88 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 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 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 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 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.

Provided in the present application are a flight duration measurement method and a related device thereof, which are applied to a field programmable gate array, the field programmable gate array being provided with at least one carry chain. The measurement method comprises: for each of a plurality of event signals, acquiring a first transmission duration of the event signal on a carry chain within a time period between an edge instant of the event signal and an edge instant of an adjacent clock signal, the first transmission duration representing an edge delay of the event signal, and the plurality of event signals comprising a transmission signal and a reception signal; acquiring a second transmission duration of each clock signal transmitted in the carry chain, the second transmission duration representing a jitter duration of the clock signal; and compensating the edge delays and the jitter durations of the plurality of event signals to an initial flight duration, so as to obtain a first flight duration, wherein the initial flight duration is obtained on the basis of edge instants of the transmission signal and the reception signal.

The invention relates to the technical field of unmanned aerial vehicle flight plan dynamic management scheme design, in particular to a multi-type unmanned aerial vehicle town multi-scene flight plan dynamic management method and system. The method comprises the following steps: receiving and analyzing a multi-scene task request to obtain an emergency degree, a load demand, a flight duration and an execution area attribute of the multi-scene task request; on the basis of task attributes, the tasks are divided into execution waves of different priorities according to the emergency degree priority and region cooperation principle; acquiring the load state, the remaining flight duration and the position information of the unmanned aerial vehicle in real time; for each wave, dynamically matching the unmanned aerial vehicles which are compatible in load, sufficient in endurance and adjacent in position; executing tasks according to a wave priority sequence, and monitoring the state of the unmanned aerial vehicle in real time; and when triggering conditions such as insufficient endurance or a new high-emergency task occur, the execution plan is dynamically adjusted. According to the invention, through wave management and dynamic closed-loop control, efficient and reliable adaptation of multi-type unmanned aerial vehicle resources and complex task requirements of cities and towns is realized.

The time-of-flight mass spectrometer provided by the embodiment of the application comprises a flight tube, a detector and an ion focusing assembly, the detector and the ion focusing assembly are arranged in the flight tube, the ion focusing assembly is arranged at the front end of the detector, the flight tube is used for flight control of ions, the ion focusing assembly is used for focusing of the ions after flight, and the detector is used for detection of the focused ions. Through focusing of the ions after flight, the number of ions detected by the detector can be improved, and the sensitivity of the time-of-flight mass spectrometer is higher.

The embodiment of the invention provides a bolt residual axial force determination method and device, electronic equipment, a medium and a product, and the method comprises the steps that a to-be-tested bolt in a first installation state is tested, the flight time difference variable quantity caused by axial force attenuation is obtained, and the first installation state represents that the bolt is in a yield section; determining an axial force attenuation based on an axial force attenuation parameter of the to-be-tested bolt in a second installation state and a flight time difference variation, the second installation state representing that the bolt is in an elastic section; and determining the residual axial force of the to-be-tested bolt according to the axial force attenuation. According to the method provided by the embodiment of the invention, the residual axial force can be calculated more accurately based on the axial force attenuation parameter of the bolt. And according to the scheme provided by the invention, bolts do not need to be disassembled in the test process, so that the continuity and completeness of the test are ensured.

The invention relates to an ultrasonic wave flight time measuring method and device, electronic equipment and a readable medium, and the method comprises the steps: applying a driving signal to a first transducer, enabling the first transducer to emit ultrasonic waves, and starting a timer to collect a transmitted waveform sequence; calculating the minimum flight time as a coarse value based on the distance between the transducers and the resultant velocity of the sound velocity and the wind speed; after the time is over, collecting a receiving waveform sequence of which the count value and the amplitude are within a preset range; transmitting and receiving waveforms are analyzed through waveform matching, a time offset value is obtained, and a coarse value is corrected to obtain first absolute flight time; switching a transmitting-receiving transducer, and similarly obtaining second absolute flight time; and matching the two received waveforms, calculating the offset time for correcting the difference between the two minimum flight times, and finally obtaining the high-precision relative flight time. The problem that the measurement precision and the operation efficiency cannot be considered when the ultrasonic flight time is measured is solved.

