37 results about "Aerodynamic torque" patented technology

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 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 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.

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.

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 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 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.

The invention discloses a miniature solar self-sustaining electrostatic aircraft, and belongs to the technical field of miniature aircrafts. The aircraft comprises a stator part, a rotor part, a solar power supply assembly and a rotor wing assembly driven by a rotor, and the rotor wing assembly is arranged below the rotor part. The core of the motor is that a damping assembly is installed on the stator component and comprises an annular support and a plurality of damping blades arranged in the circumferential direction, and the damping blades are connected with the annular support through an angle adjusting mechanism. The angle adjusting mechanism is arranged to be capable of responding to the rotating speed change of the stator component and passively adjusting the inclination angle of the damping blade, so that reverse pneumatic torque matched with the angle adjusting mechanism is dynamically provided, and rotation of the stator is restrained. Through a passive self-adaptive adjusting structure, the problem of stator instability caused by reaction torque in electrostatic driving is effectively solved, stable self-sustaining hovering of the aircraft under the natural light power supply condition is achieved, and the self-adaptive self-sustaining aircraft has the advantage of being high in self-adaption.

The invention provides a method and a device for reducing aerodynamic torque of a helicopter rotor airfoil, and the method comprises the following steps: firstly, calculating a disturbance profile coordinate by adopting a parameterized expression, and then superposing the calculated disturbance profile coordinate to an original rotor airfoil to obtain an improved airfoil aerodynamic profile and realize the reduction of the aerodynamic torque. According to the method, quantitative control over the aerodynamic configuration and the aerodynamic moment of the rotor wing type can be achieved, and multi-round iterative calculation which is serious in time consumption does not need to be carried out; main aerodynamic configuration parameters such as the maximum camber and the maximum thickness of the rotor wing type do not need to be changed, and good lift force and resistance characteristics can be maintained while the aerodynamic torque of the rotor wing type is effectively reduced.

This invention discloses an embedded conformal aerodynamic guidance system and control method for a low-spinning aircraft, belonging to the field of intelligent deformable structure design for aircraft. It includes: a navigation and attitude sensing module for acquiring navigation, attitude, and airflow attitude information of the aircraft body; a flight state calculation module for calculating the real-time flight Mach number based on navigation information; and a guidance correction decision module for determining whether safety conditions are met based on the real-time flight Mach number and whether phase synchronization conditions are met based on the roll phase angle and ideal aerodynamic torque direction angle in the attitude information. If both safety and phase synchronization conditions are met, an activation command is generated. A conformal aerodynamic actuator is used to generate local deformation in response to the activation command. The activation timing of the conformal aerodynamic actuator is precisely correlated with the roll phase of the aircraft body, activating and inflating at a specific phase to accurately correct trajectory deviations and ensure flight stability.

A dynamic torque calibration device of an electric and pneumatic torque wrench belongs to the technical field of torque measurement and is used for solving the technical problems that an existing static torque calibration device cannot adapt to dynamic torque characteristics and errors are generated due to impact and misalignment during working. The device is characterized in that a sensor fixing support, a middle support and an outer spherical bearing seat are arranged at the top of a base, a bolt-nut torque connection simulator penetrates through the outer spherical bearing seat and extends into the middle support, and one end of the bolt-nut torque connection simulator is rigidly connected with a torque sensor; the adjusting transverse plate is slidably connected to the bottom of the base through a T-shaped structure, the end of the adjusting transverse plate is provided with a supporting assembly composed of a sliding vertical plate, a supporting block and a compression spring, and the supporting block is provided with an arc-shaped hole matched with a wrench handle. The adjusting assembly comprises an adjusting lead screw and an operating block, and transverse adjustment of the supporting block is achieved through thread transmission. Belleville spring sets and conical surface clamping rings are arranged in the bolt and nut torque connection simulator, and misalignment errors are compensated through axial floating. The device realizes dynamic torque measurement through a dynamic torque sensor and a buffer structure.

A composite badminton shuttlecock and the related manufacturing processes thereof are disclosed. An example composite shuttlecock includes a base and a conical structure locked therein. The base includes a cavity, which are symmetrical about the same longitudinal axis. The conical structure extends from a locking mechanism coupled to the second end of the base using the cavity. The conical structure includes a fused multiple composite members providing an aerodynamic drag along the longitudinal axis and an aerodynamic torque about the longitudinal axis. The fused multiple composite members extend from the locking mechanism and form a reinforcement pattern with the locking mechanism. The locking mechanism includes a first arcual member and a second arcual member. The first arcual member is further from the multiple composite members and has a greater distance from the longitudinal axis than the second arcual member.

This invention discloses a fatigue testing device and method for large composite material power blades. The testing device includes: a blade to be tested, a fixing fixture, an aerodynamic / aerodynamic torque loading system, a clamping loading fixture, and a centrifugal force loading system. The blade shank and support ring are connected to the fixing fixture, and the blade body is connected to the clamping loading fixture. The clamping loading fixture is connected to both the aerodynamic / aerodynamic torque loading system and the centrifugal force loading system, with the aerodynamic / aerodynamic torque loading system perpendicular to the centrifugal force loading system, to simultaneously apply the axial centrifugal force, aerodynamic bending load, and aerodynamic torque load of the blade rotation. This invention features a compact structure, convenient operation, and high reliability. It enables the development of a fatigue load spectrum based on the blade's operating conditions, fully verifying the blade's fatigue performance and solving the problem of high-reliability verification of blade fatigue life.

