Patent Publication Number: US-2020300001-A1

Title: Aircraft door latch apparatus and related methods for use of the same

Description:
BACKGROUND 
     Technical Field 
     The present disclosure generally relates to aircraft interior components and, more particularly, to aircraft interior component latch assemblies. 
     Description of the Related Art 
     Aircraft generally include a wide variety of interior components. Aircraft interior components, for example, galley doors, passenger service units, lavatory doors, galleys, closets, and other interior furnishings generally are moveable between open and closed positions. In general, such interior furnishings may include a door jamb or frame having a strike component and a latch mechanism provided on a door that latches the door to the strike component. 
     Conventional aircraft interior components tend to expose one or more latch mechanism components, which results in an unsightly, aesthetically displeasing interior component. Furthermore, it is generally desirable to indicate to users whether the interior component has latched to the door frame or is unlatched, in an efficient manner. 
     BRIEF SUMMARY 
     The various implementations of aircraft door latch apparatuses described herein provide apparatuses that conceal various components of latch apparatus of the aircraft door latch apparatus in both latched and unlatched configuration. The various implementations of aircraft door latch apparatuses described herein provide efficient, compact, and robust forms of indicating latched and/or unlatched configurations of the aircraft door latch apparatuses. For example, in one non-limiting, example implementation, an aircraft door latch apparatus having a latched configuration and an unlatched configuration can be summarized as including a door structure of an aircraft door assembly, a handle coupled to the door structure and pivotably moveable with respect to the door structure between a latched position and an unlatched position, the handle including at least a first wall and a handle cavity, and a latch apparatus coupled to the handle. The latch apparatus may be operable to move the handle between the latched position and the unlatched position, the latch apparatus received in the handle cavity and arranged to be concealed by the handle when the aircraft door latch apparatus is in the latched configuration and the unlatched configuration. 
     In another non-limiting, example implementation, a method of operating an aircraft interior furnishing can be summarized as including latching an aircraft door assembly, the latching including magnetically coupling a latch apparatus coupled to a handle of the aircraft door assembly to a door strike coupled to a door frame of the aircraft interior furnishing; and unlatching the aircraft door assembly. The unlatching can include magnetically uncoupling the latch apparatus from the door strike, moving an indicator element of the latch apparatus to expose an indicia surface of the indicator element, the indicia surface indicating an unlatched configuration, and rotatably moving the aircraft door assembly to expose an interior of the interior furnishing. 
    
    
     
       BRIEF DESCRIPTION OF THE SEVERAL VIEWS OF THE DRAWINGS 
         FIG. 1  is an isometric view of an aircraft door latch apparatus, according to one example, non-limiting implementation. 
         FIG. 2A  is an exploded view of the aircraft door latch apparatus of  FIG. 1 . 
         FIG. 2B  is another exploded view of the aircraft door latch apparatus of  FIG. 1 . 
         FIG. 2C  is a side view of a door structure of the aircraft door latch apparatus of  FIG. 1 . 
         FIG. 2D  is a side isometric view of a handle of the aircraft door latch apparatus of  FIG. 1 . 
         FIG. 3  is a left side view of the aircraft door latch apparatus, with certain components, e.g., door structure, removed for clarity of illustration and description. 
         FIG. 4  is a right side view of the aircraft door latch apparatus, with certain components, e.g., handle, removed for clarity of illustration and description. 
         FIG. 5  is a cross-sectional view of the aircraft door latch apparatus of  FIG. 1 , taken along line  5 - 5 . 
         FIG. 6  is a cross-sectional view of the aircraft door latch apparatus of  FIG. 2A , taken along line  6 - 6 . 
         FIG. 7  is a cross-sectional view of the aircraft door latch apparatus of  FIG. 1 , taken along line  7 - 7 . 
         FIG. 8  is a cross-sectional view of the aircraft door latch apparatus of  FIG. 1 , taken along line  8 - 8 . 
     
    
    
     DETAILED DESCRIPTION 
     In the following description, certain specific details are set forth in order to provide a thorough understanding of various disclosed embodiments or implementations. However, one skilled in the relevant art will recognize that embodiments or implementations may be practiced without one or more of these specific details, or with other methods, components, materials, etc. In other instances, well-known structures associated with payload components, hinges, latches, aircraft interior furnishings, aircraft doors, aircraft frames, or other systems and apparatuses of aircrafts have not been shown or described in detail to avoid unnecessarily obscuring descriptions of the embodiments or implementations. 
