Spacecraft operations system with fly-along chaperone satellite

Abstract

The present application relates to the technical field of space debris protection, and more particularly to a flying escort small satellite and a spacecraft operation system, comprising a first cabin body, a second cabin body, a third cabin body, a first protection assembly, a second protection assembly, a third protection assembly and a fourth protection assembly, which can perform both inspection and protection tasks, and improve the utilization degree of the flying escort small satellite. When space debris with a size of 1cm-10cm attacks, the second cabin body is extended out of the third accommodating cavity of the first cabin body, the third cabin body is extended out of the fifth accommodating cavity of the second cabin body, the first protection assembly is extended out of the first accommodating cavity, the second protection assembly is extended out of the second accommodating cavity, the third protection assembly is extended out of the fourth accommodating cavity, and the fourth protection assembly is extended out of the sixth accommodating cavity, thereby forming a multi-level defense barrier, playing a multi-level interception role on the space debris with a size of 1cm-10cm, and maximizing the fragmentation and kinetic energy dissipation of the space debris.

Description

Technical Field

[0001] This invention relates to the field of space debris protection technology, and in particular to a companion escort satellite and spacecraft operation system. Background Technology

[0002] In recent years, the space environment has deteriorated significantly. The number of space debris measuring 1cm-10cm has exceeded 750,000, making this size range the most dangerous type of space debris to spacecraft. For space debris smaller than 1cm, effective protection can be achieved by adding protective structures to spacecraft. For space debris larger than 10cm, it can be tracked and cataloged through space-based monitoring systems, and spacecraft can avoid it through orbital maneuvers. However, for space debris measuring 1cm-10cm, due to its larger size and impact kinetic energy compared to millimeter-sized debris, neither adding protective structures to spacecraft nor effectively tracking and cataloging it through space-based monitoring systems can provide adequate protection. Therefore, it has become the most threatening space debris to spacecraft currently in orbit.

[0003] Therefore, how to deal with the impact risk of space debris with a size of 1-10cm has become a technical problem that urgently needs to be solved by those skilled in the art. Summary of the Invention

[0004] This invention provides a companion escort satellite and spacecraft operation system to address the problem of how to deal with the impact risk of space debris with a size of 1-10cm.

[0005] On one hand, the present invention provides a companion escort microsatellite, comprising:

[0006] The first-stage hull has a collision-facing surface at one end, with a first and second accommodating cavity formed on its sidewalls, and a third accommodating cavity formed at the other end.

[0007] The secondary compartment is located within the third accommodating cavity and can extend out of or retract into the third accommodating cavity; a fourth accommodating cavity is formed on the side wall of the secondary compartment, and a fifth accommodating cavity is formed inside it;

[0008] The third-level compartment is located within the fifth accommodating cavity and can extend out of or retract into the fifth accommodating cavity; a sixth accommodating cavity is formed on the side wall of the third-level compartment.

[0009] A primary protective component is located within the first receiving cavity and can be deployed to extend out of the first receiving cavity;

[0010] The secondary protection component is located inside the second receiving cavity and can be deployed to extend out of the second receiving cavity;

[0011] The third-level protective assembly is located inside the fourth receiving cavity and can be deployed to extend out of the fourth receiving cavity;

[0012] The Level 4 protection component is located within the sixth containment cavity and can be deployed to extend out of the sixth containment cavity.

[0013] In some embodiments, the primary protection component includes:

[0014] The first support is capable of expanding to extend out of the first receiving cavity;

[0015] The first rigid protective layer is disposed on the side of the first support body closest to the impact surface;

[0016] The first flexible protective layer is disposed on the side of the first support body away from the impact surface;

[0017] The structure of the first-level protection component is the same as that of the second-level, third-level, and fourth-level protection components.

[0018] In some embodiments, it also includes:

[0019] The frontal impact protection component, installed on the frontal impact surface, is capable of expansion.

[0020] In some embodiments, the collision protection component includes:

[0021] The second support structure, installed on the impact surface, is capable of expansion.

