CN113408106B - Antenna-start constellation communication load EMC analysis model and EMC characteristic improvement method - Google Patents
Antenna-start constellation communication load EMC analysis model and EMC characteristic improvement method Download PDFInfo
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Abstract
The invention provides an EMC analysis model of a zenith constellation communication load and an EMC characteristic improvement method, which comprises the following steps: aiming at load radiation disturbance, an EMC analysis model of a sky-start satellite load is established, wherein the EMC analysis model comprises a load cabin, a load structure cabin arranged in the load cabin and a load antenna connected to the load structure cabin, and parameters are set; according to the load EMC analysis model, determining the noise floor of the load receiving channel under ideal conditions; determining the interference of the noise floor via radiation coupling back to the load antenna; and determining the noise floor of the actual load receiving channel. By reducing one or more of the co-axial radio frequency cable conduction coefficient between the load antenna and the load, the load channel gain, the radiation coefficient of the DCS load to the satellite interference signal and the radiation coefficient of the satellite to the load antenna interference signal, and by increasing the shielding coefficient of the load structure cabin and/or the shielding coefficient of the satellite load cabin, the EMC characteristic is improved, so that the reliability and the safety of the load are greatly improved.
Description
Technical Field
The invention relates to the field of satellite communication, in particular to an EMC (Electromagnetic Compatibility, EMC for short) analysis model of a zenith constellation communication load and an EMC characteristic improvement method.
Background
The communication frequency of the satellite Internet of things mainly works in a VHF frequency band (30 MHz-300 MHz, wavelength 1 m-10 m) and a UHF frequency band (300 MHz-3 GHz, wavelength 1 m-0.1 m), but the uplink and downlink frequency bands are greatly interfered, and the interference is mainly manifested by noise floor elevation and high-power burst interference.
The sky-start satellite is used as an Internet of things satellite, and has the characteristics of low transmitting power, low signal-to-noise ratio of a received signal, small level margin of a communication link and the like. In recent years, with the rapid increase of military frequency equipment and civil radio equipment and systems, the electromagnetic environment of space in-orbit satellites presents increasingly complex situations, and the problems of incompatibility such as electromagnetic self-interference, mutual interference and the like are gradually increased, so that higher electromagnetic compatibility requirements are provided for the space satellite and the load thereof.
On the other hand, with the rapid development of modern technology, the number of electrical and electronic devices used in large-scale integrated circuits is increasing, and electronic devices tend to be integrated, miniaturized and networked. The rapid development also brings about a number of negative effects, electromagnetic interference being one of the problems. A large number of electronic devices work in the same electromagnetic environment, the frequency band is wider and wider, the power is larger and larger, the sensitivity is also improved continuously, and the cable network for connecting the devices is also more and more complex, so that the problem of electromagnetic compatibility is more serious. The scope of the electromagnetic compatibility discipline is very wide, and the satellite Internet of things field is still in a starting stage in the electromagnetic compatibility research aspect.
Electromagnetic compatibility (Electromagnetic Compatibility), EMC for short, is a science that studies electronic devices work together under the same electromagnetic environment without performance impact. Another definition is the "ability of devices and systems to function properly in their electromagnetic environment and not to constitute an intolerable electromagnetic nuisance to anything in the environment". The definition includes two meanings, firstly, the device should work normally under a certain electromagnetic environment, namely, the device should have certain electromagnetic immunity (EMS); second, the electromagnetic disturbance generated by the device itself cannot have an excessive impact on other electronic products, namely electromagnetic disturbance (EMI). To improve the electromagnetic compatibility of electronic equipment, not only the electromagnetic compatibility immunity of the equipment needs to be improved, but also the electromagnetic disturbance of the electronic equipment needs to be reduced.
Electromagnetic compatibility has become a very important discipline in modern electronics, and then electromagnetic compatibility has evolved more rapidly. Some countries have established institutions dedicated to the electromagnetic compatibility testing and management of military and civil products, and the electromagnetic compatibility standard has also become a strong technical barrier for the developed countries to limit imported products.
