33 results about "Aircraft noise" patented technology

The invention provides a broadband sound absorption structure suitable for undercarriage cabin door noise reduction and a design method, and belongs to the field of aircraft noise reduction. The sound absorption structure comprises a plurality of perforated plate type Helmholtz cavity unit cells and a plurality of embedded pipe type Helmholtz cavity unit cells. In the perforated plate type unit cells, one or more first through holes are formed in the perforated plate. And in the embedded pipe type unit cells, the embedded pipes penetrate through the perforated holes in the perforated plates and extend into the cavities. Cavities of the two single cells face the same direction, and the perforated plate forms a curved surface conformal with an undercarriage cabin door. The effective length of the neck of the perforated plate is increased by using the embedded pipe, the low-frequency sound absorption performance is improved, the sound absorption performance and the sound absorption bandwidth of the middle-frequency band are improved by using the perforated plate type Helmholtz cavity, meanwhile, the curved surface conformal design is highly matched with the special-shaped cabin door structure, and the sound absorption performance is improved. The low-frequency and medium-frequency sound absorption performance can be guaranteed, and meanwhile the light and thin requirements of an aircraft can be met; and a pure passive mechanical structure is adopted, so that the control complexity and stability risks of an active noise reduction system can be avoided.

The invention discloses an aerodynamic noise prediction model construction method of an unsteady transient maneuvering state rotor aircraft, and belongs to the technical field of aircraft noise prediction. The problem that in the prior art, a traditional aircraft noise prediction method is difficult to achieve instantaneous efficient aerodynamic noise prediction under the maneuvering state of a rotor type aircraft is solved. The method comprises the following steps: constructing a six-degree-of-freedom linearization equation of the Updating the manipulated variable and state variable of the rotor aircraft based on a trajectory tracking control law, and outputting a maneuvering flight simulation data file; the sound pressure contribution of each sound source infinitesimal to a far-field observation point is calculated based on a Farassat 1A formula, time dimension interpolation is carried out on the far-field observation point at the observation time, integral summation is carried out on the infinitesimal sound pressure contribution at the same observation time to obtain sound pressure time calendar data of the observation point, discrete Fourier transform is carried out on the sound pressure time calendar data, and the noise characteristics of the maneuvering-state rotorcraft are obtained through analysis. The method improves the calculation efficiency of calculating the infinitesimal sound pressure contribution at the observation point time, and can be used for predicting the instantaneous noise of the aircraft.

The invention provides an aircraft noise ground monitoring data optimization method for a linear flight segment, relates to the technical field of environment monitoring and noise control, and solves the problem that the noise evaluation accuracy is limited due to the fact that the influence of the flight state of an aircraft on noise propagation is not considered in an existing method. The method comprises the following steps: acquiring an aircraft track and ground key coordinates, and converting the aircraft track and the ground key coordinates into a three-dimensional rectangular coordinate system after Gaussian coordinate system conversion; determining an aircraft noise event, matching track data corresponding to the event with noise data, dynamically adjusting a confidence interval, and correcting the noise data to a confidence boundary; polynomial fitting is carried out, the ratio of the sound level slope to the flight time is used as a constraint, the minimum global error quadratic sum of noise data fitting is used as an optimization objective function, and a model is constructed; and solving model parameters by adopting a genetic algorithm to finish an optimization process. According to the method, the optimization processing mode of the aircraft noise sound level data is perfected, and the influence of the aircraft noise around the airport can be accurately judged.

