1057 results about "Nacelle" 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.

The invention discloses a floating type offshore wind turbine aerodynamic load calculation method based on a frequency domain method. The method comprises the steps that a state derivative is determined based on a blade element momentum theory quasi-steady-state assumption, and a dynamic inflow model is used for correction; establishing a pneumatic-elastic coupling two-degree-of-freedom linear dynamic model; establishing a wind wheel kinetic model; establishing a control model according to a floating type offshore wind turbine pitch angle control strategy, a torque control strategy and a floating body motion feedback control strategy; based on the pneumatic-elastic coupling two-degree-of-freedom linear dynamic model, the wind wheel dynamic model and the control model, pneumatic additional mass and pneumatic additional damping are obtained; pneumatic exciting force acting on the hub when the position of the cabin is fixed is obtained; and based on the pneumatic additional mass, the pneumatic additional damping and the pneumatic exciting force, an overall linear dynamic model of the fan is established and solved, and overall response is obtained. According to the method, the calculation result precision can be improved while the calculation efficiency is ensured, and a technical support is provided for accelerating the simulation efficiency of the offshore wind turbine.

The invention belongs to the technical field of aircraft design, and particularly relates to an integrated tilting power system integrated with hydrogen fuel cell motor electric control and an aircraft. Comprising a tilting mechanism connected with a machine body; the integrated motor and controller is fixedly connected with the tilting mechanism and located at the end, close to the upstream of the incoming flow, of the tilting mechanism; the tilting rotor wing is mounted at one end, close to the incoming flow upstream, of the integrated motor and controller; the hydrogen fuel cell is fixedly connected with the tilting mechanism and is positioned at one end, close to the downstream of the incoming flow, of the tilting mechanism; the nacelle shell wraps the tilting mechanism, the integrated motor, the controller and the hydrogen fuel cell; the nacelle outer heat dissipation fins wrap the nacelle in the circumferential direction; and the tilting mechanism, the integrated motor and controller and the liquid cooling radiating pipeline of the hydrogen fuel cell exchange heat with the radiating fins outside the nacelle.

The invention relates to the technical field of intelligent unmanned ships, in particular to a wave self-adaptive unmanned ship, a self-adaptive control system and a control method.The wave self-adaptive unmanned ship comprises a main ship body, a front arch, a rear arch, a suspension system, a propelling nacelle, a rigid sliding plate and a buoy, the main ship body is connected with the rear arch and the front arch, and the rigid sliding plate is fixed to the buoy; the propulsion nacelle is installed at the tail of the rigid sliding plate, the rear arch and the rigid sliding plate are installed through two bearings perpendicular to each other, the suspension system comprises a rocker arm, a plate spring and a TPMLM actuator, the rocker arm is connected to the rigid sliding plate, the plate spring and the TPMLM actuator are connected between the rocker arm and the rigid sliding plate and support the rocker arm to be in an upward inclined posture, and the rear arch is connected to the rigid sliding plate. The front arch is connected with the rocker arm, the plate spring and the TPMLM actuator are installed in parallel in the vertical direction, the TPMLM actuator is used for outputting active control force for restraining movement of the ship body, and the unmanned ship, the self-adaptive control system and the self-adaptive control method have the advantages that wave loads can be actively counteracted, and therefore movement restraining is achieved.

An arrangement for fixing a housing of a wind turbine gearbox in a nacelle, including a housing-fixing means, a nacelle-fixing means, and at least two spring devices. The spring devices support the housing-fixing means against the nacelle-fixing means in opposite directions along a support axis. The spring devices are arranged on different sides of a plane extending parallel to an axis of rotation of an input shaft of the wind turbine gearbox.

