CN116087638A - Electromagnetic compatibility prediction method for mass-production small satellite and related components - Google Patents
Electromagnetic compatibility prediction method for mass-production small satellite and related components Download PDFInfo
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- CN116087638A CN116087638A CN202211310140.XA CN202211310140A CN116087638A CN 116087638 A CN116087638 A CN 116087638A CN 202211310140 A CN202211310140 A CN 202211310140A CN 116087638 A CN116087638 A CN 116087638A
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- G01R—MEASURING ELECTRIC VARIABLES; MEASURING MAGNETIC VARIABLES
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- G01R31/001—Measuring interference from external sources to, or emission from, the device under test, e.g. EMC, EMI, EMP or ESD testing
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Abstract
The invention discloses an electromagnetic compatibility prediction method and related components of a mass production small satellite, which relate to the field of satellite electromagnetic compatibility and comprise the steps of firstly determining the receiving frequency of a receiver, the working frequency of other equipment possibly causing interference to the receiver and the frequency of potential interference caused by other equipment, then judging whether the receiver is interfered, positioning an interference source, interfered equipment and an interference path when the receiver is interfered, and carrying out electromagnetic compatibility prediction on the satellite, namely determining whether the frequency and/or bandwidth of the interference source need to be adjusted or not, so that the electromagnetic compatibility prediction can be carried out in the earlier stage of satellite design, weak links of the satellite design can be found in advance to provide basis for the satellite design, the waste of cost and resources is avoided, and the mass production of the satellite is avoided.
Description
Technical Field
The invention relates to the field of satellite electromagnetic compatibility, in particular to an electromagnetic compatibility prediction method and related components of a mass-production small satellite.
Background
Satellites are a system of various kinds of electronic and electrical equipment which are densely distributed, powerful and technically complex, and which not only have a wide frequency coverage range, but also have various high-power equipment and high-sensitivity equipment, such as receivers and transmitters. The satellite equipment is arranged in a relatively narrow area under the limitation of factors such as the launch weight of a carrier rocket, the layout of various antennas and equipment is very dense, and the mutual interference phenomenon is very easy to occur. Therefore, the satellite needs to be subjected to electromagnetic compatibility prediction in advance so as to ensure that the satellite can withstand various interferences encountered in the process of development and emission until in-orbit operation, and in addition, the in-orbit flight task can be successfully completed according to a preset plan.
Disclosure of Invention
The invention aims to provide an electromagnetic compatibility prediction method and related components for mass production of small satellites, which can be used for carrying out electromagnetic compatibility prediction in the early stage of satellite design, and finding out weak links of the satellite design in advance to provide basis for the satellite design, so that the cost and resource waste are avoided, and the mass production of the satellites is prevented from being influenced.
In order to solve the technical problems, the invention provides an electromagnetic compatibility prediction method for mass production of small satellites, which comprises the following steps:
determining a reception frequency of a receiver on the satellite;
determining the working frequencies of other devices except the receiver on the satellite, and determining the frequency of potential interference brought by the other devices according to the working frequencies of the other devices;
when the working frequency or the frequency of the potential interference overlaps with the receiving frequency, using a device corresponding to the working frequency or a device corresponding to the frequency of the potential interference in the other devices as an interference source, using a receiver corresponding to the receiving frequency as an interfered object, determining an interference path between the interference source and the interfered object, and determining that the frequency and/or bandwidth of the interference source need to be adjusted.
Preferably, the method further comprises:
determining the measurement and control radiation emission field intensity between the satellite and the target equipment according to the distance between the measurement and control antenna of the satellite and the target equipment in the carrying and/or emission field, the gain of the target antenna and the emission power of a transmitter connected with the rear end of the target antenna;
when the measurement and control radiation emission field intensity does not meet the field intensity requirement, the design of the measurement and control antenna and/or a transmitter connected with the rear end of the measurement and control antenna is judged to be required to be adjusted.
Preferably, the method further comprises:
establishing a single-antenna simulation model for each antenna in the satellite, and acquiring actual performance parameters of each antenna in the satellite when working in a single-antenna state;
and when the actual performance parameter does not meet the preset standard single antenna performance parameter, determining that the antenna design needs to be adjusted.
Preferably, the method further comprises:
establishing a satellite model which accords with the antenna layout of the satellite in an actual satellite loading state, and determining the actual isolation degree and the actual radiation characteristic parameters of each antenna in the satellite in the actual satellite loading state;
when the actual isolation degree of the antenna does not meet the preset standard isolation degree and/or the actual radiation characteristic parameter does not meet the preset standard, the antenna design of the satellite and/or the structural layout of the satellite are/is judged to need to be adjusted.
