CN113432825A - Wind tunnel airplane tail support model semi-active vibration damper based on magnetorheological elastomer - Google Patents
Wind tunnel airplane tail support model semi-active vibration damper based on magnetorheological elastomer Download PDFInfo
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- 229920001971 elastomer Polymers 0.000 title claims abstract description 18
- 239000000806 elastomer Substances 0.000 title claims abstract description 18
- 238000013016 damping Methods 0.000 claims abstract description 33
- 230000005284 excitation Effects 0.000 claims abstract description 20
- 230000000903 blocking effect Effects 0.000 claims description 22
- 238000002955 isolation Methods 0.000 claims description 14
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- 230000005389 magnetism Effects 0.000 claims 1
- 230000001629 suppression Effects 0.000 abstract description 15
- 230000000694 effects Effects 0.000 abstract description 14
- 238000005265 energy consumption Methods 0.000 abstract description 9
- 230000033001 locomotion Effects 0.000 abstract description 8
- 230000033228 biological regulation Effects 0.000 abstract description 3
- 238000012360 testing method Methods 0.000 description 15
- 238000009434 installation Methods 0.000 description 12
- 239000000463 material Substances 0.000 description 11
- 238000000034 method Methods 0.000 description 10
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- WABPQHHGFIMREM-UHFFFAOYSA-N lead(0) Chemical compound [Pb] WABPQHHGFIMREM-UHFFFAOYSA-N 0.000 description 3
- 238000012423 maintenance Methods 0.000 description 3
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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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Abstract
The invention discloses a wind tunnel airplane tail boom model semi-active vibration damper based on a magnetorheological elastomer, which comprises a tail boom support rod, an excitation coil and an MRE layer, wherein the MRE layer is wrapped on the tail boom support rod, and the excitation coil is sleeved on the tail boom support rod and is used for adjusting self parameters of the MRE layer. The semi-active vibration damping device disclosed by the invention not only realizes a certain supporting rod vibration suppression effect 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 of the supporting rod moves to avoid a resonance region, the effects of resonance frequency movement and damping energy consumption are achieved, and the effective control of multi-dimensional vibration is realized.
Description
Technical Field
The invention relates to the technical field of wind-driven test model parts, in particular to a semi-active vibration damper of a wind tunnel airplane tail boom model based on a magnetorheological elastomer.
Background
The wind tunnel model test is an important link in the research and development process of the aircraft and plays an irreplaceable role in the field of aerospace. The wind tunnel airplane model supporting system is a motion mechanism for realizing the change of the attitude angle of an airplane model in a wind tunnel test. In the wind tunnel test process, the tail support installation mode is the most common model support mode, and the tail support is a typical cantilever type structure consisting of a bent knife, a support rod, a force measuring scale and a model. The length of the supporting rod is generally three to five times of that of the model, and the model and the tail support supporting rod are easy to generate low-frequency large-amplitude vibration under the action of airflow pulsation load. And along with the increase of the attack angle of the model test, the vibration amplitude value can be increased, the low-frequency resonance influences the normal work of the force measuring balance, the accuracy of the aerodynamic force data of the wind tunnel is reduced, and in severe cases, the wind tunnel model test system can be damaged, and the running safety of the wind tunnel is threatened, so that the model vibration suppression is carried out, and the method has great significance on the accuracy of the measurement of the wind tunnel model test data and the safety of the test.
The vibration suppression technology of the wind tunnel model can be roughly divided into an active mode and a passive mode according to a vibration reduction mode;
the traditional passive suppression technology is mainly researched from two aspects of changing the airflow pulsation characteristic of the wind tunnel and a model supporting structure. Changing the flow field of the wind tunnel can prevent the model system from reaching the resonance frequency, thereby reducing the vibration amplitude. However, the improvement design of the wind tunnel flow field is difficult, and the modification of the model structure violates the purpose of the test. Therefore, the existing passive vibration suppression technology is mainly realized by a vibration absorption device arranged in an aircraft model. By designing parameters such as mass and appearance of the suppressor oscillator, the suppressor oscillator can resonate with the model and the vibration energy of the model is absorbed by the internal damping liquid, so that the vibration amplitude of the model is reduced. The passive suppression 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 inhibit, and the mass distribution of the model is changed to a certain extent by the inhibition device, so that the test result is influenced. Most importantly, the inhibitor has poor inhibition capability and slow response speed.
