1398 results about "Flight safety" patented technology

Several improvements to an aircraft turbine engine and Auxiliary Power Unit (APU) are disclosed, as well as methods of using these improvements in routine and emergency aircraft operations. The improvements comprise the addition of cockpit-controllable clutches that can be used to independently disconnect the engine's integrated drive generator (IDG), engine driven pump (EDP), fuel pump, and oil pump from the engine gearbox. These engine components may then be connected to air turbines by the use of additional clutches and then powered by the turbines. Similar arrangements are provided for the APU components. Cranking pads, attached to various engine and APU components, are disclosed to provide a means for externally powering the components for testing purposes and to assist with engine and APU start. Detailed methods are disclosed to use the new components for routine ground-testing and maintenance and for the enhancement of flight safety, minimization of engine component damage, and extension of engine-out flying range in the case of an emergency in-flight engine shutdown.

The invention discloses a drone control method comprising the steps that the current position and attitude of a drone are acquired; whether the drone enters a restricted area or a no-fly area is judged according to the current position and attitude of the drone; and when the drone enters the restricted area or the no-fly area, flight of the drone is controlled according to a flight control strategy corresponding to the area. The invention also discloses drone control device, the drone with the control device and a ground control system. The drone is enabled to automatically avoid the no-fly area so that flight efficiency and flight safety can be enhanced.

Several improvements to an aircraft turbine engine and Auxiliary Power Unit (APU) are disclosed, as well as methods of using these improvements in routine and emergency aircraft operations. The improvements comprise the addition of cockpit-controllable clutches that can be used to independently disconnect the engine's integrated drive generator (IDG), engine driven pump (EDP), fuel pump, and oil pump from the engine gearbox. These engine components may then be connected to air turbines by the use of additional clutches and then powered by the turbines. Similar arrangements are provided for the APU components. Cranking pads, attached to various engine and APU components, are disclosed to provide a means for externally powering the components for testing purposes and to assist with engine and APU start. Detailed methods are disclosed to use the new components for routine ground-testing and maintenance and for the enhancement of flight safety, minimization of engine component damage, and extension of engine-out flying range in the case of an emergency in-flight engine shutdown.

An avionics system and method is employed for alerting pilots of low premature descent during final landing approach. The method involves determining Final Approach Flight Safety Altitudes for a plurality of runways, identifying which runway an aircraft is likely to land on, and alerting the pilot if the aircraft altitude is lower than the final approach flight safety altitude. The method takes into account terrain information, airport and runway information, and aircraft reference data to make its determination. Particular embodiments reference the Final Approach Fix, one or more step down fix values, the Minimum Descent Altitude and the Missed Approach Point in calculating the Final Approach Flight Safety Altitudes. The system and method have particular utility with a Terrain Awareness and Warning System (“TAWS”) and display in an aircraft.

The invention relates to a miniature electric ducted propeller type intelligent unmanned aerial vehicle, which consists of a ducted casing, a bracket, a coaxial counter propeller, a fairing, a battery, a motor, a driving control circuit and a microcontroller. The machine body has a dish-shaped appearance; and the ducted casing is arranged outside a rotor wing to eliminate flight safety threat caused by the traditional structure of the exposed rotor wing and improve the working efficiency of the propeller. The aerial vehicle adopts a design of the coaxial counter double-rotor wing, cancels the inertial rotation of the machine body without a tail rotor wing, saves materials and expands the operating space. The propeller is driven by the motor; the motor is under the servo control of the driving control circuit; and the horizontal motion of the aerial vehicle in the air is implemented by a deflectable guide plate below the propeller in a matching mode. In addition, a multi-azimuth convenient slot is formed inside the ducted casing of the aerial vehicle for mounting and detaching various sensors at any time; and the microcontroller comprehensively processes information fed back by each sensor and performs autonomous flight control according to a task.

The invention discloses a three-dimensional aerial airway map of an unmanned aerial vehicle and a dynamic building method thereof. Through the unmanned aerial vehicle and based on an existing ground two-dimensional map, a three-dimensional aerial map of an area, which is needed for flight, is obtained; important information is marked on the map; an air route is designated in the three-dimensional aerial map; the three-dimensional aerial airway map is built and stored in a cloud server of the area; a user can download the data of the map by using a terminal, looks up the information, creates a flight mission, looks into the information of the unmanned aerial vehicle in real time, and meanwhile, periodically utilizes the information sent back by the unmanned aerial vehicle provided with a direction sensor and a camera to build a new three-dimensional map, to check a change which occurs on an airway and influences flight safety, and to update and maintain the map; meanwhile, the server can autonomously plan the airway and navigate for the unmanned aerial vehicle according to the real-time information and flight mission of the unmanned aerial vehicle in each area.