Preferably, after establishing the satellite model conforming to the antenna layout of the satellite in the actual satellite loading state, the method further comprises:
determining isolation and radiation characteristic parameters of each antenna under the whole satellite electromagnetic boundary condition;
and when the isolation degree of the antenna does not meet the preset standard isolation degree and/or the radiation characteristic parameter does not meet the preset standard, judging that the structural layout of the satellite and/or the antenna design of the satellite need to be adjusted.
Preferably, after determining the reception frequency of the receiver on the satellite, the method further comprises:
determining a received power of the receiver, a transmission frequency and a transmission power of a transmitter in the other device;
and judging whether the receiving frequency, the receiving power, the transmitting frequency and the transmitting power all meet radio management regulations.
Preferably, the method further comprises:
establishing a satellite model of the satellite in the actual satellite loading state, and acquiring a receiving signal of a receiving antenna in the satellite;
establishing a model of the satellite with the star structure removed, and acquiring a direct signal of the receiving antenna;
determining a multipath signal obtained by subtracting the direct signal from the received signal, and calculating amplitude attenuation and time delay of the multipath signal relative to the direct signal;
and determining the influence of multipath effects brought by the satellite body structure of the satellite on the receiver according to the amplitude attenuation and the time delay.
The invention also provides an electromagnetic compatibility prediction system of the mass production small satellite, which comprises the following steps:
a first determining unit for determining a reception frequency of a receiver on a satellite;
a second determining unit, configured to determine an operating frequency of other devices on the satellite except the receiver, and determine a frequency of potential interference caused by the other devices according to the operating frequency of the other devices;
and the electromagnetic compatibility analysis unit is used for taking the equipment corresponding to the working frequency or the equipment corresponding to the potential interference in the other equipment as an interference source, taking the receiver corresponding to the receiving frequency as an interfered object, determining an interference path between the interference source and the interfered object and determining that the frequency and/or bandwidth of the interference source need to be adjusted when the working frequency or the frequency of the potential interference overlaps with the receiving frequency.
The invention also provides an electromagnetic compatibility prediction device of the mass production small satellite, which comprises the following steps:
a memory for storing a computer program;
and the processor is used for realizing the step of the electromagnetic compatibility prediction method of the mass production small satellite when executing the computer program.
The invention also provides a computer readable storage medium, wherein the computer readable storage medium stores a computer program, and the computer program realizes the steps of the electromagnetic compatibility prediction method of the mass production small satellite when being executed by a processor.
In summary, the invention discloses an electromagnetic compatibility prediction method and related components for mass production of small satellites, which comprises the steps of firstly determining the receiving frequency of a receiver, the working frequency of other equipment possibly causing interference to the receiver and the frequency of potential interference caused by other equipment, then judging whether the receiver is interfered, positioning an interference source, interfered equipment and an interference path when the receiver is interfered, and performing electromagnetic compatibility prediction on the satellite, namely determining whether the frequency and/or bandwidth of the interference source need to be adjusted, so that the electromagnetic compatibility prediction can be performed in the early stage of satellite design, the weak links of the satellite design can be found out in advance to provide basis for the satellite design, the waste of cost and resources is avoided, and the influence on the mass production of the satellite is avoided.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings required in the prior art and the embodiments will be briefly described below, and it is apparent that the drawings in the following description are only some embodiments of the present invention, and other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a flow chart of a method for predicting electromagnetic compatibility of a mass-produced small satellite;
fig. 2 is a schematic structural diagram of an electromagnetic compatibility prediction system for mass-production satellites according to the present invention;
fig. 3 is a schematic structural diagram of an electromagnetic compatibility predicting device for mass-producing satellites according to the present invention.
Detailed Description
The core of the invention is to provide an electromagnetic compatibility prediction method and related components for mass production of small satellites, which can predict the electromagnetic compatibility in the early stage of satellite design, find out the weak links of the satellite design in advance, provide basis for the satellite design, avoid the waste of cost and resources and avoid affecting the mass production of satellites.
