CN103791811B - Aeroengine rotor based on inductance sensing with magnetic over draft support stacks assembly method and device - Google Patents

Abstract

The aeroengine rotor stack assembly method and device based on capacitive sensing and magnetic suspension support belong to the mechanical assembly technology. Its measurement method and device are based on the magnetic levitation rotary shaft system to determine the rotation reference; determine the angular positioning of the turntable based on the induction synchronizer; based on the four-probe measurement device, extract the radial error of the radial assembly surface of the rotor and the inclination error of the axial assembly surface , to obtain the influence weight of the rotor on the rotor coaxiality after assembly; measure all the rotors required for assembly respectively, and obtain the influence weight of each rotor on the rotor coaxiality after assembly; carry out vector optimization on the weights of each rotor, Get the assembly angle of each rotor. The invention can effectively solve the problem of low coaxiality of the aeroengine rotor after assembly, and has the characteristics of high coaxiality after assembly of the rotor, reduced vibration, easy installation, high flexibility and improved engine performance.

Description

Aeroengine rotor stack assembly method and device based on inductive sensing and maglev support

technical field

The invention belongs to mechanical assembly technology, and mainly relates to an aeroengine rotor stacking assembly method and device based on inductive sensing and magnetic suspension support.

Background technique

Aeroengine assembly is the last link in the manufacturing process of aeroengine, and it is also one of the most important manufacturing links. Under the conditions of the existing aero-engine design scheme and processing technology level, the quality of assembly and work efficiency have an important impact on the quality, performance and production efficiency of the engine. Therefore, in the assembly process, the coaxiality of the installed rotor should be improved as much as possible, so as to reduce the vibration of the aero-engine and improve the performance of the aero-engine. However, in actual production, the assembly of aero-engines is completely manual assembly. The level of assembly accuracy and stability depends entirely on the experience and technical level of the assemblers. There is a lack of a high-speed and effective method to guide the assembly of aero-engine rotors. Improve assembly efficiency, reduce aero-engine vibration, and improve aero-engine performance.

As the aero-engine assembly and testing technology is getting more and more attention, the aero-engine assembly and testing technology is getting more and more attention, and has become a research hotspot. More and more researchers have conducted in-depth discussions on aero-engine rotors. Rolls-Royce proposed a solution (System and method for improving the damage tolerance of a rotor assembly. European Patent Publication No.: EP2525049A2), mainly through the Each sub-test system obtains the stress signal of each position of the rotor, and the main system analyzes the signals collected by each subsystem, and analyzes the impact on assembly from the damage tolerance parameters of each rotor, thereby improving the assembly of the aeroengine rotor. The problem with this method is that the influence of the geometric quantity of the rotor on the assembly is not analyzed, and the influence of the geometric quantity on the assembly cannot be improved.

Xi'an Jiaotong University proposed a method for testing the assembly performance of an aero-engine rotor (a method for testing the assembly performance of an aero-engine rotor. Publication number: CN101799354A). The method first uses the exciter to excite the aero-engine rotor, and uses the vibration sensor and signal acquisition system software to obtain an impulse response signal of a multi-carrier coupled aero-engine rotor; The response signal is analyzed by the dual-tree complex wavelet transform method to obtain the impulse response sub-signals of the eight single-carrier aero-engine rotors; finally, the average assembly performance index is extracted from the obtained eight single-carrier aero-engine rotor impulse response sub-signals , if the obtained average assembly performance index value is greater than or equal to 10, it is judged that the assembly of the aero-engine rotor is qualified; if the obtained average value is less than 10, it is judged to be unqualified and needs to be reworked. The problem with this method is that there is no guidance on the assembly of the aeroengine rotor.

Luoxin Precision Parts (Shanghai) Co., Ltd. proposed a coaxiality measurement equipment (a coaxiality measuring instrument. Publication number: CN202024752U). The device includes a pair of transmission spindles arranged on the main body of the instrument that are synchronously controlled by a synchronous mechanism. The inner ends of the transmission spindles are respectively provided with measuring heads and positioning reference planes; above the position between the measuring heads there is a sensor measuring head . It mainly solves the measurement of coaxiality and runout of existing precision parts. The problem with this method is that only measuring the coaxiality of the tested part does not solve the problem of poor coaxiality of the rotor after assembly.