The invention relates to an unmanned aerial vehicle-mounted laser radar system, which consists of an unmanned aerial vehicle flying platform subsystem, a laser radar subsystem and ground protection and communication subsystems, wherein the unmanned aerial vehicle flying platform subsystem takes an unmanned helicopter as a carrying platform, the laser radar subsystem is used for acquiring three-dimensional spatial information and digital image data and consists of a laser scanner, an IMU (Inertial Measurement Unit), and a high-resolution aerially-photographing digital camera, and the ground protection and communication subsystems are used for protecting flying safety and timely returning working state information of the system. With the adoption of the unmanned aerial vehicle-mounted laser radar system, the patrol efficiency can be increased, the patrolling means is scientific, intuitive and accurate, the potential problems can be timely discovered so as to ensure safe operation and reduce economic losses, and thus, the unmanned aerial vehicle-mounted laser radar system has the characteristics of low cost, simplicity for operating, high accuracy of data and the like.

The invention provides a multi-target route planning and united searching method of a drone in an urban low-altitude environment, and belongs to the technical field of drone route planning. The method comprises steps of firstly, based on a static-state known obstacle, constructing a static-state safe index map, and based on an obstacle which is actively detected by the drone in a flight process and is not marked in a geographical map, constructing a dynamic state safe index map on an airborne platform; and then, based on offline searching and online searching, solving and optimizing a multi-target route planning problem of flight time and flight safety of the drone in an united manner. According to the invention, a path costing little from a start point to a termination point is planned in an offline manner; when an unknown obstacle is detected, a changed flight track is planned in an online manner through online searching, so a dynamic obstacle is avoided; and there is a quite small searching space in the online searching, so a safe route can be planned again from the drone rapidly, so requirements on real-time planning of routes for drones are met.

A radar altimeter system with a closed-loop modulation for generating more accurate radar altimeter values. The present invention combines flight safety critical sensors into a common platform to permit autonomous or semi-autonomous landing, enroute navigation and complex precision approaches in all weather conditions. An Inertial Navigation System (INS) circuit board, a radar altimeter circuit board and a Global Navigation Satellite System (GNSS) circuit board are housed in a single chassis. VHF (Very High Frequency) Omni-directional Radio (VOR), Marker Beacon (MB), and VDB (VHF Data Broadcast) receiver circuit boards may also be implemented on circuit boards in the chassis.

The invention discloses a mid-term air traffic conflict detection method based on 4D flight path and radar data, which relates to air traffic control automation. In the method, accurate 4D flight path data and real-time radar data are projected onto a display panel of an air traffic control system, each aircraft pair is filtered according to the accurate 4D flight path data and the real-time radar data, and aircrafts which are unlike to come into conflict with other aircrafts in 30 minutes are determined; and the detection is focused on the aircraft pairs which have potential to run into conflicts, the covariance between the relative speed and relative position of the aircraft pairs is calculated by using coordinate transformation according to the vertical interval and time interval of two aircrafts, and then the probability that a predicted position interval is smaller than a safe interval at time t is calculated and a detection report is made. In the invention, the drawbacks of long-term and short-term conflict detection are overcome, and the long-term conflict detection, mid-term conflict detection and short-term conflict detection are combined to ensure flight safety. The average conflict detection time is about 0.028 seconds, and the method has high real-time performance.

A method and system compares combinations of vehicle or aircraft state variables against known combinations of potentially dangerous states. Alarms and error messages are selectively generated based on such comparisons. In one embodiment, pairs of aircraft state variables are selected and compared to known undesirable pairs of state combinations that indicate an error or a condition that a crew should monitor closely. The combinations and error messages are provided by the database. The comparisons are conducted on a periodic basis monitoring real time states of the parameters collected from various sensors and commands. Experts considering a matrix that provides an exhaustive pairwise comparison of potentially important state variables initially identify undesirable state combinations. Error messages and identification of potential alarms are generated based on both knowledge of actual accidents, and on use of expert knowledge to predict potentially dangerous states.

