38 results about "Inertial load" patented technology

The invention discloses a wind power generation variable pitch load suppression method and system, and relates to the technical field of wind power generation variable pitch load suppression, and the method comprises the steps of basic data acquisition, basic data analysis, power generation rate analysis, load data analysis and load abnormity processing. Whether hydraulic variable pitch operation is carried out or not is judged, then whether the power generation rate of the wind driven generator is qualified or not is judged, the wind load, the inertia load, the gravity load and the hydraulic cylinder load of each blade are combined for analysis, then the load coupling value of each blade is obtained, and the load abnormal condition of the wind driven generator is obtained through analysis; the problem of limitation existing in the current wind power generation variable-pitch load suppression analysis process is solved, comprehensive and objective analysis of wind power generation variable-pitch load suppression analysis is achieved, and reliability and authenticity of a wind power generation variable-pitch load suppression analysis result are guaranteed.

This invention relates to the field of intelligent machine tool technology, specifically to an intelligent machine tool equipped with a transverse movement mechanism, including an up-and-down transverse movement mechanism, a left-and-right transverse movement mechanism, a left-and-right micro-movement mechanism, and a pressure mold. The left-and-right transverse movement mechanism is mounted on the outer side of the up-and-down transverse movement mechanism, and the left-and-right micro-movement mechanism is mounted on the outer side of the left-and-right transverse movement mechanism. The pressure mold is located on the top of the left-and-right micro-movement mechanism. The core of this invention lies in eliminating the independent dedicated mounting plate and instead directly connecting the mold-moving assembly to the machine head frame. By eliminating redundant mounting plates and auxiliary connectors, the overall mass and inertial load of the moving parts are effectively reduced, which is beneficial to improving the dynamic response performance and motion accuracy of the system. Secondly, the direct connection method significantly compresses the structural space, making the layout more compact and significantly improving space utilization. Based on the simplification of the overall structure, the miniaturization and lightweight design of the machine head module are realized, providing a structural foundation for the deployment and performance improvement of the equipment in a limited space.

The invention provides a leg structure of a half-horse robot and the half-horse robot, the leg structure comprises a thigh, a shank, a thigh adduction and abduction joint, a thigh pitching joint and a knee joint, the thigh adduction and abduction joint is connected with the thigh through the thigh pitching joint; the thigh adduction and abduction joints can drive the thighs to adduction and abduction, and the thigh pitching joints can drive the thighs to swing front and back; the thighs are connected with the shanks through the knee joints, and the knee joints can drive the shanks to rotate. According to the leg structure, the half-horse robot has a pure foot type working mode and a wheel foot type working mode, the steering freedom degree is achieved in the wheel foot mode, in-situ steering can be achieved, and the flexibility of the robot is improved. A rotation actuator of the knee joint is arranged on the upper portion, the inertia load of the tail end of the leg is relieved, when the leg structure swings at a high speed or falls to the ground, dynamic response of the shank part is agile, impact is small, and overall movement of the robot is stable and efficient.

The disclosure presents a shaftless, brushless motor for rotating any optical or sensing element (e.g., a lens or mirror) at a distal end of a waveguide that also delivers electromagnetic radiation (e.g., light). Herein, the waveguide itself functions as the axle on which rotating components rotate, thereby avoiding blind spots and overcoming limitations in existing “micromotors”. The shaftless, distally driven motor significantly reduces motor size, while extremely small inertial loads and bearing sizes allow for high pitch cylindrical scanning with longitudinal velocity uniformity.

The application belongs to the field of comprehensive strength, and relates to a load calculation method and device of a helicopter auxiliary landing device. After the helicopter is stopped on the deck, the deck device fixes the lower end of the probe rod, and the external load borne by the helicopter includes gravity, inertia load caused by ship movement and wind load; the support reaction force is provided by the tire and the auxiliary landing device; all the friction forces are borne by the main wheel, and the tail wheel is a steering wheel and does not bear the friction force; the method comprises the following steps: stress analysis is carried out on the fixed helicopter, and a load balance equation is established; and the load of the helicopter auxiliary landing device is solved according to the load balance equation.

