1220results about "Propellers" 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 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.

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.

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.

The invention discloses a composite blade electroforming metal wrapping sheet and a production device thereof, and relates to the technical field of blade metal wrapping sheets, the composite blade electroforming metal wrapping sheet comprises a plurality of wrapping sheet sections, one side surface of each wrapping sheet section is provided with a fixing slot, a reinforcing assembly is arranged in each wrapping sheet section, and the reinforcing assembly comprises an additional side plate arranged on one side surface of each wrapping sheet section, the multiple wrapping sheet sections and the additional side plates are combined into a wrapping sheet finished product piece, a fixed side block is arranged at one end of the wrapping sheet finished product piece, the surface of one side of the fixed side block is connected with the surface of one side of the additional side plate at one tail end of the wrapping sheet finished product piece, a connecting shaft rod is arranged on the upper surface of the fixed side block, and a turnover anchoring plate is arranged on the surface of one side of the connecting shaft rod. And a plurality of anchoring screws are arranged on the upper surface of the overturning anchoring plate, and in the scheme, by arranging the reinforcing assembly and the machining mechanism, the stability of the wrapping piece in the using process and the production efficiency are improved.

The invention discloses an unmanned aerial vehicle propeller clamping seat quick release structure which comprises a propeller fixing seat and a mounting seat in threaded connection with the propeller fixing seat, the mounting seat is used for being connected with an output shaft of a motor, and one end, away from the mounting seat, of the propeller fixing seat is rotatably connected with blades. An elastic gasket is arranged between the propeller fixing seat and the mounting seat, when the propeller fixing seat is screwed down, the elastic gasket is pressed, the reverse pre-tightening force of the elastic gasket can enable the propeller fixing seat and the mounting seat to keep the pre-tightening force, and thread loosening caused by flying vibration of the propeller can be effectively prevented; the connection reliability and safety are improved, so that the quick release structure for the paddle clamping seat of the unmanned aerial vehicle has high rigidity and vibration reduction performance, and the power transmission stability of the motor is ensured.

The present disclosure is generally related to aircraft having one or more unducted fan propulsors at locations within specific regions relative to an airfoil, such as a wing or horizontal stabilizer. More specifically, the specific regions are located where there is a relatively higher pressure air flow beneath the wings or above a horizontal stabilizer. That higher pressure air flow can be utilized to provide increased thrust from the unducted fan propulsor.

The invention relates to the field of aircrafts, and discloses a sandwich-structured composite material mute paddle, which comprises a paddle blade, and the paddle blade is a sandwich carbon fiber laminated structure composed of an upper layer prepreg laying layer unit, a foam sandwich layer and a lower layer prepreg laying layer unit; the upper-layer prepreg laying unit and the lower-layer prepreg laying unit are each of a bionic spiral structure formed by stacking multiple layers of composite material prepreg sheets in a bionic spiral laying sequence. The invention further discloses the preparation method of the composite material mute paddle of the sandwich structure. Load can be effectively transmitted and dispersed along fiber paths in different directions in the outer-layer prepreg bionic spiral structure, so that the comprehensive rigidity, the torsional property and the damage tolerance of the paddle are improved, the material characteristics are optimized, a three-section type pressurization method is adopted, a stable external pressure environment is established in the early stage of paddle foaming, and the mechanical performance of the paddle is improved. And dynamic balance and collaborative forming of internal and external pressure in the paddle forming process are achieved.

A craft is provided with a lever that can control the power / speed of the craft and semi-automatically transition the craft in various modes of operation. This makes control of the craft somewhat similar to control of a boat, thereby bringing a maritime flight control experience to a wing-in-ground effect vehicles, hydrofoiling vessels, seagliders, and seaplanes. Further, various audio, visual, and / or haptic devices in the cockpit can provide alerts / feedback to the operator on the use of the lever and mode transitions.

