157 results about "Aircraft dynamics" patented technology

The invention provides a low-altitude airspace collaborative management method and system based on digital twinning, and the method comprises the steps: analyzing the maneuvering characteristics and flight envelope characteristic parameters of an aircraft based on the obtained real-time state data of the aircraft, and calculating the maneuvering characteristics and flight envelope characteristic parameters of the aircraft by using kinematics and dynamics models, describing motion laws of different aircrafts; real-time flight data of the aircraft are combined, the motion track and attitude change of the aircraft are synchronized in real time in a virtual environment through a digital twin technology, the dynamic behavior of the aircraft is accurately reproduced, and a high-fidelity digital model is provided for flight conflict detection and flight path prediction; a multi-level and multi-granularity digital twin model is constructed according to the difference of the motion characteristics of the aircrafts, and the digital twin model comprises an airspace structure model of a macroscopic level, an aircraft group behavior model of a mesoscopic level and a single aircraft dynamic model of a microscopic level.

The embodiment of the invention provides a heterogeneous aircraft low-altitude management method and device, and the method achieves the dynamic generation of a global avoidance decision through the innovative building of an aircraft dynamics model library, and the combination of a distributed cooperative avoidance network and a multi-objective optimization algorithm. And designing a flight rule identification model, fusing visual, instrument and digital flight rules, and realizing dynamic grouping and airspace distribution based on task similarity through an airspace management decision maker. And a task priority evaluator is constructed, a conflict resolution optimization model is trained based on historical data features, and avoidance instruction optimization under multi-target constraint is realized. According to the method, the defects of the traditional technology in the aspects of cooperative avoidance, rule recognition, conflict resolution and the like are effectively overcome, and the safety and efficiency of heterogeneous aircraft low-altitude management are remarkably improved.

The invention relates to a micro-settlement control method for an extra-large-span flat-top straight-wall tunnel under the dynamic load action of an aircraft, and relates to the technical field of tunnel construction. The control method comprises the following steps: S10, uniformly spreading the weight of the airplane to each airplane wheel, and calculating to obtain a static load P1 of the airplane; s20, vertical kinetic energy of the aircraft is converted into impact force, dynamic additional force F is obtained and evenly spread to each aircraft wheel, and the dynamic load P2 of the aircraft is obtained through calculation; s30, adding the static load P1 and the dynamic load P2 to obtain an aircraft landing impact load P3; s40, the distance r from the load acting point to the calculation point and the burial depth h of the tunnel are obtained, and settlement S of the tunnel vault is calculated through the aircraft landing impact load; s50, through Moire-Coulomb model simulation analysis, the influence of the aircraft dynamic load on tunnel construction settlement is obtained; and S60, making a corresponding construction scheme according to the influence of the airplane dynamic load on tunnel construction settlement. The construction problem of undercrossing the airport runway by the tunnel can be solved, and settlement of the airport runway is controlled.

The invention discloses a low-altitude traffic flow collaborative awareness and conflict prediction method and system based on a multi-modal large model. The method comprises the following steps: collecting multi-source heterogeneous data of an aircraft, fusing and mapping the multi-source heterogeneous data to a space-time grid with dynamically adjustable granularity based on a real-time traffic situation, and realizing adaptive characterization; the method comprises the following steps of: constructing a robust special prediction model by introducing aircraft dynamics constraint and airspace rule knowledge as priori and performing fine adjustment by adopting a loss function containing an adversarial regularization item based on a pre-trained large model of the body-equipped agent; inputting spatial-temporal characteristics into the model, outputting behavior intentions and probability trajectories in an end-to-end manner, constructing an incomplete information game deduction model based on predicted trajectories, and calculating a comprehensive collision risk index fusing trajectory uncertainty, a motion state and a game deduction result; and generating a hierarchical early warning and collaborative avoidance strategy, and performing network distribution. According to the method, the accuracy, the robustness and the decision intelligence of conflict prediction under the low-altitude dense traffic flow are remarkably improved.

