Multi-dimensional combined spacecraft covert TT&C system and evaluation method

Abstract

The application discloses a kind of multi-dimensional joint spacecraft covert control systems and evaluation methods, belong to satellite covert control technical field, including ground control station and spacecraft control terminal;Ground station antenna is connected with demodulation receiving unit one, demodulation receiving unit one is connected with control service function unit one, control service function unit one is connected with inter-station link unit, service flow selection unit one and internal and external perception unit one respectively, service flow selection unit one is connected with modulation transmitting unit one, modulation transmitting unit includes radio frequency transmitting module one etc..The application improves the robustness of covert control under complex confrontation environment, while ensuring system performance, with strong adaptability, high reliability and other advantages, improve the covert performance of control system in complex environment.

Description

Technical Field

[0001] This invention relates to the field of satellite covert tracking and control technology, and more specifically, to a multi-dimensional joint spacecraft covert tracking and control system and evaluation method. Background Technology

[0002] Space tracking, telemetry, and command (TT&C) is the "lifeline" for all types of spacecraft. With an autonomous operational architecture covering air, space, land, and sea, it constructs a precise control closed loop that spans the entire lifecycle of spacecraft measurement, tracking, and control. Relying on the TT&C network, the system acquires real-time flight trajectories, attitude parameters, and operational status of launch vehicles and spacecraft, providing reliable support for core missions such as high-precision Earth observation and wide-area command and control. It is a significant manifestation of my country's strategic scientific and technological capabilities.

[0003] During telemetry, tracking, and command (TT&C) operations, the long transmission distances and extended exposure times of space TT&C links make them highly susceptible to interception and eavesdropping. Furthermore, the isolated deployment of existing TT&C infrastructure and the open 360° space environment further exacerbate this vulnerability, making TT&C links a weak link in space defense and offense. With the surge in the number of spacecraft deployed in orbit in recent years, the need to improve the stealth of electromagnetic space TT&C signals has become increasingly urgent.

[0004] Currently, covert communication has demonstrated significant research and application value. Most scholars focus on technologies such as non-stationary waveforms, frequency hopping, artificial noise, and beamforming to reduce the detection performance of eavesdroppers. However, telemetry and control systems have unique characteristics compared to communication systems, such as long target distances, long signal exposure times, high telemetry and control requirements, and difficulties in coordinating multiple telemetry and control stations. Therefore, a single method is insufficient to address the complex military and civilian covert telemetry and control needs of today. There is an urgent need to introduce multi-dimensional joint covert methods in terms of waveform, transmission, and configuration for existing space-to-ground telemetry and control scenarios to improve the covert performance of telemetry and control systems. Summary of the Invention

[0005] The purpose of this invention is to overcome the shortcomings of the prior art and provide a multi-dimensional joint spacecraft covert telemetry and control system and evaluation method, which improves the robustness of covert telemetry and control in complex combat environments. While ensuring system performance, it also has the advantages of strong adaptability and high reliability, thereby improving the covert performance of the telemetry and control system in complex environments.