The present invention addresses the problem of providing a hollow molded article that can be suitably applied to propeller blades for UAMs and drones, is lightweight, and has exceptional impact resistance. In order to solve the aforementioned problem, a hollow molded article comprises: a skin part (skin part (A)) composed of a composite material that contains a resin and reinforcing fibers, the skin part forming the outer surface of the hollow molded article; and a hollow part and a porous body in the internal space of the skin part (A), the hollow molded article being characterized in that, in regard to three planes (plane a, plane b, and plane c, in order from the plane with the greatest area) forming a rectangular parallelepiped that circumscribes the hollow molded article and has the smallest volume, the ratio (α / β) is 1.5-150, where α (cm) is the length of the long side of the plane a and β (cm) is the arithmetic average value of the lengths of the long and short sides of the plane c, and in that conditions 1 and 2 are satisfied.　Condition 1: The porous body has a specific gravity of 0.3 or lower, and at least one porous body is in contact with all or part of the inner surface of the skin part (A) forming a ridge line from either or both of a point and a surface in contact with the plane b to the plane c in top view seen from the plane a.　Condition 2: In all cross-sections perpendicular to the longitudinal direction at positions where the hollow molded article is equally divided into four sections in the longitudinal direction, the area occupied by the hollow part is 50-95%, where 100% is the sum of the area occupied by the hollow part and the area occupied by the porous body.

A method of directing particles entrained within an airflow disposed to enter a gas turbine engine of an aircraft is provided. The gas turbine engine includes a nose cone, a fan section, a compressor inlet, a compressor section, and a turbine section. The nose cone is fixed for rotation with the fan section. The method includes: providing an entrained particle removal (EPR) system configured to inject a fluid outward from the nose cone from a plurality of nozzles engaged with the nose cone, wherein the nozzles are spaced apart from one another around a circumference of the nose cone; and controlling the EPR system to inject the fluid from the plurality of nozzles into the airflow. The particles wetted by the injected fluid are subject to centrifugal force in and aft of the fan section and are directed radially outward of the compressor inlet.

A method of operating a propeller system for an aircraft, the propeller system comprising a propeller, the method comprising: receiving propeller speed information, the propeller speed information indicating propeller speed; receiving a target propeller speed; performing a propeller speed threshold adjustment process, the propeller speed threshold adjustment process comprising adjusting a propeller speed threshold as a function of the target propeller speed; comparing the propeller speed to the propeller speed threshold; and in response to propeller speed exceeding the propeller speed threshold, performing an overspeed protection process.

An assembly is provided for an aircraft. This aircraft assembly includes an airframe structure, a propulsion system and a vane. The airframe structure includes a fuselage and at least two wings. The fuselage extends longitudinally along a longitudinal centerline from a forward end of the fuselage to an aft end of the fuselage. The wings extend laterally from opposing sides of the fuselage. The propulsion system is mounted to the airframe structure. The propulsion system includes an airflow inlet into the propulsion system. The airflow inlet is spaced vertically out from a top side of the airframe structure. The vane projects vertically out from the top side of the airframe structure to a distal end of the vane. The vane laterally overlaps and is longitudinally forward of the airflow inlet.

Systems and methods include a tilt device for an aircraft vehicle. The tilt device is configured to rotate a rotor assembly between first and second positions. The tilt device comprises a linear actuator disposed within an aircraft fairing; a sleeve having a slot defined therein; and a piston coupled to the linear actuator configured to translate axially within the sleeve. A method includes actuating the linear actuator to translate the piston, wherein the rotor assembly is coupled to an end of the piston and comprises a motor and one or more rotor blades. The method further includes rotating the piston within the sleeve as the piston translates axially along the sleeve via a pin disposed within a slot defined in the sleeve, wherein the pin extends from the piston and through the slot. The method further includes actuating the motor to operate the one or more rotor blades.

A method of operating an automated fiber placement system includes supplying a plurality of tows to a tow deposition assembly of an automated fiber placement head, cutting a first tow into a first upstream and downstream tow portions, continuing to supply the first tow through a compaction roller to apply the first tow to a substrate such that a trailing edge of the first upstream tow portion substantially aligns with a leading edge of the first downstream tow portion at a first interface, cutting a second tow into a second upstream and downstream tow portions, and continuing to supply the second tow through the compaction roller to apply the second tow the substrate such that a trailing edge of the second upstream tow portion substantially aligns with a leading edge of the second downstream tow portion at a second interface that is offset from the first interface.

