Low-orbit satellite communication method and related equipment based on electric aircraft

Abstract

The present invention provides a low-orbit satellite communication method and related equipment based on an electric aircraft, wherein the electric aircraft is integrated with a satellite receiving device, and the low-orbit satellite communication method based on the electric aircraft comprises: during the operation of the electric aircraft, obtaining the current position and time of the electric aircraft, and performing satellite signal detection of the low-orbit satellite according to the current position and time; when a satellite signal is detected, locking the low-orbit satellite corresponding to the satellite signal, and adjusting the antenna beam direction of the satellite receiving device to achieve a stable satellite communication link; when a stable satellite communication link is achieved, performing low-orbit satellite communication operations based on the satellite communication link. The present invention can combine the flight characteristics of the electric aircraft to achieve flexible satellite communication link adjustment, provide stable satellite signal transmission for surrounding communication equipment, and improve communication coverage and reliability.

Description

Technical Field

[0001] The present invention relates to the field of satellite communications, and in particular to a low-orbit satellite communications method based on an electric aircraft and related equipment. Background Art

[0002] With the rapid development of low-orbit satellite communication networks, low-orbit satellite communication technology has gradually become a key means to solve the communication problem in areas where ground communication facilities cannot cover due to its advantages such as wide global coverage, low latency, and high transmission rate. The ability of low-orbit satellites to transmit data over a wide area provides great support for communications in the fields of aviation, aerospace, and ocean. However, in the field of electric aircraft, especially in application scenarios such as unmanned aerial vehicles and aerial logistics, traditional communication models face challenges.

[0003] The inventors discovered that because electric aircraft fly at high speeds in the air and their positions are constantly changing, traditional communication methods that rely on ground base stations often cannot provide stable and continuous communication guarantees. At certain flight altitudes and areas, the signal coverage of ground base stations is limited, making it difficult to ensure communication quality. At the same time, due to the dynamic environment of the aircraft, the aircraft itself becomes an ideal mobile relay receiving device, which can receive signals from low-orbit satellites through integrated satellite receiving equipment and provide relay services to other surrounding communication equipment, becoming a bridge for air communication networks. In the prior art, most of them rely on fixed satellite communication receiving systems and lack the ability to flexibly adjust the direction of the antenna beam to ensure a stable communication link. In particular, due to the operating characteristics of electric aircraft, it is impossible to dynamically adjust the satellite communication link, resulting in communication interruption or signal instability. Summary of the invention

[0004] The main purpose of the present invention is to solve the technical problem that the existing satellite communication reception lacks the ability to flexibly adjust the antenna beam direction to ensure a stable communication link;

[0005] A first aspect of the present invention provides a low-orbit satellite communication method based on an electric aircraft, wherein the electric aircraft is integrated with a satellite receiving device, and the low-orbit satellite communication method based on the electric aircraft comprises:

[0006] During the operation of the electric aircraft, obtaining the current position and time of the electric aircraft, and performing satellite signal detection of a low-orbit satellite according to the current position and time;

[0007] When a satellite signal is detected, the low-orbit satellite corresponding to the satellite signal is locked, and the antenna beam direction of the satellite receiving device is adjusted to achieve a stable satellite communication link;

[0008] When a stable satellite communication link is achieved, low-orbit satellite communication operations are performed based on the satellite communication link.

[0009] Optionally, in a first implementation of the first aspect of the present invention, during the operation of the electric aircraft, obtaining the current position and time of the electric aircraft, and performing satellite signal detection of a low-orbit satellite according to the current position and time includes:

[0010] During the operation of the electric aircraft, the current position and time of the electric aircraft are collected by a positioning system on the electric aircraft;

[0011] Performing interpolation calculation on pre-stored low-orbit satellite orbit parameters according to the current position and time to obtain a visible satellite list and the visible satellite list;

[0012] Based on the visible satellite list, beamforming processing is performed on the antenna array of the satellite receiving device to obtain multiple directional receiving beams, and satellite signals of low-orbit satellites are detected based on the directional receiving beams.

[0013] Optionally, in a second implementation of the first aspect of the present invention, when a satellite signal is detected, locking a low-orbit satellite corresponding to the satellite signal, and adjusting an antenna beam direction of the satellite receiving device to achieve a stable satellite communication link includes:

[0014] When a satellite signal is detected, the orbital parameters of the low-orbit satellite are solved and processed according to the current position and time of the electric aircraft to obtain the angle data of the electric aircraft relative to the low-orbit satellite;

[0015] Acquire attitude data of the electric aircraft, and determine a coarse beam direction of the satellite receiving device based on the angle data and the attitude data, and adjust the antenna beam direction of the satellite receiving device based on the coarse beam direction;

[0016] Determining the signal strength of the satellite signal received after the first adjustment, and determining the precise beam direction of the satellite receiving device based on the signal strength;

[0017] The antenna beam direction of the satellite receiving device is adjusted secondarily based on the precise beam direction, and the precise beam direction is dynamically tracked and adjusted to achieve a stable satellite communication link.

[0018] Optionally, in a third implementation manner of the first aspect of the present invention, the dynamically tracking and adjusting the precise beam direction to achieve a stable satellite communication link includes:

[0019] Acquiring operation control data in the electric aircraft and flight trajectory data of the electric aircraft;

[0020] Performing fusion analysis and processing on the attitude data, flight trajectory data and operation control data of the electric aircraft to obtain a prediction result of the short-term motion trend and operation intention of the electric aircraft;

[0021] Predicting a short-term beam offset of the precise beam direction according to the short-term motion trend, the operation intention prediction result and the orbital parameters of the low-orbit satellite;

[0022] The precise beam direction is dynamically tracked and adjusted according to the short-term beam offset to achieve a stable satellite communication link.

[0023] Optionally, in a fourth implementation of the first aspect of the present invention, the performing fusion analysis and processing on the attitude data, flight trajectory data, and operation control data of the electric aircraft to obtain a prediction result of the short-term motion trend and operation intention of the electric aircraft includes:

[0024] Performing multi-dimensional time series analysis on the attitude data of the electric aircraft to obtain an attitude change feature vector, and performing Kalman filtering on the motion state of the electric aircraft based on the attitude change feature vector and the flight trajectory data to obtain a smoothed motion state estimation result;

[0025] Performing neural network prediction processing on the short-term motion trend of the electric aircraft according to the motion state estimation result and historical flight data to obtain motion trend prediction results at multiple time scales;

[0026] Performing semantic segmentation and intention recognition processing on the operation control data to obtain a probability distribution of the operation intention;

[0027] Based on the motion trend prediction result and the probability distribution of the operation intention, a Monte Carlo simulation is performed on the future state of the electric aircraft to obtain the short-term motion trend and operation intention prediction results of the electric aircraft.

