Panel assembly

Abstract

The invention relates to a panel assembly comprising a panel, a beam attached to the panel, and a plurality of stiffeners attached to the panel. Each stiffener comprises a respective bridge portion crossing from a first side of the beam to a second side of the beam at an intersection. Each bridge portion has an outer surface facing away from the panel and an inner surface facing towards the panel. The inner surface of each bridge portion is offset from the panel to form a recess at the intersection, and the outer surface of each bridge portion is offset from the panel to form a protrusion at the intersection. The invention also relates to an aircraft wing and an aircraft.

Description

Technical Field

[0001] This invention relates to panel assemblies. Background Technology

[0002] Composite stiffeners come in many different forms. One well-known form is the so-called "blade" stringer. Blade stringers have a relatively high aspect ratio (depth / width), which can lead to various disadvantages: for example, the free edges of the blade may be prone to damage, and the blade may be prone to buckling.

[0003] Another form is the "Omega" or "hat" stiffener. Hat stiffeners have a relatively low aspect ratio (depth / width), which avoids the disadvantages of blade stringers, but may also introduce different problems: such as increased weight and increased spacing between stiffeners.

[0004] US2010129589 discloses an example of a "hat-shaped" reinforcement. In one example, composite material is laid on foam placed in an internal mold line tool. The fuselage skin is then placed or laid on the composite material, foam, and internal mold line tool. A problem with this manufacturing process is that the reinforcement must be assembled on the internal mold line tool, which can make the process complex and difficult to automate.

[0005] An aircraft panel assembly disclosed in WO2020 / 229501 includes a panel and a plurality of reinforcing members located on the panel. Each reinforcing member has an attachment portion attached to the panel and a structural portion spaced apart from the panel. Rib leg beams pass through the reinforcing members at a series of intersections. At each intersection, the rib leg beam is located between the panel and the structural portion of a corresponding reinforcing member. Summary of the Invention

[0006] A first aspect of the invention provides a panel assembly including a panel, a beam attached to the panel, and a plurality of reinforcements attached to the panel, wherein each reinforcement includes a corresponding bridge-like portion at an intersection, spanning from a first side of the beam to a second side of the beam, each bridge-like portion having an outer surface facing away from the panel and an inner surface facing the panel, the inner surface of each bridge-like portion being offset from the panel to form a recess at the intersection, and the outer surface of each bridge-like portion being offset from the panel to form a protrusion at the intersection.

[0007] Optionally, the inner surface of each bridge-like section follows a curved path as it deviates from the panel.

[0008] Optionally, each bridge-like portion has a bridge-like portion depth between its outer surface and its inner surface; and each reinforcement includes: a first reinforcement portion attached to a panel on a first side of the beam, the first reinforcement portion having a first reinforcement portion depth; and a second reinforcement portion attached to a panel on a second side of the beam, the second reinforcement portion having a second reinforcement portion depth, wherein the bridge-like portion depth at the top of the protrusion is substantially the same as the first reinforcement portion depth and the second reinforcement portion depth.

[0009] Optionally, each reinforcement includes a core and a housing surrounding the core.

[0010] Alternatively, the outer shell may be made of fibrous material.

[0011] Optionally, the core includes a first strip and a second strip arranged side by side, and a spacer between the strips, wherein the reinforcement extends in a longitudinal direction, and the strips and the spacer have corresponding lengths extending in the longitudinal direction of the reinforcement.

[0012] Optionally, each housing includes a leg having a first leg portion, a second leg portion, and a bridge-shaped leg portion, the first leg portion being attached to a panel on a first side of the beam, the second leg portion being attached to a panel on a second side of the beam, and the bridge-shaped leg portion being offset from the panel at the bridge-shaped portion, wherein the inner surface of the bridge-shaped leg portion provides the inner surface of the bridge-shaped portion.

[0013] Optionally, each reinforcement includes a leg, and each leg includes a first leg portion, a second leg portion, and a bridge-shaped leg portion. The first leg portion is attached to the panel on a first side of the beam, the second leg portion is attached to the panel on a second side of the beam, and the bridge-shaped leg portion is offset from the panel at the bridge-shaped portion, wherein the inner surface of the bridge-shaped portion is the inner surface of the bridge-shaped leg portion.

