CN107804046A - A kind of composite sound-deadening and noise-reducing sound lining and preparation method thereof - Google Patents

A kind of composite sound-deadening and noise-reducing sound lining and preparation method thereof Download PDF

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Publication number
CN107804046A
CN107804046A CN201710842808.8A CN201710842808A CN107804046A CN 107804046 A CN107804046 A CN 107804046A CN 201710842808 A CN201710842808 A CN 201710842808A CN 107804046 A CN107804046 A CN 107804046A
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panel
composite
solidification
sound
noise
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CN107804046B (en
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易凯
尹亮
杨智勇
尚呈元
孙建波
张毅
郭鸿俊
耿东兵
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China Academy of Launch Vehicle Technology CALT
Aerospace Research Institute of Materials and Processing Technology
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China Academy of Launch Vehicle Technology CALT
Aerospace Research Institute of Materials and Processing Technology
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    • 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
    • B32B27/00—Layered products comprising a layer of synthetic resin
    • B32B27/06—Layered products comprising a layer of synthetic resin as the main or only constituent of a layer, which is next to another layer of the same or of a different material
    • B32B27/10—Layered products comprising a layer of synthetic resin as the main or only constituent of a layer, which is next to another layer of the same or of a different material of paper or cardboard
    • 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
    • B32B27/00—Layered products comprising a layer of synthetic resin
    • B32B27/38—Layered products comprising a layer of synthetic resin comprising epoxy resins
    • 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
    • B32B3/00—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form
    • B32B3/10—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form characterised by a discontinuous layer, i.e. formed of separate pieces of material
    • B32B3/12—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form characterised by a discontinuous layer, i.e. formed of separate pieces of material characterised by a layer of regularly- arranged cells, e.g. a honeycomb structure
    • 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
    • B32B3/00—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form
    • B32B3/26—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form characterised by a particular shape of the outline of the cross-section of a continuous layer; characterised by a layer with cavities or internal voids ; characterised by an apertured layer
    • B32B3/266—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form characterised by a particular shape of the outline of the cross-section of a continuous layer; characterised by a layer with cavities or internal voids ; characterised by an apertured layer characterised by an apertured layer, the apertures going through the whole thickness of the layer, e.g. expanded metal, perforated layer, slit layer regular cells B32B3/12
    • 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
    • B32B37/00—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding
    • B32B37/06—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by the heating method
    • 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
    • B32B37/00—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding
    • B32B37/10—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by the pressing technique, e.g. using action of vacuum or fluid pressure
    • 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
    • B32B37/00—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding
    • B32B37/12—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by using adhesives
    • B32B37/1284—Application of adhesive
    • B—PERFORMING OPERATIONS; TRANSPORTING
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    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B38/00—Ancillary operations in connection with laminating processes
    • B32B38/04—Punching, slitting or perforating
    • 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
    • B32B37/00—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding
    • B32B37/12—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by using adhesives
    • B32B37/1207—Heat-activated adhesive
    • B32B2037/1215—Hot-melt adhesive
    • B32B2037/1223—Hot-melt adhesive film-shaped
    • 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
    • B32B38/00—Ancillary operations in connection with laminating processes
    • B32B2038/0052—Other operations not otherwise provided for
    • B32B2038/0076—Curing, vulcanising, cross-linking
    • 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
    • B32B38/00—Ancillary operations in connection with laminating processes
    • B32B38/04—Punching, slitting or perforating
    • B32B2038/047—Perforating
    • 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
    • B32B2260/00—Layered product comprising an impregnated, embedded, or bonded layer wherein the layer comprises an impregnation, embedding, or binder material
    • B32B2260/04—Impregnation, embedding, or binder material
    • B32B2260/046—Synthetic resin
    • 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
    • B32B2262/00—Composition or structural features of fibres which form a fibrous or filamentary layer or are present as additives
    • B32B2262/02—Synthetic macromolecular fibres
    • B32B2262/0261—Polyamide fibres
    • B32B2262/0269—Aromatic polyamide fibres
    • 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
    • B32B2262/00—Composition or structural features of fibres which form a fibrous or filamentary layer or are present as additives
    • B32B2262/10—Inorganic fibres
    • B32B2262/101—Glass fibres
    • 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
    • B32B2307/102—Insulating
    • 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
    • B32B2307/552—Fatigue strength
    • 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
    • B32B2307/558—Impact strength, toughness
    • 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
    • B32B2307/70—Other properties
    • B32B2307/718—Weight, e.g. weight per square meter
    • 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

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Soundproofing, Sound Blocking, And Sound Damping (AREA)
  • Laminated Bodies (AREA)

Abstract

The present invention relates to a kind of composite sound-deadening and noise-reducing sound lining and preparation method thereof, belong to structure/function integration technical field of composite material molding, relate generally to composite microporous panel honeycomb sandwich construction sound-deadening and noise-reducing sound lining component and its moulding technique and application, more particularly to aramid fiber and glass fiber reinforced epoxy resin matrix composite prepreg laying, the application of macromolecule acoustic membrane material, solidification of hot-press tank is molded, a large amount of micropores are processed on composite-material laminates by laser processing, Nomex aramid fibers paper honeycomb core is formed by curing a kind of microperforated panel composite sound-deadening and noise-reducing sound lining with composite material face and backboard by the way that membranaceous adhesive is Nian Jie, the sound lining can be single-degree-of-freedom sound lining structure, or multiple degrees of freedom sound lining structure, the acoustic noise reduction function of aero-engine can be realized.

Description

A kind of composite sound-deadening and noise-reducing sound lining and preparation method thereof
Technical field
The present invention relates to a kind of composite sound-deadening and noise-reducing sound lining and preparation method thereof, it is multiple to belong to structure/function integration Condensation material field shaping technique, relate generally to composite microporous panel honeycomb sandwich construction sound-deadening and noise-reducing sound lining component and its into Type process and application, and in particular to aramid fiber and glass fiber reinforced epoxy resin matrix composite prepreg laying, Solidification of hot-press tank is molded, and processes a large amount of micropores, Nomex aramid fiber paper honeycombs on composite-material laminates by laser processing Core is formed by curing a kind of microperforated panel composite sound-deadening and noise-reducing with composite material face and backboard by the way that membranaceous adhesive is Nian Jie Sound serves as a contrast, it is possible to achieve the acoustic noise reduction function of aero-engine.
Background technology
With the development of aero-engine pneumatic design technology, structure-design technique and composite technology, composite Application in big Bypass Ratio Turbofan Engine is increasingly paid attention to by each major engine manufacturer of the world and research institution, this The application of composite material component is essentially consisted in, can further improve the thrust-weight ratio and fuel efficiency of aircraft, and greatly improves hair The life-span of motivation and security reliability, while noise and noxious gas emission are reduced, increase comfortableness, economy and environment are applicable Property, meet airworthiness requirement.Composite has the high-strength lights such as the incomparable high specific strength of metal material and high specific stiffness special Property and excellent fatigue behaviour.Fan and engine weight can be mitigated using composite, improve specific stiffness, fatigability Energy, damage and defect tolerance etc., engine is the unique way for realizing higher bypass ratio and loss of weight simultaneously using advanced composite material Footpath, this also provides maximum opportunity to expand the dosage of composite on the engine.
Aircraft take off, land and flight course in along with various types of noises, noise source is numerous, frequency band distribution Extensively, it is difficult to control or even elimination comprehensively.Because the noise of aircraft is mainly derived from engine, so engine noise control is winged The key point of machine noise reduction, as long as the noise of engine effectively can be controlled and reduced, just can effectively solve making an uproar for aircraft Sound.With the application of high bypass ratio engine, jet noise has no longer been the most important noise source of aero-engine, is replaced Be fan noise.Fan noise respectively forwardly and back-propagation, and is based on Hai Muhuozi by nacelle import and pipe outlet The sound lining noise reduction technology of resonant cavity sound absorption principle is the Main Means for reducing engine blower noise.
