159 results about "Lower wing" patented technology

The invention discloses a folding wing structure of an unmanned aerial vehicle, which comprises a rotating shaft embedded in a vehicle body, wherein a lower wing elastic sheet and an upper wing elastic sheet are mounted in an inner cavity of the rotating shaft from bottom to top, a first locking block and a second locking block are respectively arranged at the free ends of the lower wing elastic sheet and the upper wing elastic sheet, the first locking block and the second locking block are respectively matched with a first notch and a second notch which are formed in the rotating shaft, the outer side of the rotating shaft is sequentially sleeved with a lower wing and an upper wing from bottom to top, the upper surface of the lower wing and the lower surface of the upper wing are each provided with a groove, the two grooves are oppositely formed to form a torsional spring groove, a torsional spring is arranged in the torsional spring groove, and the upper inner sides of the lower wingand the upper wing are provided with a first locking groove and a second locking groove correspondingly; and the outer side of the rotating shaft is further sleeved with a roller bearing, a baffle isinstalled at the top of the rotating shaft, and the roller bearing is located between the upper wing and the baffle. The processing cost of the unmanned aerial vehicle is reduced, the folding wing structure is insensitive to the structural size, and the folding wing structure can adapt to a more miniaturized barrel-shooting unmanned aerial vehicle.

A detachable multi-stage automotive fastener clip attaches a body panel to a chassis slot. The fastener clip includes a U-shaped upper clip having at least two wings laterally spaced apart. The wings include: a wing tip, a bent wing, an inclined plane. A flex point is formed on a lower wing portion operative to engage and detach with the chassis slot. A U-shaped lower clip removably attaches to the U-shaped upper clip. At least two walls are laterally spaced apart at an open wall end. A ramp, a shoulder and a retaining ledge are formed on the at least two walls away from the open wall end operative to engage the inclined plane. A base at a closed end opposite the open wall end is formed such that the base is formed between a lower wall portion from each of the at least two walls forming a U shape.

The invention discloses a variable-elongation sweepback wing scaling wing deformation device and a deformation method thereof, and relates to the technical field of deformation mechanism design of variant aircrafts, the aerodynamic configuration of a variable-elongation sweepback wing scaling wing is composed of a fuselage section, a sweepback fixed section and a telescopic section, the fuselage section is composed of a fuselage shell and an upper hatch cover, and the upper hatch cover is composed of an upper hatch cover and a lower hatch cover. The sweepback fixed section is composed of an upper wing surface shell and a lower wing surface shell, the telescopic section is an independent telescopic wing shell, the fuselage section and the shell of the sweepback wing fixed section are fixed through a sunk screw, and therefore it is guaranteed that the aerodynamic shape meets the aerodynamic design requirement; the linear guide rail is fixedly connected to the lower wing surface shell, and the telescopic wing can move along the linear guide rail; electric push rods are used for driving and are fixed in the fuselage, and inner rods of the electric push rods are connected with the telescopic wings, so that the telescopic wings are controlled to move along the linear guide rails; according to the method, the aerodynamic configuration of the scaled wing is segmented, so that the aerodynamic configuration and internal movement components of the scaled wing are mounted, and the extension length of the wing is changed by driving the telescopic wing to move along the linear guide rail through the electric push rod, so that the lift-drag ratio of the aircraft in the flying process is changed; the method can provide an implementation method for the equivalent scaling experiment of the deformable wing.

The utility model provides a cable guiding and anti-falling festoon balancing device under the condition of rotation of a chute tube of a ship loader, which comprises an annular track and a plurality of slide rail cars matched on the annular track in a rolling way, each slide rail car comprises two oppositely arranged pulley plates, a rolling shaft vertical to the pulley plates is fixedly arranged on the pulley plates, and the rolling shaft is connected with the annular track. Rollers are installed on the rolling shafts, the section of the annular rail is of an I-shaped structure, the rollers are arranged on the upper surface of a lower wing plate of the I-shaped structure in a rolling fit mode, a web plate is fixedly arranged between the two oppositely-arranged pulley plates, a sponge fixing plate is arranged below the web plate, and a sponge plate is installed on the sponge fixing plate. A U-shaped plate is installed below the sponge plate, and a plurality of clamping grooves arranged at intervals in the length direction of the sponge plate are formed in the lower surface of the sponge plate. Under the rotation working condition of the ship loader chute tube, the sliding rail vehicle and the annular rail are not prone to being jammed, disengaged and damaged, and the safety of the ship loader chute tube under the rotation working condition can be improved.

