1116 results about "Takeoff" patented technology

The invention discloses a low-altitude aircraft take-off and landing platform site selection optimization method. The method comprises the steps that real-time dynamic data and static GIS data including urban traffic flow data, meteorological data, landform data, environment data and POI data are acquired; constructing an urban three-dimensional digital model according to the static GIS data, and constructing a digital twin model according to the three-dimensional digital model and the real-time dynamic data; constructing environment constraint conditions and safety constraint conditions of candidate take-off and landing platform positions in the digital twin model; performing multi-objective optimization on the digital twin model through a particle swarm optimization algorithm, and generating an optimal candidate take-off and landing platform site selection scheme set meeting environment constraint conditions and safety constraint conditions; and dynamically updating the digital twin model according to real-time data feedback, and dynamically adjusting the site selection scheme of the take-off and landing platform. According to the method, the virtual city model is constructed through the digital twin, an accurate simulation environment and real-time feedback are provided for site selection optimization, and the accuracy and feasibility of a site selection scheme are improved.

A craft comprises at least one hull, a main wing coupled to the hull and configured to facilitate airborne operations of the craft, a plurality of propellers that include one or more electric motor propellers and one or more combustion motor propellers arranged along each of a port side and a starboard side of the main wing and configured to generate lift on the craft by blowing air over the main wing, and a control system. The control system comprises data storage having instruction code stored thereon that, when executed by one or more processors of the control system, causes the control system to: after receiving a takeoff indication, increase thrust generated by the electric motor propellers to cause the craft to transition from a hull-borne mode of operation to an airborne mode of operation, and after a thrust adjustment condition occurs, increase thrust generated by the combustion motor propellers.

A VTOL aircraft includes a lift propeller configured to provide lift during takeoff, landing and hover operations. The lift propeller is configured to be stowed close to a boom surface when not in use during, e.g., cruise flight, to minimize drag around propeller surfaces. The lift propeller may be displaced vertically with respect to the boom when switching to a lift configuration to provide greater separation from the boom to improve lift efficiency and reduce unwanted vibrations. The lift propeller may have a fail-safe configuration that allows the propeller to move passively between lift and stowed configurations, and to fully rotate even when fully retracted.

An urban air mobility building-top skyport for landing. loading and unloading. servicing. and parking short field takeoff and landing (STOL) aircraft. which includes a rotatable flight deck having at least one runway on which aircraft takeoff and land: a rotatable lower deck immediately below the flight deck and including an aircraft taxiway surrounding an enclosed central terminal with an elevator bank: and first and second aircraft ramps connecting the flight deck and the lower deck on which to taxi aircraft between the flight deck and the lower deck. A battery-swap station robotically replaces depleted batteries with fully charged batteries without the need for aircraft to cease moving at slow taxi speeds at any point during the process.

An apparatus for facilitating the landing and takeoff of electric vertical takeoff and landing aircraft (EVTOL) can comprise a moveable landing platform, a moveable charging assembly comprising a high voltage cable adapted for electrical, magnetic induction positioned within a vertically moveable column having a magnetic plate and multiple access connections, and weight sensors positioned on the landing platform. The weight sensors are operatively connected to the charging assembly such that when the sensors detect the landing of an EVTOL on the platform, the sensors trigger the charging assembly to rise up to contact the EVTOL and begin charging the EVTOL.

Described are systems and methods for adjusting a takeoff platform for a vertical takeoff and landing (VTOL) aerial vehicle. The described systems and methods allow a VTOL aerial vehicle to be oriented prior to takeoff to reduce the effects that a VTOL aerial vehicle may experience due to weather conditions at takeoff. In view of the aerodynamic characteristics of a VTOL aerial vehicle and certain weather conditions, a heading, pitch, and / or roll of the VTOL can be provided to counteract the effects the VTOL may experience from the weather conditions at takeoff.

A land to air vehicle with lower extendable wings and upper extendible wings, a body, a front hood fan, a rear fan and wheels. The wheels include wheel bases, exterior tires circumscribing the wheel bases, and a fan wheel assembly within each wheel base. The wheel assembly includes extendible fans, a rotor outer rim with teeth for holding a stator inner rim, a propeller shroud configured to house a variety of fan blades, at least one fan within the propeller shroud, a hinge fixedly attached to the outer rotor rim and the propeller shroud, a wheel motor platform and a wheel motor. The hinge is structured to allow the propeller shroud with fans to extend distally from the wheel base interior to navigate the land to air vehicle.