Domestic composite sound-deadening and noise-reducing sound lining, using honeycomb sandwich construction, panel is formed porous using woven wire Structure is used for the incidence of sound source.External aero-engine engine sound lining denoising structure uses double sheets, and panel uses metal The pure titaniums of TA1, plate thickness 0.5mm.Due to sound-deadening and noise-reducing sound lining residing specific position and working environment so that sound serves as a contrast component It is easier the unsticking for panel and honeycomb core occur, or even panel chip off-falling, phenomena such as flying off.And metal decking is in shock resistance Property, resistant to chemical etching, fatigue performance etc. Shortcomings, and weight is larger, and the structure for being unfavorable for sound-deadening and noise-reducing sound lining subtracts Weight and security performance requirement.
The content of the invention
The technology of the present invention solves problem：Overcome above-mentioned the deficiencies in the prior art, there is provided a kind of composite noise reduction drop Noise lining and preparation method thereof.
The present invention technical solution be：
A kind of composite sound-deadening and noise-reducing sound lining, sound lining is composite microporous panel honeycomb sandwich construction sound-deadening and noise-reducing Sound serves as a contrast, including composite microporous panel, paper honeycomb core intermediate layer and composite backboard；Paper honeycomb core intermediate layer is positioned at compound Between material micropore panel and composite backboard；
The material of described composite microporous panel is aramid fiber reinforced composite or glass fiber compound material；It is described Composite microporous panel on carry micropore, micropore size between 0.5-2.0mm, between 4.0-8.0mm wear by pitch of holes Porosity 1-10%；Flange is carried on four sides on described composite microporous panel, parallel to two sides in course There are osculum, a diameter of 2-5mm of osculum on the flange part carried on side；
The material in described paper honeycomb core intermediate layer is Nomex aramid fiber paper honeycomb cores, density 40-55kg/m3, it is described Rhone is carried on the face that paper honeycomb core intermediate layer is connected with backboard；
The material of described composite backboard is aramid fiber reinforced composite or glass fiber compound material；
Described composite microporous panel and composite backboard are thin layer harden structure, thickness 0.5-2.0mm.
Hole of the noise along porous panel first will into sound-deadening and noise-reducing inside configuration communication process by the friction with hole wall Part energy is converted into interior energy and noise of partly decaying, and residual acoustic waves reflect and further decayed step by step in honeycomb cavity. Vibrated in addition, noise will produce different baffles through microcellular structure and when entering the cavity of interlayer honeycomb core, and both sound Barrier vibration is overlapping will to produce a kind of resonance effects together, realize resonance effects sound-deadening and noise-reducing.
In above-mentioned composite microporous panel honeycomb sandwich construction sound-deadening and noise-reducing sound lining, panel uses aramid fiber/glass Glass fiber reinforced epoxy resin based composites laminate, the backboard use aramid fiber/glass fiber reinforced epoxy resin base Composite-material laminates.
The preparation method of composite microporous panel honeycomb sandwich construction sound-deadening and noise-reducing sound lining, comprises the following steps：
The shaping of step (1) panel
Aramid Prepreg or glass fibre prepreg are subjected to laying on the shaping female mold of panel, after coating vacuum bag, Solidified in autoclave, panel is obtained after the completion of solidification；
Curing process is：Solidification temperature is 120-140 DEG C, and vacuum gauge pressure is not more than -0.097MPa, with 10 DEG C -40 DEG C/h Heating rate is heated up, solidifying pressure 0.5MPa-0.7MPa, hardening time 2h-4h；Cool afterwards, 20 DEG C -60 of rate of temperature fall DEG C/h, less than 60 DEG C are cooled to, solidification is completed；
Step (2) machine adds
The composite material face obtained to step (1) processes micropore using laser drill mode, then counter plate flange is carried out Deburring and the machining of osculum；
The sizing of step (3) honeycomb, cutting
Honeycomb is fixed on honeycomb shaper surface, honeycomb of being shaped under the conditions of 160-165 DEG C.Then will be stereotyped Honeycomb is cut according to face plate profiles line, and processes rhone in the honeycomb side Nian Jie with backboard, obtains honeycomb core.
Step (4) assembles
One is respectively coated with the bonding plane for the composite material face that step (2) obtains and the bonding plane of composite backboard Tunic shape adhesive is glued membrane, and carries out air pressure by the glued membrane at the hot-air counter plate micropore of certain temperature and flow and open Hole, honeycomb core is bonded between panel and backboard, and edge sealing is carried out using foamed glue, then positioned and solidified；Described The temperature and flow of hot-air are respectively 40-60 DEG C and 0.1m3/s。
Step (5) solidification by cement
The assembly that step (4) is completed is placed in autoclave after solidification, and is stripped and is obtained composite noise reduction drop Noise serves as a contrast.
Prepreg is aramid fiber or glass fiber reinforced epoxy resin base prepreg in described step (one), is specifically wrapped Reinforcement and resin are included, wherein reinforcement uses aramid fabric or glass fabric, and resin uses 130 DEG C of intermediate temperature settings Epoxy resin or 180 DEG C of High Temperature Curing Epoxy Resin Systems；
Micro-group hole is processed by the way of laser drill to composite material face in described step (two)；
The honeycomb used in described step (three) is Nomex aramid fiber paper honeycomb；
In the described step (4) adhesive using 130 DEG C of solidification medium temperature glued membranes, 130 DEG C of solidification high temperature glued membranes or 170 DEG C of solidification high temperature glued membranes；Foamed glue is solid using 130 DEG C of solidification medium temperature foamed glues, 130 DEG C of solidification high temperature foamed glues or 170 DEG C Change high temperature foamed glue；
Solidifying pressure is 0.2~0.3MPa in described step (five), and heating rate is 10 DEG C~40 DEG C/h, rate of temperature fall ≤20℃/h。
A kind of composite sound-deadening and noise-reducing sound lining, sound lining is composite microporous panel honeycomb sandwich construction sound-deadening and noise-reducing Sound serves as a contrast, including composite microporous panel, two layers of paper honeycomb core intermediate layer, composite microporous interlayer and backboard, sound lining from In to outer be followed successively by composite microporous panel, one layer of paper honeycomb core intermediate layer, interlayer, another layer of paper honeycomb core intermediate layer and multiple Condensation material backboard, the material of described interlayer are composite or the composite with high polymer material, described composite wood Micropore is carried on material interlayer, and high polymer material is thin-film material and pore-free；Described high polymer material is polyacrylic acid Ester or nitrile rubber film, thickness 0.2-1mm；
Preparation method, (interlayer is composite-material laminates) step are as follows：
The shaping of step (1) panel and dividing plate
Aramid Prepreg or glass fibre prepreg are subjected to laying on the shaping female mold of panel, after coating vacuum bag, Solidified in autoclave, panel is obtained after the completion of solidification；
Aramid Prepreg or glass fibre prepreg are subjected to laying on the shaping female mold of dividing plate, after coating vacuum bag, Solidified in autoclave, dividing plate is obtained after the completion of solidification；
Curing process is：Solidification temperature is 120-140 DEG C, and vacuum gauge pressure is not more than -0.097MPa, with 10 DEG C -40 DEG C/h Heating rate is heated up, solidifying pressure 0.5MPa-0.7MPa, hardening time 2h-4h；Cool afterwards, 20 DEG C -60 of rate of temperature fall DEG C/h, less than 60 DEG C are cooled to, solidification is completed；
Step (2) machine adds
The composite material face and dividing plate obtained to step (1) processes micropore using laser drill mode, then counter plate turns over Side carries out the machining of deburring and osculum；
The sizing of step (3) honeycomb, cutting
Two pieces of honeycombs are individually fixed in honeycomb shaper surface, honeycomb of being shaped under the conditions of 160-165 DEG C.Then will Stereotyped honeycomb is cut according to face plate profiles line, and processes rhone in the honeycomb side Nian Jie with backboard, obtains honeybee Nest core.
