Electromagnetic pulse counter drone system

Abstract

This invention relates to the field of air traffic management technology and discloses an electromagnetic pulse anti-UAV system, comprising: an approach control airspace spatiotemporal topology reconstruction unit, a pulse energy radiation monitoring unit, and a control link timing rescheduling unit for controlled aircraft. This invention identifies non-cooperative UAVs within the approach control airspace where normally managed aircraft are operating, delineates restricted and blocked airspace cavities, acquires strong electromagnetic pulse energy emission timing parameters, and adjusts the downlink control data frame transmission timing of the normally managed aircraft's radio control link accordingly. It reads pulse emission period parameters and energy field dissipation cutoff time parameters, inserts transmission phase deviations into the downlink control data frames, and controls their arrival time to fall within the electromagnetic interference disappearance time domain interval. This invention enables control data frames to be precisely interleaved on the time axis during the pulse ignition vacuum period, eliminating transient impacts on the saturation interference of the aircraft's radio control link and ensuring the continuous steady state of the operating topology within the terminal's approach control airspace.

Description

Technical Field

[0001] This invention belongs to the field of air traffic management technology, and in particular relates to an electromagnetic pulse anti-drone system. Background Technology

[0002] Maintaining the continuity of aircraft arrivals is a core objective. The usual practice is to rely on setting spatial safety intervals to regulate the approach tracks of multiple aircraft. However, when low-altitude non-cooperative targets intrude into the airport's operational airspace, the use of high-power radio frequency radiation fields to clear them can cause sudden changes in the local energy field. This exogenous high-power transient electromagnetic radiation causes multipath signal flickering disturbances in ground surveillance radar systems and puts the wireless data transmission links of compliant managed aircraft within the control area under saturation impact, resulting in blind spots in avionics front-end receivers or sudden interruptions in control data frames, thus disrupting the original steady-state scheduling topology of the air traffic network.

[0003] To avoid secondary conflicts caused by the aforementioned failures, conventional systems employ avoidance strategies such as expanding physical no-fly zones or forcibly altering the control trajectories of dense flight flows. However, this linear optimization path, which simply increases spatial spacing or rigidly modifies flight routes, cannot resolve the fundamental conflict between the release of local electromagnetic treatment energy fields and the transmission of traffic control commands. Expanding the safety retreat envelope can cause traffic flow delays in adjacent dense approach sectors, leading to a decrease in the overall throughput efficiency of the hub airport. This deficiency lies in the uncoupling between the excitation action of external electromagnetic treatment energy and the spatiotemporal grid scheduling of internal traffic flows, preventing aircraft control sequences from providing feedforward responses to the transient dissipation patterns of electromagnetic energy. Existing status monitoring and early warning control methods in management and scheduling systems also have shortcomings, for example, as described in publication number CN1212. Chinese invention patent application 81326A discloses a monitoring and early warning management system and method for unmanned aerial vehicles (UAVs) in airspace. It constructs a simulated image by acquiring the real-time spatial coordinates of the UAV and compares it with the infrared and visible light contour recognition to determine the interference status. This method relies on the ideal technical premise that the aircraft continuously transmits its own spatial coordinates with high precision. Under the condition of high-power transient electromagnetic radiation or strong electromagnetic energy field release, the wireless data transmission link of the compliant managed aircraft is subjected to saturation impact, which leads to sudden interruption of downlink status report frames or data distortion. Existing technologies lack feedforward perception of the transient dissipation law of electromagnetic energy, and the simulated image used for comparison loses the real coordinate reference and cannot be accurately generated, causing large-area false alarms or control gaps. It is impossible to maintain the continuous and smooth flow of control commands in strong electromagnetic confrontation scenarios.

[0004] Therefore, the technical problem to be solved by this invention is how to achieve continuous and smooth air traffic control command flow and active decoupling control of handling energy in the scenario of overlapping external electromagnetic radiation and multi-aircraft approach topology through time-sequential peak flow, spatial heterogeneous diversion and downlink token interlocking. Summary of the Invention

[0005] The present invention aims to solve the problem of maintaining a continuous and unobstructed flow of air traffic control commands in adversarial scenarios involving external electromagnetic radiation and overlapping topologies during multi-aircraft approach.

