CN117014058A - Control method of space communication simulation system and space communication simulation system - Google Patents
Control method of space communication simulation system and space communication simulation system Download PDFInfo
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Abstract
The invention discloses a control method of a space communication simulation system and the space communication simulation system, wherein the control method of the space communication simulation system comprises the following steps: responding to a target probability distribution mode selected by a user, and acquiring a time setting parameter corresponding to the target probability distribution mode; acquiring register configuration parameters in the space communication simulation system according to the time setting parameters; controlling the space communication simulation system to work according to the register configuration parameters so that the space communication simulation system simulates data communication with the spacecraft; counting the successful communication times and the failed communication times of the space communication simulation system and the spacecraft under the configuration parameters of the register; and determining a simulation result of the space communication simulation system according to the communication success times and the communication failure times, wherein the simulation result is used for reflecting the robustness of the spacecraft communication link. The method can simulate the actual use scene of the spacecraft and complete the verification of the robustness of the communication link in the interference signal superposition scene.
Description
Technical Field
The present invention relates to the field of spatial communication simulation systems, and in particular, to a control method of a spatial communication simulation system and a spatial communication simulation system.
Background
In the related art, in order to match with high processing capability such as load switching agility of a multi-beam phased array of a spacecraft such as a tracking and data relay satellite system (Tracking and Data Relay Satellite System, TDRSS) and expandability of a return beam, a space communication simulation system needs to be established to provide a test and verification environment of ground continuous service and short message service. The communication link between the multiuser (aircraft or satellite) and the spacecraft has the characteristics of larger time delay and random access of the user under the TDRSS communication condition, and a space communication simulation system does not exist in the related technology to simulate the actual use scene of the spacecraft, so that the communication condition between the spacecraft and the multiuser under the TDRSS communication condition can not be simulated, and the verification of the robustness of the communication link under the interference signal superposition scene can not be completed.
Disclosure of Invention
The present invention aims to solve at least one of the technical problems existing in the prior art. Therefore, an object of the present invention is to provide a control method of a spatial communication simulation system, by which the actual use situation of a spacecraft can be simulated, and the verification of the robustness of a communication link in an interference signal superposition situation can be completed.
Another object of the present application is to provide a space communication simulation system.
In order to solve the above-mentioned problems, an embodiment of a first aspect of the present application provides a control method of a spatial communication simulation system for testing a communication link of a spacecraft, the control method comprising: responding to a target probability distribution mode selected by a user, and acquiring a time setting parameter corresponding to the target probability distribution mode; acquiring a register configuration parameter in the space communication simulation system according to the time setting parameter; controlling the space communication simulation system to work according to the register configuration parameters so that the space communication simulation system simulates data communication with the spacecraft; counting the successful communication times and the failed communication times of the space communication simulation system and the spacecraft under the configuration parameters of the register; and determining a simulation result of the space communication simulation system according to the communication success times and the communication failure times, wherein the simulation result is used for reflecting the robustness of the spacecraft communication link.
According to the control method of the space communication simulation system, different register configuration parameters are obtained through calculation according to the time setting parameters in the target probability distribution mode, so that accurate time delay control is conducted on communication between the space communication simulation system and the spacecraft through the different register configuration parameters, the communication success times and the communication failure times of the space communication simulation system and the spacecraft under the register configuration parameters are counted, the communication condition of the space communication simulation system and the spacecraft is achieved through the counting result, and the verification of the robustness of the communication link under the interference signal superposition scene is completed.
In some embodiments, the spatial communication simulation system comprises an FPGA and a register, and the spatial communication simulation system is controlled to work according to the register configuration parameter, including: performing parameter configuration on the register according to the register configuration parameters; and controlling the FPGA to delay and control communication signals between the space communication simulation system and the spacecraft according to the register configuration parameters in the register.
In some embodiments, the target probability distribution pattern is a uniform distribution pattern, and acquiring the time setting parameter corresponding to the target probability distribution pattern includes: and acquiring a first preset communication time interval and an allowable time delay maximum value corresponding to the uniform distribution mode, wherein the allowable time delay maximum value is less than or equal to the first preset communication time interval.
In some embodiments, obtaining register configuration parameters within the spatial communication simulation system from the time setting parameters includes: randomly generating a first value by using a rand function, wherein the range of the first value is 0, 1; obtaining a first delay value according to the maximum allowable delay value and the first value; calculating the sum of the first preset communication time interval and the first delay value to obtain a first final delay value; acquiring a first integer part and a first fractional part of the first final delay value, and taking the first integer part as a first second-level delay value; performing unit conversion on the first decimal part to obtain a first millisecond delay value; acquiring a first preset chip rate and a first preset oversampling multiple; obtaining a first single chip duration according to the first preset chip rate; obtaining a second decimal part of the first millisecond delay value, and performing unit conversion on the second decimal part to obtain a first microsecond delay value; obtaining a first ratio according to the first single chip duration and the first microsecond delay value; taking the second integer part of the first ratio as a first number of chips to be delayed; and obtaining a first clock frequency according to the first preset chip rate, the first preset oversampling multiple and a third decimal part of the first ratio.
In some embodiments, the registers include a second register, a millisecond register, a chip register, and a clock register, the parameter configuring the registers according to the register configuration parameters, including: the first second level delay value is configured to the second register, the first millisecond level delay value is configured to the millisecond register, the first number of chips to be delayed is configured to the chip register, and the first clock frequency is configured to the clock register.