The invention relates to a dynamic signal event rule engine processing method, system and device and a medium, and the method comprises the steps: writing preprocessed ship and aircraft data into message middleware; and an event rule is constructed, the event rule comprises a data source node, a service node and an output node, the service node is used for carrying out conditional judgment and logic processing on the dynamic and static data of the ship and the airplane, and the output node is used for outputting alarm information. And converting the event rule into an SQL statement of the Flink, and sending the SQL statement as a task to the Flink for operation. And when the Flink runs, reading real-time dynamic and static data of the ship and the airplane in the message-oriented middleware, judging based on an event rule, and writing the data meeting the requirement into an alarm theme. The problem that heterogeneous signals and data of different data sources are inconsistent when the event rule engine is applied to ship and aircraft dynamic signals in the prior art is solved.

The invention discloses an intelligent optimization system and method for track prediction. The method comprises the steps that 1, TLE data are preprocessed, and a data set is obtained; 2, training a machine learning model; 3, propagating the current state through aircraft dynamics by adopting an estimation algorithm, and then correcting the propagation state by utilizing a pseudo measurement method; 4, evaluating and optimizing the model; and 5, predicting and classifying. Machine learning prediction is used as UKF-based pseudo measurement prediction, a current state is propagated through an aircraft dynamics model, then the propagation state is corrected by using pseudo measurement data, and then an HMMS is used for predicting a pseudo measurement value driven by data, so that accurate estimation of a future state of an aircraft can be realized by effectively combining the prediction capability of machine learning. The method not only considers the similarity of the trajectory in the spatial dimension, but also can effectively capture the dynamic change in the time dimension, thereby more accurately predicting the flight trajectory.

The invention relates to the technical field of aircraft path planning, and particularly provides an aircraft path planning method for a space non-cooperative target. The method comprises the following steps: constructing an aircraft dynamics model and constraint conditions, and obtaining a non-convex optimal control problem; performing discretization processing on a non-convex optimal control problem through a non-equal-interval pseudo-spectrum discrete optimization model, and converting the non-convex optimal control problem into a fixed-time nonlinear programming problem about discrete nodes; according to the method, a fixed time nonlinear programming problem is convexed to form a convex sub problem, a local optimal solution of a non-convex optimal control problem is obtained through sequence iteration, under the multi-state constraint, path planning of an aircraft approaching a space non-cooperative target is achieved, the problem of no feasible solution caused by non-accurate linearization is solved, and the method is suitable for being applied to a non-cooperative target. And the convergence rate of the algorithm is accelerated.

The invention discloses an aircraft body freedom degree flutter time domain analysis method, device and equipment and a medium, and relates to the field of aircraft dynamic aeroelastic analysis, and the method comprises the steps: determining the initial steady state of an aircraft through static balancing by using an aircraft aerodynamic grid model and an aircraft structural grid model; performing motion deformation coupling analysis on the aircraft after the initial disturbance is applied under the initial steady state condition, and determining the displacement of the aircraft surface node relative to the balance position based on the analysis result; updating a pneumatic grid through displacement, obtaining surface aerodynamic force of the aircraft based on the updated pneumatic grid, mapping the aerodynamic force to a structural grid by using a pneumatic structural coupling interface, and obtaining an aerodynamic load; and carrying out motion deformation coupling iteration and pneumatic structure coupling iteration based on the pneumatic load, carrying out coupling time propulsion when a coupling residual error meets a preset condition, judging the dynamic stability of the aircraft according to the displacement in the time propulsion process, and completing the time domain analysis of the degree-of-freedom flutter of the aircraft body. And high-precision analysis of the aircraft is realized.

The invention relates to a multi-aircraft cooperative guidance method based on an MAPPO algorithm, and the method comprises the steps: building a multi-aircraft cooperative guidance model which comprises an aircraft dynamics model, a process constraint model, a terminal constraint model, and a heeling angle amplitude constraint model; when the remaining flight range is larger than or equal to 500 km, a cooperative guidance law based on improved prediction correction is designed, and an aircraft attack angle and heeling angle guidance instruction is solved, and when the remaining flight range is smaller than 500 km, the cooperative guidance law based on the MAPPO algorithm is switched to, and the aircraft attack angle and heeling angle guidance instruction is solved. The method can accurately arrive at the middle-end shift change point in a relatively large time difference, and smoothly realizes a time cooperation task. The method has high robustness for state disturbance, and has a larger time cooperation range and a better time cooperation guidance capability.