[0006] The objective of this invention is achieved through the following solution: A multi-dimensional joint spacecraft covert tracking and control system includes: In the ground telemetry and control station, the ground station antenna is connected to demodulation receiving unit 1, which in turn is connected to telemetry and control service function unit 1. Telemetry and control service function unit 1 is connected to inter-station link unit, service flow selection unit 1, and internal / external sensing unit 1, respectively. Service flow selection unit 1 is connected to modulation and transmission unit 1, which includes radio frequency transmission module 1. Multiple ground telemetry and control stations are connected via inter-station link unit, which is connected to internal / external sensing unit 1. Internal / external sensing unit 1 is connected to the central concealment decision-making and scheduling unit, which is connected to waveform concealment processing module 1 and transmission concealment module 1, respectively. The system includes a processing module 1, a waveform concealment processing module 1, a service flow selection module 1, and an inter-station link unit. The waveform concealment processing module 1, the transmission concealment processing module 1, and the waveform concealment processing module 1 are respectively connected to the modulation, beamforming, and RF transmission modules 1 to complete the concealment processing. Then, the RF transmission module 1 is connected to the ground station antenna and the performance evaluation unit 1. Part of the signal is transmitted to the spacecraft through the uplink telemetry and control link, and the other part of the signal is transmitted back to the internal and external sensing units 1 through the performance evaluation unit 1 to form a closed loop. The performance evaluation unit 1 is connected to the central concealment decision and scheduling unit to provide a reference for decision and scheduling. In the spacecraft telemetry, tracking, and command (TT&C) terminal, the spacecraft antenna is connected to demodulation receiving unit two, which in turn is connected to TT&C service function unit two. TT&C service function unit two is connected to inter-satellite link unit two, service flow selection unit two, and internal / external sensing unit two, respectively. Service flow selection unit two is connected to modulation and transmission unit two, which includes radio frequency transmission module two. The inter-satellite link unit is connected to internal / external sensing unit two, which is connected to lightweight covert decision-making and scheduling unit two. Lightweight covert decision-making and scheduling unit two is connected to waveform covert processing module two and transmission covert processing module two, respectively. The system includes waveform concealment processing module 2, service flow selection module 2, and inter-satellite link unit. Waveform concealment processing module 2 and transmission concealment processing module 2 are connected to modulation, beamforming, and radio frequency transmission module 2 respectively to complete concealment processing. Radio frequency transmission module 2 is then connected to the spacecraft antenna and performance evaluation unit 2. Part of the signal is transmitted to the ground via the downlink telemetry and control link, while another part of the signal is transmitted back to the internal and external sensing units via performance evaluation unit 2 to form a closed loop. Performance evaluation unit 2 is also connected to the lightweight concealment decision-making and scheduling unit to provide a reference for decision-making and scheduling.

[0007] Furthermore, the demodulation receiving unit includes a ground-side radio frequency receiving, preprocessing, synchronization, demodulation, decoding, and deframe module.

[0008] Furthermore, the measurement and control service unit includes ground-based remote control, telemetry, data transmission, and measurement modules.

[0009] Furthermore, the modulation and transmission unit includes a ground-side framing, encoding, modulation, and beamforming module.

[0010] Furthermore, the demodulation receiving unit two includes radio frequency receiving, preprocessing, synchronization, demodulation, decoding, and frame deframe modules for the aviation end.

[0011] Furthermore, the second telemetry and control service unit includes remote control, telemetry, data transmission, and ranging modules for the aviation end.

[0012] Furthermore, the second modulation and transmission unit includes framing, encoding, modulation, and beamforming at the airborne end.

[0013] Furthermore, multiple ground tracking and control stations are connected through inter-station link units; multiple spacecraft tracking and control terminals are connected through inter-satellite link units.

[0014] A multi-dimensional joint spacecraft stealth measurement, control, and evaluation method, based on the system described above, includes the following steps: First, information from the inter-station link unit and the telemetry and control service function unit is sent to the internal and external sensing unit. The internal and external sensing unit combines the telemetry and control information, inter-station link information, and the acquired electromagnetic signal type and strength, as well as the internal resource status of the sensing system, to drive the central concealment decision-making and scheduling unit to obtain different concealment strategies. Based on these concealment strategies, it selects transmission concealment, configuration concealment, or waveform concealment methods, adjusting modulation, beamforming, and RF transmission unit parameters to achieve ground-end concealment processing; and... The information from the inter-satellite link unit and the second telemetry and control service function unit is sent to the second internal and external sensing unit. The second internal and external sensing unit combines the telemetry and control information, the inter-satellite link information, and the type and intensity of the acquired electromagnetic signals, as well as the internal resource status of the sensing system, to drive the lightweight covert decision-making and scheduling unit to make preliminary decisions. If the mission is complex, it interacts with the central covert decision-making and scheduling unit to make auxiliary decisions on the ground. Afterwards, it is transmitted back to the spacecraft telemetry and control terminal to obtain different covert strategies. Based on the covert strategies, it drives the selection of transmission covert, configuration covert, or waveform covert methods, and adjusts the modulation, beamforming, and radio frequency transmission unit parameters to achieve covert processing at the space end. After concealment processing at the ground and space ends, the concealment results are sent to the corresponding effect evaluation unit. By establishing a concealment evaluation system, the effectiveness of the concealment method and the availability of the telemetry and control system are evaluated and the parameters are updated. The results are then sent to the central concealment decision-making and scheduling unit / lightweight concealment decision-making and scheduling unit and the corresponding internal and external sensing units to complete the dynamic feedback closed loop.