[0006] In this technical solution, an electromagnetic pulse anti-drone system includes: The approach control airspace spatiotemporal topology reconstruction unit is used to identify non-cooperative drones in the approach control airspace where normally managed aircraft are operating, and to delineate the limiting blocking airspace cell that locks the three-dimensional radiation energy field boundary of non-cooperative drones. The pulse energy radiation monitoring unit is coupled with the approach control airspace spatiotemporal topology reconstruction unit to obtain the transmission timing parameters of strong electromagnetic pulse energy emitted into the confined and blocked airspace cavity. The air traffic control link timing rescheduling unit interacts with the approach control airspace spatiotemporal topology reconstruction unit and the pulse energy radiation monitoring unit, respectively. Based on the transmission timing parameters, it adjusts the downlink control data frame transmission timing of the radio control link for normally managed aircraft within the previously reconstructed approach control airspace. The air traffic control link timing rescheduling unit completes the following steps: Step S1: Read the pulse emission period parameters and energy field dissipation cutoff time parameters input by the pulse energy radiation monitoring unit; Step S2: Based on the pulse transmission period parameter and the energy field dissipation cutoff time parameter, perform time axis interpolation phase shift operation on the downlink control data frame in the time domain to control the data transmission clock segment of the downlink control data frame to be within the electromagnetic interference disappearance time domain interval corresponding to the energy field dissipation cutoff time parameter.

[0007] Preferably, the approach control airspace spatiotemporal topology reconstruction unit is also used to monitor the spatial coordinate variance of non-cooperative UAVs for three consecutive cycles, and outputs a geometric boundary drift activation signal when it is determined that geometric boundary drift occurs in the restricted blocking airspace cavity; the control link timing reordering unit also includes a multipath topology redundancy module, which is used to extract the list of data transmission ground base stations around the normally managed aircraft in response to the geometric boundary drift activation signal, copy and map the downlink control data frame into a dual-path time-division multipath redundant control data frame stream that is concurrently transmitted through two opposite base stations, and control the downlink control data frame to be transmitted concurrently through two opposite base stations in a time-division dual-path manner.

[0008] Preferably, the control link timing reordering unit is also used to activate the parameter discretization and degradation module through a feedback loop when the real-time computing load of the internal central processing unit core is greater than 95%. The parameter discretization and degradation module is used to remove the ambient temperature sensor reading component and the cabin pressure status component in the downlink control data frame, and reconstruct the variable-length control message into a 32-bit discrete fixed-point control data frame structure containing three-dimensional spatial coordinates and velocity vectors, reducing the timing reordering processing latency to less than 2ms.

[0009] Preferably, step S2 in the control link timing reordering unit for controlled aircraft is further refined into the following sub-steps: Step S21, calculate the start and end times of the strong electromagnetic pulse energy emission based on the pulse emission period parameters; Step S22, insert transmission phase deviation into the downlink control data frame in the time domain to control the arrival time of the downlink control data frame to fall within the pulse-free time domain interval after the end time and before the next start time.

[0010] Preferably, the control link timing rescheduling unit for controlled aircraft also includes a sensitivity allocation module. The sensitivity allocation module is used to retrieve the registration information of normally managed aircraft, match the corresponding electromagnetic sensitivity threshold level according to the registration information, and allocate the corresponding holding airspace sector in the approach control airspace based on the electromagnetic sensitivity threshold level.

[0011] Preferably, the control link timing rescheduling unit for controlled aircraft also includes a trajectory conflict simulation module. The trajectory conflict simulation module is coupled with the sensitivity adjustment module to perform trajectory conflict simulation for normally managed aircraft within the holding airspace sector. When the electromagnetic sensitivity threshold level of the normally managed aircraft meets the fixed first electromagnetic tolerance level, the lateral offset distance parameter of the trajectory position of the normally managed aircraft is reduced to improve the grid resource reuse rate of the holding airspace sector.

[0012] Preferably, the control link timing rescheduling unit for controlled aircraft also includes an environmental cumulative monitoring module, which is used to continuously record the pulse radio frequency energy parameters received by the avionics front end of normally managed aircraft in the approach control airspace, and establish an electromagnetic load cumulative dataset that evolves with the operating time axis.

[0013] Preferably, the control link timing rescheduling unit for controlled aircraft further includes a trend characterization calculation module. The trend characterization calculation module is coupled with the environmental cumulative monitoring module to extract the rate of change of the first time derivative of the electromagnetic load cumulative dataset with respect to the time axis, and to calculate the load drift parameter characterizing the trend of electromagnetic stress degradation at the avionics front end.

[0014] Preferably, the control link timing rescheduling unit for controlled aircraft further includes an adaptive channel scheduling module. The adaptive channel scheduling module is coupled with the trend characterization calculation module to issue a communication channel switching command to the normally managed aircraft when the load drift parameter continuously exceeds a fixed safety threshold parameter as the load drift parameter evolves over time. This command migrates the carrier frequency of the radio control link to a fixed backup anti-interference frequency band.

[0015] Compared with existing technologies, the electromagnetic pulse anti-drone system of the present invention has the following advantages: 1. In the electromagnetic pulse anti-drone system, the physical space interleaving constraints are converted into time axis control flow through the timing staggered state machine logic. The timing reordering unit of the control link of the aircraft extracts the instruction reference update cycle and pulse excitation characterization time in the data transmission link. The radio frequency blocking sliding window is constructed based on this time. When it is calculated that the normal transmission time is inside the sliding window, the timing phase shift control word is written to the register of the instruction sending controller to adjust the normal transmission time to the adaptive transmission time after the pulse electromagnetic energy dissipation is cut off. This allows the control data frame to be accurately interspersed in the ignition vacuum period on the time axis, eliminating the saturation interference of transient impact on the aircraft's wireless control link and ensuring the continuous steady state of the operating topology in the terminal approach control airspace.

