Patent Publication Number: US-2023139014-A1

Title: Aircraft pressure panel assemblies

Description:
FIELD 
     The present disclosure relates to aircraft pressure panel assemblies. 
     BACKGROUND 
     Aircraft are generally designed to operate in low ambient atmospheric pressure while maintaining a pressurized compartment for passengers, operators, and/or cargo. Pressure panels are used to isolate and maintain different pressurized regions within an aircraft, such as, for example, a pressurized passenger compartment and an unpressurized mechanical compartment. 
     Aircraft also incorporate load-bearing supports that react to loads by flexing. For example, wings of an aircraft in flight bear the load of the aircraft and any cargo. Where a wing of an aircraft interacts with pressure panels within the fuselage, the pressure panels coupled to the wing take on the deflected shape of the wing, which generates significant forces in the adjacent pressure panels. Historically, these adjacent pressure panels are sized to react to these wing deflection induced forces, resulting in pressure panels that are heavy. 
     SUMMARY 
     Aircraft pressure panel assemblies, aircraft comprising the same, and methods of assembling the same are disclosed herein. The pressure panel assemblies have a high-pressure side and a low-pressure side opposite the high-pressure side and comprise panels, one or more splicing members, and one or more beams. The panels comprise at least a first panel and a second panel that is positioned laterally adjacent to the first panel. Each of the first panel and the second panel have a longitudinal panel length. The one or more splicing members comprise at least a first splicing member that is welded to the first panel and to the second panel along the longitudinal panel length of the first panel and the second panel. The one or more beams comprise at least a first beam that is joined directly to the first splicing member or that is joined directly to the first panel and to the second panel. The first splicing member extends along the longitudinal panel length on the high-pressure side of the first splicing member or on the high-pressure side of the first panel and of the second panel. Aircraft comprise a fuselage with a pressurized compartment and the pressure panel assembly supported by the fuselage, and with the high-pressure side facing the pressurized compartment and the low-pressure side facing away from the pressurized compartment. 
    
    
     
       BRIEF DESCRIPTION OF THE DRAWINGS 
         FIG.  1    is a perspective view of an example aircraft. 
         FIG.  2    is a schematic diagram representing pressure panel assemblies according to the present disclosure. 
         FIG.  3    is a schematic perspective view of an example pressure panel assembly according to the present disclosure. 
         FIG.  4    is a schematic perspective view of another example pressure panel assembly according to the present disclosure. 
         FIG.  5    is a schematic perspective view of another example pressure panel assembly according to the present disclosure. 
         FIG.  6    is a schematic perspective view of another example pressure panel assembly according to the present disclosure. 
         FIG.  7    is a flow chart schematically representing example methods according to the present disclosure. 
     
    
    
     DESCRIPTION 
       FIG.  1    schematically presents a commercial fixed-wing aircraft  100 , as an illustrative, non-exclusive example of an application that may utilize pressure panel assemblies  10  according to the present disclosure. However, other aerospace applications are within the scope of the present disclosure, including (but not limited to) military aircraft, rotorcraft, and space vehicles. Moreover, pressure panel assemblies  10  according to the present disclosure also may be used in non-aerospace applications to define pressure barriers, for example, including (but not limited to) marine applications, such as in submarines. 
     Aircraft  100  may include one or more pressurized compartments  104  for such purposes as comfort of operators and passengers, and for protection of cargo and equipment. Aircraft  100  typically include pressure panels  114 , sometimes referred to as pressure decks, to isolate and maintain the integrity of pressurized compartments  104  within the aircraft  100 . The pressure panels  114  are subject to the pressure differential of the pressurized compartment  104  relative to neighboring compartments and/or ambient conditions. Further, the pressure panels  114  may be subject to loads and/or deformation transmitted by other components of the aircraft  100 . Such loads and/or deformation may have their ultimate source in the weight and the lift of the aircraft  100 . 
     Aircraft  100  that include pressurized compartments  104  also may include unpressurized compartments, such as mechanical compartments for equipment that requires no pressurization. Pressure panels  114  are used to separate pressurized and unpressurized compartments. One type of unpressurized compartment is a wheel well  112 . On some aircraft, the wheel well  112  is located near where the wing assembly  106  meets the fuselage  102 . The wheel well  112  may be adjacent or under the fuselage  102  and/or may be defined by the fuselage  102 , and may be under and/or aft of the wing assembly  106 . Other configurations also are within the scope of aircraft  100  according to the present disclosure. 
     Additionally or alternatively, in some aircraft, compartments may not be actively pressurized by a pressurization system, yet compartment walls may still be subject to pressure differentials during flight, simply due to the change in altitude and/or forces of flight, and thus external air pressure may be greater or less than an internal pressure of the compartment. For example, some aircraft do not include active pressurization systems to maintain an elevated pressure within a compartment, e.g., a cargo compartment, yet pressure differentials, including positive and/or negative pressure differentials, may be imparted between the exterior of a compartment and the interior of a compartment during flight. 
