58 results about "Aerodynamic torque" patented technology

The invention provides a non-linear flight control method and system for an anti-wind disturbance unmanned aerial vehicle. The method comprises the following steps: acquiring wind field disturbance characteristics in real time by using a preset meteorological radar; inputting the wind field disturbance characteristics into a preset aerodynamic disturbance prediction model to generate an aerodynamic torque fluctuation prediction value; preset dynamic filtering processing is applied to the amplitude characteristic of the aerodynamic torque fluctuation predicted value so as to generate a control instruction correction signal; and the control instruction correction signal is coupled with a preset nonlinear control law of an unmanned aerial vehicle flight control system, so that unmanned aerial vehicle attitude offset caused by wind disturbance is inhibited in real time, and unmanned aerial vehicle nonlinear flight control is carried out. According to the method, the composite defect of hysteresis and filtering mismatch of traditional linear control in a strong wind sudden change scene is overcome, stable attitude control of the unmanned aerial vehicle in low-altitude wind shear and gust sudden attack is realized, the anti-interference response speed of the unmanned aerial vehicle is remarkably improved, and the out-of-control risk of the unmanned aerial vehicle is greatly reduced.

The invention provides a rotating speed determination method in aero-engine complete machine three-dimensional simulation, and belongs to the technical field of aero-engine simulation, and the method specifically comprises the steps: constructing a fluid-structure interaction control equation on each grid unit of an aero-engine complete machine geometric model; forming an integral coupling matrix, and solving the integral coupling matrix; simulating the calculated thermal state geometric model; the gas compressor and the turbine can only rotate around the rotating shaft; calculating aerodynamic forces acting on the compressor blades and the turbine blades; in each time step, the rotating speed is updated according to the angular acceleration; and after a plurality of iterations, when the difference value of the aerodynamic torque borne by the gas compressor and the aerodynamic torque borne by the turbine accords with a preset range, the corresponding rotating speed is the steady-state working rotating speed of the engine under the thermal state geometry. According to the processing scheme, the engine can automatically match and dynamically determine the working rotating speed in the simulation process, the inaccuracy of the preset rotating speed is avoided, and the precision and reliability of a simulation result are improved.

The invention relates to a stress calculation method, device, equipment and medium for a floating type draught fan foundation structure, and the method comprises the steps: carrying out the frequency domain potential flow water power analysis of a wet surface element model of a foundation floating body of a floating type draught fan, and obtaining the water power pressure distribution and a water power coefficient; boundary conditions are applied to the simulation model of the floating type wind turbine foundation structure, various working conditions are loaded, finite element analysis is carried out based on hydrodynamic pressure distribution, and various structural stress transfer functions are obtained; based on the hydrodynamic coefficient, performing linear processing on the fan aerodynamic force, the impeller pneumatic torque, the floating body hydrodynamic force and the mooring restoring force of the floating fan and the influence of a fan servo controller on the floating fan, and substituting a linearization result into a motion equation of the floating fan for calculation to obtain a plurality of dynamic response spectrums; and multiplying the structural stress transfer functions by the corresponding dynamic response spectrums, and adding a plurality of multiplied results to obtain a total stress spectrum. The method can improve the efficiency.

The invention discloses a fan mechanism modeling and optimizing method and system based on a neural network, and the method comprises the steps: building a model of a wind energy utilization coefficient and a thrust coefficient of a fan, and carrying out the steady-state simulation, so as to obtain a two-dimensional relation table model of the wind energy utilization coefficient and the thrust coefficient, establishing a fan aerodynamic model based on the two-dimensional relation table model; respectively establishing a fan transmission chain system model and a fan blade and tower coupling model based on the nonlinear pneumatic torque Tr and the nonlinear air thrust Ft in the fan aerodynamic model to obtain a complete fan mechanism model; and collecting actual operation data of the fan, analyzing the deviation between the fan mechanism model and the actual operation data of the fan based on the neural network, and correcting the deviation through the neural network to obtain an optimized fan mechanism model. According to the invention, the precision of fan modeling can be improved.