The invention discloses a rotorcraft flutter model design and test method for a low-speed wind tunnel test, and belongs to the technical field of low-speed wind tunnel tests. The method solves the difficult problem of how to separate key nacelle modes in rotation flutter of the tilt rotorcraft. A fuselage is connected with the side wall of a wind tunnel, wings are of a double-girder straight wing structure, one end of each wing is connected with the fuselage, the other end of each wing is connected with a nacelle mechanism, a rotating paddle is connected with the nacelle mechanism, and a motor, a yawing mechanism and a pitching mechanism are arranged in the nacelle mechanism. The yawing mechanism and the pitching mechanism are connected in a matched mode to achieve decoupling in the yawing direction and the pitching direction of the model, the motor is installed on the pitching mechanism, and the execution end of the motor is connected with a main shaft of the rotating paddle. According to the rotorcraft flutter model design and test method for the low-speed wind tunnel test, decoupling of modes in the pitching direction and the yawing direction of the model can be achieved, the flutter characteristic of the model is shown as coupling of the pitching mode and the yawing mode of a nacelle, and the test requirement of the model wind tunnel test is met.

A gas turbine engine includes a fan assembly, a turbo-engine encased within a turbo-engine cowl structure, a nacelle, and a thrust reverser system arranged, at least in part, in the nacelle. The turbo-engine includes a low-pressure compressor, a high-pressure compressor, an inter-compressor frame structure between the low-pressure compressor and the high-pressure compressor and including an outer frame portion having a cowl door engagement member on an upstream side of the outer frame portion, and a plurality of cowl doors defining the turbo-engine cowl structure. Each cowl door includes an inter-compressor frame engagement portion that engages with the cowl door engagement member of the inter-compressor frame structure, and a plurality of thrust reverser drag link connectors arranged on an outer side of the cowl door and arranged between the upstream side of the inter-compressor frame structure and a downstream side of the inter-compressor frame structure.

The application discloses a floating wind power roll damping system based on fan-geared coupling and a control method. The system comprises a fan rotor, a tower, a floating platform, a cabin and a double geared roll damping device. A sensor system is arranged on the top of the tower and the floating platform and is used for monitoring multi-degree-of-freedom motion data of the system. The data collected by the sensor is transmitted to a controller through a signal transmission device, so as to realize real-time monitoring and control of the rolling state of the system. The active precession control mechanism controls the rotation of the precession shaft according to the received servo motor driving torque control signal output by the controller, so as to realize the control of the precession motion of the geared rotor. The application further establishes a complete fan-geared coupling dynamic model and designs a control method based on multi-objective optimization. The PSO algorithm is used to simultaneously optimize the roll damping performance and the energy consumption index, and a complete Pareto optimal solution set is established. The method can realize the dynamic balance of the performance and the energy consumption.

The invention discloses a wind power cabin inspection robot, and relates to the technical field of operation and maintenance of wind power generation equipment. Comprising a walking mechanism, an installation mechanism and a detection mechanism, the walking mechanism comprises a left installation frame, a right installation frame is arranged on one side of the left installation frame, a notch is formed in one side of the right installation frame, and an insertion strip is inserted into the notch. Through the arrangement of the walking mechanism, the mounting mechanism and the detection mechanism, in the use process, after the detection mechanism moves to a target area, a second motor drives a third gear to drive a second gear to rotate, so that a rotating rod rotates around a connecting frame, the transverse detection range is expanded, and meanwhile, the third motor drives a rotating shaft to rotate; the device can cover most of equipment and dead angles in a cabin, and the visual angle can be adjusted without moving the robot body.

The utility model provides a lifting device for a tower crane. The lifting device comprises a mounting seat, a bracket, a hanging bracket and a steel wire rope, the mounting seat is fixed to the top of a cabin, the support is mounted on the mounting seat, and the hanging bracket is arranged at the top of the support and provided with the hoisting pulley block. A lifting pulley block is arranged at the rear end of the on-tower crane, and when the on-tower crane is vertically arranged, the lifting pulley block and the hoisting pulley block are oppositely arranged; the hoisting pulley block comprises at least one hoisting pulley which is coaxially arranged, and the lifting pulley block comprises at least one lifting pulley which is coaxially arranged; a guide pulley block is arranged on a suspension arm of the on-tower crane; when the on-tower crane is lifted, one end of the steel wire rope is fixed on the on-tower crane or the hanging bracket, and the other end of the steel wire rope penetrates through the lifting pulley block, the hoisting pulley block and the guide pulley block and then is connected to a power unit arranged below the fan tower; the power unit tightens the steel wire rope to lift the on-tower crane.

