US20060272279A1 - Composite panel having subsonic transverse wave speed characteristics - Google Patents
Composite panel having subsonic transverse wave speed characteristics Download PDFInfo
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- US20060272279A1 US20060272279A1 US11/129,755 US12975505A US2006272279A1 US 20060272279 A1 US20060272279 A1 US 20060272279A1 US 12975505 A US12975505 A US 12975505A US 2006272279 A1 US2006272279 A1 US 2006272279A1
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- composite panel
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- 239000002131 composite material Substances 0.000 title claims abstract description 71
- 239000000463 material Substances 0.000 claims description 23
- 239000006260 foam Substances 0.000 claims description 6
- 230000002745 absorbent Effects 0.000 claims description 5
- 239000002250 absorbent Substances 0.000 claims description 5
- 239000011162 core material Substances 0.000 description 38
- 238000007792 addition Methods 0.000 description 4
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 4
- 229910052782 aluminium Inorganic materials 0.000 description 4
- 239000004593 Epoxy Substances 0.000 description 3
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 2
- 229920000784 Nomex Polymers 0.000 description 2
- 230000005540 biological transmission Effects 0.000 description 2
- 238000010276 construction Methods 0.000 description 2
- 239000011152 fibreglass Substances 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 239000004763 nomex Substances 0.000 description 2
- 230000005855 radiation Effects 0.000 description 2
- 230000009467 reduction Effects 0.000 description 2
- 230000015572 biosynthetic process Effects 0.000 description 1
- 229910052799 carbon Inorganic materials 0.000 description 1
- 230000003247 decreasing effect Effects 0.000 description 1
- 229910002804 graphite Inorganic materials 0.000 description 1
- 239000010439 graphite Substances 0.000 description 1
- 239000003562 lightweight material Substances 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 229920000642 polymer Polymers 0.000 description 1
- 230000004044 response Effects 0.000 description 1
- 125000000391 vinyl group Chemical group [H]C([*])=C([H])[H] 0.000 description 1
- 229920002554 vinyl polymer Polymers 0.000 description 1
Images
Classifications
-
- E—FIXED CONSTRUCTIONS
- E04—BUILDING
- E04B—GENERAL BUILDING CONSTRUCTIONS; WALLS, e.g. PARTITIONS; ROOFS; FLOORS; CEILINGS; INSULATION OR OTHER PROTECTION OF BUILDINGS
- E04B1/00—Constructions in general; Structures which are not restricted either to walls, e.g. partitions, or floors or ceilings or roofs
- E04B1/62—Insulation or other protection; Elements or use of specified material therefor
- E04B1/74—Heat, sound or noise insulation, absorption, or reflection; Other building methods affording favourable thermal or acoustical conditions, e.g. accumulating of heat within walls
- E04B1/82—Heat, sound or noise insulation, absorption, or reflection; Other building methods affording favourable thermal or acoustical conditions, e.g. accumulating of heat within walls specifically with respect to sound only
- E04B1/84—Sound-absorbing elements
- E04B1/86—Sound-absorbing elements slab-shaped
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B60—VEHICLES IN GENERAL
- B60R—VEHICLES, VEHICLE FITTINGS, OR VEHICLE PARTS, NOT OTHERWISE PROVIDED FOR
- B60R13/00—Elements for body-finishing, identifying, or decorating; Arrangements or adaptations for advertising purposes
- B60R13/08—Insulating elements, e.g. for sound insulation
-
- E—FIXED CONSTRUCTIONS
- E04—BUILDING
- E04C—STRUCTURAL ELEMENTS; BUILDING MATERIALS
- E04C2/00—Building elements of relatively thin form for the construction of parts of buildings, e.g. sheet materials, slabs, or panels
- E04C2/02—Building elements of relatively thin form for the construction of parts of buildings, e.g. sheet materials, slabs, or panels characterised by specified materials
- E04C2/26—Building elements of relatively thin form for the construction of parts of buildings, e.g. sheet materials, slabs, or panels characterised by specified materials composed of materials covered by two or more of groups E04C2/04, E04C2/08, E04C2/10 or of materials covered by one of these groups with a material not specified in one of the groups
