CN104019943B - Barycenter dynamic modification method carries out properller dynamic balance method - Google Patents
Barycenter dynamic modification method carries out properller dynamic balance method Download PDFInfo
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- CN104019943B CN104019943B CN201410310793.7A CN201410310793A CN104019943B CN 104019943 B CN104019943 B CN 104019943B CN 201410310793 A CN201410310793 A CN 201410310793A CN 104019943 B CN104019943 B CN 104019943B
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Abstract
The present invention relates to a kind of barycenter dynamic modification method and carry out properller dynamic balance method, use Vector modulation and decomposition principle to be divided into two distribution be heavily separately mounted on two adjacent normal mounting position by intending being arranged on the counterweight dubbing position, make the synthetic effect of the two distribution weight be equivalent to be arranged on the trim effect specifying the first wife intending installation dubbing on position heavy；Accurately calculate point weight mass intending being arranged in two normal places by the method for dynamic corrections counterweight centroid position, improve accuracy in computation；Accurately calculating the balancing coefficient K intending trim propeller, after making, trim process is faster.The present invention can directly use this balancing coefficient to calculate the quality of required counterweight according to the vibration values numerical value measured, then carries out accurately decomposing and after calculating, counterweight being arranged on according to result of calculation the standard o'clock position specified, disposable trim success；Method is simple and convenient, is independent of the working experience of operator；Trim definite effect is reliable.
Description
Technical field
The present invention relates to a kind of aircraft maintenance technical field technology, particularly carry out properller dynamic balance method with a kind of barycenter dynamic modification method.
Background technology
At current General Aviation circle, propeller type power set make it still obtain relatively broad application with its good low pressure economy.But as a high-speed rotary part, manufacture and error in the operation such as assembling makes propeller be inevitably generated static unbalance and unbalance dynamic after installation, make propeller produce to vibrate in high-speed rotation；This vibration, except making except occupant does not feel well on airborne vehicle, also makes airborne vehicle associated components bear very big alternate load, causes structural fatigue to destroy, so propeller must carry out dynamic balancing trim to reduce its vibration values level.
The reason of propeller vibration is the inconsistent pneumatic imbalance caused of aerodynamic force on the mass unbalance owing to its barycenter deviation center of rotation causes and each blade of propeller, and both imbalances all can be passed through propeller dynamic balancing operation and suppress.By the impact of engine rotor mass eccentricity after propeller is installed on electromotor, the actually final vibration measured is by the synthesis of propeller unbalance dynamic Yu both engine rotor unbalance dynamics.In this rotor-support-foundation system being made up of propeller and engine rotor, the data such as gross mass and eccentric throw cannot be measured, so directly measuring the actual vibration value of propeller with vibration values tester in engineering to carry out dynamic balancing trim.
Vibration values tester according to measuring the vibration values of propeller and can calculate the quality m and installation site (dubbing position) that intend installing counterweight.Plan installation counterweight is arranged on dubbing after on position of propeller hub, and actual trim effect depends on the centrifugal force f=m ω of these counterweights2The size of r.Owing to, between the propeller of different model, the distance r between weight installing position from propeller center of rotation is different, it is simply that it is different for saying that the weight stack of equal in quality is arranged on the propeller of different model under specific rotation speeds produced centrifugal force f；Vice versa says that vibration values level identical on the propeller of different model needs weight mass m to be mounted to be different.Just because of grasping the actual distance r treating and dubbing on trim propeller between propeller center of rotation in advance, vibration values tester can only rely on universal model one r of estimation that it is built-in, this generates calculating error.
And for dubbing position, although for intending dubbing what position determined that trim propeller rotor-support-foundation system, but it is random for dubbing position from the angle of general evaluation system.For a secondary propeller intending trim, its light weight point is likely located at the position of any o'clock within the scope of 360 °, obviously circumferentially getting out unlimited number of screw mounting hole on propeller hub periphery is impossible to mate the installation of counterweight, the normal mounting position being actually used for installing weight stack on propeller hub only has specifically several really, it is only small that this results in the actual probability dubbing position and provide normal mounting position on propeller hub and can just overlap, if being directly arranged on immediate normal mounting position by weight stack, alignment error certainly will occur.
Vibration values tester is as a kind of universal instrument, the characteristic of all model propellers can not be contained, the characteristic of more impossible prediction with foresight new production propeller in the future, so the existence calculating error and alignment error is inevitable, it is flat that this makes vibration values tester that " successive approximation method " can only be adopted to carry out repeatedly trial, cause that the actual effect adopting tradition Calculate Ways in Practical Project is put into practice exists very big uncertainty, it can only be often the circulation constantly repeating " test-trim-re-test " under the commander of vibration values tester, waste time and energy, and the anti-trim phenomenon that more trim vibration values is more big occurs often, trim difficulty is big, experienced degree and working experience to operator require height.
Summary of the invention
The technical problem to be solved is to provide a kind of barycenter dynamic modification method and carries out properller dynamic balance method, when carrying out propeller dynamic balancing trim for using vibration values tester traditionally Calculate Ways at present in engineering there is probabilistic problem in actual effect, 100% can ensure disposable trim success when adopting new method to carry out properller dynamic balancing, reach the good result got twice the result with half the effort.