[0028] Optionally, in a fifth implementation manner of the first aspect of the present invention, when a stable satellite communication link is achieved, performing a low-orbit satellite communication operation based on the satellite communication link includes:

[0029] When a stable satellite communication link is achieved, encapsulating and performing uplink and downlink transmission processing on the self-use data packets of the electric aircraft according to a preset satellite communication protocol;

[0030] Demodulating and decoding the satellite uplink and downlink signals received by the satellite receiving device to obtain forwardable user data, and performing local network protocol conversion on the user data to obtain a data stream that complies with the WiFi transmission standard;

[0031] According to a preset data distribution strategy, the data stream is subjected to hotspot broadcast processing to complete data distribution to passengers in the electric aircraft or ground terminals, so as to realize low-orbit satellite communication operations.

[0032] Optionally, in a sixth implementation of the first aspect of the present invention, when a stable satellite communication link is achieved, after performing a low-orbit satellite communication operation based on the satellite communication link, the method further includes:

[0033] Performing real-time monitoring and processing on the data transmission rate and communication quality parameters of the satellite communication link to obtain dynamic transmission performance indicators;

[0034] Determining whether the dynamic transmission performance indicator meets a preset data transmission demand threshold, and when the dynamic transmission performance indicator does not meet the preset data transmission demand threshold, calculating the difference between the dynamic transmission performance indicator and the data transmission demand threshold;

[0035] Determine a speed adjustment requirement index corresponding to the difference, and generate a flight speed adjustment strategy based on the speed adjustment requirement index and a current flight state parameter of the electric aircraft, wherein the flight speed adjustment strategy includes a target speed range and a speed change curve of the electric aircraft;

[0036] The target speed range and the speed change curve are subjected to flight dynamics constraint analysis to obtain a speed adjustment instruction for the electric aircraft, and the speed of the electric aircraft is adjusted according to the speed adjustment instruction.

[0037] A second aspect of the present invention provides a low-orbit satellite communication device based on an electric aircraft, wherein the electric aircraft is integrated with a satellite receiving device, and the low-orbit satellite communication device based on the electric aircraft comprises:

[0038] A signal detection module, used to obtain the current position and time of the electric aircraft during the operation of the electric aircraft, and perform satellite signal detection of the low-orbit satellite according to the current position and time;

[0039] The antenna adjustment module is used to lock the low-orbit satellite corresponding to the satellite signal when a satellite signal is detected, and adjust the antenna beam direction of the satellite receiving device to achieve a stable satellite communication link;

[0040] The communication module is used to perform low-orbit satellite communication operations based on the satellite communication link when a stable satellite communication link is achieved.

[0041] A third aspect of the present invention provides a low-orbit satellite communication device based on an electric aircraft, comprising: a memory and at least one processor, wherein instructions are stored in the memory, and the memory and the at least one processor are interconnected via lines; the at least one processor calls the instructions in the memory so that the low-orbit satellite communication device based on the electric aircraft executes the steps of the above-mentioned low-orbit satellite communication method based on the electric aircraft.

[0042] A fourth aspect of the present invention provides a computer-readable storage medium, in which instructions are stored. When the computer-readable storage medium is run on a computer, the computer executes the steps of the above-mentioned low-orbit satellite communication method based on an electric aircraft.

[0043] The above-mentioned low-orbit satellite communication method and related equipment based on the electric aircraft, by obtaining the current position and time of the electric aircraft during the operation of the electric aircraft, and detecting the satellite signal of the low-orbit satellite according to the current position and time; when the satellite signal is detected, the low-orbit satellite corresponding to the satellite signal is locked, and the antenna beam direction of the satellite receiving device is adjusted to achieve a stable satellite communication link; when a stable satellite communication link is achieved, a low-orbit satellite communication operation is performed based on the satellite communication link. The present invention can combine the flight characteristics of the electric aircraft to achieve flexible satellite communication link adjustment, provide stable satellite signal transmission for surrounding communication equipment, and improve communication coverage and reliability.

[0044] Other features and advantages of the present invention will be described in the following description, and partly become apparent from the description, or understood by practicing the present invention. The purpose and other advantages of the present invention are realized and obtained by the structures particularly pointed out in the description, claims and drawings.

[0045] In order to make the above-mentioned objects, features and advantages of the present invention more obvious and easy to understand, preferred embodiments are given below and described in detail with reference to the accompanying drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0046] Figure 1 It is a schematic diagram of a first embodiment of a low-orbit satellite communication method based on an electric aircraft in an embodiment of the present invention;

[0047] Figure 2 A schematic diagram of an embodiment of a low-orbit satellite communication device based on an electric aircraft in an embodiment of the present invention;

[0048] Figure 3 It is a schematic diagram of an embodiment of a low-orbit satellite communication device based on an electric aircraft in an embodiment of the present invention. DETAILED DESCRIPTION

[0049] In order to make the purpose, technical solution and advantages of the embodiments of the present invention clearer, the technical solution of the present invention will be clearly and completely described below in conjunction with the accompanying drawings. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0050] The terms "including" and "having" and any variations thereof mentioned in the embodiments of the present invention are intended to cover non-exclusive inclusions. For example, a process, method, system, product or device end including a series of steps or units is not limited to the listed steps or units, but may optionally include other steps or units that are not listed, or may optionally include other steps or units that are inherent to these processes, methods, products or device ends.

