43 results about "Flight (process)" patented technology

The invention discloses a heavy landing prediction method based on deep learning, which is used for solving the problem of predicting whether a heavy landing risk occurs in an aircraft or not according to parameters of the flight stage of the aircraft. The method mainly comprises a construction method of an autoregressive landing model based on deep learning and a method for heavy landing detection by adopting the autoregressive landing model, wherein the method comprises the steps of: (1) an autoregressive landing model which is a model trained based on a deep learning model by using a largeamount of sample data of a normal landing flight and used for capturing an airplane landing state conversion mode, and (2) a calculation method: flight process data, such as data acquired from a QuickAccess Recorder (QAR), is taken as input, and an aircraft landing multivariate time sequence is converted into a symbolic representation sequence by utilizing time sequence symbolic representation and a landing state dictionary. The symbolic representation sequence of the flight to be predicted is subjected to fitting by using a pre-trained autoregressive landing model, and the prediction resultof the heavy landing risk occurrence probability is given.

The invention relates to a modeling method for a flight / propulsion system / jet flow noise comprehensive real-time model. The modeling method comprises the following steps: establishing a jet flow noisereal-time prediction model; establishing a component-level model of the turbofan engine with the large bypass ratio; establishing a kinetic model and a kinematics model of the double-engine transporter; and synthesizing and correcting a flight / engine / jet noise model. The invention discloses a noise reduction method for an aircraft. According to a traditional method, a flight system, a propulsionsystem and noise calculation are generally carried out separately; the inter-system coupling relationship is difficult to fully consider; the problem that the noise condition in the whole flight process cannot be covered is solved. According to the method, the problems that the calculation amount is large, and the jet flow noise cannot be calculated in real time according to flight and engine states are solved, a jet flow noise real-time prediction model is established and combined with a flight model and an engine nonlinear model, and real-time simulation of the flight state, the engine performance and the jet flow noise is achieved.

The invention provides a monitoring method, device and system for a flight ground support operation process, and the method comprises the steps: determining a target aircraft and a to-be-monitored ground support operation process according to flight plan information; and repeatedly executing the following steps until all nodes of the ground guarantee operation process are determined to be executed: step 1, determining a target object and a target action according to the current node of the ground support operation process; 2, identifying a target aircraft and a target object in the image frameof the monitoring video stream of the target camera; 3, determining whether a target action is executed or not based on the state information of the target aircraft and the target object in the imageframes at different moments; 4, if it is determined that the target action is executed, determining that the current node is executed, and the next node serving as the current node. According to theinvention, the technical problems that a flight process node monitoring method in the related technology needs manual participation and is tedious in operation are solved.

A flight training quality and efficiency evaluation method fusing physiological data and flight parameter data comprises the following steps: firstly, collecting physiological data and psychological state data in a flight process of a pilot, and then constructing a psychological state prediction model by using the collected physiological data and psychological state data based on an SVM (Support Vector Machine) method; the psychological state of the pilot in the flight process is analyzed through the psychological state prediction model, and meanwhile, the flight parameter data in the flight process is combined to quantify the analysis result, so that comprehensive evaluation of the flight training quality and efficiency of the pilot is achieved. The psychological state prediction model is constructed based on the SVM method so as to analyze the physiological data of the pilot, the psychological state of the pilot is comprehensively and accurately analyzed, meanwhile, flight training is evaluated from multiple angles in combination with a flight parameter quantitative analysis result, scientific method support is provided for pilot training quality and efficiency evaluation, and the pilot training quality and efficiency evaluation efficiency is improved. The method provides support for rapid training and efficient flight training of pilots, and provides a basis for aviation colleges to optimize a scientific training scheme.

