Distributed satellite system based on space tethered system

Abstract

The invention discloses a distributed satellite system based on a space tethered system, which comprises at least two satellites, the satellites are connected with each other through a tethered mechanism system, so that the satellites are separated and gathered, and the relative orbital positions of the satellites are changed irregularly; the tether mechanism system comprises an electromagnetic docking mechanism and a tether winding and unwinding mechanism; the satellites are combined before entering the orbit, the satellites are separated in the orbit through the electromagnetic docking mechanism after entering the orbit, the rope is released by the tether winding and unwinding mechanism, and the satellites operate in a stable flight configuration in a preset orbit; when multiple satellites are gathered, the rope is retracted by the tether retracting and releasing mechanism, and the satellites are in on-orbit butt joint through the electromagnetic butt joint mechanism. When the stable flight configuration is kept, the rope passes through the mass centers of the satellites at the same time, and the satellites are in a vertical stable posture through the tether winding and unwinding mechanism and the gravity gradient.

Description

Technical Field

[0001] The present invention relates to the field of overall design of spacecrafts, and particularly to a distributed satellite system based on space tethers. Background Art

[0002] The functional dispersion and aggregation reconstruction are important development trends of future spacecrafts and space technologies. Spacecrafts not only face non-intentional threats such as space debris with an increasing impact probability year by year, but also face various threats such as anti-satellite weapons, communication jammers, GPS jammers, and cyber attack aircrafts. At the same time, due to the certainty and predictability of the spacecraft orbit and the limited maneuvering and avoidance capabilities of the spacecraft itself, the existing on-orbit threat response capabilities of spacecrafts are seriously insufficient. The safety protection of spacecrafts has become an important issue that has to be considered when constructing the space equipment system. Summary of the Invention

[0003] The technical problem solved by the present invention is: overcoming the deficiencies of the prior art, providing a distributed satellite system based on space tethers, realizing the dispersion and combination of the satellite system, and enhancing the system elasticity and the ability to respond to security threats.

[0004] The technical solution of the present invention is: a distributed satellite system based on space tethers, including at least two satellites. Each satellite is equipped with a payload system, an integrated electronic system, an energy system, a structure system, and a control and propulsion system. The satellites are interconnected by a tether mechanism system, enabling the separation and aggregation of each satellite and periodically changing the relative orbital positions of the satellites; the tether mechanism system includes an electromagnetic docking mechanism and a tether retraction and deployment mechanism; before entering the orbit, the satellites are in a combined body, and after entering the orbit, the satellites are separated on orbit through the electromagnetic docking mechanism, and the tether retraction and deployment mechanism releases the ropes. Each satellite operates in a stable flight configuration in a predetermined orbit; the stable flight configuration is that each satellite is in a vertical stable attitude by relying on the tether retraction and deployment mechanism and the gravity gradient, and the ropes pass through the centers of mass of each satellite at the same time; when multiple satellites are aggregated, the tether retraction and deployment mechanism retrieves the ropes, and the satellites are docked on orbit through the electromagnetic docking mechanism.

[0005] Further, the tether retraction and deployment mechanism is divided into two parts, which are respectively installed on two satellites. The first component includes a rope fixing component, and the second component includes a rope retraction and deployment component, a cutter component, a rope detection component, and a rope winding component. One end of the rope is connected to the rope fixing component, and the other end passes through each component in the second component in sequence, and is always in a tension state inside the satellite body;

[0006] Both the rope winding and unwinding assembly and the rope coiling assembly are equipped with drive assemblies to actively control the speed of rope winding and unwinding. The rope detection assembly includes a tension sensor, a detection wheel, and two guide wheels. The rope is input through the first guide wheel, passes through the detection wheel, and is output through the second guide wheel. The tension sensor is connected to the detection wheel. During the winding and unwinding process, the rope drives the detection wheel to rotate, and the rope length measuring resolver in the detection wheel obtains the length of the winding and unwinding rope.

[0007] Furthermore, the rope winding and unwinding assembly includes a winding and unwinding drive assembly, a driving wheel, a driven wheel, and a pre-tightening device. The winding and unwinding drive assembly provides power for the rotation of the driving wheel, the pre-tightening device provides a positive pressure for the rope, and the driven wheel presses the rope tightly against the surface of the driving wheel to prevent the rope from slipping.

