Patent Publication Number: US-2023159151-A1

Title: Aerospace component joints for aircraft and related methods

Description:
FIELD 
     The present disclosure relates to aerospace component joints for aircraft and related methods. 
     BACKGROUND 
     Aerospace parts often are joined together with one or more adhesive bonds that hold the aerospace parts in mechanical connection with one another. Typically, an adhesive bond between two aerospace parts includes an adhesive layer between bonding faces of the two aerospace parts and forming an adhesive bond with each of the bonding faces. During operable use, exterior forces are imparted on the aerospace components joined by the adhesive bond, and these forces may be transferred, or applied to, the adhesive bond in the form of various stresses, for example shear stress and peel stress. If the various stresses applied to the adhesive bond exceed its ultimate load capacity, the adhesive bond will fail. An adhesive bond failure can be partial, in which failures affect only a portion of the adhesive bond, and the aerospace parts remain mechanically connected by the adhesive bond. An adhesive bond failure also can be complete, in which failures affect the entirety of the adhesive bond, and the adhesive bond no longer provides a mechanical connection between the aerospace parts on its own. For both partial and complete bond failures, an adhesive bond typically requires some degree of maintenance before further use. To reduce the likelihood of bond failure, rivets traditionally may be installed along the edges of an aerospace adhesive bond to limit the load applied to the adhesive bond during operable use. The rivets also may allow the joint to withstand operable stresses after adhesive bond failure. While rivets provide redundancy to the adhesive bond in this way, they also can complicate bond failure detection for the same reason. Rivets also can be difficult to install and/or maintain, particularly when at least a portion of the adhesive bond is within a confined space. 
     SUMMARY 
     Aerospace component joints for aircraft, methods of preparing a component member for the aerospace component joints, and methods of forming the aerospace component joint are disclosed herein. The aerospace component joints comprise a first component member comprising a first bonding face, a second component member comprising a second bonding face, an adhesive layer, and one or more bond-enhancing features. The first bonding face overlaps with the second bonding face and is spaced apart from the second bonding face by a gap over a bonded area of the aerospace component joint. The adhesive layer substantially fills the gap and forms an adhesive bond between the first bonding face and the second bonding face. The one or more bond-enhancing features comprise at least one of a plurality of reinforcing protrusions or one or more adhesive-receiving recesses. The reinforcing protrusions are integral with the first component member, project from the first bonding face, extend through the adhesive layer, and penetrate into the second component member via the second bonding face. The one or more adhesive-receiving recesses are defined in one or both of the first bonding face and the second bonding face, and the adhesive layer substantially fills each adhesive-receiving recess. 
     The methods of preparing the component member comprise integrating one or more bond-enhancing features into the component member, which comprises forming the reinforcing protrusions to be integral with the component member and project from a bonding face of the component member and/or creating one or more adhesive-receiving recesses in the bonding face of the component member. The methods of forming the aerospace component joint comprise operably positioning the first bonding face and the second bonding face relative to one another, adhesive-bonding the first bonding face and the second bonding face to one another, and integrating the one or more bond-enhancing features into the aerospace component joint. 
    
    
     
       BRIEF DESCRIPTION OF THE DRAWINGS 
         FIG.  1    is an illustration of an aircraft that comprises at least one aircraft component joint according to the present disclosure. 
         FIG.  2    is a schematic cross-sectional view representing examples of aerospace component joints according to the present disclosure. 
         FIG.  3    is a schematic plan view representing examples of aerospace component joints according to the present disclosure. 
         FIG.  4    is a cross-sectional view showing examples of aerospace component joints comprising adhesive-receiving recesses according to the present disclosure. 
         FIG.  5    is a cross-sectional view showing additional examples of aerospace component joints comprising adhesive-receiving recesses according to the present disclosure. 
         FIG.  6    is a cross-sectional view showing an example aerospace component joint that comprises reinforcing protrusions according to the present disclosure. 
         FIG.  7    is a cross-sectional view showing another example aerospace component joint that comprises reinforcing protrusions according to the present disclosure. 
         FIG.  8    is a cross-sectional view showing an example aerospace component joint that comprises reinforcing protrusions and adhesive-receiving recesses according to the present disclosure. 
         FIG.  9    is a flowchart schematically representing examples of methods of preparing a component member for an aerospace component joint according to the present disclosure. 
         FIG.  10    is a flowchart schematically representing examples of methods of forming an aerospace component joint according to the present disclosure. 
     
    
    
     DETAILED DESCRIPTION 
       FIGS.  1 - 10    provide examples of aerospace component joints  100  for aircraft, aircraft  10  comprising at least one aerospace component joint  100 , methods  500  of preparing a component member for an aerospace component joint  100 , and methods  600  of forming an aerospace component joint  100  according to the present disclosure. Elements that serve a similar, or at least substantially similar, purpose are labelled with like numbers in each of  FIGS.  1 - 10   , and these elements may not be discussed herein with reference to each of  FIGS.  1 - 10   . Similarly, all elements may not be labeled in each of  FIGS.  1 - 10   , but reference numerals associated therewith may be utilized herein for consistency. Elements, components, and/or features that are discussed herein with reference to one or more of  FIGS.  1 - 10    may be comprised in and/or utilized with any of  FIGS.  1 - 10    without departing from the scope of the present disclosure. 
     Generally, in the figures, elements that are likely to be comprised in a given example are illustrated in solid lines, while elements that are optional to a given example are illustrated in dashed 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 present disclosure. Additionally, in schematic  FIGS.  2  and  3   , virtual features, such as dimensions, boundaries, etc., that may be defined by aerospace component joints  100  are indicated in dot-dash lines, and these virtual features may or may not be optional to the illustrated embodiment. 
       FIG.  1    is an illustration of an aircraft  10  that comprises at least one aerospace component joint  100 , and optionally a plurality of aerospace component joints  100 , according to the present disclosure. Examples of aerospace component joints  100  are illustrated in  FIGS.  2 - 8    and discussed in more detail herein with reference thereto. As shown in the examples of  FIG.  1   , aircraft  10  typically comprises at least a fuselage  11 , wings  12  that are supported by the fuselage  11 , and at least one aerospace component joint  100 . In some examples, aircraft  10  also comprises at least one engine  14  operatively attached to fuselage  11 , such as via a corresponding wing  12 . In some examples, aircraft  10  further comprises a tail assembly  16  that is operatively attached to and/or at least partially defined by fuselage  11 . Tail assembly  16  may comprise at least one vertical stabilizer  18  and/or at least one horizontal stabilizer  20 . In some examples, fuselage  11 , wing(s)  12 , engine(s)  14 , tail assembly  16 , vertical stabilizer  18 , and/or horizontal stabilizer  20 , comprise a corresponding aerospace component joint  100  and/or comprise at least two component members that are joined by aerospace component joint  100 . Likewise, some examples of aircraft  10  comprise at least one attachment structure for operatively attaching two or more of the fuselage  11 , wing(s)  12 , engine(s)  14 , vertical stabilizer(s)  18 , and/or horizontal stabilizer(s)  20 . In some such examples, the attachment structure comprises at least one aerospace component joint  100  and/or comprises at least two component members joined together by aerospace component joint  100 . 
     While  FIG.  1    illustrates a fixed wing aircraft, other apparatuses are within the scope of the present disclosure, and the present disclosure is not limited to aircraft and aircraft applications. Illustrative non-exclusive examples of other apparatuses that are suitable to be constructed with aerospace component joints  100  comprise, but are not limited to, spacecraft, watercraft, land vehicles, structural towers, rotorcraft, tilt-wing craft, missiles, and/or rockets. 
       FIGS.  2  and  3    are schematic representations showing examples of aerospace component joints  100  for aircraft, such as for aircraft  10  of  FIG.  1   , according to the present disclosure. Specifically,  FIG.  2    is a schematic cross-sectional view of aerospace component joints  100  and  FIG.  3    is a schematic plan view of aerospace component joints  100 . With reference to the examples of  FIGS.  2  and  3   , aerospace component joints  100  comprise a first component member  102  comprising a first bonding face  104  and a second component member  106  comprising a second bonding face  108 . First bonding face  104  and second bonding face  108  overlap one another along a bonded area  114 , and first bonding face  104  and second bonding face  108  are separated from one another along the bonded area  114  by a gap  110 . Aerospace component joints  100  further comprise an adhesive layer  112  substantially filling gap  110  and forming an adhesive bond  134  between first bonding face  104  and second bonding face  108 . Thus, aerospace component joint  100  additionally or alternatively may be referred to as an adhesive-bonded aerospace component joint. As defined herein, the adhesive layer  112  “substantially filling gap  110 ” refers to the adhesive layer  112  filling at least 90% of the volume of the gap  110 . 
     Aerospace component joints  100  further comprise one or more bond-enhancing features  200  that may be configured to enhance the strength, durability, and/or longevity of aerospace component joint  100  and/or reduce the propensity for failures to occur within and/or propagate through adhesive bond  134 . As defined herein, adhesive layer  112 , the bond between adhesive layer  112  and first bonding face  104 , and the bond between adhesive layer  112  and second bonding face  108  collectively form the adhesive bond  134  between first component member  102  and second component member  106 . 
     The one or more bond-enhancing features  200  comprise at least one of a plurality of reinforcing protrusions  202  or one or more adhesive-receiving recesses  204 . Stated differently, in some examples, bond-enhancing features  200  only comprise reinforcing protrusions  202 . In other examples, bond-enhancing features  200  only comprise one or more adhesive-receiving recesses  204 . In yet other examples, bond-enhancing features  200  comprise each of reinforcing protrusions  202  and one or more adhesive-receiving recesses  204 . 
     When comprised in aerospace component joint  100 , reinforcing protrusions  202  are integral with first component member  102 , project from first bonding face  104 , extend through adhesive layer  112 , and penetrate into second component member  106  through second bonding face  108 . Thus, reinforcing protrusions  202  differ from traditional fasteners at least in that reinforcing protrusions  202  are integral and/or form a portion of first component member  102 . 
     When comprised in aerospace component joint  100 , the one or more adhesive-receiving recesses  204  are defined in one or both of first bonding face  104  and second bonding face  108 , and adhesive layer  112  substantially fills each adhesive-receiving recess  204 . In other words, each adhesive-receiving recess  204  may be described as forming, or defining, a portion of the gap  110 , and each adhesive-receiving recess  204  is configured to receive a corresponding portion of adhesive layer  112 . As defined herein, adhesive layer  112  “substantially” filling each adhesive-receiving recess  204  refers to the adhesive layer  112  filling at least 90% of the volume of each adhesive-receiving recess  204 . 
     Aerospace component joint  100  is formed between any suitable component members. As an example, first component member  102  and second component member  106  may form portions of a connecting structure in an aircraft. As another example, second component member  106  may form a portion of the skin of an aircraft and first component member  102  may be, or form a portion of, a structural component that supports the aircraft skin, for example, a stringer, a rib, a spar former, and/or a longeron. 