[0022] The second rigid protective layer is disposed on the side of the second support body away from the impact surface;

[0023] The second flexible protective layer is multi-layered and is evenly distributed within the second support body along the expansion direction of the second support body.

[0024] In some embodiments, it also includes:

[0025] The first buffer layer is installed inside the third receiving cavity;

[0026] The second buffer layer is installed at the end of the secondary compartment near the primary compartment, forming a first buffer cavity with the first buffer layer;

[0027] The third buffer layer is installed at one end of the third-level hull near the second-level hull, forming a second buffer cavity with the second buffer layer.

[0028] In some embodiments, it also includes:

[0029] The solar panel is located inside the first receiving cavity and can be deployed to extend out of the first receiving cavity.

[0030] In some embodiments, it also includes:

[0031] The first propulsion module is installed inside the first-stage compartment;

[0032] The attitude control module is installed inside the first-stage cabin.

[0033] The first communication module is installed in the first stage compartment and is connected to the first propulsion module and the attitude control module respectively.

[0034] The power supply module is installed inside the first stage compartment and is connected to the first propulsion module, attitude control module, and first communication module, respectively.

[0035] In some embodiments, it also includes:

[0036] The second propulsion module is installed inside the third-stage compartment;

[0037] The inspection module is installed inside the level 3 compartment;

[0038] The second communication module is installed in the third-stage compartment and is connected to the second propulsion module.

[0039] On the other hand, the present invention also provides a spacecraft operation system, including a spacecraft and a companion escort microsatellite;

[0040] The spacecraft is equipped with a detection and sensing module.

[0041] In some embodiments, the spacecraft includes:

[0042] Spacecraft body;

[0043] Release mechanism, installed on the spacecraft body, is used to release the escort satellite;

[0044] The recovery mechanism, installed on the spacecraft itself, is used to recover the accompanying escort satellites.

[0045] The beneficial effects of this invention are as follows: The accompanying escort microsatellite of this invention, by configuring a primary, secondary, and tertiary module, primary, secondary, tertiary, and quaternary protection components, an impact protection component, and solar panels, can perform both inspection and protection tasks, improving the utilization of the accompanying escort microsatellite and demonstrating high application prospects. When performing an inspection task, the tertiary module is located within the fifth cavity of the secondary module, while the secondary module is located within the third cavity of the primary module. The solar panels and primary protection components extend out of the first cavity, while the secondary protection components remain stationary within the second cavity, the tertiary protection components remain stationary within the fourth cavity, and the quaternary protection components remain stationary within the sixth cavity. The solar panels generate electricity using sunlight to power the accompanying escort microsatellite. When space debris of 1cm-10cm in size approaches, the accompanying escort microsatellite begins its protection mission. During this process, the second-stage module extends out of the third containment cavity of the first-stage module, the third-stage module extends out of the fifth containment cavity of the second-stage module, the solar panels and first-stage protection components deploy and extend out of the first containment cavity, the second-stage protection components deploy and extend out of the second containment cavity, the third-stage protection components deploy and extend out of the fourth containment cavity, and the fourth-stage protection components deploy and extend out of the sixth containment cavity. The impact protection components expand. The impact protection components are used to withstand the impact of space debris moving towards the impact surface, dissipate the kinetic energy of the space debris, protect the main structure of the escort satellite, and extend the service life of the escort satellite's main structure. The deployed first-stage, second-stage, third-stage, and fourth-stage protection components constitute a multi-level defense barrier, providing multi-level interception of space debris ranging from 1cm to 10cm in size, maximizing the fragmentation of space debris and dissipating its kinetic energy. Overall, when performing protection missions, it can effectively cope with the impact of space debris ranging from 1cm to 10cm in size. Attached Figure Description

[0046] Figure 1 This is a schematic diagram of the structure of some specific embodiments of the escort and protection microsatellite of the present invention;

[0047] Figure 2 yes Figure 1 The diagram shown illustrates the escort satellite in inspection mode.

[0048] Figure 3 yes Figure 1 The diagram shown illustrates the escort satellite extending its cabin.

[0049] Figure 4 yes Figure 1 The diagram shown illustrates the escort satellite in protective mode.