Step (4) assembles
It is each on the composite material face and the bonding plane of dividing plate and the bonding plane of composite backboard obtained in step (2) A tunic shape adhesive i.e. glued membrane is coated with, and a tunic shape adhesive is respectively coated with the upper and lower surface of interlayer, and is passed through Glued membrane at the hot-air counter plate and dividing plate micropore of certain temperature and flow carries out air pressure perforate, is glued between panel and interlayer Honeycomb core is tied, and bonds honeycomb core between interlayer and backboard and edge sealing is carried out using foamed glue, is then positioned and is solidified； The temperature and flow of described hot-air are respectively 40-60 DEG C and 0.1m3/s。
Step (5) solidification by cement
The assembly that step (4) is completed is placed in autoclave after solidification, and is stripped and is obtained composite noise reduction drop Noise serves as a contrast.
Preparation method (interlayer is the composite-material laminates with macromolecule material film), step is as follows：
The shaping of step (1) panel and dividing plate
Aramid Prepreg or glass fibre prepreg are subjected to laying on the shaping female mold of panel, after coating vacuum bag, Solidified in autoclave, panel is obtained after the completion of solidification；
Aramid Prepreg or glass fibre prepreg are subjected to laying on the shaping female mold of dividing plate, after coating vacuum bag, Solidified in autoclave, dividing plate is obtained after the completion of solidification；
Curing process is：Solidification temperature is 120-140 DEG C, and vacuum gauge pressure is not more than -0.097MPa, with 10 DEG C -40 DEG C/h Heating rate is heated up, solidifying pressure 0.5MPa-0.7MPa, hardening time 2h-4h；Cool afterwards, 20 DEG C -60 of rate of temperature fall DEG C/h, less than 60 DEG C are cooled to, solidification is completed；
Step (2) machine adds
The composite material face and dividing plate obtained to step (1) processes micropore using laser drill mode, then counter plate turns over Side carries out the machining of deburring and osculum；
The sizing of step (3) honeycomb, cutting
Two pieces of honeycombs are individually fixed in honeycomb shaper surface, honeycomb of being shaped under the conditions of 160-165 DEG C.Then will Stereotyped honeycomb is cut according to face plate profiles line, and processes rhone in the honeycomb side Nian Jie with backboard, obtains honeybee Nest core.
Step (4) assembles
One is respectively coated with the bonding plane for the composite material face that step (2) obtains and the bonding plane of composite backboard Tunic shape adhesive is glued membrane, is respectively coated with one layer of glued membrane in the two pieces honeycomb core side Nian Jie with dividing plate, and pass through certain temperature It is and the glued membrane at the glued membrane and honeycomb core at the hot-air counter plate micropore of flow carries out air pressure perforate, high polymer material is thin Film is coated with interlayer composite material surface, and honeycomb core is bonded between panel and interlayer, is entered at honeycomb core edge using foamed glue Row edge sealing, is then positioned and is solidified；The temperature and flow of described hot-air are respectively 40-60 DEG C and 0.1m3/s。
Step (5) solidification by cement
The assembly that step (4) is completed is placed in autoclave after solidification, and is stripped and is obtained composite noise reduction drop Noise serves as a contrast.
The present invention has the advantages that compared with prior art：
(1) present invention has carried out innovative design to the structure type of noise reduction noise-reducing acoustic liner, material technology etc., and adopts With full composite material panel/honeycomb sandwich construction scheme, structure loss of weight is effectively realized；
(2) composite material face that the present invention uses not only has higher specific strength, specific stiffness and low thermal conductivity, and And substantial amounts of acoustics microcellular structure can be devised in composite-material laminates, is made it have according to engine power, noise spectrum Excellent sound insulation acoustic resistive is shaken, shock resistance；
(3) present invention devises interlayer in sandwich sound-deadening and noise-reducing sound lining, and in the composite micropunch of interlayer Have noise reducing damping macromolecule material film on plate, make it have broader noise reduction frequency band, more excellent noise reduction；
(4) substantial amounts of acoustics microcellular structure is distributed with the composite material face that the present invention uses, and is the side by laser machining Formula processing is prepared；
(5) sandwich structure piece core of the present invention has light weight, shock resistance, sound-absorbing, sound insulation using Nomex aramid fiber honeycomb cores The excellent specific properties such as performance is good, with microcellular structure aramid fiber reinforced composite panel cooperative achievement sound-deadening and noise-reducing function；
(6) present invention employs the shaping work of heat air method in the preparation technology for preparing sandwich sound-deadening and noise-reducing sound lining Skill technology, reduce the percentage of plugged hole of the microperforated panel of the sandwich after bonding solidification；
(7) composite microporous panel honeycomb sandwich construction sound-deadening and noise-reducing sound lining disappearing available for aero-engine of the present invention Sound noise reduction, the sound lining structure of preparation is in light weight, can effectively absorb/reduce noise, excellent combination property.
(8) sound of the invention lining serves as a contrast for a kind of composite microporous panel honeycomb interlayer sound-deadening and noise-reducing sound, has structure weight Amount is light, anti-fatigue performance is excellent, structure can be designed so as to widen noise reduction frequency band and the characteristics of improve noise reduction.Wherein, five layers The composite sound-deadening and noise-reducing sound lining of structure, can have a variety of macromolecules wherein on the composite microporous plate of wall and damp Noise reduction film, it can further improve noise reduction.Turbofan aerial engine fan casing sound attenuation features are can be applied to, and can be expired The active demand of sufficient airliner or transporter turbofan aero-engine sound-deadening and noise-reducing sound lining.
(9) the invention provides a kind of composite sound-deadening and noise-reducing sound lining and its technology of preparing, it is related to composite sound lining Structure design, sound lining structure material and moulding technique field；The present invention passes through aramid fiber or glass fiber reinforcement epoxy Prepared by polymer matrix composites panel, dividing plate, backboard shaping, in panel and dividing plate by way of laser boring or machining Upper processing diameter 0.5-2.0mm micropore, sandwich layer Nomex aramid fiber paper honeycomb core layer thermal finalizations, has damping noise-reducing on dividing plate Macromolecule material film, panel, intermediate course, dividing plate and backboard are bonded using membranaceous adhesive, turn into sound-deadening and noise-reducing sound lining Structural member.Composite sound-deadening and noise-reducing sound lining has wider sound sucting band and preferable sound-deadening and noise-reducing effect.The present invention Overcome that existing metal noise-reducing acoustic liner weight is big, the deficiency of poor fatigue properties, it is compound to solve aramid fiber using laser boring The technical barrier of material panel machining drilling precision difference, has damping noise-reducing high polymer material using sandwich construction and interlayer The method of film, aramid fiber/glass fiber compound material micropore panel honeycomb sandwich construction sound-deadening and noise-reducing sound lining tool of preparation There are superior weatherability and damping noise-reducing performance, preparation method simple possible.
Brief description of the drawings
Fig. 1 is the three-decker schematic diagram of the sound lining of the present invention；
Fig. 2 is the five-layer structure schematic diagram of the sound lining of the present invention.
Embodiment
A kind of composite sound-deadening and noise-reducing sound lining：Sound-deadening and noise-reducing sound lining is prepared using composite, its panel is high-performance Aramid fiber reinforced epoxy based composites micropore panel or glass fiber reinforced epoxy resin based composites micropore face Plate, intermediate course are Nomex aramid fiber paper honeycomb cores, and backboard is high-performance aramid fiber reinforced epoxy based composites rigidity Backboard or glass fiber reinforced epoxy resin based composites rigid back, by membranaceous adhesive by panel, intermediate course and Backboard bonding solidification forms.Its sqouynd absorption lowering noise method is that noise is serving as a contrast denoising structure internal communication along the hole of porous panel to sound During, part energy is first converted into by interior energy by the friction with hole wall and decayed and part, residual acoustic waves are in honeycomb cavity In reflect and further decay step by step.Sound-deadening and noise-reducing of the sound lining available for turbofan aero-engine.
