138 results about "Ground speed" patented technology

The invention relates to the field of aviation safety, and provides a flight bumping area prediction method and system based on air-ground data fusion, and the method comprises the steps: obtaining a measurement area, and obtaining a barometric altitude through meteorological data; acquiring air detection data of the measurement aircraft so as to calculate a horizontal airspeed component; checking according to the horizontal airspeed component and the ground speed component to obtain a high-altitude wind speed component; generating an airborne data matrix, calculating the distance between a measurement point in the airborne data matrix and a grid point in a measurement area to obtain a latitude and longitude distance, and performing weight accumulation to obtain a grid point wind speed; wind field deformation is calculated, a jolting index is calculated according to the wind field deformation and normalized, a normalized jolting index is obtained, and a comprehensive jolting index is obtained through the normalized jolting index; and obtaining a target jolting index according to the ground measurement jolting index and the comprehensive jolting index to realize jolting prediction. According to the invention, accurate flight bumping prediction can be realized.

A system includes: one or more processors; and memory storing instructions, executable by the one or more processors. The instructions, when executed by the one or more processors configure the one or more processors to: obtain data indicative of a ride quality issue at an upcoming location at a worksite at which a work machine performs a current operation; identify a ride quality issue at the upcoming location at the worksite based on the data; and control the work machine based, at least, on the ride quality issue at the upcoming location at the worksite.

The invention provides an unmanned aerial vehicle flight path tracking control method, system and device and a storage medium. The method comprises the steps that the turning radius of an unmanned aerial vehicle is obtained according to the ground speed of the unmanned aerial vehicle and the target lateral acceleration; acquiring a route included angle between the known flight route and the target flight route through the route information, obtaining an advanced turning distance according to the turning radius and the route included angle, and constructing an inscribed circular arc path according to the turning radius and the circle center; the unmanned aerial vehicle is switched to the target flight route according to the relation between the to-be-flied distance and the advanced turning distance, and route updating is completed; a flight path tracking control mathematical model is established based on the relative position relation between the unmanned aerial vehicle and the arc path, a lateral acceleration instruction is obtained according to an improved variable gain guidance method and converted into a roll angle instruction, and the unmanned aerial vehicle is controlled to roll according to the roll angle instruction. According to the invention, accurate flight path tracking control can be realized, and the flight path tracking control capability and the anti-interference capability of the unmanned aerial vehicle during turning are enhanced.

The present disclosure includes devices methods and systems for detecting lost crop in a work machine operation. The method may include receiving ground speed data from one or more speed detection systems. The method may include receiving crop condition data from one or more feed data sensors. The method may include determining one or more crop condition states based at least in part on one or more of the ground speed data and the crop condition data. The method may include determining lost crop based at least in part on the one or more crop condition states. The method may include adjusting one or more combine operation parameters based at least in part on the determination of lost crop.

The invention relates to the technical field of ship navigation behavior prediction, and discloses a ship navigation behavior prediction method and system based on interpretable artificial intelligence. Comprising the following steps: acquiring ship AIS historical data and historical marine environment data in a target sea area; based on a time scale and a space scale, fusing the ship AIS historical data and the historical marine environment data, and constructing a spatio-temporal data set; performing feature decoupling on a static variable and a time-varying variable of the spatio-temporal data set, and determining historical input data, known future input data and static input data; an interpretable space-time fusion neural network model is constructed based on a dynamic gating residual neural network, a space-time characteristic variable selection network, a Fourier analysis gating neural unit and an interpretable multi-head attention mechanism so as to accurately predict ship navigation behaviors such as a ship trajectory, an over-the-ground navigational speed and an over-the-ground course. And a navigation behavior influence factor weight visualization result is output, and the method has interpretability.