For the purpose of making the objects, technical solutions and advantages of the embodiments of the present invention more apparent, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention, and it is apparent that the described embodiments are some embodiments of the present invention, but not all embodiments of the present invention. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
Referring to fig. 1, fig. 1 is a flowchart of an electromagnetic compatibility prediction method for a mass-produced small satellite according to the present invention, where the electromagnetic compatibility prediction method for a mass-produced small satellite includes:
s1: determining a reception frequency of a receiver on the satellite;
s2: determining the working frequencies of other devices except the receiver on the satellite, and determining the frequency of potential interference brought by the other devices according to the working frequencies of the other devices;
s3: when the working frequency or the potential interference frequency overlaps with the receiving frequency, the device corresponding to the working frequency or the device corresponding to the potential interference frequency in other devices is used as an interference source, the receiver corresponding to the receiving frequency is used as an interfered object, an interference path between the interference source and the interfered object is determined, and the frequency and/or bandwidth of the interference source are/is determined to be adjusted.
Considering that a receiver on a satellite is easily interfered by other devices on the satellite, in order to avoid that the receiver on the satellite is only discovered to be interfered by electromagnetic interference of other devices except the receiver on the satellite in the middle and later stages of satellite development, the problem that the receiver on the satellite can only be solved by adopting a high-cost solution is solved, and in the method, the electromagnetic interference analysis is firstly carried out on the receiver in the early stage of satellite design. Specifically, the receiving frequency of the receiver is first determined, then the operating frequency of other devices on the satellite outside the receiver is determined, and when the operating frequency overlaps with the receiving frequency of the receiver, the receiver is proved to be subjected to electromagnetic interference. And, the frequencies of other devices overlap with each other to generate additional potential interference, so the frequency of the potential interference brought by the other devices is further determined in the application.
The present application is not particularly limited as to how to determine whether the receiving frequency band overlaps the operating frequency band, and for example, fundamental wave interference, harmonic interference, subharmonic interference, local oscillation interference, and the like of other devices on the satellite except the receiver may be calculated and whether the receiving frequency band overlaps the operating frequency band may be determined respectively. Or determining whether there is interference affecting the transmitter by calculating an interference margin, proving that there is interference affecting the transmitter when the interference margin is positive, proving that there is no interference affecting the transmitter when the interference margin is negative, and expressing an equation of the interference margin as:
where PT (fE) is the transmit power of the transmitter, GT (fE, t, d, p) is the antenna gain of the transmitter, L (fE, t, d, p) is the propagation loss of fE between the transmitter and the receiver, GR (fE, t, d, p) is the antenna gain of the receiver antenna in the transmitter direction, CF (BT, BR, Δf) is the influencing factor of the transmitter and receiver frequency spacing Δf in the bandwidth BT, BR.
In the application, after the receiver is judged to be interfered, an interference source generating interference, an interfered object generating interference and an interference path between the interference source and the interfered device are further determined to further provide basis for the later modification design of the satellite. Specifically, the device for generating overlapping between the working frequency and the receiving frequency is used as an interference source, the receiver corresponding to the receiving frequency is used as an interfered object, and how to determine the interference path is not particularly limited in the application, and the selection can be performed according to actual situations.
In addition to interference from the receiver caused by signals directly transmitted by devices other than the receiver on the satellite, additional potential interference is generated after the frequencies of the signals transmitted by the devices other than the receiver on the satellite overlap, and the potential interference also causes interference to the receiver. Thus, in this embodiment, the potential interference caused by each device is also determined according to the frequencies of all the devices on the satellite, then the frequency of the potential interference is determined, and when the frequency of the potential interference and the receiving frequency overlap, the interference caused to the receiver is determined, so that the frequency and/or bandwidth of each device are determined to be adjusted.
Of particular importance in potential interference is intermodulation products generated by the signals of the device due to nonlinearities, and the application is not particularly limited as to how intermodulation products are specifically determined, for example:
where fm is the frequency of intermodulation products, bm is the bandwidth of intermodulation products, fsN is the frequency of the nth transmitter on the satellite, and BsN is the bandwidth of the nth transmitter on the satellite. In addition, the intermodulation products of each order can be obtained by adjusting the number of N, and whether the secondary radiation sources of the intermodulation products of each order have influence on the receiver and the receiving antenna again is determined based on the distribution of the secondary radiation sources of the intermodulation products of each order in space.
In addition, considering that the receiver has certain anti-interference capability, judging whether the signal intensity of intermodulation products is within a preset range or not after the frequency band of intermodulation products overlaps with the receiving frequency band, namely judging whether the influence of intermodulation products on the receiver is within an acceptable range or not, and judging that the frequency and/or bandwidth of each device need to be adjusted only when the signal intensity of intermodulation products is not within the preset range; when the signal strength of the intermodulation products is within the preset range, the receiver can resist the interference caused by the intermodulation products, so that the frequency and/or bandwidth of each device do not need to be adjusted, and the pressure for adjusting the anti-interference capacity of the satellite in the actual satellite design process is relieved on the premise of not affecting the normal operation of the satellite.
