260 results about "Flight time" patented technology

The invention discloses an airship type unmanned aerial vehicle inspection system and inspection method, and belongs to the field of inspection unmanned aerial vehicles. The system comprises a laser radar, an image acquisition device, an airship capsule filled with helium, a standby safety airbag, a communication module and a ground control center, in the method, the ground control center sets an inspection path and issues the inspection path, and the unmanned aerial vehicle flies according to a preset path. During fault detection, the high-definition camera collects images to recognize line cracks and broken strands, the thermal infrared imager monitors the joint temperature, the gas sensor detects abnormal gas, and multi-source data fusion assists in defect positioning. The routing inspection takes a starting point-terminal point connecting line of a power transmission line as a reference, identifies main obstacles and surrounding nodes to perform global planning, performs key routing inspection on a risk area in combination with historical data, and initializes and guides a flight direction through a Q value to reduce invalid exploration. The four-rotor unmanned aerial vehicle solves the problems of short flight time and poor stability of a four-rotor unmanned aerial vehicle, improves the inspection stability and cruising ability, and improves the inspection efficiency of a power transmission line and the reliability of a power system.

To provide a new technique for dynamically and efficiently operating an arrival and departure field when operating the number of unmanned aircrafts exceeding the number of simultaneous arrivals and departures at the arrival and departure field.SOLUTION: A transport control system causes a plurality of unmanned aerial vehicles to sequentially fly back and forth from a predetermined transport start point along flight routes set for the respective unmanned aerial vehicles, thereby transporting the unmanned aerial vehicles to respective given transport destinations. The transport control system repeatedly executes prediction of a predicted return time of each unmanned aerial vehicle to the transport starting point, and adjusts a flight time along a flight route of an unmanned aerial vehicle that satisfies a predetermined congestion condition based on a temporal relationship of the predicted return time, thereby adjusting the return time and adjusting the congestion.SELECTED DRAWING: Figure 3

The invention discloses a low-altitude unmanned aerial vehicle path planning method and system based on deep learning. The method comprises the following steps: acquiring flight state information and environment data of an unmanned aerial vehicle in real time; task priority calculation: calculating the task priority according to the unmanned aerial vehicle state information in combination with the task emergency degree and the task type; based on collaborative decision-making of deep reinforcement learning, decision-making is carried out on task allocation and flight paths through a deep learning algorithm in combination with unmanned aerial vehicle state and environment data and task priority information; planning an optimal flight path for the unmanned aerial vehicle according to the intelligent decision comprehensive environment data; the flight path is a discrete point set path planning target which minimizes the flight time on the premise of avoiding a no-fly zone and an obstacle; and in the process of executing the path planning by the unmanned aerial vehicle, when abnormality is detected, making a decision again, and performing path planning again until the unmanned aerial vehicle finally reaches the target position point.

The invention relates to a resource orchestration method and device for a collaborative network, equipment, a storage medium and a program product. Comprising the following steps: constructing an optimization model taking maximization of total satisfaction, minimization of service duration and minimization of energy consumption of an unmanned aerial vehicle as targets; the total satisfaction is the sum of the satisfaction of each target area, the service duration is the sum of the sensing duration, the transmission duration, the calculation time and the flight time corresponding to each target area, and the energy consumption of the unmanned aerial vehicle is the sum of the sensing energy consumption, the transmission energy consumption, the flight energy consumption and the hovering energy consumption corresponding to each target area; solving the optimization model under the constraint of a preset constraint condition to obtain a computing resource allocation strategy and a sensing communication strategy; comprise computing time, sensing duration, service sequences, flight heights and transmission power of various computing resources. By adopting the method, multi-target collaborative optimization is realized, namely, the service duration and the energy consumption of the unmanned aerial vehicle are minimized while the total satisfaction degree of the system is maximized.