[0051] To facilitate understanding of this embodiment, a low-orbit satellite communication method based on an electric aircraft disclosed in an embodiment of the present invention is first introduced in detail, wherein the electric aircraft is integrated with a satellite receiving device. Figure 1 As shown, the method comprises the following steps:

[0052] 101. During the operation of the electric aircraft, the current position and time of the electric aircraft are obtained, and satellite signals of low-orbit satellites are detected according to the current position and time;

[0053] In one embodiment of the present invention, during the operation of the electric aircraft, obtaining the current position and time of the electric aircraft, and performing satellite signal detection of low-orbit satellites based on the current position and time includes: during the operation of the electric aircraft, collecting the current position and time of the electric aircraft through a positioning system on the electric aircraft; interpolating pre-stored low-orbit satellite orbital parameters according to the current position and time to obtain a visible satellite list and the visible satellite list; performing beamforming processing on the antenna array of a satellite receiving device based on the visible satellite list to obtain multiple directional receiving beams, and performing satellite signal detection of low-orbit satellites based on the directional receiving beams.

[0054] Specifically, electric aircraft include but are not limited to drones, eVTOL (electric vertical take-off and landing aircraft), electric helicopters, electric fixed-wing aircraft and other types of electric-powered aircraft. During the operation of these electric aircraft, the current position and time data are first collected through the onboard positioning system. The onboard positioning system adopts multi-source fusion positioning technology and integrates GNSS receivers, inertial measurement units (IMUs) and barometric altimeters. The GNSS receiver receives signals from multiple satellite navigation systems such as GPS, Beidou, and Galileo to obtain the initial position coordinates; the inertial measurement unit measures the acceleration and angular velocity of the aircraft through accelerometers and gyroscopes, and performs integral operations to obtain the position change; the barometric altimeter provides accurate altitude data. The positioning system fuses these data through the extended Kalman filter algorithm to eliminate the errors of each sensor, while obtaining a unified time reference, and finally outputs high-precision position coordinates and standard time information.

[0055] Specifically, after obtaining accurate position and time data, the system immediately interpolates the pre-stored low-orbit satellite orbital parameters. The orbital parameter database stores the two-row orbital elements (TLE) of the low-orbit satellite constellation, including key parameters such as the satellite's orbital inclination, ascending node right ascension, eccentricity, etc. The system uses SGP4 (Simplified Perturbation Model) for orbit calculations. First, the TLE data is converted into the satellite's position and velocity vectors, and then the spherical trigonometry is used to calculate the azimuth and pitch angles of the satellite relative to the current position of the electric aircraft. The system also takes into account perturbation factors such as the earth's rotation and atmospheric drag, and uses the Chebyshev polynomial interpolation method to calculate the precise positions of all low-orbit satellites that may appear in the field of view at the current moment, and then generates a list of visible satellites containing satellite numbers, predicted azimuths, pitch angles, and visible durations.

[0056] Specifically, based on the generated visible satellite list, the system controls the phased array antenna to perform beamforming processing. The phased array antenna is composed of multiple radiating units, each of which is equipped with an independent phase shifter and attenuator. By adjusting the phase and amplitude of each radiating unit, the system uses an adaptive beamforming algorithm to construct multiple directional beams. Specifically, the system first calculates the phase difference required for each antenna unit based on the azimuth and elevation information in the visible satellite list, and then controls the phase shifter of each unit through the digital beamforming network (DBF), while optimizing the excitation amplitude distribution of each unit, and finally forms multiple high-gain directional receiving beams in the predicted direction of the visible satellite. The beamforming algorithm adopts the minimum variance distortionless response (MVDR) criterion to automatically suppress the side lobes in the interference direction while ensuring the pointing accuracy of the main beam.

[0057] Specifically, after beamforming is completed, the system simultaneously detects satellite signals through the formed multiple directional receiving beams. The detection process adopts a parallel signal processing architecture, and each beam channel is equipped with an independent RF front end and signal processing unit. The RF front end performs low-noise amplification and down-conversion processing on the received signal, and converts the RF signal to an intermediate frequency or baseband. The signal processing unit digitally samples the pre-processed signal, performs spectrum analysis through fast Fourier transform, and uses a matched filter algorithm to detect the characteristic sequence of the satellite signal. The system performs a threshold judgment on the detection results to determine whether there are valid satellite signals in each beam direction, and outputs parameters such as signal strength, carrier frequency, and bandwidth to provide necessary information support for subsequent satellite tracking and communication link establishment.

[0058] 102. When a satellite signal is detected, lock onto the low-orbit satellite corresponding to the satellite signal and adjust the antenna beam direction of the satellite receiving device to achieve a stable satellite communication link;

[0059] In one embodiment of the present invention, when a satellite signal is detected, the low-orbit satellite corresponding to the satellite signal is locked, and the antenna beam direction of the satellite receiving device is adjusted to achieve a stable satellite communication link, including: when a satellite signal is detected, the orbital parameters of the low-orbit satellite are solved and processed according to the current position and time of the electric aircraft to obtain the angle data of the electric aircraft relative to the low-orbit satellite; the attitude data of the electric aircraft is obtained, and based on the angle data and the attitude data, the coarse adjustment beam direction of the satellite receiving device is determined, and the antenna beam direction of the satellite receiving device is adjusted once based on the coarse adjustment beam direction; the signal strength of the satellite signal received after the first adjustment is determined, and the precise beam direction of the satellite receiving device is determined according to the signal strength; the antenna beam direction of the satellite receiving device is adjusted for a second time based on the precise beam direction, and the precise beam direction is dynamically tracked and adjusted to achieve a stable satellite communication link.

[0060] Specifically, when the electric aircraft detects a satellite signal, the system immediately starts orbit solution processing for the low-orbit satellite. The solution process first retrieves the orbital elements of the target satellite from the database, including orbital inclination, perigee angular distance, ascending node right ascension and other parameters. The system uses the improved SGP4 orbit propagation model for calculation, which takes into account the influence of perturbations such as the earth's non-spherical gravitational field, atmospheric drag, and solar gravity. During orbital propagation, the system substitutes the orbital elements into the Kepler orbit equation, obtains the position vector of the satellite in the geocentric inertial coordinate system through iterative calculation, and then converts it to the geocentric earth-fixed coordinate system through the coordinate transformation matrix. Based on the current position coordinates and world time of the electric aircraft, the system uses spherical trigonometry to calculate the azimuth and pitch angles of the electric aircraft relative to the low-orbit satellite. These two angles together constitute the relative angle data between the electric aircraft and the satellite.

