阅读说明：本技术 热声隔离系统、模块及包括该热声隔离系统和模块的飞机 (Thermoacoustic isolation system, thermoacoustic isolation module and aircraft comprising thermoacoustic isolation system and thermoacoustic isolation module ) 是由 卡门·沃伊库 丹尼尔·朗格卢瓦 让-弗朗索瓦·布莱斯 于 2020-10-30 设计创作，主要内容包括：热声隔离系统、模块及包括该热声隔离系统和模块的飞机。一种用于飞机的热声隔离模块,该热声隔离模块包括纤维毛层,该纤维毛层限定了外侧、内侧、在该外侧和该内侧之间的厚度,以及外周。该热声隔离模块还包括质量层,该质量层至少设置在纤维毛层的外侧上、纤维毛层的内侧上,或纤维毛层的外侧和内侧之间。外封装片材从外部设置在纤维毛层的外侧。类似地,内封装片材从内部设置在纤维毛层的内侧。外周接缝在与纤维毛层的外周相邻的地方将外封装片材连接到内封装片材,从而产生包封纤维毛层的封套。(Thermoacoustic isolation systems, modules, and aircraft including the same. A thermoacoustic isolation module for an aircraft includes a fiber batt defining an outer side, an inner side, a thickness between the outer side and the inner side, and an outer periphery. The thermoacoustic isolation module further comprises a mass layer which is arranged at least on the outside of the fiber batt, on the inside of the fiber batt, or between the outside and the inside of the fiber batt. The outer packaging sheet is disposed outside the fiber batt layer from the outside. Similarly, the inner packaging sheet is disposed inside the fiber batt layer from the inside. A peripheral seam joins the outer encapsulating sheet to the inner encapsulating sheet adjacent the periphery of the fibre batt, thereby creating an envelope enclosing the fibre batt.)

1. A thermoacoustic isolation module for an aircraft, the thermoacoustic isolation module comprising:

a fiber batt defining an outer side, an inner side, a thickness between the outer side and the inner side, and an outer perimeter;

a mass layer disposed at least on

On the outer side of the fiber batt layer,

on the inner side of the fibre batt, or

Between the outer side and the inner side of the fiber batt;

an outer packaging sheet disposed externally on the outside of the fiber batt layer;

an inner packaging sheet internally disposed on the inner side of the fiber batt layer; and

a peripheral seam joining the outer packaging sheet to the inner packaging sheet adjacent to the periphery of the fibre batt, thereby creating a wrapper enclosing the fibre batt.

2. The thermoacoustic module according to claim 1, wherein the fiber batt comprises a glass fiber nonwoven material.

3. The thermoacoustic module according to claim 1, wherein the mass layer comprises rubber.

4. The thermoacoustic module according to claim 1, wherein the outer packaging sheet is plastic.

5. The thermoacoustic module according to claim 1, wherein the inner packaging sheet is plastic.

6. The thermoacoustic module according to claim 1, wherein the peripheral seam extends completely around a periphery of the fiber batt.

7. The thermoacoustic module according to claim 1, further comprising a first partial seam extending a first predetermined distance from the outer circumference into the fiber batt.

8. The thermoacoustic module according to claim 7, further comprising a second partial seam extending a second predetermined distance from the outer circumference into the fiber batt.

9. The thermoacoustic module according to claim 1, further comprising a third partial seam surrounding a region of the fiber batt inward of the periphery.

10. An aircraft, comprising:

a body;

a first frame element connected to the fuselage, the first frame element including an inner leg;

a fiber batt defining an outer side, an inner side, a thickness between the outer side and the inner side, and an outer perimeter;

a mass layer disposed at least on

On the outer side of the fiber batt layer,

on the inner side of the fibre batt, or

Between the inner side and the outer side of the fiber batt;

an outer packaging sheet disposed externally on the outside of the fiber batt layer;

an inner packaging sheet internally disposed on the inner side of the fiber batt layer;

a peripheral seam joining the outer packaging sheet to the inner packaging sheet adjacent the periphery of the batt, thereby creating a jacket that encapsulates the batt and defines a cover layer edge adjacent the peripheral seam; and

a clip securing the overlay edge to the inner leg of the first frame element.

