CN113432825B - Wind tunnel aircraft tail boom model semi-active vibration damper based on magnetorheological elastomer - Google Patents
Wind tunnel aircraft tail boom model semi-active vibration damper based on magnetorheological elastomer Download PDFInfo
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- CN113432825B CN113432825B CN202110867231.2A CN202110867231A CN113432825B CN 113432825 B CN113432825 B CN 113432825B CN 202110867231 A CN202110867231 A CN 202110867231A CN 113432825 B CN113432825 B CN 113432825B
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- 229920001971 elastomer Polymers 0.000 title claims abstract description 15
- 239000000806 elastomer Substances 0.000 title claims abstract description 15
- 238000013016 damping Methods 0.000 claims abstract description 14
- 230000005389 magnetism Effects 0.000 claims description 8
- 230000005284 excitation Effects 0.000 claims description 5
- 239000003292 glue Substances 0.000 claims description 4
- 238000007789 sealing Methods 0.000 claims description 4
- 230000001629 suppression Effects 0.000 abstract description 15
- 230000000694 effects Effects 0.000 abstract description 12
- 238000005265 energy consumption Methods 0.000 abstract description 9
- 230000033001 locomotion Effects 0.000 abstract description 7
- 230000033228 biological regulation Effects 0.000 abstract description 3
- 238000012360 testing method Methods 0.000 description 15
- 239000000463 material Substances 0.000 description 12
- 238000000034 method Methods 0.000 description 11
- 230000008569 process Effects 0.000 description 10
- 230000009467 reduction Effects 0.000 description 8
- 238000009434 installation Methods 0.000 description 7
- 238000002955 isolation Methods 0.000 description 7
- 238000005516 engineering process Methods 0.000 description 6
- 230000004044 response Effects 0.000 description 6
- 230000002829 reductive effect Effects 0.000 description 5
- 230000008859 change Effects 0.000 description 4
- 230000005764 inhibitory process Effects 0.000 description 4
- 238000010008 shearing Methods 0.000 description 4
- 230000002401 inhibitory effect Effects 0.000 description 3
- WABPQHHGFIMREM-UHFFFAOYSA-N lead(0) Chemical compound [Pb] WABPQHHGFIMREM-UHFFFAOYSA-N 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 2
- 238000001125 extrusion Methods 0.000 description 2
- 238000012423 maintenance Methods 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000000452 restraining effect Effects 0.000 description 2
- 230000009471 action Effects 0.000 description 1
- 239000000853 adhesive Substances 0.000 description 1
- 230000001070 adhesive effect Effects 0.000 description 1
- 238000005452 bending Methods 0.000 description 1
- 238000011217 control strategy Methods 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
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- 238000006073 displacement reaction Methods 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
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- 238000005259 measurement Methods 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
- 230000036961 partial effect Effects 0.000 description 1
- 230000010349 pulsation Effects 0.000 description 1
- 230000002441 reversible effect Effects 0.000 description 1
- 229910001285 shape-memory alloy Inorganic materials 0.000 description 1
Classifications
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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
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/02—Wind tunnels
- G01M9/04—Details
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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
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/08—Aerodynamic models
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- Fluid Mechanics (AREA)
- General Physics & Mathematics (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The invention discloses a wind tunnel aircraft tail boom model semi-active vibration damper based on a magnetorheological elastomer, which comprises a tail boom support rod, an exciting coil and an MRE layer, wherein the MRE layer is wrapped on the tail boom support rod, and the exciting coil is sleeved on the tail boom support rod and used for adjusting self parameters of the MRE layer. The semi-active vibration damper not only realizes a certain vibration suppression effect of the support rod in a passive state without input energy, has the reliability and durability of passive control, but also can realize active parameter regulation and control under different working conditions, so that the natural frequency movement of the support rod avoids a resonance region, the effects of resonance frequency movement and damping energy consumption are achieved, and the effective control of multidimensional vibration is realized.