     The wing assembly  106  of an aircraft  100  typically includes two wing outboard sections  108  and a wing center section  110  between the wing outboard sections  108 . The wing center section  110  may pass through or under the fuselage  102 . In flight, the wing assembly  106  creates lift, which counteracts the weight of the aircraft  100 . Because the lift is distributed along the wing outboard sections  108 , the wing assembly  106  is subject to stress. Under the stress of flight, the wing assembly  106  bends, subjecting the upper portion of the wing assembly  106  to compression and the lower portion of the wing assembly  106  to tension. Components closely coupled to the wing assembly  106  are thus deformed under the displacement imposed by the wing assembly  106  during flight. For example, where the wheel well  112  is adjacent to the wing assembly  106 , a portion of the wheel well  112  may be compressed with the upper portion of the wing center section  110  of the wing assembly  106 . When a pressure panel  114  is used to form a portion of such a wheel well  112 , sometimes referred to as a horizontal pressure deck, the pressure panel  114  may be subject to the displacement of the wing assembly  106 , and thus subject to compression as well as the pressure differential between the wheel well  112  and the pressurized compartment  104 . 
     Turning to  FIG.  2   , pressure panel assemblies  10 , which may form or be a component of a pressure panel  114  of an aircraft  100 , are schematically represented. Generally, in  FIG.  2   , elements that are likely to be included in a given example are illustrated in solid lines, while elements that are optional to a given example or that correspond to an optional or alternative embodiment are illustrated in broken lines. However, elements that are illustrated in solid lines are not essential to all examples of the present disclosure, and an element shown in solid lines may be omitted from a particular example without departing from the scope of the present disclosure. 
       FIGS.  3 - 6    illustrate examples of pressure panel assemblies  10 , identified as pressure panel assemblies  300 ,  400 ,  500 , and  600 , respectively. Where appropriate, the reference numerals from the schematic illustration of  FIG.  2   . are used to designate corresponding parts of the examples of  FIGS.  3 - 6   ; however, the examples of  FIGS.  3 - 6    are non-exclusive and do not limit pressure panel assemblies  10  to the illustrated embodiments of  FIGS.  3 - 6   . That is, pressure panel assemblies  10  may incorporate any number of the various aspects, configurations, characteristics, properties, etc. of pressure panel assemblies  10  that are illustrated in and discussed with reference to the schematic representation of  FIG.  2    and/or the embodiments of  FIGS.  3 - 6   , as well as variations thereof, without requiring the inclusion of all such aspects, configurations, characteristics, properties, etc. 
     With reference to  FIG.  2   , pressure panel assemblies  10  may be described as having a high-pressure side  12  and a low-pressure side  14  that is opposite the high-pressure side  12 . That is, pressure panel assemblies  10  are intended to be installed in a specific orientation, with the high-pressure side  12  facing a relatively higher pressure environment, such as a pressurized compartment  104  of an aircraft  100 , and with the low-pressure side  14  facing a relatively lower pressure environment, such as an unpressurized compartment of the aircraft  100 . As schematically represented in  FIG.  2   , and as illustrated in the examples of  FIGS.  3 - 6   , pressure panel assemblies  10  comprise panels  50 , one or more splicing members  54  comprising at least a first splicing member  22 , and one or more beams  56  comprising at least a first beam  24 . The panels  50  comprise pairs of laterally adjacent panels  50 , including at least a first panel  16  and a second panel  18 , with the second panel  18  positioned laterally adjacent to the first panel  16 . Each of the panels  50  have a longitudinal panel length  20  that typically corresponds to an overall length of the pressure panel assembly  10  itself. By “laterally adjacent” to each other, it is meant that the panels  50  are positioned side-by-side with respect to their widths that are transverse to the longitudinal panel length  20 , as opposed to being positioned end-to-end along their longitudinal panel length  20 . Moreover, pressure panel assemblies  10  may include any suitable number of panels  50 , including three or more panels  50 , that are positioned laterally adjacent, or side-by-side, to each other, depending on the specific size of pressure panel assembly  10 .  FIG.  2    schematically illustrates, and the examples of  FIGS.  3 - 6    further comprise, an optional third panel  44  positioned laterally adjacent to the second panel  18  opposite the first panel  16 ; however, more than three panels  50  may be included in a pressure panel assembly  10 . The panels  50  of pressure panel assemblies  10  additionally or alternatively may be described as webs of the pressure panel assemblies  10 . 
