CN112158360B

CN112158360B - On-orbit service and maintenance verification method and system

Info

Publication number: CN112158360B
Application number: CN202011076568.3A
Authority: CN
Inventors: 陈晓光; 齐玢; 李恩奇; 张志贤; 胡骏; 张柏楠
Original assignee: Beijing Institute of Spacecraft System Engineering
Current assignee: Beijing Institute of Spacecraft System Engineering
Priority date: 2020-10-10
Filing date: 2020-10-10
Publication date: 2022-04-19
Anticipated expiration: 2040-10-10
Also published as: CN112158360A

Abstract

The invention relates to an on-orbit service and maintenance verification method for a manned spacecraft, which comprises the following steps of a, building a test environment, transporting materials required by on-orbit verification to an off-ground space station, and quickly building the test environment by utilizing the existing resources of the manned space system and the flexible control capability of the spaceman; b. assembling materials in the form of a cubic star module in a space station cabin, and performing on-orbit comprehensive detection on the materials; c. and releasing the target object in the material to the outside of the space station cabin, and respectively carrying out an approaching observation test and a net capture test. Compared with other technical verification methods, the method has the advantages of good technical foundation, strong support capability, small task risk, more guarantee resources, low test cost, high efficiency, comprehensive verification and the like.

Description

On-orbit service and maintenance verification method and system

Technical Field

The invention relates to an on-orbit service and maintenance verification method and system.

Background

With the rapid development of aerospace technology, on-orbit service and maintenance become an important development direction, and the wide attention of the international society is drawn.

The on-orbit service and maintenance technology is an important field of future space technology development, and aims to ensure stable and reliable operation of space assets in China and improve comprehensive use benefits of the space assets in China.

The on-orbit maintenance is a series of technical means which are mainly adopted for improving the use value of the high-value cubic star and protecting the space environment, and the main tasks of the on-orbit maintenance comprise: the method comprises the following steps of inspection tour detection, module replacement, auxiliary expansion, on-orbit filling, control take-over, auxiliary orbit transfer, active fragment removal, on-orbit processing, on-orbit assembly, on-orbit reconstruction and the like, and the related key technologies comprise a non-cooperative target identification and relative measurement technology, a mechanical arm and tail end operation technology, an on-orbit assembly technology, an on-orbit comprehensive detection technology, a flying net capture control technology, an on-orbit filling technology, an on-orbit processing technology and the like.

The on-orbit service and maintenance involve a plurality of key technologies, and a large amount of special technical research, flight tests and on-orbit application are carried out on the key technologies for a long time in main aerospace countries in the world, so that a large amount of breakthrough and achievement are obtained. From experience of development of on-orbit service and maintenance technology, on-orbit verification of related key technology is usually started from LEO. The manned spacecraft provides a good technical verification platform for on-orbit service and maintenance. The verification and application of a plurality of types of on-orbit service and maintenance technologies such as on-orbit assembly, on-orbit filling, on-orbit maintenance and the like are completed by the construction and operation of a peace-mark space station, an international space station and the like in the aerospace major countries such as the United states and Russia.

From the current technology, the verification process is basically a single test for each project, is dispersed and trivial, and a complete and mature verification scheme is not provided for on-track verification. And, each verification project is basically performed depending on the space station. If the verification is performed separately and separately, it takes a lot of time and takes up many space station resources, so a complete and efficient verification technique is needed.

Disclosure of Invention

The invention aims to provide a complete on-orbit service and maintenance verification method and a complete on-orbit service and maintenance verification system.

In order to achieve the above object, the present invention provides an on-orbit service and maintenance verification method and system, wherein the method comprises the following steps:

a. building a test environment, transporting materials required by on-orbit verification to an extra-terrestrial space station, and quickly building the test environment by utilizing the existing resources of the manned space system and the flexible control capability of the astronauts;

b. assembling materials in the form of a cubic star module in a space station cabin, and performing on-orbit comprehensive detection on the materials;

c. and releasing the target object in the material to the outside of the space station cabin, and respectively carrying out an approaching observation test and a net capture test.

