996 results about "Upper wing" patented technology

Link for a wristwatch, characterized in that it comprises a central core connecting a lower wing and an upper wing.

A robot mechanism adopts a dry cleaning method to clean the surface of live-line insulators without: using water and can perform cleaning and inspection of the surface of the live-line insulators while automatically moving along an insulator string. The robot mechanism includes a main unit having upper and lower wing frames connected with each other by a connecting bracket to surround the insulator string, a cleaning unit disposed between the upper and lower wing frames and including a base frame to perform dry cleaning with a rotational brush and a CM guide, a lift unit including a clamp and a ball-bearing screw to move the main unit up or down, and an inspection unit to electrically inspect the insulators; and a coupling unit to couple a pair of the main units to allow the pair of main units to move along a tension insulator string or a suspension insulator string.

A tiltrotor aircraft includes a fuselage; a wing member having a first rib, a second rib, a first spar, second spar; and an upper wing skin; an engine disposed at a fixed location relative to the wing member; and a proprotor having a spindle gearbox, rotor mast, and a plurality of rotor blades drivable in rotation about the rotor mast, the spindle gearbox being rotatable about a conversion axis. The spindle gearbox is located above the upper wing skin of the wing member.

A fixation device for reduction and fixation of fractures of the talus bone of the foot includes a thin titanium alloy plate having a lower wing configured for attachment to the lateral aspect of the talus and an upper wing configured for attachment to the dorsal aspect of the talus. The plate includes a substantially perpendicular or right angle bend between the lower and upper wings. In one embodiment, each wing includes three screw holes arranged in a generally triangular pattern. Two holes on each plate are situated in tabs and the center of the plate has a reduced width so that the plate presents a minimal profile. One of the tabs on the upper wing is bent away from the lower wing at a pre-determined angle so that the wing conforms to the shape of the talus. In an alternative embodiment, the upper wing includes a step portion between the lower wing and the bent tab and carrying one screw hole. In this embodiment, the bent tab is generally elongated with one or two screw holes disposed along its length.

The invention discloses a wing structure with flow control and separation control of laminar flow. A plurality of A micropores are arranged at the front end of the vertical center line of the upper wing surface of a wing, and are neatly arranged in lines and rows to form an inspiration zone; a plurality of B micropores are arranged at the back end of the vertical center line of the upper wing surface of the wing, and are neatly arranged in lines and rows to form an air blowing zone; a communicating channel in the inspiration zone and the air blowing zone is called an air flow channel, namely, an inlet of the air flow channel is communicated with the inspiration zone, while an outlet of the air flow channel is communicated with the air blowing zone; the air flow channel is arranged in the wing; the air flow channel consists of a front air flow channel, a middle air flow channel and a back air flow channel, wherein, the middle air flow channel is in an elliptic shape; an inspiration pump is arranged in the middle air flow channel; the front air flow channel and the back air flow channel are designed into a flaring shape and are oppositely arranged. The wing of the invention can delay the transition of a bounding layer from lamina flow to turbulent flow by a control method for adjusting the capacity of blowing and inspiration so as to reduce the frictional resistance on an object surface, and can delay the flow separation so as to improve the stall performance of wing profile.

A wing tip device for fixing to the outboard end of a wing, the wing defining a wing plane, includes: an upper wing-like element projecting upwardly with respect to the wing plane and having a trailing edge; and a lower wing-like element fixed with respect to the upper wing-like element and having a root chord and a trailing edge, the lower wing-like element root chord intersecting with the upper wing-like element, and the lower wing-like element projecting downwardly from the intersection. The upper wing-like element is larger than the lower wing-like element and the trailing edge of the lower wing-like element is adjacent the trailing edge of the upper wing-like element at the intersection. An included angle between the upper and lower wing-like elements at the intersection is less than, or equal to, 160 degrees.

