Stowage bin with shear fittings

Abstract

An aircraft stowage bin assembly includes shear fittings configured to route a content load from the bucket of the bin assembly to the airframe in the event of a forward load condition, such as a crash or severe turbulence. When the forward inertial load factor on the stowage bin is greater than about 1 g, the shear fittings create an efficient load path from the bucket to the airframe which bypasses the large metallic or composite endframes required by the designs of many conventional overhead stowage bins. As a result, significant reductions in overall bulk and weight, as well as lower manufacturing costs, can be realized.

Description

BACKGROUND

This disclosure relates generally to stowage bins and, more particularly, to overhead stowage bins in vehicle passenger cabins.

Modern passenger airplanes often include overhead stowage bins in the passenger cabin for storage of carry-on luggage and other items. Such bins are often mounted with numerous mountings located along the ceiling and sidewalls of the passenger cabin. These mountings are typically designed to support a predetermined amount of weight within the bins during normal flight conditions. In addition, the mountings are designed to keep the bins securely fastened to the airframe in the event of a crash or severe turbulence.

For example, current FAA regulations require that each baggage compartment have a means to protect occupants from injury by the contents of the compartment when the ultimate forward inertial load factor exceeds 9 g. To satisfy this requirement, conventional overhead stowage bins are often designed to bear their content load into large endframes during a forward load condition, such as a crash. These large endframes, in turn, typically route the loads to connecting panels attached to the airframe.

Such conventional designs are usually effective for preventing bins from detaching from their mountings and falling completely or allowing items to fall on passengers' heads during a forward load condition, such as a crash. On the other hand, these conventional designs also present a number of drawbacks. For example, conventional overhead stowage bins are often bulky and somewhat heavy. In addition, conventional overhead stowage bins can be rather costly to manufacture and assemble. These drawbacks are becoming increasingly significant, as aircraft designers strive to develop more and more efficient aircraft designs.

BRIEF DESCRIPTION

The above-mentioned drawbacks associated with existing overhead stowage bins are addressed by embodiments of the present invention, which will be understood by reading and studying the following specification.

In one embodiment, a stowage bin assembly comprises an upper panel comprising one or more first shear fitting components, a lower panel comprising one or more first shear fitting components, and a bucket comprising one or more second shear fitting components. The bucket is configured to cooperate with the upper panel and the lower panel such that, when the bin assembly is in a closed position, the first shear fitting components engage with the second shear fitting components to create a plurality of shear fittings capable of withstanding a substantial shear force between the bucket and the panels of the bin assembly.

In another embodiment, an aircraft overhead stowage bin comprises at least one support panel mounted to an interior portion of an airframe and one or more side panels coupled to at least one support panel. The aircraft overhead stowage bin further comprises a bucket coupled to the one or more side panels, the bucket configured to contain a selected weight load, as well as means for routing the weight load from the bucket directly to the at least one support panel mounted to the airframe under a forward load condition.

In another embodiment, an aircraft comprises an airframe and one or more stowage bin assemblies mounted to the airframe. Each stowage bin assembly is configured to contain a selected weight load. In addition, each stowage bin assembly comprises one or more shear fittings configured to transfer the weight load directly from the stowage bin assembly to the airframe under a forward load condition.

In another embodiment, a method of securing a stowage bin within an aircraft comprises providing at least one support panel coupled to an airframe and providing a bucket coupled to the at least one support panel and configured to contain a selected weight load. The method further comprises securing the bucket to the at least one support panel with one or more shear fittings which, in the event of a forward load condition, transfer the weight load directly from the bucket to the at least one support panel coupled to the airframe.

The details of one or more embodiments of the claimed invention are set forth in the accompanying drawings and the description below. The features, functions, and advantages can be achieved independently in various embodiments of the claimed invention, or may be combined in yet other embodiments.

DRAWINGS

FIG. 1 is a perspective view of overhead stowage bin assemblies including shear fittings.

FIG. 2A is an end cross-sectional view of the shear fitting illustrated in FIG. 1 in an open position.

FIG. 2B is an end cross-sectional view of the shear fitting illustrated in FIG. 1 in a closed position.

FIG. 3A is a perspective view of the shear fitting illustrated in FIG. 1 in an open position.

FIG. 3B is a perspective view of the shear fitting illustrated in FIG. 1 in a closed position.

FIG. 4 illustrates one exemplary alternative embodiment of the shear fitting illustrated in FIG. 1.

FIG. 5A is a block diagram illustrating the load path of a conventional overhead stowage bin under a forward load condition, such as a crash.