The composite material face of sound lining uses the thick laminates of 1.0-2.0mm, and the micropore size being distributed on laminate is in 0.5- Between 2.0mm, pitch of holes is between 4.0-8.0mm, punching rate 1-10%；Described intermediate course uses Nomex aramid fiber paper wasps Nest core, height 10.0-30.0mm, density is in 40-55kg/m3, honeycomb core cell length of side 1.5-2.0mm；The backboard of sound lining uses Laminate prepared by aramid fiber/glass fiber reinforced epoxy resin based composites, thickness 0.5-2.0mm.
The sound lining structure is flat board external form or cambered surface external form, and panel and comb core can be as needed according to certain radians It is prepared by shaping.
The installation of sound-deadening and noise-reducing sound lining has directionality, and noise source must enter via the micropore of the composite material face Sandwich cavity.
Sound-deadening and noise-reducing sound lining can be served as a contrast by more than one piece sound-deadening and noise-reducing sound and be assembled into complete circular sound-deadening and noise-reducing sound lining structure group Part.
Technology of preparing is as follows：
The shaping of step (1) panel
Aramid fiber or glass prepreg are subjected to laying on shaping mould, after coating vacuum bag, solidified in autoclave, Curing process is：Vacuum gauge pressure is not more than -0.097MPa, is heated up with 10 DEG C -40 DEG C/h heating rates, solidifying pressure 0.5MPa-0.7MPa, hardening time 2h-4h；Cool afterwards, 20 DEG C -60 DEG C/h of rate of temperature fall, be cooled to less than 60 DEG C, solidification Complete；
Step (2) machine adds
Micropore is processed using laser drill mode to composite material face.
The sizing of step (3) honeycomb, cutting
Honeycomb is fixed on honeycomb shaper surface, honeycomb of being shaped under the conditions of 160-165 DEG C.Then will be stereotyped Honeycomb is cut according to face plate profiles line.
Step (4) assembles
In composite material face and honeycomb core bonding plane and composite backboard a tunic shape is coated with honeycomb core bonding plane Adhesive, and being positioned by assembling positioning tool, counter plate and backboard carry out be bonded with cellular abutting edge, and use foamed glue To being filled in the range of sound lining structure periphery 1-2cm.
Step (5) solidification by cement
The sound lining that step (4) is completed is positioned in autoclave and solidified, composite microporous panel is obtained after the demoulding Honeycomb sandwich construction sound-deadening and noise-reducing sound serves as a contrast.
Glued membrane is using 130 DEG C of intermediate temperature setting glued membranes or 170 DEG C of solidification high temperature glued membranes in the step (4).
Solidification by cement pressure is 0.2~0.3MPa in the step (5), and heating rate is 10 DEG C~40 DEG C/h, solidification temperature Spend for 130 DEG C or 170 DEG C, soaking time 2-3h, rate of temperature fall≤20 DEG C/h.
Prepreg is aramid fiber/glass fiber reinforced epoxy resin base prepreg in the step (1), is specifically included Reinforcement and resin, wherein reinforcement use aramid fabric/glass fabric, and resin uses 130 DEG C of intermediate temperature setting rings Oxygen tree fat or 180 DEG C of High Temperature Curing Epoxy Resin Systems.
Composite microporous panel honeycomb sandwich construction sound-deadening and noise-reducing sound serves as a contrast and its component can be applied to airliner or fortune Defeated machine turbofan aero-engine sound-deadening and noise-reducing structure.
The present invention is described in further detail with specific embodiment below in conjunction with the accompanying drawings：
Embodiment 1
As shown in figure 1, the sound lining bag includes micropore panel, honeycomb core and backboard；Described honeycomb core be located at micropore panel and Between backboard；
Panel and backboard use aramid fabric intermediate temperature setting epoxy resin sweat connecting material, and glued membrane is used in 130 DEG C Warm solidified glue film.
Required using automatic blanking machine according to laying and size after carrying out blanking, by design laying angle by multilayer prepreg Successively it is laid on the shaping female mold of panel and backboard, material prepreg lamination is made, then using vacuum bag/autoclave Molding mode is solidified, and during solidification, vacuum gauge pressure is not more than -0.097MPa, 30 DEG C/h of heating rate, and temperature rises to 130 DEG C When be forced into 0.6MPa, be incubated the follow-up temperature of continuing rising of 30min, when being warming up to 130 ± 5 DEG C, be incubated 4h, then cooled speed with 40 DEG C/h Rate is cooled to less than 60 DEG C solidifications and completed, and is down to the demoulding after room temperature and obtains panel and backboard, nothing after being repaired to product flash Damage detection is stand-by.
A diameter of 2.0mm micropore, punching rate 5% are processed to composite material face by the way of Laser Processing.
The high 20mm of core, honeycomb specification are used as 40g/m3Nomex honeycombs according to outer panels shaper surface, 165 Shaped under the conditions of DEG C honeycomb.Then stereotyped honeycomb is cut according to outer panels contour line, bonded at it with backboard Rhone is processed on face.
The qualified panel of Non-Destructive Testing, backboard are placed on assembling curing mold, the face finishing of carry out type, are trimmed to needs Appearance and size, and intermediate temperature setting glued membrane is pasted after polishing cleaning is carried out to its bonding plane, then in Nomex honeycombs above and below Intermediate temperature setting glued membrane is integrally pasted in type face, and is 40 DEG C by temperature and flow is 0.1m3At/s hot-air counter plate micropore Glued membrane carry out air pressure perforate, between panel and backboard bond honeycomb core, and using foamed glue carry out edge sealing.
After panel, honeycomb core and backboard are completed, product is coated, and vacuumizes compacting, vacuum pressure No more than -0.097MPa, time 3h is compacted, after compacting, removes covering material, and appropriate chi is carried out according to type face laminating degree Very little finishing, product surface is assembled in after finishing.
The sandwich structure piece to be solidified assembled is placed in heat-pressure curing in autoclave, solidifying pressure 0.3MPa, Solidification temperature is 130 DEG C, solidifies 2~4h of soaking time, and heating rate is 25 DEG C~35 DEG C/h, rate of temperature fall≤15 DEG C/h, is dropped Temperature to less than 60 DEG C, complete by solidification.
Temperature can be stripped after being down to room temperature, and excessive glue cleaning is carried out to product after the demoulding, and carry out Non-Destructive Testing, be detected After qualified, mechanical tapping is carried out to the micropore that glued membrane excessive glue blocks, end article is obtained after cleaning.
By the sound prepared lining in a circumferential direction on the casing inwall of about 1~2 meter of diameter, and rung by alliteration Room test system and test do not install sound lining and installation sound lining after sound transmission loss difference, obtain composite sound-deadening and noise-reducing sound The noise abatement of lining.Measured, the acoustic noise reduction of embodiment 1 is horizontal up to 5dB.
Embodiment 2
Panel and backboard use glass fabric intermediate temperature setting sweat connecting material, and glued membrane uses 130 DEG C of intermediate-temperature glues Film.
Required using automatic blanking machine according to laying and size after carrying out blanking, by design laying angle by multilayer prepreg Successively it is laid on mould, material prepreg lamination is made, is then carried out using vacuum bag/autoclave molding mode Solidification, during solidification, vacuum gauge pressure is not more than -0.097MPa, 20 DEG C -40 DEG C/h of heating rate, and temperature is forced into when rising to 130 DEG C 0.6MPa, the follow-up temperature of continuing rising of 30min is incubated, when being warming up to 130 ± 5 DEG C, 4h is incubated, then with 30 DEG C -50 DEG C/h rate of temperature fall It is cooled to less than 60 DEG C solidifications to complete, is down to the demoulding after room temperature and obtains panel and backboard, it is lossless after being repaired to product flash Detect stand-by.