[0014] Optionally, each protrusion includes a pair of bevels and a top between the bevels.

[0015] Optionally, each ramp is circular where it intersects with the top.

[0016] Optionally, the panel assembly further includes a first bridge-shaped support structure and a second bridge-shaped support structure, wherein the first bridge-shaped support structure is located on the first side of the beam between the bridge-shaped portion and the panel; and the second bridge-shaped support structure is located on the second side of the beam between the bridge-shaped portion and the panel.

[0017] Optionally, each bridge section includes reinforcing fibers that extend continuously along the bridge section and cross the beam from a first side to a second side at the intersection. Optionally, at least some of the reinforcing fibers deviate from the panel at each end of the bridge section.

[0018] Optionally, the beam includes a plurality of beam recesses, and the inner surface of each bridge-shaped portion sits in a corresponding beam recess.

[0019] Optionally, each bridge-shaped portion has a pair of sidewalls connecting the outer surface to the inner surface, and the beam recess has a sidewall that contacts the sidewalls of the bridge-shaped portion.

[0020] Optionally, each reinforcement is adhered to the panel on each side of the beam.

[0021] Alternatively, the beam is adhered to the panel.

[0022] Optionally, the inner surface of each bridge section is adhered to the beam.

[0023] Optionally, each rib support beam has an increased width at each intersection, such that the width of the rib support beam at the intersection is greater than the width of the rib support beam between the intersections.

[0024] A second aspect of the invention provides an aircraft wing that includes a panel assembly according to the first aspect.

[0025] Optionally, the panel is a first covering panel of the aircraft wing; and the aircraft wing also includes a second covering panel and ribs connecting the first covering panel and the second covering panel, wherein the beam is a rib support beam attached to the ribs between the intersections.

[0026] Alternatively, the ribbed support beams are attached to the ribs between the intersecting sections by fasteners.

[0027] A third aspect of the invention provides an aircraft including a panel assembly according to the first aspect.

[0028] A fourth aspect of the invention provides an aircraft wing including an upper cover panel, a lower cover panel, ribs connecting the upper and lower cover panels, and a plurality of reinforcements attached to the upper and lower cover panels, wherein each rib is connected to each cover panel via a corresponding rib / cover member connecting device, at least one of the rib / cover member connecting devices including a rib support beam passing through the reinforcements at a series of intersections and attached to a corresponding rib among the ribs between the intersections, wherein each reinforcement is offset from the panel at each intersection to form a corresponding protruding bridge-like portion across the rib support beam at the intersection. Attached Figure Description

[0029] Embodiments of the present invention will now be described with reference to the accompanying drawings, in which:

[0030] Figure 1 The aircraft was shown;

[0031] Figure 2 The aircraft's starboard wing is shown;

[0032] Figure 3 It is a cross-sectional view of the wing box;

[0033] Figure 4 It is an isometric view of the enhanced panel components;

[0034] Figure 5 yes Figure 4 A floor plan of the components;

[0035] Figure 6 yes Figure 4 The side view of the component;

[0036] Figure 7 It is along Figure 6 A cross-sectional view taken from line CC in the diagram;

[0037] Figure 8 It is along Figure 6 A cross-sectional view taken from line BB in the middle;

[0038] Figure 9 It is along Figure 5 A cross-sectional view taken from line AA in the diagram;

[0039] Figure 10 It is along Figure 5 A cross-sectional view of line DD in the diagram;

[0040] Figure 11A A first embodiment of the ribbed support beam is shown; and

[0041] Figure 11B A second embodiment of the ribbed support beam is shown. Detailed Implementation

[0042] Figure 1 An aircraft 1 with a port wing 2 and a starboard wing 3 is shown. Each wing has a cantilever structure whose length extends from the root to the tip in the wingspan direction 42, the root of which connects to the fuselage 4 of the aircraft. Wings 2 and 3 are similar in construction and will therefore be referred to only for details. Figure 2 and Figure 3 Detailed description of starboard wing 3.

