CN114683638B - Vibration-damping noise-reducing composite damping plate for military aircraft - Google Patents

Vibration-damping noise-reducing composite damping plate for military aircraft Download PDF

Info

Publication number
CN114683638B
CN114683638B CN202210487560.9A CN202210487560A CN114683638B CN 114683638 B CN114683638 B CN 114683638B CN 202210487560 A CN202210487560 A CN 202210487560A CN 114683638 B CN114683638 B CN 114683638B
Authority
CN
China
Prior art keywords
sjy
damping
layer
parts
rubber
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.)
Active
Application number
CN202210487560.9A
Other languages
Chinese (zh)
Other versions
CN114683638A (en
Inventor
张天鹏
刘亮
韩得才
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Shenyang Stress Damper Research Co ltd
Original Assignee
Shenyang Stress Damper Research Co ltd
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Shenyang Stress Damper Research Co ltd filed Critical Shenyang Stress Damper Research Co ltd
Priority to CN202210487560.9A priority Critical patent/CN114683638B/en
Publication of CN114683638A publication Critical patent/CN114683638A/en
Application granted granted Critical
Publication of CN114683638B publication Critical patent/CN114683638B/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B15/00—Layered products comprising a layer of metal
    • B32B15/20—Layered products comprising a layer of metal comprising aluminium or copper
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B15/00—Layered products comprising a layer of metal
    • B32B15/04—Layered products comprising a layer of metal comprising metal as the main or only constituent of a layer, which is next to another layer of the same or of a different material
    • B32B15/06—Layered products comprising a layer of metal comprising metal as the main or only constituent of a layer, which is next to another layer of the same or of a different material of natural rubber or synthetic rubber
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B25/00—Layered products comprising a layer of natural or synthetic rubber
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B25/00—Layered products comprising a layer of natural or synthetic rubber
    • B32B25/04—Layered products comprising a layer of natural or synthetic rubber comprising rubber as the main or only constituent of a layer, which is next to another layer of the same or of a different material
    • B32B25/042—Layered products comprising a layer of natural or synthetic rubber comprising rubber as the main or only constituent of a layer, which is next to another layer of the same or of a different material of natural rubber or synthetic rubber
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B7/00—Layered products characterised by the relation between layers; Layered products characterised by the relative orientation of features between layers, or by the relative values of a measurable parameter between layers, i.e. products comprising layers having different physical, chemical or physicochemical properties; Layered products characterised by the interconnection of layers
    • B32B7/04—Interconnection of layers
    • B32B7/12—Interconnection of layers using interposed adhesives or interposed materials with bonding properties
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
    • B64C1/40—Sound or heat insulation, e.g. using insulation blankets
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2250/00—Layers arrangement
    • B32B2250/05—5 or more layers
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2307/00—Properties of the layers or laminate
    • B32B2307/10—Properties of the layers or laminate having particular acoustical properties
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2307/00—Properties of the layers or laminate
    • B32B2307/50—Properties of the layers or laminate having particular mechanical properties
    • B32B2307/56—Damping, energy absorption
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2605/00—Vehicles
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2605/00—Vehicles
    • B32B2605/12—Ships
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2605/00—Vehicles
    • B32B2605/16—Submarines
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2605/00—Vehicles
    • B32B2605/18—Aircraft
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/40—Weight reduction

Abstract

A vibration-damping noise-reducing composite damping plate for a military aircraft belongs to the technical field of aerospace, the damping plate has a five-layer structure, and the total thickness of the damping plate is 3.1+/-0.3 mm; the damping plate is sequentially provided with a constraint layer, a damping layer I, a constraint aluminum foil, a damping layer II and a damping layer III from the outer surface to the inner adhesive surface, and pressure-sensitive adhesives are used for adhesion between layers. According to the invention, three damping layers with different characteristics are combined with one metal layer, a stacking and pasting sequence is designed, and the constraint layer is designed on the outermost layer, so that the performance of the damping plate can be well improved, good vibration and noise reduction effects can be ensured under the long-term and large vibration use environments, the overall thickness of the damping plate can be reduced on the premise of ensuring vibration and noise reduction, the space is not occupied, and the effect of light weight is achieved, so that the damping plate is particularly suitable for military aircraft.

