WO2024093087A1

WO2024093087A1 - Adapting device for assisting in orbital transfer, and orbital transfer method

Info

Publication number: WO2024093087A1
Application number: PCT/CN2023/081472
Authority: WO
Inventors: 吴凡; 曹喜滨; 郭金生; 邱实; 王宏旭; 奚瑞辰; 陈雪芹
Original assignee: 哈尔滨工业大学
Priority date: 2022-11-02
Filing date: 2023-03-14
Publication date: 2024-05-10
Also published as: CN115402540A; CN115402540B

Abstract

An adapting device (10) for assisting in orbital transfer, and an orbital transfer method. The adapting device (10) comprises a target module (2), a docking module (3), and a connection module (4) that are provided on a substrate (1). The connection module (4) is configured to enable, after having undergone orbital transfer, a spacecraft waiting for orbital transfer to establish, in at least two connection modes, a fixed connection with a main spacecraft used for capturing the spacecraft waiting for orbital transfer, so as to keep the spacecraft waiting for orbital transfer stably on the main spacecraft.

Description

An adapter device for assisting track change and a track change method

CROSS-REFERENCE TO RELATED APPLICATIONS

This application claims the priority of a Chinese patent application filed with the Chinese Patent Office on November 2, 2022, with application number 202211361134.7 and invention name “An adapter device and track changing method for assisting track changing”. The contents of the Chinese patent application are hereby introduced into this application as a reference.

Technical Field

The present disclosure relates to the technical field of spacecraft devices, and more specifically to an adaptation device and an orbit change method for assisting orbit change.

Background technique

With the rapid advancement of technology in the field of small satellites and the reduction of launch costs, it has become a major trend to use small satellites, even micro-nano satellites, for rapid scientific experiments and technical verification, and even to form satellite constellations for military, civilian and commercial applications. In 2007, the Space Debris Coordination Committee (IADC) proposed a requirement to deorbit 25 years after the mission is completed. However, it is difficult for most satellites to deorbit and re-enter the atmosphere to burn up in a short period of time after the mission is completed, thus becoming space debris that stays in orbit for a long time and threatens other main spacecraft. Therefore, the challenges of controlling traffic in outer space are increasing day by day, and the probability of collisions and conflicts in space traffic is also increasing. The resulting space debris will affect the safety of space stations, artificial satellites, probes and spacecraft in space orbits. When space debris collides with other space devices, new space debris will be generated. Therefore, it is urgent to conduct orbit change research for space debris, or spacecraft that have not entered the set orbit/failed due to malfunctions/exhausted energy/still occupy the orbit after the mission is completed, or a series of spacecraft that need to adjust their orbits due to mission requirements.

For spacecraft, typical orbit change methods are divided into active and passive. Active orbit change is to use the power device carried by the spacecraft to be changed to lower or increase its own orbital altitude and leave the original orbit; passive orbit change is to let the spacecraft to be changed use the film sail device, electric power tether, drag ball, etc. to act on the spacecraft to be changed to change its orbital altitude. In the existing technology, the performance of the satellite at the end of its life, the reliability of the problem is reduced, and relying solely on electric propulsion or other active orbit change methods cannot guarantee reliable orbit change, and at the same time increase the additional launch mass.

In comparison, by using the adaptation device and method described in the present invention, there is no need to consider the completeness of the power function of the spacecraft to be changed, nor is there a need to carry an additional orbit change power device when the spacecraft to be changed is launched, thereby avoiding occupying precious resources for the launch of the spacecraft to be changed.

Technical content

An embodiment of the present disclosure provides an adapter device and an orbit change method for assisting orbit change. The adapter device is installed on a spacecraft to be changed that is unable to change its orbit autonomously. Through the identification, capture and fixation of the main spacecraft, the adapter device can assist the spacecraft to be changed in changing its orbit after being identified, captured and fixed.

