Flying accompanying guard small satellite and spacecraft operation system

Abstract

The invention relates to the technical field of space debris protection, in particular to an accompanying guard moonlet and spacecraft operation system which comprises a first-stage cabin, a second-stage cabin, a third-stage cabin, a first-stage protection assembly, a second-stage protection assembly, a third-stage protection assembly and a fourth-stage protection assembly. And the utilization degree of the accompanying guard moonlet is improved. When space debris with the size of 1-10 cm comes, the second-level cabin body stretches out of a third containing cavity of the first-level cabin body, the third-level cabin body stretches out of a fifth containing cavity of the second-level cabin body, the first-level protection assembly stretches out of a first containing cavity after being unfolded, the second-level protection assembly stretches out of a second containing cavity after being unfolded, and the third-level protection assembly stretches out of a fourth containing cavity after being unfolded. And the fourth-stage protection assembly is unfolded to extend out of a sixth containing cavity, a multi-stage defense barrier is formed, the multi-stage interception effect on space debris with the size being 1 cm to 10 cm is achieved, the space debris is broken to the maximum extent, and kinetic energy of the space debris is dissipated.

Description

Technical Field

[0001] The present invention relates to the field of space debris protection technology, and in particular to a small satellite escort and spacecraft operation system. Background Art

[0002] In recent years, the space environment has been deteriorating. The number of space debris with a size of 1cm-10cm has exceeded 750,000, and debris in this size range has become the space debris that poses the greatest threat to spacecraft. For space debris with a size smaller than 1cm, effective protection can be achieved by adding protective structures to spacecraft. For space debris with a size larger than 10cm, they can be tracked and catalogued through ground-based monitoring systems, and spacecraft can take orbital maneuvers to avoid them. As for space debris with a size of 1cm-10cm, due to its larger size and impact kinetic energy compared to millimeter-level space debris, it is impossible to achieve protection by adding protective structures to spacecraft, and it is difficult to be effectively tracked and catalogued by ground-based monitoring systems. Instead, it has become the space debris that currently poses the greatest threat to spacecraft in orbit.

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

[0004] The present invention provides a small satellite escort and a spacecraft operation system, which are used to solve the problem of how to deal with the impact risk of space debris with a size of 1-10 cm.

[0005] In one aspect, the present invention provides a companion escort small satellite, comprising:

[0006] The first-stage cabin has a collision surface at one end, a first accommodating cavity and a second accommodating cavity formed on the side wall, and a third accommodating cavity formed at the other end;

[0007] The secondary cabin is arranged in the third accommodating cavity and can be extended out of the third accommodating cavity or retracted into the third accommodating cavity; a fourth accommodating cavity is formed on the side wall of the secondary cabin, and a fifth accommodating cavity is formed inside the secondary cabin;

[0008] The third-stage cabin body is arranged in the fifth accommodating cavity and can extend out of the fifth accommodating cavity or retract into the fifth accommodating cavity; a sixth accommodating cavity is formed on the side wall of the third-stage cabin body;

[0009] A primary protection component is disposed in the first accommodating cavity and can be deployed to protrude out of the first accommodating cavity;

[0010] A secondary protection component is disposed in the second accommodating cavity and can be unfolded to protrude out of the second accommodating cavity;

[0011] A third-level protection component is disposed in the fourth accommodation cavity and can be deployed to extend out of the fourth accommodation cavity;

[0012] The fourth-level protection component is arranged in the sixth accommodating cavity and can be unfolded to extend out of the sixth accommodating cavity.

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

[0014] A first support body capable of expanding to protrude out of the first accommodating cavity;

[0015] A first rigid protective layer is provided on a side surface of the first support body close to the collision surface;

[0016] A first flexible protective layer is provided on a side surface of the first support body away from the collision surface;

[0017] The structures of the first-level protection component are the same as those of the second-level protection component, the third-level protection component, and the fourth-level protection component.

[0018] In some embodiments, it also includes:

[0019] The collision protection component is installed on the collision surface and can expand.