The invention provides an unmanned aerial vehicle cruising and monitoring system for forest fire. The weight of the unmanned aerial vehicle is reduced, flight time is prolonged, an unmanned aerial vehicle cruising range is enlarged, route planning is carried out for fire monitoring, and an unmanned aerial vehicle flight control system is combined with a geographic information system. The route planning not only guarantees monitoring quality and monitoring full coverage but also considers the hardware parameters and the flight safety of the cruising unmanned aerial vehicle, a rotary head carries a thermal infrared imager and a colorful high-definition camera, the thermal infrared characteristics of the image of the forest fire are fully utilized, and an automatic monitoring and identification method for forest fire information is designed. Even if the forest fire monitoring distance of the unmanned aerial vehicle is long, fire characteristics can be accurately captured. A colorful high-definition image is compressed and transmitted back to a ground command post, a high-definition fire video image can be quickly transmitted to the ground, a fire position can be accurately reported, so that convenience is brought to the ground command post in accurately judging a fire situation and organizing people to fight the fire, and precious fire-fighting time is saved.

Flight safety and air vehicle deconfliction are of paramount concern in the operation of manned aircraft. The introduction of unmanned aerial vehicles (UAVs) in quickly growing numbers raises the risks of mid-air collisions, near misses, and diversions from intended flight paths. This application discloses a series of linked process whereby such risks may be significantly reduced and may enable the safe integration of UAVs into the national airspaces of the United States and other nations. The disclosed process allows emergency responders and others to declare an emergency air operations zone (perhaps near the expected landing spot of a medivac helicopter) and notify UAV operators in the vicinity of that zone of the emergency and suggested or mandated actions for the UAV operators to take (i.e., land your airframe as soon as possible, do not approach this spot, be alert for emergency aircraft, etc.). The emergency or priority zone would be limited in location and time. The notifications are made to UAV operators either through an application running on a mobile phone or other connected device or by calls, texts, or other alerts to such devices. The process has uses beyond providing priority to emergency services. For example, a city could provide priority airspace to a film crew using UAVs and notify other UAV users to keep clear of a particular area for a limited time.

The present invention discloses a recipe of high abrasion-resistant aviation tyre tread rubber. The tyre tread rubber is mixed and refined through a mixing roll, including natural rubber which is used as the main material, high abrasion-resistant carbon black with novel process and high structure, high dispersion white carbon black, silicon alkyl coupling agent and heat stabilizer which are used as the auxiliary materials, as well as zinc oxide, stearinic acid, para-phenylene diamine type anti-aging agent, ketoamine type anti-aging agent, protective wax, insoluble sulfur, sulfenamide type accelerator, etc. The tyre tread rubber provided by the present invention has the advantages of high tensile strength, high tearing strength, low dynamic heat generation, good thermal stability and high abrasion resistance, thus prolonging the service life of the aviation tyre and ensuring the flight safety.

An embodiment of the invention discloses a UAV route generation method, a UAV route generation device, a UAV and a storage medium. The UAV route generation method comprises the steps of: acquiring a digital surface model of a to-be-operated region, wherein the digital surface model comprises elevation information of the to-be-operated region; generating an initial route of the to-be-operated region according to the digital surface model, wherein the initial route comprises a flight height of the UAV; determining an obstacle avoidance region in the initial route according to the elevation information and flight height; and adjusting the initial route based on the obstacle avoidance region to generate a target route. The UAV route generation method and the UAV route generation device do notneed to adopt acoustic radar or optical radar ranging to determine obstacles, solve the problem of UAV explosion accidents because the UAV cannot avoid obstacles timely when acoustic radar or opticalradar ranging and obstacle avoidance is adopted, determine the obstacle avoidance region precisely by means of the elevation information of the digital surface model and flight height, can generate aneffective obstacle-avoiding fight route, and guarantee the flight safety of the UAV.

An embodiment of the invention discloses a low-altitude aircraft dynamic monitoring system, and includes: a positioning device used for sending positioning data to an aircraft; an airborne terminal used for utilizing the positioning device to determine the exact position of the aircraft, broadcasting flight information of the aircraft to ground equipment through a wireless communication network, receiving data of other aircrafts sent by the ground equipment, and analyzing the received data; ground equipment used for receiving information sent by airborne terminals of aircrafts, performing real-time posture monitoring of the aircrafts, analyzing possible flight risks, broadcasting and issuing in an uplink manner and providing anti-collision alarm information; and an airborne interactive device used for being connected with the airborne terminal, and displaying real-time posture data of the aircrafts and the alarm information. Through low-altitude aircraft dynamic monitoring system provided by the invention, reasonable implementation of airspace management and traffic management are facilitated, operation economy is improved, and airspace utilization efficiency is improved, thereby fundamentally improving navigation flight safety.