     Each splicing member  54  is welded to a pair of laterally adjacent panels  50  along the longitudinal panel length  20 . That is, the first splicing member  22  is welded to the first panel  16  and to the second panel  18  along the longitudinal panel length  20 . When a third panel  44  is included, a second splicing member  46  is welded to the second panel  18  and to the third panel  44  along the longitudinal panel length  20 , and so forth depending on the number of panels  50  in a particular pressure panel assembly  10 . Additionally or alternatively, as schematically represented in  FIG.  2   , pressure panel assemblies  10  may be described as comprising welds  52  between a splicing member  54  and each of the two corresponding laterally adjacent panels  50 . Because the welds  52  run the full longitudinal panel length  20 , the welds  52  form an air-tight seal between the splicing member  54  and the respective panels  50  to prevent air from passing from the high-pressure side  12  to the low-pressure side  14  of the pressure panel assembly  10 . Accordingly, some examples of pressure panel assemblies  10  are free of fay seals between panels  50  and corresponding splicing members  54 . In some such examples, the pressure panel assemblies  10  also are free of fasteners that couple together the panels  50  and corresponding splicing members  54 . Moreover, the welds  52  will carry the load associated with any displacement, compression, shear, and/or tension experienced by the pressure panel assembly  10  during operation. For example, when a pressure panel assembly  10  is utilized as a horizontal pressure deck aligned with or adjacent to the upper surface of the wing center section  110  of an aircraft  100 , the compressive forces experienced by the horizontal pressure deck during flight will be carried by the welds  52 . In addition, the pressure differential across the pressure panel assembly  10  tends to flex the pressure panel assembly  10  towards its low-pressure side  14  which results in loads carried by the welds  52 . 
     In some examples of pressure panel assemblies  10 , a beam  56  is joined directly to a corresponding splicing member  54 , such as in the example pressure panel assemblies  300 ,  400 , and  600  of  FIGS.  3 ,  4 , and  6   . In other examples of pressure panel assemblies  10 , a beam  56  is joined directly to two laterally adjacent panels  50 , such as in the example pressure panel assembly  500  of  FIG.  5   . In either case, the beam  56  extends along the longitudinal panel length  20  on the high-pressure side  12  of the splicing member  54  or on the high-pressure side  12  of the respective panels  50 . A beam  56  of a pressure panel assembly  10  additionally or alternatively may be described as a beam assembly  56  and may include more than one structural component, such as a fitting  58  that is joined directly to either a splicing member  54  or to two laterally adjacent panels  50 , and a separate structural beam  60  that is joined directly to the fitting  58 , such as in example pressure panel assembly  600  of  FIG.  6   . By two components being “joined directly” together, it is meant that a distinct structural component is not positioned between the respective components; however, it is within the scope of being “joined directly” that an adhesive, a sealant, a gasket, or other non-structural component is positioned between the two components that are “joined directly” together. “Joined directly” is distinguished from being “coupled indirectly.” For example, with respect to pressure panel assemblies  300 ,  400 , and  600  of  FIGS.  3 ,  4 , and  6   , the beams  56  are joined directly to the respective splicing members  54  and are coupled indirectly to the panels  50  via the splicing members  54 . With respect to pressure panel assembly  500  of  FIG.  5   , the beams  56  are joined directly to corresponding panels  50  and are coupled indirectly to corresponding splicing members  54  via the panels  50 . 
     One or more of the panels  50 , the splicing member(s)  54 , and the beam(s)  56  (or at least fitting(s)  58  of the beam(s)  56 ) may be constructed of a thermoplastic material, such as a fiber reinforced thermoplastic material. The thermoplastic materials of the panels  50 , the splicing member(s)  54 , and the beam(s)  56  need not be identical when more than one are constructed of a thermoplastic material, but when two such components are welded together, such as the panels  50  and the splicing member(s)  54 , the thermoplastic materials are selected to result in a structurally sound weld having the desired properties for carrying the loads experienced by the pressure panel assembly  10  during operative use. Examples of suitable thermoplastics include (but are not limited to) polyphenylene sulfide (PPS) and polyaryletherketone (PAEK), such as polyether ether ketone (PEEK) and polyetherketoneketone (PEKK). Examples of suitable fibers include (but are not limited to) carbon fibers, glass fibers, and aramid fibers. 
     Alternatively, one or more of the panels  50 , the splicing member(s)  54 , and the beam(s)  56  (or at least fitting(s)  58  of the beam(s)  56 ) may be constructed of a metallic material, such as an aluminum alloy or a titanium alloy, a fiber-reinforced thermoset material, and/or a combination of one or more of a thermoplastic material, a metallic material, and a fiber-reinforced thermoset material. 
