Spacecraft whole-process magnetic control method and device

Abstract

The embodiment of the specification provides a spacecraft full-process magnetic control method and device, the method comprising: determining demonstration single-machine magnetic control indexes based on a single-machine list, and determining demonstration whole-machine magnetic control indexes based on the demonstration single-machine magnetic control indexes; adjusting single-machine magnetic control index determination scheme single-machine magnetic control indexes based on the demonstration whole-machine magnetic control indexes and demonstration whole-machine magnetic requirement; determining scheme whole-machine magnetic control indexes based on the scheme single-machine magnetic control indexes, and adjusting the scheme single-machine magnetic control indexes based on the scheme magnetic control indexes and the scheme whole-machine magnetic requirement to determine preliminary sample single-machine magnetic control indexes; performing a magnetic test based on the preliminary sample single-machine magnetic control indexes, determining a test result, and adjusting the preliminary sample single-machine magnetic control indexes based on the test result and preliminary sample whole-machine magnetic requirement to determine positive sample single-machine magnetic control indexes; determining positive sample whole-machine magnetic control indexes based on the positive sample single-machine magnetic control indexes, and through execution of different index decomposition algorithm, the spacecraft development party can be guided to know the magnetic control index situation in advance, and the expected index value is accurately given.

Description

TECHNICAL FIELD

[0001] Embodiments of the present specification relate to the technical field of spacecraft magnetic control, and in particular to a spacecraft full-process magnetic control method. BACKGROUND

[0002] Space magnetic field detection is one of the important tasks of spacecrafts at home and abroad. In order to make the magnetometer carried measure high-precision space magnetic field data, the spacecraft magnetic property must be controlled to reduce the magnetic field interference of the spacecraft itself on the magnetometer. Because the satellite magnetic property source and change are very complex, the spacecraft magnetic control implementation is extremely difficult. At present, the spacecraft magnetic control has become the core work of the development of space magnetic field detection spacecraft.

[0003] The development stage of the spacecraft can be divided into four stages in turn, namely, demonstration, scheme, preliminary sample and final sample. In order to achieve the expected magnetic control index, the most reliable magnetic control method is to start from the spacecraft demonstration stage and carry out corresponding magnetic control work in the spacecraft demonstration, scheme, preliminary sample and final sample stages.

[0004] Briefly speaking, magnetic control is to divide the whole spacecraft magnetic control index into the magnetic control index of each single machine according to the task proposed magnetic control index, and different index decomposition and calculation algorithms are used in different stages. Through the full implementation of the single machine index, the magnetic control index of the whole spacecraft is realized. Therefore, determining the magnetic control index of each single machine is a very important work link and content of the magnetic control work, which involves the whole stage and the whole process of the spacecraft. If the single machine index decomposition is too strict, the single machine cannot complete the index, and if the decomposition is too loose, the final whole spacecraft magnetic control index cannot meet the task requirements. At the same time, the single machine magnetic control index is an important input and constraint condition for the development of each single machine, which needs to be dynamically adjusted in different stages. Therefore, the determination algorithm of the single machine index in different stages is very important. Therefore, a scientific, reasonable and feasible spacecraft full-process magnetic control method with single machine magnetic control index decomposition and calculation algorithm as the core is needed.

[0005] At present, there is no related scheme, and therefore, a magnetic control scheme is urgently needed. SUMMARY

[0006] Therefore, the spacecraft full-process magnetic control method provided by the embodiments of the present specification. One or more embodiments of the present specification also relate to a spacecraft full-process magnetic control device, a computing device, a computer readable storage medium and a computer program to solve the technical defects in the prior art.

[0007] According to a first aspect of the embodiments of the present specification, a spacecraft full-process magnetic control method is provided, comprising:

[0008] Obtaining a single machine list, determining a demonstration single machine magnetic control index based on the single machine list, and determining a demonstration whole machine magnetic control index based on the demonstration single machine magnetic control index;

[0009] Adjusting the single machine magnetic control index to determine a scheme single machine magnetic control index based on the demonstration whole machine magnetic control index and the demonstration whole machine magnetic requirement;

[0010] Determining a scheme whole machine magnetic control index based on the scheme single machine magnetic control index, and adjusting the scheme single machine magnetic control index based on the scheme magnetic control index and the scheme whole machine magnetic requirement to determine a preliminary sample single machine magnetic control index;

[0011] Performing a magnetic test based on the preliminary sample single machine magnetic control index, determining a test result, and adjusting the preliminary sample single machine magnetic control index based on the test result and a preliminary sample whole machine magnetic requirement to determine a positive sample single machine magnetic control index;

[0012] Determining a positive sample whole machine magnetic control index based on the positive sample single machine magnetic control index.

[0013] In a possible implementation, the demonstration single machine magnetic control index is determined based on the single machine list, including:

[0014] At least two single machines are determined based on the single machine list, and historical data of the single machines is obtained;

[0015] The demonstration single machine magnetic control index is determined based on the historical data.