Description

Vibration-damping noise-reducing composite damping plate for military aircraft
Technical Field
The invention belongs to the technical field of aerospace, and particularly relates to a vibration-damping noise-reducing composite damping plate for a military aircraft.
Background
In the process of aerogun blasting, the existing military aircraft can generate huge shock waves, and the shock waves cause the failure condition of the environmental control cabin equipment at the muzzle. In addition, after the existing military aircraft flies for a period of time, the cockpit has the problem of overlarge noise, so that the normal flying and operation of a pilot are seriously influenced, and the hazard is extremely high.
At present, in order to reduce vibration and noise, a damping plate is adhered to a vibrating structural member, so that vibration energy of an adhered structure is consumed, and noise radiation is reduced. CN106151338A discloses a composite damping plate for vibration and noise reduction, which comprises a metal layer and a damping layer which are alternately bonded, wherein the number of layers of the metal layer and the damping layer is more than or equal to two; the metal layer and the damping layer are alternately designed, so that the metal layer and the damping layer can be applied to a common aircraft, and the metal layer and the damping layer are not suitable for a military aircraft, so that the vibration is very large when the military aircraft is fired by an aircraft gun, and the metal layer and the single-component glue damping layer of the composite damping plate can not meet stricter vibration reduction requirements.
CN205705615U discloses a sound insulation and heat preservation material for an aircraft cabin, which comprises a melamine foam layer, a composite polyether sponge layer, a damping plate and an aluminum foil layer, wherein the melamine foam layer, the composite polyether sponge layer, the damping plate and the aluminum foil layer are sequentially arranged from inside to outside. The damping plate structure is mainly used for reducing weight and improving heat preservation performance, is only suitable for civil aircraft, and the damping effect cannot be met for military aircraft.
Disclosure of Invention
In order to design a damping plate meeting the use requirement of a military aircraft and achieve the purpose of vibration reduction and noise reduction with higher indexes, the invention provides the vibration reduction and noise reduction composite damping plate for the military aircraft. The specific technical scheme is as follows:
the damping plate is of a five-layer structure, and the total thickness of the damping plate is 3.1+/-0.3 mm; the damping plate is sequentially provided with a constraint layer 1, a damping layer I2, a constraint aluminum foil 3, a damping layer II 4 and a damping layer III 5 from the outer surface to the inner adhesive surface;
in the above technical scheme, the thickness of the constraint layer 1 is 0.22 mm-0.30 mm, and the material is 1060 aluminum plate.
In the technical scheme, the thickness of the damping layer I2 is 0.57-0.67 mm, and the damping layer I2 is made of a polymer composite material A.
The polymer composite material A comprises the following raw materials in parts by mass: 50 to 70 parts of rubber SJY-2840, 20 to 40 parts of rubber SJY-2860, 1 to 2 parts of mixed rubber SJY-2060-D, 1 to 2 parts of mixed rubber SJY-2060-H, 0.1 to 1 part of mixed rubber SJY-2060-X and 0.1 to 1 part of mixed rubber SJY-2060-Z; the polymer composite material A is prepared by mixing, heating and vulcanizing the raw materials.
In the above technical scheme, the thickness of the constraint aluminum foil 3 is 0.06 mm-0.10 mm, and the material is 8011H18 aluminum foil. In the above technical scheme, the thickness of the damping layer II 4 is 0.57 mm-0.67 mm, and the damping layer II is made of a polymer composite material B.
The polymer composite material B comprises the following raw materials in parts by weight: 20-40 parts of rubber SJY-2840, 50-70 parts of rubber SJY-2860, 1-2 parts of mixed rubber SJY-2060-D, 1-2 parts of mixed rubber SJY-2060-H, 0.1-1 part of mixed rubber SJY-2060-X and 0.1-1 part of mixed rubber SJY-2060-Z; the polymer composite material B is prepared by mixing, heating and vulcanizing the raw materials.
In the above technical scheme, the thickness of the damping layer III 5 is 1.30 mm-1.50 mm, and the damping layer III is made of a polymer composite material C.
The polymer composite material C comprises the following raw materials in parts by mass: 50 to 70 parts of rubber SJY-2060-40, 30 to 50 parts of rubber SJY-2060-50, 0.1 to 1 part of mixed rubber SJY-2060-D, 0.1 to 1 part of mixed rubber SJY-2060-H, 0.1 to 1 part of mixed rubber SJY-2060-X and 0.1 to 1 part of mixed rubber SJY-2060-Z; the polymer composite material C is prepared by mixing, heating and vulcanizing the raw materials.
In the above technical scheme, the constraint layer 1, the damping layer I2, the constraint aluminum foil 3, the damping layer II 4 and the damping layer III 5 are adhered by pressure sensitive adhesive.
In the technical scheme, one side of the damping layer III 5 of the damping plate is adhered to the inner walls of the cockpit and the equipment cabin of the military aircraft cabin.
In the technical scheme, the damping plate is applied to military aircraft, and can also be applied to civil aircraft, vehicles, ships or submarines.
Compared with the prior art, the vibration-damping noise-reducing composite damping plate for the military aircraft has the beneficial effects that:
1. the damping plate is designed to be of a five-layer structure, wherein the constraint layer is a 1060 aluminum plate, the design thickness is 0.22-0.30 mm, the aluminum plate with the thickness can play a good role in constraining and protecting the damping layer of the high polymer composite material, the surface of the damping layer of the high polymer composite material is constrained, and the damping performance of the five-layer composite damping plate can be improved through shearing deformation between the aluminum plate constraint layer and the damping layer of the high polymer composite material.