The invention relates to a flight time difference calculation method of an ultrasonic flowmeter and related equipment, and the method comprises the steps: respectively dividing an uplink echo signal and a downlink echo signal to obtain a plurality of continuous local waves, extracting a characteristic value representing the amplitude range of the local wave from each local wave, and calculating the flight time difference of the ultrasonic flowmeter according to the characteristic value; sorting the feature values according to the sampling time of the local waves to obtain an uplink feature value sequence and a downlink feature value sequence; in a preset integer local wave shift number interval, for each preset shift number, performing translation alignment on the downlink characteristic value sequence relative to the uplink characteristic value sequence according to the preset shift number to obtain a downlink characteristic value sub-sequence; and calculating a matching difference degree between each downlink eigenvalue sub-sequence and the uplink eigenvalue sequence, determining a target local wave shift number according to the matching difference degree, and determining a flight time difference according to the target local wave shift number. According to the method, the calculation accuracy of the flight time difference is remarkably improved, and the measurement accuracy of the fluid flow is ensured.

The application discloses a speed-restricted separation method of a solid rocket engine-boosted vehicle, which comprises the following steps: S1, determining a first maximum speed threshold Vmax1, a second maximum speed threshold Vmax2 and a latest separation time Tmax; S2, comparing a full-missile flight speed Vt0 at the end of engine operation with the first maximum speed threshold Vmax1, and separating the vehicle in time at the end of engine operation when Vt0Vmax1, entering step S3; S3, delaying the separation of the vehicle after the end of engine operation; the specific method of delaying the separation is as follows: if the full-missile flight time is less than Tmax, comparing a full-missile flight speed Vt at the current time with Vmax2, separating the vehicle when VtVmax2, and continuing the full-missile flight when Vt≥Vmax2; if the full-missile flight time is greater than or equal to Tmax, separating the vehicle. The application can judge the separation time according to the real-time flight speed, provide a suitable speed after the separation of the main stage, and ensure the flight control requirements and speed requirements of the main stage after the separation.

The utility model belongs to the technical field of unmanned aerial vehicles, and particularly relates to an unmanned aerial vehicle fuselage which comprises a fuselage body, the fuselage body comprises a first frame and a second frame, the first frame and the second frame are both triangular frames, and the first frame and the second frame are fixedly connected and arranged in the axial direction of the fuselage body. The end corner of the first frame and the end corner of the second frame are arranged in a staggered mode in the direction perpendicular to the axis of the fuselage. According to the structure, the first frame and the second frame are triangular, due to the stability of the triangles, the fuselage of the unmanned aerial vehicle has stability, the first frame and the second frame are arranged in a staggered mode, and six small triangular structures are formed at the six corners, so that the fuselage is more stable and firmer; moreover, parts are convenient to replace, the fuselage is simple in structure, easy to process and mount and light in weight, and the flight time of the unmanned aerial vehicle is prolonged.

The invention discloses an intelligent dispatching method for flight departure / departure moments. The method comprises the following steps: establishing a moment distribution calculation model; establishing a flight duration calculation model; judging whether the takeoff moment and the landing moment reported by the airline company meet the flight duration requirement specified by the civil aviation bureau; whether the take-off moment or the landing moment reported by the airline company has idle moments at the take-off airport or the landing airport or not is judged; calculating a suggested moment when the landing moment declared by the airline company cannot be allocated; calculating a suggested moment when the takeoff moment declared by the airline company cannot be allocated; calculating suggested moments when the takeoff moment and the landing moment declared by the airline company cannot be allocated; an airline company calculation result is fed back; and airline company result confirmation. According to the method, the availability can be analyzed by using the preset model when the airline declares the start / fall moment of the flight; and if no time slot exists at the original moment, the adjacent moments conforming to airport flow tolerance and civil aviation duration are automatically recommended according to an airline acceptance range, so that the airline can conveniently reprogram a flight plan.

The invention discloses a two-way rocket launching window searching method, system and device and a medium, and the method comprises the steps: rapidly calculating two nearest launching windows of an ascending orbit and a descending orbit of a rocket according to the attributes of a central body, target orbit plane parameters, the geographic coordinates of launching points and the flight duration of the rocket; according to the method, the problem is converted into numerical calculation based on space geometry, the crossing moment is directly solved by using the geometrical relationship between the normal vector of the orbital plane and the inertial position vector of the launching point location and adopting efficient numerical methods such as dichotomy and the like, and complex dynamic iteration is avoided. According to the method, the calculated amount is greatly reduced, rapid searching of the launching window is achieved, the method is suitable for an interstellar detection task scene needing rapid response or multiple times of calculation, and the real-time performance of task planning is remarkably improved.

