101 results about "Flight management system" patented technology

The invention provides a navigation airport low-altitude meteorological intelligent management system based on multi-source meteorological data fusion, and the system comprises a three-dimensional grid monitoring network which is used for achieving the three-dimensional scanning and dynamic perception of an airspace meteorological environment through real-time collection of meteorological detection data; the data fusion system is used for carrying out assimilation processing on the collected real-time detection data and multi-source forecast data to generate a high-resolution three-dimensional gridding meteorological field covering an airport airspace range; the dynamic safety research and judgment module is used for researching and judging the influence of the current and future meteorological conditions of the airspace on the flight safety of each aircraft type in real time; and the management system establishment module is used for visually displaying the influence degree of the current meteorological condition on the flight through a visual chart by establishing a flight management system. According to the invention, a comprehensive meteorological safety protection system is constructed through an innovative system of intelligent perception, data fusion and decision pre-judgment, so that the problem of insufficient low-altitude meteorological service capability of an existing navigation airport is solved.

A ball flight management system includes a receiver configured to receive a wireless signal comprising an indication of an intended pitch type selected from among a plurality of intended pitch types, one or more sensors configured to measure one or more ball flight parameters of a pitched ball and output one or more measured ball flight parameters, and a recording unit in communication with the one or more sensors and the receiver, the recording unit receiving and storing the one or more measured ball flight parameters output by the one or more sensors and the indication of the intended pitch type received by the receiver, the recording unit associating the intended pitch type with the at least one measured ball flight parameter to generate a record for the pitched ball that includes the at least one measured ball flight parameter and the intended pitch type, and storing the record.

The invention provides a flight management system based on cloud-edge collaboration and an air route planning method thereof. The flight management system comprises an airborne end, a cloud platform and an edge computing node, the route planning method of the flight management system comprises the following steps: step 1, calculating an optimal flight path by a cloud platform, and predicting a meteorological condition on the flight route and corresponding real-time airspace information; 2, the cloud platform completes the route optimization of the current flight according to the data in the step 1, and sends the data to an edge computing node and an airborne end; step 3, when an emergency occurs, the edge computing node computes a corresponding release path and issues the corresponding release path to the airborne end and the air traffic control center, and the air traffic control center determines whether the aircraft executes the release path or not; according to the method, the defects of a traditional FMS in the aspects of dynamic planning capability, computing power limitation and the like can be overcome, and an extensible, high-reliability and low-cost solution is provided for a next-generation flight management system.

A method and system is provided for capturing a modified flight descent path for an aircraft has been developed. The method first generates a descent approach path for an aircraft with a flight management system (FMS). A proposed recovery path is generated for the aircraft that rejoins the descent approach path. The proposed recovery path is generated when the aircraft deviates from the descent approach path during flight operations. Inputs for the proposed recovery path for the aircraft are received with the FMS. The inputs are aircraft flight parameters that are received from aircrew members of the aircraft. The proposed recovery path is modified to comply with the inputs from the aircrew members. The modified recovery path is then integrated into the descent approach path with the FMS.

A flight management system includes a communications system configured to receive weather data from a remote source, a display system configured to generate an output for a flight display of an aircraft, and at least one processor with a non-transitory processor-readable medium storing processor-executable code. The output includes weather information based on the received weather data. The processor-executable code causes the processor to receive a user input from a user interface element of the aircraft where the user input requests updated weather information. The processor-executable code causes the processor to retrieve, via the communications system and in response to the user input, updated weather data from the remote source; calculate a departure or arrival performance flight parameter based at least in part on the updated weather data; and provide, via the display system, an output for the flight display of the aircraft where the output includes the flight parameter.

The application discloses a forest fire prevention unmanned plane automatic inspection system based on meteorological factors, which comprises a meteorological data acquisition device, an unmanned plane field and an edge computing device, a remote data analysis and flight management system and an unmanned plane; the meteorological data acquisition device is used for collecting meteorological factor data under different meteorological conditions, special holidays or different seasons in real time; the unmanned plane field and the edge computing device are used for receiving the meteorological factor data, performing cleaning processing to obtain processed data, and controlling the unmanned plane to cruise in an inspection area; the remote data analysis and flight management system is used for analyzing the processed data, judging forest fire danger meteorological grades under different conditions, formulating different unmanned plane cruise tasks, and sending the unmanned plane cruise tasks; the unmanned plane automatically executes the cruise tasks according to control commands; the system can automatically increase the unmanned plane forest fire prevention inspection frequency according to special nodes, meets actual inspection requirements, and makes forest fire prevention more efficient and intelligent.