The invention relates to a free flight analog simulation platform. The free flight analog simulation platform comprises an analog setting system, a data information system, a permission setting system, and an actual scene analog system. The implementation method of the platform includes the steps that first, a flight rule is designed, wherein in the actual scene analog module, an airplane flight process model is built on the basis of the core through that the distance is equal to the number generated when the speed is multiplied by the time; a conflict avoidance rule is designed, wherein in the actual scene analog module, the courses of airplanes are obtained through an equation of motion of the airplanes, the course included angle is calculated, and which encounter condition happens to the airplanes is judged so that corresponding avoidance measures can be taken. The free flight analog simulation platform is mainly used for the teams researching free flight to collect data and provides relevant data for free flight analog, analog logs are output, the analog data can be visually displayed for users, the users can conveniently calculate collision risk in free flight so that factors for influencing safety of free flight can be researched, and technical support is provided for achieving free flight.

The invention belongs to the technical field of unmanned aerial vehicles, and discloses a cluster formation aircraft abnormal fault level processing method, system and application, and the cluster formation aircraft abnormal fault level processing method comprises the steps: setting fault levels, and carrying out the polling detection of faults of different fault levels according to the fault priority before taking off or in the flight process; and when the flight fault of the aircraft is detected, enabling the individual aircraft to carry out corresponding processing according to the aircraft fault level list. According to the method, the current state of the airplane is judged through polling, judgment of the fault level of the airplane is achieved, corresponding state switching and processing are conducted according to the fault level, it is guaranteed that the airplane can be controlled before being out of control thoroughly, more detailed state switching can be conducted flexibly according to the state of the airplane, and the method achieves the judgment and processing of the abnormal fault level of an individual aircraft, reduces the uncontrolled risk caused by the ground station controlling the whole aircraft group or individual aircraft, and reduces the adverse impact on formation performance caused by the direct control of landing or return voyage when a fault occurs.

The invention discloses a comprehensive alarm system for flight environment monitoring, which comprises an alarm combination judgment unit and a plurality of alarm combination processing units, and is characterized in that the alarm combination judgment unit is used for receiving alarm information output by each piece of flight environment monitoring equipment, and if a plurality of alarm information is received in the same monitoring processing period, the alarm information is sent to a various alarm combination processing unit for processing; a plurality of alarm combination processing units firstly perform direction compatibility judgment and adjustment according to the combination mode of the alarm information so as to determine the maneuvering direction of a local machine, then make an avoidance strategy to determine the avoidance strategy with the minimum maneuver; and finally, the avoidance strategy is compiled into visual display information and voice broadcast codes to be output. The flight crew can be assisted in making proper operation or maneuvering avoidance measures, so that the safety of the whole flight process and the whole task process of the airplane is guaranteed.

The invention discloses a method and device for determining a flight path in high precision based on polynomial fitting, and an electronic device. The method comprises the steps that N frames of videoimages shot by a flight device in the flight process are acquired, and each frame of video image corresponds to a time point; shooting center space position information corresponding to each frame ofvideo image in the N frames of video images is determined; according to the time points corresponding to the N frames of video images and the spatial position information of the photographing centercorresponding to the N frames of video images, a polynomial fitting function is used for conducting curve fitting, a flight path curve of the flight device is determined, wherein the polynomial fitting function comprises three polynomials, and each polynomial takes a flight time parameter of the flight device as an independent variable; and a coordinate value corresponding to one direction corresponding to the space rectangular coordinate system of the flight device is used as a dependent variable. High-precision determination of the flight path of the flight device is achieved, and the cost required for determining the flight path of the flight device and the increase of the additional weight of the flight device are reduced.

The invention relates to an airplane automatic driving operation simulation method based on a long-short term memory network, and belongs to the field of airplane automatic driving. The whole-process flight data of the air route is used as a training set, the correlation of the data in the time sequence is mined by using a long-short-term memory network, and the mode that a pilot makes a driving behavior decision according to the navigation information of the air route is learned. Through training, a model learns key decision information of flight mode conversion performed by a human pilot according to navigation data. Flight mechanism analysis and data correlation analysis are carried out on independent flight stages, and corresponding model training input is determined. Through training, the model learns a mapping relation from input of a flight state, a flight environment and the like to output of operation variables. Therefore, in the actual flight process of an aircraft, according to the sensed flight state, flight environment and other data, the corresponding operation variables of the throttle lever, the pedal and the pitching rolling rocker are obtained through prediction of the long-short-term memory network model, and therefore automatic driving of the aircraft is achieved.

