CN113173261A - Composite loading field checking device and method for rotor wing balance loading test bed - Google Patents
Composite loading field checking device and method for rotor wing balance loading test bed Download PDFInfo
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- CN113173261A CN113173261A CN202110427424.6A CN202110427424A CN113173261A CN 113173261 A CN113173261 A CN 113173261A CN 202110427424 A CN202110427424 A CN 202110427424A CN 113173261 A CN113173261 A CN 113173261A
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- B—PERFORMING OPERATIONS; TRANSPORTING
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- B64F5/60—Testing or inspecting aircraft components or systems
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- G01L—MEASURING FORCE, STRESS, TORQUE, WORK, MECHANICAL POWER, MECHANICAL EFFICIENCY, OR FLUID PRESSURE
- G01L5/00—Apparatus for, or methods of, measuring force, work, mechanical power, or torque, specially adapted for specific purposes
- G01L5/16—Apparatus for, or methods of, measuring force, work, mechanical power, or torque, specially adapted for specific purposes for measuring several components of force
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Abstract
The invention particularly relates to a composite loading field checking device and method for a rotor wing balance-mounting test bed. The method comprises the following steps: the rotor wing balance (1) is positioned at the bottom of the device and is used for six-element measurement of a rotor wing system; a hub (2), wherein the hub (2) is vertically arranged at the upper part of the rotor wing balance (1); a rigid component (3), wherein one end of the rigid component (3) is connected with the center of the hub (2) in a height-adjustable mode, and the other end of the rigid component (3) is connected with the actuating cylinder (4); the actuating cylinder (4), the actuating cylinder (4) includes a first actuating cylinder (41) arranged along the vertical direction, a second actuating cylinder (42) arranged along the course direction, and a third actuating cylinder (43) arranged along the side direction. The method has the advantages that the composite loading after the rotor wing balance test bed is leveled is realized, the composite loading load is collected, the rotor wing balance is measured, whether the problem exists in the coefficient input of the rotor wing balance is checked through the comparative analysis of data, and the system precision and accuracy after the rotor wing balance test bed is leveled are given.
Description
Technical Field
The invention belongs to the technical field of helicopter model rotor tests, and particularly relates to a composite loading on-site checking device and method for a rotor skyhook test bed.
Background
The rotor balance is special equipment for measuring six-component force and moment of a rotor system, and is a key measuring system for rotor tests. The measurement accuracy and accuracy of the rotor wing balance loading test bed can be influenced by factors such as mechanical clearance and assembly, and field check on the rotor wing balance before the test is necessary.
At present, the on-site calibration after the rotor wing balance is horizontally installed on a test bed in China mainly comprises that a spring scale or a heavy object is subjected to unidirectional force loading, large-load loading cannot be carried out, and the coupling generated by six components of the rotor wing balance cannot be checked; meanwhile, the checking precision is low.
According to the method, the composite loading field checking device and method of the rotor wing balance flat-mounting test bed are designed, wide-range loading and composite loading after the rotor wing balance is mounted on the test bed are achieved, composite loading load and actual measurement values of the rotor wing balance are collected, whether problems exist in coefficient input of the rotor wing balance is checked through data comparison and analysis, and system precision and accuracy after the rotor wing balance is mounted on the test bed are judged.
Disclosure of Invention
The purpose of the invention is as follows: aiming at the problems in the prior art, the composite loading field checking device and method for the rotor wing balance loading test bed are provided, the composite loading after the rotor wing balance lifting force, the lateral force, the course force, the pitching moment and the rolling moment are loaded on the test bed can be realized, the composite loading load and the rotor wing balance measuring load are collected, whether the problem exists in the input of the rotor wing balance coefficient is checked through the comparative analysis of data, and the system precision and the accuracy after the rotor wing balance is flatly loaded on the test bed are judged.
