Spacecraft motion process measurement method and device based on broadband data transmission signal

Abstract

The invention discloses a spacecraft motion process measurement method and device based on a broadband data transmission signal, and the method comprises the steps: obtaining a downlink signal of a spacecraft in a set time period, recovering a frequency multiplication carrier signal, extracting a main carrier frequency sequence of the frequency multiplication carrier signal, obtaining a target frequency sequence through frequency multiplication inversion, and carrying out the measurement of the motion process of the spacecraft. And spacecraft motion parameters are determined after frequency characteristic information extraction. According to the method, the broadband data transmission signal is used as a measurement data source, the dynamic change characteristics of the main carrier are extracted through a carrier recovery full-process algorithm, dependence on narrowband carriers is not needed, and the problems of high tracking difficulty and insufficient real-time performance and precision caused by low signal-to-noise ratio and large dynamic Doppler frequency shift of the broadband signal are effectively solved; motion state measurement is achieved based on an existing data transmission link, and the safety and economical efficiency of a spaceflight task are improved.

Description

Technical Field

[0001] This invention relates to the field of information acquisition and processing technology, and more specifically, to a method and apparatus for measuring the motion process of a spacecraft based on broadband data transmission signals. Background Technology

[0002] With the surge in demand for high-resolution detection data and equipment status information transmission in space missions, the application of broadband data transmission signals in spacecraft is becoming increasingly widespread. Particularly during critical maneuvers such as orbital maneuvers and attitude adjustments, the continuous downlink characteristics of broadband data transmission signals become increasingly significant. Simultaneously, the high speed and wide bandwidth of broadband data transmission signals exacerbate the difficulty of dynamic tracking of spacecraft by ground stations. On the one hand, the power spectral density amortization effect, the superposition of modulation and coding losses, and stronger channel interference compared to narrowband carriers lead to a significant reduction in the signal-to-noise ratio of broadband data transmission signals, increasing the difficulty of signal acquisition and tracking. On the other hand, the large dynamic Doppler frequency shift and its rate of change generated by the high-speed motion of spacecraft, combined with the wide bandwidth characteristics of broadband data transmission signals, further exacerbates the difficulty of dynamic tracking by ground stations, ultimately resulting in insufficient measurement real-time performance and tracking accuracy.

[0003] Therefore, it is essential to study methods for measuring spacecraft motion processes based on broadband data transmission signals. Summary of the Invention

[0004] The technical problem to be solved by the present invention is to provide a method and device for measuring the motion process of spacecraft based on broadband data transmission signals, which aims to solve at least one of the above-mentioned technical problems.

[0005] In a first aspect, the technical solution of the present invention to solve the above-mentioned technical problems is as follows: a method for measuring the motion process of a spacecraft based on broadband data transmission signals, the method comprising: Acquire the downlink signal from the spacecraft within a set time period, and recover the frequency-doubled carrier signal based on the downlink signal; Extract the main carrier frequency sequence of the frequency-doubled carrier signal within a set time period; Frequency doubling inversion is performed on each carrier frequency in the main carrier frequency sequence to obtain the target frequency sequence, which is the carrier frequency sequence of the downlink signal; Frequency features are extracted from the target frequency sequence. Based on frequency characteristics, determine the spacecraft's motion parameters.

[0006] The beneficial effects of this invention are as follows: By acquiring the downlink signal of the spacecraft within a set time period and determining the frequency-doubled carrier signal, extracting the main carrier frequency sequence of the frequency-doubled carrier signal within the set time period, performing frequency-doubled inversion on the main carrier frequency sequence to obtain the target frequency sequence, extracting frequency feature information from the target frequency sequence to obtain frequency features, and finally determining the motion parameters of the spacecraft based on the frequency features, this invention achieves real-time measurement using the downlink broadband data transmission signal of the spacecraft as the measurement data source and extracting the dynamic change features of the main carrier caused by the motion of the spacecraft through the construction of a full-process carrier recovery algorithm. It does not rely on narrowband carrier signals and effectively solves the problems of high difficulty in dynamic tracking of ground stations and insufficient measurement real-time performance and tracking accuracy caused by the low signal-to-noise ratio, large dynamic Doppler frequency shift and frequency shift change rate of broadband data transmission signals. At the same time, it can rely on the existing data transmission link of the spacecraft to mine the motion state feature information contained in the signal without the need for additional measurement equipment, thus improving the safety and economy of space missions.

[0007] Based on the above technical solution, the present invention can be further improved as follows.