[0050] In the attached diagram, 110 is the primary compartment; 111 is the first receiving cavity; 112 is the second receiving cavity; 113 is the third receiving cavity; 120 is the secondary compartment; 121 is the fourth receiving cavity; 122 is the fifth receiving cavity; 130 is the tertiary compartment; 131 is the sixth receiving cavity; 140 is the primary protective assembly; 141 is the first support structure; 142 is the first rigid protective layer; 143 is the first flexible protective layer; 150 is the secondary protective assembly; 160 is the tertiary protective assembly; and 170 is the quaternary protective assembly. ; 180. Collision protection assembly; 181. Second support body; 182. Second rigid protective layer; 183. Second flexible protective layer; 191. First buffer layer; 192. Second buffer layer; 193. Third buffer layer; 194. Solar array; 1951. First propulsion module; 1952. Second propulsion module; 196. Attitude control module; 1971. First communication module; 1972. Second communication module; 198. Power supply module; 199. Inspection module; 200. Spacecraft. Detailed Implementation

[0051] The technical solution of the present invention will be clearly and completely described below with reference to the embodiments. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0052] As described in the background section, space debris measuring 1-10 cm in size poses a significant threat to long-term spacecraft operations due to its larger size and impact kinetic energy compared to millimeter-sized debris. This makes it impossible to achieve effective protection by adding protective structures to spacecraft (with a maximum protection size of 1.5 cm), and it is also difficult for space-based monitoring systems to effectively track and catalog it. Therefore, how to address the impact risk of space debris measuring 1-10 cm has become a pressing technical problem for those skilled in the art.

[0053] To solve the above problems, refer to Figure 1 , Figure 2 , Figure 3 and Figure 4On one hand, the present invention provides a companion escort microsatellite, comprising a primary module 110, a secondary module 120, a tertiary module 130, a primary protection assembly 140, a secondary protection assembly 150, a tertiary protection assembly 160, a quaternary protection assembly 170, a collision protection assembly 180, and a solar array 194. One end face of the primary module 110 is the collision face. A first receiving cavity 111 and a second receiving cavity 112 are formed on the side wall of the primary module 110, and a third receiving cavity 113 is formed at the other end. The secondary module 120 is disposed within the third receiving cavity 113 and can extend out of or retract into the third receiving cavity 113. A fourth receiving cavity 121 is formed on the side wall of the secondary module 120. A fifth receiving cavity 122 is formed inside the secondary module 120. The tertiary module 130 is disposed within the fifth receiving cavity 122 and can extend out of or retract into the fifth receiving cavity 122. A sixth receiving cavity 131 is formed on the side wall of the third-level hull 130. A first-level protection assembly 140 is disposed within the first receiving cavity 111 and can be deployed to extend out of the first receiving cavity 111. A second-level protection assembly 150 is disposed within the second receiving cavity 112 and can be deployed to extend out of the second receiving cavity 112. A third-level protection assembly 160 is disposed within the fourth receiving cavity 121 and can be deployed to extend out of the fourth receiving cavity 121. A fourth-level protection assembly 170 is disposed within the sixth receiving cavity 131 and can be deployed to extend out of the sixth receiving cavity 131. A collision protection assembly 180 is mounted on the collision surface and is capable of expansion. A solar panel 194 is disposed within the first receiving cavity 111 and can be deployed to extend out of the first receiving cavity 111.

[0054] The working process and principle of the escort satellite are as follows:

[0055] The escort satellite accompanied the spacecraft 200 during its flight. It can perform both inspection and protection missions, increasing the utilization of the escort satellite and demonstrating high application potential. When performing inspection missions, such as... Figure 2 As shown, the third-stage module 130 is located within the fifth cavity 122 of the second-stage module 120, while the second-stage module 120 is located within the third cavity 113 of the first-stage module 110. The solar array 194 and the first-stage protection assembly 140 extend out of the first cavity 111, while the second-stage protection assembly 150 remains stationary within the second cavity 112, the third-stage protection assembly 160 remains stationary within the fourth cavity 121, and the fourth-stage protection assembly 170 remains stationary within the sixth cavity 131. The solar array 194 generates electricity using sunlight to power the escort satellite. When space debris of 1cm-10cm in size approaches, the escort satellite begins its protective mission. During this process, such as... Figure 3 and Figure 4As shown, firstly, the secondary module 120 extends out of the third containment cavity 113 of the primary module 110. Then, the tertiary module 130 extends out of the fifth containment cavity 122 of the secondary module 120. Subsequently, the solar panels 194 and the primary protection assembly 140 deploy and extend out of the first containment cavity 111, the secondary protection assembly 150 deploys and extends out of the second containment cavity 112, the tertiary protection assembly 160 deploys and extends out of the fourth containment cavity 121, the quaternary protection assembly 170 deploys and extends out of the sixth containment cavity 131, and the impact protection assembly 180 expands. Figure 4 The direction of the center arrow indicates the direction of space debris movement. The impact protection assembly 180 is used to withstand impacts from space debris moving towards the impact surface, dissipating the kinetic energy of the space debris, protecting the main structure of the escort satellite, and extending the service life of the escort satellite's main structure. The deployed primary protection assembly 140, secondary protection assembly 150, tertiary protection assembly 160, and quaternary protection assembly 170 form a multi-level defense barrier, providing multi-stage interception of space debris ranging from 1cm to 10cm in size, maximizing the fragmentation of space debris and dissipating its kinetic energy. Overall, when performing protection missions, it can effectively cope with impacts from space debris ranging from 1 to 10cm in size.

[0056] Preferably, there are two first receiving cavities 111, symmetrically arranged on opposite sides of the first-stage compartment 110. There are also two second receiving cavities 112, symmetrically arranged on opposite sides of the first-stage compartment 110. There are two fourth receiving cavities 121, symmetrically arranged on opposite sides of the second-stage compartment 120. There are also two sixth receiving cavities 131, symmetrically arranged on opposite sides of the third-stage compartment 130. There are two solar panels 194, corresponding one-to-one with the two first receiving cavities 111. There are two first-stage protection components 140, corresponding one-to-one with the two first receiving cavities 111. There are two second-stage protection components 150, corresponding one-to-one with the two second receiving cavities 112. There are two third-stage protection components 160, corresponding one-to-one with the two fourth receiving cavities 121. There are two fourth-stage protection components 170, corresponding one-to-one with the two sixth receiving cavities 131. This design ensures a larger power generation area and debris interception area, which is beneficial for improving power generation and interception effectiveness.

[0057] Specifically, in the example, such as Figure 2 and Figure 4As shown, the primary protection component 140 includes a first support 141, a first rigid protective layer 142, and a first flexible protective layer 143. The first support 141 is capable of expansion to extend beyond the first receiving cavity 111. It should be noted that the first support 141 has multiple partitions to divide its interior into multiple filling cavities. Each filling cavity is filled with a compressible porous material. During launch, the first support 141 is compressed into a flat shape to reduce launch difficulty and cost. After orbit insertion, the first support 141 can expand and unfold. The first rigid protective layer 142 is disposed on the side of the first support 141 closest to the impact surface. The first rigid protective layer 142 is made of high-performance protective material, possessing certain strength and hardness, and exhibiting good impact resistance. The first flexible protective layer 143 is disposed on the side of the first support 141 furthest from the impact surface. The first flexible protective layer 143 is made of high-performance protective material, possessing certain flexibility, and exhibiting good interception capability. The structure of the primary protection component 140 is the same as that of the secondary protection component 150, the tertiary protection component 160, and the quaternary protection component 170. When deployed, the primary protection component 140, the secondary protection component 150, the tertiary protection component 160, and the quaternary protection component 170 form a multi-level defense barrier, providing multi-level interception of spatial debris ranging in size from 1cm to 10cm.

[0058] It should be noted that the deployed solar array 194 is located on the side of the deployed first rigid protective layer 142 away from the first support 141, so as to ensure that the solar array 194 can fully receive solar energy.