The application discloses a design method of a net-catch load effective capture caliber, which comprises the following steps: acquiring multi-directional contour size parameters of a waste satellite; generating a position aiming parameter of an aircraft relative to the waste satellite when launching the net-catch load based on the multi-directional contour size parameters; acquiring an installation position parameter of the net-catch load relative to the mass center of the aircraft; estimating a capture flight time t net and a deployment efficiency η of the net-catch load; and calculating an effective capture caliber R of the net-catch load based on the multi-directional contour size parameters of the waste satellite, the position aiming parameter of the aircraft relative to the waste satellite when launching the net-catch load, the installation position parameter, the capture flight time and the deployment efficiency. net The effective capture caliber of the net-catch load can be designed according to the contour size of the waste satellite, the position aiming parameter of launching, the installation position of the load, the capture flight time and the deployment efficiency, and reliable capture of waste satellites with different contour features is realized.

The invention provides a water tank icing prediction method for a flight device, a computer device and a computer readable storage medium, and the method comprises the steps: intercepting a cross section of a water tank in the flight device from a three-dimensional geometric model of the flight device, stretching the cross section according to the volume of the water tank, and forming a preset three-dimensional water tank model, stretching according to a preset three-dimensional water tank model to generate a preset computational domain; generating a preset grid according to a preset computational domain; configuring an airflow model, a water phase change model and a thin-wall heat conduction model for the preset computational domain, and setting boundary conditions for the preset computational domain to form an icing prediction model; simulating the icing prediction model according to the numerical value of the preset working condition matrix to obtain icing prediction data; and judging the icing prediction data according to a preset grading system, generating a safety boundary curve graph, and outputting flight time suggestion information. The water tank structure is simplified, a large time step length is allowed to be adopted in the simulation process, and therefore the calculation efficiency is improved.

The invention discloses a railway vehicle impact positioning method, device and equipment and a medium, and relates to the technical field of computers, and the method comprises the steps: obtaining a guided wave signal outputted by each piezoelectric sensor when a to-be-detected composite material of a railway vehicle is impacted; the piezoelectric sensor is arranged on the surface of the composite material to be detected; constructing a positioning model based on the installation position of each piezoelectric sensor and the flight time of the guided wave signal, and determining an error function of the positioning model; the function is used for quantifying the deviation between the theoretical distance and the actual distance; the theoretical distance is obtained based on the assumed coordinate of the potential impact point and the mounting position of the piezoelectric sensor, and the actual distance is obtained based on the flight time and the propagation speed of the guided wave signal; and outputting the optimal coordinate estimation of the potential impact point and the optimal propagation speed estimation of the guided wave signal by minimizing the error function. According to the invention, the inherent error caused by the constant wave velocity is avoided; the engineering implementation cost is reduced; the positioning precision is obviously improved; and the real-time performance of impact positioning is ensured.

The invention discloses an unmanned aerial vehicle side wing unfolding driving mechanism with a locking function. The locking function module is designed in the space envelope of the unfolding function module, the two functions of unfolding and locking of the side wings are achieved at the same time in the limited space, and the situation that the aerodynamic configuration of the unmanned aerial vehicle is damaged due to the fact that the wing face protruding out of the mechanism is too large is avoided; the aerodynamic resistance in the flight process of the unmanned aerial vehicle is reduced, the lift-drag ratio of the aircraft is improved, and the flight time is prolonged. And the sizes of fit clearances between the locking clamping blocks and the right hinge in the two groups of locking function modules are different. The large gap ensures that the clamping block can be locked in, and the small gap ensures that the clamping block can be locked tightly. The two gaps are matched and complemented with each other, and the reliability of the locking function of the mechanism is improved. According to the invention, the output torque of the unfolding function module is improved by adopting a double-torsion-spring parallel connection mode, and the problems that the axial space occupation of the mechanism is too large, the flight resistance is increased and the lift-drag ratio of the aircraft is reduced due to the adoption of a large-wire-diameter and single-torsion-spring scheme are avoided.

