CN106516104A - Device for reducing rotor wing vibration - Google Patents
Device for reducing rotor wing vibration Download PDFInfo
- Publication number
- CN106516104A CN106516104A CN201611082748.6A CN201611082748A CN106516104A CN 106516104 A CN106516104 A CN 106516104A CN 201611082748 A CN201611082748 A CN 201611082748A CN 106516104 A CN106516104 A CN 106516104A
- Authority
- CN
- China
- Prior art keywords
- trailing edge
- winglet
- spring steel
- enlarger
- piezoelectric actuator
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/51—Damping of blade movements
Abstract
The invention provides a device for reducing rotor wing vibration and relates to the field of aviation. The problem that the performance of a mechanism is greatly reduced due to the fact that the drive displacement of existing drivers used for driving a rotor wing trailing edge little wing is small, and the restoring force needs to be provided by a spring is solved. Five piezoelectric stack ceramics are installed between the inner walls of the short edges of a spring steel oval amplification mechanism and are connected through two wedge-shaped pre-tightening blocks. The spring steel oval amplification mechanism is used for amplifying the drive displacement produced by the piezoelectric stack ceramics. The amplification multiple alpha of the spring steel oval amplification mechanism is related to the wall thickness l of the spring steel oval amplification mechanism and the angle theta formed by arc edges. After applying voltage, a piezoelectric driver shrinks to the left side so as to produce the drive displacement, drives a trailing edge little wing connecting rod to move and then drives a trailing edge little wing to deflect around a little wing connection piece. The device is used for reducing rotor wing vibration.
Description
Technical field
The present invention relates to be used to reduce the device of rotor vibration.Belong to aviation field.
Background technology
Helicopter since the advent of the world, either suffers from very important status at military or civilian aspect.Helicopter
Have the advantages that to take off vertically/throwing power, hovering and lower-speed state under high maneuverability so that helicopter can complete to be permitted
Many unique tasks, such as rescue at sea, investigation etc..But also there are many problems to limit always to go straight up to during Helicopter Development
The development of machine technology, such as, as the riding quality that vibration and noise cause is poor, the fatigue life of structure is low and very high
Maintenance cost etc..
It is different from fixed wing airplane, as the cyclic pitch of lifting airscrew causes blade to bear the alternation of 1/rev frequencies
The inertial load of aerodynamic loading and azimuth direction, while being also subjected to than larger harmonic load in oar Pan Chu.These are unstable
Factor rotor hub can be caused to bear larger alternate load, so as to evoke the vibration of body.On the one hand these vibrations are to make
It is to produce so as to affect the main cause of helicopter performance, fatigue life and riding quality, on the other hand into helicopter fuselage vibration
One of raw blade moment of flexure, the reason for promote blade fatigue.Therefore, development of the vibration of reduction helicopter to helicopter has important
Meaning.
Vibration and noise problem are the basic obstacles for affecting helicopter work efficiency.At present, many is with regard to lifting airscrew
Research all focus on by reducing the vibration of rotor improving the integral working of helicopter.Active trailing edge winglet method is
One of method for being considered as most being hopeful realizing rotor Active Vibration Control.Early stage technology develops, mainly using bump leveller,
The method that isolation mounting etc. passively suppresses is reducing vibration.Traditional vibration isolator and dashpot be not due to needing outside energy to carry
For structure is simpler, it is easy to accomplish and there is preferable economy and reliability, obtain certain on helicopter damping technology
Application.But their weight cost is big, is not suitable with the change of rotor working speed and structural dynamic in helicopter flight state
Change, with significant limitation.With going out for intellectual material such as marmem, shape-memory polymer, piezoelectric etc.
Now with fast development so that active trailing edge winglet technical merit is greatly improved.Wherein piezoelectric is because of its response frequency
Rate is high, control is simple, small volume, it is lightweight the advantages of, using with obvious advantage in active trailing edge winglet technology.