- E04C2/284—Building elements of relatively thin form for the construction of parts of buildings, e.g. sheet materials, slabs, or panels characterised by specified materials composed of materials covered by two or more of groups E04C2/04, E04C2/08, E04C2/10 or of materials covered by one of these groups with a material not specified in one of the groups at least one of the materials being insulating
- E04C2/296—Building elements of relatively thin form for the construction of parts of buildings, e.g. sheet materials, slabs, or panels characterised by specified materials composed of materials covered by two or more of groups E04C2/04, E04C2/08, E04C2/10 or of materials covered by one of these groups with a material not specified in one of the groups at least one of the materials being insulating composed of insulating material and non-metallic or unspecified sheet-material
-
- E—FIXED CONSTRUCTIONS
- E04—BUILDING
- E04C—STRUCTURAL ELEMENTS; BUILDING MATERIALS
- E04C2/00—Building elements of relatively thin form for the construction of parts of buildings, e.g. sheet materials, slabs, or panels
- E04C2/30—Building elements of relatively thin form for the construction of parts of buildings, e.g. sheet materials, slabs, or panels characterised by the shape or structure
- E04C2/34—Building elements of relatively thin form for the construction of parts of buildings, e.g. sheet materials, slabs, or panels characterised by the shape or structure composed of two or more spaced sheet-like parts
- E04C2/36—Building elements of relatively thin form for the construction of parts of buildings, e.g. sheet materials, slabs, or panels characterised by the shape or structure composed of two or more spaced sheet-like parts spaced apart by transversely-placed strip material, e.g. honeycomb panels
- E04C2/365—Building elements of relatively thin form for the construction of parts of buildings, e.g. sheet materials, slabs, or panels characterised by the shape or structure composed of two or more spaced sheet-like parts spaced apart by transversely-placed strip material, e.g. honeycomb panels by honeycomb structures
-
- E—FIXED CONSTRUCTIONS
- E04—BUILDING
- E04B—GENERAL BUILDING CONSTRUCTIONS; WALLS, e.g. PARTITIONS; ROOFS; FLOORS; CEILINGS; INSULATION OR OTHER PROTECTION OF BUILDINGS
- E04B1/00—Constructions in general; Structures which are not restricted either to walls, e.g. partitions, or floors or ceilings or roofs
- E04B1/62—Insulation or other protection; Elements or use of specified material therefor
- E04B1/74—Heat, sound or noise insulation, absorption, or reflection; Other building methods affording favourable thermal or acoustical conditions, e.g. accumulating of heat within walls
- E04B1/82—Heat, sound or noise insulation, absorption, or reflection; Other building methods affording favourable thermal or acoustical conditions, e.g. accumulating of heat within walls specifically with respect to sound only
- E04B1/84—Sound-absorbing elements
- E04B2001/8457—Solid slabs or blocks
- E04B2001/8461—Solid slabs or blocks layered
-
- E—FIXED CONSTRUCTIONS
- E04—BUILDING
- E04B—GENERAL BUILDING CONSTRUCTIONS; WALLS, e.g. PARTITIONS; ROOFS; FLOORS; CEILINGS; INSULATION OR OTHER PROTECTION OF BUILDINGS
- E04B1/00—Constructions in general; Structures which are not restricted either to walls, e.g. partitions, or floors or ceilings or roofs
- E04B1/62—Insulation or other protection; Elements or use of specified material therefor
- E04B1/74—Heat, sound or noise insulation, absorption, or reflection; Other building methods affording favourable thermal or acoustical conditions, e.g. accumulating of heat within walls
- E04B1/82—Heat, sound or noise insulation, absorption, or reflection; Other building methods affording favourable thermal or acoustical conditions, e.g. accumulating of heat within walls specifically with respect to sound only
- E04B1/84—Sound-absorbing elements
- E04B2001/8457—Solid slabs or blocks
- E04B2001/8476—Solid slabs or blocks with acoustical cavities, with or without acoustical filling
-
- 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
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T29/00—Metal working
- Y10T29/49—Method of mechanical manufacture
- Y10T29/49826—Assembling or joining
Definitions
- This invention relates to composite panels. More specifically, the invention is a composite panel that has subsonic transverse wave speed characteristics in regions thereof for reduced sound radiation efficiency and increased sound power transmission loss.