[0043] The main structural components of the wing are made of Figure 3The wing box formed by the upper cover panel 21, lower cover panel 22, front spar 6, and rear spar 7 is shown in cross-section. Cover panels 21, 22 and spars 6, 7 are carbon fiber reinforced polymer (CFRP) laminated components. Each cover panel has a curved aerodynamic surface (the upper surface of the upper cover panel 21 and the lower surface of the lower cover panel 22) on which air flows during flight. Each cover panel also has an inner surface that carries a series of reinforcements 8 extending along the wingspan direction 42. Each cover panel carries a large number of reinforcements 8, which are shown for clarity in... Figure 2 Only five of the reinforcing members are shown in the diagram, and... Figure 3 Only seven of the reinforcing members are shown in the diagram. A larger number of reinforcing members can be installed on the wing chords. Each reinforcing member 8 is connected to one cover panel but not to another. In the case of aircraft wing cover panels, reinforcing members 8 are often referred to as stringers, but the term "reinforcing member" will be used below.

[0044] The wing box also has multiple transverse ribs, each connecting to the cover panels 21, 22 and the spars 6, 7. These ribs include the innermost inner rib 10 located at the root of the wing box, and numerous other ribs spaced apart from the innermost rib along the length of the wing box. The wing box is divided into two fuel tanks: an inner wing fuel tank defined by the inner rib 10, the mid-span rib 11, the cover panels 21, 22 and the spars 6, 7; and an outer wing fuel tank defined by the mid-span rib 11, the outer rib 12 at the tip of the wing box, the cover panels 21, 22 and the spars 6, 7.

[0045] The inner rib 10 is an attachment rib that forms the root of the wing box and connects to the central wing box 20 within the fuselage 4. The bulkhead rib 13 (shown in dashed lines) forms an internal bulkhead within the fuel tank, dividing the fuel tank into multiple compartments. Ribs 10, 11, and 12 are sealed to prevent fuel from leaking from the two fuel tanks, but the bulkhead rib 13 is not sealed, allowing fuel to flow between the compartments. (As shown in...) Figure 2 As can be seen, the reinforcing member 8 stops near the inner rib 10 and the outer rib 12, but passes through the diaphragm rib 13 and the mid-span rib 11.

[0046] Each rib 10, 11, 13 connects the upper cover panel 21 to the lower cover panel 22, and Figure 3The upper rib / cover connection device and the lower rib / cover connection device for rib 11 are shown by way of example. Rib leg beams 18 are adhered to the inner surface of each cover panel 21, 22 and are attached to the rib 11 between the reinforcing members 8 by fasteners 14 (such as bolts or rivets) passing through the rib 11 and the rib leg beams 18. The reinforcing members 8 pass through mouse hole openings 20 in the rib 11.

[0047] Each stiffener 8 crosses the rib support beam 18 at the intersection. At each intersection, the rib support beam 18 is located between the panels 21, 22 and the corresponding stiffener among the stiffeners 8.

[0048] As noted above, the upper cover panel 21 and the lower cover panel 22 provide the upper and lower walls of the fuel tank, respectively. Overfilling the fuel tank can generate significant fuel pressure, which risks causing the ribbed leg beam 18 to detach from the cover panel. The interlocking ribbed leg / stringer assembly allows the reinforcement 8 to hold the ribbed leg beam 18 against the cover panel downwards and prevents fuel pressure from separating the ribbed leg beam 18 from the cover panel.

[0049] Using a single rib leg beam 18 for each rib / cover interface reduces the manufacturing complexity of the component. It also eliminates the need to align multiple rib legs with each other.

[0050] Figure 4 and Figure 5 A panel assembly is shown, which includes: a cover panel 22; a ribbed support beam 18; and a reinforcement 8 supported on the inner surface of the cover panel 22.

[0051] Figure 7 A cross-section of one of the reinforcing members 8, transverse to its length, is shown. Each reinforcing member 8 includes a core 30 and a housing 31. The housing 31 has a closed cross-section and completely surrounds the core 30 on all sides. In this example, the housing 31 has a generally rectangular outer profile with rounded corners, although other shapes are possible.

[0052] The outer shell 31 is formed of a fiber-reinforced composite material, such as a carbon fiber-reinforced polymer. For example, the outer shell 31 may include a layer of woven fabric wound around the core 30, or the outer shell 31 may be formed by weaving.

