68 results about "Ground speed" patented technology

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 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 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.

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.

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.

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.

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.

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.

The invention provides an intelligent monitoring system for the slip rate of an unmanned tractor, and the system comprises a GNSS vehicle speed measurement unit which is used for collecting the ground speed of a vehicle and a system UTC time reference; the multi-node wheel rotating speed measuring unit comprises at least four wheel nodes and is used for collecting rotating speed data of each wheel; the GNSS vehicle speed measuring unit, the multi-node wheel rotating speed measuring unit and the central processing and display unit are connected through a star flash wireless network; and the central processing and display unit is configured to perform fusion processing on the received vehicle ground speed and system time reference data and the rotating speed data of each wheel, calculate the slip rate and interact with a whole tractor controller. The system can provide real-time and accurate four-wheel slip rate data for a traction control system of the unmanned tractor.

The invention belongs to the technical field of aviation hydraulic pressure, and discloses an aircraft hydraulic pump state judgment system which comprises a hydraulic pump, a hydraulic pump pressure annunciator, an avionics computer and a comprehensive display unit, and the hydraulic pump pressure annunciator collects signals of the hydraulic pump and sends the signals to the avionics computer; the avionics computer further obtains the ground speed of the airplane and the rotating speed of the engine by receiving an ARINC129 signal, judges the state of the hydraulic pump by integrating the pressure of the hydraulic pump, the ground speed of the airplane and the rotating speed of the engine, and displays the state through the integrated display unit. Aiming at the problem that a traditional aircraft hydraulic pump only displays a working state and a non-working state and lacks fault state display, the three states of the hydraulic pump can be accurately fed back, more accurate hydraulic pump state information can be provided for a pilot, and the pilot can be better helped to fly.

The invention belongs to the technical field of aircraft control surfaces, and particularly relates to a rotation driving device and system applied to an aircraft control surface and the aircraft control surface, the rotation driving device comprises a rotation assembly used for driving the control surface to rotate, and the rotation assembly comprises a connecting piece connected with the control surface and a driving piece connected with the connecting piece and used for driving the control surface to rotate; the driving assembly is used for driving the speed brake to rotate and comprises a first rotating shaft, a second rotating shaft, a rotating part and a driver used for driving the first rotating shaft to rotate, the rotating part is connected with the control surface, the first rotating shaft is connected with the second rotating shaft through a connector, and control surface rotation and a ground speed brake mechanism are integrated into a single movement mechanism; cooperative integration of control surface deflection and speed brake opening functions is achieved, the situation that multiple sets of complex structures of a traditional cracking type control surface coexist is simplified, the number of kinematic pairs and parts is reduced, the occupied space is reduced, meanwhile, the area proportion of the speed brake is effectively increased, the aerodynamic efficiency is improved, and the overall weight is reduced.

A system includes a work vehicle, user interface, and controller. The work vehicle includes a frame, boom, implement, perception sensor, and ground speed sensor. The perception sensor senses an approaching environment. The user interface includes controls and indicators. The controller is coupled to the controls, indicators, perception sensor, and ground speed sensor. The controller receives a command to move the work vehicle, drives the work vehicle, determines a distance to the container, determines the ground speed, determines a boom raising start distance from the container, receives a command to raise the boom, and activates one of the indicators if the user command to raise the boom occurs prior to the work vehicle reaching the boom raising start distance from the container.

This invention relates to a method and system for detecting duplicate MMSI numbers based on dynamic information from AIS messages. The method comprises: continuously receiving and parsing AIS dynamic messages within a preset time period to obtain the MMSI; storing the dynamic messages of the target MMSI to be detected; parsing the stored AIS dynamic messages to obtain the ship dynamic information contained therein, including position information, ground speed, and time stamp; calculating the actual displacement between two adjacent messages based on the position information; calculating the theoretical maximum displacement between two adjacent messages based on the ground speed and time stamp; and comparing the actual displacement D. A and the theoretical maximum displacement D T D A ≤D T This is a normal result, D A >D T The system is considered an abnormal result; a threshold judgment is made, with a preset threshold value. When the proportion of abnormal results is not greater than the preset threshold value, the MMSI is determined to be normal; otherwise, the MMSI is determined to be a duplicate number. The system includes a memory and a processor, and the processor is used to call and run instructions from the memory to execute the duplicate number detection method.

