CN111079301A - Electromagnetic compatibility analysis method for high-power radio frequency equipment in manned spacecraft - Google Patents
Electromagnetic compatibility analysis method for high-power radio frequency equipment in manned spacecraft Download PDFInfo
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Abstract
The invention relates to an electromagnetic compatibility analysis method for high-power radio frequency equipment in a manned spacecraft, which comprises the following steps: a. determining whether the frequency of the high-power radio frequency equipment and the linear combination frequency of other radio frequency equipment fall into the bandwidth of the receiving equipment; b. establishing a coupling equation between each antenna and the spacecraft to obtain the isolation between the antennas; c. calculating the signal strength of the radio frequency receiving equipment; d. calculating the safety margin between the high-power radio frequency equipment and each radio frequency receiving equipment; e. establishing a simulation model of electric field intensity radiation distribution; f. establishing an electromagnetic field equation between the high-power radio frequency equipment antenna and the spacecraft; g. and obtaining an electric field intensity distribution diagram of the high-power radio frequency equipment, and respectively judging the influence of the electric field of the high-power radio frequency equipment on equipment outside the spacecraft cabin and personnel in the spacecraft cabin. The analysis method can reflect the real influence of the electromagnetic field of the high-power radio frequency equipment on the spacecraft equipment and the astronaut through simulation analysis.
Description
Technical Field
The invention relates to the field of electromagnetic compatibility analysis, in particular to an electromagnetic compatibility analysis method for high-power radio frequency equipment in a manned spacecraft.
Background
In the existing manned spacecraft, radio frequency equipment is mainly used for data, image and voice communication between the sky and the ground, the transmitting power of the radio frequency equipment is generally in the magnitude of several watts or dozens of watts, but with the development of manned space station engineering, manned lunar landing and other deep space detection tasks, the data rate required to be transmitted between the sky and the ground is higher and higher, such as high-definition images, high-speed test data and the like, the magnitude of the traditional several mega and dozen mega reaches the magnitude of G and dozen G, the transmitting power of the space wireless communication equipment is correspondingly greatly increased, meanwhile, the space application load needs to be provided with high-power transmitting equipment, such as microwave imaging, phased array radar and the like, due to the functional requirements, the transmitting equipment power reaches the magnitude of hundreds of watts, and the transmitting power of related space application load equipment even reaches the magnitude of kilowatt.
The high-power radio frequency equipment can affect electromagnetic environments inside and outside a manned spacecraft cabin when working, especially can bring electromagnetic radiation harm to astronauts and equipment in the spacecraft when the electric field strength reaches a certain value, the greater the damage of the emission power is, the more serious the damage is, the damage of human physiological function, the reduction of equipment performance and even equipment damage can be caused, and the failure of the spacecraft flight mission can be further caused. Therefore, it is necessary to perform special analysis and test verification on the electromagnetic compatibility of the high-power radio frequency equipment of the manned spacecraft in the design and production processes of the manned spacecraft, so as to ensure the electromagnetic compatibility after the last day.
The traditional means for predicting the electromagnetic compatibility of the manned spacecraft is mainly realized through ground test verification, namely, the manned spacecraft is subjected to self-compatibility, intersystem compatibility, electric field intensity sensitivity test and the like under different test working conditions by combining an on-orbit working mode in a microwave darkroom, and meanwhile, an empirical formula or a model is assisted to be adopted for simple estimation and analysis. However, due to the limitation of ground test sites and test conditions, when ground electromagnetic compatibility tests are performed, in view of equipment safety, the transmission power of the high-power radio frequency equipment needs to be attenuated to a certain value to ensure that the safety influence on the equipment is not generated, so that the high-power radio frequency equipment cannot perform ground test verification according to the on-orbit actual transmission power, cannot truly verify whether the high-power radio frequency equipment generates electromagnetic interference on other wireless receiving equipment, and cannot verify the electric field intensity radiation influence on astronauts and electronic equipment when the high-power equipment actually works. Meanwhile, the traditional estimation means mainly analyzes the safety margin between the transmitting equipment and the receiving equipment, and cannot effectively analyze the electric field intensity radiation influence generated by the high-power transmitting equipment.
