CN119840862A - Satellite and spacecraft operation system - Google Patents

Abstract

The invention relates to the technical field of space debris protection, in particular to a satellite and spacecraft operation system, which comprises a primary cabin body, a secondary cabin body, a tertiary cabin body, a primary protection assembly, a secondary protection assembly, a tertiary protection assembly and a quaternary protection assembly, wherein the inspection task and the protection task can be executed, and the utilization degree of the satellite is improved. When space fragments with the size of 1cm-10cm come, the second-stage cabin body stretches out of the third accommodating cavity of the first-stage cabin body, the third-stage cabin body stretches out of the fifth accommodating cavity of the second-stage cabin body, the first-stage protection component stretches out of the first accommodating cavity, the second-stage protection component stretches out of the second accommodating cavity, the third-stage protection component stretches out of the fourth accommodating cavity, the fourth-stage protection component stretches out of the sixth accommodating cavity to form a multi-stage protection barrier, a multi-stage interception effect is achieved on the space fragments with the size of 1cm-10cm, the space fragments are broken to the greatest extent, and kinetic energy of the space fragments is dissipated.

Description

Satellite and spacecraft operation system

Technical Field

The invention relates to the technical field of space debris protection, in particular to a satellite and spacecraft operation system for satellite flight protection.

Background

In recent years, the spatial environment has been increasingly deteriorated. The number of space debris with a size of 1cm-10cm has exceeded 75 tens of thousands, and debris in this size range becomes the space debris that is the most harmful to the spacecraft. For space debris with the size smaller than 1cm, effective protection can be achieved by adding a protection structure to the spacecraft. For space debris with the size of more than 10cm, tracking and cataloging can be performed through a space foundation monitoring system, and a spacecraft can be avoided in an orbital maneuver mode. For space debris with the size of 1cm-10cm, the size and the impact kinetic energy of the space debris are larger than those of millimeter-sized space debris, so that the space debris cannot achieve a protection effect by additionally installing a protection structure for a spacecraft, is difficult to effectively track and catalogue by an antenna foundation monitoring system, and becomes the space debris with the greatest threat to the on-orbit spacecraft at present.

Therefore, how to cope with the collision risk of space debris with a size of 1-10cm is a technical problem to be solved by those skilled in the art.

Disclosure of Invention

The invention provides a satellite and spacecraft operation system for satellite flight protection, which is used for solving the problem of how to cope with the collision risk of space debris with the size of 1-10 cm.

In one aspect, the present invention provides a satellite for satellite flight protection comprising:

one end face of the first-stage cabin body is an impact face, a first accommodating cavity and a second accommodating cavity are formed in the side wall, and a third accommodating cavity is formed in the other end of the first-stage cabin body;

the second-level 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 second-level cabin body, and a fifth accommodating cavity is formed in the second-level 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;

the first-stage protection assembly is arranged in the first accommodating cavity and can be unfolded to extend out of the first accommodating cavity;

the second-level protection assembly is arranged in the second accommodating cavity and can be unfolded to extend out of the second accommodating cavity;

the third-stage protection assembly is arranged in the fourth accommodating cavity and can be unfolded to extend out of the fourth accommodating cavity;

the fourth-level protection assembly is arranged in the sixth containing cavity and can be unfolded to extend out of the sixth containing cavity.

In some of these embodiments, the primary guard assembly comprises:

A first support body capable of expanding to protrude from the first accommodation chamber;

The first rigid protective layer is arranged on one side surface of the first support body, which is close to the collision face;

The first flexible protective layer is arranged on one side surface of the first support body, which is far away from the collision face;

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 respectively.

In some of these embodiments, further comprising:

the collision protection assembly is arranged on the collision face and can expand.

In some of these embodiments, the head-on protection assembly comprises:

The second support body is arranged on the collision face and can expand;

The second rigid protective layer is arranged on one side surface of the second support body away from the collision face;

the second flexible protective layer is a plurality of layers and is uniformly distributed in the second support body along the expansion direction of the second support body.