The invention provides a multi-mode intelligent propulsion control method, device and equipment for a short vertical aircraft and a storage medium, and the method comprises the steps: firstly obtaining flight state data in real time, and classifying the flight state data according to a state classification model of a decision tree to generate a current flight mode; next, calling a control strategy group and performing parallel processing on the current flight mode by taking the lowest energy consumption as an optimization target so as to generate a plurality of control instructions, and calling a fusion device weight network to process the current flight mode so as to generate a fusion weight of each control instruction, and generating a final control quantity according to the plurality of control instructions and the fusion weight, and sending the final control quantity to a pre-constructed hybrid propulsion structure nonlinear model to control the short vertical aircraft, thereby solving the problem that the short vertical aircraft cannot be adaptively adjusted when a plurality of propulsion units have differential dynamic characteristics.

Systems and methods of providing guidance to assist eVTOL aerial vehicles in performing landing and takeoff operations at landing locations in GPS-denied environments are disclosed. An exemplary system includes an aerial vehicle comprising a camera configured to generate images based on information transmitted by a plurality of light sources located adjacent a landing surface for the aerial vehicle and a controller circuit configured to receive the generated images and determine a position and an orientation of the aerial vehicle based on the received images, wherein the light sources are arranged in a predetermined pattern on the landing surface, and wherein a characteristic of light emitted from each of the light sources is modulated with respect to time.

The invention discloses a decision-making method and decision-making system for low-power autonomous landing based on a vertical take-off and landing unmanned aerial vehicle, and relates to the technical field of unmanned aerial vehicle landing decision-making. Comprising the following steps: acquiring topographic point cloud data, establishing a neural network model, and extracting and predicting topographic feature parameters including obstacle density and maximum height; calculating an obstruction influence index and a vertical energy consumption influence index in combination with cruise area point cloud data and real-time environment parameters including environment temperature, wind speed and the like, and correcting a return electric quantity threshold value; dynamically correcting the return electric quantity threshold value by further combining the health parameters of the battery, including storage time, cycle charging times and environment temperature; and comparing the dynamic homeward voyage electric quantity threshold with the real-time electric quantity, and generating a landing or homeward voyage decision instruction. The horizontal flight and vertical take-off and landing energy consumption of the unmanned aerial vehicle under different topographic conditions is comprehensively considered, and correction is performed in combination with the battery performance, so that the electric quantity management strategy of the unmanned aerial vehicle is more intelligent and precise.

The invention provides a new class of transportation with a partially aerostatically supported ram air cushion ship (PASRACS) that can provide safe, fast, efficient global transport services with extraordinary comfort, luxury and amenities. The PASRACS employs inventive synergistic combinations of lift from aerostatic, aerodynamic, hydrostatic and hydrodynamic forces for different modes of operation ranging from a stationary floating configuration on a water surface, to flight in ground effect at high speed. A propulsion system can utilize hydrogen as an energy source driving fluid-dynamic thrusters, to enable zero carbon emissions operations. A transition method is provided for a PASRACS to transition from a floating mode to a takeoff mode to a flight in ground-effect mode in an inventive optimized manner. A transport method for multimodally transporting payload is provided with PASRACS vehicles and systems, with quick turn time operations enabled by the use of payload transfer transport modules and transfer vehicles.

The invention relates to the technical field of traffic engineering, and discloses an urban air traffic vertical take-off and landing field site selection optimization method based on demand maximization, and the method comprises the following steps: S1, obtaining and preprocessing online car-hailing original data; s2, dividing grids for the research area range, and taking the grid center as an alternative address of a vertical take-off and landing field; s3, screening out online car-hailing travels which are impossible to turn to urban air traffic; s4, constructing a vertical take-off and landing field site selection model based on potential demand coverage maximization; s5, outputting the selected vertical take-off and landing field address and the corresponding urban air traffic travel demand; and S6, outputting the current optimal site selection and demand as a final solution of the model. According to the method, under the condition of the specific number of vertical takeoff and landing fields, the vertical takeoff and landing field addresses which enable potential requirements of urban air traffic to achieve maximum coverage are selected, an effective solution is provided for development of the urban air traffic, and construction of a more efficient, convenient and environment-friendly urban traffic system is facilitated.