The invention discloses an adjustable test fixture device, which comprises an H beam base, two support bases arranged on the H beam base and clamped pressure sheets arranged on the tops of the support bases; two pairs of support base guide grooves are arranged on an upper wing plate of the H beam base; and one support base is movably connected to each pair of support base guide grooves. The device disclosed by the invention is simple for operation and high in precision; the positions of the support bases can be adjusted through the guide grooves on the upper wing plate of an H beam, so that the distance between the support bases can be adjusted, thus, the purpose of applying to test pieces with different geometrical sizes can be achieved; different boundary types can be realized by replacing the types of the support bases on the upper wing plate of the H beam; and the H beam base can move, thus, the adjustable test fixture is convenient to experiment and test in different places and has a certain portability.

The invention provides astress island assembled type hollow floor, comprising a column, a main beam, an assembled type hollow plate, a stress island, an upper wing plate of the assembled type hollow floor, and a joint seam, wherein the assembled type hollow plate consists of a longitudinal rib, a bidirectional loading-formed regeneration rib, a hollow hole forming member, a lower wing plate, a rib or local stirrup exposure of the rib and a stress island reserved corner; the longitudinal rib of the assembled type hollow plate is provided with two exposed ends; the stress island is arranged in such a manner that, in the fabrication of the assembled type hollow plate, a space larger than 0.18mm<2> for the stress island reserved corner is assembled at the periphery of an outer edge of the column, a column rib, a main beam rib, an upper wing plate rib and a rib in the space for the stress island reserved corner form stress island ribs, and concrete is cast to form the stress island; the joint seam is formed in a lower surface of the stress island assembled type hollow floor, and is in an intermittent state, and the joint seam is only part of thickness of the hollow floor.

A propulsion system includes an engine disposed within a fuselage, a first gearbox coupled to the engine, a wing member having an upper wing skin and torque box formed by a first rib, a second rib, a first spar and second spar, a drive shaft coupled to the first gearbox and disposed within the wing member, a second gear box coupled to the drive shaft and disposed outboard from the second rib or inboard from the first rib, and a rotatable proprotor coupled to the second gear box. The rotatable proprotor includes a plurality of rotor blades, a rotor mast having a mast axis of rotation, and a proprotor gearbox coupled to the rotor mast. The proprotor gearbox is rotatable about a conversion axis, which intersects with the mast axis of rotation at a point within a central region of the torque box and above the upper wing skin.

A tiltrotor aircraft includes a fuselage; a wing member having a first rib, a second rib, a first spar, second spar; and an upper wing skin; an engine disposed at a fixed location relative to the wing member; and a proprotor having a spindle gearbox, rotor mast, and a plurality of rotor blades drivable in rotation about the rotor mast, the spindle gearbox being rotatable about a conversion axis. The spindle gearbox is located above the upper wing skin of the wing member.

A compound rotorcraft with a fuselage and at least one main rotor, the fuselage comprising a lower side and an upper side that is opposed to the lower side, the at least one main rotor being arranged at the upper side, wherein at least one propeller is provided and mounted to a fixed wing arrangement that is laterally attached to the fuselage, the fixed wing arrangement comprising at least one upper wing that is arranged at an upper wing root joint area provided at the upper side of the fuselage and at least one lower wing that is arranged at a lower wing root joint area provided at the lower side of the fuselage, the upper and lower wings being at least interconnected at an associated interconnection region.

A truss-type corrugated steel web composite beam with an open bottom chord belongs to a bridge support member. The bottom chord opened and truss-type corrugated steel web composite beam comprises an upper wing edge concrete slab, a corrugated steel web and a bottom chord opened truss-type rectanglar steel tube concrete member. Compared with steel truss-type web composite corss section, the invention adopts the corrugated steel web with rather high shear strength to replace a steel web member, so as to guarantee quite high shear bearing capacity. The opened truss-type bottom chord is composed of two parallel-arranged rectanglar steel tubes arranged in parallel and internally cast concrete, as well as horizontal braces and batter braces between the rectanglar steel tubes. Moreover, the bottom chord adopts the steel tube concrete member to overcome the problem of rather high work volume that, in traditional composite cross section of corrugated steel web box beams and steel truss-type webs, such execution measures as scaffolding, formwork-support, concrete casting and etc. should be taken for lower wing edge concrete slabs. Meanwhie, the invention can effectively improve structure crack resistance, avoid crackage exposure and etc, and considerably increase structure durability. The bottom chord is a brace-connected open-type structure with advantages of simple structure and fast, smooth and convenient execution.

