CN111521882B - On-orbit calibration method and device for beam pointing error of deep space probe antenna - Google Patents
On-orbit calibration method and device for beam pointing error of deep space probe antenna Download PDFInfo
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Abstract
The invention discloses an on-orbit calibration method for antenna beam pointing errors of a deep space probe, which comprises the following steps: obtaining a first downlink signal power of the deep space probe without antenna beam pointing error through channel simulation; acquiring second downlink signal power of the deep space probe with antenna beam pointing error; and estimating the antenna beam pointing error according to the first downlink signal power and the second downlink signal power. According to the in-orbit calibration method for the antenna beam pointing error of the deep space probe, the in-orbit calibration can be accurately carried out on the antenna beam pointing error.
Description
Technical Field
The invention relates to the technical field of deep space communication, in particular to an on-orbit calibration method and an on-orbit calibration device for antenna beam pointing errors of a deep space probe.
Background
In deep space exploration tasks, the on-orbit calibration of the pointing error of the antenna beam faces a serious challenge because the satellite is far away from the earth, often hundreds of millions of kilometers. The antenna calibration of the CE-4 relay satellite realized in the farthest distance (about 45 kilometers) in China is completed by remote control, and in the antenna calibration of a deep space exploration task, the traditional remote control mechanism is difficult to realize due to the fact that the signal transmission distance is far.
In the related art, antenna calibration for deep space exploration tasks is mainly realized based on program control. However, in the detection process of the detector, the directional antenna is subjected to a long-time harsh environment and has multiple actions, so the antenna calibration method based on program control cannot accurately perform on-orbit calibration on the pointing error of the antenna beam.
Disclosure of Invention
The present invention is directed to solving, at least to some extent, one of the technical problems in the related art. Therefore, a first object of the present invention is to provide an in-orbit calibration method for antenna beam pointing errors of a deep space probe, which can accurately perform in-orbit calibration on the antenna beam pointing errors.
The second purpose of the invention is to provide an on-orbit calibration device for the beam pointing error of the deep space probe antenna.
In order to achieve the above object, an embodiment of a first aspect of the present invention provides an on-orbit calibration method for beam pointing errors of a deep space probe antenna, including: obtaining a first downlink signal power of the deep space probe without antenna beam pointing error through channel simulation; acquiring second downlink signal power of the deep space probe with antenna beam pointing error; and estimating the antenna beam pointing error according to the first downlink signal power and the second downlink signal power.
According to the on-orbit calibration method for the antenna beam pointing error of the deep space probe, the first downlink signal power of the deep space probe without the antenna beam pointing error is obtained through channel simulation, the second downlink signal power of the deep space probe with the antenna beam pointing error is obtained actually, and the antenna beam pointing error is estimated according to the first downlink signal power and the second downlink signal power. Therefore, the on-orbit calibration of the antenna beam pointing error can be accurately carried out.
In addition, the on-orbit calibration method for the beam pointing error of the deep space probe antenna according to the embodiment of the invention can also have the following additional technical characteristics:
according to an embodiment of the present invention, the obtaining, through channel simulation, the first downlink signal power of the deep space probe without antenna beam pointing error includes: receiving scene parameters and link parameters input by a user; establishing a simulation scene of communication between the deep space probe and a ground station according to the scene parameters, and calculating a signal transmission distance between the deep space probe and the ground station in a simulation time period; and calculating the first downlink signal power according to the link parameters and the signal transmission distance.
According to one embodiment of the invention, the scene parameters comprise scene simulation time, orbit parameters of the deep space probe and position of the ground station, and the link parameters comprise signal frequency, signal transmitting power of the deep space probe, transmitting antenna gain of the deep space probe, receiving antenna gain of the ground station, antenna polarization loss and atmospheric loss.
According to an embodiment of the present invention, the calculating the first downlink signal power according to the link parameter and the signal transmission distance includes: calculating free space propagation loss according to the signal frequency, the signal transmission distance and the light speed; calculating the first downlink signal power according to the free space propagation loss, the signal transmission power, the transmitting antenna gain, the receiving antenna gain, the antenna polarization loss and the atmospheric loss.
According to an embodiment of the present invention, the estimating an antenna beam pointing error according to the first downlink signal power and the second downlink signal power includes: acquiring a signal power difference value between the second downlink signal power and the first downlink signal power, and performing smooth filtering processing on the signal power difference value; acquiring a mapping relation function of the antenna beam pointing error and the antenna gain error; and estimating the antenna beam pointing error according to the signal power after the smoothing filtering processing and the mapping relation function.