The embodiment of the invention discloses a method and device for a high-aspect-ratio low-speed aircraft to pass through a large wind layer. The method comprises the steps that when the air speed of a traditional fixed-wing aircraft is larger than the wind speed, the traditional fixed-wing aircraft can fly forwards all the time; the high-aspect-ratio low-speed aircraft can not keep flying forwards when the space speed is possibly equal to or smaller than the wind speed at the high wind speed; and during flight retreating, in order to minimize the flight retreating distance, a sensor is installed to obtain the air speed, the ground speed, the speed course and the airframe course, the wind direction is calculated online in real time, and the airframe course is controlled to face the wind coming side, so that the flight retreating distance is minimized when the aircraft passes through the large wind layer.

A radial frequency of clip control system includes a steering angle sensor for a steerable rear wheel of a grass mowing machine, a pedal sensor for sensing an operator input for a desired ground speed at a reference point adjacent an operator seat on the grass mowing machine; and an electronic controller that uses the desired ground speed and location of each of a plurality of reel cutting units to calculate a rotational speed for each of the plurality of reel cutting units.

A speed control system is configured to control a propulsion system of a mobile agricultural machine to ramp from a first ground speed to a second ground speed based upon a location of a boundary crossing point. The speed control system generates an effective boundary crossing point location based on the location of the boundary crossing point and a system delay between when a section control signal is generated and when a corresponding section control function is performed. A section control system generates section control signals based upon the effective boundary crossing point location.

The present application relates to the technical field of aircraft anti-skid brake, in particular to a kind of self-adapting brake steady deceleration rate adjusting method based on aircraft brake energy, the method includes obtaining the brake energy state when aircraft starts braking according to aircraft ground speed and aircraft total weight signal;According to the wheel speed and the wheel speed after 1 second, the brake deceleration rate in 1s is obtained;According to the brake energy state when aircraft starts braking and the brake deceleration rate in 1s, brake pressure is adjusted until the wheel steady deceleration rate is reached.The present application obtains steady deceleration rate target range according to aircraft brake energy, realizes the control to brake pressure according to deceleration rate target range, can improve brake deceleration rate, and reduce braking distance.

The invention belongs to the technical field of aircraft brake systems, and discloses an indication control method for an aircraft wheel brake system without an anti-skid brake, which is used when an anti-skid system of an aircraft fails, and is used for prompting a pilot according to the ground speed of the aircraft and the brake pressure of all aircraft wheels, if the ground speed of the aircraft does not exceed the speed threshold value, a non-warning prompt is output to a pilot; meanwhile, brake pressure collection is carried out on all airplane wheels of the airplane, and when the brake pressure of any airplane wheel exceeds a threshold value, a warning prompt or a serious warning prompt is output to a pilot. Through the design, the operation safety and the system reliability of the aircraft brake system in a non-antiskid state can be effectively protected, and misjudgment and operation risks of a pilot caused by antiskid function failure or brake faults are avoided.

The present application relates to the technical field of ship testing and state monitoring, and proposes a ship speed dynamic determination method and device based on operation data, which comprises the following steps: automatically collecting the data of six-way draft, high-precision position and ground speed, main engine speed and water depth of the ship in the operation process through the sensor cluster installed on the ship; selecting the water area meeting the preset still water condition in the daily route to set the electronic fence area, controlling the ship to sail at different stable main engine speed points and collecting data; using the three-step iterative regression analysis algorithm to clean and model the data after cleaning, and finally fitting the relationship model between the ship still water speed and the main engine speed. The present application changes the speed determination from the expensive special voyage test to the low-cost and normalized operation process data utilization, realizes the dynamic, accurate and convenient determination of the ship speed, and provides the key data basis for the ship energy efficiency management, technical evaluation and intelligent operation and maintenance.