The application discloses a kind of aero-engine main bearing dynamics analysis method and system under motor flight condition, method includes, the dynamics model of rotor-support system under motor flight state is established, additional excitation force size under motor flight state is calculated;According to the load distribution law of shafting under the action of additional excitation force, the support reaction force of each support and the additional inertia load borne by main bearing are extracted, the coupling mechanism of the dynamic characteristics and elastohydrodynamic lubrication characteristics of main bearing is researched, the balance condition of coupling equation is proposed, and the main bearing thermal elastohydrodynamic lubrication coupling model is established;According to the mutual contact / collision action between typical interfaces between elements in bearing, a contact / collision action model considering lubrication is established;Considering the additional inertia load varying with time, based on the established main bearing thermal elastohydrodynamic lubrication coupling model, considering the force between main bearing interfaces, numerical integration is used to solve, realize the accurate analysis of the dynamic characteristics and vibration response mechanism of aero-engine main bearing.

The invention relates to the technical field of engineering machinery, in particular to a load measuring method and system applied to a rotary platform of an excavator. The excavator revolving platform is provided with at least one target measurement area, at least one strain gauge group is arranged in the target measurement area, and the method comprises the following steps: acquiring actually measured strain data corresponding to each strain gauge group, and generating an actually measured data matrix according to the actually measured strain data corresponding to all the strain gauge groups; calculating simulation strain data corresponding to each strain gauge group according to a preset excavator model, and generating a simulation data matrix according to the simulation strain data corresponding to all the strain gauge groups; and calculating target load data of the excavator revolving platform according to the actually measured data matrix and the simulation data matrix. On the basis of the preset strain gauge group, load measurement is carried out on the external load and the inertial load of the excavator revolving platform in a mode of combining virtual simulation and actual measurement, and the position of a measurement device does not need to be iteratively adjusted for multiple times, so that the load measurement efficiency is improved.

This invention relates to a tail fin structure with independent pitch and roll movements, comprising a pitch mechanism, a roll mechanism, and a connecting mechanism. The pitch mechanism includes a pitch servo and a pitch linkage, while the roll mechanism includes a roll servo and a transmission gear. The connecting mechanism includes a universal joint and a universal joint limiter. The pitch servo drives the tail fin to pitch movement via the pitch linkage. The roll servo drives the universal joint to rotate via the transmission gear, with the tail end of the universal joint connected to the tail fin to complete the roll movement. The rotation center of the pitch mechanism coincides with the center of the universal joint, and the left and right swing degrees of freedom of the universal joint are limited by the universal joint limiter, achieving independent control of pitch and roll movements. This invention allows for completely independent roll and pitch movements, significantly reducing the control precision requirements of the motor. The invention has a simple structure and reasonable design. The single-plane tail fin structure of this invention has strong wind resistance during flight and also has advantages such as low inertial load on the motor and high drive efficiency.

The application relates to a rotary switch cooperatively regulated tail edge air blowing gust generator and a use method thereof, and belongs to the technical field of wind tunnel tests. The rotary switch cooperatively regulated tail edge air blowing gust generator comprises a wing profile shell assembly, a gas supply pipeline assembly, a rotary switch assembly and a control system. The tail edge of the wing profile shell is provided with a multi-nozzle array, the rotary switch is composed of independent detachable rotary shaft units, the air blowing flow variation law can be changed by adjusting the installation combination of the rotary shaft units corresponding to the nozzles, and various customized gust outputs with consistent or inconsistent main frequencies and consistent or inconsistent phases can be realized. The control system adopts a PID or model prediction control algorithm, the rotary shaft rotation angle is fed back through an encoder, the gas supply mass flow is monitored through a flowmeter, the rotary shaft rotating speed and the gas supply pressure are cooperatively adjusted in a closed loop, the amplitude drift and the frequency deviation problems of the gust field caused by the air source fluctuation and the flow field interference under open loop control are solved, and the stability and controllability of high-speed / high-frequency gusts are significantly enhanced. The application has no inertial load and compact structure, and can be adapted to various wind tunnels.

This utility model belongs to the technical field of testing equipment, specifically a rudder system load simulation testing device, comprising: a frame and a testing component mounted on the frame; the testing component includes a testing mechanism mounted on the frame, a load mechanism mounted on the frame and located on the side of the testing mechanism, and a mounting base mounted on the frame; the testing mechanism includes a housing mounted on the side of the frame, a motor fixed inside the housing, a drive shaft connected to the drive end of the motor, a torque sensor located in the middle of the drive shaft, and an angle encoder mounted at the end of the drive shaft. This utility model, through the testing component, can reproduce inertial loads, elastic loads, and damped loads using the magnetic powder brake, variable stiffness spring assembly, and hydraulic damper in the load mechanism. Compared with traditional fixed weight loads, the dynamic characteristic simulation is more accurate, and the test data is more comprehensive.

