1058 results about "Vertical take off and landing" patented technology

A vertical take-off and landing (VTOL) unmanned aerial vehicle (UAV) storage and launch system includes a UAV pod having a UAV pod processor and a UAV selectively enclosed in the UAV pod, the UAV having only two rotors.

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.

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 relates to the technical field of aircraft fault diagnosis, in particular to a vertical take-off and landing aircraft diagnosis generalization enhancement method based on causal weight. Firstly, a directed acyclic graph between flight features and fault types is established through an information flow causal discovery method, the causal relationship between the flight features and the fault types can be clearly presented, and a basis is provided for subsequent analysis. Then, mutual information between nodes is calculated and converted into causal strength for causal enhancement, and expression of the causal relationship in the data is enhanced; in the convolutional neural network, causal weights are used for dynamic weighting to extract local features, causal features of a directed acyclic graph are combined, and feature information of different types is fully utilized. According to the method, features are fused through a graph convolutional network to obtain high-order features, adversarial training is completed through a full-connection network, the constructed fault prediction model integrates various technical advantages, the generalization ability of the model is effectively improved, the model can better adapt to different working conditions and data changes, and aircraft faults are accurately diagnosed.

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.

An airport for a vertical take-off and landing aircraft includes three or more windbreak walls that extend radially about a reference axis, and three or more take-off and landing areas for the vertical take-off and landing aircrafts, which are partitioned by two adjacent windbreak walls among the three or more windbreak walls.

A tilt propeller for a vertical takeoff and landing (VTOL) aircraft includes a linked low pitch stop (LLPS). The LLPS serves as a secondary pitch control system that is activated when a primary pitch control system fails. The LLPS may include a pitch rod coupled to a propeller blade yoke, and a mechanical coupling that correlates the tilt angle of the propeller with a pitch angle setting of the LLPS. The pitch rod may be separated by a gap from the mechanical coupling during normal operation. If the primary pitch control fails, the pitch rod is forced into contact with the mechanical coupling to close the gap and form a load-bearing path to control the pitch angle.

The invention relates to a tilting rotor unmanned aerial vehicle, in particular to an unmanned aerial vehicle combining a flying wing type structure and a multi-shaft tilting rotor. A completely fused flying wing type fuselage is formed by a low-speed wing shape, and no other fuselage characteristics exist except that bilaterally symmetrical wings are directly connected and fused in the middle; a left tilting rotor frame and a right tilting rotor frame are mounted at the left end and the right end of the flying wing type fuselage respectively; at least one to at most six brackets extend from the front part and the rear part respectively, and symmetrical tilting rotor frames are mounted on the brackets; motors and paddles are mounted on all the tilting rotor frames; and an undercarriage is mounted below the flying wing type fuselage. During tilting, a single motor and a single blade are not tilted, but a plurality of power units formed by one or more motors and blades are tilted in groups through a tilting rotor frame. Therefore, the structure is simplified, and the safety and the maneuverability are improved. The landing gear has two types, one type is a foot type landing gear suitable for vertical take-off and landing in a soft site, and the other type is a wheel type landing gear suitable for short-track take-off and landing in a hardened site.

The invention discloses a multi-modal lightweight forest fire detection method suitable for a vertical take-off and landing fixed-wing unmanned aerial vehicle platform, and the method comprises the steps: carrying out the feature alignment and weight fusion of a visible light image and an infrared image, which are synchronously collected by an unmanned aerial vehicle, through a multi-modal early fusion method, and obtaining a fusion feature; carrying out lightweight down-sampling and multi-scale feature extraction on the fusion features to obtain a multi-scale feature set; performing cross-scale feature fusion on the multi-scale feature set by adopting a bidirectional feature pyramid network, and extracting dynamic change information to obtain time sequence features; performing multi-scale context enhancement on the time sequence features by using a spatial pyramid method based on cavity convolution, and performing global context and local texture modeling by using a lightweight Transform module to obtain high-level semantic features; and based on the high-level semantic features, a target detection frame, fire level classification, prediction uncertainty estimation and a pixel-level fire probability graph are generated in parallel through a multi-task output header.

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 vertical take-off and landing airport air traffic collaborative management method and system. The method comprises the following steps: constructing an airport air model integrating a physical environment, an airspace structure, a natural environment, an aircraft state and observation information; receiving observation information in real time to drive model synchronization; performing prospective multi-dimensional conflict prediction based on the synchronous model and eVTOL dynamics; on the basis of the prediction result, generating a cooperative regulation strategy when multiple constraint conditions are met; converting the strategy into an instruction, issuing the instruction through a security data link, and verifying an execution effect based on observation information to realize closed-loop control; according to the method, the air traffic environment of the vertical take-off and landing airport is systematically and digitally reconstructed through the quintuple model, unified representation of the operating environment and the traffic subject is achieved, the problem of heterogeneous information fusion is solved, the airspace utilization efficiency and safety under high-density operation can be remarkably improved, and the method is suitable for large-scale popularization and application. And the method has strong adaptive capacity to dynamic changes such as wind power disturbance and emergency conditions.

