Airborne Tiantong phased-array antenna and application method thereof

Abstract

The invention relates to the technical field of communication, in particular to an airborne Tiantong phased-array antenna and an application method thereof. According to the method, phased-array antenna beams are driven to perform electronic scanning according to a geometric azimuth angle, beacon signal blind acquisition is performed in a preset airspace in a wide beam mode, and when an initial signal is detected, the mode is immediately switched to a narrow beam scanning mode; dynamically adjusting a phase weighting coefficient to realize pointing adjustment, so that a signal quality parameter is continuously converged in an optimal threshold interval; carrying aircraft maneuvering acceleration feedback is introduced, beam pointing offset is dynamically compensated based on a pre-constructed interference feature library, and signal fluctuation caused by a multipath effect is suppressed; and continuously checking a data validity flag bit of the main inertial navigation system, seamlessly switching to an antenna built-in inertial navigation data stream when a failure threshold is triggered, and activating a rapid recapture program to maintain zero interruption of a communication link. Through dual-source inertial navigation data fusion and intelligent beam control, rapid and accurate tracking of Tiantong satellites in an airborne environment is realized.

Description

Technical Field

[0001] The present invention relates to the field of communication technology, and in particular to an airborne Tiantong phased array antenna and an application method thereof. Background Art

[0002] With the rapid growth of aviation communication needs, traditional mechanical scanning satellite antennas have exposed obvious shortcomings in airborne environments, such as slow tracking speed, large size, and weak anti-vibration ability. It is difficult to meet the high-bandwidth and low-latency communication needs of high-speed maneuvering bodies. Existing phased array antenna solutions mostly rely on a single inertial navigation data source, which is prone to tracking loss when the carrier aircraft makes large maneuvers or the main inertial navigation fails, and lacks the ability to adaptively suppress multipath interference and attitude jitter. In addition, the traditional beam capture method adopts a fixed scanning strategy, which has low capture efficiency in complex airspace environments and is difficult to balance the coordinated optimization of wide-beam fast search and narrow-beam high-gain tracking. In response to the above problems, there is an urgent need for an airborne phased array antenna system that integrates high-precision combined navigation, intelligent beam control and anti-interference technology to achieve rapid capture, stable tracking and highly reliable communication of Tiantong satellites in dynamic environments. Summary of the Invention

[0003] The present invention overcomes the deficiencies of the prior art and provides an airborne Tiantong phased array antenna and an application method thereof.

[0004] In order to achieve the above-mentioned purpose, the technical solution adopted by the present invention is: A first aspect of the present invention discloses an application method of an airborne Tiantong phased array antenna, comprising the following steps: Synchronously collect attitude data from the airborne inertial navigation system and the antenna's built-in MEMS inertial navigation system, fuse them to generate an anti-jitter carrier attitude matrix, and calculate the geometric azimuth of the Tiantong satellite in real time; Driving the phased array antenna beam to electronically scan according to the geometric azimuth angle, first performing blind capture of beacon signals in a preset airspace in a wide beam mode, and immediately switching to a narrow beam scanning mode when an initial signal is detected; The beacon signal strength and bit error rate characteristics are extracted, combined with the inertial navigation attitude jitter compensation, and the phase weighting coefficient is dynamically adjusted to achieve pointing adjustment, so that the signal quality parameters continue to converge to the optimal threshold range; In the fine tracking phase, aircraft maneuver acceleration feedback is introduced to dynamically compensate for beam pointing deviation based on a pre-built interference signature library and suppress signal fluctuations caused by multipath effects. Continuously check the data validity flag of the main inertial navigation system, seamlessly switch to the antenna's built-in inertial navigation data stream when the failure threshold is triggered, and activate the fast recapture procedure to maintain zero interruption of the communication link.

[0005] Preferably, the attitude data of the airborne inertial navigation and the antenna built-in MEMS inertial navigation are collected synchronously, and the anti-jitter carrier attitude matrix is ​​generated by fusion, and the geometric azimuth of the Tiantong satellite is solved in real time, specifically: Collect the first attitude data stream output by the airborne fiber-optic inertial navigation system, including real-time attitude angle, angular rate, and data validity flag; and collect the second attitude data stream output by the antenna's built-in MEMS inertial navigation system, including real-time attitude angle and angular rate; Based on the data validity flag in the first attitude data stream, a credibility evaluation value of the onboard inertial navigation is calculated in real time; at the same time, a credibility evaluation value of the built-in inertial navigation is calculated according to the noise level of the second attitude data stream; Dynamically allocating a dominant fusion weight coefficient and an auxiliary fusion weight coefficient of the first attitude data stream and the second attitude data stream during a fusion process according to the airborne inertial navigation credibility evaluation value and the built-in inertial navigation credibility evaluation value; Combining the dominant fusion weight coefficient, the auxiliary fusion weight coefficient, and the preset attitude jitter suppression factor for the carrier high-frequency jitter, weighted averaging and low-pass filtering are performed on the dual-source attitude data to output an anti-jitter carrier attitude matrix; Based on the anti-shake carrier attitude matrix, the real-time acquired Tiantong satellite orbit ephemeris parameters and the carrier's Beidou positioning information, the real-time geometric azimuth of the Tiantong satellite relative to the carrier is output through conversion calculation from the geographic coordinate system to the carrier coordinate system.

[0006] Preferably, the phased array antenna beam is driven to perform electronic scanning according to the geometric azimuth angle, and blind capture of the beacon signal is first performed in a preset airspace in a wide beam mode. When the initial signal is detected, it is immediately switched to a narrow beam scanning mode, specifically: Determining an initial beam pointing center according to the geometric azimuth angle and setting a scanning range of a wide beam mode, wherein the scanning range includes a pitch sector airspace and an azimuth cone airspace centered on the geometric azimuth angle, and configuring a beam width and a scanning step increment of the wide beam; Within the scanning range, electronic beam scanning is performed according to a preset scanning trajectory, and the carrier-to-noise ratio characteristics of the beacon signal are detected at each beam dwell point. If no valid signal is detected, the scanning step increment is adjusted to optimize the scanning efficiency; When the carrier-to-noise ratio of the beacon signal is detected to exceed the preset capture threshold, the instantaneous azimuth and elevation angles of the current beam pointing are extracted as coarse alignment references, and the corresponding signal strength distribution characteristics are recorded; Based on the coarse alignment reference, the beam mode is switched to a narrow beam, and a dynamically shrinking spiral scanning path is constructed within a preset range of the coarse alignment reference, while optimizing the convergence speed of the scanning path in combination with the signal intensity distribution characteristics; During the narrow beam scanning process, the slope changes of the beacon signals at adjacent beam dwell points are compared in real time. When the signal strength reaches a local peak and the slope approaches zero, it is determined to be the optimal direction and the beam is locked.