This application belongs to the field of V-tail aircraft design, and specifically relates to a method and system for calculating the load parallel to the hinge axis of a V-tail aircraft. It assumes that the load parallel to the hinge axis of the V-tail aircraft conforms to the rotation axis ellipse equation distribution, and establishes the rotation axis ellipse equation; it sets a chord equation, the slope of which is an expression including the V-tail tilt angle; it solves the chord equation and the rotation axis ellipse equation simultaneously to obtain the intersection point coordinates; it solves the chord length based on the intersection point coordinates; it then reduces the chord length to obtain the inertial load of the tilted V-tail, i.e., the load parallel to the hinge axis. The rotation axis ellipse equation describes the coupled distribution of vertical and horizontal loads, and the intersection point is solved simultaneously using the chord equation, finally calculating the load value related to the tilt angle. This is the first time that the "composite function" and "geometric tilt angle" of the V-tail have been incorporated into the load calculation model, making the results more closely reflect the actual stress state and avoiding safety hazards or weight redundancy caused by incorrect coefficient selection.

The application relates to a rear suspension lower support fatigue life analysis method and device, computer equipment, a storage medium and a computer program product. The method comprises the following steps: firstly, obtaining the relative torsion angle between a first main cross beam and a second main cross beam, the axial displacement of a spring shock absorber, three-directional acceleration of a suspension upper support and three-directional acceleration of a suspension lower support; then, pre-processing the obtained data; then, obtaining a first full-field time-domain stress and a first strain amplitude of the rear suspension lower support under a cab inertia load condition, a second full-field time-domain stress and a second strain amplitude of the rear suspension lower support under a vibration condition and a resonance response, and a third full-field time-domain stress and a third strain amplitude of the rear suspension lower support under a low-frequency torsion condition of a vehicle frame; and finally, analyzing the fatigue life of the rear suspension lower support according to the obtained stress and strain amplitude. The method provided by the application can accurately evaluate the actual fatigue life of the rear suspension lower support.

The present application belongs to the field of helicopter structure strength design, and relates to a design analysis method of a helicopter overhanging equipment support. The method comprises the following steps: determining the positions of each interface of the helicopter overhanging equipment by analyzing the proportion of each direction component of the aerodynamic load and the inertial load under the severe load condition and the bearing capacity of the installation interface of the fuselage; designing the load transmission path and the initial main body transmission structure according to the positions of each interface, the aerodynamic load and the inertial load, and performing topology optimization on the initial main body transmission structure; and finally completing the design of the overhanging equipment support by performing detail size optimization according to the strength requirement and the dynamics requirement.

The present application belongs to the field of wind power generation ground test technology, and provides a wind turbine transmission chain test platform electromechanical coupling loading method and system, real-time wind speed and power grid frequency are obtained; dynamic nonlinear aerodynamic load, gravity load and inertia load are calculated according to the real-time wind speed, and are converted through coordinate transformation to form a basic load component; the required electromagnetic torque instruction of the generator is calculated through comprehensive inertia control according to the real-time power grid frequency; based on the physical mechanism of the reverse torque of the generator leading to the tower tube pitching, the pitching angle acceleration of the top of the tower tube is calculated, and the additional inertia bending moment generated at the main shaft due to the pitching motion is calculated; the driving control of the load motor system is carried out according to the electromagnetic torque instruction to simulate the electromagnetic torque impact, the basic load component and the additional inertia bending moment are superimposed, the control of the six-degree-of-freedom loading device is carried out to simulate the structural lateral vibration bending moment, and synchronous loading is realized. The present application greatly improves the authenticity of the test.

The present invention achieves a technology capable of estimating a ground contact load in a vehicle with sufficiently high accuracy. A ground contact load estimation device according to the present invention is configured to estimate a ground contact load of a vehicle by: acquiring a wheel angular velocity of the vehicle, a steady load, and an inertial load; calculating a first gain using the steady load and the inertial load; estimating a road surface load using the first gain, a prescribed vehicle specification, and a second gain representing a hysteresis characteristic of a tire mounted on the vehicle; and referring to the road surface load.