In some of these embodiments, further comprising:

The first buffer layer is arranged in the third accommodating cavity;

The second buffer layer is arranged at one end of the second-level cabin body close to the first-level cabin body, and a first buffer cavity is formed between the second buffer layer and the first buffer layer;

the third buffer layer is arranged at one end of the third-level cabin body, which is close to the second-level cabin body, and a second buffer cavity is formed between the third buffer layer and the second buffer layer.

In some of these embodiments, further comprising:

The solar wing is arranged in the first accommodating cavity and can be unfolded to extend out of the first accommodating cavity.

In some of these embodiments, further comprising:

the first propulsion module is arranged in the first-stage cabin body;

The attitude control module is arranged in the primary cabin body;

The first communication module is arranged in the primary cabin body and is respectively connected with the first propulsion module and the attitude regulation module;

The power supply module is arranged in the primary cabin body and is respectively connected with the first propulsion module, the attitude regulation and control module and the first communication module.

In some of these embodiments, further comprising:

the second propulsion module is arranged in the three-level cabin body;

the inspection module is arranged in the three-level cabin body;

the second communication module is arranged in the three-stage cabin body and is connected with the second propulsion module.

On the other hand, the invention also provides a spacecraft operation system, which comprises a spacecraft and a satellite for satellite flight protection;

The spacecraft is provided with a detection sensing module.

In some of these embodiments, the spacecraft comprises:

A spacecraft body;

The release mechanism is arranged on the spacecraft body and used for releasing the satellite with the flight protection;

and the recovery mechanism is arranged on the spacecraft body and used for recovering the satellite with the flight protection.

The satellite has the beneficial effects that the satellite can execute the inspection task and the protection task by arranging the first-stage cabin body, the second-stage cabin body, the third-stage cabin body, the first-stage protection component, the second-stage protection component, the third-stage protection component, the fourth-stage protection component, the collision protection component and the solar wing, so that the utilization degree of the satellite is improved, and the satellite has a higher application prospect. When the inspection task is executed, the third-level cabin is located in the fifth containing cavity of the second-level cabin, and the second-level cabin is located in the third containing cavity of the first-level cabin. The solar wing and the first-stage protection component are unfolded to extend out of the first accommodating cavity, the second-stage protection component is located in the second accommodating cavity and is not unfolded, the third-stage protection component is located in the fourth accommodating cavity and is not unfolded, and the fourth-stage protection component is located in the sixth accommodating cavity and is not unfolded. The solar wing provides electric energy for the satellite with flight protection by means of solar power generation. When space fragments with the size of 1cm-10cm come in, the satellite starts to perform the protection task. In the process, the second-stage cabin body stretches out of the third accommodating cavity of the first-stage cabin body, the third-stage cabin body stretches out of the fifth accommodating cavity of the second-stage cabin body, the solar wing and the first-stage protection assembly stretch out of the first accommodating cavity, the second-stage protection assembly stretch out of the second accommodating cavity, the third-stage protection assembly stretch out of the fourth accommodating cavity, the fourth-stage protection assembly stretch out of the sixth accommodating cavity, and the collision protection assembly expands. The collision protection assembly is used for bearing the collision of space fragments moving towards the collision face, dissipating the kinetic energy of the space fragments, protecting the main body structure of the satellite and prolonging the service life of the main body structure of the satellite. The primary protection component, the secondary protection component, the tertiary protection component and the quaternary protection component in the unfolding state form a multi-stage protection barrier, the multi-stage interception function is achieved on space fragments with the size of 1cm-10cm, the space fragments are broken to the greatest extent, and the kinetic energy of the space fragments is dissipated. Overall, the impact of space debris of a size of 1-10cm can be effectively handled when performing a protective task.

Drawings

FIG. 1 is a schematic diagram of some embodiments of a satellite according to the present invention;

FIG. 2 is a schematic view of the satellite in FIG. 1 in a patrol state;

FIG. 3 is a schematic view of the satellite of FIG. 1 with the satellite extended;

Fig. 4 is a schematic view of the satellite in fig. 1 in a protected state.

