Space construction load on-orbit application test method and device based on step-by-step optimization

Abstract

The invention discloses a space construction load in-orbit application test method and device based on step-by-step optimization, and belongs to the technical field of space application. The method comprises the steps of determining performance parameters of a space construction load, and determining a task function of the space construction load based on a task function test coefficient f; determining a first test result of the space construction load, determining a technical verification capability coefficient of the space construction load, and determining the technical verification capability of the space construction load based on the technical verification capability coefficient; determining a second test result of the space construction load, and determining the in-orbit application efficiency of the space construction load; and if the in-orbit application efficiency of the space construction load meets the requirement, transferring the space construction load into a business operation state. According to the method, the space construction load testing efficiency is improved, and the in-orbit application benefit of the space construction load can be brought into play.

Description

Technical Field

[0001] The present invention belongs to the field of space application technology, and in particular, relates to an on-orbit application testing method and device for space construction payload based on step-by-step optimization. Background Art

[0002] With the development of space technology, space payloads are becoming more and more complex. They can be built in orbit through multiple transportation and in-orbit integration of unit components of space payloads.

[0003] In order to maximize the application benefits of space construction payloads, it is necessary to conduct on-orbit application tests of space construction payloads in combination with actual operations. Since the unit components of space construction payloads need to be integrated after entering orbit, there is a big difference compared to on-orbit testing and experiments that can be carried out after the satellite enters orbit and establishes a working state.

[0004] Traditional on-orbit application test methods for remote sensing satellites have problems such as long state establishment cycle and slow application benefits, which restrict the effective application benefits of space construction payloads. In order to promote on-orbit application tests of space construction payloads, it is urgent to develop new on-orbit application test methods for space payloads, optimize the test process, and improve test benefits. Summary of the invention

[0005] The present invention provides a method and device for in-orbit application testing of space construction payload based on step-by-step optimization, which are used to solve the above-mentioned problems or at least partially solve the above-mentioned problems.

[0006] In a first aspect, a method for testing an on-orbit application of a space construction payload based on step-by-step optimization is disclosed, the method comprising:

[0007] Step S1: Determine the performance parameters of the space construction payload after on-orbit assembly, including the detector performance parameters. Antenna performance parameters Task deployment performance parameters and store-and-forward performance parameters Generate functional test data D1 based on the performance parameters; determine the mission function test coefficient f of the space construction payload based on the functional test data D1, and determine the mission function of the space construction payload based on the mission function test coefficient f; if the mission function of the space construction payload meets the requirements, proceed to step S2; otherwise, adjust the on-orbit state of the space construction payload and proceed to step S1;

[0008] Step S2: Determine the first test result of the space construction payload, the first test result includes the earth observation capability test result Environmental detection capability test results Communication transmission capability test results and comprehensive technical ability test results Generate a first functional problem list L1 and technical verification data D2 based on the first test result, determine a technical verification capability coefficient t of the space construction payload based on the technical verification data D2, and determine the technical verification capability of the space construction payload based on the technical verification capability coefficient t; if the technical verification capability of the space construction payload meets the requirements, proceed to step S3; otherwise, adjust the on-orbit state of the space construction payload and proceed to step S2;

[0009] Step S3: Determine a second test result of the space construction load, wherein the second test result includes a test resource application efficiency test result. Spectrum Utilization Effectiveness Test Results Disaster Application Performance Test Results Based on the second test result, a second functional problem list L′1 and on-orbit application data D3 are generated; based on the on-orbit application data D3, the on-orbit application efficiency coefficient a of the space construction payload is determined; based on the on-orbit application efficiency coefficient a, the on-orbit application efficiency of the space construction payload is determined; if the on-orbit application efficiency of the space construction payload meets the requirements, the space construction payload is transferred to the business operation state and the method ends; otherwise, the on-orbit state of the space construction payload is adjusted and step S3 is entered.

[0010] Preferably, in step S1, wherein:

[0011] The detector unit is subjected to a detector test F1, wherein the test objects of the detector test F1 include transmittance, pixel size, focal length, quantization bit number, working time, and the detector performance parameters are Denoted as:

[0012]

[0013] Among them, f 11 is the transmittance test result; f 12 is the pixel size test result; f 13 is the focal length test result; f 14 is the test result of quantization bit number; f 15 The test results for working hours;

[0014] The antenna unit is subjected to an antenna function test F2, wherein the test objects of the antenna function test F2 include beam width, antenna gain, beam pointing, operating bandwidth, and pulse repetition frequency. Denoted as:

[0015]

[0016] Among them, f 21 is the beam width test result; f 22is the antenna gain test result; f 23 is the beam pointing test result; f 24 is the working bandwidth test result; f 25 is the pulse repetition frequency test result;

[0017] The control unit is subjected to a task deployment performance test F3, the test objects of which include the processing speed, control accuracy, program loading time, working mode, and timing control of the control unit. Denoted as:

[0018]

[0019] Among them, f 31 is the processing speed test result of the control unit; f 31 is the control accuracy test result of the control unit; f 31 The program loading time test result of the control unit; 31 is the working mode test result of the control unit; f 31 It is the test result of the timing control of the control unit;