[0015] The beneficial effects of this invention include: This invention provides a multi-dimensional joint spacecraft covert telemetry and control system and evaluation method. Compared with traditional single-method covert systems, it deeply integrates waveform layer "feature camouflage," transmission layer "space protection," and configuration layer "dynamic camouflage," and jointly constructs a three-dimensional integrated covert system of "signal-channel-space" through a combined covert telemetry and control evaluation model. The three-dimensional system is complementary: the waveform layer ensures data is "difficult to crack," the transmission layer achieves signal "invisibility," and the configuration layer ensures system "resistance to destruction." These three elements work together to improve the robustness of covert telemetry and control in complex adversarial environments. The joint covert evaluation system completes the closed-loop of the covert telemetry and control system, ensuring system performance while possessing advantages such as strong adaptability and high reliability, thus improving the covert performance of the telemetry and control system in complex environments. Attached Figure Description

[0016] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0017] Figure 1 This is a schematic diagram of a concealed scenario for a satellite telemetry and control system according to an embodiment of the present invention; Figure 2 This is a schematic diagram illustrating the implementation of the multi-dimensional joint spacecraft covert telemetry and control system according to an embodiment of the present invention. Detailed Implementation

[0018] All features disclosed in all embodiments of this specification, or steps in all methods or processes implied in the disclosure, may be combined and / or extended or replaced in any way, except for mutually exclusive features and / or steps.

[0019] In view of the current situation, the object of the present invention is: To address the challenges of long transmission distances and extended exposure times during satellite telemetry and control (TT&C), making signals susceptible to interception and eavesdropping, which can disrupt the normal operation of the TT&C link, and the difficulty of addressing the complex military and civilian covert TT&C requirements with single methods, this paper proposes a multi-dimensional joint spacecraft covert TT&C system and evaluation method. This system deeply integrates waveform-level "feature camouflage," transmission-level "space protection," and configuration-level "dynamic camouflage," combining these elements with a covert TT&C evaluation model to construct a three-dimensional covert system encompassing "signal-channel-space." The three-dimensional system is complementary: the waveform layer ensures data is "difficult to crack," the transmission layer achieves signal "invisibility," and the configuration layer ensures system "resistance to destruction." These three elements synergistically enhance the robustness of covert TT&C in complex adversarial environments, and the joint covert evaluation system completes the closed-loop covert TT&C system.

[0020] To address the stealth requirements of the uplink, the system is centered on a ground station, centrally deploying key functional units such as internal and external sensing, method decision-making, stealth processing, and performance evaluation. The spacecraft, in conjunction with the telemetry, tracking, and command (TT&C) station, performs signal reception, demodulation, and data reconstruction, ensuring the safety and efficiency of uplink TT&C. In the downlink, the system is spacecraft-led, equipped with lightweight sensing, decision-making, processing, and evaluation functions. Combined with the auxiliary sensing capabilities of the TT&C station, it completes stealth TT&C, while the ground station handles signal demodulation and recovery.

[0021] A detailed explanation will be given using the telemetry and control uplink as an example, such as... Figure 1 As shown, a covert telemetry and control loop is established in the telemetry and control station, consisting of units for internal and external sensing, method decision-making, covert processing, and effect evaluation. This loop drives the covert telemetry and control system through a closed-loop link. Specifically, the internal and external sensing units acquire the type and intensity of electromagnetic signals, as well as the status of resources within the sensing system, comprehensively analyzing the location of potential eavesdroppers and the degree of threat they pose to the system. Secondly, based on the sensing results and task attributes, the decision-making unit makes decisions on covert methods. Subsequently, resources such as antennas, CPUs, and channels are scheduled to achieve system covert processing, including telemetry and control waveform covertness, spatial transmission covertness, and multi-station configuration covertness. Finally, based on the effectiveness evaluation unit, the effectiveness of the covert methods and the operational availability of the telemetry and control system are evaluated and parameters are updated, completing dynamic feedback.

