58 results about "Aerodynamic torque" patented technology

The invention discloses a dynamic torque detection system, comprising a bench and a torque sensor; an electrical-pneumatic torque wrench is fixedly mounted on the bench; one end of the torque sensor is connected with an output shaft of the electrical-pneumatic torque wrench; the other end of the torque sensor is connected with a sleeve through a coupling; the sleeve is rotationally fixed on the bench and is connected with a torque brake device that may provide continuous braking for torque. By providing the torque brake device that may provide continuous braking for torque to detect a torque peak, measurement precision is improved; the torque brake device is arranged as a bolt, continuous braking is achieved by tightening the bolt; compared with simulated bolts, the dynamic torque detection system as a calibrator allows an actually used bolt to be sued in the detection process, and the actual condition can be simulated to maximum extent.

A method and a power tool system are provided for performing screw joint tightening using a pneumatic torque impulse power tool that is controlled by a control unit. A torque magnitude and a torque growth are calculated based on signals delivered by an angle sensor, and pressurized air is supplied to the power tool via a flow regulating valve which is successively adjustable between zero and full power flow. The flow regulating valve is controlled by the control unit to deliver a reduced power air flow to the power tool before and during a first delivered impulse, and then to deliver full power flow until a certain torque magnitude or a percentage of a target torque level is reached, whereafter the air supply flow is again reduced until the target torque level is reached, and when the target torque level is reached the air flow is shut off.

The invention relates to a stator blade mounting structure which can be applied to the fields of ground gas turbines, aero-engines and the like. The stator blade mounting structure comprises stator blades with a pressing plate, inner and outer ring light elastic parts, inner and outer ring casings and an outer ring pressing hoop. Through the parts, the single blade dismantling function of the stator blades can be achieved. As the light elastic parts are adopted, assembling and positioning of the whole-ring stator blades are achieved through the cold-state interference magnitude of the light elastic parts and the inner and outer ring blade profiles of the blades. Under an assembly state, the stator blade mounting structure has certain rigidity and can transfer aerodynamic torque of the stator blades to the corresponding position of a casing mounting edge. By means of the structure, the weight of the ground gas turbines and the aero-engines can be remarkably reduced. The maintainabilityof the stator blades is improved while the machining difficulty of the stator blades is lowered, and the single blade dismantling function of the blades is achieved. Through the structure, under the excitation action force of mainstream unsteady airflow in a channel, the risk of self-excited vibration of the stator blades can be reduced.

A system for controlling a wind turbine generator includes a rotor blade assembly having rotor blades and a pitch actuator to control a pitch of the rotor blades, a gear box coupled to the rotor blade assembly, a power generator coupled to the gear box, and a main controller. The main controller is configured to control the aerodynamic torque applied on the rotor blades based on pitch control commands, and separately configured to control a generator speed of the power generator based on torque control commands. The system further includes a pitch controller configured to receive pitch calculation information from the main controller, calculate the pitch control commands, and return the pitch control commands to the main controller. The system further includes a torque controller configured to receive torque calculation information from the main controller, calculate the torque control commands, and return torque control commands to the main controller.

A method is disclosed for controlling a wind turbine by optimizing its production while minimizing the mechanical impact on the transmission. The wind turbine comprises a nacelle provided with a rotor on which blades are fastened, and an electrical machine linked to the rotor by a transmission, in which an pitch angle of the blades is controlled, comprising: An aerodynamic torque setpoint and an electrical machine torque setpoint making possible maximizing the recovered power are determined, from measurements of wind speed, of rotor speed and of electric machine speed. At least one of the setpoints is modified by subtracting from it a term proportional to a difference between the measured speed of the rotor and the measured speed of the electric machine. A pitch angle of the blades making possible production of the aerodynamic torque setpoint is determined. The blades are oriented according to the angle of inclination.