[0059] Specifically, in the example, such as Figure 3 and Figure 4 As shown, the impact protection assembly 180 includes a second support body 181, a second rigid protective layer 182, and multiple layers of second flexible protective layers 183. The second support body 181 is mounted on the impact surface and can expand in the direction away from the impact surface. It should be noted that the second support body 181 has a filling cavity filled with a compressible porous material. During launch, the second support body 181 is compressed into a flat shape to reduce launch difficulty and cost. After entering orbit, the second support body 181 can expand and unfold, multiplying the protective spacing. The second rigid protective layer 182 is disposed on the side of the second support body 181 away from the impact surface. The second rigid protective layer 182 is made of high-performance protective material, possessing certain strength and hardness, and exhibiting good impact resistance. The multiple layers of second flexible protective layers 183 are uniformly distributed within the second support body 181 along the expansion direction of the second support body 181. Each layer of the second flexible protective layer 183 is made of high-performance protective material and possesses a certain degree of flexibility. The multiple layers of second flexible protective layers 183 have multi-level interception capabilities.

[0060] It should be noted that because space debris measuring 1cm-10cm has high kinetic energy and destructive power, in order to prevent damage to the main structure of the escort satellite, therefore, Figure 4 As shown, the escort satellite also includes a first buffer layer 191, a second buffer layer 192, and a third buffer layer 193. The first buffer layer 191 is installed within the third receiving cavity 113. The second buffer layer 192 is installed at the end of the second-stage module 120 near the first-stage module 110, forming a first buffer cavity with the first buffer layer 191. The third buffer layer 193 is installed at the end of the third-stage module 130 near the second-stage module 120, forming a second buffer cavity with the second buffer layer 192. The first buffer layer 191, the second buffer layer 192, and the third buffer layer 193 are made of high-performance protective materials. The deployed collision protection assembly 180, the first buffer layer 191, the first buffer cavity, the second buffer layer 192, the second buffer cavity, and the third buffer layer 193 constitute an ultra-large spacing protection system, which significantly increases the protection spacing, further enhances the protection capability, and achieves protection for the main structure of the escort satellite, preventing the complete failure of the main structure of the escort satellite.

[0061] Specifically, in the example, such as Figure 3As shown, the escort satellite also includes a first propulsion module 1951, an attitude control module 196, a first communication module 1971, a power supply module 198, a second propulsion module 1952, an inspection module 199, and a second communication module 1972. In non-emergency situations, the first propulsion module 1951 handles orbital maneuvers. The attitude control module 196 provides attitude control after normal inspections and emergency protection commands. The first communication module 1971 provides normal communication with the spacecraft 200 in non-emergency situations. Under extreme conditions, such as space debris impacting the escort satellite and causing damage to its main structure, the second communication module 1972 ensures normal communication between the escort satellite and the spacecraft 200, facilitating recovery. The second propulsion module 1952 performs emergency orbital maneuvers in the event of dangerous space debris impacts and assists the escort satellite in maneuvering for recovery under extreme conditions. The first propulsion module 1951, attitude control module 196, first communication module 1971, and power supply module 198 are installed within the first-stage cabin 110. The first communication module 1971 is communicatively connected to the first propulsion module 1951, attitude control module 196, inspection module 199, and the communication module on spacecraft 200, enabling data transmission. The power supply module 198 is electrically connected to the first propulsion module 1951, attitude control module 196, first communication module 1971, and inspection module 199, providing power to these modules. During inspection missions, the first communication module 1971, first propulsion module 1951, attitude control module 196, and inspection module 199 participate in the operation. The second propulsion module 1952, inspection module 199, and second communication module 1972 are installed within the third-stage hull 130 to keep them as far away from the impact surface as possible, thus protecting them. In extreme conditions, such as if the escort satellite is damaged in a collision, the second propulsion module 1952 and second communication module 1972 can be used as emergency modules. The second communication module 1972 communicates with both the second propulsion module 1952 and the communication module on spacecraft 200, enabling data transmission.