2. The damping plate is designed to be of a five-layer structure, wherein the restrained aluminum foil adopts 8011H18 aluminum foil with the thickness of 0.06-0.10 mm, and the restrained aluminum foil is matched with the restrained aluminum plate for use in order to restrain the damping layer of the high polymer composite material of the middle transition layer, so that the restraining capability is further improved, and the damping performance of the composite damping plate is improved through transition shear deformation.
3. The damping plate is designed to be of a five-layer structure, three layers of damping layers are designed, the three layers of damping layers are all made of polymer composite materials, the component proportions of the polymer composite materials of each layer are different, the polymer composite materials with different components are matched with each other for use, the elasticity and the viscosity of the damping layers of each layer are different, and the damping plate can be better suitable for converting energy with different amplitudes, so that when deformation is generated under the action of alternating stress, part of energy is stored as potential energy, the other part of energy is dissipated or converted into heat energy, and the dissipation or conversion of the energy is expressed as mechanical damping and has the effects of vibration reduction and noise reduction.
4. The vibration reduction effect of the damping layer under different structural parameters is compared and analyzed through a finite element model, and simulation analysis shows that the vibration energy consumption caused by the shearing deformation of the composite damping layer with different components in the five-layer structure of the composite damping plate is larger, and the vibration reduction effect is better than that of a single-layer structure and that of an alternating structure of a metal layer and a single-component adhesive damping layer. Because the whole thickness of the damping plate is thinner, the change of the composition, thickness and stacking sequence of each layer of material forming the damping plate is very critical, and the composition, thickness and stacking sequence are slightly changed to greatly influence the whole damping effect and the service life.
5. The invention limits the thickness of each layer of material, the total thickness is 3.1 plus or minus 0.3mm, the whole thickness of the damping plate can be reduced without occupying space on the premise of ensuring vibration reduction and noise reduction, and the effect of light weight is achieved.
In summary, the five-layer structure is designed and combined to prepare the damping plate, so that the vibration mechanical energy can be well converted into heat energy, the equipment cabin vibration energy can be effectively reduced, the noise of the cockpit can be reduced, and experiments prove that the composite damping plate disclosed by the invention has an average sound insulation value of 7.28-7.29 dB in the frequency range of 100-6300 Hz; the composite damping plate can reduce the energy of the gun vibration by more than 30 percent through verification of a loader.
The damping plate is mainly designed for military aircraft, has higher performance, is not limited to the use of the military aircraft, and can be applied to civil aircraft, vehicles, ships or submarines, and the application range is wide.
Drawings
Fig. 1 is a schematic structural diagram of a vibration and noise reduction composite damping plate for a military aircraft according to an embodiment of the present invention, wherein: 1-constraint layer, 2-damping layer I, 3-constraint aluminum foil, 4-damping layer II, 5-damping layer III.
FIG. 2 is a graph showing the sound insulation of the vibration damping and noise reduction composite damping plate of the military aircraft in the frequency range of 100-6300 Hz in the embodiment 1 of the invention;
Detailed Description
The invention will be further described with reference to specific embodiments and figures 1-2, but the invention is not limited to these embodiments.
Example 1
As shown in figure 1, the damping plate has a five-layer structure, and the total thickness of the damping plate is 3.1 plus or minus 0.3mm; the damping plate is sequentially provided with a constraint layer 1, a damping layer I2, a constraint aluminum foil 3, a damping layer II 4 and a damping layer III 5 from the outer surface to the inner adhesive surface; the restraint layer 1, the damping layer I2, the restraint aluminum foil 3, the damping layer II 4 and the damping layer III 5 are adhered by pressure sensitive adhesive.
The thickness of the restraint layer 1 is 0.22mm, and the material is 1060 aluminum plate.
The damping layer I2 has a thickness of 0.67mm, is made of a polymer composite material A, and comprises the following raw materials in parts by weight: 60 parts of rubber SJY-2840, 30 parts of rubber SJY-2860, 2 parts of mixed rubber SJY-2060-D, 1 part of mixed rubber SJY-2060-H, 0.6 part of mixed rubber SJY-2060-X and 0.6 part of mixed rubber SJY-2060-Z; the polymer composite material A is prepared by mixing, heating and vulcanizing the raw materials.
The thickness of the constraint aluminum foil 3 is 0.10mm, and the material is 8011H18 aluminum foil.
The thickness of the damping layer II 4 is 0.67mm, the material is a polymer composite material B, and the mass part ratio of the raw materials of the polymer composite material B is as follows: 30 parts of rubber SJY-2840, 60 parts of rubber SJY-2860, 1 part of mixed rubber SJY-2060-D, 2 parts of mixed rubber SJY-2060-H, 0.6 part of mixed rubber SJY-2060-X and 0.6 part of mixed rubber SJY-2060-Z; the polymer composite material B is prepared by mixing, heating and vulcanizing the raw materials.
The thickness of the damping layer III 5 is 1.50mm, the material is a polymer composite material C, and the mass part ratio of the raw materials of the polymer composite material C is as follows: 60 parts of rubber SJY-2060-40, 40 parts of rubber SJY-2060-50, 1 part of mixed rubber SJY-2060-D, 1 part of mixed rubber SJY-2060-H, 1 part of mixed rubber SJY-2060-X and 1 part of mixed rubber SJY-2060-Z; the polymer composite material C is prepared by mixing, heating and vulcanizing the raw materials.
