plate is a movable plate and can be opened to make the load cabin in an unsealed state; the sub-satellite is arranged on the platform cabin top plate through a separation mechanism.

[0007] Optionally, the load cabin top plate is connected to one side of the load cabin side plate through a door shaft hinge, and is connected to the other side of the load cabin side plate through a compression piece.

[0008] Optionally, the door shaft hinge is a door shaft hinge, and the compression piece is a memory alloy expansion breaker.

[0009] Optionally, the load cabin side plate is composed of four flat plates, and the load cabin top plate is connected to one of the flat plates of the load cabin side plate through a door shaft hinge.

[0010] Optionally, the load cabin top plate is further fixed with a solar cell array.

[0011] Optionally, the flat plate hinged to the load cabin top plate is fixed with the solar cell array.

[0012] Optionally, a vertical rod is fixed in the load cabin, and the vertical rod is used to provide support for the load cabin side plate.

[0013] Optionally, the separation mechanism is a memory alloy pin extractor separation mechanism, a separation nut type separation mechanism, or an explosive bolt type separation mechanism.

[0014] In a second aspect, the application provides a sub-satellite separation control method applied to the concealed sub-mother satellite structure as described in the first aspect, and the method comprises the following steps: when it is needed to release the sub-satellite, controlling an adjusting mechanism to adjust the spatial orientation of the sub-mother satellite structure, so that the sub-mother satellite structure runs in a suitable posture; controlling the load cabin top plate to move, so that the load cabin top plate is in an unfolded state and exposes the sub-satellite in the load cabin; and controlling the separation mechanism to start, so that the separation mechanism separates the sub-satellite along a preset sub-satellite separation direction.

[0015] Compared with the prior art, the application has the following advantages: a load cabin is connected above a platform cabin of a mother satellite, and a sub-satellite is arranged in the load cabin; the load cabin has two states of sealing and unsealing, and when a load cabin top plate is in an unfolded state, a sub-satellite assembly arranged in the load cabin can be exposed; the sub-satellite assembly comprises a sub-satellite and a separation mechanism, the sub-satellite is arranged in the load cabin through the separation mechanism, so that a good temperature environment and an anti-radiation environment can be provided for the sub-satellite before separation, and the sub-satellite is hidden in the load cabin before separation, so that the actual use of the sub-satellite is not easy to be detected and discovered. BRIEF DESCRIPTION OF DRAWINGS

[0016] The accompanying drawings are included to provide a further understanding of the present application and are incorporated in and constitute apart of this application, illustrate embodiments of the present application and together with the description serve to explain the principles of the present application. In the drawings:

[0017] Figure 1 is a schematic diagram of a concealed parent-child star structure according to an embodiment of the present application;

[0018] Figure 2 is an exploded view of a concealed parent-child star structure according to an embodiment of the present application;

[0019] Figure 3 is a flowchart of a parent-child star separation control method according to an embodiment of the present application;

[0020] Figure 4 is a structural diagram of a parent-child star separation control device according to an embodiment of the present application;

[0021] Figure 5 is a schematic diagram of an electronic device according to an embodiment of the present application.

[0022] The various signs in the drawings represent:

[0023] 100 - platform cabin; 101 - platform cabin bottom plate; 102 - platform cabin bearing cylinder; 103 - platform cabin top plate;

[0024] 200 - sub-star assembly; 201 - sub-star; 202 - separation mechanism;

[0025] 300 - load cabin; 301 - load cabin side plate; 302 - load cabin top plate; 303 - door shaft hinge; 304 - compression piece; 305 - vertical rod; 306 - solar cell array. DETAILED DESCRIPTION

[0026] In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings needed in the embodiment description will be briefly introduced. Obviously, the drawings in the following description are only some examples or embodiments of the present application, and for those skilled in the art, the present application can also be applied to other similar scenarios without creative labor. Unless the context clearly indicates otherwise or otherwise stated, the same reference numbers in the drawings represent the same structure or operation.

[0027] As shown in the present application and claims, unless the context clearly indicates otherwise or otherwise stated, "one", "a", "an", and / or "the" do not refer to the singular, but can also include the plural. Generally speaking, the terms "comprise" and "include" only indicate the inclusion of the steps and elements explicitly identified, and these steps and elements do not constitute an exclusive list, and the method or device can also include other steps or elements.