The invention discloses a parachute flight performance prediction method based on follow-up coupling flow field analysis, and the method is suitable for a parafoil and a traditional round parachute. Parachute flight flow field aerodynamic characteristics and flight dynamic characteristics are coupled by using a body-attached dynamic grid and a self-adaptive flow field boundary technology, real-time changes of a parachute streaming flow field along with body motion are accurately reflected, and the attitude, the speed and the flight trajectory of the parachute are automatically solved and obtained. According to the method, on one hand, real-time aerodynamic characteristics and motion characteristics of the parafoil are coupled, the coupling influence of flight attitude speed change on aerodynamic force and aerodynamic torque of the parafoil is reflected, and the calculation precision is guaranteed; and meanwhile, the change of the streaming flow field of the parachute system is decoupled into the change of the relative incoming flow and the change of the posture, so that the redundancy of flow field grids and the complex grid reconstruction are avoided, and the simulation calculation efficiency is improved.

The invention discloses an active control method and system for suppressing torsional vibration of a permanent magnet synchronous wind driven generator, and the method comprises the steps: building a dual mass-rigidity-damping model through a lumped mass method based on transmission chain parameters and pneumatic torque, and obtaining a transmission chain dynamic equation; performing torsional vibration characteristic analysis on the natural wind speed, the pneumatic torque and the transmission chain dynamic equation to obtain a torsion angle, an eigenfrequency, a damping ratio equation and electromagnetic torque influence evaluation; and controller design is carried out on the torsional vibration mathematical model and the active disturbance rejection controller parameters to obtain an electromagnetic torque compensation amount, and active suppression of torsional vibration is realized. According to the invention, through cooperation of a physical model and intelligent control, a sensing-analysis-compensation closed loop is formed; a high-precision mathematical model is constructed, and a wind-machine-electricity coupling effect is captured; the ADRC regards unknown parameters and external disturbance as total disturbance, real-time estimation and compensation are carried out through a tracking differentiator, and an accurate system model is not needed; torsional vibration is restrained, and adaptability is enhanced.

The application provides a wind turbine maximum wind energy capturing control method, device and system, the method comprising: obtaining a generator speed and a low-speed shaft torsion angle; calculating optimal torque of the generator at different speeds according to the generator speed and an optimal wind energy proportionality coefficient; calculating an impeller aerodynamic torque according to the low-speed shaft torsion angle, a low-speed shaft torsion stiffness and a torsion damping coefficient; correcting the optimal torque to obtain a target electromagnetic torque according to the impeller aerodynamic torque; and controlling the generator to operate according to the target electromagnetic torque. In the application, the wind turbine realizes optimal adjustment of the electromagnetic torque in a low wind speed area, can effectively improve energy absorption efficiency when the wind turbine operates below the rated wind speed, improve control performance of the wind turbine, and further improve annual power generation of the wind turbine.

The present disclosure provides a wind turbine unit state evaluation method, a controller and a wind turbine unit. The state evaluation method comprises: obtaining a blade root bending moment of the wind turbine unit; obtaining an aerodynamic torque according to the blade root bending moment; obtaining an impeller absorbed power based on a product of the aerodynamic torque, an impeller rotating speed of the wind turbine unit and a predetermined blade absorbed efficiency; obtaining a first power according to a product of the impeller absorbed power and a predetermined unit efficiency; and evaluating a state of the wind turbine unit according to a product of the first power and an actual output power or a grid-connected power of the wind turbine unit. The state evaluation method according to the embodiment of the present disclosure can determine whether the unit has an abnormal state of too much energy accumulation.

