36 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.

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.

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 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 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 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.

This invention relates to the field of aerodynamic component technology, and in particular to a wing spoiler device for a ground effect vehicle (GEV). The wing spoiler device for a GEV includes: a base, a movable flap, the front end of which is hinged to the front of the base, and the rear end of which is fixed to the rear of the base via an adjusting fastener passing through a pre-set first adjusting and fixing hole. The spoiler device is mounted above the front wing of the GEV via the base, so that when the incoming airflow passes over the upper wing surface, it obstructs the downwash airflow converging at the trailing edge of the wing, generating vortices inside the spoiler device to reduce the lift of the upper wing surface and increase the ground effect ratio of the lower wing surface, thereby suppressing the aerodynamic center of gravity shift of the GEV. The advantages of this invention are its simple structure, low manufacturing cost, and the elimination of the need for active control components such as servos or other transmission electronic devices. It also features a robust structure, better adaptability to harsh water environments, reduced safety hazards, and extended service life of the aircraft.

The application belongs to the technical field of aircraft design, and particularly relates to a high-lift-coefficient layout aircraft and a use method thereof. The aircraft comprises a fuselage, a hump arranged on an upper middle part of the fuselage, a lower wing connected to the hump, an upper wing located above the lower wing and detachably connected to the lower wing, the upper wing being connected to the lower wing through an actuator and a four-bar linkage mechanism, the separation or adhesion of the upper wing relative to the lower wing being controlled by the actuator, a trailing edge flap and aileron arranged on a trailing edge of the lower wing, a V-tail stabilizer connected to a rear part of the fuselage and a V-tail control surface connected to a tail part of the V-tail stabilizer, and an engine connected to the fuselage. The application can greatly increase wing area and effective angle of attack, and significantly improve take-off and landing lift.

The utility model discloses a heavy fork truck arm simple combination function enhancement device, including square tube, square tube is welded together by two wing plates and two web plates, both ends of square tube are open, and the outer surface of fork truck arm is sleeved, square tube includes two section structure of butt joint section and bearing section, and butt joint section is inserted with fork truck arm, and bearing section is used for bearing pressure steel pipe, the outer surface of upper and lower wing plate of bearing section still welds wing plate reinforcing plate, and the lateral surface of web plate welds multiple stiffened plates for reinforcing on both sides, the lateral surface of web plate welds multiple lifting lugs on both sides. The device solves the problem that the fork truck of prior art cannot meet the transportation pressure steel pipe because of the short fork truck arm, and cannot be fixed well in the transportation process, and cannot be efficiently transferred in the small space, has the characteristics that the structure is simple, is convenient for manufacturing, installation, easy to disassemble and maintain, can play the function maximization of the fork truck, satisfies the narrow space construction problem, improves the unloading and secondary transportation efficiency.

An aircraft (10) comprising: a starboard swept wing (14A) and a port swept wing (14B), each swept wing having an inner wing section (26A) comprising an integrated payload fuselage (20) and an outer wing section (30A) for extending the wingspan and providing lift; the inner wing section comprising: a rear spar (40) disposed close to a trailing edge (22A) of each inner wing section to carry loads along each inner wing section; a wing surface (30), in which the wing surface is substantially shaped as an aerofoil, and in which the wing surface comprises a rear fairing (62) disposed behind the rear spar, and near to the trailing edge, and in which the wing surface comprises an upper curved portion (50) which has a substantially arcuate cross section, a front curved portion (52) which has a substantially arcuate cross section, and a lower wing surface, the upper curved portion meeting the rear spar at a rear of the upper curved portion, and the upper curved portion meeting the front curved portion at a front of the upper curved portion, and the front curved portion meeting the lower wing surface at a front of the lowerwing surface, a cabin structure (32) in each inner wing, in which the cabin structure comprises one or more floor beams (36) and a rear wall defined by the rear spar; in which the lowerwing surface comprises a front lower curved portion (117), in which the front lower curved portion is substantially arcuate in profile and extends from a front edge of the floor beam(s) of the cabin structure towards the rear wall; in which the lower wing surface of each inner wing extends below a first line A, the first line being a line on the rear wall of the cabin structure where a projection of the arcuate front lower curved portion of the wing surface meets the rear wall, and in which a rear lower portion of the lower wing surface meeting the front lower portion and continuing the lowerwing surface to a second line, which is spaced from and below the first line.