[0016] 2. In response to interference caused by noise emitted by non-cooperative aircraft leading to multipath data flickering in the ground-based airspace radar sensing data source, the airspace topology reconstruction unit continuously monitors the spatial coordinate variance for three cycles. When it determines that geometric boundary drift occurs in the limiting blocking cell, the control link timing reordering unit activates the multipath topology redundancy module, automatically extracts the list of multipath digital transmission ground base stations around the current grid of the managed aircraft, decouples the downlink control flow into a time-division redundant channel running concurrently through at least two opposite base stations, and uses different buildings to shield electromagnetic sidelobe contamination, ensuring that control data packets are accurately delivered to the avionics front end during flickering and avoiding signal interruption that could cause secondary operational conflicts.

[0017] 3. When multiple aircraft concurrency causes the CPU core computing load in the trajectory command reordering unit to reach over 95%, the system initiates a parameter discretization degradation strategy. This strategy directly truncates the data structure of aircraft within non-core hazardous grids, removes the current ambient temperature sensor readings and cabin pressure status components from their four-dimensional status report frames, and compresses variable-length control messages into a compact 32-bit discrete fixed-point data structure containing only three-dimensional spatial coordinates and velocity vectors. This effectively releases data transmission bus bandwidth and processor cache queues, and hard-truncates the downlink command timing processing delay within 2ms across the entire system, ensuring computational stability during high-density approach phases. Attached Figure Description

[0018] Figure 1 This is the timing control diagram of the electromagnetic pulse anti-drone system of the present invention; Figure 2 This is a schematic diagram of the signal flow of the electromagnetic pulse anti-drone system of the present invention. Detailed Implementation

[0019] The technical solutions of the embodiments of this application will be clearly described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this application, not all embodiments. All other embodiments obtained by those skilled in the art based on the embodiments of this application are within the scope of protection of this application.

[0020] An electromagnetic pulse anti-drone system includes: The approach control airspace spatiotemporal topology reconstruction unit is used to identify non-cooperative drones in the approach control airspace where normally managed aircraft are operating, and to delineate the limiting blocking airspace cell that locks the three-dimensional radiation energy field boundary of non-cooperative drones. The pulse energy radiation monitoring unit is coupled with the approach control airspace spatiotemporal topology reconstruction unit to obtain the transmission timing parameters of strong electromagnetic pulse energy emitted into the confined and blocked airspace cavity. The air traffic control link timing rescheduling unit interacts with the approach control airspace spatiotemporal topology reconstruction unit and the pulse energy radiation monitoring unit, respectively. Based on the transmission timing parameters, it adjusts the downlink control data frame transmission timing of the radio control link for normally managed aircraft within the previously reconstructed approach control airspace. The air traffic control link timing rescheduling unit completes the following steps: Step S1: Read the pulse emission period parameters and energy field dissipation cutoff time parameters input by the pulse energy radiation monitoring unit; Step S2: Based on the pulse transmission period parameter and the energy field dissipation cutoff time parameter, perform time axis interpolation phase shift operation on the downlink control data frame in the time domain to control the data transmission clock segment of the downlink control data frame to be within the electromagnetic interference disappearance time domain interval corresponding to the energy field dissipation cutoff time parameter.

[0021] Preferably, the approach control airspace spatiotemporal topology reconstruction unit is also used to monitor the spatial coordinate variance of non-cooperative UAVs for three consecutive cycles, and outputs a geometric boundary drift activation signal when it is determined that geometric boundary drift occurs in the restricted blocking airspace cavity; the control link timing reordering unit also includes a multipath topology redundancy module, which is used to extract the list of data transmission ground base stations around the normally managed aircraft in response to the geometric boundary drift activation signal, copy and map the downlink control data frame into a dual-path time-division multipath redundant control data frame stream that is concurrently transmitted through two opposite base stations, and control the downlink control data frame to be transmitted concurrently through two opposite base stations in a time-division dual-path manner.

[0022] Preferably, the control link timing reordering unit is also used to activate the parameter discretization and degradation module through a feedback loop when the real-time computing load of the internal central processing unit core is greater than 95%. The parameter discretization and degradation module is used to remove the ambient temperature sensor reading component and the cabin pressure status component in the downlink control data frame, and reconstruct the variable-length control message into a 32-bit discrete fixed-point control data frame structure containing three-dimensional spatial coordinates and velocity vectors, reducing the timing reordering processing latency to less than 2ms.