Description
Technical Field
The invention relates to the technical field of pneumatic test model parts, in particular to a wind tunnel aircraft tail boom model semi-active vibration damper based on a magnetorheological elastomer.
Background
Wind tunnel model test is an important link in the development process of aircrafts, and plays an irreplaceable role in the field of aerospace. The wind tunnel aircraft model support system is a motion mechanism for realizing the change of the attitude angle of the aircraft model in the wind tunnel test. In the wind tunnel test process, the tail support mounting mode is the most common model support mode, and the tail support is a typical cantilever structure consisting of a curved knife, a supporting rod, a force measuring level and a model. The length of the support rod is generally three to five times that of the model, and the model and the tail support rod are extremely easy to generate low-frequency and large-amplitude vibration under the action of airflow pulsating load. And along with the increase of the attack angle of the model test, the vibration amplitude can be increased, the low-frequency resonance influences the normal work of the force balance, the accuracy of wind tunnel aerodynamic data is reduced, a wind tunnel model test system is damaged when serious, and the safety of wind tunnel operation is threatened, so that the model vibration suppression is carried out, and the method has great significance on the accuracy of wind tunnel model test data measurement and the safety of the test.
Vibration suppression technology of wind tunnel model can be divided into active mode and passive mode according to vibration reduction mode;
the traditional passive suppression technology is mainly researched from the two aspects of changing the wind tunnel airflow pulsation characteristic and the model supporting structure. Changing the wind tunnel flow field can avoid the model system reaching the resonance frequency, thereby reducing the vibration amplitude. However, the improvement design of the wind tunnel flow field is very difficult, and the model structure modification violates the purpose of the test. Therefore, the existing passive vibration suppression technology is mainly realized by a vibration absorbing device arranged inside an aircraft model. By designing parameters such as mass, appearance and the like of the suppressor vibrator, the suppressor vibrator can resonate with the model, and the damping liquid in the suppressor vibrator absorbs the vibration energy of the model, so that the vibration amplitude of the model is reduced. The passive restraining device does not need external energy input and has the advantages of simple structure, easy realization and good reliability. However, the structural parameters are fixed, the structural parameters cannot be changed along with the change of external vibration, the time-varying broadband vibration excitation is difficult to restrain, and the mass distribution of the model is changed to a certain extent by the restraining device, so that the test result is influenced. The most critical is that the inhibition capability is poor and the response speed is slow.
The active vibration damping technology is developed along with the occurrence of intelligent materials such as piezoelectricity, shape memory alloy and the like, and adopts a corresponding control strategy according to vibration excitation characteristics to drive an actuator in real time to generate reverse moment so as to counteract bending moment of pneumatic load at a supporting rod, thereby achieving the purpose of inhibiting structural vibration. Compared with passive vibration damping, the piezoelectric actuator has strong active vibration damping adaptability, large output force and quick response. However, the piezoelectric actuator has small output displacement, poor stability and high cost, and has poor suppression effect on large amplitude during resonance, is sensitive to model structural parameters, and the existence of hysteresis is easy to cause system divergence. In addition, as the piezoelectric stacks are arranged at intervals, the optimal control effect on vibration in certain directions cannot be exerted, and the requirements of the structure on the installation precision are high, so that the vibration suppression application of the tail boom model is limited under part of test working conditions.
Therefore, in order to solve the problems, a semi-active vibration damper of a wind tunnel airplane tail support model based on a magnetorheological elastomer is needed, and vibration suppression of the wind tunnel tail support model is realized by adopting a semi-active control technology, so that on one hand, the natural frequency movement of a support rod is avoided from a resonance area by utilizing the variable stiffness characteristic generated by the magnetic control modulus of an MRE material, the large-amplitude suppression effect on resonance is good, and the vibration generated by the tail support rod is reduced; on the other hand, the viscoelasticity of the MRE material is utilized, so that stretching and shearing deformation are generated in the vibration of the MRE material to realize damping energy consumption, the effect of inhibiting multi-dimensional vibration of the support rod is finally achieved, the optimal control effect can be exerted on the vibration in all directions, the device has low requirements on the installation precision, is convenient to install, and can be widely applied to vibration inhibition of a tail stay model under various test working conditions.