11. A thermoacoustic isolation system for an aircraft, comprising:

a first frame element connected to a fuselage, the first frame element including an inner leg;

a fiber batt defining an outer side, an inner side, a thickness between the outer side and the inner side, and an outer perimeter;

a mass layer disposed at least on

On the outer side of the fiber batt layer,

on the inner side of the fibre batt, or

Between the inner side and the outer side of the fiber batt;

an outer packaging sheet disposed externally on the outside of the fiber batt layer;

an inner packaging sheet internally disposed on the inner side of the fiber batt layer;

a peripheral seam joining the outer packaging sheet to the inner packaging sheet adjacent to the periphery of the batt, thereby creating a jacket that encapsulates the batt and defines a cover layer edge adjacent to the peripheral seam; and

a clip securing the overlay edge to the inner leg of the first frame element.

12. The thermoacoustic insulation system according to claim 11, wherein the fiber batt comprises a glass fiber nonwoven mat.

13. The thermoacoustic isolation system of claim 11, wherein the mass layer comprises rubber.

14. The thermoacoustic isolation system of claim 11, wherein the outer packaging sheet is plastic.

15. The thermoacoustic isolation system of claim 11, wherein the inner packaging sheet is plastic.

16. The thermoacoustic isolation system of claim 11, wherein the peripheral seam extends completely around the periphery of the fiber batt.

17. The thermoacoustic isolation system of claim 11, further comprising a first partial seam extending a first predetermined distance from the outer circumference into the fiber batt.

18. The thermoacoustic isolation system of claim 17, further comprising a second partial seam extending a second predetermined distance from the outer circumference into the fiber batt.

19. The thermoacoustic isolation system of claim 11, further comprising a third partial seam surrounding a region of the fiber batt inward of the periphery.

20. The thermoacoustic insulation system according to claim 19, wherein the third partial seam surrounds an opening through the fiber batt.

Technical Field

The present invention relates to a construction for an aircraft insulation, and to an arrangement for mounting the insulation in an aircraft. More specifically, the present invention relates to the configuration of: thermoacoustic isolation system, thermoacoustic isolation module, and aircraft comprising the thermoacoustic isolation system and the thermoacoustic isolation module.

Background

In designing an aircraft cabin, aircraft designers have to address a number of comfort issues for passengers, among which are, inter alia, the temperature within the aircraft cabin and the magnitude of the sound within the aircraft cabin.

Although the prior art includes examples addressing both temperature control and acoustic control within an aircraft cabin, it is desirable to further improve both temperature control and acoustic control.

Disclosure of Invention

The present invention provides one or more solutions that improve upon thermoacoustic isolation systems and thermoacoustic isolation modules known in the art.

In one embodiment, the present invention provides a thermoacoustic isolation module for an aircraft, the thermoacoustic isolation module comprising a fiber batt (fiber batt) defining an outer side, an inner side, a thickness between the outer side and the inner side, and an outer periphery. The thermoacoustic isolation module further comprises a mass layer (mass layer) which is arranged at least on the outside of the fibre fleece, on the inside of the fibre fleece or between the outside and the inside of the fibre fleece. The outer packaging sheet is disposed outside the fiber batt layer from the outside. Similarly, the inner packaging sheet is disposed inside the fiber batt layer from the inside. A peripheral seam joins the outer encapsulating sheet to the inner encapsulating sheet adjacent the periphery of the fibre batt, thereby creating an envelope enclosing the fibre batt.

In one contemplated embodiment of the thermoacoustic module, the fiber batt comprises a glass fiber nonwoven material.

In another contemplated embodiment of the thermoacoustic module, the mass layer comprises rubber.

Still further, it is contemplated that the outer packaging sheet is plastic. Similarly, the inner packaging sheet may be plastic.

For one contemplated embodiment of the thermoacoustic module, the peripheral seam extends completely around the periphery of the fiber batt.

It is contemplated that the thermoacoustic module may include a first partial seam extending a first predetermined distance from the outer periphery into the fiber batt.

Separately, the thermoacoustic module may have a second partial seam extending a second predetermined distance from the outer periphery into the fiber batt.