This utility model relates to the field of automotive structural technology, specifically to an integrated pipeline fixing bracket, comprising an integrally formed frame connection part, a pipeline harness fixing part, and a cooling steel pipe fixing part. The frame connection part has multiple pre-drilled mounting holes, allowing for stable installation by utilizing existing holes on the frame with standard parts to securely connect to the frame longitudinal beams. The pipeline harness fixing part is located on the lower wing surface of the frame and has cable tie slots for easy bundling and fixing of pipeline harnesses, water pipes, and oil pipes using cable ties. The cooling steel pipe fixing part includes elongated cooling steel pipe mounting holes, allowing for minor adjustments to the position of the cooling steel pipe along the elongated hole direction, ensuring no interference with surrounding components after fixing and meeting the engine installation requirements of the production line. This utility model optimizes the vehicle pipeline fixing method, offering advantages such as high integration, stable fixing, and convenient installation, effectively solving problems such as cumbersome scattered fixing and easy pipeline interference inherent in traditional fixing methods.

The application discloses a wing parachute with one-way opening control of a lower wing surface. The wing parachute canopy is composed of a lower wing surface opening canopy and a one-way opening and closing cloth which is incompletely sewn. During inflation of the wing parachute, air is simultaneously rammed through an air inlet at a leading edge and an air inlet at the lower wing surface, and the one-way opening and closing cloth is automatically opened and closed through pressure difference between inside and outside of an air chamber. The wing parachute disclosed by the application can effectively improve inflation efficiency of the wing parachute, improve inflation performance and opening reliability of the wing parachute, ensure that the wing parachute forms a stable aerodynamic shape, thereby maintaining good aerodynamic performance, and has important significance for structural design of the ram wing parachute.

The utility model provides a kind of support tooling die for bottle body positioning, it is related to the technical field of automobile air conditioner, including bottom plate and product bracket being set on bottom plate;The product bracket surface is formed with the camber surface matching with the outline of drying bottle body, further include: first quick fixture is arranged in the width direction of drying bottle body in the side of the product bracket, for clamping fixed support upper wing;Second quick fixture is arranged in the width direction of drying bottle body in the other side of the product bracket, for clamping fixed support lower wing;Third quick fixture is arranged in the length direction of drying bottle body in the side of the product bracket, for abutting drying bottle one end to realize limit.The utility model has the beneficial effect of compact structure, convenient operation, through the synergistic effect of multiple quick fixtures, the accurate positioning and quick clamping of drying bottle and support are realized, only one person can operate, saves labor cost, is conducive to standardization operation.

The utility model provides a kind of self-unloading car crossbeam assembly and frame, above-mentioned crossbeam assembly, including crossbeam, including main part and two extension parts connected in the both ends of the main part;The main part includes upper wing plate, the lower wing plate opposite with the upper wing plate, front side plate and rear side plate connected between the upper wing plate and the lower wing plate, the rear side plate is oppositely arranged with the front side plate, the upper wing plate, the lower wing plate, the front side plate and the rear side plate are enclosed to form box beam structure;Two the extension part is connected in the both ends of the upper wing plate respectively, and it is integral structure with the upper wing plate;Suspension cylinder support, two are provided, two the suspension cylinder support is respectively connected with two the extension part one-to-one correspondence.The utility model embodiment is more stable in stress, improves strength and rigidity, prevents crossbeam cracking.

This application discloses a wing lift-to-drag ratio adjustment device and method, belonging to the field of aircraft aerodynamics design. At least two airflow passing elements are symmetrically arranged on the lower surfaces of the left and right wings of the aircraft, and can switch between a retracted state and an operational state. In the operational state, the airflow passing elements at least partially protrude from the lower wing surface, with at least the surface facing the leading edge being arc-shaped, and their cross-sectional area decreasing along the protrusion direction. This accelerates the local airflow, reduces static pressure, thereby reducing lift, while simultaneously generating form drag to increase overall aircraft drag. A drive mechanism is used to switch the state of the airflow passing elements in response to control commands; a controller is used to generate and send control commands. This application also provides a corresponding adjustment method. This application has a simple structure, low cost, and can flexibly adjust the lift-to-drag ratio according to the landing environment, with minimal impact on the aircraft's pitch moment, making it particularly suitable for long-endurance aircraft without flaps.