[0023] Preferably, step S2 in the control link timing reordering unit for controlled aircraft is further refined into the following sub-steps: Step S21, calculate the start and end times of the strong electromagnetic pulse energy emission based on the pulse emission period parameters; Step S22, insert transmission phase deviation into the downlink control data frame in the time domain to control the arrival time of the downlink control data frame to fall within the pulse-free time domain interval after the end time and before the next start time.

[0024] Preferably, the control link timing rescheduling unit for controlled aircraft also includes a sensitivity allocation module. The sensitivity allocation module is used to retrieve the registration information of normally managed aircraft, match the corresponding electromagnetic sensitivity threshold level according to the registration information, and allocate the corresponding holding airspace sector in the approach control airspace based on the electromagnetic sensitivity threshold level.

[0025] Preferably, the control link timing rescheduling unit for controlled aircraft also includes a trajectory conflict simulation module. The trajectory conflict simulation module is coupled with the sensitivity adjustment module to perform trajectory conflict simulation for normally managed aircraft within the holding airspace sector. When the electromagnetic sensitivity threshold level of the normally managed aircraft meets the fixed first electromagnetic tolerance level, the lateral offset distance parameter of the trajectory position of the normally managed aircraft is reduced to improve the grid resource reuse rate of the holding airspace sector.

[0026] Preferably, the control link timing rescheduling unit for controlled aircraft also includes an environmental cumulative monitoring module, which is used to continuously record the pulse radio frequency energy parameters received by the avionics front end of normally managed aircraft in the approach control airspace, and establish an electromagnetic load cumulative dataset that evolves with the operating time axis.

[0027] Preferably, the control link timing rescheduling unit for controlled aircraft further includes a trend characterization calculation module. The trend characterization calculation module is coupled with the environmental cumulative monitoring module to extract the rate of change of the first time derivative of the electromagnetic load cumulative dataset with respect to the time axis, and to calculate the load drift parameter characterizing the trend of electromagnetic stress degradation at the avionics front end.

[0028] Preferably, the control link timing rescheduling unit for controlled aircraft further includes an adaptive channel scheduling module. The adaptive channel scheduling module is coupled with the trend characterization calculation module to issue a communication channel switching command to the normally managed aircraft when the load drift parameter continuously exceeds a fixed safety threshold parameter as the load drift parameter evolves over time. This command migrates the carrier frequency of the radio control link to a fixed backup anti-interference frequency band.

[0029] Example 1: In the application scenario of the hub airport terminal control area constructed by this system, when a non-cooperative drone intrudes into the high-density approach airspace, the system runs on a standard air traffic management computing platform. Compliant managed aircraft within the control area conduct approach operations at a flow rate of 45 aircraft per hour. Each aircraft broadcasts a dynamic positioning report in real time, including three-dimensional position coordinates, velocity vectors, and intended flight paths. The airspace topology reconstruction unit concurrently collects the three-dimensional position coordinates of non-cooperative aircraft from ground-based airspace radar sensing data sources via a gigabit Ethernet interface at a sampling frequency of 20Hz. and the spatiotemporal trajectory state vector of the managed aircraft broadcast automatic dependent surveillance system In the solution module, the airspace topology reconstruction unit generates a three-dimensional confined blocking cavity surrounding the non-cooperative aircraft based on the three-dimensional position coordinates of the non-cooperative aircraft. : ,in, This is the horizontal diffusion radius coefficient, and in this embodiment, its set value is 850 meters. As the vertical diffusion height coefficient, when the radar tracking signal experiences a 1.2-second transient multipath scintillation due to environmental noise, the solution module activates the Discrete Markov Evolutionary Sliding Window algorithm to extract the historical velocity and acceleration components from the five lost cycles, generating a boundary quantity with a 150-meter safety compensation. Expansion restriction blocking the cellular cavity This ensures the certainty of the range within the radiation field envelope.

[0030] Pulse radiation confinement arbitration unit based on limiting and blocking the cell cavity Based on the geometric boundaries, managed aircraft within the affected buffer zone are classified and scheduled. For the 12 aircraft with an electromagnetic susceptibility threshold level of A, the control link timing rescheduling unit sets a lateral fine-tuning judgment threshold for the flight path. It also sends a lateral offset control word to achieve a 150-meter track fine-tuning. For the four sensitive aircraft with an electromagnetic susceptibility threshold of level C, the trajectory command rearrangement unit raises the judgment threshold to [missing information]. It also reconstructs the current approach flight plan and generates a dynamic 45-degree circumduction arc command.