[0016] In a possible implementation, the demonstration single machine magnetic control index is determined based on the single machine list, including:

[0017] In a case where the single machine does not have historical data, the single machine is decomposed to determine at least two modules;

[0018] Module historical data of the at least two modules is obtained, and the module historical data is accumulated to determine the demonstration single machine magnetic control index.

[0019] In a possible implementation, the demonstration whole machine magnetic control index is determined based on the demonstration single machine magnetic control index, including:

[0020] Magnetic moment data in each direction corresponding to each single machine is determined;

[0021] A total magnetic moment is determined based on the magnetic moment data in each direction;

[0022] Magnetic field data is determined by a dipole method based on the total magnetic moment, and the demonstration whole machine magnetic control index is determined based on the magnetic field data.

[0023] In a possible implementation, the scheme whole machine magnetic control index is determined based on the scheme single machine magnetic control index, including:

[0024] A scheme total magnetic moment is determined based on the scheme single machine magnetic control index;

[0025] convert the scheme magnetic field data based on the scheme total magnetic moment;

[0026] determine the scheme machine magnetic control index based on the scheme magnetic field data and the normal distribution.

[0027] In a possible implementation, the positive sample machine magnetic control index is determined by adjusting the preliminary sample machine magnetic control index based on the test result and the preliminary sample machine magnetic requirement, comprising:

[0028] determine the preliminary sample total magnetic moment based on the test result;

[0029] determine the preliminary sample machine magnetic control index based on the preliminary sample total magnetic moment, and adjust the preliminary sample machine magnetic control index to determine the positive sample machine magnetic control index based on the preliminary sample machine magnetic control index and the preliminary sample machine magnetic requirement.

[0030] In a possible implementation, the positive sample machine magnetic control index is determined by adjusting the preliminary sample machine magnetic control index based on the preliminary sample machine magnetic control index and the preliminary sample machine magnetic requirement, comprising:

[0031] In the case that the preliminary sample machine magnetic control index does not meet the preliminary sample machine magnetic requirement, the preliminary sample machine magnetic control index is reduced to determine the target machine;

[0032] determine the positive sample machine magnetic control index based on the target machine.

[0033] According to a second aspect of the embodiments of the present specification, a spacecraft full-process magnetic control device is provided, comprising:

[0034] The demonstration module is configured to obtain a machine list, determine a demonstration machine magnetic control index based on the machine list, and determine a demonstration machine magnetic control index based on the demonstration machine magnetic control index;

[0035] The scheme module is configured to adjust the machine magnetic control index to determine a scheme machine magnetic control index based on the demonstration machine magnetic control index and a demonstration machine magnetic requirement;

[0036] The preliminary sample module is configured to determine a scheme machine magnetic control index based on the scheme machine magnetic control index, and adjust the scheme machine magnetic control index to determine a preliminary sample machine magnetic control index based on the scheme machine magnetic control index and a scheme machine magnetic requirement;

[0037] The positive sample module is configured to determine a test result based on a magnetic test performed based on the preliminary sample machine magnetic control index, and adjust the preliminary sample machine magnetic control index to determine a positive sample machine magnetic control index based on the test result and a preliminary sample machine magnetic requirement;

[0038] The result module is configured to determine a positive sample machine magnetic control index based on the positive sample machine magnetic control index.

[0039] According to a third aspect of the embodiments of the present specification, a computing device is provided, comprising:

[0040] a memory and a processor;

[0041] The memory is configured to store computer-executable instructions, and the processor is configured to execute the computer-executable instructions, which, when executed by the processor, implement the steps of the spacecraft full-process magnetic control method.

[0042] According to a fourth aspect of the embodiments of the present specification, a computer-readable storage medium is provided, which stores computer-executable instructions, which, when executed by a processor, implement the steps of the spacecraft full-process magnetic control method.

[0043] According to a fifth aspect of the embodiments of the present specification, a computer program is provided, which, when executed in a computer, causes the computer to perform the steps of the spacecraft full-process magnetic control method.

[0044] The embodiments of the present specification provide a spacecraft full-process magnetic control method and device. The method comprises: determining demonstration single-machine magnetic control indicators based on a single-machine list, and determining demonstration whole-machine magnetic control indicators based on the demonstration single-machine magnetic control indicators; determining scheme single-machine magnetic control indicators based on the demonstration whole-machine magnetic control indicators and demonstration whole-machine magnetic requirements, and determining scheme whole-machine magnetic control indicators based on the scheme single-machine magnetic control indicators; adjusting the scheme single-machine magnetic control indicators based on the scheme whole-machine magnetic control indicators and scheme whole-machine magnetic requirements to determine preliminary sample single-machine magnetic control indicators; performing a magnetic test based on the preliminary sample single-machine magnetic control indicators, determining a test result, and adjusting the preliminary sample single-machine magnetic control indicators based on the test result and preliminary sample whole-machine magnetic requirements to determine positive sample single-machine magnetic control indicators; determining positive sample whole-machine magnetic control indicators based on the positive sample single-machine magnetic control indicators, and guiding a spacecraft development party to understand the magnetic control indicators in advance and accurately give expected indicator values by executing different index decomposition algorithm. BRIEF DESCRIPTION OF DRAWINGS