In addition, the thermoacoustic module may comprise a third partial seam surrounding a region of the fiber batt inside the outer periphery.

The invention also provides an aircraft comprising: a body; a first frame element connected to the fuselage, the first frame element including an inner leg; and a fiber batt defining an outer side, an inner side, a thickness between the outer side and the inner side, and an outer periphery. The aircraft further comprises a mass layer which is arranged at least on the outside of the fibre batt, on the inside of the fibre batt or between the inside and the outside of the fibre batt. The outer packaging sheet is disposed outside the fiber batt layer from the outside. The inner packaging sheet is disposed inside the fiber batt layer from the inside. The peripheral seam joins the outer packaging sheet to the inner packaging sheet adjacent the periphery of the batt, thereby creating a jacket that encapsulates the batt and defines a blanket edge adjacent the peripheral seam. The clip secures the blanket edge to the inner leg of the first frame element.

The invention also provides a thermoacoustic isolation system for an aircraft. The thermoacoustic isolation system includes a first frame member connected to the fuselage, the first frame member including an inner leg. The thermoacoustic isolation system further comprises: a fiber batt defining an outer side, an inner side, a thickness between the outer side and the inner side, and an outer periphery; a mass layer disposed at least on the outside of the fiber batt, on the inside of the fiber batt, or between the inside and outside of the fiber batt. The outer packaging sheet is disposed outside the fiber batt layer from the outside. The inner packaging sheet is disposed inside the fiber batt layer from the inside. The peripheral seam joins the outer packaging sheet to the inner packaging sheet adjacent the periphery of the batt, thereby creating a jacket that encapsulates the batt and defines a cover layer edge adjacent the peripheral seam. The clip secures the blanket edge to the inner leg of the first frame element.

Still further, the thermoacoustic insulation system may be configured such that the fiber batting comprises a non-woven mat of glass fibers.

In one embodiment, the thermoacoustic isolation system may be configured such that the mass layer comprises rubber.

For thermoacoustic insulation systems, the outer packaging sheet may be plastic. Similarly, the inner packaging sheet may also be plastic.

The thermoacoustic insulation system may be manufactured such that the peripheral seam extends completely around the periphery of the fibre batt.

In another contemplated embodiment, the thermoacoustic isolation system may include a first partial seam extending a first predetermined distance from the outer periphery into the fiber batt.

Alternatively, the thermoacoustic insulation system may comprise a second partial seam extending a second predetermined distance from the outer periphery into the fibre batt.

In yet another contemplated embodiment, the thermoacoustic insulation system can be made with a third partial seam that surrounds a region of the fiber batt that is inside the outer periphery.

In this contemplated embodiment, a third partial seam may surround the opening through the fiber batt.

Other aspects of the invention will become apparent from the following drawings and discussion.

Drawings

The accompanying drawings illustrate various non-limiting embodiments of the invention, in which:

FIG. 1 is a diagrammatic cross-section of a thermoacoustic system for an aircraft interior according to a first embodiment known in the prior art;

FIG. 2 is a diagrammatic cross-section of a thermoacoustic system for an aircraft interior according to a second embodiment known in the prior art;

FIG. 3 is a diagrammatic cross-section of a thermoacoustic system for an aircraft interior in accordance with an embodiment of the invention;

FIG. 4 is an enlarged, diagrammatic cross-section of a portion of the thermoacoustic system shown in FIG. 3, providing enhanced detail associated with a clip connecting the second barrier layer to the first frame element;

FIG. 5 is a perspective view of the inside of a portion of a first embodiment of a thermoacoustic isolation module employed in the thermoacoustic system shown in FIG. 3;

FIG. 6 is a cross-section of the thermoacoustic isolation module shown in FIG. 5, the cross-section taken along line 6-6;

FIG. 7 is a cross-section of the thermoacoustic isolation module shown in FIG. 5, the cross-section taken along line 7-7;

FIG. 8 is a cross-section of a second contemplated embodiment of the thermoacoustic isolation module shown in FIG. 5;

FIG. 9 is a cross-section of a third contemplated embodiment of the thermoacoustic isolation module shown in FIG. 5;

FIG. 10 is a perspective view of one embodiment of a clip according to the present invention;

FIG. 11 is a top view of the clip shown in FIG. 10;

FIG. 12 is a diagrammatic cross-section of a thermoacoustic system of the present invention in which two thermoacoustic isolation modules are connected to an aircraft frame using the clip shown in FIG. 10; and

FIG. 13 is an enlarged diagrammatic cross-section of the thermoacoustic system of the present invention shown in FIG. 12, showing the clip in an installed position.