The invention relates to the technical field of industrial automation control, and discloses a complete switch equipment-oriented copper bar flexible processing production cooperative control method, which comprises the following steps of: analyzing a three-dimensional design model, and establishing a discretization infinitesimal model along the longitudinal direction of a copper bar; collecting punching shear servo data to calculate a global material hardening index, and reconstructing a discrete residual stress field; performing task clustering based on the rehearsal trajectory, and calculating a cumulative inertial load factor in circulation; the optimal mechanical clamping point deviating from the geometric center is calculated according to the discrete residual stress field, and dynamic grabbing is executed; and in combination with the hardening index and the inertia load factor, calculating a bending pressing stroke containing double gain correction and executing machining. According to the method, by means of discrete stress field reconstruction and inertial load calculation, dynamic drift correction and multi-dimensional bending self-adaptive compensation of the grabbing point are achieved, and the machining precision can be improved without trial bending.

The invention discloses a loading experiment system and method suitable for a steering drive axle, and the system comprises a driving unit which is used for providing a driving force for a tested steering drive axle; the dynamometer loading unit is used for being connected with the output end of the tested steering drive axle and simulating a wheel side load; the inertia loading unit is used for being connected with the output end of the tested steering drive axle and simulating an inertia load; the external load loading unit is used for being connected with an axle housing of the tested steering drive axle and simulating an external impact load; the steering mechanism is used for driving the dynamometer loading unit or the inertia loading unit to rotate to a preset angle; the data acquisition unit is connected with the tested steering drive axle; and the control unit is connected with the driving unit, the dynamometer loading unit, the inertia loading unit and the steering mechanism, controls the driving unit, the dynamometer loading unit, the inertia loading unit and the steering mechanism to operate based on a control instruction, and communicates with the data acquisition unit to form closed-loop control. According to the invention, high-precision cooperative loading test and fault diagnosis of the steering drive axle under different steering angle working conditions can be realized.

The application discloses a new type of structure of a walking lower cross beam of a stacking machine, which comprises a lower cross beam body and a column base body, the lower cross beam body comprises a cross beam connecting rod, support seats are fixedly connected to the two ends of the cross beam connecting rod, recessed matching blocks are arranged on the surfaces of the support seats, excess holes and limiting holes are formed in the surfaces of the recessed matching blocks, the column base body comprises a base horizontal rod, base plates are fixedly arranged at the two ends of the base horizontal rod, convex matching blocks are fixedly connected to the lower portions of the base plates, insertion holes are formed in the surfaces of the convex matching blocks, and positioning rods are fixedly connected to the lower surfaces of the convex matching blocks; the column base body and the lower cross beam body are flexibly connected, when running, inertia load is consumed and dispersed through the flexible connection between the recessed matching blocks and the convex matching blocks; the force relief assembly can adjust the flexible connection excess in real time, offset the action force of the column base body shaking on the surface of the lower cross beam body, avoid excessive shaking of the lower cross beam, and improve the stability and reliability of the equipment.

This utility model relates to a connecting rod balancing mechanism for a beam pumping unit, comprising a lower connecting rod joint, a crank pin bearing housing, a crank pin, a crank, a crank pin bearing cover, and a crank pin bearing. The lower connecting rod joint and the crank pin bearing housing are fixedly connected as an integral connecting rod-crank pin structure. The key feature is that a connecting rod balance box is connected to the lower connecting rod joint or the crank pin bearing housing, forming the connecting rod balancing structure of the beam pumping unit. The connecting rod balance box is connected to the lower connecting rod joint or the crank pin bearing housing via a flange or pin. This utility model achieves a new balancing method by setting a balance box at the lower end of the connecting rod or the crank pin bearing housing. The counterweight is set at the lower end of the connecting rod or the crank pin bearing housing, reducing the force on the crank pin and lowering the risk of crank pin breakage. It also avoids the drawback of large inertial loads in beam balancing.

The invention discloses a method and a device for analyzing the load of a sucker rod in a pumping well. The method comprises the following steps of: determining a liquid column load, a vibration load, a liquid column inertia load and a friction force between a plunger and a bushing at a starting point of a sucker rod by taking a well deviation measuring point on the upper end surface of a piston of the oil well pump as the starting point to obtain an up-stroke maximum load and a down-stroke minimum load; the well deviation measuring points are sequentially traversed upwards, and corresponding well sections are obtained; based on the upper stroke maximum load and the lower stroke minimum load at the lower end point of the sucker rod, the upper stroke friction load and the lower stroke friction load between the sucker rod and the oil pipe are determined respectively; vertical stroke friction force between the sucker rod and the liquid column at the well section is determined; determining the gravity of the sucker rod at the well section and the downstroke load of the sucker rod; according to the gravity of the sucker rod at the well section, upper and lower stroke inertia loads of the sucker rod at the well section are determined respectively; and the upstroke maximum load and the downstroke minimum load of the sucker rod at the upper end point are determined. According to the method, the stress condition of the sucker rod is determined point by point, and a data basis is provided for safety analysis.