The invention discloses a hovering type miniature bionic double-flapping-wing flying robot which is composed of flapping mechanisms, a control mechanism and a power supply and control system, wherein the flapping mechanisms and the control mechanism are arranged on the two sides of a main machine frame. The flapping mechanism can rotate around the connecting shaft, power is output through the hollow cup motor, flapping motion of the bionic wings is achieved, then aerodynamic force and aerodynamic torque (rolling torque) are generated, when the bionic wings move, high lift force is generated through a clap-fling mechanism similar to insect flapping, and high aerodynamic efficiency is achieved. The control mechanism drives the whole flapping mechanism rack to rotate by virtue of a linear steering engine, so that the flapping plane of the bionic wing is changed, the aerodynamic force/moment direction is changed, and pitching and yawing torques are generated; The power supply and control system is realized by a control circuit board, and the whole system is powered by a battery. The parts are made of carbon fiber plates or 3D printing materials, so that the robot is light and small, the flight efficiency is improved, and the robot has ultrahigh maneuverability.

The invention discloses a detection technology for torque spanners. Detection equipment for the torque spanners comprises a rack, a dynamic torque sensor and a bolt clamping part, wherein one end of arotary shaft of the dynamic torque sensor is used for installing the torque spanner, and the other end of the rotary shaft of the dynamic torque sensor is connected with the bolt clamping part; the rack is provided with a positioning bracket for installing the dynamic torque sensor; a shell of the dynamic torque sensor is arranged on the positioning bracket in a supporting manner, so that a rotary shaft of the dynamic torque sensor can rotate along the torque spanners. According to the detection equipment disclosed by the invention, the dynamic torque sensor is adopted, the rotary shaft of the dynamic torque sensor rotates along the torque spanners, so that no impact is caused to the torque sensor, the actual state when a bolt is screwed can be simulated, the torque in the screwing process of the bolt can be dynamically detected, and the detection equipment can be used for verification, calibration and test of electric and pneumatic torque spanners; the sampling frequency is very high; an instantaneous peak value output by the detected torque spanners can be acquired, so that higher measurement accuracy can be guaranteed.

The invention discloses an aircraft attitude control method and system under a high-altitude condition based on numerical simulation, and relates to the field of aircraft control, and the method comprises the steps: obtaining the shape information of an aircraft and N calculation states related to the aircraft, and obtaining a physical space grid of the aircraft; constructing a first flow field based on the incoming flow condition, and calculating the calculation state 1 based on the first flow field and the physical space grid to obtain a corresponding aerodynamic coefficient or aerodynamic torque coefficient; according to the sequence of the calculation states, calculating the calculation state 2 to the calculation state N in sequence to obtain corresponding aerodynamic coefficients or aerodynamic moment coefficients, and based on the aerodynamic coefficients or aerodynamic moment coefficients corresponding to all the calculation states, obtaining aircraft aerodynamic or aerodynamic moment static derivatives under corresponding aircraft heights and flight Mach numbers; the aircraft control system performs real-time control on the aircraft attitude based on the aircraft aerodynamic force or aerodynamic moment static derivative. According to the method, the calculation cost of numerical simulation in aircraft attitude control is reduced.

The invention discloses a laser radar auxiliary control method based on impeller equivalent wind speed correction. The method comprises the following steps of reconstructing wind wheel surface aerodynamic torque of a wind generating set based on a luenberger observer; calculating current wind wheel surface equivalent wind speed of the wind generating set based on a newton method; calculating feedforward equivalent wind speed based on airborne laser radar; correcting laser radar feedforward equivalent wind speed time lag sequence; correcting laser radar feedforward equivalent wind speed numbersequence; and carrying out laser radar auxiliary control by using a laser radar auxiliary controller. The method has the following beneficial effects that the number deviation between the feedforwardequivalent wind speed provided by the airborne laser radar and the actual equivalent wind speed of a wind wheel of the wind generating set can be reduced, the actual time precision of the wind wheel of the wind generating set is improved, and the radar auxiliary control effect is improved.