Detailed Description

The invention will now be described in connection with one or more embodiments. The discussion of specific embodiments is intended to highlight the breadth and scope of the present invention and not to limit the present invention thereto. It will be appreciated by those skilled in the art that the invention may be embodied with one or more equivalents and modifications to the embodiments described herein. Such equivalents and modifications are intended to be covered by the present invention.

In the following paragraphs, the present invention is described in connection with its deployment on an aircraft. Although the insulation, insulation system, insulation module, and insulation arrangement of the present invention are discussed in connection with an aircraft, the present invention may be used in other environments, including but not limited to trains, automobiles, ships, and the like.

In the drawings, aspects of the prior art and the present invention are discussed in connection with the interior of an aircraft and the exterior of an aircraft. The interior is expected to be coincident with the aircraft passenger cabin. The exterior is expected to be the ambient environment outside the aircraft.

Various elements and features shown in the drawings are identified by reference numerals. Where appropriate, similar elements and features have the same reference numerals. Although elements and features identified with the same reference numerals are expected to share the same characteristics from one figure to the next, it should be understood that the use of the same reference numerals in different figures is not intended to indicate that the identified structure is identical in each figure.

FIG. 1 is a cross-sectional view of a thermoacoustic system 10 according to one example known in the art.

The thermoacoustic system 10 includes three basic elements: (1) a first thermal isolation layer 12, (2) a second thermal isolation layer 14, and (3) an inner panel 16. The thermoacoustic system 10 is disposed against an interior surface of a fuselage 18 of the aircraft.

In the illustrated embodiment, the fuselage 18 may be constructed of aluminum or an alloy of aluminum. Alternatively, the fuselage 18 may be constructed from a composite material. Although these materials are contemplated for fuselage 18, other materials may be used, as will be apparent to those skilled in the art.

It is contemplated that the interior surface of fuselage 18 includes one or more first frame elements 20 and one or more second frame elements 22. As shown in fig. 1, first frame element 20 is U-shaped and is attached to an inner surface of fuselage 18. The U-shaped first frame member 20 includes an inner leg 24, a body 26 and an outer leg 28. Outer leg 28 is connected to the inner surface of fuselage 18. A second frame element 22 is shown as a stiffening element, which second frame element 22 is connected to the inner surface of the fuselage 18 and extends along the longitudinal axis of the fuselage.

The first thermal insulation layer 12 is shown as a single layer abutting against the inner surface of the fuselage 18. The first thermal isolation layer 12 is typically made of fiberglass or foam.

The second thermal isolation layer 14 abuts against the inner surface of the first thermal isolation layer 12. The second thermal isolation layer 14 is also made of fiberglass or foam.

In fig. 1, first thermal isolation layer 12 includes a first batt 30 and a second batt 32. First and second batting 30, 32 is disposed against an interior surface of fuselage 18, and as such, first and second batting 30, 32 provide a first thermal barrier to insulate the aircraft cabin from ambient temperatures. As will be apparent to those skilled in the art, the interior surface of fuselage 18 is typically covered with a plurality of first and second batting layers 30 and 32. For at least this reason, the first thermally insulating layer 12 is referred to as a "layer". As is apparent, the first thermal isolation layer 12 is not a continuous layer. Instead, the first thermal insulation layer 12 is divided into a plurality of sections by at least a first frame element 20 provided on the inner surface of the fuselage 18.

Similarly, the second thermal isolation layer 14 is not a continuous layer. As shown in fig. 1, the second thermal isolation layer 14 includes a first overburden portion 34 and a second overburden portion 36. The first overburden portion 34 includes a first overburden edge 38. Similarly, the second overburden portion 36 includes a second overburden edge 40. First cover portion 34 is disposed adjacent the inner surface of first batt 30. Second cover portion 36 is disposed adjacent the inner surface of second batt 32.