[0008] Furthermore, the modulation scheme corresponding to the aforementioned downlink signal is binary phase-shift keying (BPSK) or quadrature phase-shift keying (QPSK). The recovery of the frequency-doubled carrier signal based on the downlink signal includes: If the modulation method is binary phase shift keying, the downlink signal is squared to obtain the frequency-doubled carrier signal; If the modulation method is quadrature phase shift keying, the downlink signal is subjected to a fourth power operation to obtain a frequency-doubled carrier signal.

[0009] Furthermore, the above-mentioned frequency doubling inversion of each carrier frequency in the primary carrier frequency sequence yields the target frequency sequence, including: If the modulation method is binary phase shift keying, the target frequency sequence is obtained by performing a 2-fold frequency inversion on each carrier frequency in the main carrier frequency sequence. If the modulation method is quadrature phase shift keying, the target frequency sequence is obtained by performing a quadruple frequency inversion on each carrier frequency in the main carrier frequency sequence.

[0010] Furthermore, the frequency feature information of the target frequency sequence is extracted as described above to obtain frequency features, including: Determine the rate of change of the target frequency sequence over a set time period. All carrier frequencies and frequency change rates in the target frequency sequence are identified as frequency characteristics.

[0011] Furthermore, the determination of spacecraft motion parameters based on frequency characteristics includes: Based on all carrier frequencies and frequency change rates in the target frequency sequence, the motion parameters of the spacecraft are calculated using the Doppler frequency formula. These motion parameters include the spacecraft's radial velocity and / or radial acceleration.

[0012] Secondly, to solve the above-mentioned technical problems, the present invention also provides a spacecraft motion process measurement device based on broadband data transmission signals, the device comprising: The acquisition module is used to acquire the downlink signal of the spacecraft within a set time period and recover the frequency-doubled carrier signal based on the downlink signal; The main carrier frequency sequence determination module is used to extract the main carrier frequency sequence of the frequency-doubled carrier signal within a set time period; The inversion module is used to perform frequency multiplication inversion on each carrier frequency in the main carrier frequency sequence to obtain the target frequency sequence, which is the carrier frequency sequence of the downlink signal; The extraction module is used to extract frequency feature information from the target frequency sequence to obtain frequency features; The motion parameter determination module is used to determine the motion parameters of the spacecraft based on frequency characteristics.

[0013] Thirdly, in order to solve the above-mentioned technical problems, the present invention also provides an electronic device, which includes a memory, a processor, and a computer program stored in the memory and executable on the processor. When the processor executes the computer program, it implements the spacecraft motion process measurement method based on broadband data transmission signals of this application.

[0014] Fourthly, in order to solve the above-mentioned technical problems, the present invention also provides a computer-readable storage medium storing a computer program, which, when executed by a processor, implements the spacecraft motion process measurement method based on broadband data transmission signals of the present application.

[0015] Additional aspects and advantages of this application will be set forth in part in the description which follows, and will become apparent from the description or may be learned by practice of this application. Attached Figure Description

[0016] To more clearly illustrate the technical solutions in the embodiments of the present invention, the accompanying drawings used in the description of the embodiments of the present invention will be briefly introduced below.

[0017] Figure 1 A flowchart illustrating a method for measuring spacecraft motion based on broadband data transmission signals, provided as an embodiment of the present invention; Figure 2 A flowchart illustrating another method for measuring spacecraft motion based on broadband data transmission signals, provided in one embodiment of the present invention; Figure 3 A schematic diagram of the spectrum of a downlink signal provided in one embodiment of the present invention; Figure 4A schematic diagram of the spectrum of a frequency-doubled carrier signal provided in one embodiment of the present invention; Figure 5 A schematic diagram of the measurement results of the on-orbit motion state of a spacecraft provided in one embodiment of the present invention; Figure 6 A schematic diagram of a spacecraft motion measurement device based on broadband data transmission signals, provided as an embodiment of the present invention; Figure 7 This is a schematic diagram of the structure of an electronic device provided in one embodiment of the present invention. Detailed Implementation

[0018] The principles and features of the present invention are described below. The examples given are only for explaining the present invention and are not intended to limit the scope of the present invention.

[0019] The technical solution of the present invention and how the technical solution of the present invention solves the above-mentioned technical problems are described in detail below with specific embodiments. These specific embodiments can be combined with each other, and the same or similar concepts or processes may not be described again in some embodiments. The embodiments of the present invention will now be described with reference to the accompanying drawings.