Patent CN108875239A discloses a system for analyzing radio frequency electromagnetic compatibility by using modeling simulation, in which frequency compatibility is first analyzed and electromagnetic compatibility is analyzed by establishing an electromagnetic matrix using the analysis result. According to the method, when electromagnetic compatibility analysis is carried out, a model is established only on the basis of a three-dimensional structure of the spacecraft, modeling simulation is not carried out according to the actual layout of the radio frequency equipment, so that the safety margin in the final radio frequency analysis result is only a simple estimation result, and therefore the electromagnetic interference analysis result of the radio frequency equipment on the equipment outside the spacecraft cabin is not accurate enough.
Disclosure of Invention
The invention aims to solve the problems and provides a method for analyzing the electromagnetic compatibility of high-power radio frequency equipment in a manned spacecraft.
In order to achieve the above object, the present invention provides a method for analyzing electromagnetic compatibility of high-power radio frequency equipment in a manned spacecraft, comprising the following steps:
a. determining whether the frequency of the high-power radio frequency equipment and the linear combination frequency of the high-power radio frequency equipment and other radio frequency equipment fall into the bandwidth of the radio frequency receiving equipment or not;
b. establishing an electromagnetic compatibility three-dimensional simulation model of the high-power radio-frequency equipment, and establishing a coupling equation between each equipment antenna and a spacecraft carrier based on the model to obtain the isolation between each high-power radio-frequency equipment antenna and each radio-frequency receiving equipment antenna;
c. calculating the signal intensity from the high-power radio frequency equipment to the radio frequency receiving equipment according to the transmitting power of the high-power radio frequency equipment, the out-of-band rejection value of the receiving equipment and the isolation degree;
d. comparing the signal intensity with the sensitivity of the radio frequency receiving equipment, and calculating the safety margin between the high-power radio frequency equipment and each radio frequency receiving equipment;
e. establishing a simulation model of electric field intensity radiation distribution based on a manned spacecraft cabin model and a high-power radio-frequency equipment three-dimensional directional diagram model;
f. dividing a spacecraft cabin into a plurality of areas by taking high-power radio frequency equipment as a center, and establishing an electromagnetic field equation between an antenna of the high-power radio frequency equipment and a spacecraft carrier;
g. and obtaining an electric field intensity distribution diagram of the high-power radio frequency equipment through simulation calculation, and respectively judging the influence of the electric field of the high-power radio frequency equipment on equipment outside the spacecraft cabin and personnel in the spacecraft cabin.
According to an aspect of the present invention, in the step (a), the frequency of the high power rf device includes the frequencies of the fundamental wave and the second and third harmonics.
According to one aspect of the invention, in the step (b), the three-dimensional electromagnetic compatibility simulation model is established based on a three-dimensional manned spacecraft model and an antenna three-dimensional directional diagram according to the actual configuration of the manned spacecraft;
the antenna of the high-power radio frequency equipment and the antennas of other radio frequency receiving equipment are placed according to the actual installation position in the spacecraft.
According to an aspect of the present invention, in the step (b), the coupling equation is established using a physical optics method in an electromagnetic field high frequency calculation method.
According to an aspect of the present invention, in the step (c), the out-of-band rejection value adopts an actual measurement result, and the actual measurement is performed on each receiving frequency band.
According to one aspect of the present invention, in the step (f), the electromagnetic field equation is established using a physical optical calculation method.
According to one aspect of the invention, in the step (g), a region where the extravehicular area exceeds a limit value is judged according to the electric field intensity distribution diagram, and whether equipment in the region works together with high-power radio frequency equipment or not is judged.
According to one aspect of the present invention, in the step (e), a porthole model in the spacecraft tank model is established according to a material and a structure of a porthole.
According to one aspect of the invention, in the step (g), the distribution of the electric field intensity of the high-power radio frequency equipment leaking into the spacecraft cabin is obtained by performing simulation calculation on the porthole by using a multilayer fast multipole algorithm in an electromagnetic field moment method.
According to one scheme of the invention, whether the fundamental wave of the high-power transmitting equipment or the second harmonic and the third harmonic thereof directly fall into the frequency band of other radio frequency receiving equipment or not and whether the high-power radio frequency equipment is linearly combined with other transmitting frequency points to generate a new frequency and fall into the receiving frequency band of the radio frequency receiving equipment are respectively judged. Therefore, whether the interference signals generated by the high-power radio frequency equipment fall into other receiving passbands of the manned spacecraft can be effectively judged.