The invention discloses a non-stationary channel simulation method and a non-stationary channel simulation system based on a flight simulation platform. The method comprises the following steps: S1, acquiring flight state information of the position, the altitude, the speed and the attitude of a receiving and transmitting end; s2, selecting a propagation model according to the height of the transmitting and receiving end, determining the boundary of a channel model through the latitude and longitude of the transmitting and receiving end, the height information and channel parameters needing to be simulated in the flight process, selecting different channel models, and then calculating the transmission path loss of a large-scale channel model according to the channel models; s3, performing small-scale modeling by adopting an ellipsoid geometric model according to the flight state information in the step S1, obtaining a Doppler power spectrum, and further obtaining a scattering function of a channel; and S4, inputting the transmission path loss of the large-scale channel model obtained in the step S2 and the scattering function obtained in the step S3 into a channel simulation unit for channel mode. The method overcomes the defects of few actual measurement test opportunities, high cost and the like of the aeronautical communication equipment.

The invention provides an interference simulation system. The interference simulation system comprises a vacuum subsystem, a test model subsystem, a propellant supply subsystem and a measurement and control subsystem. The test model subsystem comprises an incoming flow simulation engine, a jet flow simulation engine and an aircraft test model, the incoming flow simulation engine is used for simulating hypersonic test airflow in the flight process of an aircraft, and the jet flow simulation engine is arranged on the aircraft test model and used for simulating jet flow generated in the flight process of the aircraft. According to the scheme, firstly, an interference simulation test is carried out in a vacuum cabin, a thinner low-pressure atmospheric environment can be provided, and under thelow-pressure atmospheric environment, hypersonic test airflow is provided by adopting fuel gas jet flow generated by the incoming flow simulation engine, so that the requirements of high speed and high enthalpy can be met at the same time; therefore, the manufactured test environment is close to the flight environment. Therefore, on the basis of reducing the requirement on equipment, the servicetime of the device can be prolonged, and the accuracy of a simulation result can be improved.

The invention discloses an online prediction method for stagnation point heat flow in the flight process of an aircraft. The method comprises the following steps: 1) before actual flight, carrying out one-dimensional heat flow identification through a sequence function method by utilizing temperature data of each measuring point in a structure, and training a neural network three-dimensional correction model in combination with actually measured heat flow; 2) simplifying the Fay-Riddell stationary point heat flow engineering estimation formula, taking the actually measured heat flow and the incoming flow condition of a given trajectory as an input sequence, and correcting various coefficients in the simplified formula through a least square method to obtain a preliminary stationary point heat flow prediction formula; and 3) during actual flight, taking the stationary point identification heat flow updated in real time as new heat flow data, and performing real-time fitting through a least square method to obtain a prediction formula updated in real time to predict a stationary point heat flow value in future 10 seconds. The heat flow error indicated by the method is within 15%, and the invention comprises the rapidity of engineering estimation, so that real-time and accurate heat flow indication in the flight process can be realized.

The invention discloses a 360-degree omni-directional overload flight simulator. The center of gravity of a trainee is in the front of the center of the gravity of an airplane like in the real flight process. The 360-degree omni-directional overload flight simulator comprises a vertical lifting system, a first movement system, a second movement system and a flight cockpit system, wherein an intelligent control system has control over a front-and-rear pitching motor and a left-and-right rotating motor, the center of gravity of the trainee is in the front of the center of gravity of the airplane like in the real flight process, and the pilot can feel transverse movement and rotation at the same time; the intelligent control system converts various rotation overload motions of the vision into electric signals, and controls a stepping motor to synchronously move in the X direction, the Y direction and the Z direction. When the 360-degree omni-directional overload flight simulator is used, the training cost can be reduced, the training effect can be ensured, and the airplane driving training time of trainees such as trainee pilots can be shortened.

