CN111521882B - On-orbit calibration method and device for beam pointing error of deep space probe antenna - Google Patents

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

On-orbit calibration method and device for antenna beam pointing error of deep space probe

technical field

The invention relates to the technical field of deep space communication, in particular to an on-orbit calibration method of the antenna beam pointing error of a deep space probe and an on-orbit calibration device of the antenna beam pointing error of a deep space probe.

Background technique

In deep space exploration missions, the on-orbit calibration of antenna beam pointing errors faces severe challenges because the distance between satellites and the earth is very far, often reaching hundreds of millions of kilometers. The antenna calibration of CE-4 relay satellites that my country has achieved at the longest distance (about 450,000 kilometers) is done by remote control. In the antenna calibration of deep space exploration missions, due to the long distance of signal transmission, the traditional remote control is used. Mechanisms are difficult to implement.

In the related art, antenna calibration for deep space exploration tasks is mainly realized based on program control. However, during the detection process of the detector, the directional antenna has to go through a harsh environment for a long time and has many actions. Therefore, the antenna calibration method based on program control cannot accurately calibrate the antenna beam pointing error on-orbit.

SUMMARY OF THE INVENTION

The present invention aims to solve one of the technical problems in the related art at least to a certain extent. Therefore, the first objective of the present invention is to propose an on-orbit calibration method for the antenna beam pointing error of a deep space probe, which can accurately perform on-orbit calibration of the antenna beam pointing error.

The second object of the present invention is to provide an on-orbit calibration device for the beam pointing error of a deep space probe antenna.

In order to achieve the above object, the embodiment of the first aspect of the present invention proposes an on-orbit calibration method for the antenna beam pointing error of a deep space probe, including: obtaining the first method of a deep space probe without antenna beam pointing error through channel simulation. Downlink signal power; obtain the second downlink signal power of the deep space probe that actually has an antenna beam pointing error; estimate 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 a deep space probe according to the embodiment of the present invention, the first downlink signal power of the deep space probe without antenna beam pointing error is obtained through channel simulation, and the actual antenna beam pointing error is obtained. error of the second downlink signal power of the deep space probe, and the antenna beam pointing error is estimated according to the first downlink signal power and the second downlink signal power. In this way, the on-orbit calibration of the antenna beam pointing error can be accurately performed.

In addition, the on-orbit calibration method for the antenna beam pointing error of the deep space probe according to the embodiment of the present invention may also have the following additional technical features:

According to an embodiment of the present invention, obtaining the first downlink signal power of the deep space probe without antenna beam pointing error through channel simulation includes: receiving scene parameters and link parameters input by a user; according to the scene parameters Establish a simulation scenario for the communication between the deep space probe and the ground station, and calculate the signal transmission distance between the deep space probe and the ground station within the simulation period; calculate according to the link parameters and the signal transmission distance the first downlink signal power.

According to an embodiment of the present invention, the scene parameters include scene simulation time, orbital parameters of the deep space probe and the location of the ground station, and the link parameters include signal frequency, signal transmission of the deep space probe Power, transmit antenna gain of the deep space probe, receive 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 according to the signal frequency, the signal transmission distance and the speed of light loss; calculating the first downlink signal power according to the free space propagation loss, the signal transmit power, the transmit antenna gain, the receive antenna gain, the antenna polarization loss and the atmospheric loss.

According to an embodiment of the present invention, the estimating the antenna beam pointing error according to the first downlink signal power and the second downlink signal power includes: acquiring a difference between the second downlink signal power and the first downlink signal power The signal power difference between the two, and the signal power difference is smoothed and filtered; the mapping relationship function between the antenna beam pointing error and the antenna gain error is obtained; according to the signal power after smoothing filtering and the mapping relationship function The antenna beam pointing error is estimated.