The invention discloses a redundant locking folding wing, which solves the problem of possible locking failure of an existing single locking structure under dynamic conditions of high-speed unfolding, high-acceleration launching and the like by arranging redundant locking formed by a first locking assembly and a second locking assembly. The synchronous unfolding mechanism drives the at least two wings to rotate around the same hinge axis, so that the unfolding movement of the left and right wings is mechanically forced to be synchronized, the problems of unsynchronized unfolding, in-place time difference and the like possibly caused by respective driving are solved, and instant stability of the attitude of the aircraft is directly brought by unfolding synchronism; the risk that the attitude is out of control due to asymmetric aerodynamic torque in the unfolding stage after launching is avoided, and the method is particularly important for aircrafts sensitive to the initial attitude, such as patrolling bullets.

This invention discloses an active intelligent multi-directional gyro stabilizer and its intelligent control algorithm for improving the flutter stability of long-span bridges. The gyro stabilizer structure includes a motor, an attitude angle sensor, a power supply box, a control box, a gyro stabilizer body, and a chain drive device. The gyro stabilizer obtains the aerodynamic torque at a unit torsional angle of the main beam by identifying the flutter derivative through wind tunnel testing. When the main beam undergoes torsion, the system combines the aerodynamic torque at the corresponding torsional angle of the main beam with the instantaneous optimal mapping relationship between the torsional angle of the main beam and the spin angular velocity of the gyro stabilizer established based on artificial intelligence neural network technology. It then outputs the spin angular velocity of the gyro stabilizer at the corresponding torsional angle of the main beam, as well as the gyro precession angular velocity calculated according to gyro precession theory. The chain drive device then controls the gyro precession to generate gyro torque, intelligently controlling the motion state and attitude behavior of the stabilizer, thereby improving the flutter stability of the bridge cross-section.

This invention provides a nonlinear flight control method and system for wind-disrupted unmanned aerial vehicles (UAVs). It utilizes a pre-set weather radar to acquire wind field disturbance characteristics in real time; inputs these characteristics into a pre-set aerodynamic disturbance prediction model to generate predicted aerodynamic torque fluctuation values; applies a pre-set dynamic filtering process to the amplitude characteristics of these predicted aerodynamic torque fluctuation values ​​to generate a control command correction signal; and couples this correction signal with a pre-set nonlinear control law of the UAV flight control system to suppress UAV attitude deviation caused by wind disturbance in real time, thus performing nonlinear flight control of the UAV. This invention overcomes the combined defects of lag and filtering mismatch in traditional linear control under strong wind abrupt changes, achieving stable attitude control of the UAV during low-altitude wind shear and sudden gusts, significantly improving the UAV's anti-disturbance response speed, and greatly reducing the risk of UAV loss of control.

The invention discloses a variable geometry turbine adjustable guide vane pneumatic torque measuring device and method, and belongs to the technical field of blade pneumatic torque measurement, the variable geometry turbine adjustable guide vane pneumatic torque measuring device comprises an arc-shaped mounting frame, a static torque sensor, a driving positioning mechanism and a plurality of adjustable guide vanes, and the adjustable guide vanes are rotatably connected to the arc-shaped mounting frame at equal intervals in the circumferential direction; the static torque sensor is installed on the adjustable guide vane, and the drive positioning mechanism is installed on the arc-shaped installation frame. According to the invention, the pneumatic torques of different rotation angles of the adjustable guide vane can be measured, the position of the adjustable guide vane is restrained through the arc-shaped mounting rack, and the adjustable guide vane is taken as a measurement object and rotates by taking the rotation shaft of the adjustable guide vane as the center, so that the throat area and the outlet airflow angle can be adjusted, and the flow of mainstream gas can be adjusted; the static torque sensor can be used for measuring the pneumatic torque borne by the adjustable guide vane in real time; the adjustable guide vane is rotationally adjusted and fixed through the driving and positioning mechanism, and the stability of the adjustable guide vane of the turbine is guaranteed.

The invention discloses a variable stiffness bolt simulator and a torque wrench calibration method applied by the same, and relates to the technical field of torque calibration. According to the bolt simulator, the rigidity of the bolt simulator can be changed by installing the adjusting guide rod in different positioning holes, so that calibration of high and low torque rates of an electric torque wrench and a pneumatic torque wrench is completed. When high / low torque rate calibration is carried out, the disassembly and assembly and part replacement processes of the bolt simulator can be obviously reduced, the calibration work efficiency is greatly improved, and indexes such as repeatability and reproducibility of the output value of the calibrated torque wrench are guaranteed to a certain extent. In addition, the torque calibration measuring range is widened, and meanwhile the service life of the measuring range section bolt simulator is prolonged.