     Unless the context requires otherwise, throughout the specification and claims which follow, the word “comprise” and variations thereof, such as “comprises” and “comprising,” are to be construed in an open, inclusive sense, that is, as “including, but not limited to.” 
     Reference throughout this specification to “one embodiment,” “one implementation,” “an embodiment,” or “an implementation” means that a particular feature, structure or characteristic described in connection with the embodiment or implementation is included in at least one embodiment or implementation. Thus, the appearances of the phrases “in one embodiment,” “in one implementation,” “in an embodiment,” or “in an implementation” in various places throughout this specification are not necessarily all referring to the same embodiment or implementation. Furthermore, the particular features, structures, or characteristics may be combined in any suitable manner in one or more embodiments or implementations. 
     As used in this specification and the appended claims, the singular forms “a,” “an,” and “the” include plural referents unless the content clearly dictates otherwise. It should also be noted that the term “or” is generally employed in its sense including “and/or” unless the content clearly dictates otherwise. 
       FIGS. 1-8  illustrate an aircraft door latch apparatus  10 , according to one example, non-limiting implementation. The aircraft door latch apparatus  10  generally includes a door assembly  12  and a door frame assembly  13 . The door frame assembly  13  includes a door frame or door jamb  14  having an opening  15  and a door strike  16 . The door jamb  14  is generally coupled to an interior furnishing, with the opening  15  sized and shaped to provide access to an interior volume of the interior furnishing, as illustrated partially in  FIG. 1 , with the door jamb  14  removed in the other figures for clarity of description and illustration. The door strike  16  is coupled to the door jamb  14  and is generally configured to latch and/or unlatch the door assembly  12 , as described in more detail below. 
     The door assembly  12  includes a handle  17 , a door structure  18 , and a latch assembly  19 . Although not shown for clarity of illustration and description, the door structure  18  is generally sized and shaped to couple to a door panel of the door assembly  12 . The overall door assembly  12  may be coupled to the door frame  14 , for example, via hinges. The door assembly  12  may be rotatably moved between open and closed configurations to provide access to the interior volume of the interior furnishing and conceal or prevent access to the same. For example, the door structure  18  includes a main body  20  having at least a pair of coupling elements  21   a ,  21   b . The coupling elements  21   a ,  21   b  are generally sized and shaped to couple to the door panel. The main body  20  of the door structure  18  includes a first flange  22  and a second flange  23  that is spaced apart from the first flange  22  to define a receiving cavity  51 . The first flange  22  includes a first portion  24  that is angularly oriented relative to a horizontal axis  25  of the main body  20  at an angle α 1  and a second portion  26  that is also angularly oriented relative to a vertical axis  81  at an angle α 2 . In this manner, the first portion  24  includes a first surface  27  that extends angularly, and the second portion  26  includes a second surface  28  that extends angularly. The second flange  23 , however, is generally oriented to be parallel to the vertical axis  81 . The second flange  23  includes a first clevis  29  and a second clevis  30  that are vertically spaced apart. In particular, both the first clevis  29  and the second clevis  30  extend outwardly relative to an outer surface  31  of the second flange  23 . The first clevis  29  includes a first coupling aperture  32  and the second clevis  30  includes a second coupling aperture  33 . The first and second coupling apertures  32 ,  33  are sized and shaped to pivotably couple the handle  17  to the door structure  18  via the latch assembly  19 , as described in more detail below. 
     As illustrated in  FIGS. 1-8 , the main body  20  includes an upper recess  34  and a lower recess  35 . The upper recess  34  is located proximal to the first clevis  29  and the lower recess  35  is positioned proximal to the second clevis  30 . The upper and lower recesses  34 ,  35  are sized and shaped to allow the handle  17  to be pivotably coupleable to the door structure  18  to allow rotatable movement of the handle  17  and also concealing or covering the latch assembly  19  so as not to expose one or more components of the latch assembly  19 . 