According to one aspect of the invention, in said step (a), the existing resources of the manned space system include a space station for providing a test site, an optical cabin for observation, a cargo ship for transporting cargo, a manned ship for transporting astronauts, and a ground telemetry module for acquiring test telemetry data; the transported materials comprise a test cube composition module, a target satellite, an on-orbit comprehensive detection module and a small satellite launching device. The astronaut arranges the composition module of the test cube to a designated position in the cabin, then installs the on-orbit comprehensive detection module and the small satellite launching device on a load platform outside the cabin of the space station, and moves the target satellite to the outside of the cabin to be launched.

According to one aspect of the invention, in the step (b), the composition module of the test cube is assembled into the test cube by using the mechanical arm, the test cube is transferred to the outside of the cabin by a spacecraft, and the test cube is connected with the in-orbit comprehensive detection module by using the mechanical arm to perform in-orbit comprehensive detection on the test cube, so that the feasibility of in-orbit comprehensive detection is verified, and whether the state of the assembled satellite is normal and whether each function and performance meet requirements and whether interfaces between equipment are correct or not is confirmed.

The on-orbit comprehensive detection items comprise: power supply inspection, namely confirming the power supply and distribution functions and the normal state of the satellite-borne equipment after power-up; checking function matching to confirm that interaction of software and hardware interfaces between the devices is normal; the method comprises the following steps of (1) performing a model flight test, simulating an on-orbit flight environment through digital simulation, semi-physical simulation and other modes, carrying out full-system dynamic operation detection, and confirming the design correctness of a flight program and a control system; and (5) checking the performance, and confirming that the functions of the world link, the measurement and control data transmission and the like are normal.

The on-orbit comprehensive detection method comprises the following steps: the system is directly operated by an astronaut or operated on the ground through a space-ground link under the monitoring of the astronaut, a prefabricated automatic test instruction sequence can be used, and a single instruction can be manually sent, wherein the instruction comprises a remote control instruction and a test environment setting instruction. After the command is sent, according to the telemetering parameters fed back by the test cube and the detection data acquired by the on-orbit comprehensive detection module, whether the command result is in accordance with the expectation or not is checked after the command is interpreted. The interpretation method can adopt manual interpretation or computer automatic interpretation. When an abnormal state occurs or the command is inconsistent with the telemetering feedback, a ground technical support team and designers carry out analysis processing, when the fault needs to be repaired by changing equipment, software change can be updated on line in a data communication mode, and hardware change can be implemented by on-orbit operation of astronauts. And after the change is finished, performing on-orbit comprehensive detection again to confirm that the change is effective.

After the on-orbit comprehensive detection is finished, the testing cube satellite can be confirmed to have on-orbit deployment conditions, and the testing cube satellite is placed on the small satellite launching device by the mechanical arm to be launched.

According to one aspect of the invention, during the process of assembling the test cube and in-orbit comprehensive detection, the test cube is monitored by astronauts in real time, so that the test process can be known more comprehensively and clearly, and the test effect can be evaluated and the emergency can be processed conveniently and timely.

According to one aspect of the invention, in said step (c), the test cube is changed into an approaching observation cube and a flying net cube with approaching observation and net capturing capabilities by replacing the load cells in the constituent modules of the test cube.

According to one aspect of the invention, the approach observation test is that the target and the approach observation cube are released from the small satellite launching device outside the space station cabin in sequence, and the approach observation cube carries out non-cooperative target autonomous rendezvous and approach observation on the target.

According to one aspect of the invention, the net capture test is that the flying net cube is released from a small satellite launching device outside a space station cabin, and the target is subjected to flying net capture and dragged back to the space station.

In accordance with one aspect of the present invention, test data is collected and processed by telemetry using a surface telemetry module during the performance of a proximity observation test.

According to one aspect of the invention, both the approach observation test and the net capture test are conducted during the optical cabin observation test with the common rail of the space station.

According to one aspect of the invention, in step (c), the net capture test is performed after the approach observation test.