In some embodiments, the target probability distribution pattern is a poisson distribution pattern, and acquiring the time setting parameter corresponding to the target probability distribution pattern includes: and acquiring a second preset communication time interval and a random time delay variance corresponding to the poisson distribution mode, wherein the random time delay variance is less than or equal to the second preset communication time interval.
In some embodiments, the space communication simulation system simulates N simulated spacecraft to be in data communication with the spacecraft, N is greater than or equal to 1, and the obtaining the register configuration parameters in the space communication simulation system according to the time setting parameters includes: randomly generating a second value by using the rand function, wherein the range of the second value is 0, 1; obtaining a second time delay value corresponding to each simulation spacecraft according to the random time delay variance and the second numerical value; obtaining a delay accumulated value according to the second delay value corresponding to each simulation spacecraft; calculating the sum of the second preset communication time interval and the delay accumulated value to obtain a second final delay value; acquiring a third integer part and a fourth decimal part of the second final delay value, and taking the third integer part as a second-level delay value; performing unit conversion on the fourth decimal part to obtain a second millisecond delay value; acquiring a second preset chip rate and a second preset oversampling multiple; obtaining a second single chip duration according to the second preset chip rate; obtaining a fifth decimal part of the second millisecond delay value, and performing unit conversion on the fifth decimal part to obtain a second microsecond delay value; obtaining a second ratio according to the second single chip duration and the second microsecond delay value; taking a fourth integer part of the second ratio as a second number of chips to be delayed; and obtaining a second clock frequency according to the second preset chip rate, the second preset oversampling multiple and a sixth decimal part of the second ratio.
In some embodiments, obtaining the delay accumulated value according to the second delay value corresponding to each simulated spacecraft includes: performing accumulated computation on the second delay value corresponding to each simulation spacecraft to obtain an accumulated initial value; if the accumulated initial value does not exceed the random time delay variance, the accumulated initial value is used as the time delay accumulated value; and if the accumulated initial value exceeds the random time delay variance, performing modular operation on the accumulated initial value to obtain the time delay accumulated value.
In some embodiments, the registers include a second register, a millisecond register, a chip register, and a clock register, the parameter configuring the registers according to the register configuration parameters, including: a second integer portion of the second level delay value is configured to the second register and the second millisecond level delay value is configured to the millisecond register, and the second number of chips to be delayed is configured to the chip register and the second clock frequency is configured to the clock register.
An embodiment of a second aspect of the present invention provides a spatial communication simulation system, including: at least one processor; a memory communicatively coupled to at least one of the processors; wherein the memory stores a computer program executable by at least one of the processors, and the control method of the spatial communication simulation system described in the above embodiment is implemented when the at least one of the processors executes the computer program.
According to the space communication simulation system provided by the embodiment of the invention, the actual use scene of the spacecraft can be simulated, and the verification of the robustness of the communication link under the interference signal superposition scene is completed.
Additional aspects and advantages of the invention will be set forth in part in the description which follows, and in part will be obvious from the description, or may be learned by practice of the invention.
Drawings
The foregoing and/or additional aspects and advantages of the invention will become apparent and may be better understood from the following description of embodiments taken in conjunction with the accompanying drawings in which:
FIG. 1 is a flow chart of a method of controlling a spatial communication simulation system according to one embodiment of the present invention;
FIG. 2 is a flow chart of a register configuration parameter calculation process in a uniform distribution mode according to one embodiment of the invention;
FIG. 3 is a block diagram of the data transfer between a host computer and an FPGA according to one embodiment of the invention;
FIG. 4 is a flow chart of a register configuration parameter calculation process in poisson distribution mode according to one embodiment of the present invention;
FIG. 5 is a flow chart of a method of controlling a spatial communication simulation system according to one embodiment of the present invention;
fig. 6 is a block diagram of a spatial communication simulation system according to one embodiment of the present invention.
Reference numerals:
a spatial communication simulation system 10;
a processor 1; a memory 2.
Detailed Description
Embodiments of the present invention will be described in detail below, by way of example with reference to the accompanying drawings.
In order to solve the above problems, an embodiment of a first aspect of the present invention provides a control method of a spatial communication simulation system, where the spatial communication simulation system is used to test a communication link of a spacecraft, and the method can simulate an actual usage scenario of the spacecraft and complete verification of robustness of the communication link in an interference signal superposition scenario.
A control method of a spatial communication simulation system according to an embodiment of the present invention is described below with reference to fig. 1, where, as shown in fig. 1, the control method at least includes: step S1 to step S5.
Step S1, responding to a target probability distribution mode selected by a user, and acquiring a time setting parameter corresponding to the target probability distribution mode.
The time setting parameter is understood to be a relevant parameter for controlling the communication time of the spatial communication simulation system in different probability distribution modes.
Specifically, one or more probability distribution modes are set in control software of the spatial communication simulation system in the upper computer, a user selects a target probability distribution mode in the control software, and the spatial communication simulation system responds to the target probability distribution mode selected by the user and automatically acquires time setting parameters corresponding to the target probability distribution mode.
And S2, calculating and obtaining the register configuration parameters in the space communication simulation system by the space communication simulation system according to the time setting parameters.
And step S3, controlling the space communication simulation system to work according to the register configuration parameters so that the space communication simulation system simulates data communication with the spacecraft.
And S4, counting the successful communication times and the failed communication times of the space communication simulation system and the spacecraft under the configuration parameters of the register.