     First component member  102  and second component member  106  are formed from any suitable material or materials. In some examples, first component member  102  and second component member  106  are formed of one or more of the same materials, and in other examples, first component member  102  and second component member  106  are formed of one or more different materials. In some examples, first component member  102  is formed of a metal or a metal alloy, and second component member  106  is formed of a plastic material. In other examples, first component member  102  and second component member  106  each are formed of a plastic material. In some examples, the plastic material that forms first component member  102  and/or second component member  106  is a fiber-reinforced plastic material, or a fiber-reinforced composite material. Examples of suitable plastic materials include thermoplastic polymers, thermoset polymers, resins, cross-linking resins, epoxy polymers, melt polyaryletherketone (PAEK) polymers, polyphenylene sulfide (PPS), polyether ether ketone (PEEK), and/or polyetherketoneketone (PEKK). Examples of suitable reinforcing fibers include woven fibers, continuous fibers, chopped fibers, reinforcing particles, carbon fibers, glass fibers, boron fibers, ultra-high molecular weight polyethylene fibers, aramid fibers, and/or para-aramid fibers (e.g., KEVLAR™). Examples of suitable metals and metal alloys for forming first component member  102  comprise aluminum, titanium, and aluminum or aluminum alloys comprising manganese, silicon, scandium, zinc, magnesium, copper, and/or combinations thereof. In more general terms, first component member  102  and second component member  106  may be formed of types of fiber-reinforced plastic materials, metals, or metal alloys that are typically utilized in aircraft and/or aerospace applications, as will be understood by a person of ordinary skill in the art. 
     For examples in which first component member  102  is formed from a metal, or metal alloy, and second component member  106  is formed of a plastic material, aerospace component joint  100  may be referred to as a metal-to-composite joint. For examples in which first component member  102  and second component member  106  each are formed of a fiber-reinforced plastic material, aerospace component joint  100  may be referred to as a composite-to-composite joint. 
     Adhesive layer  112  also comprises any suitable adhesive, such as an adhesive that is typically utilized in aircraft and/or aerospace applications, as will be understood by a person of ordinary skill in the art. For examples in which first component member  102  and second component member  106  are both formed from plastic materials and/or fiber-reinforced plastic materials, the adhesive for adhesive layer  112  may be a plastic-to-plastic, or composite-to-composite adhesive. For examples in which first component member  102  is formed of a metal, or a metal alloy, and second component member  106  is formed of a plastic material, or a fiber-reinforced plastic material, the adhesive may be a metal-to-plastic, or a metal-to-composite adhesive. More specific examples of suitable adhesives comprise resins, an epoxy resin, epoxy adhesives, two-part adhesives, vulcanizing silicone rubber adhesives, polysulfide adhesives, manganese dioxide cured adhesives, sealants, and/or a curable composite material. 
     Aerospace component joint  100  may comprise a variety of conformations, and the particular conformation of aerospace component joint  100  typically is at least partially determined by the component members of the aircraft that aerospace component joint  100  is formed between. For example, while  FIG.  2    schematically illustrates first component member  102  and second component member  106  as being planar, or collinear, along aerospace component joint  100 , first component member  102  and second component member  106  additionally or alternatively may be curved, shaped, non-planar, and/or non-linear along aerospace component joint  100  without departing from the scope of the present disclosure. 
     In some examples, first bonding face  104  and second bonding face  108  extend generally parallel to one another along the bonded area  114 . As referred to herein, a first element extending “generally parallel to” a second element refers to the first element extending within 5 degrees of parallel to the second element. Also in this context, the first bonding face  104  extending generally parallel to the second bonding face  108  refers to the portions of the first bonding face  104  and the second bonding face  108  that are not modified by bond-enhancing features  200 . 
     Bonded area  114  may be defined as an area of first bonding face  104  over which adhesive layer  112  is bonded to first bonding face  104  or an area of second bonding face  108  over which adhesive layer  112  is bonded to second bonding face  108 . In particular, aerospace component joint  100  defines a width  118  that may be described as the extent of overlap between first bonding face  104  and second bonding face  108 . Aerospace component joint  100  also defines a length  116  that is measured transverse to width  118  and that represents the distance, or length, over which first bonding face  104  and second bonding face  108  are overlapped and adhesively bonded to one another. With this in mind, bonded area  114  may be defined by the width  118  and length  116  of aerospace component joint  100 . 
     In some examples, adhesive layer  112  and/or gap  110  extend between and/or define a pair of longitudinal boundaries  120  that run parallel to the length  116  of aerospace component joint  100  and that are spaced apart from one another by width  118 . For example, each longitudinal boundary  120  may be defined by an edge of first component member  102  or second component member  106  or a plane along which first bonding face  104  or second bonding face  108  diverge from extending generally parallel to one another. In more specific examples, first component member  102  comprises a first joint edge  122  that defines one of the longitudinal boundaries  120 , and second component member  106  comprises a second joint edge  124  that is opposed to first joint edge  122  and that defines the other longitudinal boundary  120 . In such examples, width  118  is defined between first joint edge  122  and second joint edge  124 . 
     Bond-enhancing features  200  are distributed in any suitable manner about aerospace component joint  100  and/or bonded area  114  thereof. As discussed in more detail herein, various stresses are applied to aerospace component joint  100  during operable use thereof (e.g., during flight operations of the aircraft) and bond-enhancing features  200  are distributed about aerospace component joint  100  in a manner that strengthens aerospace component joint  100  against the various stresses, increases the yield strength of aerospace component joint  100 , and/or reduces the propensity for failures to form within and/or propagate through adhesive bond  134 . 
     More specific examples of stresses applied to aerospace component joint  100  during operable use comprise shear stress  300  and peel stress  302 . As schematically represented in  FIG.  2   , shear stress  300  generally is aligned with width  118  and directed away from bonded area  114 , while peel stress  302  generally is aligned with a nominal thickness  130  of adhesive layer  112  and directed away from bonded area  114 . In some examples, shear stress  300  urges first component member  102  and second component member  106  away from one another in respective directions that reduce the magnitude of width  118 . In some examples, peel stress  302  urges first component member  102  and second component member  106  away from one another in respective directions that increase the separation between first bonding face  104  and second bonding face  108 . 
     In some examples, reinforcing protrusions  202  are configured to reduce, and/or disposed along aerospace component joint  100  in a manner that reduces, shear stress  300  and/or peel stress  302  applied to adhesive bond  134 . In some examples, shear stress  300  and/or peel stress  302  are concentrated in adhesive bond  134  adjacent to, or towards, longitudinal boundaries  120 . With this in mind, in some examples, reinforcing protrusions  202  comprise one or more reinforcing protrusions  202  disposed adjacent to either or both of longitudinal boundaries  120 . In some examples, reinforcing protrusions  202  are distributed along at least a substantial portion of the length of aerospace component joint  100 , such as to reduce peel stress  302  and/or shear stress  300  applied to adhesive bond  134  along at least the substantial portion of the length of aerospace component joint  100 . 
     In more specific examples, reinforcing protrusions  202  comprise a first subset  206  of reinforcing protrusions  202  disposed adjacent to, and interior of first joint edge  122 , or a first longitudinal boundary  120 , and a second subset  208  of reinforcing protrusions  202  disposed adjacent to, and interior of, second joint edge  124 , or a second longitudinal boundary  120 . In this context, an element being spaced “interior of” first joint edge  122 , second joint edge  124 , or a longitudinal boundary  120  refers to the element being spaced towards the lateral center of the gap  110  or towards the other longitudinal boundary  120 . Also in this context, first subset  206  of reinforcing protrusions  202  being disposed “adjacent to” first joint edge  122  or the first longitudinal boundary  120  refers to the first subset  206  of reinforcing protrusions  202  being positioned within 20% of width  118  from first joint edge  122  or the first longitudinal boundary  120 . Likewise, second subset  208  of reinforcing protrusions  202  is positioned within 20% of width  118  from second joint edge  124  or the second longitudinal boundary  120 . In other words, first subset  206  and second subset  208  of reinforcing protrusions  202  are spaced apart from one another along the width  118  of aerospace component joint  100 . 
     In some examples, first subset  206  of reinforcing protrusions  202  and/or second subset  208  of reinforcing protrusions  202  comprise at least one row, and optionally a plurality of rows, of reinforcing protrusions  202  that are distributed along a substantial portion of the length  116  of aerospace component joint  100 . For examples in which first subset  206  and/or second subset  208  comprises a plurality of rows of reinforcing protrusions  202 , the rows of a given subset may be spaced apart from one another about width  118  and optionally extend in parallel along length  116 . That said, the rows of a particular subset typically are positioned closer to one another than are first subset  206  and second subset  208 . 
     In some examples, reinforcing protrusions  202  are distributed along at least a substantial portion of width  118  of aerospace component joint  100 , such as to reduce peel stress  302  and/or shear stress  300  along at least the substantial portion of width  118 . In some examples, reinforcing protrusions  202  are evenly distributed along width  118 . Alternatively, in some examples, reinforcing protrusions  202  comprise at least one, and optionally a plurality of, additional subsets  210  of reinforcing protrusions  202  disposed between first subset  206  and second subset  208  of reinforcing protrusions  202 . In some examples, each additional subset  210  of reinforcing protrusions  202  comprises at least one row, and optionally a plurality of rows, of reinforcing protrusions  202  disposed along a substantial portion of length  116 . In some examples, additional subsets  210  of reinforcing protrusions  202  are spaced apart from one another, and optionally evenly spaced apart from one another, along width  118 . 
     As seen in  FIGS.  2  and  3   , aerospace component joints  100  may comprise fasteners  132 , such as rivets, that are configured to reduce shear stress  300  and peel stress  302  applied to adhesive bond  134 . Typically, fasteners  132 , or more specifically rivets, are positioned adjacent to longitudinal boundaries  120 , and extend through first component member  102 , gap  110 , and second component member  106 . First component member  102  defines a first counter face  127  opposed to first bonding face  104 , second component member  106  defines a second counter face  128  opposed to second bonding face  108 . Each fastener  132  typically engages first counter face  127  and second counter face  128  to retain first component member  102  and second component member  106  together. Unlike fasteners  132 , any given reinforcing protrusion  202  protrudes from first bonding face  104  and may extend entirely within gap  110  and second component member  106 . In other words, reinforcing protrusions  202  may not extend through first counter face  127  or second counter face  128  as do fasteners  132 . 
     Each reinforcing protrusion  202  is integral with first bonding face  104  in any suitable manner. In some examples, reinforcing protrusions  202  are formed on and/or additively manufactured on first bonding face  104 . In some examples, reinforcing protrusions  202  are welded, sintered, and/or bonded on first bonding face  104 . In some examples, reinforcing protrusions  202  are formed together with first component member  102  in a concerted process, for example, by molding first component member  102  and reinforcing protrusions  202  as portions of first component member  102 . In other examples, reinforcing protrusions  202  are formed by a subtractive manufacturing process, such as by machining, milling, and/or embossing first bonding face  104  to form reinforcing protrusions  202 . In view of the above, reinforcing protrusions typically are formed of one or more of the same materials as first component member  102  and/or one or more materials that are compatible with welding, sintering, and/or bonding to first component member  102 . 
     In some examples, bond-enhancing features  200  comprise reinforcing protrusions  202  when first component member  102  is formed of a metal, or a metal alloy, and second component member  106  is formed of a plastic material, or a fiber-reinforced plastic material. As discussed in more detail herein, in some examples, such a configuration of aerospace component joint  100  permits reinforcing protrusions to be penetrated into second component member  106  during assembly of aerospace component joint  100  without pre-forming bores within second component member  106  to receive reinforcing protrusions  202 . 