[0020] The storage and forwarding unit is subjected to a storage and forwarding test F4, wherein the test objects of the storage and forwarding test F4 include beam width, antenna gain, beam pointing, operating bandwidth, and pulse repetition frequency. Denoted as:

[0021]

[0022] Among them, f 41 is the storage capacity test result; f 42 The test result of read and write mode; f 43 To record and playback the test results; 44 is the test result of effective isotropic radiated power; f 45 This is the test result of data forwarding duration;

[0023] Generate functional test data D1 based on the performance parameters,

[0024] in, i1 is the number of components that make up the space construction load, and j1 is the number of test objects tested for each component unit;

[0025] Determine the mission function test coefficient f of the space construction load based on the function test data D1:

[0026]

[0027] in, It is the preset value of the functional test, which is determined according to the design value of the test object of each component unit of the space construction load;

[0028] If f≥f0, the mission function of the space construction payload meets the requirements, where f0 is the preset value of the mission function test coefficient obtained from the ground laboratory stage test.

[0029] Preferably, in step S2, wherein:

[0030] The space construction payload is subjected to an earth observation test T1. The test objects of the earth observation test T1 include the resolution, width, positioning accuracy, detection rate, and single-circuit working time of the space construction payload. The earth observation capability test results are Denoted as:

[0031]

[0032] Among them, t 11 Resolution test results for the loads built for the space; t 12 The width test results of the load for the space are constructed; t 13 The positioning accuracy test results of the space construction load; 14 The detection rate test results of the load for the space construction; t 15 Single-turn working time test results for the load built for the space;

[0033] The space construction payload is subjected to an environmental detection test T2. The test objects of the environmental detection test T2 include the detection object, coverage, bandwidth, sensitivity, and monitoring duration of the space construction payload. The environmental detection capability test results are Denoted as:

[0034]

[0035] Among them, t 21 Test results of the probe object for the space construction payload; 22 The coverage test results of the loads built for the space; t 23 Bandwidth test results for loads built for the space; t 24 Sensitivity test results of loads built for the space; t 25 Monitoring duration test results for the loads constructed for said space;

[0036] The space construction payload is subjected to a communication transmission test T3. The test objects of the communication transmission test T3 include the communication frequency band, code rate, bit error rate, transmission mode, and single-circuit transmission time of the space construction payload. The communication transmission capability test results are Denoted as:

[0037]

[0038] Among them, t 31 The communication frequency band test results for the space-built payload; 32 The code rate test result of the load constructed for the space; t 33 The bit error rate test result of the space-built payload; 34 Test results of the transmission method for the load constructed in the space; 35 Single-loop transmission time test results for the space-built payload;

[0039] The space construction payload is subjected to a comprehensive technical test T4. The test objects of the comprehensive technical test T4 include the number of collaborative tasks, discovery probability, guidance duration, recognition rate, and processing time of the space construction payload. The comprehensive technical capability test results are Denoted as:

[0040]

[0041] Among them, t 41 Test results of the number of collaborative tasks for the space-building payload; t 42 Probability of discovery test results for the load built for the space; 43 The test results of the guiding time of the load built for the space; t 44 The recognition rate test result of the load is constructed for the space; t 45 Processing time test results for loads built for said space;

[0042] Generate a first functional problem list L1 and technical verification data D2 based on the first test result, in, i2 is the number of technical verification tests for space construction payloads, and j2 is the number of test objects for various technical verification tests;

[0043] Calculation technology verification capability coefficient t:

[0044]

[0045] Among them, α i The importance coefficient of the space construction load technology verification test, 0≤α i ≤1 and It is an estimate of the technical verification capability, determined based on the test object design values ​​of each component unit of the space construction load;

[0046] If t≥t0, the technical verification capability of the space construction load meets the requirements, where t0 is the estimated value of the technical verification capability coefficient of the space construction load.

[0047] Preferably, in step S3, wherein:

[0048] The space construction payload is subjected to a resource survey test A1. The test objects of the resource survey test A1 include the number of tasks, coverage area, update cycle, processing accuracy, and average processing time of imaging data of the space construction payload. The test resource application efficiency test results are Denoted as:

[0049]

[0050] Among them, a 11 The test results of the number of tasks to build a payload for the space; a 12 A test result of the coverage area of ​​the load constructed for the space; a 13 Updated periodic test results for said space construction loads; a 14 The processing accuracy test results of the load for the space construction; a 15 Test results of average processing time of imaging data of the space construction payload;

[0051] The spectrum monitoring test A2 is performed on the space construction payload. The test objects of the spectrum monitoring test A2 include the monitoring times, monitoring range, monitoring cycle, detection objects, and average processing time of spectrum data of the space construction payload. Denoted as:

[0052]

[0053] Among them, a 21 The monitoring number test results of the load construction for the space; a 22 The monitoring range test results of the load construction for the space; a 23 Monitoring period test results for said space construction load; a 24 A test result of a detection object for said space construction load; a 25 The test result of the average processing time of the spectrum data of the space construction payload;