The invention belongs to the field of wind tunnel experiments in a hypersonic flow field environment, and discloses a multi-degree-of-freedom high-frequency motion simulation device for an aircraft dynamic stability test and a calculation method for realizing an actuation angle. According to the technical method, calculation is carried out on the basis of an electromechanical coupling equation, determined by electrical parameters and mechanical parameters, of a piezoelectric material. Modeling can be carried out according to a piezoelectric equation to obtain a calculation method between the voltage applied by the piezoelectric actuator and the pitching and yawing actuation angles of the device, so that the excitation effect of the device in the ground test process can be accurately controlled and predicted. The method is not only suitable for pitching and yawing two-degree-of-freedom actuation calculation, but also can be used for calculating the actuation angle of a three-axis degree-of-freedom experimental device added with rolling drive through coordinate transformation under the condition of adding parameters such as rolling angular velocity and the like in the face of the three-axis degree-of-freedom experimental device added with rolling drive. At present, according to a calculation method based on the device, calculation is carried out only by considering the degree of freedom of the pitching axis and the yawing axis.

The invention discloses a hypersonic-speed deformable aircraft online planning method based on sequence convex optimization, and belongs to the field of hypersonic-speed deformable aircraft trajectory planning. The implementation method comprises the following steps: analyzing the influence of deformation characteristics on aerodynamic characteristics of the aircraft, and constructing a trajectory planning-oriented dynamic model of the three-degree-of-freedom hypersonic deformation aircraft; taking the maximum weighting function of the terminal height and the terminal speed at the end of the task as a performance index, considering the initial boundary constraint, the terminal boundary constraint and the control quantity constraint, and combining an aircraft dynamics model to construct an initial trajectory optimization problem of the hypersonic deformation aircraft; performing convexity processing and discretization processing on the variable-elongation aircraft trajectory planning problem to obtain a trajectory planning convex problem; and a sequence convex optimization solving method based on variable time domain rolling planning and considering multi-stage continuous solving is constructed to solve the problem of gliding section trajectory planning with free terminal time, and online planning of the hypersonic deformation aircraft is realized according to a solving result.

The invention relates to the technical field of intelligent flight control, in particular to a multi-source sensing data fused low-altitude flight track offset intelligent repair method, which comprises the following steps of: performing jitter correction on a visual image stream through a motion compensation module, performing resampling on an ADS-B positioning signal by adopting a Lagrange interpolation method, and performing multi-source sensing data fusion on the ADS-B positioning signal; the radar point cloud is mapped to an image coordinate system, and a fusion track representation vector with time-space synchronization is generated; extracting a curvature abrupt change point set, an environment shielding factor and an airspace visibility gradient based on the vector, and constructing a multi-dimensional offset feature tensor in combination with aircraft dynamics constraints; inputting the tensor into a pre-trained space-time diagram neural network, and outputting a risk grading restoration decision comprising a restoration angle, a climbing rate and a speed compensation amount; injecting the repair decision into a flight control simulator for verification, and outputting a final repair instruction when the trajectory deviation value is smaller than a safety threshold value; the method has high precision and closed-loop execution flight path repairing capability, and is suitable for a flight control system in a complex low-altitude environment.

The invention discloses an aircraft dynamic recovery sorting scheduling method based on a re-flight strategy and a related device, and relates to the technical field of air traffic control, and the method comprises the steps: solving an aircraft group dynamic recovery decision model based on a state parameter of a previous decision stage, and obtaining a decision variable of each aircraft in a current decision stage; according to the decision variables of the aircrafts in the current decision stage, the recovery states of the aircrafts in the current decision stage are obtained; removing successfully recycled aircrafts from the to-be-recycled aircraft set in the previous decision-making stage to obtain the to-be-recycled aircraft set in the current decision-making stage, selecting a re-flying strategy for the recycled aircrafts failed in recycling, updating the decision variables according to the re-flying strategy, and obtaining the updated decision variables of the aircrafts in the current decision-making stage; if the aircraft set to be recycled in the current decision-making stage is empty, recycling is completed; according to the method, the recovery efficiency can be improved, and the flight safety can be guaranteed.