A diameter of 2.0mm micropore, punching rate 5% are processed to composite material face by the way of Laser Processing.
The high 20mm of core, honeycomb specification are used as 40g/m3Nomex honeycombs according to outer panels shaper surface, in 160- Shaped under the conditions of 165 DEG C honeycomb.Then stereotyped honeycomb is cut according to outer panels contour line.
The qualified outer panels of Non-Destructive Testing, backboard are placed on assembling curing mold, the face finishing of carry out type, are trimmed to needs Appearance and size, and its bonding plane is carried out to paste intermediate temperature setting glued membrane after polishing cleaning, then on Nomex honeycombs and under Intermediate temperature setting glued membrane is integrally pasted in face type face, and is 40 DEG C by temperature and flow is 0.1m3/ s hot-air counter plate micropore The glued membrane at place carries out air pressure perforate, honeycomb core is bonded between panel and backboard, and carry out edge sealing using foamed glue.
After panel, honeycomb core and backboard are completed, product is coated, and vacuumizes compacting, vacuum pressure No more than -0.097MPa, time 3h is compacted, after compacting, removes covering material, and appropriate chi is carried out according to type face laminating degree Very little finishing, product surface is assembled in after finishing.
The sandwich structure piece to be solidified assembled is placed in heat-pressure curing in autoclave, solidifying pressure 0.3MPa, Solidification temperature is 130 DEG C, solidifies 2~4h of soaking time, and heating rate is 25 DEG C~35 DEG C/h, rate of temperature fall≤15 DEG C/h, is dropped Temperature to less than 60 DEG C, complete by solidification.
Temperature can be stripped after being down to room temperature, and excessive glue cleaning is carried out to product after the demoulding, and carry out Non-Destructive Testing, be detected After qualified, mechanical tapping is carried out to the micropore that glued membrane excessive glue blocks, end article is obtained after cleaning.
By the sound prepared lining in a circumferential direction on the casing inwall of 1~2 meter of diameter, and room is rung by alliteration Test system and test does not install the difference of the sound transmission loss after sound lining and installation sound lining, obtains composite sound-deadening and noise-reducing sound lining Noise abatement.Measured, the acoustic noise reduction of embodiment 2 is horizontal up to 5dB.
Embodiment 3
Panel and backboard use aramid fabric hot setting sweat connecting material, and glued membrane uses 180 DEG C of high temperature setting glues Film.
Required using automatic blanking machine according to laying and size after carrying out blanking, by design laying angle by multilayer prepreg Successively it is laid on mould, material prepreg lamination is made, is then carried out using vacuum bag/autoclave molding mode Solidification, during solidification, vacuum gauge pressure is not more than -0.097MPa, 20 DEG C -40 DEG C/h of heating rate, and temperature is forced into when rising to 180 DEG C 0.6MPa, the follow-up temperature of continuing rising of 30min is incubated, when being warming up to 180 ± 5 DEG C, 4h is incubated, then with 30 DEG C -50 DEG C/h rate of temperature fall It is cooled to less than 60 DEG C solidifications to complete, is down to the demoulding after room temperature and obtains panel and backboard, it is lossless after being repaired to product flash Detect stand-by.
A diameter of 2.0mm micropore, punching rate 5% are processed to composite material face by the way of Laser Processing.
The high 20mm of core, honeycomb specification are used as 40g/m3Nomex honeycombs according to outer panels shaper surface, in 160- Shaped under the conditions of 165 DEG C honeycomb.Then stereotyped honeycomb is cut according to outer panels contour line.
The qualified outer panels of Non-Destructive Testing, backboard are placed on assembling curing mold, the face finishing of carry out type, are trimmed to needs Appearance and size, and its bonding plane is carried out to paste hot setting glued membrane after polishing cleaning, then on Nomex honeycombs and under Hot setting glued membrane is integrally pasted in face type face, and is 40 DEG C by temperature and flow is 0.1m3/ s hot-air counter plate micropore The glued membrane at place carries out air pressure perforate, honeycomb core is bonded between panel and backboard, and carry out edge sealing using foamed glue.
After panel, honeycomb core and backboard are completed, product is coated, and vacuumizes compacting, vacuum pressure No more than -0.097MPa, time 3h is compacted, after compacting, removes covering material, and appropriate chi is carried out according to type face laminating degree Very little finishing, product surface is assembled in after finishing.
The sandwich structure piece to be solidified assembled is placed in heat-pressure curing in autoclave, solidifying pressure 0.2MPa, Solidification temperature is 180 DEG C, solidifies 2~4h of soaking time, and heating rate is 25 DEG C~35 DEG C/h, rate of temperature fall≤15 DEG C/h, is dropped Temperature to less than 60 DEG C, complete by solidification.
Temperature can be stripped after being down to room temperature, and excessive glue cleaning is carried out to product after the demoulding, and carry out Non-Destructive Testing, be detected After qualified, mechanical tapping is carried out to the micropore that glued membrane excessive glue blocks, end article is obtained after cleaning.
By the sound prepared lining in a circumferential direction on the casing inwall of about 1~2 meter of diameter, and rung by alliteration Room test system and test do not install sound lining and installation sound lining after sound transmission loss difference, obtain composite sound-deadening and noise-reducing sound The noise abatement of lining.Measured, the acoustic noise reduction of embodiment 3 is horizontal up to 5dB.
Embodiment 4
As shown in Fig. 2 the sound lining bag includes micropore panel, two layers of honeycomb core, interlayer and backboard, wherein one layer of honeycomb core is located at Between micropore panel and interlayer, another layer of honeycomb core is between interlayer and backboard；
Panel, backboard and interlayer use aramid fabric intermediate temperature setting epoxy resin sweat connecting material, and glued membrane uses 130 DEG C intermediate temperature setting glued membrane.
Required using automatic blanking machine according to laying and size after carrying out blanking, by design laying angle by multilayer prepreg Successively be laid on the shaping female mold of panel, backboard and dividing plate, material prepreg lamination be made, then using vacuum bag/ Autoclave molding mode is solidified, and during solidification, vacuum gauge pressure is not more than -0.097MPa, 30 DEG C/h of heating rate, and temperature rises to 0.6MPa is forced at 130 DEG C, is incubated the follow-up temperature of continuing rising of 30min, when being warming up to 130 ± 5 DEG C, 4h is incubated, then with 40 DEG C/h Rate of temperature fall is cooled to less than 60 DEG C solidifications and completed, and is down to the demoulding after room temperature and obtains panel, backboard and dividing plate, product flash is entered Non-Destructive Testing is stand-by after row finishing.
To processing a diameter of 2.0mm micropore, punching rate on composite material face and dividing plate by the way of Laser Processing 5%.
The high 20mm of core, honeycomb specification are used as 40g/m3Nomex honeycombs according to outer panels shaper surface, 165 Shaped under the conditions of DEG C honeycomb.Then stereotyped honeycomb is cut according to outer panels contour line, bonded at it with backboard Rhone is processed on face.
The qualified panel of Non-Destructive Testing, backboard and dividing plate are placed on assembling curing mold, the face finishing of carry out type, are trimmed to The appearance and size needed, and the bonding plane of counter plate and backboard carries out stickup intermediate temperature setting glued membrane after polishing cleaning, including subsequent, One layer of intermediate temperature setting glued membrane of each paving in the outer Nomex honeycombs side Nian Jie with dividing plate, and be 40 DEG C by temperature and flow is 0.1m3Glued membrane at/s hot-air counter plate micropore and at honeycomb carries out air pressure perforate, is glued between panel, backboard and dividing plate Honeycomb core is tied, and edge sealing is carried out using foamed glue.
After panel, inside and outside honeycomb core, dividing plate and backboard are completed, product is coated, and vacuumizes compacting, Vacuum pressure is not more than -0.097MPa, is compacted time 3h, after compacting, removes covering material, and carry out according to type face laminating degree Appropriate size finishing, product surface is assembled in after finishing.
