CN112326122A - Coaxial forward and reverse rotation dual-rotor balance adjustment method - Google Patents
Coaxial forward and reverse rotation dual-rotor balance adjustment method Download PDFInfo
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M1/00—Testing static or dynamic balance of machines or structures
- G01M1/30—Compensating imbalance
- G01M1/32—Compensating imbalance by adding material to the body to be tested, e.g. by correcting-weights
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Abstract
The invention discloses a balance adjustment method for a coaxial forward and reverse rotating dual rotor wing, which ignores the phase of an unbalanced point and adopts a multiple model design to correlate the test weight with the dynamic balance amplitude. And determining a balance vector by using a fuzzy algorithm, and determining and adjusting the mass and the phase of the balance weight through directional vector decomposition and synthesis to achieve coaxial dual-rotor balance correction. The invention uses the existing balance test instrument, namely the method can be used for completing the balance adjustment of the coaxial forward and reverse rotating dual-rotor system without researching and developing special coaxial forward and reverse rotating dual-rotor balance test equipment.
Description
Technical Field
The invention belongs to the aviation testing technology, and relates to a balance adjustment method of a coaxial forward and reverse rotating dual-rotor wing, which is used for rotor wing balancing in the maintenance guarantee of a coaxial forward and reverse rotating dual-rotor wing helicopter.
Background
The eccentric force generated by the unbalanced weight of the rotating body and the generated vibration magnitude are in accordance with F ═ m × a, that is, the unbalanced force F generated by the unbalanced mass m during rotation has a certain functional relationship with the vibration acceleration value a of the structure.
The single-layer rotor helicopter can easily acquire the vibration amplitude and the orientation of the rotor system by using the method, and then balance adjustment of the rotor system is carried out by using a central mirror image method and a parallelogram method.
The rotor system of the coaxial forward and reverse rotation dual-rotor helicopter is influenced by coupling of two vibration sources in the same frequency and reverse directions of the upper rotor and the lower rotor, so that the accurate measurement of the position of the unbalanced point of the upper rotor and the lower rotor of the dual-rotor helicopter becomes extremely difficult, and a great deal of inconvenience is brought to the balance adjustment of the rotor system of the coaxial forward and reverse rotation dual-rotor helicopter.
The invention provides a dynamic balance adjusting method of a coaxial forward and reverse rotating dual rotor wing under the background. The adjusting method only needs to provide the vibration amplitude of the rotor system, and does not need to determine the specific position of the unbalance point, namely the vibration phase.
Disclosure of Invention
The invention aims to provide a balance adjustment method of a coaxial forward and reverse rotating dual rotor wing, which is used for balance adjustment of a rotor wing system of a coaxial forward and reverse rotating dual rotor wing helicopter, and reduces the influence on flight safety caused by the vibration of a helicopter body due to the imbalance of the rotor wing system.
The invention aims to be realized by the following technical scheme:
a balance adjustment method for coaxial forward and reverse rotating dual rotors is the same as that for an upper rotor and a lower rotor, wherein the balance adjustment for any rotor comprises the following steps:
step one, determining each loadable counterweight point of a rotor wing;
secondly, determining the mass p of the standard counterweight plate, adding the standard counterweight plate on one of the counterweight points determined in the step one, performing dynamic balance monitoring, and recording the vibration amplitude after counterweight;
step three, repeating the operation of the step two, monitoring and recording the vibration amplitude after the counterweight is added with the standard counterweight sheets on other counterweight points;
step four, taking the origin of coordinates as the circle center, and taking the initial amplitude l of the rotor wing0Making a core circle for the radius, and projecting each balance weight point of the rotor wing on the core circle in proportion;
step five, sequentially making weight test circles by taking each weight point as a circle center and the vibration amplitude value of each corresponding weight point as a radius, wherein the intersection points of the weight test circles form a polygon;
step six, solving the center of the polygon in the step five, and recording a vector of the center of the core circle pointing to the center of the polygon
Measuring the length of the connecting line between the center of the polygon and the center of the core circle, and converting the length into vibration amplitude according to a scale
Step seven, passing
And
establishing a curve model of the vibration amplitude and the counterweight mass to obtain the counterweight mass corresponding to the vibration amplitude after each counterweight;
step eight, taking the origin of coordinates as the center of a circle,
making a second core circle for the radius, and projecting each balance weight point of the rotor wing on the second core circle in proportion;
step nine, sequentially making second counterweight circles by taking each counterweight point as a circle center and each counterweight mass as a radius, wherein the intersection point of each second counterweight circle forms a second polygon;
step ten, solving the center of the second polygon in the step nine, wherein the center of the second core circle points to p of the center point of the second polygontThe balance weight which needs to be loaded for adjusting the balance of the rotor system is decomposed to two adjacent balance points by vector decomposition, so that the balance adjustment of the rotor system is realized.