[0007] Preferably, the beacon signal strength and bit error rate characteristics are extracted, combined with the inertial navigation attitude jitter compensation amount, and the phase weighting coefficient is dynamically adjusted to achieve pointing adjustment, so that the signal quality parameters continue to converge to the optimal threshold range, specifically: The beacon signal output by the phased array antenna receiving channel is sampled in real time, the in-phase component and the orthogonal component are extracted through digital down-conversion, the instantaneous signal amplitude is calculated and smoothed to generate a normalized signal strength sequence; Synchronously analyze the bit error rate statistics output by the demodulator and use sliding window filtering to generate the bit error rate change gradient characteristics; Decomposing the attitude jitter compensation output by the inertial navigation system into angular jitter components of the pitch axis and the azimuth axis, and performing spatiotemporal matching with the signal strength sequence and the bit error rate gradient feature through time alignment processing; A three-dimensional feature space is constructed, containing the signal strength attenuation slope, the bit error rate gradient extreme point, and the angular jitter component. The beam pointing offset vector is dynamically calculated within this feature space. The modulus of the beam pointing offset vector is weighted by the bit error rate gradient extreme point, and its direction is determined by the vector synthesis of the signal strength attenuation slope and the angular jitter component. Dynamically adjusting a phase weighting coefficient of each array element in a phased array antenna beamforming network according to the beam pointing offset vector, wherein an adjustment step size of the phase weighting coefficient is inversely proportional to an absolute value of a signal strength attenuation slope, and an adjustment direction is consistent with a direction of the offset vector; The variance value and the peak value of the bit error rate statistics of the adjusted signal strength sequence are continuously monitored. When both are detected to fall into the preset stable range, the phase weighting coefficient freezing mechanism is triggered, and the beam pointing enters the steady-state tracking stage.

[0008] Preferably, during the fine tracking phase, aircraft maneuver acceleration feedback is introduced to dynamically compensate for beam pointing deviation based on a pre-built interference signature library and suppress signal fluctuations caused by multipath effects. Specifically, The three-axis acceleration data output by the airborne inertial navigation system is collected in real time. The rate of change of maneuvering acceleration is extracted through differential processing to generate a feature vector containing the three-axis maneuvering overload values ​​of pitch, yaw, and roll. Input the feature vector into a pre-built interference feature library for similarity matching, extract the offset pattern that best matches the current maneuver feature through convolution kernel operation, and output the azimuth-pitch two-dimensional compensation basis vector; Based on the direction angle and modulus of the compensation base vector and the real-time beacon signal strength gradient change, a dynamic feedforward compensation is generated in the beam control loop; the amplitude of the feedforward compensation is weighted by the product of the maneuvering overload value and the signal strength attenuation slope, and the direction is consistent with the compensation base vector; Synchronously extract the polarization components of the beacon signal in a multipath interference environment, calculate the polarization correlation matrix between the left-hand circularly polarized wave and the reflected interference signal, and extract the main polarization coupling coefficient through eigenvalue decomposition; The polarization weighted network of the phased array antenna unit is dynamically reconstructed according to the main polarization coupling coefficient to generate a polarization matching weight vector for suppressing multipath reflection. The polarization matching weight vector is spatially synthesized with a dynamic feedforward compensation amount to generate a final beam pointing control instruction.

[0009] The interference feature library stores beam pointing offset patterns under typical maneuvering scenarios, where the typical maneuvering scenarios include dives and sharp turns.

[0010] Preferably, the data validity flag of the main inertial navigation system is continuously checked, and when the failure threshold is triggered, the data stream of the antenna built-in inertial navigation is seamlessly switched to, and the fast recapture procedure is activated to maintain zero interruption of the communication link, specifically: Continuously monitor the data validity flag and the accompanying confidence factor output by the main inertial navigation system. When an abnormal flag is detected or the confidence factor is continuously lower than the preset failure threshold, the main inertial navigation system data stream is determined to be invalid. Based on the failure judgment result, the dominant fusion weight coefficients are immediately allocated to the second attitude data stream output by the antenna's built-in MEMS inertial navigation system, making it the only valid data source, while freezing the main inertial navigation data stream input; Using the second posture data stream, combined with a preset posture jitter suppression factor, low-pass filtering and data smoothing are performed to reconstruct an anti-jitter carrier posture matrix; The coarse alignment reference (including azimuth and elevation) recorded during the pre-failure lock phase is used as the initial pointing center. The reconstructed carrier attitude matrix and the current satellite ephemeris are combined to determine the initial beam pointing angle for dynamic compensation. Based on this initial center, a fast spiral scan path is activated within the preset narrow beam range. During the rapid spiral scanning process, the carrier-to-noise ratio change gradient of the beacon signal is extracted in real time; when the carrier-to-noise ratio change gradient is detected to turn from positive to negative, it is determined that the signal strength has reached a local peak point, and the current beam pointing angle is immediately locked to complete rapid recapture; After beam locking, the signal strength sequence variance is continuously monitored to see if it falls within the preset stability interval. If so, the communication link is confirmed to have recovered to a zero-interruption state. If not, the convergence step size of the spiral scanning path is automatically fine-tuned based on the current carrier-to-noise ratio gradient for secondary optimization.

[0011] A second aspect of the present invention discloses an airborne Tiantong phased array antenna, and a method for applying the airborne Tiantong phased array antenna described in any one of the preceding claims, comprising: The phased array antenna surface consists of multiple antenna elements arranged in a two-dimensional rectangular grid. Each antenna element integrates an independent phase shifter and power amplifier, supports left-hand circular polarization beamforming, and covers an electronic scanning range of 30° to 90° in pitch and 360° in azimuth. The integrated navigation module has a built-in MEMS inertial navigation unit, which is interconnected with the airborne fiber-optic inertial navigation system data, supports dual-source attitude data fusion, and outputs a jitter-resistant carrier attitude matrix; The RF front-end module, which includes up- and down-converters, a low-noise amplifier, and a power splitter, down-converts the received 2170 to 2200 MHz signal to the L-band and outputs it to the multi-mode satellite receiver and satellite communication terminal. The antenna controller integrates a DSP+FPGA architecture to calculate satellite geometric azimuth in real time, control beam scanning mode switching, and dynamically optimize beam pointing based on beacon signal strength and bit error rate characteristics; The heat dissipation structure module uses a heat-conducting metal substrate and a micro fan to ensure that the temperature rise of the phased array transmitting unit is controllable under continuous high-power operation; Standardized interface, providing aviation connector for power input, service data, and Beidou positioning signals, meeting the electromagnetic compatibility requirements of airborne equipment.

[0012] The present invention solves the technical defects existing in the background technology and has the following beneficial effects: through dual inertial navigation collaborative solution, hierarchical beam scanning, dynamic anti-disturbance compensation and hot switching fault tolerance mechanism, the present invention can improve the beam pointing accuracy during high-maneuverability flight, effectively suppress signal fluctuations caused by carrier vibration and multipath interference, ensure seamless switching of the communication link when the inertial navigation system fails, and realize continuous and stable tracking of satellite links in complex environments. BRIEF DESCRIPTION OF THE DRAWINGS

[0013] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the embodiments or the description of the prior art. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, without paying any creative work, they can also obtain drawings of other embodiments based on these drawings.

[0014] Figure 1 This is a flow chart of the overall method of applying the machine-borne Tiantong phased array antenna; Figure 2 This is a partial flow chart of the method for applying the onboard Tiantong phased array antenna; Figure 3 This is a simplified module diagram of the aircraft's onboard Tiantong phased array antenna. DETAILED DESCRIPTION

[0015] In order to more clearly understand the above-mentioned objects, features and advantages of the present invention, the present invention is further described in detail below in conjunction with the accompanying drawings and specific embodiments. It should be noted that, in the absence of conflict, the embodiments of the present application and the features therein can be combined with each other.

[0016] In the following description, many specific details are set forth to facilitate a full understanding of the present invention. However, the present invention may also be implemented in other ways different from those described herein. Therefore, the scope of protection of the present invention is not limited to the specific embodiments disclosed below.