[0045] Figure 1 is a flowchart of a spacecraft full-process magnetic control method provided by an embodiment of the present specification;

[0046] Figure 2 is a structural schematic diagram of a spacecraft full-process magnetic control device provided by an embodiment of the present specification;

[0047] Figure 3 is a structural block diagram of a computing device provided by an embodiment of the present specification. DETAILED DESCRIPTION

[0048] In the following description, numerous specific details are set forth to provide a thorough understanding of the specification. However, the specification can be practiced without the specific details. In other instances, well-known methods, procedures, components, and networks have not been described in detail so as not to unnecessarily obscure the specification.

[0049] The terminology used in this description of one or more embodiments is for the purpose of describing particular embodiments only and is not intended to be limiting of one or more embodiments of the specification. As used in this description and the appended claims, the singular forms "a," "an" and "the" are intended to include the plural forms as well, unless the context clearly indicates otherwise. It will also be understood that the term "and / or" as used herein refers to and encompasses any and all possible combinations of one or more of the associated listed items.

[0050] It will be understood that, although the terms first, second, etc. can be used herein to describe various information, these terms are not intended to denote a temporal or chronological order. Rather, these terms are used solely to distinguish one from another only. For example, a first entity discussed below could later be discussed as a second entity, and similarly, a second entity discussed below could later be discussed as a first entity without departing from the scope of one or more embodiments. As used herein, the term "if' can be construed to mean "when" or "in response to determining" or "in response to a determination" or "in response to the fact that... "

[0051] In the specification, a spacecraft full-process magnetic control method is provided, and the specification also relates to a spacecraft full-process magnetic control device, a computing device, and a computer-readable storage medium, which are described in detail one by one in the following embodiments.

[0052] Referring to Figure 1 , Figure 1 A flowchart of a spacecraft full-process magnetic control method according to one embodiment of the specification is shown, which specifically includes the following steps.

[0053] Step 101: Obtain a single-machine list, determine a demonstration single-machine magnetic control index based on the single-machine list, and determine a demonstration whole-machine magnetic control index based on the demonstration single-machine magnetic control index.

[0054] In one possible implementation, determining the demonstration single-machine magnetic control index based on the single-machine list includes: determining at least two single machines based on the single-machine list, obtaining historical data of the single machines, and determining the demonstration single-machine magnetic control index based on the historical data.

[0055] In practical application, the index decomposition needs to be estimated according to the magnetism of the single machine. After all the single machines of the spacecraft are demonstrated, first, according to the single machine list, the magnetic measurement data of the similar single machine products with the same technical state are searched to serve as the magnetic control index of each single machine. Some single machine indexes are represented by magnetic moment M , such as the single machine of the platform part. Some single machine magnetic control indexes are represented by magnetic field B , such as the solar wing, heating circuit, cable network and the like.

[0056] For example, the star computer of a spacecraft needs to be allocated a magnetic control index. The test results of the star computer that has been tested for magnetism in the past can be searched. If the two star computer models are consistent, the reliability of the historical test data is very high, and the historical data can be directly decomposed into the index.

[0057] In a possible implementation, the single machine magnetic control index is determined based on the single machine list, including: in the case that the single machine does not have historical data, the single machine is decomposed to determine at least two modules; the module historical data of the at least two modules is acquired, and the module historical data is accumulated to determine the single machine magnetic control index.

[0058] In practical application, if a single machine is a new research product and there is no similar single machine in the past, the single machine can be decomposed into multiple modules, such as main structural material, screw, shaped motor and the like, and then the historical data is searched. The magnetism of each module is accumulated to serve as the index. The accumulation method overestimates the magnetism of the single machine, but the estimated magnetism of the single machine in the demonstration stage is allowed.

[0059] Step 102: based on the demonstration of the whole machine magnetic control index and the demonstration of the whole machine magnetic requirement, adjusting the single machine magnetic control index determination scheme to determine the single machine magnetic control index.

[0060] In a possible implementation, the single machine magnetic control index is determined based on the demonstration of the whole machine magnetic control index, including: determining the magnetic moment data of each direction corresponding to each single machine; determining the total magnetic moment based on the magnetic moment data in each direction; determining the magnetic field data by the dipole method based on the total magnetic moment, and determining the demonstration of the whole machine magnetic control index based on the magnetic field data.