Specifically, because the space communication simulation system is under the control of different register configuration parameters, the space communication simulation system and the spacecraft establish different communication links, so that the upper computer automatically counts the communication success times and communication failure times of the space communication simulation system and the spacecraft under the different register configuration parameters, when the space communication simulation system and the spacecraft are successful in communication, the spacecraft feeds back the communication success information to the space communication simulation system so as to indicate that the space communication simulation system and the spacecraft handshake are successful, at the moment, the space communication simulation system automatically accumulates the communication success times, when the space communication simulation system and the spacecraft are failed in communication, the spacecraft feeds back the communication failure information to the space communication simulation system so as to indicate that the space communication simulation system and the spacecraft handshake fail, at the moment, the space communication simulation system automatically accumulates the communication failure times, and therefore, the space communication simulation system is accurately controlled by the register configuration parameters under different target probability distribution modes, so that the space communication simulation system establishes the communication links with the spacecraft, the actual service scene of the spacecraft is simulated, the ground continuous service and the short message service is provided, and the satellite communication simulation system can be well tested, the satellite communication simulation system can be distributed with the space communication simulation system or the space communication simulation system under the different target probability distribution modes, and the satellite communication mode can be set up in the space communication simulation system.
And S5, determining a simulation result of the space communication simulation system according to the communication success times and the communication failure times, wherein the simulation result is used for reflecting the robustness of the spacecraft communication link.
Specifically, in the related art, no space communication simulation system can simulate the actual use scene of the spacecraft, the communication condition between the spacecraft and other spacecraft or satellite under the TDRSS communication condition can not be simulated, and the verification of the robustness of the communication link under the interference signal superposition scene can not be completed. In order to solve the problems, the application provides a space communication simulation system, which is used for controlling the space communication simulation system to communicate with a spacecraft through register configuration parameters under different probability distribution modes, so as to change the possibility of successful communication between the space communication simulation system and the spacecraft through the register configuration parameters, then counting the communication success times and communication failure times of the space communication simulation system and the spacecraft, taking the counting result as the simulation result of the space communication simulation system, completing the verification of the robustness of a communication link under an interference signal superposition scene, and reflecting the arrival probability of the spacecraft and other spacecraft or satellite under different probability distribution modes, namely the communication condition, through the simulation result.
According to the control method of the space communication simulation system, different register configuration parameters are obtained through calculation according to the time setting parameters in the target probability distribution mode, so that accurate time delay control is conducted on communication between the space communication simulation system and the spacecraft through the different register configuration parameters, the communication success times and the communication failure times of the space communication simulation system and the spacecraft under the register configuration parameters are counted, the communication condition of the space communication simulation system and the spacecraft is achieved through the counting result, and the verification of the robustness of the communication link under the interference signal superposition scene is completed.
In some embodiments, the spatial communication simulation system includes an FPGA (Field Programmable Gate Array ) and registers, and controls operation of the spatial communication simulation system according to register configuration parameters, including: performing parameter configuration on the register according to the register configuration parameters; and the control FPGA performs delay control on communication signals between the space communication simulation system and the spacecraft according to the register configuration parameters in the register.
Specifically, because the space communication simulation system is under the control of different register configuration parameters, the situation that the space communication simulation system and the spacecraft establish communication links is different, the situation that the space communication simulation system and the spacecraft establish communication links is obtained based on different register configuration parameters in the application, that is, the control software in the upper computer performs parameter configuration on the registers through the register configuration parameters, namely, the register configuration parameters are stored in the registers, the FPGA of the space communication simulation system reads the register configuration parameters, so as to perform delay control on communication signals between the space communication simulation system and the spacecraft, namely, the space communication simulation system delays the register configuration parameters and then sends communication signals to the spacecraft, so as to change the possibility of successful communication between the space communication simulation system and the spacecraft through the register configuration parameters, then statistics on the communication success times and communication failure times of the space communication simulation system and the spacecraft is carried out, and the statistics result is used as the simulation result of the space communication simulation system, so as to reflect the arrival probability of other spacecraft or satellite through the simulation result, and complete the verification of the robustness of communication links under the interference signal superposition scene, the application is realized, the FPGA is used for realizing the verification of the communication link robustness under the condition, the communication simulation system is realized through the FPGA, the communication simulation signal superposition condition is realized, the communication signal is realized through the communication simulation system is realized, the communication link simulation system is realized, and the communication link simulation condition is realized, and the communication simulation condition is realized under the actual condition is realized, and the communication condition is realized through the FPGA, and the communication simulation device is realized, and the communication simulation is realized, the method and the system provide good test and verification environments for ground continuous service and short message service, support various real-time data transmission, and simulate the arrival probability of a spacecraft and other spacecrafts or satellites in different probability distribution modes.
The method includes the steps of obtaining a register configuration parameter through a time setting parameter corresponding to a target probability distribution mode after determining the target probability distribution mode, performing delay control on communication signals between a space communication simulation system and a spacecraft through the register configuration parameter, counting the successful times and the failed times of communication between the space communication simulation system and the spacecraft, and if the successful times of communication are 6 times, enabling the arrival probability of other spacecraft or satellites to be 60%. Therefore, the condition that the space communication simulation system and the spacecraft establish communication link can be obtained through the register configuration parameters under different target probability distribution modes.