In the application, the analysis on whether the receiver in the satellite receives electromagnetic interference or not is completed through the two steps, namely, the analysis on the system compatibility of the satellite is performed.
In summary, the invention discloses an electromagnetic compatibility prediction method and related components for mass production of small satellites, which relate to the field of satellite electromagnetic compatibility, and include that firstly, the receiving frequency of a receiver, the working frequency of other equipment possibly causing interference to the receiver and the frequency of potential interference caused by other equipment are determined, then whether the receiver is interfered or not is judged, and an interference source, interfered equipment and an interference path are positioned when the receiver is interfered, and electromagnetic compatibility prediction is carried out on the satellite, namely whether the frequency and/or bandwidth of the interference source need to be adjusted or not is determined, so that the electromagnetic compatibility prediction can be carried out in the earlier stage of satellite design, the weak links of the satellite design can be found out in advance to provide basis for the satellite design, the waste of cost and resources is avoided, and the mass production of the satellite is prevented from being influenced.
Based on the above embodiments:
as a preferred embodiment, further comprising:
determining the measurement and control radiation emission field intensity between the satellite and the target equipment according to the distance between the measurement and control antenna of the satellite and the target equipment in the carrying and/or emission field, the gain of the target antenna and the emission power of a transmitter connected with the rear end of the target antenna;
when the field intensity of the measurement and control radiation emission does not meet the field intensity requirement, the related design of the measurement and control antenna and/or a transmitter connected with the rear end of the measurement and control antenna is judged to be required to be adjusted.
In the present embodiment, it is considered that the satellite is required to be in-orbit after the actual satellite is in-orbitTo send signals to target devices in the carrier or transmitting fields, it is therefore necessary to analyze and predict the satellite field strength between the satellite and the target devices in addition to the devices and antennas within the satellite. Specifically, the measurement and control radiation emission field intensity between the target antenna and the target device is determined according to the distance between the target antenna and the target device of the satellite, the gain of the target antenna and the emission power of the target antenna, for example, by
Wherein E is measurement and control radiation emission field intensity, PT is emission power of a target antenna, GT is gain of the target antenna, and R is distance between the target antenna and target equipment. When the measurement and control radiation emission field intensity does not meet the field intensity requirement, the target equipment can not normally receive the signal emitted by the target antenna, so that the gain, the emission power and other related parameters of the target antenna need to be adjusted. The field strength requirements in the present application include the field strength requirements of the carrier field and the field strength requirements of the emission field, and specific values of the field strength requirements are not particularly limited in the present application. Furthermore, the relevant design in the present application is a parameter in the transmitter that affects the field strength of the emitted measurement and control radiation.
As a preferred embodiment, further comprising:
establishing a single-antenna simulation model for each antenna in the satellite, and acquiring actual performance parameters of each antenna in the satellite when working in a single-antenna state;
and when the actual performance parameter does not meet the preset standard single antenna performance parameter, determining that the antenna design needs to be adjusted.
In this embodiment, considering that when the antenna is predicted and analyzed, whether each antenna meets the requirement in the actual satellite loading state or not needs to be considered, and whether the antenna can meet the requirement in the single antenna state or not is also required to be judged under the condition of not being interfered by other devices and antennas, therefore, firstly, a single antenna simulation model is built for each antenna in the satellite, then, the actual performance parameters of each antenna in the satellite when working in the single antenna state can be obtained, and when the actual performance parameters do not meet the preset standard single antenna performance parameters, the antenna design needs to be adjusted is judged, so that the comprehensiveness and accuracy of the comprehensive prediction and analysis on the satellite are further improved.
It should be noted that, the preset standard single antenna performance parameter is not limited in detail, and can be adjusted according to actual situations.
As a preferred embodiment, further comprising:
establishing a satellite model which accords with the antenna layout of the satellite in an actual satellite loading state, and determining the actual isolation degree and the actual radiation characteristic parameters of each antenna in the satellite in the actual satellite loading state;
when the actual isolation degree of the antenna does not meet the preset standard isolation degree and/or the actual radiation characteristic parameter does not meet the preset standard, the antenna design of the satellite and/or the structural layout of the satellite are/is judged to need to be adjusted.
