488 results about "Takeoff" patented technology

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.

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 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 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 a heterogeneous unmanned aerial vehicle cluster task allocation and region boundary point joint planning method. The method comprises the following steps: constructing an unmanned aerial vehicle motion model; constructing a collaborative detection distribution income measurement index, an estimated detection time difference measurement index and an energy consumption measurement index which take unmanned aerial vehicle task node selection parameters as optimization variables, and taking the weighted sum of the three indexes as a measurement index of collaborative detection task efficiency; establishing a heterogeneous unmanned aerial vehicle cluster task allocation and region boundary point joint planning model by taking given unmanned aerial vehicle voyage, endurance, effective communication distance and inter-vehicle anti-collision distance limitation as constraint conditions and taking minimization of a heterogeneous unmanned aerial vehicle cluster cooperative detection task efficiency cost function as an optimization target; and solving the optimization model by combining an interior point and an improved Hungary algorithm. According to the method, optimal distribution of the heterogeneous unmanned aerial vehicle cluster task area, the base takeoff point and the area boundary entry point is realized, and the heterogeneous unmanned aerial vehicle cluster cooperative detection performance is effectively improved.

The invention discloses an eVTOL vertical takeoff and landing field aircraft landing scheduling method, and relates to the technical field of aviation scheduling, and the method comprises the following steps: constructing a three-dimensional aerodynamic interference prediction mechanism fusing aircraft rotor wing downwash airflow and urban building reflection airflow, generating a local aerodynamic coupling strength distribution diagram based on real-time meteorological parameters and takeoff and landing sortie arrangement, and carrying out the three-dimensional aerodynamic interference prediction mechanism; the method is used for identifying high-interference areas. According to the invention, by constructing a three-dimensional aerodynamic interference prediction mechanism and evaluating the path sensitivity, advanced identification and risk path marking of a high-interference area are realized; landing time sequence disturbance and flight buffer control are combined, and the multi-machine rotor airflow overlapping probability is reduced. And adaptive flight control and rhythm regulation and control are carried out based on the disturbance level index, so that the flight safety, scheduling collaboration and airspace utilization efficiency of the eVTOL in the complex urban airspace are effectively improved, and multi-aircraft high-density safe collaborative landing is realized.

Combined aerospace system is a multi-stage technology to deliver payloads to orbit and to midair. The system comprises a carrier aircraft, a tow aircraft, a towed spaceplane or a rocket plane or a glider. The carrier aircraft, coupled with the spaceplane and / or the rocket plane or several gliders, takeoff from a runway and ascends to a staging altitude and speed under the carrier aircraft power. After staging, the tow aircraft will pick up the spaceplane or the rocket plane or the glider from the carrier aircraft in flight. The towed spaceplane or the rocket plane or the glider continues ascending and accelerating by the tow aircraft. The spaceplane or the rocket plane will disconnect from the tow aircraft and continue to ascend and accelerate in an atmosphere by using the ramjet engine. The spaceplane or the rocket plane equipped with a propulsion unit is used to place the spacecraft into the earth orbit. The glider will disconnect from the tow aircraft and lands in designated place. Gliders can be used for instantly delivering of correspondence, parcels, and civil goods from a supplier to wide variety of individual consumers or corporate customers.

The invention discloses a dual-hangar collaborative operation system for high-frequency inspection. The dual-hangar collaborative operation system comprises a remote server and two hangar subsystems which are adjacently deployed in an electric power inspection base station, the remote server communicates with the main control modules of the two hangar subsystems through the Ethernet and is used for issuing operation instructions and receiving motor state data and meteorological data. And the main control modules of the two hangar subsystems are in communication connection and are used for sharing meteorological data and operation state data and executing collaborative scheduling logic to realize parallel processing of take-off preparation and landing storage of the unmanned aerial vehicle. Depending on a double-hangar collaborative scheduling strategy, parallel processing of takeoff preparation and landing storage is achieved in a daily scene, while a first hangar executes takeoff preparation (cabin door opening, platform ascending and pressing rod loosening), a second hangar synchronously completes landing storage (unmanned aerial vehicle centering, pressing rod fixing and cabin door closing), and the unmanned aerial vehicle is taken off. And the total time consumption of single operation is shortened to be within 120s from 200s of a single-machine library.

The present application relates to the technical field of aviation meteorological support, and provides a meteorological display and alarm method, system, device and medium for aircraft navigation, which comprises receiving an aircraft route plan and collecting numerical weather forecasts of each place at the takeoff time of the aircraft; extracting wind speed, temperature, relative humidity, liquid water content and cloud droplet particle number density, and calculating the horizontal visibility, aircraft icing index, total cloud cover and aircraft turbulence index at the forecast time through adaptive attenuation interpolation based on feature perception; constructing an information box and a floating box of the route points on the aircraft route map; and performing meteorological display and alarm for aircraft navigation through the information box and the floating box according to the aircraft route plan. The present application uses regional meteorological forecast results to form meteorological forecast results for flight routes, can intuitively display the comprehensive meteorology on the route and form an alarm prompt, reduces the risk of information omission, increases the safety margin, and reduces the meteorological information processing workload of flight support personnel.