The technical solution of the embodiment of the present disclosure is achieved as follows:

In a first aspect, an embodiment of the present disclosure provides an adapter device for assisting orbit change, the adapter device comprising a target module, a docking module and a connection module arranged on a substrate: the substrate is fixedly mounted on the body of the spacecraft to be changed in orbit; the target module is configured to provide the attitude information and position information of the spacecraft to be changed in orbit to a main spacecraft used to capture the spacecraft to be changed in orbit by means of optical communication; the docking module is configured to establish a rigid connection with the main spacecraft to achieve the capture of the spacecraft to be changed in orbit; the connection module is configured to establish a fixed connection with the main spacecraft in at least two connection modes after the spacecraft to be changed in orbit is captured so as to stably keep the spacecraft to be changed in orbit on the main spacecraft so as to achieve the orbit change and/or capture of the spacecraft to be changed in orbit.

In a second aspect, an embodiment of the present disclosure provides a method for assisting orbit change, and the orbit change method is applied to the adapter device described in the first aspect: a main spacecraft sends a signal light to a spacecraft to be changed in orbit, and the main spacecraft obtains and analyzes the signal light reflected by a target module installed in the adapter device of the spacecraft to be changed in orbit to obtain the position information and attitude information of the spacecraft to be changed in orbit; the main spacecraft approaches the spacecraft to be changed in orbit according to the position information and attitude information of the spacecraft to be changed in orbit, so that the main spacecraft is docked with the docking module of the adapter device after rigid contact; during the operation of the connection module, the connection module establishes a fixed connection between the spacecraft to be changed in orbit and the main spacecraft in at least two connection modes.

The embodiments of the present disclosure provide an adapter device and a method for assisting orbit change, wherein the adapter device provides the attitude information and position information of the spacecraft to be changed to the main spacecraft through the target module as the control basis of the capture action, and the docking module can complete the capture of the spacecraft to be changed to achieve the orbit change of the spacecraft to be changed in a simple and low-buffered docking form, thereby improving the fault tolerance of capture, and the docking module is simple to manufacture, and the connection module can further keep the spacecraft to be changed on the main spacecraft. The adapter device has flexible configuration and a wide range of uses, and can be applied to capture and docking in complex space environments.

BRIEF DESCRIPTION OF THE DRAWINGS

In order to more clearly illustrate the technical solution of the embodiment of the present disclosure, the following briefly introduces the drawings required for describing the embodiment. The drawings described below are only exemplary embodiments of the present disclosure.

FIG1 is a schematic diagram of an adaptation device for assisting track change provided in an embodiment of the present disclosure.

FIG. 2 is a top view of a substrate in an adapter device for assisting track change provided in an embodiment of the present disclosure.

FIG3 is a side view of an adapter device for assisting track change provided in an embodiment of the present disclosure.

FIG4 is a flow chart of a track change method for assisting track change provided in an embodiment of the present disclosure.

Detailed ways

In order to make the purpose, technical solution and advantages of the present disclosure more obvious, the exemplary embodiments according to the present disclosure will be described in detail with reference to the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present disclosure, rather than all the embodiments of the present disclosure, and it should be understood that the present disclosure is not limited to the exemplary embodiments described here.

The principle of the capture-type orbit change in the prior art is to capture the spacecraft to be changed whose orbit needs to be changed by a main spacecraft carrying a capture device such as a mechanical arm or telescopic rod or a flying net, a flying claw, etc., and the spacecraft to be changed is provided with a captured device adapted to the capture device. Among them, the flying net capture is that the main spacecraft throws a lightweight and flexible flying net to the spacecraft to be changed, and at the same time connects to the flying net through a rope, wraps the spacecraft to be changed by the flying net, and uses the rope to apply tension to pull the spacecraft to be changed out of the original orbit to achieve the orbit change. However, the flying net capture is not applicable to all orbital spaces, and the control over the spacecraft to be changed is also limited, and it cannot be recycled after use; the flying claw capture is that the main spacecraft launches a harpoon with a rope at the end to the spacecraft to be changed. The harpoon can penetrate the target surface and embed itself inside the spacecraft to be changed, and the rope applies tension. The spacecraft to be changed in orbit is separated from its original orbit to achieve orbit change. Using a harpoon to capture a satellite is not applicable to all orbital spaces, and selecting the harpoon embedding position will generate space debris and damage the original spacecraft to be changed in orbit. Compared with the above two capture methods, the capture method using the orbit change adapter device described in the present invention can be applied to all orbital spaces and effectively control the spacecraft to be changed in orbit. In addition, the existing orbit change adapter only has a single connection function. Once the connection function is unstable or fails, the adapter completely loses its function, resulting in the failure of the capture action of the spacecraft.