Further, as shown in fig. 1, a first cover layer edge 38 and a second cover layer edge 40 are attached to the inner leg 24 via clips 42. As shown, the clip 42 is a U-shaped member.

The inner panel 16 is disposed adjacent to the inner surface of the second thermal isolation layer 14. As shown in fig. 1, the inner panel 16 includes three layers: (1) an absorption layer 44, (2) a mass layer 46, and (3) a decorative layer 48. The absorbent layer 44, mass layer 46, and decorative layer 48 are configured to together form an integral component of the inner panel 16. The absorbent layer 44 is disposed adjacent the second thermal insulation layer 14 when the inner panel 16 is installed in an aircraft. Decorative layer 48 forms the interior surface of interior panel 16. Mass layer 46 is sandwiched between absorbing layer 44 and decorative layer 48.

The absorbent layer 44 may be made of felt or fiberglass.

The mass layer 46 may be made of rubber or vinyl.

The decorative layer 48 may be made of any material that presents a decorative appearance to a person within the aircraft cabin.

As will be apparent to those skilled in the art, the materials for the first and second thermal insulation layers 12, 14 are typically selected to ensure that the cabin is comfortable for humans by providing a suitable thermal barrier between the aircraft cabin and the surrounding environment. As is also apparent to those skilled in the art, it is also desirable to provide a suitable sound barrier between the aircraft cabin and the surrounding environment. The sound barrier helps to minimize noise within the aircraft cabin.

It is well known that when a mass layer is placed between a noise source and a person, the mass layer will absorb certain wavelengths of sound, and therefore, the mass layer will reduce the magnitude of the noise passing therethrough. In aircraft, the mass layer 46 is typically incorporated into the inner panel 16. Such a configuration is shown in fig. 1.

Fig. 2 shows a second configuration of a thermoacoustic system 50 known in the prior art. With respect to the construction of the inner panel 52, the thermoacoustic system 50 shown in FIG. 2 differs from the thermoacoustic system 10 shown in FIG. 1. Specifically, the inner panel 52 includes a first mass layer 54 and a second mass layer 56. More specifically, the inner panel 52 is configured such that the absorber layer 44 is sandwiched between a first mass layer 54 and a second mass layer 56, with the first mass layer 54 disposed on an outer surface of the absorber layer 44.

As is apparent from the foregoing, the prior art emphasizing quality layers 46, 54, 56 are typically incorporated into the inner panels 16, 52.

The present invention recognizes one aspect found in relation to positioning the mass layers 46, 54, 56 in the inner panels 16, 52. In particular, it has been found that noise can be reduced or mitigated to a greater extent if the mass layers 46, 54, 56 are repositioned from positions in the inner panels 16, 52 than is possible with the prior art thermoacoustic systems shown in FIGS. 1 and 2. More specifically, it has been found that noise propagation can be reduced if a mass layer having particular properties is selected, and if the mass layer is located at a position between the interior panels 16, 52 and the fuselage 18 of the aircraft.

FIG. 3 illustrates one contemplated embodiment of a thermoacoustic system 60 according to the present invention.

Similar to the thermoacoustic system 10, the thermoacoustic system 60 of the present invention includes three main features: (1)

a first barrier layer 62, (2) a second barrier layer 64, and (3) an inner panel 66.

It is contemplated that the first insulating layer 62 is similar to the first thermal insulating layer 12. Specifically, it is contemplated that the first insulation layer 62 is a thermal insulation layer made of fiberglass and/or foam.

In the illustrated embodiment, the first insulation layer 62 includes a first foam layer 68, a fiberglass layer 70, and a second foam layer 72. As shown, the fiberglass layer 70 is sandwiched between the first foam layer 68 and the second foam layer 72. This configuration should not be construed as limiting the invention as other configurations of the first barrier layer 62 are also contemplated for use in the thermoacoustic system 60.