[0022] More specifically, as a first aspect of the present invention, in one embodiment, a multi-dimensional joint spacecraft covert telemetry and control system is provided, such as... Figure 2 As shown, it includes: At ground control station one, the ground station antenna is connected to demodulation and reception unit one. Demodulation and reception unit one includes a ground-side module for radio frequency reception, preprocessing, synchronization, demodulation, decoding, and deframing. Demodulation and reception unit one is connected to telemetry and control service function unit one. Telemetry and control service unit one includes ground-side remote control, telemetry, data transmission, and measurement. Telemetry and control service unit one is connected to inter-station link unit one, service flow selection unit one, and internal and external sensing unit one, respectively. Service flow selection unit one is connected to modulation and transmission unit one. Modulation and transmission unit one includes a ground-side module for framing, encoding, modulation, beamforming, and radio frequency transmission. Multiple ground control stations are connected through inter-station link units, which are connected to internal and external sensing unit one. The internal and external sensing unit 1 is connected to the central concealment decision-making and scheduling unit. The decision-making and scheduling unit is connected to the waveform concealment processing, transmission concealment processing, waveform concealment processing, service flow selection and inter-station link unit on the ground. The waveform concealment processing, transmission concealment processing and waveform concealment processing modules are connected to the modulation, beamforming and radio frequency transmission modules to complete the concealment processing. Then, the radio frequency transmission unit 1 is connected to the ground station antenna and the performance evaluation unit 1. Part of the signal is transmitted to the spacecraft through the uplink telemetry and control link, and the other part of the signal is transmitted back to the internal and external sensing unit 1 through the performance evaluation unit 1 to form a closed loop. The performance evaluation unit 1 is also connected to the central concealment decision-making and scheduling unit to provide a reference for decision-making and scheduling.

[0023] In the spacecraft telemetry, tracking, and command (TT&C) terminal, the spacecraft antenna is connected to demodulation receiving unit two. Demodulation receiving unit two includes RF reception, preprocessing, synchronization, demodulation, decoding, and deframe modules for the spacecraft. Demodulation receiving unit two is also connected to TT&C service function unit two, which includes remote control, telemetry, data transmission, and ranging. TT&C service unit two is connected to inter-satellite links, service flow selection unit two, and internal / external sensing unit two, respectively. Service flow selection unit two is connected to modulation and transmission unit two, which includes framing, encoding, modulation, beamforming, and RF transmission modules for the spacecraft. Multiple spacecraft TT&C terminals are connected via inter-satellite link units, which are connected to internal / external sensing units two. Sensing Unit 2 is connected to the Lightweight Covert Decision-Making and Scheduling Unit. The Lightweight Covert Decision-Making and Scheduling Unit is connected to the waveform covert processing, transmission covert processing, waveform covert processing, service flow selection, and inter-satellite link units at the space end. The waveform covert processing, transmission covert processing, and waveform covert processing modules are connected to the modulation, beamforming, and RF transmission modules 2 to complete the covert processing. Then, the RF transmission unit 2 is connected to the spacecraft antenna and the performance evaluation unit 2. Part of the signal is transmitted to the ground end through the downlink telemetry and control link, and another part of the signal is transmitted back to the internal and external sensing units 2 through the performance evaluation unit 2 to form a closed loop. The performance evaluation unit 2 is also connected to the Lightweight Covert Decision-Making and Scheduling Unit to provide a reference for decision-making and scheduling.

[0024] Furthermore, Figure 2 The solid line represents the normal telemetry and control (TT&C) service flow and the perception-decision-processing-evaluation loop, while the dashed line represents the control flow that enables covert functions. For the ground end, after the antenna receives the downlink TT&C link signal, it sends it to demodulation receiving unit one. Demodulation receiving unit one processes the downlink signal, completing basic tasks such as signal preprocessing, synchronization, demodulation, decoding, and deframe based on the prior information exchanged between the lightweight covert decision-scheduling unit and the central covert decision-scheduling unit. Then, it sends the deframed signal to TT&C service function unit one. TT&C service function unit one receives the signal after demodulation receiving unit one and implements remote control, telemetry, data transmission, and ranging services. Service flow selection unit one selects whether to add covert processing functions to the normal TT&C service flow and generates uplink signals from the uplink transmission mode / parameters sent by TT&C service function unit one, which are then sent to modulation transmission unit one for framing, encoding, modulation, and beamforming.

[0025] In another embodiment, based on the above system embodiment, a multi-dimensional joint spacecraft covert measurement and control evaluation method is provided, including covert processing at the ground end and covert processing at the space end.