In order to solve the above technical problems, an embodiment of the present disclosure provides an adapter device 10 for assisting orbit change, and the adapter device 10 has high connection reliability. Referring to Figure 1, it shows an adapter device 10 for assisting orbit change disclosed in an embodiment of the present disclosure, the adapter device 10 includes a target module 2, a docking module 3 and a connection module 4 installed on a substrate 1, and the adapter device 10 is installed to the body of the spacecraft to be changed through the substrate 1 to form a whole, the target module 2 can be used to capture the main spacecraft of the spacecraft to be changed to identify and obtain the position information and attitude information of the spacecraft to be changed as the control basis for capturing the spacecraft to be changed, the docking module 3 is used to establish a rigid connection with the main spacecraft to realize the capture of the spacecraft to be changed to leave the orbit, and when the spacecraft to be changed is captured, the connection module 4 interacts with the main spacecraft to realize the fixed connection of the spacecraft to be changed on the main spacecraft.

The target module 2 is configured to provide the attitude information and position information of the spacecraft to be changed to the main spacecraft used to capture the spacecraft to be changed in an optical communication manner. The main spacecraft has a light source device capable of emitting signal light, and the light source device can be an LED lamp. The target module can reflect the received signal light. The main spacecraft obtains the signal light reflected by the target module through a camera to parse the position and attitude information of the spacecraft to be changed. Then the main spacecraft uses its own attitude and orbit control unit to approach the spacecraft to be changed. The target module 2 includes a plurality of optical beacons, which are passive optical devices that can reflect the signal light emitted by the light source device and be acquired by the camera. Referring to FIG. 2 , which shows a top view of the adapter device 10 , the target module 2 is disposed at a corner of the substrate 1 , and the plurality of optical beacons include a first beacon 201 , a second beacon 202 , and a third beacon 203 distributed in a triangular shape, wherein the first beacon 201 and the second beacon 202 are configured in a rectangular shape, and the third beacon 203 is configured in an L shape. The above configuration can improve the light reflectivity per unit area of the target module 2 and maintain a small divergence. Preferably, the optical beacon has a coating to enhance the reflectivity and reflection angle to ensure the accuracy of the master spacecraft's solution of the attitude and position of the spacecraft to be changed.