[0031] When all affected managed aircraft have performed actions to exit the safety boundary and their real-time positions meet the distance determination logic, the control link timing reordering unit sends a release permission token to the pulse radiation constraint arbitration unit. Upon receiving the token, the pulse radiation constraint arbitration unit sends a timing control word to the electromagnetic pulse generator, initiating a 15μs electromagnetic pulse release action. Upon receiving the downlink release permission token, the pulse radiation constraint arbitration unit resolves it to the spatial angle vector corresponding to the azimuth of the affected compliant aircraft, calls the digital beamforming algorithm to calculate the complex weighting coefficients of each radiating element of the phased array antenna, and directly writes them into the registers of the digital phase shifter and digitally controlled attenuator connected in series with the transmitter. This causes the ground transmitter to form a narrowband null pattern with radiated energy dropping to -35 dB in the azimuth direction of the compliant aircraft's physical space. After the pulse release is completed, the system removes the restriction blocking cavity. Under the established air traffic management grid restoration of normal routing logic, the transient packet loss rate of the managed aircraft control link is 0.42%, the airspace transient capacity efficiency loss rate is 4.2%, and the negative interference time loss of the handling action on the overall air traffic flow topology continuity is 38 seconds.

[0032] Example 2: This experiment aims to verify the anti-interference control effectiveness of the spatiotemporal staggered rescheduling based invention provided by this invention under the coupling effect of complex electromagnetic environment and high-density air traffic flow. The test platform is constructed by integrating a high-precision three-dimensional air traffic flow simulator and an electromagnetic pulse radio frequency signal generator. It simulates the approach airspace within a 20-kilometer radius of the terminal control area of ​​a hub airport. The simulator is configured with 50 air traffic control data simulation terminals, generating real-time status data streams containing 40 compliant civil aircraft at an update frequency of 20Hz. At the same time, the electromagnetic pulse generator simulates non-cooperative UAV suppression signals with a pulse width of 15μs. By applying periodic gating to the pulse signal generator, multipath reflection characteristics are reproduced. In a complex electromagnetic environment, three control groups were set up for the experiment. The experimental group of this invention adopted a complete spatiotemporal topology reconstruction and timing staggered flow algorithm. The first control group only implemented basic physical space avoidance and did not perform phase shifting of the control data stream. The second control group was a high-density triggering condition outside the numerical range, further increasing the flow of compliant aircraft to 65 aircraft / hour and reducing the pulse release vacuum period to 5μs to test the system's limit anti-saturation boundary. In the experiment, the downlink update frequency of the control data of the managed aircraft was set to 10Hz, and the length of each control data frame was 8ms. In the experimental group of this invention, the pulse energy radiation monitoring unit monitored the dissipation cutoff time of the electromagnetic interference radiation field in real time. The transmission time of downlink control data frames is dynamically rearranged based on monitoring data. ,when When the signal falls within the radio frequency interference range, the instruction rearrangement unit calculates the phase deviation. The control parameter is then injected into the transmit buffer of the command transmission controller, delaying the data frame transmission time until the interference field strength has attenuated to below -80dBm in the stable region.

[0033] Data recordings show that during the two-hour continuous operation of the prototype test of this invention, the transient packet loss rate of the control link of the compliant aircraft in the strong electromagnetic radiation scenario was 0.42%. Under the premise of satisfying the topological continuity of air traffic flow, radio frequency blocking against non-cooperative targets was successfully achieved, with an average approach efficiency deviation of 0.12%. In the first control prototype test, due to the lack of a timing stagger mechanism, the compliant aircraft frequently experienced control command timeout errors during pulse release, with a link packet loss rate of 18.5%. Furthermore, the transient capacity efficiency loss rate of the controlled airspace reached 22.8% due to frequent space avoidance. Data from the second control prototype test shows that when the pulse transmission period was reduced to 5μs, the risk of buffer overflow of the command transmission controller increased due to the compression of the effective transmission window of the control link. The system triggered three safety silence protection actions. At this time, the approach trajectory offset distance exceeded the preset safety threshold of 500 meters, indicating that this condition touched the conflict boundary between the system's radio frequency blocking and the topological continuity of traffic flow.

[0034] The test results demonstrate that by dynamically matching the radio frequency blocking sliding window with the command transmission time, the risk of saturation interference to the communication link of compliant aircraft by electromagnetic pulse release is actively suppressed. Moreover, this anti-interference mechanism based on time axis interleaving, compared with the spatial physical avoidance strategy, can reduce the interference delay loss of air traffic flow and ensure that the operating topology in the terminal approach control airspace maintains a continuous steady state of more than 99% in a complex electromagnetic interference environment.