The utility model discloses a six steel double -wheel turntable formula milking machine chassis relates to the field of livestock machinery and equipment, including upper track, lower track, support base and gyro wheel subassembly, and lower track is fixedly connected in the top of support base through fastening bolt, and upper track and lower track concentricity are established, and a plurality of gyro wheel subassembly are clamped between upper track and lower track, and every gyro wheel subassembly includes two gyro wheel and corresponding gyro wheel frame, and gyro wheel frame is installed on the gyro wheel, and adjacent two gyro wheel subassembly are connected through gyro wheel frame, upper track, lower track all include I -type track main part and reinforcing web, and two reinforcing webs are symmetrically divided and are arranged in the left and right sides of I -type track main part web, and the upper end and lower end of reinforcing web are fixedly connected with the upper wing plate and lower wing plate of I -type track main part respectively, and the outer surface of upper track and lower track all is provided with hot galvanizing layer. The utility model can effectively resist the corrosion of long -term heavy load and bad environment, and avoid the early failure of track key parts.

The present application provides a puller with good assembly operability and structural strength. The puller comprises a puller body including an upper wing plate and a lower wing plate arranged opposite to each other, and a puller replacement piece including a rear mouth portion and a pair of slide rail portions extending forward from the rear mouth portion in a length direction and separated from each other, wherein opposite two side edges of one of the upper wing plate and the lower wing plate in a width direction are provided with a pair of slide groove portions extending in the length direction, and the puller replacement piece is installed on one of the upper wing plate and the lower wing plate as a part of one of the upper wing plate and the lower wing plate by a pair of the slide rail portions sliding along a pair of the slide groove portions relative to the puller body horizontally.

The application discloses a kind of electromagnetic drive micro-actuator based on FPC flexible joint and its manufacturing process, belong to bionic actuator technical field, it includes upper wing piece;Lower wing piece is oppositely arranged in the lower side of upper wing piece, and upper wing piece is connected with lower wing piece to form hollow cavity structure, and the front and rear ends of cavity open to form fluid passage;Stator is arranged in cavity, and is fixed to the front end of lower wing piece by lower fixed seat component;Vibrator is arranged in cavity, and is correspondingly arranged with stator;Upper wing piece and lower wing piece are FPC flexible circuit substrate, repel by stator and vibrator, so that the front end of cavity expands and inhales water flow, then stator and vibrator attract each other to make the front end of cavity contract, form conical spout guide structure to assist guide water flow injection, to realize jet unidirectional propulsion.The application has good propulsion performance, utilizes the compression rebound cycle of controllable electromagnetic drive cavity, forms high-speed jet, realizes periodic stable propulsion force.

The application relates to the field of building engineering, in particular to a punched steel plate jet concrete sandwich wall and a construction method thereof. The concrete sandwich wall comprises a core layer and two concrete surface layers; the core layer comprises heat preservation plates and concrete plate ribs which are alternately arranged along the length direction of the wall; the concrete surface layer comprises a concrete filling body and a plurality of first punched steel plates and second punched steel plates which are wrapped in the concrete filling body; the first punched steel plate comprises a first punched steel plate main body, a first punched steel plate upper wing, a first punched steel plate lower wing and a first punched steel plate side wing which are integrally formed; a first equilateral triangle punched hole array is formed on the first punched steel plate main body, and the upper edge of the first equilateral triangle punched hole is connected with a first equilateral triangle tongue piece; a second equilateral triangle hole array is formed on the first punched steel plate side wing; a third equilateral triangle punched hole array is formed on the second punched steel plate; the first equilateral triangle tongue piece is inserted into the inside of the third equilateral triangle punched hole to realize the overlapping fixing of the second punched steel plate and the first punched steel plate.

The application relates to a replaceable adjusting device and a use method thereof, which comprises a support, a base and an adjusting device. The support is a T-shaped plate structure arranged vertically, and the support comprises a rectangular plate and a T-shaped long side arranged on one side of the rectangular plate. The upper and lower ends of the T-shaped long side protrude from the upper and lower end faces of the rectangular plate. A long-strip-shaped pin hole is arranged in the middle of the rectangular plate, and a guide groove is arranged on the top of the rectangular plate. The base is in an E-shaped structure as a whole, and the base comprises an upper wing plate, a lower wing plate, a bottom plate and two side plates. The upper and lower ends of the front side of the bottom plate are horizontally provided with the upper wing plate and the lower wing plate respectively, and the middle of the front side of the bottom plate is provided with the two side plates side by side. The adjusting device comprises an inclination limiting bolt, a perpendicularity adjusting device, an inclination adjusting bolt and an elevation adjusting bolt. The application integrates multiple installation and adjustment functions of elevation, center, perpendicularity and inclination.