The docking module 3 is configured to establish a rigid connection with the main spacecraft to achieve the capture of the spacecraft to be changed. In the prior art, the main spacecraft can fully control the attitude and orbit of the target spacecraft to be changed when capturing the spacecraft to be changed, but there are technical problems such as rigid contact causing difficulty in capture during the capture process. In view of this, the docking module 3 is constructed to include a connecting platform 301 and a docking head 302, referring to Figures 1 to 3, the connecting platform 301 is protruding from the surface of the substrate 1 and is located at a corner adjacent to the target module 2 on the surface of the substrate 1, and the docking head 302 is coaxially arranged on the connecting platform 301. The main spacecraft obtains the attitude information and position information of the spacecraft to be changed by means of the multiple optical beacons and then docks with the docking module 3 to achieve the capture of the spacecraft to be changed, referring to Figures 1 and 2, the docking head 302 is constructed to have a spherical end, the configuration structure is simple and reliable and has low processing difficulty, and the docking head 302 can reduce the capture accuracy requirements and improve fault tolerance when being captured by the main spacecraft under this configuration. In addition, the spherical docking joint 302 reduces the mechanical collision when capturing the spacecraft to be changed in orbit, reduces the buffer, and is different from the complex docking mechanism in the prior art. The spherical docking joint 302 can be easily captured. When the spacecraft to be changed in orbit is rotating, the docking joint 302 can still be captured under lower capture accuracy requirements and attitude control requirements. After being captured by the main spacecraft, the docking joint 302 has friction with the end of the grasping device on the main spacecraft used to grasp the docking joint 302. The grasping device can be a mechanical arm that can extend out of the main spacecraft body or return to the main spacecraft body. Since the contact surface between the docking joint 302 and the end of the grasping device is a spherical surface, the spacecraft to be changed in orbit can also be de-rotated under this friction. Preferably, referring to Figure 3, the docking joint 302 protrudes 13 cm from the surface of the substrate 1.

When the spacecraft to be changed in orbit is captured by the main spacecraft, the end of the grasping device grasps the docking head 302, and drives the spacecraft to be changed in orbit to leave the original orbit and approach the main spacecraft through the contraction of the grasping device to achieve the change of orbit of the spacecraft to be changed in orbit. At this time, the spacecraft to be changed in orbit is only held on the main spacecraft by the grasping device. In order to stably hold the spacecraft to be changed in orbit, the connection module 4 in the adapter device 10 starts to work after the spacecraft to be changed in orbit contacts the main spacecraft, and establishes a fixed connection between the spacecraft to be changed in orbit and the main spacecraft. In the existing capture adapter, there is only a single connection function. Once the connection function is unstable or fails, the adapter completely loses its function, resulting in the failure of the orbit change action of the spacecraft to be changed in orbit. In view of this, the connection module 4 is constructed to be able to be used to connect with the main spacecraft in at least two different connection modes at the same time, so as to stably hold the spacecraft to be changed in orbit on the main spacecraft. The connection module 4 includes an electromagnetic connection unit 401, an adhesive connection unit 402 and a rope connection unit 403. The connection module 4 is configured to establish a connection with the main spacecraft through at least any two of the multiple connection units when the non-target satellite is captured by the main spacecraft. It should be noted that when the electromagnetic connection unit 401 and the adhesive connection unit 402 are fixedly connected with the main spacecraft, it is not required that the main spacecraft has corresponding components to cooperate with the electromagnetic connection unit 401 or the adhesive connection unit 402 to complete the establishment of the fixed connection. The rope connection unit 403 interacts with the corresponding rope connection device on the main spacecraft to establish a fixed connection. Preferably, each of the above connection units can be replaced according to the matching connection device on the main spacecraft.

Referring to Figures 1 and 2, the electromagnetic connection unit 401 is arranged under the surface of the substrate 1, preferably, arranged inside the substrate 1, and the electromagnetic connection unit 401 includes an electromagnetic connector arranged inside the substrate 1, and the electromagnetic connector is mainly composed of a permanent magnet or a ferromagnet. When the spacecraft to be changed in orbit is captured, the electromagnetic connector is adsorbed to the main spacecraft body through magnetic force, so that the spacecraft to be changed in orbit is close to the main spacecraft to achieve the stable maintenance of the spacecraft to be changed in orbit.

In another embodiment of the present disclosure, when the main spacecraft has a harpoon capable of penetrating the surface of the substrate 1 and deploying a stop pin inside the substrate 1, the adapter device 10 can replace the electromagnetic connection unit 401 with a puncture connection unit according to the configuration of the main spacecraft, wherein, referring to FIG1 , the puncture connection unit is arranged at the same position as the electromagnetic connection unit 401 in a corner of the substrate 1 adjacent to the docking module 3.