[0035] Example 3: In a specific hub airport terminal control area application scenario, when a high-density approach airspace surveillance system detects a non-cooperative drone intrusion and the intruding target is at the critical protection altitude within the terminal approach control airspace, the system initiates a targeted electromagnetic pulse blocking operation. In this scenario, the air traffic flow in the terminal control area is maintained at 60 aircraft / hour. Because the non-cooperative drone target exhibits transient scattering characteristics within the radar detection field of view, there is a data acquisition gap of 0.5 to 1.2 seconds in the original target trajectory within the calculation unit, resulting in uncertainty in the non-cooperative drone target's position. This causes jitter at the boundary of the limiting blocking cavity, which in turn triggers the collision avoidance safety logic of compliant aircraft. To address the above challenges, this invention introduces a motion state prediction and compensation mechanism based on Kalman filtering. When the original radar position signal is lost, the system uses the target's position observation sequence within the 10 data periods prior to the loss. With velocity vector Calculate the predicted position at the next time step, where The data sampling interval is 0.05 seconds. The system introduces a state covariance matrix-based approach. Location uncertainty inflation factor Its calculation logic is as follows: ,in, For matrix The largest eigenvalue, will horizontal radius Dynamically corrected to The system logic constructs a circular buffer queue containing 100 sampling periods, using the predicted location points within the missing window as completion inputs to ensure that the restricted blocking cavity maintains geometric center smoothness during data flickering.

[0036] Based on the free-space electromagnetic wave energy propagation loss model, the electromagnetic pulse transmission power provided by the pulse energy radiation monitoring unit is read. With transmit antenna gain Combined with the interference immunity sensitivity threshold of compliant aircraft wireless links Calculate the distance affected by radio frequency interference The specific formula is as follows: Among them, electromagnetic pulse transmission power The value ranges from 1000 watts to 5000 watts, and the transmit antenna gain... It is a dimensionless constant with a value range of 10 to 15, and the anti-interference sensitivity threshold is... The value ranges from 10 to 10 to 10 watts per square meter, and the calculated output RF interference effect distance is determined. Greater than 0 meters, secondly, will A logical comparison is made with the confined blocking cavity boundary generated by the spatial topology reconstruction unit. If The system determines that the compliant aircraft is in a radio frequency sensitive area and triggers instruction reordering. This decision-making process is executed based on the following logical criteria: when the real-time spatial coordinates of the compliant aircraft... Satisfying the distance criterion At that time, the trajectory command rearrangement unit locks the aircraft's approach heading and calculates the minimum lateral offset based on the remaining airspace sector capacity. ,in This is the preset lateral safety margin distance constant for aircraft collision avoidance.

[0037] By predicting and compensating for signal loss periods ranging from 0.5 to 1.2 seconds, experimental data show that during periods of data interruption from non-cooperative UAVs, the system maintains the average offset of the center position of the blocking cavity within 45 meters, reduces the number of erroneous actions triggered by the trajectory command rearrangement unit from 8 times per hour to 1 time per hour, and achieves an accuracy of 0.1ms in the interleaving control of electromagnetic pulse transmission timing and compliant aircraft control commands. While ensuring radio frequency blocking coverage of over 95% of the non-cooperative target trajectory coverage, the system controls the average flight trajectory offset length of compliant aircraft in the terminal approach control airspace within 120 meters, thus achieving the maintenance of air traffic flow topology continuity in complex electromagnetic and detection noise environments.

[0038] Example 4: To ensure the robustness of the system's operation in the approach control terminal area, a standardized pre-deployment calibration procedure must be performed before formal operation. The core of the calibration procedure is to establish the correspondence between the actual radiation attenuation curve of the electromagnetic pulse generator and the routing weights of the controlled airspace grid. The specific operation is as follows: At preset spatial sampling points 500 to 1200 meters away from the ground-based airspace radar sensing data source, a standard radio frequency field strength detector is set up. Pulse radiation tests are conducted by triggering the transmitter, and the spatial field strength values ​​under different transmission power settings are recorded. The least squares method is then used to fit the field strength attenuation function. ,in, The initial radiation intensity at the center of the emission source. For spatial distance, The environmental path loss coefficient is used to construct a corrected lookup table for blocking the cell lumen boundary using this fitting function, ensuring... The value of is physically aligned with the actual field strength attenuation envelope within an adaptive range of 500 meters to 1200 meters.