     In some examples in which both the splicing member(s)  54  and the beam(s)  56  (or at least fitting(s)  58  thereof) are constructed of a thermoplastic material, the beam(s)  56  are welded to corresponding splicing member(s)  54  along the longitudinal panel length  20 , such as in the example pressure panel assemblies  300 ,  400 , and  600  of  FIGS.  3 ,  4 , and  6   . In other such examples in which both the panels  50  and the beam(s)  56  (or at least fitting(s)  58  thereof) are constructed of a thermoplastic material, the beam(s)  56  are welded to the corresponding laterally adjacent panels  50 , such as in the example pressure panel assembly  500  of  FIG.  5   . 
     In some examples, the beam(s)  56  are fastened to at least the splicing member(s)  54  with a plurality of fasteners  26 . Fasteners  26  additionally or alternatively may be described as mechanical fasteners  26  (e.g., bolts and nuts, rivets, lock bolts, etc.), and as used herein “fasteners” does not comprise welds. In some such examples, the beam(s)  56  are fastened to both the splicing member(s)  54  and corresponding laterally adjacent panels  50 . For example, as in example pressure panel assembly  500  of  FIG.  5   , laterally adjacent panels  50  are positioned and compressed between the corresponding splicing members  54  and beams  56 . In other examples, as in example pressure panel assembly  600  of  FIG.  6   , the splicing members  54  are positioned and compressed between the beams  56  and the corresponding laterally adjacent panels  50 . In examples such as pressure panel assembly  500  and pressure panel assembly  600 , in which a splicing member  54 , a beam  56 , and corresponding laterally adjacent panels  50  are all three coupled together, the load transfer though two interfaces, rather than just one, as in the examples of  FIGS.  3  and  4   , results in a lighter weight joint with a higher load capability. 
     In some examples, as in example pressure panel assemblies  500  and  600  of  FIGS.  5  and  6   , the beam(s)  56  are fastened to the splicing member(s)  54  and a corresponding one of a pair of laterally adjacent panels  50  utilizing a first single row  28  of the fasteners  26 , and the beam(s)  56  are fastened to the splicing member(s)  54  and a corresponding other one of the pair of laterally adjacent panels  50  utilizing a second single row  30  of the fasteners  26 . In particular, in such examples where the panels  50  are welded to the splicing member(s)  54 , as well as in such examples where the splicing member(s)  54  are welded to the beam(s)  56 , because the corresponding welds  52  serve to carry loads experienced by the pressure panel assembly  10 , fewer fasteners may be needed to adequately secure the beam(s)  56  to the splicing member(s)  54  and/or the panels  50 . In other examples, more than one row of fasteners may be utilized. 
     Each of the panels  50  may be described as having a cross-sectional shape that is generally uniform along the longitudinal panel length  20 . By “generally uniform,” it is meant that the cross-sectional shape may not be perfectly uniform along the full length of the panel  50 , and that slight variations may be present, such as to due to inclusion of one or more of doublers, padups, fastener holes, and the like. In some examples of pressure panel assemblies  10 , the cross-sectional shape is concave toward the high-pressure side  12 , such as in the example pressure panel assemblies  300 ,  400 ,  500 , and  600  of  FIGS.  3 - 6   . As more particular examples, the cross-section shape may be substantially curved, substantially arced, substantially parabolic, or substantially catenary in shape. By being “substantially curved,” “substantially arced,” “substantially parabolic,” or “substantially catenary,” it is meant that at least 75% of the length of the cross-sectional shape has the identified shape (i.e., curved, parabolic, or catenary). For example, as discussed herein, some examples of panels  50  comprise one or more planar regions  40  where the panels  50  are welded to corresponding splicing members  54 , with such planar regions  40  necessarily not having a curved, parabolic, or catenary cross-sectional shape. 
     In some examples of pressure panel assemblies  10 , the splicing members  54  may be described as defining a channel  32  that faces the low-pressure side  14  of the pressure panel assembly  10 . That is, the surface or surfaces of the splicing members  54  facing the low-pressure side  14  may not be contained within a single plane. In particular, the splicing members  54  comprise surfaces that face the low-pressure side  14  and that mate with the corresponding two laterally adjacent panels  50 , and when the panels  50  are concave toward the high-pressure side  12  of the pressure panel assembly  10 , the splicing members  54  necessarily define a channel  32  that faces the low-pressure side  14  to mate with the panels  50 . In examples where the panels  50  comprise planar regions  40 , the surfaces of the splicing members  54  to which the planar regions  40  are welded also are planar. 
     By defining a channel  32  that faces the low-pressure side  14  of the pressure panel assembly  10 , when the air pressure is greater on the high-pressure side  12  of the pressure panel assembly  10 , the radii in the channel  32  will tend to close, as opposed to open. Accordingly, when the splicing members  54  have a laminar construction, such as from fiber-reinforced thermoplastic plies, interlaminar stresses are compressive rather than tensile, resulting in a more robust structure. 