Disclosure of Invention
In view of the above, the invention provides a wind tunnel airplane tail support model semi-active vibration damper based on a magnetorheological elastomer, which adopts a semi-active control technology to realize the vibration suppression of the wind tunnel tail support model, on one hand, the variable stiffness characteristic generated by the magnetic control modulus of MRE material is utilized to ensure that the natural frequency of a support rod moves to avoid a resonance area, the large amplitude suppression effect on resonance is better, and the vibration generated by the tail support rod is reduced; on the other hand, the viscoelasticity of the MRE material is utilized, so that stretching and shearing deformation are generated in the vibration of the MRE material to realize damping energy consumption, the effect of inhibiting multi-dimensional vibration of the support rod is finally achieved, the optimal control effect can be exerted on the vibration in all directions, the device has low requirements on the installation precision, is convenient to install, and can be widely applied to vibration inhibition of a tail stay model under various test working conditions.
The invention discloses a wind tunnel aircraft tail boom model semi-active vibration damper based on a magnetorheological elastomer, which comprises a tail boom support rod, an exciting coil and an MRE layer, wherein the MRE layer is wrapped on the tail boom support rod, and the exciting coil is sleeved on the tail boom support rod and used for adjusting self parameters of the MRE layer.
Further, the magnetic resonance excitation device further comprises an inner sleeve and an outer sleeve, wherein the inner sleeve is fixedly sleeved on the tail support supporting rod, the outer sleeve is sleeved outside the inner sleeve, the MRE layer by layer is filled between the outer circle of the inner sleeve and the inner circle of the outer sleeve, and the excitation coil is sleeved on the tail support supporting rod or the inner sleeve or the outer sleeve.
Further, an annular groove is formed in the outer circle of the inner sleeve, and the exciting coil is wound in the annular groove and sealed by sealing glue.
Further, a baffle table formed by protruding outwards in the radial direction is arranged at the position, close to the outer circle of the middle part, of the tail stay supporting rod, and the inner sleeve, the outer sleeve and the MRE layer are axially positioned through the baffle table.
Further, the baffle is axially separated from the inner sleeve, the outer sleeve and the MRE layer by a magnetic isolation gasket, and the inner sleeve, the outer sleeve and the MRE layer are axially abutted against the magnetic isolation gasket.
Further, the device also comprises a mounting seat, wherein the mounting seat is fixedly sleeved on the tail stay supporting rod and is axially positioned through the baffle table, and the mounting seat and the inner sleeve are respectively arranged on two axial sides of the baffle table.
Further, outer sleeve and fender platform axial fixed connection and with separate magnetism gasket axial pressure on keeping off the platform, outer sleeve axial is kept away from fender platform one end fixedly connected with apron, apron axial is pressed in inner sleeve and MRE layer axial and is kept away from fender platform one end.
Further, the MRE layer is adhered to the outer circle of the inner sleeve.
Further, the outer sleeve is formed by splicing and surrounding two-half structures.
The invention has the beneficial effects that:
according to the semi-active vibration damper, a certain vibration suppression effect of the support rod is achieved in a passive state without input energy, active parameter regulation and control under different working conditions can be achieved, the natural frequency of the tail support rod moves to avoid a resonance area, the effects of resonance frequency movement and damping energy consumption are achieved, in the active vibration damping process, the amplitude of the tail support rod is reduced due to the damping energy consumption, effective control of multidimensional vibration is achieved, and the controllable and high-robustness active control scheme is achieved; the vibration damper has small influence on the axial symmetry of the whole structure and good control stability, and the vibration damper can cope with the change of vibration frequency and amplitude in each linear direction and has certain inhibition capability on vibration in the torsion direction. The device has the advantages of response reaching millisecond level, high response speed, wide variation range, small energy consumption, good stability and reversibility and the like, can effectively cope with the wide frequency time variability of the vibration of the wind tunnel tail support model, realizes the effective control of main vibration modes, can be applied to vibration reduction of tail support struts with different sizes, can also be widely applied to vibration suppression of the tail support model under various test working conditions, has low requirements on installation precision, and is simpler in integral structure, manufacturing and assembly processes.