     The handle  17  includes a first wall  38 , a second wall  39 , a third wall  40 , and an upper wall  41 . The first, second, third, and upper walls  38 ,  39 ,  40 ,  41  are arranged to define an interior cavity  82  and a bevel edge  42 . The first wall  38  includes a first chamfer edge  43  and the third wall  40  also includes a second chamfer edge  44 . The upper and lower recesses  34 ,  35  of the main body  20  are sized and shaped to allow portions of the main body  20  to be received in the interior cavity  82  of the handle  17 . In particular, the upper recess  34  allows the second flange  23  to be received in the interior cavity  82  with the upper wall  41  being substantially flush with the main body  20  and the lower recess  35  allows the second chamfer edge  44  to be oriented in substantial alignment with the second portion  26  of the first flange  22 , with the second chamfer edge  44  in substantial alignment with an end edge  50  of the main body  20 . Thus, when the handle  17  is pivotably coupled to the door structure  18 , the handle  17  is positioned in the receiving cavity  51  of the door structure  18 , with certain portions of the door structure  18  extending into and being received in the interior cavity  82  of the handle  17  to conceal or cover the latch assembly  19 . 
     As described above, the aircraft door latch apparatus  10  is generally sized, shaped, and arranged to allow the various components of the latch assembly  19  to not be exposed. In particular, an interior of the first wall  38  includes various structural features that allow the components of the latch assembly  19  to be received therein. The first wall  38  includes a first wall element  52  and a second wall element  53  spaced apart in the vertical direction. Each of the first and second wall elements  52 ,  53  include respective pin apertures  54 ,  55 . The pin apertures  54 ,  55  are sized and shaped to align with the respective first coupling aperture  32  of the first clevis  29  and the second coupling aperture  33  of the second clevis  30 . 
     The first wall  38  includes a coupling element  56  and an indicator portion  57 . The coupling element  56  includes a coupling aperture  58  that is sized and shaped to align with the pin aperture  54  of the first wall element  52 . The coupling element  56  also includes a slot aperture  59  and a coupling pin aperture  60 . The indicator portion  57  includes a spring recess  61  and a fastener aperture  62 . The first wall  38  also includes a lower tab element  89  positioned adjacent to the second wall element  53 . As illustrated in  FIG. 2D  in more detail, the first wall  38  includes a first magnet recess  90  and a second magnet recess  91 . The first magnet recess  90  is positioned between the coupling element  56  and the indicator portion  57 . The second magnet recess  91  is positioned between the indicator portion  57  and the lower tab element  89 . The third wall  40  includes an indicator recess  64  that is elongated, for example, in the form of a slot. The indicator recess  64  is sized and shaped to slideably receive an indicator element  65  of the latch assembly  19 . 
     In particular, the latch assembly  19  includes the indicator element  65 , one or more magnet elements  66 , one or more coupling pins  67   a ,  67   b , one or more first biasing elements  68 , a second biasing element  69 , a third biasing element  70 , one or more retention pins  71   a ,  71   b , and a magnet fastener  72 . The indicator element  65  is generally sized and shaped to be slideably moveable through the indicator recess  64 . The indicator element  65  includes an indicia surface  73  that generally indicates if the aircraft door latch apparatus  10  is latched or unlatched. For example, the indicia surface  73  can comprise a bright color that is different from the color of the other surfaces of the indicator element  65 . For example, as the indicator element  65  moves out of, or away from, the indicator recess  64 , the indicia surface  73  is exposed to indicate that the aircraft door latch apparatus  10  is in the unlatched configuration. Conversely, when the aircraft door latch apparatus  10  is in a latched configuration, the indicia surface  73  is covered or concealed, indicative of a latched configuration. 
     The indicator element  65  includes a pair of retention portions  74   a ,  74   b  that are spaced apart and sized, shaped, and arranged to receive therein the one or more magnet elements  66 . Proximate to each retention portion  74   a ,  74   b , the indicator element  65  includes latch apertures  75   a ,  75   b . As described in more detail below, each latch aperture  75   a ,  75   b  is sized and shaped to receive therein portions of the door strike  16  to latch and/or unlatch the aircraft door latch apparatus  10 . The indicator element  65  includes a biasing element aperture  76  that is generally elongated, e.g., in a form of a slot. The biasing element aperture  76  is sized and shaped to slideably receive therein the magnet fastener  72 . In particular, the second biasing element  69  is sized and shaped to be received in the spring recess  61  of the handle  17 . The magnet fastener  72  is sized and shaped to be received in the biasing element aperture  76  and the fastener aperture  62  of the handle  17 . In particular, the indicator element  65  is sandwiched between a head of the magnet fastener  72  and the first wall  38  of the handle  17  and positioned adjacent to the second biasing element  69 . In this manner, the indicator element  65  is slideably moveable relative to the handle  17  and rotatably moveable with the handle  17 . In particular, the second biasing element  69  is sized and shaped to urge the indicator element  65  away from, or out of, the indicator recess  64  of the third wall  40 , with the indicator element  65  being slideably moveable relative to the magnet fastener  72  within the biasing element aperture  76 . 