An aerial and preferably marine vehicle intended to operate in its principal mode near the surface of water or land employing the Wing-in-Ground Effect (WIG) and capable to take-off and land vertically (VTOL) by means of thrust vectoring, which vehicle has a wing arranged at the lowermost part of the fuselage, propulsion units comprising four rotatable pylons extending transversely in pairs on both sides of the upper part of the fuselage, four elongated nacelles mounted on the outer tips of said pylons, which nacelles contain electric motors (E) and provided with propellers at their extremities, so that the rotation of the pylons results in turning the nacelles and thrust of propellers from substantially vertical, ensuring take-off and landing, to substantially horizontal providing a flight mode, retractable hydroskis for emergency landing on water, while said propulsion units and said wing are spaced apart vertically and horizontally and do not overlap.

An assembly including a nacelle panel of an aircraft engine, the nacelle panel including an outer skin, an inner skin and a central layer interposed between the outer skin and the inner skin, and the nacelle panel having a free inner enclosure contiguous with the outer skin, and a member forming a link including one or more degrees of freedom, the member being attached to the nacelle panel solely by one or both of the outer skin and the inner skin, and the member extending facing the free inner enclosure.

The invention relates to the technical field of aircraft propulsion systems, in particular to a special-shaped air inlet lip for an on-wing integrated distributed propulsion short cabin unit. The lip is located at the starting part of the air inlet section and is defined by an upper lip, a lower lip, a left lip and a right lip; the inner surface of the upper lip is arc-shaped; the inner surface of the lower lip is linear and is smoothly fused with the upper surface of the wing; the inner surfaces of the left and right lips are curved surfaces with curved sweep characteristics, and the lower half parts of the left and right lips are in an inward-contracting shape; the length of the air inlet channel is defined as the axial distance from the foremost edge of the upper lip to the section of the inlet of the ducted fan and is not greater than the fan diameter D; a first rectification area and a second rectification area are arranged in the air inlet channel to optimize a flow field. Through the fusion design of the special-shaped lip and the wing and the compact air inlet channel, the requirement for compact integrated layout on the wing is met, meanwhile, the additional resistance of the nacelle is effectively reduced, the total pressure recovery coefficient not lower than 0.9 and the flow coefficient larger than 0.8 are guaranteed, and uniform and stable high-quality air inlet is provided for the ducted fan.

The invention provides a wind turbine generator running temperature monitoring method and system, and the method comprises the steps: installing temperature sensors at a generator, a gear box, a main shaft bearing and a cabin environment of a wind turbine generator, and collecting temperature signals in real time; filtering the acquired signal, sending the filtered signal to a reference temperature unit, and comparing the filtered signal with a standard temperature signal to obtain a deviation; calculating a compensation coefficient according to the deviation and performing temperature drift compensation on the signal; and the corrected signal is digitalized by the analog-to-digital conversion module and then input into the controller. A reference temperature unit and a compensation calculation module are arranged in an acquisition system to form an independent calibration loop. The system reads a standard temperature signal in real time and calculates the deviation while collecting the temperature signal, and then performs linear or segmented correction compensation according to the deviation, so that the measurement error of the thermocouple or the thermistor caused by environment temperature change, aging or lead resistance drift can be effectively counteracted, and the output temperature value is always kept consistent with the actual temperature.

The application discloses a double-safety-redundant tilting actuator of a tilt-rotor unmanned aerial vehicle, which comprises a ball screw mechanism and lug connections and trunnion connections installed on the ball screw mechanism; the lug connections are fixed on the wing ribs of a wing, and the trunnion connections are fixed on a nacelle; the ball screw mechanism is configured to drive the nacelle to rotate correspondingly synchronously with extension and retraction actions of the ball screw mechanism; wherein the ball screw mechanism comprises two-stage serial ball screws and two independent driving mechanisms; the two driving mechanisms are configured to independently control the two-stage serial ball screws to complete all extension and retraction actions, so that the operation of the aircraft is safer and more reliable; when any one-stage ball screw is damaged or stuck at a certain angle to cause the ball screw to be unable to retract, the other one-stage ball screw can still normally operate, the nacelle can still rotate within a certain angle, the function of aircraft landing and taxiing can be realized, and the aircraft can be safely landed.