The invention discloses an aircraft aerodynamic parameter identification method based on a recurrent neural network. The method comprises the following steps: 1) performing a simulated flight test by using a training-level simulator in combination with flight simulation software to obtain flight data; 2) taking the six-degree-of-freedom dynamic equation set of the aircraft rigid body as a state equation of the system, and calculating to obtain corresponding aerodynamic force and aerodynamic torque according to data obtained by the test; 3) taking flight data such as an attack angle and a sideslip angle as input, taking the aerodynamic parameters calculated in the step 2 as reference data, and training by utilizing a recurrent neural network combined with a real-time recurrent learning algorithm to obtain an aerodynamic parameter identification model; 4, selecting and loading flight data which do not participate in model training into the aerodynamic parameter identification model of the recurrent neural network obtained in the third step for parameter identification, and corresponding aerodynamic force and aerodynamic moment. The parameter identification model established through the method has good applicability, accurate modeling can be completed for aerodynamic force, and application and popularization can be achieved.

The invention discloses a device for testing the pneumatic performance of an automobile. The device is used for testing the pneumatic performance of the automobile. According to the technical scheme of the invention, each tray of the device is provided with a wheel fixing assembly and the lower surface of each tray is fixedly connected with a supporting rod. The lower end of the supporting rod is fixedly connected with a force measuring balance and the force measuring balance is arranged on a force measuring balance installation frame. The force measuring balance installation frame is fixedly installed in a carrying device. An ultrasonic anemometer is installed on the roof of a testing automobile, and is used for measuring the wind speed. The ultrasonic anemometer and the force measuring balance are both connected with a controller. An automobile speed detection device on the carrying device is connected with the controller. According to the technical scheme of the invention, the device can be used for testing the pneumatic performance of the automobile directly on the road and can simulate an acting force and an acting torque basically similar to the acting force and the acting torque of the automobile when the automobile runs normally on the road. Therefore, compared with an automobile air tunnel, measured experimental data are closer to the aerodynamic force and the aerodynamic torque of the automobile during the actual running process.

The invention relates to a butterfly valve (24) for bleeding a compressor for an aircraft turbine engine, the valve including a valve body (32), a butterfly (36), and a device (42) for controlling the angular position of the butterfly, the device (42) including a mobile actuation member (64) connected to the butterfly by a link (70), the member (64) being subjected: to a first adjustable pressure force (F1) applied by air from the compressor, the first force (F1) returning the butterfly (36) to a closed position; and to a second mechanical force (F2) returning the butterfly (36) to an open position, and coming from an aerodynamic torque (C) applied by the air to the butterfly (36), of which the axis of rotation (38) is off-centre relative to the butterfly.

The invention provides a load shedding control method for a wind generating set, and the method is characterized in that the rotating speed and the rotating acceleration of a generator are monitored simultaneously, when the rotating speed is determined to be greater than a preset first rotating speed and the acceleration is greater than a preset first acceleration, or the rotating speed is determined to be greater than a preset second rotating speed and the acceleration is determined to be greater than a preset second acceleration, the stage of periodically setting a target rotating speed is entered, and the rotating speed of the generator is adjusted through a variable pitch system based on the target rotating speed. Since the running state of the generator is monitored based on the rotating speed and the rotating acceleration of the generator, the rotating speed of the generator can be controlled more stably under the working condition of high rotating speed and high acceleration, and the phenomena that the rotating speed is overhigh and the machine is shut down due to overhigh pneumatic torque and the parts of the wind generating set are damaged are avoided.

The invention discloses a method for simulating dynamic characteristics of a wind turbine system. The method comprises the following steps: (1) establishing time domain motion equations of an actual wind turbine system and a wind turbine simulation system; (2) simultaneously establishing a motion equation of the wind turbine system and the simulation system to obtain a simulation motor electromagnetic torque; (3) substituting the generator electromagnetic torque at the previous moment into a simulated motor electromagnetic torque calculation formula to obtain a simulated motor electromagnetictorque value at the current moment; and (4) carrying out torque closed-loop control on the simulation system according to the torque reference value of the simulation motor, so that the output torqueof the simulation motor follows a given value, and the simulation of the mechanical characteristics of the actual wind turbine system is completed. Compared with a traditional wind turbine simulationsystem, one-step delay introduced by an acceleration term can be eliminated, the dynamic characteristics of the wind turbine can be more accurately reproduced, and meanwhile the influence of sudden change of the aerodynamic torque of the wind turbine on the torque of the simulation motor can be reduced.

