Aerospace system test method, device, equipment and medium

Abstract

The invention relates to a spaceflight system test method, device and equipment and a medium, and the method comprises the steps: obtaining in-orbit test data of a spaceflight system through a test satellite; based on the on-orbit test data, a test report of the aerospace system is output, and the accuracy of evaluating the performance of the aerospace system is improved.

Description

Technical Field

[0001] The embodiments of the present application relate to the field of aerospace testing technology, and in particular, to an aerospace system testing method, device, equipment and medium. Background Art

[0002] Space system testing technology is an important part of ensuring that spacecraft performance meets established standards and requirements. Traditional space testing technology mainly relies on ground testing, which can simulate various environmental conditions that spacecraft may encounter in space, but cannot fully reproduce the effects of microgravity, space debris impact, solar wind and other factors on spacecraft performance, and has the problem of low accuracy. Summary of the invention

[0003] The following is a summary of the subject matter described in detail herein. This summary is not intended to limit the scope of the claims.

[0004] The main purpose of the embodiments of the present disclosure is to provide an aerospace system testing method, device, equipment and medium, which can improve the accuracy of evaluating the performance of the aerospace system.

[0005] A first aspect of an embodiment of the present application provides an aerospace system testing method, the method comprising:

[0006] Acquiring on-orbit test data of a space system through a test satellite; the space system includes the test satellite and a formal satellite that have completed networking;

[0007] Based on the on-orbit test data, a test report of the aerospace system is output.

[0008] An embodiment of the present application provides a method for testing a space system. After a test satellite is networked with a formal satellite, the on-orbit test data of the space system is directly obtained through the test satellite, so that more real and accurate test data of the operation of the space system and space environment data can be obtained. By analyzing the on-orbit test data and outputting a test report, the performance of the space system can be more accurately evaluated.

[0009] In some embodiments of the present application, before acquiring on-orbit test data of the aerospace system through the test satellite, the method further includes:

[0010] Testing multiple candidate satellites, and selecting candidate satellites that meet the requirements as target candidate satellites;

[0011] Launching the target candidate satellite in a corresponding launch window to allow the target candidate satellite to enter a predetermined orbit;

[0012] The target candidate satellite is verified in orbit, and the target candidate satellite that meets preset requirements is used as a test satellite.

[0013] In some embodiments of the present application, after the target candidate satellite is verified on-orbit and the target candidate satellite that meets preset requirements is used as a test satellite, the method further includes:

[0014] Establishing a communication link between the test satellite and the formal satellite;

[0015] formulating a data exchange protocol for the communication link;

[0016] The communication link is collaboratively tested to complete the networking of the test satellite and the formal satellite.

[0017] In some embodiments of the present application, before outputting the test of the aerospace system based on the on-orbit test data, the method further includes:

[0018] Decapsulating the on-track test data, and synchronizing the on-track test data after decapsulation;

[0019] The synchronized on-track test data is format-converted to obtain the on-track test data in a corresponding format.

[0020] In some embodiments of the present application, outputting a test report of the aerospace system based on the on-orbit test data includes:

[0021] Performing performance analysis on the on-orbit test data to obtain a performance analysis result of the aerospace system;

[0022] Identify anomalies in the on-orbit test based on the on-orbit test data, analyze the causes of the anomalies, and obtain a problem analysis result of the aerospace system;

[0023] Based on the problem analysis results, optimization suggestions for the aerospace system are obtained;

[0024] A test report of the aerospace system is outputted based on the performance analysis results, the problem analysis results and the optimization suggestions.

[0025] In some embodiments of the present application, the performing performance analysis on the on-orbit test data to obtain the performance analysis result of the aerospace system includes:

[0026] Calculating the communication transmission performance of the aerospace system from the on-orbit test data based on a throughput evaluation algorithm and a transmission delay evaluation algorithm to obtain a communication transmission performance evaluation result of the aerospace system;

[0027] Obtaining the accuracy analysis result of the aerospace system from the on-orbit test data through covariance analysis;

[0028] The performance analysis result of the aerospace system is obtained according to the communication transmission performance evaluation result and the accuracy analysis result.

[0029] In some embodiments of the present application, after outputting the test report of the aerospace system based on the on-orbit test data, the method further includes:

[0030] The aerospace system is updated according to the test report.