In addition to determining whether the receiver on the satellite is subject to electromagnetic interference, it is also necessary to determine whether each antenna on the satellite is functioning properly. Because all kinds of antennas on the satellite are installed in a relatively narrow area, coupling is easy to occur among the antennas, and therefore, in the application, the performance parameters of the antennas actually installed on the satellite are predicted and analyzed.
Specifically, a satellite model which accords with the antenna layout of the satellite in an actual satellite loading state is firstly established, then the actual isolation degree and the actual radiation characteristic parameters of each antenna on the satellite in the actual satellite loading state can be determined, and when the actual isolation degree does not meet any one of the preset standard isolation degree or the actual radiation characteristic parameters do not meet the preset standard, the antenna is judged to be unable to work normally in the satellite, so that the structural layout of the satellite or the upward antenna design needs to be adjusted.
Specifically, for the case that the actual isolation of the current antenna does not satisfy the preset standard isolation, it is necessary to increase the physical distance between the current antenna and other antennas as much as possible. For the case that the physical distance cannot be increased, an isolation device needs to be added between the current antenna and other antennas to improve the actual isolation of the current antenna.
Specifically, for the case that the actual radiation characteristic parameter of the current antenna does not meet the preset standard, a specific reason needs to be determined first, and for the case that the actual radiation characteristic parameter of the current antenna does not meet the requirement due to other antennas except the current antenna, the isolation between the current antenna and the other antennas needs to be adjusted, for example, a physical distance is increased or an isolation device is additionally arranged, that is, the antenna layout on the satellite needs to be adjusted; in the case that the actual radiation characteristic parameters of the current antenna, which are determined to be due to the structural layout of the satellite, do not meet the requirements, the adjustment can be performed by changing the position of the current antenna or changing the structural materials of the satellite, that is, the structural layout of the satellite needs to be adjusted.
Therefore, the method and the device complete verification test of whether each antenna in the actual satellite loading state meets the requirements or not through the two steps, so that the structural layout and the antenna design of the satellite are adjusted based on the result of the verification test. In addition, it should be noted that the actual satellite loading state in the present application may also be referred to as a full-size radiation model satellite, that is, a state in which each device and each antenna on the satellite are completely mounted. In addition, when the structural layout of the satellite is adjusted, the space isolation between the transmitter and sensitive equipment on the satellite needs to be satisfied as much as possible, the high-power transmitter needs to be far away from the high-sensitivity equipment, shielding of other equipment is avoided as much as possible in the view field of the antenna beam, and the structural layout of the satellite can be adjusted by adjusting the distance among the transmitting antenna, the receiving antenna, the transmitter and the receiver, and the like.
In addition, the coupling crosstalk exists between the cables in consideration of the fact that the cables are arranged inside the receiver and other devices on the satellite, so that the coupling crosstalk degree of the cable parts can be determined and optimized according to the size, winding mode, materials and the like of the cables in the receiver and other devices.
As a preferred embodiment, after establishing a satellite model conforming to the antenna layout of the satellite in the actual satellite loading state, the method further comprises:
determining isolation and radiation characteristic parameters of each antenna under the whole-satellite electromagnetic boundary condition;
when the isolation degree of the antenna does not meet the preset standard isolation degree and/or when the radiation characteristic parameter does not meet the preset standard, the structural layout of the satellite and/or the antenna design of the satellite are/is judged to need to be adjusted.
In this embodiment, a satellite model conforming to the antenna layout of the satellite in an actual satellite loading state is first established, and the isolation and radiation characteristic parameters of each antenna in the whole satellite electromagnetic boundary condition are determined, and when the situation that the isolation of the antenna does not meet any one of the preset standard isolation and radiation characteristic parameters does not meet the preset standard exists, the structural layout of the satellite and/or the antenna design of the satellite are determined to need to be adjusted, thereby further ensuring the rationality and reliability of the satellite structure.
As a preferred embodiment, after determining the reception frequency of the receiver on the satellite, it further comprises:
determining a received power of a receiver, a transmission frequency and a transmission power of a transmitter in other equipment;
and judging whether the receiving frequency, the receiving power, the transmitting frequency and the transmitting power all meet the radio management regulations.
In order to ensure that the transmitters and receivers on the satellite can meet the most basic requirements in the early stage of satellite development, the transmitting frequency and transmitting power of the transmitters and the receiving frequency and receiving power of the receivers on the satellite are determined first, and whether the transmitting frequency, the transmitting power, the receiving frequency and the receiving power all meet radio management regulations is judged. Among them, the radio management regulations include international and national radio management regulations, and it is necessary to ensure transmission frequency, transmission power, reception frequency, and reception power while satisfying the international and national radio management regulations in order to ensure accuracy of a predicted result of whether or not the transmitter and receiver on the satellite satisfy actual requirements.
