5163results about "Rotocraft" patented technology

A wind energy plant with a nacelle, a rotor, which features at least one rotor blade adjustable in its blade pitch angle, a central control device for controlling the wind energy plant and a control unit disposed in the rotor for controlling the blade pitch angle of the at least one rotor blade, wherein the central control device and the control unit in the rotor can exchange data with each other via a data link, which comprises at least one first sending and receiving device at the nacelle side and at least one second sending and receiving device at the rotor side, wherein a wireless network connection with a safety-oriented communication protocol is provided between the at least one first sending and receiving device and the at least one second sending and receiving device, and that one monitoring- and communication device at a time is associated to the first and / or the second sending and receiving device, which can monitor the function of the sending and receiving device and initiate a predetermined action in the case of an error.

A moving device that allows an unmanned aerial vehicle to easily take off and land on is described. The moving device includes a main body device that travels by a traveling device, a takeoff and landing unit that is provided in the main body device and used by an unmanned aerial vehicle to take off and land and, and a leveling table that is provided in the takeoff and landing unit. The inclination of the leveling table is adjustable with respect to the vertical axis.

An emergency module may determine occurrence of emergency events of a vehicle traversing through an environment. The emergency module may rank the emergency events according to importance level associated with each emergency event. The emergency module may select an emergency event based on the ranking. The emergency module may notify a user of the vehicle of the selected emergency event. The emergency module may identify corrective actions associated with the selected emergency event, the identified corrective actions including a user action and a non-user action. The emergency module may perform the non-user action of the identified corrective actions. The emergency module may notify the user of the vehicle of the user action.

Forming a shroud for an ACM by: forming a base having discrete sections including: a first section defining connecting features for connecting with a fixed ACM structure; a second section positioned adjacent to a compressor rotor when installed in the ACM; and a third section disposed adjacent to a drive ring bearing when installed in the ACM; forming the base includes: printing thermoplastic polymer surfaces, respectively from thermoplastic polymers, disposed against each other, a first thermoplastic polymer surface having a CTE, and a second thermoplastic polymer surface having a second CTE; forming a lower support section on the base by printing along the discrete sections of the base a mixture of a third thermoplastic polymer and a catalyst formed with metal; and forming an upper support section on the shroud by depositing on the lower support section, along each of the discrete sections, via electrolysis deposition, a metallic coating.

An aerial vehicle includes a center body, two arm assemblies arranged at the center body, a power device, and a driver mechanism mechanically coupled to the arm assemblies. The power device includes two first and two second rotor power assemblies. Each pair of first and second rotor power assemblies are installed at two ends of an arm assembly. The driver mechanism drives the arm assemblies to move relative to the center body such that distal parts of the two arm assemblies move between first and second height positions. In a direction of a roll axis of the power device, the first rotor power assemblies are closer to an installation site on the center body than the second rotor power assemblies. When the distal parts are at the second height position, spacing between the first rotor power assemblies is larger than spacing between the second rotor power assemblies.

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

An introduced autonomous aerial vehicle can include multiple cameras for capturing images of a surrounding physical environment that are utilized for motion planning by an autonomous navigation system. In some embodiments, the cameras can be integrated into one or more rotor assemblies that house powered rotors to free up space within the body of the aerial vehicle. In an example embodiment, an aerial vehicle includes multiple upward-facing cameras and multiple downward-facing cameras with overlapping fields of view to enable stereoscopic computer vision in a plurality of directions around the aerial vehicle. Similar camera arrangements can also be implemented in fixed-wing aerial vehicles.

A control unit for an aircraft capable of hovering or for a flight simulation system of the aircraft is described; the control unit is programmed to:receive in input a plurality of data associated with equipment and / or kits actually installed or simulated on the aircraft and / or with the operating configuration of the equipment and / or kits; the equipment and / or kits causing a reduction of the actual or simulated forward velocity of the aircraft;store a table defining a correspondence between each datum and a respective value of a first signal associated with a value of maximum forward velocity of the aircraft; anddisplay the lowest of the first signals.