In order to achieve the above purpose, an on-orbit calibration device for the antenna beam pointing error of a deep space probe proposed by the embodiment of the second aspect of the present invention includes: a channel simulation module, the channel simulation module is used to obtain the absence of an antenna through channel simulation. the first downlink signal power of the deep space probe with beam pointing error; an acquisition module, the acquisition module is used to acquire the second downlink signal power of the deep space probe with antenna beam pointing error actually; error estimation module, the The error estimation module is configured to estimate the 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 according to the embodiment of the present invention, the channel simulation module is used to perform channel simulation to obtain the first downlink signal power of the deep space probe without the antenna beam pointing error, and pass the channel simulation module. The acquisition module acquires the second downlink signal power of the deep space probe that actually has an antenna beam pointing error, and estimates the antenna beam pointing error according to the first downlink signal power and the second downlink signal power through the error estimation module. In this way, the on-orbit calibration of the antenna beam pointing error can be accurately performed.

In addition, the device for on-orbit calibration of the beam pointing error of a deep space probe antenna according to the embodiment of the present invention may also have the following additional technical features:

According to an embodiment of the present invention, the channel simulation module is specifically configured to: receive scene parameters and link parameters input by a user; establish a simulation scene of the communication between the deep space probe and the ground station according to the scene parameters, and calculate The signal transmission distance between the deep space probe and the ground station in the simulation period; the first downlink signal power is calculated according to the link parameter and the signal transmission distance.

According to an embodiment of the present invention, the scene parameters include scene simulation time, orbital parameters of the deep space probe and the location of the ground station, and the link parameters include signal frequency, signal transmission of the deep space probe Power, transmit antenna gain of the deep space probe, receive 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 configured to: calculate the free space propagation loss according to the signal frequency, the signal transmission distance and the speed of light; according to 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 to calculate the first downlink signal power.

According to an embodiment of the present invention, the error estimation module is specifically configured to: obtain a signal power difference between the second downlink signal power and the first downlink signal power, and calculate the signal power difference performing smoothing filtering processing; obtaining a mapping relationship function between the antenna beam pointing error and antenna gain error; and estimating the antenna beam pointing error according to the signal power after smooth filtering processing and the mapping relationship function.

Description of drawings

FIG. 1 is a flowchart of an on-orbit calibration method for a beam pointing error of a deep space probe antenna according to an embodiment of the present invention;

2 is a schematic structural diagram of a channel simulation module according to an embodiment of the present invention;

3 is a schematic diagram of the cooperative working mode of STK software and a module main program according to an embodiment of the present invention;

Fig. 4 is the amplitude-frequency response curve diagram of the smoothing filter according to a specific embodiment of the present invention;

5 is a schematic diagram of a mapping relationship between an antenna beam pointing error and an antenna gain error according to a specific embodiment of the present invention;

FIG. 6 is a schematic block diagram of an on-orbit calibration device for a beam pointing error of a deep space probe antenna according to an embodiment of the present invention.

Detailed ways

The following describes in detail the embodiments of the present invention, examples of which are illustrated in the accompanying drawings, wherein the same or similar reference numerals refer to the same or similar elements or elements having the same or similar functions throughout. The embodiments described below with reference to the accompanying drawings are exemplary, and are intended to explain the present invention and should not be construed as limiting the present invention.

The following describes an on-orbit calibration method for a beam pointing error of a deep space probe antenna and an on-orbit calibration device for a beam pointing error of a deep space probe antenna 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 a beam pointing error of a deep space probe antenna according to an embodiment of the present invention. As shown in FIG. 1 , the on-orbit calibration method for the beam pointing error of a deep space probe antenna according to an embodiment of the present invention includes the following steps:

S1, the first downlink signal power of the deep space probe without antenna beam pointing error is obtained through channel simulation.

According to an embodiment of the present invention, obtaining the first downlink signal power of a deep space probe without antenna beam pointing error through channel simulation includes: receiving scene parameters and link parameters input by a user; establishing a deep space probe according to the scene parameters The simulation scenario of the communication between the probe and the ground station is calculated, and the signal transmission distance between the deep space probe and the ground station in the simulation period is calculated; the first downlink signal power is calculated according to the link parameters and the signal transmission distance.