[0061] In practical application, in the demonstration stage, the magnetism of each single machine is obtained through the above work. Since the direction of the magnetism of each single machine is unknown, the following statistical algorithm is adopted:

[0062] For the magnetic moment M (m x , m y , m zThe single machine representing the index, assuming a total of m, the magnetic moment of the three directions of the single machine is estimated according to the maximum absolute value of the three-axis magnetic moment, that is, the magnetic moment of each single machine is estimated as:

[0063]

[0064] The total magnetic moment of the single machines is:

[0065]

[0066] Since the total index of the spacecraft magnetic control is generally in the form of a magnetic field, the magnetic moment index needs to be converted into a magnetic field index, and the conversion formula is the dipole method formula:

[0067]

[0068] Wherein, r is the position vector of the target calculation point relative to the center of all single machines.

[0069] For the single machine represented by the magnetic field B , assuming a total of n, the serial numbers are 2, 3, 4,..., n+1.

[0070] The statistical calculation formula of the magnetic control index of the whole machine is:

[0071]

[0072] At this time B t is the magnetic control index that the spacecraft can achieve in the demonstration stage, and the magnetic properties of each single machine in the above formula can be regarded as the magnetic control index of each single machine.

[0073] Step 103: Determine the scheme whole machine magnetic control index based on the scheme single machine magnetic control index, and adjust the scheme single machine magnetic control index based on the scheme magnetic control index and the scheme whole machine magnetic property requirement to determine the preliminary sample single machine magnetic control index.

[0074] In one possible implementation, determining the scheme whole machine magnetic control index based on the scheme single machine magnetic control index includes: determining the scheme total magnetic moment based on the scheme single machine magnetic control index; determining the scheme magnetic field data based on the conversion of the scheme total magnetic moment; and determining the scheme whole machine magnetic control index based on the scheme magnetic field data and the normal distribution.

[0075] In actual application, for spacecraft magnetic control work, the biggest difference between the scheme stage and the demonstration stage is that the single machine composition is basically determined in the scheme stage, and the position and direction of each single machine are roughly determined, so it is not necessary to estimate according to the maximum value. The magnetic control index of all single machines of the spacecraft is directly determined according to the historical test data M i or B i .

[0076] In the scheme phase, the following statistical algorithm can be taken:

[0077] For the single machine whose index is represented by magnetic moment M , assuming there are m machines, the total magnetic moment of these machines is:

[0078]

[0079] For the single machine whose index is represented by magnetic field B , assuming there are n machines, the serial numbers are 2, 3, 4,..., n+1. Since each single machine is basically independent of each other, the magnetic field generated by each single machine is also independent of each other. At this time, the magnetic field generated by the single machine basically conforms to the standard normal distribution, and the statistical calculation formula of the magnetic control index of the whole machine is:

[0080]

[0081] At this time B t is the magnetic control index that the spacecraft can achieve in the scheme phase. The magnetic properties of each single machine in the above formula can be taken as the magnetic control index of each single machine.

[0082] Step 104: Based on the initial sample single machine magnetic control index, a magnetic test is carried out to determine the test result, and based on the test result and the initial sample whole machine magnetic property requirement, the initial sample single machine magnetic control index is adjusted to determine the positive sample single machine magnetic control index.

[0083] In one possible implementation, based on the test result and the initial sample whole machine magnetic property requirement, the initial sample single machine magnetic control index is adjusted to determine the positive sample single machine magnetic control index, including: based on the test result, statistical simulation is carried out to determine the initial sample total magnetic moment; based on the initial sample total magnetic moment, the initial sample whole machine magnetic control index is determined, and based on the initial sample whole machine magnetic control index and the initial sample whole machine magnetic property requirement, the initial sample single machine magnetic control index is adjusted to determine the positive sample single machine magnetic control index.

[0084] In actual application, in the initial sample stage, the positions and directions of each single machine of the spacecraft are basically determined. Each single machine will develop an initial sample product, at this time, the real magnetic properties of all single machines can be obtained through a magnetic test M i or B i . At this time, for the single machine whose index is represented by magnetic moment M , assuming there are m machines, the total magnetic moment of these machines is M t The statistical simulation can be carried out by an accurate simulation method.

[0085] For the single machine whose index is represented by magnetic field B , assuming there are n machines, the serial numbers are 2, 3, 4,..., n+1.

[0086] The whole device magnetic control index statistical calculation formula is consistent with the scheme stage, and is also:

[0087]

[0088] At this time B t That is, the spacecraft can reach the magnetic control index in the prototype stage, and the magnetic properties of each single machine in the above formula can be used as the magnetic control index of each single machine.

[0089] In one possible implementation, based on the prototype whole device magnetic control index and the prototype whole machine magnetic property requirement, the prototype single machine magnetic control index is adjusted to determine the positive sample single machine magnetic control index, including: in the case that the prototype whole device magnetic control index does not meet the prototype whole machine magnetic property requirement, reducing the prototype single machine magnetic control index to determine the target single machine; based on the target single machine, a magnetic test is performed to determine the positive sample single machine magnetic control index.