The present disclosure relates to a method for calibrating an articulated robot, a computer device and a non-temporary computer-readable storage medium. The method includes: acquiring desired trajectory information regarding a desired trajectory of the end-effector; acquiring load information regarding a load subjected by the articulated robot, the load including a gravity load, an inertial load and an external load; obtaining, based on the desired trajectory information, joint position data indicating a joint position of the articulated robot; obtaining, based on the joint position data and the load information, end position change data indicating an end position change of the end-effector; and compensating, based on the end position change data, a position error of the end-effector according to a predetermined compensation strategy.

This invention relates to the field of industrial robot fault diagnosis technology, and discloses a fault early warning and remote diagnosis method for the electrical control system of an industrial robot. This method obtains mechanical load parameters through a potential load model, an inertial load model, and a basic dynamic model; obtains electrical state parameters through an electrical efficiency model; generates correction factors through a correction model based on ambient temperature; calculates dynamic current thresholds through a threshold model based on the correction factors and a basic current threshold; and finally outputs health scores and fault early warning information through a diagnostic model by combining vibration acceleration and servo loop following error. This invention integrates multi-source parameters from mechanical, electrical, and environmental sources to achieve dynamic threshold adjustment and multi-dimensional health assessment, effectively distinguishing between normal operating conditions and abnormal states, significantly improving the accuracy of fault early warnings, reducing false alarm rates, and providing a reliable remote diagnosis solution for industrial robots.

This application provides a method and apparatus for determining the load on the cable of a floating photovoltaic platform. The method acquires the motion acceleration data of the floating photovoltaic platform at the target cable guide hole under target waves; based on the traditional catenary micro-segment equilibrium equation, an equivalent inertial load term determined by the motion acceleration data is introduced to construct a modified catenary equilibrium differential equation; the modified catenary equilibrium differential equation is numerically solved, and combined with preset mooring system boundary conditions, the horizontal and vertical tensions at the target cable guide hole are obtained; the horizontal and vertical tensions are then determined as the design load of the floating photovoltaic platform cable. This method solves the key technical problem that the traditional quasi-static catenary method cannot accurately account for the platform's wave dynamic response, leading to an underestimation of the cable design load.

The invention discloses a high-precision prediction method for the aeroelastic vibration load of a rotor blade with a trailing edge winglet, and belongs to the field of helicopter rotor aeroelastic dynamics. According to the method, the influence of a trailing edge winglet inertia load generated by trailing edge winglet high-frequency motion and a complex blade section shape change generated by trailing edge winglet high-frequency motion on a rotor blade section unsteady aerodynamic load and a rotor time-varying wake is accurately calculated; and high-precision prediction of the aeroelastic vibration load of the rotor blade with the trailing edge winglet is realized. The high-precision prediction method for the aeroelastic vibration load of the rotor blade with the trailing edge winglet is suitable for the rotor blade which is in an unsteady incoming flow and has any movement and deformation, any section shape and any material distribution characteristic; the anisotropy of the composite material and the influence of non-classical effects such as transverse shear deformation, section warping and elastic coupling caused by the anisotropy of the composite material can be accurately calculated, and the method has good engineering application value.

An aircraft part has a fuselage portion and a floor, at least a part of which is joined to the fuselage portion via elastic link rods. Each elastic link rod is provided with a first end that is configured to be fixed to the floor and with a second end that is configured to be fixed to the fuselage portion. The elastic link rods are configured to exhibit a stiffness that makes it possible both to transmit loads between the floor and the fuselage portion and to absorb displacements brought about by deformations of the fuselage portion. The aircraft part thus making it possible, at a lower cost and with a lower mass, to obtain a connection between the floor and the fuselage portion that exhibits suitable elasticity to be able to transmit inertial loads while absorbing deformations of the fuselage portion.