1. Name of the designed product: clip set (butterfly). 2. Use of the designed product: for clipping articles. 3. Design points of the designed product: in shape. 4. Picture or photo best indicating the design points: assembly state diagram. 5. Component 4 is the same as component 2, and component 5 is the same as component 3, and the views of component 4 and component 5 are omitted. 6. Other circumstances needing explanation: component 1 is a butterfly base, component 2 and component 4 are butterfly lower wings, and component 3 and component 5 are upper wings.

This invention relates to the field of plastic molding, and more particularly to a composite material molding die for a target aircraft fuselage. The die includes a mold base, with a lower wing mold fixedly mounted on one side of the upper end of the mold base. An upper wing mold is positioned above the lower wing mold. A servo push cylinder is fixedly mounted on the rear of the other side of the upper end of the mold base. A connecting frame is fixedly mounted on the output end of the servo push cylinder. A carrier sleeve is fixedly mounted on the end of the connecting frame. Two shell prisms are symmetrically slidably mounted inside the carrier sleeve, extending from the upper and lower ends of the carrier sleeve respectively. Arc-shaped shells are fixedly mounted on opposite ends of the two shell prisms. Arc-shaped wiping cloths are provided on opposite surfaces of the two arc-shaped shells. A return spring is provided between the opposite ends of the two shell prisms and the carrier sleeve. This invention reduces the labor intensity of workers, facilitates use, reduces dead angles for mold release agent wiping, and ensures effective demolding after molding.

The utility model discloses a double-sided puller and a zipper, and relates to the field of zippers. A double-sided pull head comprises a pull head body and a rope used for pulling the pull head body to slide. The puller body comprises an upper wing plate, a lower wing plate and a connecting column, wherein the upper wing plate and the lower wing plate are vertically arranged, and the connecting column is fixed between the upper wing plate and the lower wing plate and located at the front end of the puller body. The upper wing plate is provided with an upper side tunnel which is through in the front-back direction, the lower wing plate is provided with a lower side tunnel which is through in the front-back direction, the front end opening of the upper side tunnel and the front end opening of the lower side tunnel both extend to the front side space of the connecting column, and the upper side tunnel, the lower side tunnel and the front side space of the connecting column form a rope channel; the rope movably penetrates through the rope channel, the head end of the rope can penetrate through the rear port of the upper side tunnel to be exposed, the head end of the rope is provided with an upper blocking part, the tail end of the rope can penetrate through the rear port of the lower side tunnel to be exposed, and the tail end of the rope is provided with a lower blocking part. The problem that the rope is broken due to scraping at least can be solved.

The utility model provides a puller for an invisible zipper, which reduces contact stress between a flange and a zipper tape and is easy to pull upwards, and the top end of the flange is difficult to be clamped on the zipper tape. The slider for the invisible slide fastener is provided with a lower wing plate, a pair of left and right guide rails vertically arranged along the side edges of the lower wing plate in the left-right direction, left and right flanges extending from the upper ends of the pair of left and right guide rails in the direction of approaching each other, a guide column, and a front mounting column and a rear mounting column which protrude upwards from the guide column at intervals in the front-back direction, the front end portion of the flange is located forward of the front end portion of the guide rail, and the starting point of the front curve portion on the inner side of the flange is located rearward of the front end portion of the guide rail.

A winglet system is configured to be secured to a wing of an aircraft. The winglet system includes an upper blade, a lower blade, and a cover plate integrally formed with the upper blade and the lower blade. The cover plate covers an opening within a transition joint between the upper blade and the lower blade. The cover plate remains coupled to the upper blade if the lower blade is separated from the winglet system.

The invisible pull head comprises a pull head body, the pull head body comprises a lower wing plate, a side plate and an upper wing plate, a separation column is arranged on the lower wing plate, a pull piece is hinged to the top of the separation column, a Y-shaped channel is formed among the separation column, the lower wing plate, the side plate and the upper wing plate, a mounting hole is formed in the top of the separation column, and the mounting hole is higher than the upper wing plate. A cloth passing space is formed between the zipper pull and the upper side of the upper wing plate when the zipper pull is horizontally placed; the separation column is provided with a front convex part, and the front convex part is internally provided with a bow-shaped accommodating cavity and a bow-shaped elastic sheet; and the mounting hole is close to the front convex part, so that the mounting hole and the upper wing plate are staggered. On one hand, a cloth passing space is formed between the pull piece and the upper wing plate by lifting the mounting position of the pull piece; and on the other hand, the rotating shaft of the pull tab and the upper wing plate are staggered in a mode that the mounting hole deviates towards the front convex part, so that the rotating shaft of the pull tab is prevented from being propped against the cloth belt, and the movement of the invisible pull head is smoother.