[0008] The rope coiling assembly includes a coiling drive assembly, a reel, a wire arranging mechanism, and a wire guiding mechanism. The coiling drive assembly provides power for the rotation of the reel, and the wire arranging mechanism drives the wire guiding mechanism to reciprocate to prevent the rope from stacking by designing a fixed coiling ratio.

[0009] Furthermore, the working modes of the tether winding and unwinding mechanism include: separation and release mode, slow rope recovery mode, fast rope recovery mode, and rope length holding mode.

[0010] In the separation and release mode, the rope release speeds of the rope winding and unwinding assembly and the rope coiling assembly are the same and greater than the separation speed of the two satellites. The winding and unwinding drive assembly and the coiling drive assembly control the active release of the rope, and there is no tension in the rope between the rope winding and unwinding assembly and the rope fixing assembly.

[0011] In the slow rope recovery mode, the rope winding and unwinding assembly winds the rope. The rope coiling assembly controls the coiling speed of the coiling drive assembly according to the tension feedback from the tension sensor. The length of the winding and unwinding rope is recorded through the detection wheel and the rope length measuring resolver to obtain the internal rope linear velocity, and the speed of the winding and unwinding drive assembly is controlled to make the two satellites recover the rope at a given speed.

[0012] In the fast rope recovery mode, the rope winding and unwinding assembly winds the rope, providing a tension for the rope between the rope winding and unwinding assembly and the rope fixing assembly, so that the rope winding acceleration is not less than 0.5 m / s 2 , with a duration of ≥3 s, and the rope coiling assembly controls the coiling speed of the coiling drive assembly according to the tension feedback from the tension sensor to make the two satellites recover quickly.

[0013] In the rope length holding mode, when the two satellites are separated or recovered to a certain distance, the rope winding and unwinding assembly is powered on and held to keep the rope length between the two satellites unchanged.

[0014] Furthermore, the cutter assembly generates gas by firing the internal igniter, pushing the cutter to cut the shear pin, and enabling the cutter to continue moving to quickly cut the rope.

[0015] Furthermore, for a binary star system, the second component of the tether retracting and deploying mechanism is arranged inside the primary star, and the first component is arranged inside the secondary star; for a multi-star system, a complete set of the second component of the tether retracting and deploying mechanism is arranged inside a secondary star, which serves as the primary star for the next secondary star, and so on.

[0016] Furthermore, the length range of the tether of the tether mechanism system is 100 m to 10 km.

[0017] Furthermore, the control and propulsion system is used to complete attitude prediction, attitude determination, and attitude control; attitude prediction is realized based on gyro measurement; attitude determination includes two methods, which are realized based on gyro and star sensor, and realized based on gyro, magnetometer, and digital sun sensor; attitude control is realized based on zero momentum control of momentum wheels and micro propulsion.

[0018] Furthermore, the structure of the structure system adopts a modular design. The main load-bearing structure is a cuboid frame, with multiple accommodation spaces formed inside. The antennas and solar energy conversion components of the satellite are installed on the outer surface of the main load-bearing structure, and the functional modules of the satellite are distributed in different accommodation spaces. Among them, the control and propulsion system and the tether mechanism system are connected to the modular main load-bearing structure through surface mounting, and the remaining functional modules are connected to the main load-bearing structure through draw-out connection.

[0019] Furthermore, solar energy conversion components are installed on the -Z, +X, -X, and -Y planes of the main load-bearing structure. The TT&C antenna is located on the +Z and -Z planes of the satellite, and the data transmission antenna is located on the +Z plane of the satellite; the control and propulsion system is fixed on the -Z plane, and the rope outlet of the tether mechanism system is located on the -Y plane and close to the +Z side; the X, Y, and Z directions take the center of the satellite bottom surface as the coordinate origin, the Z axis points to the direction of the data transmission antenna, the Y axis points in the opposite direction to the rope outlet of the tether mechanism, and the X axis, Y axis, and Z axis form a right-handed coordinate system.

[0020] The advantages of the present invention compared with the prior art are as follows:

[0021] 1) The present invention innovatively proposes a distributed satellite system, constructs an elastic dispersion system by means of a tether, and randomly changes the relative orbital positions of two spacecrafts irregularly through rope retracting and deploying actions, which can enhance the unpredictable ability of the orbits of the two satellites; at the same time, the payload and the platform can be dispersed and configured, improving the stability of the payload and promoting the practical application of the space tether distributed satellite system.