When the composite damping plate is used, one side of the damping layer III 5 is adhered to the inner walls of the cockpit and the equipment cabin of the military aircraft cabin.
FIG. 2 is a graph of sound insulation in the frequency range of 100-6300 Hz, and the average sound insulation in the frequency range of 100-6300 Hz is 7.28dB, and the sound insulation result shows that the sound insulation effect is excellent, and the composite damping plate can reduce the vibration energy of a gun by 32% through verification of a loader.
Example 2
As shown in figure 1, the damping plate has a five-layer structure, and the total thickness of the damping plate is 3.1 plus or minus 0.3mm; the damping plate is sequentially provided with a constraint layer 1, a damping layer I2, a constraint aluminum foil 3, a damping layer II 4 and a damping layer III 5 from the outer surface to the inner adhesive surface; the restraint layer 1, the damping layer I2, the restraint aluminum foil 3, the damping layer II 4 and the damping layer III 5 are adhered by pressure sensitive adhesive.
The thickness of the restraint layer 1 is 0.30mm, and the material is 1060 aluminum plate.
The damping layer I2 has a thickness of 0.67mm, is made of a polymer composite material A, and comprises the following raw materials in parts by weight: 50 parts of rubber SJY-2840, 20 parts of rubber SJY-2860, 1.5 parts of mixed rubber SJY-2060-D, 1.5 parts of mixed rubber SJY-2060-H, 0.6 part of mixed rubber SJY-2060-X and 0.6 part of mixed rubber SJY-2060-Z; the polymer composite material A is prepared by mixing, heating and vulcanizing the raw materials.
The thickness of the constraint aluminum foil 3 is 0.10mm, and the material is 8011H18 aluminum foil.
The thickness of the damping layer II 4 is 0.67mm, the material is a polymer composite material B, and the mass part ratio of the raw materials of the polymer composite material B is as follows: 20 parts of rubber SJY-2840, 50 parts of rubber SJY-2860, 1 part of mixed rubber SJY-2060-D, 1 part of mixed rubber SJY-2060-H, 0.4 part of mixed rubber SJY-2060-X and 0.8 part of mixed rubber SJY-2060-Z; the polymer composite material B is prepared by mixing, heating and vulcanizing the raw materials.
The thickness of the damping layer III 5 is 1.50mm, the material is a polymer composite material C, and the mass part ratio of the raw materials of the polymer composite material C is as follows: 50 parts of rubber SJY-2060-40, 30 parts of rubber SJY-2060-50, 0.8 part of mixed rubber SJY-2060-D, 0.8 part of mixed rubber SJY-2060-H, 0.5 part of mixed rubber SJY-2060-X and 0.5 part of mixed rubber SJY-2060-Z; the polymer composite material C is prepared by mixing, heating and vulcanizing the raw materials.
When the composite damping plate is used, one side of the damping layer III 5 is adhered to the inner walls of the cockpit and the equipment cabin of the military aircraft cabin.
The test shows that the composite damping plate of the embodiment has an average sound insulation value of 7.29dB in the frequency range of 100-6300 Hz; the composite damping plate can reduce the gun vibration energy by 31 percent through verification of a loader.
Example 3
As shown in figure 1, the damping plate has a five-layer structure, and the total thickness of the damping plate is 3.1 plus or minus 0.3mm; the damping plate is sequentially provided with a constraint layer 1, a damping layer I2, a constraint aluminum foil 3, a damping layer II 4 and a damping layer III 5 from the outer surface to the inner adhesive surface; the restraint layer 1, the damping layer I2, the restraint aluminum foil 3, the damping layer II 4 and the damping layer III 5 are adhered by pressure sensitive adhesive.
The thickness of the restraint layer 1 is 0.30mm, and the material is 1060 aluminum plate.
The damping layer I2 has a thickness of 0.57mm, is made of a polymer composite material A, and comprises the following raw materials in parts by weight: 70 parts of rubber SJY-2840, 40 parts of rubber SJY-2860, 2 parts of mixed rubber SJY-2060-D, 2 parts of mixed rubber SJY-2060-H, 1 part of mixed rubber SJY-2060-X and 1 part of mixed rubber SJY-2060-Z; the polymer composite material A is prepared by mixing, heating and vulcanizing the raw materials.
The thickness of the constraint aluminum foil 3 is 0.06mm, and the material is 8011H18 aluminum foil.
The thickness of the damping layer II 4 is 0.67mm, the material is a polymer composite material B, and the mass part ratio of the raw materials of the polymer composite material B is as follows: 40 parts of rubber SJY-2840, 70 parts of rubber SJY-2860, 1 part of mixed rubber SJY-2060-D, 1 part of mixed rubber SJY-2060-H, 0.8 part of mixed rubber SJY-2060-X and 1 part of mixed rubber SJY-2060-Z; the polymer composite material B is prepared by mixing, heating and vulcanizing the raw materials.
The thickness of the damping layer III 5 is 1.50mm, the material is a polymer composite material C, and the mass part ratio of the raw materials of the polymer composite material C is as follows: 70 parts of rubber SJY-2060-40, 50 parts of rubber SJY-2060-50, 1 part of mixed rubber SJY-2060-D, 1 part of mixed rubber SJY-2060-H, 0.4 part of mixed rubber SJY-2060-X and 0.4 part of mixed rubber SJY-2060-Z; the polymer composite material C is prepared by mixing, heating and vulcanizing the raw materials.
When the composite damping plate is used, one side of the damping layer III 5 is adhered to the inner walls of the cockpit and the equipment cabin of the military aircraft cabin.
The test shows that the composite damping plate of the embodiment has an average sound insulation value of 7.28dB in the frequency range of 100-6300 Hz; the composite damping plate can reduce the energy of the gun vibration by 31.5 percent through verification of a loader.
Example 4
As shown in figure 1, the damping plate has a five-layer structure, and the total thickness of the damping plate is 3.1 plus or minus 0.3mm; the damping plate is sequentially provided with a constraint layer 1, a damping layer I2, a constraint aluminum foil 3, a damping layer II 4 and a damping layer III 5 from the outer surface to the inner adhesive surface; the restraint layer 1, the damping layer I2, the restraint aluminum foil 3, the damping layer II 4 and the damping layer III 5 are adhered by pressure sensitive adhesive.
The thickness of the restraint layer 1 is 0.30mm, and the material is 1060 aluminum plate.
