Flap with torque member and method of forming the same

Abstract

The present application relates to a flap with a torque member and a method for forming the same. The flap includes a flap body. The flap body includes an upper skin, a lower skin opposite to the upper skin, and a plurality of spars extending between the upper skin and the lower skin. The flap also includes a torque member coupled to the flap body. A portion of the torque member is adjacent to at least one of the upper skin and the lower skin.

Description

Technical Field

[0001] The present invention relates generally to aircraft and, more particularly, to aircraft flaps having torque members and methods for forming the flaps. Background Art

[0002] Fixed-wing aircraft typically include flight control surfaces that can adjust and control the flight of the aircraft. For example, flaps mounted on the trailing edge of the wing change the effective profile of the wing and thus change the lift characteristics of the wing. In some types of flap systems, the inboard flap includes a torque member for moving the flap between a stowed position and a deployed position. Typically, the torque member extends into the side of the fuselage, or into the wing fairing structure of the fuselage, and is coupled to a flap support mechanism that controls the movement of the flap.

[0003] In many flap systems, the torque member is a tubular structure with a circular cross-sectional shape, commonly referred to as a torque tube. The torque tube is usually connected to a structural member of the flap, such as an inner wing rib. However, achieving appropriate structural performance and load-bearing performance may require a heavy torque tube and a bulky and complex connector, which increases the weight and cost of the aircraft. In addition, some flap systems use a fail-safe torque tube including a dual torque tube design, which further increases the cost, weight and complexity of the aircraft.

[0004] Therefore, those skilled in the art continue to conduct research and development work in the field of aircraft flap actuation. Summary of the invention

[0005] In one example, the disclosed flap includes a flap body. The flap body includes an upper skin, a lower skin opposite to the upper skin, and a plurality of spars extending between the upper skin and the lower skin. The flap also includes a torque member coupled to the flap body. A portion of the torque member is adjacent to at least one of the upper skin and the lower skin.

[0006] In one example, a wing of a disclosed aircraft includes a wing body and a flap. The flap includes a flap body that can be movably coupled to the wing body. The flap body includes an upper skin, a lower skin opposite to the upper skin, and a plurality of spars extending between the upper skin and the lower skin. The flap also includes a torque member coupled to the flap body. A portion of the torque member is adjacent to at least one of the upper skin and the lower skin.

[0007] In one embodiment, the disclosed method includes the following steps: (1) connecting an upper skin, a lower skin, and a plurality of spars to partially form a flap body; and (2) coupling a plurality of extension members to the flap body to partially form a torque member. The flap body is configured to be movably coupled to a wing of an aircraft. The torque member is configured to be coupled to a flap actuator of the aircraft.

[0008] Other examples of the disclosed flaps and methods will become apparent from the following detailed description, drawings, and appended claims. BRIEF DESCRIPTION OF THE DRAWINGS

[0009] Figure 1 is a schematic perspective view of an example of an aircraft;

[0010] Figure 2 is a schematic perspective view of one embodiment of a wing of an aircraft;

[0011] Figure 3 is a schematic perspective view of one embodiment of the disclosed flap;

[0012] Figure 4 is a schematic interior perspective view of an example of a portion of an aircraft showing an example of a torque member of the disclosed flap extending through an opening in a fuselage of the aircraft;

[0013] Figure 5 is a schematic partial perspective view of an example of the disclosed flap;

[0014] Figure 6 is a schematic front cross-sectional view of an example of the disclosed flap;

[0015] Figure 7 is a schematic partial plan view of an example of the disclosed flap;

[0016] Figure 8 is a schematic plan view of an example of the disclosed flap;

[0017] Fig. 9 is a schematic partial plan view of an example of the disclosed flap;

[0018] Fig.10 is a schematic partial plan view of an example of the disclosed flap;

[0019] Fig.11 is a schematic partial plan view of an example of the disclosed flap;

[0020] Fig.12 is a schematic partial plan view of an example of the disclosed flap;

[0021] Fig.13 is a schematic perspective view of an example of the disclosed flap;

[0022] Fig.14 is a flowchart of an example of the disclosed method; and

[0023] Fig.15 is a flow chart of an exemplary aircraft manufacturing and service methodology. DETAILED DESCRIPTION

[0024] The following detailed description refers to the accompanying drawings, in which specific examples described in the present disclosure are shown. Other examples with different structures and operations do not depart from the scope of the present disclosure. In different drawings, similar reference numerals may refer to the same features, elements or components.

[0025] The following provides illustrative, non-exhaustive examples that may, but do not necessarily, claim subject matter in accordance with the present disclosure.

[0026] Figure 1 2 is an illustrative example of aircraft 200. In this illustrative example, aircraft 200 is a fixed-wing aircraft. Aircraft 200 includes fuselage 202, a pair of wings 214 (also referred to as wings 214, respectively), and propulsion system 216. Aircraft 200 also includes a number of high-level systems, such as, but not limited to, electrical system 226, hydraulic system 228, and / or environmental system 230. Any number of other systems may also be included.

[0027] Fuselage 202 is the main body of aircraft 200 and includes any suitable central structure configured to accommodate a crew, one or more passengers, and / or cargo. In this illustrative example, fuselage 202 is an elongated, generally cylindrical fuselage. Fuselage 202 includes a front end portion located at a front end of fuselage 202, and a rear end portion located at a rear end of fuselage 202. As used herein, the terms "front" and "rear" have their ordinary meanings known to those of ordinary skill in the art and refer to positions relative to a direction of movement of aircraft 200. The rear end portion may also include a vertical stabilizer 240 and a horizontal stabilizer 238.

[0028] The fuselage 202 includes a body 222 defining an interior 224, which may include a passenger cabin and / or a cargo hold. A wing fairing structure 220 (e.g., a fuselage / wing fairing) may also be disposed at each interface between the fuselage 202 and the wing 214, and may extend from adjacent to (at or near) the fuselage 202 to adjacent to the wing 214 with which it is associated.

[0029] Wing 214 includes any suitable airfoil structure configured to provide lift to aircraft 200. In this illustrative example, wing 214 is an elongated structure extending from a lower portion of fuselage 202 in a swept-wing tapered platform. In other examples, wing 214 is straight or triangular. In yet other examples, wing 214 is trapezoidal, constant, elliptical, semi-elliptical, or other configurations known in the art.