The sandwich structure piece to be solidified assembled is placed in heat-pressure curing in autoclave, solidifying pressure 0.3MPa, Solidification temperature is 130 DEG C, solidifies 2~4h of soaking time, and heating rate is 25 DEG C~35 DEG C/h, rate of temperature fall≤15 DEG C/h, is dropped Temperature to less than 60 DEG C, complete by solidification.
Temperature can be stripped after being down to room temperature, and excessive glue cleaning is carried out to product after the demoulding, and carry out Non-Destructive Testing, be detected After qualified, mechanical tapping is carried out to the micropore that glued membrane excessive glue blocks, end article is obtained after cleaning.
By the sound prepared lining in a circumferential direction on the casing inwall of 1~2 meter of diameter, and room is rung by alliteration Test system and test does not install the difference of the sound transmission loss after sound lining and installation sound lining, obtains composite sound-deadening and noise-reducing sound lining Noise abatement.Measured, the acoustic noise reduction of embodiment 4 is horizontal up to 5.5dB.
Embodiment 5
As shown in Fig. 2 panel, backboard and interlayer use aramid fabric intermediate temperature setting epoxy resin sweat connecting material, Glued membrane uses 130 DEG C of intermediate temperature setting glued membranes, has polyacrylate macromolecule material film on interlayer.
Required using automatic blanking machine according to laying and size after carrying out blanking, by design laying angle by multilayer prepreg Successively be laid on the shaping female mold of panel, backboard and dividing plate, material prepreg lamination be made, then using vacuum bag/ Autoclave molding mode is solidified, and during solidification, vacuum gauge pressure is not more than -0.097MPa, 30 DEG C/h of heating rate, and temperature rises to 0.6MPa is forced at 130 DEG C, is incubated the follow-up temperature of continuing rising of 30min, when being warming up to 130 ± 5 DEG C, 4h is incubated, then with 40 DEG C/h Rate of temperature fall is cooled to less than 60 DEG C solidifications and completed, and is down to the demoulding after room temperature and obtains panel, backboard and dividing plate, product flash is entered Non-Destructive Testing is stand-by after row finishing.
To processing a diameter of 2.0mm micropore, punching rate on composite material face and dividing plate by the way of Laser Processing 5%.
The high 20mm of core, honeycomb specification are used as 40g/m3Nomex honeycombs according to outer panels shaper surface, 165 Shaped under the conditions of DEG C honeycomb.Then stereotyped honeycomb is cut according to outer panels contour line, bonded at it with backboard Rhone is processed on face.
The qualified panel of Non-Destructive Testing, backboard and dividing plate are placed on assembling curing mold, the face finishing of carry out type, are trimmed to The appearance and size needed, and the bonding plane of counter plate and backboard carries out stickup intermediate temperature setting glued membrane after polishing cleaning, including subsequent, One layer of intermediate temperature setting glued membrane of each paving in the outer Nomex honeycombs side Nian Jie with dividing plate, and be 40 DEG C by temperature and flow is 0.1m3Glued membrane at/s hot-air counter plate micropore and at honeycomb carries out air pressure perforate, and a strata third is laid in dividing plate side Olefin(e) acid ester macromolecule material film, honeycomb core is bonded between panel, backboard and dividing plate, and edge sealing is carried out using foamed glue.
After panel, inside and outside honeycomb core, the dividing plate with macromolecule material film and backboard are completed, product is entered Row cladding, and compacting is vacuumized, vacuum pressure is not more than -0.097MPa, is compacted time 3h, after compacting, removes covering material, and Appropriate size is carried out according to type face laminating degree to repair, and product surface is assembled in after finishing.
The sandwich structure piece to be solidified assembled is placed in heat-pressure curing in autoclave, solidifying pressure 0.3MPa, Solidification temperature is 130 DEG C, solidifies 2~4h of soaking time, and heating rate is 25 DEG C~35 DEG C/h, rate of temperature fall≤15 DEG C/h, is dropped Temperature to less than 60 DEG C, complete by solidification.
Temperature can be stripped after being down to room temperature, and excessive glue cleaning is carried out to product after the demoulding, and carry out Non-Destructive Testing, be detected After qualified, mechanical tapping is carried out to the micropore that glued membrane excessive glue blocks, end article is obtained after cleaning.
By the sound prepared lining in a circumferential direction on the casing inwall of 1~2 meter of diameter, and room is rung by alliteration Test system and test does not install the difference of the sound transmission loss after sound lining and installation sound lining, obtains composite sound-deadening and noise-reducing sound lining Noise abatement.Measured, the acoustic noise reduction of embodiment 5 is horizontal up to 6dB.
It is described above, it is only the optimal embodiment of the present invention, but protection scope of the present invention is not limited thereto, Any one skilled in the art the invention discloses technical scope in, the change or replacement that can readily occur in, It should all be included within the scope of the present invention.
The content not being described in detail in description of the invention belongs to the known technology of professional and technical personnel in the field.

Claims (15)

  1. A kind of 1. composite sound-deadening and noise-reducing sound lining, it is characterised in that：The sound lining bag includes micropore panel, honeycomb core and backboard；Institute The honeycomb core stated is between micropore panel and backboard；
    The material of described micropore panel is aramid fiber reinforced epoxy based composites or glass fiber reinforced epoxy Resin-based composite；
    Micropore is carried on described micropore panel；
    The material of described backboard is aramid fiber reinforced epoxy based composites or glass fiber reinforced epoxy resin base Composite.
  2. A kind of 2. composite sound-deadening and noise-reducing sound lining according to claim 1, it is characterised in that：On described micropore panel Micropore size be 0.5-2.0mm, pitch of holes 4.0-8.0mm, punching rate 1%-10%.
  3. A kind of 3. composite sound-deadening and noise-reducing sound lining according to claim 1, it is characterised in that：Described micropore panel Flange is carried on four sides, parallel to having osculum on the flange part carried on two sides in course, osculum A diameter of 2-5mm.
  4. A kind of 4. composite sound-deadening and noise-reducing sound lining according to claim 1, it is characterised in that：The material of described honeycomb core Expect for Nomex aramid fiber paper honeycomb cores, density 40-55kg/m3, draining is carried on the face that described honeycomb core is connected with backboard Groove.
  5. A kind of 5. composite sound-deadening and noise-reducing sound lining according to claim 1, it is characterised in that：Described micropore panel and Backboard is thin layer harden structure, thickness 0.5-2.0mm, and panel is compound using aramid fiber/glass fiber reinforced epoxy resin base Material laminate, backboard use aramid fiber/glass fiber reinforced epoxy resin based composites laminate.
  6. A kind of 6. preparation method of any described composite sound-deadening and noise-reducing sound linings of claim 1-5, it is characterised in that：Including Following steps：
    The shaping of step (1) panel
    Aramid Prepreg or glass fibre prepreg are subjected to laying on the shaping female mold of panel, after coating vacuum bag, in heat Solidified in pressure tank, panel is obtained after the completion of solidification；
    Step (2) machine adds
    The panel processing micropore obtained to step (1), then counter plate flange carry out the machining of deburring and osculum；
    The sizing of step (3) honeycomb, cutting
    Honeycomb is shaped under the conditions of 160-165 DEG C, then cut stereotyped honeycomb according to face plate profiles line, And rhone is processed in the honeycomb side Nian Jie with backboard, obtain honeycomb core；
    Step (4) assembles
    One layer of glued membrane is respectively coated with the bonding plane for the panel that step (2) obtains and the bonding plane of backboard, then passes through hot-air Glued membrane at counter plate micropore carries out air pressure perforate, the honeybee that between panel and backboard prepared by adhesion step (3) after the completion of perforate Nest core, and edge sealing is carried out using foamed glue, then positioned and solidified, obtain assembly；The temperature of described hot-air is 40-60 DEG C, flow 0.08-0.12m3/s；
    Step (5) solidification by cement
    The assembly that step (4) is completed is placed in autoclave after solidification, and the demoulding obtains composite sound-deadening and noise-reducing sound Lining.
