CN114683638A - Vibration and noise reduction composite damping plate for military aircraft - Google Patents

Vibration and noise reduction composite damping plate for military aircraft Download PDF

Info

Publication number
CN114683638A
CN114683638A CN202210487560.9A CN202210487560A CN114683638A CN 114683638 A CN114683638 A CN 114683638A CN 202210487560 A CN202210487560 A CN 202210487560A CN 114683638 A CN114683638 A CN 114683638A
Authority
CN
China
Prior art keywords
damping
sjy
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.)
Granted
Application number
CN202210487560.9A
Other languages
Chinese (zh)
Other versions
CN114683638B (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

Images

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

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Laminated Bodies (AREA)

Abstract

A damping and noise-reducing composite damping plate for a military aircraft belongs to the technical field of aerospace, and is of a five-layer structure, wherein the total thickness of the damping plate is 3.1 +/-0.3 mm; the damping plate is sequentially provided with a restraint layer, a damping layer I, a restraint aluminum foil, a damping layer II and a damping layer III from the outer surface to the inner sticking surface, and the layers are stuck by pressure-sensitive adhesive. According to the invention, three damping layers with different characteristics are combined with one metal layer, the stacking and pasting sequence is designed, the constraint layer is designed on the outermost layer, the performance of the damping plate can be well improved, good vibration and noise reduction effects can be ensured under 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 occupied space is not occupied, the effect of light weight is achieved, and the damping plate is particularly suitable for military airplanes.