In this application, the device on the satellite for receiving signals is referred to as a receiver, the device on the satellite for transmitting signals is referred to as a transmitter, and all devices on the satellite include the receiver, the transmitter, and other devices except the receiver and the transmitter.
In addition, attention is paid to detecting the electric field intensity between the transmitter and the sensitive equipment on the satellite, so that the sensitive equipment is prevented from being interfered by the transmitter.
As a preferred embodiment, further comprising:
establishing a satellite model of the satellite in an actual satellite loading state, and acquiring a receiving signal of a receiving antenna in the satellite;
establishing a model of the satellite after removing the star structure, and acquiring a direct signal of a receiving antenna;
determining a multipath signal obtained by subtracting the direct signal from the received signal, and calculating amplitude attenuation and time delay of the multipath signal relative to the direct signal;
the influence of multipath effects brought by the star structure of the satellite on the receiver is determined according to the amplitude attenuation and the time delay.
In view of the fact that the satellite is actually used, the receiver in the satellite is also affected by multipath effects, and other antennas on the satellite surface, solar sailboards on the satellite and other structural components bring about multipath effects, the degree to which the receiver is affected by multipath effects needs to be determined so as to better know whether the satellite design needs to be adjusted.
Specifically, in this embodiment, the satellite needs to be simulated under the condition that the star structure of the satellite is completed, that is, a satellite model of the satellite in an actual satellite loading state is first established, and a receiving signal of a receiving antenna in the satellite at the moment is obtained, and the receiving signal at the moment is a signal of the receiving antenna affected by multipath effects; then, the satellite model of the star structure is removed in a simulation mode, and the direct signal of the receiving antenna at the moment is obtained, wherein the direct signal at the moment is the signal of the receiving antenna which is not affected by multipath effects.
And determining the multipath signals obtained by subtracting the direct signals from the received signals, calculating the amplitude attenuation and the time delay of the multipath signals relative to the direct signals, and determining the influence of multipath effects on a receiver according to the amplitude attenuation and the time delay, thereby further improving the accuracy of comprehensive prediction analysis of satellites.
Referring to fig. 2, fig. 2 is a schematic structural diagram of an electromagnetic compatibility prediction system for a mass-production small satellite according to the present invention, where the electromagnetic compatibility prediction system for a mass-production small satellite includes:
a first determining unit 11 for determining a reception frequency of a receiver on a satellite;
a second determining unit 12, configured to determine an operating frequency of other devices except the receiver on the satellite, and determine a frequency of potential interference caused by the other devices according to the operating frequency of the other devices;
and the electromagnetic compatibility analysis unit 13 is configured to, when the working frequency or the frequency of the potential interference overlaps with the receiving frequency, take the device corresponding to the working frequency or the device corresponding to the frequency of the potential interference in the other devices as an interference source, take the receiver corresponding to the receiving frequency as an interfered object, determine an interference path between the interference source and the interfered object, and determine that the frequency and/or the bandwidth of the interference source need to be adjusted.
For a description of the electromagnetic compatibility prediction system for a mass-production small satellite provided by the present invention, reference is made to an embodiment of the electromagnetic compatibility prediction method for a mass-production small satellite, and details are not repeated herein.
Based on the above embodiments:
as a preferred embodiment, further comprising:
the field intensity determining unit is used for determining the measurement and control radiation emission field intensity between the satellite and the target equipment according to the distance between the measurement and control antenna of the satellite and the target equipment in the carrying and/or emission field, the gain of the target antenna and the emission power of the transmitter connected with the rear end of the target antenna;
the field intensity adjusting unit is used for judging that the design of the measurement and control antenna and/or the transmitter connected with the rear end of the measurement and control antenna is required to be adjusted when the measurement and control radiation emission field intensity does not meet the field intensity requirement.
As a preferred embodiment, further comprising:
the single antenna parameter determining unit is used for establishing a single antenna simulation model for each antenna in the satellite and acquiring actual performance parameters of each antenna in the satellite when working in a single antenna state;
and the single antenna adjusting unit is used for judging that the antenna design needs to be adjusted when the actual performance parameter does not meet the preset standard single antenna performance parameter.