Drawings
The invention is further described below with reference to the drawings and examples.
FIG. 1 is a schematic diagram of the structure of the present invention;
FIG. 2 is a schematic view of a partial structure;
Detailed Description
As shown in the figure: the wind tunnel aircraft tail boom model semi-active vibration damper based on the magnetorheological elastomer comprises a tail boom support rod 1, an exciting coil 2 and an MRE layer 3, wherein the MRE layer 3 is wrapped on the tail boom support rod, and the exciting coil 2 is sleeved on the tail boom support rod 1 and used for adjusting self parameters of the MRE layer. MRE is a magneto-rheological elastomer material, and the material is an existing material; the MRE layer is of a layered structure made of MRE materials, the specific thickness of the MRE layer can be adjusted according to actual vibration reduction requirements, the exciting coil can be embedded at the outer circle of the tail support supporting rod or can be sleeved on the tail support supporting rod, the MRE layer has viscoelasticity, and damping energy consumption is achieved through stretching and shearing deformation generated by the MRE along with vibration of the tail support supporting rod, so that the effect of passive vibration reduction is achieved; in addition, the shearing modulus and the loss factor of the MRE layer are adjusted through the magnetic field change of the exciting coil 2, so that the rigidity and the damping ratio of the structure are changed, and finally the multi-dimensional vibration of the tail support strut is restrained; the semi-active vibration damper not only realizes a certain vibration suppression effect of the support rod in a passive state without input energy, but also can realize active parameter regulation and control under different working conditions, so that the natural frequency movement of the tail support rod avoids a resonance region, and the effects of resonance frequency movement and damping energy consumption are achieved; the installation position of the whole vibration damper has small influence on the axial symmetry of the whole structure, and the control stability is better. The device has the advantages of response reaching millisecond level, high response speed, wide variation range, small energy consumption, good stability and reversibility and the like, can effectively cope with the wide frequency time variability of the vibration of the wind tunnel tail support model, realizes the effective control of main vibration modes, can be applied to vibration reduction of tail support struts with different sizes, can also be widely applied to vibration suppression of the tail support model under various test working conditions, has low requirements on installation precision, and is simpler in integral structure, manufacturing and assembly processes.
In this embodiment, the exciting coil further comprises an inner sleeve 4 and an outer sleeve 5, the inner sleeve is fixedly sleeved on the tail support rod, the outer sleeve is sleeved outside the inner sleeve, the MRE layer 3 is filled between the outer circle of the inner sleeve and the inner circle of the outer sleeve, and the exciting coil 2 is sleeved on the tail support rod 1 or the inner sleeve 4 or the outer sleeve 5. As shown in fig. 1 and 2, the inner diameter of the inner sleeve is matched with the outer diameter of the tail boom support rod, a plurality of threaded holes are formed in the inner sleeve to ensure the stability of the inner sleeve, the threaded holes are internally connected with fastening screws 10 in a threaded manner, and the fastening screws are abutted against the outer circle of the tail boom support rod to enable the inner sleeve to be fixed on the tail boom support rod; the MRE layers are extruded inside and outside the inner sleeve and the outer sleeve, so that the compactness and stability of the whole vibration reduction system are improved, and the installation, disassembly and maintenance of the whole vibration reduction system are facilitated through the arrangement of the inner sleeve and the outer sleeve.