The active vibration reduction technology is developed along with the appearance of intelligent materials such as piezoelectricity, shape memory alloy and the like, and the actuator is driven in real time to generate reverse torque according to the vibration excitation characteristic by adopting a corresponding control strategy, so that the bending moment of the pneumatic load at the supporting rod is counteracted, and the aim of inhibiting the structural vibration is fulfilled. Compared with passive vibration reduction, the piezoelectric actuator has strong active vibration reduction adaptability, large output force and quick response. However, the piezoelectric actuator has small output displacement, poor stability and high cost, so that the large-amplitude suppression effect during resonance is poor, and the model structure parameter is sensitive, and the existence of hysteresis easily causes system divergence. In addition, the piezoelectric stacks are arranged at intervals, so that the optimal control effect on vibration in certain directions cannot be exerted, and the requirement of the structure on the installation precision is high, so that the tail support model is limited in vibration suppression application under partial test working conditions.
Therefore, in order to solve the problems, a semi-active vibration damping device of a wind tunnel airplane tail boom model based on a magnetorheological elastomer is needed, vibration damping of the wind tunnel tail boom model is realized by adopting a semi-active control technology, on one hand, the variable stiffness characteristic generated by the magnetic control modulus of an MRE material is utilized, so that the inherent frequency movement of a strut is enabled to avoid a resonance region, the effect of inhibiting large amplitude during resonance is better, and the vibration generated by the tail boom strut is reduced; on the other hand, the viscoelastic property 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 restraining the multidimensional 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 requirement on the installation precision, is convenient to install, and can be widely applied to the vibration suppression of the tail boom model under various test working conditions.
Disclosure of Invention
In view of the above, the invention provides a wind tunnel airplane tail boom model semi-active vibration damping device based on a magnetorheological elastomer, which adopts a semi-active control technology to realize vibration damping of a wind tunnel tail boom model, on one hand, the variable stiffness characteristic generated by the magnetic control modulus of an MRE material is utilized to enable the inherent frequency movement of a strut to avoid a resonance region, the large amplitude damping effect during resonance is better, and the vibration generated by the tail boom strut is reduced; on the other hand, the viscoelastic property 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 restraining the multidimensional 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 requirement on the installation precision, is convenient to install, and can be widely applied to the vibration suppression of the tail boom model under various test working conditions.
The semi-active vibration damping device of the wind tunnel airplane tail boom model based on the magnetorheological elastomer comprises a tail boom support rod, an excitation coil and an MRE layer, wherein the MRE layer is wrapped on the tail boom support rod, and the excitation coil is sleeved on the tail boom support rod and used for adjusting self parameters of the MRE layer.
Further, still include inner skleeve and outer sleeve, the fixed cover of inner skleeve is on tail boom branch, the outer sleeve overlaps outside the inner skleeve, MRE fills between inner skleeve excircle and outer sleeve interior circle layer upon layer, excitation coil cover is on tail boom branch or inner skleeve or outer sleeve.
Furthermore, an annular groove is formed in the outer circle of the inner sleeve, and the magnet exciting coil is wound in the annular groove and sealed by glue.
Furthermore, a blocking platform which is formed by protruding outwards in the radial direction is arranged at the position, close to the excircle of the middle position, of the tail boom support rod, and the inner sleeve, the outer sleeve and the MRE layer are axially positioned through the blocking platform.
Further, the baffle table is axially isolated from the inner sleeve, the outer sleeve and the MRE layer through magnetic isolation gaskets, and the inner sleeve, the outer sleeve and the MRE layer axially abut against the magnetic isolation gaskets.
The tail boom support is characterized by further comprising a mounting seat, the mounting seat is fixedly sleeved on the tail boom support rod and is axially positioned through the blocking platform, and the mounting seat and the inner sleeve are respectively arranged on two axial sides of the blocking platform.