Description

Vibration and noise reduction composite damping plate for military aircraft
Technical Field
The invention belongs to the technical field of aerospace, and particularly relates to a vibration and noise reduction composite damping plate for a military aircraft.
Background
The existing military aircraft can generate huge shock waves in the process of carrying out aerial gun shooting, and the shock waves cause the failure condition of equipment in an environmental control cabin at a gun opening. In addition, after the conventional military aircraft flies for a period of time, the problem of overlarge noise occurs in the cockpit, the normal flight and operation of a pilot are seriously influenced, and the hazard is very high.
At present, in order to reduce vibration and noise, a damping plate is adhered to a vibrating structural component, so that the vibration energy of the adhered structure is consumed, and the 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 the metal layer and the damping layer is more than or equal to two; the composite damping plate is designed by alternately arranging the metal layer and the damping layer, can be applied to common airplanes and is not suitable for military airplanes, the military airplanes vibrate greatly when cannons and cannons are shot, and the alternating form of the metal layer and the single-component glue damping layer of the composite damping plate cannot meet the stricter vibration reduction requirement.
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. This patent damping plate structure is mainly in order to lighten weight and improve the thermal insulation performance, also is applicable to civil aircraft only, and the damping effect can not satisfy military aircraft.
Disclosure of Invention
In order to design a damping plate meeting the use requirement of a military aircraft and achieve the aim of vibration reduction and noise reduction with higher indexes, the invention provides the composite damping plate for vibration reduction and noise reduction of the military aircraft. The specific technical scheme is as follows:
a damping and noise-reducing composite damping plate for a military aircraft 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 restraint layer 1, a damping layer I2, a restraint aluminum foil 3, a damping layer II 4 and a damping layer III 5 from the outer surface to the inner sticking surface;
in the 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 mm-0.67 mm, and the damping layer is made of the 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 polymer composite material A is prepared by mixing, heating and vulcanizing raw materials.
In the above technical solution, the thickness of the constraint aluminum foil 3 is 0.06 mm-0.10 mm, and the material is 8011H18 aluminum foil. In the technical scheme, the thickness of the damping layer II 4 is 0.57 mm-0.67 mm, and the material is a polymer composite material B.
The polymer composite material B comprises the following raw materials in parts by mass: 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 raw materials.
In the technical scheme, the thickness of the damping layer III 5 is 1.30-1.50 mm, and the material is 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; the polymer composite material C is prepared by mixing, heating and vulcanizing raw materials.
In the technical scheme, 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 through the pressure-sensitive adhesive.
In the technical scheme, one side of the damping layer III 5 of the damping plate is stuck to the inner wall of a cockpit and an equipment cabin of a 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:
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 constraint protection role for the damping layer of the polymer composite material, the surface of the damping layer of the polymer composite material is constrained, and the damping performance of the five-layer composite damping plate can be improved through shear deformation between the aluminum plate constraint layer and the polymer composite material damping layer.
The damping plate is designed to be of a five-layer structure, wherein the constraining aluminum foil is 8011H18 aluminum foil, the thickness is 0.06 mm-0.10 mm, the aluminum foil with the thickness is used for constraining the damping layer of the polymer composite material of the middle transition layer, the constraining aluminum foil is matched with the aluminum plate of the constraining layer, the constraining capability is further improved, and the damping performance of the composite damping plate is improved through transition shear deformation.
The damping plate is designed to be of a five-layer structure, three damping layers are designed, the three damping layers are all made of polymer composite materials, the component proportion of each high-molecular composite material is different, the polymer composite materials with different components are matched for use, the elasticity and the viscosity of the damping layer of each layer are different, and the damping plate can be better suitable for converting energy with different amplitudes, so that when the damping plate is deformed 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, the dissipation or conversion of the energy is represented as mechanical damping, and the damping plate has the effects of vibration reduction and noise reduction.
And fourthly, comparing and analyzing the vibration attenuation effect of the damping layer under different structural parameters through a finite element model, and showing 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 through simulation analysis, and the vibration isolation effect is better than that of a single-layer structure and better than that of an alternating structure of the metal layer and the single-component glue damping layer. Because the whole thickness of the damping plate is thinner, the change of the components, the thickness and the stacking sequence of each layer of material forming the damping plate is very critical, and the whole damping effect and the service life can be greatly influenced by slightly changing the components, the thickness and the stacking sequence.
And fifthly, the thickness of each layer of material is limited, the total thickness is 3.1 +/-0.3 mm, 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.
In conclusion, the damping plate is prepared by combining a five-layer structure, so that the vibration mechanical energy can be well converted into heat energy, the vibration energy of the equipment cabin is effectively reduced, the noise of the cockpit is reduced, and the average sound insulation quantity of the composite damping plate is 7.28-7.29 dB within the frequency range of 100-6300 Hz through test verification; the composite damping plate can reduce the vibration energy by more than 30 percent through the verification of an installation machine.
The damping plate is mainly designed for military aircraft, has high performance, is not limited to military aircraft, can be applied to civil aircraft, vehicles, ships or submarines, and has wide application range.
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-restraint layer, 2-damping layer I, 3-restraint aluminum foil, 4-damping layer II and 5-damping layer III.
FIG. 2 is a sound insulation quantity curve diagram of the vibration 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 examples.
Example 1
