CN109823568B - Automatic measuring system for moment of airplane blade - Google Patents
Automatic measuring system for moment of airplane blade Download PDFInfo
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- CN109823568B CN109823568B CN201910104390.XA CN201910104390A CN109823568B CN 109823568 B CN109823568 B CN 109823568B CN 201910104390 A CN201910104390 A CN 201910104390A CN 109823568 B CN109823568 B CN 109823568B
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Abstract
The invention provides an automatic measuring system for the moment of an airplane blade, which comprises a testing frame, a rotating device and a moment measuring device, wherein the testing frame is provided with a testing hole; the testing frame comprises a testing frame, a testing frame bottom plate and a mandrel for fixing the blade to be tested, the testing frame is fixed on the upper bottom surface of the testing frame bottom plate, and the mandrel is fixed on the testing frame and rotates along a rotating shaft which is horizontal to the ground; the rotating device comprises a rotating bracket, a rotating bearing and a rotating driving device, the rotating bracket is in floating connection with the bottom plate of the test frame, the inner ring of the rotating bearing is fixedly connected with the rotating bracket, and the rotating driving device drives the rotating bracket to rotate by a rotating shaft which is vertical to the ground; the moment testing device comprises a balance testing plate and sensors which are fixedly connected with the outer ring of the rotary bearing, the sensors comprise front sensors and rear sensors which are arranged on the same horizontal plane in the front and at the back, and the lower bottom surface of the balance testing plate is in contact with the sensors.
Description
Technical Field
The invention relates to a helicopter propeller blade testing and balancing technology, in particular to an automatic measuring system for the moment of an airplane blade.
Background
The problem of balancing the helicopter propellers is directly related to the shafting vibration of the airplane, the vibration of the airframe and the flight safety. Therefore, how to solve the problem of balancing the propeller in the manufacturing process of the propeller is particularly important. The propeller must be balanced and measured to be assembled on the airplane, so that the flight stability and the flight safety of the helicopter are ensured.
Standard helicopter propeller blades consist of a hub and blades, which can be measured for overall balance after finishing and assembly. However, the hub and the blades of the propeller are cast and machined separately, so that static balance measurement needs to be carried out on the hub and the blades respectively. The blades are not on the central line of the propeller shaft of the propeller, and the appearance is irregular. In order to control the difference value of the moments of different blades arranged on the same propeller hub within the designed maximum allowable range and simultaneously achieve the interchangeability of the blades, the blades must be accurately measured in static balance, the balance of the blade moments can be regarded as the basic condition of the balance of the propeller, and the balance measuring method and the maximum allowable unbalance degree of the blade moments are directly related to the balance of the whole propeller. Therefore, a high-efficiency and high-precision measurement method for the blade moment is needed to ensure the reliable implementation of the static balance adjustment of the blade.
As shown in FIG. 12, the balancing moment of the blade is a screwThe product of the total weight of the propeller and the distance (eccentricity) of the center of mass of the propeller to the center of rotation of the propeller. The blade moment is composed of a blade large axis moment (blade large moment) and a blade small axis moment (blade small moment), wherein the blade large moment is the product of the weight of the blade and the distance between the center of mass of the blade and the rotation center in the direction of the blade installation axis, and the blade small moment is the product of the weight of the blade and the distance between the center of mass of the blade and the blade installation axis. In FIG. 12G is the center of mass of the blade, MOGIs the moment of the blade, MOXIs a large moment of the blade, MOYThe blade is small in moment. Imbalance value of a blade the deviation of the blade from the standard blade balancing moment is generally required to be ensured to be smaller than the maximum allowable imbalance M.
MOG＝GeOG
The static balance measurement of the propeller blades is the measurement of the mass, the large moment and the small moment of the single blades. There are generally two test principles for blade static balance measurement: (1) the absolute method measurement principle is a balance measurement method for directly measuring the blade to be measured; (2) the principle of comparison measurement is a balance measurement method for comparing a measured blade with a standard blade. The value of a standard blade is usually determined by absolute measurement, and then the moment balance measurement of the blade is completed by a comparison method.
The blade moment balance measurement can be divided into 2 methods of a balance moment balance measurement method and a sensor moment balance measurement method according to different selected means. At present, balance moment balance measurement methods are still largely adopted at home and abroad, the numerical value of the paddle is measured through weights, the measurement of the paddle moment is realized through the positions of hanging standard weights and moving the weights by utilizing the balance principle, and the method has the advantages of low test precision, low test efficiency, large influence of personnel operation factors and difficult guarantee of test repeatability; with the development of testing technology, a sensor torque balance measuring method appears, and torque data of the blade is directly measured by using a force transducer, but the existing blade torque sensor testing method still has the defects of low testing precision, high randomness and poor repeatability in single measurement.
Therefore, in the field of blade moment testing and balancing at present, the problems of low testing precision, poor repeatability, low testing efficiency and large influence of personnel operation on blade moment testing exist, and the blade moment is difficult to be measured and adjusted efficiently and accurately.
Disclosure of Invention
The invention aims to provide an automatic measuring system for the moment of an airplane blade, which can realize high-efficiency and high-precision measurement of large moment and small moment of the blade.