The present application relates to the technical field of hydraulic engineering construction, and discloses a lifting appliance for underwater hoisting of flexible gabion, which comprises a frame body, wings on the top and bottom of the frame body, and a limiting throwing assembly on the frame body. The frame body is welded from a rectangular steel plate and a channel steel, and is matched with a limiting hoop and upper and lower wings, so that the overall rigidity is strong, the carrying capacity is prominent, the double adjustment mechanism of main steel wire rope hoisting and manual control angle of traction rope can be used to flexibly adjust the underwater posture of the lifting appliance, the frame body provides a stable operation platform during the gabion filling stage, additional binding and fixing are not needed, the stone filling speed is effectively improved, the deformation of the flexible gabion during the filling, hoisting and launching process can be effectively constrained through the cooperation of the frame body, bottom plate, side plate and extension plate, and the displacement of the gabion due to the influence of water flow can be avoided, so that the flexible gabion can be thrown into the required area.

A supersonic aircraft is disclosed herein. The supersonic aircraft comprises one or more fuselages, one or more wings, at least one wing-mounted engine, at least one inlet mounted on the upper surface of or above the wing, an upper wing surface propulsion system fairing, and a lower wing surface propulsion system fairing or lower wing surface modification to account for the presence of the engine.

The bucket rod comprises a bucket rod body, a front support is arranged at the front end of the bucket rod body, a rear support is arranged at the rear end of the bucket rod body, and a connecting structure is arranged in the bucket rod body. The bucket rod body comprises an upper wing plate, a lower wing plate, a left web plate and a right web plate, the connecting structure comprises a center body and a plurality of peripheral rib plates, the center body is fixedly connected among the peripheral rib plates, the left end faces of the center body and the peripheral rib plates are fixedly connected with the left web plate, and the right end faces of the peripheral rib plates are fixedly connected with the right web plate. The right end face of the center body and the right end face of the peripheral rib plates are fixedly connected with the right web, and the ends, away from the center body, of the peripheral rib plates are fixedly connected with the upper wing plate, the lower wing plate and the rear support correspondingly. The bucket rod is reasonable in structural design, the overall rigidity and strength level of the bucket rod are obviously improved, and the force flow transmission path of the upper lug plate, the rear support and the lower lug plate hinged hole of the bucket rod is greatly optimized.

The utility model discloses a walking mechanism for R-VR-R space station experience, which is mounted on an annular track at the top in a cabin of a space station environment experience area, the lower part of the annular track is connected with a suspension mechanism, and the cross section of the track is I-shaped; the walking mechanism comprises a walking trolley frame which is arranged on the track and can walk along the track so that an experiencer can experience space floating walking in the space station environment experience area. The driving motor is mounted on one side of the traveling trolley frame; the driving walking mechanism is mounted on a frame of the traveling trolley, is positioned above a lower wing plate of the track and is in transmission connection with an output shaft of a driving motor so as to enable the traveling trolley to walk along the track; wherein the R-VR-R refers to the process from reality to virtual reality and then to reality. The walking mechanism for R-VR-R space station experience enables people to experience floating and walking in a space station floating simulation environment.

The utility model relates to the technical field of automobile parts, disclose a quick installation structure of automobile exhaust system heat shield, including upper cover body and lower cover body, the outside of upper cover body is provided with installation mechanism, the outside of upper cover body is provided with heat abstractor, the outside of upper cover body is provided with reinforcing mechanism, the outside of upper cover body is provided with connecting mechanism, the installation mechanism includes upper wing board, the outer wall fixed connection in the left side of upper cover body of upper wing board, the left side fixed connection of lower cover body has lower wing board, the bottom fixed connection of upper wing board has two fixed blocks, the front and back of two fixed blocks all are fixedly connected with elastic gasket. In the utility model, the heat shield is installed through the fixed block of upper wing board and is engaged with lower wing board, is inserted into the plug pin fixed from the embedded entry to the through hole inside, the plug pin tail connects the limiting ring and the supplementary pin, and the plug pin is prevented from popping out by abutting against, has good steady attribute, and the convenient installation and replacement are facilitated.