To reduce variation of a measurement result by aligning a mass resolution of a plurality of devices.SOLUTION: In an embodiment of a TOFMS according to the present invention, the TOFMS includes a measurement part (1) containing: each flight magnetic field formation part that forms a magnetic field for flying an ion into a flight space (153, 154, and 155); and each ion acceleration part (151 and 152) that accelerates the ion as a measurement object and feeds it into the flight space. The TOFMS comprises: a control part (3) that repeatedly executes a measurement to a predetermined sample while changing a voltage applied to an electrode contained in the measurement part, and operates the measurement part so as to calculates a mass resolution on the basis of the measurement result in each measurement; an approximate calculation part (3) that calculates an approximate for approximating a relation of them on the basis of data of a plurality of pairs of an application voltage to the electrode and a resolution corresponded to them, obtained under a control by the control part; and a voltage determination part (3) that calculates a voltage value corresponded to a target value of the mass resolution by using the approximate, and determines the voltage value as an application voltage to the electrode in the device.SELECTED DRAWING: Figure 1

The invention discloses a water outlet control method, system and equipment, and relates to the technical field of water outlet control, and the method comprises the steps: after a water supply device is started, signals are transmitted and received alternately based on two probe cores, and a first echo signal and a second echo signal of a container upper edge and a container liquid level on a container tray are obtained in real time; performing data intensity judgment based on the first echo signal and the second echo signal, and performing screening to obtain an effective echo signal; performing preprocessing based on the effective echo signal to obtain an upper edge envelope signal and a liquid surface envelope signal; acquiring corresponding first flight time and second flight time based on the upper edge envelope signal and the liquid surface envelope signal; obtaining a height difference between the upper edge of the container and the liquid level of the container based on the first flight time and the second flight time; starting and stopping of the water supply device are controlled based on the height difference; acquiring pressure data of the container tray in real time, and controlling start and stop of the water supply device based on the pressure data. Accurate recognition of the container and the water adding state is achieved, and the water outlet control precision is improved.

Method, system, and user terminal are disclosed for splicing a flight route splicing m. Various embodiments may includes: obtaining a first flight route and a second flight route of an unmanned aerial vehicle; obtaining a first estimated flight duration of the UAV required to complete the first flight route and the second flight route; obtaining the preset duration of the unmanned aerial vehicle; splicing the first flight route and the second flight route when the preset duration is greater than the first estimated flight duration. it improves the task execution efficiency of the unmanned aerial vehicle and saving the unmanned aerial vehicle resources and time, and further providing richer choices for users and providing more space for customized flight route planning for users.

The invention provides a Doppler effect elimination and fusion positioning method for a high-speed train, and the method comprises the steps: deducing a mathematical expression of a distance measurement error caused by a Doppler effect based on a bidirectional time of flight (ToF) method; secondly, using UWB / IMU time sequence prior to eliminate distance measurement error deviation, and analyzing residual error variance; and finally, constructing a self-adaptive UWB / IMU fusion positioning framework, deducing a UWB measurement equation random item closed expression, and realizing Doppler effect elimination and fusion model parameter self-adaptive adjustment. According to the method, the precision of UWB / IMU fusion positioning is remarkably improved, and the influence of the Doppler effect on the bidirectional ToF ranging and fusion positioning model is overcome.

This invention provides an information push method, electronic device, and storage medium in a network-free state, relating to the field of information push technology. The method includes: acquiring each preset location on the flight path corresponding to a target flight mission; acquiring preset information corresponding to each preset location to obtain a preset information list corresponding to the preset location list; each preset location corresponds to a sub-region; pushing the preset information corresponding to the sub-region to the display module of the target electronic device for display; if the positioning coordinates corresponding to the target electronic device cannot be acquired, then based on the flight duration of the aircraft corresponding to the flight mission and the current time, pushing the preset information in the TA to the display module of the target electronic device; this invention enables the target electronic device to push and display corresponding information when it flies to the corresponding preset location in a network-free state, thereby preventing users from missing important information related to their trip.