In order to realize solving the purpose of above-mentioned technical problem, a kind of barycenter dynamic modification method of the present invention carries out properller dynamic balance method, and step is as follows:
(1) step one: by the method for resolution of vectors, the counterweight intending being arranged on optional position is decomposed on two normal mounting position, reduce alignment error；
This step is to use Vector modulation, with decomposition principle, plan is arranged on the counterweight dubbing position to be divided on two adjacent normal mounting position that two distribution are heavily separately mounted on propeller hub, makes the synthetic effect of the two distribution weight be equivalent to be arranged on the trim effect of the first wife's weight specifying the plan dubbing on position to install；Namely the physical location that so solving needs to install counterweight dubs the difficult problem that position is inconsistent with the position that can install counterweight on propeller hub and normal mounting position；Realize method as follows:
1) by two blade horizontal positioned of propeller, with propeller hub position directly above for fiducial reference points, counterclockwise according on timepiece dial o'clock position division methods mark 12 positions successively, i.e. 12 o'clock position；Then blade is positioned at 3,9 o'clock position, and the normal place that propeller hub can be installed weight stack is positioned near 2,4,8,10 4 o'clock position；Set on four o'clock position fixing screw hole position respectively as P2、P4、P8、P10；
2) 2,4 o'clock position screw hole P on propeller hub is measured2With P4Between distance P2P4, measure 2 o'clock position screw hole P on propeller hub2And the distance OP between propeller center of rotation O2；
3) propeller center of rotation O and line segment P is set2P4Between distance be OP, if OP2With OP4Between angle ∠ P2OP41/2 be ∠ a, then calculate ∠ a=arcsin ((P according to triangle relation2P4/2)/OP2), OP=OP2*cos(a)=OP2*cos(arcsin((P2P4/2)/OP2))；Based on ∠ a, to calculate with direction straight up be starting point, counterclockwise to P2、P4、P8、P10Angle during each position:
π/2-a=π/2-arctan((P2P4/ 2)/OP), this result of calculation is for be rotated counterclockwise to P by original position2Angle value during point；
π/2+a=π/2+arctan((P2P4/ 2)/OP), this result of calculation is for be rotated counterclockwise to P by original position4The angle value of point；
π*3/2-a=π*3/2-arctan((P2P4/ 2)/OP), this result of calculation is for be rotated counterclockwise to P by original position8The angle value of point；
π*3/2+a=π*3/2+arctan((P2P4/ 2)/OP), this result of calculation is for be rotated counterclockwise to P by original position10The angle value of point；
4) P is setxPosition is dubbed for propeller, if VxFor propeller vibration values level；Estimate a balancing coefficient K, i.e. balancing unit IPS(inch per second) vibration values need weight mass to be mounted, as set K=50g/IPS；
5) use vibrex2000 type vibration values tester that the propeller intending trim carries out first time vibration values test；This type vibration values tester adopts " o'clock position " to arrange the circumferential position of propeller hub on propellerpiston；" xxIPSx:xx " information of record tester output, in this information, xxIPS represents the vibration values level of propeller, and x:xx represents the emphasis of propeller (o'clock position) on the radius of x:xx position；Then measure the horizontal V of vibration values obtained for the first timex=xxIPS；Due to propeller, to dub position and emphasis position symmetrical about propeller center of rotation, and the angle dubbed between place radius and emphasis place radius is 180 °, then dub o'clock position at Px=x:xx+6:00；Above-mentioned " o'clock position ", is with propeller hub position directly above for fiducial reference points, counterclockwise according on timepiece dial o'clock position division methods mark some positions successively, be not limited to integer o'clock；
6) according to the horizontal V of vibration valuesxWith the balancing coefficient K of estimation, the quality that calculating needs total counterweight to be mounted is M=K*Vx；
7) plan is arranged on dubs position PxTotal counterweight M resolution of vectors principle decompose and PxOn two adjacent standard mounting screw holes positions, obtain two distribution weights；Such as dub position PxAt 2:50, it is clear that be not available for installing the screw hole of weight stack on propeller hub 2:50 o'clock position, adopt vector splitting method to be decomposed into by the counterweight M intending being arranged on 2:50 and be separately mounted to P2And P4On two standard mounting screw holes positions two distribution weights, which solves intend installation site with can the inconsistent problem of installation site；
Actual installation counterweight on propeller hub comprises two fixing screws and sheet number weight stack not etc.；Weight stack is the homogeneous thin slice of falcate, is respectively drilled with a fixing screw hole at crescent moon two ends, so the barycenter of weight stack is not on the line of two fixing screw holes.On propeller hub, the centroid position of counterweight after actual installation is relevant with the quality weight of weight stack in counterweight Yu fixing screw, and weight stack quality weight more big then counterweight barycenter two fixing screw hole lines of deviation are more remote.With vector splitting method, total counterweight M is decomposed into two distribution weights and only tentatively solves installation site problem, owing to distribution heavy heart deviation fixing screw hole makes the synthetic effect of the two distribution weight and is not exclusively equivalent to be arranged on and dubs position P after installationxOn first wife weight M, alignment error is still bigger；The centroid position of distribution weight need to be modified for reducing alignment error further.
(2) step 2, accurately calculates point weight mass intending being arranged in two normal places by the method for dynamic corrections counterweight centroid position, improves accuracy in computation；
The actual installation each distribution weight average on propeller hub comprises two fixing screws and sheet number weight stack not etc.；Distribution re-mounts the centroid position deviation fixing screw line of weight stack two after on propeller hub, go out to distribute the distance of the fixing screw line of heavy heart deviation according to the quality weight calculation fixing screw and weight stack in distribution weight, then with the standard mounting screw holes P on propeller hub2、P4、P8、P10In reference count for calculate the correction centroid position after distribution weight centroid motion, more total counterweight M be decomposed into two revised on centroid position revise distribution weight；After drawing the quality revising distribution weight, go out to revise the distribution heavy heart again according to the quality weight calculation of weight stack in correction distribution weight and deviate the distance of fixing screw line, so repeatedly repeatedly revise, make the quality approaching to reality value gradually of distribution weight；
Mass Distribution uniform homogenizing its centroid position of thin slice is relevant with shape, so the centroid position of distribution weight must be positioned on the vertical plane of these two fixing screw lines at two fixing screw line midpoints；Described distribution is heavily contain weight stack and two parts of fixing screw；Total counterweight is by formula M=K*V according to vibration values levelxThe total plan directly calculated installs counterweight.But after the existing total counterweight of method volume is installed, effect is bad, therefore just needs the method for this patent that this total counterweight is resolved into two distribution and heavily installs.