According to an embodiment of the present invention, the scene parameters include the scene simulation time, the orbit parameters of the deep space probe and the position of the ground station, and the link parameters include the signal frequency, the signal transmission power of the deep space probe, and the transmission of the deep space probe. Antenna gain, receive antenna gain at ground station, antenna polarization loss and atmospheric loss.

According to an embodiment of the present invention, calculating the first downlink signal power according to the link parameters and the signal transmission distance includes: calculating the free space propagation loss according to the signal frequency, the signal transmission distance, and the speed of light; according to the free space propagation loss, signal transmission power, The transmit antenna gain, receive antenna gain, antenna polarization loss and atmospheric loss calculate the first downlink signal power.

Specifically, the channel simulation module can be used to simulate the communication channel between the deep space probe and the ground station, and calculate the first downlink signal power of the deep space probe without antenna beam pointing error. Among them, as shown in Figure 2, the construction of the channel simulation module is based on the track simulation software and the main program of the module.

Among them, STK software can be used as the track simulation software, and the Microsoft Visual C++ MFC development platform can be used as the development software of the main program of the module. The main program of the module is responsible for user parameter input, link calculation, etc.; STK software assists the main program of the module to build a simulation scene and calculate the signal transmission distance. As shown in Figure 3, the main program of the module and the STK software work together through the connect command. The main program of the module transmits the scene parameters to the STK software, and establishes a simulation scene on the STK software; during the simulation process, the main program of the module obtains the data The command is transmitted to the STK software, and the STK software returns the corresponding data report after obtaining the command.

Specifically, the scene parameters and link parameters input by the user are received through the parameter input interface of the main program of the module, and the scene parameters are sent to the STK software through the interface, and the link parameters are used as the input parameters of the link calculation. After receiving the scene parameters, the STK software can establish a simulation scene for the communication between the deep space probe and the ground station according to the scene parameters, and calculate the signal transmission distance between the deep space probe and the ground station during the simulation period, and transmit the calculated signal. The distance is sent to the module main program as an input parameter for the link calculation. The main program of the module calculates the downlink signal power of the probe received by the ground station, that is, the first downlink signal power, according to the link parameters and the signal transmission distance between the deep space probe and the ground station.

The following describes in detail 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 considers free space loss, antenna polarization loss, and atmospheric loss. First, the free-space propagation loss can be generated by the following formula according to the signal frequency (the carrier frequency of the downlink signal of the deep space probe), the signal transmission distance, and the speed of light:

Among them, f is the signal frequency, d is the signal transmission distance, c is the speed of light, and L _f is the free space propagation loss.

λ为信号波长，因此，还可根据信号波长和信号传输距离计算自由空间传播损耗。in,

λ is the signal wavelength, therefore, the free space propagation loss can also be calculated according to the signal wavelength and the signal transmission distance.

Further, the first downlink signal power can be generated by the following formula according to free space propagation loss, signal transmission power, transmit antenna gain, receive antenna gain, antenna polarization loss and atmospheric loss:

Among them, P _t is the signal transmission power; G _t is the transmit antenna gain; G _r is the receive antenna gain; Δ ₁ is the antenna polarization loss; Δ ₂ is the atmospheric loss; S _sim is the first downlink signal power.

S2, acquiring the second downlink signal power of the deep space probe that actually has an antenna beam pointing error.

S3, estimate 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 according to the first downlink signal power and the second downlink signal power includes: acquiring a signal power difference between the second downlink signal power and the first downlink signal power, and The signal power difference is smoothed and filtered; the mapping function between the antenna beam pointing error and the antenna gain error is obtained; the antenna pointing angle error is estimated according to the signal power difference and the mapping function after smoothing filtering.