[0030] In this illustrative example, propulsion system 216 includes two turbofan engines mounted to wing 214, for example, by brackets. In one example, each engine is housed in a nacelle that includes an inlet and a nozzle. In other examples, the engines may be mounted to fuselage 202 or other aircraft structures, such as the rear. In various other examples, propulsion system 216 may include more or fewer engines, and other types of engines (e.g., turboprop engines) may be used.

[0031] Aircraft 200 includes various flight control surfaces 232. Flight control surfaces 232 include any aerodynamic pivoting device for adjusting and controlling the flight and aerodynamic characteristics of aircraft 200. Examples of flight control surfaces 232 include inboard flaps 208 and / or outboard flaps 218 located on the rear end of wing 214, elevators 234 located on the rear end of horizontal stabilizers 238, rudders 236 located on the rear end of vertical stabilizers 240, and other control surfaces (e.g., nose flaps, ailerons, and spoilers). As used herein, the terms "inboard" and "outboard" have their ordinary meanings known to those skilled in the art, and refer to locations relative to the centerline of aircraft 200.

[0032] In one example, inboard flap 208 (also referred to as a plurality of inboard flaps 208) and / or outboard flap 218 (also referred to as a plurality of outboard flaps 218) comprise being installed on the trailing edge of wing 214 and be configured to pivot, rotate and / or translate (for example forward and backward) any suitable structure with respect to wing 214.Inboard flap 208 and / or outboard flap 218 are configured to change the lift characteristics of wing 214.Inboard flap 208 and / or outboard flap 218 are movable between at least rising (stowed, retracted or " flaps are put up ") position and descending (unfolded, extended or " flaps are put down ") position.In one example, inboard flap 208 and / or outboard flap 218 can pivot around fixed axis.In one example, inboard flap 208 and / or outboard flap 218 pivot by predetermined path, and this predetermined path is roughly curved arch.

[0033] In one example, the aircraft 200 also includes a flap actuator 260. The flap actuator 260 is associated with each wing 214 for actuating the inboard flap 208. In one example, the flap actuator 260 includes a motorized arm located in or housed in the fuselage 202 or the wing fairing structure 220.

[0034] In one example, the torque member 210 couples the flap actuator 260 with the associated inboard flap 208 to transfer an actuation / deactuation (e.g., lowering / raising) force from the flap actuator 260 to the associated inboard flap 208. The torque member 210 extends through an opening 206 in the aircraft 200 (e.g., an opening 206 in the fuselage 202 or a wing fairing structure 220). The size and shape of the opening 206 in the aircraft 200 are configured to accommodate the travel path of the torque member 210 when the inboard flap 208 is lowered and raised.

[0035] Figure 2 It is an illustrative example of wing 214. Wing 214 is any one of various wing structures including wing body 258. Wing body 258 made of various structural members includes but is not limited to upper wing skin 246, lower wing skin 248, multiple wing spars 250 extending between upper wing skin 246 and lower wing skin 248, and multiple wing ribs 252 extending between upper wing skin 246 and lower wing skin 248. These structural members are connected together by any of various methods, including but not limited to connection, co-solidification or integral formation by various fasteners. Wing spars 250 extend between wing root 254 of wing 214 and wing tip 256 of wing 214 along the span direction. Wing ribs 252 extend between leading edge 244 of wing 214 and trailing edge 242 of wing 214 along the chord direction. Wing 214 also includes flap 100. One example of the disclosed flap 100 is movably coupled to the wing 214 at a trailing edge 242 of the wing 214 proximate a wing root 254 .

[0036] Reference Figures 3 to 13 , various examples of flaps 100 are disclosed. The disclosed flaps 100 include a flap body 164 and a torque member 108 coupled to the flap body 164. The torque member 108 extends from the inboard end 124 of the flap body 164 in the inboard direction. In one example, the flap body 164 includes an upper skin 102, a lower skin 104 relative to the upper skin 102, and a plurality of spars 106 (also individually referred to as spars 106, and collectively referred to as spars 106) extending between the upper skin 102 and the lower skin 104. A portion of the torque member 108 is adjacent to at least one of the upper skin 102 and the lower skin 104. As used herein, the term "adjacent" refers to a first item contacting with a second item or an item adjacent along a shared boundary and sharing at least one boundary with it.

[0037] Flap 100 is an example of an inboard flap 208 of wing 214 of aircraft 200, and torque member 108 is an example of inboard flap 208 ( Figure 1In other examples, the teachings of the present disclosure may be applied to one or more other flight control surfaces 232 of aircraft 200.

[0038] In one example, flap 100 includes any suitable pivoting structure (eg, a flap 100 mounted on or otherwise movably coupled to wing body 258 of wing 214 at trailing edge 242 of wing 214). Figure 1 and Figure 2 ). In one example, the flap 100 is located adjacent to a wing fairing structure 220 of a fuselage 202 of an aircraft 200. During operation of the flap 100, the flap 100 can move between at least a raised (stowed, retracted, or "flaps up") position and a lowered (deployed, extended, or "flaps down") position to change the lift characteristics of the wing.

[0039] Reference Figure 3 , the flap body 164 includes an inboard end 124 and an outboard end 126 opposite the inboard end 124. The flap body 164 also includes a front end 112 and a rear end 116 opposite the front end 112. The torque member 108 includes an inboard end 180 and an outboard end 178 opposite the inboard end 180. In one example, the torque member 108 is coupled to the inboard end 124 of the flap body 164 and extends outwardly from the inboard end 124 of the flap body 164 in an inboard direction.

[0040] In one example, the torque member 108 includes a plurality of extension members 128 (also individually referred to as extension members 128 and collectively referred to as extension members 128). Each of the extension members 128 is coupled to the flap body 164 at the inboard end 124 and extends in an inboard direction from the inboard end 124. In one example, each of the extension members 128 is parallel to an adjacent one of the plurality of extension members 128.

[0041] As used herein, the term "parallel" has its common meaning known to those skilled in the art, and refers to a situation where a first line extending longitudinally through a first item shares the same plane with a second line extending longitudinally through a second item, and the first line and the second line are equidistant from each other. As used herein, the term "parallel" includes exact parallelism and approximate parallelism (i.e., close to parallelism, which still performs the desired function and achieves the desired result). As used herein, the term "adjacent" refers to a first item being directly adjacent to a second item, or being directly close to a second item.

[0042] In one example, the extension member 128 that partially forms the torque member 108 defines a structural member of the torque member 108. As used herein, when referring to any one of a plurality of structural members that partially form the torque member 108, the phrase "structural member" refers to a load-bearing element that is configured to carry a load or react to stresses applied to the torque member 108.