[0054] The space construction load is subjected to a disaster assessment test A3, and the test objects of the disaster assessment test A3 include the number of assessments of the space construction load, the assessment area, the type of disaster, the assessment accuracy, and the average response time. Denoted as:

[0055]

[0056] Among them, a 31 The results of the evaluation of the number of loads built for the space; a32 Evaluation area test results for the load building of the space; a 33 The results of disaster type testing for loads built into the space; a 34 The test results of the evaluation accuracy of the load for the space construction; a 35 average response time test results for loads constructed for said space;

[0057] in, i3 is the number of on-orbit application tests of space construction payloads, and j3 is the number of test objects of various on-orbit application tests;

[0058] Calculate the rail application efficiency coefficient a:

[0059]

[0060] Among them, β i is the importance coefficient of the on-orbit application test of space construction payload, 0≤β i ≤1 and It is the preset value of on-orbit application capability, which is determined according to the design value of the test object of each component unit of the space construction payload;

[0061] If a≥a0, the on-orbit application capability of the space construction payload meets the requirements; a0 is the estimated value of the on-orbit application capability coefficient of the space construction payload.

[0062] In a second aspect, a space construction payload on-orbit application test device based on step-by-step optimization is disclosed, the device comprising:

[0063] Functional test module: configured to determine the performance parameters of the space construction payload after on-orbit assembly, including the detector performance parameters Antenna performance parameters Task deployment performance parameters and store-and-forward performance parameters Generate functional test data D1 based on the performance parameters; determine the mission function test coefficient f of the space construction payload based on the functional test data D1, and determine the mission function of the space construction payload based on the mission function test coefficient f; if the mission function of the space construction payload meets the requirements, trigger the technical verification module; otherwise, adjust the on-orbit state of the space construction payload and trigger the functional test module;

[0064] Technical verification module: configured to determine a first test result of the space construction payload, the first test result including an earth observation capability test result Environmental detection capability test results Communication transmission capability test results and comprehensive technical ability test results Generate a first functional problem list L1 and technical verification data D2 based on the first test result, determine a technical verification capability coefficient t of the space construction payload based on the technical verification data D2, and determine the technical verification capability of the space construction payload based on the technical verification capability coefficient t; if the technical verification capability of the space construction payload meets the requirements, trigger an on-orbit application module; otherwise, adjust the on-orbit state of the space construction payload to trigger the technical verification module;

[0065] On-orbit application module: configured to determine a second test result of the space construction payload, wherein the second test result includes a test resource application efficiency test result Spectrum Utilization Effectiveness Test Results Disaster Application Performance Test Results Based on the second test result, a second functional problem list L′1 and on-orbit application data D3 are generated; based on the on-orbit application data D3, the on-orbit application efficiency coefficient a of the space construction payload is determined; based on the on-orbit application efficiency coefficient a, the on-orbit application efficiency of the space construction payload is determined; if the on-orbit application efficiency of the space construction payload meets the requirements, the space construction payload is transferred to the business operation state; otherwise, the on-orbit state of the space construction payload is adjusted to trigger the on-orbit application module.

[0066] In a third aspect, an electronic device is disclosed, the electronic device comprising:

[0067] at least one processor; and

[0068] a memory communicatively connected to the at least one processor; wherein,

[0069] The memory stores instructions that can be executed by the at least one processor, and the instructions are executed by the at least one processor to enable the at least one processor to perform the method described above.

[0070] In a fourth aspect, a non-transitory computer-readable storage medium storing computer instructions is disclosed, wherein the computer instructions are used to cause the computer to execute the method as described above.

[0071] The present invention has the following technical effects:

[0072] The space construction payload on-orbit application test method based on step-by-step optimization provided by the present invention clarifies the basic process and realizes the space construction payload on-orbit application test based on step-by-step optimization. Compared with the traditional on-orbit test of remote sensing satellites, the present invention aims at the characteristics that the space construction payload needs to be transported multiple times to complete the assembly, completes the on-orbit application test through step-by-step optimization, clarifies the test indicators, test process and other contents, can improve the efficiency of space construction payload testing, and is conducive to giving full play to the on-orbit application benefits of space construction payloads.

[0073] The on-orbit application test method of space construction payload based on step-by-step optimization provided by the present invention realizes the on-orbit application test of space construction payload based on step-by-step optimization, can quantitatively evaluate the on-orbit application capability of space construction payload, and improve the response speed and application efficiency of space construction payload in serving user needs. BRIEF DESCRIPTION OF THE DRAWINGS

[0074] Figure 1 A flow chart of the on-orbit application test method of space construction payload based on step-by-step optimization;

[0075] Figure 2 It is another flow chart of the on-orbit application test method of space construction payload based on step-by-step optimization;

[0076] Figure 3 A schematic diagram of the phased approach for in-orbit application testing of space-built payloads based on step-by-step optimization;

[0077] Figure 4 Schematic diagram of the structure of the on-orbit application test device for space-built payloads based on step-by-step optimization. DETAILED DESCRIPTION

[0078] The embodiments of the present invention are described in detail below with reference to the accompanying drawings.