[0031] A second aspect of an embodiment of the present invention provides an aerospace system testing device, the device comprising:

[0032] A data acquisition module, used to acquire on-orbit test data of a space system through a test satellite; the space system includes the test satellite and the formal satellite that have completed networking;

[0033] A data analysis module is used to output a test report of the aerospace system based on the on-orbit test data.

[0034] A third aspect of an embodiment of the present invention provides an electronic device, comprising: at least one control processor and a memory for communicating with the at least one control processor; the memory stores instructions that can be executed by the at least one control processor, and the instructions are executed by the at least one control processor to enable the at least one control processor to execute the above-mentioned aerospace system testing method.

[0035] A fourth aspect of an embodiment of the present invention provides a computer-readable storage medium, wherein the computer-readable storage medium stores computer-executable instructions, and the computer-executable instructions are used to enable a computer to execute the above-mentioned aerospace system testing method.

[0036] It can be understood that the beneficial effects of the second to fourth aspects compared with the related art are the same as the beneficial effects of the first aspect compared with the related art. Please refer to the relevant description in the first aspect, and no further details will be given here. BRIEF DESCRIPTION OF THE DRAWINGS

[0037] In order to more clearly illustrate the technical solutions in the embodiments of the present application, the drawings required for use in the embodiments or related technical descriptions will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative labor.

[0038] Figure 1 It is a flowchart of an embodiment of the aerospace system testing method provided by the present application;

[0039] Figure 2is a schematic structural diagram of an embodiment of a spaceflight system provided by the present application;

[0040] Figure 3 is a schematic structural diagram of an embodiment of an electronic device provided by the present application; DETAILED DESCRIPTION

[0041] In order to make the purpose, technical solution and advantages of the present application more clearly understood, the present application is further described in detail below in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain the present application and are not used to limit the present application.

[0042] Space system testing technology is an important part of ensuring that spacecraft performance meets established standards and requirements. Traditional space testing technology mainly relies on ground-based testing facilities that can simulate various environmental conditions that spacecraft may encounter in space, such as vacuum, temperature changes, radiation, etc. However, ground-based testing systems have certain limitations. They cannot fully reproduce the effects of microgravity, space debris impacts, solar wind and other factors on spacecraft performance. Satellite in-orbit testing is an important means to verify satellite functions and performance; however, due to the particularity of the space environment, traditional in-orbit testing methods face many challenges, such as inaccurate environmental simulation, insufficient test coverage, high costs, and difficulty in real-time data analysis.

[0043] Since the current aerospace system is divided into subsystems such as the space segment, ground segment, and user segment, these subsystems have many interactive interfaces and complex operating rules. Before the system is built, in order to verify the interface relationship between different systems and the end-to-end overall system performance, pure software simulation testing is generally used, but there is a problem of low simulation fidelity.

[0044] With the development of aerospace technology, the performance requirements for spacecraft are getting higher and higher. The existing aerospace system testing methods can no longer meet the testing needs of modern spacecraft. Therefore, it is necessary to develop new testing technologies and systems to improve the fidelity, efficiency and accuracy of testing.

[0045] For this purpose, refer to Figure 1 The embodiment of the present application provides a method for testing an aerospace system. The method is applied to a controller. The controller may be a server, an electronic device, or a mobile terminal, etc., which is not specifically limited here. The method includes the following steps S100 to S200:

[0046] Step S100: Acquire on-orbit test data of the aerospace system through the test satellite; the aerospace system includes the test satellite and the formal satellite that have completed networking.

[0047] In this step, the test satellite is used in the on-orbit test phase to verify whether the performance and functions of the satellite system meet the design requirements. The formal satellite is the satellite that actually performs the mission. The test satellite and the formal satellite are networked, and the on-orbit test data of the aerospace system is directly obtained through the test satellite. Among them, the on-orbit test data includes the performance indicators of the satellite, the test satellite operation data after networking with the formal networked satellite, and the space environment data. The performance indicator data of the satellite include but are not limited to the hardware performance, software performance, and sensor detection performance of the satellite. The performance indicator data is used to evaluate whether the performance of the satellite meets the design requirements. The operation data of the test satellite after networking with the formal networked satellite includes but is not limited to the communication data, coordination data, task allocation data, etc. between satellites. The collaborative working ability of the satellite system is evaluated through the operation data to ensure that the satellite system can complete the mission efficiently. The space environment data includes but is not limited to the radiation dose, high-energy particle flux, magnetic field strength, etc. in space. The survivability of the satellite in the space environment is evaluated through the space environment data, and corresponding protective measures can be taken according to the space environment data.