Referring to Figures 1 to 3, the adhesive connection unit 402 is arranged at a corner adjacent to the target module 2 on the surface of the substrate 1, and the adhesive connection unit 402, the electromagnetic connection unit 401 (or the puncture connection unit) and the docking module 3 are distributed in a triangular shape at the three corners of the surface of the substrate 1. The above arrangement configuration can firmly maintain the spacecraft to be changed on which the adapting device 10 is installed on the main spacecraft. The adhesive connection unit 402 is composed of hot melt adhesive. The hot melt adhesive has very stable performance at room temperature and will not adhere to any device or equipment. It has viscosity only when it is heated and can complete bonding within a few seconds after melting into a viscous liquid, and the bonding ability is stable. Preferably, the adhesive connection unit 402 includes a plurality of glue dots forming a rectangular adhesive array, and the arrangement of the glue dots helps to arrange the positions of other modules and/or components on the substrate 1. Among them, the adhesive connection unit 402 can also be a hot melt adhesive film. The adhesive array can begin to melt due to heat after the gripping device on the main spacecraft captures the docking joint 302 so that the adhesive connection unit 402 adheres to the gripping device, thereby directly fixing the spacecraft to be changed in orbit to the gripping device. In another embodiment of the present disclosure, the adhesive array can also begin to melt due to heat after the gripping device drives the spacecraft to be changed in orbit to contact the main spacecraft body so that the adhesive connection unit 402 adheres to the main spacecraft body, thereby directly fixing the spacecraft to be changed in orbit to the main spacecraft body.

Referring to Figures 1 and 3, further, the rope connection unit 403 includes a plurality of rope connection columns arranged on the lower surface of the base plate 1, and the rope connection columns are adapted to the main spacecraft of the flexible lasso or rope, where the flexible lasso and/or rope can be wound and locked to the rope connection columns. The rope connection columns are fixed to the base plate 1 by bolts, and by arranging the rope connection unit 403 on the lower surface of the base plate 1, the fixing direction of the adapter 10 and the main spacecraft is diversified, and the design and arrangement of the plurality of connection units on the connection module 4 are more reasonable. In the prior art, the method of driving the spacecraft to be changed in orbit by capturing has the technical problems of high capture difficulty and high energy consumption. The rope connection unit 403 can start working after the spacecraft body captures the spacecraft to be changed in orbit. In the process of the spacecraft to be changed in orbit approaching the main spacecraft, the connection between the rope and the rope connection column can assist the grasping device to control and stabilize the attitude of the spacecraft to be changed in orbit, thereby enhancing the flexibility of capturing the satellite. At the same time, it can also assist the grasping device to pull the spacecraft to be changed in orbit away from the original orbit to achieve orbit change. When the spacecraft to be changed in orbit contacts the main spacecraft body, the rope can be wound around and locked to the rope connection column to achieve the fixed connection between the spacecraft to be changed in orbit and the main spacecraft. Preferably, referring to Figures 1 and 2, the number of the rope connection columns is three or more, preferably three and distributed in a triangular shape on the lower surface of the substrate 1 to ensure the stability of the connection. Preferably, the length of the rope connection column protruding from the lower surface of the substrate 1 is 35 cm.

It should be noted that when the main spacecraft has both a harpoon for piercing the substrate 1 and a rope that can be wound around the rope connecting column, the piercing connection unit and the rope connecting unit 403 begin to connect with the main spacecraft at the same time. After the harpoon is fixed to the substrate 1, the rope connecting unit 403 is released, thereby ensuring the reliability of the connection between the main spacecraft and the adapter device 10 and saving the energy of the main spacecraft.