[0053] The housing 31 includes a foot 32, a crown 33 opposite to the foot 32, a first sidewall 34, and a second sidewall 35 opposite to the first sidewall 34. The foot 32 of the housing is attached to the cover panel 22. An adhesive flange 36 is applied at the intersection of the rounded corner of the housing 31 and the cover panel 22.

[0054] like Figure 7As observed in a cross-section transverse to the longitudinal direction of the stiffener, each sidewall 34, 35 is longer than the leg 32. For example... Figure 7 As observed in a cross section transverse to the longitudinal direction of the stiffener, each sidewall 34, 35 is also longer than the crown 33.

[0055] The first sidewall 34 and the second sidewall 35 are vertical and generally parallel to each other. The reinforcement 8 can be inspected using various non-destructive testing (NDT) techniques. In one example, ultrasonic waves are guided into the reinforcement 8 through one of the sidewalls 34 and 35, and the reflections are analyzed. The vertical orientation of the sidewalls 34 and 35 facilitates inspection of the reinforcement in this manner because the ultrasonic waves are guided back to the NDT probe, rather than being guided upwards at an angle through the inclined sidewalls as in US2010129589. However, in other embodiments, the housing 31 may have a trapezoidal cross-section, such that the first sidewall 34 and the second sidewall 35 are not parallel to each other.

[0056] The core 30 includes a first slat 40 and a second slat 41, a spacer 50 between the slats, and a cover 51 between the slats 40 and 41 and the crown 33 of the outer casing 31.

[0057] As in Figure 7 As shown, slats 40 and 41 are arranged side by side. Each slat includes an inner edge facing the panel 22, an outer edge facing away from the panel 22 and covered by the cover 51, an inner portion facing another slat, and an outer portion facing away from another slat.

[0058] The first slat 40 is adjacent to the first sidewall 34, and the second slat 41 is adjacent to the second sidewall 35. In this embodiment, the outer portion of the slat contacts the sidewalls 34 and 35 of the housing, and optionally adheres to the sidewalls 34 and 35 of the housing. In other embodiments, the outer portion of the slat may be adjacent to the sidewalls 34 and 35 of the housing, but not in contact with them.

[0059] In this embodiment, the slats 40 and 41 have rectangular cross-sections, but this is not necessary, and other cross-sectional shapes are also possible.

[0060] Preferably, the core 30 has no more than two strips 40, 41. This makes NDT testing easy and simplifies the assembly of the core 30.

[0061] The slats 40 and 41 are formed of fiber-reinforced composite materials, which may be carbon fiber-reinforced polymers similar to the material of the outer shell 31, or other types of fiber-reinforced composite materials.

[0062] The spacer 50 is formed of a material with sufficient rigidity to control the size of the gap between the slats 40 and 41. For example, the spacer 50 may be formed of a foam material.

[0063] The cover 51 is adjacent to and in contact with the crown 33 of the housing 31. The cover 51 is formed of a material that is rigid enough to provide impact protection. For example, the cover 51 may be formed of a foam material, which may be the same as or a different material from the spacer 50.

[0064] The slats 40 and 41 and the outer shell 31 are structural components that have a higher mass per unit volume than the spacer 50 and a higher mass per unit volume than the cover 51.

[0065] Each reinforcing member 8 is made of Figure 2 , Figure 5 , Figure 6 , Figure 8 and Figure 9 The longitudinal / wingspan direction indicated by arrow 42 extends outwards towards the wingtip of wing 3.

[0066] As in Figure 8 and Figure 9 As shown, the slats 40, 41, spacer 50, and cover 51 have corresponding lengths extending in the longitudinal / span direction 42 of the reinforcement 8. The slats 40, 41, spacer 50, and cover 51 extend continuously from their inner ends to their outer ends along the entire length of the reinforcement 8, or at least extend continuously along a large portion of the length of the reinforcement 8.

[0067] The slats 40 and 41 are spaced apart by a certain gap across the width of the reinforcing member, and the spacer 50 fills the gap between the slats. The slats 40 and 41 do not contact each other at any point along their respective lengths.

[0068] The outer casing 31 has a depth (in) Figure 7 The standard designation is D) and the width transverse to the length of the reinforcement (in Figure 7 The designation is W). Slats 40 and 41 are spaced apart across the width of housing 31, and the depth (D) of housing is greater than the width (W) of housing. In this example, the aspect ratio (depth / width) is approximately 4; however, the aspect ratio can vary.