[0048] Step S200: output a test report of the aerospace system based on the on-orbit test data.

[0049] In this step, if Figure 2 As shown, after the test satellite acquires the on-orbit test data, the on-orbit test data is transmitted to the ground test analysis system, and the ground test analysis system analyzes the on-orbit test data to output a test report for the aerospace system.

[0050] In one embodiment, the ground test and analysis system includes a data receiving module, a data processing and analysis module, and a user interface. The data receiving module is used to receive data from the test satellite to ensure the stability and security of data transmission; the data processing and analysis module is used to analyze the collected test data and evaluate satellite performance; the user interface is used to provide an intuitive user interface so that technicians can monitor the test process and results.

[0051] Different from the prior art, the embodiment of the present application networks the test satellite with the formal satellite, and directly obtains the on-orbit test data of the aerospace system through the test satellite, so as to obtain more real and accurate aerospace system operation test data and space environment data. By analyzing the on-orbit test data and outputting a test report, the performance of the aerospace system is more accurately evaluated, thus solving the defects of the prior art.

[0052] The specific implementation methods of the above steps are introduced below.

[0053] Before acquiring the on-orbit test data of the aerospace system by testing the satellite in step S100, the method further includes the following steps S10 to S15:

[0054] Step S10: Test multiple candidate satellites and select candidate satellites that meet the requirements as target candidate satellites.

[0055] Step S11: Launch the target candidate satellite in the corresponding launch window to make the target candidate satellite enter the predetermined orbit.

[0056] Step S12: Perform in-orbit verification on the target candidate satellite, and use the target candidate satellite that meets the preset requirements as a test satellite;

[0057] Step S13: Establish a communication link between the test satellite and the official satellite.

[0058] Step S14: Formulate a data exchange protocol for the communication link.

[0059] Step S15: perform collaborative testing on the communication link to complete the networking of the test satellite and the formal satellite.

[0060] In this embodiment, in order to reduce costs and adapt to different types of testing requirements, the target candidate satellite adopts a miniaturized and modular design, specifically, it is composed of devices such as FPGA (Field-Programmable Gate Array) and DSP (Digital Signal Processor). Most functions can be software-defined, and after being launched into orbit, it can be reconstructed in orbit according to different actual tasks. The modular design of the test satellite makes it possible to quickly replace test modules according to different test requirements, supports rapid iteration and updating of technology, and reduces costs.

[0061] In some embodiments, in order to ensure that the test satellite can accurately perform collaborative testing with the formal satellite, the target candidate satellite needs to have autonomous navigation and positioning capabilities. For example, the autonomous navigation and positioning capabilities of the test satellite can be achieved by integrating a global navigation satellite system receiver, an onboard computer, an inertial measurement unit, a laser ranging system, a data link, an atomic clock, etc.

[0062] In some implementations, in order to ensure that the test satellite can exchange data with the official satellite and the ground test and analysis system, the target candidate satellite needs to be equipped with an advanced communication system so that the target candidate satellite has communication capabilities.

[0063] In some implementations, according to actual test requirements, corresponding test equipment and sensors, such as signal generators, receivers, spectrum analyzers, etc., are mounted on the target candidate satellite to meet the test requirements for the test satellite to complete the test mission.

[0064] In some embodiments, since the positioning of the target candidate satellite is to assist in on-orbit testing and in order to reduce costs, the target candidate satellite uses commercial electronic devices and improves resistance to the effects of outer space radiation and the like through redundant backup.

[0065] In some embodiments, tests are conducted among candidate satellites to select candidate satellites that meet the requirements of miniaturization and modularization, autonomous navigation and positioning capabilities, communication capabilities, onboard test equipment, and construction based on commercial components as target candidate satellites.

[0066] In some embodiments, the launch window is analyzed and determined based on the target orbit of the target candidate satellite, such as a low earth orbit, a sun-synchronous orbit, etc., and the appropriate time is selected based on the real-time communication and monitoring situation of the ground station and the weather conditions; after the timing is determined, the target candidate satellite is launched in the corresponding launch window to allow the target candidate satellite to enter the predetermined orbit.