An introduced autonomous aerial vehicle can include multiple cameras for capturing images of a surrounding physical environment that are utilized for motion planning by an autonomous navigation system. In some embodiments, the cameras can be integrated into one or more rotor assemblies that house powered rotors to free up space within the body of the aerial vehicle. In an example embodiment, an aerial vehicle includes multiple upward-facing cameras and multiple downward-facing cameras with overlapping fields of view to enable stereoscopic computer vision in a plurality of directions around the aerial vehicle. Similar camera arrangements can also be implemented in fixed-wing aerial vehicles.

The invention provides an aircraft, and relates to the technical field of aircrafts. The aircraft comprises a fuselage, tilting rotors and fixed rotors. Wings are arranged on two sides of the fuselage, and an empennage is arranged at the tail of the The tilting rotors are symmetrically arranged on at least one of the empennage, the wings and the fuselage, each tilting rotor comprises a first propeller and a first electric engine, the first electric engines are in transmission connection with the first propellers, and the first electric engines are integrated electric engines. The fixed rotors are symmetrically installed on the wings on the two sides of the fuselage, each fixed rotor comprises a second propeller and a second electric engine, the second electric engines are in transmission connection with the second propellers, and the second electric engines are distributed electric engines. The aircraft can solve the problems that the size, weight and heat dissipation efficiency of an existing electric engine are difficult to consider, and efficient flight of the aircraft is difficult to achieve.

A control unit for an aircraft capable of hovering or for a flight simulation system of the aircraft is described, the control unit is programmed to receive at input at least a first signal associated with real or simulated flight parameters of the aircraft and to provide at output a second signal associated with a forward velocity to never exceed of the aircraft; the control unit is programmed to process a third signal associated with an actual or simulated weight of the aircraft; to associate plurality of tables to respective intervals of values of the third signal; each table associating a plurality of values of the second signal with a respective first signal; and to process the second signal, based on the table associated with the relative interval of the third signal and the respective first signals.

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.

To provide an autonomously flying unmanned aircraft freely landing on and leaving the water and its floats that can realize acoustic positioning by SBL by dispersively arranging a plurality of hydrophones in a limited space of the unmanned aircraft.SOLUTION: Lower portions of six arms 11 extending radially from a fuselage of a water-air combination drone 1 are respectively provided with float parts 14 via connectors 16. The float parts 14 sink under the water surface when the water-air combination drone 1 lands on the water surface to generate buoyancy in the water-air combination drone 1 so that the water-air combination drone 1 stays on the water surface. The float part 14 is composed of a columnar main body part 14a and a cap-like or conical projection part 14b extended downward from the main body part, and a hydrophone 20 is mounted inside the projection part 14b. The hydrophone 20 is fixed at a position and in such a posture that a pressure sensor 20a attached to an end portion of the hydrophone 20 can detect a sound wave in the water when the aerial combination drone 1 / aerial drone 1A lands on the water.SELECTED DRAWING: Figure 3

A blade pitch detection apparatus for an aircraft having a lower rotor hub assembly and an upper rotor hub assembly, the upper rotor hub assembly including a blade pitch adjustment linkage configured to maintain the rotor blades at a first blade pitch while a rotational velocity of the upper rotor hub assembly is below a threshold and to maintain the rotor blades at a second blade pitch while the rotational velocity is above a threshold. The pitch detection apparatus includes a magnet coupled to a component of the blade pitch adjustment linkage and a sensor coupled to a component of the lower rotor hub assembly and configured to generate a signal in the presence of the magnet. Processing circuitry in communication with the sensor can determine whether the plurality of rotor blades are at the first blade pitch or the second blade pitch based on the signals.

The invention discloses a high-heat-dissipation integrated ducted fan electric propulsion system, which belongs to the technical field of ducted fans and comprises a motor controller, a motor, a motor front bearing, a motor rear bearing, a front fairing, a rear fairing and an integrated fan rotating shaft integrally formed by fan blades and a motor rotating shaft. The integrated nacelle motor shell is integrally formed by a motor shell, a ducted nacelle and a plurality of groups of ducted stationary blades; cooling devices are mounted on the motor shell and the motor controller; the cooling device comprises a cooling water channel and a water cooling cavity; a cooling water channel is arranged on the motor shell; the motor controller is provided with a water cooling cavity, and the cooling water channel is communicated with the water cooling cavity; the front fairing is connected to the left end of the integrated fan rotating shaft, and the rear fairing is connected to the right end of the motor controller. The integrated level is high, the size and the weight are reduced by reducing connecting parts, and the power density is high; the system reliability is high; the system cooling efficiency is high; and the power level compatibility and the expandability are high.