An aircraft modeling method based on mechanism and PSO feedforward neural network optimization comprises the following steps that an aircraft dynamics mechanism model is constructed by establishing an aircraft rigid body model and a projectile body model; embedding the aircraft dynamics mechanism model into a PSO feedforward neural network by using the PSO feedforward neural network, adopting a mechanism embedding neural network method and utilizing rich information contained in flight data, and continuously training a difference value between a mechanism value and an actual value under different conditions according to input characteristics to obtain a neural network residual compensation model; and adding the neural network residual compensation model into the aircraft dynamics mechanism model to obtain an optimized variable configuration aircraft model. According to the method, accurate modeling of different configurations under different environments and targets can be realized, and particularly modeling of variable-configuration aircrafts can be realized.

The invention discloses a shipborne fixed-wing aircraft landing guidance law design method and system, and belongs to the field of aircraft guidance law design. The problems that the multi-coordinate system coupling effect of ship motion and aircraft dynamics is not fully decoupled and an existing method is weak in adaptability to non-stable sea conditions are solved. The method comprises the following steps: defining related coordinate systems including a world coordinate system, a landing coordinate system and a ship body coordinate system; calculating an ideal landing point height change value caused by ship deck movement in real time according to the position of the ideal position in the ship body coordinate system; utilizing a KOA-LSTM hybrid forecasting model to predict a motion heave value of a ship deck at a future critical moment; designing a compensation value for the longitudinal position deviation based on the predicted motion heave value, and carrying out dynamic compensation correction on the longitudinal guide instruction; and according to the compensated guide instruction and the real-time position of the aircraft, calculating the transverse and longitudinal deviation of the aircraft relative to the expected landing trajectory to form closed-loop control. The device is mainly used for offshore operation.

The invention discloses a dynamic safety interval control method for a low-altitude aircraft, relates to the technical field of low-altitude flight control, and solves the technical problem that the aircraft cannot be effectively controlled in the prior art. The method comprises the following steps: 1, selecting a certain aircraft as a target aircraft, calculating a potential field force FAB generated by a front aircraft on the target aircraft, and defining a state-space equation of the target aircraft in combination with an acceleration requirement of the target aircraft; if the target aircraft is an unmanned aerial vehicle, skipping to the step 2, and if the rear aircraft is a manned aircraft, skipping to the step 3; 2, eliminating a state estimation error caused by the operation time delay of the target aircraft by using an operation time delay compensation method, and obtaining a state-space equation of the target aircraft under the time delay tau; 3, solving the state-space equation by a genetic optimization algorithm to obtain an optimal interval control parameter; the dynamic interval control model provided by the invention greatly improves the operation efficiency of the complex low-altitude fusion airspace on the premise of conforming to the aircraft interval standard.

The invention discloses an aircraft attack angle protection control method based on dynamic instruction correction, belongs to the field of flight control methods, and is used for solving the tracking control problem under the condition that the aircraft attack angle is limited. Firstly, based on an aircraft dynamics model, a backstepping method is utilized to design an adaptive controller to ensure stable tracking of a system, a virtual attack angle instruction part needs to be limited by adopting a saturation function, and a limited boundary value is provided by a subsequent protection system. And then, designing a prediction model representing correlation between the attack angle and the attack angle instruction and dynamics based on the designed closed-loop control system, reversely deducing a complex function relationship between the attack angle instruction and the system state and dynamics through the prediction model, and constructing an attack angle protection system. And finally, calculating an attack angle instruction boundary value through the prediction model and a system motion state trend under the current input, and correcting an original virtual attack angle instruction boundary so as to realize attack angle protection. According to the method, stable tracking of the system under attack angle constraint can be ensured, the residual attack angle in the envelope can be fully utilized, the maneuverability of the aircraft is improved, and the method has an engineering application reference value.