     Reinforcing protrusions  202  also are conformed in any suitable manner. As examples, reinforcing protrusions  202  may comprise a plurality of pins, a plurality of columnar projections, and/or a plurality of ridges. Each reinforcing protrusion  202  defines a cross-sectional shape taken in a plane parallel to first bonding face  104 , and examples of suitable cross-sectional shapes for each reinforcing protrusion  202  comprise a circle, a square, a rectangle, a rectangle elongated along length  116 , a cross, a polygon, and/or tubular or hollow versions thereof. For some examples in which reinforcing protrusions  202  comprise a plurality of ridges, each ridge is elongate parallel to length  116  and optionally extends along at least a substantial portion of length  116 . In some more specific examples, each ridge may replace one of the rows of reinforcing protrusions  202  discussed herein in connection to first subset  206 , second subset  208 , and additional subset  210  of reinforcing protrusions  202 . 
     In some examples, each reinforcing protrusion  202  is dimensioned to protrude into second component member  106  by a selected protrusion depth  212 . In particular, second component member  106  defines a second member thickness  126  along bonded area  114  that is measured between second bonding face  108  and second counter face  128 . In some examples, each reinforcing protrusion  202  is dimensioned such that protrusion depth  212  thereof is a threshold fraction of second member thickness  126  along bonded area  114 , with examples of this threshold fraction comprising at least 60%, at least 65%, at least 70%, at least 75%, at least 80%, at least 85%, at least 90% at least 95%, at least 98%, at most 75%, at most 80%, at most 85%, at most 90%, at most 95%, at most 98%, and/or at most 99%. 
     Each reinforcing protrusion  202  also defines a cross-sectional area that is measured in a plane parallel to first bonding face  104 , and the plurality of reinforcing protrusions  202  define a cumulative cross-sectional area that is a sum of the cross-sectional areas of all reinforcing protrusions  202 . Similarly, fasteners  132  of an otherwise equivalent conventional aerospace component joint each define a fastener cross-sectional area that is measured in a plane parallel to first bonding face  104  and collectively define a cumulative fastener cross-sectional area that is the sum of the fastener cross-sectional areas of all fasteners  132 . As referred to herein, the otherwise equivalent conventional aerospace component joint comprises all of the same features, functions, dimensions, elements, etc. as aerospace component joint  100 , except that the otherwise equivalent conventional aerospace component joint comprises fasteners  132  and does not comprise bond-enhancing features  200 . In some examples, reinforcing protrusions  202  are configured such that the cumulative cross-sectional area thereof is at least substantially the same as the cumulative fastener cross-sectional area of the otherwise equivalent conventional aerospace component joint. 
     In some examples, each reinforcing protrusion  202  comprises a shear strength, and the plurality of reinforcing protrusions collectively comprise a cumulative shear strength that corresponds to the shear strength multiplied by the cumulative cross-sectional area. In some examples, reinforcing protrusions  202  are configured such that the cumulative shear strength thereof is equal to or greater than a limit shear load of the aerospace component joint  100 . As defined herein, “the limit shear load” refers to the maximum shear load that is applied to aerospace component joint  100  during operable use in the aircraft, for example, during flight operations. The limit shear load may vary based on the particular location and/or function of aerospace component joint  100 . Thus, stating the above in slightly different terms, in some examples, reinforcing protrusions  202  are configured to possess a cumulative shear strength that is equal to or greater than the maximum load applied to aerospace component joint  100  during operable use. In some examples, the cumulative shear strength of reinforcing protrusions  202  is increased by increasing the number of reinforcing protrusions, increasing the cross-sectional area of each reinforcing protrusion, and/or increasing the shear strength of the material that forms each reinforcing protrusion  202 . 
     With continued reference to  FIGS.  2  and  3   , each adhesive-receiving recess  204  may be configured to create a corresponding region of increased thickness in adhesive layer  112 . In some examples, the one or more regions of increased thickness in the adhesive layer  112  created by the one or more adhesive-receiving recesses  204  allows adhesive bond  134  to withstand larger shear stress  300  loads and/or larger peel stress  302  loads before failure. Additionally or alternatively, in some examples, the one or more regions of increased thickness in adhesive layer  112  created by adhesive-receiving recess(es)  204  causes cracks and/or failures within adhesive layer  112  to terminate in adhesive-receiving recess(es)  204 . In other words, adhesive-receiving recess(es)  204  may be configured to guide cracks and/or failures in adhesive layer  112  to terminate in adhesive-receiving recess(es)  204  and/or prevent the propagation of the cracks or failures through adhesive layer  112 . 
     More specifically, in some examples, adhesive layer  112  comprises a flexibility or elasticity that is greater than the flexibility or elasticity of first component member  102  and/or second component member  106 . In some examples, by creating one or more regions of increased thickness in adhesive layer  112 , adhesive-receiving recess(es)  204  create one or more corresponding regions of increased flexibility, or strain tolerance, within the adhesive bond  134 . In other words, each adhesive-receiving recess  204  may reduce stress concentration within adhesive bond  134  and/or distribute stresses within adhesive bond  134 . In this way, adhesive-receiving recess(es)  204  may increase the shear strength and/or peel strength of adhesive bond  134 . Additionally or alternatively, adhesive-receiving recess(es) may create one or more relief regions that prevent complete bond failure from occurring in adhesive bond  134 . 
     As perhaps best seen in  FIG.  2   , adhesive layer  112  comprises a nominal thickness  130  that is measured between first bonding face  104  and second bonding face  108  outside of the one or more adhesive-receiving recesses  204 . Each adhesive-receiving recess  204  defines a recess depth  214  that is measured parallel to nominal thickness  130 . In some examples, recess depth  214  of each adhesive-receiving recess  204  is greater than nominal thickness  130  of adhesive layer  112 . In such examples, the thickness of adhesive layer  112  along each adhesive-receiving recess  204  is greater than twice the nominal thickness  130  of adhesive layer  112 . In some examples, each adhesive-receiving recess  204  is dimensioned such that recess depth  214  thereof is a threshold fraction of nominal thickness  130  of adhesive layer  112 . More specific examples of the threshold fraction of recess depth  214  to nominal thickness  130  comprise at least 100%, at least 200%, at least 300%, at least 400%, at least 500%, at least 600%, at least 700%, at least 800%, at least 900%, at most 300%, at most 400%, at most 500%, at most 600%, at most 700%, at most 800%, at most 900%, and/or at most 1000%. 
     The one or more adhesive-receiving recesses  204  are distributed along aerospace component joint  100  in any suitable manner. In some examples, adhesive-receiving recess(es)  204  are disposed and/or extend along a substantial portion of the length  116  of aerospace component joint  100 , such as to enhance adhesive bond  134  as discussed herein along the substantial portion of length  116 . In this context, “the substantial portion” of length  116  is utilized herein to refer to at least 90% of length  116 . In some examples, aerospace component joint  100  comprises a plurality of adhesive-receiving recesses  204 . In some such examples, one or more adhesive-receiving recesses  204  are defined in first bonding face  104  and second bonding face  108 . In some examples, aerospace component joint  100  comprises a plurality of adhesive-receiving recesses  204  defined in first bonding face  104  and optionally distributed along at least a substantial portion of width  118 . In some examples, aerospace component joint  100  comprises a plurality of adhesive-receiving recesses  204  defined in second bonding face  108  and optionally distributed along at least a substantial portion of width  118 . 
     Each adhesive-receiving recess  204  comprises any suitable conformation. In some examples, adhesive-receiving recess  204  comprises a groove formed in first bonding face  104  or second bonding face  108 . In some examples, the groove extends along the substantial portion of length  116 . In some examples, the groove extends at a fixed distance between longitudinal boundaries  120  as it extends along the substantial portion of length  116 . In other examples, the groove extends in a non-linear conformation, such as an undulating conformation and/or a zig-zag conformation, along the substantial portion of length  116 . In some examples, adhesive-receiving recesses  204  comprise a plurality of grooves defined in first bonding face  104  and second bonding face  108  and optionally distributed along the width  118  of aerospace component joint  100 . In some such examples, the grooves are spaced apart from one another about the width  118 . In other examples, the grooves intersect one another as they extend along first bonding face  104  and/or second bonding face  108 . Additionally or alternatively, in some examples, adhesive-receiving recesses  204  comprise a plurality of spaced-apart divots, indents, and/or craters distributed along first bonding face  104  and/or second bonding face  108 . In some examples, first bonding face  104  and/or second bonding face  108  comprises a textured conformation that defines the plurality of adhesive-receiving recesses  204 . As examples, first bonding face  104  and/or second bonding face  108  may be machined, engraved, embossed, milled, and/or otherwise provided with a crosshatched pattern, a dimpled pattern, and/or a randomly roughened conformation that defines or forms the plurality of adhesive-receiving recesses  204  therein. 
     In some examples, adhesive-receiving recess(es)  204  comprise one or more edge recesses. In some examples, each edge recess is configured to increase the shear strength and/or the peel strength of adhesive bond  134  adjacent to a respective longitudinal boundary  120 , such as in the manner discussed herein generally for adhesive-receiving recesses  204 . More specifically, in some examples, adhesive-receiving recess(es)  204  comprise a first edge recess  216  defined in first bonding face  104  and extending interiorly from first joint edge  122  of first component member  102 . In this context, the term “interiorly” is utilized to refer to towards the lateral center of aerospace component joint  100  or towards the other longitudinal boundary  120 . In some such examples, first bonding face  104  along first edge recess  216  extends towards second bonding face  108  and forms a first edge recess angle  220  with the portion of first bonding face  104  that is immediately adjacent to first edge recess  216 . As examples, first edge recess angle  220  may be at most 175 degrees (°), at most 170°, at most 160°, at most 150°, at most 140°, at most 130°, at most 135° at most 120°, at most 110°, at least 150°, at least 140°, at least 130°, at least 120°, at least 110°, and/or at least 100°. 
     In some examples, adhesive-receiving recess(es)  204  comprise a second edge recess  218  defined in second bonding face  108  and extending interiorly from second joint edge  124  of second component member  106 . In some such examples, second bonding face  108  along second edge recess  218  forms a second edge recess angle  222  with the portion of second bonding face  108  that is immediately adjacent to second edge recess  218 . As examples, second edge recess angle  222  may be at most 175°, at most 170°, at most 160°, at most 150°, at most 140°, at most 130°, at most 135° at most 120°, at most 110°, at least 150°, at least 140°, at least 130°, at least 120°, at least 110°, and/or at least 100°. In some examples, adhesive-receiving recesses  204  comprise both of first edge recess  216  and second edge recess  218 . 
     As mentioned, in some examples, bond-enhancing features  200  comprise both of reinforcing protrusions  202  and adhesive-receiving recess(es)  204 . In such examples, adhesive-receiving recesses  204  and reinforcing protrusions  202  are distributed about aerospace component joint  100  in any suitable relationship to one another. In some examples, adhesive-receiving recesses  204  and reinforcing protrusions  202  are distributed such that reinforcing protrusions  202  extend completely outside of adhesive-receiving recesses  204 . In other words, reinforcing protrusions  202  may not extend from within, or into, adhesive-receiving recesses  204 . In some examples, adhesive-receiving recesses  204  and reinforcing protrusions  202  are disposed in an alternating relationship along the width  118  of aerospace component joint  100 . 