A method for selecting an altitude changing phase route for an aircraft is presented. The method comprises receiving sequences of multivariate flight data from at least one prior flight, receiving a set of flight parameters for the aircraft including at least a total altitude change and a takeoff weight, and receiving a set of candidate altitude changing phase routes having candidate step profiles. For each candidate altitude changing phase route, a sequence of fuel burn quantities is predicted for the respective candidate step profile based on at least the sequences of multivariate flight data and the set of flight parameters. The fuel burn quantities are summed over the candidate altitude changing phase route to obtain an estimated fuel burn. A preferred candidate altitude changing phase route having a lowest estimated fuel burn is indicated.

The invention discloses a rocket-boosted warplane ultra-short-distance launching take-off system and method. The system comprises a chassis, a high-precision track, a hydraulic lifting mechanism and a rocket sled. The rear end of the high-precision track is connected with the top of the chassis in a vertically swinging mode, the front end of the high-precision track is driven by a hydraulic lifting mechanism to ascend and descend, and the rear portion of the high-precision track is provided with a check block. The bottom of the rocket sled is provided with a sliding block used for being in sliding fit with the high-precision track. The mounting interface is used for being connected with a warplane undercarriage through an electronic lock, and the electronic lock is used for timing when a rocket engine is started, unlocking when the rocket engine reaches the working time and sending a separation success signal after being separated from a warplane. Small-overload ultra-short-distance take-off of the fighter is achieved, the volume of ground take-off facilities of the fighter is effectively reduced, the requirement for ground conditions is lowered, the flexibility and convenience of deployment are effectively improved, and the structure or a power system of the fighter is not greatly changed.

Apparatus, systems, and methods are contemplated for electric powered vertical takeoff and landing (eVTOL) aircraft. Such are craft are engineered to carry safely carry at least 500 pounds (approx. 227 kg) using a few (e.g., 2-4) rotors, generally variable speed rigid (non-articulated) rotors. It is contemplated that one or more rotors generate a significant amount of lift (e.g., 70%) during rotorborne flight (e.g., vertical takeoff, hover, etc), and tilt to provide forward propulsion during wingborne flight. The rotors preferably employ individual blade control, and are battery powered. The vehicle preferably flies in an autopilot or pilotless mode and has a relatively small (e.g., less than 45′ diameter) footprint.

The invention relates to the technical field of unmanned aerial vehicle path planning methods, in particular to an unmanned aerial vehicle path planning method based on an improved leapfrog algorithm. According to the method, dynamic weight adjustment information is obtained by carrying out dynamic adaptation matching analysis on flight stage information and environment threat information, a flight stage weight mapping matrix is established, and fitness function weights are dynamically adjusted according to core targets in take-off, cruise and landing stages; weight correction is carried out in combination with environmental data such as obstacle grid density and a meteorological threat coefficient, so that the algorithm focuses on core constraints in the current stage, and target conflicts caused by global unified weight are avoided; according to the method, environmental threats are sensed in real time by means of multi-sensor fusion, when abnormal states such as over-high obstacle density and strong wind are detected, an algorithm is triggered to be suddenly stopped and restarted, a population is reconstructed according to the current position, threat avoidance weight is enhanced, the defect that an existing mechanism can be updated only after the current iteration period is completed is overcome, and the method is suitable for large-scale popularization and application. And the response time to an abnormal environment is shortened.