According to an aspect of the present invention, a safety margin is calculated for frequencies falling within the frequency band of the receiving device. Firstly, an electromagnetic compatibility three-dimensional simulation model is established according to the actual configuration of the manned spacecraft, and a high-power radio frequency transmitting antenna and other radio frequency receiving antennas are placed according to the actual installation position in the spacecraft. And establishing a coupling equation between the antenna and the spacecraft carrier based on the model to obtain the actual radiation characteristic of the high-power transmitting antenna directional diagram after being influenced by factors such as reflection and diffraction of the cabin body. And then obtaining the numerical value of the antenna isolation between the high-power radio frequency radiation source and each receiving source. And then, according to the transmitting power and the antenna isolation of the high-power radio frequency equipment, calculating the signal intensity of the high-power radio frequency equipment reaching the receiving equipment, comparing the signal intensity with the sensitivity of the receiving equipment, and finally calculating the safety margin between the high-power transmitting equipment and each receiving equipment in the manned spacecraft. The safety margin calculation mode considers the influence of the equipment layout outside the spacecraft cabin, irregular shapes, metal obstacles and the like on the electromagnetic field environment, and is not only simple estimation. Therefore, the present invention can effectively predict the safety margin between the transmitting and receiving devices, compared to the prior art.
According to one scheme of the invention, the electric field distribution outside the spacecraft cabin is analyzed by utilizing a modeling simulation mode, and then the devices are identified to be positioned in the area with the electric field intensity exceeding the limit value, so that the real influence of the electric field of the high-power radio-frequency device on the spacecraft equipment can be judged. The porthole model is established according to the material and the structure of the porthole, and is simulated to obtain the electric field distribution of the high-power radio-frequency equipment entering the spacecraft cabin through the porthole, so that the real influence of the electric field of the high-power radio-frequency equipment on astronauts can be judged. The modeling simulation mode is not limited by a test site, and can reflect the real influence of an electric field generated by the high-power radio frequency on the spacecraft and the astronaut, so that the high-power radio frequency equipment is ensured not to generate electromagnetic interference on the spacecraft and the astronaut when in on-orbit work.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings needed in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings without creative efforts.
Fig. 1 is a flow chart schematically showing a method for analyzing electromagnetic compatibility of high-power radio frequency equipment in a manned spacecraft according to a first embodiment of the invention.
Detailed Description
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the embodiments will be briefly described below. It is obvious that the drawings in the following description are only some embodiments of the invention, and that for a person skilled in the art, other drawings can be derived from them without inventive effort.
In describing embodiments of the present invention, the terms "longitudinal," "lateral," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like are used in an orientation or positional relationship that is based on the orientation or positional relationship shown in the associated drawings, which is for convenience and simplicity of description only, and does not indicate or imply that the referenced device or element must have a particular orientation, be constructed and operated in a particular orientation, and thus, the above-described terms should not be construed as limiting the present invention.
The present invention is described in detail below with reference to the drawings and the specific embodiments, which are not repeated herein, but the embodiments of the present invention are not limited to the following embodiments.
Fig. 1 is a flow chart schematically showing a method for analyzing electromagnetic compatibility of high-power radio frequency equipment in a manned spacecraft according to a first embodiment of the invention. As shown in fig. 1, the analysis method of the present invention first analyzes the frequency compatibility between the high-power rf device and all other wireless receiving devices in the manned spacecraft. The method mainly comprises two parts for judging, wherein one part is whether the fundamental wave of the high-power transmitting equipment or the second harmonic and the third harmonic thereof directly fall into the frequency bands of other radio frequency receiving equipment; and the second is whether the high-power radio frequency equipment is linearly combined with other transmitting frequency points to generate a new frequency point and the new frequency point falls into a receiving frequency band of the radio frequency equipment. In the following, three radio frequency devices in the manned spacecraft are taken as an example for explanation, and the three radio frequency devices are respectively a high-power radio frequency device D, a low-power transmitting device P and a radio frequency receiving device S. Setting the transmitting frequency of the high-power radio frequency equipment D as fd, the second harmonic and the third harmonic as 2fd and 3fd respectively, and the bandwidth as Bd; the transmitting frequency of the low-power transmitting equipment P is fp and the bandwidth Bp is; and the receiving frequency of the radio frequency receiving device S is fs and the bandwidth Bs. Firstly, whether the fundamental wave fd, the second harmonic wave 2fd, and the third harmonic wave 3fd of the high-power RF device D directly fall into the bandwidth fs + -Bs of the RF receiving device S is determined. Then, it is determined whether the linear combination frequency mfd + nfp of the high power RF device D and the low power transmitting device P falls within the frequency width fs + -Bs of the RF receiving device S. And, the frequency compatibility analysis traverses all radio reception frequency bands. The steps are utilized to judge the frequency compatibility, so that whether the interference signals generated by the high-power radio frequency equipment fall into other receiving passbands of the manned spacecraft can be effectively judged.