[0043] In one example, the flap body 164 includes an inboard rib 168 extending between an adjacent pair of the plurality of spars 106 at the inboard end 124 of the flap body 164. Each of the plurality of extension members 128 is coupled to the inboard rib 168. In one example, the inboard rib 168 includes a buttress or flange that is vertically oriented and located on an inboard side of the inboard rib 168. In one example, each of the extension members 128 is fastened (e.g., bolted) to a buttress of the inboard rib 168. Any other suitable joint may be used to couple the outboard end of the extension member 128 to the inboard rib 168.

[0044] Each of the extension members 128 and / or the inner ribs 168 may be formed of any suitable structural material. In one example, the extension members 128 and / or the inner ribs 168 are formed of a metal material. In one example, the extension members 128 and the inner ribs 168 are made of a composite material. An example of a composite material is a fiber reinforced polymer including a polymer matrix (e.g., a thermosetting resin or a thermoplastic polymer) reinforced with fibers (e.g., glass, carbon, aramid, etc.). As an example, the composite material is a carbon fiber reinforced polymer.

[0045] In various examples, each of the extension members 128 has one of any number of different sizes and / or cross-sectional shapes. In general, the size and / or cross-sectional shape of any one of the extension members 128 depends on and may be balanced between various factors, including, but not limited to, stiffness and / or strength requirements to adequately react to loads applied to the torque member 108 and / or flap 100, fault protection requirements for the torque member 108, opening 206 ( Figure 4 The size and / or cross-sectional shape of each extension member 128 and the torque member 108 as a whole may be a factor regarding the position of the torque member 108 relative to the flap body 164 (eg, toward the forward end 112 or toward the rearward end 116 ).

[0046] The torque member 108 formed by the extension member 128 connected to the inner rib 168 of the flap body 164 can reduce the cost, complexity and / or weight of the flap 100, and can reduce the cost, complexity and / or weight associated with the production of the aircraft wing and / or the aircraft. For example, compared with a metal torque tube, the torque member 108 formed by the extension member 128 is not as expensive as manufacturing a metal (e.g., titanium or steel) torque tube, and reduces the parts and time required to assemble and connect the torque member 108. As an example, compared with a traditional steel torque tube, the extension member 128 of the torque member 108 formed by the composite material can reduce the weight of the aircraft wing. As an example, compared with connecting a traditional steel torque tube to the flap body, by connecting each of the extension members 128 to the inner rib 168 to connect the torque member 108 to the flap body 164, the complexity and cost associated with connecting the torque member 108 to the flap body 168 can be reduced. As one example, forming the torque member 108 from the extension member 128 also enables the position of the torque member 108 to be customized relative to the flap body 164 and / or the fuselage 202 , which may be used to optimize penetration of the torque member 108 through the opening 206 in the fuselage 202 .

[0047] In one example, if Figure 3 As shown, the torque member 108 is located between the front end 112 and the rear end 116 of the flap body 164, such as near the middle portion of the flap body 164. In one example, the torque member 108 is located toward the front end 112 of the flap body 164. In one example, the torque member 108 is located toward the rear end 116 of the flap body 164.

[0048] In one example, the torque member 108 has a cross-sectional shape that at least partially matches or matches a portion of the cross-sectional shape of the flap body 164 as viewed from the inboard end 124. The cross-sectional shape of the torque member 108 at least partially matches the cross-sectional shape of the flap body 164 at the inboard end 124 of the flap body 164 can reduce the complexity associated with coupling the torque member 108 to the flap body 164, and can reduce the impact of the torque member 108 on the aerodynamic characteristics of the flap 100 and / or the aircraft 200. As used herein, components having at least partially matching cross-sectional shapes can have, but are not required to have, matching dimensions and / or sizes.

[0049] In one example, the torque member 108 has a non-circular cross-sectional shape. As an example, the torque member 108 has a polygonal cross-sectional shape. In one illustrative example, the torque member 108 has a rectangular cross-sectional shape. In another illustrative example, the torque member 108 has a cross-sectional shape that includes a combination of linear and arcuate sides, such as three substantially linear sides and a fourth arcuate side connecting two of the linear sides to form a substantially rectangular cross-sectional shape.

[0050] In one example, the torque member 108 includes or is at least partially formed by a front wall 156, a rear wall 158 opposite the front wall 156, an upper wall 160, and a lower wall 162 opposite the upper wall 160. The front wall 156 and the rear wall 158 are coupled to a flap body 164.

[0051] In one example, a first extension member of the plurality of extension members 128 forms a front wall 156, and a second extension member of the plurality of extension members 128 forms a rear wall 158. An upper wall 160 and a lower wall 162 are adjacent to the upper skin 102 and the lower skin 104, respectively. In one example, as viewed from the inboard end 124, at least one of the upper wall 160 and the lower wall 162 has a contour shape that matches a portion of a flap body 164, such as a portion of a contour shape of at least one of the upper skin 102 and the lower skin 104.

[0052] As viewed from the inboard end 124, the profile shape of each of the front wall 156, the rear wall 158, the upper wall 160, and the lower wall 162 defines the cross-sectional shape of the torque member 108. In one example, the profile shape of one or more of the front wall 156, the rear wall 158, the upper wall 160, and the lower wall 162 is planar. In one example, the profile shape of one or more of the front wall 156, the rear wall 158, the upper wall 160, and the lower wall 162 is curved.

[0053] Reference Figure 4 , the flap body 164 of the flap 100 is actuated or moved between the raised position and the lowered position by the torque member 108, and the torque member 108 extends through the opening 206 formed in the fuselage 202. The opening 206 is configured to achieve a full range of movement about the torque member 108 and the associated flap body 164 during operation. In one example, the flap actuator 260 includes a flap support mechanism 212 (also commonly referred to as a flap bracket mechanism), and a motorized actuator (not shown) operably coupled to the flap support structure 212. In one example, the inboard end 180 of the torque member 108 is coupled to the flap support mechanism 212.