In general, the oscillating load that lifting airscrew oscillating load is delivered to helicopter fuselage is made up of N order harmonicses
, wherein, N is the number of rotor blade.If the rotating speed of rotor is Ω, the response frequency of oscillating load is N Ω, and this just means
When control is applied, it is desirable to which the frequency of the Additional pneumatic load that trailing edge winglet is produced will also reach more than N Ω, and rotor blade
Installing space it is limited, it is very big to the size limitation of driver, therefore requirement ratio of the active trailing edge winglet method to driver
Higher, driver to be had the characteristic of high thrust, big displacement, small size and high response frequency.Using the driver of piezoelectric
With driving force is larger and the characteristics of little drive displacement, drive displacement must be amplified and could be obtained enough drive displacements.At present
Activation configuration mainly have：Piezoelectricity induction twisted plate driving structure, L-L types, piezo tube actuator etc., these structures can be
Deflection for trailing edge winglet to a certain extent provides power output and output displacement, but there is also some shortcomings, and for example L-L types drive
Dynamic device needs spring to provide restoring force in high frequency pumping, and the usage frequency of spring is narrower so that mechanism performance greatly under
Drop.Therefore, it is that active control winglet method realizes high-efficiency vibration to design a kind of small size, lightweight, the driver of height output response
The key of control.
The content of the invention
The present invention is that have that drive displacement is little, needs to solve the existing driver for driving rotor trailing edge winglet
Spring providing restoring force, the problem for causing the performance of mechanism greatly to decline.Now provide for reducing the device that rotor vibrates.
For reducing the device of rotor vibration, the rotor includes basic blade, trailing edge winglet and trailing edge winglet connection sheet,
Trailing edge winglet is connected by winglet connection sheet with basic blade, and winglet connection sheet can occur bending and deformation,
Device for reducing rotor vibration includes metal framework, piezoelectric actuator and winglet connecting shaft,
Metal framework is cured to the inside of basic blade during paddle molding, and piezoelectric actuator is fixed on metal framework
It is interior,
Piezoelectric actuator includes spring steel ellipse enlarger, piezoelectric stack ceramics and wedge shape pretension block,
Spring steel ellipse enlarger is axially symmetric structure, and has rigidity and recoverable force function, and spring steel is oval
One arc side of shape enlarger is fixedly connected with a medial wall of metal framework, spring steel ellipse enlarger it is another
Individual arc side is connected with trailing edge winglet by winglet connecting shaft,
5 piezoelectric stack ceramics, 5 piezoelectric stacks are installed between the inwall of spring steel ellipse two straight flanges of enlarger
It is attached using two wedge shape pretension blocks between ceramics, wedge shape pretension block, is applied for 5 piezoelectric stack ceramics to installing
Certain pretightning force,
Spring steel ellipse enlarger, for the drive displacement that piezoelectric stack ceramics are produced is amplified, spring steel
Amplification a of oval enlarger is relevant with the wall thickness l and arc side angulation θ of spring steel ellipse enlarger,
After piezoelectric actuator applied voltage, piezoelectric actuator can shrink generation drive displacement to the left, drive trailing edge little
Wing connecting rod is moved, and then drives trailing edge winglet to enter horizontal deflection around winglet connection sheet.
Beneficial effects of the present invention are：
The piezoelectric actuator of the present invention has size little, lightweight, it is adaptable to the sky that helicopter blade is long and narrow and thickness is little
Between；
The output displacement of this piezoelectric actuator is relevant with the wall thickness of spring steel ellipse enlarger, and spring steel ellipse is put
The wall thickness of great institutions is less, and the displacement that piezoelectric actuator is produced is bigger；The wall thickness of spring steel ellipse enlarger is to pressure simultaneously
The driving force of electric drive and response frequency affect very big；
The output displacement of this piezoelectric actuator is larger, High power output, response frequency are high, and compact conformation can meet and go straight up to
The effective control of the dither load produced in machine rotor high-speed rotation；It is different from the driver of traditional resonance type, by
Rigidly larger in the wall thickness of piezoelectric actuator, its output frequency is identical with the electric voltage frequency of piezoelectric actuator.Piezoelectric actuator is
Controlled by the alternating voltage of applying out of phase, the frequency for driving the deflection of trailing edge winglet and the voltage for applying of driver
Frequency can be consistent.Different voltage magnitudes can drive trailing edge winglet to deflect different angles, and this driver can be real
Existing trailing edge winglet deflects 6 degree, and the additional inertance load and aerodynamic loading for deflecting generation by trailing edge winglet will be with rotor vibratory load
Partial offset is carried out, so as to realize the reduction of rotor vibratory load.The driver ellipse enlarger of the present invention has fine
Rigidity and recoverable force function, it is not necessary to additional spring substantially increases the deflection of trailing edge winglet providing restoring force
Response frequency and realize in wideband rotor vibratory load control effect.