The technical scheme for realizing the purpose of the invention is as follows: an automatic measuring system for the moment of an airplane blade comprises a test frame, a rotating device and a moment measuring device; the testing frame comprises a testing frame, a testing frame bottom plate and a mandrel for fixing the blade to be tested, the testing frame is fixed on the upper bottom surface of the testing frame bottom plate, and the mandrel is fixed on the testing frame bottom plate and rotates along a rotating shaft which is horizontal to the ground; the rotating device comprises a rotating bracket, a rotating bearing and a rotating driving device, the rotating bracket is in floating connection with the bottom plate of the test frame, the inner ring of the rotating bearing is fixedly connected with the rotating bracket, and the rotating driving device drives the rotating bracket to rotate by a rotating shaft vertical to the ground; the moment testing device comprises a balance testing plate and sensors which are fixedly connected with the outer ring of the rotary bearing, the sensors comprise front sensors and rear sensors which are arranged on the same horizontal plane in the front and at the back, and the lower bottom surface of the balance testing plate is in contact with the sensors.
By adopting the system, the test frame further comprises a test frame, a rotating device connecting seat, a profiling tool, a tool mounting plate, a locking round nut, a positioning pin, a fixing sleeve, a locking positioning pin and an index plate; the test frame is fixed in bottom surface on the test jig bottom plate, the rotary device connecting seat sets up in bottom surface under the test jig bottom plate, set up on the rotating bracket and connect the stabilizer blade with rotary device connecting seat matched with test jig, the fixed sleeve is fixed in on the test frame up end, frock mounting panel one end is fixed in the dabber and is parallel with the test jig bottom plate, the profile modeling frock sets up in the up end other end of frock mounting panel, the graduated disk sets up on fixed sleeve rear side wall, the dabber passes the through-hole of fixed sleeve and graduated disk, locking round nut overlaps in the dabber, the locating pin sets up downthehole in the dabber locating pin, the locking locating pin passes fixed sleeve and dabber cooperation.
By adopting the system, the torque measuring device comprises a balance testing frame, a torque testing device, a safety protection device, an elastic supporting device and a system balancing device; the balance test frame comprises a balance test plate, a front rotary knife edge seat, a rear rotary knife edge and a rear rotary knife edge seat; the upper end of the rear rotary knife edge is fixed on the lower end surface of the balance test board, and the lower end of the rear rotary knife edge is in contact with the groove of the rear rotary knife edge seat; the moment testing device comprises sensor support legs, a sensor upper cushion block, a front sensor, a rear sensor and a sensor base plate, wherein the sensor support legs are fixed on the lower bottom surface of the balance testing plate; the safety protection device comprises an adjustable supporting seat, a jacking screw rod, a hand wheel and an adjustable supporting block, wherein the adjustable supporting seat is fixed on the upper end surface of the platform close to the moment testing device, the adjustable supporting block is fixed, a gap is formed between the adjustable supporting block and the adjustable supporting seat, the hand wheel is arranged in the gap, the jacking screw rod penetrates through the adjustable supporting seat, the hand wheel and the adjustable supporting block, the jacking screw rod is connected with the adjustable supporting block through an oil bearing, and the jacking screw rod is in threaded connection with the hand wheel; the elastic supporting device comprises a supporting seat and a spring damping vibration isolator, the supporting seat is fixed on the upper end face of the platform and is far away from the torque testing device, the lower end of the spring damping vibration isolator is fixed on the supporting seat, and the upper end of the spring damping vibration isolator is located below the balance testing plate.
By adopting the system, the torque measuring device also comprises a system balancing device, and the system balancing device comprises a stepping motor, an installation box body, a screw rod, a bearing seat, a balancing weight and a fixed seat; the installation box is fixed in the nearly elastic supporting device department of terminal surface under the balanced survey test panel, and step motor sets up in the installation box outside, and the lead screw sets up in the installation box, and lead screw one end is connected and the other end is done through the bearing with being fixed in the fixed of installation box with step motor stretches into the rotatory output shaft of installation box and is connected, balancing weight and lead screw threaded connection.
The system is adopted, and the lifting protection device is further included and comprises a left lifting table and a right lifting table, wherein the left lifting table and the right lifting table respectively comprise a guide rod, a turbine lifter and a linear bearing; the turbine lifter is arranged in a lifter through hole of the platform, the linear bearing is fixed on the lower bottom surface of the platform, and the guide rod penetrates through the turbine lifter and is connected with the linear bearing; the uppermost ends of the guide rods in the left lifting platform and the right lifting platform are always flush and the guide rods are positioned below the test rack.
Compared with the prior art, the invention has the following advantages: (1) the testing precision is high, single random measurement of the moment of the traditional paddle is changed into multiple dynamic fixed-point measurements by adjusting the paddle to be in a plurality of working positions in the testing process, the mass deviation of the paddle to be tested is obtained through difference calculation, the testing error of a system is reduced, the testing precision of the moment of the paddle is greatly improved, and meanwhile, the high-precision balancing of the balance moment of the paddle is realized through theoretical calculation; (2) the system has good repeatability, the servo motor is adopted to control the system to realize the adjustment of four testing stations of the paddle, the high-precision positioning of the testing position of the paddle is realized, the error caused by the operation of personnel is avoided, the station consistency of the testing system is good, and the repeatability of the system testing can be effectively ensured; (3) the test device has the advantages that the automation degree is high, the test of the blade moment is realized by adopting system control, the lifting of the test frame, the movement of the servo motor and the system balance are realized by the system control, the participation of personnel is reduced in the test process, the automation level of the system is improved, and the blade moment test efficiency is improved.
The invention is further described below with reference to the accompanying drawings.
Drawings
FIG. 1 is a schematic structural diagram of an automatic measuring system for the moment of an airplane blade.
Fig. 2 is a left side view of fig. 1.
Fig. 3 is a side view of fig. 1.
Fig. 4 is a schematic diagram of the overall assembly structure of the blade to be measured and the blade moment automatic measurement system.