The invention discloses an express delivery unmanned aerial vehicle (UAV) multi-cluster safe route control method and control system, wherein, the method comprises receiving ordering of a client; planning an exclusive route for reach UAV based on ordering address information, controlling the UAV to fly to the destination according to the exclusive route, and correcting the route when the UAV is detected to deviate from the exclusive route; and controlling the UAV to hover when an obstacle is detected in a preset safety zone of the UAV, and controlling the UAV to fly according to the principle of route avoidance. The control method in the embodiment of the invention achieves orderly flight of the UAVs in the air through exclusive route planning, route deviation correction and flight safety zone emergency avoidance, and ensures the safety of simultaneous flying of a UAV multi-cluster in the air.

A navigation altitude obtaining method combining relative altitude and absolute altitude comprises the five steps of obtaining the relative altitude hrelat of an aircraft from the ground with a relative altitude measurement meter, obtaining the absolute altitude habs of the aircraft with an absolute altitude measurement meter, determining the navigation altitude source according to the relative altitude hrelat, calculating the navigation altitude hNavi by means of the absolute altitude habs if it is determined that the navigation altitude source is the absolute altitude habs in the third step, and calculating the navigation altitude hNavi by means of the relative altitude hrelat and the ground altitude hground and calculating and recording the difference value hoffset between the navigation altitude hNavi and the absolute altitude habs if it is determined that the navigation altitude source is the relative altitude hrelat in the third step. According to the navigation altitude obtaining method combining relative altitude and absolute altitude, the reliability and accuracy of the navigation altitude are improved; when the aircraft flies near the ground, the aircraft flies along with the ascending terrain, the aircraft can exit from the current state and return to an expected altitude when the aircraft flies along with the descending terrain, and then flight safety is guaranteed.

The invention discloses a tilt ducted unmanned aerial vehicle. A central duct is arranged in an inner cavity of a center of a body, and is connected with the body through a tilting axis; the part of the body connected with the tilting axis is provided with a duct tiling mechanism; wings are symmetrically arranged on two sides of the body; a nose and wingtips of the wings are provided with posture control ducts; the lateral rear of the body is provided with extraverted double vertical tails; the rear of the extraverted double vertical tails is provided with a rudder; the lower side of the body is provided with a front three-point wheel landing gear; and the central duct, the duct tilting mechanism, the posture control duct and the rubber are respectively connected with a flight control system. The tilt ducted unmanned aerial vehicle has the advantages that: 1, a tail-free and large-triangle wing fusion layout is adopted, and the pneumatic property is good; 2, a unique tilt central duct design is adopted; 3, a unique three-duct posture control design is adopted; and 4, a duct rotor wing design is adopted, namely all paddles are embedded in the ducts, and the flight safety in an complex environment is effectively improved.

The invention provides a route planning method and device for an unmanned aerial vehicle and belongs to the technical field of computers. The method comprises steps as follows: a to-be-planned map area is converted into a raster map; barriers in the raster map are marked as background points, non-barriers are marked as foreground points, and a binarized raster map is obtained; a non-barrier area formed by the foreground points in the binarized raster map is detailed on the basis of a set starting point, an end point and the boundary of the generated raster map, all routes where the unmanned aerial vehicle least probably collides with barriers from the starting point to the end point are obtained, and the problem that a route planning method in the prior art is not applicable to accurate planning of the routes where the unmanned aerial vehicle least probably collides with the barriers is solved. The non-barrier area is detailed, all the routes where the unmanned aerial vehicle least probably collides with the barriers from the starting point to the end point are obtained, and the flight safety is guaranteed.

The invention discloses an autonomous landing method for an unmanned aerial vehicle. According to the autonomous landing method, a camera is carried on the unmanned aerial vehicle to shoot ground images, an image semantic partitioning algorithm model obtained through training of a deep learning model is adopted to identify types and boundaries of all areas of the ground images, and the best landing pint is judged through ground types and ground area sizes. When emergency circumstances occur to the unmanned aerial vehicle in air, the complex ground environment can be automatically identified through the autonomous landing method, after selection, the unmanned aerial vehicle efficiently and accurately lands on a safe place, and the flight safety of the unmanned aerial vehicle is greatly promoted.