A rotating pylon assembly for aircraft thrust vectoring control. In embodiments, the rotating pylon assembly of embodiments includes a rotating sleeve disposed within a fixed boom of the aircraft, and configured to support a rotor assembly. The rotating pylon assembly includes a bearing assembly configured to functionally couple the rotating sleeve against an inner surface of the fixed boom. The bearing assembly enables the rotating sleeve to rotate against the inner surface of the fixed boom and about a longitudinal axis of the fixed boom. An actuator is configured to rotate the rotating sleeve about the longitudinal axis of the fixed boom. The rotating sleeve may cause the rotor assembly to be rotated or swung about the longitudinal axis of the fixed boom to position the rotor assembly in a position to vector the thrust provided by the rotor assembly based on a control command.

A flying vehicle with a flight part connected to a plurality of rotor wing parts and a main wing, wherein the main wing is configured such that the lift produced by the main wing during landing is reduced compared to the lift produced by the main wing during cruising. Furthermore, the main wing is fixed at a forward tilt with respect to the flight part. Furthermore, the rotor wing is connected at an angle that produces propulsion and lift during cruise. Furthermore, the rotor blades are connected at an angle that generates propulsive force during cruise.

Collective control using vertical velocity is provided. A system can include a data processing system comprising one or more processors, coupled with memory. The data processing system can receive, from a sensor, a velocity of an aerial vehicle along a vertical axis of a body of the aerial vehicle. The data processing system can generate a command for collective control of a pitch of blades of a rotor of the aerial vehicle based on a comparison of the velocity with a reference. The data processing system can control, via an actuator, the pitch of the blades of the rotor in accordance with the command.

The present invention provides a system for remote vehicle operation by human pilot and artificial intelligence systems. The system comprises: a vehicle capable of movement, a human operator and control station situated outside of the vehicle in a remote location, a bidirectional wireless communications channel, which transmits commands from the control station to the vehicle and which receives information related to the vehicle's state and its environment from the vehicle, and a human interface device conveying information to the human operator and receiving inputs.

A battery replacement system for controlling a battery pack loadout for an aircraft having at least one installed battery pack includes a vehicle including a battery storage assembly, a controller, and a battery transfer assembly. The battery storage assembly is configured for storing at least one stored battery pack. The controller is configured to identify a state of charge for each of the at least one installed battery pack installed on the aircraft, identify an energy storage prerequisite for a flight or series of flights of the aircraft, and identify a battery pack loadout plan for the aircraft. The battery pack loadout plan identifies one or more of the at least one stored battery pack to be installed on the aircraft. The controller is further configured to control the battery pack loadout for the aircraft by controlling the battery transfer assembly to install the one or more of the at least one stored battery pack into the aircraft.

An arm-equipped unmanned aerial vehicle and a control method therefor, the arm-equipped unmanned aerial vehicle comprising a tilting quadrotor unmanned aerial vehicle, a mechanical arm, and a control module (7). The tilting quadrotor unmanned aerial vehicle comprises a fuselage, tilting driving devices and tilting arms, the mechanical arm being mounted below the fuselage, the control module (7) being mounted above the fuselage, and the tilting driving devices being respectively arranged on two sides of the fuselage. Each tilting driving device is in drive connection to a tilting arm, the tilting arms extending from the head of the fuselage to the rear of the fuselage, and the tilting driving devices being used for driving the tilting arms to rotate in a vertical plane. The two ends of each tilting arm are each provided with a rotor mechanism that can be driven to rotate. The mechanical arm, the tilting driving devices and the rotor mechanisms are all connected and driven by the control module (7).

An aerial vehicle configured to fly with a load suspended therefrom includes a lift generator configured to generate lift for flight, a plurality of supports configured to support the load, an attachment to which the supports are attached, and a relay to relay and support the supports between the load and the attachment. One of the attachment and the relay is outward of, in an airframe of the aerial vehicle, an other one of the attachment and the relay in a plan view.