The invention provides a flight verification auxiliary system based on a flat plate, and belongs to the field of flight verification. The system comprises a verification platform and auxiliary systemdata synchronization module, an equipment database management editing module, a verification plan making module, a verification result management module, a verification log management module and a calculation auxiliary module which are arranged on mobile equipment. A verification platform and an auxiliary system data synchronization module communicate with the flight verification platform throughTCP / IP to realize batch file transmission between the flight verification platform and the auxiliary system;. A flight verification platform is provided with a data synchronization module. An auxiliary system on a portable tablet personal computer is used for assisting a checker in completing flight checking work, the workload of the flight checker in the flight process is greatly reduced, the probability of misoperation is reduced, and the flight checking efficiency is improved.

The invention discloses a flight tracking control signal generation device and method based on Hilbert-Huang time grid reconstruction. The flight tracking control signal generation device based on Hilbert-Huang time grid reconstruction consists of a flight altitude tracking error measurement sensor, an aircraft speed measurement sensor, an aircraft flight path angle measurement sensor, an aircraftparameter and tracking state input unit, an aircraft central control MCU (Microcontroller Unit), a flight state display unit and a controller unit. In the flight process of an aircraft, the flight altitude tracking error measurement sensor, the speed measurement sensor, the flight path angle measurement sensor and the central control MCU are started to measure and display the current flight altitude tracking error, the speed and the flight path angle states in real time; the central control MCU of the aircraft automatically executes an internal Hilbert-Huang time grid reconstruction dynamic optimization algorithm according to a state tracking instruction sent by an air traffic control mechanism, and an optimal control strategy for enabling the aircraft to reach a specified tracking statein a shortest time is obtained; and the obtained optimal control strategy is converted into a control signal to be sent to a control signal output unit.

A flight data processing method and device, a recorder, an unmanned aerial vehicle and a storage medium, the method comprising: after the unmanned aerial vehicle is powered on, updating an encryption scheme (101), obtaining flight data in a flight process of the unmanned aerial vehicle (102), and encrypting the obtained flight data according to the updated encryption scheme (103), and storing the encrypted flight data in a memory card of the unmanned aerial vehicle (104). According to the flight data processing method and device, the recorder, the unmanned aerial vehicle and the storage medium, the security of the storage card recording the encrypted flight data can be effectively improved, and the user data security is guaranteed.

The invention discloses a deformable mechanism driven by memory alloy. The deformable mechanism comprises a driver mounting bracket (1), a memory alloy driver (2), a window wall plate (3), an actuating mechanism (4) and an aircraft shell (5). A window is formed in the aircraft shell (5), and a hollow detachable window wall plate (3) is arranged at the window; and the driver mounting bracket (1) isarranged in the aircraft shell (5). And one end of the memory alloy driver (2) is connected with the driver mounting bracket (1), and the other end is connected with the actuating mechanism (4). Theactuating mechanism (4) is in an arc shape with one end tilting upwards and makes contact with the arc-shaped structure of the aircraft shell (5). The free end of the actuating mechanism (4) extends out of the aircraft shell (5) through the window wall plate (3), and the free section is higher than the upper surface of the aircraft shell (5). Flight induction resistance can be reduced in the constant-speed flight process of the aircraft, and the flight mileage is increased.

The invention relates to a flight path-based aviation ad hoc network clustering method and a computer readable storage medium, and belongs to the technical field of aviation communication. The clustering method comprises the following steps: 1) pre-storing geographical cluster information corresponding to a corresponding geographical position on an aircraft flight path; wherein the geographical cluster information comprises a geographical cluster identifier and an intra-cluster position; 2) in the flight process of the aircraft, acquiring the current geographical position of the aircraft in real time; 3) searching matched geographical cluster information according to the current geographical position; and 4) updating own geographical cluster information according to the geographical cluster information matched in the step 3). According to the invention, the geographical cluster information corresponding to the corresponding geographical position on the flight path of the aircraft is stored before the aircraft flies. The updating of the geographical cluster information can be realized only by acquiring the current geographical position in the flight process of the aircraft, so thatthe problems of poor communication real-time performance and low efficiency caused by real-time calculation of clustering related information in the flight process of the aircraft are avoided.