As discussed in connection with the first thermal insulation layer 12, the first insulation layer 62 includes a first batt 74 and a second batt 76, the first batt 74 and the second batt 76 being located on both sides of the first frame member 20. Although only two batting layers 74, 76 are shown, first thermal insulation layer 62 includes a plurality of batting layers disposed adjacent to the interior surface of fuselage 18.

The second isolation layer 64 bonds the thermal isolation layer 78 to the mass layer 80.

It is contemplated that the thermal isolation layer 78 is constructed of fiberglass material. The glass fiber material is contemplated to be a nonwoven glass fiber web. However, it is also contemplated that the fiberglass material may be a woven material, or may be a hybrid construction combining woven and non-woven components.

The mass layer 80 is expected to be made of rubber or silicone. Other materials may also be used without departing from the scope of the invention.

Parameters relevant to the choice of material for the mass layer include, but are not limited to, flexibility, good sound absorption (or attenuation), and at least moderate (moderate) stiffness. The flexibility of the mass layer 80 facilitates installation of the second insulation layer 64 in the aircraft. As described above, the mass layer 80 is provided to reduce the transmission of sound therethrough. Thus, the material selected for the mass layer 80 is selected to provide good sound absorption and/or attenuation. Still further, in order to allow the second insulation layer 64 to be installed in the aircraft interior prior to installation of the inner panel 66, it is desirable that the mass layer 80 exhibit at least moderate stiffness. Some rigidity will prevent the mass layer 80 from yielding to gravity. If the insulation layer 64 is too loose, the insulation layer 64 may interfere with the installation of the inner panel 66. Therefore, for this reason, it is preferred that the mass layer 80 have at least moderate rigidity.

According to one embodiment, the expected mass layer 80 has about 0.4lb/ft²(16.86g/m²) The weight distribution of (c). The weight distribution may be at 0.4lb/ft²(16.86g/m²) Within a range of + -10% -20%. Thus, in one variation, the weight distribution ranges from 0.4lb/ft²(16.86g/m²) . + -. 10%, calculated to be about 0.36lb/ft²To 0.44lb/ft²(15.17g/m²To 18.54g/m²). In another variation, the weight distribution ranges from 0.4lb/ft²(16.86g/m²) 15%, calculated to be about 0.34lb/ft²To 0.46lb/ft²(14.33g/m²To 19.38g/m²). In another variation, the weight distribution ranges from 0.4lb/ft²(16.86g/m²) Plus or minus 20%, calculated to be about 0.32lb/ft²To 0.48lb/ft²(13.48g/m²To 20.23g/m²)。

It is expected that the thermal isolation layer 78 made of fiberglass will not contribute appreciably (or significantly) to the weight distribution of the second isolation layer 64, which second isolation layer 64 combines the thermal isolation layer 78 with the mass layer 80. Thus, the second barrier layer 64 is understood to satisfy the same weight distribution ranges listed above. Specifically, it is contemplated that the second barrier layer 64 has about 0.4lb/ft²(16.86g/m²) 10% -20% by weight distribution.

With continued reference to fig. 3, it is contemplated that the mass layer 80 is connected to the thermal isolation layer 78 by extruding the mass layer onto the thermal isolation layer 78. Since the thermal isolation layer 78 is expected to comprise non-woven glass fibers, the molten mass layer 80 will capture portions of the glass fibers, thereby connecting the two layers to one another. Still further, as will be apparent to those skilled in the art, one or more techniques may be employed to bond the mass layer 80 to the thermal isolation layer 78. For example, the mass layer 80 may be attached to the thermal isolation layer 78 by thermal and/or ultrasonic bonding at discrete points. In this embodiment, the thermal mass layer 80 may be added at specific points via an ultrasonic excitation or heating element, thereby melting the mass layer 80, allowing the mass layer to adhere to some of the glass fibers. Still further, the mass layer 80 may be attached to the thermal isolation layer 78 via a suitable adhesive. It is also contemplated that mass layer 80 may or may not be attached to thermal isolation layer 78.