The invention discloses an aircraft landing guiding method, a display system and an aircraft, and relates to the technical field of flight control. The aircraft landing guiding method comprises the steps that under the condition that it is detected that an aircraft meets tilting guiding conditions, a flight boundary indication image of the aircraft is generated, and the flight boundary indication image is used for reflecting a tilting transition flight corridor when the aircraft safely flies to a reference hovering point from a current air position; the aircraft comprises an aircraft body and a tilt rotor assembly, the tilt rotor assembly is arranged on the aircraft body and can rotate between a cruise position and a vertical take-off and landing position, and the reference hovering point is located above a landing destination; and displaying the flight boundary indication image on a display system of the aircraft. According to the invention, a pilot can control the aircraft in real time according to the flight boundary indication image, and the aircraft can be safely transited from a cruise flight stage to a vertical landing stage.

The invention provides a high-voltage power supply and distribution system for an electric vertical take-off and landing aircraft, and belongs to the technical field of power supply and distribution regulation control systems, and the system comprises a main bus bar module which is used for the current collection and distribution of an energy storage battery and a ground DC bus high-voltage power supply, and is provided with a fuse for overload cut-off; the output bus bar module comprises six mutually-independent motor load output channels and two mutually-independent high-voltage output channels, and each motor load output channel supplies power to the two symmetrically-arranged motors at the same time and is used for distributing 12 motor loads and 2 high-voltage output loads; the power-on buffer module is used for power-on buffer of 12 paths of motor loads and restraining power-on impact current; the self-locking control module has a motor load output control self-locking function, and can keep normal output of motor load current under the condition that the monitoring unit fails; and the monitoring unit module is used for monitoring the input voltage, the output voltage and the load current, and performing power-on buffer control and high-voltage contactor self-locking control on the motor load.

The disclosure relates to hybrid unmanned aerial vehicle (UAV) having vertical take-off and landing (VTOL) capabilities. Specifically, the disclosure relates to a stable hybrid fixed angle rotor arrays UAV having VTOL capabilities with hovering capabilities using rotors and cruising using fixed wing.

The invention discloses an aircraft landing guiding method, a display system and an aircraft, and relates to the technical field of flight control. The aircraft landing guiding method comprises the steps that under the condition that it is detected that an aircraft meets tilting guiding conditions, a flight boundary indication image of the aircraft is generated, and the flight boundary indication image is used for reflecting a tilting transition flight corridor when the aircraft safely flies to a reference hovering point from a current air position; the aircraft comprises an aircraft body and a tilt rotor assembly, the tilt rotor assembly is arranged on the aircraft body and can rotate between a cruise position and a vertical take-off and landing position, and the reference hovering point is located above a landing destination; and displaying the flight boundary indication image on a display system of the aircraft. According to the invention, a pilot can control the aircraft in real time according to the flight boundary indication image, and the aircraft can be safely transited from a cruise flight stage to a vertical landing stage.

The present application discloses an aircraft. The aircraft comprises a first wing and a second wing, a fuselage to which the first wing and the second wing are mounted, a first engine operatively mounted to the first wing, and a second engine operatively mounted to the second wing. The aircraft is configured to vertically take-off and land. The first engine and the second engine are used for both (i) vertical take-off and landing, and (ii) horizontal flight.

A VTOL UAV comprising a chassis, a propulsion system mounted on the chassis, electronics including a flight control system, and a 3D LIDAR sensor mounted on the chassis. The 3D LIDAR sensor has a laser beam 360° rotation axis (R) and an azimuthal scanning angle (α) in a range of 70° to 110°. The propulsion system comprises a plurality of propellers with motors configured for flight without wings, including static hovering flight, the VTOL UAV comprising a yaw axis (Z) about which it can rotate upon itself. The 3D LIDAR sensor is statically mounted on the chassis such that the LIDAR laser beam 360° rotation axis (R) is inclined at a LIDAR inclination angle (β) with respect to the yaw axis (Z) in a range of 35° to 50°.

The invention discloses a learning-based composite layered anti-interference control system and method suitable for a large-windward-area unmanned aerial vehicle, is used for realizing robust wind resistance control of the large-windward-area unmanned aerial vehicle, and aims at the flight characteristics of large windward area and sensitivity to external wind field change in a vertical take-off and landing stage. A wind speed estimation method without an additional sensor is provided, modeling of external disturbing force is realized in combination with a Gaussian process regression algorithm, and compensation of the disturbing force is realized by using quaternion-based model prediction control, so that the influence of an external change wind field on the dynamics of the large-windward-area unmanned aerial vehicle is reduced, and the trajectory tracking precision is remarkably improved. A backstepping controller based on SO (3) is designed in an attitude control loop, a nonlinear disturbance observer is integrated, and active compensation of external disturbance torque and robust tracking control of attitude are realized. Based on the technical characteristics, a complete dynamic control link capable of estimating and feeding back compensation disturbance in real time is further constructed.