In some embodiments, the target probability distribution pattern is a uniform distribution pattern, and acquiring the time setting parameter corresponding to the target probability distribution pattern includes: and acquiring a first preset communication time interval and an allowable delay maximum value corresponding to the uniform distribution mode, wherein the allowable delay maximum value is less than or equal to the first preset communication time interval. That is, when the target probability distribution pattern selected by the user in the control software of the spatial communication simulation system in the host computer is the uniform distribution pattern, and the first preset communication time interval T0 is set by the control software in the uniform distribution pattern, the spatial communication simulation system automatically acquires the first preset communication time interval T0 corresponding to the uniform distribution pattern and the allowable delay maximum MT, and the constraint relation that the allowable delay maximum MT is less than or equal to the first preset communication time interval T0 needs to be satisfied, so that the first preset communication time interval satisfies the uniform distribution mathematical model, wherein the first preset communication time interval can be understood as a time interval that satisfies the uniform distribution pattern, which is manually set. The maximum allowable delay value can be understood as the maximum value of delay control of a preset system in the space communication simulation system.
In addition, if the maximum value MT of the allowable delay is greater than the first preset communication time interval T0, the control software in the control upper computer prompts that the maximum value MT of the allowable delay is less than or equal to the first preset communication time interval T0.
In some embodiments, as shown in FIG. 2, in the evenly distributed mode, the register configuration parameters within the resulting spatial communication simulation system are calculated by the following steps.
A first value U1 is randomly generated by using the rand function, and the range of the first value U1 is 0, 1. The rand function is a random function for generating random numbers, the control software in the upper computer returns a first value U1 randomly by using the rand function, the generated first value needs to satisfy the range of [0,1 ], and the first value can be 0, 0.1, 0.2, 0.5, 0.9, etc., which is not limited.
And obtaining a first delay value according to the maximum allowable delay value and the first value. The maximum value MT of the allowable delay is multiplied by the first value U to obtain a product result, which can be expressed as mt×u1, and the product result is taken as the first delay value x1.
And calculating the sum of the first preset communication time interval and the first delay value to obtain a first final delay value. I.e. the sum of the first preset communication time interval T0 and the first delay value x1 is taken as the first final delay value y1. Wherein the first final delay value y1 comprises an integer part and a fractional part.
And acquiring a first integer part and a first fractional part of the first final delay value y1, taking the first integer part of the first final delay value y1 as a first second delay value, and taking the first second delay value as a register configuration parameter.
The first fractional portion is unit converted to obtain a first millisecond delay value. The unit of the first fractional part of the first final delay value y1 is converted from seconds to milliseconds, namely the first fractional part is multiplied by 1000 to calculate a first fractional part after unit conversion, the first fractional part after unit conversion is used as a first millisecond delay value P1, and the first millisecond delay value P1 is used as a register configuration parameter.
A first preset chip rate Rb1 and a first preset oversampling multiple Nclk1 are acquired. That is, the space communication simulation system automatically acquires a first preset chip rate Rb1 inputted by a user in control software of the upper computer, which is required to satisfy a time interval range preset according to a standard formulated by CCSDS (Consultative Committee for Space Data Systems, international commission on consultation of space data systems), and automatically acquires a first preset oversampling multiple Nclk1 set in the control software.
A first single chip duration Tb1 is calculated from a first preset chip rate Rb1. Wherein the first single chip duration Tb1 is equal to 1/Rb1.
A second fraction of the first millisecond delay value is obtained and the second fraction is converted in units to obtain the first microsecond delay value. The unit of the second fractional part of the first millisecond-level delay value is converted into microseconds from milliseconds, namely the second fractional part is multiplied by 1000 to obtain the second fractional part after unit conversion, and the second fractional part after unit conversion is used as the first microsecond-level delay value Q1.
The first ratio R1 is obtained from the first single chip duration Tb1 and the first microsecond level delay value Q1. The first microsecond delay value Q1 is divided by the first single chip duration Tb1 to obtain a first ratio R1, and then the second integer part of the first ratio R1 is used as the first number of chips to be delayed, so that the first number of chips to be delayed is used as a register configuration parameter.
The first clock frequency is obtained from the first preset chip rate, the first preset oversampling multiple, and the third fractional portion of the first ratio R. That is, the first preset chip rate Rb1, the first preset oversampling multiple Nclk1, and the third fractional portion S1 are calculated by the following formula w1=s1×nclk1/Rb1 to obtain the first clock frequency W1, and then the first clock frequency W1 is rounded to 0, so that an integer portion of the first clock frequency W1 is reserved, and then the first clock frequency is used as a register configuration parameter.
In this way, the first second level delay value, the first millisecond level delay value, the first number of chips to be delayed and the first clock frequency are obtained through calculation through the steps in the uniform distribution mode, and the first second level delay value, the first millisecond level delay value, the first number of chips to be delayed and the first clock frequency are used as register configuration parameters. Under the uniform distribution mode, the condition that the space communication simulation system and the spacecraft establish communication links is obtained based on the register configuration parameters, namely the FPGA reads the register configuration parameters to delay and control communication signals between the space communication simulation system and the spacecraft so as to change the possibility of successful establishment of communication between the space communication simulation system and the spacecraft, then the communication success times and the communication failure times of the space communication simulation system and the spacecraft are counted, the counted result is used as the simulation result of the space communication simulation system, the arrival probability of other spacecraft or satellite with different register configuration parameters under the uniform distribution mode is reflected through the simulation result, and the verification of the robustness of the communication links under the interference signal superposition scene is completed.
It can be appreciated that different first second level delay values, first millisecond level delay values, first number of chips to be delayed and first clock frequency can be obtained through the above calculation steps in the uniform distribution mode, so as to obtain different register configuration parameters, thereby obtaining arrival probabilities of other spacecrafts and satellites corresponding to the different register configuration parameters.