The application provides a small wind turbine intelligent speed regulation control method, system and storage medium, and belongs to the field of wind turbine. The method comprises the following steps: determining the current wind condition according to the wind speed; in the case that the current wind condition is long-time strong wind condition, passive speed regulation is carried out through a passive speed regulation component to realize rapid wind avoidance; analyzing the reset torque borne by the tail rudder according to the tail rudder position; calculating the windward component of the wind wheel aerodynamic torque according to the reset torque; obtaining the variable pitch demand of the active speed regulation component according to the wind speed, the windward component of the wind wheel aerodynamic torque and the theoretical relationship curve of the pitch angle, and carrying out variable pitch until the wind turbine is in the windward state; collecting the corresponding relationship among the wind speed, the wind speed change rate, the pitch angle and the windward component of the wind wheel aerodynamic torque when the wind turbine is in the windward state, and generating an actual relationship curve of the wind speed, the wind wheel aerodynamic torque, the windward component and the pitch angle for iterating the theoretical relationship curve of the wind speed, the wind wheel aerodynamic torque, the windward component and the pitch angle.

The invention discloses a shape-preserving and resistance-reducing design method for a rotating mechanism under rotor / fuselage coupling, which comprises the following steps of: setting the slenderness ratio of a streamline shaft sleeve based on a shape resistance coefficient formula, and verifying the surface pressure distribution and the separation area of the shaft sleeve through numerical simulation to ensure that the shape resistance coefficient meets a resistance-reducing target; setting the area ratio of an outlet to an inlet of the seam based on a Venturi effect formula, so that a low-pressure area is formed in the seam to suck a wing root boundary layer and delay airflow separation; establishing an aerodynamic load and motion parameter coupling model based on an instantaneous resistance formula, analyzing flow fields under different rotation angular velocities and oblique angles through numerical simulation, and optimizing a rotation track to reduce a resistance peak value and aerodynamic torque fluctuation; the invention aims to solve the problems of airflow vortex interference, large shape resistance, high resistance peak and poor aerodynamic stability by optimizing the shape of the rotating shaft sleeve, the fuselage-wing gap structure and the wing rotating track, and improves the cruise fuel efficiency and flight stability of the aircraft.

This application discloses a simulation calculation method and system for a dual-rotor wind turbine. The method includes: calculating the target blade pitch angle and target generator torque of the front and rear wind turbines based on the basic parameters of the front and rear wind turbines, and generating control commands to control the simulation model of the dual-rotor wind turbine; calculating the blade aerodynamic forces and structural loads of the front and rear wind turbines in the simulation model based on the target blade pitch angle and target generator torque of the front and rear wind turbines; obtaining the blade aerodynamic torque of the front and rear wind turbines based on the blade aerodynamic forces, and calculating the current rotational speed of the front and rear wind turbines based on the blade aerodynamic torque, target generator torque, moment of inertia, and moment of inertia of the transmission system to update the basic parameters of the front and rear wind turbines; repeating the above operations iteratively to calculate the blade aerodynamic forces and structural loads of the front and rear wind turbines until the simulation time reaches a preset value, thus completing the time-domain simulation of the fully coupled dynamics of the dual-rotor wind turbine.

The invention relates to the technical field of wind turbine generator control, in particular to a wind turbine generator self-adaptive control method based on maximum power point tracking. The method comprises the steps of determining a pneumatic torque observation value of a wind wheel according to a filtering rotating speed and an electromagnetic torque; the torque overload rate is determined according to the difference between the observed value of the pneumatic torque and the theoretical optimal torque; determining a kinetic energy sensitivity coefficient according to the filtering rotation speed and the rated rotation speed; generating a comprehensive unloading index for triggering torque adjustment according to the torque overload rate and the kinetic energy sensitivity coefficient; according to the comprehensive unloading index, unloading processing and safe amplitude limiting are carried out on the theoretical optimal torque, and a generator torque set value is obtained; generating a torque adjusting instruction of the wind turbine generator according to the torque set value of the generator; wherein in the adjusting process, the torque adjusting instruction indicates that the maximum change rate allowed by torque decrease is larger than the maximum change rate allowed by torque increase, and therefore the adaptive capacity of the unit to the complex wind speed working condition is improved.