       FIGS.  4 - 8    are cross-sectional views providing illustrative, non-exclusive examples of aerospace component joints  100  according to the present disclosure. The cross-sectional views of  FIGS.  4 - 8    are taken in a plane parallel to the width  118  and normal to the length  116  of the illustrated aerospace component joint  100 . Specifically,  FIG.  4    provides an illustrative non-exclusive example of aerospace component joint  100  that is indicated at and referred to herein as aerospace component joint  40 ,  FIG.  5    provides an illustrative non-exclusive example of aerospace component joint  100  that is indicated at and referred to herein as aerospace component joint  50 ,  FIG.  6    provides an illustrative non-exclusive example of aerospace component joint  100  that is indicated at and referred to herein as aerospace component joint  60 ,  FIG.  7    provides an illustrative non-exclusive example of aerospace component joint  100  that is indicated at and referred to herein as aerospace component joint  70 , and  FIG.  8    provides an illustrative non-exclusive example of aerospace component joint  100  that is indicated at and referred to herein as aerospace component joint  80 . Example aerospace component joints  40 ,  50 ,  60 ,  70  and  80  are non-exclusive and do not limit aerospace component joints  100  to the illustrated embodiments of  FIGS.  4 - 8   . That is, aerospace component joints may incorporate any number of the various aspects, configurations, characteristics, properties, etc. of aerospace component joints  100  according to schematic  FIGS.  2 - 3   , and/or the examples of  FIGS.  4 - 8   , as well as variants thereof, without requiring the inclusion of all such aspects, configurations, characteristics, properties, etc. For the purpose of brevity, each discussed component, part, portion, aspect, region, etc. or variants thereof may not be discussed, illustrated, and/or labeled with respect to aerospace component joints  40 ,  50 ,  60 ,  70  and  80 ; however, it is within the scope of the present disclosure that the discussed features, variants, etc. of aerospace component joints  100  of  FIGS.  2  and  3    may be comprised and/or utilized with aerospace component joints  40 ,  50 ,  60 ,  70  and  80 . Likewise, the specific illustrated and discussed aspects of aerospace component joints  40 ,  50 ,  60 ,  70  and  80  may be comprised in and/or utilized with other aerospace component joints  100  according to the present disclosure. 
       FIGS.  4  and  5    illustrate examples in which bond-enhancing features  200  comprise adhesive-receiving recesses  204 . With initial reference to  FIG.  4   , aerospace component joint  40  comprises first component member  102  and second component member  106 . In some examples, first component member  102  is formed of a metal, or metal alloy, and second component member  106  is formed of a fiber-reinforced plastic material. In other examples, first component member  102  and second component member  106  each are formed of a fiber-reinforced plastic material. Adhesive layer  112  fills gap  110  between first bonding face  104  and second bonding face  108  and forms adhesive bond  134  therebetween. Aerospace component joint  40  further comprises a plurality of adhesive-receiving recesses  204  defined in first bonding face  104 . Here, adhesive-receiving recesses  204  are evenly spaced apart along the width  118  of aerospace component joint  40 . In some examples, each adhesive-receiving recess  204  comprises a groove that extends along at least a substantial portion of the length of aerospace component joint  40 . 
     In some examples, aerospace component joint  40  further includes fasteners  132  positioned adjacent to, and spaced interiorly of, longitudinal boundaries  120 . Each fastener  132  extends through a bore formed in first component member  102 , adhesive layer  112 , and second component member  106  and engages first counter face  127  and second counter face  128  to retain first component member  102  and second component member  106  to one another. 
     Under operative conditions, external forces apply shear stress  300  and peel stress  302  to aerospace component joint  40  via first component member  102  and second component member  106 . Adhesive-receiving recesses  204  increase loads of shear stress  300  and peel stress  302  that can be applied to adhesive bond  134  before failure. Adhesive-receiving recesses  204  also prevent failures in adhesive bond  134  from propagating through the width  118  of aerospace component joint  40 , such as discussed herein. 
     Turning to  FIG.  5   , example aerospace component joints  50  are similar to aerospace component joints  40 ; however, adhesive-receiving recesses  204  in aerospace component joints  50  further comprise first edge recess  216  and second edge recess  218 . First edge recess  216  and second edge recess  218  respectively extend inwardly from first joint edge  122  and second joint edge  124 . First edge recess  216  and second edge recess  218  each extend substantially along the length of aerospace component joint  50 . First edge recess  216  and second edge recess  218  define portions of gap  110  and are substantially filled with adhesive layer  112  to create regions of increased thickness in adhesive layer  112  adjacent to longitudinal boundaries  120  of aerospace component joint  50 . First edge recess  216  and second edge recess  218  thereby provide additional increased flexibility, or strain tolerance, along the longitudinal edge regions of aerospace component joint  50 , where shear stress  300  and peel stress  302  may be concentrated. In this way, first edge recess  216  and second edge recess  218  permit aerospace component joint  50  to withstand greater shear stress  300  and peel stress  302  loads before failure initiation in adhesive bond  134 . 
     In some examples, aerospace component joint  50  further comprises a plurality of adhesive-receiving recesses  204  defined in second bonding face  108  and spaced apart from one another along the width  118  of aerospace component joint  50 . In some such examples, adhesive-receiving recesses  204  of second bonding face  108  are spaced apart from, or non-overlapping with, the adhesive-receiving recesses  204  of first bonding face  104 . In such examples, aerospace component joint  50  comprises an alternating pattern of adhesive-receiving recesses  204  in first bonding face  104  and second bonding face  108 . In some examples, aerospace component joint  50  comprises adhesive-receiving recesses in each of first bonding face  104  and second bonding face  108  when first component member  102  and second component member  106  each are formed of a fiber-reinforced plastic material. 
     Now with reference to  FIG.  6   , aerospace component joint  60  provides an example in which bond-enhancing features  200  comprise reinforcing protrusions  202 . More specifically, reinforcing protrusions  202  are integral with first component member  102  and protrude from first bonding face  104 . Reinforcing protrusions  202  extend through adhesive layer  112  and penetrate into second component member  106  through second bonding face  108 . Reinforcing protrusions  202  extend through a substantial portion of second member thickness  126  and terminate within second component member  106 . In other words, reinforcing protrusions  202  do not extend through, and/or do not penetrate, second counter face  128  of second component member  106 . 
     Reinforcing protrusions  202  are configured to limit the shear stress  300  and/or peel stress  302  loads applied to adhesive bond  134  via first component member  102  and second component member  106 . Stated differently, reinforcing protrusions  202  are configured to accept and/or relieve a portion of the shear stress  300  and peel stress  302  loads applied to adhesive bond  134 . In this example, reinforcing protrusions  202  comprise first subset  206  of reinforcing protrusions  202  and second subset  208  of reinforcing protrusions  202  that are spaced apart from one another along width  118  and respectively positioned adjacent to and spaced inwardly from the corresponding longitudinal boundaries  120 . Such a positioning of reinforcing protrusions  202  may increase the bond-enhancing effects of reinforcing protrusions  202 , as shear stress  300  and peel stress  302  may be concentrated within adhesive bond  134  proximate to longitudinal boundaries  120 . 
     First subset  206  and second subset  208  of reinforcing protrusions  202  each comprise a respective plurality of reinforcing protrusions  202 . In some examples, first subset  206  and/or second subset  208  each comprise a plurality of rows of reinforcing protrusions  202  distributed along a substantial portion of the length of aerospace component joint  60 . Additionally or alternatively, first subset  206  and/or second subset  208  of reinforcing protrusions  202  may comprise a plurality of ridges that extend along the length of aerospace component joint  60 , such as discussed herein. 
     For reasons that are discussed in more detail herein, first component member  102  typically is formed of a metal, or metal alloy, while second component member  106  is formed of a plastic material or a fiber-reinforced plastic material. 
       FIG.  7    illustrates aerospace component joint  70 , which provides another example in which bond-enhancing features  200  comprise reinforcing protrusions  202 . Aerospace component joint  70  is similar to aerospace component joint  60 ; however, aerospace component joint  70  further comprises a plurality of additional subsets  210  of reinforcing protrusions  202 . Additionally, first subset  206  and second subset  208  of reinforcing protrusions  202  in aerospace component joint  70  comprise fewer reinforcing protrusions due to additional subsets  210  of reinforcing protrusions. 
     More specifically, in this example, each additional subset  210  of reinforcing protrusions  202  comprises a respective plurality of reinforcing protrusions  202 , and additional subsets  210  are evenly spaced apart from one another, and from first subset  206  and second subset  208 , along width  118 . Each additional subset  210  may comprise a plurality of rows of reinforcing protrusions and/or a plurality of ridges, such as discussed herein for first subset  206  and second subset  208 . 
     Stated in more general terms, reinforcing protrusions  202  are evenly distributed along at least a substantial portion of the width  118  of aerospace component joint  70 . In some examples, this distribution of reinforcing protrusions  202  delocalizes and/or distributes peel stress  302  and/or shear stress  300  loads across a larger area of aerospace component joint  70 . In some examples, such a configuration reduces stress concentration within adhesive bond  134  and thereby permits aerospace component joint  70  to withstand greater peel stress  302  and/or shear stress  300  loads before failure initiation within adhesive bond  134 . 
     Turning to  FIG.  8   , aerospace component joint  80  provides an example in which bond-enhancing features  200  comprise reinforcing protrusions  202  and adhesive-receiving recesses  204 . Like example aerospace component joints  60  and  70 , first component member  102  of aerospace component joint  80  is formed of a metal or a metal alloy, and second component member  106  of aerospace component joint  80  is formed of a plastic material or a fiber-reinforced plastic material. 
     As shown, reinforcing protrusions  202  project from first bonding face  104 , and adhesive-receiving recesses  204  are defined in first bonding face  104 . Similar to aerospace component joint  70 , reinforcing protrusions  202  comprise first subset  206  of reinforcing protrusions  202 , second subset  208  of reinforcing protrusions  202  and a plurality of additional subsets  210  of reinforcing protrusions  202  distributed between first subset  206  and second subset  208  of reinforcing protrusions  202 . In this example, adhesive-receiving recesses  204  are disposed in an alternating pattern with reinforcing protrusions  202 . Specifically, an adhesive-receiving recess  204  is disposed between adjacent subsets of reinforcing protrusions  202  to create an interspersed or alternating pattern of bond-enhancing features  200 . In some examples, bond-enhancing features  200  are distributed along a substantial portion of the length of aerospace component joint  80 . Reinforcing protrusions  202  and adhesive-receiving recesses  204  each provide the respective bond-enhancing characteristics discussed herein. In other words, aerospace component joint  80  comprises at least the bond-enhancements from reinforcing protrusions  202  in connection to aerospace component joint  70 , and the bond-enhancements from adhesive-receiving recesses  204  discussed herein in connection to aerospace component joint  40 . 
       FIG.  9    provides a flowchart that represents illustrative, non-exclusive examples of methods  500 , and  FIG.  10    provides a flowchart that represents illustrative, non-exclusive examples of methods  600  according to the present disclosure. In  FIGS.  9  and  10   , some steps are illustrated in dashed boxes indicating that such steps are optional or may correspond to an optional version of methods  500  or methods  600  according to the present disclosure. That said, not all methods  500  and/or methods  600  according to the present disclosure are required to comprise each of the steps illustrated in solid boxes. The methods and steps illustrated in  FIGS.  9  and  10    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 discussion herein. 