Specifically, after acquiring the power of the first downlink signal and the power of the second downlink signal, acquire the signal power difference between the power of the second downlink signal and the power of the first downlink signal, and analyze the signal power for the signal. The power difference is smoothed and filtered, that is,

S _filt =h*(S _rec -S _sim ),

Wherein, S _rec is the second downlink signal power; S _sim is the first downlink signal power; h is the impulse response function of the smoothing filter; S _filt is the signal power after smoothing and filtering.

Among them, the time-domain impulse response function of the smoothing filter used can be:

Among them, T is the filtering period of the smoothing filter.

It should be noted that the second downlink signal power of the deep space probe that actually has antenna beam pointing error will introduce noise due to antenna pointing jitter or measurement error. As shown in the amplitude-frequency response curve in Figure 4, the smoothing filter In fact, it is equivalent to a low-pass filter, which filters out the noise caused by the high-frequency jitter of the signal, thereby estimating the signal power difference without antenna pointing jitter or measurement error. in,

S _filt =h*(S _rec -S _sim )=h*(S _bias +NS _sim )≈S _bias -S _sim

Among them, N is the noise introduced by antenna pointing jitter or measurement error, and S _bias is the downlink signal power of the depth detector without antenna pointing jitter or measurement error.

Further, according to the pre-measured gain of the antenna of the deep space probe under each angle error, the gain difference between each angle error and no angle error can be obtained, and its expression is:

G(θ)=G ₀ (θ)-G ₀ (0),

Among them, θ is the antenna beam pointing error (antenna pointing error angle); G ₀ (θ) is the gain of the antenna at different pointing error angles, and G(θ) is the gain error of the antenna at different pointing error angles.

Further, the mapping function of the antenna beam pointing error determined by the gain error is:

θ(G)=[G(θ)] ⁻¹ ,

Among them, Figure 5 shows the typical mutual mapping relationship between the antenna beam pointing error and the antenna gain error. It is easy to know from the aforementioned link calculation formula:

S _bias -S _sim =G ₀ (θ)-G ₀ (0)=G(θ)

Therefore, the antenna beam pointing error obtained by calibration is:

θ=θ[h*(S _rec - S _sim )].

To sum up, the present invention calculates the first downlink signal power of the deep space probe without antenna beam pointing error through the channel simulation module, and receives the second downlink signal power of the deep space probe with actual antenna beam pointing error, The difference between the two signal powers is smoothed and filtered, and the antenna pointing error of the detector is finally estimated according to the mapping function between the antenna beam pointing error and the antenna gain error and the signal power after smoothing filtering. Among them, the channel simulation module is built based on the main program of the module and the orbit simulation software. The main program of the module completes the input of channel parameters and link calculation, and the orbit simulation software completes the construction of the simulation scene and the calculation of the signal transmission distance.

According to the on-orbit calibration method for the antenna beam pointing error of a deep space probe according to the embodiment of the present invention, the first downlink signal power of the deep space probe without antenna beam pointing error is obtained through channel simulation, and the actual antenna beam pointing error is obtained. error of the second downlink signal power of the deep space probe, and the antenna beam pointing error is estimated according to the first downlink signal power and the second downlink signal power. In this way, the on-orbit calibration of the antenna beam pointing error can be accurately performed.

FIG. 6 is a schematic block diagram of an on-orbit calibration device for a beam pointing error of a deep space probe antenna according to an embodiment of the present invention. As shown in FIG. 6 , the device for on-orbit calibration of the antenna beam pointing error of the deep space probe 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 used to obtain the first downlink signal power of the deep space probe without antenna beam pointing error through channel simulation; the acquisition module 200 is used to obtain the first downlink signal power of the deep space probe with actual antenna beam pointing error. 2. Downlink signal power; the error estimation module 300 is configured to estimate 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, the channel simulation module 100 is specifically configured to: receive scene parameters and link parameters input by the user; establish a simulation scene of communication between the deep space probe and the ground station according to the scene parameters, and calculate the relationship between the deep space probe and the ground station. The signal transmission distance of the ground station in the simulation period; the first downlink signal power is calculated according to the link parameters and the signal transmission distance.