As shown in fig. 3, the second isolation layer 64 includes a first capping layer 82 and a second capping layer 84. As will be apparent to those skilled in the art, the second barrier layer 64 is intended to include a plurality of cover layers in addition to the first cover layer 82 and the second cover layer 84 shown. The first cover layer 82 includes a first cover layer edge 86. Similarly, the second cover layer 84 includes a second cover layer edge 88. The first cover layer edge 86 and the second cover layer edge 88 are folded over the inner leg 24 of the first frame element 20 and connected to the first frame element 20 by a clip 90.

Fig. 4 is an enlarged view of clip 90, first cover layer edge 86, and second cover layer edge 88. As highlighted in this illustration, the first cover layer edge 86 includes a first isolation edge portion 92 and a first mass layer edge portion 94. Similarly, the second cover layer edge 88 includes a second isolation edge portion 96 and a second mass layer edge portion 98. The first cover layer edge 86 is secured against the outer surface of the inner leg 24 of the first frame element 20 by a clip 90. In addition, clips 90 secure second cover edge 88 against the inner surface of inner leg 24. By doing so, the first cover layer edge 86 and the second cover layer edge 88 provide a continuous barrier layer adjacent the inner leg 24 of the first frame element 20 to impede and/or prevent sound and/or temperature from propagating therethrough. In this illustration, arrow 100 provides an indication of the direction of propagation of sound through the thermoacoustic system 60. Arrow 100 also provides an indication of the temperature gradient across the thickness of the thermoacoustic system.

Fig. 3 also shows an inner panel 66. As shown, the inner panel 66 is positioned against an inner surface of the second barrier layer 64. The inner panel 66 contains decorative elements for the aircraft cabin.

FIG. 5 is a perspective view of the inside of a portion of a first embodiment of thermoacoustic isolation module 102 employed in thermoacoustic system 60 shown in FIGS. 3 and 4. Thermoacoustic isolation module 102 is a representative example of one contemplated embodiment and should not be construed as limiting the invention.

Thermoacoustic module 102 includes an envelope 104, envelope 104 enclosing thermal isolation layer 78 and mass layer 80. In fig. 5, the inner side of the thermal isolation layer 78 is shown facing upwards.

As will be apparent to those skilled in the art, it is contemplated that the envelope 104 is made of a suitable plastic or thermoplastic material. The envelope 104 is provided to minimize the absorption and/or retention of moisture by the thermal isolation layer 78 and/or the mass layer 80. In one contemplated embodiment, the envelope 104 does not allow moisture to pass through. In another contemplated embodiment, the envelope 104 may allow moisture to pass therethrough at least to some extent to maintain a suitable humidity within the envelope 104.

With continued reference to fig. 5, cuff 104 has a peripheral edge 106 defined by a peripheral seam 108. Although the peripheral edge 106 is illustrated as being offset from the peripheral seam 108, the peripheral edge 106 and the peripheral seam 108 may be co-located. Peripheral seam 108 may be created via thermal bonding and/or ultrasonic bonding. Other bonding techniques may also be employed without departing from the scope of the present invention.

Thermoacoustic module 102 includes a first partial seam 110, first partial seam 110 extending a first predetermined distance from peripheral edge 106 to an interior of thermoacoustic module 102. Still further, thermoacoustic module 102 includes a second partial seam 112, second partial seam 112 extending a second predetermined distance from peripheral edge 106 toward an interior of thermoacoustic module 102. It is contemplated that first partial seam 110 and second partial seam 112 are constructed via stitching that extends through thermoacoustic module 102 from an interior surface to an exterior surface. First partial seam 110 and second partial seam 112 are expected to provide structural stability to thermoacoustic module 102, which may aid in installation of thermoacoustic module 102 in an aircraft. In addition, first partial seam 110 and second partial seam 112 are intended to provide stability to thermoacoustic module 102 to help maintain the shape of thermoacoustic module 102 when thermoacoustic module 102 is connected to first frame element 20.

Although thermoacoustic module 102 is shown with first partial seam 110 and second partial seam 112, thermoacoustic module 102 may include any number of partial seams. Still further, a partial seam may extend from one location on peripheral seam 108 across thermoacoustic module 102 to another location on peripheral seam 108. Alternatively, it is contemplated that embodiments of thermoacoustic module 102 may not include any partial seams 110, 112 at all.