The invention belongs to the technical field of engine maintenance equipment design, and particularly relates to a composite material adjustable stator blade which comprises an upper shaft neck, a lower shaft neck, an upper marginal plate, a lower marginal plate, and a blade body; besides, the blade is divided into a central layer plate area, a central filling area, a reinforced layer plate area and a molded surface structure area, the central layer plate area and the reinforced layer plate area are composed of laminated plates formed by laying composite material prepregs, the central fillingarea is composed of composite material prepregs, and the molded surface structure area is composed of resin or single-layer prepregs covering the surface of the molded surface structure area; and thecentral layer plate area and the central filling area form a core bearing area of the blade, the reinforced layer plate area is located on the two sides of the core bearing area, and the molded surface structure area is used for ensuring that the composite material adjustable stator blade is smooth in appearance. According to the composite material adjustable stator blade, the design feasibility and engineering problems of the composite material adjustable stator blade are effectively solved, the problems that the blade configuration is complex, and layering is difficult to achieve are effectively solved, and the pneumatic bending moment and pneumatic torque resistance of the composite material adjustable stator blade is improved.

The invention provides an aircraft attitude control method and device and electronic equipment, and the method comprises the steps: determining a state feedback control law mathematical model based on a first attitude control mathematical model represented according to a preset format in a pre-obtained nonlinear mathematical model; determining an attitude controller mathematical model containing a fractional order differential item by adopting a sliding mode control mode based on a pre-obtained sliding mode surface control mathematical model; substituting attitude controller parameter items in the state feedback control law mathematical model, and determining an aerodynamic torque coefficient based on a pre-acquired system control quantity mathematical model and a current state value of the aircraft; calculating a rudder deflection control instruction based on the aerodynamic torque coefficient; and controlling the attitude of the aircraft based on the rudder deflection control instruction. The attitude controller mathematical model determined by the method comprises a fractional order differential item, so that the rudder can provide a large control quantity at the beginning, the rapidity and accuracy of an aircraft attitude control system are improved, and the convergence time of the aircraft attitude is shortened.

The invention discloses an aircraft attitude control method and an aircraft, and the control method comprises the steps: monitoring the pressure of pressure measurement points in real time through a plurality of pressure measurement points arranged on the aircraft; predicting flight parameters of the aircraft based on a flight parameter model and the real-time pressure of the pressure measuring point; predicting aerodynamic force and aerodynamic moment of the aircraft based on an aerodynamic force prediction model and the aircraft flight parameters; based on the aerodynamic torque, a layout scheme for generating protrusions on the surface of the aircraft is given through a protrusion position prediction model; the moment increment generated by the generated bulge meets the balancing requirement of the aircraft, and the aerodynamic force increment generated by the bulge is minimum; and forming corresponding bulges on the surface of the aircraft according to the layout scheme of the bulges so as to adjust the attitude of the aircraft. The attitude of the aircraft can be well controlled, the stealth performance of the aircraft is improved, and the influence on the aerodynamic performance is small.

The invention provides a system and a method for measuring the aerodynamic torque in a wind tunnel test of an aircraft, and solves the problem that in an existing ground wind tunnel test, the frictional resistance characteristic of measurement equipment affects the free rolling speed rate of the aircraft. The system comprises a rotating speed measuring device, a torque sensor and a motor. The rotating speed measuring device comprises a rotating shaft mechanism and a rotating speed sensor. The rotating shaft mechanism comprises a rotating shaft mounting seat and a rotating shaft, the rotating shaft penetrates the rotating shaft mounting seat through a bearing, and the front end of the rotating shaft extends out of the rotating shaft mounting seat and is coaxially connected with a test piece; the rotating speed sensor comprises a gear coaxially arranged on the rotating shaft and a proximity switch arranged in the mounting seat and matched with the gear, and the proximity switch measures the number of teeth passed by the gear to obtain the rotating speed of the rotating shaft. The torque sensor and the motor are sequentially and coaxially arranged at the rear end of the rotating shaft, the torque sensor is close to the rotating shaft, and the motor is used for driving the rotating shaft to rotate.