- Composite materials are used in many construction applications (e.g., structures, aircraft, trains, vehicles, industrial machines, etc.) because of their light weight and strength.
- the materials are frequently formed into what are known as composite panels where two sheets of one type of material are sandwiched about another type of core material.
- one type of composite panel has two sheets of a material such as graphite-epoxy, epoxy, fiberglass or aluminum sandwiched about a honeycomb core made from materials such as NOMEX, aluminum or paper.
- the resulting composite panel is light and stiffer than any of its component parts.
- sound can be radiated very efficiently because the transverse wave speed through the panel can be greater than the speed of sound in air.
- the composite panel has a supersonic transverse wave speed. If the composite panel is to be used to define a human-occupied interior space, noise radiated by the composite panel into the interior space may be unacceptable.
- Current methods of addressing this noise problem have involved the addition of noise control material to the composite panel such that the noise-controlled composite panel is characterized by a subsonic transverse wave speed. Suggested additions include a limp mass (e.g., lead vinyl) applied to one or both of the composite panel's face sheets and/or the inclusion of foam within the composite panel's core in the case of a honeycomb core.
- the extra noise-control material adds cost and weight to the composite panel.
- Another object of the present invention is to provide a composite panel that does not require the addition of noise control material to achieve subsonic transverse wave speed characteristics.
- a composite panel has first and second sheets sandwiching a core. At least one of the first and second sheets is attached to the core at first regions thereof and unattached to the core at second regions thereof.
- FIG. 1 is an exploded perspective view of a composite panel having a core with recessed regions in accordance with an embodiment of the present invention
- FIG. 2 is a cross-sectional view of the composite panel of FIG. 1 in its assembled form
- FIG. 3 is a cross-sectional view of a composite panel in accordance with another embodiment of the present invention where the recesses are different sizes;
- FIG. 4 is a cross-sectional view of a composite panel in accordance with another embodiment of the present invention where the recesses are formed on either side of the core in a mirror-image fashion;
- FIG. 5 is a cross-sectional view of a composite panel in accordance with another embodiment of the present invention where the recesses are formed on either side of the core in a non-mirror-image fashion;
- FIG. 6 is a cross-sectional view of a composite panel in accordance with another embodiment of the present invention where areas of non-attachment are provided between the core and face sheets;
- FIG. 7 is a cross-sectional view of the composite panel of FIG. 2 further having acoustically absorbent material in the panel's recesses;
- FIG. 8 is a cross-sectional view of a composite panel in accordance with another embodiment of the present invention where recesses are formed in one of the face sheets.
- composite panel 10 is a flat panel.
- composite panels constructed in accordance with the present invention can also be shaped to define contoured panels as needed.
- Composite panel 10 has face sheets 12 and 14 sandwiched about a core 16 .
- Face sheets 12 and 14 can be the same or different materials. Suitable materials for face sheets 12 and 14 include, but are not limited to, graphite epoxy, aluminum and fiberglass.
- Core 16 is a lightweight material that is bonded, attached or adhered (in ways well understood in the art) to face sheets 12 and 14 to form composite panel 10 such that the stiffness of composite panel 10 is greater than the stiffness of it's component parts.
- the transverse wave speed for typical materials and thicknesses of face sheets 12 and 14 is subsonic, the transverse wave speed is very often supersonic for a composite panel using these face sheets.
- Suitable constructions for core 16 include, but are not limited to, a honeycomb structure, a truss structure, or a foam structure.
- Suitable materials for core 16 include, but are not limited to, NOMEX, paper and aluminum in the case of honeycomb cores, and polymers and carbon in the case of foam cores.
- the core can be of varying thicknesses depending, for example, on a particular application, without departing from the scope of the present invention.