The invention discloses an aircraft landing gear shimmy test bed and a test method, the aircraft landing gear shimmy test bed comprises a main body rack, a hanging basket system, a large flywheel, a flywheel driving system, an excitation device and a follow-up displacement measurement system.The aircraft landing gear shimmy test bed can simulate the shimmy of an aircraft after undercarriages of different design configurations are subjected to interference excitation force or interference torque in the process of takeoff, taxiing, landing and the like of the aircraft; the control effect of the shimmy damping system on the stability of the undercarriage has short excitation time so as to simulate real working conditions, the shimmy stability performance of the undercarriage can be accurately detected, excitation is continuously carried out under the condition that the test state is continuously changed, and the working efficiency is greatly improved. The follow-up displacement measuring system designed by the invention can enable the exciting force and the center of the axle to be always kept on the same horizontal plane, can apply torque control and torque excitation control, is suitable for undercarriage shimmy tests with different axle heights, different tire diameters and different excitation modes, and has certain universality.

The invention provides a low-altitude heterogeneous unmanned aerial vehicle flight plan pre-tactical diversified deployment method and system, and belongs to the technical field of air traffic management and flight supervision information, and the method comprises the steps: generating an initial flight plan of a single machine, and deducing a process flight path of the initial flight plan; performing multi-aircraft track conflict detection, and identifying static and dynamic flight conflicts; heterogeneous unmanned aerial vehicle multi-factor priority evaluation is carried out, and the space resource use sequence of unmanned aerial vehicles is determined; diversified strategies such as flight routes, take-off time and flight speed are designed, and optimal release is achieved. According to the method, the optimal conflict resolution of the heterogeneous unmanned aerial vehicles in the low-altitude airspace in the pre-tactical stage is realized, the conflict of multiple unmanned aerial vehicles on limited airspace time and space use is effectively avoided, and the requirements of reasonable use and continuous safety of low-altitude airspace resources are met.

The invention belongs to the technical field of unmanned aerial vehicle accompanying flight, and particularly relates to a guiding system based on a vehicle-mounted accompanying flight unmanned aerial vehicle, which comprises the steps of carrying out state calculation on the unmanned aerial vehicle, judging whether the unmanned aerial vehicle reaches a take-off condition, checking battery power endurance of the unmanned aerial vehicle, whether a communication link is stable, and whether sending and receiving states of a control instruction are normal. The vehicle-mounted interaction platform is in signal transmission with the vehicle-mounted terminal, obtains the position information and state of the unmanned aerial vehicle in real time, maps the position information and state to a vehicle-mounted terminal screen and keeps a real-time interaction state with the unmanned aerial vehicle, and the vehicle-mounted terminal obtains the flight normal state information and the flight dynamic information of the unmanned aerial vehicle in real time and controls the unmanned aerial vehicle according to the two-state information of the unmanned aerial vehicle. The vehicle-mounted terminal can select to take over or the vehicle-mounted trusteeship platform to perform trusteeship, and the control system can send a landing instruction. According to the invention, exploration operation tasks in a large area can be completed more quickly and autonomously, dangers possibly foreseen by vehicles are avoided or eliminated, the driving safety is improved, and the dependence of the unmanned aerial vehicle on manual control is reduced.

Apparatus, systems, and methods are contemplated for electric powered vertical takeoff and landing (eVTOL) aircraft. Such are craft are engineered to carry safely carry at least 500 pounds (approx. 227 kg) using a few (e.g., 2-4) rotors, generally variable speed rigid (non-articulated) rotors. It is contemplated that one or more rotors generate a significant amount of lift (e.g., 70%) during rotorborne flight (e.g., vertical takeoff, hover, etc), and tilt to provide forward propulsion during wingborne flight. The rotors preferably employ individual blade control, and are battery powered. The vehicle preferably flies in an autopilot or pilotless mode and has a relatively small (e.g., less than 45′ diameter) footprint.

An urban air mobility building-top skyport for landing, loading and unloading, servicing, and parking short field takeoff and landing (STOL) aircraft, which includes a rotatable flight deck having at least one runway on which aircraft takeoff and land; a rotatable lower deck immediately below the flight deck and including an aircraft taxiway surrounding an enclosed central terminal with an elevator bank; and first and second aircraft ramps connecting the flight deck and the lower deck on which to taxi aircraft between the flight deck and the lower deck. A battery-swap station robotically replaces depleted batteries with fully charged batteries without the need for aircraft to cease moving at slow taxi speeds at any point during the process.