Specifically comprise the following steps that
1) the quality m of two fixing screws is measuredd；This is that the quality fixing screw in distribution weight is constant owing to change point weight mass is the sheet number by changing weight stack；
2) weight stack is homogeneous thin slice, measures the centroid position of a piece of weight stack with suspension method；Weight stack draws the line of centres of two screw holes, measures the vertical dimension d between weight stack barycenter and the two screw hole lines of centres；After weight stack and fixing screw form counterweight to be installed, if the distance between the barycenter of counterweight to be installed and fixing screw hole line is L, then L=(d* (M-md))/M；
3) set and be separately mounted to P2、P4、P8、P10The counterweight of each position is the 1st, 2,3 ... n times revised centroid position respectively P2N、P4N、P8N、P10N, then P2P2N、P4P4N、P8P8N、P10P10NIt is be mounted in P respectively2、P4、P8、P10The barycenter of the distribution weight in four normal places deviates the distance of this position fixing screw hole, and this distance can according to the quality of each distribution weight by formula L=(d* (M-md))/M calculates；
4) be starting point with position, direction (i.e. 12:00 position) straight up, counterclockwise to P2N、P4N、P8N、P10NAngle during each position is respectively as follows:
π/2-arctan((P2P4/2+P2P2N)/OP), this result of calculation is for be rotated counterclockwise to P by original position2NAngle value during point；
π/2+arctan((P2P4/2+P4P4N)/OP), this result of calculation is for be rotated counterclockwise to P by original position4NThe angle value of point；
π*3/2-arctan((P2P4/2+P8P8N)/OP), this result of calculation is for be rotated counterclockwise to P by original position8NThe angle value of point；
π*3/2+arctan((P2P4/2+P10P10N)/OP), this result of calculation is for be rotated counterclockwise to P by original position10NThe angle value of point；
5) plan is arranged on dubs position PxCounterweight M resolution of vectors principle decompose and PxAdjacent two revise on centroid position, obtain two distribution weights；Such as dub position PxAt 2:50, the counterweight M intending being arranged on 2:50 is decomposed into and is separately mounted to P2NAnd P4NTwo two distribution weights revised on centroid position, make point weight mass calculated more accurate；
Barycenter dynamic corrections is to obtain on the basis of point weight mass distributing the weight corrected Calculation that centroid position carries out in a front resolution of vectors.The process repeatedly repeating " decompose-revise-decompose " can divide the actual value of weight mass by Approach by inchmeal, makes point weight mass data that calculate more accurately, when the error of result of calculation of front and back twice is less than one thousandth gram, namely reaches requirement.In practical engineering application, the computational accuracy of weighing to weight stack and fixing screw is 1/10th grams, and find through computer computational analysis and actual test, after this method correction 5 times, the error of result of calculation is at microgram, and this is enough for practical engineering application.
(3) step 3, accurately calculates the balancing coefficient K intending trim propeller, no longer adopts the balancing coefficient of estimation, make trim process faster when again this type propeller being carried out trim after making；
It is multiplied by adjusted coefficient K by step one known vibration values level and can obtain intending the quality of total counterweight of installation, but the correction factor adopted in step one is estimation, through the resolution of vectors of step one, step 2 barycenter correction after, having been able to accomplish the total counterweight intending being arranged on optional position resolves into the distribution weight being arranged on two normal mounting position and makes the synthetic effect that the two distributes weight be equivalent to be arranged on the first wife's weight intending installation site completely, this is just that the balancing coefficient K accurately calculating this type propeller creates condition.Step is as follows:
1) P is setx1、Px2、Px3……PxnThe propeller obtained for n-th measurement dubs position, if Vx1、Vx2、Vx3……VxnFor the propeller vibration values level that n-th measurement obtains, if M1、M2、M3……MnIt is arranged on for the calculated plan of n-th and dubs PxnTotal weight mass of position；Adopt the balancing coefficient K of arbitrary estimation, for instance make K=50g/IPS；
2) all weight stacks treated on trim propeller hub are all removed, carry out first time vibration values and measure, write down the propeller that vibration values tester measures and dub position Px1V horizontal in vibration valuesx1, calculate plan and be arranged on and dub Px1Total weight mass M of position1=K*Vx1；
3) perform the resolution of vectors of step one and the barycenter correction of step 2, accurately realize " at Px1M is installed in position1Gram counterweight " trim effect；
4) again carry out vibration values measurement, write down the propeller that vibration values tester measures and dub position Px2V horizontal in vibration valuesx2；Relatively Px2And Px1Difference, if Px2And Px1Central angle is less than 3:00 that is 120 degree, for instance Px1=5:20, if 2:20 is < Px2< 8:20, then illustrate that trim is not enough, and taken balancing coefficient K is still big not, otherwise illustrates that trim is excessive, and taken balancing coefficient K is excessive；Contrast Vx2And Vx1Between difference, if difference is less than 50%, trim DeGrain is described, balancing coefficient K value is big not, otherwise illustrates that trim effect is more apparent；If V simultaneouslyx2Acceptance value close to 0.2IPS illustrates that balancing coefficient K is close to desired value；Can suitably increase or reduce the value of balancing coefficient K according to practical situation；
5) repeated execution of steps 2) ~ 4) until adopting and can making V during certain K valuexnReaching criterion of acceptability namely less than 0.2IPS, this K value is the balancing coefficient of this type propeller.It is furthermore preferred that V should be madexnBeing less than 0.1IPS, so can reach more excellent trim effect, and test this method through reality and also be able to reach more excellent trim effect, K value now just can as the balancing coefficient of this type propeller.
After performing above step one, two, three, obtain the balancing coefficient being suitable for treating trim model propeller, can directly adopt this balancing coefficient to perform step one later when carrying out the dynamic balancing trim of this model propeller again and step 2 carries out resolution of vectors and barycenter dynamic corrections, not need to perform step 3 again.Prove that the method can disposable trim success through engineering practice test.
Vibration values tester, it is preferable that the vibrex2000 type vibration values tester produced by ChadwickHelmuth.