The invention discloses an optimization method for an optimal short-distance takeoff strategy of a vertical / short-distance takeoff and landing aircraft, and the method comprises the steps: firstly building a vertical / short-distance takeoff and landing aircraft longitudinal dynamic model and a ground stress model which consider the dynamic state of an actuator, and augmenting the dynamic state of the actuator to an aircraft motion equation; secondly, the minimum ground clearance speed is solved through a constrained balancing algorithm, the speed serves as a take-off criterion, and a fixed-value take-off strategy is obtained through theoretical derivation and serves as a dynamic optimization initial value; the optimal short-distance takeoff problem is converted into an unconstrained nonlinear programming problem with fixed final state time, and a dynamic optimization takeoff strategy is solved in combination with a numerical optimization method; and finally, carrying out sensitivity analysis on the thrust-weight ratio, the thrust distribution ratio and the gravity center position to obtain an influence rule of each factor on the takeoff distance. The method has the advantages of being high in strategy optimization efficiency, short in takeoff distance and high in engineering guidance, the rapid starting capability of the vertical / short-distance takeoff and landing aircraft is remarkably improved, and technical support is provided for control of the short-distance takeoff and landing stage of the vertical / short-distance takeoff and landing aircraft.

According to the ultra-efficient energy-saving method and device for automobiles, ships, trains, submarines and aircrafts, when the automobiles and the ships advance, the heads push air to scatter all around, and negative pressure areas are formed on the bodies and the tails of the automobiles and the ships to suck and pull the automobiles and the ships. A rear flow cover 2 is additionally arranged at the head of the vehicle and vessel, scattered air is forced to leave the rear flow cover in an accelerated mode in the direction opposite to the advancing direction of the vehicle and vessel and flow towards the side and the tail of the vehicle and vessel, power (reverse thrust) is provided for the vehicle and vessel, air in a negative pressure area of the side and the tail of the vehicle and vessel is supplemented, the speed of airflow leaving the rear flow cover relative to the ground is reduced, and energy loss is reduced. A water baffle 4 is arranged on the bow, and the bottom edge of the water baffle is connected with a water pressing plate 5, so that the water pressure of the raised water level pushes the boat to advance. The water pressing plate is located on a static horizontal plane, so that the ship does not easily shovel water when advancing. The two sides of the ship are respectively provided with a manger board 1, so that waves generated by the ship surge towards the tail of the ship to reversely push the ship to advance. The air bag is arranged at the tail of the vehicle, high-pressure air generated by the windward side of the head of the vehicle is conveyed to the air bag, the air bag is prone to deformation and automatically searches for a large-negative-pressure position to fill a negative-pressure area, resistance is reduced, and safety is achieved.

The invention relates to a self-vehicle speed estimation method and device, an electronic device and a storage medium, and the method comprises the steps: obtaining trace point data captured by a radar sensor, the trace point data comprising the radial speed and azimuth angle of each target trace point; determining a static target trace point from the target trace points based on the azimuth angle of each target trace point; based on the radial speed and the azimuth angle of the stationary target plot, calculating a target ground speed corresponding to each stationary target plot; dividing a speed interval for the target ground speed based on a preset step length; based on the trace point distribution feature information of the static target trace point in each target speed interval, determining a target effective interval; and calculating the average value of the radial speed of each static target trace point in the target effective interval to obtain a self-vehicle speed estimation value. According to the invention, the problem that the precision of the vehicle speed calculated through the millimeter wave radar is insufficient when the vehicle runs at a low speed is solved, and the low-speed vehicle high-precision estimation independent of external vehicle speed input is realized.

A system for operating a radar device of a mobile machine is disclosed. The system includes an actuator operably coupled between the radar device and an exterior of the mobile machine. The system further includes a controller configured to receive an input indicative of a ground speed of the mobile machine. The controller is further configured to control the actuator to tilt the radar device with respect to a ground plane to alter a field of view of the radar device based on the input received by the controller.

Embodiments of the present invention provide a flight control method and apparatus for an unmanned aerial vehicle, a storage medium and an electronic apparatus. The method includes: acquiring a target control request of the unmanned aerial vehicle during execution of target flight tasks; detecting current energy consumption data of the unmanned aerial vehicle in response to the target control request, the current energy consumption data indicating a current energy consumption condition of the unmanned aerial vehicle; calculating remaining navigation parameters of the unmanned aerial vehicle according to the current energy consumption data and current ground speed, the remaining navigation parameters indicating a navigation time of the unmanned aerial vehicle before landing, the current ground speed indicating a current flight speed of the unmanned aerial vehicle relative to ground; and controlling the unmanned aerial vehicle to execute remaining flight tasks in the target flight tasks according to the remaining navigation parameters.