An undercarriage, a middle large rotor and a middle large motor are connected to the lower portion of a fuselage body and sequentially connected to the top of a middle small tower, and the right front portion, the left front portion, the left rear portion and the right rear portion of the fuselage body are correspondingly connected with a right front fuselage arm, a left front fuselage arm, a left rear fuselage arm, a right rear fuselage arm and a power assembly. The connecting line of the rotating centers of the rotors of the four power assemblies is square or rectangular, the rotating directions of the rotors of the power assemblies at the same opposite angles are the same, the rotating directions of the rotors of the power assemblies at different opposite angles are opposite, and the rotating faces of the two rotors opposite to the middle large rotor in rotating direction incline around the axes of the respective arms. The included angle between the rotating surfaces of the two rotors and the horizontal plane is an acute angle beta, the rotating surfaces of the two rotors with the same rotating direction as the middle large rotor incline around respective arm axes, the included angle between the rotating surfaces of the two rotors and the horizontal plane is an acute angle theta, beta is larger than theta, the reaction torque and the horizontal component torque of the rotors jointly drive the aircraft to steer, and the aircraft has the advantages of being long in endurance time, large in load and high in wind resistance. And a universal flight platform is formed.

An aircraft includes a vehicle body, a main wing fixedly connected to the vehicle body and configured to provide lift thrust for the aircraft, a canard arranged at the vehicle body near a nose and configured to provide lift thrust for the aircraft, and a multi-rotor assembly including a first rotor assembly mechanically coupled with the main wing and a second rotor assembly rotatably connected to the canard and configured with an adjustable tilting angle relative to the canard to provide at least one of lift thrust or forward pulling thrust for the aircraft.

A rotor-blade assembly has a lock system to enable and disable a folding degree of freedom and a pitching degree of freedom of a rotor blade. A grip couples a blade to a hub, the blade being pivotable about a fold axis relative to the grip, the blade and grip being pivotable together about a pitch axis relative to the hub. A fold lock prevents folding of the blade in a fold-lock position and allows folding of the rotor blade in a pitch-lock position, and a pitch lock allows pitch movement of the rotor blade in a fold-lock position and prevents pitch movement of the rotor blade in the pitch-lock position. A rotary actuator carried by the grip has actuator arms coupled through linkage to the pitch lock and fold lock, and the actuator is configured for moving the pitch lock and fold lock between the fold-lock and pitch-lock positions.

A vertical take-off or landing (VTOL) aircraft is disclosed that includes a propulsion system comprising at least four tilting propulsion assemblies and two or more lifting propulsion assemblies. Actuation of the tilting mechanisms can convert the aircraft from a hover configuration, in which all propellers produce thrust generally upward to counteract the aircraft's weight, to a forward flight configuration, in which the four or more tilting propellers produce thrust generally in a forward direction parallel to the fuselage to overcome drag in cruise flight and the lifting propellers produce no thrust or a level of thrust generally less than that required in the hover configuration.

“A tilting apparatus for an aircraft, comprising: a tiltable aircraft component which tilts between a first and second position, at least one actuator for adjusting a tilt angle of the tiltable aircraft component, and at least one passive damper connected to the tiltable aircraft component and configured to limit a rate of change of the tilt angle of the tiltable aircraft component. The at least one passive damper is on a load path separate from a load path of the at least one actuator.”

An introduced autonomous aerial vehicle can include multiple cameras for capturing images of a surrounding physical environment that are utilized for motion planning by an autonomous navigation system. In some embodiments, the cameras can be integrated into one or more rotor assemblies that house powered rotors to free up space within the body of the aerial vehicle. In an example embodiment, an aerial vehicle includes multiple upward-facing cameras and multiple downward-facing cameras with overlapping fields of view to enable stereoscopic computer vision in a plurality of directions around the aerial vehicle. Similar camera arrangements can also be implemented in fixed-wing aerial vehicles.

A propulsion system, comprising: a motor assembly including a stator and a rotor, a heat exchanger configured to receive air to cool a liquid, and a thermal plate including one or more channels configured to convey the liquid from the heat exchanger to the motor assembly. The heat exchanger is mechanically and fluidically coupled to the thermal plate.