Shenyang Liming Aero Engine (Group) Co., Ltd. proposed a clearance measurement method (a non-contact measurement method for the radial clearance of the engine rotor blade tip. Publication number: CN102175135A). This method adopts capacitance method measurement technology, and the measurement steps are as follows, first assemble the measurement system, calibrate the sensor, determine the relationship between the blade tip radial clearance and voltage, then fix the sensor on the blade, and finally measure the radial clearance of the engine rotor blade tip . The problem with this method is that it does not consider the influence of the axial installation surface on the rotor after assembly during the rotor assembly process.

The test object of aero-engine assembly is the turbine stator and rotor. Under the condition that the machining accuracy of the components meets the requirements, the final inspection depends on the state after installation and fit. The evaluation index is mainly the coaxiality parameter of the assembled rotor. The engine rotates to generate high pressure, and its rotor is composed of a number of single parts assembled together. Ideally, the axis of rotation of each part coincides with the axis of the entire engine. The high-speed rotation speed of a high-performance engine is greater than 10,000rpm, and the axial or radial deflection of a single component will inevitably cause the center of the turbine disc to deviate from the axis of rotation of the engine. Under such conditions, a very large centrifugal force will be generated, causing the rotor to rotate unbalanced , causing engine vibration, so ensuring the coaxiality of each component after assembly is the focus and difficulty of installation.

A model assembly that does not use the coaxiality optimization method, the axial and radial directions of each component have errors such as runout, eccentricity, and tilt due to the limitation of machining accuracy. If it is assembled directly and randomly, it may form a bending situation similar to "banana", that is, the upper part accumulates the eccentricity or tilt error of the lower parts, resulting in a huge overall yaw and tilt after assembly, resulting in the coaxiality of the engine rotor. Very poor, difficult to meet the requirements of use.

At present, domestic engine assembly still adopts traditional assembly methods, mainly manual testing with dial gauges. Assemble the engine from bottom to top, measure after assembling a component to ensure that the whole can meet the threshold condition of coaxiality after each addition of components, and then install another component upwards. Each time, the previous part is used as a reference, and the overall coaxiality is finally required to be within a certain range. This method consumes a lot of time and has a high possibility of rework, which greatly affects the efficiency of installation and the first-time success rate. Usually, a successful assembly takes 4 to 5 days. Moreover, because it is not the best assembly position, it usually needs to be disassembled and assembled 4 to 5 times, and workers are required to assemble with rich experience, and each assembly needs to undergo hot and cold processing. Therefore, the current aero-engine assembly method has low installation efficiency, is not easy to install, and has poor coaxiality after assembly, which affects engine performance.

Contents of the invention

Aiming at the deficiencies in the above-mentioned existing technologies, a method and device for stacking and assembling aero-engine rotors based on inductive sensing and maglev support is proposed to solve the problem of low coaxiality of the aero-engine rotors after assembly and to achieve coaxiality of the rotors after assembly. High, reduce vibration, easy installation, high flexibility, and improve engine performance.

The purpose of the present invention is achieved like this:

A method for stacking and assembling an aero-engine rotor based on inductive sensing and maglev support, the steps of the method are as follows:

Place the measured rotor on the self-aligning and tilting workbench and fix it; contact the telescopic inductive sensor measuring the axial installation datum surface with the axial installation datum surface of the tested rotor for tilt adjustment; measure the radial installation datum surface The lever-type inductive sensor is in contact with the radial installation datum surface for centering; the magnetic levitation turntable drives the measured rotor to rotate at a constant speed of 6-10r/min through the self-aligning and tilting workbench, and measures the expansion and contraction of the axial installation datum surface The inductance sensor is sampled at equal intervals on the axial installation reference plane of the rotor under test, and the lever-type inductance sensor for measuring the radial installation reference plane is sampled at equal intervals on the radial installation reference plane of the rotor under test; the number of sampling points should meet 1000 to 2000 points per circle; the sampling data on the radial installation reference plane of the tested rotor is fitted by the least square circle to evaluate the eccentricity, and the sampling data on the axial installation reference plane of the tested rotor is passed through the minimum Two times the plane fitting to evaluate the amount of inclination; according to the size and angle of the eccentricity, adjust the centering knob of the self-aligning and tilting workbench; , until the self-aligning and tilting table meets the requirement that the eccentricity of the radial reference plane is within the range of 0-3μm, and the inclination of the axial reference plane is within the range of 0-2″; The inductance sensor is in contact with the axially installed measuring surface of the rotor under test, and the lever-type inductive sensor for measuring the radially installed measuring surface is in contact with the radially installed measuring surface of the rotor under test; the magnetic levitation turntable rotates at a constant speed of 6 to 10r/min, The telescopic inductance sensor for measuring the axially installed measuring surface is sampled at equal intervals on the axially installed measuring surface of the rotor under test, and the lever type inductive sensor for measuring the radially installed measuring surface is respectively sampled at equal intervals on the radially installed measuring surface; sampling The number of points should meet 1000-2000 points per circle; the data sampled by the lever-type inductive sensor measuring the radially installed measuring surface on the radially installed measuring surface of the rotor under test is fitted by the least square circle and evaluated for concentricity; The data sampled by the telescopic inductive sensor that measures the axially installed measuring surface on the axially installed measuring surface of the rotor to be tested is fitted by the least squares plane and the verticality is evaluated; combined with the radius of the axially installed measuring surface and the measured Measure the height difference between the rotor and the final assembled rotor to obtain the influence weight of the measured rotor on the coaxiality of the assembled rotor; measure all the rotors required for assembly separately to obtain the influence weight of each rotor on the coaxiality of the assembled rotor ; Use the genetic algorithm to carry out vector optimization on the weights of each rotor to obtain the assembly angle of each rotor, and the calculation method of the influence weight of the rotor coaxiality is: In the formula: C represents the concentricity of the radially installed measuring surface of the rotor under test, Indicates the eccentric angle of the fitting circle center of the radially installed measuring surface, H indicates the height difference between the rotor under test and the final assembled rotor, R indicates the radius of the axially installed measuring surface, P indicates the perpendicularity of the axially installed measuring surface of the tested rotor, θ represents the angle at which the highest point of the fitting plane of the axial installation measuring surface is located.

The structure of an aeroengine rotor stack assembly device based on inductive sensing and magnetic suspension support is that the magnetic suspension shaft system is nested at the center of the base, and the magnetic suspension shaft system consists of a magnetic suspension main shaft, a worktable, a magnetic suspension shaft upper pressure plate, and a magnetic suspension shaft. The lower pressure plate of the shaft, the fixed length of the induction synchronizer, the sliding rule of the induction synchronizer, the upper permanent magnet, the lower permanent magnet, the upper coil, the lower coil, the motor stator and the motor rotor are composed. On the upper part, the upper pressure plate of the magnetic shaft is arranged on the upper end of the magnetic shaft, the magnetic shaft is arranged on the upper end of the lower pressure plate of the magnetic shaft, the induction synchronizer slide rule is nested on the outer ring of the lower pressure plate of the magnetic shaft, and the fixed Ruler) is fixed on the lower part of the inner side of the center of the base, and above the sliding ruler of the induction synchronizer. The upper permanent magnet is sleeved on the outer ring of the maglev main shaft and fixed on the lower end of the upper pressure plate of the maglev shaft. The upper coil is sleeved on the outer ring of the maglev main shaft. and fixed inside the base, 5-10cm below the upper permanent magnet; the lower permanent magnet is set on the outer ring of the maglev spindle, and fixed on the upper end of the lower pressure plate of the maglev shaft, and the lower coil is sleeved on the outer ring of the maglev spindle , and fixed inside the base, 5-10cm above the lower permanent magnet, the motor rotor is nested on the outer ring of the lower pressure plate of the magnetic shaft, and is located at the lower part of the induction synchronizer slider, and the motor stator is fixed at the center of the base The lower part of the inner side is located at the lower part of the induction synchronizer and the outside of the motor rotor; the self-aligning and tilting worktable is arranged at the center of the maglev shafting system, and the four-jaw pneumatic chuck is arranged at the center of the self-aligning and tilting worktable; left The motion guide rail and the right motion guide rail are symmetrically distributed on the bases on both sides of the maglev shafting system. The left column is installed on the left motion guide rail, and the right column is installed on the right motion guide rail; the left column can be moved and adjusted from top to bottom. Set the left upper pole connecting piece and the left lower pole connecting piece, the left upper horizontal measuring rod is horizontally nested on the left upper pole connecting piece, the upper lever type inductive sensor is fixedly connected with the left upper horizontal measuring rod; the left lower horizontal measuring rod is horizontally nested on the left lower On the column connector, the lower lever inductive sensor is fixedly connected with the lower left horizontal measuring rod; on the right column, the upper right column connector and the lower right column connector are set movably and adjustable from top to bottom, and the upper right horizontal measuring rod It is horizontally nested on the upper right pole connecting piece, and the upper telescopic inductive sensor is fixedly connected with the upper right horizontal measuring pole; The measuring rod is fixed.