     Methods  500  comprise preparing one or more component members for an adhesive-bonded aerospace component joint according to the present disclosure. Methods  600  comprise forming an adhesive-bonded aerospace component joint according to the present disclosure. In some examples, methods  500  comprise preparing the first component member  102  and/or the second component member  106  of the aerospace component joints  100  illustrated and discussed herein with reference to  FIGS.  2 - 8   . In some examples, methods  600  comprise forming the aerospace component joint  100  illustrated and discussed herein with reference to  FIGS.  2 - 8   . Thus, aerospace component joints  100 , first component member  102 , and/or second component member  106  thereof illustrated and discussed herein with reference to  FIGS.  2 - 8    may incorporate any of the features, functions, properties, components, etc., as well as variants thereof, as those discussed herein with reference to methods  500  and  FIG.  9    and/or methods  600  and  FIG.  10    without requiring the inclusion of all such features functions, components, etc. Likewise, the aerospace component joints  100 , the first component member  102 , and the second component member  106  thereof discussed herein with reference to  FIG.  9    and methods  500  and/or  FIG.  10    and methods  600  may incorporate any of the features, functions, properties, components, etc., as well as variants thereof, as those discussed herein with reference to  FIG.  1    without requiring the inclusion of all such features functions, components, etc. 
     With reference to  FIG.  9   , methods  500  comprise integrating  510  one or more bond-enhancing features into the component member. The integrating  510  comprises forming  515  a plurality of reinforcing protrusions to be integral with the component member and to project from a bonding face of the component member. Additionally or alternatively, the integrating  510  comprises creating  520  one or more adhesive-receiving recesses in the bonding face of the component member. In some examples, methods  500  comprise forming  505  the component member. In some examples, methods  500  comprise preparing  525  a second component member for the aerospace component joint. 
     When comprised in methods  500 , forming  505  the component member is performed in any suitable manner. In some examples, the forming  505  the component member varies depending on the material composition of the component member. For some examples in which the component member is formed from a metal, or a metal alloy, the forming  505  the component member comprises casting, molding, machining, milling, and/or additively manufacturing the metal, or metal alloy. For examples in which the component member is formed from a plastic material or a fiber-reinforced plastic material the forming  505  the component member comprises forming a layup of the plastic material or fiber-reinforced plastic material and shaping the layup of the plastic material or fiber-reinforced plastic material. In some examples, the shaping comprises milling, machining, molding, stamping, press forming, stamp forming, or continuous compression molding a feedstock material into the component member, such as the layup, into the desired shape. 
     In any of the above examples, the forming  505  the component member may comprise forming the one or more materials from which the component member is formed into the desired shape of the component member. In some examples, the forming  505  the component member comprises forming and/or shaping a bonding face of the component member. In some such examples, forming  515  the reinforcing protrusions and/or creating at  520  are performed during and/or as a portion of the forming  505  the component member. 
     In some examples, the component member is the first component member  102  of aerospace component joints  100  discussed herein, and the forming  505  the component member comprises forming the component member. Additionally or alternatively, in some examples, the component member is the second component member  106  of the aerospace component joints  100  discussed herein, and the forming  505  the component member comprises forming the second component member  106 . In some examples, methods  500  comprise preparing the first component member  102  and the second component member  106  for the aerospace component joint  100 . In some such examples, the forming  505  the component member comprises forming both of the first component member  102  and the second component member  106 , such as in the same or different processes. In more specific examples, the forming  505  the component member comprises forming the first component member  102  from a metal or metal alloy and forming the second component member  106  from a plastic material or a fiber-reinforced plastic material. 
     The forming  505  the component member is performed with any suitable sequence or timing within methods  500 , such as prior to and/or at least substantially simultaneously with integrating  510  and/or preparing  525 . 
     As shown in  FIG.  9   , methods  500  comprise integrating  510  one or more bond-enhancing features into the component member. The integrating  510  comprises forming  515  reinforcing protrusions and/or creating  520  adhesive receiving recesses. In some examples, the integrating  510  comprises one of the forming  515  the reinforcing protrusions and the creating  520 . In other examples, the integrating  510  comprises both of the forming  515  the reinforcing protrusions and the creating  520 . 
     The forming  515  the reinforcing protrusions  202  comprises forming a plurality of the reinforcing protrusions  202  to be integral with the bonding face of the component member. In some examples, the forming  515  the reinforcing protrusions comprises forming the plurality of reinforcing protrusions  202  to be integral with the first bonding face  104  of the first component member  102 . In some examples, the forming  515  comprises forming the reinforcing protrusions from a metal or metal alloy, which may be the same as or different from a metal or metal alloy from which the first component member  102  is formed. The forming  515  comprises forming any suitable number of reinforcing protrusions  202 , with any suitable distribution along the first bonding face  104 , as discussed herein. The forming  515  also comprises forming each reinforcing protrusion to have any suitable shape and/or dimensions, as discussed herein. 
     In some examples, the forming  515  the reinforcing protrusions  202  comprises forming the reinforcing protrusions  202  on the bonding face of the component member, and more specifically on the first bonding face  104  of the first component member  102 . In some such examples, the forming  515  the reinforcing protrusions  202  comprises additively manufacturing the reinforcing protrusions on the first bonding face  104 . In a more specific example, the forming  515  the reinforcing protrusions  202  comprises laser bed sintering the reinforcing protrusions on the bonding face. 
     In some examples, the forming  515  the reinforcing protrusions  202  comprises welding the plurality of reinforcing protrusions to the bonding face. In some examples, the welding comprises welding preformed reinforcing protrusions to the bonding face. In yet more specific examples, the welding comprises welding preformed pins or wires to the bonding face to create the plurality of reinforcing protrusions  202 . In some examples, the forming  515  the reinforcing protrusions  202  comprises molding and/or casting the reinforcing protrusions  202  on the first bonding face  104 . In some such examples, the forming  515  is performed at least substantially simultaneously with the forming  505  the component member. 
     Additionally or alternatively, in some examples, the forming  515  the reinforcing protrusions comprises subtractive manufacturing the bonding face of the component member to form the plurality of reinforcing protrusions. In some examples, the subtractive manufacturing comprises embossing, engraving, milling, and/or machining the bonding face to create the reinforcing protrusions  202 . 
     The creating  520  comprises creating at least one adhesive-receiving recess  204  on the bonding face and optionally creating a plurality of adhesive-receiving recesses  204  on the bonding face. The creating  520  may be performed for examples in which the component member is formed of a metal or a metal alloy and/or for examples in which the component member is formed of a plastic material or a plastic composite material. In some examples, the creating  520  comprising creating the at least one adhesive-receiving recess  204  on the first bonding face  104  of the first component member  102  or on the second bonding face  108  of the second component member  106 . For examples in which the integrating  510  comprises the forming  515  and the creating  520 , the forming  515  and the creating  520  optionally are performed on the bonding face such that the reinforcing protrusions  202  and the adhesive-receiving recesses  204  are non-overlapping and/or distributed in an alternating relationship. 
     The creating  520  comprises creating any suitable number of adhesive-receiving recesses  204 , each having any suitable conformation, dimensions, and/or disposal along the bonding face, as discussed herein. The creating  520  also is performed in any suitable manner. In some examples, the creating  520  comprises texturing the bonding face, and optionally a substantial portion of the area thereof, to create a plurality of adhesive-receiving recesses  204 , as discussed herein. In some examples, the texturing comprises forming a textured conformation that forms the adhesive-receiving recesses, with examples of the textured conformation comprising crosshatched texture, dimpled texture, and/or cratered texture. 
     In some examples, the creating  520  comprises subtractive manufacturing the one or more adhesive-receiving recesses  204  in the bonding face after the component member is formed, for example, by machining, engraving, embossing, and/or milling the one or more adhesive-receiving recesses  204  into the bonding face. Additionally or alternatively, the creating  520  comprises embossing, stamp-forming, press-forming, and/or shaping the one or more adhesive-receiving recesses into the bonding face of the component member, which may be performed while the component member is uncured, partially cured, and/or during the forming  505 . 
     In some examples, the integrating  510 , and optionally the forming  505 , are performed on, or prepare, the first component member  102  for the adhesive-bonded aerospace component joint  100 . In some such examples, methods  500  further comprise preparing  525  the second component member  106  for the adhesive-bonded aerospace component joint  100 . In some examples, the preparing  525  the second component member  106  comprises forming  505  the second component member  106 . In some examples, the preparing  525  comprises performing the creating  520  on the second component member  106 . For examples in which the methods  500  comprise performing the creating  520  on the first component member  102  and the second component member  106 , the creating  520  may be performed in the same or a different manner on the first component member  102  and the second component member  106 . In some examples, performing the creating  520  on the second component member  106  comprises disposing the one or more adhesive-receiving recesses  204  on the second bonding face  108  to be non-overlapping, when assembled in the aerospace component joint  100 , with the adhesive-receiving recesses  204  and/or the reinforcing protrusions  202  on the first bonding face  104 . In some examples, methods  500  do not include the preparing  525 , for example, when the aerospace component joint  100  only comprises bond-enhancing features  200  integrated into the first component member  102 . 
     Turning to  FIG.  10   , provided therein is a flowchart representing examples of methods  600  according to the present disclosure. Methods  600  are methods of forming an adhesive-bonded aerospace component joint between a first component member  102  and a second component member  106 . As shown in  FIG.  10   , methods  600  comprise operably positioning  605  the first bonding face of the first component member and the second component member relative to one another, adhesive-bonding  610  the first bonding face and the second bonding face with one another, and integrating  615  one or more bond-enhancing features into the aerospace component joint. The integrating  615  comprises penetrating  625  a plurality of reinforcing protrusions that project from the first bonding face into the second component member and/or substantially filling  620  one or more adhesive-receiving recesses  204  with an adhesive. In some examples, methods  600  comprise preparing  500  the first component member and/or the second component member for the aerospace component joint. In some examples, methods  600  comprise curing  630  the first component member and/or the second component member. 
     For examples in which methods  600  comprise the preparing  500 , the preparing  500  may comprise performing any of the methods  500  that are illustrated and discussed herein with reference to  FIG.  9   . In particular, the preparing  500  may comprise performing any suitable combination of the steps of methods  500  that are illustrated and discussed herein with reference to  FIG.  9    to prepare the first component member  102  and/or the second component member  106  for the aerospace component joint  100 . For examples in which methods  500  comprise the preparing  500 , at least a portion of, and optionally the entirety of, the preparing  500  is performed prior to any other step or portion of methods  500 . 
     The operably positioning  605  comprises overlapping the first bonding face  104  of the first component member  102  with the second bonding face  108  of the second component member  106 . In some examples, the operably positioning  605  comprises overlapping the first bonding face  104  with the second bonding face  108  along the length  116  of the aerospace component joint  100  and/or along the bonded area  114  of the aerospace component joint  100 . In some examples, the operably positioning  605  comprises overlapping the first bonding face  104  with the second bonding face  108  to a preselected extent that defines the width  118  of the aerospace component joint  100 . In some examples, the operably positioning  605  comprises moving the first bonding face  104  and the second bonding face  108  towards one another until the first bonding face  104  and the second bonding face  108  are spaced apart from one another by a predetermined gap  110  having a predetermined thickness. In some examples, the predetermined thickness corresponds to the nominal thickness of an adhesive layer  112 , as discussed herein. In some examples, the operably positioning  605  comprises positioning the first bonding face  104  and the second bonding face  108  to extend at least generally parallel with one another. 