The invention relates to the technical field of meteorological data analysis, and provides a Nevzorov water content probe data quality control processing method and system based on airborne in-situ observation, and the method comprises the steps: obtaining airborne in-situ observation data, and carrying out the classification based on collection sortie association information, and obtaining an initial data set; generating an observation data set through sortie time threshold combination; a quality control data set is obtained through data quality control processing of a Nevzorov probe; extracting environment and position characteristic parameters, executing cloud-entering multi-condition conjoint analysis, and screening effective observation data; constructing a baseline correction reference condition to complete water content data deviation correction, and performing grading particle spectrum number analysis based on corrected data to obtain particle spectrum distribution information; according to the method, an inversion model is constructed based on the incidence relation of the particle spectrum and the liquid water content, liquid water content inversion optimization is completed through feature matching dynamic adjustment parameters, an inversion optimization result is generated, the reliability of airborne probe observation data and the liquid water content inversion precision are improved, and accurate data support is provided for cloud microphysical research.

The invention discloses a composite material structure impact two-stage imaging positioning method based on dual-frequency time difference, and belongs to the technical field of aerospace structure health monitoring. Extracting two first narrow-band impact signals with different frequencies of the piezoelectric sensor, and calculating a theoretical flight time difference from each grid unit to the central piezoelectric sensor; during actual impact positioning, calculating an actual flight time difference of second narrowband impact signals with the same frequency collected by the central sensor; obtaining a first pixel value of each grid unit in the monitoring area according to the theoretical flight time difference and the actual flight time difference, and realizing primary imaging; and searching a grid unit with a high pixel value in the primary imaging result, performing time reversal focusing on a second narrow-band impact signal of each piezoelectric sensor to obtain a second pixel value of each grid unit, realizing secondary imaging, and obtaining an impact positioning result. According to the invention, the impact positioning of the light-weight large-area composite material structure is realized by using fewer sensors.

The application discloses a kind of based on flight flow control restriction information autonomous release sequencing method and system, method includes: flow control restriction information is structured as including time, waypoint and digitalization constraint of traffic capacity and storage;According to the constraint screening affected flight, and it is divided into A class flight with fixed calculation takeoff time and B class flight without fixed time;With A class flight time as reference, under multiple constraints such as meeting calculation wheel block time and flow control capacity, dynamically calculate distribution suggestion takeoff time slot for B class flight;Finally, generate flight autonomous release sequencing sequence and output are integrated.This application method and system realize the change from artificial experience decision to intelligent automatic calculation in release sequencing, while guaranteeing instruction compliance, significantly improve sequencing efficiency, rationality and system response dynamic change robustness.

The application provides a UAV trajectory design method and system under the constraint of a fixed-point cruise task, which comprises the following steps: acquiring a communication channel parameter of a UAV and a ground user and a cruise point position, and establishing an original trajectory optimization problem for maximizing communication throughput; mapping a time domain problem to a path domain to obtain a joint optimization problem in the path domain; constructing an artificial potential field with the ground user as the center, and equivalently taking the cruise point as a fixed pulley node; converting the joint optimization problem in the path domain into an equivalent mechanical problem of minimizing the total potential energy of a variable density rope in the artificial potential field; based on the equivalence between the joint optimization problem in the path domain and the equivalent mechanical problem, solving a segmented trajectory analytical expression; and according to whether the flight time is sufficient, constructing a rope optimal configuration and restoring a continuous trajectory of the UAV, respectively. The application solves the trajectory design demand of the UAV under the constraint of the fixed-point cruise task to realize the optimization of communication performance.

The invention provides a spherical joint accelerated life test design method and device, and the method comprises the steps: determining the accelerated life test acceleration stress according to the actual use condition of a spherical joint; adopting a finite element analysis method to obtain a stress spectrum of the spherical joint of the pipeline system under the load corresponding to the preset flight profile; integrating and converting the stress spectrum into an equivalent stress spectrum by adopting a rain flow counting method and a Goodman formula; according to the equivalent stress spectrum, the S-N curve, the Miner damage accumulation theory and the preset total number of flight times, the number of cycles corresponding to the accelerated stress of the accelerated life test is obtained; and determining a test scheme according to the accelerated stress and cycle index of the accelerated life test. The test frequency is reduced by amplifying the stress of the spherical joint under the use condition of an aircraft.