[0054] Figure 4The flap 100 is shown generally in the raised position, wherein the torque member 108 extends through the opening 206 in the fuselage 202 and is coupled to the flap support mechanism 212. In one example, the torque member 108 is configured to rotate around the axis of rotation 184 or is configured to be rotated around the axis of rotation so that the flap body 164 pivots or rotates relative to the wing 214. Alternatively or additionally, in one example, the torque member 108 is configured to translate forward and backward along the path of travel 186 or is configured to be translated forward and backward along the path of travel so that the flap body 164 moves between the forward / raised position and the backward / lowered position. In one example, the path of travel 186 is arc-shaped, so the opening 206 is an elongated arc, to achieve the full range of movement of the flap 100 (the torque member 108 and the flap body 164 associated therewith) during operation. The rotation of the torque member 108 allows the flap body 164 to pivot around the axis of rotation 184 during the actuation of the flap 100. In one example, the axis of rotation 184 is a central longitudinal axis of the torque member 108 .

[0055] In one example, the torque member 108 also includes a mounting flange 182 located at the outboard end 178 of the torque member 108 and configured to be coupled to the flap support mechanism 212. In one example, the flap support mechanism 212 includes a bracket mechanism 262, which is also commonly referred to as a bracket beam. The bracket mechanism 262 is coupled to the inboard end 180 of the torque member 108 and transmits motion to the torque member 108 during actuation of the flap support mechanism 212. In one example, the bracket mechanism 262 includes one or more link members pivotally coupled to the mounting flange 182 to achieve rotational and translational motion of the torque member 108, wherein the instantaneous center of rotation of the torque member 108 changes along the travel path 186.

[0056] Reference Figure 5 In one example, the flap 100 includes an inboard flap fairing 190 coupled to the flap body 164 proximate the inboard end 124 of the flap body 164. During actuation of the flap 100, the inboard flap fairing 190 moves with the flap 100 relative to the fuselage 202. In one example, the flap 100 also includes a door 188 coupled to the torque member 108. The door 188 moves with the torque member 108 and is positioned relative to the fuselage 202 so that the door 188 covers the opening 206 ( Figure 4 at least a portion of the device.

[0057] Reference Figures 6 to 8 In one example, the upper skin 102 ( Figure 7 and Figure 8104 and / or the upper skin 102, 104 are permanently coupled to the spar 106. As examples, one or both of the upper skin 102 and the lower skin 104 may be connected to the spar 106 by various fasteners (not shown), the spar 106 may be co-cured with one or both of the upper skin 102 and / or the lower skin 104, the spar 106 may be structurally bonded (e.g., adhesively bonded) to one or both of the upper skin 102 and / or the lower skin 104, or a combination thereof.

[0058] Reference Figure 6 In one example, each of the spars 106 includes an upper spar cap 170, a lower spar cap 172 opposite the upper spar cap 170, and a spar web 174 extending between the upper spar cap 170 and the lower spar cap 172. The upper spar cap 170 is coupled to the upper skin 102, and the lower spar cap 172 is coupled to the lower skin 104. Each of the spars 106 has one of a variety of cross-sectional shapes defined by the relative configuration of the upper spar cap 170, the lower spar cap 172, and the spar web 174. In one example, at least one of the spars 106 has a constant cross-sectional shape along the longitudinal axis of the spar 106. In one example, at least one of the spars 106 has a varying or non-constant cross-sectional shape along the longitudinal axis of the spar 106.

[0059] In one example of the spar 106, one end of the spar web 174 is connected to one end of the upper spar cap 170, and the other end of the spar web 174 is connected to one end of the lower spar cap 172, and both the upper spar cap 170 and the lower spar cap 172 protrude from the same side of the spar web 174 (commonly referred to as being C-shaped or U-shaped in cross-section).

[0060] In one example of the spar 106, one end of the spar web 174 is connected to the middle portion of the upper spar cap 170 (e.g., located between the ends of the upper spar cap 170), and the other end of the spar web 174 is connected to the middle portion of the lower spar cap 172 (e.g., located between the ends of the lower spar cap 172), and both the upper spar cap 170 and the lower spar cap 172 protrude from both sides of the spar web 174 (commonly referred to as being I-shaped or H-shaped in cross section).

[0061] Reference Figure 7 and Figure 8 In one example, the flap body 164 is partially formed by the spar 106, and the torque member 108 is partially formed by the extension member 128. In one example, the spar 106 extends between the outboard end 126 of the flap body 164 and the inboard end 124 of the flap body 164 in the span direction. The spar 106 is a structural member or load-bearing element of the flap body 164. The extension member 128 extends between the outboard end 178 and the inboard end 180 of the torque member 108.

[0062] The spar 106 may be formed of any suitable structural material. In one example, the spar 106 is made of a metallic material. In one example, the spar 106 is made of a composite material (eg, a carbon fiber reinforced polymer).

[0063] In one example, at least one of the upper skin 102 and the lower skin 104 includes a skin main portion 152 and a skin extension 154 extending from the skin main portion 152. The flap body 164 is partially formed by the skin main portion 152, and the torque member 108 is partially formed by the skin extension 154.

[0064] In one example, the skin main portion 152 extends between the outboard end 126 and the inboard end 124 of the flap body 164 in the span direction and extends between the front end 112 and the rear end 116 of the flap body 164 in the chord direction. The skin extension portion 154 extends in the inboard direction from the inboard end 124 of the flap body 164. The skin extension portion 154 extends over (e.g., covers) the extension member 128 and is coupled to the extension member 128.

[0065] The skin main portion 152 and the skin extension portion 154 are integrally formed as a single component or piece, which forms the entirety of the upper skin 102 and / or the lower skin 104. The upper skin 102 and / or the lower skin 104 can be made of any suitable structural material. In one example, the upper skin 102 and / or the lower skin 104 are made of a metal material. In one example, the upper skin 102 and / or the lower skin 104 are made of a composite material (e.g., a carbon fiber reinforced polymer).

[0066] In one example, the torque member 108 is formed of two extension members 128, each extension member 128 is coupled to the inner rib 168 of the flap body 164. In one example, the torque member 108 is formed of three extension members 128, each extension member 128 is coupled to the inner rib 168 of the flap body 164. In one example, the torque member 108 is formed of two extension members 128 and at least one extension rib 176 ( Figure 7 In any of these examples, the torque member 108 can also be formed by a skin extension 154 of at least one of the upper skin 102 and / or the lower skin 104.

[0067] In one example, at least one of the extension members 128 is laterally offset relative to one of the spars 106. Figure 7As shown, each of the extension members 128 is laterally offset relative to an adjacent one of the spars 106. In one example, at least one of the extension members 128 is coaxially aligned with one of the spars 106. Figure 8 As shown, each of the extension members 128 is coaxially aligned with one of the spars 106 with which it is associated.