In the drawings, 110, a first-level cabin, 111, a first accommodating cavity, 112, a second accommodating cavity, 113, a third accommodating cavity, 120, a second-level cabin, 121, a fourth accommodating cavity, 122, a fifth accommodating cavity, 130, a third-level cabin, 131, a sixth accommodating cavity, 140, a first-level protection component, 141, a first supporting body, 142, a first rigid protection layer, 143, a first flexible protection layer, 150, a second-level protection component, 160, a third-level protection component, 170, a fourth-level protection component, 180, an impact protection component, 181, a second supporting body, 182, a second rigid protection layer, 183, a second flexible protection layer, 191, a first buffer layer, 192, a second buffer layer, 193, a third buffer layer, 194, a solar wing, 1951, a first propulsion module, 1952, a second propulsion module, 196, a gesture control module, 1971, a first communication module, 1972, a second communication module, 198, a power supply module, 199, an inspection module, 200 and a spacecraft.

Detailed Description

The technical solutions of the present invention will be clearly and completely described in connection with the embodiments, and it is apparent that the described embodiments are some embodiments of the present invention, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.

As described in the background art, for space debris with the size of 1cm-10cm, because the size of the space debris is larger than that of the space debris with the impact kinetic energy in millimeter level, the space debris cannot realize the protection effect by additionally installing a protection structure (the limit protection size is 1.5 cm) for a spacecraft, is difficult to effectively track and catalogue by a space foundation monitoring system, and becomes the space debris with the greatest threat to the spacecraft running on the orbit for a long time at present. Therefore, how to cope with the collision risk of space debris with a size of 1-10cm is a technical problem to be solved by those skilled in the art.

In order to solve the above problems, referring to fig. 1,2,3 and 4, in one aspect, the present invention provides a satellite for satellite, including a primary hull 110, a secondary hull 120, a tertiary hull 130, a primary protection assembly 140, a secondary protection assembly 150, a tertiary protection assembly 160, a quaternary protection assembly 170, an impact protection assembly 180, and solar wings 194. One end face of the primary cabin 110 is an impact face. A first receiving chamber 111 and a second receiving chamber 112 are formed on a sidewall of the primary chamber 110, and a third receiving chamber 113 is formed at the other end. The secondary compartment 120 is disposed in the third accommodating chamber 113 and can protrude out of the third accommodating chamber 113 or retract into the third accommodating chamber 113. A fourth receiving chamber 121 is formed at a sidewall of the secondary compartment 120. A fifth accommodation chamber 122 is formed in the interior of the secondary compartment 120. The tertiary capsule 130 is disposed in the fifth receiving chamber 122 and can protrude out of the fifth receiving chamber 122 or retract into the fifth receiving chamber 122. A sixth receiving chamber 131 is formed on a sidewall of the tertiary tank 130. The primary protection component 140 is disposed in the first accommodating cavity 111 and can be unfolded to protrude out of the first accommodating cavity 111. The secondary protection assembly 150 is disposed in the second accommodating chamber 112 and can be unfolded to protrude out of the second accommodating chamber 112. The tertiary guard assembly 160 is disposed within the fourth receiving cavity 121 and is capable of being deployed to protrude out of the fourth receiving cavity 121. The four-stage shield assembly 170 is disposed within the sixth receiving chamber 131 and is capable of being deployed to protrude out of the sixth receiving chamber 131. The impact protection assembly 180 is mounted on the impact face and is capable of expanding. The solar wing 194 is disposed in the first accommodating chamber 111 and can be unfolded to protrude out of the first accommodating chamber 111.

The working process and principle of the satellite for satellite flight protection are as follows:

The satellite for satellite flight accompanies the spacecraft 200. The method can not only execute the inspection task, but also execute the protection task, improves the utilization degree of the satellite with the flight protection, and has higher application prospect. When performing the inspection task, as shown in fig. 2, the tertiary tank 130 is located in the fifth receiving cavity 122 of the secondary tank 120, and the secondary tank 120 is located in the third receiving cavity 113 of the primary tank 110. The solar wing 194 and the primary shield assembly 140 are deployed out of the first receiving cavity 111, while the secondary shield assembly 150 is positioned in the second receiving cavity 112 without being deployed, the tertiary shield assembly 160 is positioned in the fourth receiving cavity 121 without being deployed, and the quaternary shield assembly 170 is positioned in the sixth receiving cavity 131 without being deployed. The solar wing 194 supplies electric energy to the satellite for satellite flight protection by means of solar power generation. When space fragments with the size of 1cm-10cm come in, the satellite starts to perform the protection task. In this process, as shown in fig. 3 and 4, first, the secondary compartment 120 protrudes out of the third receiving cavity 113 of the primary compartment 110, and then, the tertiary compartment 130 protrudes out of the fifth receiving cavity 122 of the secondary compartment 120. Thereafter, the solar wing 194 and the primary protection assembly 140 are unfolded to protrude from the first receiving cavity 111, the secondary protection assembly 150 is unfolded to protrude from the second receiving cavity 112, the tertiary protection assembly 160 is unfolded to protrude from the fourth receiving cavity 121, the quaternary protection assembly 170 is unfolded to protrude from the sixth receiving cavity 131, and the impact protection assembly 180 is inflated. The arrow direction in fig. 4 is the direction of the movement of the spatial debris. The impact protection assembly 180 is used for bearing impact of space debris moving towards an impact surface, dissipating kinetic energy of the space debris, protecting the main structure of the satellite and prolonging the service life of the main structure of the satellite. The primary protection assembly 140, the secondary protection assembly 150, the tertiary protection assembly 160 and the quaternary protection assembly 170 in the unfolded state form a multi-stage protection barrier, and play a multi-stage interception role on space fragments with the size of 1cm-10cm, so that the space fragments are broken to the greatest extent, and the kinetic energy of the space fragments is dissipated. Overall, the impact of space debris of a size of 1-10cm can be effectively handled when performing a protective task.

Preferably, the first accommodating chambers 111 are two and symmetrically arranged at two opposite sides of the primary cabin 110. The two second accommodating chambers 112 are also symmetrically disposed on two opposite sides of the primary cabin 110. The four accommodating chambers 121 are symmetrically arranged at two opposite sides of the secondary cabin 120. The six accommodating chambers 131 are two and symmetrically arranged at two opposite sides of the three-stage cabin 130. The solar wings 194 are two and correspond to the two first accommodating chambers 111 one by one. The number of the first-stage protection components 140 is two, and the first-stage protection components correspond to the two first accommodating cavities 111 one by one. The two secondary protection components 150 are in one-to-one correspondence with the two second accommodating cavities 112. The three-stage protection components 160 are two and correspond to the two fourth accommodating cavities 121 one by one. The four-stage protection components 170 are two and correspond to the two sixth accommodation cavities 131 one by one. Therefore, a larger power generation area and a larger fragment interception area are ensured, and the power generation capacity and the interception effect are improved.

Specifically, in the exemplary embodiment, as shown in fig. 2 and 4, primary shield assembly 140 includes a first support 141, a first rigid shield 142, and a first flexible shield 143. The first supporting body 141 can be expanded to protrude out of the first receiving chamber 111. It should be noted that a plurality of spacers are provided in the first supporting body 141 to divide the inside of the supporting body into a plurality of filling cavities. Each filling chamber is filled with a compressible porous material. In the case of firing, the first supporting body 141 is compressed to be flat, so as to reduce the firing difficulty and the firing cost. After the insertion, the first supporting body 141 can be expanded and unfolded. The first rigid protection layer 142 is disposed on a side of the first support body 141 near the impact surface. The first rigid protective layer 142 is made of a high-performance protective material, has certain strength and hardness, and has good collision resistance. The first flexible protection layer 143 is disposed on a side of the first support body 141 away from the impact surface. The first flexible protective layer 143 is made of a high performance protective material, has a certain flexibility, and has good interception. The primary shield assembly 140 is identical in structure to the secondary shield assembly 150, the tertiary shield assembly 160, and the quaternary shield assembly 170, respectively. The primary protective assembly 140, the secondary protective assembly 150, the tertiary protective assembly 160 and the quaternary protective assembly 170 in the unfolded state form a multi-stage protective barrier, and play a role in multi-stage interception of space debris with the size of 1cm-10 cm.

It should be noted that the unfolded solar wing 194 is located on the side of the unfolded first rigid protection layer 142 away from the first support 141, so as to ensure that the solar wing 194 can fully receive solar energy.

