Patent Publication Number: US-2023159170-A1

Title: Installment System for Overhead Bins

Description:
CROSS-REFERENCE TO RELATED APPLICATIONS 
     This application claims the benefit of priority of U.S. Provisional Patent Application No. 63/281,222 entitled Quick Installation and Removal of Overhead Bins and filed on Nov. 19, 2021, the disclosure of which is herein incorporated by reference in its entirety. 
    
    
     BACKGROUND OF THE INVENTION 
     1. Field 
     The disclosed embodiments relate generally to storage components. More specifically, the embodiments relate to easily installable and removable overhead bins for aircraft. 
     2. Description of the Related Art 
     Removable overhead stowage bins for use in aircraft are known. For example, U.S. Pat. No. 9,169,019 to Costabel discloses a fastening system having a first bracket that attaches to an overhead storage bin, a second bracket that attaches to a supporting structure, a pin that connects the first and second brackets, and a spring to lock the pin in place. U.S. Pat. No. 6,769,831 to Aquino et al. discloses a quick-disconnect fastener assembly for installing stowage bins having a tubular connector that engages a pin; the tubular connector can be rotated in a first direction to lock the pin and in the opposite direction to unlock the pin. U.S. Pat. No. 5,842,668 to Spencer discloses a quick fit overhead stowage compartment having one hook and two clevis fittings on each end of a stowage bin that are fastened with a tie rod. U.S. Pat. No. 3,666,214 to Matuska discloses quickly removable storage bins having a snubber pivotably connected at an upper end to the storage bin and at a lower end to a lever, with the lever and the snubber being connected to a pivot pin. 
     SUMMARY 
     This summary is provided to introduce a selection of concepts in a simplified form that are further described below in the detailed description. This summary is not intended to identify key features or essential features of the claimed subject matter, nor is it intended to be used to limit the scope of the claimed subject matter. Other aspects and advantages of the invention will be apparent from the following detailed description of the embodiments and the accompanying drawing figures. 
     In an embodiment, an installment system for an overhead bin in an aircraft includes: a liner disposed on an underside of a cabin ceiling of the aircraft; a receptacle mechanically coupled to a structure above the cabin ceiling via a bracket, wherein the receptacle protrudes through an opening in the liner; a bin having a top side with at least one attachment point, the at least one attachment point including: a stud mechanically coupled to the top side; and a screw disposed within the stud, wherein the stud includes a rounded flange configured to insert into the receptacle for removably securing the bin beneath the liner. 
     In another embodiment, an installation method for an overhead bin in an aircraft is provided, wherein the overhead bin includes at least one stud on a top side of the overhead bin and a ceiling of the aircraft includes at least one receptacle, the installation method includes: raising the overhead bin to engage the at least one stud with the at least one receptacle; sliding the overhead bin in an outboard direction for inserting the at least one stud into a narrow portion of the at least one receptacle; and turning a screw disposed within the at least one stud in a first direction for increasing a tension within the at least one receptacle, thereby securing the overhead bin beneath the ceiling. 
     In yet another embodiment, a removable overhead bin for use in an aircraft includes: a plurality of brackets mounted to an overhead structure above a ceiling in the aircraft; a liner disposed on an underside of the ceiling, wherein the liner includes a finished surface visibly exposed inside the aircraft; a plurality of receptacles each mechanically coupled to a respective one of the brackets, wherein the liner includes a plurality of openings configured to each receive a respective one of the receptacles for protruding through the liner; and a removable bin having a top side with a plurality of attachment points, each of the attachment points including: a stud mechanically coupled to the top side, wherein the stud includes an exposed end having a larger diameter configured for inserting into a respective one of the receptacles; and a screw disposed within the stud, wherein the screw is configured for turning thereby tightening the stud within the receptacle for removably securing the removable bin beneath the liner. 