In addition, practice also proves that if the electromagnetic compatibility problem is solved in the product design development and production stage, the possibility of electromagnetic interference is considered from the design of a circuit to the selection of components, the integral anti-interference capability is improved from the inside of the system, and the improvement cost after the design and shaping of the product and even mass production is greatly reduced. Therefore, increasing the electromagnetic compatibility of the load of the zenithal constellation DCS (Data Collection System ) has become an unprecedented task. Some problems that occur during in-orbit communications of a zenith satellite also require investigation and resolution of the associated electromagnetic compatibility issues.
Disclosure of Invention
The technical problem to be solved by the invention is to provide an EMC analysis model and an EMC characteristic improvement method for the communication load of a Tianqi constellation aiming at the defects in the prior art.
According to the invention, an EMC analysis model of a zenith constellation communication load and an EMC characteristic improvement method are provided, comprising the following steps:
for loading radiation harassment, an EMC analysis model of the overhead satellite loading is established, comprising a loading cabin, a loading structural cabin arranged in the loading cabin, and a loading antenna connected to the loading structural cabin, and the following parameters are set:
R 0 natural noise and interference signals entering the load antenna from the outside;
c: the coaxial radio frequency cable conduction coefficient between the load antenna and the load;
g: load channel gain;
R d : the radiation coefficient of DCS load to the star interference signal;
R s : the radiation coefficient of the star body to the load antenna interference signal;
E d : the shielding factor of the load structure compartment,
E s : shielding coefficient of star load cabin;
according to the load EMC analysis model, determining the noise floor N of the load receiving channel under ideal conditions 0 The method comprises the following steps: n (N) 0 ＝R 0 +C+G (in dB for ease of calculation);
the interference of the noise floor via radiation coupling back to the load antenna is determined as follows:
N 1 ＝[(N 0 -E d )*R d -E s ]*R s +C+G；
the same principle is as follows: n (N) i ＝[(N i-1 -E d )*R d -E s ]*R s +C+G，
Wherein: i is a natural number, N i The interference of the load antenna is coupled back for the ith radiation.
Therefore, the actual load receiving channel noise floor is determined as:
preferably, the EMC characteristics are improved by reducing the co-axial radio frequency cable conductivity C between the payload antenna and the payload, the payload channel gain G, DCS, the radiation coefficient Rd of the payload to the satellite interfering signal, and the radiation coefficient Rs of the satellite to the payload antenna interfering signal.
Preferably, the EMC characteristics are improved by increasing the shielding factor of the Ed loading structure compartment and the shielding factor Es of the star loading compartment.
Preferably, the co-axial radio frequency cable conductivity between the load antenna and the load is a fixed value.
Preferably, the radiation coefficient of DCS load to star disturbing signals is reduced by attaching wave absorbing materials inside the load cabin.
Preferably, the shielding factor of the load structure compartment is increased by adding shielding material.
Preferably, the shielding coefficient of the star load capsule is increased by adding shielding material.
Preferably, the EMC characteristics are improved by wrapping the load connector slots, the structural slots with shielding material.
Preferably, the EMC characteristics are improved by masking the load power supply lines and the data lines.
Preferably, the EMC characteristics are improved by wrapping the holes of the cable on the satellite load compartment plate with shielding material.
Drawings
The invention will be more fully understood and its attendant advantages and features will be more readily understood by reference to the following detailed description, when taken in conjunction with the accompanying drawings, in which:
fig. 1 schematically shows an example of an EMC analysis model employed in accordance with a preferred embodiment of the invention.
Fig. 2 schematically shows a DCS payload EMC test connection block diagram employed in accordance with a preferred embodiment of the invention.
Fig. 3 schematically shows the 240MHz spectrum (noise floor-95 dBm) obtained by testing before implementation of the EMC characteristic improvement measure according to the preferred embodiment of the invention.