[0020] The data acquisition process involved in this invention follows the principles of legality, legitimacy, and necessity. Based on obtaining the explicit authorization and consent of the user, only the minimum necessary information required to achieve the purpose is collected, and data security protection obligations are fulfilled in accordance with the law.

[0021] The solution provided by the embodiments of the present invention can be applied to any application scenario that requires measurement of the motion process of a spacecraft. The solution provided by the embodiments of the present invention can be executed by any electronic device, such as a user's terminal device, including at least one of the following: smartphone, tablet computer, laptop computer, desktop computer, smart speaker, smartwatch, smart TV, and smart in-vehicle device.

[0022] This invention provides a possible implementation, such as... Figure 1 The diagram shows a flowchart of a method for measuring spacecraft motion based on broadband data transmission signals. This method can be executed by any electronic device, such as a terminal device, or by a terminal device and a server. For ease of description, the method provided in this embodiment will be described below using a terminal device as the execution subject. Figure 1 The flowchart shown indicates that the method may include the following steps: S10: Acquire the downlink signal of the spacecraft within a set time period, and recover the frequency-doubled carrier signal based on the downlink signal; S20, extract the main carrier frequency sequence of the frequency-doubled carrier signal within a set time period; S30, perform frequency doubling inversion on each carrier frequency in the main carrier frequency sequence to obtain the target frequency sequence, which is the carrier frequency sequence of the downlink signal; S40, extract frequency feature information from the target frequency sequence to obtain frequency features; S50 determines the spacecraft's motion parameters based on frequency characteristics.

[0023] The method of this invention acquires the downlink signal of the spacecraft within a set time period and determines the frequency-doubled carrier signal. It then extracts the main carrier frequency sequence of the frequency-doubled carrier signal within the set time period, performs frequency-doubled inversion on the main carrier frequency sequence to obtain the target frequency sequence, extracts frequency feature information from the target frequency sequence to obtain frequency features, and finally determines the motion parameters of the spacecraft based on the frequency features. This method realizes real-time measurement by using the downlink broadband data transmission signal of the spacecraft as the measurement data source and extracting the dynamic change features of the main carrier caused by the motion of the spacecraft through the construction of a carrier recovery full-process algorithm. It does not rely on narrowband carrier signals and effectively solves the problems of high difficulty in dynamic tracking of ground stations and insufficient measurement real-time performance and tracking accuracy caused by the low signal-to-noise ratio, large dynamic Doppler frequency shift and frequency shift change rate of broadband data transmission signals. At the same time, it can rely on the existing data transmission link of the spacecraft to mine the motion state feature information contained in the signal without the need for additional measurement equipment, thus improving the safety and economy of space missions.

[0024] The following specific embodiments further illustrate the solution of the present invention. In these embodiments, the method can rely on the existing data transmission links of spacecraft to mine the motion state characteristic information contained in the signals, which is in line with the development trend of broadband data transmission signals. It can effectively solve measurement technology problems and has important practical significance for improving the safety and economy of space missions and ensuring the smooth implementation of missions.

[0025] Based on this, combined Figure 2 The spacecraft motion measurement method based on broadband data transmission signals provided in this embodiment may include the following steps: S10: Acquire the downlink signal of the spacecraft within a set time period, and recover the frequency-doubled carrier signal based on the downlink signal; Specifically, for ease of description, the downlink broadband data transmission signal transmitted by the spacecraft during orbital maneuvers and attitude changes will be referred to as the downlink signal or data transmission signal below, and this downlink signal will be used as the measurement data source. The downlink signal is a sequence of signals continuously transmitted by the spacecraft within a set duration. For example, in a spacecraft tracking experiment in orbit, the set duration is from 0:00:00 to 0:02:24, and the acquisition parameters are set with a bandwidth of 1MHz and a quantization bit depth of 8 bits.

[0026] The above time points The downlink signal can be determined based on the following formula: ; in, Encoded data under different modulation schemes, For the spacecraft's launch power, The carrier frequency of the downlink signal. This represents the initial phase of the downlink signal.

[0027] To recover the frequency-doubled carrier signal from the downlink signal, the modulation and coding information carried by the downlink signal needs to be eliminated through nonlinear transformation. If the modulation scheme corresponding to the downlink signal is binary phase-shift keying (BPSK) or quadrature phase-shift keying (QPSK), then in S10 above, recovering the frequency-doubled carrier signal from the downlink signal includes: If the modulation method is binary phase shift keying, squaring the downlink signal yields a frequency-doubled carrier signal, which can also be called a 2-fold frequency-doubled carrier signal. If the modulation method is four-phase phase shift keying, the downlink signal is subjected to a fourth power operation to obtain a frequency-doubled carrier signal, which can also be called a 4-fold frequency-doubled carrier signal.