     In some examples, such as in example pressure panel assemblies  300  and  600  of  FIGS.  3  and  6   , each splicing member  54  is welded to the high-pressure side  12  of the corresponding two laterally adjacent panels  50 , and each beam  56  is joined directly to a corresponding splicing member  54 . 
     In other examples, such as in the example pressure panel assemblies  400  and  500  of  FIGS.  4  and  5   , each splicing member  54  is welded to the low-pressure side  14  of the corresponding two laterally adjacent panels  50 , and each beam  56  is joined directly to the high-pressure side  12  of the corresponding two laterally adjacent panels  50 . In such examples, when the air pressure is greater on the high-pressure side  12  of the pressure panel assembly  10 , the panels  50  push against the splicing members  54 , thereby compressing the welds  52  between the panels  50  and the splicing members  54 . 
     In some examples, such as in the example of pressure panel assemblies  500  and  600  of  FIGS.  5  and  6   , the splicing members  54  may be described as being V-shaped. 
     Additionally or alternatively, in some examples, a splicing member  54  may comprise a first leg  34  that is welded to the first panel  16  and a second leg  36  that is welded to the second panel  18 , with the first leg  34  being non-planar with the second leg  36 . Such welds  52  may be described as forming lap joints. In some examples, the first leg  34  and the second leg  36  are planar, and the corresponding panels  50  comprise planar regions  40  that are welded to the first leg  34  and to the second leg  36 . In some examples, such as in example pressure panel assemblies  300  and  400  of  FIGS.  3  and  4   , the splicing member  54  further comprises a base  42  between the first leg  34  and the second leg  36 , with a corresponding beam  56  being joined directly to the base  42 . In some such examples, as in the pressure panel assemblies  300  and  400  of  FIGS.  3  and  4   , the base  42  is planar and is joined directly to a planar surface of the corresponding beam  56 . 
     As in the example pressure panel assemblies  300  and  400  of  FIGS.  3  and  4   , some beams  56  comprise a base flange or flanges  62  having a width  64 , and a pair of laterally adjacent panels  50  are spaced laterally apart from each other by greater than the width  64 . That is, in some examples of pressure panel assemblies  10 , two laterally adjacent panels  50  are spaced apart by a gap  66 , with the gap  66  being greater than or equal to the width  64  and with the corresponding beam  56  being positioned vertically above the gap  66 . Herein, such positional terms as “vertically” are used for convenience, are non-limiting, and refer to the general layout of the example pressure panel assemblies  10  of  FIGS.  3 - 6    as presented on the page. 
       FIG.  7    schematically provides a flowchart that represents illustrative, non-exclusive examples of methods  200  according to the present disclosure. In  FIG.  7   , some steps are illustrated in dashed boxes indicating that such steps may be optional or may correspond to an optional version of a method  200 . That said, not all methods according to the present disclosure are required to include the steps illustrated in solid boxes. The methods and steps illustrated in  FIG.  7    are not limiting and other methods and steps are within the scope of the present disclosure, including methods having greater than or fewer than the number of steps illustrated, as understood from the discussions herein. 
     Methods  200  refer to methods of assembling a pressure panel assembly  10  according to the present disclosure. As schematically presented in  FIG.  7   , methods  200  comprise at least welding  202  a first panel  16  to a splicing member  54  along a longitudinal panel length  20  of the first panel  16 ; welding  204  a second panel  18  to the splicing member  54  along a longitudinal panel length  20  of the second panel  18 ; and directly joining  206  a beam  56  to (i) the splicing member  54  along the longitudinal panel length  20  on the high-pressure side  12  of the splicing member  54  or (ii) to the first panel  16  and to the second panel  18  along the longitudinal panel length  20  on the high-pressure side  12  of the first panel  16  and of the second panel  18 . Welding  202  and welding  204  collectively may be described as welding two laterally adjacent panels  50  to a corresponding splicing member  54  along the longitudinal panel length  20  of the panels  50 . Examples of welding techniques that may be used include (but are not limited to) induction welding, resistance welding, conduction welding, ultrasonic welding, and film joining. 
     In some methods  200 , the directly joining  206  comprises welding  208  the beam  56  to the high-pressure side  12  of the splicing member  54 , as in example pressure panel assemblies  300 ,  400 , and  600  of  FIGS.  3 ,  4 , and  6   . In some methods  200 , the directly joining  206  additionally or alternatively comprises fastening  210  the beam  56  to the high-pressure side  12  of the splicing member  54  with a plurality of fasteners  26 , as in example pressure panel assemblies  300 ,  400 , and  600  of  FIGS.  3 ,  4 , and  6   . 
     In other methods  200 , the directly joining  206  comprises welding  212  the beam  56  to the high-pressure side  12  of the first panel  16  and of the second panel  18 , as in example pressure panel assembly  500  of  FIG.  5   . In some methods, the directly joining  206  additionally or alternatively comprises fastening  214  the beam  56  to the high-pressure side  12  of the first panel  16  and of the second panel  18  with a plurality of fasteners  26 , as in example pressure panel assembly  500  of  FIG.  5   . 