The technical scheme of the invention is as follows: in order to achieve the above object, according to a first aspect of the present invention, there is provided a composite loading field calibration apparatus for a rotor mast rig test stand, comprising:
the rotor wing balance 1 is positioned at the bottom of the device and is used for six-element measurement of a rotor wing system;
a hub 2, wherein the hub 2 is vertically arranged on the upper part of the rotor balance 1;
a rigid component 3, wherein one end of the rigid component 3 is connected with the center of the hub 2 in a height adjustable mode, and the other end of the rigid component 3 is connected with the actuating cylinder 4;
the actuating cylinder 4 comprises a first actuating cylinder 41 arranged along the vertical direction, a second actuating cylinder 42 arranged along the course direction and a third actuating cylinder 43 arranged along the side direction; the first actuating cylinder 41 is fixed right above the rigid component 3, the center of the first actuating cylinder is coaxial with the hub 2, and one end of an output shaft of the first actuating cylinder 41 is rigidly and fixedly connected with the upper end face of the rigid component 3; the second actuating cylinder 42 is fixed on one side of the course right above the rigid component 3, the center of the second actuating cylinder 42 is coaxial with the center of the course, and one end of an output shaft of the second actuating cylinder 42 is rigidly and fixedly connected with the rigid component 3; the third actuating cylinder 43 is fixed on one side of the rigid component 3 in the lateral direction, the center of the third actuating cylinder is coaxial with the lateral center, and one end of an output shaft of the third actuating cylinder 43 is rigidly and fixedly connected with the rigid component 3.
In a possible embodiment, the actuator 4 is a force closed-loop actuator having a force sensor at the output shaft end.
In one possible embodiment, the rotor balance 1 comprises a force sensor.
According to a second aspect of the invention, a composite loading field checking method for a rotor wing balance-mounted test bed is provided, and the device is characterized by specifically comprising the following steps:
s1: one end of the rigid component 3 is arranged in the center of the hub 2, and the other end of the rigid component is respectively connected with the first actuating cylinder 41, the second actuating cylinder 42 and the third actuating cylinder 43;
s2: determining the lateral force F of the rotor balance according to the range of the rotor balancexLifting force FyCourse force FzAnd the distance L between the upper end face of the rigid assembly 3 and the upper surface of the rotor balance 1 is calculated by the following formula one:
L＝Mx/Fxis like
Wherein M isxIs the range of the rolling moment of the rotor wing balance;
s3: before the rotor wing balance is loaded, the initial reading F of the force and the moment in each direction of the rotor wing balance is collectedx0、Fy0、Fz0、Mx0、Mz0；
S4, the first actuating cylinder 41 loads the lifting force F on the rotor balancey1And collecting the lift force F measured by the corresponding rotor balancey2；
S5: lift F measured by the rotor balance collectedy2Subtracting the initial reading F of the lift direction of the rotor balancey0And then loading force F with the actuator cylinder 41y1Performing checking error analysis, and calculating a lift error epsilon 1 of the rotor wing balance according to the following formula II;
ε1＝(Fy2-Fy0-Fy1)/Fy1100% of formula II
S6: the second actuating cylinder 42 loads the heading force F on the rotor balancez1Corresponding to the loaded pitching moment Mz1,Mz1Calculated according to equation three below:
Mz1＝Fz1l formula III
And collecting the course force F of the rotor balance in the corresponding statez2And pitching moment Mz2；
S7: the collected course force F of the rotor balancez2Subtracting the initial reading F of the rotor balance course force directionz0Pitching moment Mz2Subtracting rotor wing balance pitching moment initial reading Mz0Respectively, and the loading force F of the actuating cylinder 41z1、Mz1Carrying out error analysis;
calculating the heading force error epsilon 2 of the rotor balance according to the following formula:
ε2＝(Fz2-Fz0-Fz1)/Fz1100% of formula IV
Calculating the pitching moment error epsilon 3 according to the following formula five:
ε3＝(Mz2-Mz0-Mz1)/Mz1100% of formula V
S8: the second actuator cylinder 43 applies a force F to the rotor balancex1Corresponding to the loaded pitching moment Mx1，Mx1Calculated according to the following equation six:
Mx1＝Fx1l type six
And collecting the course force F of the rotor balance in the corresponding statex2And pitching moment Mx2；
S9: the lateral force F of the rotor balance to be collectedx2Subtracting the initial reading F of the rotor balance lateral force directionx0Rolling moment Mx2Subtracting the initial roll moment M of the rotor balancex0And respectively the loading force F of the actuating cylinder 41x1、Mx1Carrying out error analysis;
and calculating the lateral force error epsilon 4 of the rotor wing balance according to the following formula:
ε4＝(Fx2-Fx0-Fx1)/Fx1100% formula seven
And calculating the roll torque error epsilon 5 according to the following formula eight:
ε5＝(Mx2-Mx0-Mz1)/Mx1100% of formula eight
S10: verifying whether error ranges of epsilon 1, epsilon 2, epsilon 3, epsilon 4 and epsilon 5 meet the calibration requirements or not, and if so, passing the calibration; otherwise, the calibration fails.
