50 results about "Flight management system" patented technology

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.

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.

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 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.

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.

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.

The invention belongs to the technical field of flight management systems, and relates to a navigation sensor monitoring method based on a flight management system. The method comprises the following steps: firstly, carrying out input validity judgment according to a working state word and navigation data of an airborne navigation sensor; then stability judgment is carried out on the navigation data; effectiveness judgment is carried out according to input effectiveness judgment and stability judgment results, and a sliding window filter is introduced in effectiveness judgment to carry out smoothing processing on local outliers to reduce false alarms; and finally, performing redundancy voting judgment, and voting sensor data which can be used for navigation data fusion through data comparison among navigation sensors. And when monitoring that the navigation data is invalid, sending out alarm information. According to the method, navigation sensor data monitoring is carried out from three dimensions of sensor states, single sensor data and multi-sensor voting, the reliability of sensor monitoring results is improved by fully utilizing multi-sensor redundant information, fault sensor information can be identified, and the fault-tolerant capability of the system is improved. The method is easy to implement, has high engineering practical value, and has been applied to civil aircraft flight management system projects.

An avionics system includes a flight management system and a receiving unit. The receiving unit has a processor and a communication link. The receiving unit is configured to generate at least one dedicated message, transmit at least one dedicated header frame to a data network, generate a set of qualifying data frames, and transmit at least a subset of the qualifying data frames to the data network. The flight management system is configured to receive the transmissions from the receiving unit.

The present disclosure provides a turbulence management system for providing suggestions to a pilot that mitigate the effects of turbulence. These suggestions can be output to the pilot using an EFB. As mentioned above, an EFB can be communicatively coupled to a FMS such that the EFB has access to the data in the FMS. From the pilot's interactions with the FMS, the EFB can identify the pilot's intent such as landing, taking off, plotting a course change, changing altitude, maintaining a cruising altitude, etc. Once the intent is known, the EFB can output a suggestion to the pilot that satisfies the intent, but mitigates the harmful effects of turbulence. In one aspect, this suggestion is generated using the flight plant and aircraft metrics available from the FMS.

The invention discloses a vertical navigation method based on a state machine. The method comprises the following steps: S1, acquiring vertical navigation parameters sent from an autopilot and aircraft state parameters output by an atmosphere data calculation module in real time; s2, acquiring flight plan information from a flight management system, and acquiring a next effective height constraint from the currently activated flight plan; s3, when the effective height constraint is obtained, calculating the required vertical speed RVS from the current position to the height constraint; s4, executing a vertical navigation state machine, and processing each state of the state machine according to the current state of the airplane and the vertical mode received from the autopilot; and S5, processing the output of each state of the state machine to obtain a vertical navigation instruction, sending the vertical navigation instruction to the autopilot, and completing closed-loop interaction with the autopilot. Based on the mechanism of the state machine, the automatic state switching of the vertical navigation is realized, and the safety efficiency and the automation degree of the vertical navigation are improved.

The head-up guidance system for aircraft takeoff of the present invention includes: a display panel for mode selection and notification, a sensor group, a flight management system, a takeoff guidance calculation module, a symbol image generation module, and a head-up display device. The head-up guidance system and mode switching logic for aircraft takeoff are suitable for various large transport aircraft and have versatility.

The application provides an anti-fraud detection method, a data processing method and a flight management system. The method comprises the following steps: selecting a navigation source as a first navigation source and selecting another navigation source as a second navigation source from a plurality of preset navigation sources; acquiring navigation data of the plurality of preset navigation sources and performing fraud detection calculation on the first navigation source by using the navigation data; determining whether the first navigation source is fraudulent according to a result of the fraud detection calculation, and performing fraud detection calculation on the second navigation source by using the navigation data except the first navigation source in the case that the first navigation source is determined to be fraudulent. The application performs fraud detection on the navigation data of the first navigation source by using the navigation data of the second navigation source and other navigation sources, so that the detection accuracy is higher, and pseudo-range level fraud interference detection on the first navigation source can be realized.

The invention provides an aircraft performance parameter input system and method, and the system comprises a data collection module which is disposed on an installation type EFB device, and is used for collecting the aircraft system data of a flight management system of an aircraft and the environment data of a ground server; and the performance calculation module is deployed on the portable EFB equipment and the mounted EFB equipment, and is used for calculating and evaluating whether the take-off, cruise and landing performances of the airplane meet the safe operation standard or not according to the airplane system data and the environment data provided by the data acquisition module. According to the aircraft performance parameter input system and the input method thereof, the automation degree of the aircraft performance calculation module can be improved, and the consistency and the correctness of unit inspection data are helped; by applying the system and the input method, the situation that a unit spends a lot of time for data input and proofreading work can be avoided, the workload of the unit is reduced, and the possibility of human errors is reduced, so that the flight safety is improved.

This disclosure relates to a humidity-based performance adjustment system and method in an aircraft flight management system. One method includes obtaining first humidity data representing a first humidity value at a departure airport. The method further includes obtaining second humidity data indicating a second humidity value at an arrival airport. The method also includes determining a first fuel flow rate adjustment based on the first humidity data for a first flight phase from a first altitude at the departure airport to a threshold altitude. The method further includes determining a second fuel flow rate adjustment based on the second humidity data for a second flight phase from the threshold altitude to a second altitude at the arrival airport. The method also includes estimating the total fuel flow rate of the flight based on the first and second fuel flow rate adjustments.

1. Name of the product in this design: Graphical User Interface for Low-Altitude Flight Management of Electronic Equipment. 2. Intended use of this design: for use in an electronic device. 3. The key design feature of this product is its graphical user interface. 4. The picture or photo that best illustrates the key design points: Design 1 front view. 5. Other views are omitted as they are standard design. 6. Design 1 is designated as the basic design. 7. Purpose of the graphical user interface: This interface is the interface for the low-altitude flight management system, used to view and manage information at various levels during flight activities. 8. Other situations requiring explanation: The map in the lower right corner of the interface is used to demonstrate the interface effect and is not subject to protection.

The flying device will avoid colliding with objects that it needs to avoid. [Solution] The flying device 2 includes a detection unit 272 that detects an object to be avoided, which is an object that the flying device 2 is intended to avoid, located within an area captured by an image of the area including the ground surface below the flight path it is flying; a calculation unit 273 that calculates a movable area, which is an area in which the object to be avoided may move within a predetermined time; a specification unit 274 that identifies the area to which the flying device 2 may fall onto the ground within a predetermined time based on the flight state of the flying device 2; and a modification unit 275 that, if the movable area of ​​the object to be avoided is included in the identified area to be avoided, changes the flight path to a modified route, which is a modified route in which the movable area is not included in the identified area to be avoided, based on the flight state corresponding to the modified route.

The present application belongs to the technical field of flight management system, and particularly relates to a kind of over point turn track calculation method.The method extracts flight plan information, calculates the turning direction according to the azimuth information of the front and rear flight segments, and further calculates the azimuth of the straight transition segment.First, the center angle corresponding to the transition arc 1 is calculated, the starting point coordinates of the straight transition segment are calculated, the end point coordinates of the straight transition segment are calculated, the turning center coordinates corresponding to the transition arc 1 are calculated, the turning center coordinates corresponding to the transition arc 2 are calculated, the turning end point coordinates corresponding to the transition arc 2 are calculated, and finally the complete track of the over point turn is calculated in combination with the first waypoint, the second waypoint and the third waypoint in the flight plan.The flight transition analysis algorithm increases the determinability and repeatability of the track, and improves the flight quality of the aircraft during the over point turn.