[0079] like Figure 1 As shown, the present invention provides a method for testing the on-orbit application of a space construction payload based on step-by-step optimization, the method comprising:

[0080] Step S1: Determine the performance parameters of the space construction payload after on-orbit assembly, including the detector performance parameters. Antenna performance parameters Task deployment performance parameters and store-and-forward performance parameters Generate functional test data D1 based on the performance parameters; determine the mission function test coefficient f of the space construction payload based on the functional test data D1, and determine the mission function of the space construction payload based on the mission function test coefficient f; if the mission function of the space construction payload meets the requirements, proceed to step S2; otherwise, adjust the on-orbit state of the space construction payload and proceed to step S1;

[0081] Step S2: Determine the first test result of the space construction payload, the first test result includes the earth observation capability test result Environmental detection capability test results Communication transmission capability test results and comprehensive technical ability test results Generate a first functional problem list L1 and technical verification data D2 based on the first test result, determine a technical verification capability coefficient t of the space construction payload based on the technical verification data D2, and determine the technical verification capability of the space construction payload based on the technical verification capability coefficient t; if the technical verification capability of the space construction payload meets the requirements, proceed to step S3; otherwise, adjust the on-orbit state of the space construction payload and proceed to step S2;

[0082] Step S3: Determine a second test result of the space construction load, wherein the second test result includes a test resource application efficiency test result. Spectrum Utilization Effectiveness Test Results Disaster Application Performance Test Results Based on the second test result, a second functional problem list L′1 and on-orbit application data D3 are generated; based on the on-orbit application data D3, the on-orbit application efficiency coefficient a of the space construction payload is determined; based on the on-orbit application efficiency coefficient a, the on-orbit application efficiency of the space construction payload is determined; if the on-orbit application efficiency of the space construction payload meets the requirements, the space construction payload is transferred to the business operation state and the method ends; otherwise, the on-orbit state of the space construction payload is adjusted and step S3 is entered.

[0083] Space construction payloads are usually composed of detector units, antenna units, control units, storage and forwarding units and other components. After on-orbit assembly through multiple transportations, component function tests can be carried out based on component connectivity tests.

[0084] The present invention realizes an on-orbit application test of space construction payload based on step-by-step optimization, which can quantitatively evaluate the on-orbit application capability of space construction payload.

[0085] The step S1 comprises:

[0086] The detector unit is subjected to a detector test F1, wherein the test objects of the detector test F1 include transmittance, pixel size, focal length, quantization bit number, working time, and the detector performance parameters are Denoted as:

[0087]

[0088] Among them, f 11 is the transmittance test result; f 12is the pixel size test result; f 13 is the focal length test result; f 14 is the test result of quantization bit number; f 15 This is the working time test result.

[0089] The antenna unit is subjected to an antenna function test F2, wherein the test objects of the antenna function test F2 include beam width, antenna gain, beam pointing, operating bandwidth, and pulse repetition frequency. Denoted as:

[0090]

[0091] Among them, f 21 is the beam width test result; f 22 is the antenna gain test result; f 23 is the beam pointing test result; f 24 is the working bandwidth test result; f 25 This is the pulse repetition frequency test result.

[0092] The control unit is subjected to a task deployment performance test F3, the test objects of which include the processing speed, control accuracy, program loading time, working mode, and timing control of the control unit. Denoted as:

[0093]

[0094] Among them, f 31 is the processing speed test result of the control unit; f 31 is the control accuracy test result of the control unit; f 31 The program loading time test result of the control unit; 31 is the working mode test result of the control unit; f 31 It is the test result of the timing control of the control unit.

[0095] The storage and forwarding unit is subjected to a storage and forwarding test F4, wherein the test objects of the storage and forwarding test F4 include beam width, antenna gain, beam pointing, operating bandwidth, and pulse repetition frequency. Denoted as:

[0096]

[0097] Among them, f 41 is the storage capacity test result; f 42 The test result of read and write mode; f 43 To record and playback the test results; 44 is the test result of effective isotropic radiated power; f45 This is the test result of data forwarding duration.

[0098] Generate functional test data D1 based on the performance parameters,

[0099] in, i1 is the number of components that make up the space construction load, and j1 is the number of test objects tested for each component unit.

[0100] Determine the mission function test coefficient f of the space construction load based on the function test data D1:

[0101]

[0102] in, It is the preset value of the functional test, which is determined according to the design value of the test object of each component unit of the space construction load;

[0103] If f≥f0, the mission function of the space construction payload meets the requirements, and the process goes to step S2; wherein f0 is a preset value of the mission function test coefficient obtained during the ground laboratory phase test.

[0104] The step S2 comprises:

[0105] The space construction payload is subjected to an earth observation test T1. The test objects of the earth observation test T1 include the resolution, width, positioning accuracy, detection rate, and single-circuit working time of the space construction payload. The earth observation capability test results are Denoted as:

[0106]

[0107] Among them, t 11 Resolution test results for the loads built for the space; t 12 The width test results of the load for the space are constructed; t 13 The positioning accuracy test results of the space construction load; 14 The detection rate test results of the load for the space construction; t 15 Single lap duration test results for the space construction load.

