CN113374825A - Variable-rigidity and variable-damping clamp bracket for aero-engine and preparation method thereof - Google Patents
Variable-rigidity and variable-damping clamp bracket for aero-engine and preparation method thereof Download PDFInfo
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- CN113374825A CN113374825A CN202110674953.6A CN202110674953A CN113374825A CN 113374825 A CN113374825 A CN 113374825A CN 202110674953 A CN202110674953 A CN 202110674953A CN 113374825 A CN113374825 A CN 113374825A
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- 238000013016 damping Methods 0.000 title claims abstract description 120
- 238000002360 preparation method Methods 0.000 title abstract description 7
- 239000000463 material Substances 0.000 claims abstract description 64
- 238000009826 distribution Methods 0.000 claims abstract description 4
- 229910001285 shape-memory alloy Inorganic materials 0.000 claims description 52
- 229920001971 elastomer Polymers 0.000 claims description 30
- 239000000806 elastomer Substances 0.000 claims description 25
- 238000003825 pressing Methods 0.000 claims description 6
- 238000000034 method Methods 0.000 claims description 4
- 239000011248 coating agent Substances 0.000 claims description 3
- 238000000576 coating method Methods 0.000 claims description 3
- 239000000945 filler Substances 0.000 claims description 2
- 238000004519 manufacturing process Methods 0.000 claims 1
- 125000006850 spacer group Chemical group 0.000 claims 1
- 230000000694 effects Effects 0.000 description 12
- 238000010586 diagram Methods 0.000 description 8
- 238000002955 isolation Methods 0.000 description 3
- 230000007774 longterm Effects 0.000 description 2
- 239000012752 auxiliary agent Substances 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000002131 composite material Substances 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 239000003822 epoxy resin Substances 0.000 description 1
- 239000011521 glass Substances 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 229920000647 polyepoxide Polymers 0.000 description 1
- 230000003014 reinforcing effect Effects 0.000 description 1
- 230000035939 shock Effects 0.000 description 1
- 230000001629 suppression Effects 0.000 description 1
- 239000000725 suspension Substances 0.000 description 1
- 230000001960 triggered effect Effects 0.000 description 1
Images
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
- F16F15/00—Suppression of vibrations in systems; Means or arrangements for avoiding or reducing out-of-balance forces, e.g. due to motion
- F16F15/02—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems
- F16F15/04—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems using elastic means
- F16F15/06—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems using elastic means with metal springs
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
- F16F15/00—Suppression of vibrations in systems; Means or arrangements for avoiding or reducing out-of-balance forces, e.g. due to motion
- F16F15/02—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems
- F16F15/022—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems using dampers and springs in combination
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
- F16F15/00—Suppression of vibrations in systems; Means or arrangements for avoiding or reducing out-of-balance forces, e.g. due to motion
- F16F15/02—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems
- F16F15/023—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems using fluid means
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
- F16F15/00—Suppression of vibrations in systems; Means or arrangements for avoiding or reducing out-of-balance forces, e.g. due to motion
- F16F15/02—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems
- F16F15/04—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems using elastic means
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
- F16F15/00—Suppression of vibrations in systems; Means or arrangements for avoiding or reducing out-of-balance forces, e.g. due to motion
- F16F15/02—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems
- F16F15/04—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems using elastic means
- F16F15/046—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems using elastic means using combinations of springs of different kinds
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Acoustics & Sound (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Vibration Prevention Devices (AREA)
Abstract
The invention belongs to the field of aero-engine components, and particularly relates to a variable-stiffness and variable-damping hoop support of an aero-engine and a preparation method thereof. The technical scheme of the invention is as follows: the utility model provides an aeroengine becomes rigidity damping clamp support, includes support body, apron, screw and becomes rigidity damping material filling block, support body and apron are L shape structure, the support body is equipped with along a plurality of cavities of its central line symmetric distribution, and it places to become excessive cooperation of rigidity damping material filling block in the cavity, the apron passes through the screw with the support body is installed together and will become rigidity damping material filling block shutoff and be in the support body. According to the variable-rigidity and variable-damping hoop support for the aircraft engine, provided by the invention, under the condition of low vibration, the hoop support is in a low-rigidity and small-damping state, and when vibration is increased, the rigidity and the damping of the hoop support are increased, so that the purpose of reducing the vibration of the hoop support and the connected hoop and pipeline of the aircraft engine is achieved.
Description
Technical Field
The invention belongs to the field of aero-engine components, and particularly relates to a variable-stiffness and variable-damping hoop support of an aero-engine and a preparation method thereof.