The invention relates to an unmanned aerial vehicle ejection control method based on plasma pneumatic gain and a medium, and relates to the technical field of unmanned aerial vehicle system design and launching. In the scheme, the current flight stage of the unmanned aerial vehicle is judged, in response to a judgment result of an inertia climbing stage, an expected pitch angle is set as a catapult pitch angle, a leading edge DBD is started at rated power, and meanwhile, a trailing edge DBD is kept closed; and in response to the judgment result of the unpowered glide / glide stage, controlling the unmanned aerial vehicle at the highest lift-drag ratio, starting the trailing edge DBD at the rated power, calculating the difference value obtained by subtracting the reference angle of attack from the real-time angle of attack in real time, judging whether the difference value is greater than a preset first threshold value or not, and if so, starting the leading edge DBD at the maximum power until the difference value is not greater than the preset first threshold value. Compared with the prior art, the terminal height is increased or the endurance is prolonged, and the flight performance of the ejection unmanned aerial vehicle is improved.

The application discloses a method for unmanned aerial vehicle assisted thermal sensing MEC network task scheduling and resource allocation. In the case of considering CPU thermal constraints, the cruising time of the unmanned aerial vehicle is minimized by jointly optimizing user admission policy, task scheduling, unmanned aerial vehicle hovering trajectory, flight time, and computing and communication resource allocation. The optimization problem is further decomposed into three sub-problems and iteratively processed in order. Simulation results show that the method has good performance improvement effect compared with other algorithms.

The invention discloses a leg identification and vertical speed stable switching correction method, and belongs to the technical field of aerospace flight control. The method comprises the following steps of: firstly, judging a current flight segment of an airplane and a flight segment switching opportunity in real time by integrating multiple criteria such as on-way projection, semi-plane, flight path angle consistency and a remaining time threshold; then, the vertical speed of the target is dynamically calculated based on the real-time height difference and the remaining flight time, amplitude limiting and rate smoothing are conducted on the vertical speed of the target, and continuous transition of the vertical speed in the flight segment switching process is achieved; and finally, dynamically correcting the vertical speed of the target according to the real-time flight state, so that the aircraft accurately meets the height requirement at the target waypoint. The method has the advantages of being high in leg recognition precision, stable in vertical speed switching, high in dynamic correction capacity, simple in algorithm, easy to implement and the like, and the flight safety and comfort can be effectively improved.

The application provides a method for measuring liquid level in a container based on DTOF, a DTOF module and the container. The container is provided with the DTOF module. The method for measuring liquid level in the container comprises the following steps: emitting detection light to the container; receiving reflected light reflected by the detection light; obtaining total flight time according to the emission time of the detection light and the receiving time of the reflected light; calculating target distance according to the total flight time, light speed and the refractive index of the medium through which the detection light is transmitted to the current liquid surface of the container; determining the liquid level in the container according to the target distance and notifying the user. In addition, the application also provides a device for measuring liquid level in a container based on DTOF and the container. The technical scheme of the application effectively solves the problem that the liquid level in the container cannot be accurately measured.

The invention discloses an unmanned aerial vehicle route planning method based on channel engineering and related equipment, and the method comprises the steps: generating a strip-shaped inspection region according to spatial position information, further generating a plurality of parallel routes, connecting the parallel routes into a continuous flight route, and carrying out the optimization; calculating available flight time of the unmanned aerial vehicle according to battery parameter information and power consumption parameter information of the unmanned aerial vehicle, setting a plurality of segmentation points on a continuous flight route, segmenting the continuous flight route into a plurality of safe sub-flight segments, and setting safe landing preparation points; and according to the orthoimage and the three-dimensional point cloud data of the strip-shaped inspection area, constructing a three-dimensional environment model of the strip-shaped inspection area, further generating an obstacle avoidance path, and obtaining a safety inspection route. According to the embodiment of the invention, through the technologies of parallel route generation and segmentation, three-dimensional obstacle avoidance and the like, the problems of low efficiency, insufficient coverage rate, large potential safety hazard and the like in a traditional inspection mode are solved. The method can be widely applied to the technical field of unmanned aerial vehicle route planning.

