221 results about "Flight duration" patented technology

The invention provides a gas ultrasonic transducer fast matching method, device and equipment and a storage medium, original measurement data such as flight time are obtained by deploying an ultrasonic transducer in a gas ultrasonic flowmeter in a gas conveying pipeline, and multi-dimensional data acquisition is carried out in combination with other sensor parameters. Wavelet noise reduction and dynamic time warping processing are carried out on collected signals, signal quality and time sequence consistency are improved, time domain, frequency domain, environment and statistical features are extracted, and multi-dimensional feature vectors are formed. Modeling is carried out through a time sequence feature branch and an environment feature branch, weighted fusion is carried out by adopting an attention mechanism, and the recognition capability of the model on key features is enhanced. A machine learning model is trained based on fusion features, a multi-objective loss function and a data enhancement strategy are adopted, the prediction precision and generalization ability of the model are improved, and a compensation value is output to calibrate the original traffic in real time. According to the method, the accuracy and stability of gas flow measurement in a complex environment are effectively improved, and the method has a good engineering application prospect.

The invention discloses an unmanned aerial vehicle hybrid power system configuration optimization method based on a self-adaptive genetic algorithm, and the method comprises the following steps: S1, determining an unmanned aerial vehicle flight platform and collecting task parameters of an unmanned aerial vehicle, the task parameters of the unmanned aerial vehicle comprising flight duration, load capacity W and task environment parameters, recording power consumption of the unmanned aerial vehicle in different flight stages; s2, establishing an unmanned aerial vehicle energy consumption mathematical model, and calculating the total energy consumption of the unmanned aerial vehicle in each flight stage; s3, constructing an optimization objective function of the hybrid power supply of the unmanned aerial vehicle; and S4, performing optimization according to the target function, and outputting an optimal hydrogen fuel cell proportion to enable the target function to be minimum. By optimizing the power distribution proportion of the hydrogen fuel cell and the lithium battery and combining the efficient global optimization capability of the adaptive genetic algorithm, the power supply configuration is dynamically adjusted, and the cruising ability and the energy utilization efficiency of the unmanned aerial vehicle are remarkably improved.

The invention provides a target aircraft carbon emission determination system, and relates to the technical field of aircraft carbon emission determination. The method comprises the steps that the flight duration T of a target aircraft on a target flight path, the take-off weight of the target aircraft and the flight height and the flight speed of the target aircraft in the level flight stage on the target flight path are acquired, and the flight duration T of the target aircraft on the target flight path is calculated according to the model of the target aircraft; determining a carbon emission calculation weight corresponding to the target aircraft from a preset carbon emission calculation weight mapping table so as to determine the carbon emissions of the climbing stage, the level flight stage and the landing stage, and further obtaining the corresponding carbon emission of the target aircraft flying on the target flight path; according to the invention, the determined carbon emission corresponding to the flight of the target aircraft on the target flight path is more accurate.

Methods for Ultrasonic Flow Metering, Ultrasonic Flow Meter Calibration, and Ultrasonic Fluid Characterization. Focusing on the governing principles and equations of flow measurement for ultrasonic flow meters, using temperature referenced differential and absolute time of flight measurements to characterize fluid motion. As well as, experimental solutions to meter calibration constants, thermal expansion, concentration change in fluid validation / correction using a ratiometric approach comparing expected and measured zero flow measurements, change of fluid in process validation / correction using acoustic properties of a specific fluid, and zero flow correlations / validation based on time of flight and temperature, referenced to historically captured data and the acoustic properties of the fluid in the process.

The invention discloses a self-adaptive ultrasonic measurement method and system based on multi-channel cooperation, and relates to the technical field of ultrasonic measurement. The method comprises the following steps: collecting original flight time signals of each channel; meanwhile, environment data are collected in real time; original flight time signals are processed, effective signal arrival pre-flight time is extracted, and a fusion data set is constructed; constructing a two-dimensional sound channel spectrogram based on the multi-sound channel time sequence of the pre-flight time, and performing feature extraction based on a lightweight convolutional neural network to generate an abnormal confidence vector; analyzing the sound channel state based on the abnormal confidence vector; constructing a physical information neural network, and analyzing the corrected sound velocity value of each sound channel and the two-dimensional sound velocity field distribution on the section of the whole pipeline; training an online sequence extreme learning machine model in combination with historical measurement data; and based on the final fusion weight of each sound channel and the corresponding sound channel flow velocity, carrying out weighted fusion to generate a flow velocity optimal estimation value. And the measurement precision and robustness are improved.