[0067] In some embodiments, a corresponding test plan is formulated according to the specification requirements of the test satellite, and the target candidate satellite is tested on-orbit according to the test plan to verify whether the target candidate satellite meets the on-orbit test function and performance requirements of the test satellite. Subsequently, according to the actual situation, appropriate frequencies and channels are equipped for the communication between the test satellite and the formal satellite to establish a communication link between the test satellite and the candidate satellite, and an exchange protocol for the communication link is formulated to ensure the consistency of data exchanged between the test satellite and the formal satellite. The communication link is collaboratively tested to ensure that the test satellite and the formal satellite can exchange data smoothly and complete the networking of the test satellite and the formal satellite.

[0068] Before outputting the test of the aerospace system based on the on-orbit test data in step S200, the method further includes the following steps S101 to S102:

[0069] Step S101 : decapsulate the on-track test data, and synchronize the on-track test data after decapsulation.

[0070] Step S102: convert the format of the synchronized on-orbit test data to obtain on-orbit test data of a corresponding format.

[0071] In this embodiment, after the test satellite collects the on-orbit test data, it encapsulates the on-orbit test data into data packets, and transmits the data packets to the ground test analysis system using the communication payload carried by the test satellite or through other satellites. After the ground test analysis system receives the data packets of the on-orbit test data, it preprocesses the data packets.

[0072] In some embodiments, preprocessing the data packet specifically involves decapsulating the data packet, i.e., extracting the on-orbit test data from the transmission format and restoring it to the original format or data state; since data may be out of sync during the transmission process due to network delays, data packet loss, or clock drift of different systems, the on-orbit test data is synchronized, and the order and timestamp of the on-orbit test data are adjusted to ensure that the data is correctly arranged in chronological order; the synchronized on-orbit test data is format converted to simplify the subsequent data processing process.

[0073] Outputting the test report of the aerospace system based on the on-orbit test data in step S200 includes the following steps S210 to S240:

[0074] Step S210: Perform performance analysis on the on-orbit test data to obtain performance analysis results of the aerospace system.

[0075] Step S220: Identify anomalies in the on-orbit test based on the on-orbit test data, analyze the causes of the anomalies, and obtain problem analysis results for the aerospace system.

[0076] Step S230: Based on the problem analysis results, optimization suggestions for the aerospace system are obtained.

[0077] Step S240: Output a test report of the aerospace system according to the performance analysis results, problem analysis results and optimization suggestions.

[0078] In this embodiment, an in-depth analysis of the aerospace system is performed based on the on-orbit test data, including but not limited to analyzing key performance indicators such as communication transmission throughput and transmission delay in the on-orbit test data, and generating corresponding performance analysis results. The obtained performance analysis results will form a performance benchmark for the aerospace system and provide a reference for subsequent optimization.

[0079] In some embodiments, abnormal phenomena that deviate from the normal operating range are identified by reviewing on-orbit test data; wherein the abnormal phenomena may be signal distortion, data packet loss, abnormal energy consumption, hardware failure or other unexpected behaviors; based on all identified abnormal phenomena, the problems of the aerospace system are analyzed and the causes of these problems are determined, and based on the problem analysis results, specific optimization suggestions are formulated in a targeted manner, and the performance analysis results, problem analysis results and optimization suggestions are integrated to generate a test report for the aerospace system.

[0080] The step S210 of performing performance analysis on the on-orbit test data to obtain the performance analysis result of the aerospace system includes the following steps S211 to S213:

[0081] Step S211, calculating the communication transmission performance of the aerospace system from the on-orbit test data based on the throughput evaluation algorithm and the transmission delay evaluation algorithm, and obtaining the communication transmission performance evaluation result of the aerospace system.

[0082] Step S212: Obtain the accuracy analysis result of the aerospace system from the on-orbit test data through covariance analysis.

[0083] Step S213: Obtain a performance analysis result of the aerospace system according to the communication transmission performance evaluation result and the accuracy analysis result.

[0084] In this embodiment, the on-orbit test data is analyzed by different algorithms, for example, to evaluate the communication transmission throughput, transmission delay, and positioning accuracy.