The present application relates to a kind of multi-airport flight time slot resource allocation method, belong to air traffic control automation technical field, the present application is aimed at the characteristics of complex constraint, strong coupling of multi-airport time slot allocation problem, constructs multi-airport flight time slot optimization model, under the premise of guaranteeing all airport take-off, landing capacity constraint, airport passing time constraint and flight time constraint between take-off and landing airport, make full use of airport time slot resource, generate feasible full track multi-airport flight time slot allocation scheme, while taking into account the fairness between flights, minimize maximum flight time slot adjustment amount;The method of the present application can simultaneously process the flight time slot allocation problem of multi-airport, full season, create value for multiple key subjects of air transportation system, realize the maximization of overall social benefit.Rational time slot allocation improves the punctuality of passengers, improves travel experience;Help airport to realize collaborative resource planning and efficient operation, enhance hub competitiveness.

This invention discloses a fire-fighting drone, comprising a fuselage and multiple aircraft mounted on the fuselage, including a probe head disposed on the fuselage; a magazine located on the fuselage for storing fire extinguishing bombs, with a bomb-dropping hole at the bottom of the magazine; a mounting slot located at the bottom of the fuselage; and a bomb-dropping mechanism disposed within the mounting slot. This fire-fighting drone provides high bomb-dropping accuracy and excellent fire-fighting effect. It employs a partially engaged gear and rack drive system combined with a spring energy storage mechanism to achieve catapult-style deployment of fire extinguishing bombs. The moment the partially engaged gear and rack disengage, the bomb-dropping tube rapidly resets under the elastic potential energy of the spring, using inertia to project the fire extinguishing bomb. This catapult method imparts a certain initial velocity to the fire extinguishing bomb, enabling it to fly along a specific trajectory towards the target fire point, effectively shortening the flight time of the fire extinguishing bomb.

A method and system for dynamic, health-aware contingency management for an autonomous Unmanned Aircraft System (UAS). A Fault Detection Module monitors a command-and-control (C2) link. A Prognostic Health Management (PHM) Module continuously calculates a Predicted Remaining Flight Time (RFT_Available) based on component health. In response to detecting a critical fault in the C2 link, a Contingency Decision Module (CDM) is initiated. The CDM accesses a Trajectory Option Set (TOS) of contingency trajectories (e.g., Return to Home, Divert) and dynamically calculates a Required RFT (RFT_Required) for each. The CDM selects an optimal trajectory by using the RFT_Available as a hard constraint, ensuring the RFTAvailable≥RFTRequired+SafetyMargin. This couples an external operational fault (C2 loss) with an internal health constraint (RFT) to ensure a fail-operational response

The application discloses a flight path planning method and device, the method comprises the following steps: determining the type of the flight section by the current state information and the task route, so as to determine the end speed of the flight section; determining the current available acceleration according to the current working condition parameter, combining the current state information, the end speed of the flight section and the target horizontal speed to determine the horizontal acceleration instruction and the horizontal expected remaining flight time; taking the horizontal expected remaining flight time as a constraint, combining the current state information, the end speed of the flight section and the current available acceleration to determine the vertical acceleration instruction; and sending the horizontal acceleration instruction and the vertical acceleration instruction to the flight control system to control the flight of the unmanned aerial vehicle. The application aims to solve the problems of the flight precision and task continuity of the existing speed and trajectory control method of the automatic route flight of the unmanned aerial vehicle, and the difficulty in adapting to the complex dynamic environment. The smooth connection of the unmanned aerial vehicle among multiple flight sections is realized, and the flight safety is ensured.

This invention proposes a method and system for ground handling process analysis and anchoring based on multi-source spatiotemporal fusion. The method includes: collecting flight operation data, ADS-B trajectory data, vehicle positioning data, and onboard process sensor data; unifying execution time and coordinates and cleaning anomalies; extracting flight anchor points based on ADS-B trajectories using Dynamic Time Warping (DTW) to construct flight time / space fences; inputting vehicle positioning data and process sensor data into the vehicle process state machine to obtain structured process instances; retrieving process instances that meet the conditions within the time window and spatial fence; constructing a confidence score based on spatiotemporal distance to achieve accurate binding of processes to target flights. This invention achieves automated analysis and accurate operation anchoring of airport ground handling service processes, contributing to improved ground handling operations.