Background
The aircraft engine hoop support is used as a connecting piece, not only plays a role in connecting and supporting, but also has a great effect in reducing vibration generated in the working process of an engine. The existing hoop support is single in rigidity and damping, and as a casing of an aero-engine in the working process is often influenced by unbalanced vibration of a rotor system, the hoop support, the hoop and a pipeline system connected with the hoop support are often subjected to vibration exceeding and fatigue failure. The problem of vibration damage of parts of the external pipeline system of the aircraft engine is one of important factors causing other faults of the engine, and the vibration suppression problem of the clamp bracket per se is very necessary to be researched.
At present, people have conducted preliminary research on variable-rigidity variable-damping structures, and invent variable-rigidity variable-damping devices, but all have some problems. The patent CN106522378A is a shape memory alloy variable-stiffness variable-damping limiting protection shock isolation device, and adopts some mechanical structures to ensure that a support does not generate instability, but the mechanism constraint is complex, the triggered variable-stiffness variable-damping condition identification is not accurate enough, and the variable-stiffness variable-damping effect is not obvious; patent CN 210390744U introduces a variable-rigidity bracket, but the means for realizing the variable rigidity is to replace reinforcing ribs with different rigidities on mounting holes, and active disassembly and replacement are required each time; patent CN 109505962A is a C-shaped bracket with variable supporting stiffness, in which the structure for adjusting the stiffness by adjusting the pre-compression amount of the supporting rubber is too complicated, and in the long-term service process of the rubber body, the performance of the rubber body is gradually degraded, so that the stiffness changing effect is difficult to be ensured; the patent CN112498708A is an aviation unmanned aerial vehicle and an aeroengine mounting bracket, the support end of the mounting bracket of the aeroengine is connected with an airplane, and vibration reduction is realized by matching with a rubber pad, but the structural appearance of the bracket is complex and is not easy to connect and mount, the vibration reduction effect of the rubber after long-term use is difficult to ensure, and the vibration reduction effect is not obvious; the patent CN 211502049U relates to an aircraft engine moving support, which has the effects of reducing the weight of the moving support and reducing the difficulty of pushing and pulling an aircraft engine, but the support does not have the effects of changing rigidity and damping; patent CN109333417A discloses an adjustable mounting bracket for a light aircraft engine, which comprises a supporting frame, a rotating component and a clamping component, but the supporting frame is more in cooperation, is not suitable for the mounting form of a hoop, does not have the effects of changing rigidity and damping, and cannot play a role in vibration damping and isolation; patent CN 210977682U provides a piston aeroengine support, including fixed frame, last bracing piece and bottom suspension fagging pole, but its installation is more complicated, and application scope is not wide, and does not have variable rigidity and becomes damping effect, also does not have vibration isolation damping effect to the clamp of connecting and pipeline structure.
Disclosure of Invention
The invention provides a variable-rigidity and variable-damping hoop support for an aero-engine and a preparation method thereof.
The technical scheme of the invention is as follows:
the utility model provides an aeroengine becomes rigidity damping clamp support, includes support body, apron, screw and becomes rigidity damping material filling block, support body and apron are L shape structure, the support body is equipped with along a plurality of cavities of its central line symmetric distribution, and it places to become excessive cooperation of rigidity damping material filling block in the cavity, the apron passes through the screw with the support body is installed together and will become rigidity damping material filling block shutoff and be in the support body.
Further, aeroengine become rigidity variable damping clamp support, the support body includes mutually perpendicular's support body one and support body two, cavity quantity is 12, support body one and support body two are equipped with 6 respectively the cavity, the cavity is along the perpendicular support body central line direction arranges that quantity is two.
Further, aeroengine becomes rigidity variable damping clamp support, become rigidity variable damping material filling block including parcel shell and a plurality of become rigidity variable damping structure spare, a plurality of become rigidity variable damping structure spare are placed in the parcel shell.
Furthermore, the variable-rigidity variable-damping hoop support for the aero-engine is 9 in number, and the variable-rigidity variable-damping structural members are distributed in three rows and three columns in the wrapping shell.
Furthermore, the variable-rigidity variable-damping hoop support of the aircraft engine comprises a variable-rigidity variable-damping structural part, a damping material layer and a shape memory alloy spiral wire, wherein the variable-rigidity variable-damping structural part comprises an elastic body, a shape memory alloy strip, a damping material layer and a shape memory alloy spiral wire; the elastomer comprises an elastomer material and an elastomer wrapping layer, and the elastomer wrapping layer wraps and molds the elastomer material; the four shape memory alloy strips are uniformly arranged around the elastic body, the damping material layer is arranged on the outer molded surface of the shape memory alloy strips, inward pressing force is applied to the four shape memory alloy strips, and the elastic body, the shape memory alloy strips and the damping material layer are plugged into the shape memory alloy spiral wire.