The verification system comprises a transportation unit, a test unit, an evaluation unit and an on-orbit operation unit;

the transport unit includes:

the freight ship is used for transporting materials required by on-orbit verification to the space station;

the on-orbit operation unit comprises:

the mechanical arm group comprises an in-cabin mechanical arm and an out-cabin mechanical arm which are respectively arranged inside and outside the cabin body of the space station;

the small satellite launching device is transported to the space station by the transportation unit and is installed outside a cabin of the space station;

the evaluation unit includes:

the ground remote measuring module is used for collecting and processing test data approaching an observation test;

the optical cabin is used for observing the processes of the approach observation test and the net capture test in an extraterrestrial space and transmitting the images to the space station in real time;

the test unit comprises:

testing the cube satellite and the target satellite;

and the on-orbit comprehensive detection module is used for carrying out on-orbit comprehensive detection on the assembled test cube.

According to one aspect of the invention, the test cube is composed of a cube platform unit and a load cell, which can be evolved to approach the observation cube and the fly net cube by replacing the load cell.

The approach observation cube and the flying net cube evolved by the test cube are in the same orbit with the target satellite after being released and are lower or higher than the orbit of the optical cabin.

According to one aspect of the invention, the transport unit further comprises a manned spacecraft for transporting the astronaut up to the space station.

According to one embodiment of the present invention, first, materials are transported by a cargo ship to an extra-terrestrial space station, and then, as the case may be, astronauts are also transported by a manned ship. The method comprises the steps that a spacecraft arranges a composition module of a test cube to a designated position in a cabin, then an in-orbit comprehensive detection module and a small satellite launching device are installed on a load platform outside the cabin of a space station, a target satellite is moved to the outside of the cabin to be launched, then the test cube conveyed by the composition module is assembled by using a mechanical arm inside the cabin of the space station, the assembled test cube is moved to the outside of the cabin by the spacecraft, and then the in-orbit comprehensive detection is carried out on the test cube, so that the verification of in-orbit assembly and comprehensive detection is completed. And then releasing the target satellite, and respectively converting the target satellite into the approach observation cube and the flying net cube by replacing the load unit of the test cube. And respectively releasing to carry out proximity observation and fly net capture on the target satellite, thereby verifying autonomous rendezvous, proximity observation and net capture of the non-cooperative target. The whole test process is observed by an optical cabin of the common rail of the space station and is monitored by an astronaut in real time, so that the test process can be more comprehensively and clearly known, the test effect can be conveniently and timely evaluated, the emergency situation can be conveniently processed, and the test data which is close to observation is collected and processed by a ground telemetering module. According to the concept of the invention, both the approach observation and the net capture test are completed by the test cube, so the verification method firstly verifies the on-orbit assembly and the comprehensive detection, and then carries out the approach observation and the net capture test. Therefore, when two subsequent tests are carried out, the load cell can be enabled to have the functions of approaching observation or fly net capture only by replacing the load cell, and a series of tests carried out by the cubic star can improve the efficiency of the whole test compared with the existing single test. In addition, in the invention, the astronauts participate in building the system and monitoring in real time, and compared with the existing on-orbit service without verification participated by the astronauts, a series of technical verification can be carried out instead of single verification.

According to one scheme of the invention, the net capture test is arranged to be carried out after the approach observation test, and the ideal result of the net capture test is to drag the target satellite back to the space station, so that the target satellite is used as the final test item of the method, the target satellite is released only once, and the recovery of the test equipment is also completed at the same time.

Drawings

In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings needed in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings without creative efforts.

FIG. 1 schematically illustrates a schematic diagram of an authentication method according to an embodiment of the present invention;

FIG. 2 is a schematic diagram schematically illustrating the test environment set-up steps in one embodiment of the present invention;

FIG. 3 schematically illustrates the steps of in-track assembly and in-track testing in one embodiment of the present invention.

Detailed Description

In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the embodiments will be briefly described below. It is obvious that the drawings in the following description are only some embodiments of the invention, and that for a person skilled in the art, other drawings can be derived from them without inventive effort.

In describing embodiments of the present invention, the terms "longitudinal," "lateral," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like are used in an orientation or positional relationship that is based on the orientation or positional relationship shown in the associated drawings, which is for convenience and simplicity of description only, and does not indicate or imply that the referenced device or element must have a particular orientation, be constructed and operated in a particular orientation, and thus, the above-described terms should not be construed as limiting the present invention.

The present invention is described in detail below with reference to the drawings and the specific embodiments, which are not repeated herein, but the embodiments of the present invention are not limited to the following embodiments.

