CN109305344A - Has the unmanned plane rotor arm configuration of segmentation restriction damping layer in a kind of outer surface - Google Patents
Has the unmanned plane rotor arm configuration of segmentation restriction damping layer in a kind of outer surface Download PDFInfo
- Publication number
- CN109305344A CN109305344A CN201811173843.6A CN201811173843A CN109305344A CN 109305344 A CN109305344 A CN 109305344A CN 201811173843 A CN201811173843 A CN 201811173843A CN 109305344 A CN109305344 A CN 109305344A
- Authority
- CN
- China
- Prior art keywords
- damping layer
- rotor arm
- restriction
- unmanned plane
- visco
- 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.)
- Pending
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/001—Vibration damping devices
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/32—Rotors
Abstract
The present invention provides a kind of outer surfaces with the unmanned plane rotor arm configuration of segmentation restriction damping layer.The unmanned plane rotor arm includes rotor arm body, restriction damping layer and visco-elastic damping layer.Rotor arm body uses the hollow cylinder structure of carbon fibre material；Restriction damping layer and visco-elastic damping layer are using segmentation hollow cylinder shell structure, and aluminium alloy, ZN-1 damping rubber is respectively adopted in the two material；Rotor arm, visco-elastic damping layer and restriction damping layer three successively tight bond from inside to outside.The present invention is by the restriction damping layer of the outer surface line bonus segmentation in unmanned plane rotor arm, and making visco-elastic damping layer using the elastic bending vibration of rotor arm, deformation occurs, so that the vibrational energy of unmanned plane rotor arm be made to dissipate rapidly to carry out vibration damping.The configuration of the present invention is simple, does not influence the main structure of unmanned plane, and does not need additional additional mass and control device, increases the stability of unmanned plane during flying, inhibition of vibration is significant in practical applications.
Description
Technical field
The present invention relates to machinery field, specifically a kind of shock-damping structure is more specifically a kind of rotation of multi-rotor unmanned aerial vehicle
Wing arm structure vibration controlling.
Background technique
It is widely applied in terms of currently, unmanned plane is between high-altitude shooting, logistics, agriculture.Especially in recent years
The oily dynamic formula multi-rotor unmanned aerial vehicle of rapid development makes its application obtain further genralrlization because of the continuous promotion of its bearing capacity,
But big load capacity exacerbates the vibration problem of complete machine structure, not only influences unmanned plane during flying stability, also easily causes nobody
The destruction of machine complete machine structure.
In recent years, a large amount of correlative studys show that the structural vibration of unmanned plane is mainly derived from the resonance of rotor arm, and the vibration
Dynamic form is based on mode of flexural vibration.Traditional vibration suppression mode generally includes the control of active and passive type.Though passive type bump leveller
Remarkable result can be generated at intrinsic frequency, but additional has the bump leveller of relatively large quality will on unmanned plane
Seriously affect its cruising ability, load-bearing capacity and flight stability etc.；Using piezoelectric ceramics as the active vibration suppression method of representative
With biggish flexibility, there is good vibration suppressioning effect to the low-frequency range of vibration, but its control system need to provide volume
Outer energy resource supply device, not only increases the economic cost of complete machine structure, and reduces the robustness of system, therefore it is at nobody
There is biggish limitation in the application of the vibration suppression of machine rotor arm.
Accordingly, it is desirable to obtain, one kind is simple and compact for structure, does not influence unmanned plane main structure and economically feasible, presses down
The effective passive type that shakes inhibits the method for vibration.
Summary of the invention
In view of the deficiencies of the prior art, the present invention provides one kind by rotor arm outer surface for unmanned plane rotor arm
The vibration suppressing method of additional segments restriction damping layer.The principle of this method makes viscoplasticity using the elastic bending vibration of rotor arm
Deformation occurs for damping layer, and visco-elastic damping layer converts thermal energy for part strain energy in deformation process, so that unmanned plane be made to revolve
The vibrational energy of wing arm, which dissipates rapidly, carries out vibration damping.Meanwhile the present invention is by using the method for arranging of segmented restriction damping layer,
The shear-deformable of visco-elastic damping layer is increased, to improve the damping characteristic of unmanned plane rotor arm, inhibition of vibration is very aobvious
It writes.