This invention discloses an airborne display and control method for enhancing situational awareness and flight operations, comprising: providing onboard operational information and basic traffic, weather, and terrain displays based on flight phases and crew operational requirements, configuring display content and layout, and establishing basic situational awareness; providing a list of traffic aircraft dynamic information, setting aircraft of interest, and acquiring operational information of aircraft of interest to establish enhanced traffic situational awareness; receiving conflict detection, conflict prediction, and conflict resolution information at short, medium, and long ranges, and outputting alarm information in visual, auditory, or tactile forms according to alarm priority to establish enhanced conflict alarm situational awareness; applying for and receiving control clearance for enhanced flight operations through CPDLC, calling the flight operation setup program, and inputting the information required for enhanced flight operations; and generating target flight paths and target flight states in real time based on enhanced flight operation requirements, and implementing enhanced flight operations by the crew or flight management system.

A flight analytics system may receive, from a flight recorder of an aircraft, flight data corresponding to one or more routes flown by the aircraft. The flight analytics system may obtain, based on a downlink message sent by the aircraft in-flight, version information of a first navigation database (NavDB) used in-flight by a flight management system of the aircraft while flying the one or more routes. The flight analytics system may determine, based on the version information of the first NavDB, a second NavDB that matches the first NavDB. The flight analytics system may perform, using the second NavDB, flight data analysis on the flight data. The flight analytics system may output, based on the flight data analysis, flight analytics data for the one or more routes flown by the aircraft.

A method includes obtaining first humidity data indicative of a first humidity value at an origin airport of a flight. The method also includes obtaining second humidity data indicative of a second humidity value at a destination airport. The method also includes determining, based on the first humidity data, a first fuel flow rate adjustment for a first phase of flight from a first altitude of the origin airport to a threshold altitude. The method also includes determining, based on the second humidity data, a second fuel flow rate adjustment for a second phase of flight from the threshold altitude to a second altitude of the destination airport. The method also includes estimating total fuel flow for the flight based on the first fuel flow rate adjustment and the second fuel flow rate adjustment.

TITLE: Flight management system adapted for scalable energy management The present invention relates to a flight management system (12) comprising: - a flight organization device (16) including: + a calculation module (20) configured to calculate a trajectory and guidance instructions for the aircraft (10) from positioning data (26) and a flight plan for the aircraft (10), and + an estimation module (22) configured to estimate a set of aeronautical quantity(ies) (28) of the aircraft (10); and - an energy management device (18) including a prediction module (34) configured to predict a set of energy quantity(ies) (40) of the aircraft (10) at at least one point of the calculated trajectory. The flight organization device (16) and the power management device (18) are separated and distinct from each other via at least one partitioning among a software partitioning and a hardware partitioning.Figure for the abbreviation: Figure 2.

The invention relates to the technical field of airport operation, in particular to a ferry vehicle scheduling method and a server. Through multi-system interaction with the flight management system, the airport management system and the ferry vehicle management system, the flight data, the airport operation information and the vehicle information of the ferry vehicle are acquired, and the ferry vehicle is scheduled by fusing multi-dimensional information, so that the scheduling of the ferry vehicle meets the transport capacity requirement of the target flight, and the scheduling efficiency is improved. And dynamic scheduling can be carried out based on the real-time passenger flow and the operation state of the airport, so that the scheduling flexibility of the ferry vehicle is improved.

The invention provides a method and a device for judging the flight stage of a transport aircraft conforming to the operation expectation of a pilot, and the method comprises the steps: determining a guided flight stage of a current period according to a preset period, a working mode of an autopilot, a preselected height, a horizontal flight plan and a vertical flight plan; the guided flight stage comprises climbing CLM, cruising CRS and descending DES; the guide flight stage is used for generating a vertical guide instruction of the flight management system; and determining a man-machine interface flight stage according to the working mode of the autopilot, the preselected height, the horizontal flight plan and the vertical flight plan based on the judgment result of the guided flight stage. The method accords with the operation intention of the unit, enhances the vertical situation awareness capability of the unit, and provides a precondition for the output of the vertical guide instruction combination.