The invention discloses an automatic control method of a four-power-source tiltable aircraft, relates to the technical field of flight control of tiltable aircrafts, is realized based on a PX4 flight control system, and is suitable for a tiltable aircraft provided with four independent tiltable power sources and corresponding tilting execution mechanisms. According to the method, through configuration of a tilting angle control module, a power distribution module and a full-stage flight logic scheduling module, full-stage automatic control of vertical take-off and landing, suspension, horizontal take-off, fixed-point horizontal flight, automatic cruise, one-key return flight, fixed-angle flight, power source fault handling and the like is achieved. Smooth transition of all flight modes is achieved, the stability of the attitude, the height and the position of the tiltable aircraft in different flight stages is maintained, meanwhile, the functions of automatic obstacle avoidance, fault emergency and the like are integrated, flight safety is guaranteed, flight stability and applicability are improved, and the method can be widely applied to various tiltable aircraft operation scenes.

The invention belongs to the field of aircraft design and control, and particularly relates to a control method of a combined type unmanned aerial vehicle based on passive hinge tilting. The composite unmanned aerial vehicle carries a tilting device and a fixed wing, the tilting of the tilting device is controlled by differential speed of motors at the two ends of the tilting device, and vertical take-off and landing and tilting transition of the unmanned aerial vehicle are controlled by adopting a PID control law. The main control board controls the main power motor and provides main power for the vertical take-off and landing stage and the horizontal cruise stage of the unmanned aerial vehicle. The sub-control board controls tilting motors at the two ends of the tilting device and provides power for enabling the tilting device to tilt. When the unmanned aerial vehicle takes off and lands, the tilting device is in a locked state, and after the unmanned aerial vehicle reaches a cruise height, the unmanned aerial vehicle is controlled to fly horizontally through the tilting device to complete a cruise task; and after the cruise is finished, the unmanned aerial vehicle is controlled to enter a hovering state through the tilting device. According to the invention, decoupling of forward flight and pitch angle attitude is realized, multiple purposes are realized, and flight tasks can be completed in a complex environment.

The invention discloses an eVTOL vertical take-off and landing airport site selection method considering travel mode selection behaviors, and relates to the field of urban low-altitude traffic facility site selection. The method comprises the following steps: firstly, considering a travel mode selection behavior, and constructing an urban air traffic (UAM) travel demand prediction model; secondly, solving an eVTOL vertical take-off and landing airport candidate point set by adopting an iterative weighted clustering algorithm according to an original traffic mode time value of a demand point; and finally, constructing a site selection model by taking reduction of the total cost of the network, reduction of the total travel time of the network and improvement of the UAM service rate as targets, and solving by adopting an NSGA-III algorithm. According to the method, the optimal eVTOL vertical take-off and landing airport site selection scheme can be given, meanwhile, the optimal travel mode of each journey of the whole network is solved, the model is more practical, and the urban travel efficiency is effectively improved.

The invention provides a section-operation-power system joint optimization design method for an electric vertical take-off and landing aircraft. The method comprises the following steps: defining a power system design variable, a section design variable and an operation optimization variable of the electric vertical take-off and landing aircraft; a power system quality model, an aircraft profile demand analysis model, a variable pitch propeller operation performance model and a motor operation performance model are established; power system design and operation control plan making of the electric vertical take-off and landing aircraft are combined, section-operation-power system joint optimization design of the electric vertical take-off and landing aircraft is achieved, and the characteristic of great difference between the wide-speed-range operation characteristic of a variable-pitch propeller and the hovering and cruising flight stage of the vertical take-off and landing aircraft is considered to the maximum extent. And compared with the design of firstly carrying out physical system design and then carrying out operation control design, the optimal design of the overall performance of the aircraft is realized.

An electrical propulsion system for a vertical take-off and landing (VTOL) aircraft comprises an electrical motor assembly and an inverter assembly. The inverter assembly comprises a housing, a capacitor assembly, at least one printed circuit board assembly (PCBA), and a plurality of positioning pins. The capacitor assembly comprises a center hole, at least one capacitor, a capacitor housing having at least one busbar, and a plurality of through holes in the capacitor housing. The capacitor assembly and the at least one PCBA are positioned inside the housing. The plurality of positioning pins pass through the through the plurality of through holes of the capacitor housing and the at least one PCBA and are connected to the housing.