Fig. 4 schematically shows the 240MHz spectrum (noise floor-115 dBm) tested after implementation of the EMC characteristic improvement measure according to a preferred embodiment of the invention.
It should be noted that the drawings are for illustrating the invention and are not to be construed as limiting the invention. Note that the drawings representing structures may not be drawn to scale. Also, in the drawings, the same or similar elements are denoted by the same or similar reference numerals.
Detailed Description
In order that the invention may be more readily understood, a detailed description of the invention is provided below along with specific embodiments and accompanying figures.
According to the design scheme and the whole star structure of the Tianqi constellation communication load, an EMC analysis model of the Tianqi constellation communication load is built for the first time, a calculation formula of the load electromagnetic interference noise floor is given, and theoretical basis is provided for EMC analysis and EMC protection of the Tianqi satellite DCS (Data Collection System ) communication load.
Practice shows that if the electromagnetic compatibility can be considered in the load design and development process, the advantages and the disadvantages of the anti-interference device are considered, and the reliability and the safety of the load can be greatly improved. The analysis method adopting the model is successfully applied in the process of testing and developing the communication load EMC of the Tianqi constellation, and a series of improvement measures proposed by the analysis model are proved to be very effective according to facts, so that the sensitivity of the receiver can be improved by more than 2 dB. The model and the calculation formula have reference significance for further improving EMC characteristics of the same type of communication load.
DCS load EMC analysis model
Aiming at the problem of the current and increasingly worsened electromagnetic interference, the DCS load also needs to standardize and improve the related standard of electromagnetic compatibility, thereby improving the electromagnetic compatibility of the product.
The electromagnetic interference modes mainly include the following:
1) Radiation interference: electromagnetic interference sources couple (interfere) signals to another electrical network in spatial form (electric field, magnetic field).
2) Conduction interference: electromagnetic interference sources couple (interfere) signals on one electrical network to another electrical network through a conductive medium. Typically defined by a voltage or current.
3) Electrostatic discharge: the charge transfer that occurs when objects with different electrostatic potentials come into close proximity or contact.
4) An electrical fast transient pulse train: there is a pulse of a specific duration (specified as 15 ms) and a specific pulse period (300 ms).
5) Surge (impact): instantaneous overvoltage/current exceeding normal operating voltage.
The frequency band of DCS load work is relatively high and is mainly between 240MHz and 400MHz, so that the radiation interference is the most main interference source of the DCS load in the satellite in-orbit flight process.
There are three basic elements that form electromagnetic interference or electromagnetic hazard: electromagnetic interference sources, electromagnetic energy coupling pathways, and sensitive objects. Here, DCS loading is taken as a sensitive object, and the electromagnetic energy coupling approach mainly considers radiation coupling and conduction coupling. Conductive coupling requires a complete electrical connection between the electromagnetic interference source and the sensitive object, whereas radiative coupling is the coupling of signals (interference) by the interference source to the sensitive object by spatial form (electric field, magnetic field). The electromagnetic interference source may be a load or any component on the satellite that generates electromagnetic interference.
In order to ensure that the DCS load is not influenced by electromagnetic interference of other electronic equipment of a satellite platform and normal operation of other equipment while the DCS load works normally, three elements are needed to be cut in for solving the problems of the development of the DCS load and the electromagnetic interference in the in-orbit operation, and the nature of the interference is analyzed.
An EMC analysis model as shown in fig. 1 is here built for loading radiation harassment according to the configuration of the overhead satellites loading and the whole satellites, wherein the EMC analysis model comprises a loading cabin, a loading structure cabin arranged in the loading cabin, and a loading antenna connected to the loading structure cabin. For definition of parameters, wherein:
R 0 external access load dayNatural noise of the wire and interference signals; human intervention cannot be performed;
c: the coaxial radio frequency cable conduction coefficient between the load antenna and the load; a fixed value;
g: load channel gain;
R d : the radiation coefficient of DCS load to the star interference signal; the application of wave-absorbing material inside the load compartment can be considered;
R s : the radiation coefficient of the star body to the load antenna interference signal;
E d : the shielding factor of the load cell can be increased by increasing the shielding material.