[0069] Compared to the reinforcement in US2010129589, the relatively higher aspect ratio (depth / width) makes reinforcement 8 lighter and easier to arrange on the panel with smaller spacing between adjacent reinforcements.

[0070] Compared to conventional blade reinforcements, reinforcement 8 also has a relatively low aspect ratio (depth / width), which makes reinforcement 8 less prone to buckling and damage at its free edges.

[0071] The spacer 50 is sandwiched between a pair of strips 40, 41 so that the width of the reinforcement 8 can be customized by appropriately selecting the width of the spacer 50.

[0072] Placing the spacer 50 between a pair of slats 40 and 41 allows the mechanical properties of the reinforcing member 8 to vary along its length by changing the relative width of the spacer and the slats.

[0073] exist Figure 8 An example of this situation is shown in the figure. The slats 40, 41, spacer 50, and the gap between slats 40 and 41 are... Figure 8 The text is shown as having the corresponding width. Figure 8 In the transition region 52 shown, the width of the slats 40 and 41 decreases along the longitudinal direction 42, that is, towards the tip of the wing. The width of the spacer 50 and the gap between the slats increase in opposite directions in the same transition region 52.

[0074] Therefore, the total width of the stiffener—that is, the width between the sidewalls 34 and 35—remains unchanged in the transition region 52. This ensures that even if the width and cross-sectional area of ​​the slats 40 and 41 change, the width and cross-sectional area of ​​the core 30 remain substantially unchanged along the length of the stiffener.

[0075] The stringer 8 is manufactured by assembling a core 30 having spacers 50 located between slats 40 and 41, and then surrounding the core 30 with a housing 31, for example by winding or weaving the housing 31 around the core 30.

[0076] The reinforcing member 8 can be fitted as a dry fiber preform, i.e., a dry fiber preform having a shell 31 and slats 40, 41 formed of porous dry fiber material. Alternatively, the reinforcing member 8 can be fitted as a prepreg, i.e., a prepreg having a shell 31 and slats 40, 41 fitted with a composite material reinforced with "prepreg" fibers.

[0077] The cover panel 22 can be laid on the molding tool as a dry fiber preform, and the reinforcement 8 can be placed on the panel located on the molding tool. Each reinforcement 8 can be fitted as a prepreg and pre-cured before being placed on the cover panel 22, or each reinforcement 8 can be placed on the cover panel 22 as a dry fiber preform.

[0078] The cover panel preform on the molding tool is then infused with a matrix material, which is then cured. The curing of the matrix material adheres the reinforcement 8 to the panel 22. If each reinforcement 8 is pre-cured before being laid onto the panel 22, the reinforcement is adhered to the panel 22 via a co-curing joint. If each reinforcement is placed on the cover panel 22 as a dry fiber preform, then the reinforcement and the panel 22 preform are co-infused with the matrix material, such that each reinforcement 8 is adhered to the panel 22 via a co-curing joint.

[0079] It is advantageous to use a housing 31 with a closed cross-section that completely surrounds the core 30, because it allows the reinforcement 8 to be easily assembled and handled “offline” in an automated process, rather than being laid “online” on the molding tool as in US2010129589.

[0080] As in Figure 9 and Figure 10 As shown, each reinforcing member 8 includes a corresponding bridge-like portion 60, which extends from the first side of the rib support beam 18 at the intersection. Figure 9 and Figure 10 (on the left side) across the ribbed foot beam 18 to the second side of the ribbed foot beam 18 ( Figure 9 and Figure 10 (Right side).

[0081] Each bridge-shaped portion 60 has an outer surface 61 facing away from the panel 22 and an inner surface 62 facing the panel 22. The inner surface 62 of each bridge-shaped portion is offset from the panel to form a recess 63 at the intersection, and the outer surface 61 of each bridge-shaped portion is offset from the panel to form a protrusion 64 at the intersection.

[0082] Each protrusion 64 includes a pair of bevels 70 and a flat top 71 between the bevels. Each bevel 70 is rounded where it intersects with the top 71. Other shapes are also possible: for example, the top 71 and / or the bevels 70 may be continuously rounded.

