76 results about "Aerodrome" patented technology

An Aerodrome providing safe storage for Unmanned Aerial Vehicles (UAVs) that includes an enclosure to protect UAVs from the elements (weather). The Aerodrome includes an enclosure, a foldable flight deck, a service interface, and a telescoping video and audio feed unit. The aerodrome can be remotely operated, and can be mounted on a roof of a structure or vehicle, allowing a completely automated service of the UAV without the need of a person being physically present in the vicinity of the UAV.

The inventive aircraft with off-aerodrome landing consists of a body (1), a lifting wing (2) and the onboard part of a rope arresting and landing device comprising an arresting hook (5) which is provided with a grip (6). In the preferred embodiment, said aircraft is provided with a propeller (3) arranged in an annular empennage (4). Said arresting hook is arranged in such a way that it is rotatable around the transversal axis (8) of the aircraft situated in a longitudinal spacing of the aerodynamic mean chord of the wing. The aircraft leads for landing with the upwardly deployed arresting hook in such a way that the trajectory (12) of a top pickup point (6) is higher than the trajectory (13) of the highest top point of the aircraft and higher than a cable or rope (14) tensed on a landing area. The trajectory (13′) of the highest point of the aircraft located ahead of the arresting hook passes at a lower level than the cable (14). In said conditions, the grip of the arresting hook holds the cable which has a required effort for drawing it from a stationary arresting device. By overcoming said effort, the aircraft spends a flight kinetic energy and stops being suspended on the cable.

A monitoring system of mobile objects on airport is prepared for connecting monitor center to the third party network and each ground station through cable network to receive information of airplane position, GPS positioning and each mobile terminal (EMT) position and to send anti-collision alarm (AA) and free message to each ground station; connecting ground station to EMT and mobile terminal to mobile terminal by radio self-organized network for broadcasting position information to ground station and the other mobile terminal by EMT as well as for broadcasting AA and free message to EMT by ground station.

A system and method for making a decision of whether to carry additional fuel on an aircraft for a particular flight based on a forecast, such as for low visibility and ceiling. Preferably, observations-based probabilistic forecasts are utilized. The forecast probability of the weather at the planned aerodrome being below a prescribed minimum level is calculated using statistical regression analysis of past data. An optimal probability is estimated using cost parameters on an individual flight bases. If this forecast probability is greater than the optimal probability for a particular flight, then extra fuel is carried by that flight. This is in contrast to current practice whereby the same categorical forecast is applied to all flights. The combination of improved short-term forecasts and identification of optimal forecast probabilities minimizes the financial impact of errors and weather forecasts on airline operations thereby providing a superior financial outcome.

The inventive aircraft with off-aerodrome landing consists of a body (1), a lifting wing (2) and the onboard part of a rope arresting and landing device comprising an arresting hook (5) which is provided with a grip (6). In the preferred embodiment, said aircraft is provided with a propeller (3) arranged in an annular empennage (4). Said arresting hook is arranged in such a way that it is rotatable around the transversal axis (8) of the aircraft situated in a longitudinal spacing of the aerodynamic mean chord of the wing. The aircraft leads for landing with the upwardly deployed arresting hook in such a way that the trajectory (12) of a top pickup point (6) is higher than the trajectory (13) of the highest top point of the aircraft and higher than a cable or rope (14) tensed on a landing area. The trajectory (13′) of the highest point of the aircraft located ahead of the arresting hook passes at a lower level than the cable (14). In said conditions, the grip of the arresting hook holds the cable which has a required effort for drawing it from a stationary arresting device. By overcoming said effort the aircraft spends a flight kinetic energy and stops being suspended on the cable.

The invention discloses a course self-correcting method for unmanned aerial vehicle and is based on a magnetic course sensor. The invention can be used for the course self-correcting of the unmanned aerial vehicle which can independently take off and land. A real heading angle can be got from the longitude and latitude information of two landmarks; a magnetic heading angle can be got by the magnetic course sensor; thus a magnetic variation of the location of an aerodrome can be got; the real heading angle of the aerial vehicle in the takeoff and landing process can be calculated at the real time. The invention provides a method with simple principles; no magnetic variation diagram is needed; the quantity of information for the operator of the unmanned aerial vehicle to know is lowered; the operation and control process is simplified.