Systems and methods for preventing side door accidents using existing time of flight (TOF) sensors include receiving sensor data captured by a sensor system of a vehicle and mapping the sensor data to generate a depth map of a proximity area around the vehicle. Here, the depth map includes objects in the proximity area around the vehicle. The system and method also include determining whether an object in the proximity area is within a region of interest corresponding to the door, and when the object is within the region of interest of the door, generating a notification for a user of the vehicle that alerts the user that the door cannot be opened.

The invention belongs to the technical field of guidance laws. The invention provides an aircraft space-time cooperative guidance method under uncontrollable conditions with time-varying speed. According to the embodiment of the invention, firstly, an aircraft space-time cooperative guidance model under the condition of time-varying speed and uncontrollability is established; secondly, in order to deal with the problem of inaccurate residual flight time estimation caused by the time-varying flight speed, constructing a BP neural network to predict the total flight time under different initial flight parameters and collision angle constraints; finally, a two-stage method guiding strategy is adopted, the collision time is adjusted in the time precision control and angle rough control guiding stage, the deviation of the collision time is converged to a certain range, the angle precision control guiding stage is entered, and the collision angle and the collision time of the aircraft are controlled at the same time under the condition that the flight speed is uncontrollable.

An electronic device, comprising circuitry configured to determine Time-of-Flight histogram data from raw data obtained by a Time-of-Flight pixel array; generate, based on spot coordinates of spots received by the Time-of-Flight pixel array, a dot mask, the dot mask being indicative of dot pixels; select, based on the dot mask, one or more dot pixels; select, based on the dot mask and based on a predetermined set of coordinates on the Time-of Flight pixel array, one or more valley pixels, and calculate one or more residual histograms by subtracting one or more valley histograms, generated by the valley pixels, from one or more dot histograms, generated by the dot pixels; and generate depth information based on the one or more residual histograms.

The invention discloses a transmitting module, a laser radar and related electronic equipment. The invention provides a novel laser radar detection scheme, through histogram scaling design of rough measurement and fine measurement, light flight time counting is accumulated by a histogram with low time resolution, and the position of a signal peak corresponding to an object is generally determined; and then the local histogram with high time resolution is used to accumulate the light flight time counting to improve the distance measurement precision, and the design can greatly reduce the storage area of a laser radar receiving chip on the basis of not reducing the distance measurement performance, thereby reducing the chip cost.

A system and method for processing time-of-flight signals from a plurality of time-of-flight sensors. A set of time-of-flight signals is received from each of a plurality of time-of-flight sensors, each set of time-of-flight signals including time-of-flight signals for a plurality of regions of an environment. The sets of time-of-flight signals are processed to identify adjacent time-of-flight sensors and to determine a relative position and orientation between the adjacent time-of-flight sensors.

The invention relates to the technical field of engineering machinery remote control, and discloses a safety control system and method for wireless remote control operation of an engineering machinery landing leg, and the method comprises the following steps: measuring the distance of a UWB positioning tag on a remote controller through UWB receiving nodes at different positions of an engineering machinery vehicle body; the distance between the UWB positioning tag and each UWB receiving node is measured based on a bidirectional time-of-flight method, and the real-time position of the remote controller relative to the engineering machinery is calculated according to a plurality of distance values; the number of the UWB receiving nodes is at least three; in combination with the real-time position and the type of the supporting leg, judging whether the position of the remote controller is located in the dangerous area of the supporting leg, locking all the supporting leg operation authorities when the remote controller is located in the dangerous area, enabling the visible-side supporting leg operation authority and locking the invisible-side supporting leg operation authority when the remote controller is located outside the dangerous area, and generating a control instruction; and the control instruction is sent to a landing leg hydraulic control system so as to limit the landing leg operation authority.