In another embodiment of the present disclosure, in order to further enhance the connection stability between the spacecraft to be changed and the main spacecraft after being captured, and to enhance the diversity and versatility of the functions of the adapter device 10, the adapter device 10 also includes a locking module 5, the locking module 5 includes a latch hole 51 arranged on the substrate 1, the locking module 5 can be adapted to the main spacecraft with a latch, and the latch is inserted into the latch hole 51 in a retractable manner to stably lock the spacecraft to be changed on the main spacecraft. When the spacecraft to be changed is captured and the connection module 4 completes the connection, the locking module 5 cooperates with the main spacecraft to start working, and the latch is inserted into the latch hole 51, wherein, preferably, the number of the latch holes 51 is three, referring to Figures 1 to 3, the latch holes 51 are arranged on three adjacent surfaces at a corner of the substrate 1, and the arrangement directions of the three latch holes 51 are perpendicular to each other, ensuring that the supporting force of the latch on the substrate 1 is perpendicular to each other to stably maintain the substrate 1.

Referring to Figures 2 and 3, the substrate 1 is configured in a square shape. Preferably, the substrate 1 has a side length of 80 cm and a thickness of 6 cm. Then, the total thickness of the adapter 10 is 54 cm. The substrate 1 is fixedly mounted on the body of the spacecraft to be changed orbit, thereby forming a whole with the spacecraft to be changed orbit. The mounting method thereof can be welding or other mounting connection methods used in the field of space devices in the prior art.

Referring to FIG. 4 , the embodiment of the present disclosure further discloses a trajectory change method for assisting trajectory change, the trajectory change method is applied to the adaptation device disclosed in the above embodiment of the present disclosure, and in the process of using the trajectory change method to drive the spacecraft to be traversed to achieve trajectory change in a capture manner:

S401: The main spacecraft sends a signal light to the spacecraft to be changed orbit, and the main spacecraft obtains and analyzes the signal light reflected by the target module installed in the adapter device of the spacecraft to be changed orbit to obtain the position information and attitude information of the spacecraft to be changed orbit;

S402: the main spacecraft approaches the spacecraft to be changed orbit according to the position information and attitude information of the spacecraft to be changed orbit, so that the main spacecraft is in rigid contact with the docking module of the adapter device and then docks with the docking module;

S403: During the operation of the connection module, the connection module establishes a fixed connection between the spacecraft to be changed orbit and the main spacecraft in at least two connection modes.

Among them, the light source device of the main spacecraft emits signal light, the target module can reflect the signal light so that it is captured by the camera on the main spacecraft, and the information processing unit of the main spacecraft can analyze the captured light to obtain the attitude and position information of the spacecraft to be changed. The main spacecraft can rely on the information to approach the spacecraft to be changed to achieve subsequent actions.

After the main spacecraft approaches the spacecraft to be changed in orbit, the grasping device installed on the main spacecraft is rigidly docked with the docking module to capture the spacecraft to be changed in orbit. After being captured, the grasping device contracts to drive the spacecraft to be changed in orbit to approach the main spacecraft. Specifically, the docking module includes a connecting platform and a docking head. The grasping device extends out of the main spacecraft body to approach the spacecraft to be changed in orbit. The grasping device is preferably a mechanical arm that can extend out of the main spacecraft body or return to the main spacecraft body. The front end of the mechanical arm is configured as a claw-like structure that can be opened and closed to grasp the docking head. The docking head is configured to be spherical. Through the friction between the grasping device and the spherical docking head, the main spacecraft can derotate the spacecraft to be changed in orbit, thereby controlling the posture of the spacecraft to be changed in orbit, so that the spacecraft to be changed in orbit tends to a stable state. After the grasping device captures the spacecraft to be changed in orbit, it begins to contract to the main spacecraft body, thereby driving the spacecraft to be changed in orbit to leave the original orbit and realize orbit change.