The damping layer I2 has a thickness of 0.67mm, is made of a polymer composite material A, and comprises the following raw materials in parts by weight: 50 parts of rubber SJY-2840, 40 parts of rubber SJY-2860, 2 parts of mixed rubber SJY-2060-D, 1 part of mixed rubber SJY-2060-H, 0.1 part of mixed rubber SJY-2060-X and 1 part of mixed rubber SJY-2060-Z; the polymer composite material A is prepared by mixing, heating and vulcanizing the raw materials.
The thickness of the constraint aluminum foil 3 is 0.08mm, and the material is 8011H18 aluminum foil.
The thickness of the damping layer II 4 is 0.65mm, the damping layer II is made of a polymer composite material B, and the polymer composite material B comprises the following raw materials in parts by weight: 20 parts of rubber SJY-2840, 70 parts of rubber SJY-2860, 2 parts of mixed rubber SJY-2060-D, 1 part of mixed rubber SJY-2060-H, 0.1 part of mixed rubber SJY-2060-X and 1 part of mixed rubber SJY-2060-Z; the polymer composite material B is prepared by mixing, heating and vulcanizing the raw materials.
The thickness of the damping layer III 5 is 1.4mm, the material is a polymer composite material C, and the mass part ratio of the raw materials of the polymer composite material C is as follows: 50 parts of rubber SJY-2060-40, 50 parts of rubber SJY-2060-50, 1 part of mixed rubber SJY-2060-D, 0.1 part of mixed rubber SJY-2060-H, 0.1 part of mixed rubber SJY-2060-X and 1 part of mixed rubber SJY-2060-Z; the polymer composite material C is prepared by mixing, heating and vulcanizing the raw materials.
When the composite damping plate is used, one side of the damping layer III 5 is adhered to the inner walls of the cockpit and the equipment cabin of the military aircraft cabin.
The test shows that the composite damping plate of the embodiment has an average sound insulation value of 7.29dB in the frequency range of 100-6300 Hz; the composite damping plate can reduce the energy of the gun vibration by 30.4 percent through verification of a loader.
Example 5
As shown in figure 1, the damping plate has a five-layer structure, and the total thickness of the damping plate is 3.1 plus or minus 0.3mm; the damping plate is sequentially provided with a constraint layer 1, a damping layer I2, a constraint aluminum foil 3, a damping layer II 4 and a damping layer III 5 from the outer surface to the inner adhesive surface; the restraint layer 1, the damping layer I2, the restraint aluminum foil 3, the damping layer II 4 and the damping layer III 5 are adhered by pressure sensitive adhesive.
The thickness of the restraint layer 1 is 0.30mm, and the material is 1060 aluminum plate.
The damping layer I2 has a thickness of 0.67mm, is made of a polymer composite material A, and comprises the following raw materials in parts by weight: 70 parts of rubber SJY-2840, 20 parts of rubber SJY-2860, 1 part of mixed rubber SJY-2060-D, 2 parts of mixed rubber SJY-2060-H, 1 part of mixed rubber SJY-2060-X and 0.1 part of mixed rubber SJY-2060-Z; the polymer composite material A is prepared by mixing, heating and vulcanizing the raw materials.
The thickness of the constraint aluminum foil 3 is 0.10mm, and the material is 8011H18 aluminum foil.
The thickness of the damping layer II 4 is 0.57mm, the material is a polymer composite material B, and the mass part ratio of the raw materials of the polymer composite material B is as follows: 40 parts of rubber SJY-2840, 50 parts of rubber SJY-2860, 1 part of mixed rubber SJY-2060-D, 2 parts of mixed rubber SJY-2060-H, 1 part of mixed rubber SJY-2060-X and 0.1 part of mixed rubber SJY-2060-Z; the polymer composite material B is prepared by mixing, heating and vulcanizing the raw materials.
The thickness of the damping layer III 5 is 1.30mm, the material is a polymer composite material C, and the mass part ratio of the raw materials of the polymer composite material C is as follows: 70 parts of rubber SJY-2060-40, 30 parts of rubber SJY-2060-50, 0.1 part of mixed rubber SJY-2060-D, 1 part of mixed rubber SJY-2060-H, 1 part of mixed rubber SJY-2060-X and 0.1 part of mixed rubber SJY-2060-Z; the polymer composite material C is prepared by mixing, heating and vulcanizing the raw materials.
When the composite damping plate is used, one side of the damping layer III 5 is adhered to the inner walls of the cockpit and the equipment cabin of the military aircraft cabin.
The test shows that the composite damping plate of the embodiment has an average sound insulation value of 7.28dB in the frequency range of 100-6300 Hz; the composite damping plate can reduce the energy of the gun vibration by 30.8 percent through verification of a loader.
Example 6
As shown in figure 1, the damping plate has a five-layer structure, and the total thickness of the damping plate is 3.1 plus or minus 0.3mm; the damping plate is sequentially provided with a constraint layer 1, a damping layer I2, a constraint aluminum foil 3, a damping layer II 4 and a damping layer III 5 from the outer surface to the inner adhesive surface; the restraint layer 1, the damping layer I2, the restraint aluminum foil 3, the damping layer II 4 and the damping layer III 5 are adhered by pressure sensitive adhesive.
The thickness of the restraint layer 1 is 0.28mm, and the material is 1060 aluminum plate.
The damping layer I2 has a thickness of 0.60mm, is made of a polymer composite material A, and comprises the following raw materials in parts by weight: 55 parts of rubber SJY-2840, 25 parts of rubber SJY-2860, 1.2 parts of mixed rubber SJY-2060-D, 1.2 parts of mixed rubber SJY-2060-H, 0.3 part of mixed rubber SJY-2060-X and 0.3 part of mixed rubber SJY-2060-Z; the polymer composite material A is prepared by mixing, heating and vulcanizing the raw materials.
The thickness of the constraint aluminum foil 3 is 0.10mm, and the material is 8011H18 aluminum foil.
The thickness of the damping layer II 4 is 0.60mm, the material is a polymer composite material B, and the mass part ratio of the raw materials of the polymer composite material B is as follows: 25 parts of rubber SJY-2840, 55 parts of rubber SJY-2860, 1.2 parts of mixed rubber SJY-2060-D, 1.2 parts of mixed rubber SJY-2060-H, 0.3 part of mixed rubber SJY-2060-X and 0.3 part of mixed rubber SJY-2060-Z; the polymer composite material B is prepared by mixing, heating and vulcanizing the raw materials.