Fig. 5 is a schematic structural diagram of the mounting and positioning mechanism.
Fig. 6 is a schematic structural view of the balance testing jig 31.
Fig. 7 is a detailed view of the safety shield apparatus of fig. 1.
Fig. 8 is a detailed view of the balancing apparatus of the system of fig. 1.
FIG. 9 is a schematic diagram of an aircraft blade moment test of the present invention.
FIG. 10 is a schematic view of the centroid test in the height direction of the aircraft blade of the present invention.
FIG. 11 is a schematic diagram of the calculation principle of the airplane blade moment test.
FIG. 12 is a schematic view of the blade balancing moment calculation.
Detailed Description
With reference to fig. 1, 2, 3, and 4, an automatic measuring system for a blade moment of an aircraft includes a testing jig 1, a rotating device 2, a moment measuring device 3, a lift protecting device 4, and a testing platform 5. The test frame 1 is used for mounting and fixing the blade to be tested; the rotating device 2 is used for realizing automatic rotation of the torque of the paddle to be tested and realizing adjustment of a paddle testing station; the torque measuring device 3 is used for measuring the blade balance torque and realizing the automatic balance of the test system; the lifting protection device 4 is used for realizing safe lifting of the test frame 1 and avoiding damage to a test sensor caused by direct impact when a blade to be tested is installed; the test platform 5 is used for bearing the test frame 1, the rotating device 2, the moment measuring device 3, the lifting protection device 4 and the blade to be tested, and is an installation support platform of the overall measurement assembly and adjustment device.
With reference to fig. 1, 2 and 5, the test jig 1 comprises a test jig frame 11, a lifting protection device connecting seat 12, a test jig bottom plate 13, a rotating device connecting seat 14, a profiling tool 15, a tool mounting plate 16 and a mounting and positioning mechanism 17; the mounting and positioning mechanism 17 comprises a locking round nut 171, a positioning pin 172, a mandrel 173, a fixing sleeve 174, a locking positioning pin 175 and an indexing disc 176. The test frame 11 is fixed on the upper and lower surfaces of the test frame base plate 13. The two connection seats 12 are disposed and fixed to the left and right ends of the lower end surface of the test frame 11 in fig. 1. The rotating device connecting seat 14 is disposed on the bottom surface of the bottom plate 13 of the testing jig. The rotating bracket 21 is provided with a test jig connecting leg 22 which is matched with the rotating device connecting seat 14. The lower end surface of the fixing sleeve 174 is fixed to the upper end surface of the test frame 11, and the fixing sleeve 174 is provided with a projection higher than the test frame 11, the projection being provided with a through hole from an axis in the left-right direction of fig. 1. One end of the tool mounting plate 16 is fixed on the left side wall of the fixing sleeve 174 and is parallel to the test frame bottom plate 13. The profile modeling frock 15 is the same with the paddle appearance that awaits measuring for bear the paddle, and profile modeling frock 15 sets up in the other end of frock mounting panel 16 up end. An indexing disk 176 is disposed on the rear sidewall of the fixed sleeve 174. The spindle 173 penetrates through the through holes of the fixing sleeve 174 and the indexing disc 176, the locking round nut 171 is sleeved on the spindle 173, the positioning pin 172 is arranged in the positioning pin hole in the spindle 173, four locking positioning pin holes are uniformly distributed in the spindle 173 along the circumferential direction, the locking positioning pin 175 penetrates through the fixing sleeve 174 to be matched with the spindle 173, and when the spindle 173 rotates to a certain working position, the locking positioning pin 175 is inserted into the locking positioning pin hole and locks the spindle 173.
The test frame 11 is a mounting bracket for the blade to be tested, the lifting protection device connecting base 12 is arranged below the test frame for realizing the connection with the lifting protection device 4, the test frame bottom plate 13 is arranged below the test frame 11 and fixedly connected with the test frame 11, the rotating device connecting base 14 is arranged below the test frame bottom plate 12 for realizing the connection with the rotating device 2, the tool mounting plate 16 is fixed with the mounting and positioning mechanism 17, the profiling tool 15 is mounted on the tool mounting plate 16 for realizing the blade support, the mounting and positioning mechanism 17 is mounted on the test frame 11 through a mounting hole and can rotate around the axis of the mounting hole relative to the test frame 11, the locking round nut 171 is sleeved on the mandrel 173, the product is connected with the blade to be tested through threads during the product mounting for realizing the mounting and fixing of the blade to be tested, and the positioning pin 172 is arranged in the mandrel 173, the positioning device is used for positioning the mounting posture of the paddle to be tested, the mandrel 173 is a mounting positioning shaft of the paddle to be tested, the end face of the mandrel 173 is a positioning reference face of the paddle to be tested, the mounting positioning of the paddle to be tested is realized through the axis and the end face, the fixing sleeve 174 is used for realizing the connection of the mounting positioning mechanism 17 and the test frame 11, the locking pin 175 is used for locking the mounting positioning mechanism 17, the dividing plate 176 is used for confirming the rotation angle of the mounting positioning mechanism relative to the test frame 11, and the paddle is prevented from rotating relative to the test frame 11 around the mounting hole under a specific test station.