The invention discloses a fixed-wing aircraft non-airport take-off and landing adaptability evaluation method based on test flight performance data, and belongs to the field of aviation aircraft design. Comprising typical difference analysis of a non-airport environment and an airport environment, takeoff and landing sliding tolerance analysis of the unmanned aerial vehicle in the non-airport environment and takeoff and landing lateral deviation tolerance analysis of the unmanned aerial vehicle in the non-airport environment. The non-airport take-off and landing adaptive capacity of the airplane is analyzed through take-off and landing data of previous test flights. Key differences and possible problems faced by taking off and landing in the non-airport environment are found out by comparing the test flight airport environment with the non-airport environment, and key constraints of taking off and landing in the non-airport environment are formed; taking-off and landing taxiing section flight parameters in the test flight data are extracted, conformity analysis is carried out from all constraint dimensions, and the conformity analysis comprises analysis of taxiing tolerance based on grounding point deviation and analysis of taxiing feasibility of all levels of roads based on taxiing side offset distance probability distribution; whether field cleaning work needs to be carried out or not during taking-off and landing is evaluated by combining airplane height and highway guardrail design standard comparison.

A seat unit for a passenger of an aircraft, including a seat and a shell, the seat including a sitting portion and a backrest movable on a base, respectively actuated by a motor-driven mechanism, the unit including a means for detecting the presence of the passenger on the seat, the seat being configured to adopt a takeoff / taxiing / landing position when a presence of the passenger is detected, in which the sitting portion is away from the shell and in which the backrest is reclined in the direction of the shell, and a docking position when a presence of the passenger is not detected, in which the sitting portion is close to the shell, and in which the backrest is substantially parallel to the shell, so as to widen the egress between two seat units.

A seat unit for a passenger of an aircraft, including a seat and a shell, the seat including a sitting portion and a backrest movable on a base, respectively actuated by a motor-driven mechanism, the unit including a means for detecting the presence of the passenger on the seat, the seat being configured to adopt a takeoff / taxiing / landing position when a presence of the passenger is detected, in which the sitting portion is away from the shell and in which the backrest is reclined in the direction of the shell, and a docking position when a presence of the passenger is not detected, in which the sitting portion is close to the shell, and in which the backrest is substantially parallel to the shell, so as to widen the egress between two seat units.

To provide cooling paths for motors, such as lift motors of powered aerial vehicles.SOLUTION: A VTOL aircraft includes a plurality of lift propellers configured to be rotated by lift motors to provide vertical thrust during takeoff, landing and hovering operations. The lift propellers are configured to generate a cooling airflow to cool the lift motors during use. During a cruise operation when the VTOL aircraft is in forward motion, the lift propellers may be stowed in a stationary position. Therefore, the cooling airflow may be reduced or eliminated when it is not needed.SELECTED DRAWING: Figure 4A

A craft comprises a hull, a wing, a hydrofoil, and a control system. The wing is configured to generate upwards aero lift as air flows past the wing to facilitate wing-borne flight of the craft. The hydrofoil is configured to generate upwards hydrofoil lift during a first mode of operation as water flows past the hydrofoil to facilitate hydrofoil-borne movement of the craft through the water. While the craft is hydrofoil-borne, the control system is configured to determine the upwards aero lift generated by the wing. The control system is further configured to control the hydrofoil to generate downwards hydrofoil lift to counteract the upwards aero lift generated by the wing that maintains the hydrofoil at least partially submerged in the water while the determined upwards aero lift is below a threshold lift.

A method of aligning an aircraft with a landing platform in motion comprises measuring a GPS heading with at least one GPS sensor positioned at a known location relative to the landing platform while the landing platform is in motion, measuring an orientation of the aircraft with an orientation sensor fixed relative to the aircraft, calculating an orientation of the landing platform from the GPS heading, calculating an orientation offset between the measured orientation of the aircraft and the calculated orientation of the landing platform, and changing an orientation of the aircraft or the landing platform to reduce the orientation offset. A system for landing and securing an aircraft in an enclosure, a system for disconnecting a tether from an aircraft, and a system for landing an aircraft in an enclosure are also described.

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.