The implication definition of symbol used is as follows:
P2、P4、P8、P10For the fixing screw hole position on 2,4,8,10 o'clock of propeller hub four normal mounting position；
P2N、P4N、P8N、P10NFor being arranged on P2、P4、P8、P10The counterweight of each position is the 1st, 2,3 ... the revised centroid position of n times；
P2P2N、P4P4N、P8P8N、P10P10NFor being arranged on P2、P4、P8、P10The barycenter of the distribution weight in four normal places deviates the distance of this position fixing screw hole；
D is the distance on weight stack between weight stack barycenter and two mounting screw holes lines；
IPS: unit is inch per second, for the unit of vibration values parameter；
PxFor dubbing position, x:xx+6:00 in the output data " xxIPSx:xx " of vibration values tester obtain；
VxFor vibration values numerical value, " xxIPS " in the output data " xxIPSx:xx " of vibration values tester obtain；
Px1、Px2、Px3……PxnThe propeller obtained for n-th measurement dubs position；
Vx1、Vx2、Vx3……VxnFor the propeller vibration values level that n-th measurement obtains
M1、M2、M3……MnIt is arranged on for the calculated plan of n-th and dubs PxnTotal weight mass of position
K is balancing coefficient, the weight mass that every IPS vibration values needs, and unit is g/IPS(gram/IPS).
mdIt it is the quality of two fixing screws；
M is the quality of total counterweight；
In the technical program, used formulation process is as follows:
For certain two-bladed porpeller, it is assumed that vibration values tester requires the weight stack that quality is M is arranged on 4:30 position (OC direction), because 4:30 is positioned at the normal mounting position P at 4,8 o'clock4、P8Between, according to resolution of vectors principle, the counterweight forces in OC direction can be resolved into P4Position (OA direction), P8Two distribution weights of position (OB direction), the synthetic effect after making the two distribution re-mount is equivalent to the total counterweight M being arranged on 4:30 position (OC direction).Step is as follows:
1) resolution of vectors
Parallelogram law according to known conditions and resolution of vectors, can obtain:
In OAC, according to the cosine law, have
OA2=AC2+ CO2-2*AC*CO*COS (∠ ACO) ... ... ... ... ... ... (1)
According to sine, have
S⊿AOC=CO*OA*SIN (∠ COA)/2,
S⊿AOC=OA*AC*SIN (∠ OAC)/2,
CO*OA*SIN (∠ COA)=OA*AC*SIN (∠ OAC) can be obtained ... ... ... ... (2)
Can be obtained by formula (1), formula (2)
OA2=CO2*(SIN2(∠COA)/SIN2(∠ OAC)+1-2*SIN (∠ COA) * COS (∠ ACO)/SIN (∠ OAC)) ... ... ... ... ... ... ... ... (3)
According to the cosine law in CBO, there are ∠ AOC, ∠ COB, ∠ OAC
OB2=BC2+ CO2-2*BC*CO*COS (∠ BCO) ... ... ... ... ... ... (4)
According to sine, have
S⊿CBO=CO*OB*SIN (∠ COB)/2,
S⊿CBO=OB*BC*SIN (∠ OBC)/2,
CO*OB*SIN (∠ COB)=OB*BC*SIN (∠ OBC) can be obtained ... ... ... ... ... (5)
Can be obtained by formula (4), formula (5)
OB2=CO2*(SIN2(∠COB)/SIN2(∠ OBC)+1-2*SIN (∠ COB) * COS (∠ BCO)/SIN (∠ OBC) ... ... ... ... ... ... ... ... (6)
Due to AOC ≌ BCO, ∠ COB=∠ ACO, ∠ BCO=∠ AOC=∠ COA, ∠ OBC=∠ CAO=∠ OAC can be obtained, substitute into formula (3) and formula (6) can obtain:
OA2=CO2*(SIN2(∠AOC)/SIN2(∠ OAC)+1-2*SIN (∠ AOC) * COS (∠ COB)/SIN (∠ OAC)) ... ... ... ... ... ... ... ... (7)
OB2=CO2*(SIN2(∠COB)/SIN2(∠ OAC)+1-2*SIN (∠ COB) * COS (∠ AOC)/SIN (∠ OAC)) ... ... ... ... ... ... ... ... (8)
Just by formula (7) and formula (8) can be decomposed into according to resolution of vectors principle be arranged on P by intending the total counterweight M that be arranged on 4:30 position respectively4、P8Distribution weight on two normal mounting position.
2) parameter is determined
In formula (7) and formula (8), to ∠ AOC, ∠ COB, tri-angles of ∠ OAC value be determined as follows:
A) angle position calculated with the 12:00 4:30 position being reference is: 4* π/6+30* π/360=π * 3/4；
B) first time decomposition computation time ∠ AOC, ∠ COB, tri-angles of ∠ OAC value be respectively as follows:
∠AOC=π*3/4-π/2-arctan((P2P4/2)/OP)=π/4-arctan((P2P4/2)/OP)
∠COB=π*3/2-arctan((P2P4/2)/OP)-π*3/4=π*3/4-arctan((P2P4/2)/OP)
∠OAC=π-∠AOC-∠COB=2*arctan((P2P4/2)/OP)
3) second time and above ∠ AOC when revising decomposition computation, ∠ COB, tri-angles of ∠ OAC value be respectively as follows:
∠AOC=π*3/4-π/2-arctan((P2P4/2+P4P4N)/OP)=π/4-arctan((P2P4/2+P4P4N)/OP)
∠COB=π*3/2-arctan((P2P4/2+P8P8N)/OP)-π*3/4=π*3/4-arctan((P2P4/2+P8P8N)/OP)
∠OAC=π-∠AOC-∠COB=arctan((P2P4/2+P4P4N)/OP)+arctan((P2P4/2+P8P8N)/OP)
By adopting technique scheme, the present invention has following beneficial effect:
Present invention employs the vector splitting method of barycenter dynamic corrections and carry out properller dynamic balancing, performed the present invention in steps, measure the balancing coefficient of this type propeller after, as needed to carry out the dynamic balancing trim of this model propeller again, this balancing coefficient can be directly used to calculate the quality of required counterweight according to the vibration values numerical value measured, step one of the present invention and step 2 is used to carry out accurately decomposing and after calculating again, according to result of calculation, counterweight is arranged on the standard o'clock position specified, disposable trim success can be ensured.After computer computing technique, artificial done simply measuring is treated the vibration values data of trim propeller and is arranged on propeller hub according to calculation by computer by counterweight, simple and convenient, is completely independent of proficiency level and the working experience of operator；And trim definite effect is reliable.