The invention relates to a real-time fixed wing aircraft simulation system and a simulation method. The real-time fixed wing aircraft simulation system comprises a lower computer, a host computer, a ground station unit, an instrument unit, a vision unit and a parameter interface unit, wherein the lower computer is used for operating an aircraft model in a real-time embedded system, the host computer is used for compiling an aircraft model application program into the real-time embedded operation system and sending the compiled real-time embedded operation system to the lower computer, PID control parameters of the aircraft model are modified in real time, an operation state of the aircraft model is monitored, and the parameter interface unit is used for sending designated aircraft model parameters to the lower computer to realize real-time simulation of a designated fixed wing aircraft. Through the system and the method, a flight scene is simulated in real time, versatility of the aircraft simulation system is improved, complex programming and debugging are avoided, and simulation cost is reduced.

The invention relates to an airport ground device, in particular to an airport snow sweeper, which comprises an automobile chassis, a front suspender and a snow pushing shovel. The automobile chassis is provided with a box body in which a power device is arranged. The airport snow sweeper is characterized in that the automobile chassis is provided with foldable snow pushing plates at two ends of the snow pushing shovel through the suspender; the front parts of front wheels of the automobile chassis are provided with a movable snow blower respectively; the rear part of the automobile chassis is provided with a snow cleaning rolling brush device through a fixing bracket; and the rear end of the automobile chassis is provided with a snow blower through the fixing bracket and the snow cleaning rolling brush device. With the adoption of the structure, the airport snow sweeper has advantages of reasonable structure, convenient utilization, small amount of snow residues, high cleaning rate, qualified friction coefficient, and the like.

The embodiment of the invention discloses an aircraft simulation cockpit control system. The aircraft simulation cockpit control system comprises a computer-aided system, an interaction module, a physiological state detection module, an emergency shutdown module and an auxiliary display module, wherein the computer-aided system comprises a server and a client, and the client presents a corresponding virtual flight scene according to training parameters set by a user on the server and presents the virtual flight scene to a current trainer through VR glasses; the interaction module is used for receiving an operation instruction input by a current trainer, and the client simulates flight of the flight simulator in the virtual flight scene according to the operation instruction; the physiological state detection module is wearable and is used for monitoring physiological parameters of a current trainer; and the emergency shutdown module is used for resetting the flight simulator and locking the flight simulator when the flight simulator is in a fault state and / or the physiological parameters exceed / exceed preset parameter thresholds or a user trigger instruction is received.

A system and method for making a decision of whether to carry additional fuel on an aircraft for a particular flight based on a forecast, such as for low visibility and ceiling. Preferably, observations-based probabilistic forecasts are utilized. The forecast probability of the weather at the planned aerodrome being below a prescribed minimum level is calculated using statistical regression analysis of past data. An optimal probability is estimated using cost parameters on an individual flight bases. If this forecast probability is greater than the optimal probability for a particular flight, then extra fuel is carried by that flight. This is in contrast to current practice whereby the same categorical forecast is applied to all flights. The combination of improved short-term forecasts and identification of optimal forecast probabilities minimizes the financial impact of errors and weather forecasts on airline operations thereby providing a superior financial outcome.

Methods and apparatus are provided for automated control of aerodrome lighting. An exemplary system includes a communication radio, an aerodrome lighting data source, and a processor. The communication radio is configured to selectively transmit radio frequency (RF) signals. The aerodrome lighting data source is configured to at least selectively supply aerodrome lighting data representative of light control characteristics of aerodrome lighting associated with individual aerodromes. The processor is in operable communication with the aerodrome lighting data source and the communication radio, and is configured to selectively retrieve, from the aerodrome lighting data source, aerodrome lighting data associated with an individual aerodrome, and selectively command the communication radio to transmit RF signals consistent with the light control characteristics associated with the individual aerodrome.