- One embodiment of the present invention addresses this problem by forming recesses in core 16 adjacent face sheet 12 . More specifically, an array of recesses 18 are formed in core 16 so that face sheet 12 is only bonded/attached/adhered to core 16 at regions 16 A while the entire side of face sheet 14 is bonded/attached/adhered to the other side of core 16 as indicated by 14 A.
- the number, size, depth and shape of recesses 18 and resulting size/shape of regions 16 A can vary without departing from the scope of the present invention. In general, a balance must be struck between stiffness requirements and noise requirements of composite panel 10 . With respect to noise reduction, the greater the area of the recesses, the greater the reduction in sound radiation efficiency and increase in sound power transmission loss.
- composite panel 10 must have sufficient attachment regions 16 A (between face sheet 12 and core 16 ) to achieve the necessary stiffness requirements. Accordingly, any given application of the present invention will require these two criteria to be balanced.
- identically-sized recesses 18 are formed just on one side of core 16 .
- the present invention is not so limited.
- composite panel 30 in FIG. 3 has recesses 38 formed in core 16 that are of different sizes. Note that the shapes of recesses 38 could vary too.
- composite panel 40 has recesses 48 formed on either side of core 16 in a mirror-image fashion so that the regions of face sheets 12 and 14 contacting and attached to core 16 are similarly mirror images of one another.
- Composite panel 50 in FIG. 5 utilizes recesses 58 on opposing sides of core 16 , but in a non-mirror-image fashion.
- FIG. 6 Another embodiment of the present invention is illustrated by a composite panel 60 in FIG. 6 where, rather than forming recesses in core 16 , regions of non-attachment 16 B are formed between face sheets 12 / 14 and core 16 . That is, face sheets 12 and 14 are coupled to core 16 only at attachment regions 16 A while remaining uncoupled or unattached to core 16 at non-attached regions 16 B.
- friction losses will be generated between the non-attached regions 16 B of core 16 and face sheets 12 and 14 . In many applications, this will be sufficient to produce a satisfactory low frequency response. However, higher-frequency buzzing may occur thereby making this embodiment most suitable for applications where high-frequency buzzing is not problematic.
- Still another embodiment of the present invention involves adding an acoustically absorbent material (a wide variety of which are well known in the art) to some or all of the recesses formed in the composite panel's core.
- FIG. 7 illustrates the FIG. 2 embodiment with recesses 18 further having an acoustically absorbent material 20 partially or completely filling recesses 18 .
- the present invention is not limited to the formation of recesses in the core of a composite panel.
- a composite panel 70 illustrated in FIG. 8 has recesses 78 formed in face sheet 12 .
- recesses could also be formed in face sheet 14 in a mirror-image or non-mirror-image fashion with respect to recesses 78 .
- recesses could be formed in one or both of face sheets 12 / 14 and in core 16 without departing from the scope of the present invention.
- the advantages of the present invention are numerous.
- Composite panels having local regions characterized by subsonic transverse wave speeds can be constructed without requiring the addition of noise control material. Rather, the present invention addresses the transverse wave speed problem of composite panels by actually eliminating material thereby decreasing the weight of the panel.
- Cores and/or face sheets with recesses formed therein can be easily achieved using automated manufacturing processes.
- the present invention can be used wherever composite materials are used in weight sensitive, noise environments such as aerospace and ground vehicles, trains and industrial machines.
- a nail and a screw may not be structural equivalents in that a nail employs a cylindrical surface to secure wooden parts together, whereas a screw employs a helical surface, in the environment of fastening wooden parts, a nail and a screw may be equivalent structures.
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- Engineering & Computer Science (AREA)
- Architecture (AREA)
- Physics & Mathematics (AREA)
- Acoustics & Sound (AREA)
- Civil Engineering (AREA)
- Structural Engineering (AREA)
- Electromagnetism (AREA)
- Mechanical Engineering (AREA)
- Laminated Bodies (AREA)
- Soundproofing, Sound Blocking, And Sound Damping (AREA)
Abstract
A composite panel has first and second sheets sandwiching a core with at least one of the sheets being attached to the core at first regions thereof and unattached to the core at second regions thereof.