FIG. 5B is a block diagram illustrating the load path of a stowage bin assembly with shear fittings under a forward load condition, such as a crash.

FIG. 6B is a schematic of an aircraft including overhead stowage bin assemblies with shear fittings.

Like reference numbers and designations in the various drawings indicate like elements.

DETAILED DESCRIPTION

In the following detailed description, reference is made to the accompanying drawings that form a part hereof, and in which is shown by way of illustration specific illustrative embodiments in which the invention may be practiced. These embodiments are described in sufficient detail to enable those skilled in the art to practice the invention, and it is to be understood that other embodiments may be utilized and that logical, mechanical, and electrical changes may be made without departing from the spirit and scope of the present invention. The following detailed description is, therefore, not to be taken in a limiting sense.

FIG. 1 is a perspective view of one embodiment of overhead stowage bin assemblies 100 including shear fittings 105. For purposes of illustration in this disclosure, the bin assemblies 100 are described primarily with reference to an aircraft, such as, for example, the aircraft 600 illustrated in FIG. 6. The bin assemblies 100 can also be used, however, in other passenger vehicles, such as buses, trains, ships, etc.

For illustrative purposes, a reverse view of the bin assemblies 100 is shown, i.e., a view from the perspective of one located behind the bin assemblies 100 rather than the perspective of a passenger. In addition, a first bin assembly 100A is shown in a closed position, and a second bin assembly 100B is shown in an open position.

In the illustrated embodiment, each bin assembly 100 comprises an upper panel 110, a lower panel 115, two side panels 120, and a bucket 125. Each shear fitting 105 comprises a male component 130 and a female component 135, which become engaged when the bucket 120 is closed, as described in more detail below.

If desired, the bin assembly 100 can be designed to have a traditional appearance and to be operated by passengers and flight crew in the same way as a conventional overhead stowage bin. For example, the upper panel 110, lower panel 115, and side panels 120 can be fabricated from a variety of suitable materials, such as composites, plastics, etc., and can be mounted to the ceiling and sidewalls of an aircraft passenger cabin using a variety of conventional techniques that are well-known to those of ordinary skill in the art. Exemplary mounting hardware 140 is illustrated in FIG. 1.

Similarly, the bucket 125 can be fabricated from a variety of well-known materials and can be designed to cooperate with the upper panel 110, lower panel 115, and side panels 120 using conventional techniques. For example, in the illustrated embodiment, the bucket 120 includes a standard pivot mechanism near the back and a latch mechanism near the front (not shown) such that the bin assembly 100 can be opened and closed by operating the latch and rotating the bucket about the pivot, in a manner that is familiar to many airline passengers and flight crew. In other embodiments, the bin assembly 100 can be opened and closed with an articulating mechanism or any other suitable mechanism for opening and closing the bin assembly 100.

FIGS. 2 and 3 illustrate the embodiment of the shear fitting 105 shown in FIG. 1 in more detail. Specifically, FIG. 2A is an end cross-sectional view of the shear fitting 105 in an open position, and FIG. 2B is an end cross-sectional view of the shear fitting 105 in a closed position. FIG. 3A is a perspective view of the shear fitting 105 in an open position, and FIG. 3B is a perspective view of the shear fitting 105 in a closed position. For illustrative purposes, FIGS. 3A and 3B show the shear fitting 105 without the surrounding bin structures or support panels.

The shear fitting 105 comprises a male component 130 and a female component 135. In the illustrated embodiment, the male component 130 is attached to the bucket 125 of the bin assembly 100, and the female component 135 is attached to a support panel 200 of the bin assembly 100, such as the upper panel 110 or the lower panel 115. In other embodiments, the female component 135 may be attached to the bucket 125, and the male component 130 may be attached to the support panel 200.

In some embodiments, the shear fitting 105 is designed such that the male component 130 engages with the female component 135 when the bin assembly 100 is closed, as illustrated in FIGS. 2 and 3. When so engaged, the shear fitting 105 is preferably designed to withstand a substantial shear force between the bucket 125 and the corresponding support panel 200 of the bin assembly 100. Thus, when the bin assembly 100 experiences a forward load condition, such as a forward inertial load factor greater than about 1 g, the shear fitting 105 creates an efficient load path for the contents of the bin assembly 100, as described in more detail below.

The male component 130 and the female component 135 of the shear fitting 105 may comprise any suitable material, such as, for example, metals (e.g., aluminum, steel, etc.), alloys, composites, etc. In addition, the male component 130 and the female component 135 of the shear fitting 105 can be attached to the corresponding structure of the bin assembly 100 using any suitable method.