A preventive method for preventing suicidal hijack by means of aircraft-carried global position electronic map is disclosed. The data such as the identity of the pilot on the aircraft, the real-time data of the aircraft-carried global position device, the electronic maps of the flight courses, data for automatically entering aerodromes, data for ground piloting, data of the fixed or movable targets on the ground or water requested to be protected, and the pre-fixed electronic maps of the flight-prohibition targets within the whole airspace, are collected and processed by computers, so as to determine whether the aircraft is in a legal or illegal manipulation condition, and thereby automatically protect the flight security and public security. By means of high-techs, this invention enhances the ability of aircrafts for preventing suicidal hijacks. Thus incidents such as Sep. 11 suicidal hijack can be prevented. In case of a normal hijack, the pilot can still deal with such accident according to conventional flight routine, but the aircraft will automatically refuse flying to the flight-prohibition targets.

The invention provides an aircraft driving training system and method based on 5G communication. The system involves a VR camera, a first operator and a first VR helmet; the VR camera is used for shooting a first user performing aircraft driving training and obtaining human body image depth information of the first user so as to determine human body skeleton action data; the first operator is usedfor receiving a flight operation instruction sent by the first user; and the first VR helmet is internally provided with a virtual flight scene and a virtual operation interface which are displayed to the first user, the flight operation instruction is matched with the virtual operation interface, the first VR helmet matches a preset human body model in a human body three-dimensional model library with the human body skeleton movement data to generate a human body movement posture simulation image, and the first VR helmet, on the basis of the flight operation instruction from the first operator, adjusts the virtual flight scene, and sends out the adjusted virtual flight scene and the human body movement posture simulation image in real time through a 5G communication network.

The invention provides a short-distance takeoff ideal scheme of a running take-off airplane. The core technology is that a runway is divided into a fixed part and a dynamic part, and the fixed part is closely connected with the dynamic part, so that the airplane is static relative to the fixed runway when running on the dynamic runway and enters into the fixed runway till being accelerated at a preset speed on the dynamic runway, therefore, the airplane can realize the short-distance takeoff under the status of high initial speed and large kinetic energy. The airplane not only meets the best requirements of the aircraft carrier airplane such as short-distance takeoff, full-load takeoff and full-oil takeoff, but also has the capability of short-distance landing. A crawler type integrated dynamic runway has the functions of short takeoff and landing, can be used for preventing the airplane from rushing out of the runway in a land aerodrome, can be used for building a military field aerodrome, can be used for building a temporary takeoff and landing point for the vehicle-mounted (carrier-based) military aircraft, possibly brings the development direction of the miniaturization and the submarine trend of the aircraft carrier, and possibly brings the great change of an air operation mode. The airplane jointly uses three schemes such as a crawler type integrated dynamic runway, a three-point type synchronous running wheel short-distance take-off airplane, a straight line type synchronous column wheel short-distance take-off airplane, and the like.

The invention provides an aircraft flight conflict detection method. The aircraft flight conflict detection method comprises the steps of acquiring a first information source of a current aircraft anda second information source of an adjacent aircraft; calculating the relative movement speed of the adjacent aircraft relative to the current aircraft based on the first information source and the second information source; predicting that the adjacent aircraft flies for a first preset time period relative to the current aircraft at the relative movement speed, and then calculating a third latitude and longitude of the adjacent aircraft; calculating the distance between the adjacent aircraft and the current aircraft according to the first longitude and latitude and the third longitude and latitude; and comparing the sum of a first protection radius and a second protection radius with the distance between the adjacent aircraft and the current aircraft, and judging whether a flight conflictsituation exists or not. Aiming at the characteristics of aircraft types, flight characteristics and safety intervals, alarm time is used as a unique judgment basis to adapt to different flight scenes.