[0061] Specifically, after obtaining the relative angle data, the system starts the coarse adjustment process of the antenna beam. First, the attitude data of the electric aircraft, including pitch angle, roll angle and yaw angle, is obtained through the airborne inertial measurement unit. The inertial measurement unit uses high-precision fiber optic gyroscopes and accelerometers to achieve high-frequency attitude solution through quaternion algorithms. The system converts and fuses the attitude data of the electric aircraft with the previously calculated satellite relative angle data to obtain the target pointing angle in the antenna coordinate system. Based on this target pointing angle, the system calculates the initial phase difference of each radiating unit of the phased array antenna, and controls the phase shifter of each unit through the digital beamforming network to complete a coarse adjustment of the antenna beam direction. The coarse adjustment process uses the classic phase weighted algorithm, and the main goal is to quickly form a main beam pointing to the target satellite within a larger spatial range.

[0062] Specifically, after completing a coarse adjustment, the system measures the received signal through a dedicated signal strength detection circuit. The measurement circuit includes a low-noise amplifier, a bandpass filter, and a logarithmic detector, which can accurately measure the signal power in different frequency bands. The system performs spectrum analysis and energy statistics on the measured signal strength, while considering the influence of the noise floor and interference signals, and calculates the signal-to-noise ratio and signal quality indicators. Based on these measurement data, the system uses a gradient search algorithm to accurately search the beam direction within a small range in the coarse adjustment direction to find the precise direction with the maximum signal strength. During the search process, the system also monitors the stability and continuity of the signal to ensure that the precise beam direction found has good communication performance.

[0063] Specifically, after determining the precise beam direction, the system starts the secondary adjustment and dynamic tracking mechanism. The secondary adjustment uses an adaptive beamforming algorithm to optimize the amplitude and phase weights of each antenna unit, while ensuring the accuracy of the main beam pointing, and automatically generates nulls to suppress clutter in the interference direction. The system generates the optimal weight vector based on the precise beam direction and controls the antenna array in real time through a digital beamforming processor. At the same time, the system establishes a dynamic tracking model based on Kalman filtering, which combines satellite orbit prediction and real-time signal measurement data to predict the satellite's motion trajectory and compensate for Doppler frequency deviation in real time. The system continuously monitors the signal quality through a feedback control loop. When the performance of the communication link fluctuates, the automatic fine-tuning mechanism is triggered to correct the beam direction in real time, thereby maintaining a stable satellite communication link.

[0064] Furthermore, the dynamic tracking and adjustment of the precise beam direction to achieve a stable satellite communication link includes: acquiring the operation control data in the electric aircraft and the flight trajectory data of the electric aircraft; performing fusion analysis and processing on the attitude data, flight trajectory data and operation control data of the electric aircraft to obtain the short-term motion trend and operation intention prediction results of the electric aircraft; predicting the short-term beam offset of the precise beam direction based on the short-term motion trend, the operation intention prediction results and the orbital parameters of the low-orbit satellite; and dynamically tracking and adjusting the precise beam direction based on the short-term beam offset to achieve a stable satellite communication link.

[0065] Specifically, the operation data acquisition of electric aircraft is realized through a multi-layer perception architecture. The system collects the pilot's control input data in real time through the flight control bus, including thrust control amount , pitch control amount , Roll control amount and yaw control At the same time, the system obtains flight trajectory data from the navigation block, which includes the three-dimensional spatial position coordinates , velocity vector and the acceleration vector The data is transmitted to the central processing unit via a high-speed data bus with a sampling frequency of 200Hz to ensure that the system can capture the rapid changes in the motion state of the electric aircraft. The system pre-processes the collected raw data, including digital filtering and denoising, outlier detection and data synchronization, and finally obtains a standardized control input vector and the motion state vector s In the multi-source data fusion analysis, the system uses a multi-modal data fusion algorithm enhanced by deep learning. First, the system describes the motion state of the electric aircraft by constructing the dynamic state equation:

[0066] ;

[0067] in, is the extended state vector, which includes position, velocity, acceleration and attitude angle; is the time-varying system matrix, is the control input matrix, is process noise. The system uses a recurrent neural network (RNN) to establish a nonlinear mapping model, which is specifically expressed as:

[0068] ;

[0069] ;

[0070] in, is the hidden state, is the weight matrix, is the bias vector. Through this model, the system can predict the movement trend of the aircraft. At the same time, the attention mechanism is introduced to analyze the pilot's operation intention. The calculation formula of the attention weight vector is:

[0071] ;

[0072] in, is the attention weight vector, is the transformation matrix, is the parameter vector. Based on the fusion analysis results, the system constructs a beam deviation prediction model. First, the predicted motion trend vector and operation intention vector Orbital parameters of low-orbit satellites Combined, construct the state prediction equation:

[0073] ;

[0074] in, is the beam pointing angle, They are the mapping matrices of motion trend, operation intention and orbit parameters respectively. is the prediction error. In order to optimize the prediction results, the system adopts the adaptive Kalman filter algorithm, and its prediction and update equations are as follows:

[0075] ;

[0076] ;

[0077] ;

[0078] in, is the forecast error covariance matrix, is the Kalman gain matrix, is the observation matrix. Finally, the system performs dynamic tracking adjustment according to the predicted beam offset. The nonlinear model predictive control (NMPC) strategy is used in the adjustment process, and the optimization objective function is constructed as:

[0079] ;

[0080] in, is the desired beam direction, is the weight coefficient. By solving this optimization problem, the system obtains the control sequence:

[0081] ;

[0082] The system converts the optimal control sequence into the phase adjustment of the antenna array:

[0083] ;

[0084] in, is the array element spacing, is the working wavelength, is the phase compensation amount. Phase adjustment is performed through the digital beamforming network, and the system completes dynamic tracking of the beam direction.

[0085] Furthermore, the fusion analysis and processing of the attitude data, flight trajectory data and operation control data of the electric aircraft to obtain the short-term motion trend and operation intention prediction results of the electric aircraft includes: performing multi-dimensional time series analysis and processing on the attitude data of the electric aircraft to obtain the attitude change feature vector, and performing Kalman filtering on the motion state of the electric aircraft based on the attitude change feature vector and the flight trajectory data to obtain a smoothed motion state estimation result; performing neural network prediction processing on the short-term motion trend of the electric aircraft according to the motion state estimation result and historical flight data to obtain multi-time scale motion trend prediction results; performing semantic segmentation and intention recognition processing on the operation control data to obtain the probability distribution of the operation intention; based on the motion trend prediction result and the probability distribution of the operation intention, performing Monte Carlo simulation on the future state of the electric aircraft to obtain the short-term motion trend and operation intention prediction results of the electric aircraft.