Referring to fig. 1 and 2, the rotating device 2 includes a rotating bracket 21, a rotating bearing 23, and a rotation driving device 24. The rotary bracket 21 is connected with the bottom plate 13 of the test frame in a floating way, the inner ring of the rotary bearing 23 is fixedly connected with the rotary bracket 21, and the rotary driving device 24 is fixedly connected with the rotary bracket 21 by a rotary shaft vertical to the ground. The test jig connecting support leg 22 is arranged above the rotating bracket 21 and used for being connected with a test jig, the rotating bearing 23 is arranged below the rotating bracket, the inner ring of the bearing is fixed with the rotating bracket 21, the outer ring of the bearing is fixedly connected with the torque measuring device 3, the rotating driving device 24 is arranged below the rotating bracket, and the rotating driving device drives the rotating bracket to rotate around the axis of the rotating bearing 23, so that the test station of the blade to be tested is adjusted, and driving power is provided for the rotation of the rotating device 2.
With reference to fig. 1, 2, 6, 7 and 8, the torque measuring device 3 includes a balance testing jig 31, a torque testing device 32, a safety protection device 33, an elastic supporting device 34 and a system balancing device 35. The upper part of the balance test frame 31 is fixedly connected with the outer ring of the rotary bearing in the rotary device 2 to bear the weight and load of all parts above the balance test frame, the torque test device 32 is arranged below the balance test frame 31 and used for measuring the torque of the blade, the safety protection device 33 and the elastic support device 34 are symmetrically distributed below the balance test frame 31, the safety protection device 33 is used for preventing the test sensor from being damaged by overlarge load in the contact process of the test frame 1 and the rotary device 2, the elastic support device 34 is used for stabilizing the balance test frame 31 and preventing the balance test frame 31 from overturning, the system balance device 35 is fixed on the balance test frame 31, and the balance of the system quality is realized by adjusting the position of a balancing weight of the system balance test frame 31.
The balance testing frame 31 comprises a balance testing plate 311, a front rotary knife edge 312, a front rotary knife edge seat 313, a rear rotary knife edge 314 and a rear rotary knife edge seat 315. The front rotary tool opening seat 313 and the rear rotary tool opening seat 315 are arranged on the platform 51 in a front-back manner, the upper end of the front rotary tool edge 312 is fixed on the lower end surface of the balance test plate 311, the lower end of the front rotary tool opening seat is in groove contact with the front rotary tool opening seat 313, and the upper end of the rear rotary tool edge 314 is fixed on the lower end surface of the balance test plate 311, and the lower end of the rear rotary tool edge 314 is in groove contact with the rear rotary tool opening seat 315. The balance test board 311 can rotate relative to the connecting line of the contact positions of the front rotary knife edge 312, the front rotary knife edge seat 313, the rear rotary knife edge 314 and the rear rotary knife edge seat 315 under the action of the front rotary knife edge 312, the front rotary knife edge seat 313, the rear rotary knife edge 314 and the rear rotary knife edge seat 315.
The moment testing device 32 includes a sensor support 321, a sensor upper pad 322, a front sensor 323, a front sensor attachment plate 324, a rear sensor 325, a rear sensor attachment plate 326, a sensor pad 327, a left rail and slide 328, and a right rail and slide 329. The sensor support leg 321 is fixed on the bottom surface of the balance test board 311, the sensor upper cushion block 322 is fixed on the lower end of the sensor support leg 321, the front sensor 323 and the rear sensor 324 are arranged on the front end and the rear end of the sensor cushion plate 327 in fig. 1 through a sensor connecting plate, the sensor cushion plate 327 can move back and forth on the platform 51, and the lower part of the sensor cushion plate 327 is fixedly connected with the left guide rail and the slide block 328, the right guide rail and the slide block 329. The sensor support 321 enables the load from the balance testing frame 31 and the upper part thereof to act on the front sensor 323 and the rear sensor 325 which are arranged in parallel through the sensor upper backing plate 322, and the front sensor 323 and the rear sensor 325 realize the measurement of the moment of the blade to be measured by measuring the load acting on the front sensor 323 and the rear sensor 325. The sensor backing plate 327 can slide back and forth along the guide rail to adjust the position of the sensor and protect the sensor, thereby avoiding damage to the sensor caused by excessive load acting on the sensor during the installation of the test system.
The safety protection device 33 comprises an adjustable support base 331, a jacking screw 332, a hand wheel 333 and an adjustable support block 335. The adjustable supporting seat 331 is fixed on the upper end surface of the platform 51 near the moment testing device 32, the adjustable supporting block 335 is fixed and a gap is arranged between the adjustable supporting seat 331 and the hand wheel 333, the jacking screw rod 332 penetrates through the adjustable supporting seat 331, the hand wheel 333 and the adjustable supporting block 335, the jacking screw rod 332 is connected with the adjustable supporting block 335 through the oil-containing bearing 334, and the jacking screw rod 332 is in threaded connection with the hand wheel. The lifting movement of the lifting screw 332 can be realized by rotating the hand wheel 333, and when the lifting screw 332 is in a lifting state, the balance test frame is lifted, so that the sensor support leg 321 is separated from the sensor.
The elastic supporting device 34 comprises a supporting seat 341 and a spring damping vibration isolator 342. The supporting seat 341 is fixed on the upper end surface of the platform 51 far away from the moment testing device 32, the lower end of the spring damping vibration isolator 342 is fixed on the supporting seat 341, and the upper end is located below the balance testing board 311. When the safety protection device 33 is in the upper station state, the jacking screw 332 of the safety protection device 33 is in contact with the balance testing jig 31, the balance testing jig 31 rotates around the axis of the knife edge of the balance testing jig, the other side of the knife edge of the balance testing jig is in contact with the elastic supporting device 34, the spring damping vibration isolator 342 is compressed, and the supporting seat 341 is arranged below the spring damping vibration isolator to support the spring damping vibration isolator.