[0022] 2) The design of the distributed satellite system of the present invention makes multiple satellites in a vertically stable attitude by means of a tether and the gravity gradient effect. Based on this design, a long-term stable and length-adjustable measurement baseline can be provided for the interferometric SAR, and a longer imaging opportunity can be provided for interferometric measurement compared with the formation satellite system, greatly improving the terrain elevation measurement accuracy and mapping efficiency.

[0023] 3) The distributed satellite system of the present invention adopts an open, flexible and reconfigurable software and hardware architecture, which can be extended to a multi-subplatform system, connecting physically dispersed systems to form a highly integrated, multi-satellite integrated or inter-satellite integrated comprehensive system.

[0024] 4) The distributed satellite system can achieve multi-satellite aggregation based on tether mechanisms and electromagnetic docking mechanisms, providing a solution for the on-orbit construction of future ultra-large spacecraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] Figure 1 It is the composition of the tethered double-satellite system in a specific embodiment of the present invention;

[0026] Figure 2 It is the launch state configuration of the tethered double-satellite system in a specific embodiment of the present invention;

[0027] Figure 3 It is the flight state configuration of the tethered double-satellite system in a specific embodiment of the present invention;

[0028] Figure 4 It is the satellite modular layout of the tethered double-satellite system in a specific embodiment of the present invention;

[0029] Figure 5 It is the specific implementation manner of the tether retraction and deployment mechanism of the present invention. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0030] In order to better understand the technical solution of the present invention, the specific embodiments of the present invention will be described below.

[0031] As Figure 1 shown, the distributed satellite system based on space tethers proposed by the present invention is described by taking the tethered double-satellite system as an example in this embodiment. It consists of a mother satellite and a daughter satellite. Each satellite includes six major systems: a payload system, an information and communication integration system, an energy system, a modular reconfigurable structure system, a control and propulsion system, and a tether mechanism system (including an electromagnetic docking mechanism and a tether retraction and deployment mechanism). It adopts an integrated open architecture and is a distributed satellite system that can be physically separated and informationally integrated.

[0032] As Figure 2 shown, in this embodiment, the mother satellite and the daughter satellite are combined side by side in the Y direction by explosion bolts during launch, with a compact structure, which can not only adapt to the upper stage of liquid rockets for carrying, but also adapt to the separate transportation of small solid rockets. After the double satellites are in orbit, the explosion bolts are unlocked, and then they are separated through the electromagnetic docking mechanism. The tether retraction and deployment mechanism releases the tether. Using the control and propulsion system, both the mother satellite and the daughter satellite reach their respective predetermined flight positions and maintain a stable configuration for operation; the stable flight configuration of the double satellites is as Figure 3As shown, when in distributed flight, the satellites are arranged one above the other. By relying on the tether retraction and deployment mechanism and the gravity gradient, each sub-satellite is in a vertically stable attitude, and the tether passes through the centers of mass of the mother satellite and the sub-satellites simultaneously when the dual satellites are in flight. When multiple satellites converge, the tether retraction and deployment mechanism retracts the tether, and the sub-satellites autonomously combine and dock in orbit through the electromagnetic docking mechanism; each sub-satellite can fly in a combined state or a dispersed holding state.

[0033] The preferred design solutions for each subsystem are described below:

[0034] The payload system is configured according to mission requirements. The technical solution of the present invention is particularly applicable to the interferometric SAR payload.

[0035] The information and communication integrated system, that is, the integrated electronic system of the satellite, preferably adopts a multi-functional fusion and definable design. On a single-piece hardware platform, through software, it realizes integrated communication of TT&C, data transmission, and inter-satellite (high-speed and low-speed) communication. The reliability of software configuration loading is solved through a configuration file triple modular redundancy, and the software is reconfigured to define the system functions through on-orbit uploaded configuration files.

[0036] The energy system transfers energy between the mother satellite and the sub-satellites, realizes power grid connection between satellites and bidirectional energy transmission, and ensures that each satellite has sufficient energy to carry out relevant tasks before separation.