[0026] At the ground end, information from the inter-station link unit and the telemetry and control service function unit is sent to the internal and external sensing unit. The internal and external sensing unit combines the telemetry and control information, the inter-station link information, and the type and intensity of the acquired electromagnetic signal, as well as the internal resource status of the sensing system, to drive the central concealment decision-making and scheduling unit to obtain different concealment strategies, including whether to perform concealment processing, the selection of concealment processing methods, and the scheduling rules of resources such as antennas, CPUs, and channels. Based on the concealment strategy, the unit selects transmission concealment, configuration concealment, or waveform concealment, and adjusts the parameters of the modulation, beamforming, and radio frequency transmission units to achieve concealment processing.

[0027] In the aerospace sector, for the spacecraft telemetry and control terminal, after the antenna receives the uplink telemetry and control link signal, it sends it to demodulation receiving unit two. Demodulation receiving unit two processes the uplink signal, and based on the prior information exchanged between the lightweight covert decision-making and scheduling unit and the central covert decision-making and scheduling unit, it completes basic tasks such as signal preprocessing, synchronization, demodulation, decoding, and deframing. Then, it sends the deframing signal to telemetry and control service function unit two. Telemetry and control service function unit two receives the signal after demodulation receiving unit two and implements service functions such as remote control, telemetry, data transmission, and ranging. Service flow selection unit two selects whether to enable covert processing according to the covert strategy, and generates downlink signals from the downlink transmission mode / parameters sent by telemetry and control service function unit two, and then sends them to modulation transmission unit two for framing, encoding, modulation, and beamforming.

[0028] In addition, the information from the inter-satellite link unit and the second telemetry and control service function unit is sent to the second internal and external sensing unit. The second internal and external sensing unit combines the telemetry and control information, the inter-satellite link information, and the type and intensity of the acquired electromagnetic signals, as well as the internal resource status of the sensing system, to drive the lightweight covert decision-making and scheduling unit to make preliminary decisions. If the task is more complex, it will interact with the central covert decision-making and scheduling unit to make auxiliary decisions on the ground segment. Then, it will be transmitted back to the spacecraft to obtain different covert strategies, including whether to carry out covert processing, the selection of covert processing methods, and the scheduling rules of resources such as antennas, CPUs, and channels. Based on the covert strategy, the selection of transmission covert, configuration covert, or waveform covert units is driven, and the parameters of modulation, beamforming, and radio frequency transmission units are adjusted to achieve covert processing.

[0029] More specifically, the concealment methods include waveform concealment, designing non-stationary measurement and control waveforms, and achieving multi-dimensional parameter randomization through parameter manipulation of symbols, chips, and carrier frequencies. This disrupts the eavesdropper's ability to match and identify signal characteristics, preventing the exposure of system operation patterns due to fixed waveforms. Traditional waveforms have fixed symbol durations and rates, while in non-stationary measurement and control waveforms, the duration of each symbol is random, and the rate also varies randomly. Therefore, the cyclostationarity of the signal can be suppressed, reducing the probability of signal interception.

[0030] The transmission concealment process utilizes phased array antennas to enhance radiation capabilities in the direction of legitimate users from a spatial perspective through beamforming and artificial noise techniques, while achieving energy blanking and sidelobe noise reduction in the reconnaissance direction, thus concealing the signal. More specifically, by injecting artificial noise into the sidelobe region of the beam and ensuring its orthogonality to the main lobe signal, the signal constellation diagram received by the eavesdropping party is severely distorted, preventing them from correctly demodulating the information. Simultaneously, in the main lobe direction, the signal received by the spacecraft exhibits only minor amplitude fluctuations, enabling accurate demodulation of the transmitted information. This technique significantly alters the signal characteristics of the beam's sidelobe region without affecting the main lobe signal, reducing the eavesdropping party's efficiency in detecting and utilizing the sidelobe signal, thereby achieving concealed telemetry and control.