The invention discloses an intelligent flight route planning method and system for a low-altitude logistics aircraft, and the method comprises the steps: obtaining the three-dimensional space map data of the current position of the aircraft, including the coordinate information of a building and a telegraph pole, and the boundary range of a no-fly zone; acquiring wind speed, wind direction and rainfall data of the current area from a meteorological data source, and calculating meteorological impact factors by combining aircraft performance parameters; dynamically adjusting the candidate flight routes according to the maneuvering characteristic parameters of the aircraft, and calculating the flight time, the energy consumption cost and the safety risk score of each route; meteorological changes in the flight process are monitored in real time, and if the meteorological conditions exceed a preset threshold value, the meteorological data are obtained again, and the meteorological influence factors are updated; and carrying out local optimization adjustment on the current flight route according to the updated meteorological influence factor, generating a new flight route segment and replacing the original segment.

The invention discloses a distributed cooperative guidance method and system for striking a maneuvering target and electronic equipment, and relates to the technical field of target guidance, and the method comprises the steps: obtaining the speed and normal overload of the maneuvering target and a current missile, and a missile-target sight angle between the current missile and the maneuvering target; based on the speed and the normal overload of the current missile and the maneuvering target, and the missile-target sight angle, determining the estimation of the residual flight time; calculating an estimation consistency error based on the estimation of the remaining flight time of the current missile and the estimation of the remaining flight time of all non-current missiles; and determining parameters of a fixed time jammer and a distributed time cooperative guidance law based on the speed, the normal overload and the estimation consistency error of the current missile, the missile-target sight angle, and the speed and the normal overload of the maneuvering target, obtaining a target fixed time jammer and a target distributed time cooperative guidance law, and guiding the current missile. According to the invention, the ambulance attack on the maneuvering target is realized.

The invention provides a flight time determination method of an ultrasonic flowmeter and related equipment, and relates to the field of ultrasonic measurement. The method comprises the following steps: acquiring uplink and downlink echo signals of the ultrasonic flowmeter, and determining uplink and downlink envelope arrays corresponding to the uplink and downlink echo signals; determining uplink and downlink characteristic waves and respective zero crossing point time of the uplink and downlink characteristic waves based on the uplink and downlink envelope arrays; according to a preset interval length and the respective zero crossing point time of the uplink characteristic wave and the downlink characteristic wave, a first envelope interval array and a second envelope interval array as well as a front offset envelope interval array and a rear offset envelope interval array are intercepted from the uplink envelope array and the downlink envelope array respectively; envelope difference arrays between the first envelope interval array and the second envelope interval array, between the first envelope interval array and the front offset envelope interval array and between the first envelope interval array and the rear offset envelope interval array are calculated, and the flight time of the ultrasonic flowmeter is determined according to the envelope difference arrays.

The motion data monitoring method includes: collecting, by an electronic device, an angular velocity signal and an acceleration signal of a user; obtaining, by the electronic device, a waveform feature of the angular velocity signal based on the angular velocity signal, and obtaining a waveform feature of the acceleration signal based on the acceleration signal; determining, by the electronic device, a gait feature of the user according to the waveform feature of the angular velocity signal and the waveform feature of the acceleration signal, where the gait feature includes a duration of flight from off-ground of a foot of the user to touching of the ground; and determining, by the electronic device, motion data according to the gait feature, where the motion data includes a jump height.

The invention provides a power transmission tower fine inspection method and system based on a vertical take-off and landing fixed-wing unmanned aerial vehicle, a storage medium and electronic equipment, and relates to the field of power transmission tower fine inspection. According to the method, by determining the ascending circling point and the descending circling point near each airport, the inspection process of the vertical take-off and landing fixed-wing unmanned aerial vehicle is divided into three stages of circling ascending, tower inspection and circling descending; the motion state of the unmanned aerial vehicle is described by adopting a Durbin vehicle model so as to accurately calculate the flight duration of the unmanned aerial vehicle, so that the inspection task can be completed within the safe flight duration, and the safety of the unmanned aerial vehicle is guaranteed. In addition, the optimal inspection path is planned for the vertical take-off and landing fixed-wing unmanned aerial vehicle under various constraint conditions, so that the information acquisition quality and efficiency of the unmanned aerial vehicle during fine inspection are effectively improved.