[0017] like Figure 1 As shown, the first aspect of the present invention discloses an application method of an airborne Tiantong phased array antenna, comprising the following steps: S102: Synchronously collect attitude data from the airborne inertial navigation system and the antenna's built-in MEMS inertial navigation system, fuse them to generate an anti-jitter carrier attitude matrix, and calculate the geometric azimuth of the Tiantong satellite in real time; S104, driving the phased array antenna beam to perform electronic scanning according to the geometric azimuth angle, first performing blind capture of beacon signals in a preset airspace in a wide beam mode, and immediately switching to a narrow beam scanning mode when an initial signal is detected; S106, extracting beacon signal strength and bit error rate characteristics, combining them with inertial navigation attitude jitter compensation, and dynamically adjusting the phase weighting coefficient to achieve pointing adjustment, so that the signal quality parameters continue to converge to the optimal threshold range; S108: Introducing aircraft maneuver acceleration feedback during the fine tracking phase, dynamically compensating for beam pointing deviation based on a pre-built interference signature library, and suppressing signal fluctuations caused by multipath effects; S110, continuously checking the data validity flag of the main inertial navigation system, seamlessly switching to the antenna built-in inertial navigation data stream when the failure threshold is triggered, and activating the fast recapture program to maintain zero interruption of the communication link.

[0018] It should be noted that this invention solves the technical problems of poor satellite tracking stability and easy signal interruption in airborne phased array antennas in highly dynamic flight environments. Through dual inertial navigation collaborative solution, hierarchical beam scanning, dynamic anti-disturbance compensation, and hot-swap fault-tolerant mechanisms, it can improve beam pointing accuracy during highly maneuverable flight, effectively suppress signal fluctuations caused by carrier vibration and multipath interference, ensure seamless communication link switching in the event of an inertial navigation system failure, and achieve continuous and stable satellite link tracking in complex environments.

[0019] Preferably, the attitude data of the airborne inertial navigation and the antenna built-in MEMS inertial navigation are collected synchronously, and the anti-shake carrier attitude matrix is ​​generated by fusion, and the geometric azimuth of the Tiantong satellite is solved in real time, such as Figure 2As shown, specifically: S202, collecting a first attitude data stream output by the airborne fiber-optic inertial navigation system, including real-time attitude angle, angular rate, and data validity flag; and collecting a second attitude data stream output by the antenna's built-in MEMS inertial navigation system, including real-time attitude angle and angular rate; S204, calculating the onboard inertial navigation credibility evaluation value in real time based on the data validity flag in the first attitude data stream; and at the same time, calculating the built-in inertial navigation credibility evaluation value based on the noise level of the second attitude data stream; It should be noted that the system analyzes the data validity flag in the first posture data stream in real time. When the flag is in the "valid" state: first count the number of consecutive valid data cycles N. When N exceeds the preset threshold (such as 5 cycles), according to the formula K1=1-0.1×(N max -N) calculate the initial credibility, where N max The maximum number of consecutive valid cycles allowed (e.g., 20) is also detected. If the attitude angle change between consecutive cycles exceeds the threshold, K1 is attenuated by a factor of 0.9. Finally, considering the data update rate, a weighted correction of 0.8 is applied to K1 when the rate falls below the standard value. The final output is the airborne inertial navigation credibility assessment value, K1.

[0020] For the second attitude data stream, the system first collects the raw angular velocity data output by the MEMS inertial navigation system, calculates the variance σ² through a sliding window (e.g., 10 sampling points), and then outputs the built-in inertial navigation credibility assessment value K2 based on the preset noise-credibility mapping curve (K2=1 when σ²≤0.01, K2=0.9-5×(σ²-0.01) when 0.01<σ²≤0.1, and K2=0.4 when σ²>0.1). At the same time, when a high-frequency noise component exceeding 500Hz is detected, K2 is downgraded by 0.7 times.

[0021] S206, dynamically allocating a dominant fusion weight coefficient and an auxiliary fusion weight coefficient of the first attitude data stream and the second attitude data stream during the fusion process according to the airborne inertial navigation credibility evaluation value and the built-in inertial navigation credibility evaluation value; It should be noted that the system employs a dynamic weighting strategy based on the real-time calculated airborne inertial navigation (INS) credibility assessment values ​​K1 and K2. When K1 ≥ 0.8 and K1 - K2 > 0.2, the first attitude data stream is designated as the dominant data source, assigned a dominant fusion weight coefficient α of 0.7 to 0.9, while the second attitude data stream is assigned a secondary fusion weight coefficient β of 1 - α. When K2 > K1 or K1 < 0.6, the weighting strategy automatically switches, giving the INS data stream a dominant weight α of 0.6 to 0.8. In the transition period (|K1 - K2| ≤ 0.2), a balanced weight α of 0.5 is used. The weight coefficients are updated every 100ms, and smoothing filtering is used to prevent drastic fluctuations, ensuring the stability of dual-source data fusion.

[0022] S208: Combining the dominant fusion weight coefficient, the auxiliary fusion weight coefficient, and a preset attitude jitter suppression factor for high-frequency jitter of the carrier, weighted averaging and low-pass filtering are performed on the dual-source attitude data (the first attitude data stream and the second attitude data stream), and outputting an anti-jitter carrier attitude matrix; The attitude jitter suppression factor refers to a pre-set low-pass filter parameter used to filter out high-frequency attitude jitter of the carrier. The cutoff frequency is set to 5-10 Hz based on the typical vibration characteristics of the carrier. It is used to effectively suppress the impact of short-term and severe attitude fluctuations on satellite pointing calculations during data fusion. S210, based on the anti-shake carrier attitude matrix, the real-time acquired Tiantong satellite orbit ephemeris parameters and the carrier's Beidou positioning information, output the real-time geometric azimuth of the Tiantong satellite relative to the carrier through conversion calculation from the geographic coordinate system to the carrier coordinate system.

[0023] In one embodiment of the present invention, when an emergency rescue drone performs a search and rescue mission in a mountainous area and experiences severe vibrations due to complex airflow, the system simultaneously collects the attitude angle, angular rate, and validity flag output by the fiber-optic inertial navigation system of the drone's main flight control system, as well as the real-time attitude data from the antenna's built-in MEMS inertial navigation system. By dynamically evaluating the credibility of the dual-source data (main inertial navigation weight 0.8 / built-in inertial navigation weight 0.2) and performing data fusion, a stable carrier attitude matrix is ​​generated. Based on this matrix, Tiantong satellite real-time ephemeris, and airborne Beidou positioning data, the precise azimuth angle of the satellite relative to the drone (e.g., 55.2° pitch and 268.7° azimuth) is calculated in real time. Even when the drone encounters a 15° attitude fluctuation caused by strong crosswinds, the system can maintain stable satellite pointing, ensuring a continuous and unobstructed communication link with the rescue command center.