Term defines
1. o'clock position
The o'clock position of indication of the present invention, is the agreement that the relative position along propeller hub periphery on propeller hub is carried out.It is defined as: towards propeller Plane of rotation, centered by propeller center of rotation, arranging direction straight up is 12 o'clock (or 0 o'clock), then with this as the starting point in the counterclockwise direction by timepiece dial o'clock scale every 30 ° of method be defined as 1 successively, 2,3 ... 11 o'clock, representing with " dividing " less than 30 °, such as Fig. 1.So the time format data of " x:xx " just have expressed a specific radial direction, and this direction starts from direction straight up to obtain along rotation (x*30+xx*0.5) ° angle counterclockwise.Radial direction determines that the relative position on rear circumference namely on propeller hub periphery determines that.
2. emphasis and dubbing
The propeller emphasis of indication of the present invention, it is that the rotor-support-foundation system formed with engine rotor by propeller produced vibration equivalent in high-speed rotation becomes the barycenter of propeller to deviate vibration produced by center of rotation, under this premise on propeller Plane of rotation on circumference centered by the center of rotation of propeller, with propeller hub periphery place, definition propeller emphasis is exactly the intersection point of propeller equivalence barycenter place radius and circumference, so propeller emphasis not necessarily propeller particle；Opposed helical oar emphasis, dubbing is exactly be 180 ° symmetrical point with emphasis on circumference.
Due to propeller emphasis and dubbing all on the circumference at propeller hub periphery place, so having only to emphasis and dubbing the direction of place radius and just can describe emphasis and the position dubbed.Emphasis and the description dubbing position are represented with the o'clock position of " x:xx ".The data form that vibration values tester exports after vibration values is tested is " xxIPSx:xx ", and wherein xxIPS is the vibration values level measured, the o'clock position that x:xx attaches most importance to, then dub and be positioned at x:xx+6:00 position.
3. dynamic balancing trim
The counterweight dubbing installation appropriate mass in position at propeller makes the equivalent barycenter of propeller return on propeller center of rotation.Vibration values can not be reduced to zero by dynamic balancing trim, with less than 0.2IPS(inch per second in engineering) for qualified.
Accompanying drawing explanation
Fig. 1 be on propeller Plane of rotation internal propeller propeller hub periphery o'clock position distribution.
Fig. 2 is the distance signal between the position of mounting screw holes on the weight stack of homogenizing thin slice and the position of weight stack barycenter and barycenter and two screw hole lines；
Fig. 3 can install for the 2 of weight stack, 4,8,10 4 standard o'clock position P on certain type two-bladed porpeller propeller hub2、P4、P8、P10Signal and the method carrying out propeller hub characteristic measurement；
Fig. 4 to Fig. 6 respectively weight stack actual installation on propeller hub and the left view of counterweight barycenter modification method schematic diagram, front view, right view.
In figure, L4、L8Represent that the distribution heavy heart deviates the distance of its two fixing screw holes line.
Fig. 7 is the resolution of vectors method being undertaken the counterweight forces of any non-standard installation site decomposing.
Detailed description of the invention
Below in conjunction with drawings and Examples, this patent is explained further explanation.But the protection domain of this patent is not limited to specific embodiment.
The vibration values information that vibration values tester provides after measuring is " xxIPSx:xx ", these contain vibration values size and emphasis positional information, and wherein xxIPS is the vibration values level measured, the o'clock position that x:xx attaches most importance to, then dub and be positioned at x:xx+6:00 position.The position that dubs provided after calculating due to tester is actual to dub position, and this position is frequently not the standard o'clock position on propeller hub, so not having screw hole cannot install counterweight in this position.Can only being that counterweight is arranged on position of immediate standard o'clock when adopting traditional method to carry out dynamic balancing trim, this just brings bigger error in mounting position.
Vibration values tester is according to being using its built-in trim model as basis about the calculating that should install weight mass, this trim model and the actual characteristic treating trim propeller differ greatly, cause that the plan installation weight mass that tester calculates is very inaccurate, cause trim difficulty.
The present invention by obtaining more accurate balancing coefficient, resolution of vectors and three kinds of methods of counterweight barycenter dynamic corrections solve vibration values tester existing for traditional method and calculate and error existing for the link such as weight mass calculating is big and " Approach by inchmeal " trim theory is brought multiple difficulty at weight installing position.
Certain type propeller vibration values tester that the present embodiment uses is as follows to the division of vibration values level:
| best | less than 0.05 |
| very good | 0.05-0.09 |
| good | 0.10-0.14 |
| acceptable | 0.15-0.19 |
| unacceptable | 0.20-1.19 |
| warning | great than 1.2 |
It is respectively adopted tradition Calculate Ways and adopts the method for the present invention to carry out actual trim Contrast on effect as follows:
The embodiment 1. dynamic balancing trim Contrast on effect on TB200 aircraft:
1) traditional method is used
Traditional method is that result of calculation is directly exported as solution with dubbing position data by propeller vibration values tester according to the vibration values level measured, its calculating process is solidificated in inside tester as a part for systems soft ware, and it is not or not user is open as know-how, have only to during traditional method select function menu according to the prompting on tester interface so adopting, it is absent from selecting the problem of balancing coefficient and barycenter dynamic corrections, and the solution of traditional method is to install a counterweight a position.
The dynamic balancing trim process of traditional method is as follows:
When trim is to the 7th time, vibration values is reduced to 0.18IPS by 0.46IPS, already belongs to tolerance interval.Adopt traditional method co-continuous trim 7 times, be finally mounted with 35.9 grams in 10:00 position, install 23.7 grams in 2:00 position.
Owing to the actual installation position of counterweight can not be completely the same with the theoretical installation site that vibration values tester requires during employing traditional method, so installing the emphasis position that all can find propeller of again measuring after counterweight is be constantly occurring change every time；By the viewpoint of the present invention, the balancing coefficient of the trim model that vibration values tester is built-in is too small；And, owing to vibration values tester is as a versatility instrument, without reference to the individual model sized data treating trim propeller, sayed as in its product description, its solution is " trial " property, this just determines employing traditional method and carries out a dynamic balancing trim necessarily process repeatedly attempted, even the propeller of same model is carried out dynamic balancing trim is also such.