For example, in the illustrated embodiment, the male component 130 of the shear fitting 105 is surface mounted to the bucket 125 with a bonding adhesive and suitable fasteners, such as screws, rivets, etc. The female component 135 of the shear fitting 105 is embedded within the support panel 200 of the bin assembly 100 by first creating a cavity 205 within the support panel 200. The female component 135 is then mounted to the back surface of the support panel 200 using a bonding adhesive and suitable fasteners, such as screws, rivets, etc. Many other suitable mounting configurations and techniques can be implemented for attaching the male component 130 and the female component 135 of the shear fitting 105 to the corresponding structure of the bin assembly 100.

In some embodiments, the male component 130 and the female component 135 of the shear fitting 105 can be formed as integral parts of the bucket 125 and support panel(s) 200 of the bin assembly 100 during the manufacturing process. For example, if the bucket 125 is manufactured using an injection molding process, the mold can be modified to include the male component 130 or female component 135 of the shear fitting 105, such that the appropriate component is formed as an integral part of the bucket 125 during manufacture.

In the illustrated embodiment, the male component 130 of the shear fitting 105 comprises a single extension having a thick portion 210 near the base and a thinner portion 215 near the tip. The female component 135 of the shear fitting 105 comprises a single groove 220 having a complementary cross-sectional profile to accommodate the male component 130. While this particular configuration presents certain structural advantages, numerous other suitable configurations are possible.

For example, one alternative embodiment is illustrated in FIG. 4, in which the male component 130 of the shear fitting 105 comprises multiple extensions, and the female component 135 comprises a corresponding number of grooves. In other embodiments, the shear fitting 105 may comprise a mortise and tenon joint. As another example, the cross-sectional profile of the extension(s) and groove(s) may vary widely to optimize the performance of the shear fitting 105 in a given setting. For example, the male component 130 may comprise an angled or curved extension, if desired. Many other possible configurations of the shear fitting 105 will become apparent to those of ordinary skill in the art in view of the present disclosure, and are within the scope of this application.

FIG. 5A is a block diagram illustrating the load path 405 of a conventional overhead stowage bin under a forward load condition, such as a crash. As illustrated, in the event of a forward load condition, the contents of the stowage bin apply a forward content load 410 within the bin. In some circumstances, the forward content load 410 can be quite significant. Therefore, current FAA regulations require that each overhead stowage bin be able to withstand an ultimate forward inertial load factor of 9 g.

One common approach for satisfying this requirement is illustrated in FIG. 5A. As shown, when the contents of the stowage bin apply a forward content load 410, the bin channels the load 410 through a pivot boss 415 forward through the cabin until it reaches a large metallic or composite endframe 420 which, in turn, typically routes the load 410 to connecting panels attached to the airframe 425, thereby creating the load path 405 illustrated in FIG. 5A.

FIG. 5B, by contrast, is a block diagram illustrating the load path 405 of a stowage bin assembly 100 with shear fittings 105 under a forward load condition, according to one embodiment of the present application. As shown, when the contents of the bin assembly 100 apply a forward content load 410, it is transferred to the shear fittings 105 which, in turn, route the load 410 directly to one or more support panels 200 (e.g., upper panel 110 or lower panel 115) attached to the airframe 425, thereby creating the load path illustrated in FIG. 5B. Thus, the shear fittings 105 create a more efficient load path 405 to the airframe 425 under forward load conditions, resulting in a number of advantages over conventional overhead stowage bins.

For example, as illustrated in FIG. 1, the bin assembly 100 with shear fittings 105 can advantageously be designed without a strongback, or rear, panel. In conventional overhead stowage bin design, a strongback panel is often necessary to provide sufficient structural support to satisfy the regulatory requirements for forward load conditions. By eliminating the need for a strongback panel, the shear fittings 105 can advantageously reduce the overall bulk and weight of the stowage bin assemblies 100. This can also simplify and lower the cost of the manufacturing process for the bin assemblies 100.

In addition, the shear fittings 105 create a load path 405 that bypasses the large metallic or composite endframes 420 typically required to handle forward loads in conventional overhead stowage bin design. As a result, certain endpanels can be made smaller or eliminated altogether, since they are used primarily for only vertical and lateral loads. Hence, the bin assembly 100 with shear fittings 105 advantageously enables additional reductions in overall bulk and weight within the passenger cabin, as well as additional cost savings in materials and labor.

Although this invention has been described in terms of certain preferred embodiments, other embodiments that are apparent to those of ordinary skill in the art, including embodiments that do not provide all of the features and advantages set forth herein, are also within the scope of this invention. Accordingly, the scope of the present invention is defined only by reference to the appended claims and equivalents thereof.