[0028] In the description of the present application, it should be understood that the orientation words such as "front, back, upper, lower, left, right", "transverse, vertical, perpendicular, horizontal" and "top, bottom" and the like indicated orientation or position relationship are generally based on the orientation or position relationship shown in the drawings, and are only for the convenience of describing the present application and simplifying the description, without the opposite description, these orientation words do not indicate and imply that the device or element referred to must have a particular orientation or be constructed and operated in a particular orientation, therefore it cannot be understood as a limitation on the scope of protection of the present application; the orientation words "inner, outer" refer to the inner and outer relative to the contour of each component itself.

[0029] For the convenience of description, spatial relative terms such as "over", "above", "upper surface", "upper" and the like can be used herein to describe the spatial positional relationship of one device or feature with other devices or features as shown in the drawings. It should be understood that the spatial relative terms are intended to include different orientations in use or operation in addition to the orientation of the device described in the drawings. For example, if the device in the drawing is inverted, the device described as "above" or "over" other devices or structures will be positioned "below" or "under" other devices or structures. Thus, the exemplary term "above" can include both "above" and "below" orientations. The device can also be positioned in other different ways (rotated 90 degrees or in other orientations), and the spatial relative descriptions used herein are interpreted accordingly.

[0030] 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 in sequence. On the contrary, various steps can be processed in reverse order or simultaneously. Meanwhile, or other operations are added to these processes, or one or more steps of operation are removed from these processes.

[0031] Embodiment one

[0032] Figure 1 is a schematic diagram of a hidden parent-child star structure according to an embodiment of the present application, Figure 2 is an exploded view of a hidden parent-child star structure according to an embodiment of the present application, with reference to Figure 1 and Figure 2The concealed parent-child satellite structure includes a parent satellite and a child satellite assembly 200. The parent satellite includes a platform cabin 100 and a payload cabin 300. The platform cabin 100 is connected to the payload cabin 300. The child satellite assembly 200 is arranged in the payload cabin 300. The payload cabin 300 has two states, i.e., closed and unclosed. When the top plate 302 of the payload cabin 300 is in the unclosed state, the child satellite assembly 200 arranged in the payload cabin 300 is exposed. When the payload cabin 300 is in the closed state, the child satellite assembly 200 is hidden in the payload cabin 300. The child satellite assembly 200 includes a child satellite 201 and a separation mechanism 202. The child satellite 201 is arranged in the payload cabin 300 through the separation mechanism 202.

[0033] In the embodiment, the parent satellite includes a platform cabin force cylinder 102. A platform cabin bottom plate 101 is arranged below the platform cabin force cylinder 102. The bottom of the platform cabin force cylinder 102 is used for connection with a launch vehicle or has a connection port for connection with the launch vehicle. A platform cabin top plate 103 is arranged above the platform cabin force cylinder 102. The shape of the platform cabin force cylinder 102 can be a reverse circular truncated cone, a square, a cylinder or a circular truncated cone. The shape can be determined according to the number and layout of devices and is not limited herein.

[0034] The platform cabin 100 is connected to the payload cabin 300. Of course, the payload cabin 300 can have a separate bottom plate or share a plate with the platform cabin 100, i.e., share the platform cabin top plate 103. Since the payload cabin 300 has two states, i.e., closed and unclosed, when the child satellite 201 needs to be released, the top plate 302 of the payload cabin 300 is in the unclosed state. When the payload cabin 300 is in the closed state, the child satellite 201 is hidden in the payload cabin 300 before separation and the actual use of the child satellite 201 is not easy to be detected and discovered. Since the child satellite 201 is in the closed environment of the payload cabin 300 before separation, the payload cabin 300 can provide a good temperature environment and anti-radiation environment for the child satellite 201. In addition, the child satellite 201 is in the closed environment before separation. The parent satellite is easy to control the temperature of the child satellite 201, create a good temperature environment and anti-radiation environment for the child satellite 201 and prolong the on-orbit life of the child satellite 201. Before the child satellite 201 separates, the parent satellite performs a conventional on-orbit task. The body-mounted solar panel can ensure the energy supply of the whole satellite. After the child satellite 201 separates, the parent satellite performs a special on-orbit task. The energy demand increases. At this time, the top plate 302 of the payload cabin 300 has been expanded. The energy demand of the parent satellite during the special task period is ingeniously supplemented.