[0108] The space construction payload is subjected to an environmental detection test T2. The test objects of the environmental detection test T2 include the detection object, coverage, bandwidth, sensitivity, and monitoring duration of the space construction payload. The environmental detection capability test results are Denoted as:

[0109]

[0110] Among them, t21 Test results of the probe object for the space construction payload; 22 The coverage test results of the loads built for the space; t 23 Bandwidth test results for loads built for the space; t 24 Sensitivity test results of loads built for the space; t 25 The monitoring duration test results of the load for the space construction are as follows.

[0111] The space construction payload is subjected to a communication transmission test T3. The test objects of the communication transmission test T3 include the communication frequency band, code rate, bit error rate, transmission mode, and single-circuit transmission time of the space construction payload. The communication transmission capability test results are Denoted as:

[0112]

[0113] Among them, t 31 The communication frequency band test results for the space-built payload; 32 The code rate test result of the load constructed for the space; t 33 The bit error rate test result of the space-built payload; 34 Test results of the transmission method for the load constructed in the space; 35 Single-turn transmission time test results for the space construction payload.

[0114] The space construction payload is subjected to a comprehensive technical test T4. The test objects of the comprehensive technical test T4 include the number of collaborative tasks, discovery probability, guidance time, recognition rate, and processing time of the space construction payload. The comprehensive technical capability test results are Denoted as:

[0115]

[0116] Among them, t 41 Test results of the number of collaborative tasks for the space-building payload; t 42 Probability of discovery test results for the load built for the space; 43 The test results of the guiding time of the load built for the space; t 44 The recognition rate test result of the load is constructed for the space; t 45 Processing time test results for the space build load.

[0117] Generate a first functional problem list L1 and technical verification data D2 based on the first test result, in, i2 is the number of technical verification tests for space construction payloads, and j2 is the number of test objects for various technical verification tests;

[0118] It is the first functional problem identifier, which is unique; The name of the component involved in the first functional problem; A detailed description of the first functional problem; is the impact degree and solution time requirement of the first functional problem; k1 is the number of the first functional problem.

[0119] Calculation technology verification capability coefficient t:

[0120]

[0121] Among them, α i The importance coefficient of the space construction load technology verification test, 0≤α i ≤1 and It is an estimate of the technical verification capability and is determined based on the design values ​​of the test objects of each component of the space construction load.

[0122] If t≥t0, the technical verification capability of the space construction load meets the requirements, and the process proceeds to step S3; wherein t0 is an estimated value of the technical verification capability coefficient of the space construction load.

[0123] α i The importance of space construction load testing is generally assigned based on relevant technical verification tests, and can also be determined through negotiation based on user requirements.

[0124] The step S3 comprises:

[0125] The space construction payload is subjected to a resource survey test A1. The test objects of the resource survey test A1 include the number of tasks, coverage area, update cycle, processing accuracy, and average processing time of imaging data of the space construction payload. The test resource application efficiency test results are Denoted as:

[0126]

[0127] Among them, a 11 The test results of the number of tasks to build a payload for the space; a 12 A test result of the coverage area of ​​the load constructed for the space; a 13 Updated periodic test results for said space construction loads; a 14 The processing accuracy test results of the load for the space construction; a 15 The test results of the average processing time of imaging data of the space construction payload are as follows.

[0128] The spectrum monitoring test A2 is performed on the space construction payload. The test objects of the spectrum monitoring test A2 include the monitoring times, monitoring range, monitoring cycle, detection objects, and average processing time of spectrum data of the space construction payload. Denoted as:

[0129]

[0130] Among them, a 21 The monitoring number test results of the load construction for the space; a 22 The monitoring range test results of the load construction for the space; a 23 Monitoring period test results for said space construction load; a 24 A test result of a detection object for said space construction load; a 25 The test results of the average processing time of the spectrum data of the space construction payload are as follows.

[0131] The space construction load is subjected to a disaster assessment test A3, and the test objects of the disaster assessment test A3 include the number of assessments of the space construction load, the assessment area, the type of disaster, the assessment accuracy, and the average response time. Denoted as:

[0132]

[0133] Among them, a 31 The results of the evaluation of the number of loads built for the space; a 32 Evaluation area test results for the load building of the space; a 33 The results of disaster type testing for loads built into the space; a 34 The test results of the evaluation accuracy of the load for the space construction; a 35 Average response time test results for the space construction loads.

[0134] in, i3 is the number of on-orbit application tests of space construction payloads, and j3 is the number of test objects of various on-orbit application tests.

[0135] It is the second function problem identifier, which is unique; The name of the component involved in the second functional problem; A detailed description of the second functional problem; is the impact degree and solution time requirement of the second functional problem; k2 is the number of the second functional problem.