In order to achieve the above object, an in-orbit calibration apparatus for beam pointing error of a deep space probe antenna according to an embodiment of a second aspect of the present invention includes: the channel simulation module is used for obtaining the first downlink signal power of the deep space probe without antenna beam pointing error through channel simulation; the acquisition module is used for acquiring the second downlink signal power of the deep space probe with the actual antenna beam pointing error; an error estimation module, configured to estimate an antenna beam pointing error according to the first downlink signal power and the second downlink signal power.
According to the on-orbit calibration device for the antenna beam pointing error of the deep space probe, channel simulation is carried out through the channel simulation module to obtain the first downlink signal power of the deep space probe without the antenna beam pointing error, the second downlink signal power of the deep space probe with the antenna beam pointing error is obtained through the obtaining module, and the antenna beam pointing error is estimated through the error estimation module according to the first downlink signal power and the second downlink signal power. Therefore, the on-orbit calibration of the antenna beam pointing error can be accurately carried out.
In addition, the on-orbit calibration device for the beam pointing error of the deep space probe antenna according to the embodiment of the invention can also have the following additional technical characteristics:
according to an embodiment of the present invention, the channel simulation module is specifically configured to: receiving scene parameters and link parameters input by a user; establishing a simulation scene of communication between the deep space probe and a ground station according to the scene parameters, and calculating a signal transmission distance between the deep space probe and the ground station in a simulation time period; and calculating the first downlink signal power according to the link parameters and the signal transmission distance.
According to one embodiment of the invention, the scene parameters comprise scene simulation time, orbit parameters of the deep space probe and position of the ground station, and the link parameters comprise signal frequency, signal transmitting power of the deep space probe, transmitting antenna gain of the deep space probe, receiving antenna gain of the ground station, antenna polarization loss and atmospheric loss.
According to an embodiment of the present invention, the channel simulation module is further specifically configured to: calculating free space propagation loss according to the signal frequency, the signal transmission distance and the light speed; calculating the first downlink signal power according to the free space propagation loss, the signal transmission power, the transmitting antenna gain, the receiving antenna gain, the antenna polarization loss and the atmospheric loss.
According to an embodiment of the invention, the error estimation module is specifically configured to: acquiring a signal power difference value between the second downlink signal power and the first downlink signal power, and performing smooth filtering processing on the signal power difference value; acquiring a mapping relation function of the antenna beam pointing error and the antenna gain error; and estimating the antenna beam pointing error according to the signal power after the smoothing filtering processing and the mapping relation function.
Drawings
FIG. 1 is a flowchart of an in-orbit calibration method for beam pointing errors of an antenna of a deep space probe according to an embodiment of the invention;
FIG. 2 is a block diagram of a channel simulation module according to one embodiment of the present invention;
FIG. 3 is a schematic diagram of the manner in which STK software works in conjunction with the main program of a module, according to one embodiment of the present invention;
FIG. 4 is a graph of the magnitude-frequency response of a smoothing filter in accordance with one embodiment of the present invention;
FIG. 5 is a diagram illustrating a mapping relationship between antenna beam pointing error and antenna gain error according to an embodiment of the present invention;
fig. 6 is a block diagram of an on-orbit calibration apparatus for beam pointing error of a deep space probe antenna according to an embodiment of the present invention.
Detailed Description
Reference will now be made in detail to embodiments of the present invention, examples of which are illustrated in the accompanying drawings, wherein like or similar reference numerals refer to the same or similar elements or elements having the same or similar function throughout. The embodiments described below with reference to the drawings are illustrative and intended to be illustrative of the invention and are not to be construed as limiting the invention.
The following describes an on-orbit calibration method for deep space probe antenna beam pointing errors and an on-orbit calibration device for deep space probe antenna beam pointing errors according to embodiments of the present invention with reference to the accompanying drawings.
Fig. 1 is a flowchart of an on-orbit calibration method for beam pointing errors of a deep space probe antenna according to an embodiment of the invention. As shown in fig. 1, the in-orbit calibration method for beam pointing error of deep space probe antenna according to the embodiment of the present invention includes the following steps:
and S1, obtaining the first downlink signal power of the deep space probe without the antenna beam pointing error through channel simulation.