[0037] The modular reconfigurable structure system designs the main load-bearing structure as a cuboid frame, with multiple accommodating spaces formed inside. The entire satellite adopts a modular design, and the layout is as Figure 4 shown, divided into a payload and payload electronics module (belonging to the payload system), an integrated electronics module (belonging to the information and communication integrated system), a body-mounted solar wing and battery module (belonging to the energy system), a propulsion module, and a control execution and sensor module (belonging to the control and propulsion system), a tether module (belonging to the tether mechanism system), etc.; body-mounted solar wings are installed on the -Z, +X, -X, -Y planes of the satellite, the TT&C antennas are arranged on the +Z and -Z planes of the satellite, the data transmission antennas are arranged on the +Z plane of the satellite, the control and propulsion system is fixed on the -Z plane, and the rope outlet of the tether mechanism is arranged at the central position on the -Y plane (near the +Z side) of the mother satellite. Except for the modular main load-bearing structure, TT&C data transmission antennas, payloads, and body-mounted solar wings, other modules are independent of each other, with simple interfaces, reducing the design coupling between modules. The control execution and sensor module, power module, integrated electronics module, and payload electronics module are connected to the modular main load-bearing structure through pull-out connections; the propulsion module and tether module are connected to the modular main load-bearing structure through external attachment connections.

[0038] The control and propulsion system includes a depth integration controller, attitude sensors, attitude actuators, and a micro-propulsion module. The specific control components are mainly miniaturized mature products. Star sensors, momentum wheels, and fiber optic gyroscopes are mature products, while magnetometers, magnetic torque actuators, sun sensors, etc. adopt off-the-shelf products. The attitude determination schemes adopt attitude prediction methods based on gyro measurements, attitude determination methods using gyro + star sensors, and attitude determination methods using magnetometer + sun sensor + gyro. The attitude control scheme adopts the zero-momentum control method of the momentum wheel and combines with the micro-propulsion module to complete the attitude and orbit coordinated control required during the adjustment of various stages such as combined flight, tether release and recovery, tether maintenance, inter-satellite synchronization, and independent flight.

[0039] The tether mechanism system includes an electromagnetic docking mechanism and a tether retraction and deployment mechanism. Among them, the electromagnetic docking mechanism can adopt a "rod-like - cone-like" micro-modular electromagnetic docking mechanism; the tether retraction and deployment mechanism includes a rope retraction and deployment component, a rope winding component, a rope detection component, a cutter component, and a rope fixing component, and has functions such as tether storage, release, recovery, arrangement, tension measurement, retraction and deployment length measurement, and cutting.

[0040] Specifically, the tethered double-star system realizes the autonomous separation and aggregation of the double stars without consuming fuel through the tether retraction and deployment mechanism. As Figure 5 shown, the specific composition and working principle of the tether retraction and deployment mechanism are as follows: The rope retraction and deployment component, the cutter component, the rope detection component, and the rope winding component are integrally installed on the side of the main star, and the rope outlet passes through the satellite's centroid. The rope fixing component is installed on the side of the sub-star and includes a tension sensor and a cutter component. Among them, the tension sensor is connected to the rope through a ball joint. The rope end connected to the rope fixing component is on the mother star side, passes through the rope retraction and deployment component, the cutter component, the rope detection component, and the rope winding component, and is connected to the drum in the rope winding component.

[0041] The rope retraction and deployment component consists of a retraction and deployment drive component, a driving wheel, a driven wheel, and a pre-tightening device. The retraction and deployment drive component provides power for the rotation of the driving wheel, the pre-tightening device provides sufficient normal pressure for the rope, and the driven wheel keeps the rope close to the surface of the driving wheel to ensure that the rope does not slip.

[0042] The rope detection component includes a tension sensor, a detection wheel, and two guide wheels. The rope is input by the first guide wheel, passes through the detection wheel, and is output by the second guide wheel. The rope drives the detection wheel to rotate during the retraction and deployment process, and the rope length measurement resolver records the retraction and deployment length of the rope. The tension sensor is used to feedback the rope tension and records the retraction and deployment length of the rope through the detection wheel and the rope length measurement resolver.

[0043] The rope winding assembly includes a winding drive assembly, a reel, a wire arranging mechanism, and a wire guiding mechanism. The wire arranging mechanism consists of a reciprocating cam, a guide rail, a slider, etc., which drives the wire guiding mechanism to move reciprocally. Through the design of preventing stacking with a fixed winding ratio, precise winding and accurate arrangement control of the rope are achieved.

[0044] The cutter assembly fires through an internal igniter to generate high-temperature and high-pressure gas, which pushes the cutter to cut the shear pin, and the cutter continues to move at high speed to cut the rope.