Description of the drawings
Fig. 1 is the blade internal cross section figure for reducing the device of rotor vibration described in specific embodiment one；
Fig. 2 is the metal framework schematic diagram for fixing piezoelectric actuator；
Structural representations of the Fig. 3 for piezoelectric actuator；
Structural representations of the Fig. 4 for winglet connecting shaft；
Fig. 5 is piezoelectric actuator system scheme of installation.
Specific embodiment
Specific embodiment one：Illustrate present embodiment referring to figs. 1 to Fig. 5, described in present embodiment for dropping
The device of low rotor vibration, the rotor include basic blade 1, trailing edge winglet 5 and trailing edge winglet connection sheet 6,
Trailing edge winglet 5 is connected by winglet connection sheet 6 with basic blade 1, and winglet connection sheet 6 can occur bending and deformation,
Device for reducing rotor vibration includes metal framework 2, piezoelectric actuator 3 and winglet connecting shaft 4,
Metal framework 2 is cured to the inside of basic blade 1 during paddle molding, and piezoelectric actuator 3 is fixed on metal
In framework 2,
Piezoelectric actuator 3 includes spring steel ellipse enlarger 7, piezoelectric stack ceramics 8 and wedge shape pretension block 9,
Spring steel ellipse enlarger 7 is axially symmetric structure, and has rigidity and recoverable force function, and spring steel is oval
One arc side of shape enlarger 7 is fixedly connected with a medial wall of metal framework 2, spring steel ellipse enlarger 7
Another arc side is connected with trailing edge winglet 5 by winglet connecting shaft 4,
5 piezoelectric stack ceramics, 8,5 piezo stacks are installed between the inwall of spring steel ellipse 7 two straight flanges of enlarger
It is attached using two wedge shape pretension blocks 9 between heap ceramics 8, wedge shape pretension block 9, for 5 piezoelectric stack potteries to installing
Porcelain 8 applies certain pretightning force,
Spring steel ellipse enlarger 7, for the drive displacement that piezoelectric stack ceramics 8 are produced is amplified, spring
Amplification a of steel ellipse enlarger 7 is had with the wall thickness l and arc side angulation θ of spring steel ellipse enlarger 7
Close,
After 3 applied voltage of piezoelectric actuator, piezoelectric actuator 3 can shrink to the left and produce drive displacement, drive trailing edge
Winglet connecting rod 4 is moved, and then drives trailing edge winglet 5 to enter horizontal deflection around winglet connection sheet 6.
In present embodiment, 2 main fixations of metal framework can be in 1 forming process of basic blade by metal
Framework 2 is fixed on inside basic blade 1；Metal framework 2 and piezoelectric actuator 3 are installed at 1 span 0.62R of basic blade.
Winglet connection sheet 6 can occur bending and deformation, and allow trailing edge winglet 5 to enter horizontal deflection around winglet connection sheet 6.It is right
After 3 applied voltage of piezoelectric actuator, piezoelectric actuator 3 can shrink to the left, drive trailing edge winglet connecting rod 4 to move, and then drive
Dynamic trailing edge winglet 5 is deflected.If the voltage for applying is alternating voltage, piezoelectric actuator 3 can drive trailing edge winglet to deflect about 5.
The broadside up and down of spring steel ellipse enlarger 7 has must radian, in order to replied in driving
Restoring force is provided in journey, and then improves the response frequency of piezoelectric actuator.The effect of wedge shape pretension block 9 is to install 5 piezoelectricity
Apply certain pretightning force when stacking ceramic 8, to ensure the compactedness of internal structure, prevent due to driving caused by rigging error
Displacement is failed.
Specific embodiment two：Present embodiment is to the dress for reducing rotor vibration described in specific embodiment one
Put and be described further, in present embodiment, the chord length of trailing edge winglet 5 is the 20% of 1 length of basic blade.
Specific embodiment three：Present embodiment is to the dress for reducing rotor vibration described in specific embodiment one
Put and be described further, in present embodiment, one end of two wedge shape pretension blocks 9 is provided with 3 piezoelectric stack ceramics 8, two
The other end of wedge shape pretension block 9 is provided with 2 piezoelectric stack ceramics 8.
Specific embodiment four：Present embodiment is to the dress for reducing rotor vibration described in specific embodiment one
Put and be described further, in present embodiment, the wall thickness of spring steel ellipse enlarger 7 is more than 1.5mm.