According to an embodiment of the present invention, the scene parameters include the scene simulation time, the orbit parameters of the deep space probe and the position of the ground station, and the link parameters include the signal frequency, the signal transmission power of the deep space probe, and the transmission of the deep space probe. Antenna gain, receive antenna gain at ground station, antenna polarization loss and atmospheric loss.

According to an embodiment of the present invention, the channel simulation module 100 is further configured to: calculate the free space propagation loss according to the signal frequency, the signal transmission distance and the speed of light; according to the free space propagation loss, signal transmission power, transmit antenna gain, receive antenna gain, The first downlink signal power is calculated from the antenna polarization loss and atmospheric loss.

According to an embodiment of the present invention, the error estimation module 300 is specifically configured to: obtain the signal power difference between the second downlink signal power and the first downlink signal power, and perform smooth filtering processing on the signal power difference; obtain the antenna The mapping relationship function between the beam pointing error and the antenna gain error; the antenna beam pointing error is estimated according to the signal power after smooth filtering and the mapping relationship function.

It should be noted that, for details that are not disclosed in the on-orbit calibration device for the beam pointing error of the deep space probe antenna according to the embodiment of the present invention, please refer to the method for on-orbit calibration of the beam pointing error of the deep space probe antenna according to the embodiment of the present invention. The disclosed details will not be described in detail here.

According to the on-orbit calibration device for the antenna beam pointing error of the deep space probe according to the embodiment of the present invention, the channel simulation module is used to perform channel simulation to obtain the first downlink signal power of the deep space probe without the antenna beam pointing error, and pass the channel simulation module. The acquisition module acquires the second downlink signal power of the deep space probe that actually has an antenna beam pointing error, and estimates the antenna beam pointing error according to the first downlink signal power and the second downlink signal power through the error estimation module. In this way, the on-orbit calibration of the antenna beam pointing error can be accurately performed.

It should be understood that various parts of the present invention may be implemented in hardware, software, firmware or a combination thereof. In the above-described embodiments, 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, it can be implemented by any one or a combination of the following techniques known in the art: Discrete logic circuits, application specific integrated circuits with suitable combinational logic gates, Programmable Gate Arrays (PGA), Field Programmable Gate Arrays (FPGA), etc.

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” and other indicated orientations or positional relationships are based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the indicated device or element must have a specific orientation, construction and operation in a particular orientation, and therefore should not be construed as a limitation of the present invention.

In addition, the terms "first" and "second" are only used for descriptive purposes, and should not be construed as indicating or implying relative importance or implying the number of indicated technical features. Thus, a feature delimited with "first", "second" may expressly or implicitly include at least one of that feature. In the description of the present invention, "plurality" means at least two, such as two, three, etc., unless otherwise expressly and specifically defined.

In the present invention, unless otherwise expressly specified and limited, the terms "installed", "connected", "connected", "fixed" and other terms should be understood in a broad sense, for example, it may be a fixed connection or a detachable connection , or integrated; it can be a mechanical connection or an electrical connection; it can be directly connected or indirectly connected through an intermediate medium, it can be the internal connection of two elements or the interaction relationship between the two elements, unless otherwise specified limit. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to specific situations.

In the present invention, unless otherwise expressly specified and limited, a first feature "on" or "under" a second feature may be in direct contact between the first and second features, or the first and second features indirectly through an intermediary touch. Also, the first feature being "above", "over" and "above" the second feature may mean that the first feature is directly above or obliquely above the second feature, or simply means that the first feature is level higher than the second feature. The first feature being "below", "below" and "below" the second feature may mean that the first feature is directly below or obliquely below the second feature, or simply means that the first feature has a lower level than the second feature.

In the description of this specification, description with reference to the terms "one embodiment," "some embodiments," "example," "specific example," or "some examples", etc., mean specific features described in connection with the embodiment or example , structure, material or feature is included in at least one embodiment or example of the present invention. In this specification, schematic representations of the above terms are not necessarily directed 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, those skilled in the art may combine and combine the different embodiments or examples described in this specification, as well as the features of the different embodiments or examples, without conflicting each other.