[0028] For downlink signals modulated by binary phase shift keying (BPSK), For downlink signals The squaring operation can be represented as: ; For downlink signals modulated by quadrature phase shift keying (QPSK): ; For downlink signals The fourth power operation can be represented as: ; Optionally, in practical engineering systems, a center frequency of [missing information] can be used. The bandpass filter removes the DC component and the second harmonic component, thus obtaining the fourth harmonic carrier signal.

[0029] S20, extract the main carrier frequency sequence of the frequency-doubled carrier signal within a set time period; Specifically, for a frequency-doubled carrier signal, the primary carrier frequency can be accurately extracted using an open-loop measurement method based on the cross-correlation of the locally reconstructed signal. This involves: first, performing a Fast Fourier Transform (FFT) on the frequency-doubled carrier signal to determine a coarse estimate of the primary carrier frequency and its corresponding frequency band in the frequency domain; second, using the coarse estimate as the center frequency, performing a Linear Frequency Modulation Z-Transform (CZT) on the frequency-doubled carrier signal to refine the spectrum within the local frequency band, obtaining a refined estimate of the primary carrier frequency; and third, reconstructing a sinusoidal signal model using the refined estimate as the reference frequency, cross-correlating the reconstructed signal model with the frequency-doubled carrier signal, and determining the final estimate of the primary carrier frequency based on the correlation peak position. This implementation process is existing technology and will not be elaborated further here.

[0030] Through the above processing, the main carrier frequency sequence within the set time period is obtained. The main carrier frequency sequence is a discrete time sequence, and each element corresponds to the frequency estimate of a sampling time.

[0031] S30, perform frequency doubling inversion on each carrier frequency in the main carrier frequency sequence to obtain the target frequency sequence, which is the carrier frequency sequence of the downlink signal; Specifically, the carrier frequency corresponding to the main carrier frequency sequence is 2 or 4 times the original carrier frequency, and it needs to be accurately recovered. In this scheme, based on the modulation scheme information of the downlink signal, frequency doubling inversion is performed on the main carrier frequency sequence, specifically including: If the modulation method is BPSK, the target frequency sequence is obtained by performing a 2-fold frequency inversion (i.e., dividing by 2) on each carrier frequency in the main carrier frequency sequence. If the modulation method is QPSK, the target frequency sequence is obtained by performing a 4-fold frequency inversion (i.e., dividing by 4) on each carrier frequency in the main carrier frequency sequence.

[0032] The value of the target frequency sequence is equal to the carrier frequency of the downlink signal. The value taken at the corresponding moment restores the original carrier frequency sequence of the downlink signal before modulation.

[0033] S40, extract frequency feature information from the target frequency sequence to obtain frequency features; Specifically, due to the relative motion between the spacecraft and the ground station, the main carrier frequency of the downlink signal received by the ground station from the spacecraft shifts relative to the transmission frequency. These frequency characteristics include the instantaneous values ​​of the target frequency sequence at each moment and the rate of change of the target frequency sequence over a set time period.

[0034] The above S40 includes: Determine the rate of change of the target frequency sequence over a set time period, i.e., perform time differentiation on the target frequency sequence. Define all carrier frequencies (instantaneous values) and their rates of change in the target frequency sequence as frequency characteristics.

[0035] S50 determines the spacecraft's motion parameters based on frequency characteristics.

[0036] Alternatively, one implementation of the above S50 is as follows: Based on all carrier frequencies and frequency change rates in the target frequency sequence, the motion parameters of the spacecraft are calculated using the Doppler frequency formula. These motion parameters include the spacecraft's radial velocity and / or radial acceleration.

[0037] downlink Doppler frequency of spacecraft From the Doppler frequency formula: in, For spacecraft frequency relay ratio, This refers to the uplink transmission frequency from the ground station to the spacecraft. The radial relative velocity of the spacecraft with respect to the ground station. It is the speed of light.

[0038] Under normal operating conditions, the uplink transmission frequency of the ground station to the spacecraft can be considered approximately constant. Taking the time derivative, we get: in, This represents the radial acceleration of the spacecraft relative to the ground station.

[0039] Then, based on all carrier frequencies in the target frequency sequence (i.e. ) and the rate of change of frequency (i.e. Using the Doppler frequency formula described above, the motion parameters of the spacecraft are calculated, including the spacecraft's radial velocity and / or radial acceleration.