The invention provides a civil aircraft safety perception method and system based on virtual flight, and relates to the technical field of aircraft safety perception. A dynamic and hierarchical three-dimensional wind shear field model is constructed through space-time alignment and fusion of multi-source meteorological data; deep coupling of wind disturbance and aircraft dynamic response is realized based on a small disturbance theory and a flight dynamics model; continuous and dynamic quantification of risks is realized by combining and analyzing flight parameters and a safety threshold value dynamically adjusted based on wind disturbance intensity and utilizing multi-parameter risk level weighted integration; according to the method, the risk coefficient is coupled with the three-dimensional terrain and the virtual flight trajectory, hierarchical color mapping is adopted to carry out visual space visualization, and a complete closed loop from environment modeling to risk early warning is formed, so that the identification accuracy and timeliness of the flight risk in the wind shear environment are greatly improved, and the scientificity and practicability of security situation awareness are enhanced.

The invention discloses a self-adaptive unmanned aerial vehicle control method for an improved neural network. The method comprises the following steps: constructing a PID controller SSA-BP-PID of a BP neural network; optimizing a PID controller SSA-BP-PID based on a sparrow search algorithm SSA, updating a population position and assigning a value to a weight value and a threshold value of the SSA-BP-PID, so that the SSA-BP-PID outputs an updated PID parameter and a control law; calculating output attitude data of the aircraft according to the control law in combination with an aircraft kinetic model; and S3, setting the number of iterations, constructing a fitness function as a minimization target in combination with the overshoot, the adjustment time and the steady-state error, and iteratively calculating the steps S2-S3 to obtain output attitude data for controlling the flight of the unmanned aerial vehicle. The method is used for optimizing PID controller parameters, compared with a traditional PID control method, the method has remarkable advantages in the aspects of dynamic response speed, steady-state precision, anti-interference capacity and the like, and the control performance of the four-rotor unmanned aerial vehicle is improved.

The invention provides a high-speed aircraft online trajectory planning method based on improved polynomial guidance, which solves the problems of calculation delay and poor trajectory smoothness in the existing autonomous path planning, and comprises the following steps: establishing a plane-coordinate system and a motion equation set of a high-speed aircraft, and determining constraint conditions in the flight process of the high-speed aircraft; constructing an optimization model containing an adaptive penalty function based on an improved sequential quadratic programming algorithm, and generating an obstacle avoidance path point set; performing trajectory optimization by adopting an improved polynomial, generating a trajectory meeting aircraft dynamics constraints among the path points generated in the step 2, and selecting a key path point set; based on the obstacle avoidance path point set and the key path point set, adopting a centripetal parameterized Catmull-Rom spline curve to process the generated path to obtain a smooth trajectory; a guidance instruction is obtained based on smooth trajectory analysis and calculation, and the high-speed aircraft is guided to sail according to the planned trajectory. And the real-time calculation efficiency is improved on the basis of realizing the smooth trajectory.

The present application discloses a method, device, equipment and medium for dynamic load balance in aircraft dynamics analysis under a non-inertial system, and relates to the field of structural dynamics analysis, including: determining the inertial parameters of the aircraft finite element model, and calculating the position vector of the unit integration point based on the coordinates of the unit node; solving the rigid body motion based on the inertial parameters and the external load of the finite element model, obtaining the target vector, and determining the acceleration vector of each unit integration point according to the position vector and the target vector; determining the inertial load of the unit integration point based on the acceleration vector, generating an equivalent node inertial load through the inertial load, accumulating each equivalent node inertial load and the non-inertial system external load vector, and obtaining the node load vector of the non-inertial system; determining the unbalanced force and unbalanced moment according to the node load vector and the non-inertial system coordinate origin, and correcting the equivalent node inertial load to complete the load balance. The present application realizes the dynamic balance of the load in the non-inertial system.