Methods and systems are provided for a transportation vehicle. One method includes retrieving data associated with one or more seat attributes associated with one or more passenger seats of an aircraft; identifying a first attribute associated with a passenger seat that does not meet a configurable threshold condition defined for the first attribute for aircraft takeoff, landing or both take-off and landing; determining an action associated with the first attribute that can modify the first attribute to comply with the threshold condition for aircraft takeoff, landing or both take-off and landing; and executing the action associated with the first attribute to meet the threshold condition with the aircraft takeoff, landing or both take-off and landing.

To provide a power supply system, a moving body and a control method for the power supply system.SOLUTION: In a power supply system 26 mounted on an electrically-driven vertical takeoff / landing aircraft (eVTOL aircraft), a battery controller 94 provides a flight controller 86 with first information representing the upper limit of electric power that a battery can input / output continuously for a first period and second information representing the upper limit of electric power that the battery can input / output continuously for a second period, and a motor controller 98 controls a plurality of VTOL drive devices each having a VTOL electric motor and a plurality of cruise drive devices each having a cruise electric motor.SELECTED DRAWING: Figure 3

A craft comprises at least one hull, at least one wing configured to generate upwards acro lift as air flows past the at least one wing to facilitate wing-borne flight of the craft, at least one retractable hydrofoil configured to generate upwards hydrofoil lift during a first mode of operation as water flows past the at least one hydrofoil to facilitate hydrofoil-borne movement of the craft through the water, and a control system that comprises data storage having instruction code stored thereon that causes the control system to during a takeoff operation when the craft is accelerating through the water and is supported by the at least one hydrofoil, control the at least one hydrofoil to generate downwards hydrofoil lift that maintains the at least one hydrofoil submerged at a predetermined hydrofoil depth threshold below the water surface; and when the craft reaches a takeoff condition, cause the least one retractable hydrofoil to release the craft from the water to facilitate wing-borne flight of the craft.

A system for displaying an engine out flight plan via an aircraft display device includes a processor and computer-readable memory operably connected to the processor. The computer-readable memory is encoded with instructions that, when executed by the processor, cause the system to perform the following step: receive an engine out procedure, generate the engine out flight plan based upon the engine out procedure, display the engine out flight plan via the aircraft display device, receive an indication of an engine anomaly, and update a guidance aid overlay on the aircraft display device to display a flight attitude based upon the engine out flight plan in response to the indication of the engine anomaly via the aircraft display device.

The invention relates to the technical field of low-altitude aircraft operation safety, in particular to a low-altitude aircraft-oriented conflict-free flight path planning method before takeoff, which comprises the following steps of: calculating a basic protection interval and an aerodynamic disturbance range of a low-altitude aircraft and determining a three-dimensional dynamic safety boundary; discretizing the airspace into a regular three-dimensional grid array; constructing preset space-time paths before takeoff of the low-altitude aircrafts, mapping the preset space-time paths to the three-dimensional grid array, and identifying all the preset space-time paths before takeoff with space-time overlapping by analyzing the expected space-time occupation section; constructing a space-time path optimization algorithm, and setting priority decision rules of various types of low-altitude aircrafts; generating a space-time path adjustment instruction with the minimum comprehensive adjustment cost; and integrating all space-time path adjustment instructions to generate a conflict-free track before takeoff. According to the method, the conflict in the preset flight path before the low-altitude aircraft takes off is detected and released, and the method can be used for formulating the conflict-free preset flight path and flight path of the low-altitude aircraft before the low-altitude aircraft takes off.

This invention provides a method, apparatus, and medium for implementing a multi-UAV formation flight system, relating to the field of UAV formation flight technology. The ground station and multiple UAVs are networked together. Multiple UAVs are grouped by a task management thread. Based on the grouping, tasks are distributed to the UAVs in real time, and feedback on the UAV execution results is obtained in real time. Based on the feedback information, the task management thread is triggered to distribute tasks to the next group of UAVs in real time. While ensuring real-time task distribution, UAV collisions can be avoided. The takeoff and landing process is streamlined, preventing UAVs from being misplaced and collisions during takeoff.

The invention relates to the technical field of unmanned aerial vehicle control, in particular to a transition control method of a tailstock type unmanned aerial vehicle, which comprises the following steps of: establishing an inertia, airframe and airflow coordinate system, and constructing a longitudinal dynamic model based on the coordinate system; calculating a velocity trajectory by adopting a polynomial and deriving, solving coefficients by combining initial and conversion completion conditions, and generating velocity, acceleration and jerk trajectories; related variables are calculated according to the kinetic model and the speed trajectory; an expected airspeed and a pitch angle are tracked through an airspeed controller and a pitch angle controller respectively, and an accelerator control quantity and a pitch control quantity are output; and when the conversion time exceeds a specified value, judging whether mode conversion is completed or not according to whether the actual airspeed reaches the cruise airspeed, and if not, continuously tracking parameters. According to the technical scheme, the speed trajectory is smooth and controllable, it is ensured that the unmanned aerial vehicle with any takeoff weight safely completes mode conversion, and the problem that stable and reliable flight mode conversion cannot be achieved for the tailstock type unmanned aerial vehicle with any takeoff weight is solved.