According to an embodiment of the present invention, obtaining the first downlink signal power of the deep space probe without the antenna beam pointing error through channel simulation includes: receiving scene parameters and link parameters input by a user; establishing a simulation scene of communication between the deep space probe and the ground station according to the scene parameters, and calculating the signal transmission distance between the deep space probe and the ground station in a simulation period; and calculating the power of the first downlink signal according to the link parameter and the signal transmission distance.
According to one embodiment of the invention, the scene parameters comprise scene simulation time, orbit parameters of the deep space probe and position of the ground station, and the link parameters comprise signal frequency, signal transmitting power of the deep space probe, transmitting antenna gain of the deep space probe, receiving antenna gain of the ground station, antenna polarization loss and atmospheric loss.
According to one embodiment of the present invention, calculating the first downlink signal power according to the link parameter and the signal transmission distance includes: calculating free space propagation loss according to the signal frequency, the signal transmission distance and the light speed; and calculating the first downlink signal power according to the free space propagation loss, the signal transmitting power, the transmitting antenna gain, the receiving antenna gain, the antenna polarization loss and the atmospheric loss.
Specifically, the channel simulation module is responsible for simulating a communication channel between the deep space probe and the ground station, and calculating the first downlink signal power of the deep space probe without antenna beam pointing error. As shown in fig. 2, the channel simulation module is built based on track simulation software and a module main program.
The STK software can be used as track simulation software, and a Microsoft Visual C + + MFC development platform can be used as development software of a module main program. The main program of the module is responsible for user parameter input, link calculation and the like; and (4) the STK software auxiliary module main program builds a simulation scene and calculates the signal transmission distance. As shown in fig. 3, the module main program and the STK software perform cooperative work through a connect command, the module main program transmits scene parameters to the STK software, and a simulation scene is established on the STK software; in the simulation process, the module main program transmits a data acquisition command to the STK software, and the STK software returns a corresponding data report after acquiring the command.
Specifically, the scene parameters and the link parameters input by the user are received through a parameter input interface of the module main program, the scene parameters are sent to the STK software through an interface, and the link parameters are used as input parameters of link calculation. After receiving the scene parameters, the STK software can establish a simulation scene of communication between the deep space probe and the ground station according to the scene parameters, calculate the signal transmission distance between the deep space probe and the ground station in a simulation period, and send the calculated signal transmission distance to the module main program to be used as an input parameter of link calculation. And the module main program calculates the downlink signal power of the detector received by the ground station, namely the first downlink signal power, according to the link parameters and the signal transmission distance between the deep space detector and the ground station.
The following describes how to calculate the first downlink signal power according to the link parameters and the signal transmission distance between the deep space probe and the ground station.
Specifically, the link calculation mainly takes into account free space loss, antenna polarization loss, and atmospheric loss. First, the free-space propagation loss can be generated according to the signal frequency (carrier frequency of the down-going signal of the deep space probe), the signal transmission distance, and the speed of light by the following formula:
wherein f is the signal frequency, d is the signal transmission distance, c is the speed of light, LfIs a free space propagation loss.
Wherein,
λ is the signal wavelength, and therefore, the free-space propagation loss can also be calculated from the signal wavelength and the signal transmission distance.
Further, the first downlink signal power may be generated from the free-space propagation loss, the signal transmission power, the transmit antenna gain, the receive antenna gain, the antenna polarization loss, and the atmospheric loss by the following equation:
wherein, PtTransmitting power for the signal; gtGain for the transmit antenna; grGain for the receive antenna; delta1Is the antenna polarization loss; delta2Atmospheric losses; ssimIs the first downlink signal power.
And S2, acquiring the second downlink signal power of the deep space probe with the actual antenna beam pointing error.
And S3, estimating the antenna beam pointing error according to the first downlink signal power and the second downlink signal power.
According to an embodiment of the present invention, estimating the antenna beam pointing error based on the first downlink signal power and the second downlink signal power comprises: acquiring a signal power difference value between the power of the second downlink signal and the power of the first downlink signal, and performing smooth filtering processing on the signal power difference value; acquiring a mapping relation function of the antenna beam pointing error and the antenna gain error; and estimating the antenna pointing angle error according to the signal power difference value after the smoothing filtering processing and the mapping relation function.