Referring to fig. 1, a schematic diagram of the verification method of the present invention is shown, and the present invention is mainly directed to the verification of on-orbit service and maintenance technologies, including on-orbit assembly, on-orbit comprehensive detection, proximity observation and netting verification. Since all the on-orbit service or maintenance projects need to be completed on-orbit, in order to improve the authenticity and the effectiveness of verification, the verification of the projects is also completed on-orbit. Therefore, the first step of the verification method of the present invention is to set up a test environment, and all the materials required for on-track verification are transported to the off-ground space station a through the cargo ship 11 (i.e., S1 in fig. 1).

The verification method is different from the traditional method and is characterized in that a verification environment is built by utilizing the flexible control capability of an astronaut based on the existing conditions and resources of the manned aerospace system, and a series of verifications are carried out on a plurality of on-orbit service and maintenance technologies. Therefore, if there is no astronaut B currently in the space station a, the manned spacecraft 12 is used to transport the astronaut B participating in the verification to the space station a at the same time as the material is transported (i.e., S2 in fig. 1). In the present invention, the test cube is stored in modular form in the cargo ship 11, since it is of modular design. The constituent modules of the test cubes 21 included in the material transported by the cargo ship 11 are arranged by the astronaut to a designated position inside the cabin (i.e., S3 in fig. 2), and the target satellite 22 is arranged to a designated position outside the cabin, and then the in-orbit integrated detection module 23 and the small satellite transmitting device 42 are mounted on the space station load platform outside the cabin (i.e., S4 in fig. 2) so as to conduct subsequent tests.

In the verification process, because the verification tests of the invention all depend on the test cube star, the third step of the verification method is the on-orbit assembly aiming at the test cube star, so that the subsequent verification can be directly carried out by using the assembled test cube star, and the test efficiency can be improved. The main process of the verification test of the on-rail assembly is to assemble the component modules of the test cube 21 in the material so as to verify the feasibility of the on-rail assembly. This step is assembled within the bay by the robotic arm within the bay of the space station a, and the assembly test is monitored and evaluated in real time by the astronaut (i.e., S5 in fig. 3). In practice, the equipment after the on-track assembly needs to be comprehensively inspected to verify the accuracy of the assembly. The comprehensive detection process is also finished in the in-orbit, so that the subsequent step of the in-orbit assembly test is to comprehensively detect the assembled test cube 21, thereby verifying the feasibility of the in-orbit comprehensive detection. At this time, the on-rail integrated detection module 23 is grasped by the robot arm outside the cabin of the space station a and is mounted on the on-rail integrated detection interface outside the cabin of the space station a, thereby completing the connection of the on-rail integrated detection module 23 with the space station a (i.e., S6 in fig. 3). The test cube 21 is then transferred by the astronaut B to the outside of the cabin of the space station a, and the test cube 21 is grasped by the outside-cabin robot arm 41B and mounted on the in-orbit comprehensive inspection module 23 for comprehensive inspection (i.e., S7 in fig. 3). And confirming whether the assembled satellite state is normal, whether each function and performance meet the requirements and whether the interfaces between the devices are correct. The comprehensive detection items comprise: power supply inspection, namely confirming that the power supply and distribution function and the state of the satellite-borne equipment after power-up are normal; checking function matching to confirm that interaction of software and hardware interfaces between the devices is normal; the method comprises the following steps of (1) performing a model flight test, simulating an on-orbit flight environment through a digital simulation or semi-physical simulation mode, carrying out full-system dynamic operation detection, and confirming the design correctness of a flight program and a control system; and (5) checking the performance, and confirming that the world link and the measurement and control data transmission are normal. The comprehensive detection method comprises the following steps: directly operating by an astronaut or operating on the ground through a space-ground link under the monitoring of the astronaut, and sending a single instruction by using a prefabricated automatic test instruction sequence or manually, wherein the instruction comprises a remote control instruction and a test environment setting instruction; after the instruction is sent, according to the telemetering parameters fed back by the test cube and the detection data acquired by the on-orbit comprehensive detection module, whether the instruction result is in accordance with the expectation or not is checked after the instruction is interpreted; the interpretation method adopts manual interpretation or computer automatic interpretation; when an abnormal state or a condition that an instruction is inconsistent with telemetering feedback occurs, a ground technical support team and designers carry out analysis processing, when the fault needs to be repaired by changing equipment, software change is updated on line in a data communication mode, and hardware change is implemented by on-orbit operation of astronauts; after the change is finished, performing on-orbit comprehensive detection again to confirm that the change is effective; after the detection is finished, the testing cube is confirmed to have the on-orbit deployment condition, and the testing cube is placed on the small satellite launching device to be launched by the mechanical arm. Therefore, the detection is carried out by depending on the space station A, the existing design resources such as grid-connected power supply, information transmission, backup and takeover among cabin sections and the like of the space station A are mainly utilized, and the detection data can be transmitted to the space station A for analysis.