The invention discloses an acoustic metamaterial suitable for full-band coupling noise reduction of a large-curvature aircraft cabin, and relates to the technical field of aircraft noise reduction, the acoustic metamaterial comprises a core body layer, two panel layers which are located on two sides of the core body layer and have different thicknesses, and two hard frame layers located between the core body layer and the two panel layers, the hard frame layer is formed by attaching a plurality of hard frames with hollow patterns to the inner surface of the panel layer in a discrete distribution mode. The technical problems that when a traditional acoustic material is installed on a large-curvature surface, a supporting structure is complex, the low and medium frequency noise reduction efficiency is low, and full-band noise cannot be covered are solved, the acoustic metamaterial provided by the invention is installed by being matched with the large-curvature surface in an aircraft cabin, meanwhile, a multi-order modal vibration response and structural damping coupling mechanism is utilized, and the noise reduction performance of the acoustic metamaterial is improved. The low-frequency noise reduction limitation is broken through, low-frequency, medium-frequency and high-frequency full-band noise isolation is covered, cutting is convenient, and the cabin space is not occupied.

The application provides a kind of transport aircraft cabin top structure noise multi-point measurement method under flight full working condition, and belongs to the technical field of aircraft noise testing.The application uses cargo compartment lifting slide rail as existing installation datum, and forms adjustable measurement point layout structure by telescopic cross bar device and height adjusting lifting rod, so that fast installation, stable fixation and spatial positioning of noise testing sensor in the top area of transport aircraft cabin can be realized without damaging original structure of aircraft body.The application can execute multi-point noise measurement of complex environment in the top area of aircraft cabin without changing original structure of transport aircraft, so that sensor can be stably and reliably installed in flight vibration environment, and effective coverage and accurate identification of key noise area in the top area can be realized.

The invention belongs to the field of aircraft noise reduction, and discloses an aircraft cabin active noise reduction control method and related equipment, and the method comprises the steps: collecting the vibration, rotating speed, cabin sound pressure and other multi-modal data of an aircraft in real time, and carrying out the flight state classification through a pre-trained multilayer neural network model; and the current accurate working condition is determined by combining state machine conversion logic, and finally, the parameters of the feed-forward filter are dynamically adjusted through a minimum mean square algorithm to realize noise reduction. According to the method, the high-frequency component suppression capability in a multi-source coupled noise scene is effectively improved, the noise reduction efficiency is kept stable in the whole flight period, the convergence speed is improved compared with a traditional scheme, and the local optimum problem is avoided through a state self-adaptive feed-forward mechanism.

This invention discloses a superstructure design method for suppressing noise loads in aircraft under high-speed environments, relating to the field of aircraft design. The method includes: obtaining characteristic noise frequencies through simulation using a typical cavity model; introducing various designable structures such as micro-perforated plates, Helmholtz resonators, and porous materials to construct acoustic superstructures capable of suppressing or phase-shifting noise loads at these frequencies; and solidifying the acoustic superstructure assembly style through ground tests or wind tunnel tests to facilitate its physical realization. This invention addresses the problem that commonly used cavity noise reduction methods cannot be applied to high-speed cavity structures by designing and optimizing various acoustic superstructure assemblies capable of suppressing or phase-shifting noise loads to achieve optimized suppression of noise loads in aircraft cavities under high-speed environments.

The invention discloses an active noise reduction method, device and equipment for a take-off and landing point of a hovercar and a program product. The method comprises the steps that real-time noise signals and real-time environment parameters around a take-off and landing platform and real-time attitude parameters of the hovercar are acquired; performing propagation attenuation compensation on the real-time noise signal to obtain a corrected noise signal; matching in the model noise model library to obtain a corresponding rotor noise reference spectrum, an airflow noise reference spectrum and a power system noise reference spectrum; performing feature analysis on the corrected noise signal to obtain a rotor noise component, an airflow noise component and a power system noise component; predicting the change trend of the noise component through an adaptive filtering algorithm to obtain a predicted noise signal, and predicting the next airspace position of the hovercar according to the real-time attitude parameters; and generating an offset sound wave signal according to the predicted noise signal, and transmitting the offset sound wave signal to a next airspace position. The method realizes active noise reduction of the take-off and landing point of the hovercar, and can be applied to the technical field of hovercars.