Description
- The invention described herein was made by employees of the United States Government and may be manufactured and used by or for the Government for governmental purposes without the payment of any royalties thereon or therefor.
- 1. Field of the Invention
- This invention relates to composite panels. More specifically, the invention is a composite panel that has subsonic transverse wave speed characteristics in regions thereof for reduced sound radiation efficiency and increased sound power transmission loss.
- 2. Description of the Related Art
- Composite materials are used in many construction applications (e.g., structures, aircraft, trains, vehicles, industrial machines, etc.) because of their light weight and strength. The materials are frequently formed into what are known as composite panels where two sheets of one type of material are sandwiched about another type of core material. For example, one type of composite panel has two sheets of a material such as graphite-epoxy, epoxy, fiberglass or aluminum sandwiched about a honeycomb core made from materials such as NOMEX, aluminum or paper. The resulting composite panel is light and stiffer than any of its component parts. However, as can be the case with most lightweight and stiff materials, sound can be radiated very efficiently because the transverse wave speed through the panel can be greater than the speed of sound in air. In other words, the composite panel has a supersonic transverse wave speed. If the composite panel is to be used to define a human-occupied interior space, noise radiated by the composite panel into the interior space may be unacceptable. Current methods of addressing this noise problem have involved the addition of noise control material to the composite panel such that the noise-controlled composite panel is characterized by a subsonic transverse wave speed. Suggested additions include a limp mass (e.g., lead vinyl) applied to one or both of the composite panel's face sheets and/or the inclusion of foam within the composite panel's core in the case of a honeycomb core. However, the extra noise-control material adds cost and weight to the composite panel.
- Accordingly, it is an object of the present invention to provide a composite panel having subsonic transverse wave speed characteristics.
- Another object of the present invention is to provide a composite panel that does not require the addition of noise control material to achieve subsonic transverse wave speed characteristics.
- In accordance with the present invention, a composite panel has first and second sheets sandwiching a core. At least one of the first and second sheets is attached to the core at first regions thereof and unattached to the core at second regions thereof.
- Other objects, features and advantages of the present invention will become apparent upon reference to the following description of the preferred embodiments and to the drawings, wherein corresponding reference characters indicate corresponding parts throughout the several views of the drawings and wherein:
-
FIG. 1 is an exploded perspective view of a composite panel having a core with recessed regions in accordance with an embodiment of the present invention; -
FIG. 2 is a cross-sectional view of the composite panel ofFIG. 1 in its assembled form; -
FIG. 3 is a cross-sectional view of a composite panel in accordance with another embodiment of the present invention where the recesses are different sizes; -
FIG. 4 is a cross-sectional view of a composite panel in accordance with another embodiment of the present invention where the recesses are formed on either side of the core in a mirror-image fashion; -
FIG. 5 is a cross-sectional view of a composite panel in accordance with another embodiment of the present invention where the recesses are formed on either side of the core in a non-mirror-image fashion; -
FIG. 6 is a cross-sectional view of a composite panel in accordance with another embodiment of the present invention where areas of non-attachment are provided between the core and face sheets; -
FIG. 7 is a cross-sectional view of the composite panel ofFIG. 2 further having acoustically absorbent material in the panel's recesses; and -
FIG. 8 is a cross-sectional view of a composite panel in accordance with another embodiment of the present invention where recesses are formed in one of the face sheets. - Referring now to the drawings, and more particularly to
FIGS. 1 and 2 , a composite panel in accordance with an embodiment of the present invention is shown and is referenced generally bynumeral 10. For illustration,composite panel 10 is a flat panel. However it is to be understood that composite panels constructed in accordance with the present invention can also be shaped to define contoured panels as needed. -