[0068] In one example, any one of the extension members 128 includes an upper extension cover, a lower extension cover relative to the upper extension cover, and an extension web extending between the upper extension cover and the lower extension cover. Each of the extension members 128 has one of various cross-sectional shapes (e.g., C-shape, I-shape, etc.) defined by the relative configuration of the upper extension cover, the lower extension cover, and the extension web. In one example, at least one of the extension members 128 has a constant cross-sectional shape along the longitudinal axis of the extension member 128. In one example, at least one of the extension members 128 has a variable or non-constant cross-sectional shape along the longitudinal axis of the extension member 128. In some examples, the cross-sectional shape of the extension member 128 is substantially matched with the cross-sectional shape of the spar 106 for forming the flap body 164. In one example, the skin extension portion 152 of at least one of the upper skin 102 and / or the lower skin 104 is coupled to the opposite ends of one or more (e.g., the upper extension cover and the lower extension cover) of the extension member 128.

[0069] Reference Figure 8 In one example, the flap body 164 also includes other structural elements. In one example, the flap body 164 also includes an additional spar 106 extending between the outboard end 126 and the inboard end 124 of the flap body 164. In one example, the flap body 164 also includes a plurality of outboard ribs 166 (also individually referred to as outboard ribs 166) extending between the upper skin 102 and the lower skin 104. In one example, the outboard ribs 166 extend between an adjacent pair of spars 106 in the chord direction.

[0070] Reference Figures 9 to 12 In one example, the plurality of spars 106 includes a front spar 110 located proximate to a front end 112 of the flap body 164 (e.g., at or near the front end 112). In one example, the plurality of spars 106 also includes a rear spar 114 located proximate to a rear end 116 of the flap 100. In one example, the plurality of spars 106 also includes an intermediate spar 118 located between the front spar 110 and the rear spar 114. Figures 9 to 12 In FIG. 1 , the upper skin 102 is not shown.

[0071] Reference Fig. 9In one example, the flap 100 includes a front spar 110 and a rear spar 114. In one example, the front spar 110 and the rear spar 114 extend between the outboard end 126 and the inboard end 124 of the flap body 164. In one example, the inboard rib 168 extends between and is coupled to the front spar 110 and the rear spar 114. In one example, the inboard rib 168 is also located along the chord direction of the upper skin 102 ( Fig. 9 The flap body 164 extends between the front spar 110 and the rear spar 114 and is coupled to the upper skin 102 and the lower skin 104. The flap body 164 is partially formed by the front spar 110, the rear spar 114 and the inner rib 168. When viewed from the inner end 124 of the flap body 164, each of the plurality of extension members 128 is located between the front spar 110 and the rear spar 114.

[0072] In one example, the plurality of extension members 128 includes a first extension member 144 (e.g., a first extension member of the extension members 128) coupled to the inboard rib 168. In one example, the plurality of extension members 128 includes a second extension member 146 (e.g., a second extension member of the extension members 128) coupled to the inboard rib 168. The torque member 108 includes (is formed in part by) the first extension member 144 and the second extension member 146. The first extension member 144 and the second extension member 146 extend between the outboard end 178 and the inboard end 180 of the torque member 108.

[0073] In one example, first extension member 144 and second extension member 146 are laterally spaced apart from each other. In one example, first extension member 144 and second extension member 146 are parallel to each other. In one example, first extension member 144 is laterally spaced apart from front spar 110 toward rear spar 114. In one example, second extension member 146 is laterally spaced apart from rear spar 114 toward front spar 110.

[0074] Reference Fig.10 In one example, the flap 100 includes a front spar 110, an intermediate spar 118, and a rear spar 114. In one example, the front spar 110, the intermediate spar 118, and the rear spar 114 extend between the outboard end 126 and the inboard end 124 of the flap body 164. In one example, the inboard rib 168 extends between the front spar 110 and the rear spar 114 and is coupled to the front spar 110, the intermediate spar 118, and the rear spar 114. The flap body 164 is partially formed by the front spar 110, the intermediate spar 118, the rear spar 114, and the inboard rib 168. The torque member 108 is partially formed by the first extension member 144 and the second extension member 146.

[0075] In one example, the first extension member 144 is located between the front spar 110 and the intermediate spar 118 when viewed from the inboard end 124 of the flap body 164. In one example, the second extension member 146 is located between the rear spar 114 and the intermediate spar 118 when viewed from the inboard end 124 of the flap body 164.

[0076] Reference Fig.11 In one example, the flap 100 includes a front spar 110 and a rear spar 114. In one example, the front spar 110 and the rear spar 114 extend between the outboard end 126 and the inboard end 124 of the flap body 164. In one example, the inboard rib extends between and is coupled to the front spar 110 and the rear spar 114. The flap body 164 is partially formed by the front spar 110, the rear spar 114, and the inboard rib 168.

[0077] In one example, the plurality of extension members 128 include a third extension member 148 (e.g., a third extension member of the extension members 128) coupled to the inner rib 168. In one example, the third extension member 148 is located between the first extension member 144 and the second extension member 146 when viewed from the inner end 124 of the flap body 164. The torque member 108 includes the first extension member 144, the second extension member 146, and the third extension member 148 (partially formed by the first extension member 144, the second extension member 146, and the third extension member 148). The first extension member 144, the second extension member 146, and the third extension member 148 extend between the outboard end 178 and the inboard end 180 of the torque member 108.

[0078] Reference Fig.12 In one example, the flap 100 includes a front spar 110 and a rear spar 114. In one example, the front spar 110 and the rear spar 114 extend between the outboard end 126 and the inboard end 124 of the flap body 164. In one example, the inboard rib 168 extends between and is coupled to the front spar 110 and the rear spar 114. The flap body 164 is partially formed by the front spar 110, the rear spar 114, and the inboard rib 168.

[0079] In one example, the torque member 108 includes (is partially formed by) an extension rib 176 that extends between the first extension member 144 and the second extension member 146. In one example, the extension rib 176 is located at any one of a variety of locations between the outboard end 178 and the inboard end 180 of the torque member 108. The extension rib 176 is configured to redistribute loads between the first extension member 144 and the second extension member 146 during actuation of the flap 100. In one example, the extension rib 176 is located at the upper skin 102 ( Fig.12 ) and the lower skin 104 and / or is connected to the upper skin 102 (not shown) Fig.12 ) and / or the lower skin 104.