The embodiment of the invention discloses an aircraft noise prediction method and device, electronic equipment and a storage medium, and relates to the technical field of aircraft aeroacoustics and computational fluid mechanics, and the method comprises the steps: obtaining a core parameter, calculating a load noise sound pressure level through a formula, and obtaining a load noise sound pressure level; calculating a thickness noise sound pressure level based on Hawkins and Lowson methods to construct a low-precision data field; sampling points are screened by adopting Latin hypercube sampling, the sampling points are calculated by combining an unsteady flow field with a sound integration method to obtain a high-precision sound pressure level, and high-precision data are obtained through flow field solution; calculating to obtain a system error of the empirical formula, and obtaining a parameter-error mapping table according to the parameter combination of the sampling points and the system error; and constructing an error prediction model by adopting a Gaussian process regression model and training, inputting parameters of a to-be-predicted point into the model to obtain an error compensation prediction value, and combining with the low-precision sound pressure level to obtain a prediction result. The problem that precision and efficiency cannot be achieved at the same time in the prior art is solved.

Vertical take-off and landing (VTOL) aircraft can provide opportunities to incorporate aerial transportation into transportation networks for cities and metropolitan areas. However, VTOL aircraft may be noisy. To accommodate this, the aircraft may utilize onboard sensors, offboard sensing, network, and predictive temporal data for noise signature mitigation. By building a composite understanding of real data offboard the aircraft, the aircraft can make adjustments to the way it is flying and verify this against a predicted noise signature (via computational methods) to reduce environmental impact. This might be realized via a change in translative speed, propeller speed, or choices in propulsor usage (e.g., a quiet propulsor vs. a high thrust, noisier propulsor). These noise mitigation actions may also be decided at the network level rather than the vehicle level to balance concerns across a city and relieve computing constraints on the aircraft.

The invention relates to an aircraft noise event identification method and device and electronic equipment, and the method comprises the steps: obtaining the noise data of a monitoring point, and the noise data comprises an A-weighting sound pressure level time sequence and 1 / 3 octave spectrum data; detecting noise events based on the A-weighted sound pressure level time sequence, and determining a starting moment, a peak moment and an ending moment of each noise event; extracting spectrum features of each noise event at a plurality of predetermined time points to form a plurality of feature vectors, wherein the plurality of predetermined time points at least comprise a peak moment and an intermediate moment determined based on a starting moment and an ending moment; respectively inputting the plurality of feature vectors into a pre-trained machine learning classification model to obtain a plurality of corresponding preliminary classification results; and determining a final classification result of the noise event according to the voting decision of the plurality of preliminary classification results. According to the method, the defect that aircraft noise and non-aircraft noise are difficult to effectively distinguish according to sound level time domain features is overcome, and the recognition accuracy and reliability are improved.

The invention discloses a propeller noise reduction design method of an eVTOL aircraft and a related device. The method comprises the steps that according to spatial design parameter data, a plurality of spatial design parameter combinations meeting the design requirements of the total lift force requirement and the structural strength requirement of the eVTOL aircraft are obtained; performing distributed propeller system-level noise simulation processing on the propeller design corresponding to each spatial design parameter combination to obtain a system-level noise simulation result corresponding to each spatial design parameter combination; obtaining a first space design parameter combination with the lowest total noise according to a system-level noise simulation result; and performing noise reduction design processing on the propeller in the first space design parameter combination to obtain a propeller noise reduction design result. In the embodiment of the invention, the rapid reconstruction of the full-aircraft noise field is realized, compared with the complete modeling, the calculation amount is obviously reduced, and the time period of the distributed propeller multi-parameter design optimization is shortened.