In this embodiment, the outer circle of the inner sleeve 4 is provided with an annular groove, and the exciting coil is wound in the annular groove and sealed by sealing glue. And in combination with the illustration of fig. 2, the exciting coil is positioned in the annular groove, and is sealed in the annular groove so that the exciting coil is encapsulated in the annular groove, the outer contour of the sealing glue is flush with the outer circle of the inner sleeve, so that the outer circle of the whole inner sleeve is smooth and cylindrical, a lead wire is reserved for the exciting coil, a corresponding lead wire hole for the lead wire to penetrate out is formed in the outer sleeve, the exciting coil and the inner sleeve are integrated into a whole through the structure, the assembly process is simplified, a regular annular cavity is formed between the inner sleeve and the outer sleeve, and the MRE layer forms a regular annular layer based on the extrusion of the annular cavity, so that the whole MRE layer is uniformly distributed around the tail support rod, and the vibration reduction effect is improved.
In the embodiment, the tail support supporting rod is provided with a baffle table 6 which is formed by protruding outwards in the radial direction at the position close to the outer circle of the middle part, and the inner sleeve, the outer sleeve and the MRE layer are axially positioned through the baffle table. The baffle table is in a round table structure, the right end of the supporting rod is in a longer cantilever structure and is directly exposed in a wind field, the end is connected with the aircraft model, the left end of the supporting rod is sleeved in the mounting seat, the vibration damper is simple in structure, and the whole vibration damper system has little influence on the wind field to be tested.
In this embodiment, the baffle 6 is axially separated from the inner sleeve, the outer sleeve and the MRE layer by a magnetic isolation gasket 7, and the inner sleeve, the outer sleeve and the MRE layer are axially abutted against the magnetic isolation gasket. The magnetic isolation gasket is made of known magnetic isolation materials, and the magnetic isolation gasket is arranged to be beneficial to improving the magnetic leakage phenomenon.
In this embodiment, still include mount pad 8, mount pad 8 fixed coat is in tail brace branch and through fender platform axial positioning, mount pad and inner skleeve divide to locate the axial both sides of fender platform. In combination with the illustration of fig. 1, the mount pad is arranged on the left side of the baffle table, the inner sleeve, the outer sleeve and the MRE are arranged on the right side of the baffle table, the right end of the mount pad and the left end of the baffle table are respectively provided with a positioning hole, and the corresponding two are matched with the positioning holes through the positioning pin 12 to form positioning, so that the mount pad and the circumferential mounting positioning of the tail stay support rod are facilitated, the left end of the tail stay support rod is in threaded connection with the locking nut 11, the locking nut 11 is propped against the left end of the mount pad, the right end of the mount pad is pressed on the left side of the baffle table, and then the axial positioning is formed on the mount pad, and the axial dimension of the mount pad can be reasonably designed according to the axial structure of the left end of the support rod during application, so that the mount pad has strong adaptability.
In this embodiment, the outer sleeve is axially and fixedly connected with the baffle table and axially presses the magnetism isolating gasket on the baffle table, one end of the outer sleeve, which is axially far away from the baffle table, is fixedly connected with a cover plate 9, and the cover plate is axially pressed on one end of the inner sleeve and the MRE layer, which is axially far away from the baffle table. The flange plate is formed by extending radially outwards at the left end of the outer sleeve, the connecting screw penetrates through the flange plate and the magnetism isolating gasket and is fixedly connected with the right end of the baffle table, so that the flange plate of the outer sleeve is axially pressed at the right end of the magnetism isolating gasket, the magnetism isolating gasket and the outer sleeve are axially positioned through the structure, the inner sleeve and the MRE layer are axially positioned at two ends by combining the cover plate, the inner sleeve, the MRE layer and the exciting coil are packaged in the outer sleeve, and good protection effect is formed on the internal structure of the vibration damper.
In this embodiment, the MRE layer is bonded to the outer circumference of the inner sleeve. The stability of the MRE layer is improved by the adhesive structure.
In this embodiment, the outer sleeve is formed by splicing and surrounding two half structures. The outer sleeve is similar to a hoop structure, the assembly of the outer sleeve and the inner sleeve and the MRE layer is facilitated through the structure, the circumferential extrusion effect can be formed on the MRE layer, the mounting stability of the MRE layer is improved, the vibration damper does not need to detach an experimental model, measure force level and the like in the mounting and maintaining processes, the assembly process is simple, the use process is simplified, and the later maintenance process is simplified.