A wind turbine with adaptive nacelle preferably includes a geared blade shaft; and at least one reciprocating generator unit. The geared blade shaft includes a plurality of blade magnets attached to an outer perimeter of the blade shaft, which extend a portion of a length of the blade shaft. Each reciprocating generator unit preferably includes an intermediate magnetic gear, at least one magnetic generator gear, at least one electrical generator, at least one actuator and a retention frame. The intermediate magnetic gear and the at least one generator magnetic gear are pivotally retained in the retention frame. The at least one electrical generator is retained on the retention frame. The at least one actuator is used move the reciprocating generator unit to engage rotation of the geared blade shaft with the intermediate magnetic gear. Rotation of the geared blade shaft causes rotation of the electrical generator.

A gas turbine engine disposed within a nacelle is provided that includes an open rotor propulsion system, compressor, combustion, and turbine sections, a lubrication system, and a turbine active clearance control system. The turbine active clearance control system includes first and second valves, a heat exchanger, and a nacelle air inlet device. The heat exchanger receives air from the air inlet device, accepts a lubricant flow therethrough, and permits heat transfer between the air flow and the lubricant to produce a conditioned air flow. The first valve receives conditioned air flow from the heat exchanger and may pass the conditioned air flow to the second valve. The second valve receives a second air flow from the air inlet device. The turbine active clearance control system may operate in a heating mode in which conditioned air flow, or a combined air flow is provided to the turbine case clearance control segment.

The invention provides a dynamic yaw error compensation method and system based on a cabin type wind lidar. The method comprises the following steps: firstly, acquiring three-dimensional wind field data at a preset distance in front of a wind turbine, simultaneously acquiring operation state parameters of the wind turbine, then extracting unstable transverse component and longitudinal velocity gradient distribution in an incoming wind flow direction, and then calculating a real-time yaw error amount caused by dynamic change of a wind field; and converting the real-time yaw error amount into a feed-forward compensation control signal by combining the dynamic response characteristic of the yaw system of the wind turbine, finally inputting the feed-forward compensation control signal into a main controller of the wind turbine, and adjusting an angle set value of the yaw system so as to complete yaw error compensation of the laser radar. According to the technical scheme, the alignment precision, the wind energy capturing efficiency and the operation stability of the wind generating set under the complex changing wind condition are improved, and high-precision and high-reliability compensation of the dynamic yaw error is achieved.

An aircraft seat connector for mounting an aircraft seat to a mounting rail provided at a floor of an aircraft cabin is provided. The aircraft seat connector comprises a base portion for being introduced into the mounting rail and a seat connection portion. The seat connection portion extends from the base portion and is configured for being releasably coupled to an aircraft seat. The seat connection portion allows for coupling the aircraft seat to the seat connection portion in at least two different spatial orientations.

An aircraft propulsion assembly that has a nacelle with a front opening and a rear opening, a propeller driven by an electric motor, a fuel cell supplying the electric motor with electric current, an inner channel arranged in the nacelle between the front opening and the rear opening. The electric motor and the fuel cell are disposed in the inner channel. A motorized fan is arranged at the rear part so as to draw in the air present in the inner channel and expel it to the outside through the rear opening. A control unit controls the motorized fan. With such an arrangement, the outside air cools the inside of the nacelle and the dihydrogen is evacuated.

In accordance with certain aspects, noise cancellation systems and methods are utilized to mitigate engine tonal noise at sleeping locations in the aircraft cabin space. In one embodiment, an onboard noise cancellation system is provided that includes a plurality of microphones, the plurality of microphones, and a plurality of speakers, and a noise cancellation circuit. In this embodiment the plurality of speakers are arranged proximate to a bed in the sleeping area of the aircraft cabin. Likewise, the plurality of speakers are arranged proximate to the proximate to the bed in the sleeping area. The noise cancellation circuit is further coupled to the plurality of speakers, and the noise cancellation circuit is configured to drive the plurality of speakers to generate noise cancellation audio to at least partially cancel engine noise in a region above the bed.