An echo processing method and apparatus, relating to the field of LiDAR, and used for filtering interference noise generated by a target object having high reflectivity. The method comprises: determining from a plurality of pieces of statistical data first statistical data of which the frequencies are greater than a preset threshold value, each of the plurality of pieces of statistical data comprising a plurality of times of flight and a frequency corresponding to each of the plurality of times of flight, and the statistical data being data obtained by accumulating and counting the times of flight recorded in corresponding pixels (S802); according to first position information and a preset offset value, determining interference noise, the first position information being position information of first pixels corresponding to the first statistical data in an SPAD array, the interference noise being generated by a target object having high reflectivity, and the preset offset value being a preset position offset value of the first pixels in the transverse direction of the SPAD array (S803); and filtering interference noise in the plurality of pieces of statistical data, so as to obtain target data (S805).

The invention provides an automatic gain control method and circuit of an ultrasonic flow metering device, and aims to improve the accuracy and stability of flow metering. According to the method, the gain is automatically adjusted by measuring the pulse width of an echo signal and comparing the pulse width with an expected value. The circuit comprises a transmitting circuit, an ultrasonic transducer, a variable gain amplifier, a variable threshold comparator, a zero-crossing comparator, a flight time measuring unit, a pulse width measuring unit, a time-to-digital converter and a calculation and control unit. According to the scheme, independent gain configuration of uplink and downlink flight time and a fine gain adjustment strategy based on echo amplitude change can be realized. In addition, by setting the allowable maximum pulse width change value, whether the measurement error is within a reasonable range can be automatically judged, and re-measurement can be carried out when necessary. According to the integrated design scheme, the flexibility and the response speed of measurement are improved, the signal processing flow is optimized, and an innovative solution is provided for ultrasonic flow metering.

The invention relates to a multi-unmanned aerial vehicle area coverage path rapid planning method, and relates to the field of non-electrical variable control or adjustment systems. The method comprises the following steps: using an intelligent path planning model to plan three-dimensional coordinate data corresponding to each space point of a flight area covered by a certain flight path used by a current unmanned aerial vehicle group for completing a target flight path; the flight duration corresponding to a certain flight path is intelligently predicted according to various route data and multiple flight configuration information; and taking the flight path corresponding to the minimum value in the flight durations as a planned flight path. According to the invention, the technical problems that the minimization of the total flight time and the obstacle constraint are difficult to consider, and the path planning operation cost and the time cost are high are solved; and an intelligent path planning model is adopted to traverse flight durations corresponding to flight paths simulated by the current unmanned aerial vehicle group for completing the target flight line based on multiple basic data, so that the technical problem is solved.

A system of a multi-rotor aircraft that capitalizes on the advantages of fixed wing elements combined with rotary wing structures. The fixed wing elements can help to generate lift once the aircraft is airborne and can thus reduce the need for larger lifting rotors which can allow for longer flight times and distances. Additionally, the systems disclosed herein take advantage of a partial in-wing configuration with a number of rotors to reduce the overall footprint of the vehicle while maintaining the flight efficiency that comes with combining features of fixed and rotary wing elements, and increasing operator safety by shrouding rotating parts. The unique configurations allow for a decoupling of the pitch, yaw and roll authority to reduce the complexity in control systems and improve the flight efficiency of the aircraft. Additional configurations implement the use of smaller thrust rotors that can be used to generate thrust as well as control yaw and thus counteract any remaining unbalanced torque.

The invention discloses an elastomer layer carbon fiber composite material damage positioning method based on elliptic probability fusion, which comprises the following steps: taking different sensors as excitation sources, and collecting Lamb wave signals of a plurality of sensing paths; performing continuous wavelet transform by using a complex Morlet wavelet, and extracting actually measured flight time; introducing a layered wave velocity correction model to optimize an elliptical orbit method, and calculating theoretical flight time and damage probability; introducing a dynamic short-axis optimization model to optimize a probability weighting method, and calculating a damage probability; generating prior distribution by using results calculated by an elliptical orbit method and a probability weighting method; constructing a likelihood function based on the difference between the actually measured flight time and the theoretical flight time; the posterior distribution of the damage position is obtained through the Bayesian theorem in combination with the prior distribution and the likelihood function; sampling the posterior distribution by using an adaptive MCMC algorithm, and generating a probability cloud picture of the damage position; and outputting a final imaging result of the damage position, and positioning the damage position.