Further, the outer sleeve is fixedly connected with the blocking platform in the axial direction and presses the magnetic isolation gasket on the blocking platform in the axial direction, a cover plate is fixedly connected to one end, far away from the blocking platform, of the outer sleeve in the axial direction, and the cover plate is pressed on the inner sleeve in the axial direction and one end, far away from the blocking platform, of the MRE layer in the axial direction.
Further, the MRE layer is bonded on the outer circle of the inner sleeve.
Further, the outer sleeve is formed by splicing and encircling two half-type structures.
The invention has the beneficial effects that:
the semi-active vibration damping device not only realizes a certain strut vibration suppression effect 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 strut of the tail boom avoids a resonance region, the effects of resonance frequency movement and damping energy consumption are achieved, in the active vibration damping process, the amplitude of the strut of the tail boom is reduced due to the damping energy consumption, the effective control of multi-dimensional vibration is realized, and the active vibration damping device has the controllability and high robustness of an active control scheme; the damping device has small influence on the axial symmetry of the whole structure due to the installation position, has good control stability, can cope with the change of vibration frequency and amplitude in each linear direction, and has certain inhibition capability on the vibration in the torsional direction. The device has the advantages of response reaching millisecond level, high response speed, wide variation range, low energy consumption, good stability and reversibility and the like, can effectively deal with the broadband time-varying property of the vibration of the wind tunnel tail boom model, realize effective control on main vibration modes, can be applied to vibration reduction of tail boom supporting rods with different sizes, can also be widely applied to vibration suppression of the tail boom model under various test working conditions, has low requirement on installation precision, and is simpler in overall structure, manufacturing and assembling processes.
Drawings
The invention is further described below with reference to the figures and examples.
FIG. 1 is a schematic structural view of the present invention;
FIG. 2 is a partial schematic view of the structure;
Detailed Description
As shown in the figure: the semi-active vibration damping device of the wind tunnel aircraft tail boom model based on the magnetorheological elastomer comprises a tail boom support rod 1, an excitation coil 2 and an MRE layer 3, wherein the MRE layer 3 is wrapped on the tail boom support rod, and the excitation coil 2 is sleeved on the tail boom support rod 1 and used for adjusting self parameters of the MRE layer. The MRE is a magnetorheological elastomer material which 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 excitation coil can be embedded in the outer circle of the tail boom supporting rod or can be sleeved on the tail boom supporting rod, the MRE layer has viscoelasticity, and the MRE generates stretching and shearing deformation along with the vibration of the tail boom supporting rod to realize damping energy consumption and achieve the effect of passive vibration reduction; in addition, the shear modulus and the loss factor of the MRE layer are adjusted through the change of the magnetic field of the excitation coil 4, so that the rigidity and the damping ratio of the structure are changed, and the suppression of the multidimensional vibration of the tail boom support rod is finally realized; the semi-active vibration damping device not only realizes a certain strut vibration suppression effect 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 strut of the tail strut avoids a resonance region, and the effects of resonance frequency movement and damping energy consumption are achieved; the whole vibration damper is small in influence of the installation position of the whole vibration damper on the axial symmetry of the whole structure, good in control stability, capable of coping with the changes of vibration frequency and amplitude in each linear direction and capable of inhibiting vibration in the torsional direction to a certain degree. The device has the advantages of response reaching millisecond level, high response speed, wide variation range, low energy consumption, good stability and reversibility and the like, can effectively deal with the broadband time-varying property of the vibration of the wind tunnel tail boom model, realize effective control on main vibration modes, can be applied to vibration reduction of tail boom supporting rods with different sizes, can also be widely applied to vibration suppression of the tail boom model under various test working conditions, has low requirement on installation precision, and is simpler in overall structure, manufacturing and assembling processes.