The verification of on-orbit assembly and detection can be completed through the test process, and then an approaching observation test and a net capture test are carried out. The approach observation test comprises two items of non-cooperative target autonomous rendezvous and approach observation, and is intended to verify whether approach observation and autonomous rendezvous can be carried out on the celestial body flying in orbit. This step begins with the above-described microsatellite launching device 42 releasing a target object (i.e., S8 in FIG. 1), which in the present invention is a microcube, as a non-cooperative object. The approaching observation test needs to be supported by another cube which needs to have the capability of autonomous rendezvous and approaching observation. In the invention, because the test cube 21 is a modularized cube structure, the test cube can be evolved into a cube with the verification function-approaching observation cube only by replacing the load unit 21b in the component module, S9 in fig. 1 is a release indication of the cube, and the approaching observation cube is deformation of the test cube 21, so that other drawing labels are not used for representation. And then the approaching observation cube performs non-cooperative target autonomous rendezvous and approaching observation on the target, and completes verification of the two technologies. The entire test is observed by the optical pod 32 (i.e., S12 in fig. 1), and the observed images are transmitted to the space station for real-time monitoring by the spacecraft for real-time assessment and emergency handling in the event of an emergency, while the relevant data generated during the test is gathered and processed by the ground telemetry module 31 (i.e., S11 in fig. 1).

The target object of the net capture test may be the target object, and the main purpose of the test is to use fly net capture technology to net capture the target flying in orbit and drag the target flying in orbit back to the space station a, so as to verify the recovery process when the target flying in orbit has defects. It will be appreciated that this test is preferably performed after the approach observation test, since the target is dragged back into the chamber after completion of the test, thereby eliminating the need to release the target again and completing the cube star recovery work. This test is carried out using a flying net cube, which can likewise be formed by replacing the load cells 21b of the test cube 21 according to the procedure described above. After the reloading is completed, the target object is released (namely S13 in FIG. 1), and the target object is automatically intersected with the target object and subjected to net capture by the target object until the target object is dragged back to the space station A, so that the flying net capture control technology is verified. The entire test procedure is also observed by the optical chamber 32 (i.e., S15 in fig. 1).

Therefore, the method respectively completes on-orbit assembly, on-orbit comprehensive detection, autonomous intersection, approach observation and net capture test. These several items do intersect during the validation process, for example, the process of reloading the test cube 21 close to the observation cube and the flying net cube by replacing the load cell 21b is actually further validated for on-track assembly. And the two kinds of cuboids which are reassembled can be further subjected to on-orbit comprehensive detection according to the requirements, so that the accuracy of the reassembling step is verified. The reason why the astronaut B participates in the methods is that on one hand, complex test environments are quickly built by utilizing the flexible control capability of the astronaut, so that a series of technologies of task verification at one time are realized, and the cost is reduced; on the other hand, the test effect is evaluated in real time and faults are eliminated by utilizing the monitoring and decision-making capability of astronauts, and the reliability is improved. The method is developed by utilizing the existing resources of the manned space system, does not need to independently launch the test cube, is also beneficial to realizing a series of technologies of one-time task verification and is beneficial to reducing the test cost.