The invention relates to the field of civil aerodrome navigational lights, in particular to an airport runway center line light. The light is characterized in that: a light cover is provided with two concave holes. Each concave hole has a prism which is connected on a wall of an cavity in the light cover by a bolt. A bromine-tungsten light bulb is arranged under each prism and provided with a color filter and a light bulb protective casing. The bromine-tungsten light bulbs are arranged on a light bulb support. Upper part of inner cover is provided with a flat sealing ring and lower part of the inner cover is provided with an O-shaped sealing ring; the cavity of the light cover is connected with a top cover of a base through internal-external threads to form an integral light. Based on a theory of optical interference, the light can produce white or red light at different distances under the reflection of the prisms, the light beam ranges from negative 5 degrees to positive five degrees in a horizontal direction and from zero to 7 degrees in a vertical direction, and an average light intensity is 5000cd. Compared with the prior art, the light has the advantages of double-layer sealing structure, good waterproof property achieved by connecting an input wire with the inner cover with a waterproof plug, high shock and pressure resistance, capacity of bearing 13.34 KN horizontal shear without damaging structure or part displacement and looseness, and capacity of protecting a optical system from being damaged and parting from displacing when impacted in the top center by a 40 Joule steel ball.

A preventive method for preventing suicidal hijack by means of aircraft-carried global position electronic map is disclosed. The data such as the identity of the pilot on the aircraft, the real-time data of the aircraft-carried global position device, the electronic maps of the flight courses, data for automatically entering aerodromes, data for ground piloting, data of the fixed or movable targets on the ground or water requested to be protected, and the pre-fixed electronic maps of the flight-prohibition targets within the whole airspace, are collected and processed by computers, so as to determine whether the aircraft is in a legal or illegal manipulation condition, and thereby automatically protect the flight security and public security. By means of high-techs, this invention enhances the ability of aircrafts for preventing suicidal hijacks. Thus incidents such as 9.11 suicidal hijack can be prevented. In case of a normal hijack, the pilot can still deal with such accident according to conventional flight routine, but the aircraft will automatically refuse flying to the flight-prohibition targets.

The invention discloses an unmanned aerial vehicle operation monitoring method and system and a monitoring platform, and the method comprises the steps: obtaining operation parameters, a flight scene and flight control information of an unmanned aerial vehicle, calling a pre-established risk prediction model, and calculating the risk occurrence probability in the current scene; calling an accident evaluation model pre-established based on the accident scene, and calculating the accident severity of the unmanned aerial vehicle in the current flight scene and the operation state; and according to the risk occurrence probability and the accident severity, calculating to obtain a risk estimated value, and outputting the risk estimated value. According to the monitoring method disclosed by the invention, through the risk prediction model, the quantitative risk value of ground personnel injury caused by the operation of the unmanned aerial vehicle in unit time is calculated, and autonomous safe flight of the unmanned aerial vehicle is realized.

The invention discloses a method for constructing a 3D flying scenario of a near space aerostat based on STK. The method includes the following steps: converting the format of a MDL file of the near space aerostat, correcting the color of the MDL file, and increasing movements and defining the movements of the near space aerostat, establishing the flying scenario of the near space aerostat in combination with a synthesized landform map of a flying region, obtaining a 3D flying scenario of the near space aerostat by accessing flight track data and external data drive, and realizing dynamic simulation of the flight process of the near space aerostat by real-time updating the content of the 3D flying scenario. According to the invention, the method can better and dynamically display the flying scenario of the near space aerostat of the air above of a specific area, can switch the center and range of a field of view. The method can produce fine models, has high map resolution, and has expandable data interfaces.

The invention discloses a method for creating a large-terrain simulation scene of an unmanned aerial vehicle. The method comprises the following steps: preparing elevation data, image data, cultural feature data, three-dimensional model data and texture data required for simulating a flight scene; importing the prepared data into vector data, and converting the vector data into vector data with aspecial vector file format; giving specific information to the vector data, assigning values according to purposes, and constructing a ground object model; determining the number and distance of LOD,the grid sampling interval and the size of virtual texture according to the size of the area, the precision of the texture and the flight height during flight simulation of the unmanned aerial vehicle; and generating a terrain model suitable for hardware rendering through the MetaFlight data model. The unmanned aerial vehicle simulation scene created by the method is basically consistent with an actual flight scene, any cultural characteristic data can be added, an infinite simulation flight scene can be theoretically manufactured, and the average loading and displaying time is within 30 seconds.