The present invention discloses a dual-motor coaxial different-direction dual-propeller structure of an electric paramotor. The structure comprises a cylindrical mounting shaft with a central hole inside, wherein a first brushless motor is fixedly sleeved on the mounting shaft; a first blade assembly is rotationally sleeved on the mounting shaft; a second brushless motor is fixedly sleeved on the mounting shaft; a second blade assembly is rotationally sleeved on the mounting shaft; the first blade assembly is in transmission connection with the first brushless motor; the second blade assembly is in transmission connection with the second brushless motor; and during flight, the first brushless motor and the second brushless motor respectively drive the first blade assembly and the second blade assembly to rotate in opposite directions.

Embodiments of the invention are directed to systems and methods for reducing drag on an aircraft. The aircraft can include at least one propulsion system with rotor blades configured to reduce aerodynamic drag when the propulsion system is deactivated. To reduce the amount of drag, the rotor blades can be locked into an aerodynamic position, and prevented from passively spinning. Additionally, the rotor blades can be configured to have angular positions that reduce drag. For example, the rotor blades as a group may be configured to generally point toward and / or away from an airflow current.

An electric vertical take-off and landing aircraft comprises a fuselage and a tilt wing. The tilt wing is tiltable relative to the fuselage in a range of tilt wing angles. Control surfaces are arranged at the tilt wings. The aircraft comprises a horizontal stabilizer with an elevator, in particular a stabilator, a vertical stabilizer with a rudder, in particular a fully movable stabilizer, at least one electric engine for powering main propellers arranged at the tilt wing and at least one software control device. The control device is configured to control at least the control surfaces , the main propellers and the tilt wing angle during hover and transition between hover and cruise flight.

A VTOL aircraft (300, 600) includes a lift propeller (312, 612) configured to provide lift during take-off, landing, and hover operations. The lift propellers (312, 612) are configured to stow close to the boom surface (323, 623) when not in use, for example, during a cruise flight, to minimize drag around the surface of the propellers (312, 612). The lift propellers (312, 612) are vertically displaceable relative to the booms (322, 622) when switched to a lift configuration to provide a greater spacing from the booms (322, 622) to improve lift efficiency and reduce unwanted vibrations. The lift propeller (312, 612) may have a fail-safe configuration that allows the propeller (312, 612) to passively move between a lift configuration and a stowed configuration, and to fully rotate even when fully retracted.

The invention discloses a powerful propeller and an aircraft, and belongs to the technical field of aircrafts. The powerful propeller comprises a cover disc, a stator and a rotor, the cover disc comprises a central bearing seat, a radial support and an outer mounting frame which are sequentially connected from inside to outside, the rotor comprises a paddle mounting column, paddles and an outer ring which are sequentially connected from inside to outside, and the outer ring is provided with a permanent magnet which is in induction fit with the stator; the paddle mounting column is connected with the central bearing seat through a bearing; and the outer mounting frame is fixedly connected with the stator. Airflow loss of the blade tip can be avoided, and thrust is greatly improved. According to the invention, the coaxial contra-rotating technology can be realized. And the two coaxial fans can achieve a better superposition effect, so that the noise is reduced. The rotating directions of the two blades which are coaxially designed are opposite, the rotating torque of the propeller can be offset, and balance of the aircraft fuselage can be kept beneficially. According to the invention, a negative pressure suction air cooling technology can be designed according to needs to solve the problem of motor heat dissipation, and extra electric energy consumption is not needed.

The present disclosure is generally related to aircraft having one or more unducted fan propulsors at locations within specific regions relative to an airfoil, such as a wing or horizontal stabilizer. More specifically, the specific regions are located where there is a relatively higher pressure air flow beneath the wings or above a horizontal stabilizer. That higher pressure air flow can be utilized to provide increased thrust from the unducted fan propulsor.

A propeller blade or airfoil for a turboprop engine made from composite material including a matrix-densified fibrous reinforcement, the propeller blade or airfoil including, in the direction of its span, a root and an aerodynamic profile. The fibrous reinforcement includes a fibrous preform having three-dimensional weaving with a root preform portion and an aerodynamic profile preform portion. The fibrous preform includes a separation delimiting a recess that forms a cavity extending both into the root and into the aerodynamic profile. A spar is present in the cavity, the spar including an aerodynamic profile shaping portion positioned in a first portion of the cavity and a root shaping portion positioned in a second portion of the cavity. The root has a rotationally symmetric shape.