This application provides a cascaded extended simulation method for wind turbine drivetrains. It involves constructing a primary dynamic simulation model of the entire wind turbine and a secondary dynamic simulation model of the drivetrain multibody dynamics, including a gearbox multibody dynamics model, a coupling model, and a generator multibody dynamics model. The primary dynamic simulation model of the entire wind turbine outputs standard values ​​of the total aerodynamic torque and the generator electromagnetic torque to the secondary dynamic simulation model of the drivetrain multibody dynamics based on the input three-dimensional turbulent wind field. The gearbox multibody dynamics model outputs the vibration characteristics and load characteristics of each component within the gearbox based on the total aerodynamic torque and the generator electromagnetic torque. The generator multibody dynamics model outputs the actual value of the generator electromagnetic torque based on the standard value of the generator electromagnetic torque and the generator rotor angular velocity. This method improves the simulation performance of both the gearbox and generator multibody dynamics models.

The application relates to the field of wind power generation technology and discloses a bionic vertical shaft wind driven generator and a control system thereof, which comprises a base, the top of the base is rotationally connected with a central support shaft, the outer wall of an upper fixing ring is uniformly fixedly connected with support rods, the outer wall of a lower fixing ring is uniformly fixedly connected with connecting rods, one end of the support rods and the connecting rods is fixedly connected with blades in cooperation, the blades are continuous spiral curved surface structures spirally rising around the central support shaft, the blades are made of light high-strength composite materials, and the blades adopt airfoil cross sections and taper from roots to tops. Natural wind blows towards the blades, the blades adopt a bionic golden spiral continuous curved surface structure simulating the nautilus shell, can generate aerodynamic torque under most wind directions, can make airflow smoothly transition, can effectively capture wind energy under most wind directions, and the blades are made of light high-strength composite materials, so that the wind resistance of the blades in a strong wind environment is enhanced.

The application discloses a wind turbine dynamic model experiment platform rotational inertia compensation method based on energy flow equivalence. The application is based on the energy angle, and a rotational inertia compensation strategy based on energy flow equivalence is proposed by reproducing the energy flow direction of an actual wind turbine on a wind turbine dynamic model experiment platform. The rotational inertia of the wind turbine dynamic model experiment platform is obtained, the compensation torque is calculated directly by using the theoretical value of the aerodynamic torque and the electromagnetic torque, the aerodynamic torque instruction actually issued is calculated and corrected, the communication time delay of the driving side and the test side control loop of the wind turbine dynamic model experiment platform is obtained respectively, and finally the parameters of the time delay alignment module are determined according to the measurement results. Compared with the traditional rotational inertia compensation strategy based on the rotational speed difference, the rotational inertia compensation method provided by the application does not need to collect the transmission chain information, fundamentally eliminates the acceleration time delay, and has good stability and accuracy when simulating the wind turbine with a hundred times rotational inertia.

Disclosed inventions include:integrated pneumatic flow pressure regulator assemblies with and / or without filters and / or swivels, per FIGS. 1A, 1B, 1C, 1D, 1E, 1F, 1G, 1H, 1I, 1J, 1K, 1L, 1M and 1N for use with all of Applicant's pneumatic torque gun models;activation, or trigger, lock safety assemblies, per FIGS. 2A1, 2A2, 2B1 and 2B2, for use with all of Applicant's electric and pneumatic torque gun models;automatic torque gun shifting assemblies including:rotation speed-sensing centrifugal multi-speed automatic shifting assemblies, per FIGS. 3A, 3B and 3C, for use with all of Applicant's electric and pneumatic torque gun models;torque-sensing centrifugal multi-speed automatic shifting assemblies, per FIGS. 4A, 4B, 4C, 4D, 4E, 4F, 4G, 4H, and 4I, for use with all of Applicant's electric and pneumatic torque gun models;helical cam, or wobbling, turning force multiplication assemblies, per FIGS. 5A, 5B, 5C, 5D, 5E, 5F and 5G, for use with all of Applicant's electric and pneumatic torque gun models;pneumatic pressure release, or burst, valve assemblies, per FIGS. 6A, 6B, 6C, 6D, 6E, 6F, 6G, 6H, 6I and 6J, that allow bleeding of pressure to unstick a locked up tool for use with all of Applicant's pneumatic torque gun models;pneumatic fluid directional valve assemblies, per FIGS. 7A, 7B and 7C, for use with all of Applicant's pneumatic torque gun models;pneumatic fluid directional and activation, or trigger, lock safety valve assemblies, per FIGS. 8A and 8B, for use with all of Applicant's pneumatic torque gun models; andpneumatic tool cycle counter, or odometer, assemblies, per FIGS. 9A and 9B, that recognize tool actuations as drops in pneumatic pressure for use with all of Applicant's pneumatic torque gun models.