The invention discloses a flight arrival time prediction method based on a flight path, belongs to the technical field of civil aviation data analysis, and aims to improve the accuracy of flight scheduling and air traffic management. Comprising the following steps: S100, preprocessing an aviation flight path data set; s200, data set feature extraction and model input: converting field features into binary representation, and generating differential features; s300, generating a data set label: calculating a prediction label through the difference between the ALDT and the TIME of the last track point; s400, model construction: a BERT encoder and a simplified decoder predict the remaining flight time of the flight; s500, model training and optimization: constructing two independent models of south wind and north wind; based on flight trajectory data, high-precision arrival time prediction is realized under the condition that external data such as weather is not introduced, and the method has wide applicability and efficient calculation performance. The model is suitable for real-time deployment of an airport management system, and provides accurate data support for flight scheduling and air traffic management.

An illustrative sensor controller includes: a transmitter, a receiver, a time-of-flight circuit, and a phase shift circuit. The transmitter is configured to provide a drive signal to an ultrasonic sending transducer to generate an acoustic burst. The receiver is configured to receive a response signal from an ultrasonic receiving transducer. The time-of-flight circuit is configured to detect an arrival of the acoustic burst in the response signal and to measure a first time of flight associated with that arrival. The phase shift circuit is configured to measure a phase shift of the acoustic burst in the response signal and to determine a second time of flight corresponding to the phase shift.

The invention relates to the field of non-destructive testing of aerospace composite materials, and provides a composite material detection method based on ultrasonic lamb wave filtering back projection imaging, which comprises the following steps: acquiring a lamb wave signal penetrating through a composite material; performing noise reduction on the Lamb wave signal to obtain an optimized Lamb wave signal; performing continuous wavelet transform on the optimized lamb wave signal to obtain a flight time parameter of the optimized lamb wave signal in the composite material; and based on the flight time parameter, in combination with a filtering back projection method reconstruction algorithm, obtaining an internal image of the composite material so as to detect the internal defect of the composite material. According to the method, the Lamb wave signal is combined with the continuous wavelet transform and the filtering back projection method, a high-quality composite material internal damage image with few artifacts can be obtained without baseline signal auxiliary imaging, and nondestructive testing can be effectively, rapidly and accurately carried out on the plate-shaped composite material.

The invention discloses a collaborative planning method for multi-unmanned aerial vehicle dynamic target positioning, and belongs to the field of unmanned aerial vehicle trajectory planning and visual perception, and the method comprises the steps: obtaining the position information of each unmanned aerial vehicle and a dynamic target in real time; modeling a multi-unmanned aerial vehicle system into a pseudo-rigid body structure, taking the geometric center of the structure as a path search node, and performing multi-unmanned aerial vehicle cooperative path search on the basis of the position information under the condition of meeting obstacle avoidance constraint and topological consistency constraint to obtain an initial trajectory of each unmanned aerial vehicle; multi-unmanned aerial vehicle combined continuous time-space trajectory optimization is carried out on the initial trajectory, the optimization target is to minimize control cost and flight time cost, and dynamic feasibility constraint, environment obstacle avoidance constraint, cluster mutual avoidance constraint and public view field constraint are met. By introducing the topological consistency constraint and the public view field constraint, mutual visibility among multiple machines is effectively maintained in a complex obstacle environment, it is guaranteed that a public view field area is not shielded, and the robustness of a dynamic target observation system is improved.

The invention relates to the technical field of electric power material storage warehouse inspection, in particular to an intelligent inspection system of an electric power material storage warehouse, which comprises a database module used for storing comprehensive information of the electric power material storage warehouse, and a model construction module used for constructing a three-dimensional space model of the electric power material storage warehouse according to the comprehensive information; according to the invention, the feature vectors of the plurality of sub-tasks in each inspection area are constructed and the plurality of sub-tasks are clustered, so that a plurality of relatively balanced task sets can be obtained, the plurality of sub-tasks can be reasonably distributed, all unmanned aerial vehicles in the inspection area can be utilized to the maximum extent, the operation efficiency of the unmanned aerial vehicles is improved, and the working efficiency of the unmanned aerial vehicles is improved. According to the method, the unmanned aerial vehicle can inspect more sub-tasks within the average flight duration, path planning can be carried out on the task set, the shooting point position path and the inspection path of the sub-tasks are balanced, and integrity and continuity of inspection data corresponding to each sub-task are facilitated while the inspection efficiency is ensured.