In order to solve the above technical problems, the technical solution adopted by the present invention is that:
A kind of outer surface has the unmanned plane rotor arm configuration of segmentation restriction damping layer, and rotor arm is hollow cylinder structure,
Its material uses carbon fiber；Visco-elastic damping layer is segmentation hollow cylinder shell structure, and internal diameter is identical as rotor arm outer diameter, outer diameter
It is identical as restriction damping layer internal diameter；Restriction damping layer is segmentation hollow cylinder shell structure, internal diameter and visco-elastic damping layer outer diameter
It is identical；Rotor arm outer surface, visco-elastic damping layer and restriction damping layer three successively tight bond from inside to outside；The viscoplasticity
Damping layer and restriction damping layer are subsection setup, and notch is arranged in viscoelastic damping interlayer, and damping-constraining interlayer is also provided with notch.
Viscoelastic damping layer material uses ZN-1 damping rubber.
Damping-constraining layer material uses aluminium alloy.
Every section of visco-elastic damping layer and restriction damping layer equal length, adjacent two sections of visco-elastic damping layers and restriction damping layer
There are the notch of every section of restriction damping layer length 5-8%.
The thickness of visco-elastic damping layer increases, and deformation is easy, and inhibition of vibration is good, but the too thick weight that will cause increases；Constraint
The thickness of damping layer increases, and total amount also relative increase, therefore, inertia is larger, the shearing force of opposite visco-elastic damping layer with regard to big,
But restriction damping layer is too thick, will increase weight and is affected to the energy consumption and performance of unmanned plane；Comprehensively consider, visco-elastic damping layer
With a thickness of 2-5mm, restriction damping layer with a thickness of 1-3mm.
In order to guarantee that the inertia for being more easier deformation and restriction damping layer in every section of visco-elastic damping layer is larger, viscoplasticity resistance
The length of Buddhist nun's layer is less than every section of restriction damping layer length.
Length and guarantee visco-elastic damping layer to increase restriction damping layer as far as possible restriction damping layer adjacent when deforming are not
It can collide, the distance of every section of damping-constraining interlayer is the 1.5-2% of every section of restriction damping layer length.
Venthole is arranged in the surface of restriction damping layer.It is generated inside one side visco-elastic damping layer shear-deformable generated
Heat can be discharged by venthole, and on the other hand, the upper surface that venthole causes restriction damping layer is rough, also increases
The resistance of restriction damping layer and air when vibration is conducive to the inertia for improving restriction damping layer, and then improves viscoelastic damping
The deformation of layer.
Advantages of the present invention and beneficial effect are:
1, the present invention is generated by way of in unmanned plane rotor arm additional constraint damping layer using visco-elastic damping layer
Shearing deformation dissipation vibrational energy, inhibition of vibration are very significant；
2, the configuration of the present invention is simple, does not influence the main structure of unmanned plane, and does not need additional additional mass, energy confession
To device and control device, the stability of unmanned plane is increased；
3, the present invention uses the segmented restriction damping layer of ring-cutting form, to reduce what restriction damping layer deformed damping layer
Limitation generates visco-elastic damping layer bigger shear-deformable, obtains better inhibition of vibration.
Detailed description of the invention
Fig. 1 is specific embodiment of the invention integral structure layout schematic diagram；
Fig. 2 is the partial structural diagram of the specific embodiment of the invention；
Fig. 3 is the amplitude and time relationship comparison diagram of structure of the invention and the rotor arm without structure of the invention；
Fig. 4 is the amplitude and frequency relation comparison diagram of structure of the invention and the rotor arm without structure of the invention；
Wherein, 1- rotor arm, 2- visco-elastic damping layer, 3- restriction damping layer, 4- engine hold-down support, 5- unmanned plane machine
Body connecting support, 6- notch, 7- venthole.