     Illustrative, non-exclusive examples of inventive subject matter according to the present disclosure are described in the following enumerated paragraphs: 
     A. A pressure panel assembly ( 10 ) having a high-pressure side ( 12 ) and a low-pressure side ( 14 ) opposite the high-pressure side ( 12 ), the pressure panel assembly ( 10 ) comprising: 
     panels ( 50 ) comprising at least a first panel ( 16 ) and a second panel ( 18 ) positioned laterally adjacent to the first panel ( 16 ), wherein the first panel ( 16 ) and the second panel ( 18 ) each have a longitudinal panel length ( 20 ); 
     one or more splicing members ( 54 ) comprising at least a first splicing member ( 22 ) welded to the first panel ( 16 ) and to the second panel ( 18 ) along the longitudinal panel length ( 20 ) of the first panel ( 16 ) and the second panel ( 18 ); and one or more beams ( 56 ) comprising at least a first beam ( 24 ) joined directly to the first splicing member ( 22 ) or joined directly to the first panel ( 16 ) and to the second panel ( 18 ), and extending along the longitudinal panel length ( 20 ) on the high-pressure side ( 12 ) of the first splicing member ( 22 ) or on the high-pressure side ( 12 ) of the first panel ( 16 ) and of the second panel ( 18 ). 
     A1. The pressure panel assembly ( 10 ) of paragraph A, wherein the panels ( 50 ) and the one or more splicing members ( 54 ) are constructed of a thermoplastic material, optionally a fiber reinforced thermoplastic material. 
     A2. The pressure panel assembly ( 10 ) of any of paragraphs A-A1, wherein the one or more beams ( 56 ) and the one or more splicing members ( 54 ) are constructed of a thermoplastic material, optionally a fiber reinforced thermoplastic material, and wherein the first beam ( 24 ) is welded to the first splicing member ( 22 ) along the longitudinal panel length ( 20 ). 
     A3. The pressure panel assembly ( 10 ) of any of paragraphs A-A1, wherein the one or more beams ( 56 ) and the panels ( 50 ) are constructed of a thermoplastic material, and wherein the first beam ( 24 ) is welded to the first panel ( 16 ) and to the second panel ( 18 ) along the longitudinal panel length ( 20 ). 
     A4. The pressure panel assembly ( 10 ) of any of paragraphs A-A1, wherein the one or more beams ( 56 ) are constructed of a metallic material, and wherein the first beam ( 24 ) is fastened to the first splicing member ( 22 ) along the longitudinal panel length ( 20 ) with a plurality of fasteners ( 26 ). 
     A5. The pressure panel assembly ( 10 ) of any of paragraphs A-A1, wherein the one or more beams ( 56 ) are constructed of a metallic material, and wherein the first beam ( 24 ) is fastened to the first panel ( 16 ), to the second panel ( 18 ), and to the first splicing member ( 22 ) along the longitudinal panel length ( 20 ) with a plurality of fasteners ( 26 ). 
     A5.1. The pressure panel assembly ( 10 ) of paragraph A5, wherein the first panel ( 16 ) and the second panel ( 18 ) are positioned and compressed between the first splicing member ( 22 ) and the first beam ( 24 ). 
     A5.2. The pressure panel assembly ( 10 ) of paragraph A5, wherein the first beam ( 24 ) is fastened to the first panel ( 16 ), to the second panel ( 18 ), and to the first splicing member ( 22 ) along the longitudinal panel length ( 20 ) with the plurality of fasteners ( 26 ), and wherein the first splicing member ( 22 ) is positioned and compressed between the first beam ( 24 ) and the first panel ( 16 ) and between the first beam ( 24 ) and the second panel ( 18 ). 
     A5.3. The pressure panel assembly ( 10 ) of any of paragraphs A5-A5.2, wherein the first beam ( 24 ) is fastened to the first panel ( 16 ) and to the first splicing member ( 22 ) utilizing a first single row ( 28 ) of the fasteners ( 26 ), and wherein the first beam ( 24 ) is fastened to the second panel ( 18 ) and to the first splicing member ( 22 ) utilizing a second single row ( 30 ) of the fasteners ( 26 ). 
     A6. The pressure panel assembly ( 10 ) of any of paragraphs A-A5.3, wherein the pressure panel assembly ( 10 ) is free of fay seals between the one or more splicing members ( 54 ) and the panels ( 50 ). 