The invention relates to a wingtip eddy diffusion device, comprising an upper winglet and a lower winglet which play the role of an end plate to block bottom wing surface air current from flowing to the upper wing surface; the upper winglet and the lower winglet are both of symmetrical airfoil profile; the symmetrical airfoil profile can avoid intense shock wave under supercritical air current condition, extra wave drag; certain deflection exists in wingtips of corresponding wings of the two winglets, thus improving lifting force of wings. The invention has the advantages of weakening wingtip eddy diffusion and trailing vortex intensity, downwash field of wingtips of wings and induced drag.

The invention refers to a suspension pylon (4) for an aircraft engine (2), the pylon including a rigid structure (10) forming a box provided with a lower spar (28) and an upper spar (26), and an engine mounting system (11) installed fixed on the structure (10) and in particular including a forward attachment (6) with an attachment body provided with a horizontal fixing surface (40) held in contact with a horizontal fixing surface (38) of the structure (10). According to the invention, the attachment body is arranged such that its horizontal fixing surface (40) is located along a vertical direction (Z) of the pylon, upwards from a forward end (28a) of the lower spar and downwards from a forward end (26a) of the upper spar. Furthermore, the structure (10) includes at least one forward fitting (42a, 42b) making up a forward closing rib (36) of the box, this fitting (42a, 42b) defining said horizontal fixing surface (38).

Aircraft having thrust vectoring for switchably providing upper surface blowing. The aircraft generally includes a wing and an engine. The engine can be rotatably supported to supporting structure to allow the engine to be controllably rotated relative to the wing, and / or the engine can include a thrust vectoring nozzle. The engine's thrust vectoring capabilities allow the exhaust flow to be controllably vectored to switch on or off upper surface blowing depending on the aircraft's phase of operation. During a first phase, the exhaust flow can be vectored to flow across the upper wing surface to provide upper surface blowing to augment lift. During a second phase, the exhaust flow can be discharged generally downstream or rearwardly. The engine is positioned relative to the wing such that the exhaust flow does not provide upper surface blowing during the second phase.

The invention is a variable section conversion node for profiled steel concrete framework-steel support structure, interconnecting in-pillar profiled steel, in-beam profiled steel, steel support, in-pillar reinforced concrete and in-beam reinforced concrete and pouring then into an organic whole, where the steel support is orthogonally connected with in-pillar an in-beam profiled steel flange plates by section conversion, the web of the in-beam profiled steel in the node connection position is converted into heightening variable section web and the top surface of the heightening variable section web is welded with widening variable section upper wing plate, the bottom surface of the heightening variable section web is welded with widening variable section lower wing plate; the shape of the steel support in the node connecting position is converted into structure of variable section node conversion region and two flange plates of the steel support in variable section conversion region are orthogonally connected with the in-pillar and in-beam profiled steel respectively. And the invention intensifies fore bearing performance of node regions of the profiled steel concrete framework-steel support structure and ability of cooperating of profiled steel and reinforced concrete.

The invention provides a suspension type monorail traffic system, which comprises a rail beam, an upright post for supporting the rail beam, a truck frame arranged on the rail beam, a carriage suspended below the truck frame, and a driving wheel and a guide wheel which are arranged on the truck frame, wherein the rail beam is a transverse H-shaped beam; the transverse H-shaped beam comprises an upper wing plate and a lower wing plate which are arranged at an interval; the upper wing plate is parallel to the lower wing plate or is at an included angle to but not intersected with the lower wing plate, and a webplate is connected between the upper wing plate and the lower wing plate; and the lower wing plate provides a rolling rail for the driving wheel, and the webplate provides the rolling rail for the guide wheel. The suspension type monorail traffic system has the advantages of compact structure, low cost, simple installation and convenient maintenance.

The invention provides a vaginal dilator with double side wings, comprising an upper wing, a pressing handle, a lower wing, and a handle; the upper wing and the lower wing are connected through a pin; the pressing handle and the handle are meshed with each other through a first dilation fixing structure; the vaginal dilator further comprises an arc flexible locating sleeve rotatably connected with the upper wing; both ends of the sleeve are respectively provided with a mounting base; the base is provided with a mounting hole for holding the side wings capable of being held between the upper and the lower wings; the rear part of the side wings is provided with a second dilation fixing device meshed with the upper part of the rear end of the upper wing; and a passage can be installed in the side wing. Compared with the prior art, the vaginal dilator with double side wings has the advantages of wider field range, simple structure and easy manufacturing.