The verification system for realizing the verification method comprises a transportation unit 1, a test unit 2, an evaluation unit 3 and an on-orbit operation unit 4. The transport unit 1 is responsible for transporting the materials required for the test up to the space station a. It therefore comprises a freight ship 11, although, according to the above, if there is no astronaut B in space station a, the transport unit 1 should also comprise a manned spacecraft 12 to transport the astronaut to space station a together. It can be seen that the transport unit 1 is a complete set of heaven and earth transport systems. The testing unit 2 contains the main materials to be transported, including a testing cube 21, a target satellite 22 and an on-orbit comprehensive detection module 23. The test cube 21 therein is transported in modular form for subsequent in-orbit assembly testing. In the invention, the test cube 21 comprises a cube platform unit 21a, a load unit 21b and the like, and the test cube can be developed to approach an observation cube and a flying net cube by replacing the load unit 21 b. The target satellite 22 is the target of the verification method of the present invention, and the approaching observation test and the net capture test are both performed using the cubic satellite as the target. After release, both the approach observation cube and the fly-net cube are in orbit with the target satellite 22, which facilitates the performance of the test. The in-orbit comprehensive detection module 23 mainly functions to perform in-orbit comprehensive detection on the assembled test cube 21 under the support of the space station a, and therefore, an interface for connecting the space station a and the test cube 21 should be provided thereon. Thus, after the on-orbit comprehensive detection module 23 is connected with the space station a, the test cube 21 is connected with the module, so that a series of on-orbit comprehensive detections can be performed on the test cube 21 and on-orbit detection data can be transmitted to the space station a.

The on-orbit operation unit 4 comprises a space station a, a set of arms 41 and a small satellite launching device 42. In summary, the verification method of the present invention is completed by relying on the space station a, especially on the in-orbit assembly and comprehensive detection steps, and the space station a provides a test environment for the two kinds of verification. Therefore, the outboard of the space station a should be provided with an on-orbit comprehensive detection interface so as to be connected with the on-orbit comprehensive detection module 23. The robot group 41 is mounted on the space station a, and includes an inside robot 41a and an outside robot 41b respectively mounted inside and outside the cabin. As described in the above method, the in-cabin robot 41a mainly performs on-track assembly verification, while the out-cabin robot 41b operates to perform grabbing and connecting of the out-cabin equipment. The target satellite 22, the approach observation cube and the flying net cube in the above verification method are all released by the small satellite launching device 42, and the small satellite launching device 42 in the invention is also installed outside the space station a as a material after being transported by the cargo ship 11 in an uplink manner. The evaluation unit 3 includes a surface telemetry module 31 and an optical bay 32, the surface telemetry module 31 being located at the surface for gathering and processing data during the approach observation test. While the optical compartment 32 is located in an extra-terrestrial space for observing the test processes of the proximity observation test and the net capture test. As shown in fig. 1, the optics bay 32 operates in conjunction with the space station rail to facilitate the observation of the approach observation and net capture tests performed on either the low orbit or the high orbit.

In summary, the verification method and system of the invention provide a set of complete verification scheme, and compared with other technical verification methods, the method and system have the advantages of good technical foundation, strong support capability, small task risk, more guaranteed resources, low test cost, high efficiency, comprehensive verification and the like.

The above description is only one embodiment of the present invention, and is not intended to limit the present invention, and it is apparent to those skilled in the art that various modifications and variations can be made in the present invention. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims

1. An on-orbit service and maintenance verification method comprises the following steps:

c. releasing the target object in the material to the outside of the space station cabin, and respectively carrying out an approaching observation test and a net capture test;

in said step (a), the manned space system already has resources including a space station for providing a test site, an optical capsule for observation, a cargo ship for transporting cargo, a manned ship for transporting astronauts, and a ground telemetry module for acquiring test telemetry data;

the required materials comprise a test cube composition module, a target object satellite, an on-orbit comprehensive detection module and a small satellite launching device;

the astronaut arranges the composition module of the test cube to a designated position in the cabin, then installs the on-orbit comprehensive detection module and the small satellite launching device on a load platform outside the cabin of the space station, and moves the target satellite to the outside of the cabin to be launched.