The invention discloses an ultrasonic guided wave damage ellipse imaging positioning method and equipment for a layer decreasing composite material laminated plate. The method comprises the following steps: S1, acquiring thickness change direction information of the laminated plate and position coordinates of an excitation transducer and a receiving transducer; s2, according to the material characteristic parameters, simulating and calculating the propagation time of ultrasonic guided waves transmitted from an excitation transducer to any point to generate a first theoretical propagation time map, and simulating and calculating the propagation time of the ultrasonic guided waves transmitted from any point to a receiving transducer to generate a second theoretical propagation time map to generate a second theoretical propagation time map; coupling influence of thickness change and material anisotropy on guided wave propagation is considered in the simulation process; s3, transmitting an ultrasonic guided wave signal, and extracting the actual flight time of a damaged wave packet; s4, calculating theoretical total propagation time, and determining a candidate area where damage exists; and S5, on the basis of repeated operation of the multiple groups of transducer pairs, taking a plurality of candidate region intersections to determine a final damage position. The objective of the invention is to solve the positioning error problem caused by the structural characteristics of a laminated plate in a traditional algorithm, and to realize more accurate damage detection and positioning.

The invention discloses a flow data processing method applied to a small-caliber pipeline, and belongs to the technical field of ultrasonic flow measurement. The invention discloses a flow data processing method applied to a small-caliber pipeline. The flow data processing method comprises smoothing processing, Kalman filtering and zero drift processing. Flight time data are obtained through a time-to-digital converter in the ultrasonic water meter, data smoothing processing and Kalman filtering are carried out on the flight time data so that measurement errors in the measurement process of the ultrasonic water meter can be reduced, and then a zero drift processing method is carried out. The external interference of the ultrasonic water meter at low flow and the instability of the water meter are reduced, so that the application range, the precision and the reliability of the measurement of the ultrasonic water meter can be effectively improved.

A vertical takeoff and landing (VTOL) aircraft includes a maximum takeoff weight (MTOW) of about 1700-kg, a cruising speed of about 80-knots equivalent airspeed (EAS) to about 100-knots EAS, a nominal range of about 300-km, a nominal flight time of about 4-hours, and at least one pair of rotors configured to provide vertical thrust. Each rotor of the at least one pair includes an about 2-meter propeller diameter, a disk loading of about 67-kg / m2 to about 110-kg / m2, and an operating speed of about 1800 rotations-per-minute (RPM) to about 2700-RPM.

The invention relates to an automatic launching system, in particular to an automatic aerial launching system and method for cluster unmanned aerial vehicles, and the system comprises a mother unmanned aerial vehicle, and a first sub unmanned aerial vehicle and a second sub unmanned aerial vehicle which are symmetrically mounted below the mother unmanned aerial vehicle. The throwing structure is arranged at the bottom of the mother unmanned aerial vehicle, when the child unmanned aerial vehicle needs to be thrown, throwing interference of the mother unmanned aerial vehicle to the child unmanned aerial vehicle can be reduced, a steering engine is arranged in the throwing structure, and the child unmanned aerial vehicle can be thrown through the left-right swinging action of the steering engine; according to the unmanned aerial vehicle launching structure, launching of the two auxiliary unmanned aerial vehicles which are arranged at the bottom of the main unmanned aerial vehicle and connected with the steering engines in a matched mode can be controlled, the overall weight of the launching structure is reduced, and the flight duration is prolonged; the undercarriages on the corresponding sides can be kept parallel to the bottom of the mother unmanned aerial vehicle after rotating, interference of the undercarriages on the launching route of the child unmanned aerial vehicle is avoided, and the launching effect of the child unmanned aerial vehicle is improved.