The invention provides a fan propelling device, a driving assembly for a robot and the robot, the fan propelling device comprises a duct shell, the duct shell is of a structure with two open ends and limits an axial airflow channel, and a first fan assembly and a second fan assembly are coaxially and sequentially arranged in the duct shell; a first fairing and a second fairing are arranged between the first fan assembly and the second fan assembly, the first fairing and the second fairing are connected through a supporting structure, and the supporting structure is arranged on the inner wall of the duct shell. The embodiment of the invention realizes high thrust density and low pneumatic loss, and is suitable for flight propulsion requirements of humanoid robots and other various robots. The embodiment of the invention has the advantages of high dynamic response, good stability and excellent terrain adaptability, and is particularly suitable for high-performance flight and positioning tasks of a future robot in a complex air-ground collaborative environment.

Aspects of the present disclosure generally relate to systems and methods for flight control of aircraft driven by an electric propulsion system and in other types of vehicles. In some embodiments, an aircraft is disclosed, the aircraft comprising: at least one electric propulsion unit; at least one sensor configured to measure at least one aircraft condition; and at least one flight control computer configured to dynamically vary at least one torque command for the at least one electric propulsion unit based at least on the at least one aircraft condition; wherein the at least one electric propulsion unit is configured to generate thrust based on at least one dynamically changed torque command.

Variable pitch propeller, comprising at least two blades and a rotor with a hub, the hub comprising a blade support for each blade of the propeller, each blade comprising a blade foot designed to cooperate with one of said blade supports in order to maintain the blade in position in the rotor while allowing the pitch to be changed, comprising: - a blade foot comprising a composite core (11), disposed in an outer sleeve (13) of the blade support resting on it by means of an elastomer buffer (12), - a blade support (4) having an upper bearing (2) and a lower bearing (3) in contact with the outer sleeve (13), the blade support (4) also comprising at least two half-jaws (14) cooperating with the composite core (11) in order to prevent the blade foot from moving in a radial direction relative to the blade support (4). Figure for the abridged version: Fig 8

Variable pitch fan blade (8a) for an unfaired turbomachine fan, the blade (8a) comprising an aerodynamic blade (9) and a base (10), the blade (9) comprising a recess opening simultaneously onto the upper and lower surfaces (14) and a leading edge (15) of the blade (9), the blade (8a) further comprising a measuring device (26) housed in the recess and clipped onto the blade (9), the measuring device (26) comprising a streamlined body (28) whose outer surface (29) is complementary to the outer surface (30) of the blade (9) to ensure aerodynamic continuity, the body (28) carrying at least one measuring instrument (31) configured to measure at least one parameter of an airflow upstream of the blade (9). Figure for the abstract: 2

The present disclosure is generally related to aircraft having one or more unducted fan propulsors at locations within specific regions relative to an airfoil, such as a wing or horizontal stabilizer. More specifically, the specific regions are located where there is a relatively higher pressure air flow beneath the wings or above a horizontal stabilizer. That higher pressure air flow can be utilized to provide increased thrust from the unducted fan propulsor.

An actuation system (1) for adjusting the pitch of the fan blades (20) of an aircraft engine, comprising a hydraulic power supply (3), a hydraulic cylinder (5), and a hydraulic circuit including a hydraulic channel equipped with a check valve (43) and a distribution valve (41) adapted to selectively adopt two configurations, such that when the distribution valve (41) is in the first configuration, the hydraulic cylinder (5) is configured to be position-controlled by the hydraulic power supply (3), and when the distribution valve (41) is in the second configuration, the control fluid can only flow from a retraction chamber (5f) to an extension chamber (5c) so that the piston of the hydraulic cylinder (5) moves in the first direction of travel, the fan blades orienting themselves towards a safety position known as the "feathered position." Figure for the abstract: Fig. 5

A variable toroidal propeller (10) is proposed, comprising a hub (12) and toroidal propeller blades (14) connected to the hub (12). The hub (12) is configured to operably couple the blades (14) to an actuator (44), and the blades (14) are configured to deform when the actuator (44) is operated.