190 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.

Described are various embodiments of a flight management method and system using same. In one embodiment, a digital flight management system comprises: a digital processing environment comprising instructions to access: flight request data related to a flight plan; aircraft parameter data; a flight risk data source; and geographical data. The instructions are executable to: calculate a predicted flight path; digitally compare the predicted flight path with flight risk data from the flight risk data source to assess a flight risk associated with the predicted flight path; and display via a user interface the predicted fight path in accordance with the flight risk.

The invention discloses a forest fire prevention unmanned aerial vehicle automatic inspection system based on meteorological factors. The forest fire prevention unmanned aerial vehicle automatic inspection system comprises a meteorological data acquisition device, an unmanned aerial vehicle field and edge calculation device, a remote data analysis and flight management system and an unmanned aerial vehicle. The meteorological data acquisition device is used for acquiring meteorological factor data of different meteorological conditions, special festivals and holidays or different seasons in real time; the unmanned aerial vehicle field and edge computing device is used for receiving the meteorological factor data, cleaning and processing the meteorological factor data to obtain processed data, and controlling the unmanned aerial vehicle to cruise the inspection area; the remote data analysis and flight management system is used for analyzing the processed data, judging forest fire danger meteorological levels under different conditions, formulating cruise tasks of different unmanned aerial vehicles and sending the cruise tasks of the unmanned aerial vehicles; the unmanned aerial vehicle automatically executes a cruising task according to the control command; the system can automatically increase the forest fire prevention inspection frequency of the unmanned aerial vehicle according to the special nodes, meets the actual inspection requirements, and enables the forest fire prevention to be more efficient and intelligent.

According to the instruction consistency studying and judging device based on the data chain, consistency comparison between unit intentions and control instructions is achieved, potential conflicts are studied and judged, and flight safety is improved. The system comprises an air-ground data interaction cooperation system, an air-ground interconnection and instruction consistency research and judgment system, and a data link flight instruction verification and intention extraction system. The air-ground data interaction and cooperation system is used for acquiring and processing data required by system operation and providing data support for other modules; the air-ground interconnection and instruction consistency research and judgment system judges the timeliness according to the instruction type and continuously monitors the intention of the unit according to a certain strategy; the data link flight instruction verification and intention extraction system realizes real-time acquisition of activated airway and flight path profile data extracted from the airborne flight management system through a safety ground-air data link and extracts unit intention information and high-precision flight path profile information.

The invention belongs to the technical field, and relates to a flight management system sensor simulation test method based on an RT real-time environment. Real-time fault simulation of a bus signal output by a sensor is realized by a flight management system semi-physical test method verification platform through a software programming technology and a programmable software interface technology; comprising the steps of single-byte setting, fault data simulation, normal data simulation, switching between a sensor bus signal simulation interface and a real object interface, bus signal transmission path fault simulation and flight management system sensor simulation test. The semi-physical simulation test method is high in real-time performance, small in size, strong in function, high in precision and capable of achieving the functions of fault simulation, data interaction, object / simulation interface switching and the like of bus signals, and has the advantages of being high in speed, comprehensive in function, capable of achieving fault simulation and the like.

Vehicle systems and methods are provided for updating vehicle systems in response to an update event at one of the vehicle systems, such as, for example, an update at a flight management system (FMS) of an aircraft. One method involves the FMS obtaining event data from an external source indicative of an update event, updating flight data at the FMS to an updated state based at least in part on the event data, and then adding the event data to an event queue after updating the flight data at the FMS to the updated state. One or more other vehicle systems can asynchronously retrieve the event data from the event queue and independently update in response to the event data.

A flight management system of an aircraft includes a first non-critical or open world module for creating an enhanced enriched flight plan, the first module being configured to create the enhanced enriched flight plan iteratively by the following steps: initialisation of pseudo-constraints; and iterative enhancement of the choice of pseudo-constraints, until an objective of enhancement or of absence of enhancement with respect to the last best choice of pseudo-constraints is reached, based on at least one optimisation criterion and on at least one parameter representative of the environment of the flight of the aircraft; the second critical or flight management avionics module certified to calculate a path, comprising at least one critical computer and / or at least one critical piece of software for calculating and delivering as output a secured path, based on the enhanced enriched flight plan supplied by the first module.