[0086] Specifically, the attitude data, flight trajectory data and operation control data of the electric aircraft are fused and analyzed to obtain the short-term motion trend and operation intention prediction results of the electric aircraft. This can also be achieved through the following steps. When performing multi-dimensional time series analysis on the attitude data of the electric aircraft, the system collects the quaternion attitude data of the aircraft through the attitude sensor, including pitch angle, roll angle and yaw angle information. The attitude data collection adopts a high-precision fiber optic gyroscope and accelerometer combination system with a sampling frequency of 200Hz to ensure that high-frequency attitude changes are captured. The system performs time-frequency domain analysis on the collected attitude data through wavelet transform to extract multi-scale features. The mathematical representation of wavelet transform is:

[0087] ;

[0088] in, is the scale factor, is the translation factor, is a quaternion sequence. Through wavelet transform, the system extracts energy features, entropy features and kurtosis features from the transformation results to construct the feature vector of attitude change. These feature vectors are then combined with the flight trajectory data and the Unscented Kalman Filter (UKF) algorithm is used for state estimation. The state equation of the filter is:

[0089] ;

[0090] in, is the sigma point, is the control input, is the process noise. Through this method, the system obtains a smoothed motion state estimation result, which provides basic data support for subsequent trend prediction.

[0091] Based on these smoothed motion state estimation results, the system uses a bidirectional long short-term memory network (Bi-LSTM) to predict the short-term motion trend of electric aircraft. The system first divides the historical data into time windows, each of which contains 100 consecutive state samples. For the data in each time window, the system uses a Bi-LSTM network to extract features and model sequences. The calculation of the LSTM unit is implemented through a gating mechanism, including a forget gate, an input gate, and an output gate. The system uses a sliding prediction window method to predict the state of multiple future time points, with a prediction time span ranging from 100ms to 5s to form multi-time scale prediction results. At the same time, the system trains a deep neural network through historical flight data to establish a state transition model, thereby further improving the prediction accuracy. The prediction results contain complete motion state information such as position, velocity, acceleration, and attitude angle. For the processing of operation control data, the system uses a special intention recognition module for analysis. First, the original operation control data is semantically segmented to divide the continuous control operation sequence into operation segments with clear operation intentions. The segmentation process uses a temporal convolutional network (TCN) to model long-term dependencies through multiple layers of causal convolution. The output of the convolutional layer is calculated by the following formula:

[0092] ;

[0093] in, The expansion rate ensures that the receptive field grows exponentially with the number of layers. For the segmented operation fragments, the system uses an attention-based intent recognizer to classify and calculate the probability distribution of different operation intentions. The attention weight is calculated using the following formula:

[0094] ;

[0095] in, is the attention score. Through this method, the system obtains a probability distribution containing multiple possible operation patterns, reflecting the uncertainty of operation control. After obtaining the motion trend prediction results and the probability distribution of operation intentions, the system uses the Monte Carlo method to simulate and predict future states. The simulation process first generates a large number of sample particles based on the current state, and each particle represents a possible future state. For each particle, the system evolves the state according to the motion model and the probability distribution of operation intentions, and the state transition probability is modeled by the following formula:

[0096] ;

[0097] The system assigns weights to all particles

[0098] ;

[0099] in, The particle filter is based on the observation data. The importance resampling is used to maintain the diversity of particles. Finally, the system obtains a comprehensive prediction result through weighted averaging, which contains the prediction information of short-term movement trend and operation intention. This prediction method based on particle filtering can effectively handle the nonlinear characteristics and uncertainty of the system and provide more reliable prediction results.

[0100] 103. When a stable satellite communication link is achieved, low-orbit satellite communication operations are carried out based on the satellite communication link.

[0101] In one embodiment of the present invention, when a stable satellite communication link is achieved, performing low-orbit satellite communication operations based on the satellite communication link includes: when a stable satellite communication link is achieved, encapsulating and processing uplink and downlink transmission of the electric aircraft's own data packets according to a preset satellite communication protocol; demodulating and decoding the satellite uplink and downlink signals received by the satellite receiving device to obtain forwardable user data, and performing local network protocol conversion on the user data to obtain a data stream that meets the WiFi transmission standard; and performing hotspot broadcasting on the data stream according to a preset data distribution strategy to complete data distribution to passengers in the electric aircraft or ground terminals to achieve low-orbit satellite communication operations.

[0102] Specifically, after establishing a stable satellite communication link, the system first starts to process the self-use data of the electric aircraft. The self-use data of the electric aircraft mainly includes three categories: flight status data (including attitude parameters, motion parameters, positioning data), system operating data (including power system status, control system status, communication system status) and load data (including aerial images, environmental monitoring data). The data processing module first classifies and marks these raw data, assigns priority identifiers to different types of data, among which flight status data has the highest priority. Subsequently, the data is grouped and encapsulated according to the preset satellite communication protocol, and each data packet contains three parts: synchronization header, data area and check area. The synchronization header is used for frame synchronization and packet identification, the data area adopts a segmented storage structure, and the check area contains a CRC check code. The system uses a combination of differential coding and interleaved coding for channel coding, and transmits uplink through the satellite channel. On the downlink, the system receives control instructions and broadcast data from the satellite, and uses the same protocol structure for parsing and processing.

[0103] Specifically, when the satellite receiving device receives the uplink and downlink signals, the signals are first pre-amplified by a low-noise amplifier, and then the out-of-band noise is suppressed by a bandpass filter. The filtered signal is sent to the digital down-conversion module to convert the RF signal into a digital baseband signal. The baseband signal is demodulated by a digital signal processor, and the demodulation process includes three key steps: carrier synchronization, symbol timing recovery, and phase correction. The demodulated data stream enters the decoding module, and the system uses the Viterbi algorithm for forward error correction decoding to restore the original data bit stream. The decoded data is processed by the protocol parsing module to extract the payload data. For user data that needs to be forwarded, the system converts it from the satellite communication protocol format to the standard TCP / IP protocol format to construct a data packet that meets the WiFi transmission standard. The protocol conversion process involves data frame reorganization, address remapping, and flow parameter adjustment to ensure that data can be transmitted normally in the local network.