[0040] Based on the geometric relationship between the ground station and the spacecraft, if the spacecraft's radial acceleration remains constant within a certain time period, it indicates that the spacecraft did not perform orbital maneuvers or attitude adjustments during that period. If the spacecraft's radial acceleration changes within a certain time period, it indicates that the spacecraft performed maneuvers during that period. The frequency variation of the time-frequency graph reflects the spacecraft's motion changes, and its slope characterizes the spacecraft's radial acceleration.

[0041] The above method was applied to a tracking experiment of an in-orbit spacecraft, and the spectrum of the downlink signal measured was as follows: Figure 3As shown. The frequency-doubled carrier recovery algorithm was used to process the broadband data transmission signal, revealing that the modulation scheme of the spacecraft during this downlink data transmission period was QPSK. The recovered frequency-doubled carrier spectrum is shown below. Figure 4 As shown. The main carrier frequency is accurately extracted, the main carrier frequency is accurately recovered, and the main carrier frequency features are extracted from the frequency-doubled carrier signal. The output measurement results are as follows. Figure 5 As shown.

[0042] Analysis of the spacecraft's Doppler frequency variations revealed a continuous change in radial acceleration between 0:00:00 and 0:02:24, indicating that the spacecraft underwent maneuvers, suggesting that it performed orbital maneuvers and attitude adjustment coupling. After 0:02:24, the radial acceleration remained constant, indicating that the spacecraft ceased all maneuvers and was operating stably. This measurement result closely matches the actual events observed during this observation period, thus validating the effectiveness of the spacecraft motion measurement method based on broadband data transmission signals.

[0043] It should be noted that the measurement of spacecraft motion can be understood as the process of determining motion parameters in this scheme.

[0044] Compared with the prior art, the solution of this application has the following advantages: This invention acquires the downlink signal of a spacecraft within a set time period and determines the frequency-doubled carrier signal. It then extracts the main carrier frequency sequence of the frequency-doubled carrier signal within the set time period, performs frequency-doubled inversion on the main carrier frequency sequence to obtain the target frequency sequence, extracts frequency feature information from the target frequency sequence to obtain frequency features, and finally determines the spacecraft's motion parameters based on the frequency features. This invention achieves real-time measurement using the spacecraft's downlink broadband data transmission signal as the measurement data source. It extracts the dynamic change features of the main carrier caused by spacecraft motion through a fully constructed carrier recovery algorithm, eliminating the need for narrowband carrier signals. This effectively solves the problems of low signal-to-noise ratio, large dynamic Doppler frequency shift, and high frequency shift rate of broadband data transmission signals, which lead to difficulties in dynamic tracking by ground stations and insufficient measurement real-time performance and tracking accuracy. Furthermore, it leverages the existing data transmission link of the spacecraft to mine the motion state feature information contained in the signal without the need for additional measurement equipment, thus improving the safety and economy of space missions.

[0045] Based on and Figure 1 Using the same principle as the method shown, this embodiment of the invention also provides a spacecraft motion process measurement device 20 based on broadband data transmission signals, such as... Figure 6 As shown, the spacecraft motion process measurement device 20 based on broadband data transmission signals may include an acquisition module 210, a main carrier frequency sequence determination module 220, an inversion module 230, an extraction module 240, and a motion parameter determination module 250, wherein: The acquisition module 210 is used to acquire the downlink signal of the spacecraft within a set time period and recover the frequency-doubled carrier signal based on the downlink signal; The main carrier frequency sequence determination module 220 is used to extract the main carrier frequency sequence of the frequency-doubled carrier signal within a set time period; The inversion module 230 is used to perform frequency multiplication inversion on each carrier frequency in the main carrier frequency sequence to obtain the target frequency sequence, which is the carrier frequency sequence of the downlink signal; Extraction module 240 is used to extract frequency feature information from the target frequency sequence to obtain frequency features; The motion parameter determination module 250 is used to determine the motion parameters of the spacecraft based on frequency characteristics.

[0046] Optionally, the modulation scheme corresponding to the downlink signal is binary phase shift keying or quadrature phase shift keying. When the acquisition module 210 recovers the frequency-doubled carrier signal based on the downlink signal, it is specifically used for: If the modulation method is binary phase shift keying, the downlink signal is squared to obtain the frequency-doubled carrier signal; If the modulation method is quadrature phase shift keying, the downlink signal is subjected to a fourth power operation to obtain a frequency-doubled carrier signal.