In one possible embodiment, in step S2, the rotor balance lateral force FxLifting force FyCourse force FzThe loading range does not exceed 80% of the range of the rotor balance.
In a possible embodiment, in step S2, the distance L between the upper end surface of the rigid component 3 and the upper surface of the rotor balance 1 can also be calculated by the following formula nine:
L＝Mz/Fznine-degree of expression
Wherein M iszIs the rotor balance pitching moment.
In a possible embodiment, in step S4, the first ram 41 is simultaneously applied to the rotor balance to apply the loading force F to the rotor balancey1The second actuator cylinder 42 applies a loading force F to the rotor balancez1The second actuator cylinder 43 applies a loading force F to the rotor balancex1Collecting rotor balance lift force Fy2Course force Fz2Lateral force Fx2Pitching moment Mz2Rolling moment Mx2。
In one possible embodiment, in said step S10, the calibration requirement is that the error range of e 1, e 2, e 3, e 4, e 5 is not more than 1%.
The invention has the beneficial effects that:
the invention provides a composite loading field checking device and method for a rotor wing balance flat-mounting test bed, which can realize composite loading after the rotor wing balance flat-mounting test bed, collect composite loading load and rotor wing balance measurement, check whether the coefficient input of the rotor wing balance is in problem or not through data comparison and analysis, and ensure the system precision and accuracy after the rotor wing balance flat-mounting test bed.
Drawings
FIG. 1 is a schematic view of the apparatus of the present invention;
FIG. 2 is a flow chart of the method of the present invention;
wherein:
1-a rotor balance; 2-a hub; 3-a rigid component; 41-a first actuator cylinder; 42-a second actuator cylinder; 43-third actuating cylinder.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
As shown in fig. 1, a rotor balance loading test bed composite loading field checking device is characterized by comprising:
the rotor wing balance 1 is positioned at the bottom of the device and is used for six-element measurement of a rotor wing system;
a hub 2, wherein the hub 2 is vertically arranged on the upper part of the rotor balance 1;
a rigid component 3, wherein one end of the rigid component 3 is connected with the center of the hub 2 in a height adjustable mode, and the other end of the rigid component 3 is connected with the actuating cylinder 4;
the actuating cylinder 4 comprises a first actuating cylinder 41 arranged along the vertical direction, a second actuating cylinder 42 arranged along the course direction and a third actuating cylinder 43 arranged along the side direction; the first actuating cylinder 41 is fixed right above the rigid component 3, the center of the first actuating cylinder is coaxial with the hub 2, and one end of an output shaft of the first actuating cylinder 41 is rigidly and fixedly connected with the upper end face of the rigid component 3; the second actuating cylinder 42 is fixed on one side of the course right above the rigid component 3, the center of the second actuating cylinder 42 is coaxial with the center of the course, and one end of an output shaft of the second actuating cylinder 42 is rigidly and fixedly connected with the rigid component 3; the third actuating cylinder 43 is fixed on one side of the rigid component 3 in the lateral direction, the center of the third actuating cylinder is coaxial with the lateral center, and one end of an output shaft of the third actuating cylinder 43 is rigidly and fixedly connected with the rigid component 3.
The actuator cylinder 4 is a power closed-loop actuator cylinder, and the output shaft end of the power closed-loop actuator cylinder is provided with a force sensor.
The rotor balance 1 comprises a force sensor.