The invention provides a civil aviation passenger plane high-precision positioning method based on multiple sensors. The civil aviation passenger plane high-precision positioning method comprises thesteps of calculating flight correction GPS height, calculating flight correction radio height, calculating flight correction inertial navigation height and calculating flight optimal height data. Theinvention relates to electronic equipment and a storage medium, which are used for executing the method. Compared with an existing passenger plane high-precision positioning technology, equipment nodes and infrastructures do not need to be additionally configured, universality is high, and high-precision positioning requirements in most flight scenes can be met; compared with traditional airborneGPS positioning, the positioning accuracy is greatly improved, and a firmer guarantee is provided for flight safety of a passenger plane; high-precision positioning can be realized only by acquiring asmall amount of earlier-stage empirical data, so that the method has good practicability and expandability; the high-precision positioning data provided by the invention provides more real flight passenger plane basic position data for academic research in many fields of the civil aviation industry.

A drone and a positioning method thereof, a drone communication system and an operation method thereof are provided. The positioning method of the drone is applicable for a drone to cruise in a flight field. The positioning method includes the following steps: flying according to a destination coordinate in the flight field; sensing a plurality of base stations via a first wireless communication module to obtain a plurality of first radio wave signals of the plurality of base stations; positioning according to the plurality of first radio wave signals to determine a current coordinate of the drone; and flying toward the destination coordinate in the flight field according to the current coordinate. In this way, the drone is capable of reliably positioning to effectively perform automatic flight missions.

A laser tracker is installed on the ground, and an active target is mounted on an air vehicle. A reference coordinate system is set for the laser tracker, and a flight scenario created in advance based on a 3D model is used. Flight of the air vehicle is performed while an amount of deviation from the flight scenario is being calculated using position information obtained by the laser tracker, and corrections are being made. The air vehicle is instructed not only on an amount of movement but also on speed, so that efficient flight can be performed in consideration of battery capacity.

The present invention provides a lifting type building, which includes a floor, a wall, and a metal roof panel; it is characterized in that the wall is directly fixed on the floor, and the floor under the wall is evenly arranged with A number of foundations under the wall; several rows of central columns are evenly arranged on the floor inside the wall, continuous section steel is arranged on the inner surface of the wall, steel roof trusses are fixedly installed on the central columns, and the steel roof trusses The ends are respectively fixedly connected on the continuous section steel; the lifting type building and its construction method method of the present invention use the roof wall connection support instead of the skin to transmit the shear force, so that the design method is more in line with the domestic norms; the lifting wall is It is an enclosure component and also the main load-bearing and force-transmitting component. It is prefabricated on the poured indoor floor (including the decorative structure), installed and positioned by a crane, and supported by temporary supports at the same time; the exterior facade is beautiful and durable, and the construction is more efficient. Safe and fast.

There is provided a method and apparatus for simulating a flight scenario during a live flight of an aircraft. The method comprises:(i) generating (60) images comprising scenes relevant to the simulated flight scenario at a simulated altitude;(ii) calculating, using live flight data received for the aircraft and with reference to a predetermined flight model (65), simulated flight data for the simulated flight scenario at the simulated altitude; and(iii) displaying, on a display system (35) of the aircraft, the calculated simulated flight data while controlling the display of said generated scene images to simulate movement of the aircraft through the displayed scene at a rate and in a direction corresponding to the displayed simulated flight data.The method and apparatus may optionally alter the response of the aircraft to control actions (70) by a pilot to simulate the response expected of the aircraft having the simulated flight characteristics.

A stationary object identification system includes memory and a transmitter. The memory has obstacle data stored therein that includes a plurality of parameters associated with each of a plurality of stationary obstacles located at a location, such as an aerodrome. The transmitter is in operable communication with the memory and is configured to generate a plurality of signals. Each of the signals is associated with a different one of the stationary obstacles and has a power level representative of the plurality of parameters associated with the stationary obstacle.