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

[0021] A second support body is mounted on the collision surface and is capable of expanding;

[0022] A second rigid protective layer is provided on a side surface of the second support body away from the collision surface;

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

[0024] In some embodiments, it also includes:

[0025] A first buffer layer is installed in the third accommodating cavity;

[0026] The second buffer layer is installed at one end of the secondary cabin body close to the primary cabin body, and forms a first buffer cavity between the second buffer layer and the first buffer layer;

[0027] The third buffer layer is installed at one end of the third-stage cabin body close to the second-stage cabin body, and forms a second buffer cavity between the third buffer layer and the second buffer layer.

[0028] In some embodiments, it also includes:

[0029] The solar wing is arranged in the first accommodating cavity and can be unfolded to protrude out of the first accommodating cavity.

[0030] In some embodiments, it also includes:

[0031] The first propulsion module is installed in the first-stage cabin;

[0032] The attitude control module is installed in the first-level cabin;

[0033] 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;

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

[0035] In some embodiments, it also includes:

[0036] The second propulsion module is installed in the third-stage cabin;

[0037] Inspection module, installed in the third-level cabin;

[0038] The second communication module is installed in the third-stage cabin and 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 small satellite;

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

[0041] In some of these embodiments, the spacecraft comprises:

[0042] Spacecraft body;

[0043] The release mechanism is installed on the spacecraft body and is used to release the escort small satellite;

[0044] The recovery mechanism is installed on the spacecraft body and is used to recover the escort small satellite.

[0045] The beneficial effects of the present invention are as follows: the escort small satellite of the present invention can perform both inspection tasks and protection tasks by setting a first-level cabin, a second-level cabin, a third-level cabin, a first-level protection component, a second-level protection component, a third-level protection component, a fourth-level protection component, a collision protection component and a solar wing, thereby improving the utilization of the escort small satellite and having a high application prospect. When performing the inspection task, the third-level cabin is located in the fifth accommodating cavity of the second-level cabin, and the second-level cabin is located in the third accommodating cavity of the first-level cabin. The solar wing and the first-level protection component are unfolded and extend out of the first accommodating cavity, while the second-level protection component is located in the second accommodating cavity and does not unfold, the third-level protection component is located in the fourth accommodating cavity and does not unfold, and the fourth-level protection component is located in the sixth accommodating cavity and does not unfold. The solar wing generates electricity with the help of sunlight to provide electrical energy for the escort small satellite. When space debris with a size of 1cm-10cm strikes, the escort small satellite begins to perform the protection task. During this process, the secondary cabin body sticks out of the third accommodation cavity of the primary cabin body, the third cabin body sticks out of the fifth accommodation cavity of the secondary cabin body, the solar wing and the first-level protection assembly unfold and stick out of the first accommodation cavity, the second-level protection assembly unfolds and sticks out of the second accommodation cavity, the third-level protection assembly unfolds and sticks out of the fourth accommodation cavity, the fourth-level protection assembly unfolds and sticks out of the sixth accommodation cavity, and the collision protection assembly expands. The collision protection assembly is used to withstand the impact of space debris moving toward the collision surface, dissipate the kinetic energy of space debris, protect the main structure of the escort small satellite, and extend the service life of the main structure of the escort small satellite. The first-level protection assembly, the second-level protection assembly, the third-level protection assembly, and the fourth-level protection assembly in the unfolded state constitute a multi-level defense barrier, which plays a multi-level interception role for space debris with a size of 1cm-10cm, maximizes the fragmentation of space debris, and dissipates the kinetic energy of space debris. On the whole, when performing protection tasks, it can effectively deal with the impact of space debris with a size of 1-10cm. BRIEF DESCRIPTION OF THE DRAWINGS

[0046] Figure 1 It is a schematic structural diagram of some specific embodiments of a companion escort small satellite of the present invention;

[0047] Figure 2 yes Figure 1 The schematic diagram of the escort small satellite shown is in the inspection state;

[0048] Figure 3 yes Figure 1 The schematic diagram of the escort small satellite during cabin extension is shown;

[0049] Figure 4 yes Figure 1 The schematic diagram shown is of the escort small satellite in a protective state.