[0031] The concealed beamforming configuration employs distributed beamforming technology. By precisely controlling the phase and amplitude of antenna elements, it not only optimizes the focusing gain of the main lobe in the target direction and creates a deep null in the direction of the listening node, but also achieves angle-range domain beamforming. More specifically, using distributed beamforming technology, antenna nodes collaborate through data sharing, and the main telemetry and control station / master satellite makes dynamic mission decisions and antenna scheduling based on real-time resource status. During the collaborative beamforming process, by precisely controlling the phase and amplitude of antenna elements, it not only optimizes the focusing gain of the main lobe in the target direction and creates a deep null in the direction of the listening node, but also achieves angle-range domain beamforming. Compared to conventional beamforming technology, this solves the risk of difficulty in avoiding eavesdropping in the same direction and reduces the probability of signal interception. Among them, distributed beam coordination technology relies on inter-station link units / inter-satellite link units for multi-station / multi-satellite coordination. The inter-station link units / inter-satellite link units extract parameters based on telemetry, remote control and other information in the telemetry and control business function units, and receive decision and scheduling instructions from the master telemetry and control station / master satellite through antennas to realize time synchronization of master and slave telemetry and control station / master and slave satellite systems, multi-station / multi-satellite data distribution, and calculation of satellite-to-ground distance between distributed telemetry and control stations / distributed satellite arrays, thus completing high-speed interconnection and coordination between distributed telemetry and control stations / distributed satellite arrays.

[0032] After multi-domain joint concealment processing, the concealment results are sent to the effectiveness evaluation unit. By establishing a concealment evaluation system, the effectiveness of the concealment method and the operational availability of the measurement and control system are assessed, and parameters are updated. These updates are then sent to the central concealment decision-making and scheduling unit / lightweight concealment decision-making and scheduling unit and internal and external sensing units to complete a dynamic feedback loop. Specifically, the assessment of concealment effectiveness and the operational availability of the measurement and control system include: 1) Covert transmission rate Taking the uplink signal of the telemetry, tracking, and command (TT&C) system as an example, when conducting TT&C operations, an achievable covert rate is defined, which is the rate from the ground TT&C station to the spacecraft. Rate from ground control station to listening station The difference, of which and For a finite codeword length, the rate can be expressed as follows: (1); in, That is, when Greater than At that time, the achievable concealment rate is 0, and the system basically has no concealment performance. Greater than At that time, the system possesses stealth capabilities.

[0033] achievable concealment rate This can be further expressed as: (2); in, and These are the signal-to-noise ratios for the legitimate party and the eavesdropping party, respectively.

[0034] 2) Detection error probability From the perspective of the monitoring party, taking the uplink signal of telemetry and control as an example, according to signal detection theory, in order to determine whether the telemetry and control station is transmitting information, the monitoring party's detection can be regarded as a binary hypothesis testing process, that is, the monitoring party needs to distinguish between the following two hypotheses: (3); in, It is a measurement and control signal. The mean is 0 and the variance is Additive white Gaussian noise, This means that the monitoring party did not receive the monitoring and control signal; This indicates that the monitoring party has received the monitoring and control signal. The monitoring party will use a radiometer to detect the power level of the surrounding environment and can make different decisions, as shown below: (4); in, A pre-set threshold for the eavesdropper; when the eavesdropper receives a signal with a certain power... < At that time, the listening party supports the hypothesis. Decision Conversely, a decision is made. ,support The error probabilities for the two scenarios are respectively... (5); The overall detection error probability is as follows: (6); From a worst-case perspective, if the eavesdropper employs the optimal detection method to achieve the minimum probability of detection errors, then the concealment constraint can be expressed as: Among them, concealment tolerance It is a predetermined value, and The smaller the size, the higher the level of concealment performance.

[0035] 3) Latency jitter Time delay jitter is not a fixed delay, but rather a dynamic characteristic that fluctuates rapidly and randomly around the mean time delay. The aforementioned multi-station / satellite configuration concealment techniques, and the method of scheduling different antennas to relay telemetry and control signals, will introduce time delay jitter, causing the receiver's phase-locked loop to lose lock, thus affecting the effectiveness and reliability of telemetry and control services. Time delay jitter can be expressed as follows: (7); in, For the first i The actual transmission delay of each data packet For average delay, N This represents the number of data packets.

[0036] Time delay jitter will cause phase error accumulation, which can be expressed as: (8); in, For carrier frequency; The phase-locked loop (PLL) will lose lock when the phase error accumulates beyond a threshold. > (9); From the above formula, we can obtain the upper limit of the allowable latency jitter: (10); Therefore, during covert monitoring and control, it is necessary to monitor latency jitter in real time. If the latency jitter exceeds the acceptable threshold during the monitoring and control process, the system will take action. If the result is positive, it proves that the concealed measurement and control process is abnormal; otherwise, it means that the concealed system can ensure the normal operation of the measurement and control system while improving its concealment.