Systems and methods are provided for displaying differential ground speed for traffic surrounding an aircraft. The system includes an aircraft control panel in a cockpit of an ownship aircraft and a digital traffic display located on the control panel. The digital traffic display provides cockpit display of traffic information (CDTI) that shows a speed scale with a graphical display of the ground speed of the ownship aircraft and the ground speed of traffic to follow (TTF). The separation scale also shows a graphical display of a separation distance between the ownship aircraft and the TTF. A change in separation distance is calculated based of the difference in ground speed between the ownship aircraft and the TTF. An advisory / warning indicator that shows a color-coded status of the change in separation distance in comparison a pre-determined desired separation distance between the ownship aircraft and the TTF.

The invention belongs to the technical field of accurate measurement seeding, and discloses a seeding machine accurate speed measurement method and system based on radar Beidou inertial navigation multi-source data fusion. The speed measurement system comprises a seed sowing device driven by a motor to operate, a speed monitoring module, a display screen and a control unit for implementing the accurate speed measurement method. The speed monitoring module comprises a ground speed radar, an inertial measurement element and a Beidou receiver; the display screen is used for selecting a speed measurement mode and displaying a seeding state; and the control unit calculates the advancing speed of the precise seeder based on the speed related data obtained by the speed monitoring module and the selected speed measurement mode, and then adjusts the rotating speed of the motor according to the advancing speed of the precise seeder. According to the invention, multiple speed measurement modes, namely Beidou speed measurement, radar speed measurement and inertial navigation speed measurement, are integrated and combined pairwise, fusion speed measurement of different modes can be selected and switched according to environmental conditions, the limitation of a single mode can be effectively overcome, and a complex environment can be effectively dealt with.

The application discloses an autonomous ship navigation induction method, which predicts the behavior of the autonomous ship and surrounding ships through a trained trajectory space-time prediction model, thereby inducing the navigation of the autonomous ship. The establishment process of the prediction model comprises the following steps: obtaining the voyage time sequence data of the ships around the autonomous ship, constructing a ship navigation situation awareness graph G θ of the autonomous ship θ , which reflects the navigation situation of the autonomous ship and surrounding ships, wherein the ship navigation posture comprises ship coordinates, a time stamp, a ground speed and a ground heading; through entity embedding of the ship navigation situation awareness graph G θ , a ship trajectory vector is obtained, and the spatial features between ships, the local time features of the ships and the global time features of the ships are captured by machine learning; the obtained features are decoded by deep learning, so as to train the trajectory space-time prediction model.

A walk-behind powered equipment unit (e.g., grounds care vehicle such as a power mower) having a ground speed control system. The system may include a handle formed by a handle tube having a proximal end attached to the housing, and a handlebar mounted to the handle tube at a handlebar pivot such that the handlebar may pivot about the handlebar pivot relative to the handle tube in response to a force F applied by the operator to the handlebar, e.g., when the operator walks in a forward direction. An actuator of the handlebar, in response to pivotal motion of the handlebar about the handlebar pivot, imparts a force Fs to a force sensor. The force sensor is configured to produce an electrical sensor signal corresponding to the force F and provide that signal to a propulsion motor.

The invention relates to the technical field of eVTOL and the like, and provides a horizontal reference path calculation method for an eVTOL waiting mode, which comprises the following steps: acquiring the position, track angle, ground speed and waiting mode type of the current eVTOL, determining a waiting positioning point according to the acquired information, and constructing an entering track; establishing an auxiliary dividing line by taking the entry edge as a reference to divide the space into four quadrants, and determining an entry path type according to the quadrant where the entry track is located; calling a corresponding path node generation rule to construct an entry section according to the path type, constructing an execution section, and generating an exit section when an end condition is met; in the entering section, the translation distance of the navigational arc is limited and subjected to interference checking, the arc parameter or the position of the waiting point is adjusted if necessary, and finally a complete reference path is formed. According to the method, the dynamic adaptability, geometric coordination and flight safety of path planning are improved.

The invention relates to the technical field of aircraft brake control, in particular to an aircraft brake system derating optimization control method based on a high-torque brake material, and the method comprises the steps: obtaining the enclave ground speed of an aircraft, a brake instruction signal and a maximum brake instruction signal; acquiring an anti-skid control signal according to the wheel speed change when the anti-skid state recognition treatment is carried out; according to the difference between the anti-skid control signal and the brake control quantity, the number of times of occurrence of deep anti-skid is obtained; derating optimization is conducted on the brake control quantity according to the number of times of deep skid prevention, and the brake control optimization quantity is obtained; and performing brake control according to the brake control optimization quantity. According to the method, the change of the anti-skid control signal is effectively judged, and the brake pressure is derated and optimized in time, so that stable and efficient braking can be completed in the normal landing braking process of an airplane, and the reliability and safety of a braking system are improved.