The invention relates to the technical field of unmanned aerial vehicle path planning, in particular to a transformer substation unmanned aerial vehicle inspection path planning method and system based on a road network space, and the method comprises the steps: determining an inspection target of an unmanned aerial vehicle for transformer substation inspection, and dividing the inspection target into a forced constraint layer and a quality optimization layer; determining a first inspection point in the flight direction forced constraint layer of the unmanned aerial vehicle and the data acquisition time of the related data of the current inspection point, comparing the data acquisition time and the flight time used by the first inspection point with corresponding thresholds, and determining whether to construct a flight correction model of the unmanned aerial vehicle based on a comparison result; and determining and adjusting the flight time of other inspection points of the flight direction forced constraint layer in sequence based on the corrected flight parameters of the unmanned aerial vehicle. According to the closed-loop feedback system based on the shared memory, real-time linkage of path planning, image recognition and path dynamic correction is achieved, the unmanned aerial vehicle can adjust the inspection path in real time according to the image recognition result, and the inspection efficiency and quality are improved.

The invention discloses an ultrasonic detection method and system for gas flow velocity and concentration, and relates to the field of semiconductor gas concentration detection.The ultrasonic detection method comprises the following steps that a first ultrasonic transducer and a second ultrasonic transducer are arranged on a to-be-detected gas pipeline; the first transducer is controlled to emit ultrasonic waves, the ultrasonic waves are received by the second transducer, and first flight time is obtained; the second transducer is controlled to transmit ultrasonic waves, the ultrasonic waves are received by the first transducer, and second flight time is obtained; on the basis of the mathematical relationship between the first flight time and the second flight time, the average flow velocity of the gas in the gas pipeline is calculated; calculating the sound velocity in the gas by using the obtained average flow velocity of the gas, the first flight time or the second flight time, the propagation path length and the non-zero included angle; and determining the concentration of the gas according to the calculated sound velocity of the gas and the physical property parameters of the gas. By adopting the scheme, the flow velocity and the concentration of the gas can be synchronously measured in a high-precision and non-contact manner through a single technical means.

The invention discloses a parcel delivery method, device and equipment based on an unmanned aerial vehicle logistics system and a storage medium, the unmanned aerial vehicle logistics system comprises at least one group of heterogeneous unmanned aerial vehicles and a plurality of delivery sites, and the method comprises the following steps: constructing a task scheduling model; the task scheduling model takes minimization of the maximum completion time of all parcel delivery tasks as a target function, and constructs a multi-dimensional constraint condition set based on the isomerism, flight time limitation and loading capacity constraint of the unmanned aerial vehicle; solving the task scheduling model by adopting a genetic algorithm to generate a high-quality task scheduling scheme meeting the multi-dimensional constraint condition set; and controlling at least one group of heterogeneous unmanned aerial vehicles to execute package loading, path planning and site access according to the task scheduling scheme, and completing the distribution task. Therefore, through mutual cooperation of the task scheduling model and the genetic algorithm, a targeted high-quality task scheduling scheme is provided according to actual conditions, so that the resource utilization rate and the overall distribution efficiency are improved.

The invention relates to a method and an apparatus for analyzing a sample material on a sample carrier, comprising the following modes of operation: providing a time-of-flight mass analyzer having an ion generating unit, an ion generation unit having a mount for the sample carrier, an ion receiver, a flight path defining a longest flight time therebetween, an ion selector disposed along the path, and a clock generator for repeatedly triggering an ion generation pulse at the sample carrier and a subsequent pulse for accelerating ion species into the flight path; defining one or more mass-to-charge ratio (m / z) ranges, each range upper limit corresponding to a flight time shorter than the longest flight time; selecting the cycle period of the ion generation pulse so that the continuous pulse interval is shorter than the longest flight time but longer than the acceleration time; and using the mass analyzer, selecting a pulse cycle mode and an ion selector to analyze the sample material.

The invention particularly relates to a descending path construction method for continuous descending operation of a large passenger plane, which comprises the following steps of: according to speed and height information of a cruising stage of the plane, waypoint speed constraint and height constraint information of a descending stage and speed and height information of a descending end point, combining a performance database of the plane in different flight modes; and constructing an optimal slow vehicle descending path by using a dynamic programming algorithm. According to the method, the slow vehicle descending path which meets performance requirements and air route constraints and is minimum in oil consumption or shortest in flight time can be constructed, and the method is of great significance to reduction of the operation cost of the civil aviation passenger plane and reduction of pollutant emission.