In some embodiments, the registers include a second register, a millisecond register, a chip register, and a clock register, the parameter configuring the registers according to the register configuration parameters, comprising: the first second level delay value is configured to the second register and the first millisecond level delay value is configured to the millisecond register and the first number of chips to be delayed is configured to the chip register and the first clock frequency is configured to the clock register.
Specifically, control software in the upper computer configures a first second-level delay value to a second register, sends the first second-level delay value stored in the second register to the FPGA, reads the first second-level delay value stored in the second register, and performs delay control on communication signals between the space communication simulation system and the spacecraft according to the first second-level delay value in the second register so as to complete second-level delay control on the communication signals between the space communication simulation system and the spacecraft; and the control software in the upper computer configures the first millisecond delay value to the millisecond register, sends the first millisecond delay value stored in the millisecond register to the FPGA, reads the first millisecond delay value stored in the millisecond register, and performs delay control on communication signals between the space communication simulation system and the spacecraft according to the first millisecond delay value in the millisecond register so as to complete millisecond delay control on the communication signals between the space communication simulation system and the spacecraft.
The control software in the upper computer configures the first number of chips to be delayed to a chip register, sends the first number of chips to be delayed stored in the chip register to the FPGA, reads the first number of chips to be delayed stored in the chip register, and performs delay control on communication signals between the space communication simulation system and the spacecraft according to the first number of chips to be delayed stored in the chip register so as to complete chip-level delay control on the communication signals between the space communication simulation system and the spacecraft; and the control software in the upper computer configures the first clock frequency to the clock register, sends the first clock frequency stored in the clock register to the FPGA, reads the first clock frequency stored in the clock register, and performs delay control on communication signals between the space communication simulation system and the spacecraft according to the first clock frequency in the clock register so as to complete clock-level delay control on the communication signals between the space communication simulation system and the spacecraft. Therefore, the communication signals between the space communication simulation system and the spacecraft are controlled to be delayed through the register configuration parameters, so that the communication success times and the communication failure times of the space communication simulation system and the spacecraft are counted, the actual use scene of the spacecraft is simulated, and the robustness of the communication link of the spacecraft in the interference signal superposition scene is verified.
In addition, as shown in fig. 3, the upper computer and the FPGA perform data transmission through a data bus.
In an embodiment, in the uniform distribution mode, the FPGA may be sequentially controlled to delay control the communication signal between the space communication simulation system and the spacecraft according to the first second delay value of the second register, the first millisecond delay value of the millisecond register, the first number of chips to be delayed of the chip register, and the first clock frequency of the clock register.
In some embodiments, the target probability distribution pattern is a poisson distribution pattern, and acquiring the time setting parameter corresponding to the target probability distribution pattern includes: and acquiring a second preset communication time interval and a random time delay variance corresponding to the Poisson distribution mode, wherein the random time delay variance is less than or equal to the second preset communication time interval. That is, when the target probability distribution mode selected by the user in the control software in the host computer is the poisson distribution mode, and the second preset communication time interval T1 is set by the control software in the poisson distribution mode, the spatial communication simulation system can automatically acquire the second preset communication time interval T1 corresponding to the poisson distribution mode, and acquire the random time delay variance λ automatically generated by the simulation system, and the constraint relation that the random time delay variance λ is less than or equal to the second preset communication time interval T1 needs to be satisfied, so that the time delay variance satisfies the poisson distribution mathematical model. The second preset communication time interval may be understood as a time interval manually set to meet the poisson distribution mode requirement.
In addition, if the random time delay variance lambda > the second preset communication time interval T1, the control software controlling the space communication simulation system prompts that the random time delay variance lambda is smaller than or equal to the second preset communication time interval T1.
In some embodiments, N simulated spacecraft to be in data communication with the spacecraft are simulated in the space communication simulation system, and N is more than or equal to 1. Based on this, as shown in fig. 4, in the poisson distribution mode, the register configuration parameters in the spatial communication simulation system are obtained by calculation through the following steps.
The range of the second numerical value U2 is [0,1 ] by using the rand function, namely, the control software in the upper computer returns the second numerical value U2 randomly by using the rand function, and the generated second numerical value U2 needs to meet the range of [0,1 ], and the second numerical value can be 0, 0.1, 0.2, 0.5, 0.9 and the like, which is not limited. And obtaining a second time delay value corresponding to each simulation spacecraft according to the random time delay variance lambda and the second numerical value U2, namely substituting the random time delay variance lambda and the second numerical value U2 into a calculation formula delta t= -1/lambda ln (1-U) of the second time delay value delta t to calculate and obtain the second time delay value delta t corresponding to each simulation spacecraft. And obtaining a time delay accumulated value according to the second time delay value corresponding to each simulation spacecraft, namely calculating the sum value of the second time delay values corresponding to all the simulation spacecrafts, and taking the sum value as the time delay accumulated value. And calculating and obtaining a second final delay value y2 through the sum of a second preset communication time interval T1 and the delay accumulated value, wherein the second final delay value y2 comprises an integer part and a decimal part, obtaining a third integer part and a fourth decimal part of the second final delay value y2, taking the third integer part as a second-level delay value, and taking the second-level delay value as a register configuration parameter.
The fourth fractional portion is subjected to unit conversion to obtain a second millisecond-level delay value. The unit of the fourth fraction part of the second final delay value is converted from seconds to milliseconds, namely the fourth fraction part is multiplied by 1000 to calculate a fourth fraction part after unit conversion, the fourth fraction part after unit conversion is taken as a second millisecond delay value P2, and the second millisecond delay value P2 is taken as a register configuration parameter.
