652 results about "Takeoff" patented technology

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.

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.

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 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 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 relates to the technical field of aircraft wake flow risk analysis, and discloses a mixed operation airport small single-shot training aircraft wake flow encountering risk analysis method. Collecting flight operation programs and information of each subject of training flight, extracting key flight features, and obtaining an average movement track of typical flight tasks of the public transport aircraft and the small training aircraft through clustering analysis; secondly, analyzing a running track and a cross point, carrying out numerical simulation analysis on wake flow of the cross point of the track based on CFD, and constructing an aircraft trailing vortex wake flow dissipation database; finally, an improved strip-shaped belt method is used for calculating extra lift force changes, caused by wake flow vortex fields, of all the parts, then the rolling torque coefficient of the small training aircraft during wake flow encounter is calculated, and the wake flow encounter risk is evaluated. According to the method, the risk that the general single-shot coach aircraft encounters the wake flow of the front civil aviation transport aircraft in the take-off, approach and other stages of the mixed-purpose airport can be accurately evaluated, and the operation efficiency of the mixed-purpose airport is further improved.

Vertical takeoff and landing vehicles (VTOLs) of the type used for the point-to-point delivery and transport of payloads (e.g., packages, equipment, etc.) and personnel, are significantly stabilized at least during takeoff and landing with present aspects significantly ameliorating or significantly eliminating destabilizing effects, including ground effect, during VTOL takeoff and / or landing. VTOL performance is further improved through the use of increased lift pressure and battery charging during takeoff.

A gearbox simulation test device disclosed by the present invention comprises a device seat and an adjusting device, an analysis assembly is installed on one side of the device seat, a driving assembly is horizontally erected on the rear side of the analysis assembly, and a movable table group is arranged on one side of the power output end of the driving assembly. The adjusting device is arranged on the side, away from the driving assembly, of the movable table set, and a fixed angle plate is arranged on the side edge of the device base. According to the gearbox simulation test device, the adjusting device and the movable table group are arranged, the adjusting device can simulate complex variable loads borne by a gearbox of a helicopter in different flight states, such as different load conditions during takeoff, cruising and landing, and the movable table group is used for installing and fixing the gearbox and meanwhile, can simulate the complex variable loads of the gearbox in different flight states. Structural self-adaption is achieved through cooperation with operation of the adjusting device, and the device base, the analysis assembly, the driving assembly, the movable table set and the adjusting device have structural disassembly and assembly performance so that structural maintenance and adjustment can be facilitated.

The invention discloses an unmanned aerial vehicle emergency guarantee system for bridge structure emergencies, and relates to the technical field of bridge safety detection, and the system comprises a bridge monitoring module which is used for monitoring the posture change of a bridge in real time based on a pressure-sensitive sensing technology, and controlling an unmanned aerial vehicle to execute catapult-assisted take-off and segmented landing in combination with an electromagnetic catapult technology; the intelligent warning module is used for executing a corresponding cruise strategy based on the pressure-sensitive attitude monitoring result, driving the unmanned aerial vehicle to inspect the bridge and triggering acousto-optic and character projection warning according to the inspection result; and the power generation and storage module is used for realizing energy supply and stable operation of a storage battery by utilizing solar energy. According to the invention, by introducing the electromagnetic ejection technology, the device has the characteristics of high acceleration and instantaneous strike, and can realize second-level response under an emergency situation, so that the emergency efficiency is greatly improved; solar power supply can prolong the endurance time of the unmanned aerial vehicle in an environment with sufficient sunlight, reduce the frequency of battery replacement and reduce the operation and maintenance cost.

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 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 civil aviation pilot manual manipulation proficiency quantitative evaluation method and device, and the method comprises the steps: S1, setting a research flight stage which comprises a stage from takeoff to climbing, a stage from approaching to landing, and intercepting the QAR data of the research flight stage; and S2, intercepting data from a takeoff stage to a climbing stage and an approaching stage to a landing stage, and performing quantitative evaluation on the manipulation proficiency degree. According to the invention, the high manual operation intensity and difficulty of the takeoff-to-climbing stage and the approaching-to-landing stage are taken as the research flight stage, and multi-aspect evaluation values can be respectively obtained according to the takeoff-to-climbing stage and the approaching-to-landing stage; meanwhile, the evaluation result from the takeoff to the climbing stage, the evaluation result from the approaching to the landing stage and the comprehensive evaluation result from the research flight stage are obtained through weighted fusion, staged, aspect-divided and multi-fusion manual manipulation quantitative evaluation is achieved, and the flight training effect and the operation skill of a pilot can be improved.

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.

The invention relates to the technical field of undercarriages, in particular to a folding undercarriage device of a low-altitude aircraft, which comprises an aircraft body, a pesticide spraying mechanism for crop fertilization is arranged on the aircraft body, a height-adjustable undercarriage mechanism is arranged at the lower end of the aircraft body, and a landing buffer mechanism is arranged on the undercarriage mechanism. The landing buffering mechanism is used for reducing impact on the undercarriage mechanism at the moment of landing, a linkage auxiliary mechanism is arranged on the aircraft body, the undercarriage mechanism comprises a fixing plate body, and the fixing plate body is detachably installed on the aircraft body. By arranging the undercarriage mechanism and adopting a dynamic folding design, after taking off, the second-stage frame body retracts to drive the telescopic joint to be shortened, so that the overall height is reduced, air turbulence during flight can be effectively reduced, meanwhile, the first-stage frame body rotates to be parallel to the fuselage, the cross sectional area of the undercarriage mechanism is greatly reduced, and the overall height is reduced. And the wind resistance loss during high-speed flight can be obviously reduced.

The invention belongs to the field of wing-in-ground-effect ship system design, and discloses a wing-in-ground-effect ship adopting a hybrid power energy management and vector control cooperative system, which comprises a ship body, a hybrid energy system, an electric propulsion system, a data acquisition system and a flight control module. According to the invention, a plurality of groups of tilting ducted fans are adopted in front of and behind the wings, and the stable and efficient propulsion requirements of all working conditions of take-off, ground-effect flight, non-ground-effect flight, turning and short-distance landing of the wing-in-ground-effect ship are met through vector control and adjustment; an eddy current system and a power battery are adopted to achieve multi-mode switching work such as a pure electric mode, an eddy current mode, a mixed electric mode and a charging mode through a power grid, and the power requirement of the wing-in-ground-effect ship under all working conditions is met. The control strategy and cooperation scheme of the hybrid power energy management module and the ducted fan vector control module have the capability of remarkably improving the energy efficiency and the flight performance of the wing-in-ground-effect ship, and the problems that a traditional wing-in-ground-effect ship is low in energy utilization rate and poor in maneuverability are solved.

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.

A VTOL aircraft includes a plurality of lift propellers configured to be rotated by lift motors to provide vertical thrust during takeoff, landing, and hover operations. The lift propeller is configured to generate a flow of cooling air to cool the lift motor during use. During cruise operation, the lift propellers may be stowed in a rest position when the VTOL aircraft is in forward motion. Thus, when the flow of cooling air is not needed, the flow of cooling air may be reduced or eliminated.

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.