Specifically, in the illustrated example, as shown in fig. 3 and 4, the head-on protection assembly 180 includes a second support body 181, a second rigid protection layer 182, and a plurality of second flexible protection layers 183. The second support 181 is attached to the collision surface and can expand in a direction away from the collision surface. The second support 181 is formed with a filling cavity filled with a compressible porous material. During the launching, the second supporting body 181 is compressed to be flat, so as to reduce the launching difficulty and the launching cost. After the track is put in, the second supporting body 181 can expand and spread, and the protection interval is multiplied. The second rigid protection layer 182 is disposed on a side of the second support 181 away from the impact surface. The second rigid shield 182 is made of a high performance shielding material, has a certain strength and hardness, and has a good collision resistance. The plurality of second flexible protection layers 183 are uniformly distributed in the second support body 181 along the expansion direction of the second support body 181. Each second flexible protective layer 183 is made of a high performance protective material having a certain compliance. The multi-layer second flexible protective layer 183 has multi-level interception capability.

It should be noted that since space debris having a size of 1cm to 10cm has large kinetic energy and large destructive power, in order to prevent the main structure of the satellite from being damaged, the satellite further includes a first buffer layer 191, a second buffer layer 192, and a third buffer layer 193 as shown in fig. 4. The first buffer layer 191 is installed in the third receiving chamber 113. The second buffer layer 192 is installed at one end of the secondary cabin 120 near the primary cabin 110, and forms a first buffer cavity with the first buffer layer 191. The third buffer layer 193 is installed at one end of the third cabin 130 near the second cabin 120, and forms a second buffer chamber with the second buffer layer 192. The first, second and third buffer layers 191, 192 and 193 are made of a high performance protective material. The unfolded head-on 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 form an ultra-large-space protection system, so that the protection space is greatly increased, the protection capability is further enhanced, the protection of the main body structure of the satellite with flight protection is realized, and the main body structure of the satellite with flight protection is prevented from being completely failed.

Specifically, in the illustrated example, as shown in fig. 3, the satellite further includes a first propulsion module 1951, a posture adjustment module 196, a first communication module 1971, a power supply module 198, a second propulsion module 1952, a patrol module 199, and a second communication module 1972. In non-emergency conditions, the first propulsion module 1951 completes the derailment control. The gesture control module 196 provides gesture control following normal inspection and emergency protection instructions. The first communication module 1971 provides normal communication with the spacecraft 200 in a non-emergency state. When the space debris impacts the satellite, the main structure of the satellite is damaged, and the second communication module 1972 ensures normal communication between the satellite and the spacecraft 200, so that the satellite is convenient to implement and recycle. The second propulsion module 1952 emergently orbits when dangerous space debris comes in and assists satellite maneuver recovery in extreme conditions. The first propulsion module 1951, the attitude control module 196, the first communication module 1971, and the power supply module 198 are mounted within the primary enclosure 110. The first communication module 1971 is respectively in communication connection with the first propulsion module 1951, the gesture control module 196, the inspection module 199 and the communication module on the spacecraft 200, and can realize data transmission. The power supply module 198 is electrically connected to the first propulsion module 1951, the gesture control module 196, the first communication module 1971, and the inspection module 199, respectively, and is configured to supply power to the first propulsion module 1951, the gesture control module 196, the first communication module 1971, and the inspection module 199. In performing the inspection task, the first communication module 1971, the first propulsion module 1951, the gesture 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 three-stage cabin 130, so that the second propulsion module 1952, the inspection module 199 and the second communication module 1972 are far away from the collision face as far as possible, and a protection effect is provided for the second propulsion module 1952, the inspection module 199 and the second communication module 1972. In extreme conditions, such as those where the satellite is subject to collision damage, the second propulsion module 1952 and the second communication module 1972 are used as emergency modules. The second communication module 1972 is respectively in communication connection with the second propulsion module 1952 and the communication module on the spacecraft 200, and can realize data transmission.

On the other hand, the invention also provides a spacecraft 200 operation system, which comprises the spacecraft 200 and the satellite for satellite flight protection. The spacecraft 200 is provided with a detection sensing module for detecting whether space debris with the size of 1cm-10cm is hit. When detecting that space debris with the size of 1cm-10cm is hit, the satellite with the flight attendant protection is controlled to quickly prop to the corresponding position, and the protection task is started to be executed, so that the phenomenon that the spacecraft 200 cannot collide with a time-varying orbit due to insufficient early warning time is avoided. In the space debris-free attack stage, the satellite for satellite flight protection patrols and examines the important part of the outer surface of the spacecraft 200.