E s : shielding coefficient of star load cabin; this coefficient can be increased by adding a shielding material;
noise floor N of load receiving channel under ideal condition according to load EMC analysis model 0 Should be as shown in the following formula (in dB):
N 0 ＝R 0 +C+G (1)
the interference of the noise floor via radiation coupling back to the load antenna is:
N 1 ＝[(N 0 -E d )*R d -E s ]*R s +C+G (2)
the same principle is as follows: n (N) i ＝[(N i-1 -E d )*R d -E s ]*R s +C+G (3)
Wherein: i is a natural number, N i The interference of the load antenna is coupled back for the ith radiation.
Therefore, the actual load receiving channel noise floor is determined as:
from the above equation, it can be seen that it is desirable to minimize C, G, rd, rs while increasing Ed and Es. Some measures to improve the EMC characteristics are also proposed later on based on this analytical model.
Application of EMC analysis model in EMC test
In the EMC laboratory, EMC testing was performed on DCS loads according to the test connection block diagram shown in fig. 2. As shown in fig. 2, a 401M antenna and a 240/320 antenna are configured for a satellite having DCS loading, with the loading ground test being communicated with the 401M antenna of the satellite via one 401M antenna through one attenuator, and with the 240/320 antenna of the satellite via another attenuator.
The test is mainly used for verifying the load receiving sensitivity in the whole satellite wireless state and judging whether the load receiving sensitivity is influenced by the platform or not.
In order to improve the EMC characteristics of the payload, the payload channel gain G may be reduced according to the formula, for which G is reduced by 10dB, and the spectrum processing results of 240MHz bands before and after the reduction are shown in fig. 3 and 4. It can be seen that the noise floor is reduced by 20dBm. In addition, the test report of data reception shows that the sensitivity of the receiver is improved by at least more than 2 dB.
Along with the development of the satellite Internet of things, the EMC problem of DCS load is increasingly outstanding. Because of the characteristics of low signal-to-noise ratio and large Doppler frequency shift of the satellite communication of the Internet of things, signal capturing and demodulation are relatively difficult, and the EMC problem of solving the load is greatly helpful to the improvement of the problem. In addition, practice also proves that if the problem of electromagnetic compatibility is solved in the load design and development stage, the possibility of electromagnetic interference is considered from the design of a circuit to the selection of components, the integral anti-interference capability is improved from the inside of the system, and the improvement cost after loading is greatly reduced.
According to equation (1), the channel gain G is reduced by 10dB and the initial noise will also be reduced by 10dB. And the noise floor is eventually reduced by 20dBm. It is shown that the radiation disturbance in the loop is close to an order of magnitude to the initial noise, so that the channel gain is reduced, and the influence of the radiation disturbance on the noise floor is also reduced.
Increasing Ed and Es can also improve the EMC characteristics of the load, depending on the model, and the following measures can be taken later:
1) Wrapping the load connector gaps and the structural gaps by using shielding materials;
2) Carrying out shielding treatment on the load power supply line and the data line;
3) And wrapping the holes of the threading cables on the satellite load cabin board by using shielding materials.
The reasons for the electromagnetic interference in the working frequency band of the load are researched by carefully analyzing the electromagnetic environment, electromagnetic compatibility and electromagnetic interference principles of the load, and the electromagnetic interference can be restrained by reasonably applying an electromagnetic compatibility method. Therefore, the DCS load can work normally and reliably in a space complex electromagnetic environment, the function and performance of the DCS load electromagnetic compatibility meet the design requirements, and the accuracy of data communication is greatly improved, so that the EMC analysis model and the calculation formula have important practical significance. The model is also improved continuously in the subsequent load development and use, so that the model is more suitable for practical application.