[0024] Preferably, the phased array antenna beam is driven to perform electronic scanning according to the geometric azimuth angle, and blind capture of the beacon signal is first performed in a preset airspace in a wide beam mode. When the initial signal is detected, it is immediately switched to a narrow beam scanning mode, specifically: Determining an initial beam pointing center according to the geometric azimuth angle and setting a scanning range of a wide beam mode, wherein the scanning range includes a pitch sector airspace and an azimuth cone airspace centered on the geometric azimuth angle, and configuring a beam width and a scanning step increment of the wide beam; Within the scanning range, electronic beam scanning is performed according to a preset scanning trajectory, and the carrier-to-noise ratio characteristics of the beacon signal are detected at each beam dwell point. If no valid signal is detected, the scanning step increment is adjusted to optimize the scanning efficiency; When it is detected that the carrier-to-noise ratio of the beacon signal exceeds the preset capture threshold, the instantaneous azimuth and elevation angles of the current beam pointing are extracted as coarse alignment references, and the corresponding signal strength distribution characteristics are recorded; wherein the preset capture threshold is the carrier-to-noise ratio (CNR) threshold range of the beacon signal of 20-30dB / Hz, and the specific value is dynamically adjusted according to the Tiantong satellite signal strength and the ambient noise level; Based on the coarse alignment reference, the beam mode is switched to a narrow beam, and a dynamically shrinking spiral scanning path is constructed within a preset range of the coarse alignment reference, while optimizing the convergence speed of the scanning path in combination with the signal intensity distribution characteristics; For example, the system uses the coarse alignment reference point as the center and generates an initial spiral scanning path within the preset range of ±5° in azimuth and ±4° in pitch. Based on the recorded signal strength distribution characteristics, if the area with a larger intensity gradient is located to the upper right of the reference point, the starting offset point of the spiral path is set in this quadrant, and the direction of the line connecting the reference point and the intensity peak point is used as the main axis of the spiral contraction. At the same time, the contraction step size of the spiral circle is dynamically adjusted according to the intensity gradient value - for every 1dB / ° increase in the gradient, the step size is correspondingly reduced by 0.2°, and additional sampling points are inserted in the area where the intensity changes slowly, so that the scanning path can adaptively converge quickly to the area with the strongest signal until the peak point that meets the locking conditions is detected.

[0025] During the narrow beam scanning process, the slope changes of the beacon signals at adjacent beam dwell points are compared in real time. When the signal strength reaches a local peak and the slope approaches zero, it is determined to be the optimal direction and the beam is locked.

[0026] Among them, the wide beam mode is a large-range search mode with a beam width of 10°-20° and a scanning step increment of 5°-8°; the narrow beam scanning mode is a high-precision tracking mode with a beam width of 2°-5° and a scanning step increment of 0.5°-2°.

[0027] In one embodiment of the present invention, when communicating based on the aforementioned satellite geometric azimuth (55.2° in elevation, 268.7° in azimuth), the system first scans in a zigzag trajectory within the airspace of 45°-65° in elevation and 250°-290° in azimuth in wide-beam mode with a beamwidth of 18°, pausing for 80ms at each dwell point to detect beacon signals. For example, if a carrier-to-noise ratio exceeding 23dB / Hz is detected at 53.6° in elevation and 271.2° in azimuth, the system immediately records the orientation as a coarse alignment reference and switches to narrow-beam mode with a beamwidth of 4°. A dynamic spiral path with a radius of 8° is constructed around the reference, and the convergence step size is adaptively adjusted based on the signal strength gradient. Finally, the beam is locked at 54.8° in elevation and 269.3° in azimuth, at which point the signal strength reaches its peak and the slope difference between adjacent points is less than 0.15dB / ms, achieving rapid and precise alignment consistent with the azimuth data.

[0028] Preferably, the beacon signal strength and bit error rate characteristics are extracted, combined with the inertial navigation attitude jitter compensation amount, and the phase weighting coefficient is dynamically adjusted to achieve pointing adjustment, so that the signal quality parameters continue to converge to the optimal threshold range, specifically: The beacon signal output by the phased array antenna receiving channel is sampled in real time, the in-phase component and the orthogonal component are extracted through digital down-conversion, the instantaneous signal amplitude is calculated and smoothed to generate a normalized signal strength sequence; Synchronously analyze the bit error rate statistics output by the demodulator and use sliding window filtering to generate the bit error rate change gradient characteristics; Decomposing the attitude jitter compensation output by the inertial navigation system into angular jitter components of the pitch axis and the azimuth axis, and performing spatiotemporal matching with the signal strength sequence and the bit error rate gradient feature through time alignment processing; The attitude jitter compensation output by the inertial navigation system refers to the high-frequency attitude angle fluctuation component of the carrier measured in real time by the airborne inertial navigation system. The method for obtaining it is: after the raw attitude angle data is processed by 50-100Hz high-pass filtering, it is decomposed into the pitch axis and azimuth axis angular jitter components through coordinate system transformation. It is used to compensate for the instantaneous deviation of the phased array beam pointing. A three-dimensional feature space is constructed, containing the signal strength attenuation slope, the bit error rate gradient extreme point, and the angular jitter component. The beam pointing offset vector is dynamically calculated within this feature space. The modulus of the beam pointing offset vector is weighted by the bit error rate gradient extreme point, and its direction is determined by the vector synthesis of the signal strength attenuation slope and the angular jitter component. It is important to note that a three-dimensional feature space is established with the signal strength attenuation slope (dB / s), bit error rate gradient (% / s), and angular jitter component (° / s) as the coordinate axes. Real-time signal characteristic parameters are mapped into this space. The offset vector modulus is corrected at the extreme points of the bit error rate gradient using a preset weight coefficient (0.6-0.8) to prioritize communication quality. The signal strength attenuation slope (e.g., -1.2dB / s) and the angular jitter component (e.g., 0.5° / s in elevation and 0.3° / s in azimuth) are vector-synthesized, and the offset angle (e.g., 35° in elevation) is calculated using the inverse tangent function. The final output beam pointing offset vector combines communication performance indicators and the effects of mechanical vibration, and its modulus and direction are updated every 200ms.

[0029] Dynamically adjusting a phase weighting coefficient of each array element in a phased array antenna beamforming network according to the beam pointing offset vector, wherein an adjustment step size of the phase weighting coefficient is inversely proportional to an absolute value of a signal strength attenuation slope, and an adjustment direction is consistent with a direction of the offset vector; It should be noted that based on the real-time calculated beam pointing offset vector (e.g., modulus 0.4°, +0.3° in elevation / -0.25° in azimuth), the phase of each phased array element is adjusted through the following steps: First, the offset vector is decomposed into its components in elevation and azimuth. Then, the basic adjustment step size is determined based on the absolute value of the current signal strength attenuation slope (e.g., a slope of 1 dB / s corresponds to a step size of 0.08λ), and a dynamic scaling factor of 0.8-1.2 is introduced. The phase delay compensation required in elevation and azimuth is determined based on the position coordinates of each element in the array (e.g., edge elements require a compensation of 0.12λ). Finally, the updated phase weighting coefficients are distributed to each element through the beamforming network, ensuring that the phase adjustment direction of all elements is consistent with the offset vector (e.g., uniformly increasing the elevation phase and decreasing the azimuth phase).

[0030] The variance value and the peak value of the bit error rate statistics of the adjusted signal strength sequence are continuously monitored. When both are detected to fall into the preset stable range, the phase weighting coefficient freezing mechanism is triggered, and the beam pointing enters the steady-state tracking stage.

[0031] In one embodiment of the present invention, after locking onto a satellite beam (54.8° in elevation, 269.3° in azimuth), the system collects the in-phase and quadrature components of the beacon signal in real time, applies a sliding average filter to generate a normalized signal strength sequence, and simultaneously monitors the bit error rate gradient (e.g., a 5% decrease per second) output by the demodulator. When the onboard inertial navigation system detects high-frequency jitter of 0.5° in pitch and 0.3° in azimuth due to crosswind, the system aligns the jitter compensation with the signal's temporal and spatial characteristics, calculates a pointing offset vector (modulus 0.4°, +0.3° in pitch / -0.25° in azimuth) in three-dimensional feature space, and dynamically adjusts the phase weighting coefficients of 32 array elements (maximum adjustment step size 0.1λ) based on this offset. A coefficient freeze is triggered when the signal strength fluctuation is less than ±0.02 for three consecutive seconds, enabling stable tracking in high-jitter environments.