The invention discloses a hopping wave detection and compensation method and system of an ultrasonic flow metering device, and belongs to the technical field of ultrasonic measurement. The method comprises the following steps: under a plurality of set water temperature conditions, acquiring forward and reverse flight time of ultrasonic waves under static water flow; obtaining the water temperature of the water flow to be measured and the forward and reverse flight time of the ultrasonic wave under the water flow to be measured; the forward and reverse flight time of the ultrasonic waves under the static water flow under the water temperature condition of the to-be-measured water flow is obtained; based on the time difference of the forward and reverse flight time of the ultrasonic waves under the water flow to be measured and the static water flow under the water temperature condition of the water flow to be measured and a set time difference threshold value, whether hopping waves exist or not is judged, and the hopping wave direction is judged; on the basis of the time difference and the ultrasonic period, compensating forward and reverse flight time with hopping waves; and calculating the water flow velocity based on the compensated forward and reverse flight time. According to the invention, the accuracy of ultrasonic flow measurement and the measurement efficiency can be effectively considered.

The utility model provides a mass spectrometer which comprises a rack, and the rack is provided with a plurality of containing spaces arranged in the height direction of the rack and a vacuum cavity arranged side by side with the containing space on the bottommost layer. The flight time mass analyzer is fixed outside the rack; the vacuumizing module is at least positioned in the accommodating space at the bottommost layer and is used for vacuumizing the vacuum cavity; the shell wraps the rack and the flight time mass analyzer, and a display screen is integrated on the shell; a module assembly is further included, the module assembly at least comprises an industrial mainboard, and the industrial mainboard is located in one containing space; the industrial mainboard is used for converting signals collected by the time-of-flight mass analyzer into atlases and displaying the atlases on the display screen. The industrial mainboard for processing the signals acquired by the time-of-flight mass analyzer and the display screen are integrated on the mass spectrometer, so that a work station does not need to be additionally established to process and detect data, the integration level of the mass spectrometer is improved, and the occupied space of the mass spectrometer is reduced.

A method of in situ measurement of an acoustoelastic constant (L) of a railway rail, using an ultrasonic wedge sensor to measure a stress-free (unloaded) time-of-flight (t0) in the vertical direction of the rail. Next, a vertical load of known load value is applied to the rail. While the vertical load is applied, the ultrasonic wedge sensor is used to measure a stressed time-of-flight value. The difference between the stress-free and the stressed time-of-flight is calculated to obtain a time-of-flight difference value (Δt). Based on the load value, the stress-free time-of-flight value, and the time-of-flight difference value, the acoustoelastic constant, L, may be calculated. The wedge sensor may be further used to measure the (stressed) horizontal time of flight, and a time-of-flight difference value in the horizontal direction may be used to measure longitudinal stress.

Embodiments of the present invention provide a method for measuring the time-of-flight of a low-signal-to-noise ratio ultrasonic echo signal, relating to the field of measurement technology. The method comprises the steps of acquiring an echo signal; performing noise reduction and reconstruction on the acquired echo signal using an empirical wavelet transform to obtain a reconstructed echo signal; obtaining a preset reference echo peak value and a reconstructed echo peak value, and calculating the echo characteristic peak of the echo signal using a preset characteristic peak location algorithm; obtaining echo characteristic points of the echo; and measuring the echo time-of-flight based on the obtained echo characteristic points according to a preset measurement algorithm. This method can achieve higher-precision time-of-flight measurements of ultrasonic echo signals using a simpler calculation method.

The invention provides an earth-moon transfer orbit iterative calculation method based on earth-moon relative motion, which comprises the following steps: firstly, calculating an ideal earth-moon transfer orbit number according to the deviation between the current flight time and the theoretical time, and taking the ideal earth-moon transfer orbit number as an iterative guidance target orbit; and then, by utilizing the characteristic that the shutdown time of the rocket in the flight section can be predicted in the iterative guidance calculation process, the influence of the flight time deviation on the earth-moon transfer orbit is compensated to the number of target orbits in real time, so that correction of a guidance program angle instruction is realized, and the rocket is controlled to fly towards a more ideal earth-moon transfer orbit all the time.

The invention relates to a method for calculating the flight height of an aircraft based on a numerical weather forecast model, and the method comprises the steps: determining the flight route and the flight duration of the aircraft, and reading the topographic data on the flight route; initializing a numerical weather forecast model; operating the numerical weather forecast model to obtain a meteorological data set corresponding to the flight time of the aircraft on the flight route; calculating the meteorological data set through interpolation to obtain a meteorological data set corresponding to the flight time of the aircraft on the flight route; and calculating the flight height of the aircraft on the flight route along with the flight time change according to the meteorological data set. The precision of aircraft pressure altitude calculation is remarkably improved, and the method has important significance in improving the flight safety of civil aircrafts.