[0136] Calculate the rail application efficiency coefficient a:

[0137]

[0138] Among them, β i is the importance coefficient of the on-orbit application test of space construction payload, 0≤β i ≤1 and It is the preset value of on-orbit application capability, which is determined according to the design value of the test object of each component unit of the space construction payload;

[0139] If a≥a0, the on-orbit application capability of the space construction payload meets the requirements; a0 is the estimated value of the on-orbit application capability coefficient of the space construction payload.

[0140] β i The importance of space construction load testing is generally assigned based on relevant on-orbit application tests, and can also be determined through negotiation based on user requirements.

[0141] like Figure 2-Figure 3 As shown, the present invention provides a method for testing the on-orbit application of a space construction payload based on step-by-step optimization, the method comprising:

[0142] 1) Carry out functional test F. After the space construction payload completes on-orbit assembly, on the basis of component connectivity test, carry out detector test F1, antenna function test F2, mission deployment test F3, and storage and forwarding test F4 to test the mission function performance indicators of the space construction payload and obtain functional test data D1;

[0143] 2) Organize technical verification test T. Use the functional test data D1 to complete the on-orbit state parameter tuning of the space construction payload, organize and carry out earth observation test T1, environmental detection test T2, communication transmission test T3, and comprehensive technical test T4 to verify the new technology verification capability of the space construction payload, obtain the functional problem list L1 and technical verification data D2, and carry out additional mission function tests for the first functional problem list L1;

[0144] 3) Implement on-orbit application test A. Use the technical verification data D2 to optimize the application mode of space construction payloads, organize resource survey test A1, spectrum monitoring test A2 and disaster assessment test A3, evaluate the on-orbit application capability of space construction payloads, obtain the second functional problem list L′1 and on-orbit application data D3, and conduct supplementary technical verification tests for the second functional problem list L′1.

[0145] like Figure 4 As shown, the present invention provides a space construction payload on-orbit application test device based on step-by-step optimization, the device comprising:

[0146] Functional test module 201: configured to determine the performance parameters of the space construction payload after on-orbit assembly, the performance parameters including the detector performance parameters Antenna performance parameters Task deployment performance parameters and store-and-forward performance parameters Generate functional test data D1 based on the performance parameters; determine the mission function test coefficient f of the space construction payload based on the functional test data D1, and determine the mission function of the space construction payload based on the mission function test coefficient f; if the mission function of the space construction payload meets the requirements, trigger the technical verification module; otherwise, adjust the on-orbit state of the space construction payload and trigger the functional test module;

[0147] Technical verification module 202: configured to determine a first test result of the space construction payload, the first test result including an earth observation capability test result Environmental detection capability test results Communication transmission capability test results and comprehensive technical ability test results Generate a first functional problem list L1 and technical verification data D2 based on the first test result, determine a technical verification capability coefficient t of the space construction payload based on the technical verification data D2, and determine the technical verification capability of the space construction payload based on the technical verification capability coefficient t; if the technical verification capability of the space construction payload meets the requirements, trigger an on-orbit application module; otherwise, adjust the on-orbit state of the space construction payload to trigger the technical verification module;

[0148] On-orbit application module 203: configured to determine a second test result of the space construction payload, wherein the second test result includes a test resource application efficiency test result Spectrum Utilization Effectiveness Test Results

[0149] Disaster Application Performance Test Results Based on the second test result, a second functional problem list L′1 and on-orbit application data D3 are generated; based on the on-orbit application data D3, the on-orbit application efficiency coefficient a of the space construction payload is determined; based on the on-orbit application efficiency coefficient a, the on-orbit application efficiency of the space construction payload is determined; if the on-orbit application efficiency of the space construction payload meets the requirements, the space construction payload is transferred to the business operation state; otherwise, the on-orbit state of the space construction payload is adjusted to trigger the on-orbit application module.

[0150] The above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit them. Although the present invention has been described in detail with reference to the above embodiments, it should be understood by those skilled in the art that the technical solutions described in the above embodiments can still be modified, or some or all of the technical features therein can be replaced by equivalents, and these modifications or replacements do not make the essence of the corresponding technical solutions deviate from the scope of the technical solutions of the embodiments of the present invention.

Claims

1. A method for testing on-orbit application of space construction payload based on step-by-step optimization, characterized in that: The method comprises: Step S1: Determine the performance parameters of the space construction payload after on-orbit assembly, including the detector performance parameters. Antenna performance parameters Task deployment performance parameters and store-and-forward performance parameters Generate functional test data D1 based on the performance parameters; determine the mission function test coefficient f of the space construction payload based on the functional test data D1, and determine the mission function of the space construction payload based on the mission function test coefficient f; if the mission function of the space construction payload meets the requirements, proceed to step S2; otherwise, adjust the on-orbit state of the space construction payload and proceed to step S1; Step S2: Determine the first test result of the space construction payload, the first test result includes the earth observation capability test result Environmental detection capability test results Communication transmission capability test results and comprehensive technical ability test results Generate a first functional problem list L1 and technical verification data D2 based on the first test result, determine a technical verification capability coefficient t of the space construction payload based on the technical verification data D2, and determine the technical verification capability of the space construction payload based on the technical verification capability coefficient t; if the technical verification capability of the space construction payload meets the requirements, proceed to step S3; otherwise, adjust the on-orbit state of the space construction payload and proceed to step S2; Step S3: Determine a second test result of the space construction load, wherein the second test result includes a test resource application efficiency test result. Spectrum Utilization Effectiveness Test Results Disaster Application Performance Test Results Based on the second test result, a second functional problem list L′1 and on-orbit application data D3 are generated; based on the on-orbit application data D3, the on-orbit application efficiency coefficient a of the space construction payload is determined; based on the on-orbit application efficiency coefficient a, the on-orbit application efficiency of the space construction payload is determined; if the on-orbit application efficiency of the space construction payload meets the requirements, the space construction payload is transferred to the business operation state and the method ends; otherwise, the on-orbit state of the space construction payload is adjusted and step S3 is entered.