As shown in fig. 2, a method for performing composite loading field calibration on a rotor balance loading test bed, taking a rotor balance to perform composite loading field calibration on the loading test bed, includes the following steps:
first, the rotor balance is scaled as follows:
TABLE 1 certain rotor balance Range
| Component(s) of | Fy | Fx | Fz | Mz | Mx |
| Design load | 9600N | 850N | 620N | 620N·m | 850N·m |
Determining the distance between the force loading center of the rigid component 3 and the upper plate of the rotor balance according to the measuring range of the rotor balance as
L＝Mz/Fz1 m;
according to the measuring range of the rotor wing balance, determining that the composite loading field check load of the rotor wing balance is as follows according to the load not exceeding 80% of the load of the rotor wing balance:
Fy1＝7680N；Fx1＝680N；Fz1＝496N。
moment corresponding to loading:
Mx1＝680N·m Mz1＝496N·m
before the rotor wing balance is loaded, the initial reading F of the force and the moment in each direction of the rotor wing balance is collectedx0＝0；Fy0＝0；Fz0＝0；Mx0＝0；Mz0＝0。
Force F applied to the rotor balance by the first actuator 41y17680N; loaded with force F by the second actuator cylinder 42z1496N, corresponding to the loading moment Mz1＝496 N.m; loaded by a third actuating cylinderx1680N, corresponding to the loading moment Mx1＝680N·m。
Collecting rotor balance load Fy27700N; course force Fz2500N; lateral force Fx2683N; pitching moment Mz2501N · m; rolling moment Mx2＝683N·m。
By theoretical loading of the load Fy1，Fz1，Fx1，Mz1；Mx1And calculating the composite loading error of each component of the rotor balance according to the difference value of the actual measurement load of the rotor balance as follows:
ε1＝(Fy2-Fy0-Fy1)/Fy1*100％＝0.28％
ε2＝(Fx2-Fx0-Fx1)/Fx1*100％＝0.8％
ε3＝(Mx2-Mx0-Mz1)/Mx1*100％＝1％
ε4＝(Fz2-Fz0-Fz1)/Fz1*100％＝0.44％
ε5＝(Mz2-Mz0-Mz1)/Mz1*100％＝0.44％
the error ranges are not more than 1%, and the calibration is passed.
The foregoing is merely a detailed description of the embodiments of the present invention, and some of the conventional techniques are not detailed. The scope of the present invention is not limited thereto, and any changes or substitutions that can be easily made by those skilled in the art within the technical scope of the present invention will be covered by the scope of the present invention. The protection scope of the present invention shall be subject to the protection scope of the claims.
Claims (8)
1. The utility model provides a rotor balance dress test bench composite loading field check device which characterized in that includes:
the rotor wing balance (1) is positioned at the bottom of the device and is used for six-element measurement of a rotor wing system;
a hub (2), wherein the hub (2) is vertically arranged at the upper part of the rotor wing balance (1);
a rigid component (3), wherein one end of the rigid component (3) is connected with the center of the hub (2) in a height-adjustable mode, and the other end of the rigid component (3) is connected with the actuating cylinder (4);
the actuating cylinder (4), the actuating cylinder (4) comprises a first actuating cylinder (41) arranged along the vertical direction, a second actuating cylinder (42) arranged along the course direction and a third actuating cylinder (43) arranged along the lateral direction; the first actuating cylinder (41) is fixed right above the rigid component (3), the center of the first actuating cylinder is coaxial with the hub (2), and one end of an output shaft of the first actuating cylinder (41) is rigidly and fixedly connected with the upper end face of the rigid component (3); the second actuating cylinder (42) is fixed on one side of the course right above the rigid component (3), the center of the second actuating cylinder is coaxial with the center of the course, and one end of an output shaft of the second actuating cylinder (42) is rigidly and fixedly connected with the rigid component (3); the third actuating cylinder (43) is fixed on one lateral side right above the rigid component (3), the center of the third actuating cylinder is coaxial with the lateral center, and one end of an output shaft of the third actuating cylinder (43) is rigidly and fixedly connected with the rigid component (3).
2. The rotor balance loading test bed composite loading field checking device according to claim 1, wherein the actuator cylinder (4) is a force closed loop actuator cylinder, and a force sensor is arranged at an output shaft end of the force closed loop actuator cylinder.
3. A rotor balance rig composite loading field verification device according to claim 1, characterised in that the rotor balance (1) comprises a force sensor.