Finally, it is noted that the above embodiments are only for illustrating the technical solution of the present invention and not for limiting the same, and although the present invention has been described in detail with reference to the preferred embodiments, it should be understood by those skilled in the art that modifications and equivalents may be made thereto without departing from the spirit and scope of the technical solution of the present invention, which is intended to be covered by the scope of the claims of the present invention.
Claims (6)
1. Wind tunnel aircraft tail boom model semi-active vibration damper based on magneto-rheological elastomer, its characterized in that: the device comprises a tail support supporting rod, an exciting coil and an MRE layer, wherein the MRE layer is wrapped on the tail support supporting rod, and the exciting coil is sleeved on the tail support supporting rod and used for adjusting self parameters of the MRE layer;
the magnetic resonance excitation device comprises a tail support supporting rod, an outer sleeve, an exciting coil, a Magnetic Resonance (MRE) layer by layer, a magnetic resonance (SPR) layer and a magnetic resonance (SPR) layer, wherein the MRE layer by layer is filled between the outer circle of the inner sleeve and the inner circle of the outer sleeve; the outer circle of the inner sleeve is provided with an annular groove, and the exciting coil is wound in the annular groove and sealed by sealing glue;
the MRE layer magnetic control modulus is utilized to generate variable rigidity, so that the natural frequency of the tail support rod moves to avoid resonance, and the multidimensional vibration of the tail support rod is restrained;
the tail support supporting rod is provided with a baffle table which is formed by protruding outwards in the radial direction at the position, close to the outer circle of the middle part, of the tail support supporting rod, and the inner sleeve, the outer sleeve and the MRE layer are axially positioned through the baffle table.
2. The magnetorheological elastomer-based wind tunnel aircraft tail boom model semi-active vibration damper according to claim 1, wherein: the baffle is axially separated from the inner sleeve, the outer sleeve and the MRE layer by a magnetism isolating gasket, and the inner sleeve, the outer sleeve and the MRE layer are axially abutted against the magnetism isolating gasket.
3. The magnetorheological elastomer-based wind tunnel aircraft tail boom model semi-active vibration damper according to claim 1, wherein the damper is characterized in that: the mounting seat is fixedly sleeved on the tail support rod and axially positioned through the baffle table, and the mounting seat and the inner sleeve are respectively arranged on two axial sides of the baffle table.
4. A wind tunnel aircraft tail boom model semi-active vibration damping device based on a magnetorheological elastomer according to claim 3, wherein: the outer sleeve is axially and fixedly connected with the baffle table and axially presses the magnetism isolating gasket on the baffle table, one end, away from the baffle table, of the outer sleeve is fixedly connected with a cover plate, and the cover plate is axially pressed on one end, away from the baffle table, of the inner sleeve and the MRE layer.
5. The magnetorheological elastomer-based wind tunnel aircraft tail boom model semi-active vibration damper according to claim 1, wherein: the MRE layer is adhered to the outer circle of the inner sleeve.
6. The magnetorheological elastomer-based wind tunnel aircraft tail boom model semi-active vibration damper according to claim 5, wherein: the outer sleeve is formed by splicing and surrounding two half structures.
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| CN202110867231.2A CN113432825B (en) | 2021-07-29 | 2021-07-29 | Wind tunnel aircraft tail boom model semi-active vibration damper based on magnetorheological elastomer |
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| CN202110867231.2A CN113432825B (en) | 2021-07-29 | 2021-07-29 | Wind tunnel aircraft tail boom model semi-active vibration damper based on magnetorheological elastomer |
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| CN114486167B (en) * | 2022-04-18 | 2022-06-24 | 中国空气动力研究与发展中心低速空气动力研究所 | Follow-up sealing system and method for floor notch of low-speed wind tunnel model tail support ground effect test |
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| CN103487231A (en) * | 2013-09-24 | 2014-01-01 | 大连理工大学 | Active vibration abatement device of supporting rod type wind tunnel model |
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