[0047] Optionally, when the inversion module 230 performs frequency doubling inversion on each carrier frequency in the main carrier frequency sequence to obtain the target frequency sequence, it is specifically used for: If the modulation method is binary phase shift keying, the target frequency sequence is obtained by performing a 2-fold frequency inversion on each carrier frequency in the main carrier frequency sequence. If the modulation method is quadrature phase shift keying, the target frequency sequence is obtained by performing a quadruple frequency inversion on each carrier frequency in the main carrier frequency sequence.

[0048] Optionally, when the extraction module 240 extracts frequency feature information from the target frequency sequence to obtain frequency features, it is specifically used for: Determine the rate of change of the target frequency sequence over a set time period. All carrier frequencies and frequency change rates in the target frequency sequence are identified as frequency characteristics.

[0049] Optionally, when determining the motion parameters of the spacecraft based on frequency characteristics, the aforementioned motion parameter determination module 250 is specifically used for: Based on all carrier frequencies and frequency change rates in the target frequency sequence, the spacecraft's motion parameters are calculated using the Doppler frequency formula. These motion parameters include the spacecraft's radial velocity and / or radial acceleration. The spacecraft motion process measurement device based on broadband data transmission signals in this embodiment of the invention can execute the spacecraft motion process measurement method based on broadband data transmission signals provided in this embodiment of the invention. The implementation principle is similar. The actions performed by each module and unit in the spacecraft motion process measurement device based on broadband data transmission signals in each embodiment of the invention correspond to the steps in the spacecraft motion process measurement method based on broadband data transmission signals in each embodiment of the invention. For detailed functional descriptions of each module of the spacecraft motion process measurement device based on broadband data transmission signals, please refer to the descriptions in the corresponding spacecraft motion process measurement methods based on broadband data transmission signals shown above, which will not be repeated here.

[0050] The aforementioned spacecraft motion process measurement device based on broadband data transmission signals can be a computer program (including program code) running on a computer device. For example, the spacecraft motion process measurement device based on broadband data transmission signals is an application software. The device can be used to execute the corresponding steps in the method provided in the embodiments of the present invention.

[0051] In some embodiments, the spacecraft motion process measurement device based on broadband data transmission signals provided in this invention can be implemented using a combination of hardware and software. As an example, the spacecraft motion process measurement device based on broadband data transmission signals provided in this invention can be a processor in the form of a hardware decoding processor, which is programmed to execute the spacecraft motion process measurement method based on broadband data transmission signals provided in this invention. For example, the processor in the form of a hardware decoding processor can be one or more application-specific integrated circuits (ASICs), DSPs, programmable logic devices (PLDs), complex programmable logic devices (CPLDs), field-programmable gate arrays (FPGAs), or other electronic components.

[0052] In other embodiments, the spacecraft motion measurement device based on broadband data transmission signals provided in this invention can be implemented in software. Figure 6 A spacecraft motion process measurement device based on broadband data transmission signals, stored in a memory, is shown. It can be software in the form of programs and plug-ins, and includes a series of modules, including an acquisition module 210, a main carrier frequency sequence determination module 220, an inversion module 230, an extraction module 240, and a motion parameter determination module 250, for implementing the spacecraft motion process measurement method based on broadband data transmission signals provided in the embodiments of the present invention.

[0053] The modules described in the embodiments of the present invention can be implemented in software or hardware. The names of the modules are not, in some cases, limiting the scope of the module itself.

[0054] Based on the same principles as the methods shown in the embodiments of the present invention, the embodiments of the present invention also provide an electronic device, which may include, but is not limited to: a processor and a memory; the memory for storing computer programs; and the processor for executing the methods shown in any embodiment of the present invention by invoking the computer programs.

[0055] In one alternative embodiment, an electronic device is provided, such as Figure 7 As shown, Figure 7 The illustrated electronic device 4000 includes a processor 4001 and a memory 4003. The processor 4001 and the memory 4003 are connected, for example, via a bus 4002. Optionally, the electronic device 4000 may further include a transceiver 4004, which can be used for data interaction between the electronic device and other electronic devices, such as sending and / or receiving data. It should be noted that in practical applications, the transceiver 4004 is not limited to one type, and the structure of the electronic device 4000 does not constitute a limitation on the embodiments of the present invention.

[0056] Processor 4001 may be a CPU (Central Processing Unit), a general-purpose processor, a DSP (Digital Signal Processor), an ASIC (Application Specific Integrated Circuit), an FPGA (Field Programmable Gate Array), or other programmable logic devices, transistor logic devices, hardware components, or any combination thereof. It can implement or execute the various exemplary logic blocks, modules, and circuits described in conjunction with the disclosure of this invention. Processor 4001 may also be a combination that implements computational functions, such as including one or more microprocessor combinations, a combination of a DSP and a microprocessor, etc.