[0083] The inner surface 62 of each bridge-like portion follows a curved path 65 as it deviates upward and away from the panel. Other shapes are also possible: for example, the inner surface 62 may be a continuous circle.

[0084] As in Figure 10 As shown, each reinforcing member 8 includes: a first reinforcing portion 66 attached to the panel 22 on a first side of the ribbed support beam 18, the first reinforcing portion 66 having a first reinforcing portion depth D1; and a second reinforcing portion 67 attached to the panel on a second side of the ribbed support beam 18, the second reinforcing portion 67 having a second reinforcing portion depth D2. The bridge-like portion 60 has a bridge-like portion depth D3 between its outer surface 61 and inner surface 62.

[0085] The bridge-shaped portion at the top of the protrusion 64 has a depth D3 that is approximately the same as the depth D1 of the first reinforcing member portion and the depth D2 of the second reinforcing member portion.

[0086] Each shell includes Figure 7 The support leg 32 shown extends continuously over the bridge-like portion 60. (As shown in...) Figure 9 As shown, the support 32 has a first support portion 32a, a second support portion 32b, and a bridge-shaped support portion 32c. The first support portion 32a is adhered to the panel on a first side of the ribbed support beam 18, the second support portion 32b is adhered to the panel on a second side of the ribbed support beam 18, and the bridge-shaped support portion 32c is offset from the panel at the bridge-shaped portion 60. The inner surface of the bridge-shaped support portion 32c provides the inner surface 62 of the bridge-shaped portion 60.

[0087] At each intersection, a pair of bridge-like support structures 80, 81 are provided. The pair of bridge-like support structures 80, 81 includes a first bridge-like support structure 80 located on the first side of the ribbed support beam between the bridge-like portion and the panel, and a second bridge-like support structure 81 located on the second side of the ribbed support beam between the bridge-like portion and the panel. The support structures 80, 81 are not wound within the housing 31 and can be added as part of the ribbed support beam 18 for seating the reinforcement 8 thereon. The support structures 80, 81 can be made of foam material or carbon fiber composite material.

[0088] Each leg 32 includes reinforcing fibers that extend continuously along the bridge portion 60 and cross the beam from the first side to the second side at the intersection. Some or all of the reinforcing fibers in the leg 32 may deviate from the panel at each end of the bridge portion 60. Some or all of the reinforcing fibers in the remainder of the housing 31 may also deviate from the panel at each end of the bridge portion 60.

[0089] Each slat 40, 41 includes reinforcing fibers that extend continuously along the bridge portion 60 and cross the beam from the first side to the second side at the intersection. Some or all of the reinforcing fibers in the slats 40, 41 may be offset from the panel at each end of the bridge portion.

[0090] As in Figure 11A As shown, the ribbed support beam 18 has a beam recess 90 at each intersection. The beam recess 90 reduces the height of the ribbed support beam 18 at the intersection, so that the bridge-like portion 60 does not have to be too far off the panel.

[0091] Each beam recess 90 has a base 91 and a pair of angled sidewalls 92. The inner surface of each bridge-shaped portion 60 is seated in a corresponding beam recess of the beam recess 90 and in contact with the base 91.

[0092] The width of the ribbed support beam 18 increases at each intersection, so the width of the ribbed support beam 18 at the intersection (at the base 91 of each beam recess 90) is greater than the width of the ribbed support beam 18 at the protrusion 93 between the intersections.

[0093] Figure 11B An alternative embodiment of the ribbed support beam 18 is shown. Figure 11B Ribbed foot beam 18 and Figure 11A The ribbed support beam 18 is the same as that in the previous section, except that the base of each beam recess has a cut-out portion 95 with vertical sidewalls. The reinforcing member 8 is accommodated in the cut-out portion 95.

[0094] Each bridge-like portion 60 has a pair of sidewalls 34, 35 connecting the outer surface 61 to the inner surface 62. Figure 11B In this embodiment, the vertical sidewall of the cut-off portion 95 contacts the sidewalls 34 and 35 of the bridge-shaped portion 60. This provides support for the reinforcement 8, thereby preventing the reinforcement 8 from tipping over laterally.

[0095] Each reinforcement 8 can be adhered to the panel 22 on each side of the ribbed support beam 18 by means of a co-bonded joint or co-cured joint as described above.