[0032] Preferably, during the fine tracking phase, aircraft maneuver acceleration feedback is introduced to dynamically compensate for beam pointing deviation based on a pre-built interference signature library and suppress signal fluctuations caused by multipath effects. Specifically, The three-axis acceleration data output by the airborne inertial navigation system is collected in real time. The rate of change of maneuvering acceleration is extracted through differential processing to generate a feature vector containing the three-axis maneuvering overload values ​​of pitch, yaw, and roll. For example, the system acquires three-axis raw acceleration data (X / Y / Z axes) from the airborne inertial navigation system at a 100Hz sampling rate in real time. It first uses a sliding average filter to eliminate high-frequency noise, then performs a first-order differential operation on the data in each axis to calculate the instantaneous rate of change (for example, a change from 1.2g to 1.5g on the X axis yields a rate of change of 3g / s). The filtered acceleration value (in g) and its rate of change (in g / s) are combined along the three axes (pitch, yaw, and roll) to generate a six-dimensional feature vector. The data for each axis undergoes coordinate system transformation and alignment to the antenna carrier coordinate system. Finally, it undergoes normalization to bring the values ​​of each dimension into the range of 0-1, forming a standardized maneuvering overload feature vector for subsequent matching.

[0033] Input the feature vector into a pre-built interference feature library for similarity matching, extract the offset pattern that best matches the current maneuver feature through convolution kernel operation, and output the azimuth-pitch two-dimensional compensation basis vector; Based on the direction angle and modulus of the compensation base vector and the real-time beacon signal strength gradient change, a dynamic feedforward compensation is generated in the beam control loop; the amplitude of the feedforward compensation is weighted by the product of the maneuvering overload value and the signal strength attenuation slope, and the direction is consistent with the compensation base vector; It should be noted that the modulus of the compensation basis vector (e.g., 0.5°) is multiplied by the real-time beacon signal strength gradient (e.g., -1.2 dB / s), then multiplied by a preset weighting factor (typically 0.3) to obtain the initial amplitude of the feedforward compensation (0.5 × 1.2 × 0.3 = 0.18°). This amplitude is further adjusted to the current maneuvering g-load value (e.g., 1.2g on the roll axis) (e.g., 1.2g corresponds to a magnification factor of 1.15), resulting in a final compensation amplitude of 0.21°. The compensation direction directly uses the original azimuth angle of the compensation basis vector (e.g., +30° in azimuth). This is decomposed into the phased array's pitch and azimuth control dimensions through coordinate transformation, generating dynamic feedforward compensation commands that directly act on the beam steering loop. These commands are updated every 50ms and are superimposed on the feedback control output.

[0034] Synchronously extract the polarization components of the beacon signal in a multipath interference environment, calculate the polarization correlation matrix between the left-hand circularly polarized wave and the reflected interference signal, and extract the main polarization coupling coefficient through eigenvalue decomposition; It should be noted that the dual-polarized receiving channels of the phased array antenna synchronously collect the left-hand circularly polarized (LHCP) main component and right-hand circularly polarized (RHCP) reflected interference component of the beacon signal. The time-domain signals of the two polarization channels are cross-correlated to construct a 2×2 polarization correlation matrix. This matrix is ​​then subjected to eigenvalue decomposition, and the eigenvector corresponding to the maximum eigenvalue is extracted as the main polarization component. This eigenvector is projected onto the LHCP basis to calculate the projection coefficient. Finally, this coefficient is normalized to a main polarization coupling coefficient in the range of 0–1 (e.g., 0.35), which is used to quantify the intensity of multipath interference. A coefficient closer to 1 indicates weaker interference, while a coefficient closer to 0 indicates more severe multipath interference.

[0035] The polarization weighted network of the phased array antenna unit is dynamically reconstructed according to the main polarization coupling coefficient to generate a polarization matching weight vector for suppressing multipath reflection. The polarization matching weight vector is spatially synthesized with a dynamic feedforward compensation amount to generate a final beam pointing control instruction.

[0036] The interference feature library stores beam pointing offset patterns under typical maneuvering scenarios, where the typical maneuvering scenarios include dives and sharp turns.

[0037] In one embodiment of the present invention, when an aircraft encounters strong crosswinds and requires an emergency turn, the system collects three-axis acceleration data (e.g., 1.2g for roll and 0.8g for yaw) from the inertial navigation system in real time. After differential processing, it generates a feature vector that is input into the interference feature library. It then matches an offset pattern similar to a "sharp turn" and outputs a compensation basis vector (e.g., +0.6° for azimuth / -0.3° for pitch). Combined with the current beacon signal strength gradient (e.g., -1.5dB / s), a dynamic feedforward compensation (e.g., +0.72° for azimuth / -0.36° for pitch) is generated in the beam steering loop. Simultaneously, a polarization-weighted network is reconstructed based on the main coupling coefficients of the polarization correlation matrix caused by detected multipath interference to generate a suppression weight vector, ultimately synthesizing a compensation instruction for azimuth +0.68° / pitch -0.32°.

[0038] Preferably, the data validity flag of the main inertial navigation system is continuously checked, and when the failure threshold is triggered, the data stream of the antenna built-in inertial navigation is seamlessly switched to, and the fast recapture procedure is activated to maintain zero interruption of the communication link, specifically: Continuously monitor the data validity flag and the accompanying confidence factor output by the main inertial navigation system. When an abnormal flag is detected or the confidence factor is continuously lower than the preset failure threshold (lower than 0.5 for three consecutive times), the main inertial navigation data stream is determined to be invalid. Among them, the flag abnormality refers to the data validity flag output by the airborne main inertial navigation system appearing in the "invalid" state for N consecutive cycles (N≥3), or the flag undergoing unexpected jumps between the valid / invalid states (such as jumping more than 5 times within 1 second), indicating that there are reliability issues with the inertial navigation data.

[0039] Based on the failure judgment result, the dominant fusion weight coefficients are immediately allocated to the second attitude data stream output by the antenna's built-in MEMS inertial navigation system, making it the only valid data source, while freezing the main inertial navigation data stream input; Using the second posture data stream, combined with a preset posture jitter suppression factor, low-pass filtering and data smoothing are performed to reconstruct an anti-jitter carrier posture matrix; The coarse alignment reference (including azimuth and elevation) recorded during the pre-failure lock phase is used as the initial pointing center. The reconstructed carrier attitude matrix and the current satellite ephemeris are combined to determine the initial beam pointing angle for dynamic compensation. Based on this initial center, a fast spiral scan path is activated within the preset narrow beam range. During the rapid spiral scanning process, the carrier-to-noise ratio change gradient of the beacon signal is extracted in real time; when the carrier-to-noise ratio change gradient is detected to turn from positive to negative, it is determined that the signal strength has reached a local peak point, and the current beam pointing angle is immediately locked to complete rapid recapture; After beam locking, the signal strength sequence variance is continuously monitored to see if it falls within the preset stability range (less than 0.05 for 10 seconds and the fluctuation range does not exceed ±0.02). If so, the communication link is confirmed to have recovered to a zero-interruption state. If not, the convergence step size of the spiral scanning path is automatically fine-tuned based on the current carrier-to-noise ratio change gradient for secondary optimization.

[0040] It should be noted that this method, through intelligent monitoring and rapid switching of the primary and backup inertial navigation systems, achieves high-reliability operation of the airborne satellite communication system in the event of an inertial navigation failure. It can restore the satellite link extremely quickly after a primary inertial navigation failure, effectively resolving the communication interruption problem caused by inertial navigation failures in traditional systems. Furthermore, through closed-loop signal stability detection and adaptive adjustment of scanning parameters, it ensures continuous and stable communication quality after recapture, improving the fault tolerance and continuous service reliability of the airborne phased array antenna system.