     The one or more coupling pins  67   a ,  67   b  are sized and shaped to pivotably couple the handle  17  to the door structure  18 . In particular, the coupling pin  67   a  is received in the first coupling aperture  32  of the first clevis  29  and the pin aperture  54  disposed in the first wall element  52  of the handle  17 . In addition, the coupling pin  67   b  is received in the second coupling aperture  33  of the second clevis  30  and the pin aperture  55  disposed in the second wall element  53  of the handle  17 . 
     As illustrated in  FIGS. 1-8 , the coupling pin  67   a  extends through the third biasing element  70 . In particular, the third biasing element  70  is positioned between the coupling element  56  and the first wall element  52 , with the coupling pin  67   a  extending through the coupling element  56  and the third biasing element  70 . In some implementations, the third biasing element  70  may comprise a torsion spring. In particular, the third biasing element  70  is sized and shaped to rotatably urge the handle  17  to the latched configuration. For example, if the handle  17  is moved from the latched position to the unlatched position by rotary movement thereof in a counterclockwise direction, the third biasing element  70  generally urges to rotatably move the handle  17  to the latched position by rotary movement in a clockwise direction. 
     The retention pins  71   a  protrude outwardly in a perpendicular orientation relative to the shaft of the coupling pin  67   a . In particular, one of the retention pins  71   a  is coupled to the coupling pin  67   a  and protrudes outwardly from the slot aperture  59  of the coupling element  56 . Another one of the retention pins  71   a  protrudes outwardly from the coupling pin aperture  60  of the coupling element  56 . One of the one or more first biasing elements  68  is positioned adjacent to an end of the shaft of the coupling pin  67   a  and a lower one of the retention pins  71   a . In this manner, the retention pins  71   a  and the first biasing element  68 , e.g., a spring, facilitate alignment of the handle  17 , the indicator element  65 , and the door structure  18 . Similarly, the retention pin  71   b  protrudes outwardly from the coupling pin  67   b  toward the third wall  40  and into an alignment slot  78  disposed in the main body  20  of the door structure  18 . Another one of the one or more first biasing elements  68  is positioned between an end of the shaft of the coupling pin  67   b  and a spring coupling surface  79  disposed in the main body  20  of the door structure  18 . Again, in this manner, the retention pin  71   b  and the first biasing element  68  facilitate alignment of the handle  17 , the indicator element  65 , and the door structure  18 . 
     As described above, the aircraft door latch apparatus  10  moves between a latched and/or an unlatched configuration. In particular, the door strike  16  receives the indicator element  65  to latch the aircraft door latch apparatus  10 . The door strike  16  includes a strike recess  92  extending therethrough. A pair of tab elements  93   a ,  93   b  protrude outwardly from a strike surface  94  positioned at one end of the strike recess  92 . The strike recess  92  is sized and shaped to receive therein the indicator element  65  and facilitate movement of the indicator element  65 . The tab elements  93   a ,  93   b  are sized and shaped to be received in the latch apertures  75   a ,  75   b  when the aircraft door latch apparatus  10  is in the latched configuration. 
     In particular, during operation, the aircraft door latch apparatus  10  may be moved between latched and unlatched configurations. In the latched configuration, as shown in  FIGS. 6 and 7  in detail, the tab elements  93   a ,  93   b  of the door strike  16  are received in the latch apertures  75   a ,  75   b , and the indicator element  65  is positioned adjacent to, or in mating alignment with, the strike surface  94 . With continued reference to  FIGS. 1-8 , the one or more magnet elements  66  received in the retention portions  74   a ,  74   b  of the indicator element  65  are positioned adjacent to the door strike  16 . The one or more magnet elements  66  are magnetically coupled to the door strike  16 , which may comprise a ferromagnetic material, such as steel. The magnetic forces of the one or more magnet elements  66  are attracted to the door strike  16 , and counteract, and overcome biasing forces of the second biasing element  69  which urges the indicator element  65  to move out of the strike recess  92  and the indicator recess  64  of the third wall  40  in direction  95  to expose the indicia surface  73  of the indicator element  65 . 