The invention relates to a multi-target aircraft dynamic scheduling method based on an entropy weight method and deep reinforcement learning, and the method comprises the steps: obtaining a to-be-maintained aircraft set, building a heterogeneous graph model based on a maintenance project set and a maintenance aircraft position set of each aircraft, carrying out the extraction of graph features through an encoder, carrying out the feature aggregation of the extracted nodes, and obtaining a multi-target aircraft dynamic scheduling model; aggregated feature vectors are obtained; obtaining a multi-target aircraft dynamic scheduling strategy based on the SAC network obtained by reinforcement learning training; a multi-target aircraft dynamic scheduling strategy is obtained by combining the SAC network obtained by reinforcement learning training, and in the training method of the SAC network, based on an entropy weight method, an aircraft maintenance aircraft position scheduling problem is converted into a Markov decision process, so that a multi-target aircraft maintenance aircraft position scheduling strategy can be obtained based on the obtained dynamic weight. While the flexibility of the SAC algorithm is brought into full play, it is guaranteed that multi-target balance and optimal action selection are balanced, dynamic scheduling is reasonably dealt with, and efficient coordination of multi-target optimization and real-time response of dynamic events under complex constraints are achieved.

The invention discloses a target vehicle dynamic tracking method based on multiple aircrafts, and the method comprises the steps: setting a multi-aircraft group, and enabling all aircrafts in the multi-aircraft group to have electronic fences; an inner-surrounding aircraft is determined, and a middle-surrounding aircraft is determined based on the collision sequence of the inner-surrounding aircraft electronic fence and other aircraft electronic fences; and the middle-surrounding aircraft obtains a predicted driving track of the target vehicle based on the motion parameters of the target vehicle, selects peripheral aircrafts based on the predicted driving track, and dynamically tracks the target vehicle by the peripheral aircrafts. The problem that vehicles in a monitoring area cannot be continuously monitored due to the fact that the monitoring area is vacuum when a plurality of common aircrafts are dispatched to fly along with a target vehicle in the prior art is solved. According to the invention, under the condition of ensuring continuous, stable and dynamic tracking of the target vehicle, the computing resource consumption of a single aircraft is reduced based on reasonable task planning of the aircraft.

The invention provides an airport flying area crossing traffic command system based on an A-SMGCS system, and belongs to the technical field of intelligent traffic, and the system comprises a sensor layer which is used for collecting aircraft dynamic data, to-be-passed authorized object data, environment meteorological data, and dynamic obstacle data; the data processing and decision-making layer is used for carrying out standardization processing and space-time mapping processing on the collected data, judging existing potential conflicts in combination with a dynamic threshold adjustment mechanism, and generating an issuing instruction based on a multi-target optimization decision; and the execution layer is used for controlling crossing traffic management and control equipment according to the issued instruction and feeding back an execution result to the data processing and decision-making layer in real time to form closed-loop control. The traffic conflict risk of the airport flight area crossing is effectively reduced, the crossing passing efficiency is improved, the vehicle waiting time and the aircraft taxiing delay are reduced, the fine scheduling requirement for scene movement is met, and reliable support is provided for safe and efficient traffic operation of the airport flight area.

This invention discloses an airborne display and control method for enhancing situational awareness and flight operations, comprising: providing onboard operational information and basic traffic, weather, and terrain displays based on flight phases and crew operational requirements, configuring display content and layout, and establishing basic situational awareness; providing a list of traffic aircraft dynamic information, setting aircraft of interest, and acquiring operational information of aircraft of interest to establish enhanced traffic situational awareness; receiving conflict detection, conflict prediction, and conflict resolution information at short, medium, and long ranges, and outputting alarm information in visual, auditory, or tactile forms according to alarm priority to establish enhanced conflict alarm situational awareness; applying for and receiving control clearance for enhanced flight operations through CPDLC, calling the flight operation setup program, and inputting the information required for enhanced flight operations; and generating target flight paths and target flight states in real time based on enhanced flight operation requirements, and implementing enhanced flight operations by the crew or flight management system.