[0090] In actual application, after the prototype stage of development, part of the single machine exceeds the index requirement, and then leads to the whole device index exceeding the standard, at this time, the single machine manufacturer can be proposed to reduce the single machine magnetic property by replacing low magnetic material, cable layout design, magnetic compensation, magnetic shielding, low magnetic leakage design, etc.

[0091] Step 105: determining the positive sample whole device magnetic control index based on the positive sample single machine magnetic control index.

[0092] In actual application, the single machine after modification must be tested again to obtain the real magnetic property of all single machines M i Or B i Finally, the positive sample single machine product produced is tested one by one, and the integration assembly work is carried out after meeting the index requirement.

[0093] For the single machine whose index is represented by magnetic moment M The total magnetic moment of the single machine cannot be obtained by statistics, but should be obtained by actual test M t .

[0094] For the single machine whose index is represented by magnetic field B There are n in total, and the serial numbers are 2, 3, 4,..., n+1.

[0095] The whole device magnetic control index statistical calculation formula is consistent with the scheme stage, and is also:

[0096]

[0097] At this time B tThat is the spacecraft in the final reaches of the magnetic control index, is the final result of the magnetic control work.

[0098] In an embodiment, in a certain satellite actual magnetic control process, the magnetic control task index is 0.5nT, the satellite carries out the magnetic control work according to the embodiment of the present specification, and finally controls the magnetic control to 0.33nT, which is better than the index requirement.

[0099] It should be noted that if the spacecraft magnetic control method is not a full-process magnetic control, but directly from the positive sample stage, once the single machine product produced by it exceeds the index, if the rectification is carried out, the rectification cost is large and the progress is delayed, if the rectification is not carried out, the spacecraft factory index can only be compromised, which affects the spacecraft task quality or causes the spacecraft life to decrease.

[0100] If the index decomposition algorithm is too strict in each stage, such as all according to the algorithm of the positive sample stage, it will lead to the work cannot be carried out because there is no real data, and it may also lead to the expected index value is too low, which brings great difficulty to the subsequent work, and easily leads to the index out of control. If the index decomposition algorithm is too loose, such as all according to the algorithm of the demonstration stage, it will lead to the index estimation value is too high, deviating from the actual situation.

[0101] The embodiment of the present specification gives a full-process phased magnetic control work guidance scheme, by executing different index decomposition algorithms, the spacecraft manufacturer can be guided to understand the magnetic control index in advance, and the expected index value can be accurately given. The actual research and development experience of multiple space magnetic field measurement spacecrafts shows that the method according to the present invention can reach and be better than the task magnetic control index.

[0102] In summary, the embodiment of the present specification provides a spacecraft full-process magnetic control method and device, the method comprises: determining the demonstration single machine magnetic control index based on the single machine list, and determining the demonstration whole device magnetic control index based on the demonstration single machine magnetic control index; adjusting the single machine magnetic control index to determine the scheme single machine magnetic control index based on the scheme single machine magnetic control index and the scheme whole device magnetic control index; determining the scheme whole device magnetic control index based on the scheme single machine magnetic control index, and adjusting the scheme single machine magnetic control index to determine the preliminary sample single machine magnetic control index based on the scheme whole device magnetic control index and the scheme whole device magnetic control index; performing magnetic test based on the preliminary sample single machine magnetic control index, determining the test result, and adjusting the preliminary sample single machine magnetic control index to determine the positive sample single machine magnetic control index based on the test result and the preliminary sample whole device magnetic control index; determining the positive sample whole device magnetic control index based on the positive sample single machine magnetic control index, by executing different index decomposition algorithms, the spacecraft manufacturer can be guided to understand the magnetic control index in advance, and the expected index value can be accurately given.

[0103] Corresponding to the above method embodiment, the present specification also provides a spacecraft full-process magnetic control device embodiment, Figure 2A structural diagram of a spacecraft full-process magnetic control device is shown. As shown in the figure, the device includes: Figure 2

[0104] A demonstration module 201 is configured to obtain a single-machine list, determine a demonstration single-machine magnetic control index based on the single-machine list, and determine a demonstration whole-machine magnetic control index based on the demonstration single-machine magnetic control index;

[0105] A scheme module 202 is configured to determine a scheme single-machine magnetic control index based on the demonstration whole-machine magnetic control index and a demonstration whole-machine magnetic requirement, and adjust the single-machine magnetic control index based on the scheme single-machine magnetic control index;

[0106] A preliminary sample module 203 is configured to determine a scheme whole-machine magnetic control index based on the scheme single-machine magnetic control index, and adjust the scheme single-machine magnetic control index based on the scheme magnetic control index and a scheme whole-machine magnetic requirement to determine a preliminary sample single-machine magnetic control index;

[0107] A positive sample module 204 is configured to determine a test result based on a magnetic test based on the preliminary sample single-machine magnetic control index, and adjust the preliminary sample single-machine magnetic control index based on the test result and a preliminary sample whole-machine magnetic requirement to determine a positive sample single-machine magnetic control index;

[0108] A result module 205 is configured to determine a positive sample whole-machine magnetic control index based on the positive sample single-machine magnetic control index.