In this embodiment, still include inner skleeve 4 and outer sleeve 5, the inner skleeve is fixed to be overlapped on the tail boom branch, the outer sleeve overlaps outside the inner skleeve, 3 layers of MRE are filled between inner skleeve excircle and outer sleeve interior circle, excitation coil 2 overlaps on tail boom branch 1 or inner skleeve 2 or outer sleeve 3. 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, in order to ensure the stability of the inner sleeve, a plurality of threaded holes are formed in the inner sleeve, fastening screws 10 are connected to the threaded holes in an internal thread manner, and the fastening screws abut against the outer circle of the tail boom support rod to fix the inner sleeve on the tail boom support rod; the MRE layer is extruded inside and outside the inner sleeve and the outer sleeve, so that the compactness and the stability of the whole vibration damping system are improved, and the installation, the disassembly and the maintenance of the whole vibration damping system are facilitated through the arrangement of the inner sleeve and the outer sleeve.
In this embodiment, an annular groove is formed in the outer circle of the inner sleeve 4, and the excitation coil is wound in the annular groove and sealed by glue. Combine shown in fig. 2, excitation coil is located the ring channel, and seal the glue in the ring channel so that excitation coil encapsulates in the ring channel, and seal glue outline and inner skleeve excircle parallel and level, make whole inner skleeve excircle be smooth cylindric, wherein the lead wire should be reserved to excitation coil, corresponding set up the lead wire hole that supplies the lead wire to wear out on the outer skleeve, integrate excitation coil and inner skleeve in an organic whole through this structure, simplify the assembling process, make simultaneously to form regular annular chamber between inner skleeve and the outer skleeve, the MRE layer forms regular annular stratiform based on this annular chamber's extrusion, make whole MRE layer around tail boom branch evenly distributed, improve the damping effect.
In this embodiment, a stop 6 formed by protruding radially outward is arranged at the position of the tail boom support rod close to the excircle of the middle position, and the inner sleeve, the outer sleeve and the MRE layer are axially positioned by the stop. As shown in a combined figure 2, the baffle platform is of a circular truncated cone structure, the right end of the supporting rod is of a longer cantilever structure and is directly exposed in a wind field, the end part of the baffle platform is connected with an airplane model, and the left end of the baffle platform is sleeved in the mounting seat.
In this embodiment, the blocking platform 6 is axially isolated 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 axially abut against the magnetic isolation gasket. The magnetic isolation gasket is made of known magnetic isolation materials, and the magnetic leakage phenomenon is favorably improved through the arrangement of the magnetic isolation gasket.
In this embodiment, the tail boom further comprises a mounting seat 8, the mounting seat 8 is fixedly sleeved on the tail boom support rod and is axially positioned through the blocking platform, and the mounting seat and the inner sleeve are respectively arranged on two axial sides of the blocking platform. Combine shown in figure 1, the mount pad sets up in the left side that keeps off the platform, the inner skleeve, outer sleeve and MRE level are located the right side that keeps off the platform, the right-hand member of mount pad and the left end that keeps off the platform respectively are provided with a locating hole, corresponding the two cooperates this locating hole formation location through locating pin 12, in order to do benefit to the circumference installation location of mount pad and tail-stay branch, tail-stay branch left end threaded connection has lock nut 11, lock nut 11 supports the left end at the mount pad, and make the mount pad right-hand member press in the left side that keeps off the platform, and then form axial positioning to the mount pad, can be according to the axial dimension of the axial rational in infrastructure design mount pad of branch left end during the application, very strong adaptability has.
In this embodiment, the outer sleeve is axially and fixedly connected with the blocking table and axially presses the magnetic isolation gasket on the blocking table, one end of the outer sleeve axially far away from the blocking table is fixedly connected with the cover plate 9, and the cover plate axially presses the inner sleeve and one end of the MRE layer axially far away from the blocking table. As shown in fig. 2, the left end of the outer sleeve is provided with a flange plate which extends radially outwards, the connecting screw penetrates through the flange plate and the magnetic isolation 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 magnetic isolation gasket, the magnetic isolation gasket and the outer sleeve are axially positioned through the structure, meanwhile, the cover plate is combined to form axial two-end positioning of the inner sleeve and the MRE layer, the inner sleeve, the MRE layer and the magnet exciting coil are all packaged in the outer sleeve, and a good protection effect is formed on the internal structure of the vibration damping device.