In present embodiment, the wall thickness of spring steel ellipse enlarger 7 is more than 1.5mm so that piezoelectric actuator 3 has
Larger driving force and response frequency.
Specific embodiment five：Present embodiment is to the dress for reducing rotor vibration described in specific embodiment one
Put and be described further, in present embodiment, the thickness of piezoelectric stack ceramics 8 is 7mm.
Specific embodiment six：Present embodiment is to the dress for reducing rotor vibration described in specific embodiment one
Put and be described further, in present embodiment, amplification a of spring steel ellipse enlarger 7 is put with spring steel ellipse
The relational expression of the wall thickness l and arc side angulation θ of great institutions 7 is：
In formula, u represents displacement.
In present embodiment, amplification and the spring steel ellipse enlarger 7 of spring steel ellipse enlarger 7
Wall thickness l and angle, θ are relevant, and angle, θ is less, and the amplification of spring steel ellipse enlarger 7 is bigger, and spring steel ellipse is put
The wall thickness l of great institutions 7 is less, and the displacement that piezoelectric actuator 3 is produced is bigger.
Specific embodiment seven：Present embodiment is to the dress for reducing rotor vibration described in specific embodiment six
Put and be described further, in present embodiment, the span of arc side angulation θ is 4 ° to 30 °.
Specific embodiment eight：Present embodiment is to the dress for reducing rotor vibration described in specific embodiment one
Put and be described further, in present embodiment, be 0-150V to the scope of 3 applied voltage of piezoelectric actuator.
In present embodiment, to 3 applied voltage of piezoelectric actuator after, piezoelectric actuator 3 can shrink to the left, drive trailing edge
Winglet connecting rod 4 is moved, and then drives trailing edge winglet 5 to deflect.If the voltage for applying is alternating voltage, 3 meeting of piezoelectric actuator
Trailing edge winglet is driven to deflect about 5.
Specific embodiment nine：Present embodiment is to the dress for reducing rotor vibration described in specific embodiment one
Put and be described further, in present embodiment, the left end of trailing edge winglet connecting rod 4 is by screw thread and the right side of piezoelectric actuator 3
Fixed, the right-hand member of trailing edge winglet connecting rod 4 is connected by smooth axle with trailing edge winglet.
Specific embodiment ten：Present embodiment is to the dress for reducing rotor vibration described in specific embodiment nine
Put and be described further, in present embodiment, trailing edge winglet 5 enters horizontal deflection around winglet connection sheet 6, inertia force △ L can be produced
The inertia force and aerodynamic loading that can be produced with basic blade 1 with aerodynamic loading torque △ M is offset, so as to reach vibration damping
Effect.
In present embodiment, the additional inertance load and aerodynamic loading for deflecting generation by trailing edge winglet will be carried with rotor vibration
Lotus carries out partial offset, so as to realize the reduction of rotor vibratory load.
Claims (10)
1. it is used for reducing the device of rotor vibration, the rotor includes that basic blade (1), trailing edge winglet (5) and trailing edge winglet connect
Contact pin (6),
Trailing edge winglet (5) is connected by winglet connection sheet (6) with basic blade (1), and winglet connection sheet (6) can bend change
Shape,
Characterized in that,
Device for reducing rotor vibration includes metal framework (2), piezoelectric actuator (3) and winglet connecting shaft (4),
Metal framework (2) is cured to the inside of basic blade (1) during paddle molding, and piezoelectric actuator (3) is fixed on gold
In category framework (2),
Piezoelectric actuator (3) includes spring steel ellipse enlarger (7), piezoelectric stack ceramics (8) and wedge shape pretension block (9),
Spring steel ellipse enlarger (7) is axially symmetric structure, and has rigidity and recoverable force function, and spring steel is oval
One arc side of enlarger (7) is fixedly connected with a medial wall of metal framework (2), spring steel ellipse enlarger
(7) another arc side is connected with trailing edge winglet (5) through metal framework (2) by winglet connecting shaft (4),
5 piezoelectric stack ceramics (8), 5 piezo stacks are installed between the inwall of spring steel ellipse (7) two straight flanges of enlarger
It is attached using two wedge shapes pretension block (9) between heap ceramics (8),
Wedge shape pretension block (9), applies certain pretightning force for 5 piezoelectric stack ceramics (8) to installing,
Spring steel ellipse enlarger (7), for the drive displacement that piezoelectric stack ceramics (8) is produced is amplified, spring
The wall thickness l of amplification a and spring steel ellipse enlarger (7) of steel ellipse enlarger (7) and angle formed by arc side
θ is relevant for degree,
After piezoelectric actuator (3) applied voltage, piezoelectric actuator (3) can shrink to the left and produce drive displacement, drive trailing edge
Winglet connecting rod (4) is moved, and then drives trailing edge winglet (5) to enter horizontal deflection around winglet connection sheet (6).