[0057] Bus 4002 may include a pathway for transmitting information between the aforementioned components. Bus 4002 may be a PCI (Peripheral Component Interconnect) bus or an EISA (Extended Industry Standard Architecture) bus, etc. Bus 4002 can be divided into address bus, data bus, control bus, etc. For ease of representation, Figure 7 The bus is represented by a single thick line, but this does not mean that there is only one bus or one type of bus.

[0058] The memory 4003 may be ROM (Read Only Memory) or other types of static storage devices capable of storing static information and instructions, RAM (Random Access Memory) or other types of dynamic storage devices capable of storing information and instructions, or EEPROM (Electrically Erasable Programmable Read Only Memory), CD-ROM (Compact Disc Read Only Memory) or other optical disc storage, optical disc storage (including compressed optical discs, laser discs, optical discs, digital universal optical discs, Blu-ray discs, etc.), magnetic disk storage media or other magnetic storage devices, or any other medium capable of carrying or storing desired program code in the form of instructions or data structures and accessible by a computer, but not limited thereto.

[0059] The memory 4003 stores application code (computer program) for executing the present invention, and its execution is controlled by the processor 4001. The processor 4001 executes the application code stored in the memory 4003 to implement the content shown in the foregoing method embodiments.

[0060] Among these, electronic devices can also be terminal devices. Figure 7 The electronic device shown is merely an example and should not be construed as limiting the functionality and scope of use of the embodiments of the present invention.

[0061] This invention provides a computer-readable storage medium storing a computer program that, when run on a computer, enables the computer to execute the corresponding content in the aforementioned method embodiments.

[0062] According to another aspect of the present invention, a computer program product or computer program is also provided, comprising computer instructions stored in a computer-readable storage medium. A processor of a computer device reads the computer instructions from the computer-readable storage medium and executes the computer instructions, causing the computer device to perform the methods provided in the various embodiments described above.

[0063] Computer program code for performing the operations of this invention can be written in one or more programming languages ​​or a combination thereof, including object-oriented programming languages ​​such as Java, Smalltalk, and C++, and conventional procedural programming languages ​​such as C or similar languages. The program code can be executed entirely on the user's computer, partially on the user's computer, as a standalone software package, partially on the user's computer and partially on a remote computer, or entirely on a remote computer or server. In cases involving remote computers, the remote computer can be connected to the user's computer via any type of network—including a local area network (LAN) or a wide area network (WAN)—or can be connected to an external computer (e.g., via the Internet using an Internet service provider).

[0064] It should be understood that the flowcharts and block diagrams in the accompanying drawings illustrate the architecture, functionality, and operation of possible implementations of methods and computer program products according to various embodiments of the present invention. In this regard, each block in a flowchart or block diagram may represent a module, segment, or portion of code containing one or more executable instructions for implementing the specified logical function. It should also be noted that in some alternative implementations, the functions indicated in the blocks may occur in a different order than those indicated in the drawings. For example, two consecutively indicated blocks may actually be executed substantially in parallel, and they may sometimes be executed in reverse order, depending on the functions involved. It should also be noted that each block in the block diagrams and / or flowcharts, and combinations of blocks in the block diagrams and / or flowcharts, may be implemented using a dedicated hardware-based system that performs the specified function or operation, or using a combination of dedicated hardware and computer instructions.

[0065] The computer-readable storage medium provided in this invention can be, for example, but not limited to, an electrical, magnetic, optical, electromagnetic, infrared, or semiconductor system, apparatus, or device, or any combination thereof. More specific examples of a computer-readable storage medium may include, but are not limited to: an electrical connection having one or more wires, a portable computer disk, a hard disk, random access memory (RAM), read-only memory (ROM), erasable programmable read-only memory (EPROM or flash memory), optical fiber, portable compact disk read-only memory (CD-ROM), optical storage device, magnetic storage device, or any suitable combination thereof. In this invention, a computer-readable storage medium can be any tangible medium containing or storing a program that can be used by or in conjunction with an instruction execution system, apparatus, or device.

[0066] The aforementioned computer-readable storage medium carries one or more programs, which, when executed by the electronic device, cause the electronic device to perform the method shown in the above embodiments.