    
    
     
       BRIEF DESCRIPTION OF THE SEVERAL VIEWS OF THE DRAWINGS 
       Illustrative embodiments are described in detail below with reference to the attached drawing figures, which are incorporated by reference herein and wherein: 
         FIG.  1    illustrates an aircraft cabin comprising overhead bins installed above a seating area for some embodiments; 
         FIG.  2    illustrates an overhead bin for some embodiments; 
         FIG.  3 A  illustrates an attaching mechanism for installing the overhead bin into the aircraft for some embodiments; 
         FIG.  3 B  illustrates a stud and a screw for the attaching mechanism for some embodiments; 
         FIG.  3 C  illustrates a mating receptacle for the attaching mechanism for some embodiments; 
         FIG.  3 D  provides a cross-sectional view of the mating receptacle, the stud, and the screw for some embodiments; 
         FIG.  3 E  illustrates a close-up view of the attaching mechanism and the overhead bin for some embodiments; and 
         FIG.  4    illustrates an exemplary method for installing the overhead bin in an aircraft for some embodiments. 
     
    
    
     The drawing figures do not limit the invention to the specific embodiments disclosed and described herein. The drawings are not necessarily to scale, emphasis instead being placed upon clearly illustrating the principles of the invention. 
     DETAILED DESCRIPTION 
     The following detailed description references the accompanying drawings that illustrate specific embodiments in which the invention can be practiced. The embodiments are intended to describe aspects of the invention in sufficient detail to enable those skilled in the art to practice the invention. Other embodiments can be utilized and changes can be made without departing from the scope of the invention. 
     The following detailed description is, therefore, not to be taken in a limiting sense. The scope of the invention is defined only by the appended claims, along with the full scope of equivalents to which such claims are entitled. 
     In this description, references to “one embodiment,” “an embodiment,” or “embodiments” mean that the feature or features being referred to are included in at least one embodiment of the technology. Separate references to “one embodiment,” “an embodiment,” or “embodiments” in this description do not necessarily refer to the same embodiment and are also not mutually exclusive unless so stated and/or except as will be readily apparent to those skilled in the art from the description. For example, a feature, structure, act, etc. described in one embodiment may also be included in other embodiments, but is not necessarily included. Thus, the technology can include a variety of combinations and/or integrations of the embodiments described herein. 
     Embodiments are generally directed to an installment system for a removable overhead bin. The overhead bin may be used in aircraft and installed beneath the ceiling in the cabin for forming an overhead storage area. The overhead bin may comprise a plurality of attachment points for installing into the ceiling area. Each attachment point may comprise a stud connected to the overhead bin, a receptacle disposed in the overhead storage area, and a screw. The studs and the receptacles may be configured to carry substantially all the loads imparted onto the overhead bin. For installation, the overhead bin may be raised and slid in an outboard direction to insert the stud with the receptacle. Each stud may then be secured with the screw (e.g., via a screwdriver). By providing a quick and easy installation method that requires the use of a single tool, the aircraft may be adaptable to varying use cases. If less weight and more overhead space are desired, the overhead bins may be quickly removed to reduce weight and increase overhead cabin space even for an individual trip. 
       FIG.  1    illustrates a portion of an aircraft cabin  100  for some embodiments. Not all portions of aircraft cabin  100  are shown in  FIG.  1    for clarity of illustration. As shown, aircraft cabin  100  may comprise a seating region  102  adjacent windows, which may comprise seats, couches, tables, consoles, and/or benches (not shown). Above seating region  102 , overhead bins  104  may be installed. As illustrated, in some embodiments, aircraft cabin  100  may be configured for five overhead bins  104  to be installed on a side of aircraft cabin  100 . Broadly, any number of overhead bins  104  may be installed into aircraft cabin  100 . In some embodiments, overhead bins  104  are configured to store luggage, supplies, and the like. 
     Aircraft cabin  100  may also comprise liner  106 . Liner is disposed on an underside of the ceiling in aircraft cabin  100 . In some embodiments, liner  106  is disposed on the interior ceiling and wall panels. When overhead bins  104  are installed, liner  106  may be disposed substantially above and curve behind the overhead bins  104 . When overhead bins  104  are removed from aircraft cabin  100 , liner  106  is visible to occupants of the cabin. In some embodiments, liner  106  provides a finished and aesthetically pleasing appearance within the interior of aircraft cabin  100 . In some embodiments, liner  106  comprises wood paneling, veneers, leather, fabric, carpet, vinyl, or any combination thereof. 
     Typical aircraft cabins are unfinished behind any overhead stowage, thereby presenting an unpleasing appearance when exposed. However, because liner  106  presents a finished interior, overhead bins  104  may be removed without detracting from the aesthetics of aircraft cabin  100 . As such, overhead bins  104  may be removed to reduce weight and/or to alter the aircraft configuration without detracting from the passenger experience. 