[0104] Specifically, in the data distribution phase, the system processes and distributes the converted data stream according to the pre-configured distribution strategy. First, a WiFi hotspot is established, configured as the 802.11ac standard, and supports 2.4GHz and 5GHz dual-band working modes. The hotspot adopts the WPA3 encryption standard and provides secure access services through pre-shared keys. The system establishes a data distribution priority queue, and different types of data are assigned to queues of different priorities according to their service quality requirements. For passengers on electric aircraft, the system provides onboard WiFi services, supporting high-speed Internet access and onboard entertainment services. For ground terminal users, the system provides mobile hotspot coverage during the flight of electric aircraft to achieve air-to-ground distribution of data. The system maintains a stable network connection through dynamic power control and adaptive rate adjustment, while implementing bandwidth management and flow control to ensure the transmission quality of critical business data. The distribution system also includes a data caching mechanism to locally cache frequently accessed content and reduce the bandwidth occupancy of satellite links.

[0105] Furthermore, when a stable satellite communication link is achieved, after performing low-orbit satellite communication operations based on the satellite communication link, it also includes: real-time monitoring and processing of the data transmission rate and communication quality parameters of the satellite communication link to obtain a dynamic transmission performance indicator; judging whether the dynamic transmission performance indicator meets a preset data transmission demand threshold, and when the dynamic transmission performance indicator does not meet the preset data transmission demand threshold, calculating the difference between the dynamic transmission performance indicator and the data transmission demand threshold; determining a speed adjustment demand index corresponding to the difference, and generating a flight speed adjustment strategy based on the speed adjustment demand index and the current flight state parameters of the electric aircraft, wherein the flight speed adjustment strategy includes a target speed range and a speed change curve of the electric aircraft; performing flight dynamics constraint analysis on the target speed range and the speed change curve to obtain a speed adjustment instruction of the electric aircraft, and adjusting the speed of the electric aircraft according to the speed adjustment instruction.

[0106] Specifically, the system monitors the satellite communication link in real time through a dedicated performance monitoring module. The monitoring content includes key parameters such as data transmission rate, channel quality, bit error rate and link delay. The transmission rate monitoring adopts a sliding window mechanism to calculate the data throughput in real time. The calculation formula is:

[0107] ;

[0108] in, Indicates the amount of data transmitted within the window period, is the duration of the window. For monitoring of communication quality parameters, the system covers indicators such as signal-to-noise ratio (SNR), bit error rate (BER) and link availability. The system calculates dynamic transmission performance indicators through a weighted comprehensive evaluation method, and the calculation formula is:

[0109] ;

[0110] in, is the weight coefficient, is the peak transmission rate, The monitoring module updates the performance evaluation results every 100ms and stores the evaluation data in the performance log database. The system compares the calculated dynamic transmission performance index with the preset data transmission demand threshold to determine whether the current communication performance meets the demand.

[0111] When the system finds that the performance indicator is lower than the threshold, it calculates the performance difference:

[0112] ;

[0113] in, is the preset performance requirement threshold. Based on this difference, the system uses a fuzzy logic controller to calculate the speed adjustment requirement index. The input of the fuzzy controller is the performance difference and the rate of change, and the output is the speed adjustment intensity. The fuzzy rules are defined by the expert knowledge base, and the Mamdani reasoning mechanism is used for decision making. The speed adjustment requirement index is defuzzified and the result is standardized to the [0,1] interval.

[0114] In addition, the system combines the current state parameters of the electric aircraft, including flight altitude, attitude, remaining power, etc. to build speed adjustment constraints. Based on the calculated speed adjustment demand index, the system generates a specific flight speed adjustment strategy. The target speed range is determined based on performance requirements and flight constraints, expressed as:

[0115] ;

[0116] The upper speed limit The following conditions are met:

[0117] ;

[0118] in, Due to power system limitations, Due to structural strength limitations, The velocity change curve is described by a cubic spline function to ensure the smoothness of the velocity change. When the velocity change curve is generated, the constraints of acceleration and jerk are considered, and the optimal velocity trajectory is calculated by minimizing the energy consumption. The mathematical expression of the optimization problem is:

[0119] ;

[0120] in, and is the weight coefficient, and They are speed and acceleration functions, respectively. After determining the target speed range and speed change curve, the system performs flight dynamics constraint analysis. First, a six-degree-of-freedom dynamic model of the electric aircraft is established, including the center of mass motion equation and attitude motion equation. The system calculates the aerodynamic force, thrust, and gravity involved in the speed adjustment process and evaluates the feasibility of the adjustment strategy. The constraint analysis takes into account multiple factors such as engine performance, battery energy, and structural loads, and verifies the safety of the speed adjustment process through numerical simulation. Based on the analysis results, the system generates specific speed adjustment instructions, including thrust adjustment instructions and attitude adjustment instructions. After receiving these instructions, the control system implements speed adjustment through a distributed actuator network, ensures that the stability of the flight attitude is maintained during the adjustment process, and completes the entire speed adjustment process.

[0121] In this embodiment, during the operation of the electric aircraft, the current position and time of the electric aircraft are obtained, and satellite signal detection of the low-orbit satellite is performed according to the current position and time; when the satellite signal is detected, the low-orbit satellite corresponding to the satellite signal is locked, and the antenna beam direction of the satellite receiving device is adjusted to achieve a stable satellite communication link; when a stable satellite communication link is achieved, a low-orbit satellite communication operation is performed based on the satellite communication link. The present invention can combine the flight characteristics of the electric aircraft to achieve flexible satellite communication link adjustment, provide stable satellite signal transmission for surrounding communication equipment, and improve communication coverage and reliability.

[0122] The above describes the low-orbit satellite communication method based on the electric aircraft in the embodiment of the present invention. The following describes the low-orbit satellite communication device based on the electric aircraft in the embodiment of the present invention. The electric aircraft is integrated with a satellite receiving device. Figure 2 In one embodiment of the present invention, a low-orbit satellite communication device based on an electric aircraft includes:

[0123] The signal detection module 201 is used to obtain the current position and time of the electric aircraft during the operation of the electric aircraft, and perform satellite signal detection of the low-orbit satellite according to the current position and time;

[0124] The antenna adjustment module 202 is used to lock the low-orbit satellite corresponding to the satellite signal when a satellite signal is detected, and adjust the antenna beam direction of the satellite receiving device to achieve a stable satellite communication link;

[0125] The communication module 203 is used to perform low-orbit satellite communication operations based on the satellite communication link when a stable satellite communication link is achieved.