The present invention discloses a data-driven ship stall estimation method and system. The method includes: collecting historical ocean environment information, historical ship navigation information, and historical ship main engine information; performing a first data preprocessing on the historical ocean environment information and historical ship navigation information, and performing a second data preprocessing on the historical ship main engine information; calculating a first impact speed based on the ground speed and current velocity; establishing a mapping relationship between the main engine speed and the ground speed based on wind speed and wave height screening samples to obtain a still water speed calculation model, and calculating a second impact speed; obtaining the ship stall value by the difference between the first impact speed and the second impact speed; and constructing a ship stall prediction model that inputs real-time ship navigation information and outputs the current ship stall estimation result. This method achieves rapid and accurate calculation of ship stall through data-driven means, avoids the complex calculation process of traditional mechanism models, and significantly enhances its engineering application value.

The invention relates to a vehicle speed determination method, device and equipment, a vehicle and a chip, and belongs to the technical field of vehicles. The method comprises the steps that under the condition that a first vehicle is in a slipping state, current observation information of a target object is determined, the current observation information of the target object is used for indicating the current speed of the target object relative to the first vehicle, and the target object is an object which is observed to obtain a fixed ground speed when the first vehicle is not in the slipping state; and determining the current speed of the first vehicle based on the current observation information of the target object and the fixed ground speed of the target object. Therefore, the target object and the fixed ground speed of the target object can be accurately determined before the first vehicle slips, the current observation information and the fixed ground speed of the target object can be comprehensively considered when the first vehicle slips, the current speed of the first vehicle is determined, and the current speed of the first vehicle can be accurately obtained when the first vehicle slips.

The utility model provides a GPS velocimeter for a model airplane unmanned aerial vehicle, the GPS velocimeter is clamped in a remote controller, one end of the velocimeter is externally connected with a display, the other end of the velocimeter is externally connected with a power supply end, the GPS velocimeter comprises an actuation system, a chip in the actuation system is provided with a common velocity measurement unit and an accurate velocity measurement unit, the common velocity measurement unit and the accurate velocity measurement unit are both electrically connected with the chip, a receiver is arranged in parallel with the chip and electrically connected with the chip, and the receiver is electrically connected with the chip. The common speed measurement unit outputs standard NMEA data and is suitable for daily speed measurement in a low-power-consumption state; the precise speed measurement unit outputs ground speed based on the Doppler effect, high-precision scene requirements such as racing or complex surveying and mapping are met, the receiver ensures that GPS signals are rapidly received and processed, efficient operation of the system is achieved, the defect of a single-precision mode is overcome through the design, precision and power consumption are considered, and various task requirements are met.

The application discloses a UAV cluster integrated control system based on formation flight, and relates to the field of flight control technology.The system comprises a flight acquisition module, an atmosphere acquisition module, a cluster control module and a display module.The flight acquisition module acquires data and stabilizes the output of posterior coordinates, ground speed and attitude angle through drift compensation Kalman filtering.The atmosphere acquisition module relies on a database of aerodynamic characteristics, and solves airspeed, barometric altitude and angle of attack through a model of atmospheric solution that is fused with model-specific aerodynamic correction coefficients and adaptive weighting.The cluster control module establishes an airflow disturbance model to quantify airflow disturbance intensity and generate disturbance coefficients of UAVs and adjacent UAVs, and dynamically outputs adjustment instructions with the minimum formation deviation and the stable attitude of a single machine as the target.The display module is used for 3D visualization monitoring of flight formation.The system significantly improves the stability and adaptability of formation flight, and is suitable for UAV cluster cooperative operation in complex scenarios.

An aircraft includes a control unit configured to set a horizontal ground speed based on wind information, including information about wind direction and wind speed.