Composite panel 10 hasface sheets core 16.Face sheets face sheets Core 16 is a lightweight material that is bonded, attached or adhered (in ways well understood in the art) toface sheets composite panel 10 such that the stiffness ofcomposite panel 10 is greater than the stiffness of it's component parts. As a result, while the transverse wave speed for typical materials and thicknesses offace sheets core 16 include, but are not limited to, a honeycomb structure, a truss structure, or a foam structure. Suitable materials forcore 16 include, but are not limited to, NOMEX, paper and aluminum in the case of honeycomb cores, and polymers and carbon in the case of foam cores. The core can be of varying thicknesses depending, for example, on a particular application, without departing from the scope of the present invention. - One embodiment of the present invention addresses this problem by forming recesses in
core 16adjacent face sheet 12. More specifically, an array ofrecesses 18 are formed incore 16 so thatface sheet 12 is only bonded/attached/adhered tocore 16 atregions 16A while the entire side offace sheet 14 is bonded/attached/adhered to the other side ofcore 16 as indicated by 14A. The number, size, depth and shape ofrecesses 18 and resulting size/shape ofregions 16A can vary without departing from the scope of the present invention. In general, a balance must be struck between stiffness requirements and noise requirements ofcomposite panel 10. With respect to noise reduction, the greater the area of the recesses, the greater the reduction in sound radiation efficiency and increase in sound power transmission loss. This is because eachregion 12A offace sheet 12 adjacent to arecess 18 is uncoupled fromcore 16 so that transverse wave speed at this local region ofcomposite panel 10 is reduced to the subsonic transverse wave speed offace sheet 12. With respect to stiffness,composite panel 10 must havesufficient attachment regions 16A (betweenface sheet 12 and core 16) to achieve the necessary stiffness requirements. Accordingly, any given application of the present invention will require these two criteria to be balanced. - In the illustrated embodiment discussed thus far, identically-sized
recesses 18 are formed just on one side ofcore 16. However, the present invention is not so limited. For example,composite panel 30 inFIG. 3 hasrecesses 38 formed incore 16 that are of different sizes. Note that the shapes ofrecesses 38 could vary too. InFIG. 4 ,composite panel 40 hasrecesses 48 formed on either side ofcore 16 in a mirror-image fashion so that the regions offace sheets core 16 are similarly mirror images of one another.Composite panel 50 inFIG. 5 utilizesrecesses 58 on opposing sides ofcore 16, but in a non-mirror-image fashion. - Another embodiment of the present invention is illustrated by a
composite panel 60 inFIG. 6 where, rather than forming recesses incore 16, regions ofnon-attachment 16B are formed betweenface sheets 12/14 andcore 16. That is,face sheets core 16 only atattachment regions 16A while remaining uncoupled or unattached tocore 16 at non-attachedregions 16B. As sound radiates throughcomposite panel 60, friction losses will be generated between the non-attachedregions 16B ofcore 16 andface sheets - Still another embodiment of the present invention involves adding an acoustically absorbent material (a wide variety of which are well known in the art) to some or all of the recesses formed in the composite panel's core. For example,
FIG. 7 illustrates theFIG. 2 embodiment withrecesses 18 further having an acoustically absorbent material 20 partially or completely filling recesses 18. - The present invention is not limited to the formation of recesses in the core of a composite panel. For example, a
composite panel 70 illustrated inFIG. 8 hasrecesses 78 formed inface sheet 12. Although not illustrated, recesses could also be formed inface sheet 14 in a mirror-image or non-mirror-image fashion with respect to recesses 78. Still further, recesses could be formed in one or both offace sheets 12/14 and incore 16 without departing from the scope of the present invention. - The advantages of the present invention are numerous. Composite panels having local regions characterized by subsonic transverse wave speeds can be constructed without requiring the addition of noise control material. Rather, the present invention addresses the transverse wave speed problem of composite panels by actually eliminating material thereby decreasing the weight of the panel. Cores and/or face sheets with recesses formed therein can be easily achieved using automated manufacturing processes. The present invention can be used wherever composite materials are used in weight sensitive, noise environments such as aerospace and ground vehicles, trains and industrial machines.