2) by new method:
When adopting new method, if for the first time certain type propeller being carried out dynamic balancing trim, namely when there is no the balancing coefficient of this model propeller, as described in this description, the characteristic geometric dimension of this model propeller need to be measured, perform resolution of vectors, barycenter correction, three steps of balancing coefficient, to obtaining the balancing coefficient being suitable for this type propeller comparatively accurately.
Execution process is as follows:
Performed the present invention in steps, measure the balancing coefficient of this type propeller after, as needed to carry out the dynamic balancing trim of this model propeller again, can directly use this balancing coefficient that the vibration values measured is calculated the weight mass obtaining intending installing, step one of the present invention and step 2 is used to carry out accurately decomposing and calculating again, and according to result of calculation, counterweight is arranged on the standard o'clock position specified, disposable trim success can be ensured.
In the process performing new method, all counterweight that last time install is removed after adjusting K value every time and again the first vibration values level measured is carried out trim, after adjusting K value in this example, counterweight point 0.46IPS4:50 carries out trim all again every time, each balanced is that an independent process is unrelated with trim last time, so the final counterweight gross mass installed the not weight mass of cumulative all previous installation as adopting traditional method.And it can be seen that the revised data of barycenter are compared with the data only carrying out resolution of vectors or there is some difference, this difference can bring about certain trim error, so carrying out what barycenter correction was a need on the basis of resolution of vectors.Can also reach a conclusion from the process of successive adjustment balancing coefficient K, as long as balancing coefficient K value is suitable, adopt new method trim once just level very low for vibration values trim value can be fully able to realization；When adopting K=70 in this example, the effect that reaches is disposable from 0.46IPS vibration values to be reduced to 0.03IPS, and traditional method to be continuous trim be just down to 0.19IPS 7 times；In the final weight mass installed, new method is finally mounted with 41.5 grams, installs 21.1 grams in 2:00 position in 10:00 position, traditional method is finally mounted with 35.9 grams in 10:00 position, 23.7 grams are installed in 2:00 position, if it is contemplated that the final weight mass installed also can further increase after adopting traditional method to be further continued for carrying out repeatedly trim, vibration values also can decline further, and simply trim number of times is too much, wastes time and energy.
The advantage contrasting visible new method is in that disposable trim success, time saving and energy saving, and trim effect is more excellent.
The embodiment 2. dynamic balancing trim Contrast on effect on LE500 aircraft:
1) traditional method is used
Traditional method is that result of calculation is directly exported as solution with dubbing position data by propeller vibration values tester according to the vibration values level measured, have only to select function menu according to the prompting on tester interface, the problem being absent from selecting balancing coefficient and barycenter dynamic corrections, and the solution of traditional method is " trail " character, it is characterized in that a position, one counterweight being installed every time, and trim is all carry out on upper basis once every time, the final weight mass installed is to install adding up of weight mass for each time.
Adopting traditional method co-continuous trim 7 times, the effect reached is 0.16IPS, is finally mounted with 21.7 grams in 10:00 position, installs 37.5 grams in 2:00 position.If continuation trim, vibration values can reduce further, but trim number of times is too much, wastes time and energy.
2) new method
For the first time this type propeller is carried out dynamic balancing trim, owing to not yet obtaining the balancing coefficient of this model propeller, so needing to measure the characteristic geometric dimension of this model propeller, and perform resolution of vectors, barycenter correction, three steps of balancing coefficient, this balancing coefficient just can be adopted, thus accomplishing disposable trim success after obtaining the balancing coefficient being suitable for this type propeller comparatively accurately.
Vibration values disposable can be reduced to 0.05IPS by 0.52IPS when adopting K=80 by the 4th trim, have been able to reach extraordinary trim effect, but observe the emphasis position after this this trim at 12:35, emphasis position before trim is at 6:45, difference 12:35-6:45=5:50 > 3:00, therefore it is excessive to belong to trim, illustrates that balancing coefficient K value is chosen greatly, historical facts or anecdotes list reduces balancing coefficient and takes K=75 and carry out trim test at this, and the most suitable balancing coefficient eventually found is K=75.Balancing coefficient adopts and installs 34.3 grams in 10:00 position during K=75, installs 50.8 grams in 2:00 position, and the effect reached is disposable by 0.52IPS, vibration values to be reduced to 0.03IPS.
After finding the appropriate value of balancing coefficient K, this K value should be recorded, when again the propeller of this model being carried out trim, can directly adopt this K value later, disposable trim success can be accomplished.
By above comparative example it can be seen that adopting new method is that the trim effect to different balancing coefficients is tested, adopt and only need trim once during each balancing coefficient to be tested, if balancing coefficient choose suitably can disposable trim success；What vibration values tester adopted is the scheme of " Approach by inchmeal ", this scheme determine actual carry out dynamic balancing trim time need repeatedly test run to operate, waste time and energy.The method of the present invention, owing to reducing alignment error to greatest extent and calculating error, decreases the number of times adding counterweight as far as possible and accomplishes to settle at one go, so final trim effect is much better than traditional method.
The method adopting polishing weight stack thickness when carrying out the test of this trim embodiment, the strict quality controlling weight stack meets theoretical value.In actual engineer applied, counterweight for being accurate to 0.1 gram is more difficult satisfied, therefore owing to the weight stack quality of actual installation and theoretical value have certain deviation in actual engineer applied, therefore traditional method and the actual trim effect adopting new method is adopted all to be inferior to the statistics effect of this theoretical validation test in actual engineer applied environment.And the result of statistics shows in practical engineering application, in practical engineering application environment, adopt the actual trim number of times that traditional method carries out dynamic balancing trim on average to have more 2 ~ 3 times than the trim number of times that this theoretical validation is tested, namely adopt traditional method that vibration values is on average needed by 0.4 ~ 0.5IPS trim to below 0.2IPS continuous trim 10 times in common engineering applied environment；And adopting new method disposable success rate that vibration values is reduced to below 0.15IPS in the general operation environment of practical engineering application is 100%.The method of the present invention is more suitable for the engineer applied of reality as can be seen here.