As a preferred embodiment, further comprising:
the actual satellite loading parameter determining unit is used for establishing a satellite model which accords with the antenna layout of the satellite in an actual satellite loading state and determining the actual isolation degree and the actual radiation characteristic parameters of each antenna in the satellite in the actual satellite loading state;
the actual satellite loading analysis unit is used for judging that the antenna design of the satellite and/or the structural layout of the satellite need to be adjusted when the actual isolation degree of the antenna does not meet the preset standard isolation degree and/or the actual radiation characteristic parameter does not meet the preset standard after the satellite model which accords with the antenna layout of the satellite in the actual satellite loading state is established.
As a preferred embodiment, further comprising:
the whole-satellite electromagnetic boundary determining unit is used for determining the isolation degree and radiation characteristic parameters of each antenna under the whole-satellite electromagnetic boundary condition at the moment after establishing a satellite model which accords with the antenna layout of the satellite in the actual satellite loading state;
the whole satellite electromagnetic boundary analysis unit is used for judging the structural layout of the satellite and/or the antenna design of the satellite to be adjusted when the isolation degree of the antenna does not meet the preset standard isolation degree and/or the radiation characteristic parameter does not meet the preset standard.
As a preferred embodiment, further comprising:
a correlation parameter determining unit for determining a reception power of a receiver, a transmission frequency and a transmission power of a transmitter in other devices after determining a reception frequency of the receiver on a satellite;
and the radio management regulation judging unit is used for judging whether the receiving frequency, the receiving power, the transmitting frequency and the transmitting power all meet the radio management regulation.
As a preferred embodiment, further comprising:
the receiving signal acquisition unit is used for establishing a satellite model of the satellite in an actual satellite loading state and acquiring receiving signals of a receiving antenna in the satellite;
the direct signal acquisition unit is used for establishing a model of the satellite after the star structure is removed, and acquiring a direct signal of the receiving antenna;
the multipath signal determining unit is used for determining a multipath signal obtained by subtracting the direct signal from the received signal and calculating the amplitude attenuation and the time delay of the multipath signal relative to the direct signal;
and the multipath effect analysis unit is used for determining the influence of multipath effects brought by the star structure of the satellite on the receiver according to the amplitude attenuation and the time delay.
Referring to fig. 3, fig. 3 is a schematic structural diagram of an electromagnetic compatibility prediction apparatus for mass-production satellites according to the present invention, where the electromagnetic compatibility prediction apparatus for mass-production satellites includes:
a memory 21 for storing a computer program;
a processor 22 for implementing the steps of the above-described electromagnetic compatibility prediction method for mass-produced satellites when executing a computer program.
For a description of the electromagnetic compatibility prediction apparatus for a mass-production small satellite provided by the present invention, reference is made to an embodiment of the electromagnetic compatibility prediction method for a mass-production small satellite, which is not described herein.
The application also provides a computer readable storage medium, wherein the computer readable storage medium stores a computer program, and the computer program realizes the steps of the electromagnetic compatibility prediction method of the mass production small satellite when being executed by a processor.
For a related description of a computer-readable storage medium provided in the present invention, please refer to an embodiment of the above method for predicting electromagnetic compatibility of a mass-produced small satellite, which is not described herein.
In the present specification, each embodiment is described in a progressive manner, and each embodiment is mainly described in a different point from other embodiments, and identical and similar parts between the embodiments are all enough to refer to each other. For the device disclosed in the embodiment, since it corresponds to the method disclosed in the embodiment, the description is relatively simple, and the relevant points refer to the description of the method section.
The steps of a method or algorithm described in connection with the embodiments disclosed herein may be embodied directly in hardware, in a software module executed by a processor, or in a combination of the two. The software modules may be disposed in Random Access Memory (RAM), memory, read Only Memory (ROM), electrically programmable ROM, electrically erasable programmable ROM, registers, hard disk, a removable disk, a CD-ROM, or any other form of storage medium known in the art.
The previous description of the disclosed embodiments is provided to enable any person skilled in the art to make or use the present invention. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the generic principles defined herein may be applied to other embodiments without departing from the spirit or scope of the invention. Thus, the present invention is not intended to be limited to the embodiments shown herein but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.
Claims (10)
1. An electromagnetic compatibility prediction method for mass-production satellites is characterized by comprising the following steps:
determining a reception frequency of a receiver on the satellite;
determining the working frequencies of other devices except the receiver on the satellite, and determining the frequency of potential interference brought by the other devices according to the working frequencies of the other devices;
when the working frequency or the frequency of the potential interference overlaps with the receiving frequency, using a device corresponding to the working frequency or a device corresponding to the frequency of the potential interference in the other devices as an interference source, using a receiver corresponding to the receiving frequency as an interfered object, determining an interference path between the interference source and the interfered object, and determining that the frequency and/or bandwidth of the interference source need to be adjusted.