The invention relates to the technical field of aircraft noise reduction, in particular to a duct noise reduction method and device based on electric vertical take-off and landing design, and the method comprises the steps: determining target noise to be subjected to noise reduction of an eVTOL aircraft duct; based on the target to-be-denoised noise and a preset resonant frequency expression of a Helmholtz resonator, target Helmholtz resonator units meeting different frequency requirements are obtained, and corresponding resonant noise reduction unit parameters are determined according to the target Helmholtz resonator units; based on the resonance noise reduction unit parameters, determining a distribution proportion corresponding to the target Helmholtz resonator unit so as to distribute the target Helmholtz resonator unit in an acoustic liner of an eVTOL aircraft duct, and constructing a target sound absorber; and noise reduction is performed on blade passing noise and tubular cavity resonance noise generated in the operation process of the eVTOL aircraft based on the target sound absorber. Therefore, the problems of serious noise pollution and the like caused by the eVTOL aircraft are solved.

The invention discloses an aircraft noise load suppression superstructure design method in a high-speed environment, and relates to the field of aircraft design, and the method comprises the steps: obtaining a characteristic noise frequency through the simulation of a typical cavity model; various designable structures such as a micro-perforated plate, a Helmholtz resonator and a porous material are introduced to construct an acoustic superstructure capable of suppressing noise load or performing phase transfer, and the acoustic superstructure assembly style is solidified through methods such as ground test or wind tunnel test verification so as to facilitate materialization. In order to solve the problem that a common cavity noise reduction method cannot be applied to a high-speed cavity structure, multiple acoustic superstructure assemblies capable of suppressing noise load or performing phase transfer are designed for optimization, so that suppression optimization of the noise load of an aircraft cavity in a high-speed environment is realized.

The invention provides a stiffened plate sound insulation optimization method and device, and belongs to the technical field of aircraft noise control, and the method comprises the steps: obtaining the structure parameters of a stiffened plate, and determining the sound insulation analysis frequency of the stiffened plate; constructing a structural finite element model of the stiffened plate based on the structural parameters, determining the mesh size of the finite element model, and performing acoustic mesh division on the structural finite element model of the stiffened plate according to the mesh size; a plurality of plane wave sound sources are arranged around the structural finite element model of the stiffened plate, reverberation-noise elimination structures are arranged between the structural finite element model of the stiffened plate and the plane wave sound sources, an acoustic-solid coupling finite element matrix equation of the stiffened plate is established, and a reverberation-noise elimination sound insulation analysis model is obtained; determining a sound reduction index optimization range of the stiffened plate, and building a sound reduction index optimization objective function of the stiffened plate; sound-vibration coupling sound insulation analysis of the stiffened plate is carried out based on the reverberation-noise elimination sound insulation analysis model, meanwhile, iteration is carried out on the stiffened plate sound insulation index optimization objective function, and finally sound insulation index optimization of the stiffened wall plate is achieved.

The application discloses an aircraft APU air inlet sound source simulation device and a simulation method, and belongs to the technical field of aircraft noise testing. The aircraft APU air inlet sound source simulation device comprises a loudspeaker, a waveguide tube, a fixed connection assembly, a measurement microphone and an electrical and signal control assembly, the measurement microphone and the waveguide tube are fixed on the fixed connection assembly, the loudspeaker is fixed on the waveguide tube, one end of the electrical and signal control assembly is connected to the measurement microphone, and the other end of the electrical and signal control assembly is connected to the loudspeaker, the aircraft APU air inlet sound source simulation method comprises a method for simulating a sound mode sound source and a method for simulating wideband noise / single-frequency noise. The application is aimed at a sound mode generating device in a rectangular pipe of an APU air inlet, and the equation group formed by a response function of a control method part has great innovation.

The invention provides an acoustic metamaterial suitable for a leading edge slat, a design method and the slat, and belongs to the field of aircraft noise reduction. The acoustic metamaterial comprises a plurality of acoustic metamaterial subunits, and each subunit is composed of a micro-perforated plate and a cavity. And at least one of the plurality of subunits is linear and the internal channel of the cavity is linear, and at least one of the plurality of subunits is curved and the internal channel of the cavity is curved. The linear and curved subunits form a conformal unitary structure by an adaptive arrangement including profile adaptation within the airfoil profile and location distribution and combination within a profile perpendicular to the airfoil profile and along the leading and trailing edges. According to the invention, extremely limited space in the slat is utilized to the maximum extent through conformal design, a sound wave propagation path is prolonged at a sub-wavelength scale through linear and curved cavity channels, efficient low-frequency sound absorption is realized, broadband noise is covered through combination of multiple subunits, and the problem of insufficient low-frequency sound absorption in a slat space in a traditional scheme is effectively solved.