Claims (5)
1. barycenter dynamic modification method carries out a properller dynamic balance method, it is characterized in that: step is as follows:
(1) step one: by the method for resolution of vectors, the counterweight intending being arranged on optional position is decomposed on two normal mounting position, reduce alignment error；
This step is to use Vector modulation, with decomposition principle, plan is arranged on the counterweight dubbing position to be divided on two adjacent normal mounting position that two distribution are heavily separately mounted on propeller hub, makes the synthetic effect of the two distribution weight be equivalent to be arranged on the trim effect of the first wife's weight specifying the plan dubbing on position to install；Namely the physical location that so solving needs to install counterweight dubs the difficult problem that position is inconsistent with the position that can install counterweight on propeller hub and normal mounting position；Realize method as follows:
1) by two blade horizontal positioned of propeller, with propeller hub position directly above for fiducial reference points, counterclockwise according on timepiece dial o'clock position division methods mark 12 positions successively, i.e. 12 o'clock position；Then blade is positioned at 3,9 o'clock position, and the normal place that propeller hub can be installed weight stack is positioned near 2,4,8,10 4 o'clock position；Set on four o'clock position fixing screw hole position respectively as P2、P4、P8、P10；
2) 2,4 o'clock position screw hole P on propeller hub is measured2With P4Between distance P2P4, measure 2 o'clock position screw hole P on propeller hub2And the distance OP between propeller center of rotation O2；
3) propeller center of rotation O and line segment P is set2P4Between distance be OP, if OP2With OP4Between angle ∠ P2OP41/2 be ∠ a, then calculate ∠ a=arcsin ((P according to triangle relation2P4/2)/OP2), OP=OP2*cos(a)=OP2*cos(arcsin((P2P4/2)/OP2))；Based on ∠ a, to calculate with direction straight up be starting point, counterclockwise to P2、P4、P8、P10Angle during each position:
π/2-a=π/2-arctan((P2P4/ 2)/OP), this result of calculation is for be rotated counterclockwise to P by original position2Angle value during point；
π/2+a=π/2+arctan((P2P4/ 2)/OP), this result of calculation is for be rotated counterclockwise to P by original position4The angle value of point；
π*3/2-a=π*3/2-arctan((P2P4/ 2)/OP), this result of calculation is for be rotated counterclockwise to P by original position8The angle value of point；
π*3/2+a=π*3/2+arctan((P2P4/ 2)/OP), this result of calculation is for be rotated counterclockwise to P by original position10The angle value of point；
4) P is setxPosition is dubbed for propeller, if VxFor propeller vibration values level；Estimating a balancing coefficient K, namely balancing unit IPS vibration values needs weight mass to be mounted, IPS and inch per second；
5) use vibrex2000 type vibration values tester that the propeller intending trim carries out first time vibration values test；This type vibration values tester adopts " o'clock position " to arrange the circumferential position of propeller hub on propellerpiston；" xxIPSx:xx " information of record tester output, in this information, xxIPS represents the vibration values level of propeller, and x:xx represents the emphasis of propeller o'clock position on the radius of x:xx position；Then measure the horizontal V of vibration values obtained for the first timex=xxIPS；Due to propeller, to dub position and emphasis position symmetrical about propeller center of rotation, and the angle dubbed between place radius and emphasis place radius is 180 °, then dub o'clock position at Px=x:xx+6:00；
6) according to the horizontal V of vibration valuesxWith the balancing coefficient K of estimation, the quality that calculating needs total counterweight to be mounted is M=K*Vx；
7) plan is arranged on dubs position PxTotal counterweight M resolution of vectors principle decompose and PxOn two adjacent standard mounting screw holes positions, obtain two distribution weights；
(2) step 2, accurately calculates point weight mass intending being arranged in two normal places by the method for dynamic corrections counterweight centroid position, improves accuracy in computation；
Specifically comprise the following steps that
1) the quality m of two fixing screws is measuredd；
2) weight stack is homogeneous thin slice, measures the centroid position of a piece of weight stack with suspension method；Weight stack draws the line of centres of two screw holes, measures the vertical dimension d between weight stack barycenter and the two screw hole lines of centres；After weight stack and fixing screw form counterweight to be installed, if the distance between the barycenter of counterweight to be installed and fixing screw hole line is L, then L=(d* (M-md))/M；
3) set and be separately mounted to P2、P4、P8、P10The counterweight of each position is the 1st, 2,3 ... n times revised centroid position respectively P2N、P4N、P8N、P10N, then P2P2N、P4P4N、P8P8N、P10P10NIt is be mounted in P respectively2、P4、P8、P10The barycenter of the distribution weight in four normal places deviates the distance of this position fixing screw hole, and this distance can according to the quality of each distribution weight by formula L=(d* (M-md))/M calculates；
4) be starting point with position, direction straight up and 12:00 position, counterclockwise to P2N、P4N、P8N、P10NAngle during each position is respectively as follows:
π/2-arctan((P2P4/2+P2P2N)/OP), this result of calculation is for be rotated counterclockwise to P by original position2NAngle value during point；
π/2+arctan((P2P4/2+P4P4N)/OP), this result of calculation is for be rotated counterclockwise to P by original position4NThe angle value of point；
π*3/2-arctan((P2P4/2+P8P8N)/OP), this result of calculation is for be rotated counterclockwise to P by original position8NThe angle value of point；
π*3/2+arctan((P2P4/2+P10P10N)/OP), this result of calculation is for be rotated counterclockwise to P by original position10NThe angle value of point；
5) plan is arranged on dubs position PxCounterweight M resolution of vectors principle decompose and PxAdjacent two revise on centroid position, obtain two distribution weights；
The process repeatedly repeating " decompose-revise-decompose " can divide the actual value of weight mass by Approach by inchmeal, makes point weight mass data that calculate more accurately, when the error of result of calculation of front and back twice is less than one thousandth gram, namely reaches requirement；