It should be noted that, unless specifically stated otherwise, the terms "first," "second," "third," and the like in the specification are used merely as a distinction between various components, elements, steps, etc. in the specification, and are not used to denote a logical or sequential relationship between various components, elements, steps, etc.
It will be appreciated that although the invention has been described above in terms of preferred embodiments, the above embodiments are not intended to limit the invention. Many possible variations and modifications of the disclosed technology can be made by anyone skilled in the art without departing from the scope of the technology, or the technology can be modified to be equivalent. Therefore, any simple modification, equivalent variation and modification of the above embodiments according to the technical substance of the present invention still fall within the scope of the technical solution of the present invention.
Claims (10)
1. An improvement method of an EMC analysis model of a zenith constellation communication load is characterized by comprising the following steps:
for loading radiation harassment, an EMC analysis model of the overhead satellite loading is established, comprising a loading cabin, a loading structural cabin arranged in the loading cabin, and a loading antenna connected to the loading structural cabin, and the following parameters are set:
R 0 natural noise and interference signals entering the load antenna from the outside;
c: the coaxial radio frequency cable conduction coefficient between the load antenna and the load;
g: load channel gain;
R d : the radiation coefficient of DCS load to the star interference signal;
R s : the radiation coefficient of the star body to the load antenna interference signal;
E d : shielding coefficient of the load structure cabin;
E s : shielding coefficient of star load cabin;
according to the load EMC analysis model, determining the noise floor N of the load receiving channel under ideal conditions 0 The method comprises the following steps: n (N) 0 ＝R 0 +C+G；
The interference of the noise floor via radiation coupling back to the load antenna is determined as follows:
N 1 ＝[(N 0 -E d )*R d -E s ]*R s +C+G；
the same principle is as follows:
N i ＝[(N i -1-E d )*R d -E s ]*R s +c+g, wherein: i is a natural number, N i The interference of the load antenna is returned for the ith radiation coupling;
therefore, the actual load receiving channel noise floor is determined as:
2. the method of claim 1, wherein the EMC characteristics are improved by reducing one or more of a co-axial radio frequency cable conductivity between the payload antenna and the payload, a payload channel gain, a radiation coefficient of DCS payload to star interfering signals, and a radiation coefficient of star to payload antenna interfering signals.
3. The improvement of a zenith constellation communication payload EMC analysis model according to claim 1 or 2, characterized in that the EMC characteristics are improved by increasing the shielding factor of the payload structure compartment and/or the shielding factor of the star payload compartment.
4. The improvement in a sky-start constellation communication payload EMC analysis model according to claim 1 or 2, characterized in that the co-axial radio frequency cable conductivity between the payload antenna and the payload is a fixed value.
5. The improvement of an EMC analysis model of a zenith constellation communication load according to claim 1 or 2, characterized in that the radiation coefficient of DCS load to star disturbing signals is reduced by means of attaching wave absorbing material inside the load compartment.
6. The improvement in a sky-start constellation communication payload EMC analysis model according to claim 1 or 2, characterized in that the shielding factor of the payload structural cabin is increased by adding shielding material.
7. The improvement in a sky-start constellation communication payload EMC analysis model according to claim 1 or 2, characterized in that the shielding factor of the star payload cabin is increased by adding shielding material.
8. The improvement of an EMC analysis model for a zenith constellation communication payload according to claim 1 or 2, wherein the EMC characteristics are improved by wrapping the payload connector slots, the structural slots with shielding material.
9. The improvement method of an EMC analysis model of a zenith constellation communication payload according to claim 1 or 2, wherein EMC characteristics are improved by masking the payload supply line and the data line.
10. The improvement in a sky-start constellation communication payload EMC analysis model according to claim 1 or 2, characterized in that the EMC characteristics are improved by wrapping the holes of the cable on the satellite payload bay board with shielding material.
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| US10149200B2 (en) * | 2016-06-07 | 2018-12-04 | Iridium Satellite Llc | Interference mitigation for a satellite network |
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