The spacecraft 200 may be a satellite, a manned spacecraft, or a cargo spacecraft, and for the manned spacecraft, the safety of personnel is greatly ensured by the satellite.

Specifically, in the illustrated example, the spacecraft 200 includes a spacecraft 200 body, a release mechanism, and a recovery mechanism. The release mechanism is mounted on the spacecraft 200 body for releasing the satellite. The recovery mechanism is installed on the spacecraft 200 body and is used for recovering the satellite for satellite flight protection.

The working process and principle of the spacecraft 200 operation system are as follows:

The satellite or its components are transported to the manned airship by the carrier, and the assembly, function debugging and in-orbit release are carried out. The satellite has the functions of communication, propulsion, inspection, protection and the like. When in orbit, the spacecraft 200 releases the assembled and functionally-debugged satellite through a release mechanism, and the satellite realizes the satellite function by virtue of the first propulsion module 1951 and the attitude control module 196. In the normal course of the time it is the case, the satellite for satellite flight protection carries out routine inspection on the daily operation health condition of the spacecraft 200 through the inspection function. In the process, the satellite for satellite navigation carries out traversal inspection on the health condition of the outer surface of the important part of the spacecraft 200. The inspection function is mainly realized by an inspection module 199 of a satellite with a flight guard. Thus, the inspection module 199 includes a high resolution camera, a data storage transmission unit, and the like. The high-resolution camera photographs the heavy spot part during inspection to acquire an outer surface image, and temporarily stores the image through the data storage and transmission unit and transmits the image to the spacecraft 200. The analysis and communication system of the spacecraft 200 receives information and performs health analysis to realize the inspection of daily operation health conditions of the spacecraft 200. When the detection sensing module of the spacecraft 200 detects that space debris with the size of 1cm-10cm is hit, the information such as the position of the dangerous space debris, the possible collision direction and the like is sent to the satellite with the flight protection through an analysis and communication system, and sending an emergency propulsion mode starting instruction to the satellite according to the possible early warning time, so that the satellite can quickly reach a dangerous area, and the protection of dangerous space fragments is implemented. When dangerous debris protection is carried out, the protection distance reaches the meter level. After the satellite with the flight guard completes the inspection task or the protection task. When recovery maintenance is required, the spacecraft 200 sends an instruction to the satellite through the analysis and communication system, receives the instruction through the first communication module 1971/the second communication module 1972 of the satellite, starts the first propulsion module 1951/the second propulsion module 1952 to complete recovery work, and the astronaut carries out maintenance and repair work. Under extreme conditions, when dangerous space debris impacts the small satellite body to cause serious structural damage, the emergency communication module and the emergency propulsion module which are positioned in the three-stage extension body far away from the impact surface are started to complete emergency communication and orbit maneuver to realize recovery, and uncontrollable space debris formed by the satellite body is avoided.

Preferably, the release mechanism may be a release jaw.

Preferably, the retrieval mechanism may be a retrieval cable.

In the description of the present 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", "circumferential", etc. indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings are merely for convenience in describing the present invention and simplifying the description, and do not indicate or imply that the device or element being referred to must have a specific orientation, be configured and operated in a specific orientation, and therefore should not be construed as limiting the present invention.

Furthermore, the terms "first," "second," and the like, are used for descriptive purposes only and are not to be construed as indicating or implying a relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defining "a first" or "a second" may explicitly or implicitly include at least one such feature. In the description of the present invention, the meaning of "plurality" means at least two, for example, two, three, etc., unless specifically defined otherwise.

In the present invention, unless explicitly specified and limited otherwise, the terms "mounted," "connected," "secured," and the like are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally formed, mechanically connected, electrically connected, or communicable with each other, directly connected, indirectly connected through an intervening medium, or in communication between two elements or in an interactive relationship between two elements, unless otherwise explicitly specified. The specific meaning of the above terms in the present invention can be understood by those of ordinary skill in the art according to the specific circumstances.