[0062] On the other hand, the present invention also provides a spacecraft 200 operation system, including the spacecraft 200 and a companion escort microsatellite. A detection and sensing module is installed on the spacecraft 200 to detect the presence of space debris ranging from 1cm to 10cm in size. When space debris of 1cm to 10cm is detected, the companion escort microsatellite is controlled to quickly reach the corresponding position and begin performing its protective mission, thus avoiding a collision due to insufficient warning time preventing the spacecraft 200 from changing its orbit in time. During the period without space debris, the companion escort microsatellite inspects important parts of the spacecraft 200's exterior.

[0063] It should be noted that Spacecraft 200 can be a satellite, a manned spacecraft, or a cargo spacecraft, etc. For manned spacecraft, the use of escort satellites greatly ensures the safety of personnel.

[0064] Specifically, in the exemplary example, spacecraft 200 includes a spacecraft body, a release mechanism, and a recovery mechanism. The release mechanism, mounted on the spacecraft body, is used to release the accompanying escort microsatellite. The recovery mechanism, mounted on the spacecraft body, is used to recover the accompanying escort microsatellite.

[0065] The working process and principle of the Spacecraft 200 operation system are as follows:

[0066] The escort satellite or its components are transported to the manned spacecraft by a cargo spacecraft for in-orbit assembly, functional testing, and release. The escort satellite possesses communication, propulsion, inspection, and protection functions. During in-orbit release, spacecraft 200 releases the assembled and functionally tested escort satellite via a release mechanism. With the aid of the first propulsion module 1951 and attitude control module 196, the escort satellite performs its escort function. Under normal circumstances, the escort satellite performs routine inspections of spacecraft 200's daily operational health. During this process, the escort satellite conducts a comprehensive inspection of the health status of key areas on the outer surface of spacecraft 200. The inspection function is primarily implemented through the escort satellite's inspection module 199. Therefore, the inspection module 199 includes a high-resolution camera and a data storage and transmission unit. The high-resolution camera captures images of key areas during inspections to obtain outer surface images, which are then temporarily stored and transmitted to spacecraft 200 via the data storage and transmission unit. The analysis and communication system of Spacecraft 200 receives information and conducts health status analysis to perform routine health checks on Spacecraft 200. When the detection and sensing module of Spacecraft 200 detects space debris ranging from 1cm to 10cm in size, it sends information such as the location and possible impact direction of the dangerous space debris to the escort satellite via the analysis and communication system. Based on the possible warning time, it also sends a command to the escort satellite to activate the emergency propulsion mode, enabling the escort satellite to quickly reach the danger zone and implement space debris protection. During dangerous debris protection, the protection distance reaches the meter level. After the escort satellite completes its inspection or protection mission, if recovery and maintenance are required, Spacecraft 200 sends a command to the escort satellite via the analysis and communication system. This command is received by the escort satellite's first communication module 1971 / second communication module 1972, which then activates the first propulsion module 1951 / second propulsion module 1952 to complete the recovery operation. Astronauts then carry out inspection and maintenance work. Under extreme conditions, when dangerous space debris impacts the small satellite and causes severe structural damage, the emergency communication module and emergency propulsion module located in the third-stage extension body furthest from the impact surface are activated to complete emergency communication and orbital maneuvers to achieve recovery, thus preventing the satellite from becoming uncontrollable space debris.

[0067] Preferably, the release mechanism can be a release gripper.

[0068] Preferably, the recycling mechanism can be a recycling cable.

[0069] In the description of this invention, it should be understood that the terms "center," "longitudinal," "lateral," "length," "width," "thickness," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," "clockwise," "counterclockwise," "axial," "radial," and "circumferential" indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are used only for the convenience of describing this invention and simplifying the description, and are not intended to indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this invention.

[0070] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one of that feature. In the description of this invention, "a plurality of" means at least two, such as two, three, etc., unless otherwise explicitly specified.

[0071] In this invention, unless otherwise explicitly specified and limited, the terms "installation," "connection," "linking," and "fixing," etc., should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part; they can refer to a mechanical connection, an electrical connection, or a connection that allows communication between them; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components, unless otherwise explicitly limited. Those skilled in the art can understand the specific meaning of the above terms in this invention according to the specific circumstances.