Specific embodiment
In the following, in conjunction with the drawings and the specific embodiments, being described in further details to the present invention.
As shown in Figs. 1-2, unmanned plane rotor arm according to the present invention uses segmented restriction damping layer comprising rotor
Arm body, segmented restriction damping layer and visco-elastic damping layer, specific structure are as follows:
Rotor arm body 1 is hollow cylinder structure, and material uses carbon fiber；Visco-elastic damping layer 2 is segmentation open circles
Pole-shell structure, internal diameter is identical as 1 outer diameter of rotor arm, and outer diameter is identical as 3 internal diameter of restriction damping layer, and material is damped using ZN-1
Rubber；Restriction damping layer 3 is segmentation hollow cylinder shell structure, and internal diameter is identical as 2 outer diameter of visco-elastic damping layer, and material uses
Aluminium alloy；Visco-elastic damping layer, restriction damping layer are the composite structure Zi in outer close adhesion, and there are notch between each section
6.Visco-elastic damping layer 2 is bonded between biggish 1 ontology of rotor arm of rigidity and restriction damping layer 3, visco-elastic damping layer is made
Drawing caused by the surface contacted with rotor arm body 1 deformation be different from its with caused by 3 contact surface of restriction damping layer
Drawing deformation has the function that passive energy dissipation to generate inside visco-elastic damping layer 2 shear-deformable.
The course of work of segmented restriction damping layer provided by the present invention is as follows:
When unmanned plane rotor arm 1 vibrates, it will locally generating small elastic bending deflection.At this point, due to
The deformation of drawing caused by the surface that visco-elastic damping layer 2 is contacted with rotor arm 1 is different from visco-elastic damping layer 2 and damping-constraining
The drawing deformation of 3 contact surface of layer, therefore shear-deformable, shear-deformable caused strain energy conversion is generated inside damping material
A large amount of energy dissipation is caused for thermal energy, significantly reduces the structural vibration of rotor arm 1, the dissipation of thermal energy passes through venthole
7 discharges, the upper surface that venthole causes restriction damping layer is rough, the resistance of restriction damping layer and air when also increasing vibration
Power is conducive to the inertia for improving restriction damping layer, and then improves the deformation of visco-elastic damping layer 2.Venthole can be a certain
It is arranged on the restriction damping layer of section, especially the restriction damping layer at engine hold-down support, because the position is far from machine
Body, and the arm of force is larger, relative amplitude is larger.In the actual application of the present embodiment, with six rotor fuel dynamic formula unmanned plane centers
The flight controller fixed supported slab of position be vibration-testing point, respectively to using surface have segmented restriction damping layer nobody
Machine rotor arm has carried out transient oscillation test with the unmanned plane using common unmanned plane rotor arm, sinusoidal excitation is tested, test knot
Shown in fruit following Fig. 3 and Fig. 4, show that unmanned plane rotor arm configuration of the surface with segmented restriction damping layer can have in figure
The reduction complete machine oscillation of effect, vibration suppression rate is up to 70% or so.
Every section of visco-elastic damping layer and restriction damping layer equal length, adjacent two sections of visco-elastic damping layers and restriction damping layer
There are the notch of every section of restriction damping layer length 5-8%.
The thickness of visco-elastic damping layer increases, and deformation is easy, and inhibition of vibration is good, but the too thick weight that will cause increases；Constraint
The thickness of damping layer increases, and total amount also relative increase, therefore, inertia is larger, the shearing force of opposite visco-elastic damping layer with regard to big,
But restriction damping layer is too thick, will increase weight and is affected to the energy consumption and performance of unmanned plane；Comprehensively consider, visco-elastic damping layer
With a thickness of 2-5mm, restriction damping layer with a thickness of 1-3mm.
It is a further embodiment that: in order to guarantee to be more easier deformation and restriction damping layer in every section of visco-elastic damping layer
Inertia it is larger, the length of visco-elastic damping layer is less than every section of restriction damping layer length.