For purposes of this disclosure, the terms "one embodiment," "some embodiments," "example," "a particular example," or "some examples," etc., mean that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the invention. In this specification, schematic representations of the above terms are not necessarily directed to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples. Furthermore, the different embodiments or examples described in this specification and the features of the different embodiments or examples may be combined and combined by those skilled in the art without contradiction.

While embodiments of the present invention have been shown and described above, it will be understood that the above embodiments are illustrative and not to be construed as limiting the invention, and that variations, modifications, alternatives and variations may be made to the above embodiments by one of ordinary skill in the art within the scope of the invention.

Claims (10)

1. A satellite for satellite flight protection, comprising:

one end face of the first-stage cabin body is an impact face, a first accommodating cavity and a second accommodating cavity are formed in the side wall, and a third accommodating cavity is formed in the other end of the first-stage cabin body;

The second-level 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 second-level cabin body, and a fifth accommodating cavity is formed in the second-level 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, and a sixth accommodating cavity is formed on the side wall of the third-stage cabin body;

the first-stage protection assembly is arranged in the first accommodating cavity and can be unfolded to extend out of the first accommodating cavity;

the second-level protection assembly is arranged in the second accommodating cavity and can be unfolded to extend out of the second accommodating cavity;

The third-stage protection assembly is arranged in the fourth accommodating cavity and can be unfolded to extend out of the fourth accommodating cavity;

the fourth-level protection assembly is arranged in the sixth containing cavity and can be unfolded to extend out of the sixth containing cavity.

2. The satellite of claim 1, wherein the primary shield assembly comprises:

A first support body capable of expanding to protrude from the first accommodation chamber;

The first rigid protective layer is arranged on one side surface of the first support body, which is close to the collision face;

The first flexible protective layer is arranged on one side surface of the first support body away from the collision face;

The structure of the primary protection assembly is the same as that of the secondary protection assembly, the tertiary protection assembly and the quaternary protection assembly respectively.

3. The satellite according to claim 1, characterized by further comprising:

And the impact protection assembly is arranged on the impact surface and can expand.

4. The satellite of claim 3, wherein the head-on protection assembly comprises:

the second support body is arranged on the collision face and can expand;

the second rigid protective layer is arranged on one side surface of the second support body away from the collision face;

The second flexible protective layer is a plurality of layers and is uniformly distributed in the second support body along the expansion direction of the second support body.

5. The satellite according to any one of claims 1 to 4, further comprising:

The first buffer layer is arranged in the third accommodating cavity;

the second buffer layer is arranged at one end of the secondary cabin body, which is close to the primary cabin body, and a first buffer cavity is formed between the second buffer layer and the first buffer layer;

and the third buffer layer is arranged at one end of the third-stage cabin body, which is close to the second-stage cabin body, and a second buffer cavity is formed between the third buffer layer and the second buffer layer.

6. The satellite according to any one of claims 1 to 4, further comprising:

The solar wing is arranged in the first accommodating cavity and can be unfolded to extend out of the first accommodating cavity.

7. The satellite according to any one of claims 1 to 4, further comprising:

The first propulsion module is arranged in the primary cabin body;

the attitude control module is arranged in the primary cabin body;

The first communication module is arranged in the primary cabin body and is respectively connected with the first propulsion module and the attitude regulation module;

The power supply module is arranged in the primary cabin body and is respectively connected with the first propulsion module, the gesture regulation and control module and the first communication module.

8. The satellite according to claim 7, characterized by further comprising:

The second propulsion module is arranged in the three-stage cabin body;

The inspection module is arranged in the three-stage cabin body;

and the second communication module is arranged in the three-stage cabin body and is connected with the second propulsion module.

9. A spacecraft operation system comprising a spacecraft and a satellite according to any one of claims 1 to 8;

and the spacecraft is provided with a detection sensing module.

10. The spacecraft operating system of claim 9, wherein said spacecraft comprises:

A spacecraft body;

the release mechanism is arranged on the spacecraft body and used for releasing the satellite;

and the recovery mechanism is arranged on the spacecraft body and is used for recovering the satellite for satellite flight protection.