2. The method according to claim 1, characterized in that The step S1, wherein: The detector unit is subjected to a detector test F1, wherein the test objects of the detector test F1 include transmittance, pixel size, focal length, quantization bit number, working time, and the detector performance parameters are Denoted as: Among them, f 11 is the transmittance test result; f 12 is the pixel size test result; f 13 is the focal length test result; f 14 is the test result of quantization bit number; f 15 The test results for working hours; The antenna unit is subjected to an antenna function test F2, wherein the test objects of the antenna function test F2 include beam width, antenna gain, beam pointing, operating bandwidth, and pulse repetition frequency. Denoted as: Among them, f 21 is the beam width test result; f 22 is the antenna gain test result; f 23 is the beam pointing test result; f 24 is the working bandwidth test result; f 25 is the pulse repetition frequency test result; The control unit is subjected to a task deployment performance test F3, the test objects of which include the processing speed, control accuracy, program loading time, working mode, and timing control of the control unit. Denoted as: Among them, f 31 is the processing speed test result of the control unit; f 31 is the control accuracy test result of the control unit; f 31 The program loading time test result of the control unit; 31 is the working mode test result of the control unit; f 31 It is the test result of the timing control of the control unit; The storage and forwarding unit is subjected to a storage and forwarding test F4, wherein the test objects of the storage and forwarding test F4 include beam width, antenna gain, beam pointing, operating bandwidth, and pulse repetition frequency. Denoted as: Among them, f 41 is the storage capacity test result; f 42 The test result of read and write mode; f 43 To record and playback the test results; 44 is the test result of effective isotropic radiated power; f 45 This is the test result of data forwarding duration; Generate functional test data D1 based on the performance parameters, in, i1 is the number of components that make up the space construction load, and j1 is the number of test objects tested for each component unit; Determine the mission function test coefficient f of the space construction load based on the function test data D1: in, It is the preset value of the functional test, which is determined according to the design value of the test object of each component unit of the space construction load; If f≥f0, the mission function of the space construction payload meets the requirements, where f0 is the preset value of the mission function test coefficient obtained from the ground laboratory stage test.

3. The method according to claim 1, characterized in that The step S2, wherein: The space construction payload is subjected to an earth observation test T1. The test objects of the earth observation test T1 include the resolution, width, positioning accuracy, detection rate, and single-circuit working time of the space construction payload. The earth observation capability test results are Denoted as: Among them, t 11 Resolution test results for the loads built for the space; t 12 The width test results of the load for the space are constructed; t 13 The positioning accuracy test results of the space construction load; 14 The detection rate test results of the load for the space construction; t 15 Single-turn working time test results for the load built for the space; The space construction payload is subjected to an environmental detection test T2. The test objects of the environmental detection test T2 include the detection object, coverage, bandwidth, sensitivity, and monitoring duration of the space construction payload. The environmental detection capability test results are Denoted as: Among them, t 21 Test results of the probe object for the space construction payload; 22 The coverage test results of the loads built for the space; t 23 Bandwidth test results for loads built for the space; t 24 Sensitivity test results of loads built for the space; t 25 Monitoring duration test results for the loads constructed for said space; The space construction payload is subjected to a communication transmission test T3. The test objects of the communication transmission test T3 include the communication frequency band, code rate, bit error rate, transmission mode, and single-circuit transmission time of the space construction payload. The communication transmission capability test results are Denoted as: Among them, t 31 The communication frequency band test results for the space-built payload; 32 The code rate test result of the load constructed for the space; t 33 The bit error rate test result of the space-built payload; 34 Test results of the transmission method for the load constructed in the space; 35 Single-loop transmission time test results for the space-built payload; The space construction payload is subjected to a comprehensive technical test T4, and the test objects of the comprehensive technical test T4 include the number of collaborative tasks, discovery probability, guidance time, recognition rate, Processing time, will be comprehensive technical ability test results Denoted as: Among them, t 41 Test results of the number of collaborative tasks for the space-building payload; t 42 Probability of discovery test results for the load built for the space; 43 The test results of the guiding time of the load built for the space; t 44 The recognition rate test result of the load is constructed for the space; t 45 Processing time test results for loads built for said space; Generate a first functional problem list L1 and technical verification data D2 based on the first test result, in, i2 is the number of technical verification tests for space construction payloads, and j2 is the number of test objects for various technical verification tests; Calculation technology verification capability coefficient t: Among them, α i The importance coefficient of the space construction load technology verification test, 0≤α i ≤1 and It is an estimate of the technical verification capability, determined based on the test object design values ​​of each component unit of the space construction load; If t≥t0, the technical verification capability of the space construction load meets the requirements, where t0 is the estimated value of the technical verification capability coefficient of the space construction load.