[0041] In the present invention, the application method may further comprise the following steps: Orthogonal dual-channel sampling is performed on the received beacon signal to extract the instantaneous Stokes parameters of the left-hand circular polarization (LHCP) and right-hand circular polarization (RHCP) components, and the polarization ellipse inclination variance is calculated as the multipath fading depth characteristic; When the polarization ellipse tilt angle variance exceeds the axial ratio deterioration dynamic threshold, an orthogonal polarization switching instruction is generated to switch the transmitter to a transmission mode opposite to the current dominant receiving polarization rotation direction; The cross-polarization component of the received signal after switching is collected, and a time-varying polarization correlation matrix containing the co-polarization and cross-polarization power ratio is constructed. The variance of its main diagonal elements is extracted to generate the polarization purity degradation factor. Performing a convolution operation on the polarization purity degradation factor and the measured reciprocal error data of the antenna unit to output an amplitude-phase joint compensation vector for the LHCP / RHCP channel, wherein the amplitude-phase compensation amount is weighted and corrected by the asymmetric component of the polarization correlation matrix; A Kronecker product operation is performed on the joint compensation vector and the phased array baseband precoding matrix to generate polarization-optimized beamforming weights, which are loaded into a digital beamformer and fed back in real time to update the trace norm of the polarization correlation matrix. When the trace norm converges to a steady-state interval, the weight update is frozen.

[0042] For example, during an emergency rescue drone mission, a phased array antenna receives the S-band Tiantong satellite beacon signal. The received signal is first sampled in two orthogonal channels, and the Stokes parameters of the LHCP and RHCP components (e.g., S1=0.82, S2=-0.17, S3=0.43) are extracted in real time. The variance of the polarization ellipse tilt angle is calculated to be 12.7° (a characteristic of multipath fading depth) over a continuous 200 millisecond period. When this value exceeds the preset 8° axial ratio degradation dynamic threshold, an orthogonal polarization switching command is generated, switching the transmitter from LHCP to RHCP mode. The cross-polarization component of the switched signal is then collected to construct a polarization correlation matrix (co-polarization power ratio 0.91, cross-polarization power ratio 0.09). The variance of the main diagonal elements, 0.15, is extracted to form the polarization purity degradation factor. This factor is convolved with pre-measured antenna element reciprocal error data (amplitude error ±0.8dB, phase error ±5°) to output a joint amplitude-phase compensation vector (LHCP channel amplitude compensation +0.6dB / phase compensation -3°). Finally, this vector is Kronecker-producted with the baseband precoding matrix to generate optimized weights, which are then loaded into the beamformer. The weights are frozen after the trace norm of the polarization correlation matrix converges from an initial 0.28 to 0.18 (in the steady-state range [0.15, 0.2]) in real time, effectively reducing the received signal bit error rate.

[0043] It should be noted that to address the signal polarization mismatch and axial ratio degradation caused by multipath interference in airborne environments, and to avoid the degradation of communication quality in dynamic reflection scenarios associated with traditional fixed polarization modes, this example utilizes real-time polarization state monitoring and adaptive transmit polarization switching, combined with joint channel error compensation and closed-loop beamforming optimization, to suppress the impact of multipath fading on signal quality, improve antenna axial ratio stability, and ensure anti-interference and transmission reliability of communication links in complex reflection environments.

[0044] In the present invention, the application method may further comprise the following steps: An electron density probe array is deployed along the longitudinal axis of the aircraft. A spatiotemporally synchronized original sequence of electron density is acquired with a sampling interval of 1 / 4 of the carrier frequency. The plasma oscillation frequency characteristics are extracted through adaptive sliding window filtering. Calculating the instantaneous ratio of the oscillation frequency characteristic quantity to the Tiantong satellite carrier frequency, triggering the direction switching when the ratio exceeds a critical threshold: if the ratio gradient is positive, switching to left-hand circular polarization, and if it is negative, maintaining right-hand circular polarization, and generating a confidence factor for the direction switching; The current electron density raw sequence is input into a pre-constructed dispersion relation matrix to obtain a complex dielectric constant tensor; the absolute value of the imaginary part of the off-diagonal component of the tensor is extracted as the orthogonal polarization phase difference reference quantity, and then multiplied by the hand-direction switching confidence factor to generate a dynamic compensation phase angle; It should be noted that when the currently acquired raw electron density sequence is input into the pre-constructed dispersion relation matrix, the raw sequence is first normalized to eliminate data bias caused by measurement errors. The processed electron density values ​​are then substituted into the matrix and, combined with the preset collision frequency parameter, the complex real and imaginary parts of the dielectric constant are determined. A magnetic field coupling correction is then performed based on the current geomagnetic environment parameters to obtain a three-dimensional dielectric constant tensor that incorporates anisotropic characteristics. Finally, this tensor is symmetry-checked to ensure that it satisfies the physical constraints of Maxwell's equations, and the final dielectric constant tensor is output for phase compensation calculations.

[0045] After applying the dynamic compensation phase angle, the cross-polarization discrimination rate of the orthogonal component of the downlink signal is demodulated in real time; when the discrimination rate is lower than the mismatch threshold, a correlation operation is performed on the phase lag of the cross-polarization component and the dielectric constant tensor, a tensor error compensation coefficient is output, and a dispersion relation matrix is ​​iteratively updated; The variance value of the signal delay spread after iterative update is statistically calculated and convolved with the plasma oscillation frequency characteristic to generate a penetration efficiency index. When the index shows a monotonically increasing trend for three consecutive sampling periods, it is determined that the abnormal mode wave is continuously excited.

[0046] Among them, the pre-constructed dispersion relation matrix is ​​a complex tensor established based on the measured data of plasma frequency, collision frequency and electron density. Its diagonal elements represent the real part of the dielectric constant along different spatial axes (determines the phase delay), and the non-diagonal elements contain the anisotropic coupling component caused by the magnetic field (affects the polarization rotation).

[0047] For example, an array of six electron density probes is deployed equidistantly along the longitudinal axis of the spacecraft. With a sampling interval of one-quarter of the Tiantong satellite's S-band 2.1 GHz carrier (approximately 119 ps), the raw plasma sheath electron density sequence is synchronously acquired. An adaptive sliding window filter with a window length of 15 sampling points is used to extract the oscillation frequency characteristic (typically 80-120 MHz). The instantaneous ratio of this characteristic to the carrier frequency is calculated in real time. When the ratio gradient continuously increases and exceeds a critical threshold of 1.5 times, a left-hand circular polarization switch is triggered, generating a confidence factor of 0.92. The current density sequence is input into a pre-constructed dispersion relation matrix (calibrated through wind tunnel testing and containing the electron density-collision frequency mapping and the geomagnetic field coupling coefficient). The dielectric constant tensor is obtained, and the absolute value of the imaginary part of its off-diagonal component is extracted as a phase difference reference. This is multiplied by the confidence factor to generate the dynamically compensated phase angle. After applying compensation, the downlink signal is demodulated in real time. When the cross-polarization discrimination rate drops to the 40% mismatch threshold, the detected phase lag is cross-correlated with the dielectric constant tensor, outputting a tensor error compensation coefficient matrix that is iteratively updated. After the update, the signal delay spread variance is calculated and convolved with the oscillation frequency characteristic to generate a penetration efficiency index. When the index maintains an increase of more than 15% for three consecutive sampling periods, it is determined that the abnormal mode is continuously excited, thereby maintaining the satellite communication link.