     The operably positioning  605  is performed with any suitable sequence or timing within methods  600 , such as prior to, or as a portion of, the adhesive-bonding  610 , and/or the integrating  615  and/or prior to the curing  630 . 
     The adhesive-bonding  610  the first bonding face  104  and the second bonding face  108  with one another comprises forming the adhesive bond  134  between the first bonding face  104  and the second bonding face  108 , as discussed herein. In some examples, the adhesive-bonding  610  comprises introducing an adhesive between the first bonding face  104  and the second bonding face  108 . In particular, the adhesive-bonding  610  comprises substantially filling the gap  110  between the first bonding face  104  and the second bonding face  108  with an adhesive layer  112 . In some examples, the substantially filling the gap with the adhesive layer  112  comprises applying an adhesive to one or more of the first bonding face  104  and the second bonding face  108 . In some examples, substantially filling the gap  110  with the adhesive comprises moving the first bonding face  104  and the second bonding face  108  towards one another during the operably positioning  605 . Thus, in some examples, portions of the adhesive-bonding  610  and the operably positioning  605  are performed together. In some examples, the adhesive bonding comprises curing the adhesive between the first bonding face  104  and the second bonding face  108 , such as subsequent to the operably positioning  605 , and/or the substantially filling  620  the gap  110  with the adhesive layer  112 . In some examples, the curing the adhesive layer  112  comprises setting, hardening, and/or solidifying the adhesive layer  112  and/or binding the adhesive layer  112  to the first bonding face  104  and the second bonding face  108 . 
     Methods  600  further comprise integrating  615  the one or more bond-enhancing features  200  into the adhesive-bonded aerospace component joint  100 . The integrating  615  comprises the penetrating  625  and/or the substantially filling  620 . The penetrating  625  comprises penetrating a plurality of reinforcing protrusions  202 , which project from the first bonding face  104  of the first component member  102  into the second component member  106  through the second bonding face  108  of the second component member  106 , as discussed herein. Examples of the reinforcing protrusions  202  are discussed herein. In some examples, the penetrating  625  comprises penetrating each reinforcing protrusion  202  to the protrusion depth  212  within the second component member  106 , as discussed herein. 
     The penetrating  625  may be performed for examples in which the first component member  102  is formed of a metal, or metal alloy, and the second component member  106  is formed of a plastic or a fiber-reinforced plastic material. In some such examples, the second component member  106  is uncured, or partially cured, during the penetrating  625 , such as to permit the plurality of reinforcing protrusions to be penetrated into the second component member  106  without forming corresponding bores in the second component member for receiving the reinforcing protrusions  202 . As discussed in more detail herein, in some such examples, methods  600  further comprise curing  630 . In some such examples, methods  600  comprise methods of co-bonding the first component member  102  and the second component member  106 . 
     In some examples, the penetrating  625  is performed substantially simultaneously with the operably positioning  605 . In particular, in some examples, the moving the first bonding face  104  and the second bonding face  108  towards one another during the operably positioning  605  comprises the penetrating  625 . In some examples, the penetrating  625  is performed subsequent to the introducing adhesive between the first bonding face  104  the second bonding face  108  and prior to the curing the adhesive between the first bonding face  104  and the second bonding face  108 . 
     The substantially filling  620  comprises substantially filling the one or more adhesive-receiving recesses  204  with an adhesive. As discussed herein, the one or more adhesive-receiving recesses  204  are comprised in either or both of the first bonding face  104  of the first component member  102  and the second bonding face  108  of the second component member  106 . Examples of adhesive-receiving recesses  204  are discussed herein. In some examples, the substantially filling  620  comprises substantially filling the one or more adhesive-receiving recesses  204  with the adhesive layer  112  and/or with adhesive from the adhesive layer  112 . In some examples, the substantially filling  620  is performed during, or as a portion of, the adhesive-bonding  610 . In particular, in some examples, the introducing the adhesive between the first bonding face  104  and the second bonding face  108  during the adhesive-bonding  610  comprises partially, and optionally substantially, filling the one or more adhesive-receiving recesses  204  with the adhesive. 
     Additionally or alternatively, in some examples, at least a portion of the substantially filling  620  is performed during the operably positioning  605 . In particular, in some examples, the operably positioning  605  comprises flowing portions of the adhesive layer  112  into the one or more adhesive-receiving recesses  204  as the first bonding face  104  and the second bonding face  108  are moved towards one another. In any such examples, the substantially filling  620  is performed prior to the curing the adhesive. In some examples, the adhesive-bonding  610  comprises curing the adhesive layer  112  within the one or more adhesive-receiving recesses  204 . In other words, in some examples, the adhesive-bonding  610  comprises adhesive bonding the adhesive layer  112  to the surfaces of the one or more adhesive-receiving recesses  204 , which form portions of the first bonding face  104  or the second bonding face  108 , as discussed herein. 
     The substantially filling  620  is performed with any suitable sequence or timing within methods  600 , such as prior to, and/or substantially simultaneously with the penetrating  625 . The substantially filling  620  also may be performed prior to, or during the operably positioning and/or as a portion of the adhesive-bonding  610 . 
     In some examples, methods  600  further comprise curing  630  one or more of the first component member  102  and the second component member  106 . The curing  630  is performed for examples in which the first component member  102  and/or the second component member  106  are formed of a plastic material or a fiber-reinforced plastic material that is uncured, or partially cured, during one or more steps of methods  600 . In a more specific example, the curing  630  is performed for examples in which the integrating  615  comprises the penetrating  625 , the first component member  102  is formed of a metal or a metal alloy, and the second component member  106  is uncured, or partially cured, during the penetrating  625 , as discussed herein. In such examples, the curing  630  is performed subsequent to the penetrating  625 . In this way, the second component member  106  is cured with the reinforcing protrusions of the first component member  102  penetrated therein. In some examples, the curing  630  is performed substantially simultaneously with the curing the adhesive or the adhesive layer of the adhesive-bonding  610 . Examples of the curing  630  comprise cooling the second component member  106  and/or thermosetting the plastic or fiber-reinforced plastic material that forms the second component member  106 . 
     Illustrative, non-exclusive examples of inventive subject matter according to the present disclosure are described in the following enumerated paragraphs: 
     A. An aerospace component joint ( 100 ) for an aircraft ( 10 ), the aerospace component joint ( 100 ) comprising: 
     a first component member ( 102 ) comprising a first bonding face ( 104 ); 
     a second component member ( 106 ) comprising a second bonding face ( 108 ) that overlaps with the first bonding face ( 104 ) along a bonded area ( 114 ) of the aerospace component joint ( 100 ), wherein the first bonding face ( 104 ) and the second bonding face ( 108 ) are separated from one another along the bonded area ( 114 ) by a gap ( 110 ); 
     an adhesive layer ( 112 ) substantially filling the gap ( 110 ) and forming an adhesive bond ( 134 ) between the first bonding face ( 104 ) and the second bonding face ( 108 ); 
     one or more bond-enhancing features ( 200 ), comprising at least one of:
         a plurality of reinforcing protrusions ( 202 ) integral with the first component member ( 102 ), wherein the plurality of reinforcing protrusions ( 202 ) projects from the first bonding face ( 104 ), extends through the adhesive layer ( 112 ), and penetrates into the second component member ( 106 ) through the second bonding face ( 108 ); or   one or more adhesive-receiving recesses ( 204 ) defined in one or both of the first bonding face ( 104 ) and the second bonding face ( 108 ), wherein the adhesive layer ( 112 ) substantially fills each adhesive-receiving recess ( 204 ) of the one or more adhesive-receiving recesses ( 204 ).       

     A1. The aerospace component joint ( 100 ) of paragraph A, wherein the first bonding face ( 104 ) and the second bonding face ( 108 ) extend generally parallel to one another along the bonded area ( 114 ). 
     A2. The aerospace component joint ( 100 ) of any of paragraphs A-A1, wherein the adhesive layer ( 112 ) extends a length ( 116 ) of the aerospace component joint ( 100 ) and extends between a pair of longitudinal boundaries ( 120 ), wherein the longitudinal boundaries ( 120 ) extend the length ( 116 ) of the aerospace component joint ( 100 ) and are spaced apart from one another by a width ( 118 ) of the aerospace component joint ( 100 ). 
     A3. The aerospace component joint ( 100 ) of any of paragraphs A-A2, wherein the first component member ( 102 ) comprises a first joint edge ( 122 ) that defines one of a/the pair of longitudinal boundaries ( 120 ) and the second component member ( 106 ) comprises a second joint edge ( 124 ) that defines the other of the pair of longitudinal boundaries ( 120 ). 
     A4. The aerospace component joint ( 100 ) of any of paragraphs A-A3, wherein the plurality of reinforcing protrusions ( 202 ) is distributed along a substantial portion of a/the length ( 116 ) of the aerospace component joint ( 100 ). 
     A5. The aerospace component joint ( 100 ) of any of paragraphs A2-A4, wherein the plurality of reinforcing protrusions ( 202 ) is distributed along at least a substantial portion of the width ( 118 ) of the aerospace component joint ( 100 ). 
     A6. The aerospace component joint ( 100 ) of any of paragraphs A2-A5, wherein the plurality of reinforcing protrusions ( 202 ) comprises a first subset ( 206 ) of reinforcing protrusions ( 202 ) and a second subset ( 208 ) of reinforcing protrusions ( 202 ), wherein the first subset ( 206 ) of reinforcing protrusions ( 202 ) protrude into the second component member ( 106 ) adjacent to, and interior of, a/the first joint edge ( 122 ), and wherein the second subset ( 208 ) of reinforcing protrusions ( 202 ) protrude into the second component member ( 106 ) adjacent to, and interior of, a/the second joint edge ( 124 ). 
     A7. The aerospace component joint ( 100 ) of paragraph A6, wherein the first subset ( 206 ) of reinforcing protrusions ( 202 ) and the second subset ( 208 ) of reinforcing protrusions ( 202 ) are spaced apart from one another along the width ( 118 ) of the aerospace component joint ( 100 ). 
     A8. The aerospace component joint ( 100 ) of any of paragraphs A6-A7, wherein the plurality of reinforcing protrusions ( 202 ) further comprises at least one, and optionally a plurality of, additional subsets ( 210 ) of reinforcing protrusions ( 202 ), disposed between the first subset ( 206 ) of reinforcing protrusions ( 202 ) and the second subset ( 208 ) of reinforcing protrusions ( 202 ). 
     A9. The aerospace component joint ( 100 ) of any of paragraphs A6-A8, wherein the first subset ( 206 ) of reinforcing protrusions ( 202 ) and/or the second subset ( 208 ) of reinforcing protrusions ( 202 ) comprises at least one row, and optionally a plurality of rows, of reinforcing protrusions ( 202 ) that are distributed along a substantial portion of the length ( 116 ) of the aerospace component joint ( 100 ). 