[0045] The main working modes of the tethering mechanism system include: separation and release mode, slow rope recovery mode, fast rope recovery mode, and rope length holding mode. Among them, the separation and release mode means that when the two celestial bodies separate, the rope releasing speed of the rope pay-off and take-up assembly and the rope winding assembly approaches the same, and the rope speed is greater than the separation speed of the two celestial bodies. The pay-off and take-up drive assembly and the winding drive assembly control the active release of the rope. At this time, there is no tension in the rope between the rope fixing assembly of the rope pay-off and take-up assembly, and it does not hinder the separation of the celestial bodies; the slow rope recovery mode means that the rope pay-off and take-up assembly winds the rope, and the rope winding assembly controls the winding speed of the winding drive assembly according to the tension feedback by the tension sensor, detects the linear speed of the internal rope, and controls the speed of the pay-off and take-up drive assembly, so as to achieve the rope recovery of the two celestial bodies at a given speed, and the rope recovery linear speed is adjustable; the fast rope recovery mode means that the rope pay-off and take-up assembly winds the rope, provides tension to the rope, and realizes that the rope winding acceleration is not less than 0.5m / s 2 , the duration is ≥3s, and the rope winding assembly controls the winding speed of the winding drive assembly according to the tension feedback by the tension sensor, so as to achieve fast recovery; the rope length holding mode means that after the two celestial bodies separate or recover to a certain distance, the rope pay-off and take-up assembly is powered on and held, and there is no external tension on the rope to overcome the friction of the friction wheel train, and the rope length between the two celestial bodies can be maintained.

[0046] For a multi-star system, only need to arrange a complete set of each component in the above-mentioned mother star in the sub-star again as the mother star of the next sub-star, and so on.

[0047] In the tethered binary star system of this embodiment, a stable formation flight configuration is formed. In the range of 100m to 10km, the tethered fast or slow pay-off and take-up tests can be gradually carried out, and the tethered orbit maneuver and safety avoidance ability tests can be carried out.

[0048] It can be understood that the present invention is described through embodiments. Those skilled in the art know that without departing from the spirit and scope of the present invention, various changes or equivalent replacements can be made to these features and embodiments. In addition, under the teaching of the present invention, these features and embodiments can be modified to adapt to specific situations without departing from the spirit and scope of the present invention. Therefore, the present invention is not limited by the specific embodiments disclosed herein, and the embodiments that can fall within the scope of the claims of this application all belong to the scope protected by the present invention.

[0049] The content not described in detail in the specification of the present invention belongs to the well-known technology of those skilled in the art.

Claims

1. A distributed satellite system based on a space tether, comprising at least two satellites, each satellite being equipped with a payload system, an integrated electronic system, an energy system, a structural system and a control and propulsion system, characterized in that: The satellites are connected to each other by a tether mechanism system, so that the satellites can be separated and aggregated, and the relative orbital positions of the satellites can be changed irregularly; the tether mechanism system includes an electromagnetic docking mechanism and a tether retracting and releasing mechanism; the satellites are a combination before entering orbit, and after entering orbit, the satellites are separated in orbit through the electromagnetic docking mechanism, and the tether retracting and releasing mechanism releases the rope, and each satellite maintains a stable flight configuration in a predetermined orbit; the stable flight configuration relies on the tether retracting and releasing mechanism and the gravity gradient to keep each satellite in a vertical stable posture, and the rope passes through the center of mass of each satellite at the same time; when multiple satellites aggregate, the tether retracting and releasing mechanism retracts the rope, and the satellites dock in orbit through the electromagnetic docking mechanism.

2. The space tether-based distributed satellite system according to claim 1, characterized in that: The tether retractable mechanism is divided into two parts, which are respectively installed on two satellites. The first component includes a rope fixing component, and the second component includes a rope retractable component, a cutter component, a rope detection component and a rope winding component. One end of the rope is connected to the rope fixing component, and the other end passes through each component in the second component in sequence, and is always in a tensioned state inside the satellite. Both the rope retracting and releasing assembly and the rope winding assembly have a driving assembly to actively control the rope retracting and releasing and winding speeds; the rope detection assembly includes a tension sensor, a detection wheel and two guide wheels. The rope is input by the first guide wheel and output by the second guide wheel after passing through the detection wheel. The tension sensor is connected to the detection wheel. During the retracting and releasing process, the rope drives the detection wheel to rotate. The rope length in the detection wheel is measured by rotation to obtain the length of the retracted and released rope.