[0109] In a possible implementation, the demonstration single-machine magnetic control index is determined based on the single-machine list, including:

[0110] At least two single-machines are determined based on the single-machine list, and historical data of the single-machines is obtained;

[0111] The demonstration single-machine magnetic control index is determined based on the historical data.

[0112] In a possible implementation, the demonstration single-machine magnetic control index is determined based on the single-machine list, including:

[0113] In a case where the single-machine does not have historical data, the single-machine is decomposed to determine at least two modules;

[0114] Module historical data of the at least two modules is obtained, and the module historical data is accumulated to determine the demonstration single-machine magnetic control index.

[0115] In a possible implementation, the demonstration whole-machine magnetic control index is determined based on the demonstration single-machine magnetic control index, including:

[0116] Magnetic moment data of each direction corresponding to each single-machine is determined;

[0117] A total magnetic moment is determined based on the magnetic moment data of each direction;

[0118] ​The magnetic field data is determined based on the total magnetic moment by the dipole method, and the demonstration integrator magnetic control index is determined based on the magnetic field data.

[0119] In a possible implementation, the scheme integrator magnetic control index is determined based on the scheme single-machine magnetic control index, comprising:

[0120] The scheme total magnetic moment is determined based on the scheme single-machine magnetic control index;

[0121] The scheme magnetic field data is determined based on the conversion of the scheme total magnetic moment;

[0122] The scheme integrator magnetic control index is determined based on the scheme magnetic field data and the normal distribution.

[0123] In a possible implementation, the positive sample single-machine magnetic control index is determined based on the test result and the initial sample integrator magnetic control index, comprising:

[0124] The initial sample total magnetic moment is determined based on the statistical simulation of the test result;

[0125] The initial sample integrator magnetic control index is determined based on the initial sample total magnetic moment, and the positive sample single-machine magnetic control index is determined based on the adjustment of the initial sample single-machine magnetic control index and the initial sample integrator magnetic control index and the initial sample integrator magnetic control index and the initial sample integrator magnetic control index.

[0126] In a possible implementation, the positive sample single-machine magnetic control index is determined based on the adjustment of the initial sample single-machine magnetic control index and the initial sample integrator magnetic control index, comprising:

[0127] In the case that the initial sample integrator magnetic control index does not meet the initial sample integrator magnetic control index, the initial sample single-machine magnetic control index is reduced to determine the target single machine;

[0128] The positive sample single-machine magnetic control index is determined based on the magnetic test of the target single machine.

[0129] The spacecraft full-process magnetic control method and device are provided, the device comprises: determining the demonstration single-machine magnetic control index based on the single-machine list, and determining the demonstration integrator magnetic control index based on the demonstration single-machine magnetic control index; adjusting the single-machine magnetic control index to determine the scheme single-machine magnetic control index based on the demonstration integrator magnetic control index and the demonstration integrator magnetic control index; determining the scheme integrator magnetic control index based on the scheme single-machine magnetic control index, and adjusting the scheme single-machine magnetic control index to determine the initial sample single-machine magnetic control index based on the scheme magnetic control index and the scheme integrator magnetic control index; determining the test result based on the magnetic test of the initial sample single-machine magnetic control index, and adjusting the initial sample single-machine magnetic control index to determine the positive sample single-machine magnetic control index based on the test result and the initial sample integrator magnetic control index; determining the positive sample integrator magnetic control index based on the positive sample single-machine magnetic control index, and the different index decomposition algorithm is executed to guide the spacecraft development party to understand the magnetic control index in advance and accurately give the expected index value.

[0130] The above is a schematic scheme of the spacecraft full-process magnetic control device of the embodiment. It should be noted that the technical scheme of the spacecraft full-process magnetic control device and the technical scheme of the spacecraft full-process magnetic control method described above belong to the same concept, and the technical scheme of the spacecraft full-process magnetic control device is not described in detail. Details can be seen from the description of the technical scheme of the spacecraft full-process magnetic control method.

[0131] Figure 3 A structural block diagram of a computing device 300 according to one embodiment of the present specification is shown. The components of the computing device 300 include, but are not limited to, a memory 310 and a processor 320. The processor 320 is connected to the memory 310 through a bus 330, and a database 350 is used to save data.