The avionics computer, in particular a flight management system, comprises a processing unit configured to compare a first altitude with what is referred to as a threshold altitude, the first altitude corresponding to the altitude of a missed approach point relative to the runway, the threshold altitude being equal to the sum of a second altitude corresponding to the altitude of the runway and of a threshold crossing height, and to determine a terminal point that has an altitude equal to the threshold altitude and that forms, with the position of the missed approach point, a straight line segment that has a slope equal to the slope of the straight line segment defined by the missed approach point and a final approach fix, said terminal point being capable of being used as anchor point, the avionics computer thus having improved properties especially in terms of availability and robustness.

The present disclosure relates to an FMS configured to accept a plurality of flight legs (beyond the standard five) for consideration when developing a flight plan. Allowing an FMS to receive a plurality of flight legs, beyond just five, is achieved by calculating a lateral trajectory and a vertical trajectory based on the current state of the flight path. This may be done mid-flight or initially when a given flight plan is entered by the pilot. The sequence of leg types that are entered may be used to generate a predicted final trajectory and output a GUI (graphical user interface) of the predicted final trajectory.

The application provides a kind of low-altitude weather intelligent management system of navigable airport based on multi-source weather data fusion, including three-dimensional grid monitoring network, for realizing three-dimensional scanning and dynamic perception of airspace weather environment by real-time acquisition of weather detection data;Data fusion system, for assimilating the real-time detection data collected and multi-source forecast data, generating high-resolution three-dimensional grid weather field covering the airspace range of the airport;Dynamic safety research module: for real-time research and judgment of the influence of current and future weather conditions on the flight safety of each aircraft type;Management system establishment module: the influence of current weather conditions on flight is visually displayed by establishing a flight management system in the form of visual charts.The application solves the problem of insufficient low-altitude weather service capability of existing navigable airport by intelligent perception, data fusion and decision-making prediction innovation system, and constructs a comprehensive weather safety protection system.

The invention discloses a low-altitude flight management system comprehensive capability dynamic evaluation and bottleneck identification method and system, and relates to the technical field of low-altitude flight and management systems, and the method comprises the steps: building a hierarchical index system, and obtaining the operation original data of a low-altitude flight management system, the hierarchical index system comprises a first hierarchy, a second hierarchy and a third hierarchy; performing index calculation based on the original data and the hierarchical index system to obtain index data; performing network construction and quantization processing on the hierarchical index system based on the index data to obtain a capability coupling network; based on the index data and the capability coupling network, carrying out comprehensive capability dynamic evaluation on the low-altitude flight management system to obtain a dynamic evaluation result; and based on the dynamic evaluation result and the capability coupling network, bottleneck identification processing is carried out on the low-altitude flight management system to obtain a bottleneck identification result, and the bottleneck identification result represents a node playing a role in restricting the capability of the low-altitude flight management system.

This invention relates to the field of helicopter flight management system technology, and in particular to a half-plane segment switching method for low-altitude obstacle avoidance flight. This method extracts flight plan information, calculates the turning direction based on the azimuth information of the preceding and following segments, and further calculates the turning angle. Based on the turning direction and angle, it calculates the azimuth of the angle bisector of the preceding and following segments, and then determines whether the helicopter meets the segment switching conditions based on the sign of its offset from the angle bisector. This segment switching method is independent of flight technical errors and significantly improves segment switching efficiency.

This disclosure relates to improved techniques for upgrading legacy flight management systems (FMSs) installed in an aircraft. In certain embodiments, an integrated guidance system (IGS) can be installed in an aircraft having a legacy FMS to provide enhance flight functionalities, such as required navigation performance (RNP), localizer performance with vertical guidance (LPV), and automatic dependent surveillance-broadcast (ADS-B), capabilities. Additionally, the IGS described can include, inter alia, a navigator system that receives and processes information from an ADS-B system to implement a variety of automated following options, each of which can provide an automated mechanism for controlling a flight path of the aircraft relative to another aircraft that is being tracked by an ADS-B system.

The embodiment of the invention relates to the technical field of flight management, and provides a flight plan management method and device for a flight management system, and the method comprises the steps: analyzing a navigation database file of a target protocol, and writing the analyzed navigation data into a target database, the navigation data including airports, waypoints, routes and flight program data; a flight plan creating instruction input by a target user is received through CDU simulation unit software, and the flight plan creating instruction at least comprises a takeoff airport, a target airport and waypoint numbers or route names; based on the flight plan creation instruction, extracting target data from a target database, and generating a flight plan; receiving and responding to an activation instruction input by the target user, and activating the flight plan; and controlling the target flight trainer to execute the activated flight plan based on the activated flight plan. The creation, editing, activation and dynamic over-point calculation of the flight plan can be completely reproduced in the trainer through simulation software, and the cost is reduced.