[0126] In an embodiment of the present invention, the low-orbit satellite communication device based on an electric aircraft runs the above-mentioned low-orbit satellite communication method based on an electric aircraft, and the low-orbit satellite communication device based on an electric aircraft obtains the current position and time of the electric aircraft during the operation of the electric aircraft, and performs satellite signal detection of the low-orbit satellite according to the current position and time; when a satellite signal is detected, the low-orbit satellite corresponding to the satellite signal is locked, and the antenna beam direction of the satellite receiving device is adjusted to achieve a stable satellite communication link; when a stable satellite communication link is achieved, a low-orbit satellite communication operation is performed based on the satellite communication link. The present invention can combine the flight characteristics of the electric aircraft to achieve flexible satellite communication link adjustment, provide stable satellite signal transmission for surrounding communication equipment, and improve communication coverage and reliability.

[0127] above Figure 2The low-orbit satellite communication device based on an electric aircraft in an embodiment of the present invention is described in detail from the perspective of modular functional entities. The low-orbit satellite communication device based on an electric aircraft in an embodiment of the present invention is described in detail from the perspective of hardware processing.

[0128] Figure 3 3 is a schematic diagram of the structure of a low-orbit satellite communication device based on an electric aircraft provided by an embodiment of the present invention. The low-orbit satellite communication device 300 based on an electric aircraft may have relatively large differences due to different configurations or performances, and may include one or more processors (central processing units, CPU) 310 (for example, one or more processors) and a memory 320, and one or more storage media 330 (for example, one or more mass storage device terminals) storing application programs 333 or data 332. Among them, the memory 320 and the storage medium 330 can be short-term storage or permanent storage. The program stored in the storage medium 330 may include one or more modules (not shown in the figure), and each module may include a series of instruction operations in the low-orbit satellite communication device 300 based on the electric aircraft. Furthermore, the processor 310 may be configured to communicate with the storage medium 330, and execute a series of instruction operations in the storage medium 330 on the low-orbit satellite communication device 300 based on the electric aircraft to implement the steps of the above-mentioned low-orbit satellite communication method based on the electric aircraft.

[0129] The low-orbit satellite communication device 300 based on the electric aircraft may also include one or more power supplies 340, one or more wired or wireless network interfaces 350, one or more input and output interfaces 360, and / or one or more operating systems 331, such as Windows Serve, Mac OS X, Unix, Linux, FreeBSD, etc. It will be appreciated by those skilled in the art that Figure 3 The illustrated structure of the low-orbit satellite communication device based on an electric aircraft does not constitute a limitation on the low-orbit satellite communication device based on an electric aircraft provided by the present invention, and may include more or fewer components than illustrated, or a combination of certain components, or a different arrangement of components.

[0130] The present invention also provides a computer-readable storage medium, which may be a non-volatile computer-readable storage medium or a volatile computer-readable storage medium. Instructions are stored in the computer-readable storage medium. When the instructions are executed on a computer, the computer executes the steps of the low-orbit satellite communication method based on an electric aircraft.

[0131] Those skilled in the art can clearly understand that, for the convenience and brevity of description, the specific working process of the above-described system, device, or unit can refer to the corresponding process in the aforementioned method embodiment and will not be repeated here.

[0132] If the integrated unit is implemented in the form of a software functional unit and sold or used as an independent product, it can be stored in a computer-readable storage medium. Based on this understanding, the technical solution of the present invention is essentially or the part that contributes to the prior art or the whole or part of the technical solution can be embodied in the form of a software product. The computer software product is stored in a storage medium, including several instructions to enable a computer device (which can be a personal computer, server, or network device, etc.) to perform all or part of the steps of the method described in each embodiment of the present invention. The aforementioned storage medium includes: U disk, mobile hard disk, read-only memory (ROM), random access memory (RAM), disk or optical disk and other media that can store program code.

[0133] As described above, the above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit the same. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that the technical solutions described in the aforementioned embodiments may still be modified, or some of the technical features thereof may be replaced by equivalents. However, these modifications or replacements do not deviate the essence of the corresponding technical solutions from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. A low-orbit satellite communication method based on an electric aircraft, characterized in that: The electric aircraft is integrated with a satellite receiving device, and the low-orbit satellite communication method based on the electric aircraft includes: During the operation of the electric aircraft, obtaining the current position and time of the electric aircraft, and performing satellite signal detection of a low-orbit satellite according to the current position and time; When a satellite signal is detected, the low-orbit satellite corresponding to the satellite signal is locked, and the antenna beam direction of the satellite receiving device is adjusted to achieve a stable satellite communication link; when a satellite signal is detected, the low-orbit satellite corresponding to the satellite signal is locked, and the antenna beam direction of the satellite receiving device is adjusted to achieve a stable satellite communication link, including: when a satellite signal is detected, the orbital parameters of the low-orbit satellite are solved according to the current position and time of the electric aircraft to obtain the angle data of the electric aircraft relative to the low-orbit satellite; the attitude data of the electric aircraft is obtained, and the coarse adjustment beam direction of the satellite receiving device is determined based on the angle data and the attitude data, and the antenna beam direction of the satellite receiving device is adjusted once based on the coarse adjustment beam direction; the signal strength of the satellite signal received after one adjustment is determined, and the satellite receiving device is determined according to the signal strength. The precise beam direction of the device; based on the precise beam direction, the antenna beam direction of the satellite receiving device is adjusted secondary, and the precise beam direction is dynamically tracked and adjusted to achieve a stable satellite communication link; wherein, the dynamic tracking and adjustment of the precise beam direction to achieve a stable satellite communication link includes: acquiring the operation control data in the electric aircraft and the flight trajectory data of the electric aircraft; fusing and analyzing the attitude data, flight trajectory data and operation control data of the electric aircraft to obtain the short-term motion trend and operation intention prediction results of the electric aircraft; predicting the short-term beam offset of the precise beam direction according to the short-term motion trend, the operation intention prediction results and the orbital parameters of the low-orbit satellite; dynamically tracking and adjusting the precise beam direction according to the short-term beam offset to achieve a stable satellite communication link; When a stable satellite communication link is achieved, low-orbit satellite communication operations are performed based on the satellite communication link; the data transmission rate and communication quality parameters of the satellite communication link are monitored and processed in real time to obtain a dynamic transmission performance indicator; it is determined whether the dynamic transmission performance indicator meets a preset data transmission demand threshold, and when the dynamic transmission performance indicator does not meet the preset data transmission demand threshold, the difference between the dynamic transmission performance indicator and the data transmission demand threshold is calculated; a speed adjustment demand index corresponding to the difference is determined, and a flight speed adjustment strategy is generated based on the speed adjustment demand index and the current flight state parameters of the electric aircraft, wherein the flight speed adjustment strategy includes a target speed range and a speed change curve of the electric aircraft; flight dynamics constraint analysis is performed on the target speed range and the speed change curve to obtain a speed adjustment instruction of the electric aircraft, and the speed of the electric aircraft is adjusted according to the speed adjustment instruction.