2. it is according to claim 1 for reduce rotor vibration device, it is characterised in that the chord length of trailing edge winglet (5)
For the 20% of basic blade (1) length.
3. it is according to claim 1 for reduce rotor vibration device, it is characterised in that two wedge shapes pretension block (9)
One end be provided with 3 piezoelectric stack ceramics (8), the other end of two wedge shapes pretension block (9) is provided with 2 piezoelectric stack ceramics
(8)。
4. it is according to claim 1 for reduce rotor vibration device, it is characterised in that spring steel ellipse enlarger
The wall thickness of structure (7) is more than 1.5mm.
5. the device for reducing rotor vibration according to claim 1, it is characterised in that piezoelectric stack ceramics (8)
Thickness is 7mm.
6. it is according to claim 1 for reduce rotor vibration device, it is characterised in that spring steel ellipse enlarger
The relational expression of the wall thickness l and arc side angulation θ of amplification a of structure (7) and spring steel ellipse enlarger (7) is：
In formula, u represents displacement.
7. it is according to claim 6 for reduce rotor vibration device, it is characterised in that arc side angulation θ's
Span is 4 ° to 30 °.
8. it is according to claim 1 for reduce rotor vibration device, it is characterised in that piezoelectric actuator (3) is applied
Alive scope is 0-150V.
9. it is according to claim 1 for reduce rotor vibration device, it is characterised in that trailing edge winglet connecting rod (4)
Right side of the left end by screw thread with piezoelectric actuator (3) fix, right-hand member and the trailing edge winglet of trailing edge winglet connecting rod (4) pass through
Smooth axle connection.
10. it is according to claim 9 for reduce rotor vibration device, it is characterised in that trailing edge winglet (5) is around little
Wing connection sheet (6) enters horizontal deflection, and can produce inertia force △ L and aerodynamic loading torque △ M can be used with what basic blade (1) produced
Property power and aerodynamic loading are offset, so as to reach the effect of vibration damping.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611082748.6A CN106516104A (en) | 2016-11-30 | 2016-11-30 | Device for reducing rotor wing vibration |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611082748.6A CN106516104A (en) | 2016-11-30 | 2016-11-30 | Device for reducing rotor wing vibration |
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| CN106516104A true CN106516104A (en) | 2017-03-22 |
Family
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| CN201611082748.6A Pending CN106516104A (en) | 2016-11-30 | 2016-11-30 | Device for reducing rotor wing vibration |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108639335A (en) * | 2018-04-04 | 2018-10-12 | 北京航空航天大学 | A kind of plastic deformation system of the lifting airscrew aileron towards vibration and noise control |
| CN108750079A (en) * | 2018-04-07 | 2018-11-06 | 南京理工大学 | Piezoelectric actuator hysteresis compensation method for lifting airscrew vibration control |
| CN109665089A (en) * | 2018-12-26 | 2019-04-23 | 南京航空航天大学 | Using the helicopter blade trailing edge flap driving mechanism of flexible hinge |
| CN110758715A (en) * | 2019-12-06 | 2020-02-07 | 中国民航大学 | Deformable wing based on shape memory alloy driving |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108639335A (en) * | 2018-04-04 | 2018-10-12 | 北京航空航天大学 | A kind of plastic deformation system of the lifting airscrew aileron towards vibration and noise control |
| CN108750079A (en) * | 2018-04-07 | 2018-11-06 | 南京理工大学 | Piezoelectric actuator hysteresis compensation method for lifting airscrew vibration control |
| CN109665089A (en) * | 2018-12-26 | 2019-04-23 | 南京航空航天大学 | Using the helicopter blade trailing edge flap driving mechanism of flexible hinge |
| CN110758715A (en) * | 2019-12-06 | 2020-02-07 | 中国民航大学 | Deformable wing based on shape memory alloy driving |
| CN110758715B (en) * | 2019-12-06 | 2022-11-25 | 中国民航大学 | Deformable wing based on shape memory alloy drive |
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