4. A composite loading field check method for a rotor wing balance loading test bed adopts the composite loading field check device for the rotor wing balance loading test bed according to any one of claims 1 to 3, and is characterized by comprising the following steps:
s1: one end of the rigid component (3) is arranged in the center of the hub (2), and the other end of the rigid component is respectively connected with the first actuating cylinder (41), the second actuating cylinder (42) and the third actuating cylinder (43);
s2: determining the lateral force F of the rotor balance according to the range of the rotor balancexLifting force FyCourse force FzAnd the distance L between the upper end surface of the rigid component (3) and the upper surface of the rotor balance (1) is calculated by the following formula I:
L＝Mx/Fxis like
Wherein M isxIs the range of the rolling moment of the rotor wing balance;
s3: before the rotor wing balance is loaded, the initial reading F of the force and the moment in each direction of the rotor wing balance is collectedx0、Fy0、Fz0、Mx0、Mz0；
S4, applying a lifting force F to the rotor balance by the first actuating cylinder (41)y1And collecting the lift force F measured by the corresponding rotor balancey2；
S5: lift F measured by the rotor balance collectedy2Subtracting the initial reading F of the lift direction of the rotor balancey0And then with the force F applied to the actuator cylinder (41)y1Performing error analysis, and calculating lift error epsilon of the rotor balance according to the following formula II1；
ε1＝(Fy2-Fy0-Fy1)/Fy1100% of formula II
S6: the second actuating cylinder (42) loads a heading force F on the rotor balancez1Corresponding to the loaded pitching moment Mz1,Mz1Calculated according to equation three below:
Mz1＝Fz1l formula III
And collecting the course force F of the rotor balance in the corresponding statez2And pitching moment Mz2；
S7: the collected course force F of the rotor balancez2Subtracting the initial reading F of the rotor balance course force directionz0Pitching moment Mz2Subtracting rotor wing balance pitching moment initial reading Mz0Respectively associated with the loading force F of said actuating cylinder (41)z1、Mz1Carrying out error analysis;
calculating course force error epsilon of the rotor wing balance according to the following formula2：
ε2＝(Fz2-Fz0-Fz1)/Fz1100% of formula IV
Calculating the error epsilon of the pitching moment according to the formula3：
ε3＝(Mz2-Mz0-Mz1)/Mz1100% of formula V
S8: the second actuator cylinder (43) applies a force F to the rotor balancex1Corresponding to the loaded pitching moment Mx1，Mx1Calculated according to the following equation six:
Mx1＝Fx1l type six
And collecting the course force F of the rotor balance in the corresponding statex2And pitching moment Mx2；
S9: the lateral force F of the rotor balance to be collectedx2Subtracting the initial reading F of the rotor balance lateral force directionx0Rolling moment Mx2Subtracting the initial roll moment M of the rotor balancex0And respectively said actuator cylinder (41) is loaded with a force Fx1、Mx1Carrying out error analysis;
according to the following formula, the lateral force error epsilon of the rotor wing balance is calculated4：
ε4＝(Fx2-Fx0-Fx1)/Fx1100% formula seven
Calculating the rolling moment error epsilon according to the following formula5：
ε5＝(Mx2-Mx0-Mz1)/Mx1100% of formula eight
S10: verification of epsilon1、ε2、ε3、ε4、ε5Whether the error range of (1) meets the calibration requirement or not, and if so, the calibration is passed; otherwise, the calibration fails.
5. The rotor balance loading test bed composite feeder according to claim 4Onboard verification method, characterized in that in step S2, the rotor balance lateral force FxLifting force FyCourse force FzThe loading range does not exceed 80% of the range of the rotor balance.
6. The method for the composite loading on-site verification of the rotor balance loading test bed according to claim 4, wherein in the step S2, the distance L between the upper end face of the rigid assembly (3) and the upper surface of the rotor balance (1) can be calculated by the following formula nine:
L＝Mz/Fznine-degree of expression
Wherein M iszIs the rotor balance pitching moment.
7. The method for rotor balance rig composite loading field verification according to claim 4, wherein in step S4, the first ram (41) is simultaneously applied to the rotor balance to apply a loading force F to the rotor balancey1The second actuator cylinder (42) applies a loading force F to the rotor balancez1The second actuator cylinder (43) applies a loading force F to the rotor balancex1Collecting rotor balance lift force Fy2Course force Fz2Lateral force Fx2Pitching moment Mz2Rolling moment Mx2。
8. The method for rotor-scale rig composite-loading field calibration according to claim 4, wherein in step S10, the calibration requirement is ε1、ε2、ε3、ε4、ε5The error range of (2) is not more than 1%.
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