[0085] In some embodiments, throughput refers to the amount of data that can be successfully transmitted by the aerospace system per unit time, usually in bits per second (bps); the throughput evaluation algorithm calculates the average throughput and peak throughput based on the actual data transmission rate recorded during the on-orbit test to evaluate the effectiveness of the communication link and the efficiency of bandwidth utilization. Transmission delay refers to the total time from the data packet being sent at the source to being received at the target, including processing delay, propagation delay, and queuing delay; the transmission delay evaluation algorithm calculates the average delay and delay jitter (i.e., the degree of delay change) by analyzing the timestamp information of the data packet to evaluate the stability and response speed of the communication link.

[0086] In some embodiments, covariance analysis is used to study the performance fluctuations of aerospace systems under different conditions (such as different orbital positions, different time points) and evaluate the operational accuracy and stability of aerospace systems. Covariance analysis can reveal the relationship between various performance parameters and help identify which factors have the greatest impact on system accuracy. For example, in satellite positioning or attitude control tasks, covariance analysis can help quantify navigation errors, attitude angle deviations, etc., and then evaluate the positioning accuracy and attitude control accuracy of the aerospace system.

[0087] In this embodiment, the on-orbit test data is analyzed by different algorithms, for example, the communication transmission throughput, transmission delay and positioning accuracy are evaluated, and the performance analysis results of the aerospace system are obtained based on the different analysis results, so as to comprehensively analyze the performance of the aerospace system.

[0088] After outputting the test report of the aerospace system based on the on-orbit test data in step S200, the method includes the following step S201:

[0089] Step S201: Update the aerospace system according to the test report.

[0090] In this embodiment, the test report is analyzed, including communication transmission performance, accuracy and other key performance indicators. Based on the data analysis results, the improvement direction of the aerospace system is determined, including but not limited to increasing the data transmission rate, reducing the transmission delay, improving the measurement accuracy or enhancing the reliability of the system. According to the determined improvement direction, the corresponding improvement plan is designed, and finally the aerospace system is modified and updated according to the improvement plan.

[0091] In this embodiment, after the aerospace system is modified and updated, ground testing is first performed to verify whether the update effectively solves the problem and improves the performance of the aerospace system, and then the updated aerospace system is verified on-orbit to ensure that the updated aerospace system achieves the expected results.

[0092] Some embodiments of the present application provide an aerospace system testing device, the device comprising a data acquisition module and a data analysis module, specifically:

[0093] A data acquisition module, used to acquire on-orbit test data of a space system through a test satellite; the space system includes the test satellite and the formal satellite that have completed networking;

[0094] A data analysis module is used to output a test report of the aerospace system based on the on-orbit test data.

[0095] It should be noted that the aerospace system testing device provided in this embodiment and the above-mentioned aerospace system testing method are based on the same inventive concept, so the relevant content of the above-mentioned aerospace system testing method is also applicable to the content of the aerospace system testing device, and therefore, it will not be repeated here.

[0096] like Figure 3 The embodiment of the present application further provides an electronic device, the electronic device comprising:

[0097] at least one memory;

[0098] at least one processor;

[0099] at least one program;

[0100] The programs are stored in the memory, and the processor executes at least one program to implement the aerospace system testing method described above in the present disclosure.

[0101] The electronic device may be any intelligent terminal including a mobile phone, a tablet computer, a personal digital assistant (PDA), a vehicle-mounted computer, etc.

[0102] The electronic device according to the embodiment of the present application is described in detail below.

[0103] The processor 1600 may be implemented by a general-purpose central processing unit (CPU), a microprocessor, an application-specific integrated circuit (ASIC), or one or more integrated circuits, and is used to execute relevant programs to implement the technical solutions provided in the embodiments of the present invention.

[0104] The memory 1700 can be implemented in the form of a read-only memory (ROM), a static storage device, a dynamic storage device, or a random access memory (RAM). The memory 1700 can store an operating system and other application programs. When the technical solution provided in the embodiment of this specification is implemented by software or firmware, the program code is stored in the memory 1700, and the processor 1600 calls and executes the aerospace system test method of the embodiment of the present invention.

[0105] Input / output interface 1800, used to implement information input and output;

[0106] The communication interface 1900 is used to realize the communication interaction between the device and other devices. The communication can be realized through a wired manner (such as USB, network cable, etc.) or a wireless manner (such as mobile network, WIFI, Bluetooth, etc.);

[0107] Bus 2000 , which transmits information between various components of the device (e.g., processor 1600 , memory 1700 , input / output interface 1800 , and communication interface 1900 );

[0108] The processor 1600 , the memory 1700 , the input / output interface 1800 , and the communication interface 1900 are connected to each other in communication within the device via the bus 2000 .