The invention discloses a control method of an offshore wind power system, and relates to the technical field of offshore wind power generation control, and the offshore wind power system comprises a wind generating set, a converter, a vibration and stress sensor and a controller. According to the invention, the technical problem of how to effectively suppress the key structure load while ensuring the power output is solved. According to the technical scheme, the method is characterized in that a front wind speed sequence is previewed through a cabin type laser radar, and loads of a tower drum and blades are collected in real time; establishing a parameterized state space model, and performing online identification and state estimation on aerodynamic parameters and unmodeled dynamics by adopting an unscented Kalman filter algorithm; in each control period, taking power tracking and load suppression as multiple targets, and based on the updated model and the preview wind speed, solving a finite time domain optimal control problem; and finally, the optimal pitch angle and generator torque increment instruction is analyzed and executed. The method is mainly used for improving the service life and stability of the offshore wind turbine generator.

The invention discloses a flight control method and system for a vertical take-off and landing tilting quad-rotor unmanned aerial vehicle, and aims to solve the technical problem of poor time-varying adaptability of a control system in a nacelle tilting transition stage. According to the method, in a rotor wing flight mode and a nacelle tilting transition mode, attitude angle deviation, deviation change rate and flight speed of the unmanned aerial vehicle are obtained in real time, a fuzzy inference engine is adopted to dynamically output basic control quantity based on a predefined rule base, and a final control instruction is generated in combination with pneumatic feed-forward compensation quantity based on speed to drive a pneumatic control surface. According to the method, fuzzy intelligent decision making and feed-forward dynamic compensation are fused, the limitation that traditional control depends on an accurate model is broken through, the control precision and adaptability of a transition stage are remarkably improved, overshoot is effectively restrained, the adjusting time is shortened, the robustness of a system under model parameter changes and external interference is enhanced, and the system reliability is improved. And a reliable technical guarantee is provided for full-mode flight of the tilt-rotor unmanned aerial vehicle.

The invention relates to an underwater turbine (100), in particular an underwater turbine (100) of a tidal power plant, having at least one rotor shaft (8), wherein: one end of the rotor shaft (8) can be connected, for conjoint rotation, to a rotatable rotor hub (4) which bears rotor blades (6), and the other end of the rotor shaft extends into a stationary housing of the underwater turbine (100), in particular a nacelle (2) of the tidal power plant; the underwater turbine (100) has a positive-engagement rotor rotation lock (20) in an interior of the stationary housing of the underwater turbine; the rotor rotation lock (20) has at least one translatable locking element (28), which can be brought from a free position, in which the rotor rotation lock (20) does not act, into a locking position, in which the locking element (28) prevents rotation of the rotor shaft (8), and at least one receptacle (26), which is designed such that, in the locking position, the at least one receptacle is engaged with the at least one locking element (28) in order to prevent rotation of the rotor shaft (8).

The application relates to the technical field of offshore wind turbine operation and maintenance, and discloses a disassembly-free cabin cover type generator replacement hoist and a rooting method thereof, which comprises the following: a plurality of rooting bases, a main frame arranged in a cabin cover, a plurality of rooting lifting lugs on the main frame, and the plurality of rooting bases installed on at least three rooting lifting lugs; a plurality of supporting legs connected with the plurality of rooting bases in one-to-one correspondence, the cabin cover being provided with hoisting holes corresponding to the plurality of rooting lifting lugs and penetrating through upper and lower surfaces, the upper ends of the supporting legs extending to the outside from the hoisting holes and being connected with mounting seats, and the mounting seats being provided with hoists. The supporting legs are arranged in the cabin cover by using the hoisting holes of the cabin cover, the cabin cover does not need to be disassembled, the connecting structure of horizontal waist holes and vertical waist holes is adopted between the supporting legs, the rooting bases and the mounting seats, the horizontal position and the axial rotation angle of the supporting legs can be adjusted during assembly, then the supporting legs are connected and fixed through fastening bolts, the hoist lifting lugs of the main frames of various wind turbines can be adapted, and standardized operation can be realized.