(3) step 3, accurately calculates the balancing coefficient K intending trim propeller, no longer adopts the balancing coefficient of estimation, make trim process faster when again this plan trim propeller being carried out trim after making；
Step is as follows:
1) P is setx1、Px2、Px3……PxnThe propeller obtained for n-th measurement dubs position, if Vx1、Vx2、Vx3……VxnFor the propeller vibration values level that n-th measurement obtains, if M1、M2、M3……MnIt is arranged on for the calculated plan of n-th and dubs PxnTotal weight mass of position；Adopt the balancing coefficient K of arbitrary estimation；
2) all weight stacks treated on trim propeller hub are all removed, carry out first time vibration values and measure, write down the propeller that vibration values tester measures and dub position Px1V horizontal in vibration valuesx1, calculate plan and be arranged on and dub Px1Total weight mass M of position1=K*Vx1；
3) perform the resolution of vectors of step one and the barycenter correction of step 2, accurately realize " at Px1M is installed in position1Gram counterweight " trim effect；
4) again carry out vibration values measurement, write down the propeller that vibration values tester measures and dub position Px2V horizontal in vibration valuesx2；Relatively Px2And Px1Difference, if Px2And Px1Central angle less than 3:00 that is 120 degree, then illustrates that trim is not enough, and taken balancing coefficient K is still big not, otherwise illustrates that trim is excessive, and taken balancing coefficient K is excessive；Contrast Vx2And Vx1Between difference, if difference is less than 50%, trim DeGrain is described, balancing coefficient K value is big not, otherwise illustrates that trim effect is more apparent；If V simultaneouslyx2Acceptance value close to 0.2IPS illustrates that balancing coefficient K is close to desired value；Can suitably increase or reduce the value of balancing coefficient K according to practical situation；
5) repeated execution of steps 2) ~ 4) until adopting and can making V during certain K valuexnReaching criterion of acceptability namely less than 0.2IPS, this K value is this balancing coefficient treating trim propeller；
After performing above step one, two, three, obtain the balancing coefficient being suitable for treating trim propeller, carrying out this again can directly adopt this balancing coefficient execution step one and step 2 to carry out resolution of vectors and barycenter dynamic corrections later when the dynamic balancing trim of trim propeller, does not need to perform step 3 again.
2. barycenter dynamic modification method according to claim 1 carries out properller dynamic balance method, it is characterized in that: adopt accurate balancing coefficient K directly according to formula M=K*VxCalculate the total weight mass intending installing；Barycenter dynamic modification method is adopted to accurately calculate the accurate centroid position of two distribution weights；Adopt vector splitting method that the former counterweight being arranged on a position is decomposed into two the distribution weights being now arranged on two positions.
3. barycenter dynamic modification method according to claim 1 carries out properller dynamic balance method, it is characterized in that: described vibration values tester is the vibrex2000 type vibration values tester produced by ChadwickHelmuth.
4. barycenter dynamic modification method according to claim 1 carries out properller dynamic balance method, it is characterized in that: described " o'clock position ", with propeller hub position directly above for fiducial reference points, counterclockwise according on timepiece dial o'clock position division methods mark 12 positions successively.
5. barycenter dynamic modification method according to claim 1 carries out properller dynamic balance method, it is characterized in that: described VxnLess than 0.1IPS.
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| CN105181249B (en) * | 2015-06-04 | 2017-12-01 | 中国航空工业集团公司上海航空测控技术研究所 | An a kind of counterweight method of adjustment for lifting airscrew balance |
| CN105021348B (en) * | 2015-08-07 | 2017-09-26 | 长春理工大学 | A kind of revolving body centroid position measurement error computational methods |
| CN105775124A (en) * | 2016-03-08 | 2016-07-20 | 哈尔滨飞机工业集团有限责任公司 | Special dynamic balance adjusting method for helicopter main blade |
| CN106595957A (en) * | 2016-10-25 | 2017-04-26 | 江苏大学 | Ship propeller eccentric mass automatic detection method |
| CN107389268B (en) * | 2017-06-30 | 2019-08-09 | 西安交通大学 | A kind of multiple spot spot dynamic balance method based on fast algorithm |
| CN109850138A (en) * | 2017-11-30 | 2019-06-07 | 中光电智能机器人股份有限公司 | Unmanned plane and its propeller |
| CN109404485B (en) * | 2018-10-19 | 2021-03-16 | 淄柴动力有限公司 | Dynamic balance weight removing method for ductile iron crankshaft of medium-high speed marine diesel engine |
| CN110608845A (en) * | 2019-10-21 | 2019-12-24 | 山西汾西重工有限责任公司 | Dynamic balance test mechanism and dynamic balance test method for lamellar propeller |
| CN112364433B (en) * | 2020-10-27 | 2022-05-10 | 成都飞机工业（集团）有限责任公司 | Efficient fixed-wing aircraft flight dynamics model balancing method |
| CN112611512A (en) * | 2021-01-10 | 2021-04-06 | 郭森森 | Helicopter rotor dynamic balance adjusting method based on APP |
| CN113190987B (en) * | 2021-04-22 | 2023-06-23 | 扬州大学 | Deviation correction-based optimal rotation speed determination method for pollen removal of pine ears |
| CN113247243B (en) * | 2021-06-29 | 2021-09-28 | 四川腾盾科技有限公司 | Seesaw type unmanned helicopter rotor wing structure and chord direction dynamic balance balancing method |
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| US4150920A (en) * | 1977-12-02 | 1979-04-24 | The United States Of America As Represented By The Secretary Of The Army | Rotor blade tipweight assembly |
| US6139271A (en) * | 1998-03-17 | 2000-10-31 | Chadwick-Helmuth Company, Inc. | Helicopter rotor blade weighting |
| CN2574034Y (en) * | 2002-04-15 | 2003-09-17 | 中国船舶重工集团公司天津修船技术研究所 | Propeller static balancing instrument |
| FR2926535B1 (en) * | 2008-01-23 | 2011-08-12 | Eurocopter France | DEVICE AND METHOD FOR DYNAMICALLY BALANCING A BLADE |
| CN201637539U (en) * | 2010-03-19 | 2010-11-17 | 天津修船技术研究所 | Instrument for measuring gravity center of propeller blade with controllable pitch |
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