[0109] An embodiment of the present invention further provides a storage medium, which is a computer-readable storage medium. The computer-readable storage medium stores computer-executable instructions, and the computer-executable instructions are used to enable a computer to execute the above-mentioned aerospace system testing method.

[0110] The memory, as a non-transient computer-readable storage medium, can be used to store non-transient software programs and non-transient computer executable programs. In addition, the memory may include a high-speed random access memory, and may also include a non-transient memory, such as at least one disk storage device, a flash memory device, or other non-transient solid-state storage device. In some embodiments, the memory may optionally include a memory remotely disposed relative to the processor, and these remote memories may be connected to the processor via a network. Examples of the above-mentioned network include, but are not limited to, the Internet, an intranet, a local area network, a mobile communication network, and combinations thereof.

[0111] The embodiments described in the present invention are intended to more clearly illustrate the technical solutions of the embodiments of the present invention and do not constitute a limitation on the technical solutions provided by the embodiments of the present invention. Those skilled in the art will appreciate that with the evolution of technology and the emergence of new application scenarios, the technical solutions provided by the embodiments of the present invention are also applicable to similar technical problems.

[0112] Those skilled in the art will appreciate that the technical solutions shown in the figures do not limit the embodiments of the present invention and may include more or fewer steps than shown in the figures, or a combination of certain steps, or different steps.

[0113] The device embodiments described above are merely illustrative, and the units described as separate components may or may not be physically separated, that is, they may be located in one place or distributed on multiple network units. Some or all of the modules may be selected according to actual needs to achieve the purpose of the solution of this embodiment.

[0114] Those skilled in the art will appreciate that all or some of the steps in the methods disclosed above, and the functional modules / units in the systems and devices may be implemented as software, firmware, hardware, or a suitable combination thereof.

[0115] The terms "first", "second", "third", "fourth", etc. (if any) in the specification of the present application and the above-mentioned drawings are used to distinguish similar objects, and are not necessarily used to describe a specific order or sequence. It should be understood that the data used in this way can be interchangeable where appropriate, so that the embodiments of the present application described herein can be implemented in an order other than those illustrated or described herein. In addition, the terms "including" and "having" and any of their variations are intended to cover non-exclusive inclusions, for example, a process, method, system, product or device comprising a series of steps or units is not necessarily limited to those steps or units clearly listed, but may include other steps or units that are not clearly listed or inherent to these processes, methods, products or devices.

[0116] It should be understood that in the present application, "at least one (item)" means one or more, and "plurality" means two or more. "And / or" is used to describe the association relationship of associated objects, indicating that three relationships may exist. For example, "A and / or B" can mean: only A exists, only B exists, and A and B exist at the same time, where A and B can be singular or plural. The character " / " generally indicates that the objects associated before and after are in an "or" relationship. "At least one of the following" or similar expressions refers to any combination of these items, including any combination of single or plural items. For example, at least one of a, b or c can mean: a, b, c, "a and b", "a and c", "b and c", or "a and b and c", where a, b, c can be single or multiple.

[0117] In the several embodiments provided in the present application, it should be understood that the disclosed devices and methods can be implemented in other ways. For example, the device embodiments described above are only schematic. For example, the division of units is only a logical function division. There may be other division methods in actual implementation, such as multiple units or components can be combined or integrated into another system, or some features can be ignored or not executed. Another point is that the mutual coupling or direct coupling or communication connection shown or discussed can be through some interfaces, indirect coupling or communication connection of devices or units, which can be electrical, mechanical or other forms.

[0118] The units described as separate components may or may not be physically separated, and the components shown as units may or may not be physical units, that is, they may be located in one place or distributed on multiple network units. Some or all of the units may be selected according to actual needs to achieve the purpose of the solution of this embodiment.

[0119] In addition, each functional unit in each embodiment of the present application may be integrated into one processing unit, or each unit may exist physically separately, or two or more units may be integrated into one unit. The above-mentioned integrated unit may be implemented in the form of hardware or in the form of software functional units.