The invention relates to the technical field of aerodynamics, in particular to a mass center eccentricity-based spinning flyer dynamic stability quantitative analysis method. The method comprises the following steps: constructing a six-degree-of-freedom dynamic model containing a mass center eccentricity additional inertial effect; determining a test working condition, performing simulation under the test working condition, and obtaining aerodynamic torque data of the asymmetric flow field; obtaining an interpolation table for the test condition based on the asymmetric flow field aerodynamic torque data; carrying out coupling simulation based on the six-degree-of-freedom kinetic model and the interpolation table of the test working conditions, and outputting state parameters of the spinning flyer; and quantitative indexes are extracted based on the state parameters of the spinning flyer. According to the method, dynamic simulation can be realized through interpolation coupling, the stability rule of the spinning flyer is quantified according to mechanisms, and quantitative analysis is effectively and accurately performed on the dynamic stability of the spinning flyer.

The invention discloses a fan variable pitch control method based on wind speed feedforward and ESO observer compensation. According to the method, the problem that the actual wind speed is difficult to predict is considered, optimal estimation is carried out on the pneumatic torque of the wind wheel through the Kalman filter, and recursive estimation of the wind speed is achieved based on the physical relation between the torque and the wind speed. The feedforward control law is optimized according to the wind speed, and the influence of turbulent wind on the fan performance is reduced; meanwhile, a nonlinear control controller is designed, and the influence of parameter uncertainty and external disturbance existing in the controller is eliminated by using a cascade ESO. Compared with a traditional control method, the method can better stabilize the generation power of the wind turbine unit at the time-varying wind speed, and has better dynamic performance.

The present application relates to the technical field of wind power generation control, in particular to an event-triggered wind turbine sliding mode control method and system based on data driving, which calculates the error by real-time acquisition of actual and expected aerodynamic torque of the wind turbine, quantifies the error by a quantizer and restricts it to a preset range by a prescribed performance function, constructs a sliding surface function and a torque controller based on the equivalent error to generate a control signal, screens the control signal by an event-triggered mechanism, and iteratively optimizes until the error converges or the preset time is reached to maximize the power generation efficiency. This method has strong robustness under wind speed gradual change / mutation conditions, reduces communication volume through quantization and event-triggered mechanism, and achieves the collaborative optimization of power generation efficiency and communication energy consumption.

The present invention relates to the field of aircraft control technology. The present invention provides a method, system, and storage medium for adaptive attitude control of a cross-domain, variable-configuration, high-speed aircraft based on neural network identification. The method addresses the problem that existing methods require unified parameterized modeling of the aircraft's aerodynamics and identification of the parameters in advance. This method fails to address the attitude control challenges posed by aerodynamic uncertainty when the aerodynamic parameter model of the cross-domain, variable-configuration, high-speed aircraft is completely unknown. The present invention constructs a three-channel neural network model, including a pitch channel neural network model, a yaw channel neural network model, and a roll channel neural network model. A loss function is constructed based on the weighted sensitivity of the influence of rudder error on attitude changes, and a three-channel rudder error solver neural network model is trained. An online transfer learning sample library is constructed for online transfer learning, and a backstepping controller is used to solve the aerodynamic torque, ultimately solving for the yaw command.