     A7. The pressure panel assembly ( 10 ) of any paragraphs A-A6 except for paragraphs A5-A5.3, wherein the pressure panel assembly ( 10 ) is free of fasteners that couple together the one or more splicing members ( 54 ) and the panels ( 50 ) 
     A8. The pressure panel assembly ( 10 ) of any of paragraphs A-A7, wherein the panels ( 50 ) each have a cross-sectional shape that is generally uniform along the longitudinal panel length ( 20 ), and wherein the cross-sectional shape is concave toward the high-pressure side ( 12 ). 
     A8.1. The pressure panel assembly ( 10 ) of paragraph A8, wherein the cross-sectional shape of the panels ( 50 ) is substantially catenary. 
     A9. The pressure panel assembly ( 10 ) of any of paragraphs A-A8.1, wherein the one or more splicing members ( 54 ) define a channel ( 32 ) that faces the low-pressure side ( 14 ). 
     A9.1. The pressure panel assembly ( 10 ) of paragraph A9, wherein the first splicing member ( 22 ) is welded to the high-pressure side ( 12 ) of the first panel ( 16 ) and the second panel ( 18 ). 
     A9.1.1. The pressure panel assembly ( 10 ) of paragraph A9.1, wherein the first beam ( 24 ) is joined directly to the first splicing member ( 22 ). 
     A9.2. The pressure panel assembly ( 10 ) of paragraph A9, wherein the first splicing member ( 22 ) is welded to the low-pressure side ( 14 ) of the first panel ( 16 ) and the second panel ( 18 ). 
     A9.2.1. The pressure panel assembly ( 10 ) of paragraph A9.2, wherein the first beam ( 24 ) is joined directly to the first panel ( 16 ) and to the second panel ( 18 ). 
     A9.3. The pressure panel assembly ( 10 ) of any of paragraphs A9-A9.2.1, wherein the first splicing member ( 22 ) is generally V-shaped. 
     A9.4. The pressure panel assembly ( 10 ) of any of paragraphs A9-A9.3, wherein the first splicing member ( 22 ) comprises a first leg ( 34 ) welded to the first panel ( 16 ) and a second leg ( 36 ) welded to the second panel ( 18 ), and wherein the first leg ( 34 ) is non-planar with the second leg ( 36 ). 
     A9.4.1. The pressure panel assembly ( 10 ) of paragraph A9.4, wherein each of the first leg ( 34 ) and the second leg ( 36 ) is planar, wherein the first panel ( 16 ) comprises a first panel planar region ( 40 ) welded to the first leg ( 34 ), and wherein the second panel ( 18 ) comprises a second panel planar region ( 40 ) welded to the second leg ( 36 ). 
     A9.4.2. The pressure panel assembly ( 10 ) of any of paragraphs A9.4-A9.4.1, wherein the first splicing member ( 22 ) further comprises a base ( 42 ) between the first leg ( 34 ) and the second leg ( 36 ), and wherein the first beam ( 24 ) is joined directly to the base ( 42 ). 
     A9.4.2.1. The pressure panel assembly ( 10 ) of paragraph A9.4.2, wherein the base ( 42 ) is planar. 
     A10. The pressure panel assembly ( 10 ) of any of paragraphs A-A9.4.2.1, wherein each of the one or more beams ( 56 ) comprises a base flange ( 62 ) having a width ( 64 ) that is transverse to the longitudinal panel length ( 20 ), and wherein the first panel ( 16 ) and the second panel ( 18 ) are spaced laterally apart by greater than the width ( 64 ). 
     A11. The pressure panel assembly ( 10 ) of any of paragraphs A-A10, wherein the second panel ( 18 ) is spaced laterally apart from the first panel ( 16 ) by a gap ( 66 ), and wherein the first beam ( 24 ) is positioned vertically above the gap ( 66 ). 
     A11.1. The pressure panel assembly ( 10 ) of paragraph A11 when depending from paragraph A10, wherein the gap ( 66 ) is greater than or equal to the width ( 64 ). 
     A12. The pressure panel assembly ( 10 ) of any of paragraphs A-A11.1, 
     wherein the panels ( 50 ) further comprise a third panel ( 44 ) positioned laterally adjacent to the second panel ( 18 ) opposite the first panel ( 16 ), wherein the third panel ( 44 ) has the longitudinal panel length ( 20 ); 
     wherein the one or more splicing members ( 54 ) further comprise a second splicing member ( 46 ) welded to the second panel ( 18 ) and to the third panel ( 44 ) along the longitudinal panel length ( 20 ) of the second panel ( 18 ) and the third panel ( 44 ); and 
     wherein the one or more beams ( 56 ) further comprise a second beam ( 48 ) joined directly to the second splicing member ( 46 ) or joined directly to the second panel ( 18 ) and to the third panel ( 44 ), and extending along the longitudinal panel length ( 20 ) on the high-pressure side ( 12 ) of the second splicing member ( 46 ) or on the high-pressure side ( 12 ) of the second panel ( 18 ) and of the third panel ( 44 ). 