The invention has the beneficial effects that: the invention ignores the phase of the unbalanced point and adopts a multiple model design to correlate the test weight with the dynamic balance amplitude. And determining a balance vector by using a fuzzy algorithm, and determining and adjusting the mass and the phase of the balance weight through directional vector decomposition and synthesis to achieve coaxial dual-rotor balance correction. The invention uses the existing balance test instrument, namely the method can be used for completing the balance adjustment of the coaxial forward and reverse rotating dual-rotor system without researching and developing special coaxial forward and reverse rotating dual-rotor balance test equipment.
Drawings
FIG. 1 is a schematic diagram of the dynamic balance monitoring result synthesis;
FIG. 2 is a schematic view of a vibration amplitude versus counterweight mass curve model;
FIG. 3 is a schematic illustration of a mass and phase solution for a balancing weight.
Detailed Description
The invention is described in further detail below with reference to the figures and the examples.
The dynamic balance adjustment of the traditional rotating part mostly adopts a central mirror image method, the balance adjustment method of the coaxial forward and reverse rotating double-rotor system shown in the embodiment is out of the traditional thinking, an unbalanced point is not required to be positioned, and a multiple dynamic response model design is adopted, so that the test weight is related to the dynamic balance amplitude. And determining a balance vector by using a fuzzy algorithm, and determining the mass and the phase of a balance weight through directional vector decomposition and synthesis to achieve balance adjustment of the coaxial dual-rotor system.
For a coaxial dual rotor system, the imbalance of the upper rotor contributes more to the balance effect of the coaxial dual rotor system, so the balance adjustment is performed first from the upper rotor. Mainly comprises the following steps:
step one, determining a loadable counterweight point of an upper-layer rotor wing, taking a clamping machine as an example, and taking the counterweight point as the root part of a blade, wherein the total of three points are determined.
Step two, determining the mass p (such as 100 grams) of the standard weight plate, adding the standard weight plate on the No. 1 weight point determined in the step one, performing dynamic balance monitoring, and recording the vibration amplitude l after weight balancing1。
Step three, repeating the operation of the step two, monitoring and recording the vibration amplitude l after the counterweight is added with the standard counterweight sheets on the No. 2 counterweight point and the No. 3 counterweight point respectively2And l3。
Step four, taking the origin of coordinates as the circle center, and taking the initial amplitude l of the rotor wing0Making a core circle for the radius ofThe No. 1, 2 and 3 counterweight points of the upper rotor wing are projected on the core circle in proportion.
Step five, respectively taking No. 1, No. 2 and No. 3 key points as circle centers, i1、l2、l3The trial circles are sequentially made for the radius, and the intersection points of several trial circles form a polygon, as shown in fig. 1.
And step six, solving the center of the polygon in the step five, and connecting the center of the polygon with the center of the core circle. The vector of the center of the core circle pointing to the center of the polygon is the resultant of the standard mating rotor vibration loaded on the number 1, 2 and 3 counterweight points in sequence
Measuring the length of the connecting line between the center of the pentagon and the center of the core circle, and converting the length into a vibration amplitude according to a scale
If it is not
And (l)1+l2+l3) The result of/3 is very different, choose to
Step seven, passing
And
establishing a curve model of vibration amplitude and counterweight mass to obtain l0、l1、l2、l3Corresponding p0、p1、p2、p3As shown in fig. 2.
Step eight, taking the origin of coordinates as the center of a circle,
making a second core circle for the radius, and proportionally adding No. 1, No. 2 and No. 3 counterweight points of the upper rotor wingProjected on a circle.
Step nine, respectively using No. 1, No. 2 and No. 3 key points as circle centers, p1、p2、p3The counterweight circles are made for the radii in turn, and the intersection of several counterweight circles forms a second polygon, as shown in fig. 3.
Step ten, solving the center of the second polygon in the step nine, wherein the center of the second core circle points to p of the center point of the second polygontThe balance weight which needs to be loaded for adjusting the balance of the rotor system is decomposed to two adjacent balance points by vector decomposition, so that the balance adjustment of the rotor system is realized.
The balance adjustment principle of the upper layer rotor wing and the lower layer rotor wing of the coaxial double-rotor wing is the same, and finally the dynamic balance adjustment of the coaxial double-rotor wing system is realized.
It should be understood that equivalents and modifications of the technical solution and inventive concept thereof may be made by those skilled in the art, and all such modifications and alterations should fall within the scope of the appended claims and protection of the present invention.