[0035] In some embodiments, the bottom of the payload cabin 300 is the platform cabin top plate 103, i.e., the payload cabin 300 and the platform cabin 100 can share a plate, saving design space and reducing the mass of the whole satellite. The side of the payload cabin 300 is the payload cabin side plate 301, and the top of the payload cabin 300 is the payload cabin top plate 302. Among them, the platform cabin top plate 103 and the payload cabin side plate 301 are fixed plates, and the payload cabin top plate 302 is a movable plate and can be opened to make the payload cabin 300 in an unsealed state. That is, when the payload cabin 300 is in a sealed state, the platform cabin top plate 103, the payload cabin side plate 301, and the payload cabin top plate 302 form a sealed space. When it is necessary to change the payload cabin 300 to an unsealed state, since only the payload cabin top plate 302 is a movable plate, opening the payload cabin top plate 302 can make the payload cabin 300 in an unsealed state.

[0036] In addition, from the structure design of the fixed plate and the movable plate of the payload cabin 300 described above, only the payload cabin top plate 302 is a movable plate, and other plates are fixed plates, which minimizes the movable parts of the payload cabin 300 and improves the overall structural stability of the payload cabin 300. The sub-satellite 201 is arranged on the platform cabin top plate 103 through the separation mechanism 202, which is used to separate the sub-satellite 201 from the mother satellite to carry out independent flight or perform other tasks.

[0037] In some embodiments, the payload cabin top plate 302 is connected to one side of the payload cabin side plate 301 through a door shaft hinge 303, and is connected to the other side of the payload cabin side plate 301 through a pressing piece 304. In this embodiment, the payload cabin side plate 301 is a movable plate, and its activity effect is to make the payload cabin 300 be able to be sealed or unsealed. The payload cabin top plate 302 is connected to one side of the payload cabin side plate 301 through the door shaft hinge 303, which has a restoring force or a restoring elastic force. Without other external force intervention, through the restoring action of the door shaft hinge 303, the payload cabin top plate 302 can be in an open position, or in other words, the payload cabin 300 is in an unsealed state. If the payload cabin 300 is to be in a sealed state, external force is needed to press the cabin top plate 302 to form a sealed space.

[0038] The load cabin top plate 302 is connected to the other side of the load cabin side plate 301 through the compression member 304, that is, after the load cabin top plate 302 is covered to form a closed space of the load cabin 300, the load cabin top plate 302 is fixed or buckled through the compression member 304, the covering state of the load cabin top plate 302 is maintained, and the load cabin 300 is in a closed state. When the load cabin top plate 302 needs to be restored to the unfolded state, only the compression member 304 needs to be disconnected or the compression force of the compression member 304 on the load cabin side plate 301 needs to be removed, and then the load cabin top plate 302 is automatically restored to the unfolded state under the restoring force of the door shaft hinge 303. Illustratively, the door shaft hinge 303 can be a door shaft hinge, and the compression member 304 can be a memory alloy expander.

[0039] In some embodiments, the load cabin side plate 301 is composed of four plates, and the load cabin top plate 302 can be connected to one of the plates of the load cabin side plate 301 through the door shaft hinge 303. In this embodiment, although only one closed space of the load cabin 300 is needed, different structures or shapes of the load cabin 300 have an influence on the installation, integration and structural design of the satellite. According to actual needs, the load cabin 300 can be a square load cabin, a cylindrical load cabin or an inverted conical load cabin, etc., which is not specifically limited here. Generally, it is more appropriate to design the load cabin 300 into a cubic structure. For example, the load cabin 300 includes upper and lower plates, which are the platform cabin top plate 103 and the load cabin top plate 302, respectively, and the side of the load cabin 300, that is, the load cabin side plate 301, is composed of four plates. At this time, one of the four plates is in a hinged relationship with the load cabin top plate 302, and the remaining one or more plates are in a compression relationship with the load cabin top plate 302. For example, the compression member 304 can be arranged on one plate that is not in a hinged relationship, or the compression member 304 can be arranged on two plates that are not in a hinged relationship, or even the compression member 304 can be arranged on other plates that are not in a hinged relationship.

[0040] In some embodiments, the load cabin top plate 302 also has a solar cell array 306 fixed thereon. The solar cell array 306 can provide energy for the parent-child satellite structure, and in general, the area of the cabin top plate 302 is large enough to accommodate a larger solar cell array 306. The load cabin top plate 302 with the solar cell array 306 is also called an expandable sail plate. Further, the plate hinged to the load cabin top plate 302 can also have a solar cell array 306 fixed thereon, and when the load cabin top plate 302 is in the unfolded state, it can form a larger sail plate with the hinged plate in form, which is equivalent to increasing the use area of the solar cell array 306, and is beneficial to the acquisition of solar energy.

