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58 results about "Aerodynamic torque" patented technology

Aerodynamic torque is caused when non-uniform static pressure distribution from fluid flows past the ball. Dynamic torque study. MOGAS is investigating the impact of aerodynamic torque on an overall torque curve, with a goal to customize the torque curve to suit the user’s specific flow conditions.

Stator blade mounting structure

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.
Owner:INST OF ENGINEERING THERMOPHYSICS - CHINESE ACAD OF SCI

Torque ripple suppression method for direct-drive wind turbine generator

The invention provides a torque ripple suppression method for a direct-drive wind turbine generator, and relates to the technical field of wind power generation. The method comprises: for electromagnetic torque pulsation, using a harmonic voltage compensation suppression method: using a low-pass filter to extract a higher harmonic current component, calculating and superposing a harmonic voltage compensation value to a reference voltage, and the harmonic component being offset; for aerodynamic torque pulsation, using an independent variable pitch control method, establishing a weight coefficient distributor, calculating pitch angles corresponding to different blades through a mathematical model of weight coefficient distribution and acting on a variable pitch mechanism, and aerodynamic torque pulsation caused by pitch angle pulsation being reduced; and finally, on the basis of a harmonic voltage compensation method, arranging a rotating speed controller, the difference value between the actual rotating speed and the rated rotating speed of a generator serving as a deviation value and being introduced into the input end of the rotating speed controller, the output end of the rotating speed controller being a unified pitch angle reference value, and then achieving the cooperative suppression of pneumatic torque pulsation and electromagnetic torque pulsation in combination with anindependent variable pitch control method.
Owner:SHENYANG POLYTECHNIC UNIV

Detection equipment and detection method for torque spanners

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.
Owner:中国测试技术研究院力学研究所

Aircraft attitude control method and system under high-altitude condition based on numerical simulation

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.
Owner:CALCULATION AERODYNAMICS INST CHINA AERODYNAMICS RES & DEV CENT

UAV(unmanned aerial vehicle) stability augmentation control method and device and UAV

The invention discloses an UAV(unmanned aerial vehicle) stability augmentation control method and device. A control module obtains a current disturbance moment of an UAV platform, determines precession angle velocity of a gyro device needing for suppressing disturbance according to the current disturbance moment and generates a driving instruction for driving the gyro device to generate a corresponding control moment, and sends the driving instruction to a servo-driven module; and the servo-driven module receives the driving instruction, drives the gyro device to deflect to provide the corresponding control moment so as to suppress the interference of the current transient disturbance on UAV attitudes. The control method and device can increase additional mechanical torque control quantityunder the condition of not changing an original aerodynamic moment control structure, and quickly provide the control moment which is far greater than that capable of being provided by the aerodynamic torque of an UAV body, thereby solving the problem of easy instability of the UAV when the UAV is subjected to the impact load, and greatly improving disturbance resistance and impact resistance capability of the UAV. Besides, the invention also provides the UAV having the technical advantages above.
Owner:COOL HIGH TECH BEIJING CO LTD +1

Aircraft aerodynamic parameter identification method based on recurrent neural network

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.
Owner:NANJING UNIV OF AERONAUTICS & ASTRONAUTICS

Device for testing pneumatic performance of automobile

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.
Owner:ZHEJIANG UNIV

Method for simulating dynamic characteristics of wind turbine system

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.
Owner:NANJING UNIV OF POSTS & TELECOMM

Composite material adjustable stator blade

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.
Owner:AECC SHENYANG ENGINE RES INST

Aircraft attitude control method and device and electronic equipment

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.
Owner:BEIJING INSTITUTE OF TECHNOLOGYGY

System and method for measuring aerodynamic torque in wind tunnel test of aircraft

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.
Owner:XIAN AEROSPACE PROPULSION TESTING TECHN INST
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