7 results about "Pitch rate" patented technology

The present invention provides a method and device for identifying and analyzing a pilot's landing ability, and belongs to the field of aviation safety and safety management. The method comprises: obtaining flight data before the aircraft lands; processing the pitch rate in the flight data by a pitch rate sequence change point detection algorithm to obtain the peaks and troughs of the pitch rate; and determining the dynamic behavior of the aircraft when approaching the ground according to the peaks and troughs of the pitch rate. The present invention proposes for the first time a pilot landing ability identification system based on a combination of change point detection and pattern recognition with data drive, which has broad application prospects and significant practical value.

The invention relates to control of a wind turbine during a stopping process, wherein a stopping controller is used to pitch the blades at a plurality of preset pitch rates including a first pitch rate and a second pitch rate. The stopping controller is arranged to obtain a desired pitch angle for the stopping process and to add an envelope band to the desired pitch angle. During the stopping process, pitching is performed at a pitch rate selected from the plurality of preset pitch rates, and the pitch rate is varied according to a criterion to keep the pitch value within the envelope band.

The subject of the present invention is "System and method for protecting a wind turbine from overload due to a pitch system fault". A method for protecting a wind turbine from overload caused by a fault during operation includes receiving, by means of a controller, a plurality of pitch signals from a plurality of pitch control mechanisms of a pitch system of the wind turbine, the pitch system being configured to rotate a plurality of rotor blades mounted to a rotatable hub of a rotor of the wind turbine about respective pitch axes. In addition, the method includes determining a common pitch rate of the pitch system as a function of the plurality of pitch signals. The method also includes defining a minimum pitch rate threshold value that varies with a speed parameter of the wind turbine. In addition, the method includes receiving a first speed parameter of the wind turbine. In addition, the method includes comparing the common pitch rate with a minimum pitch rate threshold value for the first speed parameter. Thus, the method includes controlling the wind turbine based on the comparison.

This invention constructs a sliding mode surface by superimposing the pitch angle error signal, the pitch rate signal, and the nonlinear piecewise integral signal of the error. A second-order nonlinear error coupling filter is then designed to obtain the first-order and second-order output signals of the sliding mode filter. These are then superimposed through error coupling to obtain a hybrid differential signal of the second-order sliding mode surface. By superimposing equivalent control terms and adaptive disturbance estimation terms, the desired value of the main motor armature voltage is calculated using second-order sliding mode control. Then, using an inversion design approach, the desired armature voltage rate signal is gradually obtained by integrating the piecewise coupled pitch angle error signal. Finally, the helicopter pitch control signal is obtained through equivalent voltage and error feedback and inversion calculation, and then sent to the main motor, thus realizing attitude tracking control of the helicopter pitch channel.

Flight control systems, flight control laws, and aircraft are provided. An flight control system includes an input configured to receive a pitch rate command, a processor operative to receive the pitch angle command, to calculate a pitch angle saturation limit, to compare the sum of the pitch rate command, the scaled pitch rate, and the scaled pitch angle to the pitch angle saturation limit, to convert the pitch rate command system to the pitch angle command system in response to the sum exceeding the pitch angle saturation limit value to limit the pilot pitch-up pitch rate command , and to couple the pitch rate command to an aircraft control surface for the failure case of one of control surface, and the aircraft control surface configured to adjust an aircraft control surface setting in response to the pitch rate command and / or pitch angle command to protect an aircraft from being in stall condition.

A flight control system, flight control rules, and an aircraft are provided. A flight control system includes an input device configured to receive a pitch rate command, a processor operable to receive a pitch angle command, calculate a pitch angle saturation limit, compare a sum of the pitch rate command, a scaled pitch rate, and a scaled pitch angle to the pitch angle saturation limit, convert the pitch rate command system to a pitch angle command system to limit a pilot's pitch up pitch rate command in response to the sum exceeding the pitch angle saturation limit value, and couple the pitch rate command to an aircraft control surface for a failure condition of one of the control surfaces, and the aircraft control surface is configured to adjust the aircraft control surface setting in response to the pitch rate command and / or the pitch angle command to protect the aircraft from a stall condition.

The invention discloses a wind turbine generator control method and system based on dynamic independent variable pitch gain adjustment. The method comprises the steps that S1, operation data of a wind turbine generator are monitored in real time; s2, calculating a generator rotating speed error, a generator rotating speed change rate, a wind speed change rate and a wind direction change rate according to the operation data; s3, judging whether gust working conditions are met or not, and if all gust working conditions are met, setting a gust control trigger flag bit as TRUE; s4, when the trigger flag bit is TRUE, obtaining an independent variable-pitch proportional gain Kp scheduling coefficient according to the product of the rotating speed error and the rotating speed change rate, and finally obtaining an independent variable-pitch additional variable-pitch rate; and S5, outputting a step variable pitch rate signal according to the trigger flag bit, and superposing the independent variable pitch additional variable pitch rate to obtain a comprehensive variable pitch rate instruction so as to execute a variable pitch action. The method has the advantages of cost reduction, efficiency improvement, reliability improvement and the like.