The invention discloses a wing folding and unfolding mechanism of an unmanned aerial vehicle. The mechanism mainly comprises a vehicle body reinforcing frame, a wing rotary shaft, a rotary body driving part, an upper wing, a lower wing and a coaxial contrarotation mechanism. When the unmanned aerial vehicle is launched, a fixed cylinder is opened, and coaxial contrarotation equal-angle movement of the upper and lower wings is realized through the coaxial contrarotation mechanism under the effect of a torsional spring. The mechanism disclosed by the invention is simple in integral structure, compact, high in transmission efficiency by applying gear drive and small in frictional force. The two wings share the rotary shaft, so that the area occupied by the wings is reduced and the unmanned aerial vehicle is convenient to transport and launch, thereby further improving the capacity of systematic combat.

The invention relates to a replaceable prefabricated combined beam structure which comprises a steel beam, prefabricated concrete plates and high strength bolt connectors. The prefabricated concrete plates are located on upper wing edge plates which are parallelly arranged on the steel beam, and adjacent prefabricated concrete plates in a span direction are connected through an external prestressing tendon; lower holes corresponding to the high strength bolt connectors are formed in the upper wing edge plates of the steel beam, reserved holes corresponding to the connectors are formed in the prefabricated concrete plate, and the high strength bolt connectors are connected through the reserved holes and the lower holes from top to bottom. The invention also provides a manufacturing process of the replaceable prefabricated combined beam structure. The invention provides the replaceable prefabricated combined beam structure which is simple to construct and relatively high in assembling efficiency, and the manufacturing process.

The invention provides an airplane with a combined-wing layout of a flying wing and forward-swept wings. The airplane is characterized in that thin-wing type vertical columns A and B are additionally arranged at the 70% wingspan positions of the outer sides of two side wings of a flying-wing airplane with backward-swept wings, a thin-wing type vertical column C is additionally arranged at the tail part of the flying-wing airplane, and horizontal forward-swept wings are additionally arranged at the top ends of the three thin-wing type vertical columns A, B and C so as to form the combined-wing layout of the flying wing and the forward-swept wings; elevators are arranged on the horizontal forward-swept wings and a rudder is arranged on the vertical column C; a duct type air inlet channel is adopted on the upper wing surface of the flying wing, and cracking type drag rudders are distributed at the thin-wing type vertical columns A and B. The airplane provided by the invention has the advantages that under the condition that the structure strength is effectively guaranteed, the effective aspect ratio of the wings is increased, the induced drag is reduced, the lift-drag characteristics of the airplane are improved, the stealth performance of the airplane is improved, direct-force control of the airplane in the vertical direction is realized and the detecting accuracy under the maneuvering condition is improved.

The invention discloses a distributed type electric ducted fan flap lifting system. The distributed type electric ducted fan flap lifting system is provided with a plurality of ducted fans which are in linear arrangement at the front edge of the upper wing surface of a wing at certain distances, the front edge of a duct stretches to be positioned in front of the front edge of the wing, the rear edge of the duct is located at the maximum thickness position of the wing, and a rear edge flap is arranged at the rear edge of the wing, corresponding to the position of the ducted fan. The distributed type electric ducted fan flap lifting system is safe and has low noise, small vibration, high lifting force and good economical efficiency during working. A hovercar adopting the distributed type electric ducted fan flap lifting system can realize vertical takeoff and landing, high-speed horizontal flight and smooth conversion between the vertical takeoff and landing state and the high-speed horizontal flight state.

The present invention relates to a high strength Al—Zn alloy product with an improved combination of corrosion resistance and toughness, the alloy including essentially (in weight percent): Zn: 6.0-9.5, Cu: 1.3-2.4, Mg: 1.5-2.6, Mn and Zr<0.25 but preferably in a range between 0.05 and 0.15 for higher Zn contents, other elements each less than 0.05 and less than 0.25 in total, balance aluminium, wherein (in weight percent): 0.1[Cu]+1.3<[Mg]<0.2[Cu]+2.15. The invention also relates to a method to produce these alloy products, and to some preferred applications thereof such as upper wing applications in aerospace.