A second preset chip rate Rb2 and a second preset oversampling multiple Nclk2 are acquired. That is, the spatial communication simulation system automatically acquires a second preset chip rate Rb2 input by the user in the control software of the upper computer, and a second preset oversampling multiple set in the control software, wherein the second preset chip rate needs to satisfy a time interval range preset according to the CCSDS formulation standard. And obtaining a second single chip duration Tb2 according to the second preset chip rate Rb2, wherein the second single chip duration Tb2 is equal to 1/Rb2. The second millisecond delay value P2 includes an integer part and a fractional part, a fifth fractional part of the second millisecond delay value P2 is obtained, and the fifth fractional part is subjected to unit conversion to obtain a second microsecond delay value, namely, the unit of the fifth fractional part of the second millisecond delay value P2 is converted from millisecond to microsecond, that is, the fifth fractional part is multiplied by 1000 to calculate a fifth fractional part after unit conversion, and the fifth fractional part after unit conversion is used as the second microsecond delay value Q2.
A second ratio is obtained from the second single chip duration Tb2 and the second microsecond level delay value Q2. The second microsecond delay value Q2 is divided by the second single chip duration Tb2 to obtain a second ratio R2, and the fourth integer part of the second ratio R2 is used as the second number of chips to be delayed, so that the second number of chips to be delayed is used as a register configuration parameter.
And obtaining a second clock frequency according to the second preset chip rate, the second preset oversampling multiple and a sixth fractional part of the second ratio. That is, the second clock frequency W2 is obtained by calculating the second preset chip rate Rb2, the second preset oversampling multiple Nclk2, and the sixth fractional portion S2 of the second ratio by the following formula w2=s2×nclk2/Rb2, and then rounding the second clock frequency W2 to 0, thereby preserving the integer portion of the second clock frequency W2, and then using the second clock frequency as a register configuration parameter.
The method comprises the steps of obtaining a second-level delay value, a second millisecond-level delay value, a second number of chips to be delayed and a second clock frequency through calculation in a poisson distribution mode, taking the second-level delay value, the second millisecond-level delay value, the second number of chips to be delayed and the second clock frequency as register configuration parameters, obtaining the condition that a communication link is established between a space communication simulation system and a spacecraft based on the register configuration parameters in the poisson distribution mode, namely, reading the register configuration parameters by an FPGA (field programmable gate array), so as to delay control communication signals between the space communication simulation system and the spacecraft, changing the possibility of successful communication between the space communication simulation system and the spacecraft, counting the communication success times and the communication failure times of the space communication simulation system and the spacecraft, taking the counted result as simulation results of the space communication simulation system and the simulation spacecraft, reflecting the arrival probability of the register configuration parameters corresponding to other spacecraft and satellite in the poisson distribution mode through the simulation results, and completing verification of the robustness of the communication link under the interference signal superposition scene.
It can be appreciated that different second level delay values, second millisecond level delay values, second number of chips to be delayed, and second clock frequency can be obtained through the above calculation steps in the poisson distribution mode, so as to obtain different register configuration parameters, thereby obtaining arrival probabilities of other spacecrafts and satellites with different register configuration parameters.
In some embodiments, obtaining the delay accumulated value according to the second delay value corresponding to each simulated spacecraft includes: performing accumulated computation on the second delay value corresponding to each simulation spacecraft to obtain an accumulated initial value; if the accumulated initial value does not exceed the random time delay variance, the accumulated initial value is used as a time delay accumulated value; if the accumulated initial value exceeds the random time delay variance, performing modular operation on the accumulated initial value to obtain a time delay accumulated value.
Specifically, the second delay value corresponding to each analog spacecraft is accumulated to obtain an accumulated initial value, where the calculation formula Δt= -1/λln (1-U2) of the second delay value Δt is a randomly generated second value, if the space communication analog system generates N analog spacecraft, the second delay value corresponding to the 1 st analog spacecraft is t1=Δt1= -1/λln (1-U2), the second delay value corresponding to the 2 nd analog spacecraft is t2=t1+Δt2, Δt2= -1/λln (1-U2), the second delay value corresponding to the 3 rd analog spacecraft is t3=t2+Δt3, Δt3= -1/λln (1-U2), and the second delay value corresponding to the N analog spacecraft is tn=tn+Δtn, Δtn= -1/λn (1-U2), thus the accumulated initial value of t3+t2+t3+t3+t2.
The system can not buffer when the accumulated initial value is larger than the random time delay variance, so that the time delay accumulated value is obtained by judging the magnitude of the accumulated initial value, if the accumulated initial value does not exceed the random time delay variance, the accumulated initial value is satisfied, and the accumulated initial value is taken as the time delay accumulated value; if the accumulated initial value exceeds the random delay variance, the accumulated initial value may have a negative number or complex number, and the system cannot buffer when the accumulated initial value is greater than the random delay variance, performing modulo operation on the accumulated initial value to obtain a delay accumulated value, that is, performing modulo operation on the accumulated initial value and the random delay variance to obtain an absolute value of the accumulated initial value, taking the absolute value of the accumulated initial value as the delay accumulated value, so that the delay accumulated value has no negative number or complex number, and the accumulated initial value is lower than the random delay variance.
In some embodiments, the registers include a second register, a millisecond register, a chip register, and a clock register, the parameter configuring the registers according to the register configuration parameters, comprising: a second integer portion of the second level delay value is configured to the second register and the second millisecond level delay value is configured to the millisecond register and the second number of chips to be delayed is configured to the chip register and the second clock frequency is configured to the clock register.