The invention relates to the technical field of aircraft dynamic model testing, and discloses a method for testing lift force and resistance of an aircraft with a power system through a dynamic model test, which comprises the following steps: step 1, mounting an acceleration sensor and a corresponding data acquisition module on a rail car in a fastening manner, and recording acceleration data of the rail car; secondly, a support is fastened and installed on the rail car, and an aircraft with a power system is installed on the support; step 3, installing a two-dimensional force transducer; 4, debugging and starting a power system; and step 5, data processing: through the obtained acceleration data and the lift force data and resistance data of each fulcrum, the speed, lift force and resistance corresponding to each moment are obtained through data processing. According to the invention, the lift force and resistance of the aircraft can be simply, efficiently and accurately tested.

The application provides a kind of aircraft servo elastic dynamics model correction method considering operating surface gap, first aircraft structure is divided into substructure, and the aircraft dynamics model containing aileron gap nonlinearity is established according to substructure branch modal;And additional inertia force caused by aircraft operating aileron deflection is introduced in dynamics model, and the aircraft open-loop servo elastic motion equation containing aileron gap nonlinearity under independent generalized coordinate is obtained;According to sensor output equation, rudder transfer function and flight control system equation, the aircraft nonlinear servo elastic closed-loop system model containing aileron gap nonlinearity is established, and the model is corrected based on ground vibration test, rudder frequency response test and gap measurement test result, and the stability of the model is judged based on simulation analysis result and open-loop frequency response test result and is further corrected, which improves the accuracy of gap nonlinearity aircraft aerodynamic servo elastic characteristic evaluation, and is helpful to guide aircraft servo elastic ground test engineering practice.

The invention provides an aircraft dynamic derivative test device in a strong interference environment, which relates to the technical field of aircraft aerodynamic characteristic tests and comprises an interference flow field establishing device, a dynamic derivative measuring device and a synchronous control module. The disturbing flow field establishing device is composed of a shock wave generator, a supporting connecting piece and a wind tunnel attack angle mechanism, the shock wave generator is connected with the wind tunnel attack angle mechanism through the supporting connecting piece, + / -15-degree pitching and + / -10-degree yawing motion is achieved based on the wind tunnel attack angle mechanism, and multiple types of strong disturbing flow fields can be established by replacing the shock wave generator; the dynamic derivative measuring device is installed in a plug-in mechanism of a wind tunnel, based on a forced vibration test method, a model is driven by a high-precision servo motor to vibrate slightly, precise acquisition is realized by matching with a high-frequency dynamic balance and a data filtering unit, and the displacement of the model relative to a shock wave generator can be adjusted through the plug-in mechanism. According to the scheme, a real strong interference environment can be accurately reproduced, and the dynamic derivative measurement accuracy is improved.

The invention relates to the technical field of high-speed aircraft health management, and particularly discloses an interpretable aircraft state sensing and predicting system and method. The method comprises the following steps: constructing and training a lightweight anomaly diagnosis network with an expansion perception layer; aircraft dynamics, kinematics and fault mechanism formulas are used as soft constraints to be embedded into the future state estimation network; an SHAP interpretation framework is used for sorting the importance of the input features, and a network structure is optimized accordingly; and finally, accurate diagnosis of abnormal types and positions and rapid prediction of aircraft states at a plurality of moments in the future are realized. According to the method, by introducing three innovation points of an expansion perception layer, physical information embedding and feature importance sorting, the diagnosis accuracy and the model interpretability are remarkably improved, and the high-performance calculation requirement in a scene with limited calculation power is met.

The application provides a kind of aircraft dynamics modeling method containing multi-degree-of-freedom actuator, the modeling method returns general mechanics and advanced theory and thought of mechanics basic disciplines, aircraft is regarded as multi-rigid body system, based on virtual power principle and multi-body system topological configuration recursive modeling method, the deformation multi-body system dynamics model suitable for aircraft containing multi-actuator is established, and the motion characteristics of multi-degree-of-freedom, strong coupling between the motion characteristics of aircraft external body attitude motion and internal component relative motion are accurately described.