2. The verification method according to claim 1, wherein in the step (b), the composition modules of the test cube are assembled into the test cube by using a mechanical arm, the test cube is transferred to the outside of a cabin by a astronaut, and then the test cube is connected with the in-orbit comprehensive detection module by using the mechanical arm to perform in-orbit comprehensive detection on the test cube, so that the feasibility of the in-orbit comprehensive detection is verified, and whether the state of the assembled satellite is normal, whether each function and performance meet requirements and whether an inter-equipment interface is correct are confirmed;

the on-orbit comprehensive detection items comprise:

power supply inspection, namely confirming that the power supply and distribution function and the state of the satellite-borne equipment after power-up are normal;

checking function matching to confirm that interaction of software and hardware interfaces between the devices is normal;

the method comprises the following steps of (1) performing a model flight test, simulating an on-orbit flight environment through a digital simulation or semi-physical simulation mode, carrying out full-system dynamic operation detection, and confirming the design correctness of a flight program and a control system;

checking the performance, and confirming that the world link and the measurement and control data transmission are normal;

the on-orbit comprehensive detection method comprises the following steps: directly operating by an astronaut or operating on the ground through a space-ground link under the monitoring of the astronaut, and sending a single instruction by using a prefabricated automatic test instruction sequence or manually, wherein the instruction comprises a remote control instruction and a test environment setting instruction;

after the instruction is sent, according to the telemetering parameters fed back by the test cube and the detection data acquired by the on-orbit comprehensive detection module, whether the instruction result is in accordance with the expectation or not is checked after the instruction is interpreted, and the interpretation method adopts manual interpretation or computer automatic interpretation;

when an abnormal state or a condition that an instruction is inconsistent with telemetering feedback occurs, a ground technical support team and designers carry out analysis processing, when the fault needs to be repaired by changing equipment, software change is updated on line in a data communication mode, and hardware change is implemented by on-orbit operation of astronauts;

after the change is finished, performing on-orbit comprehensive detection again to confirm that the change is effective;

after the detection is finished, the testing cube is confirmed to have the on-orbit deployment condition, and the testing cube is placed on the small satellite launching device to be launched by the mechanical arm.

3. The authentication method according to claim 2, wherein in the step (c), the test cube is changed into an approaching observation cube and a flying net cube with approaching observation and net capturing capabilities by replacing load units in the component modules of the test cube;

the approach observation test comprises the steps that a target satellite and an approach observation cube are released from a small satellite launching device outside a space station cabin in sequence, and the approach observation cube carries out non-cooperative target autonomous rendezvous and approach observation on the target satellite;

the net capture test is to release the flying net cubic satellite from a small satellite launching device outside a space station cabin, capture the flying net of a target satellite and drag the target satellite back to the space station.

4. The verification method according to claim 3, wherein during the performance of the proximity observation test, the test data is compiled and processed by telemetry using a surface telemetry module.

5. The validation method of claim 4, wherein the approach observation test and the netting test are both performed by optical capsule observation test with a common rail of the space station.

6. The method of validating as defined in claim 5, wherein, in the step (c), the net capture test is performed after the proximity observation test.

7. A system for implementing the validation method of any one of claims 1 to 6, comprising a transport unit (1), a test unit (2), an evaluation unit (3) and an on-track operation unit (4);

the transport unit (1) comprises:

a cargo ship (11) for transporting materials required for on-track verification to the space station;

the on-orbit operation unit (4) comprises:

the mechanical arm group (41) comprises an in-cabin mechanical arm (41a) and an out-cabin mechanical arm (41b) which are respectively arranged inside and outside a cabin body of the space station;

a small satellite launcher (42) transported by the transport unit (1) to a space station, installed outside a space station cabin;

the evaluation unit (3) comprises:

a ground telemetry module (31) for compiling and processing test data approaching an observation test;

an optical cabin (32) for observing the processes of the approach observation test and the net capture test in the extraterrestrial space and transmitting the images to the space station in real time;

the test unit (2) comprises:

a test cube (21) and a target satellite (22);

and the on-orbit comprehensive detection module (23) is used for carrying out on-orbit comprehensive detection on the assembled test cube (21).

8. The system according to claim 7, characterized in that the test cube (21) is composed of a cube platform unit (21a) and a load unit (21b) which can be evolved to approach observation and fly net cubes by replacing the load unit (21 b);

the approach observation and flight net cuboids evolved by the test cuboids (21) are in the same orbit as the target satellite (22) after release.

9. The system according to claim 8, characterized in that said transport unit (1) further comprises a manned spacecraft (12) for transporting the astronaut up to the space station.