The present invention proposes a device and a method for calculating a safe 4D flight path for an aircraft to avoid conflicts with stationary or moving objects. The device according to the invention comprises a flight path safety module that interacts with a flight management system and consists of a conflict risk assessment module and a conflict resolution module. The conflict resolution results in a hierarchically ordered list of solution flight paths, which can be based on a lateral and / or a vertical solution and / or a combined solution, depending on the current state of the aircraft, the type of conflict, and the type of object.

The invention discloses a task management system and a task management method suitable for a swarm unmanned aerial vehicle system, and in the task management system, hardware cross-linking, remote control instruction transmission and remote measurement information transmission are carried out between a command control subsystem and a flight control subsystem; the flight control subsystem is connected with the task control subsystem, and task control and management information for the swarm unmanned aerial vehicle system is processed through the task control subsystem, so that modification of the unmanned aerial vehicle from a single unmanned aerial vehicle to multiple unmanned aerial vehicles is realized by additionally arranging the task control subsystem; the task control subsystem and the task load subsystem are crosslinked, and the task control subsystem is used for transmitting a remote control instruction and a telemetering return of the task load subsystem and receiving task image information from the task load subsystem; the command and control subsystem and the task load subsystem are crosslinked, and the task load subsystem transmits task image information to the command and control subsystem, so that the ground station can display the task image information in real time. According to the technical scheme provided by the invention, the problem that the existing flight management system of the unmanned aerial vehicle is difficult to realize information interaction, instruction control, cooperative task execution and autonomous task planning among multiple unmanned aerial vehicles in a swarm unmanned aerial vehicle system is solved.

This disclosure relates to improved techniques for upgrading legacy flight management systems (FMSs) installed in an aircraft. In certain embodiments, an integrated guidance system (IGS) can be installed in an aircraft having a legacy FMS to provide enhance flight functionalities, such as required navigation performance (RNP), localizer performance with vertical guidance (LPV), and automatic dependent surveillance-broadcast (ADS-B), capabilities. Additionally, the IGS described can include, inter alia, a navigator system that receives and processes information from an ADS-B system to implement a variety of automated following options, each of which can provide an automated mechanism for controlling a flight path of the aircraft relative to another aircraft that is being tracked by an ADS-B system.

The invention relates to the technical field of unmanned aerial vehicle inspection, in particular to an unmanned aerial vehicle intelligent inspection system for a photovoltaic power generation matrix, and the system comprises a flight management system which comprises a control platform for remotely managing the flight line of an unmanned aerial vehicle body and a landing platform for guiding the unmanned aerial vehicle body to stop on site; and the battery replacing system is connected with the landing platform and comprises a battery disassembling assembly arranged on one side of the landing platform and a switching unit arranged on one side of the landing platform. Through mutual cooperation of the flight management system and the battery replacement system, flight of the unmanned aerial vehicle body can be managed, battery replacement can be carried out in time when the electric quantity of the unmanned aerial vehicle body is insufficient, and the problems that an existing unmanned aerial vehicle body is limited in electric quantity endurance and long in charging and battery replacement time, and the inspection efficiency is affected are solved.

In order to help pilots relying on manual visual inspection to realize autonomous landing more safely, the invention provides a method for assisting autonomous landing by using an airborne Doppler navigation radar and an airborne radar altimeter. Firstly, the glide speed can be obtained by directly utilizing the existing speed detection data of the airborne Doppler navigation radar. And secondly, calculating an inclination angle in a vertical plane by using detection data of Doppler frequency shift by a Doppler navigation radar, thereby obtaining a glide angle. Or the glide angle is calculated according to the trigonometric function relation by using the three-dimensional velocity component measured by the airborne Doppler navigation radar. And then on the basis of acquiring height measurement data by using an airborne radar altimeter, calculating a glide distance by using the acquired glide angle and a trigonometric function relationship. Furthermore, if the aircraft is further provided with a flight management system, an automatic driving system and the like, technical support can be provided for semi-automatic landing by using landing data provided by an airborne Doppler navigation radar and a radar altimeter.