[0132] The computing device 300 also includes an access device 340, which enables the computing device 300 to communicate via one or more networks 360. Examples of these networks include a public switched telephone network (PSTN), a local area network (LAN), a wide area network (WAN), a personal area network (PAN), or a combination of communication networks such as the Internet. The access device 340 can include one or more of any type of network interface (e.g., a network interface card (NIC)), wired or wireless, such as an IEEE 802.11 wireless local area network (WLAN) wireless interface, a Worldwide Interoperability for Microwave Access (Wi-MAX) interface, an Ethernet interface, a Universal Serial Bus (USB) interface, a cellular network interface, a Bluetooth interface, a near field communication (NFC).

[0133] In one embodiment of the present specification, the above-mentioned components of the computing device 300 and other components not shown in the Figure 3 may be connected to each other, for example, through a bus. It should be understood that Figure 3 The structural block diagram of the computing device shown is only for the purpose of example, and is not a limitation on the scope of the present specification. Those skilled in the art can add or replace other components as needed.

[0134] The computing device 300 can be any type of stationary or mobile computing device, including a mobile computer or mobile computing device (e.g., a tablet computer, a personal digital assistant, a laptop computer, a notebook computer, a netbook, etc.), a mobile phone (e.g., a smartphone), a wearable computing device (e.g., a smart watch, smart glasses, etc.), or other type of mobile device, or a stationary computing device such as a desktop computer or a personal computer (PC). The computing device 300 can also be a mobile or stationary server.

[0135] The processor 320 is configured to execute computer-executable instructions to implement the steps of the spacecraft full-process magnetic control method described above. The above is a schematic solution of a computing device according to an embodiment of the present disclosure. It should be noted that the technical solution of the computing device and the technical solution of the spacecraft full-process magnetic control method described above belong to the same concept, and the details of the technical solution of the computing device that are not described in detail can be referred to the description of the technical solution of the spacecraft full-process magnetic control method.

[0136] An embodiment of the present disclosure further provides a computer-readable storage medium storing computer-executable instructions, which, when executed by a processor, implement the steps of the spacecraft full-process magnetic control method described above.

[0137] The above is a schematic solution of a computer-readable storage medium according to an embodiment of the present disclosure. It should be noted that the technical solution of the storage medium and the technical solution of the spacecraft full-process magnetic control method described above belong to the same concept, and the details of the technical solution of the storage medium that are not described in detail can be referred to the description of the technical solution of the spacecraft full-process magnetic control method.

[0138] An embodiment of the present disclosure further provides a computer program, which, when executed in a computer, causes the computer to perform the steps of the spacecraft full-process magnetic control method described above.

[0139] The above is a schematic solution of a computer program according to an embodiment of the present disclosure. It should be noted that the technical solution of the computer program and the technical solution of the spacecraft full-process magnetic control method described above belong to the same concept, and the details of the technical solution of the computer program that are not described in detail can be referred to the description of the technical solution of the spacecraft full-process magnetic control method.

[0140] The above-described embodiments of the application have several aspects, no single one of which is solely responsible for the application's desirable attributes. Without limiting the scope of the application as expressed by the claims which follow, some further embodiments make these aspects even more useful. Other embodiments can result in less desirable attributes.

[0141] The computer readable medium can include any entity or apparatus capable of carrying the computer program code, recording medium, U disk, mobile hard disk, magnetic disk, optical disk, computer memory, Read-Only Memory (ROM), Random Access Memory (RAM), electrical carrier signal, telecommunication signal, software distribution medium, etc. It should be noted that the computer readable medium can include appropriate contents according to the requirements of legislation and patent practice in the jurisdiction, for example, in some jurisdictions, according to legislation and patent practice, the computer readable medium does not include electrical carrier signals and telecommunication signals.

[0142] It should be noted that for the foregoing method embodiments, the acts described can be performed in a different order than that described, and that various interlocking and / or parallel configurations are also possible according to the certain embodiments of the present specification. Furthermore, certain of the acts can be left out of the present specification, or can be performed concurrently, or can be performed at different times, than is described in the present specification. It is also possible for one or more of the acts to be performed before, after, and / or concurrently with other acts in a different order and / or concurrently with other acts according to the certain embodiments of the present specification.

[0143] In the above embodiments, the description of each embodiment is focused on different aspects, and the parts not described in detail in a certain embodiment can be referred to the relevant description of other embodiments.

[0144] The above disclosed preferred embodiments of the present specification are only used to help explain the present specification. Alternative embodiments do not describe all the details and do not limit the application to the specific embodiments described. Obviously, according to the content of the embodiments of the present specification, many modifications and changes can be made. The present specification selects and describes these embodiments in order to better explain the principles and practical applications of the embodiments of the present specification, so that those skilled in the art can well understand and use the present specification. The present specification is limited by the claims and their full scope and equivalents.