A vibration and noise reduction composite damping plate for a military aircraft is shown in figure 1, and is of a five-layer structure, wherein the total thickness of the damping plate is 3.1 +/-0.3 mm; the damping plate is sequentially provided with a restraint layer 1, a damping layer I2, a restraint aluminum foil 3, a damping layer II 4 and a damping layer III 5 from the outer surface to the inner sticking 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 through pressure-sensitive adhesive.
The thickness of the constraint layer 1 is 0.22mm, and the material is 1060 aluminum plate.
Damping layer I2's thickness is 0.67mm, and the material is polymer composite A, and polymer composite A's raw materials composition part by mass ratio is: 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 raw materials.
The thickness of the constraint aluminum foil 3 is 0.10mm, and the material is 8011H18 aluminum foil.
The thickness of damping layer II 4 is 0.67mm, and the material is polymer composite B, and polymer composite B's raw materials component part by mass ratio is: 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 raw materials.
The thickness of damping layer III 5 is 1.50mm, and the material is polymer composite C, and polymer composite C's raw materials component part by mass ratio is: 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 raw materials.
When the composite damping plate is used, one surface of the damping layer III 5 is adhered to the inner walls of a cockpit and an equipment cabin of a military aircraft cabin.
Fig. 2 is a sound insulation quantity curve diagram of the composite damping plate in the embodiment, which is detected by tests, in a frequency range of 100-6300 Hz, the average sound insulation quantity is 7.28dB in the frequency range of 100-6300 Hz, and the sound insulation quantity result shows that the composite damping plate has excellent sound insulation effect, and the composite damping plate can reduce the shot vibration energy by 32% through installation verification.
Example 2
A vibration and noise reduction composite damping plate for a military aircraft is shown in figure 1, and is of a five-layer structure, wherein the total thickness of the damping plate is 3.1 +/-0.3 mm; the damping plate is sequentially provided with a restraint layer 1, a damping layer I2, a restraint aluminum foil 3, a damping layer II 4 and a damping layer III 5 from the outer surface to the inner sticking 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 through pressure-sensitive adhesive.
The thickness of the restraint layer 1 is 0.30mm, and the material is 1060 aluminum plate.
Damping layer I2's thickness is 0.67mm, and the material is polymer composite A, and polymer composite A's raw materials composition part by mass ratio is: 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 raw materials.
The thickness of the constraint aluminum foil 3 is 0.10mm, and the material is 8011H18 aluminum foil.
The thickness of damping layer II 4 is 0.67mm, and the material is polymer composite B, and polymer composite B's raw materials component part by mass ratio is: 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 raw materials.
The thickness of damping layer III 5 is 1.50mm, and the material is polymer composite C, and polymer composite C's raw materials component part by mass ratio is: 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 raw materials.
When the composite damping plate is used, one surface of the damping layer III 5 is adhered to the inner walls of a cockpit and an equipment cabin of a military aircraft cabin.
The composite damping plate of the embodiment is tested, and the average sound insulation quantity is 7.29dB within the frequency range of 100-6300 Hz; the composite damping plate can reduce the vibration energy of the gun by 31 percent through the verification of an installation machine.
Example 3
A vibration and noise reduction composite damping plate for a military aircraft is shown in figure 1, and is of a five-layer structure, wherein the total thickness of the damping plate is 3.1 +/-0.3 mm; the damping plate is sequentially provided with a restraint layer 1, a damping layer I2, a restraint aluminum foil 3, a damping layer II 4 and a damping layer III 5 from the outer surface to the inner sticking 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 through pressure-sensitive adhesive.
The thickness of the restraint layer 1 is 0.30mm, and the material is 1060 aluminum plate.
The thickness of damping layer I2 is 0.57mm, and the material is polymer composite A, and polymer composite A's raw materials composition part by mass ratio is: 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 raw materials.
The thickness of the constraint aluminum foil 3 is 0.06mm, and the material is 8011H18 aluminum foil.
The thickness of damping layer II 4 is 0.67mm, and the material is polymer composite B, and polymer composite B's raw materials component part by mass ratio is: 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 raw materials.
The thickness of damping layer III 5 is 1.50mm, and the material is polymer composite C, and polymer composite C's raw materials component part by mass ratio is: 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 raw materials.
When the composite damping plate is used, one surface of the damping layer III 5 is adhered to the inner walls of a cockpit and an equipment cabin of a military aircraft cabin.
The composite damping plate of the embodiment is tested, and the average sound insulation amount is 7.28dB within the frequency range of 100-6300 Hz; the composite damping plate can reduce the vibration energy of the gun by 31.5 percent through the verification of an installation machine.
Example 4
A vibration and noise reduction composite damping plate for a military aircraft is shown in figure 1, and is of a five-layer structure, wherein the total thickness of the damping plate is 3.1 +/-0.3 mm; the damping plate is sequentially provided with a restraint layer 1, a damping layer I2, a restraint aluminum foil 3, a damping layer II 4 and a damping layer III 5 from the outer surface to the inner sticking 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 through pressure-sensitive adhesive.
The thickness of the restraint layer 1 is 0.30mm, and the material is 1060 aluminum plate.
Damping layer I2's thickness is 0.67mm, and the material is polymer composite A, and polymer composite A's raw materials composition part by mass ratio is: 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 raw materials.
The thickness of the constraint aluminum foil 3 is 0.08mm, and the material is 8011H18 aluminum foil.
The thickness of damping layer II 4 is 0.65mm, and the material is polymer composite B, and polymer composite B's raw materials component part by mass ratio is: 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 raw materials.
The thickness of damping layer III 5 is 1.4mm, and the material is polymer composite C, and polymer composite C's raw materials component part by mass ratio is: 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 raw materials.
When the composite damping plate is used, one surface of the damping layer III 5 is adhered to the inner walls of a cockpit and an equipment cabin of a military aircraft cabin.
The composite damping plate of the embodiment is tested, and the average sound insulation amount is 7.29dB in the frequency range of 100-6300 Hz; the composite damping plate can reduce the vibration energy of the gun by 30.4 percent through the verification of an installation machine.