The invention discloses a test flight planning method for the maximum take-off weight of a fixed-wing unmanned aerial vehicle. The test flight planning method comprises the steps of determining the type of the unmanned aerial vehicle; according to the empty aircraft weight of the current sortie unmanned aerial vehicle, the maximum weight of the current sortie unmanned aerial vehicle and a preset weight span, the takeoff weight of the current sortie unmanned aerial vehicle is obtained; obtaining a climbing gradient of the current sortie unmanned aerial vehicle according to the flight parameters of the current sortie unmanned aerial vehicle; obtaining a climbing gradient prediction value of the next unmanned aerial vehicle according to the take-off ground clearance speed of the current unmanned aerial vehicle, the take-off weight of the current unmanned aerial vehicle and the take-off weight of the next unmanned aerial vehicle; and judging whether the flight test of the next unmanned aerial vehicle is carried out or not until all flight sorties of tests are completed and the actual flight climbing gradient of the last sortie of unmanned aerial vehicle meets a preset requirement, and at the moment, verifying that the maximum takeoff weight of the unmanned aerial vehicle meets a design requirement. According to the invention, the safety risk in the test flight process is reduced, and the test flight efficiency is remarkably improved.

A flight control method, an apparatus, an aircraft, a terminal, a system and a storage medium. The method comprises: determining a maximum airspeed vector of an aircraft (S101); determining a current wind speed vector of a current flight environment of the aircraft (S102); determining a current ground speed target direction of the aircraft during flight (S103); on the basis of the maximum airspeed vector, the current wind speed vector and the current ground speed target direction, determining a maximum ground speed vector of the aircraft, the direction of the maximum ground speed vector being the current ground speed target direction (S104); and controlling the flight of the aircraft on the basis of the maximum ground speed vector, such that the magnitude of the flight ground speed of the aircraft is less than or equal to the magnitude of the maximum ground speed vector (S105).

A complex nonlinear load variable control method based on UAV electric braking is proposed. When the UAV aborts takeoff or during landing roll, the electric braking control system first iterates the mathematical model of the control system by querying parameters such as ground conditions and weather conditions from the flight control system, updating the control objective and threshold values ​​of various output parameters. Then, the electric braking control system incorporates parameters such as the UAV's current mass, airspeed, ground speed, and wheel speed into the closed-loop control logic of the braking process, and introduces differential control and ABS anti-skid control strategies to achieve rapid response and adjustment in abnormal situations during braking. Finally, closed-loop control of the actuator braking force is achieved primarily using current and secondarily using position. This invention can replace hydraulic braking control, enabling rapid short-distance braking of UAVs under complex nonlinear load variables and solving problems such as wheel lock-up during braking and single-sided wheel lock-up in crosswinds.

The application belongs to the technical field of aircraft nose wheel turning system, and is a high-reliability aircraft nose wheel turning system, which comprises a turning instruction sensor, a turning control valve, a turning control unit, a turning execution mechanism, a turning angle feedback sensor, a brake control unit and a comprehensive management computer; after receiving the aircraft wheel speed signal and the ground speed signal simultaneously, the turning control unit executes the large and small angle control law switching logic according to the aircraft wheel speed signal; after judging that the aircraft wheel speed signal is invalid, it is judged whether the received ground speed signal is valid, if valid, the turning control unit executes the large and small angle control law switching logic according to the received ground speed signal; by simultaneously referring to the aircraft wheel speed signal and the ground speed signal, when the aircraft wheel speed signal is invalid, the ground speed signal is still used to control the large-angle turning of the nose wheel, preventing the nose wheel turning system from being unable to turn at a large angle when the aircraft wheel speed signal is invalid, and improving the task reliability of the aircraft.

The present disclosure provides a method of monitoring for an unstable approach of an aircraft during flight in one aspect, the method including: determining, using values of a ground speed and a height of the aircraft derived from measurements acquired during the flight, a specific energy of the aircraft during an approach phase of the flight. The method further includes determining a reference specific energy of the aircraft, defining an energy range relative to the reference specific energy, and visually displaying, using a first flight instrument of the aircraft, an indicator of the specific energy relative to the energy range.