- Although only a few exemplary embodiments of this invention have been described in detail above, those skilled in the art will readily appreciate that many modifications are possible in the exemplary embodiments without materially departing from the novel teachings and advantages of this invention. Accordingly, all such modifications are intended to be included within the scope of this invention as defined in the following claims. In the claims, means-plus-function and step-plus-function clauses are intended to cover the structures or acts described herein as performing the recited function and not only structural equivalents, but also equivalent structures. Thus, although a nail and a screw may not be structural equivalents in that a nail employs a cylindrical surface to secure wooden parts together, whereas a screw employs a helical surface, in the environment of fastening wooden parts, a nail and a screw may be equivalent structures.
Claims (22)
1. A composite panel comprising first and second sheets sandwiching a core with at least one of said first and second sheets attached to said core at first regions thereof and unattached to said core at second regions thereof.
2. A composite panel as in claim 1 wherein each of said second regions is a recess formed in at least one of said core, said first sheet and said second sheet.
3. A composite panel as in claim 1 wherein said first and second sheets are the same material.
4. A composite panel as in claim 1 wherein said first and second sheets are different materials.
5. A composite panel as in claim 1 wherein said core is selected from the group consisting of a honeycomb core, a truss core and a foam core.
6. A composite panel as in claim 1 wherein transverse wave speed of each of said first and second sheets is subsonic.
7. A composite panel as in claim 1 wherein said second regions adjacent to said first sheet are mirror imaged with respect to said second regions adjacent to said second sheet.
8. A composite panel as in claim 1 wherein said second regions are identically sized and shaped.
9. A composite panel as in claim 2 further comprising acoustically absorbent material in said recess.
10. A composite panel comprising first and second sheets adjacent to and sandwiching a core therebetween with at least one of said first and second sheets attached to said core at first regions thereof and unattached to said core at second regions thereof such that said composite panel is characterized as having a subsonic transverse wave speed at portions thereof bounded by said second regions.
11. A composite panel as in claim 10 wherein each of said second regions is a recess formed in at least one of said core, said first sheet and said second sheet.
12. A composite panel as in claim 10 wherein said first and second sheets are the same material.
13. A composite panel as in claim 10 wherein said first and second sheets are different materials.
14. A composite panel as in claim 10 wherein said core is selected from the group consisting of a honeycomb core, a truss core and a foam core.
15. A composite panel as in claim 10 wherein transverse wave speed of each of said first and second sheets is subsonic.
16. A composite panel as in claim 10 wherein said second regions adjacent to said first sheet are mirror imaged with respect to said second regions adjacent to said second sheet.
17. A composite panel as in claim 10 wherein said second regions are identically sized and shaped.
18. A composite panel as in claim 11 further comprising acoustically absorbent material in said recess.
19. A composite panel as in claim 10 wherein a face of said first sheet is completely attached to said core.
20. A composite panel as in claim 19 wherein each of said second regions is a recess formed in at least one of said core and said second sheet.
21. A composite panel as in claim 19 wherein said core is selected from the group consisting of a honeycomb core, a truss core and a foam core.
22. A composite panel as in claim 19 wherein said second regions are identically sized and shaped.
Priority Applications (3)
Application Number | Priority Date | Filing Date | Title |
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US11/129,755 US20060272279A1 (en) | 2005-05-13 | 2005-05-13 | Composite panel having subsonic transverse wave speed characteristics |
US11/946,207 US20080128202A1 (en) | 2005-05-13 | 2007-11-28 | Composite Panel with Reinforced Recesses |