The system balancing device 35, the system balancing device 35 includes a stepping motor 351, a mounting box 353, a lead screw 354, a bearing seat 355, a counterweight 356, and a fixing seat 357. The mounting box 353 is fixed at the position of the lower end face of the balance test board 311 close to the elastic supporting device 34, the stepping motor 351 is arranged outside the mounting box 353, the screw rod 354 is arranged in the mounting box 353, one end of the screw rod 354 is connected with a rotating output shaft of the stepping motor 351 extending into the mounting box 353, the other end of the screw rod 354 is connected with a fixing device 357 fixed in the mounting box 353 through a bearing, and the balancing weight 356 is in threaded connection with the screw rod 354. The rotation of the lead screw 354 around the axis can be realized by the driving of the stepping motor 351 and the stepping motor reducer 352, and the balancing weight 356 is in T-shaped threaded connection with the lead screw 354 and can move along the axis direction of the lead screw 354, so that the system is balanced.
With reference to fig. 1, the lifting protection device 4 includes a left lifting platform 41, a linkage shaft 42, a lifting stepping motor 43, a turbine speed reducer 44 and a right lifting platform 45, the left lifting platform 41 and the right lifting platform 45 are arranged in bilateral symmetry and can move up and down to realize the conversion of the stations of the test system, the linkage shaft is used for realizing the linkage of the left lifting platform 41 and the right lifting platform 45 to ensure the consistency of the movement speed and the movement position of the left lifting platform and the right lifting platform, and the lifting stepping motor 43 and the turbine speed reducer 44 drive the rotation of the linkage shaft. The left lifting platform 41 comprises a left guide rod 411, a left worm gear lifter 412, a left lifter mounting plate 413, a left connecting plate 414 and a left linear bearing 415, the left lifter mounting plate 413 is mounted below the testing platform 5, the left worm gear lifter 412 is fixed below the left lifter mounting plate 413, the left connecting plate 414 is arranged below the worm gear lifter 412, the left linear bearing 415 is fixedly connected with the testing platform 5, the left guide rod 411 can move up and down under the action of the left worm gear lifter 412 and the left linear bearing 415, and station conversion of the testing system is achieved. The right lifting platform 45 comprises a right guide rod 451, a right worm gear lift 452, a right lift mounting plate 453, a right connecting plate 454 and a right linear bearing 455, and the connection mode is the same as that of the left lifting platform 41. The lifting stepping motor 43 is fixed on the platform 51, the turbine speed reducer 44 is connected with an output shaft of the lifting stepping motor 43, the input end of the linkage shaft 42 is connected with the turbine speed reducer 44, and the two output ends are respectively in threaded connection with the two guide rods.
Referring to fig. 1, the testing platform 5 includes a platform 51, a frame 52, and leveling feet 53, wherein the platform 51 is disposed above the frame 52, and the leveling feet 53 are disposed below the frame 52.
The testing jig is characterized in that the lower portion of the testing jig 1 is in floating connection with the rotating device 2 and the lifting protection device 4, when the lifting protection device 3 is located at an upper station, the testing jig 1 is separated from the rotating device 2, the testing jig 1 is in contact with the lifting protection device 4, and the testing jig 1 is supported by the lifting protection device 4. When the lifting protection device 4 is positioned at a lower station, the test frame 1 is separated from the lifting protection device 4, the test frame 1 is in contact with the rotating device 2, and the test frame 1 is supported by the rotating device 2, so that the torque of the blade to be measured is measured. The rotating device 2 is arranged on the moment measuring device 3, the rotating device 2 can rotate relative to the moment measuring device to realize the adjustment of a testing station of the blade to be tested, the moment measuring device 3 is arranged on the testing platform 4, and the lifting protection device 4 is fixedly arranged on the testing platform.
The testing method of the system comprises preparation work, adjustment and installation work, testing work and ending work.
(1) Preparation work:
step 1.1, adjusting a rotating device to align a rotating bracket with a test rack, and ensuring that the test rack can be reliably contacted with the rotating device;
step 1.2, installing a profiling tool of the blade in place, adjusting a system balancing device, ensuring that the measured values of 4 test station position sensors in the no-load state of the system are basically consistent, and testing and recording the measured values of the 4 test station position sensors in the no-load state;
and 1.3, adjusting the lifting protection device to an upper station to enable the test frame to be in contact with the lifting protection device.
(2) Adjusting and installing:
2.1, adjusting the installation angle of the mandrel to align the scale lines of the mandrel with the 0-degree scale lines of the index plate, and locking and fixing the mandrel through a locking pin;
step 2.2, connecting the mounting interface of the paddle with a mandrel of a mounting and positioning mechanism, and determining the mounting posture of the paddle through a positioning pin;
step 2.3, relatively fixing the locking nut and the blade through threaded connection;
and 2.4, adjusting the lifting protection device to a lower station, separating the test frame from the lifting protection device, and contacting the test frame with the rotating device.