[0041] In some embodiments, vertical rods 305 are fixed within the payload bay 300. These rods 305 provide support for the payload bay side panels 301, enhancing installation convenience and structural stability. For example, if the payload bay side panels 301 are composed of four flat panels, four vertical rods 305 can be fixed at the four corners of the payload bay 300 floor or the platform bay roof 103 to provide support for the four flat panels. Alternatively, the vertical rods 305 can be omitted, and the payload bay side panels 301 can be directly joined to the payload bay roof 302 and the platform bay roof 103 to form a stable payload bay 300 structure.

[0042] In some embodiments, the separation mechanism 202 can be a memory alloy pin puller, a separation nut, or an explosive bolt. The separation mechanism 202 is a critical component for separating or capturing satellites 201. Therefore, the separation mechanism 202 is determined based on a combination of considerations, including the number of satellites 201, the direction of separation, the arrangement of satellites 201, and cost. For example, if the payload bay 300 contains six satellites 201, each connected to a separate separation mechanism 202, a small memory alloy pin puller can be used.

[0043] The concealed parent-subsatellite structure provided in this embodiment is characterized by arranging a subsatellite assembly 200 in the payload cabin 300 of the parent satellite; the payload cabin 300 has two states, closed and open, and when the payload cabin top plate 302 is in the unfolded state, the subsatellite assembly 200 placed in the payload cabin 300 can be exposed; the subsatellite assembly 200 includes a subsatellite 201 and a separation mechanism 202, and the subsatellite 201 is arranged in the payload cabin 300 through the separation mechanism 202, thereby providing a good temperature environment and radiation resistance environment for the subsatellite 201 before separation, and the subsatellite 201 is hidden in the payload cabin before separation, and its actual use is not easy to be detected and discovered.

[0044] Example 2

[0045] Figure 3 This is a flow chart of a satellite separation control method according to an embodiment of the present invention, with reference to Figure 3 The method 300 shown can be applied to the concealed parent-daughter satellite structure provided in the first embodiment, and can also be applied to the control process of other related structures, including:

[0046] S310: When the sub-satellite 201 needs to be released, the control adjustment mechanism adjusts the spatial orientation of the sub-satellite structure so that the sub-satellite structure operates in a suitable posture.

[0047] When the sub-satellite 201 does not need to be released, the solar cell array on the top plate 302 of the payload cabin can keep sun orientation to maximize the energy acquisition through the solar cell array 306. But when the sub-satellite 201 needs to be released, due to the performance of the separation mechanism 202 and the requirement of the separation direction of the sub-satellite 201, the spatial orientation of the mother-daughter satellite structure needs to be adjusted so that the mother-daughter satellite structure can operate in a suitable posture, so that the subsequent sub-satellite 201 can separate in the preset direction to meet the task requirements of the sub-satellite 201.

[0048] S320, control the action of the payload cabin 300, so that the payload cabin 300 is in an unfolded state, and the sub-satellite 201 in the payload cabin 300 is exposed.

[0049] Before the sub-satellite 201 separates, the payload cabin 300 is in a closed state, and the payload cabin top plate 302 is pressed by the pressing member 304, such as a memory alloy expansion breaker, on the Z-axis flat plate, for example, during the satellite launch phase and before the independent flight task of the sub-satellite in orbit. The sub-satellite 201 is hidden in the closed payload cabin 200. When the sub-satellite 201 needs to be released, the action of the payload cabin 300 is controlled, that is, the action of the pressing member 304 is controlled, such as disconnecting the pressing member 304 or canceling the pressing force of the pressing member 304 on the payload cabin top plate 302. Under the action of the restoring force of the door shaft hinge 303, the payload cabin top plate 302 can rotate around the corresponding shaft (such as the Z-axis in the Figure 1 or Figure 2 payload cabin 300), and the payload cabin top plate 302 automatically restores to the unfolded state, exposing the sub-satellite 201 in the payload cabin 300, so that the sub-satellite 201 separates from the mother-daughter satellite structure.

[0050] S330, control the start of the separation mechanism 202, and the separation mechanism 202 separates the sub-satellite 201 along the preset sub-satellite separation direction.