Claims

1. A stowage bin assembly comprising:

an upper panel comprising one or more first shear fitting components;

a lower panel comprising one or more first shear fitting components; and

a bucket comprising one or more second shear fitting components,

wherein the bucket is configured to cooperate with the upper panel and the lower panel such that, when the bin assembly is in a closed position, the first shear fitting components engage with the second shear fitting components to create a plurality of shear fittings capable of withstanding a substantial shear force between the bucket and the panels of the bin assembly.

2. The stowage bin assembly of claim 1, wherein the first shear fitting components comprise female components and the second shear fitting components comprise male components.

3. The stowage bin assembly of claim 1, wherein the first shear fitting components comprise male components and the second shear fitting components comprise female components.

4. The stowage bin assembly of claim 1, wherein the first and second shear fitting components comprise metal.

5. The stowage bin assembly of claim 1, wherein the first and second shear fitting components comprise a composite material.

6. The stowage bin assembly of claim 1, wherein the first shear fitting components are mounted on a back surface of the upper panel and lower panel and engage with the second shear fitting components through one or more cavities in the upper panel and lower panel.

7. The stowage bin assembly of claim 1, wherein the second shear fitting components are surface mounted to the bucket.

8. The stowage bin assembly of claim 1, wherein the shear fitting components are mounted to the upper panel, the lower panel, and the bucket with a bonding adhesive and one or more screws or rivets.

9. The stowage bin assembly of claim 1, wherein the first shear fitting components are formed as an integral part of the upper panel and lower panel.

10. The stowage bin assembly of claim 1, wherein the second shear fitting components are formed as an integral part of the bucket.

11. The stowage bin assembly of claim 1, wherein each second shear fitting component comprises one extension having a thick portion near its base and a thinner portion near its tip.

12. The stowage bin assembly of claim 11, wherein each first shear fitting component comprises one groove configured to engage with the extension of the second shear fitting components.

13. The stowage bin assembly of claim 1, wherein the shear fittings are capable of withstanding a forward inertial load factor of at least about 9 g.

14. The stowage bin assembly of claim 1, wherein the stowage bin assembly lacks a strongback panel.

15. The stowage bin assembly of claim 1, wherein the stowage bin assembly is configured for use in an aircraft.

16. The stowage bin assembly of claim 1, wherein the stowage bin assembly is configured for use in a bus, a train, or a ship.

17. An aircraft overhead stowage bin comprising:

at least one support panel mounted to an interior portion of an airframe;

one or more side panels coupled to the at least one support panel;

a bucket coupled to the one or more side panels, the bucket configured to contain a selected weight load; and

means for routing the weight load from the bucket directly to the at least one support panel mounted to the airframe under a forward load condition.

18. The aircraft overhead stowage bin of claim 17, wherein the means for routing the weight load comprises one or more shear fittings.

19. The aircraft overhead stowage bin of claim 17, wherein the forward load condition comprises a forward inertial load factor on the overhead stowage bin which is greater than about 1 g.

20. An aircraft comprising:

an airframe; and

one or more stowage bin assemblies mounted to the airframe, each stowage bin assembly configured to contain a selected weight load,

wherein each stowage bin assembly comprises one or more shear fittings configured to transfer the weight load directly from the stowage bin assembly to the airframe under a forward load condition.

21. The aircraft of claim 20, wherein the forward load condition comprises a forward inertial load factor on the one or more stowage bin assemblies which is greater than about 1 g.

22. The aircraft of claim 20, wherein the one or more shear fittings comprise metal.

23. The aircraft of claim 20, wherein the one or more shear fittings comprise a composite material.

24. The aircraft of claim 20, wherein the one or more stowage bin assemblies lack a strongback panel.

25. The aircraft of claim 20, wherein the aircraft lacks an endframe configured to route the weight load to the airframe under a forward load condition.

26. A method of securing a stowage bin within an aircraft, the method comprising:

providing at least one support panel coupled to an airframe;

providing a bucket coupled to the at least one support panel and configured to contain a selected weight load; and

securing the bucket to the at least one support panel with one or more shear fittings which, in the event of a forward load condition, transfer the weight load directly from the bucket to the at least one support panel coupled to the airframe.

27. The method of claim 26, wherein the at least one support panel and the bucket comprise a composite material.

28. The method of claim 26, wherein the one or more shear fittings comprise metal.

29. The method of claim 26, wherein the one or more shear fittings comprise a composite material.

30. The method of claim 26, wherein the forward load condition comprises a forward inertial load factor which is greater than about 1 g.