An electric propulsion system for a vertical take-off and landing (VTOL) aircraft having a heat exchanger to cool fluids used in an electrical engine, the electric propulsion system comprising at least one electrical engine mechanically connected directly or indirectly to a fuselage of the VTOL aircraft and electrically connected to an electrical power source. The electrical engine may comprise an electrical motor having a stator and a rotor; a gearbox assembly comprising a sun gear; at least one planetary gear; a ring gear; and a planetary carrier. The electric engine may include an inverter assembly comprising a thermal plate and an inverter assembly housing; an end bell assembly that is connected to the thermal plate of the inverter assembly; and a heat exchanger comprising an array of cooling fins and tubes.

Provided are computer-implemented methods for autonomously controlling an aircraft with vertical take-off and landing capabilities and folding wings that includes controlling a plurality of thrust producing components of an aircraft to cause the aircraft to rise vertically when wings of the aircraft are in a first folded configuration, where when the wings of the aircraft are in the first folded configuration, a leading edge of each wing is oriented in a vertical direction setting motor controller gains based on the wings of the aircraft being in the first folded configuration, and causing the aircraft to align with a direction of airflow when the wings of the aircraft are in the first folded configuration, and controlling thrust producing components and control surfaces and internal articulation mechanisms of the aircraft to cause the aircraft to transition from folded wing configuration to unfolded wing configuration. Systems and computer program products are also provided.

The invention relates to a foldable tilting four-rotor aircraft concept scheme design method based on task requirements. According to the method, task demand indexes such as voyage, cruising speed, task load, cruising height and hovering height are used as input, and the total design weight, power device parameters, rotor wing geometric parameters and fuselage and wing parameters of the aircraft are determined in sequence; and performance indexes such as hovering lift limit, level flight speed, climbing performance, practical lift limit, voyage and endurance in a helicopter mode and a fixed wing mode are calculated and analyzed respectively. And performing matching judgment on a performance calculation result and a task requirement, and performing iterative adjustment on key parameters such as a paddle disc load when the task requirement is not met, so as to form a closed-loop concept design process driven by the task requirement. According to the method, the vertical take-off and landing capacity and the fixed wing cruising performance can be systematically considered in the conceptual design stage, and systematicness, repeatability and engineering feasibility of scheme design of the folding type tilting four-rotor aircraft are improved.

An electric propulsion system for a vertical take-off and landing aircraft has an inverter assembly, a gearbox assembly, an electric motor assembly. The inverter assembly, the gearbox assembly, and the electric motor assembly may be substantially aligned along an axis. The inverter assembly, the gearbox assembly, and the electric motor assembly may each abut at least one of the other assemblies. The power engine may use a liquid, such as oil, to cool and lubricate components of the inverter assembly, the gearbox assembly, and the electric motor assembly. Further, the power engine may use a volume of oil below a threshold volume for cooling and lubricating components such that the power engine does not require a fire barrier.

The invention provides an attitude control method and device for a vertical take-off and landing unmanned aerial vehicle, equipment and a medium, relates to the technical field of flight control law design, and is used for solving the problem of how to realize rapid transition of the vertical take-off and landing unmanned aerial vehicle from a horizontal state to a vertical state. The method comprises the following steps: determining a current stage of the vertical take-off and landing unmanned aerial vehicle in a transition process according to a pitch angle and a flight speed of the vertical take-off and landing unmanned aerial vehicle; the transition process refers to the process of transition from a horizontal state to a vertical state; determining a pitch angle speed control target according to the current stage; a proportional integral differential control law structure is adopted, and a pitching control surface control instruction is determined according to the pitching angular velocity control target and the pitching angular velocity; the vertical take-off and landing unmanned aerial vehicle can be controlled to be rapidly transited to a vertical state from a horizontal state through a pitching control surface control instruction.

The invention discloses a vertical take-off and landing aircraft with improved linked wing tilting ducted fan layout, and belongs to the technical field of pneumatic and power systems of vertical take-off and landing aircrafts. The aircraft comprises an improved joined wing structure layout and a tilting ducted fan system integrally designed with the improved joined wing structure layout. The improved joined wing structure layout comprises a front wing, a rear wing, a vertical connecting wing surface, a vertical stabilizer and a fuselage. The front wing is divided into a front wing inner side wing surface and a front wing outer side wing surface by a vertical connecting wing surface, and adopts a sweepback wing belt dihedral structure; two ends of the rear wing are respectively arranged above the front wing through a vertical connecting wing surface, the middle part of the rear wing is arranged above the tail part of the fuselage through a vertical stabilizer, and the rear wing adopts a forward swept wing structure; the tilting ducted fan system comprises a front wing integrated ducted fan flap 7, a rear wing integrated ducted fan lifting control surface 9 and a tail propelling ducted fan 16. The core problems that pitching of a traditional connected wing is out of control, the weight of a tilting structure is large, and the energy efficiency is low are solved.