[0048] It should be noted that to address the problem of communication signal attenuation and interruption caused by the plasma sheath when the drone re-enters the blackout zone, this embodiment effectively maintains the stability of the satellite communication link by monitoring the dynamic characteristics of the plasma electron density in real time, intelligently switches polarization modes, and accurately compensates for phase offsets. This improves signal penetration in plasma environments, ensuring stable and reliable communication quality. Furthermore, a closed-loop feedback mechanism continuously optimizes compensation accuracy, achieving adaptive, anti-interference communication in complex electromagnetic environments.

[0049] like Figure 3 As shown, the second aspect of the present invention discloses an airborne Tiantong phased array antenna, and an application method of the airborne Tiantong phased array antenna described in any one of the above items includes: Phased array antenna surface 1, composed of multiple antenna elements arranged in a two-dimensional rectangular grid. Each antenna element integrates an independent phase shifter and power amplifier, supports left-hand circular polarization beamforming, and covers an electronic scanning range of 30° to 90° in pitch and 360° in azimuth; Integrated navigation module 2, with built-in MEMS inertial navigation unit, is interconnected with the airborne fiber-optic inertial navigation system, supports dual-source attitude data fusion, and outputs a jitter-resistant carrier attitude matrix; The RF front-end module 3, which includes up- and down-converters, a low-noise amplifier, and a power splitter, down-converts the received 2170 to 2200 MHz signal to the L-band and outputs it to the multi-mode satellite receiver and the satellite communication terminal. Antenna controller 4, integrating DSP+FPGA architecture, calculates satellite geometric azimuth in real time, controls beam scanning mode switching, and dynamically optimizes beam pointing based on beacon signal strength and bit error rate characteristics; The heat dissipation structure module 5 uses a heat-conducting metal substrate and a micro fan to ensure that the temperature rise of the phased array transmitting unit is controllable under continuous high-power operation; Standardized interface 6 provides an aviation connector for power input, service data, and Beidou positioning signals, meeting the electromagnetic compatibility requirements of airborne equipment.

[0050] In the several embodiments provided in this application, it should be understood that the disclosed devices and methods can be implemented in other ways. The device embodiments described above are merely schematic. For example, the division of the units is merely a logical function division. In actual implementation, there may be other division methods, such as: multiple units or components can be combined, or can be integrated into another system, or some features can be ignored or not executed. In addition, the coupling, direct coupling, or communication connection between the components shown or discussed can be through some interfaces, and the indirect coupling or communication connection of the devices or units can be electrical, mechanical or other forms.

[0051] The units described above as separate components may or may not be physically separated, and the components displayed as units may or may not be physical units; they may be located in one place or distributed across multiple network units; some or all of the units may be selected according to actual needs to achieve the purpose of the scheme of this embodiment.

[0052] In addition, all functional units in the embodiments of the present invention may be integrated into one processing unit, or each unit may be separately used as a unit, or two or more units may be integrated into one unit; the above-mentioned integrated units may be implemented in the form of hardware or in the form of hardware plus software functional units.

[0053] Those skilled in the art will appreciate that all or part of the steps of the above-mentioned method embodiments may be implemented by hardware associated with program instructions, and the aforementioned program may be stored in a computer-readable storage medium. When the program is executed, the program executes the steps of the above-mentioned method embodiments. The aforementioned storage medium includes various media that can store program codes, such as mobile storage devices, read-only memories (ROMs), random access memories (RAMs), magnetic disks, or optical disks.

[0054] Alternatively, if the integrated units described above are implemented as software modules and sold or used as standalone products, they can also be stored on a computer-readable storage medium. Based on this understanding, the technical solutions of the embodiments of the present invention, or the portion that contributes to the prior art, can be embodied in the form of a software product. This computer software product, stored on a storage medium, includes instructions for enabling a computer device (such as a personal computer, server, or network device) to execute all or part of the methods of the various embodiments of the present invention. The aforementioned storage media include various media capable of storing program code, such as removable storage devices, ROM, RAM, magnetic disks, or optical disks.

[0055] The above are only specific embodiments of the present invention, but the scope of protection of the present invention is not limited thereto. Any technician familiar with this technical field can easily think of changes or replacements within the technical scope disclosed by the present invention, which should be covered by the scope of protection of the present invention.

Claims

1. An application method of an airborne Tiantong phased array antenna, characterized in that: The following steps are involved: Synchronously collect attitude data from the airborne inertial navigation system and the antenna's built-in MEMS inertial navigation system, fuse them to generate an anti-jitter carrier attitude matrix, and calculate the geometric azimuth of the Tiantong satellite in real time; Driving the phased array antenna beam to electronically scan according to the geometric azimuth angle, first performing blind capture of beacon signals in a preset airspace in a wide beam mode, and immediately switching to a narrow beam scanning mode when an initial signal is detected; The beacon signal strength and bit error rate characteristics are extracted, combined with the inertial navigation attitude jitter compensation, and the phase weighting coefficient is dynamically adjusted to achieve pointing adjustment, so that the signal quality parameters continue to converge to the optimal threshold range; In the fine tracking phase, aircraft maneuver acceleration feedback is introduced to dynamically compensate for beam pointing deviation based on a pre-built interference signature library and suppress signal fluctuations caused by multipath effects. Continuously check the data validity flag of the main inertial navigation system, seamlessly switch to the antenna's built-in inertial navigation data stream when the failure threshold is triggered, and activate the fast recapture procedure to maintain zero interruption of the communication link.

2. The application method of the airborne Tiantong phased array antenna according to claim 1, characterized in that: Synchronously collect attitude data from the airborne inertial navigation system and the antenna's built-in MEMS inertial navigation system, fuse them to generate a jitter-resistant carrier attitude matrix, and calculate the geometric azimuth of the Tiantong satellite in real time. Specifically: Collect the first attitude data stream output by the airborne fiber-optic inertial navigation system, including real-time attitude angle, angular rate, and data validity flag; and collect the second attitude data stream output by the antenna's built-in MEMS inertial navigation system, including real-time attitude angle and angular rate; Based on the data validity flag in the first attitude data stream, a credibility evaluation value of the onboard inertial navigation is calculated in real time; at the same time, a credibility evaluation value of the built-in inertial navigation is calculated according to the noise level of the second attitude data stream; Dynamically allocating a dominant fusion weight coefficient and an auxiliary fusion weight coefficient of the first attitude data stream and the second attitude data stream during a fusion process according to the airborne inertial navigation credibility evaluation value and the built-in inertial navigation credibility evaluation value; Combining the dominant fusion weight coefficient, the auxiliary fusion weight coefficient, and the preset attitude jitter suppression factor for the carrier high-frequency jitter, weighted averaging and low-pass filtering are performed on the dual-source attitude data to output an anti-jitter carrier attitude matrix; Based on the anti-shake carrier attitude matrix, the real-time acquired Tiantong satellite orbit ephemeris parameters and the carrier's Beidou positioning information, the real-time geometric azimuth of the Tiantong satellite relative to the carrier is output through conversion calculation from the geographic coordinate system to the carrier coordinate system.