[0050] In the attached drawings, 110, first-level cabin; 111, first accommodating chamber; 112, second accommodating chamber; 113, third accommodating chamber; 120, second-level cabin; 121, fourth accommodating chamber; 122, fifth accommodating chamber; 130, third-level cabin; 131, sixth accommodating chamber; 140, first-level protection assembly; 141, first support body; 142, first rigid protection layer; 143, first flexible protection layer; 150, second-level protection assembly; 160, third-level protection assembly; 170, fourth-level protection assembly ; 180. Collision protection assembly; 181. Second support body; 182. Second rigid protection layer; 183. Second flexible protection layer; 191. First buffer layer; 192. Second buffer layer; 193. Third buffer layer; 194. Solar wing; 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 DESCRIPTION

[0051] The technical solution of the present invention will be clearly and completely described below in conjunction with the embodiments. Obviously, the described embodiments are part of the embodiments of the present invention, rather than all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0052] As described in the background technology, for space debris with a size of 1cm-10cm, due to its larger size and impact kinetic energy compared to millimeter-sized space debris, it is impossible to achieve protection by adding protective structures to spacecraft (the maximum protection size is 1.5cm), and it is difficult to be effectively tracked and cataloged by the ground-based monitoring system. Instead, it has become the space debris with the greatest threat to long-term spacecraft in orbit. Therefore, how to deal with the impact risk of space debris with a size of 1-10cm has become a technical problem that needs to be solved urgently by those skilled in the art.

[0053] To solve the above problems, refer to Figure 1 , Figure 2 , Figure 3 and Figure 4On the one hand, the present invention provides a small satellite for escorting flight, including a first-stage cabin 110, a second-stage cabin 120, a third-stage cabin 130, a first-stage protection assembly 140, a second-stage protection assembly 150, a third-stage protection assembly 160, a fourth-stage protection assembly 170, a collision protection assembly 180 and a solar wing 194. One end face of the first-stage cabin 110 is a collision face. A first accommodating cavity 111 and a second accommodating cavity 112 are formed on the side wall of the first-stage cabin 110, and a third accommodating cavity 113 is formed at the other end. The second-stage cabin 120 is arranged in the third accommodating cavity 113, and can be extended out of the third accommodating cavity 113 or retracted into the third accommodating cavity 113. A fourth accommodating cavity 121 is formed on the side wall of the second-stage cabin 120. A fifth accommodating cavity 122 is formed inside the second-stage cabin 120. The third-stage cabin 130 is arranged in the fifth accommodating cavity 122, and can be extended out of the fifth accommodating cavity 122 or retracted into the fifth accommodating cavity 122. A sixth accommodating cavity 131 is formed on the side wall of the third-stage cabin 130. The first-stage protection component 140 is disposed in the first accommodating cavity 111 and can be unfolded to protrude from the first accommodating cavity 111. The second-stage protection component 150 is disposed in the second accommodating cavity 112 and can be unfolded to protrude from the second accommodating cavity 112. The third-stage protection component 160 is disposed in the fourth accommodating cavity 121 and can be unfolded to protrude from the fourth accommodating cavity 121. The fourth-stage protection component 170 is disposed in the sixth accommodating cavity 131 and can be unfolded to protrude from the sixth accommodating cavity 131. The collision protection component 180 is installed on the collision surface and can expand. The solar wing 194 is disposed in the first accommodating cavity 111 and can be unfolded to protrude from the first accommodating cavity 111.