Length and guarantee visco-elastic damping layer to increase restriction damping layer as far as possible restriction damping layer adjacent when deforming are not
It can collide, the distance of every section of damping-constraining interlayer is the 1.5-2% of every section of restriction damping layer length.
The above, preferred embodiment only of the invention, but not have any restrictions to the present invention, it is all according to this
Inventive technique refers to any simple modification, the change made to above-described embodiment, still falls within the protection scope of the technology of the present invention
It is interior.
Claims (8)
1. a kind of outer surface is with the unmanned plane rotor arm configuration of segmentation restriction damping layer, it is characterised in that: rotor arm is hollow
Cylindrical structure, material use carbon fiber；Visco-elastic damping layer is segmentation hollow cylinder shell structure, internal diameter and rotor arm outer diameter
Identical, outer diameter is identical as restriction damping layer internal diameter；Restriction damping layer is segmentation hollow cylinder shell structure, and internal diameter and viscoplasticity hinder
Buddhist nun's layer outer diameter is identical；Rotor arm outer surface, visco-elastic damping layer and restriction damping layer three successively tight bond from inside to outside；Institute
It states visco-elastic damping layer and restriction damping layer is subsection setup, notch, damping-constraining interlayer is arranged in viscoelastic damping interlayer
Notch is set.
2. outer surface according to claim 1 exists with the unmanned plane rotor arm configuration of segmentation restriction damping layer, feature
In: viscoelastic damping layer material uses ZN-1 damping rubber.
3. outer surface according to claim 1 exists with the unmanned plane rotor arm configuration of segmentation restriction damping layer, feature
In: damping-constraining layer material uses aluminium alloy.
4. outer surface according to claim 1 exists with the unmanned plane rotor arm configuration of segmentation restriction damping layer, feature
In: every section of visco-elastic damping layer and restriction damping layer equal length, adjacent two sections of viscoelastic damping interlayers and adjacent two sections of constraints
Damping interlayer, there are the notch of every section of restriction damping layer length 5-8%.
5. outer surface according to claim 1 exists with the unmanned plane rotor arm configuration of segmentation restriction damping layer, feature
In: visco-elastic damping layer with a thickness of 2-5mm, restriction damping layer with a thickness of 1-3mm.
6. outer surface according to claim 1 exists with the unmanned plane rotor arm configuration of segmentation restriction damping layer, feature
In: the length of every section of visco-elastic damping layer is less than every section of restriction damping layer length.
7. outer surface according to claim 6 exists with the unmanned plane rotor arm configuration of segmentation restriction damping layer, feature
In: the distance of every section of damping-constraining interlayer is the 1.5-2% of every section of restriction damping layer length.
8. outer surface according to claim 1 exists with the unmanned plane rotor arm configuration of segmentation restriction damping layer, feature
In: venthole is arranged in the surface of restriction damping layer.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811173843.6A CN109305344A (en) | 2018-10-09 | 2018-10-09 | Has the unmanned plane rotor arm configuration of segmentation restriction damping layer in a kind of outer surface |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811173843.6A CN109305344A (en) | 2018-10-09 | 2018-10-09 | Has the unmanned plane rotor arm configuration of segmentation restriction damping layer in a kind of outer surface |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109305344A true CN109305344A (en) | 2019-02-05 |
Family
ID=65225542