The invention discloses an innovative aircraft noise reduction suppression device, and particularly relates to the technical field of aircrafts, the innovative aircraft noise reduction suppression device comprises an aircraft main body, one side of the aircraft main body is provided with a control assembly, the control assembly comprises a noise reduction system, and the bottom of the aircraft main body is fixedly connected with two supports; a plurality of audio sensors are fixedly connected to the top of the aircraft body, a reverse sound wave noise reduction device is fixedly installed at the top of the aircraft body, and a height sensor is fixedly installed at the bottom of the control assembly. By monitoring the noise of the aircraft in real time and adopting a reverse sound wave noise reduction measure, noise pollution to the ground in the flight process of the aircraft can be remarkably reduced, the environmental protection performance of the aircraft can be improved, and the influence of the noise on the surrounding environment can be reduced.

The invention relates to the technical field of noise calculation and prediction, in particular to an airport aircraft noise calculation and prediction method and device. Constructing a dynamic noise source physical model, a sound source propagation attenuation physical model, a terrain influence mapping physical model and a meteorological dynamic correction physical model, and calculating the dynamic sound power level, the lateral diffraction correction factor, the geometric attenuation, the terrain attenuation and the atmospheric attenuation of the noise source according to the constructed physical models; calculating to obtain a sound pressure level prediction value of the receiving point; and the measured value and the predicted value can be subjected to space-time matching to optimize the parameters of the sound propagation path in each physical model. According to the technical scheme, the measured value and the predicted value are dynamically coupled, meanwhile, multiple complex factors are considered, the prediction accuracy in the complex environment is remarkably improved, and technical support is provided for civil aviation noise treatment.

The invention relates to an aircraft noise source positioning method and device, a medium and application, and the method comprises the steps: S1, grouping M microphone arrays to form m sub-arrays, M and m being integers; s2, aiming at each sub-array, solving sound source space distribution to obtain a sound source positioning result of each sub-array; and S3, multiplying the m sound source localization results by the m-power root of the product to obtain a result as a final sound source localization result. The method provided by the invention can be suitable for more complex and more practical microphone array distribution, and a sound source positioning result with higher precision can be obtained.

The invention provides a device and a method for measuring the sound insulation performance of a translational compressible sealing element, and belongs to the technical field of aircraft noise control. The device comprises an acoustic measurement box with an opening; the number of the horizontal sliding cover plates is two, and the two horizontal sliding cover plates are in butt joint with each other, so that a mounting surface of the sealing element is formed at the butt joint surface; the cover plate sliding restraining device is of an asymmetric U-shaped structure, the short edge of the U-shaped structure is fixed to the edge of the outer side of the opening of the acoustic measurement box, and a gap is formed between the long edge of the U-shaped structure and the edge of the opening of the acoustic measurement box; the horizontal sliding cover plate is arranged in a gap between the cover plate sliding restraint device and the acoustic measurement box; and the compression screw is installed on the cover plate sliding restraining device and used for locking the horizontal sliding cover plate, and the horizontal sliding cover plate is locked through the compression screw, so that the sealing piece is in a stable compression state.

The purpose of the present invention is to provide a flight body navigation management device capable of determining, with a small amount of calculation, a flight path in which noise does not become a problem. A navigation management device determines a flight path of a flight body and performs navigation management of the flight body. The navigation management device sets, in advance, organism noise level information indicating, for each flying body, an organism noise level that is the level of noise emitted by the flying body. The navigation management device specifies, on the basis of the body noise level of a flying body that is the subject of determination of a flight path, a flight-enabled region indicating an airspace in which the flying body can fly. The navigation management device determines a flight path of the flight body on the basis of the specified flight-enabled area.