[0037] 4) Measurement accuracy Measurement accuracy refers to the error between the distance measurement, velocity measurement, and angle measurement results involved in the measurement and control system and the actual parameters. A QOS evaluation system for the measurement and control system is constructed to complete the measurement accuracy assessment. The specific steps are as follows: The distance measurement error, velocity measurement error, and angle measurement error are respectively... , as well as .

[0038] ① Normalization processing First of all , as well as Normalization was performed using the range method: (11); (12); (13); ② Set weights The weights of the three indicators—distance measurement, velocity measurement, and angle measurement—can be determined based on expert scoring, entropy weighting, principal component analysis, and other methods. , , .

[0039] ③ Measurement accuracy of the measurement and control system (14); When QoS is close to 1, it indicates that the system's measurement accuracy is good and it is not affected by the concealment function; when QoS is close to 0, it indicates that the system's measurement accuracy is poor and the system cannot guarantee the normal operation of measurement and control services.

[0040] Finally, the parameters are updated based on the evaluation results and sent to the central covert decision-making and scheduling unit / lightweight covert decision-making and scheduling unit and the internal and external sensing 12 units to complete the dynamic feedback closed loop.

[0041] In summary, this invention addresses the need for constructing covert telemetry and control links by building a three-dimensional covert processing method that integrates waveform concealment, transmission masking, and configuration concealment. This ensures that waveform layer data is "difficult to crack," transmission layer signals are "invisible," and the configuration layer system is "resistant to destruction." These three elements synergistically enhance the robustness of covert telemetry and control in complex adversarial environments. Furthermore, by combining internal and external sensing, method decision-making, and effectiveness evaluation, a closed-loop enhancement effect is formed, realizing a multi-dimensional joint spacecraft covert telemetry and control system. The beneficial effects of this method can be applied not only to satellite telemetry and control but also extended to the telemetry and control of missiles and other spacecraft.

[0042] The units described in the embodiments of the present invention can be implemented in software or hardware, and the described units can also be located in a processor. The names of these units do not necessarily limit the specific unit itself.

[0043] According to one aspect of the present invention, a computer program product or computer program is provided, the computer program product or computer program including 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 optional implementations described above.

[0044] In another aspect, embodiments of the present invention also provide a computer-readable medium, which may be included in the electronic device described in the above embodiments; or it may exist independently and not assembled into the electronic device. The computer-readable medium carries one or more programs, which, when executed by the electronic device, cause the electronic device to perform the methods described in the above embodiments.

Claims

1. A multi-dimensional joint spacecraft covert telemetry and control system, characterized in that, include: In the ground telemetry and control station, the ground station antenna is connected to demodulation receiving unit 1, which in turn is connected to telemetry and control service function unit 1. Telemetry and control service function unit 1 is connected to inter-station link unit, service flow selection unit 1, and internal / external sensing unit 1, respectively. Service flow selection unit 1 is connected to modulation and transmission unit 1, which includes radio frequency transmission module 1. Multiple ground telemetry and control stations are connected via inter-station link unit, which is connected to internal / external sensing unit 1. Internal / external sensing unit 1 is connected to the central concealment decision-making and scheduling unit, which is connected to waveform concealment processing module 1 and transmission concealment module 1, respectively. The system includes a processing module 1, a waveform concealment processing module 1, a service flow selection module 1, and an inter-station link unit. The waveform concealment processing module 1, the transmission concealment processing module 1, and the waveform concealment processing module 1 are respectively connected to the modulation, beamforming, and RF transmission modules 1 to complete the concealment processing. Then, the RF transmission module 1 is connected to the ground station antenna and the performance evaluation unit 1. Part of the signal is transmitted to the spacecraft through the uplink telemetry and control link, and the other part of the signal is transmitted back to the internal and external sensing units 1 through the performance evaluation unit 1 to form a closed loop. The performance evaluation unit 1 is connected to the central concealment decision and scheduling unit to provide a reference for decision and scheduling. In the spacecraft telemetry, tracking, and command (TT&C) terminal, the spacecraft antenna is connected to demodulation receiving unit two, which in turn is connected to TT&C service function unit two. TT&C service function unit two is connected to inter-satellite link unit two, service flow selection unit two, and internal / external sensing unit two, respectively. Service flow selection unit two is connected to modulation and transmission unit two, which includes radio frequency transmission module two. The inter-satellite link unit is connected to internal / external sensing unit two, which is connected to lightweight covert decision-making and scheduling unit two. Lightweight covert decision-making and scheduling unit two is connected to waveform covert processing module two and transmission covert processing module two, respectively. The system includes waveform concealment processing module 2, service flow selection module 2, and inter-satellite link unit. Waveform concealment processing module 2 and transmission concealment processing module 2 are connected to modulation, beamforming, and radio frequency transmission module 2 respectively to complete concealment processing. Radio frequency transmission module 2 is then connected to the spacecraft antenna and performance evaluation unit 2. Part of the signal is transmitted to the ground via the downlink telemetry and control link, while another part of the signal is transmitted back to the internal and external sensing units via performance evaluation unit 2 to form a closed loop. Performance evaluation unit 2 is also connected to the lightweight concealment decision-making and scheduling unit to provide a reference for decision-making and scheduling.