Compared with prior art, the characteristics of the present invention are:

The present invention can obtain the coaxiality weight of each rotor by measuring the concentricity and perpendicularity of each rotor, and then vector-optimize the coaxiality weight of each rotor to obtain a guiding installation angle, saving 40% of installation time and Cost, 98% one-time installation success rate, predictable installation progress, improve engine stability, reduce engine vibration, save engine fuel consumption, reduce _CO2 emissions, and reduce engine noise pollution.

Description of drawings:

Figure 1 is a schematic diagram of the structure of the four-probe measuring device

Figure 2 is a schematic diagram of the structure of the maglev shafting system

Part number in the picture: 1—base, 2—maglev shafting, 2a—maglev spindle, 2b—worktable, 2c—upper pressure plate of maglev shaft, 2d—lower pressure plate of maglev shaft, 2e—inductive synchronizer scale, 2f—induction synchronizer slide rule, 2g1—upper permanent magnet, 2g2—lower permanent magnet, 2h1—upper coil, 2h2—lower coil, 2i—motor stator, 2j—motor rotor, 3—alignment and tilting workbench, 4 —Four-jaw pneumatic chuck, 5a—left column, 5b—right column, 6a—left lower horizontal measuring rod, 6b—right lower horizontal measuring rod, 6c—left upper horizontal measuring rod, 6d—right upper horizontal measuring rod, 7a—left lower column Rod connector, 7b—right lower rod connector, 7c—left upper rod connector, 7d—right upper rod connector, 8a—lower lever inductive sensor, 8b—upper lever inductive sensor, 9a—bottom telescopic Inductance sensor, 9b—upper telescopic inductance sensor, 10a—left motion guide rail, 10b—right motion guide rail.

detailed description

Below in conjunction with accompanying drawing, the present invention is described in further detail:

A method and device for stacking and assembling aircraft engine rotors based on inductive sensing and maglev support. The method and device are as follows: a four-jaw pneumatic chuck 4 is arranged on the center position of a centering and tilting workbench 3 . The left moving guide rail 10a and the right moving guide rail 10b are symmetrically distributed on the base 1 on both sides of the magnetic suspension shaft system 2, the left column 5a is installed on the left moving guide rail, and the right column 5b is installed on the right moving guide rail. On the left column 5a, the left upper column connector 7c and the left lower column connector 7a are movably adjusted sequentially from top to bottom, and the left upper horizontal measuring rod 6c is horizontally nested on the left upper column connector 7c. The sensor 8b is fixedly connected with the upper left lateral measuring rod 6c; the lower left lateral measuring rod 6a is horizontally nested on the lower left pole connecting piece 7a, and the lower lever type inductive sensor 8a is fixedly connected with the lower left lateral measuring rod 6a. On the right column 5b, the upper right column connecting piece 7d and the right lower column connecting piece 7b are movably adjusted sequentially from top to bottom, and the upper right horizontal measuring rod 6d is horizontally nested on the right upper column connecting piece 7d. The inductance sensor 9b is fixedly connected with the upper right transverse measuring rod 6d; the lower right transverse measuring rod 6b is horizontally nested on the lower right pole connector 7b, and the lower telescopic inductive sensor 9a is fixedly connected with the lower right transverse measuring rod 6b. The magnetic levitation shaft system 2 is nested in the center position of the base 1, and the magnetic levitation shaft system 2 is composed of a magnetic levitation main shaft 2a, a worktable 2b, a magnetic levitation shaft upper pressure plate 2c, a magnetic levitation shaft lower platen 2d, an induction synchronizer scale 2e, The induction synchronizer slide rule 2f, the upper permanent magnet 2g1, the lower permanent magnet 2g2, the upper coil 2h1, the lower coil 2h2, the motor stator 2i and the motor rotor 2j are composed, and the workbench 2b is arranged on the upper end of the upper pressure plate 2c of the magnetic levitation shaft The upper pressure plate 2c of the magnetic suspension shaft is arranged on the upper end of the magnetic suspension main shaft 2a, the magnetic suspension main shaft 2a is arranged on the upper end of the lower pressure plate 2d of the magnetic suspension shaft, and the induction synchronizer slide rule 2f is nested on the outer ring of the lower pressure plate 2d of the magnetic suspension shaft, The fixed length 2e of the induction synchronizer is fixed on the inner lower part of the center position of the base 1, and is located above the sliding ruler 2f of the induction synchronizer, and is located outside the sliding ruler 2f of the induction synchronizer, and the upper permanent magnet 2g1 is sleeved on the outer ring of the maglev main shaft 2a, And fixed on the lower end of the upper pressure plate 2c of the magnetic suspension shaft, the upper coil 2h1 is sleeved on the outer ring of the magnetic suspension main shaft 2a, and fixed inside the base 1, 5-10cm below the upper permanent magnet 2g1; the lower permanent magnet 2g2 is sleeved on the magnetic suspension On the outer ring of the main shaft 2a, and fixed on the upper end of the lower pressure plate 2d of the maglev shaft, the lower coil 2h2 is sleeved on the outer ring of the maglev main shaft 2a, and fixed inside the base 1, 5-10cm above the lower permanent magnet 2g2; the motor The rotor 2j is nested on the outer ring of the lower pressure plate 2d of the magnetic shaft, and is located at the lower part of the induction synchronizer slide rule 2f, and the motor stator 2i is fixed on the lower part of the inner side of the center of the base 1, and is located at the lower part of the induction synchronizer scale 2e and the motor The rotor 2j is external. The maglev shaft system 2 drives the tested rotor to rotate at a constant speed of 6-10r/min. The lower telescopic inductive sensor 9a samples at equal intervals on the axial installation reference plane of the tested rotor. The lower lever inductive sensor 8a Sampling is carried out at equal intervals on the radial installation datum plane of the rotor, and the number of sampling points should satisfy 1000 to 2000 points per revolution. The sampling data on the radial installation datum plane of the rotor to be tested is fitted by the least square circle to evaluate the eccentricity. The amount of inclination is obtained by fitting the sampled data on the axial installation datum plane of the rotor under test through least squares plane fitting; and angle, adjust the centering and tilting workbench 3 until the eccentricity of the radial reference plane is within the range of 0-3 μm; according to the size and angle of the inclination, adjust the centering and tilting workbench 3 until the axial reference plane is satisfied The size of the inclination is within the range of 0 to 2", the upper right pole connecting piece 7d is vertically nested on the upper side of the right upright column 5b, the right upper horizontal measuring pole 6d is horizontally nested on the right upper pole connecting piece 7d, and the upper telescopic The inductance sensor 9b is fixedly connected with the upper right horizontal measuring rod 6d, and the upper telescopic inductance sensor 9b is in contact with the axially installed measuring surface of the rotor under test, and the left upper column connecting piece 7c is vertically nested on the upper side of the left column 5a, and the upper left The horizontal measuring rod 6c is horizontally nested on the left upper pole connector 7c, the upper lever type inductive sensor 8b is fixedly connected with the left upper horizontal measuring rod 6c, and the upper lever type inductive sensor 8b is in contact with the radially installed measuring surface of the rotor under test; the magnetic levitation The shaft system 2 rotates at a constant speed of 6 to 10r/min. The upper telescopic inductive sensor 9b samples at equal intervals on the axial installation measurement surface of the rotor under test, and the upper lever inductance sensor 8b is installed on the radial direction of the rotor under test for measurement. Sampling at equal intervals on the surface; the number of sampling points should meet the requirements of 1000-2000 points per circle; the data sampled by the upper lever inductive sensor 8b on the radial installation measurement surface of the rotor under test is fitted by the least square circle and evaluated to determine the concentricity. The data sampled by the upper telescopic inductance sensor 9b on the axially installed measuring surface of the tested rotor is fitted by least squares plane and evaluated to obtain the verticality, combined with the radius of the axially installed measuring surface and the measured rotor and The height difference of the final assembled rotor is used to obtain the influence weight of the measured rotor on the assembled rotor coaxiality; all the rotors required for assembly are measured separately to obtain the influence weight of each rotor on the assembled rotor coaxiality; The weights of the rotors are optimized using the genetic algorithm to obtain the assembly angles of the rotors. The calculation method of the weights affecting the coaxiality of the rotors is: In the formula: C represents the concentricity of the radially installed measuring surface of the rotor under test, Indicates the eccentric angle of the fitting circle center of the radially installed measuring surface, H indicates the height difference between the rotor under test and the final assembled rotor, R indicates the radius of the axially installed measuring surface, P indicates the perpendicularity of the axially installed measuring surface of the tested rotor, θ represents the angle at which the highest point of the fitting plane of the axial installation measuring surface is located.