       FIG.  2    illustrates overhead bin  104  for some embodiments. Overhead bin  104  may be substantially rectangular. In some embodiments, overhead bin  104  is one of a shelf, a pivot, or a translating stowage bin. Overhead bin  104  may comprise a front face  202  comprising a handle  204  thereon. Handle  204  may be actuated by a user to open overhead bin  104 , thereby exposing a cavity (not shown) in which luggage or other items may be stored. Overhead bin  104  may further comprise top face  206 , left face  208 , right face  210 , and back face  212 . Back face  212  may be disposed substantially opposite to front face  202 . In some embodiments, top face  206  and back face  212  are formed from the same piece of material. In some embodiments, the transition between top face  206  and back face  212  is rounded or arcuate. Top face  206 , left face  208 , and right face  210  may be substantially perpendicular to front face  202  and back face  212 . Left face  208  and right face  210  may be substantially opposite one another. Top face  206  may be substantially perpendicular to left face  208  and right face  210 . Front face  202  may be disposed substantially opposite to back face  212 . 
     Top face  206  may comprise a first attachment point  214   a,  a second attachment point  214   b,  a third attachment point  214   c,  and a fourth attachment point  214   d.  It should be noted that overhead bin  104  is not limited to four attachment points and may comprise any number of attachment points. As discussed below with respect to  FIGS.  3 A- 3 D , attachment points  214   a,    214   b,    214   c,    214   d  may be configured for installing overhead bin  104  within aircraft cabin  100 . In some embodiments, first attachment point  214   a  is disposed on top face  206  near left face  208  and back face  212 . In some embodiments, second attachment point  214   b  is disposed on top face  206  near left face  208  and front face  202 . In some embodiments, third attachment point  214   c  is disposed on top face  206  near right face  210  and back face  212 . In some embodiments, fourth attachment point  214   d  is disposed on top face  206  near right face  210  and front face  202 . 
     Overhead bin  104  may comprise a first bracket  216   a,  a second bracket  216   b,  a third bracket  216   c,  and a fourth bracket  216   d  installed thereon. In some embodiments, first bracket  216   a  corresponds to first attachment point  214   a,  second bracket  216   b  corresponds to second attachment point  214   b,  third bracket  216   c  corresponds to third attachment point  214   c,  and fourth bracket  216   d  corresponds to fourth attachment point  214   d.  In some embodiments, brackets  216   a - d  are intercostal structure configured to carry loads between aircraft structure frames. In some embodiments, brackets  216   a - d  are disposed above liner  106 , between an interior ceiling of aircraft cabin  100  and the exterior of the aircraft body. In some embodiments, brackets  216   a - d  are permanently fastened to girders, frames, and/or struts in the fuselage structure via fasteners such as rivets. 
     In some embodiments, overhead bin  104  comprises a length from left face  208  to right face  210  of about 3 ft to about 5 ft. In some embodiments, overhead bin  104  comprises a depth from front face  202  to back face  212  of about 1 ft to about 3 ft. In some embodiments, overhead bin  104  comprises a height from a bottom face (not shown) of overhead bin  104  to top face  206  of about 0.5 ft to about 1.5 ft. In some embodiments, overhead bin  104  is fabricated from composites (e.g., honeycomb core), thermosets, thermoplastics, metals, metal alloys, or any combination thereof 
       FIG.  3 A  illustrates fourth attachment point  214   d  for some embodiments. In some embodiments, attachment points  214   a,    214   b,    214   c,    214   d  are substantially similar. In some embodiments, fourth attachment point  214   d  comprises a stud  302 , a screw  304 , and a mating receptacle  306 . Stud  302  may comprise internal threads configured to receive a screw  304  therein. In some embodiments, mating receptacle  306  is mounted in liner  106  and operably connected to fourth bracket  216   d  as described below with respect to  FIGS.  3 C- 3 D . In some embodiments, liner  106  comprises an opening  307  for receiving mating receptacle  306  therein. Stud  302  and mating receptacle  306  used at attachment points  214   a - d  may be configured to carry loads applied to overhead bin  104  (e.g., the weight of bin  104  plus the weight of any items stowed therein). In some embodiments, stud  302  and mating receptacle  306  are larger than typical components used for aircraft stowage as discussed further below. In some embodiments, attachment points  214   a - d  are configured to carry loads of about 100-lbs. 