[0080] In one example, the torque member 108 includes a plurality of extended ribs 176 such as Fig.12 As shown. In one example, the extension ribs 176 are equally spaced along the torque member 108 between the outboard end 178 and the inboard end 180 of the torque member 108. The number of extension ribs 176 can vary depending on, for example, the loads applied to the torque member 108, the fault protection requirements of the torque member 108, and the desired stiffness of the torque member 108. In one example, one of the extension ribs 176 is located proximate to the inboard end 180 of the torque member 108. In one example, at least one of the extension ribs 176 is located between the outboard end 178 and the inboard end 180 of the torque member 108, for example, between one of the extension ribs 176 located at the inboard end 180 of the torque member 108 and the inboard rib 168.

[0081] Reference Fig.14 In one example, the flap 100 includes a front spar 110 and a rear spar 114. The flap body 164 is partially formed by the front spar main portion 120 and the rear spar 114. The torque member 108 is partially formed by the front spar extension 122. In one example, the front spar main portion 120 and the rear spar 114 extend between the inboard end 124 and the outboard end 126 of the flap body 164, and the front spar extension 122 extends between the outboard end 178 and the inboard end 180 of the torque member 108.

[0082] Although Fig.11 and Fig.12 Not shown, but in other examples, the flap body 164 may also include additional spars 106 (eg, the intermediate spars 118 ).

[0083] exist Figures 9 to 12 In the example shown, the first extension member 144 forms a front wall 156 ( Figure 3), and the second extension member 146 forms a rear wall 158 ( Figure 3 ). Figures 9 to 12 In the example shown, the skin extension 154 ( Figures 9 to 12 ) (also referred to as an upper skin extension) forms an upper wall 160 ( Figure 3 ), and the skin extension 154 (also referred to as the lower skin extension) of the lower skin 104 forms the lower wall 162 of the torque member 108. The skin main portion 152 (also referred to as the upper skin main portion) of the upper skin 102 forms the upper skin panel of the flap body 164, and the skin main portion 152 (also referred to as the lower skin main portion) of the lower skin 104 forms the lower skin panel of the flap body 164.

[0084] Reference Fig.13 In one example, one or both of the upper skin 102 and / or the lower skin 104 only partially forms the flap body 164. In one example, one or both of the upper skin 102 and / or the lower skin 104 extend between the outboard end 126 and the inboard end 124 of the flap body 164 and terminate at the inboard end 124 of the flap body 164.

[0085] In one example, the flap 100 also includes an upper skin extension member 194 in place of an upper skin extension portion. In one example, the upper skin extension member 194 extends between the inboard end 180 and the outboard end 178 of the torque member 108 and is coupled to the extension members 128 (e.g., the first extension member 144 and the second extension member 146). The upper skin extension member 194 is adjacent to the upper skin 102. The torque member 108 includes the upper skin extension member 194 (is partially formed by the upper skin extension member 194).

[0086] In one example, the flap 100 also includes a lower skin extension member 196 in place of the lower skin extension portion. In one example, the lower skin extension member 196 extends between the inboard end 180 and the outboard end 178 of the torque member 108 and is coupled to the extension member 128 (e.g., the first extension member 144 and the second extension member 146). The lower skin extension member 196 is adjacent to the lower skin 104. The torque member 108 is partially formed by the lower skin extension member 196.

[0087] In the illustrated embodiment, the skin extensions 154, upper skin extension members 194, and lower skin extension members 196 of the upper skin 102 and lower skin 104 extend all the way to and terminate at the inboard end 180 of the torque member 108. In other examples, one or more of the skin extensions 154, upper skin extension members 194, and / or lower skin extension members 196 of the upper skin 102 and lower skin 104 terminate before the inboard end 180 of the torque member 108. In one example, the skin extensions 154, upper skin extension members 194, and / or lower skin extension members 196 of the upper skin 102 and lower skin 104 extend at least to the point where the torque member 108 passes through the opening 206 ( Figure 4 The point at which the fuselage 202 is entered.

[0088] In certain aerospace implementations, failsafe measures may be beneficial to ensure continued safe flight and landing. One example of a failsafe measure is a redundant load path that is not used until a primary load path fails. Another example of a failsafe measure is having two or more load paths where failure of any one load path redistributes the load to another load path, each load path being able to react to the entire load. Another example of a failsafe measure is having sufficient spare load carrying capacity in each structural member defining a given load path, so that the load path is able to react to the entire load after a structural member fails, is damaged, or otherwise compromised.

[0089] In some examples, such as Fig.11 In the illustrative example shown, the torque member 108 of the disclosed flap 100 includes a failsafe configuration. Fig.11 ), several pairs of two adjacent extension members 128 can form redundant load paths. In one example, the first extension member 144 and the third extension member 148 define the first load path, the third extension member 148 and the second extension member 146 define the second load path, and the first extension member 144 and the second extension member 146 define the third load path. In this example, each of the load paths can react to the entire load applied to the flap 100, and a load path failure (e.g., caused by damage to an extension member 128) can be redistributed to another load path. In one example, one of the redundant load paths is loaded, and the other of the redundant load paths is unloaded. Once the loaded load path fails, the load is redistributed to the unloaded load path. In one example, each of the redundant load paths is loaded, and any one of the loaded load paths can react to the entire load when another fails.

[0090] In some examples, such as Fig. 9 , Fig.10 and Fig.12 In the illustrative example shown, the torque member 108 of the disclosed flap 100 may include a failsafe configuration. In one example, each of the extension members 128 has a backup load capacity that exceeds the entire load applied to the flap 100. In one example ( Fig. 9 , Fig.10 and Fig.12 ), first extension member 144 and second extension member 146 define a load path, and each of first extension member 144 and second extension member 146 has a spare load-bearing capacity exceeding the entire load applied to flap 100.

[0091] Reference Fig.14 , an example method 1000 is also disclosed. In one example, the method 1000 is used to form a flap 100. In one example, the method 1000 includes a step of forming a torque member 108 with a plurality of extension members 128 coupled to a flap body 164 to form the flap 100 (block 1002). The flap body 164 is configured to be movably coupled to a wing 214 of an aircraft 200. The torque member 108 is configured to be operably coupled to a flap actuator 260 of the aircraft 200.

[0092] In one example, the method 1000 includes the step of providing the lower skin 104, the upper skin 102, and the plurality of spars 106 (block 1004). As used herein, the term "providing" does not require any specific delivery or receipt of the provided items. Rather, the term "provided" is used to refer to items that are available for use or otherwise in a ready state or condition.