The invention discloses a simulation test method and system for inertia and frequency coupling of a transmission chain of a wind turbine generator, and the method comprises the steps: building a virtual spring-damping system to form a wind wheel inertia and frequency coupling simulation feedback loop, and reproducing the first-order inherent frequency of the transmission chain; an auxiliary state feedback controller is built to form a test platform inertia and frequency coupling simulation feedback loop, and second-order inherent frequency is reproduced; driving motor input torque is obtained through simulation, so that a transfer function from the pneumatic torque to the rotating speed of the generator is equal to the transfer characteristic of an actual wind turbine generator, and generator torque is obtained; constructing a rotational inertia model, and outputting actual generator torque and rotating speed; constructing a torsional rigidity shaft connection model of a driving motor-an elastic flange-a tested wind turbine generator, calculating a simulation feedback ring by applying a second-order inherent frequency, and adjusting to realize a first-order inherent frequency of the generator; the unit maintains the required rotating speed, and the torque and rotating speed of the pneumatic torque output generator are adjusted. The natural frequency reproduction effect of the coupling mode of the wind wheel and the transmission chain is improved.

The invention provides a coupled six-degree-of-freedom elastic aircraft flight simulation method. The method comprises the following steps: step 1, modeling a kinematic equation of an aircraft; 2, according to the virtual work principle, modeling is conducted on a kinetic equation of the aircraft on the basis of the kinematic equation; 3, performing elastic correction on the airflow angle of the aircraft, and calculating aerodynamic force borne by the aircraft and corresponding aerodynamic torque according to the airflow angle subjected to elastic correction; calculating an external force, an elastic deformation generalized force and a moment borne by the aircraft; 4, substituting the external force, the torque and the elastic deformation generalized force borne by the aircraft into the kinetic equation in the step 2 to obtain a kinetic equation after elastic correction of the aircraft, and calculating flight parameters of the aircraft according to the kinetic equation so as to realize flight simulation of the aircraft; according to the method, flight simulation considering the aeroelastic effect and the rigid-elastic coupling effect at the same time can be achieved, and finally more accurate flight simulation is provided for the elastic aircraft.

The invention discloses a pneumatic torque measuring device and method for a swirler, and relates to the technical field of measuring tools. The device comprises a test cylinder; the bearing is arranged on the testing cylinder; the swirler is arranged in the bearing; a fixing support and a torque sensor; the torque sensor is arranged on the fixed bracket; a torque measuring cap; the torque measuring cap is arranged between the swirler and the torque sensor and is used for being in transmission connection with the swirler and the torque sensor; the wind resistance generated by the torque measuring cap is smaller than or equal to the wind resistance of the tail end of the swirler in actual use. The pneumatic torque generated by acting on the swirler through high-temperature compressed gas is directly transmitted to the torque sensor through the torque measuring cap, the torque sensor converts mechanical torque into an electric signal to be output, deviation introduced in an intermediate link can be avoided, measurement errors in a high-temperature environment can be reduced, and the measurement accuracy is improved. And the accuracy of pneumatic torque measurement of the swirler is improved.

This invention provides a method and related apparatus for assessing leading-edge erosion of wind turbine blades, belonging to the technical field of wind turbine blade reliability assessment. The method includes: acquiring meteorological data of the wind turbine to be assessed; discretizing the wind turbine blade along its spanwise direction into multiple blade element micro-segments; calculating a bidirectional coupling correction factor for each rainfall event recorded at each blade element micro-segment based on the instantaneous surface morphology of the wind turbine blade; calculating the Miner total cumulative damage variable based on this correction factor, and then calculating the aerodynamic coefficient after damage; calculating the aerodynamic torque based on the aerodynamic coefficient, and then calculating the equivalent annual power generation loss rate, ultimately determining the degree of erosion attenuation of the wind turbine. This invention quantifies the bidirectional coupling mechanism of rain and sand by introducing a liquid resistance-solid buffer attenuation factor and a solid-promoting liquid-water hammer amplification factor, and achieves phased determination of the latency period and mass loss period based on Miner linear cumulative damage, enabling efficient and accurate assessment of the time-varying impact of blade leading-edge erosion on annual power generation.