Although the embodiments of the present invention have been shown and described above, it should be understood that the above-mentioned embodiments are exemplary and should not be construed as limiting the present invention. Embodiments are subject to variations, modifications, substitutions and variations.

Claims (6)

1. an on-orbit calibration method of a deep space probe antenna beam pointing error, is characterized in that, comprising: The first downlink signal power of the deep space probe without antenna beam pointing error is obtained through channel simulation, wherein the scene parameters and link parameters input by the user are received, and the deep space probe and the ground are established according to the scene parameters. The simulation scenario of station communication is calculated, and the signal transmission distance between the deep space probe and the ground station within the simulation period is calculated, and the first downlink signal power is calculated according to the link parameter and the signal transmission distance; Obtain the second downlink signal power of the deep space probe that actually has an antenna beam pointing error; The antenna beam pointing error is estimated according to the first downlink signal power and the second downlink signal power, wherein the signal power difference between the second downlink signal power and the first downlink signal power is obtained, and the The signal power difference is smoothed and filtered to obtain a mapping relationship function between the antenna beam pointing error and the antenna gain error, and the antenna beam pointing error is estimated according to the smoothed filtered signal power and the mapping relationship function. 2. The on-orbit calibration method of the antenna beam pointing error of a deep space probe according to claim 1, wherein the scene parameters include scene simulation time, orbital parameters of the deep space probe and the position of the ground station , the The link parameters include signal frequency, signal transmit power of the deep space probe, transmit antenna gain of the deep space probe, receive antenna gain of the ground station, antenna polarization loss, and atmospheric loss. 3 . The on-orbit calibration method for antenna beam pointing error of a deep space probe according to claim 2 , wherein the first downlink signal power is calculated according to the link parameter and the signal transmission distance. 4 . include: Calculate the free space propagation loss according to the signal frequency, the signal transmission distance and the speed of light; according to the free space propagation loss, the signal transmit power, the transmit antenna gain, the receive antenna gain, and the antenna polarization The loss and the atmospheric loss calculate the first downlink signal power. 4. An on-orbit calibration device for a beam pointing error of a deep space probe antenna is characterized in that, comprising: A channel simulation module, the channel simulation module is used to obtain the first downlink signal power of the deep space probe without antenna beam pointing error through channel simulation, wherein the scene parameters and link parameters input by the user are received, according to the Scenario parameters establish a simulation scenario for the communication between the deep space probe and the ground station, and calculate the signal transmission distance between the deep space probe and the ground station within the simulation period, according to the link parameters and the signal transmission distance Calculate the power of the first downlink signal from the distance; an acquisition module, which is used to acquire the second downlink signal power of the deep space probe that actually has an antenna beam pointing error; an error estimation module, the error estimation module is configured to estimate the antenna beam pointing error according to the first downlink signal power and the second downlink signal power, wherein the second downlink signal power and the first downlink signal power are obtained The signal power difference between the two, and the signal power difference is smoothed and filtered to obtain the mapping relationship function between the antenna beam pointing error and the antenna gain error. According to the signal power after smoothing filtering and the mapping relationship function estimates the antenna beam pointing error. 5. The on-orbit calibration device of deep space probe antenna beam pointing error according to claim 4, is characterized in that, The scene parameters include the scene simulation time, the orbital parameters of the deep space probe and the position of the ground station, and the link parameters include the signal frequency, the signal transmission power of the deep space probe, the deep space probe The transmit antenna gain of the ground station, the receive antenna gain of the ground station, the antenna polarization loss and the atmospheric loss. 6. The on-orbit calibration device of the antenna beam pointing error of a deep space probe according to claim 5, wherein the channel simulation module is specifically also used for: Calculate free space propagation loss according to the signal frequency, the signal transmission distance and the speed of light; The first downlink signal power is calculated according to 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.

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