     To move the aircraft door latch apparatus  10  from the latched to the unlatched configuration, the handle  17  may be rotated in a first rotary direction R 1 , which as illustrated, may be a counterclockwise direction. In particular, the handle  17  may pivotably rotate with respect to the door structure  18  in the first rotary direction R 1  via coupling pins  67   a ,  67   b , which define respective pivot points. As the user applies rotary forces to move the handle  17  in the first rotary direction R 1 , such rotary forces overcome the biasing forces applied by the third biasing element  70 , e.g., a torsion spring. As described earlier, the third biasing element  70  is generally sized and shaped to urge the handle  17  into the latched configuration, e.g., urging the third biasing element  70  to move in a second rotary direction R 2 , which may be a clockwise direction. 
     As the handle  17  is moved in the first rotary direction R 1 , the indicator element  65  moves within the strike recess  92  away from the strike surface  94  in direction  96 . For example, a user may rotary handle  17  in first rotary direction R 1 , until the indicator element  65  moves away from the strike surface  94 , which results in forces applied by the user to overcome the magnetic forces between the one or more magnet elements  66  and the door strike  16 . Such movement moves the aircraft door latch apparatus  10  from the latched configuration to the unlatched configuration. In particular, as the indicator element  65  moves away from the strike surface  94 , the tab elements  93   a ,  93   b  are moved out of the latch apertures  75   a ,  75   b . As the magnetic forces between the one or more magnet elements  66  and the door strike  16  are reduced, the biasing forces of the second biasing element  69  are sufficient to move the indicator element  65  relative to the magnet fastener  72  and through the biasing element aperture  76 , which moves the indicator element out of the indicator recess  64  of the third wall  40  and exposes the indicia surface  73 . As the indicia surface  73  is exposed, such indicates to a user that the aircraft door latch apparatus  10  is in the unlatched configuration. 
     Thereafter, the handle  17  may be rotated in the second rotary direction R 2 , which may be a clockwise direction. Rotary movement of the handle  17  in the second rotary direction R 2  causes the handle  17  to rotate with the door structure  18  in the second rotary direction R 2 . In particular, as the door structure  18  and the handle  17  moves in the second rotary direction R 2 , the aircraft door coupled to the door structure  18  may move from a closed position to an open position. As the door structure  18  is moved to the open position, and the handle  17  is released by the user, the biasing forces of the third biasing element  70  urge the handle  17  to rotatably move in the second rotary direction R 2  toward a position similar to the position of the handle  17  in the latched configuration illustrated in  FIGS. 1 and 4-8 . However, as the indicator element  65  is away from the door strike  16 , the indicator element  65  remains in a position similar to the position of the indicator element  65  in the unlatched configuration. In other words, the indicia surface  73  of the indicator element  65  remains exposed due to the biasing forces of the second biasing element  69 . 
     Thereafter, the door structure  18  may be rotated in the first rotary direction R 1 , which moves with the handle  17 . As the door structure  18  and the handle  17  are returned to the latched position, the indicator element  65  is positioned adjacent to the strike surface  94 . In particular, as described above, the third biasing element  70  returns the handle  17  to a position similar to the position of the handle  17  in the latched configuration. In some implementations, the one or more magnet elements  66  may be sized and shaped to magnetically couple to the door strike  16  when the indicator element  65  is positioned adjacent to the strike surface  94  even if the indicator element  65  is not moved into the strike recess  92  of the door strike  16 . In other words, the indicia surface  73  may be exposed as the indicator element  65  is moved out of the indicator recess  64  of the third wall  40 . However, as the door structure  18  and the handle  17  are moved toward the door strike  16 , the magnetic forces between the one or more magnet elements  66  and the door strike  16  move the indicator element  65  into the indicator recess  64  of the third wall  40  and into the strike recess  92  of the door strike  16  to return the aircraft door latch apparatus  10  to the latched configuration. In some implementations, however, the user may manually push the indicator element  65  as the door structure  18  and the handle  17  are moved toward the door strike  16 . 
     Moreover, the various embodiments described above can be combined to provide further embodiments. 
     These and other changes can be made to the embodiments in light of the above-detailed description. In general, in the following claims, the terms used should not be construed to limit the claims to the specific embodiments disclosed in the specification and the claims, but should be construed to include all possible embodiments along with the full scope of equivalents to which such claims are entitled. Accordingly, the claims are not limited by the disclosure.