Specifically, after acquiring a first downlink signal power and a second downlink signal power, acquiring a signal power difference between the second downlink signal power and the first downlink signal power, and performing a smoothing filtering process on the signal power difference, that is,
Sfilt＝h*(Srec-Ssim)，
wherein S isrecIs the second downlink signal power; ssimIs the first downlink signal power; h is the impulse response function of the smoothing filter; sfiltIs the smoothed filtered signal power.
The time domain impulse response function of the adopted smoothing filter can be as follows:
where T is the filter period of the smoothing filter.
It should be noted that, the second downlink signal power of the deep space probe in which the antenna beam pointing error actually exists may introduce noise due to jitter of the antenna pointing direction or the measurement error, and as shown in the amplitude-frequency response curve of fig. 4, the smoothing filter is actually equivalent to a low-pass filter, and may filter the noise caused by the high-frequency jitter of the signal, so as to estimate the signal power difference value without the antenna pointing jitter or the measurement error. Wherein,
Sfilt＝h*(Srec-Ssim)＝h*(Sbias+N-Ssim)≈Sbias-Ssim
wherein N is noise introduced by antenna directional jitter or measurement error, SbiasThe power of the downlink signal of the depth detector under the condition that the antenna pointing jitter or the measurement error does not exist.
Further, according to the gain of the antenna of the deep space probe under each angle error measured in advance, the gain difference between each angle error and the gain without the angle error can be obtained, and the expression is as follows:
G(θ)＝G0(θ)-G0(0)，
wherein θ is an antenna beam pointing error (antenna pointing error angle); g0And (theta) is the gain of the different pointing error angles of the antenna, and G (theta) is the gain error of the different pointing error angles of the antenna.
Further, the mapping relation function for determining the antenna beam pointing error by the gain error is as follows:
θ(G)＝[G(θ)]-1，
fig. 5 shows a typical mapping relationship between antenna beam pointing error and antenna gain error. As is apparent from the foregoing link calculation equation:
Sbias-Ssim＝G0(θ)-G0(0)＝G(θ)
therefore, the antenna beam pointing error obtained by calibration is:
θ＝θ[h*(Srec-Ssim)]。
in summary, the present invention calculates the first downlink signal power of the deep space probe without the antenna beam pointing error through the channel simulation module, receives the second downlink signal power of the deep space probe with the antenna beam pointing error, performs the smoothing filtering on the difference between the two signal powers, and finally estimates the antenna pointing error of the probe according to the mapping relation function between the antenna beam pointing error and the antenna gain error and the signal power after the smoothing filtering processing. The channel simulation module is built based on a module main program and track simulation software, the module main program completes channel parameter input and link calculation, and the track simulation software completes simulation scene construction and signal transmission distance calculation.
According to the on-orbit calibration method for the antenna beam pointing error of the deep space probe, the first downlink signal power of the deep space probe without the antenna beam pointing error is obtained through channel simulation, the second downlink signal power of the deep space probe with the antenna beam pointing error is obtained actually, and the antenna beam pointing error is estimated according to the first downlink signal power and the second downlink signal power. Therefore, the on-orbit calibration of the antenna beam pointing error can be accurately carried out.
Fig. 6 is a block diagram of an on-orbit calibration apparatus for beam pointing error of a deep space probe antenna according to an embodiment of the present invention. As shown in fig. 6, the on-orbit calibration apparatus for beam pointing error of deep space probe antenna according to the embodiment of the present invention may include: a channel simulation module 100, an acquisition module 200 and an error estimation module 300.
The channel simulation module 100 is configured to obtain, through channel simulation, a first downlink signal power of the deep space probe without an antenna beam pointing error; the obtaining module 200 is configured to obtain a second downlink signal power of the deep space probe where an antenna beam pointing error actually exists; the error estimation module 300 is configured to estimate an antenna beam pointing error according to the first downlink signal power and the second downlink signal power.
According to an embodiment of the present invention, the channel simulation module 100 is specifically configured to: receiving scene parameters and link parameters input by a user; establishing a simulation scene of communication between the deep space probe and the ground station according to the scene parameters, and calculating the signal transmission distance between the deep space probe and the ground station in a simulation period; and calculating the power of the first downlink signal according to the link parameter and the signal transmission distance.
According to one embodiment of the invention, the scene parameters comprise scene simulation time, orbit parameters of the deep space probe and position of the ground station, and the link parameters comprise signal frequency, signal transmitting power of the deep space probe, transmitting antenna gain of the deep space probe, receiving antenna gain of the ground station, antenna polarization loss and atmospheric loss.