  7. A kind of 7. preparation method of composite sound-deadening and noise-reducing sound lining according to claim 6, it is characterised in that：Described In step (1), curing process is：Solidification temperature is 120-140 DEG C, and vacuum gauge pressure is not more than -0.097MPa, with 10 DEG C -40 DEG C/h heating rates are heated up, solidifying pressure 0.5MPa-0.7MPa, hardening time 2h-4h；Cool afterwards, rate of temperature fall 20 DEG C -60 DEG C/h, less than 60 DEG C are cooled to, solidification is completed；
    Prepreg is aramid fiber or glass fiber reinforced epoxy resin base prepreg in described step (one), specifically includes increasing Strong body and resin, wherein reinforcement use aramid fabric or glass fabric, and resin uses 130 DEG C of intermediate temperature setting epoxies Resin or 180 DEG C of High Temperature Curing Epoxy Resin Systems.
  8. A kind of 8. preparation method of composite sound-deadening and noise-reducing sound lining according to claim 6, it is characterised in that：Described In step (2), micropore is processed by the way of laser drill to composite material face；The honeybee used in described step (three) Nest is Nomex aramid fiber paper honeycombs；Glued membrane is high using 130 DEG C of solidification medium temperature glued membranes, 130 DEG C of solidifications in the described step (4) Warm glued membrane or 170 DEG C of solidification high temperature glued membranes；Foamed glue using 130 DEG C of solidification medium temperature foamed glues, 130 DEG C of solidification high temperature foamed glues or 170 DEG C of solidification high temperature foamed glues；Solidifying pressure is 0.2~0.3MPa in described step (five), and heating rate is 10 DEG C~40 DEG C/h, rate of temperature fall≤20 DEG C/h.
  9. A kind of 9. composite sound-deadening and noise-reducing sound lining, it is characterised in that：The sound lining bag includes micropore panel, two layers of honeycomb core, interlayer And backboard, wherein one layer of honeycomb core, between micropore panel and interlayer, another layer of honeycomb core is between interlayer and backboard；
    The material of described micropore panel is aramid fiber reinforced composite or glass fiber compound material；
    Micropore is carried on described micropore panel；
    The material of described backboard is aramid fiber reinforced composite or glass fiber compound material；
    Described interlayer is composite-material laminates.
  10. A kind of 10. composite sound-deadening and noise-reducing sound lining according to claim 9, it is characterised in that：Described interlayer also wraps The macromolecule material film above composite-material laminates is included, micropore is carried on composite-material laminates；Described macromolecule material Expect that for polyacrylate or nitrile rubber, the thickness of macromolecule material film is 0.2-1mm.
  11. 11. served as a contrast according to a kind of any described composite sound-deadening and noise-reducing sound of claim 9-10, it is characterised in that：Described is micro- Micropore size on hole face plate is 0.5-2.0mm, pitch of holes 4.0-8.0mm, punching rate 1%-10%；
    Flange is carried on four sides of described micropore panel, parallel to the flange part carried on two sides in course On have osculum, a diameter of 2-5mm of osculum；
    The material of described honeycomb core is Nomex aramid fiber paper honeycomb cores, density 40-55kg/m3, described honeycomb core and backboard Rhone is carried on the face of connection；
    Described micropore panel and backboard are thin layer harden structure, thickness 0.5-2.0mm, and panel uses aramid fiber/glass fibers Reinforced epoxy based composites laminate is tieed up, backboard uses aramid fiber/glass fiber reinforced epoxy resin based composites Laminate.
  12. 12. the preparation method of the composite sound-deadening and noise-reducing sound lining described in a kind of claim 9, it is characterised in that including following step Suddenly：
    The shaping of step (1) micropore panel and dividing plate
    Aramid Prepreg or glass fibre prepreg are subjected to laying on the shaping female mold of panel, after coating vacuum bag, in heat Solidified in pressure tank, panel is obtained after the completion of solidification；
    Aramid Prepreg or glass fibre prepreg are subjected to laying on the shaping female mold of dividing plate, after coating vacuum bag, in heat Solidified in pressure tank, dividing plate is obtained after the completion of solidification；
    Step (2) machine adds
    Panel and dividing plate the processing micropore obtained to step (1), then counter plate flange carries out deburring and the machinery of osculum adds Work；
    The sizing of step (3) honeycomb, cutting
    Two pieces of honeycombs are shaped under the conditions of 160-165 DEG C respectively, then by stereotyped honeycomb according to face plate profiles line Cut, and rhone is processed in the honeycomb side Nian Jie with backboard, obtain two pieces of honeycomb cores；
    Step (4) assembles
    One layer of glued membrane is respectively coated with the panel and the bonding plane of dividing plate and the bonding plane of backboard obtained in step (2), and in interlayer Upper and lower surface be respectively coated with one layer of glued membrane, promoting the circulation of qi is then entered by the glued membrane at the micropore of hot-air counter plate and dividing plate Hole is pressed off, one piece of honeycomb core is bonded between panel and interlayer, another piece of honeycomb core is bonded between interlayer and backboard, then simultaneously Edge sealing, positioning are carried out using foamed glue and solidified, obtains assembly；The temperature of described hot-air is 40-60 DEG C, hot-air Flow is 0.08-0.12m3/s；
    Step (5) solidification by cement
    The assembly that step (4) is completed is placed in autoclave after solidification, and is stripped and is obtained composite sound-deadening and noise-reducing sound Lining.
  13. A kind of 13. preparation method of composite sound-deadening and noise-reducing sound lining according to claim 12, it is characterised in that：It is described The step of (one) in, curing process is：Solidification temperature is 120-140 DEG C, and vacuum gauge pressure is not more than -0.097MPa, with 10 DEG C -40 DEG C/h heating rates are heated up, solidifying pressure 0.5MPa-0.7MPa, hardening time 2h-4h；Cool afterwards, rate of temperature fall 20 DEG C -60 DEG C/h, less than 60 DEG C are cooled to, solidification is completed；
    Prepreg is aramid fiber or glass fiber reinforced epoxy resin base prepreg in described step (one), specifically includes increasing Strong body and resin, wherein reinforcement use aramid fabric or glass fabric, and resin uses 130 DEG C of intermediate temperature setting epoxies Resin or 180 DEG C of High Temperature Curing Epoxy Resin Systems；
    In described step (two), micropore is processed by the way of laser drill to composite material face；Described step (three) The middle honeycomb used is Nomex aramid fiber paper honeycomb；In the described step (4) glued membrane using 130 DEG C of solidification medium temperature glued membranes, 130 DEG C of solidification high temperature glued membranes or 170 DEG C of solidification high temperature glued membranes；Foamed glue is using 130 DEG C of solidification medium temperature foamed glues, 130 DEG C of solidifications High temperature foamed glue or 170 DEG C of solidification high temperature foamed glues；Solidifying pressure is 0.2~0.3MPa in described step (five), heating speed Rate is 10 DEG C~40 DEG C/h, rate of temperature fall≤20 DEG C/h.