[0054] The working process and principle of escorting small satellites are as follows:

[0055] The escort small satellite accompanies the spacecraft 200 in flight. It can perform both inspection and protection tasks, which improves the utilization of the escort small satellite and has a high application prospect. When performing inspection tasks, such as Figure 2 As shown, the third-stage cabin 130 is located in the fifth accommodating cavity 122 of the second-stage cabin 120, and the second-stage cabin 120 is located in the third accommodating cavity 113 of the first-stage cabin 110. The solar wing 194 and the first-stage protection assembly 140 are unfolded and extend out of the first accommodating cavity 111, while the second-stage protection assembly 150 is located in the second accommodating cavity 112 and does not unfold, the third-stage protection assembly 160 is located in the fourth accommodating cavity 121 and does not unfold, and the fourth-stage protection assembly 170 is located in the sixth accommodating cavity 131 and does not unfold. The solar wing 194 generates electricity with the help of sunlight to provide electrical energy for the escort small satellite. When space debris with a size of 1cm-10cm strikes, the escort small satellite begins to perform protection tasks. In this process, such as Figure 3 and Figure 4As shown, first, the secondary cabin 120 extends out of the third accommodation cavity 113 of the primary cabin 110, and then the tertiary cabin 130 extends out of the fifth accommodation cavity 122 of the secondary cabin 120. After that, the solar wing 194 and the primary protection assembly 140 unfold and extend out of the first accommodation cavity 111, the secondary protection assembly 150 unfolds and extends out of the second accommodation cavity 112, the tertiary protection assembly 160 unfolds and extends out of the fourth accommodation cavity 121, the quaternary protection assembly 170 unfolds and extends out of the sixth accommodation cavity 131, and the collision protection assembly 180 expands. Figure 4 The direction of the middle arrow is the direction of movement of space debris. The collision protection component 180 is used to withstand the impact of space debris moving toward the collision surface, dissipate the kinetic energy of space debris, protect the main structure of the escort small satellite, and extend the service life of the main structure of the escort small satellite. The first-level protection component 140, the second-level protection component 150, the third-level protection component 160, and the fourth-level protection component 170 in the unfolded state constitute a multi-level defense barrier, which plays a multi-level interception role for space debris with a size of 1cm-10cm, breaks up space debris to the greatest extent, and dissipates the kinetic energy of space debris. On the whole, when performing protection tasks, it can effectively deal with the impact of space debris with a size of 1-10cm.

[0056] Preferably, there are two first accommodating chambers 111, which are symmetrically arranged on opposite sides of the first-stage cabin 110. There are two second accommodating chambers 112, which are also symmetrically arranged on opposite sides of the first-stage cabin 110. There are two fourth accommodating chambers 121, which are symmetrically arranged on opposite sides of the second-stage cabin 120. There are two sixth accommodating chambers 131, which are symmetrically arranged on opposite sides of the third-stage cabin 130. There are two solar wings 194, which correspond one-to-one to the two first accommodating chambers 111. There are two first-stage protection components 140, which correspond one-to-one to the two first accommodating chambers 111. There are two second-stage protection components 150, which correspond one-to-one to the two second accommodating chambers 112. There are two third-stage protection components 160, which correspond one-to-one to the two fourth accommodating chambers 121. There are two fourth-stage protection components 170, which correspond one-to-one to the two sixth accommodating chambers 131. In this way, a larger power generation area and debris interception area are guaranteed, which is conducive to improving power generation and interception effects.

[0057] Specifically, in the example, Figure 2 and Figure 4As shown, the first-level protection assembly 140 includes a first support body 141, a first rigid protection layer 142 and a first flexible protection layer 143. The first support body 141 can expand to protrude from the first accommodating cavity 111. It should be noted that a plurality of partitions are provided in the first support body 141 to divide the interior of the support body into a plurality of filling cavities. Each filling cavity is filled with a compressible porous material. During launch, the first support body 141 is compressed into a flat shape to reduce the launch difficulty and launch cost. After entering orbit, the first support body 141 can expand and unfold. The first rigid protection layer 142 is provided on one side of the first support body 141 close to the collision surface. The first rigid protection layer 142 is made of high-performance protection material, has a certain strength and hardness, and has good collision resistance. The first flexible protection layer 143 is provided on one side of the first support body 141 away from the collision surface. The first flexible protection layer 143 is made of high-performance protection material, has a certain flexibility, and has good interception performance. The structure of the primary protection assembly 140 is the same as that of the secondary protection assembly 150, the tertiary protection assembly 160, and the quaternary protection assembly 170. The primary protection assembly 140, the secondary protection assembly 150, the tertiary protection assembly 160, and the quaternary protection assembly 170 in the deployed state constitute a multi-level defense barrier, which plays a multi-level interception role for space debris with a size of 1 cm-10 cm.