Furthermore, the aeroengine becomes rigidity and becomes damping clamp support, the screw with be equipped with the gasket between the apron.
The preparation method of the aeroengine variable-rigidity variable-damping hoop support comprises the following steps:
1) placing an elastomer material in an elastomer wrapping layer to be wrapped and formed into an elastomer;
2) uniformly arranging four shape memory alloy strips around the elastic body;
3) coating a damping material on the outer molded surface of the shape memory alloy strip to form the damping material layer;
4) applying inward pressing force to the four shape memory alloy strips, and plugging the elastic body, the shape memory alloy strips and the damping material layer into the shape memory alloy spiral wire to form a variable-rigidity variable-damping structural member;
5) placing 9 variable-rigidity variable-damping structural members in the wrapping shell in a three-row and three-column mode to form variable-rigidity variable-damping material filling blocks;
6) respectively placing 12 variable-rigidity variable-damping material filling blocks in 12 cavities in an excessive fit manner;
7) and the cover plate is installed together with the frame body through the screws, and the variable-rigidity variable-damping material filling block is blocked in the cavity.
The invention has the beneficial effects that: the variable-rigidity variable-damping clamp bracket for the aero-engine can realize rigidity change according to internal temperature rise caused by vibration intensity; the strength of the frame body can meet the basic strength requirement of the frame body under a low-vibration environment, and when vibration is intensified, the internal structure of the cavity can become more compact due to the change of various internal structures, so that the number of supporting structures is increased, and the rigidity of the hoop support can be improved; the damping material layer in the invention has viscoelasticity, the damping performance of the damping material layer is greatly influenced by temperature and frequency, when vibration is intensified, the damping material is more prone to viscous flow state along with the rise of temperature, and meanwhile, the elastic body in the invention is also changed into loose state from compact state before deformation, and the two parts can enhance the damping in the frame body.
Drawings
FIG. 1 is an external view of a variable stiffness and variable damping clamp bracket of an aircraft engine;
FIG. 2 is a schematic view of an assembly relationship of a variable-stiffness variable-damping clamp bracket of an aircraft engine;
FIG. 3 is a schematic view of the assembly relationship between a variable-stiffness variable-damping material filling block and a cavity;
FIG. 4 is a structural diagram of the variable stiffness and damping material filling block before deformation; wherein, (a) is a structural schematic diagram before deformation of the variable-stiffness variable-damping material filling block, (b) is a schematic diagram before deformation of the shape memory alloy strip, and (c) is a schematic diagram before deformation of the shape memory alloy spiral wire;
FIG. 5 is a structural diagram of the variable stiffness and damping material filling block after deformation; wherein, (a) is a structural schematic diagram of the deformed variable-stiffness and variable-damping material filling block, (b) is a schematic diagram of the deformed shape memory alloy strip, and (c) is a schematic diagram of the deformed shape memory alloy spiral wire.
Detailed Description
As shown in fig. 1-4, an aeroengine becomes rigidity damping change clamp support, includes support body 1, apron 2, screw 3 and becomes rigidity damping material filled block 5, support body 1 and apron 2 are L shape structure, support body 1 is equipped with along its central line symmetric distribution's 12 cavities, becomes rigidity damping material filled block 5 and excessively cooperates and places in the cavity, apron 2 passes through screw 3 with support body 1 is installed together and will become rigidity damping material filled block 5 shutoff and be in support body 1, screw 3 with be equipped with gasket 4 between apron 2. The frame body 1 comprises a first frame body and a second frame body which are perpendicular to each other, the first frame body and the second frame body are respectively provided with 6 cavities, and the number of the cavities is two along the direction perpendicular to the central line of the frame body 1. In order to make the variable stiffness and damping effect as obvious as possible, the volume proportion of the chambers in the frame body 1 is as large as possible while the clip carrier meets the requirement of basic bearing stiffness.
The variable-rigidity variable-damping material filling block 5 comprises a wrapping shell 10 and 9 variable-rigidity variable-damping structural members, wherein the 9 variable-rigidity variable-damping structural members are placed in the wrapping shell 10 and are distributed in three rows and three columns in the wrapping shell 10.