(3) And (3) testing work:
3.1, slowly adjusting the safety protection device to separate a jacking screw of the safety protection device and a spring damping vibration isolator of the elastic supporting device from the balance test frame, so that the support legs of the sensor are in contact with the upper connecting plate of the sensor, and the system enters a test state;
step 3.2, measuring the large moment and the small distance of the blade: the rotation of the rotating bracket relative to the balance test frame is realized through the rotating driving device, the acting force of the paddle on the sensor in 4 azimuth states is obtained, and the large moment and the small moment of the paddle around the rotating shaft of the propeller are obtained through data acquisition and difference calculation; the included angle between the connecting lines of the adjacent working positions and the center is 90 degrees;
step 3.3, measuring the mass center of the blade in the height direction: the rotary bracket is adjusted to a second station through a rotary driving device, namely the rotary bracket in an initial test state rotates for 90 degrees around a rotary shaft of the rotary bracket, so that the installation axis of the paddle is parallel to the connecting line of front and rear knife edge contact points of the balance test frame, the scale line of the mandrel is respectively aligned with 90 degrees, 180 degrees and 270 degrees of the dividing plate through the rotary installation positioning mechanism, the measured values of the sensors at 4 angular positions are obtained, and the barycenter parameter of the paddle in the height direction is obtained through data acquisition and difference value calculation.
(4) Ending work:
step 4.1, adjusting the rotary bracket to an initial position through the rotary driving device, aligning the lifting protection device connecting seat of the test jig with the lifting protection device, and ensuring that the lifting protection device connecting seat and the lifting protection device can be an integral body;
step 4.2, adjusting the safety protection device to separate the sensor support legs from the upper sensor connecting plate;
and 4.3, taking down the blade to be tested to finish the test.
With reference to fig. 9, 10 and 11, the testing principle of the present invention is detailed as follows:
(1) the test mechanism is as follows: the measured paddle rotates around a rotating shaft in the vertical direction of the test system to realize the adjustment of the test station of the measured paddle, the relative position of the mass center of the measured paddle relative to the rotating shaft of the test system can be obtained by measuring the measured values of the sensors in the states of four stations and calculating the difference value, and the large moment and the small moment of the paddle are obtained by calculation; and meanwhile, the measured paddle rotates around the axis of the paddle in the horizontal direction, and the measurement of the centroid parameter of the paddle in the height direction is realized by adjusting the four angle positions.
(2) The moment calculation method comprises the following steps: the test system is in a balanced stable state, a moment balance equation acting on the moment measuring device can be obtained according to a moment balance principle, the relative displacement of the mass center of the tested blade relative to a rotating shaft of the test system is obtained by measuring the change condition of a load acting on the sensor, the mass center positions in the large moment direction and the small moment direction are obtained, and the large moment and the small moment of the tested blade can be obtained by combining the relative position relation between a test reference and a rotating shaft.
(3) Calculation of height-direction centroid: when the paddle rotates around the installation axis of the paddle, a moment balance equation of a test system can be obtained at any one angular position, and the measurement of the height direction of the paddle can be realized by measuring the measurement values of the sensors at 4 angular positions and calculating the difference value.
The invention realizes the accurate measurement of the large moment and the small moment of the airplane blade by rotating the blade to be measured around the axis in the vertical direction through a plurality of fixed point tests, greatly improves the test precision of the moment of the existing airplane blade, and provides a reliable technical means for improving the static balance adjustment of the airplane blade; the full-automatic accurate positioning of the paddle testing station is realized by adopting system control, the operation error of manual alignment is avoided, the testing repeatability of the system is ensured, the testing efficiency is improved, and the automation level of the testing system is improved; meanwhile, the paddle to be measured rotates around the axis in the horizontal direction, and high-precision measurement of the mass center of the airplane paddle in the height direction is achieved through multiple times of measurement of specific angles; the paddle to be tested can reliably ensure the mounting and positioning of the paddle to be tested through the mounting and positioning mode of the mandrel, the round nut and the positioning pin, the deformation under the action of gravity is prevented through the profiling tool, and meanwhile, the mounting and the supporting of a product are facilitated; the system balancing device is adopted to realize the tare weight balancing of the system, so that the loads acting on the sensor under the states of 4 test stations of the paddle are basically consistent, the measuring range of the sensor is favorably reduced, and the test precision of the system is improved.
Practical measurement example
The mass is 10kg, and the length is Z8 series tail rotor blade of 2m, adopts traditional balance moment test method and high accuracy aircraft paddle moment test system to carry out the technological comparison:
Claims (8)
1. an automatic measuring system for the moment of an airplane blade is characterized by comprising a testing frame (1), a rotating device (2) and a moment measuring device (3); wherein
The test frame (1) comprises a test frame (11), a test frame bottom plate (13) and a mandrel (173) for fixing the blade to be tested,
the testing frame (11) is fixed on the upper bottom surface of the testing frame bottom plate (13),
the mandrel (173) is arranged on the test frame (11) and rotates along a rotating shaft horizontal to the ground;
the rotating device (2) comprises a rotating bracket (21), a rotating bearing (23) and a rotating driving device (24),
the rotary bracket (21) is connected with the bottom plate (13) of the test frame in a floating way,
the inner ring of the rotary bearing (23) is fixedly connected with the rotary bracket (21),
a rotating shaft of the rotating driving device (24) vertical to the ground is connected with the rotating bracket (21);
the torque measuring device (3) comprises a balance test board (311) fixedly connected with the outer ring of the rotating bearing (23) and a sensor,
the sensors comprise a front sensor (323) and a rear sensor (325) which are arranged in the same horizontal plane and in the front and the rear,
the lower bottom surface of the balance test plate (311) is contacted with the sensor;
the test rack (1) also comprises a rotating device connecting seat (14), a profiling tool (15), a tool mounting plate (16), a locking round nut (171), a positioning pin (172), a fixing sleeve (174), a locking positioning pin (175) and an index plate (176); wherein
The rotating device connecting seat (14) is arranged on the lower bottom surface of the testing frame bottom plate (13),
the rotating bracket (21) is provided with a test frame connecting support leg (22) matched with the rotating device connecting seat (14), the fixed sleeve (174) is fixed on the upper end surface of the test frame (11),
one end of the tool mounting plate (16) is fixed on the mandrel (173) and is parallel to the testing frame bottom plate (13),
the profiling tool (15) is arranged at the other end of the upper end surface of the tool mounting plate (16),
the index plate (176) is arranged on the rear side wall of the fixed sleeve (174),
the mandrel (173) passes through the through holes of the fixed sleeve (174) and the indexing disc (176),
a locking round nut (171) is sleeved on the mandrel (173),
the positioning pin (172) is arranged in a positioning pin hole in the mandrel (173),
the locking positioning pin (175) penetrates through the fixing sleeve (174) to be matched with the mandrel (173) so that the mandrel (173) is fixed on the working position.