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

[0059] Specifically, in the example, Figure 3 and Figure 4 As shown, the collision protection assembly 180 includes a second support body 181, a second rigid protective layer 182 and a multi-layer second flexible protective layer 183. The second support body 181 is installed on the collision surface and can expand in the direction away from the collision surface. It should be noted that the second support body 181 is formed with a filling cavity, and the filling cavity is filled with a compressible porous material. During launch, the second support body 181 is compressed into a flat shape to reduce the difficulty and cost of launch. After entering orbit, the second support body 181 can expand and unfold, and the protection distance is doubled. The second rigid protective layer 182 is arranged on a side surface of the second support body 181 away from the collision surface. The second rigid protective layer 182 is made of high-performance protective material, has a certain strength and hardness, and has good collision resistance. The multi-layer second flexible protective layer 183 is evenly distributed in 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 a high-performance protective material and has a certain degree of flexibility. The multi-layer second flexible protective layer 183 has a multi-level interception performance.

[0060] It should be pointed out that since space debris with a size of 1cm-10cm has great kinetic energy and destructive power, in order to prevent the main structure of the escort satellite from being damaged, Figure 4 As shown, the escort small 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 in the third accommodating cavity 113. The second buffer layer 192 is installed at one end of the secondary cabin 120 close to the primary cabin 110, and a first buffer cavity is formed between the first buffer layer 191 and the third buffer layer 193. The third buffer layer 193 is installed at one end of the third cabin 130 close to the secondary cabin 120, and a second buffer cavity is formed between 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 greatly improves the protection spacing, further enhances the protection capability, realizes the protection of the main structure of the escort small satellite, and avoids the complete failure of the main structure of the escort small satellite.

[0061] Specifically, in the example, Figure 3As shown, the escort small 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. Under non-emergency conditions, the first propulsion module 1951 completes the orbit change control. The attitude control module 196 provides attitude control after normal inspection and emergency protection instructions. The first communication module 1971 provides normal communication with the spacecraft 200 under non-emergency conditions. When space debris hits the escort small satellite, causing the main structure of the escort small satellite to be damaged under extreme conditions, the second communication module 1972 ensures that the escort small satellite can communicate normally with the spacecraft 200, which is convenient for recovery. The second propulsion module 1952 performs emergency orbit maneuvers when dangerous space debris strikes, and assists the escort small satellite in maneuvering and recovery under extreme conditions. The first propulsion module 1951, the attitude control module 196, the first communication module 1971 and the power supply module 198 are installed in the first-stage cabin 110. The first communication module 1971 is respectively connected to the first propulsion module 1951, the attitude control module 196, the inspection module 199 and the communication module on the spacecraft 200 for communication, and data transmission can be realized. The power supply module 198 is respectively connected to the first propulsion module 1951, the attitude control module 196, the first communication module 1971 and the inspection module 199 for supplying power to the first propulsion module 1951, the attitude control module 196, the first communication module 1971 and the inspection module 199. When performing the inspection task, the first communication module 1971, the first propulsion module 1951, the attitude control module 196 and the inspection module 199 participate in the work. The second propulsion module 1952, the inspection module 199 and the second communication module 1972 are installed in the third-stage cabin 130 so that the second propulsion module 1952, the inspection module 199 and the second communication module 1972 are as far away from the collision surface as possible, and the second propulsion module 1952, the inspection module 199 and the second communication module 1972 are protected. Under extreme working conditions, such as when the escort small satellite is damaged by collision, the second propulsion module 1952 and the second communication module 1972 are used as emergency modules. The second communication module 1972 is respectively connected to the second propulsion module 1952 and the communication module on the spacecraft 200 to realize data transmission.