The variable-rigidity variable-damping structural part comprises an elastic body 9, a shape memory alloy strip 8, a damping material layer 7 and a shape memory alloy spiral wire 6; the elastomer 9 comprises an elastomer material and an elastomer wrapping layer, and the elastomer wrapping layer wraps and molds the elastomer material; the four shape memory alloy strips 8 are uniformly arranged around the elastic body 9, the damping material layer 7 is arranged on the outer molded surface of the shape memory alloy strips 8, inward pressing force is applied to the four shape memory alloy strips 8, and the elastic body 9, the shape memory alloy strips 8 and the damping material layer 7 are plugged into the shape memory alloy spiral wire 6.
The preparation method of the aeroengine variable-rigidity variable-damping hoop support comprises the following steps:
1) placing an elastomer material in an elastomer wrapping layer to wrap and form an elastomer 9;
2) arranging four strips 8 of shape memory alloy uniformly around said elastic body 9;
3) coating damping material on the outer molded surface of the shape memory alloy strip 8 to form the damping material layer 7;
4) applying inward pressing force to the four shape memory alloy strips 8, and plugging the elastic body 9, the shape memory alloy strips 8 and the damping material layer 7 into the shape memory alloy spiral wire 6 to form a variable-stiffness variable-damping structural member;
5) placing 9 variable-rigidity variable-damping structural members in the wrapping shell 10 in three rows and three columns to form variable-rigidity variable-damping material filling blocks 5;
6) 12 variable-rigidity variable-damping material filling blocks 5 are respectively placed in 12 cavities in an excessive matching manner;
7) the cover plate 2 is installed together with the frame body 1 through the screws 3, and the variable-rigidity variable-damping material filling block 5 is sealed in the cavity.
As shown in fig. 4 and 5, the variable stiffness and variable damping clamp bracket for the aircraft engine specifically realizes the variable stiffness mode as follows: before deformation, the section of the shape memory alloy strip 8 is in a double arc shape, the section of the shape memory alloy spiral wire 6 is in a circular shape, a gap is arranged between the two shape memory alloy strips 8, and the elastic body 9 is in a pressed state; the vibration causes the internal temperature of the hoop support to rise, the shape of the shape memory alloy can be changed due to the influence of the temperature of the shape memory alloy, the section of the shape memory alloy strip 8 is changed into a shape with an inner circle and an outer square, the section of the shape memory alloy spiral wire 6 is changed into a square, gaps among the shape memory alloy strips 8 disappear, and the elastic body 9 is in a relaxed state; the 9 variable-rigidity variable-damping structural members can bear force mutually, so that the integral stressed bodies of the frame body 1 are increased, and the rigidity is enhanced. The specific implementation of the variable damping mode is as follows: the damping material layer 7 is a composite system composed of epoxy resin, filler, auxiliary agents and the like, when the vibration is low, the damping material layer 7 tends to be in a glass state with poor fluidity, when the vibration is intensified, the damping material layer 7 tends to be in a viscous state along with the rise of the temperature, and the damping is enhanced; due to the fact that the temperature rises, the shape of the shape memory alloy strip 8 changes, the size of the elastic body 9 contained in the shape memory alloy strip 8 is increased, the inside of the elastic body 9 becomes loose, the friction damping effect of each part is improved, and therefore the damping material layer 7 and the elastic body 9 enable the damping of the frame body 1 to be enhanced.
Claims (7)
1. The utility model provides an aeroengine becomes rigidity damping clamp support, its characterized in that, becomes damping material filling block including support body, apron, screw and variable rigidity, support body and apron are L shape structure, the support body is equipped with a plurality of cavities along its central line symmetric distribution, and the damping material filling block excessively cooperates and places to become rigidity in the cavity, the apron passes through the screw with the support body is installed together and will become rigidity damping material filling block shutoff and be in the support body.
2. The aircraft engine variable-stiffness variable-damping clamp bracket according to claim 1, wherein the bracket body comprises a first bracket body and a second bracket body which are perpendicular to each other, the number of the chambers is 12, the first bracket body and the second bracket body are respectively provided with 6 chambers, and the number of the chambers is two along a direction perpendicular to the center line of the bracket body.
3. The aircraft engine variable stiffness and variable damping clip bracket of claim 1, wherein the variable stiffness and variable damping material filler block comprises a wrap shell and a plurality of variable stiffness and variable damping structures disposed within the wrap shell.
4. The aircraft engine variable stiffness and damping clamp bracket according to claim 3, wherein the variable stiffness and damping structure members are 9 in number and are distributed in three rows and three columns in the wrapping shell.