Claims (2)

1. an aeroengine rotor stacking assembly method based on inductance sensing with magnetic over draft support, it is characterised in that The method is: measured rotor is positioned over regulation of mental activities and adjusts on the workbench that inclines fixing；Axial reference for installation will be measured The telescopic inductance sensor in face contacts with the axially mounted datum level of measured rotor, inclines for tune；Measure Radially the lever inductance sensor of datum clamp face contacts, for regulation of mental activities with radially datum clamp face；Magnetic Floating turntable adjusts the workbench that inclines to drive measured rotor at the uniform velocity to rotate with the speed of 6～10r/min through regulation of mental activities, measures The telescopic inductance sensor of axially mounted datum level is carried out on the axially mounted datum level of measured rotor Interval sampling, the lever inductance sensor measuring radially datum clamp face is installed in the radial direction of measured rotor Equal interval sampling is carried out on datum level；Sampling number should meet often 1000～2000 points of circle；By tested turn Sampled data on the radial direction datum clamp face of son, by Least Square Circle matching, assesses offset, will The axially mounted datum level up-sampling data of measured rotor, by least square plane matching, assess inclination Amount；Size according to offset and angle, regulation regulation of mental activities adjusts the regulation of mental activities knob of the workbench that inclines；According to inclination The size of amount and angle, regulation regulation of mental activities adjusts the tune of workbench of inclining to incline knob, until regulation of mental activities adjusts the workbench that inclines full The size of foot radial reference face offset is in 0～3 μ m, and the size of axial datum level tilt quantity exists 0～2 " in the range of；The telescopic inductance sensor of axially mounted measuring surface and the axle of measured rotor will be measured To installing measuring surface contact, measure the lever inductance sensor radially installing measuring surface and measured rotor Measuring surface contact is radially installed；Magnetic floating turntable at the uniform velocity rotates with the speed of 6～10r/min, measures axially peace Telescopic inductance sensor equal interval sampling in the axially mounted measuring surface of measured rotor of dress measuring surface, The lever inductance sensor measuring radially installation measuring surface is adopted respectively in radially installation measuring surface at equal intervals Sample；Sampling number should meet often 1000～2000 points of circle；The lever radially installing measuring surface will be measured Inductance sensor installs the data of measuring surface up-sampling by Least Square Circle matching in the radial direction of measured rotor And assess concentricity；The telescopic inductance sensor of axially mounted measuring surface will be measured in measured rotor The data of axially mounted measuring surface up-sampling by least square plane matching and assess perpendicularity；In conjunction with The radius of axially mounted measuring surface and this measured rotor and the final difference in height assembling rotor, obtain this tested Rotor on assembling after rotor coaxial degree affect weights；Measure the whole rotors needed for assembling respectively, obtain Each rotor on assembling after rotor coaxial degree affect weights；Genetic algorithm is used to carry out the weights of each rotor Vector optimization, obtains the angle of assembling of each rotor, and the calculation affecting weights of rotor coaxial degree is:In formula: C represents that measured rotor radially installs the concentricity of measuring surface,Representing the eccentric angle radially installing the measuring surface matching center of circle, H represents measured rotor and finally assembles rotor Difference in height, R represents the radius of axially mounted measuring surface, and P represents the axially mounted measuring surface of measured rotor Perpendicularity, θ represents the angle at the fit Plane peak place of axially mounted measuring surface.