According to an embodiment of the present invention, the channel simulation module 100 is further specifically configured to: calculating free space propagation loss according to the signal frequency, the signal transmission distance and the light speed; and calculating the first downlink signal power according to the free space propagation loss, the signal transmitting power, the transmitting antenna gain, the receiving antenna gain, the antenna polarization loss and the atmospheric loss.
According to an embodiment of the invention, the error estimation module 300 is specifically configured to: acquiring a signal power difference value between the power of the second downlink signal and the power of the first downlink signal, and performing smooth filtering processing on the signal power difference value; acquiring a mapping relation function of the antenna beam pointing error and the antenna gain error; and estimating the antenna beam pointing error according to the signal power after the smoothing filtering processing and the mapping relation function.
It should be noted that, for details that are not disclosed in the in-orbit calibration apparatus for beam pointing error of deep space probe antenna according to the embodiment of the present invention, please refer to details that are disclosed in the in-orbit calibration method for beam pointing error of deep space probe antenna according to the embodiment of the present invention, and detailed descriptions thereof are omitted here.
According to the on-orbit calibration device for the antenna beam pointing error of the deep space probe, channel simulation is carried out through the channel simulation module to obtain the first downlink signal power of the deep space probe without the antenna beam pointing error, the second downlink signal power of the deep space probe with the antenna beam pointing error is obtained through the obtaining module, and the antenna beam pointing error is estimated through the error estimation module according to the first downlink signal power and the second downlink signal power. Therefore, the on-orbit calibration of the antenna beam pointing error can be accurately carried out.
It should be understood that portions of the present invention may be implemented in hardware, software, firmware, or a combination thereof. In the above embodiments, the various steps or methods may be implemented in software or firmware stored in memory and executed by a suitable instruction execution system. For example, if implemented in hardware, as in another embodiment, any one or combination of the following techniques, which are known in the art, may be used: a discrete logic circuit having a logic gate circuit for implementing a logic function on a data signal, an application specific integrated circuit having an appropriate combinational logic gate circuit, a Programmable Gate Array (PGA), a Field Programmable Gate Array (FPGA), or the like.
In addition, in the description of the present invention, the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", "axial", "radial", "circumferential", etc. indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience of description and simplicity of description, but do not indicate or imply that the device or element referred to must have a particular orientation, be constructed in a particular orientation, and be operated, and thus, should not be construed as limiting the present invention.
Furthermore, the terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one such feature. In the description of the present invention, "a plurality" means at least two, e.g., two, three, etc., unless specifically limited otherwise.
In the present invention, unless otherwise expressly stated or limited, the terms "mounted," "connected," "secured," and the like are to be construed broadly and can, for example, be fixedly connected, detachably connected, or integrally formed; can be mechanically or electrically connected; they may be directly connected or indirectly connected through intervening media, or they may be connected internally or in any other suitable relationship, unless expressly stated otherwise. The specific meanings of the above terms in the present invention can be understood by those skilled in the art according to specific situations.
In the present invention, unless otherwise expressly stated or limited, the first feature "on" or "under" the second feature may be directly contacting the first and second features or indirectly contacting the first and second features through an intermediate. Also, a first feature "on," "over," and "above" a second feature may be directly or diagonally above the second feature, or may simply indicate that the first feature is at a higher level than the second feature. A first feature being "under," "below," and "beneath" a second feature may be directly under or obliquely under the first feature, or may simply mean that the first feature is at a lesser elevation than the second feature.
In the description herein, references to the description of the term "one embodiment," "some embodiments," "an example," "a specific example," or "some examples," etc., mean that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the invention. In this specification, the schematic representations of the terms used above are not necessarily intended to refer to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples. Furthermore, various embodiments or examples and features of different embodiments or examples described in this specification can be combined and combined by one skilled in the art without contradiction.
Although embodiments of the present invention have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting the present invention, and that variations, modifications, substitutions and alterations can be made to the above embodiments by those of ordinary skill in the art within the scope of the present invention.