Claims

1. A method for full-process magnetic control of a spacecraft, characterized in that, include: Obtain a list of individual units, determine the magnetic control indicators of each individual unit based on the list, and determine the magnetic control indicators of the entire device based on the magnetic control indicators of each individual unit. Based on the demonstrated overall magnetic control index and the demonstrated overall magnetic requirements, the single-unit magnetic control index is adjusted to determine the single-unit magnetic control index of the scheme. Based on the single-unit magnetic control index of the above scheme, the magnetic control index of the whole device of the scheme is determined, and the single-unit magnetic control index of the scheme is adjusted based on the magnetic control index of the above scheme and the magnetic requirements of the whole device of the scheme to determine the initial single-unit magnetic control index of the prototype. Magnetic tests were conducted based on the initial sample's single-unit magnetic control parameters to determine the test results. Based on the test results and the overall magnetic requirements of the initial sample, the initial sample's single-unit magnetic control parameters were adjusted to determine the final sample's single-unit magnetic control parameters. The magnetic control index of the prototype assembly is determined based on the magnetic control index of the prototype unit.

2. The method according to claim 1, characterized in that, The process of determining and validating the individual magnetic control indicators based on the individual unit list includes: Based on the list of individual machines, at least two individual machines are identified, and the historical data of the individual machines is obtained. Based on the historical data, the single-machine magnetic control index was determined and demonstrated.

3. The method according to claim 2, characterized in that, The process of determining and validating the individual magnetic control indicators based on the individual unit list includes: If no historical data exists on the single machine, the single machine is decomposed to identify at least two modules; Obtain the module historical data of at least two modules, and accumulate the module historical data to determine and verify the single-machine magnetic control index.

4. The method according to claim 1, characterized in that, The process of determining the overall magnetic control index of the device based on the single-unit magnetic control index includes: Determine the magnetic moment data for each individual unit in each direction; The total magnetic moment is determined based on the magnetic moment data in each direction; The magnetic field data is determined using the dipole method based on the total magnetic moment, and the magnetic control index of the entire device is determined and verified based on the magnetic field data.

5. The method according to claim 1, characterized in that, The process of determining the overall magnetic control index of the scheme based on the single-unit magnetic control index includes: The total magnetic moment of the scheme is determined based on the single-machine magnetic control index of the aforementioned scheme. The magnetic field data of the scheme are determined by converting the total magnetic moment of the scheme. The magnetic control parameters of the entire device are determined based on the magnetic field data and normal distribution of the proposed scheme.

6. The method according to claim 1, characterized in that, The process of adjusting the magnetic control parameters of the prototype unit based on the test results and the magnetic requirements of the initial prototype unit to determine the magnetic control parameters of the final prototype unit includes: Based on the experimental results, statistical simulation was performed to determine the total magnetic moment of the initial sample. Based on the total magnetic moment of the initial sample, the magnetic control index of the initial sample assembly is determined. Based on the magnetic control index of the initial sample assembly and the magnetic requirements of the initial sample assembly, the magnetic control index of the initial sample unit is adjusted to determine the magnetic control index of the final sample unit.

7. The method according to claim 6, characterized in that, The step of adjusting the individual magnetic control parameters of the initial sample unit to determine the individual magnetic control parameters of the final sample unit based on the initial sample unit's magnetic control parameters and the initial sample unit's magnetic requirements includes: If the magnetic control index of the initial sample does not meet the magnetic requirements of the initial sample unit, reduce the magnetic control index of the initial sample unit to determine the target unit. Magnetic tests were conducted on the target unit to determine the magnetic control parameters of the prototype unit.

8. A spacecraft full-process magnetic control device, characterized in that, include: The demonstration module is configured to obtain a list of individual machines, determine the magnetic control index of the individual machines to be demonstrated based on the list of individual machines, and determine the magnetic control index of the entire device to be demonstrated based on the magnetic control index of the individual machines to be demonstrated. The solution module is configured to adjust the single-machine magnetic control index based on the magnetic control index of the entire device and the magnetic requirements of the entire device to determine the single-machine magnetic control index of the solution. The prototype module is configured to determine the overall magnetic control index of the scheme based on the single-unit magnetic control index of the scheme, and adjust the single-unit magnetic control index of the scheme based on the magnetic control index of the scheme and the magnetic requirements of the overall scheme to determine the single-unit magnetic control index of the prototype. The prototype module is configured to conduct magnetic tests based on the magnetic control index of the prototype unit, determine the test results, and adjust the magnetic control index of the prototype unit based on the test results and the magnetic requirements of the prototype unit to determine the magnetic control index of the prototype unit. The results module is configured to determine the magnetic control index of the sample assembler based on the magnetic control index of the sample unit.

9. A computing device, characterized in that, include: Memory and processor; The memory is used to store computer-executable instructions, and the processor is used to execute the computer-executable instructions, which, when executed by the processor, implement the steps of the spacecraft full-process magnetic control method according to any one of claims 1 to 7.

10. A computer-readable storage medium storing computer-executable instructions that, when executed by a processor, implement the steps of the spacecraft full-process magnetic control method according to any one of claims 1 to 7.

Images