2. an aeroengine rotor stacking assembling device based on inductance sensing with magnetic over draft support, is characterized in that magnetic Floating axle system (2) is nested on pedestal (1) center, described magnetic floating axle system (2) by Magnetic suspension spindle (2a), Platen (2c) on workbench (2b), magnetic floating axle, magnetic floating axle pressing disc (2d), inductosyn scale (2e), Inductosyn slide rule (2f), upper permanent magnet (2g1), lower permanent magnet (2g2), upper coil (2h1), Lower coil (2h2), motor stator (2i) and rotor (2j) are constituted, and described workbench (2b) is joined Putting on magnetic floating axle on platen (2c) upper end, on magnetic floating axle, platen (2c) is arranged in Magnetic suspension spindle (2a) On upper end, Magnetic suspension spindle (2a) is arranged on magnetic floating axle pressing disc (2d) upper end, and sensing synchronizes Device slide rule (2f) is nested on magnetic floating axle pressing disc (2d) outer shroud, and inductosyn scale (2e) is solid It is scheduled on pedestal (1) center lower inside, and is positioned at the top of inductosyn slide rule (2f), on Permanent magnet (2g1) is enclosed within Magnetic suspension spindle (2a) outer shroud, and is fixed on magnetic floating axle under platen (2c) End, upper coil (2h1) is enclosed within Magnetic suspension spindle (2a) outer shroud, and it is internal to be fixed on pedestal (1), At the 5-10cm of upper permanent magnet (2g1) lower section；Lower permanent magnet (2g2) is enclosed within Magnetic suspension spindle (2a) outward On ring, and being fixed on magnetic floating axle pressing disc (2d) upper end, lower coil (2h2) is enclosed within Magnetic suspension spindle (2a) On outer shroud, and it is internal to be fixed on pedestal (1), at the 5-10cm of lower permanent magnet (2g2) top, and motor Rotor (2j) is nested on magnetic floating axle pressing disc (2d) outer shroud, and is positioned at inductosyn slide rule (2f) Bottom, motor stator (2i) admittedly fits over pedestal (1) center lower inside, and is positioned at sensing synchronization Device scale (2e) bottom and rotor (2j) are outside；Regulation of mental activities is adjusted the workbench (3) that inclines to be arranged in magnetic and is floated On axle system (2) center, four paws air spider (4) is arranged in regulation of mental activities and adjusts workbench (3) center of inclining On position；Left movement guide rail (10a) and right motion guide rail (10b) are symmetrically distributed in magnetic floating axle system (2) On the pedestal (1) of both sides, left column (5a) is arranged on left movement guide rail, and right column (5b) is installed On right motion guide rail；Left column (5a) may move adjustably suit upper left post the most successively Joint element for bar (7c) and lower-left mast connector (7a), upper left horizontal measuring staff (6c) horizontal nest is on a left side On upper prop joint element for bar (7c), upper lever formula inductance sensor (8b) and the horizontal measuring staff in upper left (6c) It is connected；Lower-left horizontal measuring staff (6a) horizontal nest on lower-left mast connector (7a), lower lever Inductance sensor (8a) is connected with the horizontal measuring staff in lower-left (6a)；On right column (5b) from top to bottom Removable adjustably suit upper right mast connector (7d) and bottom right mast connector (7b), upper right successively Laterally measuring staff (6d) horizontal nest is in upper right mast connector (7d), upper telescopic inductance sensor (9b) it is connected with the horizontal measuring staff of upper right (6d)；Bottom right horizontal measuring staff (6b) horizontal nest is at bottom right post On joint element for bar (7b), under telescopic inductance sensor (9a) and the horizontal measuring staff in bottom right (6b) be connected.