2. The system of claim 1, wherein the mandrel (173) has four locking dowel holes evenly distributed circumferentially, the locking dowel (175) mating with the locking dowel holes.
3. The system according to claim 1, characterized in that the moment measuring device (3) comprises a balance test frame (31), a moment test device (32), a safety protection device (33), an elastic support device (34), a system balancing device (35); wherein
The balance testing frame (31) comprises a balance testing plate (311), a front rotary knife edge (312), a front rotary knife edge seat (313), a rear rotary knife edge (314) and a rear rotary knife edge seat (315); wherein
The front rotary tool opening seat (313) and the rear rotary tool opening seat (315) are arranged on the platform (51) in the front-back direction,
the upper end of the front rotary knife edge (312) is fixed on the lower end surface of the balance test plate (311), the lower end of the front rotary knife edge is contacted with the groove of the front rotary knife edge seat (313),
the upper end of the rear rotary knife edge (314) is fixed on the lower end surface of the balance test plate (311), and the lower end of the rear rotary knife edge is in contact with a groove of the rear rotary knife edge seat (315);
the moment testing device (32) comprises a sensor support leg (321), a sensor upper cushion block (322), a front sensor (323), a rear sensor (325) and a sensor cushion plate (327),
the sensor feet (321) are fixed on the lower bottom surface of the balance test plate (311),
the sensor upper cushion block (322) is fixed at the lower end of the sensor supporting leg (321),
the front sensor (323) and the rear sensor (325) are arranged on the sensor backing plate (327) through a sensor connecting plate,
the sensor pad (327) moves back and forth on the platform (51);
the safety protection device (33) comprises an adjustable supporting seat (331), a jacking screw rod (332), a hand wheel (333) and an adjustable supporting block (335),
the adjustable supporting seat (331) is fixed on the upper end surface of the platform (51) near the moment testing device (32),
the adjustable supporting block (335) is fixed and a gap is arranged between the adjustable supporting block and the adjustable supporting seat (331),
a hand wheel (333) is arranged in the gap,
the jacking screw rod (332) passes through the adjustable supporting seat (331), the hand wheel (333) and the adjustable supporting block (335),
the jacking screw rod (332) is connected with the adjustable supporting block (335) through an oil bearing (334),
the jacking screw rod (332) is in threaded connection with a hand wheel;
the elastic supporting device (34) comprises a supporting seat (341) and a spring damping vibration isolator (342),
the supporting seat (341) is fixed on the upper end surface of the platform (51) far away from the moment testing device (32),
the lower end of the spring damping vibration isolator (342) is fixed on the supporting seat (341) and the upper end is positioned below the balance test board (311).
4. The system according to claim 3, characterized in that the moment measuring device (3) further comprises a system balancing device (35), the system balancing device (35) comprising a stepping motor (351), a mounting box (353), a lead screw (354), a bearing seat (355), a balancing weight (356), a fixed seat (357); wherein
The mounting box body (353) is fixed at the position, close to the elastic supporting device (34), of the lower end face of the balance test board (311), the stepping motor (351) is arranged outside the mounting box body (353),
the screw rod (354) is arranged in the mounting box body (353),
one end of the screw rod (354) is connected with a rotating output shaft of a stepping motor (351) extending into the mounting box body (353), and the other end is connected with a fixed seat (357) fixed in the mounting box body (353) through a bearing,
the balancing weight (356) is in threaded connection with the screw rod (354).
5. A system according to claim 3, characterised in that the platform (51) is provided with linear guides from front to rear, the guides being provided with slides on which the sensor pads (327) are provided.
6. The system according to claim 1, further comprising a lift protection device (4), the lift protection device (4) comprising a left lift table (41), a right lift table (45), the left lift table (41) and the right lift table (45) each comprising a guide rod, a turbine lift, a linear bearing; wherein
The turbine lifter is arranged in the lifter through hole of the platform (51),
the linear bearing is fixed on the lower bottom surface of the platform (51),
the guide rod penetrates through the turbine lifter and is in threaded connection with the turbine lifter,
the guide rod is also connected with the linear bearing;
the uppermost ends of the guide rods in the left lifting platform (41) and the right lifting platform (45) are always flush and the guide rods are positioned below the test rack (1).
7. The system according to claim 6, characterized in that the lifting protection device (4) further comprises a linkage shaft (42), a lifting stepping motor (43), a turbine reducer (44); wherein
The lifting stepping motor (43) is fixed on the platform (51),
the turbine speed reducer (44) is connected with an output shaft of the lifting stepping motor (43),
the input end of the linkage shaft (42) is connected with the turbine speed reducer (44) and the two output ends are respectively in threaded connection with the two guide rods.
8. System according to claim 6 or 7, characterized in that the lower end face of the test frame (11) is provided with a lifting protection device connection seat (12) matching with the guide rod.