[0093] In one example, the method 1000 includes a step (block 1006) of joining together the lower skin 104, the upper skin 102, and the plurality of spars 106 to partially form the flap body 164. The lower skin 104, the upper skin 102, and the plurality of spars 106 may be joined together using various methods or operations, including but not limited to fastening, co-curing, bonding, or a combination thereof.

[0094] In one example, the method 1000 includes coupling an inboard rib 168 to a plurality of spars 106 to partially form a flap body 164 (block 1008 ). In one example, the inboard rib 168 extends between an adjacent pair of spars 106 at the inboard end 124 of the flap body 164 .

[0095] In one example, the method 1000 includes the step of coupling a plurality of extension members 128 to the inboard end 124 of the flap body 164 to partially form the torque member 108 (block 1010 ). In one example, the plurality of extension members 128 are coupled to the inboard rib 168 .

[0096] In one example, the method 1000 includes a step of partially forming the flap body 164 with the skin main portion 152 of the upper skin 102 (block 1012) and a step of partially forming the torque member 108 with the skin extension portion 154 of the upper skin 102 (block 1014). Alternatively, the method 1000 includes a step of partially forming the flap body 164 with the upper skin 102 (block 1016) and a step of partially forming the torque member 108 with the upper skin extension member 194 (block 1018).

[0097] In one example, the method 1000 includes a step of partially forming the flap body 164 with the skin main portion 152 of the lower skin 104 (block 1020) and a step of partially forming the torque member 108 with the skin extension portion 154 of the lower skin 104 (block 1022). Alternatively, the method 1000 includes a step of partially forming the flap body 164 with the lower skin 104 (block 1024) and a step of partially forming the torque member 108 with the lower skin extension member 196 (block 1026).

[0098] In one example, the method 1000 is also used to form the wing 214 of the aircraft 200. In one example, the method 1000 includes a step (block 1028) of movably coupling the flap body 164 of the flap 100 to the wing body 258 of the wing 214 at the trailing edge 242 of the wing 214. According to the method 1000, the flap 100 can be coupled to the wing 214 during the manufacture of the wing 214. Alternatively, according to the method 1000, the conventional inboard flap of the aircraft 200 can be replaced with the flap 100, such as during the maintenance or repair of the aircraft 200.

[0099] In one example, the method 1000 is also used to form an aircraft 200. In one example, the method 1000 includes a step of coupling the wing 214 to the fuselage 202 of the aircraft 200 (block 1030). In one example, the method 1000 includes a step of operably coupling the inboard end 180 of the torque member 108 to the flap actuator 260 (block 1032). In one example, the torque member 108 extends into the fuselage 202 through the opening 206 in the fuselage 202.

[0100] In one example, method 1000 is also used to operate flap 100. In one example, method 1000 includes a step (frame 1034) of actuating flap 100 between an ascending position and a descending position. In one example, flap actuator 260 pivots and / or translates flap body 164 of flap 100 relative to wing 214 via torque member 108.

[0101] The examples of flap 100 and method 1000 disclosed herein may be used in a variety of potential applications, particularly in the transportation industry, including, for example, aerospace applications. Figure 1 and Fig.15 Examples of flap 100 and method 1000 may be used in aircraft manufacturing and service method 1100 (eg, Fig.15 ) and aircraft 200 (as shown in the flowchart of Figure 1 The disclosed example aircraft applications may include the formation of the flap 100 and the use of the flap 100 as a flight control surface of an aircraft 200.

[0102] like Fig.15 As shown, during pre-production, the illustrative method 1100 may include the specification and design (block 1102) and material procurement (block 1104) of the aircraft 200. During the production of the aircraft 200, the component and subassembly manufacturing (block 1106) and system integration (block 1108) of the aircraft 200 may be included. Thereafter, the aircraft 200 may undergo certification and delivery (block 1110) to be put into service (block 1112). The disclosed flap 100 and method 1000 may form part of the component and subassembly manufacturing (block 1106) and / or system integration (block 1108). Routine maintenance and repair (block 1114) may include modification, reconfiguration, refurbishment, etc. of one or more systems of the aircraft 200, such as repairing and / or replacing the inboard flap.

[0103] Each process of the illustrative method may be performed or executed by a system integrator, a third party, and / or an operator (e.g., a customer). For the purpose of this specification, a system integrator may include, but is not limited to, any number of aircraft manufacturers and main system subcontractors; a third party may include, but is not limited to, any number of vendors, subcontractors, and suppliers; an operator may be an airline, a leasing company, a military entity, a service organization, etc.

[0104] exist Fig.15 During any one or more stages of the manufacturing and maintenance method 1100 shown in the flowchart shown, the examples of the flap 100 and method 1000 shown and described herein can be used. For example, the components and subassemblies (e.g., flap 100 or wing 214) corresponding to the component or subassembly manufacturing (box 1106) can be produced or manufactured in a manner similar to the components or subassemblies produced when the aircraft 200 is put into service (box 1112). In addition, one or more examples of the flap 100, method 1000, or a combination thereof can be used during system integration (box 1108) and / or certification and delivery (box 1110). Similarly, one or more examples of the flap 100, method 1000, or a combination thereof can be utilized, for example, but not limited to, when the aircraft 200 is put into service (box 1112) and during maintenance and repair (box 1114).

[0105] Although an example of aerospace is shown, the principles disclosed herein may be applied to other industries, such as the automotive industry. Therefore, in addition to aircraft, the principles disclosed herein may be applicable to other vehicles (e.g., land vehicles, marine vessels, spacecraft, etc.).

[0106] Reference herein to an "example" means that one or more features, structures, elements, components, characteristics, and / or operating steps described in conjunction with the example are included in at least one embodiment and / or implementation of the subject matter according to the present disclosure. Therefore, the phrase "example" and similar language throughout the present disclosure may, but need not, refer to the same example. In addition, the subject matter characterizing any one example may, but need not, include the subject matter characterizing any other example.

[0107] As used herein, a system, device, structure, article, element, component, or hardware that is "configured to" perform a specific function is indeed able to perform the specific function without any changes, rather than being able to perform the specific function only after further modification. In other words, a system, device, structure, article, element, component, or hardware that is "configured to" perform a specific function is specifically selected, created, implemented, used, programmed, and / or designed to achieve the purpose of performing a specific function. As used herein, "configured to" means an existing characteristic of a system, device, structure, article, element, component, or hardware that enables a system, device, structure, article, element, component, or hardware to perform a specific function without further modification. For the purposes of this disclosure, a system, device, structure, article, element, component, or hardware that is described as "configured to" perform a specific function may additionally or alternatively be described as "suitable for" and / or "operable to" perform this function.