     A10. The aerospace component joint ( 100 ) of any of paragraphs A2-A9, wherein the one or more adhesive-receiving recesses ( 204 ) extend along a substantial portion of the length ( 116 ) of the aerospace component joint ( 100 ). 
     A11. The aerospace component joint ( 100 ) of any of paragraphs A-A10, wherein one of the one or more adhesive-receiving recesses ( 204 ) comprises a groove formed in one of the first bonding face ( 104 ) and the second bonding face ( 108 ), and wherein the groove extends along the substantial portion of a/the length ( 116 ) of the aerospace component joint ( 100 ). 
     A12. The aerospace component joint ( 100 ) of paragraph A11, wherein the groove extends at a fixed distance between a/the pair of longitudinal boundaries ( 120 ) as it extends along the substantial portion of the length ( 116 ) of the aerospace component joint ( 100 ). 
     A13. The aerospace component joint ( 100 ) of paragraph A11, wherein the groove comprises a non-linear conformation. 
     A14. The aerospace component joint ( 100 ) of any of paragraphs A-A13, wherein the one or more adhesive-receiving recesses ( 204 ) comprise a plurality of adhesive-receiving recesses ( 204 ) defined in one of the first bonding face ( 104 ) or the second bonding face ( 108 ). 
     A15. The aerospace component joint ( 100 ) of paragraph A14, wherein the plurality of adhesive-receiving recesses ( 204 ) comprises a plurality of grooves defined in the one of the first bonding face ( 104 ) or the second bonding face ( 108 ). 
     A16. The aerospace component joint ( 100 ) of paragraph A15, wherein the plurality of grooves are spaced apart from one another along a/the width ( 118 ) of the aerospace component joint ( 100 ). 
     A17. The aerospace component joint ( 100 ) of paragraph A14, wherein the one of the first bonding face ( 104 ) or the second bonding face ( 108 ) comprises a textured conformation that defines the plurality of adhesive-receiving recesses ( 204 ). 
     A18. The aerospace component joint ( 100 ) of any of paragraphs A14-A17, wherein the plurality of adhesive-receiving recesses ( 204 ) are distributed along a/the width ( 118 ) of the aerospace component joint ( 100 ). 
     A19. The aerospace component joint ( 100 ) of any of paragraphs A-A18, wherein the plurality of reinforcing protrusions ( 202 ) comprises one or more of a plurality of pins, a plurality of columnar projections, and a plurality of ridges. 
     A20. The aerospace component joint ( 100 ) of any of paragraphs A-A19, wherein each reinforcing protrusion ( 202 ) of the plurality of reinforcing protrusions ( 202 ) is dimensioned to protrude into the second component member ( 106 ) by a protrusion depth ( 212 ), wherein the second component member ( 106 ) defines a second member thickness ( 126 ) along the bonded area ( 114 ) that is measured between the second bonding face ( 108 ) and a second counter face ( 128 ) of the second component member ( 106 ) that opposes the second bonding face ( 108 ), wherein the protrusion depth ( 212 ) of each reinforcing protrusion ( 202 ) is a threshold fraction of the second member thickness ( 126 ), and wherein the threshold fraction of the protrusion depth ( 212 ) to the second member thickness ( 126 ) is at least 60%, at least 65%, at least 70%, at least 75%, at least 80%, at least 85%, at least 90% at least 95%, at least 98%, at most 75%, at most 80%, at most 85%, at most 90%, at most 95%, at most 98%, and/or at most 99%. 
     A21. The aerospace component joint ( 100 ) of any of paragraphs A-A20, wherein each reinforcing protrusion ( 202 ) defines a cross-sectional area that is measured parallel to the first bonding face ( 104 ), wherein the plurality of reinforcing protrusions ( 202 ) defines a cumulative cross-sectional area that is a sum of the cross-sectional area of each of the plurality of reinforcing protrusions ( 202 ). 
     A22. The aerospace component joint ( 100 ) of paragraph A21, wherein the plurality of reinforcing protrusions ( 202 ) is configured such that the cumulative cross-sectional area thereof is at least substantially the same as a cumulative fastener cross-sectional area of fasteners comprised in an otherwise equivalent conventional aerospace component joint. 
     A23. The aerospace component joint ( 100 ) of paragraph A21, wherein each reinforcing protrusion ( 202 ) of the plurality of reinforcing protrusions ( 202 ) comprises a shear strength, wherein the plurality of reinforcing protrusions ( 202 ) comprises a cumulative shear strength that is the cumulative cross-sectional area multiplied by the shear strength, and wherein the plurality of reinforcing protrusions ( 202 ) is configured such that the cumulative strength thereof is equal to or greater than a limit shear load of the aerospace component joint ( 100 ). 
     A24. The aerospace component joint ( 100 ) of any of paragraphs A-A23, wherein the one or more adhesive-receiving recesses ( 204 ) each define a portion of the gap ( 110 ). 
     A25. The aerospace component joint ( 100 ) of any of paragraphs A-A24, wherein the adhesive layer ( 112 ) comprises a nominal thickness ( 130 ) that is measured between the first bonding face ( 104 ) and the second bonding face ( 108 ) outside of the one or more adhesive-receiving recesses ( 204 ), wherein each of the one or more adhesive-receiving recesses ( 204 ) defines a recess depth ( 214 ), wherein the recess depth ( 214 ) of each adhesive-receiving recess ( 204 ) is a threshold fraction of the nominal thickness ( 130 ), and wherein the threshold fraction of the recess depth ( 214 ) to the nominal thickness ( 130 ) is at least 100%, at least 200%, at least 300%, at least 400%, at least 500%, at least 600%, at least 700%, at least 800%, at least 900%, at most 300%, at most 400%, at most 500%, at most 600%, at most 700%, at most 800%, at most 900%, and/or at most 1000%. 
     A26. The aerospace component joint ( 100 ) of any of paragraphs A-A25, wherein each of the one or more adhesive-receiving recesses ( 204 ) is configured to create one or more corresponding regions of increased thickness in the adhesive layer ( 112 ). 
     A27. The aerospace component joint ( 100 ) of any of paragraphs A-A26, wherein the one or more adhesive-receiving recesses ( 204 ) comprises a first edge recess ( 216 ) defined in the first bonding face ( 104 ) and extending interiorly from a/the first joint edge ( 122 ) of the first component member ( 102 ). 
     A28. The aerospace component joint ( 100 ) of paragraph A27, wherein the first bonding face ( 104 ) along the first edge recess ( 216 ) extends towards the second bonding face ( 108 ) and forms a first edge recess angle ( 220 ) with the first bonding face ( 104 ) immediately adjacent to the first edge recess ( 216 ), and wherein the first edge recess angle ( 220 ) is at most 175 degrees (°), at most 170°, at most 160°, at most 150°, at most 140°, at most 130°, at most 135° at most 120°, at most 110°, at least 150°, at least 140°, at least 130°, at least 120°, at least 110°, and/or at least 100°. 
     A29. The aerospace component joint ( 100 ) of any of paragraphs A-A28, wherein the one or more adhesive-receiving recesses ( 204 ) comprises a second edge recess ( 218 ) defined in the second bonding face ( 108 ) and extending interiorly from a/the second joint edge ( 124 ) of the second component member ( 106 ). 
     A30. The aerospace component joint ( 100 ) of paragraph A29, wherein the second bonding face ( 108 ) along the second edge recess ( 218 ) extends towards the first bonding face ( 104 ) and forms a second edge recess angle ( 222 ) with the second bonding face ( 108 ) immediately adjacent to the second edge recess ( 218 ), and wherein the second edge recess angle ( 222 ) is at most 175°, at most 170°, at most 160°, at most 150°, at most 140°, at most 130°, at most 135° at most 120°, at most 110°, at least 150°, at least 140°, at least 130°, at least 120°, at least 110°, and/or at least 100°. 
     A31. The aerospace component joint ( 100 ) of any of paragraphs A-A30, wherein the first component member ( 102 ) is formed of a metal or a metal alloy, and the second component member ( 106 ) is formed of a plastic material. 
     A32. The aerospace component joint ( 100 ) of paragraph A31, wherein the plastic material is a fiber-reinforced plastic material. 
     A33. The aerospace component joint ( 100 ) of any of paragraphs A-A32, wherein the one or more bond-enhancing features ( 200 ) comprises the plurality of reinforcing protrusions ( 202 ) and the one or more adhesive-receiving recesses ( 204 ). 
     A34. The aerospace component joint ( 100 ) of any of paragraphs A-A33, wherein the one or more adhesive-receiving recesses ( 204 ) is defined in the first bonding face ( 104 ). 
     A35. The aerospace component joint ( 100 ) of any of paragraphs A-A34, wherein the one or more adhesive-receiving recesses ( 204 ) comprises a plurality of adhesive-receiving recesses ( 204 ), and wherein the plurality of reinforcing protrusions ( 202 ) and the plurality of adhesive-receiving recesses ( 204 ) are disposed in an alternating relationship along a/the width ( 118 ) of the aerospace component joint ( 100 ). 
     A36. The aerospace component joint ( 100 ) of any of paragraphs A-A35, wherein the one or more bond-enhancing features ( 200 ) only comprises the plurality of reinforcing protrusions ( 202 ). 
     A37. The aerospace component joint ( 100 ) of any of paragraphs A-A35, wherein the one or more bond-enhancing features ( 200 ) only comprises the one or more adhesive-receiving recesses ( 204 ). 
     A38. The aerospace component joint ( 100 ) of paragraph A37, wherein the first component member ( 102 ) and the second component member ( 106 ) are formed of a/the plastic material, and wherein the one or more adhesive-receiving recesses ( 204 ) comprises at least one adhesive-receiving recess ( 204 ) defined in each of the first bonding face ( 104 ) and the second bonding face ( 108 ). 
     A39. The aerospace component joint ( 100 ) of any of paragraphs A-A38, wherein the one or more adhesive-receiving recesses ( 204 ) are configured to prevent bond failures from propagating through the adhesive bond ( 134 ). 
     A40. The aerospace component joint ( 100 ) of any of paragraphs A-A39, wherein the plurality of reinforcing protrusions ( 202 ) is configured to reduce peel stress and/or shear stress applied to the adhesive bond ( 134 ) through the first component member ( 102 ) and the second component member ( 106 ). 
     A41. The aerospace component joint ( 100 ) of any of paragraphs A-A40, wherein the aerospace component joint ( 100 ) is formed according to the method ( 600 ) of any of paragraphs C-C11. 
     A42. An aircraft ( 10 ) comprising the aerospace component joint ( 100 ) of any of paragraphs A-A41. 
     A43. An aircraft ( 10 ) comprising a plurality of aerospace component joints ( 100 ), wherein each aerospace component joint ( 100 ) of the plurality of aerospace component joints ( 100 ) is the aerospace component joint ( 100 ) of any of paragraphs A-A41. 
     B. A method ( 500 ) of preparing a component member for an adhesive-bonded aerospace component joint ( 100 ), the method comprising: 
     integrating ( 510 ) one or more bond-enhancing features ( 200 ) into the component member, wherein the integrating ( 510 ) comprises at least one of:
         forming ( 515 ) a plurality of reinforcing protrusions ( 202 ) to be integral with the component member and to project from a bonding face of the component member; and   creating ( 520 ) one or more adhesive-receiving recesses ( 204 ) in the bonding face of the component member.       