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811173843.6A Pending CN109305344A (en) | 2018-10-09 | 2018-10-09 | Has the unmanned plane rotor arm configuration of segmentation restriction damping layer in a kind of outer surface |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109305344A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2021217437A1 (en) * | 2020-04-28 | 2021-11-04 | 深圳市大疆创新科技有限公司 | Vibration mode optimization method, vibration mode optimization device and unmanned aerial vehicle |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5712447A (en) * | 1996-05-14 | 1998-01-27 | The United States Of America As Represented By The Secretary Of The Navy | Vibrationally and acoustically insulated structure |
| CN1663884A (en) * | 2005-03-22 | 2005-09-07 | 哈尔滨工业大学 | Vibration reduction restriction damping layer of spacecraft |
| CN105864272A (en) * | 2016-05-24 | 2016-08-17 | 西南交通大学 | Low-frequency vibration isolation metamaterial shaft structure |
| CN206860241U (en) * | 2017-07-06 | 2018-01-09 | 乐山职业技术学院 | Vibration damping harden structure and aero-engine |
| CN107810344A (en) * | 2015-06-15 | 2018-03-16 | 3M创新有限公司 | Multilayer damping material |
-
2018
- 2018-10-09 CN CN201811173843.6A patent/CN109305344A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5712447A (en) * | 1996-05-14 | 1998-01-27 | The United States Of America As Represented By The Secretary Of The Navy | Vibrationally and acoustically insulated structure |
| CN1663884A (en) * | 2005-03-22 | 2005-09-07 | 哈尔滨工业大学 | Vibration reduction restriction damping layer of spacecraft |
| CN107810344A (en) * | 2015-06-15 | 2018-03-16 | 3M创新有限公司 | Multilayer damping material |
| CN105864272A (en) * | 2016-05-24 | 2016-08-17 | 西南交通大学 | Low-frequency vibration isolation metamaterial shaft structure |
| CN206860241U (en) * | 2017-07-06 | 2018-01-09 | 乐山职业技术学院 | Vibration damping harden structure and aero-engine |
Non-Patent Citations (1)
| Title |
|---|
| 郑冀等编著: "《材料物理性能》", 29 February 2008, 天津大学出版社 * |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2021217437A1 (en) * | 2020-04-28 | 2021-11-04 | 深圳市大疆创新科技有限公司 | Vibration mode optimization method, vibration mode optimization device and unmanned aerial vehicle |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| Lu et al. | Nonlinear dissipative devices in structural vibration control: A review | |
| US7811063B2 (en) | Damping element for a wind turbine rotor blade | |
| Bilgen et al. | Macro-fiber composite actuators for flow control of a variable camber airfoil | |
| CN101871499A (en) | Piezoelectric liquid inertia vibration eliminator | |
| CA2242214C (en) | Structural component haivng means for actively varying its stiffness to control vibrations | |
| CN109578503A (en) | Forked type piezo-electric stack damping ring | |
| Bernhard et al. | Analysis of a bending-torsion coupled actuator for a smart rotor with active blade tips | |
| CN109305344A (en) | Has the unmanned plane rotor arm configuration of segmentation restriction damping layer in a kind of outer surface | |
| CN104454986A (en) | Ultrasonic aerodynamic bearing | |
| CN111853145A (en) | Lattice sandwich intelligent vibration reduction structure based on magnetoelectric rheological body | |
| CN105221623A (en) | A kind of propeller driven airplane noise reduction multiple resonance points dynamic vibration absorber | |
| CN101830084B (en) | Novel powder impact damping honeycomb sandwich structure | |
| CN109050861B (en) | Marine damping propeller shaft | |
| Barrett | All-moving active aerodynamic surface research | |
| CN104590558A (en) | Piezoelectric composite material helicopter blade structure and control method thereof | |
| CN100572845C (en) | Piezoelectric liquid inertia vibration eliminator | |
| Yang et al. | A modified Fourier solution for free damped vibration analysis of sandwich viscoelastic-core conical shells and annular plates with arbitrary restraints | |
| Thakkar et al. | Active twist control of smart helicopter rotor-a survey | |
| CN101949423A (en) | Viscoelastic damping anti-torque vibration damper | |
| Mehrabani et al. | Multidisciplinary optimization of a stiffened shell by genetic algorithm | |
| Wei et al. | Vibration characteristics of rotating sandwich beams filled with electrorheological fluids | |
| CN102996706B (en) | Piezoelectric-dry friction composite damping device | |
| Chopra | Recent progress on the development of a smart rotor system | |
| CN207475431U (en) | A kind of miniature broadband vibrational energy collector | |
| Vos et al. | Post-buckled precompressed (PBP) piezoelectric actuators for UAV flight control |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20190205 |
|
| RJ01 | Rejection of invention patent application after publication |