The application discloses a kind of single-box three-chamber cross-section girder bridge shear lag effect analysis method, belong to bridge construction control technical field.The method includes the following steps: S1. with quadratic parabola function to build shear lag warping displacement function, select the coordinate at the location of half of box girder section, i.e. the wing plate longitudinal displacement function of single-box three-chamber thin-walled box girder considering shear lag effect is obtained;S2. calculate the normal strain and shear strain of upper and lower wing plate and web of thin-walled box girder;S3. calculate the strain energy of upper and lower wing plate and web of thin-walled box girder;S4. calculate the total potential energy of single-box three-chamber girder system;S5. according to the principle of minimum potential energy, simplification is carried out using the method of partial integration, and the control differential equation set and boundary conditions of single-box three-chamber thin-walled box girder considering shear lag effect are obtained.The application discloses a kind of single-box three-chamber cross-section girder bridge shear lag effect analysis method, and the prediction result of main girder stress and deformation is more in line with actual situation, improves the accuracy of single-box three-chamber cross-section girder bridge construction process, and higher safety.

AIRCRAFT ASSEMBLY COMPRISING MEANS FOR ATTACHING A WING TO AN ENGINE PITCH The invention relates to an aircraft assembly (1) comprising an engine pylon (106) with side panels (208a-b) and upper (204) and lower (206) spars, an additional fitting (104c) attached to a wing structure (104a), starboard (252a) and port (252b) clevises attached to the structure (104a) and hinged to the associated side panel (208a-b), a forward connecting rod (254) mounted and hinged between the upper spar (204) and the additional fitting (104c), a rear connecting rod (256) mounted and hinged between the lower spar (206) and the structure (104a), and a lug with an axis parallel to a vertical direction (Z) and having an end A proximal end is integral with the upper spar (204), and a distal end is mounted in a window of the additional fitting (104c) via a linear annular connection. With such an assembly, the force transfer paths are multiplied.Fig. 2.

The utility model provides an orthodontic bracket which comprises a bottom plate, a fixing block is arranged on the bottom plate, the fixing block comprises an upper wing and a lower wing, a sliding groove is formed in the top surface of the upper wing in a penetrating mode, a lock cover is connected in the sliding groove in a sliding mode, a first groove is formed in the sliding groove, and the first groove is formed in the vertical inner wall of the side, close to the bottom plate, in the sliding groove. A through hole is formed in the position, corresponding to the first groove, of the lock cover, a shaft wire is arranged in the through hole, one end of the shaft wire is located in the first groove, a limiting protruding block is arranged on the vertical inner wall of one side of the first groove and divides the first groove into two symmetrical containing grooves, and the shaft wire is made of deformable materials. The first groove with the limiting bump in the sliding chute is matched with the deformable shaft wire, so that the shaft wire is adjusted between the two placing grooves and is blocked and fixed by the limiting bump when the lock cover is opened and closed, stress concentration of a traditional sliding rail is avoided, the risk that the lock cover falls off is reduced, and stable transmission and effect of correction force are guaranteed.

The present invention is a zipper (1) having left and right zipper tapes (10), at least one slider (20), and a stopper (30) for the slider (20) to abut against, the stopper (30) being fixed across the left and right zipper tapes (11) and having a shape in which a portion of the stopper (30) can be inserted between the upper wing plate (22) and the lower wing plate (23) of the slider (20), the interval in the tape width direction between the left and right zipper teeth (13) in a state in which the left and right zipper tapes (10) are separated is defined as a tooth interval (A), the maximum value of the dimension in the tape width direction of the connecting column (24) of the slider (20) is defined as a column maximum width (B), and the tooth interval (A) is a size of 100% or more and 150% or less of the column maximum width (B). Thus, when the slider (20) is caused to slide toward the stopper (30), it is difficult for the zipper teeth (13) to fall over in the vicinity of the stopper (30), and it is possible to suppress the zipper teeth (13) from being caught in the slider (20).