The invention discloses a human body lifting and holding transfer flying robot. The device is characterized by comprising (100) a land-air dual-purpose duct propeller device. And (200) a robot crawling supporting leg device. And (300) an abdominal cavity type nacelle structure. And (400) the robot hand device is lifted and held. And (500) a master control device. And (600) final assembly. The mechanisms and the systems are reasonably combined. Through AI learning training and intelligent control, the problems of emergency rescue, battlefields and other various environment areas where rescue workers are inconvenient to enter can be effectively solved. And when manpower and transport capacity are not enough, wounded personnel can be rescued, and dead personnel remains can be carried, lifted and transferred. The unmanned aerial vehicle can fly in the air, run on the land and crawl on the field. People needing to be rescued are found, and the human body is lifted and held into the cabin through the robot to be carried and transferred.

The present application relates to wind turbine, provide a kind of wind turbine disc device, including support frame (5);Driving mechanism (3), the driving mechanism (3) is provided with driving gear (301);Mounting disc (4), the mounting disc (4) is detachably mounted on the support frame (5);Adapter disc (1), the adapter disc (1) is used to detachably connect the brake disc of wind turbine, the adapter disc (1) is formed with inner ring gear (101), the adapter disc (1) is separately provided with the support frame (5);Wherein, the mounting disc (4) is formed with positioning installation structure, the driving mechanism (3) is detachably installed on the mounting disc (4) by positioning installation structure, to make the driving gear (301) with the inner ring gear (101) meshing connection.The present application wind turbine disc device does not need to disassemble the top cover of wind turbine nacelle, can be hoisted into nacelle and is installed blade, save time and effort.

This application discloses a wind turbine and a lightning strike current measuring device. The wind turbine includes a lightning arrester, a lightning conductor, a magnetic field sensor, and a controller. The lightning arrester is installed on the blade of the wind turbine to receive lightning strike current. The lightning conductor is located inside the blade and arranged along the length of the blade. One end of the lightning conductor is electrically connected to the lightning arrester, and the other end is electrically connected to the nacelle of the wind turbine. The magnetic field sensor is installed on the yaw platform of the wind turbine to detect the electromagnetic induction value generated when the lightning strike current flows through the yaw platform. The controller is electrically connected to the magnetic field sensor and receives the electromagnetic induction value and calculates the lightning strike current value based on the electromagnetic induction value. The technical solution provided by this application, through the magnetic field sensor preset on the yaw platform, detects the electromagnetic induction value generated when the current flows through in real time and transmits the electromagnetic induction value to the controller electrically connected to it. The controller can accurately calculate the lightning strike current value.

The utility model relates to the technical field of generator cabin cover transfer, and discloses a large wind generator cabin cover transfer tool which comprises a sweeping board, a second guide rail and a sliding block, an adjusting mechanism is fixedly installed on the top end face of the sweeping board, and a fastening mechanism is fixedly installed on the top end face of the adjusting mechanism. When the cabin cover is transported, firstly, the position and orientation of a belt outlet are adjusted through a rotating piece and a mounting sleeve, a fastening belt on the side face of a sleeve is pulled out, the fastening belt crosses over the cabin cover and is fixed to a connecting rod, a shifting rod is shifted to limit the rotating direction of a ratchet wheel, a servo motor is started, the connecting rod is driven to rotate, and the fastening belt is wound on the side face of the connecting rod; after fastening is completed, a servo motor stops rotating, then a poking rod is poked to drive a poking block to deflect, a second clamping block is pushed to move and is matched with a reset spring to abut against a ratchet wheel, a connecting rod is prevented from rotating reversely after power is lost, the stability of the cabin cover can be improved, and the cabin cover can be prevented from being protected when the device is used; and the practicability of the device and the convenience of fixing the cabin cover are improved.