The invention discloses an aircraft noise isoline generation method based on QAR data. The method comprises the following steps: S1, collecting and processing flight QAR data; s2, data preprocessing; s3, reconstructing a flight path; s4, calculating a thrust value; s5, correcting the noise source intensity through the correction model in combination with the airplane NDP curve and the data table, and constructing a noise source intensity model; and S6, constructing a noise model, carrying out gridding, calculating a noise value of each grid unit, carrying out correction and accumulation calculation on the noise values, and then drawing an aviation noise isoline. Compared with the prior art, the method can accurately simulate the noise levels of different flight stages based on the noise isoline calculation of the QAR data in combination with the actual operation parameters of the airplane, and has the advantages of being high in accuracy and high in reliability. A built-in noise prediction model is utilized, a space gridding technology is combined, noise intensity distribution is visually displayed in a contour line form, a noise contour line can be dynamically updated, and noise change conditions in different time periods can be reflected.

The invention discloses a supersonic aircraft noise audible visualization method and device, and relates to the field of aviation acoustics. Firstly, supersonic aircraft engine parameters are obtained; and calculating noise data generated by different parts of the supersonic aircraft engine through a data prediction algorithm. Secondly, carrying out superposition and dynamic correction on noise data of different parts; and constructing a three-dimensional model of the aircraft and the flight scene. And finally, superposing the noise test virtual scene with a real scene, testing the supersonic aircraft engine, and displaying a test result. According to the method, on the basis of the mixed reality technology, an approval person and a designer are allowed to experience personally and evaluate the noise influence in a virtual environment, so that whether the design meets regulatory requirements or not is more effectively verified, abstract noise data are converted into audible and visual immersive experience, complex noise prediction data are displayed in a real-time and three-dimensional mode, and the method is more practical. And a designer can intuitively find the noise problem.

The invention provides a laying and pressure applying device for an acoustic covering layer on the surface of an aircraft and a using method of the laying and pressure applying device, and belongs to the field of aircraft noise reduction. The plurality of positioning plates are arranged on the ring body at intervals in the circumferential direction of the ring body; the plurality of pressing blocks are arranged on the positioning plate in a one-to-one correspondence manner; a plurality of covering parts are laid on the surface of the aircraft, and the pressing blocks are tightly attached to the covering parts respectively; the ring body is tightly hooped outside the aircraft and enables the pressing blocks to press and cover the covering pieces on the surface of the aircraft. According to the invention, the ring body is arranged outside the aircraft to tightly hoop the aircraft, so that the plurality of pressing blocks simultaneously press a circle of covering part to apply pressure, the laying efficiency of the acoustic covering layer is improved, uniform pressure can be applied to the circle of covering part, and the overall laying quality and surface flatness of the covering part are ensured; and due to the characteristic that the distance between the ring bodies is flexible and adjustable, the laying device can adapt to the surfaces of aircrafts with different convex body structures, is also suitable for covering parts with different specifications and sizes, and has good universality and adaptability.

The invention provides an aircraft ground acoustic characteristic field measurement method, and belongs to the technical field of aircraft noise control, and the method comprises the steps: determining an aircraft test piece type used for ground acoustic characteristic measurement, the aircraft test piece type being a full-size aircraft or an aircraft cabin; aircraft acoustic characteristic measurement is carried out on the test piece, and the aircraft acoustic characteristic measurement comprises static sound insulation characteristic measurement, cabin reverberation time measurement, engine or power device driving measurement, airborne equipment noise measurement and sound vibration correlation measurement; and obtaining the static sound insulation characteristic of the airframe structure, the reverberation time of a cabin, the surface noise characteristic of the aircraft, the engine noise directivity, the engine noise source characteristic, the attenuation characteristic of the noise radiation value of airborne equipment along with the distance in different directions and the coupling characteristic of noise and vibration according to the measurement result of the acoustic characteristic of the aircraft. According to the method, the acoustic characteristics of the actual installation state of the airborne equipment are measured by using the full-size aircraft or the aircraft cabin, and the effectiveness of aircraft noise control measures can be verified.