Example 5
A vibration and noise reduction composite damping plate for a military aircraft is shown in figure 1, and is of a five-layer structure, wherein the total thickness of the damping plate is 3.1 +/-0.3 mm; the damping plate is sequentially provided with a restraint layer 1, a damping layer I2, a restraint aluminum foil 3, a damping layer II 4 and a damping layer III 5 from the outer surface to the inner sticking 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 through pressure-sensitive adhesive.
The thickness of the restraint layer 1 is 0.30mm, and the material is 1060 aluminum plate.
Damping layer I2's thickness is 0.67mm, and the material is polymer composite A, and polymer composite A's raw materials composition part by mass ratio is: 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 raw materials.
The thickness of the constraint aluminum foil 3 is 0.10mm, and the material is 8011H18 aluminum foil.
The thickness of damping layer II 4 is 0.57mm, and the material is polymer composite B, and polymer composite B's raw materials component part by mass ratio is: 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 raw materials.
The thickness of damping layer III 5 is 1.30mm, and the material is polymer composite C, and polymer composite C's raw materials component part by mass ratio is: 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 raw materials.
When the composite damping plate is used, one surface of the damping layer III 5 is adhered to the inner walls of a cockpit and an equipment cabin of a military aircraft cabin.
The composite damping plate of the embodiment is tested, and the average sound insulation amount is 7.28dB within the frequency range of 100-6300 Hz; the composite damping plate can reduce the vibration energy of the gun by 30.8 percent through the verification of an installation machine.
Example 6
A vibration and noise reduction composite damping plate for a military aircraft is shown in figure 1, and is of a five-layer structure, wherein the total thickness of the damping plate is 3.1 +/-0.3 mm; the damping plate is sequentially provided with a restraint layer 1, a damping layer I2, a restraint aluminum foil 3, a damping layer II 4 and a damping layer III 5 from the outer surface to the inner sticking 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 through pressure-sensitive adhesive.
The thickness of the constraint layer 1 is 0.28mm, and the material is 1060 aluminum plate.
The thickness of damping layer I2 is 0.60mm, and the material is polymer composite A, and polymer composite A's raw materials composition part by mass ratio is: 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 raw materials.
The thickness of the constraint aluminum foil 3 is 0.10mm, and the material is 8011H18 aluminum foil.
The thickness of damping layer II 4 is 0.60mm, and the material is polymer composite B, and polymer composite B's raw materials component part by mass ratio is: 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 raw materials.
The thickness of damping layer III 5 is 1.50mm, and the material is polymer composite C, and polymer composite C's raw materials component part by mass ratio is: 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 raw materials.
When the composite damping plate is used, one surface of the damping layer III 5 is adhered to the inner walls of a cockpit and an equipment cabin of a military aircraft cabin.
The composite damping plate of the embodiment is tested, and the average sound insulation amount is 7.29dB in the frequency range of 100-6300 Hz; the installation proves that the composite damping plate can reduce the vibration energy by 33.4 percent.
Example 7
A vibration-damping noise-reducing composite damping plate for a military aircraft is shown in figure 1, and is of a five-layer structure, wherein the total thickness of the damping plate is 3.1 +/-0.3 mm; the damping plate is sequentially provided with a restraint layer 1, a damping layer I2, a restraint aluminum foil 3, a damping layer II 4 and a damping layer III 5 from the outer surface to the inner sticking 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 through pressure-sensitive adhesive.
The thickness of the restraint layer 1 is 0.26mm, and the material is 1060 aluminum plate.
Damping layer I2's thickness is 0.62mm, and the material is polymer composite A, polymer composite A's raw materials composition part by mass ratio is: 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 raw materials.
The thickness of the constraint aluminum foil 3 is 0.10mm, and the material is 8011H18 aluminum foil.
The thickness of damping layer II 4 is 0.62mm, and the material is polymer composite B, and polymer composite B's raw materials component part by mass ratio is: 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 raw materials.
The thickness of damping layer III 5 is 1.40mm, and the material is polymer composite C, and polymer composite C's raw materials component part by mass ratio is: 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 raw materials.
When the composite damping plate is used, one surface of the damping layer III 5 is adhered to the inner walls of a cockpit and an equipment cabin of a military aircraft cabin.
The composite damping plate of the embodiment is tested, and the average sound insulation amount is 7.28dB within the frequency range of 100-6300 Hz; the composite damping plate can reduce the shot vibration energy by 33 percent through the verification of an installation machine.
Example 8
A vibration and noise reduction composite damping plate for a military aircraft is shown in figure 1, and is of a five-layer structure, wherein the total thickness of the damping plate is 3.1 +/-0.3 mm; the damping plate is sequentially provided with a restraint layer 1, a damping layer I2, a restraint aluminum foil 3, a damping layer II 4 and a damping layer III 5 from the outer surface to the inner sticking 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 through pressure-sensitive adhesive.
The thickness of the restraint layer 1 is 0.30mm, and the material is 1060 aluminum plate.
Damping layer I2's thickness is 0.67mm, and the material is polymer composite A, and polymer composite A's raw materials composition part by mass ratio is: 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 raw materials.
The thickness of the constraint aluminum foil 3 is 0.06mm, and the material is 8011H18 aluminum foil.
The thickness of damping layer II 4 is 0.57mm, and the material is polymer composite B, and polymer composite B's raw materials component part by mass ratio is: 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 raw materials.
The thickness of damping layer III 5 is 1.40mm, and the material is polymer composite C, and polymer composite C's raw materials component part by mass ratio is: 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 raw materials.
When the composite damping plate is used, one surface of the damping layer III 5 is adhered to the inner walls of a cockpit and an equipment cabin of a military aircraft cabin.
The composite damping plate of the embodiment is tested, and the average sound insulation amount is 7.29dB in the frequency range of 100-6300 Hz; the composite damping plate can reduce the vibration energy of the gun by 31.2 percent through the verification of an installation machine.