The invention provides an unmanned aerial vehicle distribution task scheduling optimization method considering an endurance state, and belongs to the field of intelligent manufacturing. The method comprises the following steps: aiming at the problems of takeoff sequence, task allocation and endurance state change of an unmanned aerial vehicle in a distribution task, constructing a power consumption model based on flight stage division; under constraint conditions of unmanned aerial vehicle electric quantity, loading capacity, safe flight height and the like, converting the scheduling scheme into a three-layer integer sequence including a take-off sequence, a task allocation sequence and an execution sequence for expression and optimization; a task interruption and battery replacement decision-making mechanism and a battery replacement station selection cost function under the condition of insufficient electric quantity are introduced, and a swarm intelligence algorithm is adopted for solving, so that the optimization target of minimizing the total task completion time, the total battery replacement frequency and the flight distance standard deviation is achieved.

The invention discloses a takeoff point rear side operation safety interval calculation method and system under the influence of engine jet flow, and the method combines laser wind finding radar measurement experiment, data assimilation, computational fluid dynamics (CFD) numerical simulation and other methods, and measures the engine jet flow data of a takeoff aircraft at an airport runway end through a laser wind finding radar; constructing a double-engine nozzle model by using a computational fluid mechanics method, correcting a numerical simulation model by using a data assimilation method in combination with high-credibility laser radar wind measurement experimental data, and calculating an influence distance of typical aircraft engine jet flow; a model of the airplane under the influence of engine jet flow is established by using a CFD method, the model and the model are combined to calculate the minimum safety interval of rear side crossing, and reliable data reference is provided for a multi-runway airport to use a take-off point rear side runway crossing mode. The accurate safety interval between the front and rear airports is defined, and the overall operation efficiency of airports in China is remarkably improved.

A system for inspecting surfaces of an aircraft prior to takeoff. The system includes a device movable relative to the surfaces of the aircraft. At least one camera on the device is provided for determining conditions of the surfaces of the aircraft. The at least one camera is configured to provide images indicative of the presence or absence of contaminates and / or fluid failure on the critical surfaces of the aircraft. A control module is provided for receiving the images from the at least one camera. The control module is programmed to determine, based on the images from the at least one camera, a status of the surfaces of the aircraft and to communicate that status to an external location.

The invention relates to the technical field of aircrafts and navigation, in particular to a return flight control method and device, a chip and an unmanned aerial vehicle. The method comprises the following steps: after the autonomous aircraft takes off, acquiring motion state information of the autonomous aircraft through satellite positioning equipment and / or one or more sensors; when the autonomous aircraft flies until the satellite positioning equipment can provide a positioning signal with specified precision, the current position information of the autonomous aircraft at the current moment is obtained through the satellite positioning equipment, and the initial position information of the autonomous aircraft is reversely deduced through the current position information and the historical motion state information; the initial position information is used for performing return flight control on the autonomous aircraft during return flight of the autonomous aircraft. Therefore, based on the multi-source navigation data, the positioning blind area in the take-off stage is avoided through the mode of calculating the initial position in a delayed mode, the problem that the homeward voyage precision of the lightweight aircraft is insufficient in the environment that GPS signals are interfered is solved, and therefore the homeward voyage precision is improved, and the safety and reliability of the system are improved.

The present invention discloses a flapping-wing aircraft capable of catapult takeoff and having a sweep-torsion mechanism, belonging to the field of aircraft technology. The aircraft comprises: a fuselage frame, left and right flapping wings, a passive torsion mechanism, a sweep mechanism, a catapult takeoff mechanism, a transmission flapping mechanism, and a tail rudder, wherein: a passive torsion mechanism and a sweep mechanism are provided at the roots of the left and right flapping wings, the catapult takeoff mechanism is provided in the middle of the fuselage, and a hip joint, thigh, ankle joint, calf, foot, and toe joint are provided from top to bottom, the inner and outer sides of the hip joint are controlled by a servo motor for relative rotation, the ankle joint and toe joint are provided with elastic energy storage torsion springs, a synchronous pulley and its drive mechanism are provided between the outer side of the hip joint and the outer side of the ankle joint to control the relative rotation between the thigh and the calf, and perform energy storage for catapult takeoff. In summary, the aircraft can perform catapult takeoff flight, and can perform passive torsion and sweeping motions during the flapping of the wings, which helps to increase the flapping wing lift and the overall payload of the aircraft.