     A12.1. The pressure panel assembly ( 10 ) of paragraph A12, further comprising the subject matter of any of paragraphs A1-A11, but with respect to the second panel ( 18 ), the third panel ( 44 ), the second splicing member ( 46 ), and the second beam ( 48 ) in place of the first panel ( 16 ), the second panel ( 18 ), the first splicing member ( 22 ), and the first beam ( 24 ), respectively. 
     A13. Use of the pressure panel assembly ( 10 ) of any of paragraphs A-A12.1 as a pressure deck of an aircraft ( 100 ). 
     B. An aircraft ( 100 ) comprising: 
     a fuselage ( 102 ) with a pressurized compartment ( 104 ); and 
     the pressure panel assembly ( 10 ) of any of paragraphs A-A12.1 supported by the fuselage ( 102 ), wherein the high-pressure side ( 12 ) faces the pressurized compartment ( 104 ) and the low-pressure side ( 14 ) faces away from the pressurized compartment ( 104 ). 
     B1. The aircraft ( 100 ) of paragraph B, further comprising: 
     a wing assembly ( 106 ) comprising wing outboard sections ( 108 ) and a wing center section ( 110 ) between the wing outboard sections ( 108 ), wherein the wing assembly ( 106 ) is supported by the fuselage ( 102 ), wherein the pressure panel assembly ( 10 ) is coupled to the wing center section ( 110 ), and wherein the low-pressure side ( 14 ) faces a wheel well ( 112 ) of the aircraft ( 100 ). 
     C. A method ( 200 ) of assembling the pressure panel assembly ( 10 ) of any of paragraphs A-A12.1, the method ( 200 ) comprising: 
     welding ( 202 ) the first panel ( 16 ) to the first splicing member ( 22 ) along the longitudinal panel length ( 20 ); 
     welding ( 204 ) the second panel ( 18 ) to the first splicing member ( 22 ) along the longitudinal panel length ( 20 ); and 
     directly joining ( 206 ) the first beam ( 24 ) to (i) the first splicing member ( 22 ) along the longitudinal panel length ( 20 ) on the high-pressure side ( 12 ) of the first splicing member ( 22 ) or (ii) to the first panel ( 16 ) and to the second panel ( 18 ) along the longitudinal panel length ( 20 ) on the high-pressure side ( 12 ) of the first panel ( 16 ) and of the second panel ( 18 ). 
     C1. The method ( 200 ) of paragraph C, wherein the directly joining ( 206 ) comprises welding ( 208 ) the first beam ( 24 ) to the high-pressure side ( 12 ) of the first splicing member ( 22 ). 
     C2. The method ( 200 ) of any of paragraphs C-C1, wherein the directly joining ( 206 ) comprises fastening ( 210 ) the first beam ( 24 ) to the high-pressure side ( 12 ) of the first splicing member ( 22 ) with a/the plurality of fasteners ( 26 ). 
     C3. The method ( 200 ) of paragraph C, wherein the directly joining ( 206 ) comprises welding ( 212 ) the first beam ( 24 ) to the high-pressure side ( 12 ) of the first panel ( 16 ) and of the second panel ( 18 ). 
     C4. The method ( 200 ) of paragraph C or C3, wherein the directly joining ( 206 ) comprises fastening ( 214 ) the first beam ( 24 ) to the high-pressure side ( 12 ) of the first panel ( 16 ) and of the second panel ( 18 ) with a/the plurality of fasteners ( 26 ). 
     As used herein, the term “and/or” placed between a first entity and a second entity means one of (1) the first entity, (2) the second entity, and (3) the first entity and the second entity. Multiple entries listed with “and/or” should be construed in the same manner, i.e., “one or more” of the entities so conjoined. Other entities optionally may be present other than the entities specifically identified by the “and/or” clause, whether related or unrelated to those entities specifically identified. Thus, as a non-limiting example, a reference to “A and/or B,” when used in conjunction with open-ended language such as “comprising,” may refer, in one example, to A only (optionally including entities other than B); in another example, to B only (optionally including entities other than A); in yet another example, to both A and B (optionally including other entities). These entities may refer to elements, actions, structures, steps, operations, values, and the like. 
     The various disclosed elements of apparatuses and steps of methods disclosed herein are not required to all apparatuses and methods according to the present disclosure, and the present disclosure includes all novel and non-obvious combinations and subcombinations of the various elements and steps disclosed herein. Moreover, one or more of the various elements and steps disclosed herein may define independent inventive subject matter that is separate and apart from the whole of a disclosed apparatus or method. Accordingly, such inventive subject matter is not required to be associated with the specific apparatuses and methods that are expressly disclosed herein, and such inventive subject matter may find utility in apparatuses and/or methods that are not expressly disclosed herein.