An object of the present disclosure is to provide a flight management apparatus capable of improving the safety of flying objects. In one example, a flight management apparatus (10) of the present disclosure includes a determination unit (12) configured to determine whether a specific space cell in a space is already reserved based on a reservation state about the specific space cell, when the flight management apparatus receives a request for permission to move to the specific space cell from a flying object; and a permission unit (13) configured to permit the movement to the specific space cell of the flying object when the determination unit determines the specific space cell is not reserved, and not to permit the movement to the specific space cell of the flying object when the determination unit determines the specific space cell is already reserved.

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 discloses a head-up guidance system for an aircraft takeoff process. The system comprises a display panel for mode selection and notification, a sensor group, a flight management system, a takeoff guidance calculation module, a symbol picture generation module and head-up display equipment. The method is used for a head-up guidance system and mode switching logic in the takeoff process of an aircraft, is suitable for various large transportation aircrafts, and has universality.

A flight display provides Runway Alignment Indications on an Airport Moving Map. The Runway Alignment Indications include Landing Runway Detection Zones on the Airport Moving Map for the crew-selected runway or the FMS arrival runway. The Landing Runway Detection Zones are geometrically sized, oriented, and placed in relation to the applicable landing runway approach thresholds.

An aircraft includes at least one source collecting a set of navigational parameters of the aircraft, the at least one source obtaining flight data for the aircraft and including at least one of a global positioning system, an inertial reference system, or a sensor. The aircraft further includes a flight control computer communicatively coupled to the source and including a first processor and a first memory having a machine-readable medium, as well as a flight management system communicatively coupled to the flight control computer.

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.

Systems and methods are provided for management of an active flight plan during operation of an aircraft. The systems include a flight management system, a communications system configured to receive flight mission data from external sources, a display device, and a controller. The controller is configured to, by a processor: receive the flight mission data that includes recommended updates to the active flight plan, generate an inactive flight plan including the active flight plan modified based on the recommended updates, access the inactive flight plan to determine an impact of the recommended updates on the active flight plan, render a graphical image on the display device that presents a contextual preview of the recommended updates and the impact thereof, and in response to acceptance of the recommended updates, modify the active flight plan based on the recommended updates or replace the active flight plan with the inactive flight plan.

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 computer-implemented method for retrieving flight data in a medical emergency includes receiving, by one or more processors of a first user device and via an application programming interface, an indication of a medical emergency aboard an aircraft; retrieving, by the one or more processors and responsive to receiving the indication of the medical emergency, flight data associated with the medical emergency from a flight management system associated with the aircraft; automatically categorizing, by the one or more processors, the retrieved flight data based at least on one or more flight data fields associated with the medical emergency to generate categorized flight data; and transmitting, by the one or more processors, at least some of the categorized flight data to a second user device external to 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.

Electronic installation and method for decision support with simulation flight plan, civil aircraft and associated computer program This electronic installation (15) for decision support for an operator of a civil aircraft (10) comprises an information display system (18); a human-machine interface (19); and a flight management system (20) comprising a module (30) for acquiring flight plan parameters defined by the operator, a module (32) for determining at least one flight plan from the flight plan parameters, and a module (34) for displaying, on the information display system, each flight plan determined.The determination module (32) determines a simulation flight plan, separate from and in addition to an active flight plan, from associated flight plan parameters, the display module (34) temporarily displaying the simulation flight plan, the latter being automatically erased if no operator action associated with the simulation flight plan is detected by the human-machine interface for a predetermined period. Figure for the abstract: Figure 1.

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.

The invention provides a radio automatic tuning method and device for a helicopter flight management system, and the method comprises the steps: S1, a flight management system obtains the position information of a helicopter, and the position information comprises latitude and longitude; s2, searching a preset database by the flight management system, and determining whether the helicopter enters a coverage range of a second ground platform except the first ground platform or not; the first ground platform is the currently accessed ground platform; the preset database stores the frequency and the coverage range of each radio communication navigation ground station; and S3, if yes, switching the frequency of the airborne radio communication navigation equipment to the frequency of the second ground station. Frequency tuning can be automatically carried out on radio communication and navigation equipment according to the current position of the helicopter, the operation automation degree in the flight process is greatly improved, and the operation load of a unit is effectively reduced.