US12/894,326 US8087494B2 (en) | 2005-05-13 | 2010-09-30 | Method of making a composite panel having subsonic transverse wave speed characteristics |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US11/129,755 US20060272279A1 (en) | 2005-05-13 | 2005-05-13 | Composite panel having subsonic transverse wave speed characteristics |
Related Child Applications (2)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US11/946,207 Continuation-In-Part US20080128202A1 (en) | 2005-05-13 | 2007-11-28 | Composite Panel with Reinforced Recesses |
US12/894,326 Continuation US8087494B2 (en) | 2005-05-13 | 2010-09-30 | Method of making a composite panel having subsonic transverse wave speed characteristics |
Publications (1)
Publication Number | Publication Date |
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US20060272279A1 true US20060272279A1 (en) | 2006-12-07 |
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Application Number | Title | Priority Date | Filing Date |
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US11/129,755 Abandoned US20060272279A1 (en) | 2005-05-13 | 2005-05-13 | Composite panel having subsonic transverse wave speed characteristics |
US12/894,326 Expired - Fee Related US8087494B2 (en) | 2005-05-13 | 2010-09-30 | Method of making a composite panel having subsonic transverse wave speed characteristics |
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US12/894,326 Expired - Fee Related US8087494B2 (en) | 2005-05-13 | 2010-09-30 | Method of making a composite panel having subsonic transverse wave speed characteristics |
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US20080178544A1 (en) * | 2005-04-28 | 2008-07-31 | Clark Ronald A | Styro board |
US8087494B2 (en) * | 2005-05-13 | 2012-01-03 | United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Method of making a composite panel having subsonic transverse wave speed characteristics |
US20110041310A1 (en) * | 2005-05-13 | 2011-02-24 | United States of America as represented by the Administrator of the National Aeronautics and | Method of Making a Composite Panel Having Subsonic Transverse Wave Speed Characteristics |
US7631727B2 (en) * | 2006-05-24 | 2009-12-15 | Airbus Deutschland Gmbh | Sandwich structure with frequency-selective double wall behavior |
US20070292658A1 (en) * | 2006-05-24 | 2007-12-20 | Airbus Deutschland Gmbh | Sandwich structure with frequency-selective double wall behavior |
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US8282085B2 (en) * | 2006-12-11 | 2012-10-09 | Eurocopter | Absorbent covering |
US8336804B2 (en) * | 2008-12-17 | 2012-12-25 | Airbus Operations Gmbh | Aircraft cabin panel with core recesses for acoustic absorption |
US20100148001A1 (en) * | 2008-12-17 | 2010-06-17 | Airbus Operations Gmbh | Aircraft cabin panel with core recesses for acoustic absorption |
DE102010015638A1 (en) * | 2010-04-20 | 2011-10-20 | Airbus Operations Gmbh | plate absorber |
DE102010015638B4 (en) * | 2010-04-20 | 2015-02-12 | Airbus Operations Gmbh | Aircraft cabin plate absorber |
EP2560866A1 (en) * | 2010-04-20 | 2013-02-27 | Airbus Operations GmbH | Panel absorber |
US8534418B2 (en) | 2010-04-20 | 2013-09-17 | Airbus Operations Gmbh | Plate absorber |
EP2780641A4 (en) * | 2011-11-16 | 2015-11-25 | Huntair Inc | Sound-absorptive panel for an air handling system |
CN103129734A (en) * | 2011-11-23 | 2013-06-05 | 波音公司 | Noise reduction system for composite structures |
US20140299409A1 (en) * | 2011-11-23 | 2014-10-09 | The Boeing Company | Noise reduction system for composite structures |
US8770343B2 (en) * | 2011-11-23 | 2014-07-08 | The Boeing Company | Noise reduction system for composite structures |
US20130126267A1 (en) * | 2011-11-23 | 2013-05-23 | The Boeing Company | Noise Reduction System for Composite Structures |
US9353518B2 (en) * | 2011-11-23 | 2016-05-31 | The Boeing Company | Noise reduction system for composite structures |
US10967955B2 (en) * | 2017-10-09 | 2021-04-06 | Airbus Operations Gmbh | Vertical tail unit for flow control |
US10974817B2 (en) * | 2017-10-09 | 2021-04-13 | Airbus Operations Gmbh | Vertical tail unit for flow control |
US20210214072A1 (en) * | 2017-10-09 | 2021-07-15 | Airbus Operations Gmbh | Vertical tail unit for flow control |
US11565795B2 (en) * | 2017-10-09 | 2023-01-31 | Airbus Operations Gmbh | Vertical tail unit for flow control |
US11004439B2 (en) * | 2018-02-26 | 2021-05-11 | Toyota Motor Engineering & Manufacturing North America, Inc. | Acoustic absorber |
US20240068233A1 (en) * | 2022-08-26 | 2024-02-29 | Louisiana-Pacific Corporation | Structural panel with exterior insulating foam layer |
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