[0039] A logic conflict verification experiment based on approach sector traffic flow density was conducted, setting an operational load of 45 to 65 compliant aircraft per hour in the approach airspace. Random interference signals matching the motion characteristics of non-cooperative UAVs were injected into the simulation. When the state vector reported by the Automatic Dependent Surveillance-Broadcast (ADS) system of managed aircraft in the airspace was detected... When the predicted distance to the confined cavity boundary is less than 200 meters, the trajectory command rearrangement unit triggers a dynamic offset command for changing the path. In complex airspace environments, the system introduces building shielding mechanisms as physical protection redundancy. In high-altitude line-of-sight environments lacking direct physical shielding media, the system adjusts the transmission elevation angle of the ground base station, utilizing Fresnel diffraction generated by the top edges of ground buildings. By calculating the shielding ratio of the Fresnel zone, the system controls the downlink signal to propagate along a specific diffraction path. Utilizing the high-frequency attenuation characteristics of electromagnetic pulse sidelobe signals at building edges, a local electromagnetic shadow zone is formed at the receiving end of the managed aircraft. This virtual shielding window constructed using ground object diffraction effects, combined with the aforementioned temporal phase deviation injection, forms a dual protection in the spatiotemporal dimension. The system also correlates the average trajectory deviation of each managed aircraft after rerouting with the aircraft's electromagnetic sensitivity level. During this correlation verification, the system introduces a time first derivative rate of change parameter to assess the degradation trend of the electromagnetic environment. Specifically, this parameter is defined as the change in energy field intensity E per unit time, ΔE / Based on preliminary experiments investigating the electromagnetic susceptibility of commercial aircraft avionics systems, this invention sets a safety threshold of 1.5V / (m·μs). When the rate of change of the electromagnetic pulse rising edge exceeds this threshold for three consecutive sampling cycles, it is determined that there is a risk of electromagnetic degradation. The system will then forcibly increase the phase offset margin of the downlink control data frame to ensure that the data packet completely avoids transient surge interference that may be caused by the pulse rising edge. If the rate of change is below this lower bound, standard timing is maintained to balance the throughput efficiency of the link. In actual testing, when... At the mileage, the packet loss rate of the control command link for all models was within a safety margin of less than 0.5%, verifying that the logic triggering mechanism under this parameter setting has system-level operational determinism in multi-aircraft approach conditions.

[0040] Example 5: In a multi-sensor fusion surveillance scenario within the aircraft approach terminal control area, to eliminate logical gaps between radar sensing data sources and communication links under multipath reflection interference, the system constructs a data cleaning procedure based on spatiotemporal correlation verification. Pre-set parameters are available within the control area. There are 1 spatial observation sampling points, with a geometric interval between the sampling points being 1. The numerical value was set to 500 meters, and the background noise power spectral density at each sampling point was... Through 24-hour rolling monitoring and mean smoothing, a spatiotemporal perturbation benchmark library is constructed. The solution module then calculates the non-cooperative target's 3D position report based on the received data. With compliant aircraft state vector Real-time spatial topology continuity consistency scan is performed, where the position consistency criterion is defined as follows: ,in, For the instantaneous coordinates of compliant aircraft at any given time, This is the maximum permitted approach speed for the aircraft type. The value is set to 15 meters, which is three times the variance of the inherent position noise of the radar measurement system.

[0041] When the system detects a transient abrupt change signal in the sampling point data stream that violates the above criteria, it automatically triggers the benchmark library adaptive calibration process. The calibration process execution logic is as follows: The solution module locks the normal state trajectory sequence of the 20 periods before the abrupt change occurs and calculates the positional fluctuation variance within the sequence. ;Use the corresponding current interference field strength from the offline calibration reference library Correction coefficient The abrupt change points are then subjected to a second-order weighted interpolation process, and the corrected coordinates are obtained. ,in The weighting coefficient for extrapolating from historical trajectories is set to 0.65. The residual confidence level for the original observations is set to 0.35. The predicted location coordinates of non-cooperative targets within the missing window are calculated based on historical trajectory extrapolation. The raw observation position coordinates returned by the radar sensing data source; verified by the validation module. Capacity constraints of adjacent approach airspace sectors The physical distance, if the distance satisfies Then update the system record queue. The system also issues trajectory correction commands. This calibration and correction process eliminates false alarms in non-cooperative target perception caused by multipath effects, ensuring that the heading command link of compliant aircraft maintains more than 99.9% real-time command interaction during dynamic changes in the electromagnetic environment at a traffic flow of 60 aircraft per hour in the controlled airspace. Furthermore, the fluctuation range of physical trajectory offset during the overall approach process is locked within the engineering-allowed 80-meter error envelope range, supporting the determinism of traffic management under all-weather operating conditions.

[0042] The embodiments of this application have been described above with reference to the accompanying drawings. Unless otherwise specified, the embodiments and features in the embodiments of this application can be combined with each other. This application is not limited to the specific embodiments described above. The specific embodiments described above are merely illustrative and not restrictive. Those skilled in the art can make many other forms under the guidance of this application without departing from the spirit of this application and the scope of protection of this invention, and all of these forms are within the scope of protection of this application.