The invention discloses a design method of an electronic stabilization system based on a six-degree-of-freedom motion platform, and belongs to the technical field of mechanical design, automation and the like. The method comprises the following steps: 1) obtaining attitude information of a carrier (aircraft) through a gyroscope and an acceleration sensor; 2) converting the attitude information into an electric signal and transmitting the electric signal through an integrated circuit; 3) establishing a six-degree-of-freedom motion control system based on a computer PCI bus by a DSP + FPGA architecture; 4) establishing a linear error model, and performing error correction; and (5) designing a core mechanical structure of the six-degree-of-freedom seat. In the flight process of the aircraft, the damping seat automatically adjusts the state of the seat in a three-dimensional space according to the swinging, pitching and rotating states of the aircraft, so that the relative posture of the seat and the ground surface is kept unchanged, and the damping effect is achieved. The passenger using the aircraft damping seat does not feel uncomfortable due to speed change, turning and take-off and landing acceleration of the aircraft, and really feels smooth flight.

The invention discloses a pilot operation quality assessment method based on curve fitting, which includes the following steps: S1, based on the analysis of historical flight data, determine the influencing factors to determine whether the flight is affected; S2, for each influencing factor, obtain Perform curve fitting on sparse control points and dense control points during the flight process to obtain the optimal flight curve for each influencing factor; S3, calculate the flight error based on the difference between the actual flight curve and the optimal flight curve, and calculate the flight error based on the differences between all influencing factors. Flight errors evaluate pilot operational quality. This method can fully consider the impact of environmental factors on the actual flight curve during aircraft navigation, and can fully consider outliers when performing curve fitting, and can effectively evaluate the pilot's operational quality.

The invention relates to a free flight analog simulation platform. The free flight analog simulation platform comprises an analog setting system, a data information system, a permission setting system, and an actual scene analog system. The implementation method of the platform includes the steps that first, a flight rule is designed, wherein in the actual scene analog module, an airplane flight process model is built on the basis of the core through that the distance is equal to the number generated when the speed is multiplied by the time; a conflict avoidance rule is designed, wherein in the actual scene analog module, the courses of airplanes are obtained through an equation of motion of the airplanes, the course included angle is calculated, and which encounter condition happens to the airplanes is judged so that corresponding avoidance measures can be taken. The free flight analog simulation platform is mainly used for the teams researching free flight to collect data and provides relevant data for free flight analog, analog logs are output, the analog data can be visually displayed for users, the users can conveniently calculate collision risk in free flight so that factors for influencing safety of free flight can be researched, and technical support is provided for achieving free flight.

The invention provides a flight body trajectory control method based on drop point prediction and virtual tracking so as to realize accurate control of a flight body with relatively weak control capability under relatively large trajectory deviation. According to the method, theoretical landing points Xt and Zt and residual flight time Tt of a flight body are predicted according to ballistic parameters in actual flight, and position deviations X and Z of the theoretical landing points and a target point are calculated. According to the estimated drop point deviation and the flight time, the longitudinal X / Tt and the lateral deviation Z / Tt which need to be eliminated per second are calculated, feedback control is formed according to the real-time position (Xf, Zf) and the scheme trajectory position (Xp, Zp) of the flight body and the longitudinal XTi / Tt and the lateral deviation ZTi / Tt which need to be eliminated at the corresponding moment in the flight process, the flight body is controlled to gradually eliminate the trajectory deviation, and the trajectory deviation of the flight body is eliminated. And taking the deviation between the predicted drop point and the target point as a final control index, approaching the target point, and realizing accurate strike on the target.