Specifically, under a poisson distribution mode, the control software in the upper computer configures a second-level delay value to a second register, and sends the second-level delay value stored in the second register to the FPGA, and the FPGA reads the second-level delay value stored in the second register and performs delay control on a communication signal between the space communication simulation system and the spacecraft according to the second-level delay value in the second register so as to complete second-level delay control on the communication signal between the space communication simulation system and the spacecraft; and the control software in the upper computer configures the second millisecond delay value to the millisecond register, sends the second millisecond delay value stored in the millisecond register to the FPGA, reads the second millisecond delay value stored in the millisecond register, and performs delay control on communication signals between the space communication simulation system and the spacecraft according to the second millisecond delay value in the millisecond register so as to complete millisecond delay control on the communication signals between the space communication simulation system and the spacecraft.
The control software in the upper computer configures the second number of chips to be delayed to the chip register, and sends the second number of chips to be delayed stored in the chip register to the FPGA, and the FPGA reads the second number of chips to be delayed stored in the chip register and performs delay control on communication signals between the space communication simulation system and the spacecraft according to the second number of chips to be delayed stored in the chip register so as to complete chip-level delay control on the communication signals between the space communication simulation system and the spacecraft; and the control software in the upper computer configures the second clock frequency to the clock register, sends the second clock frequency stored in the clock register to the FPGA, reads the second clock frequency stored in the clock register, and performs delay control on communication signals between the space communication simulation system and the spacecraft according to the second clock frequency in the clock register so as to complete clock-level delay control on the communication signals between the space communication simulation system and the spacecraft. Therefore, the communication signals between the space communication simulation system and the spacecraft are controlled to be delayed through the register configuration parameters, so that the communication success times and the communication failure times of the space communication simulation system and the spacecraft are counted, the actual use scene of the spacecraft is simulated, and the robustness of the communication link of the spacecraft in the interference signal superposition scene is verified.
In an embodiment, in the poisson distribution mode, the FPGA may be sequentially controlled to delay control the communication signal between the space communication simulation system and the spacecraft according to the second delay value of the second register, the second millisecond delay value of the millisecond register, the second number of chips to be delayed of the chip register, and the second clock frequency of the clock register.
The following describes an example of a control method of the spatial communication simulation system according to the embodiment of the present invention with reference to fig. 5, and the specific contents are as follows.
Step S21, selecting the target probability distribution pattern to be a uniform distribution pattern or a poisson distribution pattern, and executing step S22 or step S26.
Step S22, if the target probability distribution mode is the uniform distribution mode, acquiring a time setting parameter corresponding to the uniform distribution mode: a first preset communication time interval T0 and an allowable delay maximum MT.
And S23, adjusting T0 and MT to meet the constraint relation that MT is less than or equal to T0.
In step S24, a register configuration parameter in the uniform distribution mode is calculated, where the register configuration parameter includes a first second level delay value, a first millisecond level delay value, a first number of chips to be delayed, and a first clock frequency.
In step S25, the FPGA performs delay control on the communication signal between the space communication simulation system and the spacecraft by using the register configuration parameters in the uniformly distributed mode.
Step S26, if the target probability distribution mode is a Poisson distribution mode, acquiring a time setting parameter corresponding to the Poisson distribution mode: a second preset communication time interval T1 and a random delay variance lambda.
In step S27, T1 and lambda are adjusted to satisfy the constraint relation of lambda.ltoreq.T1.
In step S28, a register parameter configuration in the poisson distribution mode is calculated, where the register parameter configuration includes a second level delay value, a second millisecond level delay value, a second number of chips to be delayed, and a second clock frequency.
In step S29, the FPGA performs delay control on the communication signal between the space communication simulation system and the spacecraft through the register configuration parameters in the poisson distribution mode.
An embodiment of the second aspect of the present invention provides a spatial communication simulation system, as shown in fig. 6, including: at least one processor 1 and a memory 2 in communication with the at least one processor 1.
Wherein the memory 2 stores a computer program executable by the at least one processor 1, the at least one processor 1 implementing the control method of the spatial communication simulation system in the above embodiment when executing the computer program.
It should be noted that, the specific implementation manner of the spatial communication simulation system 10 according to the embodiment of the present invention is similar to the specific implementation manner of the control method of the spatial communication simulation system according to any of the above embodiments of the present invention, and please refer to the description of the method section specifically, and for redundancy reduction, the description is omitted here.
According to the space communication simulation system provided by the embodiment of the invention, the actual use scene of the spacecraft can be simulated, and the verification of the robustness of the communication link under the interference signal superposition scene is completed.
In the description of the present specification, reference to the terms "one embodiment," "some embodiments," "illustrative embodiments," "examples," "specific examples," or "some examples," etc., means 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, schematic representations of the above terms do not necessarily refer to the same embodiments or examples.
While embodiments of the present invention have been shown and described, it will be understood by those of ordinary skill in the art that: many changes, modifications, substitutions and variations may be made to the embodiments without departing from the spirit and principles of the invention, the scope of which is defined by the claims and their equivalents.
Claims (10)
1. A method for controlling a space communication simulation system for testing a communication link of a spacecraft, the method comprising:
Responding to a target probability distribution mode selected by a user, and acquiring a time setting parameter corresponding to the target probability distribution mode;
acquiring a register configuration parameter in the space communication simulation system according to the time setting parameter;
controlling the space communication simulation system to work according to the register configuration parameters so that the space communication simulation system simulates data communication with the spacecraft;
counting the successful communication times and the failed communication times of the space communication simulation system and the spacecraft under the configuration parameters of the register;
and determining a simulation result of the space communication simulation system according to the communication success times and the communication failure times, wherein the simulation result is used for reflecting the robustness of the spacecraft communication link.