Claims

1. An electromagnetic pulse counter drone system, comprising: include: The approach control airspace spatiotemporal topology reconstruction unit is used to identify non-cooperative drones in the approach control airspace where normally managed aircraft are operating, and to delineate the limiting blocking airspace cell that locks the three-dimensional radiation energy field boundary of non-cooperative drones. The pulse energy radiation monitoring unit is coupled with the approach control airspace spatiotemporal topology reconstruction unit to obtain the transmission timing parameters of strong electromagnetic pulse energy emitted into the confined and blocked airspace cavity. The air traffic control link timing rescheduling unit interacts with the approach control airspace spatiotemporal topology reconstruction unit and the pulse energy radiation monitoring unit, respectively. Based on the transmission timing parameters, it adjusts the downlink control data frame transmission timing of the radio control link for normally managed aircraft within the previously reconstructed approach control airspace. The air traffic control link timing rescheduling unit completes the following steps: Step S1: Read the pulse emission period parameters and energy field dissipation cutoff time parameters input by the pulse energy radiation monitoring unit; Step S2: Based on the pulse transmission period parameter and the energy field dissipation cutoff time parameter, perform time axis interpolation phase shift operation on the downlink control data frame in the time domain to control the data transmission clock segment of the downlink control data frame to be within the electromagnetic interference disappearance time domain interval corresponding to the energy field dissipation cutoff time parameter.

2. An electromagnetic pulse counter-UAV system according to claim 1, wherein, The approach control airspace spatiotemporal topology reconstruction unit is also used to monitor the spatial coordinate variance of non-cooperative UAVs for three consecutive cycles, and outputs a geometric boundary drift activation signal when it determines that geometric boundary drift has occurred in the restricted blockage airspace cell. The control link timing reordering unit also includes a multipath topology redundancy module, which is used to extract the list of data transmission ground base stations around the normally managed aircraft in response to the geometric boundary drift activation signal, copy and map the downlink control data frames into a dual-path time-division multipath redundant control data frame stream that is concurrently transmitted through two opposite base stations, and control the downlink control data frames to be transmitted concurrently through the two opposite base stations in a time-division dual-path manner.

3. The electromagnetic pulse anti-drone system according to claim 1, characterized in that, The aircraft control link timing reordering unit is also used to activate the parameter discretization and degradation module through a feedback loop when the real-time computing load of the internal central processing unit core is greater than 95%. The parameter discretization and degradation module is used to remove the ambient temperature sensor reading component and the cabin pressure status component in the downlink control data frame, and reconstruct the variable-length control message into a 32-bit discrete fixed-point control data frame structure containing three-dimensional spatial coordinates and velocity vectors, reducing the timing reordering processing latency to less than 2ms.

4. The electromagnetic pulse anti-drone system according to claim 1, characterized in that, Step S2 in the control link timing reordering unit for air traffic control is further broken down into the following sub-steps: Step S21, calculate the start and end times of the strong electromagnetic pulse energy emission based on the pulse emission period parameters; Step S22, insert transmission phase deviation into the downlink control data frame in the time domain to ensure that the arrival time of the downlink control data frame falls within the pulse-free time domain interval after the end time and before the next start time.

5. An electromagnetic pulse anti-drone system according to claim 1, characterized in that, The control link timing rescheduling unit for controlled aircraft also includes a sensitivity allocation module. The sensitivity allocation module is used to retrieve the registration information of normally managed aircraft, match the corresponding electromagnetic sensitivity threshold level according to the registration information, and allocate the corresponding holding airspace sector in the approach control airspace based on the electromagnetic sensitivity threshold level.

6. An electromagnetic pulse anti-drone system according to claim 5, characterized in that, The control link timing rescheduling unit for air traffic control also includes a trajectory conflict simulation module. The trajectory conflict simulation module is coupled with the sensitivity adjustment module to perform trajectory conflict simulation for normally managed aircraft within the holding airspace sector. When the electromagnetic sensitivity threshold level of the normally managed aircraft meets the fixed first electromagnetic tolerance level, the lateral offset distance parameter of the trajectory position of the normally managed aircraft is reduced to improve the grid resource reuse rate of the holding airspace sector.

7. An electromagnetic pulse anti-drone system according to claim 1, characterized in that, The control link timing rescheduling unit for controlled aircraft also includes an environmental cumulative monitoring module, which is used to continuously record the pulse radio frequency energy parameters received by the avionics front end of normally managed aircraft in the approach control airspace, and establish an electromagnetic load cumulative dataset that evolves with the operating time axis.

8. An electromagnetic pulse anti-drone system according to claim 7, characterized in that, The control link timing rescheduling unit for air traffic control also includes a trend characterization calculation module. This module couples data signals with the environmental cumulative monitoring module to extract the rate of change of the first time derivative of the electromagnetic load cumulative dataset with respect to the time axis, and calculates the load drift parameters characterizing the trend of electromagnetic stress degradation at the avionics front end.

9. An electromagnetic pulse anti-drone system according to claim 8, characterized in that, The control link timing rescheduling unit for air traffic control also includes an adaptive channel scheduling module. The adaptive channel scheduling module is coupled with the trend characterization calculation module to send a communication channel switching command to the normally managed aircraft when the load drift parameter continuously exceeds a fixed safety threshold parameter as the load drift parameter evolves over time. This command migrates the carrier frequency of the radio control link to a fixed backup anti-jamming frequency band.

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