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| CN201910104390.XA CN109823568B (en) | 2019-02-01 | 2019-02-01 | Automatic measuring system for moment of airplane blade |
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| CN201910104390.XA CN109823568B (en) | 2019-02-01 | 2019-02-01 | Automatic measuring system for moment of airplane blade |
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| CN112161744B (en) * | 2020-09-29 | 2022-06-21 | 南京乾利合科技有限责任公司 | Rotary high-precision moment balance |
| CN114018476B (en) * | 2020-12-25 | 2022-09-30 | 南京乾利合科技有限责任公司 | Air suspension rotary frame of static balancing machine and air suspension static balancing machine |
| CN113148225B (en) * | 2021-04-20 | 2022-11-22 | 中国直升机设计研究所 | Testing device and testing method for fixing and rotating helicopter blades |
Citations (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR1116466A (en) * | 1953-11-16 | 1956-05-08 | Doman Helicopters | Device for measuring the aerodynamic moment of step of an aerodynamic structure |
| CA2434487A1 (en) * | 2002-07-17 | 2004-01-17 | Snecma Moteurs | Process for distributing turbomachine rotor blades |
| CN1844872A (en) * | 2005-12-29 | 2006-10-11 | 南京航空航天大学 | Optical fiber grating sensing system for measuring distribution load on rotating wings |
| CN102944361A (en) * | 2012-12-06 | 2013-02-27 | 哈尔滨工业大学 | Device for calibrating dynamic balance parameter of helicopter rotor blade |
| CN103063363A (en) * | 2012-12-29 | 2013-04-24 | 中国人民解放军总参谋部第六十研究所 | Measuring apparatus and method of unpiloted helicopter rotor blades static moment and barycenter |
| CN203053640U (en) * | 2012-12-29 | 2013-07-10 | 中国人民解放军总参谋部第六十研究所 | An integrated measuring device capable of measuring the mass static moment and the center of gravity of the blade of an unmanned helicopter |
| CN103528740A (en) * | 2013-10-14 | 2014-01-22 | 国家海洋技术中心 | Device for measuring thrust force of propeller and magnetic transmission torque |
| CN104122017A (en) * | 2013-04-24 | 2014-10-29 | 哈尔滨飞机工业集团有限责任公司 | Hinge moment measurement system of helicopter main blade dynamic balance testing bench |
| CN205719531U (en) * | 2016-06-29 | 2016-11-23 | 湖南航天机电设备与特种材料研究所 | A kind of propeller dynamic trait test device |
| CN106768639A (en) * | 2017-03-27 | 2017-05-31 | 江苏科技大学 | Tuning for Controllable Pitch Propeller blade gravity center measurement device and measuring method |
| CN107328524A (en) * | 2017-05-26 | 2017-11-07 | 广州市番禺远航螺旋桨制造有限公司 | Adjustable pitch propeller static balance measuring method and its device |
| CN107588922A (en) * | 2017-08-31 | 2018-01-16 | 北京电子工程总体研究所 | The analogue measurement device of the direction aerodynamic force of unmanned plane three and three direction aerodynamic moments |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| ES2389325T3 (en) * | 2009-03-25 | 2012-10-25 | Siemens Aktiengesellschaft | Arrangement to determine a static moment of a shovel |
-
2019
- 2019-02-01 CN CN201910104390.XA patent/CN109823568B/en active Active
Patent Citations (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR1116466A (en) * | 1953-11-16 | 1956-05-08 | Doman Helicopters | Device for measuring the aerodynamic moment of step of an aerodynamic structure |
| CA2434487A1 (en) * | 2002-07-17 | 2004-01-17 | Snecma Moteurs | Process for distributing turbomachine rotor blades |
| CN1844872A (en) * | 2005-12-29 | 2006-10-11 | 南京航空航天大学 | Optical fiber grating sensing system for measuring distribution load on rotating wings |
| CN102944361A (en) * | 2012-12-06 | 2013-02-27 | 哈尔滨工业大学 | Device for calibrating dynamic balance parameter of helicopter rotor blade |
| CN103063363A (en) * | 2012-12-29 | 2013-04-24 | 中国人民解放军总参谋部第六十研究所 | Measuring apparatus and method of unpiloted helicopter rotor blades static moment and barycenter |
| CN203053640U (en) * | 2012-12-29 | 2013-07-10 | 中国人民解放军总参谋部第六十研究所 | An integrated measuring device capable of measuring the mass static moment and the center of gravity of the blade of an unmanned helicopter |
| CN104122017A (en) * | 2013-04-24 | 2014-10-29 | 哈尔滨飞机工业集团有限责任公司 | Hinge moment measurement system of helicopter main blade dynamic balance testing bench |
| CN103528740A (en) * | 2013-10-14 | 2014-01-22 | 国家海洋技术中心 | Device for measuring thrust force of propeller and magnetic transmission torque |
| CN205719531U (en) * | 2016-06-29 | 2016-11-23 | 湖南航天机电设备与特种材料研究所 | A kind of propeller dynamic trait test device |
| CN106768639A (en) * | 2017-03-27 | 2017-05-31 | 江苏科技大学 | Tuning for Controllable Pitch Propeller blade gravity center measurement device and measuring method |
| CN107328524A (en) * | 2017-05-26 | 2017-11-07 | 广州市番禺远航螺旋桨制造有限公司 | Adjustable pitch propeller static balance measuring method and its device |
| CN107588922A (en) * | 2017-08-31 | 2018-01-16 | 北京电子工程总体研究所 | The analogue measurement device of the direction aerodynamic force of unmanned plane three and three direction aerodynamic moments |
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