The invention discloses a fuselage-free unmanned aerial vehicle, an aviation container and a modular transportation system and method, and aims to solve the problems of high transportation cost of traditional aviation goods and low transportation efficiency of land goods. The aircraft is not provided with a warehouse and adopts a flying wing type layout or a conventional layout, wings in the flying wing type layout or the conventional layout are used for generating lift force and enter a straight wing flight mode after taking off, and the wings are provided with power systems, flight control systems and mounting structures used for being detachably connected with the streamline aerodynamic configuration aviation containers. Through the dynamic combination mode of the aircraft and the containers, the single aircraft can achieve the operation cycle of circularly transporting at least three containers. Through continuous container reloading operation, the aircraft can keep a continuous flight state without waiting for a loading and unloading process. And meanwhile, the container can be quickly circulated among different aircrafts through the modular design. According to the transportation mode, optimal configuration of transportation resources is achieved through efficient cooperation of the aircraft and the container.

The invention discloses a bionic robot with walking, jumping and taking-off functions and a movement method, and belongs to the technical field of robots. The robot comprises a control system, a flapping wing mechanism and two leg mechanisms. Each leg mechanism comprises a driving device I, an execution connecting rod mechanism and a buffer foot part, the buffer foot part is connected with the execution connecting rod mechanism, and the execution connecting rod mechanism is driven by the driving device I; the flapping wing mechanism comprises a driving device II, a transmission mechanism, wings and an empennage; the execution link mechanism is connected with the transmission mechanism, the wings and the empennage are respectively connected with the transmission mechanism, the transmission mechanism is driven by the driving device II, the control system is used for controlling the driving device I and the driving device II, and the motion modes comprise walking, jumping and flying. The multi-mode bird-simulating robot has a multi-mode bird-simulating motion function, can autonomously realize mode switching from land motion to air flight, and remarkably improves the motion performance of the robot.

The invention discloses an automatic takeoff control method for a large fixed-wing unmanned aerial vehicle. The takeoff stage of the unmanned aerial vehicle is divided into a takeoff running stage, a takeoff obstacle crossing stage, a first takeoff climbing stage and a second takeoff climbing stage. In the takeoff taxiing stage, controlling the unmanned aerial vehicle to accelerate to a front wheel lifting speed, controlling the unmanned aerial vehicle to keep a target roll angle, and controlling a yaw angle and a lateral offset distance of the unmanned aerial vehicle to align to a runway center line; in the takeoff obstacle crossing stage, controlling the unmanned aerial vehicle to climb to an obstacle crossing height at a target pitch angle, and controlling the unmanned aerial vehicle to keep a target course angle; in the first take-off and climbing stage, the unmanned aerial vehicle is controlled to climb to a safe height at a target pitch angle, and the unmanned aerial vehicle is controlled to keep a target side offset distance and a track angle; in the second take-off and climbing stage, the unmanned aerial vehicle is controlled to keep the target speed, and meanwhile the unmanned aerial vehicle is controlled to keep the target side offset distance and track angle. Automatic takeoff of the unmanned aerial vehicle can be accurately controlled, and the robustness and safety of automatic takeoff of the unmanned aerial vehicle are greatly improved.

The embodiments of the present invention provide a power processing method and device for a flying car. The method includes: obtaining state parameters of the operating state of the flying car; performing iterative calculation of theoretical values based on the state parameters of the operating state and basic aerodynamic data to obtain the power value of the flying car in the operating state; generating the total power of the flying car under the state parameters of the current operating state according to the power value. By adopting the combined means of theoretical calculation and CFD, the basic aerodynamic data with fewer calculation cases is obtained by using the CFD method, and the data source of theoretical calculation is supplemented. While improving the accuracy of theoretical calculation, the power values of the whole machine of the flying car at different hover altitudes, different forward flight speeds, different climbing speeds, and different takeoff weights can be quickly calculated, and the power requirements corresponding to the complete speed-altitude envelope can be obtained, so as to provide parameter basis for power selection. Since the calculation workload of CFD is greatly reduced, the effects of low calculation cost and high timeliness are achieved.