[0072] In this invention, the terms "one embodiment," "some embodiments," "example," "specific example," or "some examples," etc., refer to a specific feature, structure, material, or characteristic described in connection with that embodiment or example, which is included in at least one embodiment or example of the invention. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples. Moreover, without contradiction, those skilled in the art can combine and integrate the different embodiments or examples described in this specification, as well as the features of different embodiments or examples.

[0073] Although embodiments of the present invention have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting the present invention. Those skilled in the art can make changes, modifications, substitutions and variations to the above embodiments within the scope of the present invention.

Claims

1. A companion / escort microsatellite, characterized in that, include: The first-stage hull has a collision-facing surface at one end, with a first and second accommodating cavity formed on its sidewalls, and a third accommodating cavity formed at the other end. The secondary compartment is located within the third accommodating cavity and can extend out of or retract into the third accommodating cavity; a fourth accommodating cavity is formed on the side wall of the secondary compartment, and a fifth accommodating cavity is formed inside it; A third-level compartment is disposed within the fifth accommodating cavity and can extend out of or retract into the fifth accommodating cavity; a sixth accommodating cavity is formed on the side wall of the third-level compartment; A primary protective component is disposed within the first receiving cavity and can be deployed to extend out of the first receiving cavity; A secondary protective component is disposed within the second receiving cavity and can be deployed to extend out of the second receiving cavity; A three-level protective assembly is disposed within the fourth accommodating cavity and can be deployed to extend out of the fourth accommodating cavity; The fourth-level protection component is located inside the sixth accommodating cavity and can be deployed to extend out of the sixth accommodating cavity.

2. The escort satellite according to claim 1, characterized in that, The primary protection component includes: The first support is capable of expanding to extend out of the first receiving cavity; A first rigid protective layer is disposed on the side of the first support body near the impact surface; A first flexible protective layer is disposed on the side of the first support body away from the impact surface; The structure of the first-level protection component is the same as that of the second-level protection component, the third-level protection component, and the fourth-level protection component.

3. The escort satellite according to claim 1, characterized in that, Also includes: The frontal impact protection component, installed on the frontal impact surface, is capable of expansion.

4. The escort satellite according to claim 3, characterized in that, The collision protection assembly includes: The second support, installed on the impact surface, is capable of expansion. A second rigid protective layer is disposed on the side of the second support body away from the impact surface; The second flexible protective layer is multi-layered and is evenly distributed within the second support body along the expansion direction of the second support body.

5. The escort satellite according to any one of claims 1 to 4, characterized in that, Also includes: The first buffer layer is installed inside the third receiving cavity; The second buffer layer is installed at one end of the secondary compartment near the primary compartment, forming a first buffer cavity with the first buffer layer; The third buffer layer is installed at one end of the third-level cabin near the second-level cabin, forming a second buffer cavity between the third buffer layer and the second buffer layer.

6. The escort satellite according to any one of claims 1 to 4, characterized in that, Also includes: The solar panel is located inside the first receiving cavity and can be deployed to extend out of the first receiving cavity.

7. The escort satellite according to any one of claims 1 to 4, characterized in that, Also includes: The first propulsion module is installed inside the first-stage compartment; The attitude control module is installed inside the first-stage cabin; The first communication module is installed in the first-stage cabin and is connected to the first propulsion module and the attitude control module respectively. The power supply module is installed inside the first-stage cabin and is connected to the first propulsion module, the attitude control module, and the first communication module, respectively.

8. The escort satellite according to claim 7, characterized in that, Also includes: The second propulsion module is installed inside the third-level cabin; The inspection module is installed inside the third-level cabin; The second communication module is installed inside the third-level cabin and is connected to the second propulsion module.

9. A spacecraft operation system, characterized in that, Includes spacecraft and escort microsatellites as described in any one of claims 1 to 8; The spacecraft is equipped with a detection and sensing module.

10. The spacecraft operation system according to claim 9, characterized in that, The spacecraft includes: Spacecraft body; A release mechanism, installed on the spacecraft body, is used to release the escort satellite; A recovery mechanism, installed on the spacecraft body, is used to recover the escort satellite.

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