The disclosure relates to a turbine having contrarotating first and second rotors, and a method of operating such a turbine. The turbine comprises a generator having first and second generator parts. The first generator part comprises at least one electromagnet and is arranged to rotate with the first rotor. The second generator part comprises at least one electrical winding and is arranged to rotate with the second rotor. The method comprises controlling the current in the at least one electromagnet and / or the at least one electrical winding such that the difference between the aerodynamic torque acting on each of the first and second rotors is minimised.

This invention discloses a wide-range control method and device for aerodynamic torque of a multi-rotor unmanned aerial vehicle (UAV), and the UAV itself. The invention utilizes the redundant control degrees of freedom in the null space of the control matrix to optimize and adjust the control allocation. First, aerodynamic lift and aerodynamic torque control generate reference values ​​for lift current and various aerodynamic torque currents. Then, pseudo-inverse allocation is performed using the control matrix to obtain the initial pseudo-inverse q-axis current reference values ​​for each permanent magnet synchronous motor. Furthermore, redundant adjustment vectors are constructed using the null space of the control matrix, and the pseudo-inverse allocation results are corrected by solving for the optimal solution of the redundant adjustment vectors, resulting in optimized q-axis current reference values. By utilizing the redundant control degrees of freedom of the multi-rotor UAV, this invention significantly expands the adjustment range of aerodynamic torque within the same allowable current range, improving the dynamic performance of the multi-rotor UAV and increasing the safety margin.

The invention belongs to the technical field of wind power generation, and provides a method, a system and equipment for estimating the effective wind speed of a fan with an unknown Cp curve and a medium. Deducing a pneumatic torque expression based on an extended Kalman filtering algorithm; and establishing simultaneous equations of the relation function of the pneumatic torque and the wind speed and the pneumatic torque expression, and solving a wind speed estimated value by using a Newton iteration method. According to the method, a known Cp curve is not needed, calculation is fast, robustness is high, high precision can be kept even under the complex turbulence working condition, only conventional operation data are needed, and the fan control precision and the power generation efficiency are greatly improved.

The invention discloses a triggering mechanism and a powder suction device, and the triggering mechanism comprises a support which is provided with a triggering air inlet channel; the air inlet baffle is rotationally arranged on the support and can rotate back and forth between the eleventh position and the thirteenth position, and the air inlet baffle passes through the twelfth position when rotating from the eleventh position to the thirteenth position; the air inlet baffle comprises a second rotating shaft and a door plate connected to one side of the second rotating shaft; the door plate comprises a first separation part; the second rotating shaft is arranged outside the side wall of the triggering air inlet channel, one part of the door plate is arranged in the triggering air inlet channel, the other part of the door plate extends to the second rotating shaft, and when the air inlet baffle rotates between the eleventh position and the twelfth position, the first separation part is matched with the side wall of the triggering air inlet channel to block the triggering air inlet channel. By means of the arrangement, the pneumatic torque of the air inlet baffle can be increased, the air suction triggering function can be achieved conveniently, and therefore the powder can be depolymerized better, and the powder depolymerization effect and the powder emptying utilization rate are improved.

The application discloses a torsional moment load loading device for a toothed sleeve connecting structure of an aero-engine power turbine rotor, which comprises a test-bed base, a power turbine rotor test piece, a front supporting seat, a rear supporting seat, a torsional moment load loading structure, an L-shaped support, a torsional load loading threaded support, an angular limiting spline shaft adapter plate and an angular limiting spline, wherein the front supporting seat and the rear supporting seat are used for supporting the power turbine rotor test piece; the torsional moment load loading device is installed between a compressor and a turbine of the power turbine rotor test piece, the L-shaped support is used for restraining the torsional moment load loading structure; and the angular limiting spline shaft adapter plate and the angular limiting spline exert circumferential restraint on a power output shaft of the power turbine rotor. The application can exert torsional moment load on the toothed sleeve connecting structure rotor test piece, and simulate the aerodynamic torque effect of the power turbine on the rotor in a working state.