The thickness of the damping layer III 5 is 1.50mm, the material is a polymer composite material C, and the mass part ratio of the raw materials of the polymer composite material C is as follows: 55 parts of rubber SJY-2060-40, 35 parts of rubber SJY-2060-50, 0.3 part of mixed rubber SJY-2060-D, 0.3 part of mixed rubber SJY-2060-H, 0.3 part of mixed rubber SJY-2060-X and 0.3 part of mixed rubber SJY-2060-Z; the polymer composite material C is prepared by mixing, heating and vulcanizing the raw materials.
When the composite damping plate is used, one side of the damping layer III 5 is adhered to the inner walls of the cockpit and the equipment cabin of the military aircraft cabin.
The test shows that the composite damping plate of the embodiment has an average sound insulation value of 7.29dB in the frequency range of 100-6300 Hz; the composite damping plate can reduce the energy of the gun vibration by 33.4 percent through verification of a loader.
Example 7
As shown in figure 1, the damping plate has a five-layer structure, and the total thickness of the damping plate is 3.1 plus or minus 0.3mm; the damping plate is sequentially provided with a constraint layer 1, a damping layer I2, a constraint aluminum foil 3, a damping layer II 4 and a damping layer III 5 from the outer surface to the inner adhesive surface; the restraint layer 1, the damping layer I2, the restraint aluminum foil 3, the damping layer II 4 and the damping layer III 5 are adhered by pressure sensitive adhesive.
The thickness of the restraint layer 1 is 0.26mm, and the material is 1060 aluminum plate.
The damping layer I2 has a thickness of 0.62mm, is made of a polymer composite material A, and comprises the following raw materials in parts by weight: 65 parts of rubber SJY-2840, 35 parts of rubber SJY-2860, 1.8 parts of mixed rubber SJY-2060-D, 1.8 parts of mixed rubber SJY-2060-H, 0.8 part of mixed rubber SJY-2060-X and 1 part of mixed rubber SJY-2060-Z; the polymer composite material A is prepared by mixing, heating and vulcanizing the raw materials.
The thickness of the constraint aluminum foil 3 is 0.10mm, and the material is 8011H18 aluminum foil.
The thickness of the damping layer II 4 is 0.62mm, the material is a polymer composite material B, and the mass part ratio of the raw materials of the polymer composite material B is as follows: 35 parts of rubber SJY-2840, 65 parts of rubber SJY-2860, 1.8 parts of mixed rubber SJY-2060-D, 1.8 parts of mixed rubber SJY-2060-H, 1 part of mixed rubber SJY-2060-X and 0.8 part of mixed rubber SJY-2060-Z; the polymer composite material B is prepared by mixing, heating and vulcanizing the raw materials.
The thickness of the damping layer III 5 is 1.40mm, the material is a polymer composite material C, and the mass part ratio of the raw materials of the polymer composite material C is as follows: 65 parts of rubber SJY-2060-40, 45 parts of rubber SJY-2060-50, 1 part of mixed rubber SJY-2060-D, 1 part of mixed rubber SJY-2060-H, 0.2 part of mixed rubber SJY-2060-X and 0.2 part of mixed rubber SJY-2060-Z; the polymer composite material C is prepared by mixing, heating and vulcanizing the raw materials.
When the composite damping plate is used, one side of the damping layer III 5 is adhered to the inner walls of the cockpit and the equipment cabin of the military aircraft cabin.
The test shows that the composite damping plate of the embodiment has an average sound insulation value of 7.28dB in the frequency range of 100-6300 Hz; the composite damping plate can reduce the energy of the gun vibration by 33 percent through verification of a loader.
Example 8
As shown in figure 1, the damping plate has a five-layer structure, and the total thickness of the damping plate is 3.1 plus or minus 0.3mm; the damping plate is sequentially provided with a constraint layer 1, a damping layer I2, a constraint aluminum foil 3, a damping layer II 4 and a damping layer III 5 from the outer surface to the inner adhesive surface; the restraint layer 1, the damping layer I2, the restraint aluminum foil 3, the damping layer II 4 and the damping layer III 5 are adhered by pressure sensitive adhesive.
The thickness of the restraint layer 1 is 0.30mm, and the material is 1060 aluminum plate.
The damping layer I2 has a thickness of 0.67mm, is made of a polymer composite material A, and comprises the following raw materials in parts by weight: 60 parts of rubber SJY-2840, 30 parts of rubber SJY-2860, 1.5 parts of mixed rubber SJY-2060-D, 1.5 parts of mixed rubber SJY-2060-H, 0.5 part of mixed rubber SJY-2060-X and 0.5 part of mixed rubber SJY-2060-Z; the polymer composite material A is prepared by mixing, heating and vulcanizing the raw materials.
The thickness of the constraint aluminum foil 3 is 0.06mm, and the material is 8011H18 aluminum foil.
The thickness of the damping layer II 4 is 0.57mm, the material is a polymer composite material B, and the mass part ratio of the raw materials of the polymer composite material B is as follows: 30 parts of rubber SJY-2840, 60 parts of rubber SJY-2860, 1.5 parts of mixed rubber SJY-2060-D, 1.5 parts of mixed rubber SJY-2060-H, 0.5 part of mixed rubber SJY-2060-X and 0.5 part of mixed rubber SJY-2060-Z; the polymer composite material B is prepared by mixing, heating and vulcanizing the raw materials.
The thickness of the damping layer III 5 is 1.40mm, the material is a polymer composite material C, and the mass part ratio of the raw materials of the polymer composite material C is as follows: 60 parts of rubber SJY-2060-40, 40 parts of rubber SJY-2060-50, 0.5 part of mixed rubber SJY-2060-D, 0.5 part of mixed rubber SJY-2060-H, 0.5 part of mixed rubber SJY-2060-X and 0.5 part of mixed rubber SJY-2060-Z; the polymer composite material C is prepared by mixing, heating and vulcanizing the raw materials.
When the composite damping plate is used, one side of the damping layer III 5 is adhered to the inner walls of the cockpit and the equipment cabin of the military aircraft cabin.
The test shows that the composite damping plate of the embodiment has an average sound insulation value of 7.29dB in the frequency range of 100-6300 Hz; the composite damping plate can reduce the energy of the gun vibration by 31.2 percent through verification of a loader.