The invention provides a device and method for measuring the sound insulation performance of a rotary compressible sealing element, and belongs to the technical field of aircraft noise control. The fixed cover plate is arranged on one side of the opening of the acoustic measurement box, and the mounting position of the fixed cover plate can be adjusted in the width direction of the acoustic measurement box; a rotating part outside the side wall of the rotating cover plate is rotatably arranged on the other side of the acoustic measurement box; wherein the butt joint surfaces of the fixed cover plate and the rotary cover plate are in mutually reversed L shapes, and when the rotary cover plate is matched, a butt joint gap width is formed between the fixed cover plate and the rotary cover plate. The sound insulation performance of the sealing element under different compression amount conditions can be measured, the sound insulation performance can be used as an index for evaluating the sound insulation performance of the sealing element, a basis is provided for development and improvement of the sealing element, and meanwhile support is provided for aircraft noise control.

The invention provides an airport aircraft noise prediction method fusing an ellipsoid and a nonlinear function, relates to the technical field of environment monitoring and noise control, and solves the problem that the existing method is difficult to accurately describe the limitation of the propagation process of noise in a real dynamic environment. The method comprises the following steps: acquiring aircraft track data and ground monitoring point coordinates and noise data, and converting the data into a three-dimensional rectangular coordinate system; screening effective noise events based on the noise data, and performing association matching with the track data; based on the Morse theory of a motion sound source, constructing an ellipsoid model representing the sound level contour surface of the aircraft noise; based on noise attenuation characteristics and an ellipsoid model, combining Doppler effect and atmospheric absorption attenuation, and constructing a nonlinear function of noise sound level attenuation along with distance; and carrying out parameter optimization solution by utilizing a genetic algorithm to obtain optimal parameters of the model and outputting a noise prediction result. According to the method, an existing noise prediction technology system is perfected, and the aircraft noise influence in the peripheral area of the airport can be accurately evaluated.

This invention relates to the field of low-altitude airspace management technology, specifically to a method, system, and storage medium for generating noise maps and optimizing flight paths for low-altitude aircraft. The method includes: extracting deep environmental features through an environmental feature encoding network; calculating a real-time noise map centered on the aircraft's current position using a physical-data hybrid noise prediction network, combining a physical acoustic model with neural network correction terms; generating a sequence of optimized flight actions for the future time domain based on the current noise map, aircraft state, and target point using a silent path optimization network; executing the first action in the action sequence, updating the aircraft state, and returning to perform rolling optimization for the next moment until the target point is reached. This invention, through the deep integration of a physical model and a data-driven model, ensures the correctness of acoustic principles while utilizing neural networks to compensate for complex environmental factors, achieving high-precision, real-time noise distribution prediction.

The present invention relates to the field of noise calculation and prediction technology, and specifically to a method and device for calculating and predicting airport aircraft noise. The method can obtain aircraft track data and real-time meteorological data, construct a dynamic noise source physical model, a sound source propagation attenuation physical model, a terrain influence mapping physical model, and a meteorological dynamic correction physical model. Based on the constructed physical model, the method calculates the dynamic sound power level, lateral diffraction correction factor, geometric attenuation, terrain attenuation, and atmospheric attenuation of the noise source, and then calculates the predicted sound pressure level at the receiving point. The method can also match the measured values ​​with the predicted values ​​in time and space to optimize the parameters of the sound propagation path in each physical model. The technical solution shown in the present invention dynamically couples the measured values ​​with the predicted values, and at the same time, considers multiple complex factors, significantly improving the prediction accuracy in complex environments, providing technical support for civil aviation noise control.