4. The method according to claim 1, characterized in that The step S3, wherein: The space construction payload is subjected to a resource survey test A1. The test objects of the resource survey test A1 include the number of tasks, coverage area, update cycle, processing accuracy, and average processing time of imaging data of the space construction payload. The test resource application efficiency test results are Denoted as: Among them, a 11 The test results of the number of tasks to build a payload for the space; a 12 A test result of the coverage area of ​​the load constructed for the space; a 13 Updated periodic test results for said space construction loads; a 14 The processing accuracy test results of the load for the space construction; a 15 Test results of average processing time of imaging data of the space construction payload; The spectrum monitoring test A2 is performed on the space construction payload. The test objects of the spectrum monitoring test A2 include the monitoring times, monitoring range, monitoring cycle, detection objects, and average processing time of spectrum data of the space construction payload. Denoted as: Among them, a 21 The number of test results for monitoring the load of the space; a 22 The monitoring range test results of the load construction for the space; a 23 Monitoring period test results for said space construction load; a 24 A test result of a detection object for said space construction load; a 25 The test result of the average processing time of the spectrum data of the space construction payload; The space construction load is subjected to a disaster assessment test A3, and the test objects of the disaster assessment test A3 include the number of assessments of the space construction load, the assessment area, the type of disaster, the assessment accuracy, and the average response time. Denoted as: Among them, a 31 The results of the evaluation of the number of loads built for the space; a 32 Evaluation area test results for the load building of the space; a 33 The results of disaster type testing for loads built into the space; a 34 The test results of the evaluation accuracy of the load for the space construction; a 35 average response time test results for loads constructed for said space; in, i3 is the number of on-orbit application tests of space construction payloads, and j3 is the number of test objects of various on-orbit application tests; Calculate the rail application efficiency coefficient a: Among them, β i is the importance coefficient of the on-orbit application test of space construction payload, 0≤β i ≤1 and It is the preset value of on-orbit application capability, which is determined according to the design value of the test object of each component unit of the space construction payload; If a≥a0, the on-orbit application capability of the space construction payload meets the requirements; a0 is the estimated value of the on-orbit application capability coefficient of the space construction payload.

5. A space construction payload on-orbit application test device based on step-by-step optimization, characterized in that: The device comprises: Functional test module: configured to determine the performance parameters of the space construction payload after on-orbit assembly, including the detector performance parameters Antenna performance parameters Task deployment performance parameters and store-and-forward performance parameters Generate functional test data D1 based on the performance parameters; determine the mission function test coefficient f of the space construction payload based on the functional test data D1, and determine the mission function of the space construction payload based on the mission function test coefficient f; if the mission function of the space construction payload meets the requirements, trigger the technical verification module; otherwise, adjust the on-orbit state of the space construction payload and trigger the functional test module; Technical verification module: configured to determine a first test result of the space construction payload, the first test result including an earth observation capability test result Environmental detection capability test results Communication transmission capability test results and comprehensive technical ability test results Generate a first functional problem list L1 and technical verification data D2 based on the first test result, determine a technical verification capability coefficient t of the space construction payload based on the technical verification data D2, and determine the technical verification capability of the space construction payload based on the technical verification capability coefficient t; if the technical verification capability of the space construction payload meets the requirements, trigger an on-orbit application module; otherwise, adjust the on-orbit state of the space construction payload to trigger the technical verification module; On-orbit application module: configured to determine a second test result of the space construction payload, wherein the second test result includes a test resource application efficiency test result Spectrum Utilization Effectiveness Test Results Disaster Application Performance Test Results Based on the second test result, a second functional problem list L′1 and on-orbit application data D3 are generated; based on the on-orbit application data D3, the on-orbit application efficiency coefficient a of the space construction payload is determined; based on the on-orbit application efficiency coefficient a, the on-orbit application efficiency of the space construction payload is determined; if the on-orbit application efficiency of the space construction payload meets the requirements, the space construction payload is transferred to the business operation state; otherwise, the on-orbit state of the space construction payload is adjusted to trigger the on-orbit application module.

6. An electronic device, characterized in that: The device comprises: at least one processor; and a memory communicatively connected to the at least one processor; wherein, The memory stores instructions that can be executed by the at least one processor, and the instructions are executed by the at least one processor to enable the at least one processor to perform the method according to any one of claims 1 to 4.

7. A non-transitory computer-readable storage medium storing computer instructions, characterized in that: The computer instructions are used to cause the computer to execute the method according to any one of claims 1 to 4.

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