During the operation of the connection module, the connection module on the spacecraft to be changed orbit establishes a fixed connection between the spacecraft to be changed orbit and the main spacecraft in at least two connection modes, and the connection module includes an electromagnetic connection unit, an adhesive connection unit and a rope connection unit. Specifically, the connection module can select at least two of the above connection units according to the devices equipped by the main spacecraft to achieve a fixed connection between the spacecraft to be changed orbit and the main spacecraft, wherein:

When the spacecraft to be changed in orbit approaches the main spacecraft body under the drive of the grasping device, the electromagnetic connection unit fixedly connects the spacecraft to be changed in orbit to the main spacecraft by electromagnetic force adsorption through an electromagnetic connector or a permanent magnet. In another embodiment, the electromagnetic connection can directly fix the spacecraft to be changed in orbit to the grasping device through the electromagnetic force.

The adhesive connection unit includes an adhesive array, and the adhesive array is heated and melted when approaching the main spacecraft body under the drive of the grasping device, and the spacecraft to be changed to the main spacecraft body is adhered to the main spacecraft body through the adhesive array. In another embodiment, the adhesive array can begin to be heated and melted after the grasping device captures the docking head, thereby directly fixing the spacecraft to be changed to the grasping device;

The rope connection unit includes a rope connection column. After the spacecraft to be changed in orbit approaches and contacts the main spacecraft body under the drive of the grasping device, the main spacecraft extends a rope, and the rope is wound around and locked to the rope connection column. Through the mechanical connection between the rope and the rope connection column, the spacecraft to be changed in orbit is stably maintained on the main spacecraft body. In another embodiment of the present disclosure, after the grasping device captures the connecting head, the main spacecraft extends a rope and winds it around the rope connection column to assist the grasping device in adjusting and stabilizing the posture of the spacecraft to be changed in orbit, thereby improving the reliability and efficiency of capturing the spacecraft to be changed in orbit. When the grasping device contracts to drive the spacecraft to be changed in orbit to leave the original orbit and approach the main spacecraft, the ropes can contract together to speed up the orbit change process. When the spacecraft to be changed in orbit contacts the main spacecraft body, the rope is locked to the rope connection column to stably maintain the spacecraft to be changed in orbit on the main spacecraft.

It should be noted that the technical solutions described in the embodiments of the present disclosure can be combined arbitrarily without conflict.

The above is only a specific embodiment of the present disclosure, but the protection scope of the present disclosure is not limited thereto. Any person skilled in the art who is familiar with the technical field can easily think of changes or substitutions within the technical scope disclosed in the present disclosure, which should be included in the protection scope of the present disclosure. Therefore, the protection scope of the present disclosure should be based on the protection scope of the claims.

Industrial Applicability

In this embodiment, the adapter device provides the attitude information and position information of the spacecraft to be changed to the main spacecraft through the target module as the control basis of the capture action. The docking module can complete the capture of the spacecraft to be changed and realize the change of the spacecraft to be changed in a simple and low-buffered docking form, which improves the fault tolerance of capture. The docking module is simple to manufacture, and the connection module can further keep the spacecraft to be changed on the main spacecraft. The adapter device has flexible configuration and a wide range of uses, and can be applied to capture and docking in complex space environments.

Claims

An adapter device for assisting track change, the adapter device comprising a target module, a docking module and a connection module arranged on a substrate, characterized in that:

The base plate is fixedly mounted on the body of the spacecraft to be changed in orbit;

The target module is configured to provide the attitude information and position information of the spacecraft to be changed orbit to the main spacecraft used to capture the spacecraft to be changed orbit in a manner of optical communication;

The docking module is configured to establish a rigid docking with the main spacecraft to achieve the capture of the spacecraft to be changed in orbit;