[0096] Similarly, the ribbed support beam 18 can be adhered to the panel 22 via a co-bonded joint or a co-cured joint.

[0097] In addition, the inner surface 62 of each bridge section can be adhered to the rib support beam 18 via a co-bonded joint or a co-cured joint.

[0098] In summary, the aircraft wing 3 includes an upper cover panel 21, a lower cover panel 22, ribs 10, 11, 12, and 13 connecting the upper cover panel to the lower cover panel, and multiple reinforcing members 8 attached to the upper and lower cover panels. Ribs 11 and 13 are connected via... Figure 3 The corresponding rib / cover connection devices shown are connected to each cover panel 21, 22. Each rib / cover connection device includes a rib support beam 18 that passes through the reinforcement 8 at a series of intersections and is attached to a corresponding rib among the ribs 11, 13 between the intersections. Figure 4 and Figure 6 As shown, each stiffener 8 deviates from the panel at each intersection to form a corresponding protruding bridge-like portion 60 that spans the ribbed support beam 18 at the intersection. This is an improvement over the arrangement in WO2020 / 229501 because the bridge-like portion 60 can extend continuously across the intersection without any change in the cross-section of the stiffener.

[0099] Each stiffener 8 has two consecutive load-bearing members (slats 40, 41) extending the length of the stiffener. These slats 40, 41 have foam members 50 between them, allowing any increase in slat thickness to occupy the interior of the stiffener (increase and decrease in foam thickness) while maintaining a consistent external profile. A foam cap 51 is present at the top of the stiffener to prevent impact on the edges of the structural layers and improve damage tolerance. Where the stiffener 8 interlocks with / crosses the ribbed support beam 18, there are members (interlocking supports 80, 81) useful for allowing structural members to sit on the top. The entire stiffener 8 is then wound or braided.

[0100] The aforementioned reinforcing panel is a cover for an aircraft wing, but the present invention can be applied to other types of reinforcing panel assemblies for aircraft. For example, the reinforcing panel assembly can form the skin of an aircraft fuselage, which includes longitudinal beams extending in a longitudinal direction and a frame extending circumferentially around the fuselage. In this case, the longitudinal beams may have bridge-like portions offset from the skin and crossing the frame, or the frame may have bridge-like portions offset from the skin and crossing the longitudinal beams. Similarly, the longitudinal beams can be formed as shown in... Figure 7 As shown, or the framework can be formed as in Figure 7 As shown in the diagram. In the latter case, the longitudinal direction of the stiffener is the circumferential direction of the frame.

[0101] In other embodiments, the reinforcing panel assembly can be part of a different vehicle, such as a ship or spacecraft; or the reinforcing panel assembly can be used in something other than a vehicle.

[0102] Each reinforcing member 8 in the above embodiments, including the bridge-shaped portion 60, includes a core 30 and a shell 31 surrounding the core. In other embodiments, each reinforcing member 8 (including the bridge-shaped portion 60) may have a different structure: for example, the reinforcing member 8 may be a "blade" reinforcing member with a T-shaped cross section or a "cap" reinforcing member with an omega-shaped cross section.

[0103] When the word "or" appears, it will be interpreted as meaning "and / or", meaning that the items referred to are not necessarily mutually exclusive and can be used in any appropriate combination.

[0104] Although the invention has been described above with reference to one or more preferred embodiments, it will be understood that various changes or modifications may be made without departing from the scope of the invention as defined by the appended claims.

Claims

1. A panel assembly, the panel assembly comprising a panel, a beam attached to the panel, and a plurality of reinforcements attached to the panel, wherein, Each reinforcement includes a corresponding bridge-like portion that spans from a first side of the beam to a second side of the beam at an intersection. Each bridge-like portion has an outer surface facing away from the panel and an inner surface facing the panel. The inner surface of each bridge-like portion is offset from the panel to form a recess at the intersection, and the outer surface of each bridge-like portion is offset from the panel to form a protrusion at the intersection.

2. The panel assembly according to claim 1, wherein, The inner surface of each bridge-shaped portion follows a curved path as the bridge-shaped portion deviates from the panel.