After the frequency compatibility analysis is completed, if the interference signal generated by the high-power radio frequency device actually falls into the passband of the receiving device, the signal strength from the high-power receiving device to the receiving device needs to be calculated, so that the safety margin is obtained. Firstly, an electromagnetic compatibility three-dimensional simulation model (namely an electromagnetic compatibility three-dimensional simulation model) is established based on a manned spacecraft three-dimensional model and an antenna three-dimensional directional diagram and according to the actual configuration of the manned spacecraft. The antenna of the high-power radio frequency equipment and the antennas of other radio frequency receiving equipment are placed according to the actual installation position in the spacecraft, so that the established three-dimensional simulation model is ensured to have real electromagnetic characteristics. And based on the established electromagnetic compatibility three-dimensional model, establishing a coupling equation between each equipment antenna and the spacecraft carrier by adopting a physical optical method (PO) in an electromagnetic field high-frequency calculation method. And obtaining the actual radiation characteristic of the antenna directional diagram of the high-power transmitting equipment after the antenna directional diagram is influenced by factors such as reflection and diffraction of the spacecraft cabin, and further obtaining the antenna isolation numerical value between the high-power radio-frequency radiation source and each radio-frequency receiving source. And then, the signal strength from the high-power radio frequency equipment to the radio frequency receiving equipment is calculated according to the transmitting power of the high-power radio frequency equipment, the out-of-band rejection value of the receiving equipment and the isolation degree. In order to ensure the accuracy of the obtained signal strength, the out-of-band rejection value of the high-power radio frequency equipment can be considered during calculation. And then, comparing the signal intensity with the sensitivity of the radio frequency receiving equipment, calculating the safety margin (namely the attenuation amount of the signal) between the high-power radio frequency equipment and each radio frequency receiving equipment, and confirming whether the obtained safety margin meets the index requirement. In order to improve the accuracy of safety margin analysis, the out-of-band inhibition value adopts an actual measurement result, and each receiving frequency band is actually measured. Therefore, the safety margin of the invention fully considers the influence of the layout of equipment outside the spacecraft cabin, irregular shapes, metal obstacles and the like on the electromagnetic field environment, and not only carries out simple estimation. Therefore, the present invention can effectively predict the safety margin between the transmitting and receiving devices, compared to the prior art.
After the safety margin is analyzed, simulation analysis is carried out on the electric field intensity distribution condition of the high-power radio frequency equipment on the whole spacecraft cabin body, and whether the electric field generated by the high-power radio frequency equipment influences the extravehicular layout electronic equipment and the spaceman working area in the sealed cabin is confirmed. In order to reflect the real electric field intensity of the high-power radio-frequency equipment, the simulation model of the electric field intensity radiation distribution is established based on the manned spacecraft cabin model and the three-dimensional directional diagram model of the high-power radio-frequency equipment. Then the spacecraft cabin is divided into a plurality of areas from near to far by taking the high-power radio frequency equipment as a center. And finally, establishing an electromagnetic field equation between the high-power transmitting antenna and the spacecraft carrier by adopting a physical optical calculation method, and obtaining an electric field intensity distribution diagram of the high-power radio frequency equipment through simulation calculation.
After the electric field intensity distribution map is obtained, the electric field intensity of which region in the spacecraft cabin body exceeds the limit value can be judged according to the electric field intensity distribution map and the regions divided into the cabin body, and then the devices in the regions with the electric field intensity exceeding the limit value can be determined. And then judging whether the devices are interfered by the electromagnetic interference of the high-power radio frequency equipment. Generally speaking, the device working with the high-power radio frequency device is interfered by the electromagnetism of the device, so that corresponding electromagnetic protection measures are taken for the device working with the high-power radio frequency device. Therefore, the electric field intensity distribution diagram obtained through modeling simulation reflects electric field radiation generated by real transmitting power of the high-power radio-frequency equipment, and the transmitting power does not need to be reduced like a ground test, so that the accuracy of analysis is ensured, and the equipment outside the spacecraft cabin is effectively protected from electromagnetic interference of the high-power radio-frequency equipment.