An industrial power system includes a hybrid electric transmission assembly to transfer power from an internal combustion engine to an industrial load. The transmission assembly includes a first driveshaft coupled to the engine and a second driveshaft coupled to the load with a primary drivetrain gear assembly coupling the first driveshaft to the second driveshaft. An electric drive gearset is disposed between the primary drivetrain gear assembly and the load. An electric motor is couplable to the electric drive gearset, thereby allowing power to be passed from the electric motor to drive the load and bypass the primary drivetrain gear assembly during the gear change. The system may include a plurality of electric motors each having an electric motor axis and an output gearset coupled to the electric drive gearset, where each of the electric motor axii are spaced radially outward from the first and second driveshafts.

The invention relates to the technical field of intelligent suspension conveying, in particular to a glass product suspension conveying device and method.The device comprises a traveling frame and a walking component, a supporting frame is connected to the bottom of the walking component and comprises two sets of vertical plates arranged at intervals, and connecting plates are fixedly arranged at the top ends of the two sets of vertical plates; the top end of the connecting plate is fixedly connected with the bottom of the walking part, the bottom ends of the two vertical plates are connected with a bearing plate through a turnover mechanism, and multiple vacuum suction cups are arranged at the bottom end of the bearing plate and used for adsorbing feeding position glass on the top of the conveying table. According to the invention, in the process of converting a glass product from a horizontal state to a vertical state or a nearly vertical state, gentle and controlled posture change can be completed along the potential energy reduction direction, so that the adverse stress states of overturning impact, inertial load and an adsorption interface are reduced from the source; the problems of adsorption failure and glass damage caused by sudden acceleration change and lateral load superposition in a traditional driving axis overturning mode are solved, the conveying efficiency is improved, and the safety of suspension conveying is enhanced.

This invention discloses an impact equivalent test method based on energy accumulation, relating to the field of dynamic impact testing under inertial loads. The method first establishes a physical analysis model under overload impact and determines the form of the external inertial load; using this physical model, it establishes the governing equations, geometric equations, and constitutive equations of the structure; it calculates the elastoplastic response process using discrete difference techniques and obtains the corresponding energy values; it compares and selects the principal energy and plots an energy accumulation contour map; it extracts the energy accumulation contour lines and performs numerical fitting to determine a suitable fitting function; and it establishes an equivalent relationship between long and short pulse widths based on the selected fitting function. This invention fully considers the dynamic response process of the structure under elastoplastic theory, establishes an equivalent criterion between long and short pulse widths from the perspective of energy accumulation, provides guidance for the selection of inertial load parameters required for dynamic impact environments, and further promotes the engineering process of equivalent methods for extreme overload simulation environment tests.

The invention belongs to the technical field of wind power generation ground tests, and provides a wind turbine generator transmission chain test platform electromechanical coupling loading method and system, and the method comprises the steps: obtaining a real-time wind speed and a power grid frequency; according to the real-time wind speed, dynamic nonlinear aerodynamic load, gravity load and inertia load are calculated, and basic load components are formed through coordinate transformation; according to the real-time power grid frequency, comprehensive inertia control is carried out, and an electromagnetic torque instruction required by a generator is calculated; based on the physical mechanism that the reverse moment of the generator causes the pitching of the tower drum, calculating the pitching angle acceleration of the top end of the tower drum, and calculating the additional inertia bending moment generated at the main shaft due to the pitching motion; and according to the electromagnetic torque instruction, driving control of a load motor system is performed to simulate electromagnetic torque impact, superpose a basic load component and add an inertia bending moment, and control of a six-degree-of-freedom loading device is performed to simulate a structure side vibration bending moment so as to realize synchronous loading. According to the invention, the authenticity of the test is greatly improved.

The invention provides a centering calculation method for a high-speed shaft system of a gas turbine unit with a gear box, which comprises the following steps of: carrying out statics calculation on the high-speed shaft system of the gas turbine unit, establishing a coupling relationship of translational degrees of freedom, and releasing rotational degrees of freedom; the axial displacement at the gas compressor side bearing is restrained; applying a gravitational acceleration inertial load; applying a meshing force radial component at the meshing position of the gearbox pinion shaft; setting an initial displacement boundary condition at each bearing position; performing statics calculation on the high-speed shaft system of the gas turbine unit; calculating a corner difference; carrying out finite element optimization calculation on the high-speed shaft system of the gas turbine unit to obtain an optimal hot-state mounting position of each bearing, and converting the optimal hot-state mounting position into an optimal cold-state mounting position; and finally, the opening values of the first coupling flange and the second coupling flange under the cold-state installation working condition are calculated according to the optimal cold-state installation position and are used for guiding field installation. The method reliably ensures that the high-speed shaft system of the gas turbine unit can be better thermally centered under the rated load operation condition.