[0120] If the integrated unit is implemented in the form of a software functional unit and sold or used as an independent product, it can be stored in a computer-readable storage medium. Based on this understanding, the technical solution of the present application is essentially or the part that contributes to the prior art or all or part of the technical solution can be embodied in the form of a software product, and the computer software product is stored in a storage medium, including multiple instructions to enable an electronic device (which can be a personal computer, server, or network device, etc.) to execute all or part of the steps of each embodiment method of the present application. The aforementioned storage medium includes: U disk, mobile hard disk, read-only memory (Read-Only Memory, ROM), random access memory (Random Access Memory, RAM), disk or optical disk and other media that can store programs.

[0121] The above is a specific description of the preferred implementation of the embodiments of the present application, but the embodiments of the present application are not limited to the above-mentioned implementation methods. Technical personnel familiar with the field can also make various equivalent modifications or substitutions without violating the spirit of the embodiments of the present application. These equivalent modifications or substitutions are all included in the scope defined by the claims of the embodiments of the present application.

Claims

1. A method for testing aerospace systems. It is characterized in that The method comprises: Acquiring on-orbit test data of a space system through a test satellite; the space system includes the test satellite and a formal satellite that have completed networking; Based on the on-orbit test data, a test report of the aerospace system is output.

2. The aerospace system testing method according to claim 1, It is characterized in that Before acquiring the on-orbit test data of the aerospace system by testing the satellite, the method further comprises: Testing multiple candidate satellites, and selecting candidate satellites that meet the requirements as target candidate satellites; Launching the target candidate satellite in a corresponding launch window to allow the target candidate satellite to enter a predetermined orbit; The target candidate satellite is verified in orbit, and the target candidate satellite that meets preset requirements is used as a test satellite.

3. The aerospace system testing method according to claim 2, It is characterized in that After the target candidate satellite is verified on-orbit and the target candidate satellite that meets preset requirements is used as a test satellite, the method further includes: Establishing a communication link between the test satellite and the formal satellite; formulating a data exchange protocol for the communication link; The communication link is collaboratively tested to complete the networking of the test satellite and the formal satellite.

4. The aerospace system testing method according to claim 1, It is characterized in that Before outputting the test of the aerospace system based on the on-orbit test data, the method further includes: Decapsulating the on-track test data, and synchronizing the on-track test data after decapsulation; The synchronized on-track test data is format-converted to obtain the on-track test data in a corresponding format.

5. The aerospace system testing method according to claim 1, It is characterized in that Outputting a test report of the aerospace system based on the on-orbit test data includes: Performing performance analysis on the on-orbit test data to obtain a performance analysis result of the aerospace system; Identify anomalies in the on-orbit test based on the on-orbit test data, analyze the causes of the anomalies, and obtain a problem analysis result of the aerospace system; Based on the problem analysis results, optimization suggestions for the aerospace system are obtained; A test report of the aerospace system is outputted based on the performance analysis results, the problem analysis results and the optimization suggestions.

6. The aerospace system testing method according to claim 5, It is characterized in that The performing performance analysis on the on-orbit test data to obtain the performance analysis result of the aerospace system includes: Calculating the communication transmission performance of the aerospace system from the on-orbit test data based on a throughput evaluation algorithm and a transmission delay evaluation algorithm to obtain a communication transmission performance evaluation result of the aerospace system; Obtaining the accuracy analysis result of the aerospace system from the on-orbit test data through covariance analysis; The performance analysis result of the aerospace system is obtained according to the communication transmission performance evaluation result and the accuracy analysis result.

7. The aerospace system testing method according to claim 1, It is characterized in that After outputting the test report of the aerospace system based on the on-orbit test data, the method further includes: The aerospace system is updated according to the test report.

8. An aerospace system testing device, It is characterized in that The device comprises: A data acquisition module, used to acquire on-orbit test data of a space system through a test satellite; the space system includes the test satellite and the formal satellite that have completed networking; A data analysis module is used to output a test report of the aerospace system based on the on-orbit test data.

9. An electronic device, It is characterized in that It comprises at least one controller and a memory for communicating with the controller; the memory stores instructions that can be executed by the at least one controller, and the instructions are executed by the at least one controller to enable the at least one controller to perform the aerospace system testing method as described in any one of claims 1 to 7.

10. A computer-readable storage medium, It is characterized in that The computer-readable storage medium stores a computer program, and when the computer program is executed, the aerospace system testing method according to any one of claims 1 to 7 is implemented.

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