An automatic non-standard steel welding production line comprises an automatic wing plate pushing system, wing plate conveying systems, an automatic web discharging and feeding system, an automatic T-steel welding system, an automatic T-steel turnover system, an automatic H-steel welding system and an automatic finished product conveying system. The wing plate conveying systems include an upper wing plate conveying system and a lower wing plate conveying system, and the wing plate conveying systems and the automatic web discharging and feeding system are arranged vertically. In the automatic non-standard steel welding production line, all the devices are simple in structure, easy to operate, stable in mutual connection, continuous automatic welding production of non-standard steel can be realized, weld seams on two sides of a plate are welded at the same time, and the automatic non-standard steel welding production line is small in distortion, less in capital investment, small in space occupation, suitable for non-standard steel manufactures with various scales, timesaving, laborsaving, manpower saving, high in working efficiency and good in product quality.

The invention relates to a steel column and beam structure used in the building and a welding device thereof, particularly discloses a steel column and beam structure with a corrugated steel web and a special welding device thereof. The steel column and beam structure comprises an upper wing plate, a lower wing plate and a web plate arranged between the upper wing plate and the lower wing plate, wherein the upper wing plate and the lower wing plate are made of plates with the thickness of 4-30mm, the web plate is a corrugated steel web plate with the thickness of 4-10mm, and the surfaces of the upper wing plate, the lower wing plate and the web plate are prepared with 50-500Mu m of roughness; the welding device of the steel column and beam structure with the corrugated steel web comprises a welding tractor and a welding gun arranged on the welding tractor, wherein tool sliding bars which are symmetrical are arranged on the welding tractor, a magnetic adsorption piece is arranged at the bottom of the welding tractor, four driving wheels are symmetrically arranged at two sides of the magnetic adsorption piece, and a track positioning retainer is arranged in a bracket at the middle part of the welding tractor. The middle web plate adopts the corrugated steel web plate, the steel beam and column with the corrugated steel web is welded by using the special welding device, therefore, the invention has the advantages of light weight and strong earthquake resistance.

The invention provides a vaginal dilator with upper and lower wings provided with auxiliary wings, comprising an upper wing, a press handle, a lower wing, a handle, an upper auxiliary wing and a lower auxiliary wing, wherein the press handle is integrated with the upper wing and stretches downwards along an obtuse-angle direction at the rear end of the upper wing, and the handle is integrated with the lower wing and stretches downwards in an approximate right angle direction along the rear end of the lower wing; the two sides of the rear ends of the upper wing and the lower wing are connected through pin shafts; the press handle is meshed with the handle through an expansion fixed structure; the upper auxiliary wing and the lower auxiliary wing arranged at the inner sides of the upper wing and the lower wing are respectively connected with the upper wing and the lower wing and are provided with a channel; and the channel comprises a channel main body and a channel cover, the channel cover is matched with the channel main body in a sealing mode, and the channel main body is provided with at least one hole facing the inner sides of the upper wing and the lower wing. Compared with the prior art, the vaginal dilator with the upper and lower wings provided with the auxiliary wings greatly improves the smoke discharge capability and provides a channel for installing a lighting device and a camera device. The vaginal dilator has the advantages of simple structure and easy manufacture.

According to the present invention, a plasma processing apparatus for performing surface processing of a substrate by means of plasma discharge is provided comprising: a processing chambers 10R and 10L for performing surface processing of a substrate W; a load-lock chamber 11 which is arranged in between these processing chambers 10R and 10L; and transporting mechanisms which are capable of performing substrate transport between load-lock chamber 11 and processing chamber 10R, and between load-lock chamber 11 and processing chamber 10L; these transporting mechanisms are freely movable in a reciprocating manner in the direction in which processing chamber 10R, load-lock chamber 11, and processing chamber 10L are contiguously arranged; wherein, upper wing 20U and lower wing 20L, which are spaced apart in a vertical manner with respect to each other, are provided as the aforementioned transporting mechanisms.