[0051] Taking six sub-satellites 201 as an example, the separation mechanism 202 is controlled to start, and the six sub-satellites 201 are separated from the platform cabin top plate 103 through the unlocking of the small memory alloy puller separation mechanism 202, and fly out in the +X direction of the mother satellite under the action of the spring push rod of the small memory alloy puller separation mechanism 202 to carry out independent flight tasks.

[0052] The sub-satellite separation control method provided by the embodiment can accurately control the separation of the sub-satellite 201 according to the task requirements of the sub-satellite 201 when it needs to separate from the mother-daughter satellite structure, carry out independent flight tasks, and realize the function of carrying multiple sub-satellites 201 in a hidden manner by a launch vehicle and carrying out in-orbit multi-satellite cooperative tasks.

[0053] Embodiment three

[0054] Figure 4 is a structural schematic diagram of a sub-satellite separation control device according to an embodiment of the present application, andFigure 4 The device 400 can be applied to the hidden parent-child star structure provided in Embodiment One, and can also be applied to the control process of other related structures. The device 400 mainly includes:

[0055] The adjusting module 401 is configured to control the adjusting mechanism to adjust the spatial orientation of the parent-child star structure when the child star 201 needs to be released, so that the parent-child star structure operates in a suitable posture.

[0056] The unfolding module 402 is configured to control the load cabin 300 to move, so that the top plate 302 of the load cabin 300 is in an unfolded state, and the child star 201 in the load cabin 300 is exposed.

[0057] The releasing module 403 is configured to control the separating mechanism 202 to start, and the separating mechanism 202 separates the child star 201 along a preset child star separation direction.

[0058] Details of other operations performed by the modules in the embodiment can be referred to Embodiment Two, which will not be described here.

[0059] The child star separation control device provided in the embodiment can accurately control the child star 201 to separate when the child star 201 needs to be separated from the parent-child star structure according to the task requirement of the child star 201, and the child star 201 can carry out an independent flight task, which realizes the function of carrying multiple child stars 201 by one parent star in a hidden manner and carrying out an on-orbit multi-star cooperative task through one launch vehicle.

[0060] The application further provides an electronic device including a memory for storing programs or instructions executable by a processor, and the processor for executing the programs or instructions to realize the processes of the above-mentioned child star separation control method embodiments and achieve the same technical effects. To avoid repetition, details will not be described here.

[0061] Figure 5is a schematic diagram of an electronic device according to an embodiment of the present application. The electronic device 500 can include an internal communication bus 501, a processor 502, a read-only memory (ROM) 503, a random access memory (RAM) 504, and a communication port 505. When applied to a personal computer, the electronic device 500 can further include a hard disk 506. The internal communication bus 501 can enable data communication between components of the electronic device 500. The processor 502 can make judgments and issue prompts. In some embodiments, the processor 502 can be composed of one or more processors. The communication port 505 can enable data communication between the electronic device 500 and the outside. In some embodiments, the electronic device 500 can send and receive information and data from a network through the communication port 505. The electronic device 500 can further include different forms of program storage units and data storage units, such as the hard disk 506, the read-only memory (ROM) 503, and the random access memory (RAM) 504, which can store various data files used by the computer processing and / or communication, and possible programs or instructions executed by the processor 502. The results processed by the processor 502 are transmitted to a user device through the communication port 505 and displayed on a user interface.

[0062] The embodiment of the present application further provides a readable storage medium, and the readable storage medium stores programs or instructions, which are executed by a processor to realize each process of the above-mentioned sub-star separation control method embodiment and achieve the same technical effects. To avoid repetition, details are not described herein.

[0063] The computer readable medium can include a propagated data signal with computer program code embodied therein, for example, in baseband or as part of a carrier wave. Such a propagated signal can take any of a variety of forms, including but not limited to electro-magnetic, optical, or any suitable combination thereof. Computer readable medium can be any medium that can be read by a computer, including any suitable combination of optical, electrical, or magnetic storage mediums. The program code embodied on the computer readable medium can be transmitted using any appropriate medium, including but not limited to wireless, wire line, optical fiber cable, RF, or any suitable combination thereof.

[0064] The processor is the processor in the electronic device in the above-mentioned embodiments. The readable storage medium includes a computer readable storage medium, such as a computer read-only memory (ROM), a random access memory (RAM), a magnetic disk or an optical disk, etc.