     Bracket  308  may be used to affix stud  302  and screw  304  to overhead bin  104 . Bracket face  310  may abut against an inside surface of left face  208  or right face  210  of overhead bin  104  (see  FIG.  3 E ) and be secured thereto via screws, bolts, rivets, and the like. Fourth attachment point  214   d  may also comprise a first nut  312   a  on a top face  314  of bracket  308 , and a second nut  312   b  on a bottom face  316  of bracket  308 . Bracket  308  may comprise an opening therethrough (not shown) for receiving stud  302  and screw  304 . 
       FIG.  3 B  illustrates stud  302  and screw  304  for some embodiments with stud  302  partially transparent for clarity of illustration. As shown, screw  304  may be inserted into an opening of stud  302  at a stud distal end  318  such that only a head of screw  304  protrudes from stud distal end  318 . Stud  302  may be threaded on an outer surface. A screw distal end  320  may protrude from a stud proximal end  322 . Screw  304  may comprise a screw end  324  at screw distal end  320  that engages within a receptacle hole  326  (see  FIG.  3 C ) of mating receptacle  306 . 
     In embodiments, stud proximal end  322  provides an exposed end configured to engage with a slot  329  (see  FIG.  3 A  and  FIG.  3 C ) in mating receptacle  306 . Specifically, stud proximal end  322  may comprise a rounded flange having a larger diameter configured for inserting within slot  329 . In some embodiments, stud proximal end  322  comprises a width of about 17 mm to about 21 mm. In some embodiments, stud distal end  318  comprises a width of about 6 mm to about 10 mm. In some embodiments, stud  302  comprises a height of about 17 mm to about 21 mm. 
       FIG.  3 C  illustrates mating receptacle  306  for some embodiments. Portions of the assembly for mounting mating receptacle  306  and fourth bracket  216   d  have been omitted for clarity of illustration. As described above, mating receptacle  306  may be substantially circular or dome-shaped. In some embodiments, mating receptacle  306  comprises a width of about 40 mm to about 50 mm. In some embodiments, mating receptacle  306  comprises a height of about 8 mm to about 12 mm. In some embodiments, mating receptacle  306  is an anchor mating receptacle. In embodiments, mating receptacle  306  comprises receptacle hole  326  configured to receive screw end  324  when overhead bin  104  is installed in aircraft cabin  100 , and mating receptacle  306  comprises slot  329  configured to receive stud proximal end  322 , as best viewed in  FIG.  3 D . 
       FIG.  3 D  provides a cross-sectional view of mating receptacle  306 , stud  302 , screw  304 , and receptacle hole  326 . Receptacle hole  326  is a through-hole, as depicted in  FIG.  3 D , but receptacle hole  326  could, in embodiments, be a shallow hole, a cut out, a scoop, or an indent configured to receive stud proximal end  322 . 
     Returning to  FIG.  3 C , slot  329  may be configured with a wide opening at both ends such that mating receptacle  306  may be used on either side of the aircraft for receiving stud  302 . Slot  329  may also comprise a narrow portion  327  where stud proximal end  322  is secured upon installment. Mating receptacle  306  may be mounted within liner  106  via receptacle fasteners  328 . In some embodiments, fourth bracket  216   d  is coupled to mating receptacle  306  via bracket fasteners  330 . In some embodiments, bracket fasteners  330  are configured as acoustic isolators to provide sound dampening. In some embodiments, a mounting bracket  332  is disposed above mating receptacle  306 , and bracket fasteners  330  mounted thereto. Brackets  216   a,    216   b ,  216   c  may be connected to attachment points  214   a,    214   b,    214   c  in a substantially similar manner as described above with respect to fourth bracket  216   d.    
     In operation, turning of screw  304  is used engage stud  302  within mating receptacle  306 . For example, turning of screw  304  in a first direction engages the screw end  324  into receptacle hole  326  and the rounded flange of stud proximal end  322  is tightened within the narrow portion of slot  329 . The head of screw  304  is tightened securing it against stud  302 . In some embodiments, screw  304  is partially engaged upon installment of overhead bin  104 . As such, when overhead bin  104  is installed, an installer simply has to fully engage screw  304  (e.g., with a screwdriver), thereby tightening fourth attachment point  214   d  into place. Screw  304  may be fully engaged by hand, with a screwdriver, with a hex driver, or with a drill, for example. Turning of screw  304  in a second direction opposite the first direction loosens screw  304  thereby decreasing tension against stud  302 , then disengages screw  304  from hole  326  enabling its removal therefrom. 