2. The method for controlling a spatial communication simulation system according to claim 1, wherein the spatial communication simulation system comprises an FPGA and a register, and wherein controlling the operation of the spatial communication simulation system according to the register configuration parameter comprises:
performing parameter configuration on the register according to the register configuration parameters;
and controlling the FPGA to delay and control communication signals between the space communication simulation system and the spacecraft according to the register configuration parameters in the register.
3. The method for controlling a spatial communication simulation system according to claim 2, wherein the target probability distribution pattern is a uniform distribution pattern, and acquiring the time setting parameter corresponding to the target probability distribution pattern comprises:
and acquiring a first preset communication time interval and an allowable time delay maximum value corresponding to the uniform distribution mode, wherein the allowable time delay maximum value is less than or equal to the first preset communication time interval.
4. A control method of a space communication simulation system according to claim 3, wherein obtaining a register configuration parameter in the space communication simulation system based on the time setting parameter comprises:
randomly generating a first value by using a rand function, wherein the range of the first value is 0, 1;
obtaining a first delay value according to the maximum allowable delay value and the first value;
calculating the sum of the first preset communication time interval and the first delay value to obtain a first final delay value;
acquiring a first integer part and a first fractional part of the first final delay value, and taking the first integer part as a first second-level delay value;
performing unit conversion on the first decimal part to obtain a first millisecond delay value;
Acquiring a first preset chip rate and a first preset oversampling multiple;
obtaining a first single chip duration according to the first preset chip rate;
obtaining a second decimal part of the first millisecond delay value, and performing unit conversion on the second decimal part to obtain a first microsecond delay value;
obtaining a first ratio according to the first single chip duration and the first microsecond delay value;
taking the second integer part of the first ratio as a first number of chips to be delayed;
and obtaining a first clock frequency according to the first preset chip rate, the first preset oversampling multiple and a third decimal part of the first ratio.
5. The method for controlling a spatial communication simulation system according to claim 4, wherein the registers include a second register, a millisecond register, a chip register, and a clock register, and wherein parameter configuration of the registers according to the register configuration parameters includes:
the first second level delay value is configured to the second register, the first millisecond level delay value is configured to the millisecond register, the first number of chips to be delayed is configured to the chip register, and the first clock frequency is configured to the clock register.
6. The method for controlling a spatial communication simulation system according to claim 2, wherein the target probability distribution pattern is a poisson distribution pattern, and acquiring the time setting parameter corresponding to the target probability distribution pattern comprises:
and acquiring a second preset communication time interval and a random time delay variance corresponding to the poisson distribution mode, wherein the random time delay variance is less than or equal to the second preset communication time interval.
7. The method for controlling a space communication simulation system according to claim 6, wherein N simulated spacecraft to be in data communication with the spacecraft are simulated in the space communication simulation system, N is equal to or greater than 1, and the obtaining the register configuration parameters in the space communication simulation system according to the time setting parameters includes:
randomly generating a second value by using the rand function, wherein the range of the second value is 0, 1;
obtaining a second time delay value corresponding to each simulation spacecraft according to the random time delay variance and the second numerical value;
obtaining a delay accumulated value according to the second delay value corresponding to each simulation spacecraft;
calculating the sum of the second preset communication time interval and the delay accumulated value to obtain a second final delay value;
Acquiring a third integer part and a fourth decimal part of the second final delay value, and taking the third integer part as a second-level delay value;
performing unit conversion on the fourth decimal part to obtain a second millisecond delay value;
acquiring a second preset chip rate and a second preset oversampling multiple;
obtaining a second single chip duration according to the second preset chip rate;
obtaining a fifth decimal part of the second millisecond delay value, and performing unit conversion on the fifth decimal part to obtain a second microsecond delay value;
obtaining a second ratio according to the second single chip duration and the second microsecond delay value;
taking a fourth integer part of the second ratio as a second number of chips to be delayed;
and obtaining a second clock frequency according to the second preset chip rate, the second preset oversampling multiple and a sixth decimal part of the second ratio.
8. The method for controlling a space communication simulation system according to claim 7, wherein obtaining the delay integrated value from the second delay value corresponding to each simulation spacecraft comprises:
performing accumulated computation on the second delay value corresponding to each simulation spacecraft to obtain an accumulated initial value;
If the accumulated initial value does not exceed the random time delay variance, the accumulated initial value is used as the time delay accumulated value;
and if the accumulated initial value exceeds the random time delay variance, performing modular operation on the accumulated initial value to obtain the time delay accumulated value.
9. The control method of a spatial communication simulation system according to claim 7 or 8, wherein the registers include a second register, a millisecond register, a chip register, and a clock register, and the parameter configuration of the registers according to the register configuration parameters includes:
a second integer portion of the second level delay value is configured to the second register and the second millisecond level delay value is configured to the millisecond register, and the second number of chips to be delayed is configured to the chip register and the second clock frequency is configured to the clock register.
10. A space communication simulation system, comprising:
at least one processor;
a memory communicatively coupled to at least one of the processors;
wherein said memory has stored therein a computer program executable by at least one of said processors, which when executing said computer program implements the method of controlling a spatial communication simulation system according to any of claims 1-9.
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