Claims (6)
1. An on-orbit calibration method for beam pointing errors of a deep space probe antenna is characterized by comprising the following steps:
obtaining a first downlink signal power of a deep space probe without antenna beam pointing error through channel simulation, wherein a scene parameter and a link parameter input by a user are received, a simulation scene of communication between the deep space probe and a ground station is established according to the scene parameter, a signal transmission distance between the deep space probe and the ground station in a simulation time period is calculated, and the first downlink signal power is calculated according to the link parameter and the signal transmission distance;
acquiring second downlink signal power of the deep space probe with antenna beam pointing error;
estimating the antenna beam pointing error according to the first downlink signal power and the second downlink signal power, wherein a signal power difference value between the second downlink signal power and the first downlink signal power is obtained, smoothing filtering processing is performed on the signal power difference value, a mapping relation function of the antenna beam pointing error and an antenna gain error is obtained, and the antenna beam pointing error is estimated according to the signal power after smoothing filtering processing and the mapping relation function.
2. The on-orbit calibration method for the beam pointing error of the deep space probe antenna according to claim 1, wherein the scene parameters comprise scene simulation time, orbit parameters of the deep space probe and the position of the ground station, and the method comprises
The link parameters comprise signal frequency, signal transmitting power of the deep space probe, transmitting antenna gain of the deep space probe, receiving antenna gain of the ground station, antenna polarization loss and atmospheric loss.
3. The method for on-orbit calibration of beam pointing error of deep space probe according to claim 2, wherein the calculating the first downlink signal power according to the link parameter and the signal transmission distance comprises:
calculating free space propagation loss according to the signal frequency, the signal transmission distance and the light speed; calculating the first downlink signal power according to the free space propagation loss, the signal transmission power, the transmitting antenna gain, the receiving antenna gain, the antenna polarization loss and the atmospheric loss.
4. An on-orbit calibration device for beam pointing errors of a deep space probe antenna is characterized by comprising the following components:
the system comprises a channel simulation module, a channel selection module and a channel selection module, wherein the channel simulation module is used for obtaining a first downlink signal power of a deep space probe without antenna beam pointing errors through channel simulation, receiving scene parameters and link parameters input by a user, establishing a simulation scene of communication between the deep space probe and a ground station according to the scene parameters, calculating a signal transmission distance between the deep space probe and the ground station in a simulation time period, and calculating the first downlink signal power according to the link parameters and the signal transmission distance;
the acquisition module is used for acquiring the second downlink signal power of the deep space probe with the actual antenna beam pointing error;
and the error estimation module is used for estimating an antenna beam pointing error according to the first downlink signal power and the second downlink signal power, acquiring a signal power difference value between the second downlink signal power and the first downlink signal power, performing smooth filtering processing on the signal power difference value, acquiring a mapping relation function of the antenna beam pointing error and an antenna gain error, and estimating the antenna beam pointing error according to the signal power after the smooth filtering processing and the mapping relation function.
5. The on-orbit calibration device for beam pointing error of deep space probe antenna according to claim 4,
the scene parameters comprise scene simulation time, orbit parameters of the deep space probe and the position of the ground station, and the link parameters comprise signal frequency, signal transmitting power of the deep space probe, transmitting antenna gain of the deep space probe, receiving antenna gain of the ground station, antenna polarization loss and atmospheric loss.
6. The in-orbit calibration device for beam pointing errors of deep space probe antennas of claim 5, wherein the channel simulation module is further configured to:
calculating free space propagation loss according to the signal frequency, the signal transmission distance and the light speed;
calculating the first downlink signal power according to the free space propagation loss, the signal transmission power, the transmitting antenna gain, the receiving antenna gain, the antenna polarization loss and the atmospheric loss.
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| CN112162158B (en) * | 2020-09-03 | 2022-09-20 | 国家卫星气象中心(国家空间天气监测预警中心) | Method and device for evaluating pointing mismatch of antenna of on-orbit terahertz detector |
| CN112485757B (en) * | 2020-10-26 | 2022-06-28 | 国家卫星气象中心(国家空间天气监测预警中心) | On-orbit calibration method and system for antenna electric shaft of satellite-borne terahertz detector |
| CN112362080B (en) * | 2020-10-30 | 2021-12-24 | 中国人民解放军63921部队 | Spacecraft antenna on-orbit pointing calibration satellite-ground data synchronization deviation determination method |
| CN113156225B (en) * | 2021-04-25 | 2022-05-27 | 上海航天测控通信研究所 | Deep space high-gain antenna on-orbit pointing calibration method |
| CN115507880B (en) * | 2022-11-23 | 2023-05-02 | 中国人民解放军63921部队 | Method for calibrating on-orbit orientation of spacecraft antenna by using ground multiple antennas |
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