       FIG.  3 E  illustrates a close-up view of fourth attachment point  214   d  for some embodiments. For clarity of illustration, top face  206  is illustrated semi-transparently, and liner  106  and front face  202  have been omitted from  FIG.  3 E . As described above, bracket face  310  may abut against the inside surface of right face  210  and may be secured thereto. Similarly, for first attachment point  214   a  and second attachment point  214   b,  bracket face  310  may abut against the inside surface of left face  208  and may be secured there to. Top face  206  may comprise an opening therethrough (not shown) through which bracket  308  may be inserted such that bottom face  316  abuts against top face  206  as shown. Also illustrated in  FIG.  3 E  are bracket fasteners  330  for connecting fourth bracket  216   d  to fourth attachment point  214   d.  In some embodiments, bracket fasteners  330  comprise any combination of washers, brackets, nuts, screws, or bolts. As shown, bracket fasteners  330  may abut against mounting bracket  332 . Washers  334  may also be present for connecting mating receptacle  306  and fourth bracket  216   d  in overhead bin  104 . In some embodiments, washers  334  are disposed between fourth bracket  216   d  and mating receptacle  306 . In some embodiments, washers  334  are configured to close out visibility from aircraft cabin  100  to the rest of the aircraft structure. In some embodiments, washers  334  comprise plastic and black fabric (e.g., a plastic washer with a black fabric exterior). 
       FIG.  4    illustrates an exemplary method  400  for installation of overhead bin  104  for some embodiments. At step  402 , overhead bin  104  may be raised to engage studs  302  to mating receptacles  306 . Once raised, at step  404 , overhead bin  104  may be slid outboard to fully engage attachment points  214   a,    214   b,    214   c,    214   d . Next, at step  406 , screws  304  may be turned to lock attachment points  214   a,    214   b,    214   c ,  214   d.  In some embodiments, turning screws  304  causes screw end  324  to insert into receptacle hole  326  while also rotating stud proximal end  322  downward to press against narrow portion  327  in slot  329  (see  FIGS.  3 A- 3 C ). In some embodiments, screws  304  are partially engaged such that only a substantially small turn is required to fully lock overhead bin  104 . 
     To remove overhead bin  104 , the reverse process outlined in method  400  may be followed. Screws  304  may be turned and unlocked from mating receptacles  306  whereby  302  is loosened (e.g., screw distal end  320  is no longer engaged in hole  326 ). Overhead bin  104  may then be slid inboard to disengage studs  302  from mating receptacles  306 . Thereafter, overhead bin  104  may be lowered. As described above, attachment points  214   a,    214   b,    214   c,    214   d  allow for the quick installation and removal of overhead bins  104  from aircraft cabin  100 . Therefore, the aircraft may be easily configured for different uses, and overhead bins  104  may be removed to save weight and space. As described above, the aircraft may be operated with overhead bins  104  removed, and the finished liner  106  provides the appearance that no components are missing from the aircraft. 
     While embodiments herein have been described with respect to overhead bins  104  and attachment points  214   a,    214   b,    214   c,    214   d  used in aircraft, overhead bins  104  may be used in other situations. Overhead bin  104  may be configured for use on a boat or train, for example. As another example, overhead bin  104  may be used within houses, offices, workshops, and the like. Attachments points  214   a,    214   b ,  214   c,    214   d  may be used in various situations requiring the attachment of an easily removable component. 
     Many different arrangements of the various components depicted, as well as components not shown, are possible without departing from the spirit and scope of what is claimed herein. Embodiments have been described with the intent to be illustrative rather than restrictive. Alternative embodiments will become apparent to those skilled in the art that do not depart from what is disclosed. A skilled artisan may develop alternative means of implementing the aforementioned improvements without departing from what is claimed. 
     It will be understood that certain features and subcombinations are of utility and may be employed without reference to other features and subcombinations and are contemplated within the scope of the claims. Not all steps listed in the various figures need be carried out in the specific order described.