Claims (10)

1. A vibration and noise reduction composite damping plate for a military aircraft is characterized in that the damping plate has a five-layer structure, and the total thickness of the damping plate is 3.1+/-0.3 mm; the damping plate is sequentially provided with a constraint layer (1), a damping layer I (2), a constraint aluminum foil (3), a damping layer II (4) and a damping layer III (5) from the outer surface to the inner adhesive surface;
the constraint layer (1) is made of 1060 aluminum plates;
the damping layer I (2) is made of a polymer composite material A; the polymer composite material A comprises the following raw materials in parts by mass: 50-70 parts of rubber SJY-2840, 20-40 parts of rubber SJY-2860, 1-2 parts of mixed rubber SJY-2060-D, 1-2 parts of mixed rubber SJY-2060-H, 0.1-1 part of mixed rubber SJY-2060-X and 0.1-1 part of mixed rubber SJY-2060-Z;
the constraint aluminum foil (3) is made of 8011H18 aluminum foil;
the damping layer II (4) is made of a polymer composite material B; the polymer composite material B comprises the following raw materials in parts by weight: 20-40 parts of rubber SJY-2840, 50-70 parts of rubber SJY-2860, 1-2 parts of mixed rubber SJY-2060-D, 1-2 parts of mixed rubber SJY-2060-H, 0.1-1 part of mixed rubber SJY-2060-X and 0.1-1 part of mixed rubber SJY-2060-Z;
the damping layer III (5) is made of a polymer composite material C; the polymer composite material C comprises the following raw materials in parts by mass: 50-70 parts of rubber SJY-2060-40, 30-50 parts of rubber SJY-2060-50, 0.1-1 part of mixed rubber SJY-2060-D, 0.1-1 part of mixed rubber SJY-2060-H, 0.1-1 part of mixed rubber SJY-2060-X and 0.1-1 part of mixed rubber SJY-2060-Z.
2. The vibration and noise reduction composite damping plate for the military aircraft according to claim 1, wherein the thickness of the constraint layer (1) is 0.22-0.30 mm.
3. The vibration and noise reduction composite damping plate for the military aircraft according to claim 1, wherein the thickness of the damping layer I (2) is 0.57-0.67 mm.
4. The vibration-damping noise-reducing composite damping plate for the military aircraft according to claim 3, wherein the polymer composite material A is prepared by mixing, heat-refining and vulcanizing.
5. The vibration and noise reduction composite damping plate for the military aircraft according to claim 1, wherein the thickness of the constraint aluminum foil (3) is 0.06-0.10 mm.
6. The vibration and noise reduction composite damping plate for the military aircraft according to claim 1, wherein the thickness of the damping layer II (4) is 0.57-0.67 mm.
7. The vibration-damping noise-reducing composite damping plate for the military aircraft according to claim 6, wherein the polymer composite material B is prepared by mixing, heat-mixing and vulcanizing.
8. The vibration and noise reduction composite damping plate for the military aircraft according to claim 1, wherein the thickness of the damping layer III (5) is 1.30 mm-1.50 mm.
9. The vibration-damping noise-reducing composite damping plate for the military aircraft according to claim 8, wherein the polymer composite material C is prepared by mixing, heat-mixing and vulcanizing.
10. The vibration and noise reduction composite damping plate for the military aircraft according to claim 1, wherein the constraint layer (1), the damping layer I (2), the constraint aluminum foil (3), the damping layer II (4) and the damping layer III (5) are adhered by pressure sensitive adhesive; one side of a damping layer III (5) of the damping plate is adhered to the inner walls of a cockpit and an equipment cabin of a military aircraft cabin; the damping plate is applicable to military aircraft, but also to civil aircraft, vehicles, ships and submarines.
CN202210487560.9A 2022-05-06 2022-05-06 Vibration-damping noise-reducing composite damping plate for military aircraft Active CN114683638B (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN202210487560.9A CN114683638B (en) 2022-05-06 2022-05-06 Vibration-damping noise-reducing composite damping plate for military aircraft