A slider for a slide fastener includes a slider body (11) and two pullers (20, 21) pivotally attached to the slider body (11). The slider body (11) forms an upper wing (12), a lower wing (13), a connecting post (14) connecting the upper and lower wings, and side flanges (15). The side flanges protrude from side edges of the upper and lower wings towards a geometrical mid-plane (P) that lies between the wings (12, 13), so as to form a Y-shaped channel (19) between the upper and lower wings. The upper wing (12) and the lower wing (13) have respective opposite outer surfaces (23, 24) which are substantially flat, and are symmetrical with respect to the geometrical mid-plane (P). At least one locking protrusion (30) protrudes inwardly into the Y-shaped channel (19) from at least one of the side flanges (15) of the slider body (11).

The present application relates to the technical field of aircraft design, and particularly relates to a wide-speed-range aircraft based on a variable high-pressure capture wing shape and a control method thereof, which comprises a fuselage, an upper wing surface, a lower wing surface, a foldable canard, a variable high-pressure capture wing and a control system. The variable high-pressure capture wing is arranged above the fuselage and the upper wing surface, and is used for switching between a subsonic forward-swept configuration and a supersonic backward-swept configuration according to a flight speed range; the foldable canard is arranged at a leading edge of the wing surface, and is used for unfolding in a subsonic stage and folding to be attached to the lower wing surface in a supersonic stage; and the control system determines a current stage according to flight state parameters, and cooperatively drives the high-pressure capture wing and the canard to perform a configuration switching action. The present application realizes adaptive matching of an aerodynamic shape and a flight speed range through variable design.

The utility model discloses an adjustable assembly joint of an H-shaped steel beam column and a support, which comprises an H-shaped steel component serving as a steel beam column, a support piece and a connecting piece for connecting the H-shaped steel component and the support piece, and the connecting piece comprises a third connecting plate in bolted connection with a web of the H-shaped steel component; a first connecting plate parallel to upper and lower wing plates of the H-shaped steel component is vertically fixed in the middle of the outer side of the third connecting plate; an arc-shaped edge is arranged on the outer side of the first connecting plate, a connecting hole is formed in the circle center area of the arc-shaped edge, and the supporting piece is in bolted connection with the first connecting plate through the connecting hole. The connecting piece solves the problems that an existing connecting piece is welded to an H-shaped steel component, consequently, the connecting piece protrudes out of the section of the steel component, transportation is inconvenient, and follow-up installation accuracy is affected due to the fact that the connecting piece is prone to collision in the transportation process.

The present invention provides a zipper pull. The zipper pull (1) of the present invention has a zipper pull body (10) having an upper wing plate (20) and a lower wing plate (30). A pair of groove portions (50, 60) are provided on the inner surface of the upper wing plate (20) and / or the lower wing plate (30). In a cross-sectional view of the zipper pull body (10), with the outermost position in the zipper pull width direction of the outer periphery of the connecting post (40) defined as the outermost position (41), the inner groove side edge portion (52a) of each groove portion (50, 60) is positioned inside the zipper pull width direction than the outermost position (41), and the outer groove side edge portion (52b) of each groove portion (50, 60) is positioned outside the zipper pull width direction than the outermost position (41). Therefore, even with repeated sliding operations, it is not easy to cause scraping of the zipper teeth caused by the inner surface of the zipper pull body (10).

A giant airliner structure, comprising a fuselage and at least two upper and lower layers of wings arranged on two sides of the fuselage, wherein a rudder (8) is provided between the adjacent upper and lower wings.

The utility model relates to bridge deck clamp technical field, especially shrinkable bridge deck clamp fixed structure, include: two channel steels, all are provided with mounting hole, and the mounting hole of two channel steels is installed with the pin shaft, connecting rod, place in the clearance of two channel steels, and connecting rod is connected with the channel steel rotation through the pin shaft of wearing, sliding block, place in the upper end of channel steel, and the one end rotation of sliding block and connecting rod is away from the pin shaft, nut, install in the edge clearance of two channel steels, main keel, lower wing blade and the wedge surface on sliding block are connected, and along the wedge surface downward movement and promote the separation of sliding block to both sides, clamping block, fix in the one side of sliding block close to main keel, and clamping block moves with sliding block, connecting steel sheet, adhere to the one side of sliding block away from the channel steel, and the hole of connecting steel sheet is provided with the hole of adapting with sliding block bolt hole, screw rod, pass through the bolt hole of connecting steel sheet and sliding block, and with nut screw connection: through the utility model improves the convenience of dismounting.