Claims (2)
1. A balance adjustment method for coaxial forward and reverse rotating dual rotors is characterized in that the balance adjustment method for the rotors on any layer is the same as that of the rotors on the lower layer, and comprises the following steps:
step one, determining each loadable counterweight point of a rotor wing;
secondly, determining the mass p of the standard counterweight plate, adding the standard counterweight plate on one of the counterweight points determined in the step one, performing dynamic balance monitoring, and recording the vibration amplitude after counterweight;
step three, repeating the operation of the step two, monitoring and recording the vibration amplitude after the counterweight is added with the standard counterweight sheets on other counterweight points;
step four, taking the origin of coordinates as the circle center, and taking the initial amplitude l of the rotor wing0Making a core circle for the radius, and projecting each balance weight point of the rotor wing on the core circle in proportion;
step five, sequentially making weight test circles by taking each weight point as a circle center and the vibration amplitude value of each corresponding weight point as a radius, wherein the intersection points of the weight test circles form a polygon;
step six, solving the center of the polygon in the step five, and recording a vector of the center of the core circle pointing to the center of the polygon
Measuring the length of the connecting line between the center of the polygon and the center of the core circle, and converting the length into vibration amplitude according to a scale
Step seven, passing
And
establishing a curve model of the vibration amplitude and the counterweight mass to obtain the counterweight mass corresponding to the vibration amplitude after each counterweight;
step eight, taking the origin of coordinates as the center of a circle,
making a second core circle for the radius, and projecting each balance weight point of the rotor wing on the second core circle in proportion;
step nine, sequentially making second counterweight circles by taking each counterweight point as a circle center and each counterweight mass as a radius, wherein the intersection point of each second counterweight circle forms a second polygon;
step ten, solving the center of the second polygon in the step nine, wherein the center of the second core circle points to p of the center point of the second polygontThe balance weight which needs to be loaded for adjusting the balance of the rotor system is decomposed to two adjacent balance points by vector decomposition, so that the balance adjustment of the rotor system is realized.
2. A method according to claim 1, wherein in step six, if at all, the balance adjustment is made in the case of a coaxial forward/reverse dual rotor
The difference between the average value of the vibration amplitude after each balance weight is larger, and the average value of the vibration amplitude after each balance weight is selected as the average value
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|---|---|---|---|---|
| JPH04351348A (en) * | 1991-05-30 | 1992-12-07 | Hitachi Ltd | Rotor balance correcting method |
| US20110158809A1 (en) * | 2009-12-31 | 2011-06-30 | Zhihong Luo | Dual-rotor model helicopter control system |
| CN104316266A (en) * | 2014-08-26 | 2015-01-28 | 中国直升机设计研究所 | Correction-function-contained dynamic balance adjustment phase calculating method of helicopter model |
| US9216821B1 (en) * | 2012-01-03 | 2015-12-22 | The Boeing Company | Methods and systems for helicopter rotor blade balancing |
| CN105181249A (en) * | 2015-06-04 | 2015-12-23 | 中国航空工业集团公司上海航空测控技术研究所 | Primary balance weight adjustment method for helicopter rotor balance |
| CN205801506U (en) * | 2016-05-24 | 2016-12-14 | 北京浩恒征途航空科技有限公司 | The center frame of multi-rotor aerocraft |
| CN109747817A (en) * | 2019-03-11 | 2019-05-14 | 王继华 | A kind of no empennage vector coaxal helicopter design |
| CN110243541A (en) * | 2019-07-18 | 2019-09-17 | 新兴铸管股份有限公司 | Blower on-line dynamic balancing calculation method |
| CN110926699A (en) * | 2019-11-08 | 2020-03-27 | 深圳精匠云创科技有限公司 | Rotor dynamic balance correction method and automation equipment using same |
-
2020
- 2020-09-25 CN CN202011021075.XA patent/CN112326122B/en active Active
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH04351348A (en) * | 1991-05-30 | 1992-12-07 | Hitachi Ltd | Rotor balance correcting method |
| US20110158809A1 (en) * | 2009-12-31 | 2011-06-30 | Zhihong Luo | Dual-rotor model helicopter control system |
| US9216821B1 (en) * | 2012-01-03 | 2015-12-22 | The Boeing Company | Methods and systems for helicopter rotor blade balancing |
| CN104316266A (en) * | 2014-08-26 | 2015-01-28 | 中国直升机设计研究所 | Correction-function-contained dynamic balance adjustment phase calculating method of helicopter model |
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| CN109747817A (en) * | 2019-03-11 | 2019-05-14 | 王继华 | A kind of no empennage vector coaxal helicopter design |
| CN110243541A (en) * | 2019-07-18 | 2019-09-17 | 新兴铸管股份有限公司 | Blower on-line dynamic balancing calculation method |
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