     B1. The method ( 500 ) of paragraph B, wherein the forming ( 515 ) the plurality of reinforcing protrusions ( 202 ) comprises forming the plurality of the reinforcing protrusions ( 202 ) on the bonding face of the component member. 
     B2. The method ( 500 ) of paragraph B1, wherein the forming ( 515 ) the plurality of reinforcing protrusions ( 202 ) comprises additively manufacturing the plurality of reinforcing protrusions ( 202 ) on the bonding face of the component member. 
     B3. The method ( 500 ) of paragraph B, wherein the forming ( 515 ) the plurality of reinforcing protrusions ( 202 ) comprises welding the plurality of reinforcing protrusions to the bonding face of the component member. 
     B4. The method ( 500 ) of any of paragraphs B-133, wherein the creating ( 520 ) comprises machining the one or more adhesive-receiving recesses ( 204 ) into the bonding face of the component member. 
     B5. The method ( 500 ) of any of paragraphs B-133, wherein the creating ( 520 ) comprises stamp-forming, molding, press-forming, and/or shaping the one or more adhesive-receiving recesses ( 204 ) into the bonding face of the component member. 
     B6. The method ( 500 ) of any of paragraphs B-135, wherein the method ( 500 ) further comprises forming ( 505 ) the component member, and wherein the creating ( 520 ) is performed during the forming the component member. 
     B7. The method ( 500 ) of paragraph B6, wherein the forming ( 505 ) the component member comprises one of press forming, stamp forming, or continuous compression molding a feedstock material into the component member, and wherein the creating ( 520 ) is performed during the one of the press forming, the stamp forming, or the continuous compression molding. 
     B8. The method ( 500 ) of any of paragraphs B-137, wherein the component member is a first component member ( 102 ), and wherein the method ( 500 ) further comprises preparing ( 525 ) a second component member ( 106 ), and wherein the preparing the second component member ( 106 ) comprises performing the creating ( 520 ) on the second component member ( 106 ). 
     B9. The method ( 500 ) of any of paragraphs B-138, wherein the aerospace component joint ( 100 ) is the aerospace component joint ( 100 ) of any of paragraphs A-A40. 
     C. A method ( 600 ) of forming an adhesive-bonded aerospace component joint ( 100 ) between a first component member ( 102 ) comprising a first bonding face ( 104 ) and a second component member ( 106 ) comprising a second bonding face ( 108 ), the method ( 600 ) comprising: 
     operably positioning ( 605 ) the first bonding face ( 104 ) and the second bonding face ( 108 ) relative to one another, wherein the operably positioning ( 605 ) comprises overlapping the first bonding face ( 104 ) and the second bonding face ( 108 ) with one another; 
     adhesive-bonding ( 610 ) the first bonding face ( 104 ) and the second bonding face ( 108 ) with one another; and 
     integrating ( 615 ) one or more bond-enhancing features ( 200 ) into the aerospace component joint ( 100 ), wherein the integrating ( 615 ) comprises one or more of:
         penetrating ( 625 ) a plurality of reinforcing protrusions ( 202 ), which project from the first bonding face ( 104 ) of the first component member ( 102 ), into the second component member ( 106 ) through the second bonding face ( 108 ) of the second component member ( 106 );   substantially filling ( 620 ) one or more adhesive-receiving recesses ( 204 ) with an adhesive, wherein the one or more adhesive-receiving recesses ( 204 ) are comprised in one or both of the first bonding face ( 104 ) of the first component member ( 102 ) and the second bonding face ( 108 ) of the second component member ( 106 ).       

     C1. The method ( 600 ) of paragraph C, wherein the operably positioning ( 605 ) comprises moving the first bonding face ( 104 ) and the second bonding face ( 108 ) towards one another until the first bonding face ( 104 ) and the second bonding face ( 108 ) are spaced apart from one another by a predetermined gap ( 110 ). 
     C2. The method ( 600 ) of paragraph C1, wherein the penetrating ( 625 ) is performed substantially simultaneously with the moving. 
     C3. The method ( 600 ) of any of paragraphs C-C2, wherein the adhesive-bonding ( 610 ) comprises introducing adhesive between the first bonding face ( 104 ) and the second bonding face ( 108 ), and wherein the substantially filling ( 620 ) is performed at least substantially simultaneously with the introducing. 
     C4. The method ( 600 ) of paragraph C3, wherein the adhesive-bonding ( 610 ) further comprises curing the adhesive between the first bonding face ( 104 ) and the second bonding face ( 108 ). 
     C5. The method ( 600 ) of paragraph C4, wherein the curing ( 630 ) comprises curing the adhesive within the one or more adhesive-receiving recesses ( 204 ). 
     C6. The method ( 600 ) of any of paragraphs C-C5, wherein the second component member ( 106 ) is uncured or partially cured during the penetrating ( 625 ), and wherein the method ( 600 ) further comprises curing ( 630 ) the second component member ( 106 ) subsequent to the penetrating ( 625 ). 
     C7. The method ( 600 ) of any of paragraphs C-C6, wherein the integrating ( 615 ) comprises the penetrating ( 625 ). 
     C8. The method ( 600 ) of any of paragraphs C-C7, wherein the integrating ( 615 ) comprises the filling ( 620 ). 
     C9. The method ( 600 ) of any of paragraphs C-C8, further comprising preparing ( 500 ) the first component member ( 102 ) for the aerospace component joint ( 100 ), wherein the preparing ( 500 ) comprises performing the method of any of paragraphs B-139, and wherein the first component member ( 102 ) is the component member of any of paragraphs B-139. 
     C10. The method ( 600 ) of paragraph C9, wherein the preparing ( 500 ) further comprises preparing ( 525 ) the second component member ( 106 ) for the aerospace component joint ( 100 ). 
     C11. The method ( 600 ) of any of paragraphs C-C10, wherein the aerospace component joint ( 100 ) is the aerospace component joint ( 100 ) of any of paragraphs A-A40. 
     As used herein, the phrase, “for example,” the phrase, “as an example,” and/or simply the term “example,” when used with reference to one or more components, features, details, structures, embodiments, and/or methods according to the present disclosure, are intended to convey that the described component, feature, detail, structure, embodiment, and/or method is an illustrative, non-exclusive example of components, features, details, structures, embodiments, and/or methods according to the present disclosure. Thus, the described component, feature, detail, structure, embodiment, and/or method is not intended to be limiting, required, or exclusive/exhaustive; and other components, features, details, structures, embodiments, and/or methods, including structurally and/or functionally similar and/or equivalent components, features, details, structures, embodiments, and/or methods, are also within the scope of the present disclosure. 
     As used herein, the terms “selective” and “selectively,” when modifying an action, movement, configuration, or other activity of one or more components or characteristics of an apparatus, mean that the specific action, movement, configuration, or other activity is a direct or indirect result of one or more dynamic processes, as described herein. The terms “selective” and “selectively” thus may characterize an activity that is a direct or indirect result of user manipulation of an aspect of, or one or more components of, the apparatus, or may characterize a process that occurs automatically, such as via the mechanisms disclosed herein. 
     As used herein, the terms “adapted” and “configured” mean that the element, component, or other subject matter is designed and/or intended to perform a given function. Thus, the use of the terms “adapted” and “configured” should not be construed to mean that a given element, component, or other subject matter is simply “capable of” performing a given function but that the element, component, and/or other subject matter is specifically selected, created, implemented, utilized, programmed, and/or designed for the purpose of performing the function. It is also within the scope of the present disclosure that elements, components, and/or other recited subject matter that is recited as being adapted to perform a particular function may additionally or alternatively be described as being configured to perform that function, and vice versa. Similarly, subject matter that is recited as being configured to perform a particular function may additionally or alternatively be described as being operative to perform that function. 
     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. 
     As used herein, the phrase “at least one,” in reference to a list of one or more entities should be understood to mean at least one entity selected from any one or more of the entities in the list of entities, but not necessarily including at least one of each and every entity specifically listed within the list of entities and not excluding any combinations of entities in the list of entities. This definition also allows that entities may optionally be present other than the entities specifically identified within the list of entities to which the phrase “at least one” refers, whether related or unrelated to those entities specifically identified. Thus, as a non-limiting example, “at least one of A and B” (or, equivalently, “at least one of A or B,” or, equivalently “at least one of A and/or B”) may refer, in one embodiment, to at least one, optionally including more than one, A, with no B present (and optionally including entities other than B); in another embodiment, to at least one, optionally including more than one, B, with no A present (and optionally including entities other than A); in yet another embodiment, to at least one, optionally including more than one, A, and at least one, optionally including more than one, B (and optionally including other entities). In other words, the phrases “at least one,” “one or more,” and “and/or” are open-ended expressions that are both conjunctive and disjunctive in operation. For example, each of the expressions “at least one of A, B, and C,” “at least one of A, B, or C,” “one or more of A, B, and C,” “one or more of A, B, or C,” and “A, B, and/or C” may mean A alone, B alone, C alone, A and B together, A and C together, B and C together, A, B, and C together, and optionally any of the above in combination with at least one other entity. 
     As used herein, “at least substantially,” when modifying a degree or relationship, includes not only the recited “substantial” degree or relationship, but also the full extent of the recited degree or relationship. A substantial amount of a recited degree or relationship may include at least 75% of the recited degree or relationship. For example, an object that is at least substantially formed from a material includes an object for which at least 75% of the object is formed from the material and also includes an object that is completely formed from the material. As another example, a first direction that is at least substantially parallel to a second direction includes a first direction that forms an angle with respect to the second direction that is at most 22.5 degrees and also includes a first direction that is exactly parallel to the second direction. As another example, a first length that is substantially equal to a second length includes a first length that is at least 75% of the second length, a first length that is equal to the second length, and a first length that exceeds the second length such that the second length is at least 75% of the first length. 
     In the present disclosure, several of the illustrative, non-exclusive examples have been discussed and/or presented in the context of flow diagrams, or flow charts, in which the methods are shown and described as a series of blocks, or steps. Unless specifically set forth in the accompanying description, it is within the scope of the present disclosure that the order of the blocks may vary from the illustrated order in the flow diagram, including with two or more of the blocks (or steps) occurring in a different order, concurrently, and/or repeatedly. 
     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. 
     It is believed that the disclosure set forth above encompasses multiple distinct inventions with independent utility. While each of these inventions has been disclosed in its preferred form, the specific embodiments thereof as disclosed and illustrated herein are not to be considered in a limiting sense as numerous variations are possible. The subject matter of the inventions includes all novel and non-obvious combinations and subcombinations of the various elements, features, functions and/or properties disclosed herein. Similarly, where the claims recite “a” or “a first” element or the equivalent thereof, such claims should be understood to include incorporation of one or more such elements, neither requiring nor excluding two or more such elements. 
     It is believed that the following claims particularly point out certain combinations and subcombinations that are directed to one of the disclosed inventions and are novel and non-obvious. Inventions embodied in other combinations and subcombinations of features, functions, elements, and/or properties may be claimed through amendment of the present claims or presentation of new claims in this or a related application. Such amended or new claims, whether they are directed to a different invention or directed to the same invention, whether different, broader, narrower, or equal in scope to the original claims, are also regarded as included within the subject matter of the inventions of the present disclosure.