A system for synchronizing communications in a radio ranging process involves transmitting calibration signals according to a predetermined schedule of nominal transmission times. Timing offsets are determined. A start time is determined for a transmission of a ranging signal. The start time is earlier than a nominal start time of the ranging signal by at least the largest timing offset. Another system for synchronization involves a radio device transmitting a calibration signal to a second radio device and receiving a calibration response signal from the second radio device. A time-of-flight value is determined in dependence on a time of departure of the calibration signal and a time of arrival of the calibration response signal. A ranging signal is transmitted at a time determined in dependence on the determined time-of-flight value. A ranging response signal is received and processed to determine a range value.

The invention discloses a method for determining the economic flight speed of an unmanned aerial vehicle, and relates to the technical field of unmanned aerial vehicles. The method comprises the steps of 1, establishing an air resistance energy consumption model; 2, establishing a recoil gravity power consumption model; 3, establishing a hovering delivery energy consumption model; 4, establishing a flight kinetic energy / potential energy loss model; 5, establishing an electric energy-mechanical energy conversion loss model of the unmanned aerial vehicle; step 6, establishing an airborne electrical equipment consumption model during constant-speed flight; 7, establishing an energy consumption model of the unmanned aerial vehicle flying from the node i to the node j and completing cargo delivery; and 8, establishing an economic flight speed model under the condition that the load of the unmanned aerial vehicle is f. The method breaks through the limitation that traditional path planning only pays attention to the path length or the flight time, takes the economic flight speed as an optimization target, further reduces the energy consumption, and has remarkable technical innovation.

Exemplary system, method and computer-accessible medium for selecting at least one location of (i) at least one receiver or transceiver or (ii) at least one transmitter or transceiver can be provided. For example, it is possible to facilitate a receipt, from the at least one transmitter or transceiver, of a plurality of signals by the receiver(s) or transceiver(s). Each of the signals has a multipath component. Then, it is possible to determine time of flight (ToF) information and angle of arrival (AoA) information of the multipath components present in the signals. Further, it is possible to determine one or more possible locations of (i) the receiver(s) or transceiver(s) or (ii) the transmitter(s) or transceiver(s) based on the ToF information, the AoA information, and a model of physical surroundings. The location(s) of (i) the receiver(s) or transceiver(s), or (ii) the transmitter(s) or transceiver(s) can be selected based on the one or more possible locations.

The invention discloses an unmanned aerial vehicle remaining endurance prediction method and device, electronic equipment, a medium and a product. The method comprises the following steps: when an unmanned aerial vehicle runs, acquiring an unmanned aerial vehicle equipment state, running environment data, unmanned aerial vehicle flight data, current air density, a wind speed correction coefficient, a battery aging correction coefficient and a battery temperature correction coefficient in real time; calculating the total power consumption of the whole machine in the current flight state; correcting the total power consumption to obtain corrected average power consumption for endurance evaluation; calculating the current effective residual electric quantity; and calculating the theoretical residual flight duration without considering the return flight constraint in the current flight state. The method can solve the problems of large prediction error and low reliability caused by neglecting the dynamic flight environment and the real-time state of the battery.

A scheme of the TOFMS of the present application has: a flight space forming electrode (11, 12) that forms a flight space in which ions are separated according to m / z; an ion detection section (13) that detects ions flying in the flight space; a voltage switching section (4, 2) that switches a voltage applied to the flight space forming electrode from a first voltage that makes ions of a first polarity fly to a second voltage that makes ions of a second polarity fly at a prescribed switching timing; an ion information acquisition section (30, 32) that obtains a flight time or m / z of the ions of the second polarity based on a detection result of the ions of the second polarity obtained by the ion detection section after the voltage is switched by the voltage switching section; a correction information storage section (31) that stores correction information corresponding to an elapsed time from the switching timing and information related to a deviation of the flight time or m / z; and a correction section (33) that corrects the flight time or m / z according to the elapsed time from the switching timing using the correction information stored in the correction information storage section.