[0067] The above description is merely a preferred embodiment of the present invention and an explanation of the technical principles employed. Those skilled in the art should understand that the scope of disclosure in this invention is not limited to technical solutions formed by specific combinations of the above-described technical features, but should also cover other technical solutions formed by arbitrary combinations of the above-described technical features or their equivalents without departing from the above-disclosed concept. For example, technical solutions formed by substituting the above features with (but not limited to) technical features with similar functions disclosed in this invention.

Claims

1. A method for measuring the motion process of a spacecraft based on broadband data transmission signals, characterized in that, include: Acquire the downlink signal of the spacecraft within a set time period, and recover the frequency-doubled carrier signal based on the downlink signal; Extract the main carrier frequency sequence of the frequency-doubled carrier signal within the set time period; Frequency doubling inversion is performed on each carrier frequency in the main carrier frequency sequence to obtain the target frequency sequence, which is the carrier frequency sequence of the downlink signal; Frequency feature information is extracted from the target frequency sequence to obtain frequency features; Based on the frequency characteristics, the motion parameters of the spacecraft are determined.

2. The method according to claim 1, characterized in that, The downlink signal corresponds to a modulation scheme of binary phase shift keying (BPS) or quadruple phase shift keying (QPS), and the step of recovering the frequency-doubled carrier signal based on the downlink signal includes: If the modulation method is binary phase shift keying, the downlink signal is squared to obtain the frequency-doubled carrier signal; If the modulation method is quadrature phase shift keying, the downlink signal is subjected to a fourth power operation to obtain the frequency-doubled carrier signal.

3. The method according to claim 2, characterized in that, The step of performing frequency doubling inversion on each carrier frequency in the main carrier frequency sequence to obtain the target frequency sequence includes: If the modulation method is binary phase shift keying, the target frequency sequence is obtained by performing a 2-fold frequency inversion on each carrier frequency in the main carrier frequency sequence. If the modulation method is quadrature phase shift keying, the target frequency sequence is obtained by performing a quadruple frequency inversion on each carrier frequency in the main carrier frequency sequence.

4. The method according to any one of claims 1 to 3, characterized in that, The step of extracting frequency feature information from the target frequency sequence to obtain frequency features includes: Determine the rate of change of the target frequency sequence within the set time period. The frequency features are defined as all carrier frequencies in the target frequency sequence and the frequency change rate.

5. The method according to claim 4, characterized in that, Determining the spacecraft's motion parameters based on the frequency characteristics includes: Based on all carrier frequencies and frequency change rates in the target frequency sequence, the motion parameters of the spacecraft are calculated using the Doppler frequency formula. These motion parameters include the radial velocity and / or radial acceleration of the spacecraft.

6. A spacecraft motion measurement device based on broadband data transmission signals, characterized in that, include: The acquisition module is used to acquire the downlink signal of the spacecraft within a set time period and recover the frequency-doubled carrier signal based on the downlink signal; The main carrier frequency sequence determination module is used to extract the main carrier frequency sequence of the frequency-doubled carrier signal within the set time period; The inversion module is used to perform frequency doubling inversion on each carrier frequency in the main carrier frequency sequence to obtain a target frequency sequence, wherein the target frequency sequence is the carrier frequency sequence of the downlink signal; The extraction module is used to extract frequency feature information from the target frequency sequence to obtain frequency features; The motion parameter determination module is used to determine the motion parameters of the spacecraft based on the frequency characteristics.

7. The apparatus according to claim 6, characterized in that, The downlink signal corresponds to a modulation scheme of binary phase shift keying (BPS) or quadrature phase shift keying (QPS). When the acquisition module recovers the frequency-doubled carrier signal based on the downlink signal, it is specifically used for: If the modulation method is binary phase shift keying, the downlink signal is squared to obtain the frequency-doubled carrier signal; If the modulation method is quadrature phase shift keying, the downlink signal is subjected to a fourth power operation to obtain the frequency-doubled carrier signal.

8. The apparatus according to claim 7, characterized in that, When the inversion module performs frequency doubling inversion on each carrier frequency in the main carrier frequency sequence to obtain the target frequency sequence, it is specifically used for: If the modulation method is binary phase shift keying, the target frequency sequence is obtained by performing a 2-fold frequency inversion on each carrier frequency in the main carrier frequency sequence. If the modulation method is quadrature phase shift keying, the target frequency sequence is obtained by performing a quadruple frequency inversion on each carrier frequency in the main carrier frequency sequence.

9. An electronic device, characterized in that, It includes a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein the processor executes the computer program to implement the method of any one of claims 1-5.

10. A computer-readable storage medium, characterized in that, The computer-readable storage medium stores a computer program that, when executed by a processor, implements the method of any one of claims 1-5.

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