2. The method for predicting electromagnetic compatibility of a mass-produced small satellite as recited in claim 1, further comprising:
determining the measurement and control radiation emission field intensity between the satellite and the target equipment according to the distance between the measurement and control antenna of the satellite and the target equipment in the carrying and/or emission field, the gain of the target antenna and the emission power of a transmitter connected with the rear end of the target antenna;
when the measurement and control radiation emission field intensity does not meet the field intensity requirement, the design of the measurement and control antenna and/or a transmitter connected with the rear end of the measurement and control antenna is judged to be required to be adjusted.
3. The method for predicting electromagnetic compatibility of a mass-produced small satellite as recited in claim 1, further comprising:
establishing a single-antenna simulation model for each antenna in the satellite, and acquiring actual performance parameters of each antenna in the satellite when working in a single-antenna state;
and when the actual performance parameter does not meet the preset standard single antenna performance parameter, determining that the antenna design needs to be adjusted.
4. The method for predicting electromagnetic compatibility of a mass-produced small satellite as recited in claim 1, further comprising:
establishing a satellite model which accords with the antenna layout of the satellite in an actual satellite loading state, and determining the actual isolation degree and the actual radiation characteristic parameters of each antenna in the satellite in the actual satellite loading state;
when the actual isolation degree of the antenna does not meet the preset standard isolation degree and/or the actual radiation characteristic parameter does not meet the preset standard, the antenna design of the satellite and/or the structural layout of the satellite are/is judged to need to be adjusted.
5. The method for predicting electromagnetic compatibility of a mass-produced minisatellite according to claim 4, further comprising, after establishing a satellite model conforming to an antenna layout of said satellite in an actual satellite loading state:
determining isolation and radiation characteristic parameters of each antenna under the whole satellite electromagnetic boundary condition;
and when the isolation degree of the antenna does not meet the preset standard isolation degree and/or the radiation characteristic parameter does not meet the preset standard, judging that the structural layout of the satellite and/or the antenna design of the satellite need to be adjusted.
6. The method for predicting electromagnetic compatibility of a mass-produced small satellite of claim 1, further comprising, after determining a reception frequency of a receiver on the satellite:
determining a received power of the receiver, a transmission frequency and a transmission power of a transmitter in the other device;
and judging whether the receiving frequency, the receiving power, the transmitting frequency and the transmitting power all meet radio management regulations.
7. The electromagnetic compatibility prediction method of a mass-produced small satellite according to any one of claims 1 to 6, further comprising:
establishing a satellite model of the satellite in the actual satellite loading state, and acquiring a receiving signal of a receiving antenna in the satellite;
establishing a model of the satellite with the star structure removed, and acquiring a direct signal of the receiving antenna;
determining a multipath signal obtained by subtracting the direct signal from the received signal, and calculating amplitude attenuation and time delay of the multipath signal relative to the direct signal;
and determining the influence of multipath effects brought by the satellite body structure of the satellite on the receiver according to the amplitude attenuation and the time delay.
8. An electromagnetic compatibility prediction system for mass-produced satellites, comprising:
a first determining unit for determining a reception frequency of a receiver on a satellite;
a second determining unit, configured to determine an operating frequency of other devices on the satellite except the receiver, and determine a frequency of potential interference caused by the other devices according to the operating frequency of the other devices;
and the electromagnetic compatibility analysis unit is used for taking the equipment corresponding to the working frequency or the equipment corresponding to the potential interference in the other equipment as an interference source, taking the receiver corresponding to the receiving frequency as an interfered object, determining an interference path between the interference source and the interfered object and determining that the frequency and/or bandwidth of the interference source need to be adjusted when the working frequency or the frequency of the potential interference overlaps with the receiving frequency.
9. An electromagnetic compatibility predicting device for mass-production satellites, comprising:
a memory for storing a computer program;
a processor for implementing the steps of the method for predicting electromagnetic compatibility of mass produced satellites according to any one of claims 1 to 7 when executing the computer program.
10. A computer-readable storage medium, characterized in that the computer-readable storage medium has stored thereon a computer program which, when executed by a processor, implements the steps of the method for predicting electromagnetic compatibility of mass-produced satellites according to any one of claims 1 to 7.
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| CN202211310140.XA CN116087638A (en) | 2022-10-25 | 2022-10-25 | Electromagnetic compatibility prediction method for mass-production small satellite and related components |
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