3. The application method of the airborne Tiantong phased array antenna according to claim 1, characterized in that: The phased array antenna beam is driven to perform electronic scanning according to the geometric azimuth angle. The beacon signal is first blindly captured in a preset airspace in a wide beam mode. When the initial signal is detected, it is immediately switched to a narrow beam scanning mode. Specifically, Determining an initial beam pointing center according to the geometric azimuth angle and setting a scanning range of a wide beam mode, wherein the scanning range includes a pitch sector airspace and an azimuth cone airspace centered on the geometric azimuth angle, and configuring a beam width and a scanning step increment of the wide beam; Within the scanning range, electronic beam scanning is performed according to a preset scanning trajectory, and the carrier-to-noise ratio characteristics of the beacon signal are detected at each beam dwell point. If no valid signal is detected, the scanning step increment is adjusted to optimize the scanning efficiency; When the carrier-to-noise ratio of the beacon signal is detected to exceed the preset capture threshold, the instantaneous azimuth and elevation angles of the current beam pointing are extracted as coarse alignment references, and the corresponding signal strength distribution characteristics are recorded; Based on the coarse alignment reference, the beam mode is switched to a narrow beam, and a dynamically shrinking spiral scanning path is constructed within a preset range of the coarse alignment reference, while optimizing the convergence speed of the scanning path in combination with the signal intensity distribution characteristics; During the narrow beam scanning process, the slope changes of the beacon signals at adjacent beam dwell points are compared in real time. When the signal strength reaches a local peak and the slope approaches zero, it is determined to be the optimal direction and the beam is locked.

4. The application method of the airborne Tiantong phased array antenna according to claim 1, characterized in that: The beacon signal strength and bit error rate characteristics are extracted, combined with the inertial navigation attitude jitter compensation, and the phase weighting coefficient is dynamically adjusted to achieve pointing adjustment, so that the signal quality parameters continue to converge to the optimal threshold range. Specifically: The beacon signal output by the phased array antenna receiving channel is sampled in real time, the in-phase component and the orthogonal component are extracted through digital down-conversion, the instantaneous signal amplitude is calculated and smoothed to generate a normalized signal strength sequence; Synchronously analyze the bit error rate statistics output by the demodulator and use sliding window filtering to generate the bit error rate change gradient characteristics; Decomposing the attitude jitter compensation output by the inertial navigation system into angular jitter components of the pitch axis and the azimuth axis, and performing spatiotemporal matching with the signal strength sequence and the bit error rate gradient feature through time alignment processing; A three-dimensional feature space is constructed, containing the signal strength attenuation slope, the bit error rate gradient extreme point, and the angular jitter component. The beam pointing offset vector is dynamically calculated within this feature space. The modulus of the beam pointing offset vector is weighted by the bit error rate gradient extreme point, and its direction is determined by the vector synthesis of the signal strength attenuation slope and the angular jitter component. Dynamically adjusting a phase weighting coefficient of each array element in a phased array antenna beamforming network according to the beam pointing offset vector, wherein an adjustment step size of the phase weighting coefficient is inversely proportional to an absolute value of a signal strength attenuation slope, and an adjustment direction is consistent with a direction of the offset vector; The variance value and the peak value of the bit error rate statistics of the adjusted signal strength sequence are continuously monitored. When both are detected to fall into the preset stable range, the phase weighting coefficient freezing mechanism is triggered, and the beam pointing enters the steady-state tracking stage.

5. The application method of the airborne Tiantong phased array antenna according to claim 1, characterized in that: During the fine tracking phase, aircraft maneuver acceleration feedback is introduced to dynamically compensate for beam pointing deviation based on a pre-built interference signature library and suppress signal fluctuations caused by multipath effects. Specifically: The three-axis acceleration data output by the airborne inertial navigation system is collected in real time. The rate of change of maneuvering acceleration is extracted through differential processing to generate a feature vector containing the three-axis maneuvering overload values ​​of pitch, yaw, and roll. Input the feature vector into a pre-built interference feature library for similarity matching, extract the offset pattern that best matches the current maneuver feature through convolution kernel operation, and output the azimuth-pitch two-dimensional compensation basis vector; Based on the direction angle and modulus of the compensation base vector and the real-time beacon signal strength gradient change, a dynamic feedforward compensation is generated in the beam control loop; the amplitude of the feedforward compensation is weighted by the product of the maneuvering overload value and the signal strength attenuation slope, and the direction is consistent with the compensation base vector; Synchronously extract the polarization components of the beacon signal in a multipath interference environment, calculate the polarization correlation matrix between the left-hand circularly polarized wave and the reflected interference signal, and extract the main polarization coupling coefficient through eigenvalue decomposition; The polarization weighted network of the phased array antenna unit is dynamically reconstructed according to the main polarization coupling coefficient to generate a polarization matching weight vector for suppressing multipath reflection. The polarization matching weight vector is spatially synthesized with a dynamic feedforward compensation amount to generate a final beam pointing control instruction.

6. The application method of the airborne Tiantong phased array antenna according to claim 5, characterized in that: The interference feature library stores beam pointing offset patterns in typical maneuvering scenarios, where the typical maneuvering scenarios include dives and sharp turns.

7. The application method of the airborne Tiantong phased array antenna according to claim 1, characterized in that: Continuously check the data validity flag of the main inertial navigation system. When the failure threshold is triggered, seamlessly switch to the antenna built-in inertial navigation data stream and activate the fast recapture procedure to maintain zero interruption of the communication link. Specifically: Continuously monitor the data validity flag and the accompanying confidence factor output by the main inertial navigation system. When an abnormal flag is detected or the confidence factor is continuously lower than the preset failure threshold, the main inertial navigation system data stream is determined to be invalid. Based on the failure judgment result, the dominant fusion weight coefficients are immediately allocated to the second attitude data stream output by the antenna's built-in MEMS inertial navigation system, making it the only valid data source, while freezing the main inertial navigation data stream input; Using the second posture data stream, combined with a preset posture jitter suppression factor, low-pass filtering and data smoothing are performed to reconstruct an anti-jitter carrier posture matrix; The coarse alignment reference recorded during the pre-failure locking phase is used as the initial pointing center. The initial beam pointing angle for dynamic compensation is determined by combining the reconstructed carrier attitude matrix and the current satellite ephemeris. Based on this initial center, a fast spiral scan path is activated within the preset narrow beam range. During the rapid spiral scanning process, the carrier-to-noise ratio change gradient of the beacon signal is extracted in real time; when the carrier-to-noise ratio change gradient is detected to turn from positive to negative, it is determined that the signal strength has reached a local peak point, and the current beam pointing angle is immediately locked to complete rapid recapture; After beam locking, the signal strength sequence variance is continuously monitored to see if it falls within the preset stability range; If it falls within the range, the communication link is confirmed to be restored to the zero interruption state; if it does not fall within the range, the convergence step of the spiral scanning path is automatically fine-tuned based on the current carrier-to-noise ratio change gradient for secondary optimization.

8. An airborne Tiantong phased array antenna, applied to the method for applying the airborne Tiantong phased array antenna according to any one of claims 1 to 8, characterized in that: include: The phased array antenna surface consists of multiple antenna elements arranged in a two-dimensional rectangular grid. Each antenna element integrates an independent phase shifter and power amplifier, supports left-hand circular polarization beamforming, and covers an electronic scanning range of 30° to 90° in pitch and 360° in azimuth. The integrated navigation module has a built-in MEMS inertial navigation unit, which is interconnected with the airborne fiber-optic inertial navigation system data, supports dual-source attitude data fusion, and outputs a jitter-resistant carrier attitude matrix; The RF front-end module, which includes up- and down-converters, a low-noise amplifier, and a power splitter, down-converts the received 2170 to 2200 MHz signal to the L-band and outputs it to the multi-mode satellite receiver and satellite communication terminal. The antenna controller integrates a DSP+FPGA architecture to calculate satellite geometric azimuth in real time, control beam scanning mode switching, and dynamically optimize beam pointing based on beacon signal strength and bit error rate characteristics; The heat dissipation structure module uses a heat-conducting metal substrate and a micro fan to ensure that the temperature rise of the phased array transmitting unit is controllable under continuous high-power operation; Standardized interface, providing aviation connector for power input, service data, and Beidou positioning signals, meeting the electromagnetic compatibility requirements of airborne equipment.

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