The invention belongs to the technical field of aircraft flight control system design, and relates to an aircraft landing grounding point prediction and alarm method based on a real-time flight trajectory. According to the method, the position of the aircraft landing grounding point is predicted and iteratively updated in real time by judging the actual landing stage of the aircraft and combining the actual position information, height information and speed information in the flight of the aircraft. And further judging whether the aircraft has the risk of rushing out of the runway or not by using the position of the grounding point, the landing runway information and the required skating distance information in the flight management system, and if so, performing rushing-out alarm. According to the method, the position of the aircraft grounding point can be rapidly and iteratively predicted in the actual flight process of the aircraft, and the method can adapt to complex uncertainty in the flight process; and then the landing runway information and the required sliding distance information in the flight management system are combined to judge whether the airplane has the risk of rushing out of the runway or not, and the runway rushing-out alarm is correspondingly carried out.

To automatically set an optimum flight route only by selecting various work objects.SOLUTION: A flight management server according to the present invention is connected to a user terminal and an unmanned aerial vehicle via a network. The flight management server includes a storage unit configured to store flight route information including flight parameters and a plurality of destination Bettobu applications, a reception unit configured to receive a flight request including at least a flight location and a flight purpose, a generation unit configured to generate, based on the flight request, a flight mission including a flight route generated with reference to the flight route information and a flight application selected from the destination Bettobu applications, and a communication unit configured to transmit the generated flight mission to the unmanned aerial vehicle.SELECTED DRAWING: Figure 2

This invention discloses a cloud-edge-airborne collaborative intelligent flight management system and method. The system includes: a cloud brain decision center for generating and evolving a global flight strategy knowledge graph based on hierarchical federated meta-reinforcement learning; an edge intelligent collaborative network whose nodes possess multimodal threat causal prediction and distributed collaborative decision-making capabilities based on graph neural networks and game theory; and an airborne autonomous safety agent integrating a trusted execution environment and formal verification, employing a hierarchical-reflective adaptive controller with independent reflection layers. The system ensures trusted data synchronization across layers through a blockchain-enabled decentralized data lake and achieves closed-loop collaborative evolution of strategies, models, and control logic based on a digital twin simulation environment. This method realizes autonomous intelligent management from global strategy optimization and local real-time collaboration to airborne safety execution, significantly improving flight safety, efficiency, and system adaptability in complex airspace.

A method and system for developing a taxiing plan for an aircraft based on maximizing use of inertial thrust has been developed. First, taxiways include distances and stopping points for the aircraft are downloaded from a taxiway database with a flight management system (FMS). A desired speed is determined for the aircraft while using the taxiway along with calculating required engine thrust that is necessary to maintain the speed. A speed dissipation segment of each taxiway is calculated which is the estimated distance on the taxiway where the aircraft will stop if the thrust from the aircraft engine is reduced to idle and the speed of the aircraft relies on inertial thrust that dissipates along the segment. The start point of the speed dissipation segment is displayed to the pilot of the aircraft so the pilot may reduce the aircraft engine thrust to idle upon reaching the start point.

Electronic installation and decision support method with enhanced energy alert management, aircraft and associated computer program This electronic installation (15) for decision support of an aircraft operator (10) includes a display system (18) and a flight management system (20).The flight management system (20) includes: + a low-power alert module (30) that activates if the remaining power is estimated to be insufficient for a current flight plan; the alert module (30) inhibits the alert for a time delay from the moment the remaining power is estimated to be insufficient, with the alert being issued only when the time delay has elapsed; + a display module (32) for displaying information about the alert on the display system (18); + a module (34) for calculating the aircraft's (10) range; + a module (36) for detecting if the aircraft (10) is climbing; and + a modification module (38) that increases the time delay if the calculated range exceeds a threshold and the aircraft (10) is climbing. (See Figure 1 for abbreviations.)

The embodiment of the invention relates to the technical field of flight management, and provides a flight plan waypoint management method and device for a flight management system, and the method comprises the steps: obtaining and analyzing a navigation database file which accords with a target protocol, writing the analyzed navigation data into a target database, and creating a waypoint data table set; a waypoint operation instruction triggered by a target user is received, and the waypoint operation instruction is input through pre-constructed CDU simulation unit software; and based on the waypoint operation instruction, querying the waypoint data table set through flight management simulation software, executing waypoint operation processing, and returning an operation processing result to the CDU simulation unit software in real time for picture refreshing. Therefore, the simulation software can completely reproduce the creation, editing and deletion operation control of the flight plan waypoint in the trainer, and the cost is reduced.