Furthermore, as shown in FIG. 5, thermoacoustic module 102 may include a third partial seam 114, which third partial seam 114 is structured as a frame having an "X" in its interior. As with other partial seams 110, 112, third partial seam 114 is expected to provide structural stability to thermoacoustic module 102 to facilitate mounting thermoacoustic module 102 against first barrier layer 62.

The thermoacoustic module may further include a fourth partial seam 116. Here, fourth partial seam 116 surrounds opening 118 through thermoacoustic module 102. Opening 118 may be positioned such that, for example, a conduit may pass through thermoacoustic module 102.

FIG. 6 is a cross-section of thermoacoustic isolation module 102 shown in FIG. 5, the cross-section being taken along line 6-6. The jacket 104 is shown with an outer packaging sheet 120 and an inner packaging sheet 122, the outer packaging sheet 120 and the inner packaging sheet 122 being joined together at a peripheral seam 108. As discussed above, the mass layer 80 is positioned adjacent to the outer surface of the thermal isolation layer 78.

FIG. 7 is a cross-section of thermoacoustic isolation module 102 shown in FIG. 5, the cross-section being taken along line 7-7. In this view, a first partial seam 110 is shown. Because the first partial seam 110 compresses the thermal isolation layer 78 and the mass layer 80, the thermal isolation layer 78 has two compressed regions 124.

FIG. 8 is a cross-section of a second contemplated embodiment of thermoacoustic isolation module 126 shown in FIG. 5. In this second embodiment, the mass layer 80 is disposed at an intermediate position between the outer surface of the thermal isolation layer 78 and the inner surface of the thermal isolation layer 78.

FIG. 9 is a cross-section of a third contemplated embodiment of thermoacoustic isolation module 128 shown in FIG. 5. In this third embodiment, the mass layer 80 is disposed adjacent to the inner surface of the thermal isolation layer 78.

With respect to the three embodiments of thermoacoustic isolation modules 102, 126, and 128, it is contemplated that the most suitable embodiment may be thermoacoustic isolation module 102. It has been found that sound attenuation increases as the distance between the mass layer 80 and the inner panel 66 increases. In other words, as the mass layer 80 moves closer to the inner surface of the fuselage 18, sound attenuation is improved.

FIG. 10 is a perspective view of one embodiment of a clip 130 according to the present invention.

The clip 130 is made as an integral unit from a suitable material, such as metal. The clip 130 includes a first end 132 and a second end 134. Between the first end 132 and the second end 134, the clip 130 includes a first inflection 136, a first straight section 138, a second inflection 140, a second straight section 142, a third inflection 144, a third straight section 146, a fourth inflection 148, and a fourth straight section 150. The clips 130 form substantially an R-shaped structure deployed as shown in fig. 13.

Fig. 11 is a top view of the clip shown in fig. 10.

FIG. 12 is a diagrammatic cross-section of thermoacoustic system 152 of the present invention in which thermoacoustic isolation module 102 is connected to the aircraft frame using clip 130 shown in FIG. 10. To cover the clip 130, an adhesive tape 154 is applied on top of the clip 130. Adhesive tape 154 is pressed against thermoacoustic module 102 and clip 130 in the direction of arrows 156, 158.

FIG. 13 is an enlarged diagrammatic cross-section of thermoacoustic system 152 of the present invention shown in FIG. 12, showing clip 130 in an installed position in enlarged detail.

As noted above with respect to fig. 4, the clip 130 secures the first and second cover edges 86, 88 against the inner leg 24 of the first frame element 20 in a manner that maintains a suitable thermoacoustic barrier between the aircraft cabin and the surrounding environment. Specifically, as noted, the thermal insulation layer 78 and the mass layer 80 are each secured against the inner leg 24 of the first frame member 24. As a result of this configuration, there is no isolation gap due to the presence of the first frame 20. Thus, the present invention provides a configuration that avoids (or at least minimizes) the following localized regions: in this local area, the isolation may be insufficient, thereby adversely affecting the comfort of the passengers.

As noted above, the present invention may be implemented in any of a variety of configurations without departing from the scope of the invention. Any and all equivalents and modifications obvious to those skilled in the art are intended to be covered by the present invention.