The invention discloses a method for controlling an unmanned aerial vehicle through a brain-computer interface based on signal fusion, a medium and equipment. According to the method, electroencephalogram signals of a user are collected in real time, power spectrum density analysis is carried out, a dynamic attention score is calculated, and concentration is divided into three levels of a resting state, a preparation state and a concentration state; meanwhile, head inertial attitude parameters and masseter surface electromyogram signals are collected. And generating a take-off instruction when the concentration state continuously reaches a preset duration, generating a direction control command based on weighted fusion of the electroencephalogram signal and the attitude parameter, and generating a landing instruction when an occlusion action is detected and the electroencephalogram power is lower than a resting state reference value. According to the invention, full-process natural control of the unmanned aerial vehicle from takeoff, flight to landing is realized through multi-mode signal fusion, and the control precision and reliability are improved.

The present application belongs to the field of aviation ground test technology, and provides a rotorcraft take-off safety diagnosis and lift measurement device, which comprises a main take-off platform, a force balance, a vibration acceleration sensor, an information acquisition system and a computer loaded with a weight gravity center calculation program and a rotor dynamic balance program, wherein the main take-off platform is flush with the runway as a rigid take-off platform of the rotorcraft, a frame balance structure is fixedly connected below the main take-off platform and a force balance capable of measuring force in the circumferential direction is arranged below the main take-off platform, a vibration acceleration sensor is arranged on the lower surface of the main take-off platform, a strain gauge is arranged on each force bar of the force balance, the information acquisition system acquires data of the vibration acceleration sensor and the strain gauge and sends the data to the computer for calculation of the weight gravity center and rotor dynamic balance of the rotorcraft. The device can automatically measure the weight gravity center of the rotorcraft, and can accurately evaluate the weight gravity center and rotor dynamic balance level before take-off after the rotorcraft is normally started.

To provide a control device for facilitating addition and subtraction of a control object airspace by a computer.SOLUTION: A control device includes: an input section for inputting a control object airspace map which indicates an airspace for a flying body to fly; a division section for dividing the control object airspace map into a plurality of convex closed areas; a classification section for respectively classifying the convex closed areas divided by the division section into one or more areas among a merging convex closed area, a branch convex closed area, a translation convex closed area, a taking-off / landing convex closed area, and an uninvadable convex closed area; and an output section for outputting a control object airspace map on which a classification result of the convex closed areas is reflected.SELECTED DRAWING: Figure 11

This invention discloses an aircraft flight status identification method and system based on ADS-B, comprising: acquiring ADS-B data of the aircraft in real time and caching the ADS-B data in a high-speed cache database; extracting the latest ADS-B data points of the aircraft from the high-speed cache database at set time intervals, and storing multiple consecutively extracted latest ADS-B data points into a fixed-length queue of a preset length to form a temporal ADS-B data sequence; calculating estimated parameters for status determination by combining the aircraft's flight dynamic data with preset geospatial information; and identifying the current flight stage of the aircraft through a state machine model based on the temporal ADS-B data sequence and the estimated parameters, wherein the current flight stage includes one of taxiing, takeoff, climb, cruise, descent, approach, and landing. The method and system of this application improve the accuracy, continuity, and real-time performance of flight status identification.

A kind of wheel holding device of aircraft tractor, it includes: car body, pedestal turntable, load floor, hydraulic cylinder group, clamping push plate, rotating motor and front pressing plate;Pedestal turntable, load floor, hydraulic cylinder group, clamping push plate, rotating motor and front pressing plate are all installed on car body.The wheel holding device of aircraft tractor provided by the present application has the advantages that: the wheel holding device does not need engine power, and moves by external ground power from the exit of the aircraft to the end of the runway waiting for takeoff, and the pilot controls the tractor to carry out departure operation, with the advantages of simple operation, safety, stable work, long service life, high lifting height, wide application range, etc.

A final approach and takeoff (FATO) surface for a VTOL aircraft redirects downwash as outwash and may capture outwash from the VTOL aircraft to generate electricity. The FATO surface system may include a central solid plateau configured to capture downwash from the VTOL aircraft to enhance a ground effect for optimal stabilization during takeoff and landing. A floor grate surrounding the plateau may allow outwash to pass through to a subsurface where the outwash is channeled to exhausts or at least one turbine for generating electricity from the outwash. Redirecting the downwash to outwash reduces undesirable effects such as noise and airspeed associated with the VTOL aircraft. The electricity may be used to recharge the VTOL, electric vehicles parked at a vertiport of the FATO surface system, may be used by a building at the vertiport, or may be delivered to a local power grid.