The invention discloses a design method of a ground station three-dimensional navigation map of a small unmanned air vehicle. The method comprises the steps of Google Earth application program interface (API)-based map data acquisition, geographical coordinate conversion and navigation function implementation. Network map data of a flight area can be stored into a local two-dimensional array by a Google Earth API; map data is drawn into a ground station navigation map area by a three-dimensional drawing interface, so that a three-dimensional map can be formed; flight destinations of the unmanned air vehicle are inquired in local map data and are drawn in the three-dimensional map, so that the three-dimensional map navigation function can be realized. By virtue of the method, the three-dimensional navigation map with low cost can be provided for a ground station of the small unmanned air vehicle, the map display intuition is improved, and the flight safety of the unmanned air vehicle can be improved under complex terrain conditions.

The invention relates to flight management system and method thereof based on multi-task parallel processing. The system comprises an electronic flight instrument system display unit, a multifunctional control display unit, a flight management system processing unit and a display unit with a control button, wherein the multifunctional control display unit is used for maintaining existing functions of formulating and executing a flight plan; and the flight management system processing unit is connected with the multifunction control display unit and used for copying the formulated flight plan and carrying out assessment and dynamic modification on the flight plan. The invention converts the traditional signal processing scheme into a parallel processing scheme: one processing scheme is used for maintaining the traditional functions of formulating and executing the flight plan, and the other processing scheme is used for providing the dynamic modification and assessment functions; and flight personnel can effectively prepare and scientifically assess the change basis by dynamically modifying an assessment scheme, therefore, the invention can satisfy the changeful practical needs and improve the flight safety and the flight operation effectiveness.

The invention mainly provides a flight monitoring device for carrying out monitoring on a flight state of an unmanned aerial vehicle. The unmanned aerial vehicle is provided with a detection device for detecting a flight state parameter of the unmanned aerial vehicle. The flight monitoring device comprises a data acquisition module for collecting a detection signal of the detection device, a monitoring module for generating operation state information of the unmanned aerial vehicle based on a pre-stored reference condition and the collected detection signal, and a network communication module for transmitting the operation state information to a third-party server. In addition, the invention also provides an unmanned aerial vehicle including the flight monitoring device, a ground control station and a corresponding flight monitoring method. According to the scheme, a manned aerial vehicle operator can carry out maintenance and real-time fault monitoring on the unmanned aerial vehicle regularly and timely, thereby effectively improving the flight safety factor of the unmanned aerial vehicle and reducing the probability of fault occurrence during the flight process of the unmanned aerial vehicle.

The group of inventions relates to aviation and to transport means having (static and dynamic) air discharge, in particular to self-stabilizing wing-in-ground-effect craft of types A, B and C. The following technical results are achieved: increased flight safety and maneuvering safety, increased load-bearing capacity and flight height in ground effect mode, reduced dimensions, improved take-off and landing characteristics, as well as amphibian characteristics and economic efficiency, increased functionality and a wider range of operational alignments, and greater ease of use and maintenance. This result is achieved by simultaneously applying the methods for generating a system of aerodynamic forces, the structural solutions and the piloting methods conceptually linked therewith which are proposed in the present group of inventions to “flying wing” or “composite wing” design layouts.

The invention discloses an unmanned aerial vehicle automatic collision avoidance system, including an unmanned aerial vehicle situation sensing module used for single level or pixel level target detection, tracking and recognition and abstraction of global cognition of environment from information to realize cognition of environment; an unmanned aerial vehicle collision threat assessment and prediction module used for making a threat assessment and conflict prediction of static obstacles, extreme weather and moving targets in a detected area when an unmanned aerial vehicle runs in airspace; and an unmanned aerial vehicle decision collision avoidance module used for generating corresponding behavior selection after the unmanned aerial vehicle obtains a flight conflict trend through assessment prediction, planning a feasible optimal collision avoidance path in time through a flight path planner, and outputting an avoidance decision and a maneuvering instruction. The unmanned aerial vehicle automatic collision avoidance system can realize automatic sensing and avoidance during flight of the unmanned aerial vehicle in the air, realizes systemization, automation and intelligentization of unmanned aerial vehicle collision prevention, and remarkably improves flight safety of all aircrafts when the unmanned aerial vehicle and other aircrafts share airspace.