A kind of steel bridge distortion fatigue carbon fiber cloth and multi-limb angle steel composite reinforcing structure and process, vertical steel plate beam web is arranged between upper wing plate and lower wing plate, vertical stiffening rib is arranged between steel plate beam web and wing plate, horizontal node plate is vertically arranged in the height direction of steel plate beam web, vertical stiffening rib vertically passes through horizontal node plate, and horizontal node plate web gap area and vertical stiffening rib web gap area are reinforced using carbon fiber reinforced resin base and multi-limb angle steel composite structure;When reinforcing using the reinforcing process, before the strength of composite structure glue layer is not consolidated to form, auxiliary device needs to be fixed, after removing auxiliary reinforcing device, carbon fiber cloth is pasted on the surface of angle steel to form composite reinforcing structure layer.The reinforcing structure is suitable for 50-100mm long distortion fatigue crack reinforcement, can effectively improve the stress performance of web gap, improve the ability of inhibiting detail distortion fatigue crack initiation and expansion, has the advantages of convenient construction, low cost and excellent performance.

This application relates to the field of vehicle technology. The present invention provides a riding vehicle, comprising: a power system including a power source providing power; a walking system including wheels that can be driven by the power system; a frame supporting the power system; a housing assembly housing the frame and the power system; and a control system for controlling the movement of the riding vehicle. The riding vehicle further comprises: two winglets respectively connected to both sides of the vehicle body, each winglet including an upper wing and a lower wing. The upper wing is connected to both sides of the vehicle body and extends outward relative to the vehicle body, while the lower wing is connected to both the upper wing and the vehicle body. The upper wing includes a windward portion, the upper end of which has a first windward surface, at least partially being a curved surface concave inward towards the windward portion. This application provides a riding vehicle that effectively prevents the front wheel from lifting off during high-speed travel by providing winglets, and the winglets do not excessively increase wind resistance.

The present application relates to a kind of box beam / column's assembly welding method and assembly welding structure, the method is: after main body workpiece is assembled together, concentrate on the welding of workpiece, box shape assembly: lower wing plate is fixed as bottom plate;Install baffle on lower wing plate;Assemble left web plate and right web plate;Assemble upper wing plate;Box shape welding: welding machine enters from the welding hole of upper wing plate, and the welding of each baffle and left, right web plate is carried out electric slag welding;Component is turned over 90 degrees, and welding machine enters from the welding opening of web plate side, and the welding of each baffle and upper, lower wing plate is carried out electric slag welding;Finally, the welding of four longitudinal welds of box shape outside;The structure is: baffle all is electric slag welding weld around;Upper wing plate is provided with welding hole corresponding to first weld, and first weld is continued to the surface of upper wing plate welding hole from lower wing plate;Left web plate / right web plate two sides are provided with welding opening corresponding to second weld, and second weld is connected with the longitudinal weld of left web plate / right web plate two sides.

The application provides a rocket sub-stage wing parachute recovery attitude fault-tolerant control method, so as to compensate for the interference torque caused by the actuator failure and unknown disturbance, realize attitude fault-tolerant control, construct a combination body actuator failure model based on a wing parachute-sub-stage combination body kinematics model; a sliding mode disturbance observer is designed to estimate the lumped interference torque caused by the actuator failure and unknown disturbance; a finite time preset performance backstepping sliding mode attitude fault-tolerant controller is designed based on preset performance theory and backstepping sliding mode control. The application estimates the lumped interference torque by using the sliding mode disturbance observer, combines preset performance control and backstepping sliding mode control, designs a finite time attitude fault-tolerant controller, and realizes accurate control of the attitude of the wing parachute-sub-stage combination body under the influence of the actuator failure and uncertain disturbance.

The present disclosure relates to assembly line fabrication and assembly of aircraft wings. Systems and methods for assembling a wing are provided. The method includes suspending an upper wing panel of an aircraft below a shuttle, translating a rib into position, and placing the rib in contact with the upper wing panel, and then securing the rib to the upper wing panel while the upper wing panel is suspended. Some methods include installing a rib and spar to the upper wing panel while the upper wing panel is suspended, and joining a lower wing panel to the rib and spar. Some methods involve joining a rib to a spar (e.g., in whole or in part) to create a support structure, and then securing the support structure to the upper wing panel. The system includes a shuttle to suspend the upper wing panel, and a cart including a support to hold the rib, a chassis to translate the rib into position below the upper wing panel, and a lifting device to lift the rib into contact with the upper wing panel.