[0062] On the other hand, the present invention also provides a spacecraft 200 operation system, including a spacecraft 200 and a companion escort satellite. A detection and sensing module is provided on the spacecraft 200, and the detection and sensing module is used to detect whether there is any space debris with a size of 1cm-10cm. When it is detected that there is space debris with a size of 1cm-10cm, the companion escort satellite is controlled to quickly reach the corresponding position and start to perform the protection task, thereby avoiding the phenomenon that the spacecraft 200 cannot change its orbit in time due to insufficient warning time and suffers a collision. In the stage where there is no space debris attack, the companion escort satellite inspects the important parts of the surface of the spacecraft 200.

[0063] It should be noted that the spacecraft 200 may be a satellite, a manned spacecraft or a cargo spacecraft, etc. For a manned spacecraft, the safety of the personnel is greatly guaranteed by the help of a small satellite for escort.

[0064] Specifically, in the exemplary embodiment, the spacecraft 200 includes a spacecraft 200 body, a release mechanism, and a recovery mechanism. The release mechanism is installed on the spacecraft 200 body and is used to release the escort satellite. The recovery mechanism is installed on the spacecraft 200 body and is used to recover the escort satellite.

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

[0066] The companion escort satellite or its components are transported to the manned spacecraft by the cargo spacecraft for in-orbit assembly, functional debugging and in-orbit release. The companion escort satellite has the functions of communication, propulsion, inspection and protection. When released in orbit, the spacecraft 200 releases the assembled and functionally debugged companion escort satellite through the release mechanism, and the companion escort satellite realizes the companion function with the help of the first propulsion module 1951 and the attitude control module 196. Under normal circumstances, the companion escort satellite performs routine inspections on the daily operation health of the spacecraft 200 through the inspection function. In this process, the companion escort satellite conducts a traversal inspection on the health of the outer surface of the key parts of the spacecraft 200. The inspection function is mainly realized by the inspection module 199 of the companion escort satellite. Therefore, the inspection module 199 includes a high-resolution camera and a data storage and transmission unit. The high-resolution camera takes pictures of the key parts during the inspection to obtain the outer surface image, and temporarily stores the image through the data storage and transmission unit and sends it to the spacecraft 200. The analysis and communication system of the spacecraft 200 receives information and conducts health status analysis to implement routine health status inspection of the spacecraft 200. When the detection and perception module of the spacecraft 200 detects that there is space debris with a size of 1cm-10cm, the analysis and communication system sends information such as the location of dangerous space debris and possible impact direction to the companion escort satellite, and sends an instruction to the companion escort satellite whether to start the emergency propulsion mode according to the possible warning time, so that the companion escort satellite can quickly reach the dangerous area and implement dangerous space debris protection. When performing dangerous debris protection, the protection distance reaches the meter level. When the companion escort satellite completes the inspection task or protection task. When recovery and maintenance are required, the spacecraft 200 sends instructions to the companion escort satellite through the analysis and communication system, and after receiving the instructions through the first communication module 1971 / second communication module 1972 of the companion escort satellite, the first propulsion module 1951 / second propulsion module 1952 is started to complete the recovery work, and the astronauts carry out inspection and maintenance work. Under extreme conditions, when dangerous space debris hits the small satellite body and causes serious damage to the structure, the emergency communication module and emergency propulsion module located in the three-stage extension body farthest from the impact surface are activated to complete emergency communications and orbital maneuvers to achieve recovery, thereby preventing the satellite body from forming uncontrollable space debris.

[0067] Preferably, the release mechanism may be a release jaw.

[0068] Preferably, the retrieval mechanism may be a retrieval cable.

[0069] In the description of the present invention, it is to be understood that the terms “center”, “longitudinal”, “lateral”, “length”, “width”, “thickness”, “up”, “down”, “front”, “back”, “left”, “right”, “vertical”, “horizontal”, “top”, “bottom”, “inside”, “outside”, “clockwise”, “counterclockwise”, “axial”, “radial”, “circumferential”, etc., indicating orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the referred device or element must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as limiting the present invention.