The connection module is configured to establish a fixed connection with the main spacecraft in at least two connection modes after the spacecraft to be changed orbit is captured, so as to stably maintain the spacecraft to be changed orbit on the main spacecraft, thereby realizing the orbit change of the spacecraft to be changed orbit.
The adapter device according to claim 1 is characterized in that the docking module includes a connecting platform protruding from the surface of the substrate and a docking head arranged on the connecting platform, and the docking head is constructed into a spherical shape.
The adaptation device according to claim 1 is characterized in that the connection module includes an electromagnetic connection unit, an adhesive connection unit and a rope connection unit, and the connection module is configured to use at least two of the electromagnetic connection unit, the adhesive connection unit and the rope connection unit to simultaneously establish a fixed connection with the main spacecraft after the main spacecraft captures the spacecraft to be changed.
The adapter device according to claim 3 is characterized in that the electromagnetic connection unit includes an electromagnetic connector arranged inside the substrate, and the electromagnetic connector is configured so that when the main spacecraft captures the spacecraft to be changed, the electromagnetic connector establishes a fixed connection between the spacecraft to be changed and the main spacecraft by mutual attraction through electromagnetic force.
The adaptation device according to claim 3 is characterized in that the adhesive connection unit includes an adhesive array arranged on the surface of the substrate, and the adhesive connection unit is configured so that when the main spacecraft captures the spacecraft to be changed orbit, the adhesive array melts and adheres to the main spacecraft to establish a fixed connection between the spacecraft to be changed orbit and the main spacecraft.
The adaptation device according to claim 3 is characterized in that the rope connection unit includes a rope connection column arranged at the bottom of the base plate, and the rope connection unit is configured so that when the main spacecraft captures the spacecraft to be changed orbit, the rope connection column is wrapped and locked by the rope loop on the main spacecraft to establish a fixed connection between the spacecraft to be changed orbit and the main spacecraft.
The adapter device according to claim 1 is characterized in that the adapter device also includes a locking module, the locking module includes a latch hole arranged on the substrate, the locking module is configured to adapt to a main spacecraft with a latch, and the locking module starts to work after the connection module establishes a fixed connection with the main spacecraft, and receives the latch through the latch hole.
A track changing method for assisting track changing, the track changing method is applied to the adapter device according to any one of claims 1 to 7, characterized in that:

The main spacecraft sends a signal light to the spacecraft to be changed in orbit, and the main spacecraft obtains and analyzes the signal light reflected by the target module installed in the adapter device of the spacecraft to be changed in orbit to obtain the position information and attitude information of the spacecraft to be changed in orbit;

The main spacecraft approaches the spacecraft to be changed orbit according to the position information and attitude information of the spacecraft to be changed orbit, so that the main spacecraft is docked with the docking module of the adapter device after being in rigid contact with the docking module;

During the operation of the connection module, the connection module establishes a fixed connection between the spacecraft to be changed orbit and the main spacecraft in at least two connection modes.
The orbit change method according to claim 8 is characterized in that the connection module includes an electromagnetic connection unit, an adhesive connection unit and a rope connection unit, and accordingly, the connection module establishes a fixed connection between the spacecraft to be changed and the main spacecraft in at least two connection modes, specifically referring to:

The connection module realizes the fixed connection between the spacecraft to be changed and the main spacecraft in at least two ways as follows, wherein:

The electromagnetic connection unit is used to fix the spacecraft to be changed to the main spacecraft by mutual attraction of electromagnetic force;

The hot glue array in the bonding unit is melted by heat, and the spacecraft to be changed orbit is fixed to the main spacecraft by melting and then solidifying the glue array;

The rope connecting unit is used to receive the rope thrown out by the main spacecraft, and the rope is wound around and locked on the rope connecting column of the rope connecting unit to fix the spacecraft to be changed to the main spacecraft.
The orbit change method according to claim 8 is characterized in that the docking module includes a spherical docking head, and accordingly, the main spacecraft approaches the spacecraft to be changed according to the position information and attitude information of the spacecraft to be changed, so that the main spacecraft is docked with the docking module after rigid contact with the docking module of the adapter device, specifically referring to:

The main spacecraft autonomously brakes and approaches the spacecraft to be changed orbit according to the position information and attitude information of the spacecraft to be changed orbit;

The main spacecraft approaches the spacecraft to be changed orbit with the docking head as the target;

The main spacecraft grabs the docking head and de-rotates the spacecraft to be changed in orbit by friction.