[0108] Unless otherwise indicated, the terms "first", "second", etc. are used herein only as labels and are not intended to impose any order, position, or hierarchical requirements on the various applications to which these terms refer. In addition, reference to a "second" item does not require or exclude the existence of lower-numbered items (e.g., "first" items) and / or higher-numbered items (e.g., "third" items).

[0109] As used herein, "connection" and similar terms refer to two or more elements being engaged, linked, fastened, connected, communicated or otherwise associated with another (e.g., mechanically, electrically, fluidically, optically, electromagnetically). In various examples, elements can be associated in a direct or indirect manner. As an example, element A can be directly associated with element B. As another example, element A can be indirectly associated with element B, for example, via another element C. It should be understood that not all associations between all disclosed elements must be shown. Therefore, there can also be connections other than those shown in the figure.

[0110] As used herein, the phrase "at least one" when used with a list of items means that different combinations of one or more of the listed items may be used, and only one of each item in the list may be required. For example, "at least one of item A, item B, and item C" may include, but is not limited to, item A, or item A and item B. This example may also include item A, item B, and item C, or item B and item C. In other examples, "at least one" may be, for example, but not limited to, two of item A, one of item B, and ten of item C; four of item B and seven of item C; and other suitable combinations.

[0111] exist Fig.14 and Fig.15 In the embodiment of the present invention, as described above, each box can represent an operation and / or a portion thereof, and the line connecting each box does not imply any particular order or subordination of the operation or its portion. Each box represented by a dotted line represents an alternative operation and / or its portion. The dotted line connecting each box (if any) represents an alternative subordination of an operation or its portion. It should be understood that not all subordination relationships between the various disclosed operations must be shown. Fig.14 and Fig.15 The attached disclosures describing the operations of the methods disclosed herein should not be construed herein as necessarily determining the order in which the operations are performed. On the contrary, although an illustrative order is shown, it should be understood that the order of the operations can be modified when appropriate. Therefore, the operations shown can be modified, added and / or omitted, and certain operations can be performed in different orders or simultaneously. In addition, it should be understood by those skilled in the art that not all described operating steps need to be performed.

[0112] This application is a continuation-in-part of U.S. patent application serial number 15 / 941,378 filed on March 30, 2018.

[0113] Although various embodiments and / or examples of the disclosed antenna, aerospace vehicle, and method have been shown and described, modifications may occur to those skilled in the art upon reading the specification. The present application includes such modifications and is limited only by the scope of the claims.

Claims

1. A flap (100) for a wing of an aircraft, the flap comprising: A flap body (164), the flap body comprising: Upper skin (102); a lower skin (104), the lower skin being opposite to the upper skin (102); and a plurality of spars (106) extending between the upper skin (102) and the lower skin (104); and a torque member (108) coupled to the flap body (164); and wherein a portion of the torque member (108) is adjacent to at least one of the upper skin (102) and the lower skin (104); Wherein, the flap body (164) further includes an inner end (124) and an outer end (126) opposite to the inner end (124); The torque member (108) includes a plurality of extension members (128); and Each extension member of the plurality of extension members (128) is coupled to the inboard end (124) of the flap body (164); Wherein: at least one of the upper skin (102) and the lower skin (104) includes a skin main portion (152) and a skin extension portion (154) extending from the skin main portion (152); The flap body (164) is partially formed by the skin main portion (152); and The torque member (108) is formed in part by the skin extension (154).

2. The flap (100) according to claim 1, wherein: The torque member (108) has a non-circular cross-sectional shape.

3. The flap (100) according to claim 1, wherein: Each extension member of the plurality of extension members (128) is parallel to an adjacent extension member of the plurality of extension members (128).

4. The flap (100) according to claim 1, wherein: The torque member (108) includes at least one of an upper skin extension member (194) adjacent to the upper skin (102) and a lower skin extension member (196) adjacent to the lower skin (104).

5. The flap (100) according to claim 1, wherein: The flap body (164) further includes an inboard rib (168) extending between an adjacent pair of spars among the plurality of spars (106) at the inboard end (124) of the flap body (164); and Each extension member of the plurality of extension members (128) is coupled to the inboard rib (168).

6. The flap (100) according to claim 5, wherein: The plurality of spars (106) include a front spar (110) and a rear spar (114); The inboard rib (168) extends between the front spar (110) and the rear spar (114); and The plurality of extension members (128) are located between the front spar (110) and the rear spar (114).

7. The flap (100) according to claim 6, wherein: The plurality of extension members (128) include: a first extension member (144) coupled to the inboard rib (168); and a second extension member (146) coupled to the inboard rib (168); and The first extension member (144) and the second extension member (146) are laterally spaced apart from each other.

8. The flap (100) according to claim 7, wherein: The first extension member (144) is laterally spaced from the front spar (110); and The second extension member (146) is laterally spaced from the rear spar (114).

9. The flap (100) according to claim 7, wherein: The plurality of spars (106) further includes an intermediate spar (118) located between the front spar (110) and the rear spar (114); The first extension member (144) is located between the front spar (110) and the intermediate spar (118); and The second extension member (146) is located between the rear spar (114) and the intermediate spar (118).

10. The flap (100) according to claim 7, wherein: The plurality of extension members (128) further includes a third extension member (148) coupled to the inner rib (168); and The third extension member (148) is located between the first extension member (144) and the second extension member (146).

11. The flap (100) according to claim 7, wherein: The torque member (108) also includes an extension rib (176) extending between the first extension member (144) and the second extension member (146).

12. A wing of an aircraft, the wing comprising: Wing body; as well as The flap according to any one of claims 1 to 11, The flap body is movably coupled to the wing body.

13. The wing according to claim 12, wherein: The torque member is configured to be coupled to a flap actuator of the aircraft.

14. A method for forming a flap (100) according to any one of claims 1 to 11, the method comprising: connecting an upper skin (102), a lower skin (104), and a plurality of spars (106) to partially form a flap body (164); as well as A plurality of extension members (128) are coupled to the flap body (164) to partially form a torque member (108), wherein: The flap body is configured to be movably coupled to a wing (214) of an aircraft (200); and The torque member (108) is configured to be coupled to a flap actuator (260) of the aircraft (200).

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