The invention discloses a multichannel coordinated loading system flight by flight spectrum experiment method which is technically characterized in that (1), during flight system simulation, the occurrence probability of an A working condition during first flight is e, wherein the e is larger than 0 and smaller than 1; (2), the occurrence probability of the A working condition during first flightis the e, because the e is smaller than 1, the A working condition is not simulated in the system for the first time, and this time the cumulative probability is e; (3), because the A working condition is not simulated in the first flight system, the probability of the A working condition during second flight is the sum e+e of the last cumulative probability and the original probability, namely 2*e; (4), the probability of the A working condition during third flight is the sum of the second cumulative probability and the original probability of the A working condition; (5), during the Nth flight, the total time of the A working conditions simulated before is an integer taken from N*e, the alpha is set as the time of the A working conditions, and the beta is decimal part of the N*e, that isalpha / N is approximately equal to the e. According to the multichannel coordinated loading system flight by flight spectrum experiment method, all working conditions of an aircraft in the flight process are fully simulated.

The invention discloses a flight test flow state distinguishing method based on friction resistance change rules. The method comprises the following steps: (1) calculating the axial force coefficientCA_identification of an aircraft corresponding to each flight moment in the whole flight process of the aircraft by adopting an aerodynamic identification method; (2) calculating the wave resistance Cap_calculation corresponding to each flight moment in the whole flight process of the aircraft according to an aerodynamic data table of the aircraft; (3) performing subtraction on the axial force coefficient CA_identification of the aircraft corresponding to each flight moment in the whole flight process of the aircraft and the wave resistance Cap_calculation, so as to obtain a friction resistance Caf_identification changing curve for the whole flight process of the aircraft; (4) dividing a friction resistance curve into two sections by taking the minimum point in the friction resistance curve as a boundary, dividing each section of the friction resistance curve into a plurality of sub-intervals, and calculating the friction resistance variation delta Caf_identification in each sub-interval; and (5) finding out the biggest influence factor of the delta Caf_identification, and if the flow state change causes the dominance of the friction resistance variation delta Caf_tran to the deltaCaf_identification, judging that the surface flow state of the aircraft changes so that transition from laminar flow to turbulent flow occurs.

The invention provides an aircraft flight safety control method and system and a server. The method comprises steps that a first safety threshold and a second safety threshold are set for at least oneflight parameter in the flight process of an aircraft; at least one flight parameter value of the aircraft in the flight process is acquired; safe operation is carried out based on the at least one flight parameter value, when the at least one flight parameter value is between the first safety threshold and the second safety threshold or equal to the second safety threshold, a blow-up system of the aircraft is released from insurance; when the at least one flight parameter value is greater than the second safety threshold, the blow-up system is made to blow up the aircraft. The method is advantaged in that through setting the safety range for the flight parameters of the aircraft in the flight process, the pipeline for guaranteeing the safe flight of the aircraft can be formed, so faultsof the flight process of the aircraft can be better handled and dealt with, and damage to ground facilities and personnel can be avoided.

According to the various aspects of multiple embodiments, it provides equipment and methods from multiple independent systems (such as flight management systems and ground air traffic control) in the entire flight history.During the flight process, many trajectory differences (such as flying intentions, controllers interference, or actual flights caused by predictive errors and predictive trajectories) will form interference. Therefore, dynamic monitoring of these deviations and controlling a dynamic synchronizationcycle.A dynamic trajectory synchronization algorithm attempts to return each system in these systems to the balance whenever a disturbance causes imbalance.The disturbances include the deviation of the atmospheric conditions and the predictive atmospheric conditions, the changes in pilot preferences, and a variety of unpredictable events that require the movement of the controller (such as the needs of the interval with other aircraft or the changes in flow weather, special use airspace or scheduling requirements).

The invention discloses a mobile time-slot aviation control method based on 4D track, establishes a mobile time-slot model, uses modern computer, network technology and big data processing technology, and performs a large number of calculations and predictions in the flight control work by the computer system to provide a visual mobile time slot model for tower flight controllers, and change the previous control mode that relied on human mental calculation, visual judgment, and manual guidance and command into a global (full flight process) and visualized time slot allocation control model. The use of mobile time slot management methods in military and civil aviation radar control systems can greatly reduce the difficulty of flight deployment, reduce errors caused by human factors, and improve the level of control automation.