3. The panel assembly according to any of the preceding claims, wherein, Each bridge-like portion has a bridge-like portion depth between its outer surface and its inner surface; and each reinforcement includes: a first reinforcement portion attached to the panel on the first side of the beam, the first reinforcement portion having a first reinforcement portion depth; and a second reinforcement portion attached to the panel on the second side of the beam, the second reinforcement portion having a second reinforcement portion depth, wherein the bridge-like portion depth at the top of the protrusion is substantially the same as the depth of the first reinforcement portion and the depth of the second reinforcement portion.

4. The panel assembly according to any of the preceding claims, wherein, Each reinforcement includes a core and a housing surrounding the core.

5. The panel assembly according to claim 4, wherein, Each housing includes a leg having a first leg portion, a second leg portion, and a bridge-shaped leg portion, the first leg portion being attached to the panel on a first side of the beam, the second leg portion being attached to the panel on a second side of the beam, and the bridge-shaped leg portion being offset from the panel at the bridge portion, wherein the inner surface of the bridge-shaped leg portion provides the inner surface of the bridge portion.

6. The panel assembly according to any one of claims 1 to 4, wherein, Each reinforcement includes a leg, and each leg includes a first leg portion, a second leg portion, and a bridge-shaped leg portion, the first leg portion being attached to the panel on a first side of the beam, the second leg portion being attached to the panel on a second side of the beam, and the bridge-shaped leg portion being offset from the panel at the bridge portion, wherein the inner surface of the bridge portion is the inner surface of the bridge-shaped leg portion.

7. The panel assembly according to any of the preceding claims, wherein, Each protrusion includes a pair of ramps and a top between the ramps.

8. The panel assembly according to claim 7, wherein, Each ramp is circular where it intersects with the top.

9. The panel assembly according to any of the preceding claims further includes a first bridge-shaped support structure and a second bridge-shaped support structure, the first bridge-shaped support structure being located on the first side of the beam between the bridge-shaped portion and the panel, and the second bridge-shaped support structure being located on the second side of the beam between the bridge-shaped portion and the panel.

10. The panel assembly according to any of the preceding claims, wherein, Each bridge-like portion includes reinforcing fibers that extend continuously along the bridge-like portion and cross the beam from the first side to the second side of the beam at the intersection.

11. The panel assembly according to any of the preceding claims, wherein, The beam includes a plurality of beam recesses, and the inner surface of each bridge portion sits in a corresponding beam recess among the beam recesses.

12. The panel assembly of claim 11, wherein, Each bridge-shaped portion has a pair of sidewalls connecting the outer surface to the inner surface, and the beam recess has a sidewall that contacts the sidewalls of the bridge-shaped portion.

13. The panel assembly according to any of the preceding claims, wherein, Each reinforcement member is attached to the panel on each side of the beam.

14. The panel assembly according to any of the preceding claims, wherein, The beam is adhered to the panel.

15. The panel assembly according to any of the preceding claims, wherein, The inner surface of each bridge-like portion is adhered to the beam.

16. The panel assembly according to any of the preceding claims, wherein, Each rib support beam has an increased width at each intersection, such that the width of the rib support beam at the intersection is greater than the width of the rib support beam between the intersections.

17. An aircraft wing, the aircraft wing comprising a panel assembly according to any of the preceding claims.

18. The aircraft wing according to claim 17, wherein, The panel is a first cover panel of the aircraft wing; and the aircraft wing also includes a second cover panel and ribs connecting the first cover panel to the second cover panel, wherein the beam is a rib support beam attached to the ribs between the intersecting portions.

19. The aircraft wing according to claim 18, wherein, The rib support beam is attached to the ribs between the intersecting portions by fasteners.

20. An aircraft comprising a panel assembly according to any one of claims 1 to 16.

21. An aircraft wing, the aircraft wing comprising an upper cover panel, a lower cover panel, ribs connecting the upper cover panel to the lower cover panel, and a plurality of reinforcing members attached to the upper cover panel and the lower cover panel, wherein, Each rib is connected to each cover panel via a corresponding rib / cover connection device, at least one of the rib / cover connection devices including a rib support beam that crosses the reinforcement at a series of intersections and is attached to a corresponding rib among the ribs between the intersections, wherein each reinforcement is offset from the panel at each intersection to form a corresponding protruding bridge-like portion that crosses the rib support beam at the intersection.

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