  14. 14. the preparation method of the composite sound-deadening and noise-reducing sound lining described in a kind of claim 10, it is characterised in that including as follows Step：
    The shaping of step (1) panel and dividing plate
    Aramid Prepreg or glass fibre prepreg are subjected to laying on the shaping female mold of panel, after coating vacuum bag, in heat Solidified in pressure tank, panel is obtained after the completion of solidification；
    Aramid Prepreg or glass fibre prepreg are subjected to laying on the shaping female mold of dividing plate, after coating vacuum bag, in heat Solidified in pressure tank, dividing plate is obtained after the completion of solidification；
    Step (2) machine adds
    Panel and dividing plate the processing micropore obtained to step (1), then counter plate flange carries out deburring and the machinery of osculum adds Work；
    The sizing of step (3) honeycomb, cutting
    Two pieces of honeycombs are shaped under the conditions of 160-165 DEG C respectively, then by stereotyped honeycomb according to face plate profiles line Cut, and rhone is processed in the honeycomb side Nian Jie with backboard, obtain two pieces of honeycomb cores；
    Step (4) assembles
    One layer of glued membrane is respectively coated with the bonding plane for the panel that step (2) obtains and the bonding plane of backboard, two pieces of honeycomb cores with The side of dividing plate bonding is respectively coated with one layer of glued membrane, and passes through the glued membrane at the glued membrane and honeycomb core at hot-air counter plate micropore Air pressure perforate is carried out, macromolecule material film is then coated with interlayer composite material surface, is bonded between panel and interlayer One piece of honeycomb core, edge sealing is carried out using foamed glue at honeycomb core edge, is then positioned and is solidified, obtain assembly；It is described Hot-air temperature be 40-60 DEG C, flow 0.08-0.12m3/s；
    Step (5) solidification by cement
    The assembly that step (4) is completed is placed in autoclave after solidification, and is stripped and is obtained composite sound-deadening and noise-reducing sound Lining.
  15. A kind of 15. preparation method of composite sound-deadening and noise-reducing sound lining according to claim 14, it is characterised in that：It is described The step of (one) in, curing process is：Solidification temperature is 120-140 DEG C, and vacuum gauge pressure is not more than -0.097MPa, with 10 DEG C -40 DEG C/h heating rates are heated up, solidifying pressure 0.5MPa-0.7MPa, hardening time 2h-4h；Cool afterwards, rate of temperature fall 20 DEG C -60 DEG C/h, less than 60 DEG C are cooled to, solidification is completed；
    Prepreg is aramid fiber or glass fiber reinforced epoxy resin base prepreg in described step (one), specifically includes increasing Strong body and resin, wherein reinforcement use aramid fabric or glass fabric, and resin uses 130 DEG C of intermediate temperature setting epoxies Resin or 180 DEG C of High Temperature Curing Epoxy Resin Systems；
    In described step (two), micropore is processed by the way of laser drill to composite material face；Described step (three) The middle honeycomb used is Nomex aramid fiber paper honeycomb；In the described step (4) glued membrane using 130 DEG C of solidification medium temperature glued membranes, 130 DEG C of solidification high temperature glued membranes or 170 DEG C of solidification high temperature glued membranes；Foamed glue is using 130 DEG C of solidification medium temperature foamed glues, 130 DEG C of solidifications High temperature foamed glue or 170 DEG C of solidification high temperature foamed glues；Solidifying pressure is 0.2~0.3MPa in described step (five), heating speed Rate is 10 DEG C~40 DEG C/h, rate of temperature fall≤20 DEG C/h.
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CN108516075A (en) * 2018-03-22 2018-09-11 镇江市逸帆航空部件有限公司 Cabin noise reduction isolation board and cabin noise-reduction method based on passive flowing control
CN108533589A (en) * 2018-03-19 2018-09-14 中国南方航空股份有限公司 A kind of adhering method in metal noise-reducing structure extension splicing face
CN109483962A (en) * 2018-11-20 2019-03-19 华侨大学 A kind of multi-layer sandwich composite construction and the automobile dash board using the structure
CN109913139A (en) * 2019-03-11 2019-06-21 江苏惠沣环保科技有限公司 A kind of sound insulation glue film and preparation method thereof
CN110481061A (en) * 2019-09-17 2019-11-22 中国航发沈阳发动机研究所 A kind of method for punching of fibre reinforced composites, acoustical panel and its sound lining
CN110487533A (en) * 2019-09-17 2019-11-22 中国航发沈阳发动机研究所 A kind of sound lining testpieces, assemble method and its test structure
CN110486169A (en) * 2019-09-17 2019-11-22 中国航发沈阳发动机研究所 A kind of acoustical panel and the sound lining with it
CN110486334A (en) * 2019-09-17 2019-11-22 中国航发沈阳发动机研究所 A kind of sound lining and the engine with it
CN110749233A (en) * 2019-10-28 2020-02-04 上海机电工程研究所 Honeycomb adapter and method of manufacture
CN110815901A (en) * 2019-10-17 2020-02-21 成都飞机工业（集团）有限责任公司 Method for controlling through hole rate of acoustic lining wall plate made of honeycomb sandwich composite material
CN110936635A (en) * 2019-12-05 2020-03-31 南京航空航天大学 Composite honeycomb component based on compression molding of flow guiding process and method
CN110962400A (en) * 2018-09-30 2020-04-07 嘉迪声学科技有限公司 Sound insulation device
CN111113957A (en) * 2019-12-27 2020-05-08 中国民用航空飞行学院 Through hole edge packaging method for honeycomb sandwich composite material structural member
CN111232182A (en) * 2020-03-06 2020-06-05 中国商用飞机有限责任公司 Interior trim panel and application thereof
CN111674057A (en) * 2020-06-17 2020-09-18 湖北三江航天红阳机电有限公司 Forming method of heat insulation preventing layer of cabin section
CN112208743A (en) * 2019-07-09 2021-01-12 中国航发商用航空发动机有限责任公司 Component end structure, method for producing same, aircraft and aircraft component
CN112339360A (en) * 2020-10-29 2021-02-09 株洲时代新材料科技股份有限公司 Light noise-eliminating sound-insulating material for nacelle and preparation process thereof
CN112976701A (en) * 2021-03-03 2021-06-18 北京汽车研究总院有限公司 Honeycomb panel, manufacturing method thereof, vehicle body panel and vehicle
CN113858656A (en) * 2021-09-24 2021-12-31 成都佳驰电子科技股份有限公司 Integrated forming process of sawtooth-shaped hollow-structure composite wave-absorbing component
CN115923255A (en) * 2021-10-05 2023-04-07 通用电气公司 Solid adhesive film for acoustic liners and method
CN114654864B (en) * 2022-02-17 2023-06-09 成都飞机工业（集团）有限责任公司 Preparation method of honeycomb sandwich structure acoustic liner plate
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CN108516075A (en) * 2018-03-22 2018-09-11 镇江市逸帆航空部件有限公司 Cabin noise reduction isolation board and cabin noise-reduction method based on passive flowing control
CN110962400A (en) * 2018-09-30 2020-04-07 嘉迪声学科技有限公司 Sound insulation device
CN109483962A (en) * 2018-11-20 2019-03-19 华侨大学 A kind of multi-layer sandwich composite construction and the automobile dash board using the structure
CN109483962B (en) * 2018-11-20 2020-12-01 华侨大学 Automobile front panel with multi-layer sandwich composite structure and application of structure
CN109913139A (en) * 2019-03-11 2019-06-21 江苏惠沣环保科技有限公司 A kind of sound insulation glue film and preparation method thereof
CN112208743A (en) * 2019-07-09 2021-01-12 中国航发商用航空发动机有限责任公司 Component end structure, method for producing same, aircraft and aircraft component
CN110486169B (en) * 2019-09-17 2021-10-01 中国航发沈阳发动机研究所 Sound-absorbing plate and sound lining with same
CN110487533A (en) * 2019-09-17 2019-11-22 中国航发沈阳发动机研究所 A kind of sound lining testpieces, assemble method and its test structure
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CN110815901A (en) * 2019-10-17 2020-02-21 成都飞机工业（集团）有限责任公司 Method for controlling through hole rate of acoustic lining wall plate made of honeycomb sandwich composite material
US11897234B2 (en) 2019-10-24 2024-02-13 The University Of Limerick Composite materials for damping acoustic vibrations
CN110749233A (en) * 2019-10-28 2020-02-04 上海机电工程研究所 Honeycomb adapter and method of manufacture
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CN111113957A (en) * 2019-12-27 2020-05-08 中国民用航空飞行学院 Through hole edge packaging method for honeycomb sandwich composite material structural member
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