[0070] In addition, the terms "first" and "second" are used for descriptive purposes only and should not be understood as indicating or implying relative importance or implicitly indicating the number of the indicated technical features. Therefore, the features defined as "first" and "second" may explicitly or implicitly include at least one of the features. In the description of the present invention, the meaning of "plurality" is at least two, such as two, three, etc., unless otherwise clearly and specifically defined.

[0071] In the present invention, unless otherwise clearly specified and limited, the terms "installed", "connected", "connected", "fixed" and the like should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral one; it can be a mechanical connection, an electrical connection, or communication with each other; it can be a direct connection, or an indirect connection through an intermediate medium, it can be the internal connection of two elements or the interaction relationship between two elements, unless otherwise clearly defined. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0072] In the present invention, the terms "one embodiment", "some embodiments", "examples", "specific examples", or "some examples" etc. mean that the specific features, structures, materials or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the present invention. In this specification, the schematic representations of the above terms do not necessarily refer to the same embodiment or example. Moreover, the described specific features, structures, materials or characteristics may be combined in any one or more embodiments or examples in a suitable manner. In addition, those skilled in the art may combine and combine the different embodiments or examples described in this specification and the features of the different embodiments or examples, without contradiction.

[0073] Although the embodiments of the present invention have been shown and described above, it is to be understood that the above embodiments are exemplary and are not to be construed as limitations of the present invention. A person skilled in the art may change, modify, replace and vary the above embodiments within the scope of the present invention.

Claims

1. A small satellite escort, characterized in that: include: The first-stage cabin has a collision surface at one end, a first accommodating cavity and a second accommodating cavity formed on the side wall, and a third accommodating cavity formed at the other end; A secondary cabin body is arranged in the third accommodating cavity and can extend out of the third accommodating cavity or retract into the third accommodating cavity; a fourth accommodating cavity is formed on the side wall of the secondary cabin body, and a fifth accommodating cavity is formed inside the secondary cabin body; The third-stage cabin body is arranged in the fifth accommodating cavity and can extend out of the fifth accommodating cavity or retract into the fifth accommodating cavity; a sixth accommodating cavity is formed on the side wall of the third-stage cabin body; A primary protection component, disposed in the first accommodating cavity and capable of being unfolded to protrude out of the first accommodating cavity; A secondary protection component, disposed in the second accommodating cavity and capable of being unfolded to protrude out of the second accommodating cavity; A third-level protection component, disposed in the fourth accommodating cavity and capable of being unfolded to protrude out of the fourth accommodating cavity; The fourth-level protection component is arranged in the sixth accommodating cavity and can be unfolded to extend out of the sixth accommodating cavity.

2. The escort small satellite according to claim 1, characterized in that: The first-level protection component includes: A first support body capable of expanding to extend out of the first accommodating cavity; A first rigid protective layer is provided on a side surface of the first supporting body close to the collision surface; A first flexible protective layer is provided on a side surface of the first support body away from the collision 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 small satellite according to claim 1, characterized in that: Also includes: The collision protection component is installed on the collision surface and can expand.

4. The escort small satellite according to claim 3, characterized in that: The collision protection component comprises: A second support body, mounted on the collision surface, capable of expanding; A second rigid protective layer is provided on a side surface of the second support body away from the collision surface; The second flexible protective layer is multi-layered and evenly distributed inside the second supporting body along the expansion direction of the second supporting body.

5. The companion escort small satellite according to any one of claims 1 to 4, characterized in that: Also includes: A first buffer layer is installed in the third accommodating cavity; A second buffer layer is installed at one end of the secondary cabin body close to the primary cabin body, and forms a first buffer cavity between the second buffer layer and the first buffer layer; The third buffer layer is installed at one end of the third-stage cabin body close to the second-stage cabin body, and forms a second buffer cavity between the third buffer layer and the second buffer layer.

6. The escort small satellite according to any one of claims 1 to 4, characterized in that: Also includes: The solar wing is arranged in the first accommodating cavity and can be unfolded to protrude out of the first accommodating cavity.

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

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

9. A spacecraft operation system, characterized in that: A spacecraft comprising a small companion satellite as claimed in any one of claims 1 to 8; The spacecraft is provided with a detection and perception module.

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

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