The invention relates to an aircraft path following method and device, electronic equipment and a storage medium, and the method comprises the steps: obtaining the hovering center, the hovering radius and the hovering direction of a hovering task when the aircraft needs to be switched from the execution of a linear task to the execution of the hovering task; determining a preview distance according to the ground speed of the aircraft, and determining a gradual-change circling cut-in distance, a gradual-change circling cut-out distance and a stable circling cut-in distance according to the preview distance; acquiring a current relative distance between the aircraft and the circling center position in real time; if the current relative distance is larger than the stable circling cut-in distance, the guiding direction of the aircraft is adjusted in a self-adaptive mode according to the size relation between the current relative distance and the gradually-changed circling cut-in distance, the gradually-changed circling cut-out distance and the stable circling cut-in distance, and the aircraft is controlled to move according to the guiding direction. According to the invention, the smooth switching of the aircraft from the execution of the routing task to the execution of the hovering task can be realized.

This application relates to the field of eyepoint data compensation technology, providing a method and system for compensating eyepoint data in flight simulators, solving the problems of poor real-time performance and low accuracy of eyepoint data in flight simulations. The method includes: establishing a shared memory region between the simulation logic processing module and the eyepoint data sending module of the flight simulator; this region contains updated state variables in the form of frame IDs and a first-in-first-out shared eyepoint data area; after completing a frame attitude calculation, the simulation logic processing module updates the frame ID; the eyepoint data sending module obtains the latest eyepoint data through the position corresponding to the latest frame ID; then, combined with the instructor's station settings, airspeed, and ground speed data, the aircraft attitude mode is determined to be stationary, stable, or maneuvering; finally, linear interpolation is used for the stable mode, and a pre-trained lightweight LSTM is used for the maneuvering mode to predictively compensate the latest eyepoint data, obtaining the compensated data. This application improves the real-time performance and accuracy of eyepoint data in flight simulations.

The invention provides an aircraft roll angle reconstruction method and system, and belongs to the technical field of aircraft control, the method comprises the steps that aircraft state signals are acquired, and the state signals comprise a ground speed signal Vg, a vacuum speed signal Vt, a yaw angle rate signal R, a pitch angle rate signal Q and a pitch angle signal Pitch; and under the condition that the roll angle signal fails, according to a lift force and gravity balance principle in a rolling state of the airplane, an approximate roll angle reconstruction signal is constructed based on a ground speed signal or a vacuum speed signal, a yaw angle rate signal, a pitch angle rate signal and a pitch angle signal.

This application provides a wind velocity measurement apparatus for an aircraft. The wind velocity measurement apparatus for an aircraft includes an aircraft attitude obtaining apparatus, an ultrasonic or laser wind measurement apparatus, an attitude adjustment apparatus, an aircraft parameter obtaining apparatus, and a control apparatus. The ultrasonic or laser wind measurement apparatus is configured to measure a relative wind angle. The aircraft parameter obtaining apparatus is configured to obtain a ground velocity and a set course angle of an aircraft. The control apparatus is capable of adjusting, based on an attitude of the aircraft, an attitude of the ultrasonic or laser wind measurement apparatus via the attitude adjustment apparatus until a transmit end and a receive end of the ultrasonic or laser wind measurement apparatus are both kept horizontal. This application further provides a corresponding wind velocity measuring method for an aircraft, and a greenhouse gas detection apparatus.

The invention relates to the technical field of aircraft power control, and discloses an artificial intelligence optimized vertical fixed wing power control method and system, and the method comprises the steps: obtaining the original airspeed data of an airspeed sensor, the ground speed data of a global positioning system and the acceleration data of an inertial measurement unit, and generating the ground speed of an aircraft based on the data fusion. Under the low-wind-speed condition, the ground speed of the aircraft is used as the reference airspeed, the difference between the original airspeed data of the airspeed sensor and the reference airspeed is continuously compared, and the sliding average value of the difference is calculated. When the sliding average value continuously exceeds the preset tolerance range, the method can identify that the airspeed sensor has continuous calibration drift. And then, according to the identified continuous calibration drift, performing real-time compensation on original airspeed data of an airspeed sensor to obtain calibrated airspeed data, and inputting the calibrated airspeed data into flight mode switching judgment logic to trigger an action instruction of a tilting mechanism.