Claims (10)

1. A vibration damping and noise reducing composite damping plate for a military aircraft is characterized in that 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 restraint layer (1), a damping layer I (2), a restraint aluminum foil (3), a damping layer II (4) and a damping layer III (5) from the outer surface to the inner sticking surface.
2. The damping and noise-reducing composite damping plate for military aircraft according to claim 1, wherein the thickness of the constraining layer (1) is 0.22 mm-0.30 mm, and the material is 1060 aluminum plate.
3. The damping and noise-reducing composite damping plate for the military aircraft as claimed in claim 1, wherein the damping layer I (2) is 0.57mm to 0.67mm thick and is made of polymer composite material A.
4. The damping and noise-reducing composite damping plate for military aircraft according to claim 3, wherein 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 polymer composite material A is prepared by mixing, heating and vulcanizing raw materials.
5. The damping and noise-reducing composite damping plate for military aircraft as defined in claim 1, wherein the restraining aluminum foil (3) has a thickness of 0.06-0.10 mm and is 8011H18 aluminum foil.
6. The damping and noise-reducing composite damping plate for the military aircraft as claimed in claim 1, wherein the damping layer II (4) is 0.57mm to 0.67mm thick and made of polymer composite material B.
7. The damping and noise-reducing composite damping plate for military aircraft according to claim 6, wherein the polymer composite material B comprises the following raw materials in parts by mass: 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 raw materials.
8. The damping and noise-reducing composite damping plate for the military aircraft as claimed in claim 1, wherein the damping layer III (5) is 1.30mm to 1.50mm thick and made of polymer composite material C.
9. The damping and noise-reducing composite damping plate for military aircraft according to claim 8, wherein 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; the polymer composite material C is prepared by mixing, heating and vulcanizing raw materials.
10. The damping and noise-reducing composite damping plate for the military aircraft as defined in 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 through a 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 the military aircraft cabin; the damping plate is applied to military aircraft, and can also be applied 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 true CN114683638A (en) 2022-07-01
CN114683638B 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)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN117227306A (en) * 2023-11-10 2023-12-15 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 (4)

* 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
US20100323194A1 (en) * 2007-02-09 2010-12-23 Yoshifumi Matsuda Vibration damper and vibration damping structure
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

Patent Citations (4)

* 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
US20100323194A1 (en) * 2007-02-09 2010-12-23 Yoshifumi Matsuda Vibration damper and vibration damping structure
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

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN117227306A (en) * 2023-11-10 2023-12-15 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
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

Also Published As

Publication number Publication date
CN114683638B (en) 2024-02-02

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
US6260660B1 (en) Aircraft cabin interior noise treatment
EP0772958B1 (en) Internally damped circuit articles
US6831876B1 (en) Acoustic window
US7467687B2 (en) Thermal—acoustic enclosure
US20030057017A1 (en) Sound-proofing panel, in particular a rotorcraft structural or lining panel
CN101486265B (en) Cumulative cutter shielding composite material for aerobus serving cabin door air emergency opening
US8127889B1 (en) Noise reduction system for structures
Tho et al. Accurate bird strike simulation methodology for BA609 tiltrotor
CN112848554A (en) High-toughness fiber-reinforced foamed aluminum gradient anti-explosion composite structure
JP2019011039A (en) Structural panels for exposed surfaces
CN219214323U (en) Vibration-damping noise-reducing composite damping plate for military aircraft
US6722611B1 (en) Reinforced aircraft skin and method
US20070284185A1 (en) Damped structural panel and method of making same
US20120040159A1 (en) Structural composite panel for an aircraft including a protection against high energy impacts
CN110001170A (en) A kind of flexible foam filled honeycomb damping-constraining sandwich and preparation method thereof
CN201333819Y (en) Strengthening aluminum honeycomb panel
Urcia et al. Structurally integrated phased arrays
May et al. Bird strike analyses on RACER fast rotocraft
CN110733436B (en) A self-adaptation damping plate for new energy automobile
EP3228536A1 (en) Composite insulation for reducing broadband aircraft noise
CN201659720U (en) Sound absorbing and insulating thermal insulating material product
Fink et al. Structurally integrated constrained layer damping for noise reduction on sandwich and semi-monocoque helicopter structures
CN210441746U (en) Wallboard of radar invisible shelter

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