3. The space tether-based distributed satellite system according to claim 2, characterized in that: The rope retracting assembly includes a retracting drive assembly, a driving wheel, a driven wheel and a pre-tensioning device. The retracting drive assembly provides power for the driving wheel to rotate, the pre-tensioning device provides positive pressure for the rope, and the driven wheel presses the rope against the surface of the driving wheel to prevent the rope from slipping. The rope winding assembly includes a winding drive assembly, a drum, a wire arrangement mechanism and a conductor mechanism. The winding drive assembly provides power for the drum to rotate, and the wire arrangement mechanism drives the conductor mechanism to reciprocate. The fixed winding ratio is designed to prevent rope stacking.

4. The space tether-based distributed satellite system according to claim 2, characterized in that: The working modes of the tether retracting and releasing mechanism include: separation release mode, slow rope retracting mode, fast rope retracting mode, and rope length maintaining mode; In the separation release mode, the rope releasing speeds of the rope retracting assembly and the rope winding assembly are consistent and greater than the two-star separation speed, the retracting drive assembly and the winding drive assembly control the active release of the rope, and there is no tension on the rope between the rope retracting assembly and the rope fixing assembly; In the slow rope recovery mode, the rope retracting assembly retracts the rope, and the rope winding assembly controls the winding speed of the winding drive assembly according to the tension fed back by the tension sensor. The length of the retracted rope is recorded through the detection wheel and the rope length measurement rotary transformer, the internal rope linear speed is obtained, and the speed of the retracting drive assembly is controlled, so that the two satellites retract the rope at a given speed; In the rope fast recovery mode, the rope retracting assembly retracts the rope, providing tension for the rope between the rope retracting assembly and the rope fixing assembly, so that the rope retracting acceleration is not less than 0.5m / s 2 , lasting ≥ 3s, and the rope winding assembly controls the winding speed of the winding drive assembly according to the tension fed back by the tension sensor, so that the two satellites can be quickly recovered; In the rope length holding mode, when the two satellites are separated or recovered to a certain distance, the rope retracting assembly is powered on to keep the rope length between the two satellites unchanged.

5. The space tether-based distributed satellite system according to claim 2, characterized in that: The cutter assembly ignites the internal igniter to generate gas, which pushes the cutter to cut the shear pin, allowing the cutter to continue moving to quickly cut the rope.

6. The distributed satellite system based on space tether according to any one of claims 2 to 5, characterized in that: For a binary star system, the second component of the tether retraction and extension mechanism is arranged in the parent star, and the first component is arranged in the daughter star; for a multi-star system, a complete set of the second component of the tether retraction and extension mechanism is arranged in the daughter star, which serves as the mother star of the next daughter star, and so on.

7. The space tether-based distributed satellite system according to claim 1, characterized in that: The tether length of the tether mechanism system ranges from 100m to 10km.

8. The space tether-based distributed satellite system according to claim 1, characterized in that: The control propulsion system is used to complete attitude estimation, attitude determination and attitude control; attitude estimation is implemented based on gyro measurement; attitude determination includes two methods, based on gyro and star sensor and based on gyro, magnetometer and digital sun sensor; attitude control is implemented based on momentum wheel zero momentum control and micro propulsion.

9. The space tether-based distributed satellite system according to claim 1, characterized in that: The structural system adopts a modular design. The main load-bearing structure is a rectangular frame with multiple accommodating spaces formed inside. The satellite's antenna and solar energy conversion components are installed on the outer surface of the main load-bearing structure, and the satellite's functional modules are distributed in different accommodating spaces. Among them, the control propulsion system and the tether mechanism system are connected to the modular main load-bearing structure through a stick-on connection, and the remaining functional modules are connected to the main load-bearing structure through a pull-out connection.

10. The space tether-based distributed satellite system according to claim 9, characterized in that: The -Z, +X, -X and -Y surfaces of the main load-bearing structure are installed with solar energy conversion components, the measurement and control antenna is located on the +Z and -Z surfaces of the satellite, and the data transmission antenna is located on the +Z surface of the satellite; the control propulsion system is fixed on the -Z surface, and the rope outlet of the tether mechanism system is located on the -Y surface and close to the +Z side; the X, Y and Z directions take the center of the bottom surface of the satellite as the coordinate origin, the Z axis points to the direction of the data transmission antenna, the Y axis points in the opposite direction to the rope outlet of the tether mechanism, and the X axis, Y axis and Z axis form a right-handed coordinate system.

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