The invention relates to the technical field of geographic surveying and mapping, and discloses an unmanned aerial vehicle-mounted laser radar geographic surveying and mapping data acquisition system and method, and the system comprises an unmanned aerial vehicle platform, a laser radar sensor, a position attitude measurement unit and an airborne calculation unit. The airborne computing unit shunts the original point cloud into a look-ahead point set and a surveying and mapping point set through a view field partitioning module; the geometric prediction module solves a predicted incident angle of the surface micro-element by using the look-ahead point set in combination with the pose; the instruction generation module reversely calculates acquisition parameters including the pulse frequency and the flight ground speed according to the parameters, and generates space anchor point coordinates; the space synchronization execution module issues parameters when the unmanned aerial vehicle arrives at the anchor point; and the real-time feedback verification module triggers override interruption according to the actual density of the surveying and mapping point set. According to the method, adaptive parameter adjustment is realized through prospective perception and closed-loop feedback, the problem of non-uniform distribution of point clouds of complex terrains is solved, and the integrity and efficiency of geographic surveying and mapping data acquisition of the unmanned aerial vehicle-mounted laser radar are improved.

39 #22754449v1<GHMATTERS Abstract An aerator for a turf surface has a traction control, an OPC bail, and an aeration bail capable of single handed operation. A controller automatically lowers a tine head to begin aerating at a start location marked when the aeration bail is closed and lifts the tine head to end aeration at an end location marked when the aeration bail is released. The controller further causes the tines that enter the turf surface at the start location to penetrate to a desired hole depth. The controller also automatically adjusts ground speed to maintain a desired hole spacing during an aeration pass, but permits the operator to speed up during a turnaround between passes with a steerable front wheel freewheeling to mitigate wheel scrubbing. A handle assembly having a spring counterbalance is height adjustable and automatically engages a parking brake when placed in an upright non-operating position. Abstract aeration at an end location marked when the aeration bail is released. The controller further 39 #22754449v1<GHMATTERS 20 26 20 47 44 18 J un 2 02 6 A b s t r a c t 2 0 2 6 2 0 4 7 4 4 1 8 J u n 2 0 2 6 a e r a t i o n a t a n e n d l o c a t i o n m a r k e d w h e n t h e a e r a t i o n b a i l i s r e l e a s e d . T h e c o n t r o l l e r f u r t h e r 3 9 # 2 2 7 5 4 4 4 9 v 1 < G H M A T T E R S

The invention discloses a method and a system for evaluating the regional residence capability of a long-endurance aircraft, and belongs to the technical field of aerospace. According to the method, based on battery parameters, solar radiation and historical data of a wind field, an airspeed time change rule of the long-endurance aircraft which meets day and night energy circulation and maximally utilizes solar energy is determined through a nested optimization algorithm; combining the airspeed and the wind speed vector to synthesize the ground speed, updating the position by adopting a fixed time step length, and iteratively solving the farthest distance of the residence point capable of going back and forth in the specified time in each direction through a dichotomy method; and finally, a closed circle is defined by the farthest points in all the directions, and quantitative evaluation of the long-endurance aircraft area residence capability is achieved. According to the method, the all-day optimal airspeed change of the long-endurance aircraft is determined through the nested optimization algorithm, and the farthest residence point in each direction is iteratively solved in combination with vector calculation and the dichotomy, so that the problem of lack of an effective evaluation method for the regional residence capability of the long-endurance aircraft in the prior art is solved; and an important basis can be provided for task planning and performance optimization of the long-endurance aircraft.

The invention discloses a VNAV vertical deviation calculation method satisfying vertical side cutting, and the method comprises the steps: obtaining the position of an aircraft, the position of each waypoint of a flight plan, horizontal path data, vertical path data, the ground speed of the aircraft, and the air pressure altitude of the aircraft, and calculating the distance between the aircraft and the end point of the flight plan, and the vertical path segment of the aircraft; the method comprises the following steps: determining whether an aircraft is in a vertical path transition section, and when the aircraft is in the vertical path transition section, calculating a virtual vertical path transition path constructed at a constant vertical acceleration, and calculating the vertical deviation based on the path, so as to achieve the purpose of VNAV vertical deviation calculation meeting vertical side cutting. According to the method, engineering implementation is easy, the guiding target of the VNAV can be optimized into a vertical bypass path with the constant vertical acceleration in the vertical path transition section under the condition that the calculation load is small, and the flight quality and the comfort level of passengers are guaranteed while the vertical path is accurately tracked.