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN202210487560.9A CN114683638B (en) 2022-05-06 2022-05-06 Vibration-damping noise-reducing composite damping plate for military aircraft

Publications (2)

Publication Number Publication Date
CN114683638A CN114683638A (en) 2022-07-01
CN114683638B true CN114683638B (en) 2024-02-02

Family

ID=82144517

Family Applications (1)

Application Number Title Priority Date Filing Date
CN202210487560.9A Active CN114683638B (en) 2022-05-06 2022-05-06 Vibration-damping noise-reducing composite damping plate for military aircraft

Country Status (1)

Country Link
CN (1) CN114683638B (en)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN117227306B (en) * 2023-11-10 2024-01-30 苏州国融前沿技术有限公司 Vibration-damping noise-reducing composite damping plate structure for aircraft and processing equipment thereof

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH05220883A (en) * 1991-12-19 1993-08-31 Nitto Denko Corp Damping sheet
CN106393909A (en) * 2016-08-31 2017-02-15 西安立远新材料科技开发有限公司 High damping composite plate
CN206335907U (en) * 2016-08-31 2017-07-18 西安立远新材料科技开发有限公司 A kind of NEW TYPE OF COMPOSITE damping sheet

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
ES2873923T3 (en) * 2007-02-09 2021-11-04 Sekisui Chemical Co Ltd Vibration damping material and vibration damping structure

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH05220883A (en) * 1991-12-19 1993-08-31 Nitto Denko Corp Damping sheet
CN106393909A (en) * 2016-08-31 2017-02-15 西安立远新材料科技开发有限公司 High damping composite plate
CN206335907U (en) * 2016-08-31 2017-07-18 西安立远新材料科技开发有限公司 A kind of NEW TYPE OF COMPOSITE damping sheet

Also Published As

Publication number Publication date
CN114683638A (en) 2022-07-01

Similar Documents

Publication Publication Date Title
CN108717850B (en) Double-layer plate cavity vibration and noise reduction structure
CN114683638B (en) Vibration-damping noise-reducing composite damping plate for military aircraft
CN108119588B (en) Low-frequency broadband vibration suppression structure based on double-period forbidden band characteristic
US4581284A (en) Fiber compound material
EP0772958B1 (en) Internally damped circuit articles
EP1657374B1 (en) Thermal - Acoustic enclosure
CN107825773B (en) Aluminum-plastic composite film for lithium battery flexible package
EP3281861A1 (en) A rotary wing aircraft with a fuselage that comprises at least one structural stiffened panel
CN1663884A (en) Vibration reduction restriction damping layer of spacecraft
US20100206159A1 (en) Shield for explosive cutter
Burton et al. Structural analysis of the adhesive bond in a honeycomb core sandwich panel
CN219214323U (en) Vibration-damping noise-reducing composite damping plate for military aircraft
CN112848554A (en) High-toughness fiber-reinforced foamed aluminum gradient anti-explosion composite structure
US8127889B1 (en) Noise reduction system for structures
CN110001170B (en) Flexible foam filled honeycomb constrained damping sandwich structure and preparation method thereof
US5338599A (en) Vibration-damping structural component
WO2009133257A2 (en) Structural aircraft panel made of composite material incorporating protection against high-energy impacts
CN201333819Y (en) Strengthening aluminum honeycomb panel
CN201659720U (en) Sound absorbing and insulating thermal insulating material product
CN106151338A (en) A kind of vibration and noise reducing composite damping board
CN114166069A (en) Light multilayer composite structure bulletproof armor plate and preparation method thereof
CN110688780A (en) Novel buffer structure based on bionic principle
CN203901857U (en) Reinforced aluminum honeycomb panel
CN111793450A (en) Medium-high temperature curing epoxy structure adhesive film with thermal breaking performance applied to sound absorption and noise reduction honeycomb plate and preparation method thereof
Adetu et al. Upon Using of Plastics Layer in Light Multilayered Armor

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
GR01 Patent grant
GR01 Patent grant