In this embodiment, the MRE layer is bonded to the outer circle of the inner sleeve. The stability of the MRE layer is increased by the adhesive structure.
In this embodiment, the outer sleeve is formed by splicing and enclosing two half-type structures. The outer sleeve is similar staple bolt structure, does benefit to the assembly with inner skleeve and MRE layer through this structure, and can form circumference extrusion effect to MRE layer, improves the installation stability on MRE layer, and this vibration damper need not dismantle experimental model, dynamometry balance etc. at installation and maintenance in-process, and assembly process is simple, simplifies the use to simplify the later maintenance process.
Finally, the above embodiments are only for illustrating the technical solutions of the present invention and not for limiting, 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 or equivalent substitutions may be made to the technical solutions of the present invention without departing from the spirit and scope of the technical solutions of the present invention, and all of them should be covered in the claims of the present invention.
Claims (9)
1. A wind tunnel aircraft tail boom model semi-active vibration damper based on magnetorheological elastomers is characterized in that: including tail boom branch, excitation coil and MRE layer, MRE layer parcel is on tail boom branch, excitation coil overlaps on tail boom branch and is used for adjusting the self parameter on MRE layer.
2. The wind tunnel aircraft tail boom model semi-active vibration damping device based on the magnetorheological elastomer according to claim 1, characterized in that: still include inner skleeve and outer sleeve, the fixed cover of inner skleeve is on tail boom branch, the outer sleeve overlaps outside the inner skleeve, MRE fills between inner skleeve excircle and outer sleeve interior circle layer upon layer, excitation coil cover is on tail boom branch or inner skleeve or outer sleeve.
3. The wind tunnel aircraft tail boom model semi-active vibration damping device based on the magnetorheological elastomer according to claim 2, characterized in that: the excircle of the inner sleeve is provided with an annular groove, and the magnet exciting coil is wound in the annular groove and sealed by glue.
4. The wind tunnel aircraft tail boom model semi-active vibration damping device based on the magnetorheological elastomer according to claim 2, characterized in that: the tail boom support rod is provided with a baffle table which is formed by protruding outwards in the radial direction at the position close to the excircle of the middle part, and the inner sleeve, the outer sleeve and the MRE layer are axially positioned through the baffle table.
5. The wind tunnel aircraft tail boom model semi-active vibration damping device based on the magnetorheological elastomer according to claim 4, wherein: the blocking table is axially isolated from the inner sleeve, the outer sleeve and the MRE layer through magnetic isolation gaskets, and the inner sleeve, the outer sleeve and the MRE layer axially abut against the magnetic isolation gaskets.
6. The wind tunnel airplane tail boom model semi-active vibration damper based on the magnetorheological elastomer according to claim 4, characterized in that: the tail boom is characterized by further comprising a mounting seat, the mounting seat is fixedly sleeved on the tail boom supporting rod and is axially positioned through the blocking platform, and the mounting seat and the inner sleeve are respectively arranged on two axial sides of the blocking platform.
7. The wind tunnel airplane tail boom model semi-active vibration damping device based on the magnetorheological elastomer according to claim 5, characterized in that: the outer sleeve is fixedly connected with the blocking platform in the axial direction and presses the magnetism isolating gasket on the blocking platform in the axial direction, a cover plate is fixedly connected to one end, far away from the blocking platform, of the outer sleeve in the axial direction, and the cover plate is pressed on the inner sleeve in the axial direction and one end, far away from the blocking platform, of the MRE layer in the axial direction.
8. The wind tunnel aircraft tail boom model semi-active vibration damping device based on the magnetorheological elastomer according to claim 2, characterized in that: the MRE layer is bonded on the outer circle of the inner sleeve.
9. The wind tunnel aircraft tail boom model semi-active vibration damping device based on the magnetorheological elastomer according to claim 8, wherein: the outer sleeve is formed by splicing and encircling two half-type structures.
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