2. The multi-dimensional joint spacecraft covert telemetry and control system according to claim 1, characterized in that, The demodulation receiving unit includes a ground-side radio frequency receiving, preprocessing, synchronization, demodulation, decoding, and frame deframe module.

3. The multi-dimensional joint spacecraft covert telemetry and control system according to claim 1, characterized in that, The measurement and control service unit includes ground-based remote control, telemetry, data transmission, and measurement modules.

4. The multi-dimensional joint spacecraft covert telemetry and control system according to claim 1, characterized in that, The modulation and transmission unit includes ground-side framing, encoding, modulation, and beamforming modules.

5. The multi-dimensional joint spacecraft covert telemetry and control system according to claim 1, characterized in that, The demodulation receiving unit 2 includes radio frequency reception, preprocessing, synchronization, demodulation, decoding, and frame deframe modules for the aviation end.

6. The multi-dimensional joint spacecraft covert telemetry and control system according to claim 1, characterized in that, The second measurement and control service unit includes remote control, telemetry, data transmission, and ranging modules for the aviation end.

7. The multi-dimensional joint spacecraft covert telemetry and control system according to claim 1, characterized in that, The modulation and transmission unit 2 includes framing, encoding, modulation, and beamforming at the airborne end.

8. The multi-dimensional joint spacecraft covert tracking and control system according to claim 1, characterized in that, Multiple ground tracking and control stations are connected through inter-station link units; multiple spacecraft tracking and control terminals are connected through inter-satellite link units.

9. A multi-dimensional joint spacecraft stealth measurement and control evaluation method, characterized in that, The system based on claim 8 includes the following steps: First, information from the inter-station link unit and the telemetry and control service function unit is sent to the internal and external sensing unit. The internal and external sensing unit combines the telemetry and control information, inter-station link information, and the acquired electromagnetic signal type and strength, as well as the internal resource status of the sensing system, to drive the central concealment decision-making and scheduling unit to obtain different concealment strategies. Based on these concealment strategies, it selects transmission concealment, configuration concealment, or waveform concealment methods, adjusting modulation, beamforming, and RF transmission unit parameters to achieve ground-end concealment processing; and... The information from the inter-satellite link unit and the second telemetry and control service function unit is sent to the second internal and external sensing unit. The second internal and external sensing unit combines the telemetry and control information, the inter-satellite link information, and the type and intensity of the acquired electromagnetic signals, as well as the internal resource status of the sensing system, to drive the lightweight covert decision-making and scheduling unit to make preliminary decisions. If the mission is complex, it interacts with the central covert decision-making and scheduling unit to make auxiliary decisions on the ground. Afterwards, it is transmitted back to the spacecraft telemetry and control terminal to obtain different covert strategies. Based on the covert strategies, it drives the selection of transmission covert, configuration covert, or waveform covert methods, and adjusts the modulation, beamforming, and radio frequency transmission unit parameters to achieve covert processing at the space end. After concealment processing at the ground and space ends, the concealment results are sent to the corresponding effect evaluation unit. By establishing a concealment evaluation system, the effectiveness of the concealment method and the availability of the telemetry and control system are evaluated and the parameters are updated. The results are then sent to the central concealment decision-making and scheduling unit / lightweight concealment decision-making and scheduling unit and the corresponding internal and external sensing units to complete the dynamic feedback closed loop.

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