5. The aircraft engine variable stiffness and damping clamp bracket according to claim 4, wherein the variable stiffness and damping structure comprises an elastomer, a shape memory alloy strip, a damping material layer and a shape memory alloy spiral wire; the elastomer comprises an elastomer material and an elastomer wrapping layer, and the elastomer wrapping layer wraps and molds the elastomer material; the four shape memory alloy strips are uniformly arranged around the elastic body, the damping material layer is arranged on the outer molded surface of the shape memory alloy strips, inward pressing force is applied to the four shape memory alloy strips, and the elastic body, the shape memory alloy strips and the damping material layer are plugged into the shape memory alloy spiral wire.
6. The aircraft engine variable stiffness and damping clip bracket of claim 1, wherein a spacer is disposed between the screw and the cover plate.
7. The method for manufacturing a variable stiffness and variable damping clamp bracket for an aircraft engine according to claim 5, comprising the steps of:
1) placing an elastomer material in an elastomer wrapping layer to be wrapped and formed into an elastomer;
2) uniformly arranging four shape memory alloy strips around the elastic body;
3) coating a damping material on the outer molded surface of the shape memory alloy strip to form the damping material layer;
4) applying inward pressing force to the four shape memory alloy strips, and plugging the elastic body, the shape memory alloy strips and the damping material layer into the shape memory alloy spiral wire to form a variable-rigidity variable-damping structural member;
5) placing 9 variable-rigidity variable-damping structural members in the wrapping shell in a three-row and three-column mode to form variable-rigidity variable-damping material filling blocks;
6) respectively placing 12 variable-rigidity variable-damping material filling blocks in 12 cavities in an excessive fit manner;
7) and the cover plate is installed together with the frame body through the screws, and the variable-rigidity variable-damping material filling block is blocked in the cavity.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110674953.6A CN113374825B (en) | 2021-06-18 | 2021-06-18 | Variable-rigidity variable-damping clamp bracket for aero-engine and preparation method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110674953.6A CN113374825B (en) | 2021-06-18 | 2021-06-18 | Variable-rigidity variable-damping clamp bracket for aero-engine and preparation method thereof |
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| Publication Number | Publication Date |
|---|---|
| CN113374825A true CN113374825A (en) | 2021-09-10 |
| CN113374825B CN113374825B (en) | 2022-07-19 |
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| CN202110674953.6A Active CN113374825B (en) | 2021-06-18 | 2021-06-18 | Variable-rigidity variable-damping clamp bracket for aero-engine and preparation method thereof |
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Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2584936Y (en) * | 2002-12-17 | 2003-11-05 | 哈尔滨工业大学 | Multi-layer structure vibration damper capable of bearing space loading |
| CN1904102A (en) * | 2006-08-02 | 2007-01-31 | 哈尔滨工程大学 | Preparation method of Ni-Ti Series functional continuous gradient spaped memory alloy |
| CN101429788A (en) * | 2008-09-26 | 2009-05-13 | 李惠 | Shape memory alloy damper |
| CN102644686A (en) * | 2012-04-09 | 2012-08-22 | 北京航空航天大学 | Method for manufacturing damping structural piece of aviation engine supporting system |
| CN106869010A (en) * | 2016-12-23 | 2017-06-20 | 大连理工大学 | The damper of shape-memory alloy wire is twined outside a kind of high-damping rubber cylinder segmented |
| US20180298822A1 (en) * | 2017-04-14 | 2018-10-18 | General Electric Company | Support assembly having variable stiffness member |
| CN111828533A (en) * | 2020-06-29 | 2020-10-27 | 东南大学 | Shear type variable-rigidity viscoelastic device and working method thereof |
-
2021
- 2021-06-18 CN CN202110674953.6A patent/CN113374825B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2584936Y (en) * | 2002-12-17 | 2003-11-05 | 哈尔滨工业大学 | Multi-layer structure vibration damper capable of bearing space loading |
| CN1904102A (en) * | 2006-08-02 | 2007-01-31 | 哈尔滨工程大学 | Preparation method of Ni-Ti Series functional continuous gradient spaped memory alloy |
| CN101429788A (en) * | 2008-09-26 | 2009-05-13 | 李惠 | Shape memory alloy damper |
| CN102644686A (en) * | 2012-04-09 | 2012-08-22 | 北京航空航天大学 | Method for manufacturing damping structural piece of aviation engine supporting system |
| CN106869010A (en) * | 2016-12-23 | 2017-06-20 | 大连理工大学 | The damper of shape-memory alloy wire is twined outside a kind of high-damping rubber cylinder segmented |
| US20180298822A1 (en) * | 2017-04-14 | 2018-10-18 | General Electric Company | Support assembly having variable stiffness member |
| CN111828533A (en) * | 2020-06-29 | 2020-10-27 | 东南大学 | Shear type variable-rigidity viscoelastic device and working method thereof |
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