Because the spacecraft cabin shell has a good shielding effect, an electric field generated by the high-power radio frequency equipment cannot penetrate through the cabin shell to enter the cabin. The porthole which is a non-ideal metal conductor can cause the electric field generated by the high-power radio frequency equipment to leak into the cabin. Therefore, simulation analysis is carried out on the porthole, and the electric field intensity of the high-power radio frequency equipment transmitted from the porthole to the cabin is judged. Firstly, in the spacecraft cabin model, a porthole model is established according to the material property and the structure of the porthole, and is simulated by adopting a multilayer fast multipole (MLFMM) algorithm in an electromagnetic field moment method (MOM), so that the electric field distribution condition of high-power radio-frequency equipment leaking into the cabin through the porthole is obtained. Therefore, the real influence of the electric field generated by the high-power radio frequency equipment on the astronaut in the cabin can be judged, and the astronaut can be effectively protected from being interfered by the electromagnetism generated by the high-power radio frequency equipment.
The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents, improvements and the like that fall within the spirit and principle of the present invention are intended to be included therein.
Claims (9)
1. A method for analyzing electromagnetic compatibility of high-power radio frequency equipment in a manned spacecraft is characterized by comprising the following steps:
a. determining whether the frequency of the high-power radio frequency equipment and the linear combination frequency of the high-power radio frequency equipment and other radio frequency equipment fall into the bandwidth of the radio frequency receiving equipment or not;
b. establishing an electromagnetic compatibility three-dimensional simulation model of the high-power radio-frequency equipment, and establishing a coupling equation between each equipment antenna and a spacecraft carrier based on the model to obtain the isolation between each high-power radio-frequency equipment antenna and each radio-frequency receiving equipment antenna;
c. calculating the signal intensity from the high-power radio frequency equipment to the radio frequency receiving equipment according to the transmitting power of the high-power radio frequency equipment, the out-of-band rejection value of the receiving equipment and the isolation degree;
d. comparing the signal intensity with the sensitivity of the radio frequency receiving equipment, and calculating the safety margin between the high-power radio frequency equipment and each radio frequency receiving equipment;
e. establishing a simulation model of electric field intensity radiation distribution based on a manned spacecraft cabin model and a high-power radio-frequency equipment three-dimensional directional diagram model;
f. dividing a spacecraft cabin into a plurality of areas by taking high-power radio frequency equipment as a center, and establishing an electromagnetic field equation between an antenna of the high-power radio frequency equipment and a spacecraft carrier;
g. and obtaining an electric field intensity distribution diagram of the high-power radio frequency equipment through simulation calculation, and respectively judging the influence of the electric field of the high-power radio frequency equipment on equipment outside the spacecraft cabin and personnel in the spacecraft cabin.
2. The method according to claim 1, wherein in step (a), the frequencies of the high power RF devices include the frequencies of fundamental and second and third harmonics.
3. The method according to claim 1, wherein in step (b), the electromagnetic compatibility three-dimensional simulation model is established based on a manned spacecraft three-dimensional model and an antenna three-dimensional directional pattern according to the actual configuration of the manned spacecraft;
the antenna of the high-power radio frequency equipment and the antennas of other radio frequency receiving equipment are placed according to the actual installation position in the spacecraft.
4. The method for analyzing electromagnetic compatibility of high-power radio frequency equipment in manned spacecraft according to claim 1, wherein in the step (b), the coupling equation is established by a physical optics method in an electromagnetic field high-frequency calculation method.
5. The method according to claim 1, wherein in step (c), the out-of-band rejection value is measured and the actual measurement is performed for each received frequency band.
6. The method according to claim 1, wherein in step (f), the electromagnetic field equation is established by a physical-optical calculation method.
7. The method according to claim 1, wherein in step (g), the area outside the cabin exceeding the limit value is determined according to the electric field intensity distribution map, and whether the devices in the area and the high-power radio frequency devices work simultaneously is determined.
8. The method for analyzing electromagnetic compatibility of high-power radio-frequency equipment in a manned spacecraft according to claim 1, wherein in the step (e), a porthole model in the spacecraft cabin model is established according to materials and structures of portholes.
9. The method for analyzing the electromagnetic compatibility of the high-power radio-frequency equipment in the manned spacecraft according to the claim 1, wherein in the step (g), the distribution situation of the electric field intensity of the high-power radio-frequency equipment leaking into the spacecraft cabin is obtained by performing simulation calculation on the porthole by adopting a multilayer fast multipole algorithm in an electromagnetic field moment method.
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