2. The low-orbit satellite communication method based on an electric aircraft according to claim 1, characterized in that: The acquiring of the current position and time of the electric aircraft during the operation of the electric aircraft, and performing satellite signal detection of a low-orbit satellite according to the current position and time comprises: During the operation of the electric aircraft, the current position and time of the electric aircraft are collected by a positioning system on the electric aircraft; Interpolating and calculating pre-stored low-orbit satellite orbit parameters according to the current position and time to obtain a visible satellite list; Based on the visible satellite list, beamforming processing is performed on the antenna array of the satellite receiving device to obtain multiple directional receiving beams, and satellite signals of low-orbit satellites are detected based on the directional receiving beams.

3. The low-orbit satellite communication method based on an electric aircraft according to claim 1, characterized in that: The fusion analysis and processing of the attitude data, flight trajectory data and operation control data of the electric aircraft to obtain the short-term motion trend and operation intention prediction results of the electric aircraft includes: Performing multi-dimensional time series analysis on the attitude data of the electric aircraft to obtain an attitude change feature vector, and performing Kalman filtering on the motion state of the electric aircraft based on the attitude change feature vector and the flight trajectory data to obtain a smoothed motion state estimation result; Performing neural network prediction processing on the short-term motion trend of the electric aircraft according to the motion state estimation result and historical flight data to obtain motion trend prediction results at multiple time scales; Performing semantic segmentation and intention recognition processing on the operation control data to obtain a probability distribution of the operation intention; Based on the motion trend prediction result and the probability distribution of the operation intention, a Monte Carlo simulation is performed on the future state of the electric aircraft to obtain the short-term motion trend and operation intention prediction results of the electric aircraft.

4. The low-orbit satellite communication method based on an electric aircraft according to claim 1, characterized in that: When a stable satellite communication link is achieved, performing a low-orbit satellite communication operation based on the satellite communication link includes: When a stable satellite communication link is achieved, encapsulating and performing uplink and downlink transmission processing on the self-use data packets of the electric aircraft according to a preset satellite communication protocol; Demodulating and decoding the satellite uplink and downlink signals received by the satellite receiving device to obtain forwardable user data, and performing local network protocol conversion on the user data to obtain a data stream that complies with the WiFi transmission standard; According to a preset data distribution strategy, the data stream is subjected to hotspot broadcast processing to complete data distribution to passengers in the electric aircraft or ground terminals, so as to realize low-orbit satellite communication operations.

5. A low-orbit satellite communication device based on an electric aircraft, characterized in that: The electric aircraft is integrated with a satellite receiving device, and the low-orbit satellite communication device based on the electric aircraft includes: A signal detection module, used to obtain the current position and time of the electric aircraft during the operation of the electric aircraft, and perform satellite signal detection of the low-orbit satellite according to the current position and time; An antenna adjustment module is used to, when a satellite signal is detected, lock the low-orbit satellite corresponding to the satellite signal, and adjust the antenna beam direction of the satellite receiving device to achieve a stable satellite communication link; the method of locking the low-orbit satellite corresponding to the satellite signal and adjusting the antenna beam direction of the satellite receiving device to achieve a stable satellite communication link includes: when a satellite signal is detected, solving the orbital parameters of the low-orbit satellite according to the current position and time of the electric aircraft to obtain the angle data of the electric aircraft relative to the low-orbit satellite; acquiring the attitude data of the electric aircraft, and determining the coarse adjustment beam direction of the satellite receiving device based on the angle data and the attitude data, and adjusting the antenna beam direction of the satellite receiving device based on the coarse adjustment beam direction; determining the signal strength of the satellite signal received after one adjustment, and determining the desired signal strength according to the signal strength. The precise beam direction of the satellite receiving device; based on the precise beam direction, the antenna beam direction of the satellite receiving device is adjusted for the second time, and the precise beam direction is dynamically tracked and adjusted to achieve a stable satellite communication link; wherein, the dynamic tracking and adjustment of the precise beam direction to achieve a stable satellite communication link includes: acquiring the operation control data in the electric aircraft and the flight trajectory data of the electric aircraft; fusing and analyzing the attitude data, flight trajectory data and operation control data of the electric aircraft to obtain the short-term motion trend and operation intention prediction results of the electric aircraft; predicting the short-term beam offset of the precise beam direction according to the short-term motion trend, the operation intention prediction results and the orbital parameters of the low-orbit satellite; dynamically tracking and adjusting the precise beam direction according to the short-term beam offset to achieve a stable satellite communication link; The communication module is used to perform low-orbit satellite communication operations based on the satellite communication link when a stable satellite communication link is achieved.

6. A low-orbit satellite communication device based on an electric aircraft, characterized in that: The low-orbit satellite communication device based on an electric aircraft comprises: a memory and at least one processor, wherein instructions are stored in the memory; The at least one processor calls the instructions in the memory to enable the low-orbit satellite communication device based on the electric aircraft to perform the steps of the low-orbit satellite communication method based on the electric aircraft as described in any one of claims 1-4.

7. A computer-readable storage medium having instructions stored thereon, characterized in that: When the instructions are executed by the processor, the steps of the low-orbit satellite communication method based on the electric aircraft as described in any one of claims 1 to 4 are implemented.

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