[0065] It is apparent that the foregoing disclosure of the application is merely exemplary in nature and that various modifications and improvements to the embodiments specifically disclosed herein can readily occur to those skilled in the art. The novel methods and compositions of matter of this application are not limited to the embodiments described but only by the claims which follow.

[0066] In addition, some of the embodiments of the present application have been described as processes that are depicted as a flow diagram or series of interconnected blocks. Although each can describe the operations as a sequential process, many of the operations can be performed in parallel or concurrently. In addition, the order of the operations can be rearranged. A process can have additional steps not included in the figure. Furthermore, embodiments of the methods can be implemented by hardware, software, firmware, middleware, microcode, hardware description languages, or any combination thereof. When the method is implemented at least partially in software, the software code can be executed by a processor or controller. In one embodiment, a processor or controller can be specifically designed to execute the software code. Alternatively, a processor or controller can be a commercially available processor or controller that executes the software code.

[0067] It is also important to note that while the above describes example embodiments of the application, these descriptions should not be viewed in terms of limiting the scope of the application. The disclosures of the various publications, articles and patents, referred to or cited to herein, are hereby incorporated by reference in their entirety into the present document.

[0068] While the application has been described with reference to the currently preferred embodiments, those skilled in the art will recognize various changes, modifications, and improvements that can be made thereto without departing from the spirit and scope of the application. Accordingly, it is intended, therefore, to be limited only by the scope of the appended claims.

Claims

1. A concealed parent-daughter satellite structure, characterized in that: include: A mother satellite and a sub-satellite assembly (200), wherein the mother satellite comprises a platform cabin (100) and a payload cabin (300), the payload cabin (300) is connected to the platform cabin (100), and the sub-satellite assembly (200) is arranged in the payload cabin (300); The payload cabin (300) has two states: closed and open. When the payload cabin top plate (302) is in the unfolded state, the satellite assembly (200) placed in the payload cabin (300) can be exposed. The bottom of the payload cabin (300) is the platform cabin top plate (103), the side is the payload cabin side plate (301), and the top is the payload cabin top plate (302). The platform cabin top plate (103) and the payload cabin side plate (301) are fixed plates, and the payload cabin top plate (302) is a movable plate that can be opened to allow the payload cabin to be opened. The load cabin (300) is in an unsealed state; the satellite (201) is arranged on the platform cabin top plate (103) via a separation mechanism (202); the load cabin side plate (301) is composed of four flat plates, and the load cabin top plate (302) is connected to a flat plate in the load cabin side plate (301) via a door shaft hinge (303); a solar cell array (306) is also fixed on the load cabin top plate (302), and the solar cell array (306) is fixed on a flat plate hinged to the load cabin top plate (302); The sub-satellite assembly (200) comprises a sub-satellite (201) and a separation mechanism (202), and the sub-satellite (201) is arranged in the payload cabin (300) via the separation mechanism (202).

2. The concealed parent-daughter satellite structure according to claim 1, characterized in that: The load compartment top plate (302) is connected to one side of the load compartment side plate (301) via a door shaft hinge (303), and the load compartment top plate (302) is connected to the other side of the load compartment side plate (301) via a pressing member (304).

3. The concealed parent-daughter satellite structure according to claim 2, characterized in that: The door shaft hinge (303) is a door shaft hinge, and the pressing piece (304) is a memory alloy expander.

4. The concealed parent-daughter satellite structure according to claim 1, wherein: A vertical rod (305) is fixed in the load compartment (300), and the vertical rod (305) is used to provide support for the load compartment side panel (301).

5. The concealed parent-daughter satellite structure according to claim 1, wherein: The separation mechanism (202) is a memory alloy pin puller separation mechanism, a separation nut type separation mechanism, or an explosive bolt type separation mechanism.

6. A satellite separation control method, characterized in that: Applicable to the concealed parent-daughter satellite structure according to any one of claims 1 to 5, comprising: When the sub-satellite (201) needs to be released, the control adjustment mechanism adjusts the spatial orientation of the sub-satellite structure so that the sub-satellite structure operates in a suitable posture; Controlling the movement of the payload cabin (300) to place the payload cabin top plate (302) in an unfolded state, exposing the satellite (201) in the payload cabin (300); The separation mechanism (202) is controlled to start, and the separation mechanism (202) separates the sub-satellite (201) along a preset sub-satellite separation direction.

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