The present application belongs to the technical field of commercial vehicle chassis design and manufacturing, in particular to a front structure of a commercial vehicle frame and a vehicle. The front structure of the frame cuts off the upper and lower wings completely to form a maximum installation window in the area corresponding to the cooling module installation of the left and right longitudinal beams. An everted beam is arranged outside the longitudinal beam for reinforcement. The everted beam is disconnected in front of the leaf spring ear support and turned into an inverted structure to strengthen the support area. The left and right leaf spring ear supports are moved outward to the center of the frame to further widen the space. Meanwhile, a round pipe pocket beam is added below the leaf spring ear support to form a high-stiffness closed-loop load-bearing structure with the longitudinal beam and the support. The vehicle applying the front structure of the frame can successfully match a gas engine with a displacement of ≥ 13L and a large-size cooling module under the strict limitation of a vehicle height ≤ 2850mm, effectively solving the contradiction between space, strength and heat dissipation.

The utility model discloses a rotary lock zipper head relates to zipper technical field, include: the pull head body, connecting column, the hook lock, elastic part and the pull piece, the pull head body includes the upper wing plate, the lower wing plate and the lock core of connecting both, connecting column rotatably connected in the upper wing plate, and its rotation axis is parallel with the first direction, the hook lock is installed in the hook lock jack hole that the connecting column is close to the lower wing plate end portion set, and the hook lock includes the locking portion, and the upper wing plate is provided with the slot for the locking portion to pass through, and the hook lock jack hole is installed with the elastic part for urging the locking portion to stretch out from the slot, the pull piece is connected in the connecting column through the cross bar, and the pull piece can urge the connecting column to rotate around its axis, when the cross bar is parallel with the second direction, the locking portion can stretch out the slot to lock the zipper, when the cross bar is parallel with the third direction, the locking portion retracts the slot to unlock the zipper. This can eliminate the friction between the hook and zipper tooth, and further reduce the risk of scratch of the hook on the zipper tooth.

A centrifugal mineral processing and separation device with multi-force field coupling and continuous operation includes a centrifugal mineral processing equipment body driven by a first drive mechanism to rotate. The centrifugal mineral processing equipment body consists of a enrichment cylinder, a concentrate collection cylinder, and a tailings collection cylinder coaxially mounted and fixed from the inside to the outside. The top of the enrichment cylinder is open, and the inner cavity is a separation chamber with a feed pipe inside. The gap between the outer wall of the enrichment cylinder and the inner wall of the concentrate collection cylinder forms a concentrate chamber, and the gap between the outer wall of the concentrate collection cylinder and the inner wall of the tailings collection cylinder forms a tailings chamber. The top of the enrichment cylinder is connected to the tailings chamber via an overflow guide plate. The enrichment cylinder wall is provided with multi-stage enrichment rings axially, and the enrichment rings extend radially, each containing an enrichment chamber connected to the separation chamber. The enrichment chamber is evenly distributed with a backwashing device to loosen the bed. Valves are provided on the upper wing plate and / or the lower wing plate to control the connection and disconnection between the enrichment chamber and the concentrate chamber. This device simplifies the ore discharge process, enhances the dispersion of the material layer and the particle penetration, and the backwashing water mechanism and ultrasonic force field work together to effectively solve the bed caking problem, increase the single unit processing capacity, and realize continuous operation.

The application belongs to the field of unmanned aerial vehicles, and particularly relates to a wing unfolding mechanism and an unmanned aerial vehicle. The unmanned aerial vehicle comprises the wing unfolding mechanism, the wing unfolding mechanism comprises a fixed shaft, an upper joint and a lower joint, opposite ends of the upper joint and the lower joint are enclosed to form an installation cavity, a torsional spring is installed in the installation cavity, the fixed shaft penetrates through the upper joint, the torsional spring and the lower joint, two torsional arms of the torsional spring are connected with the upper joint and the lower joint respectively, the fixed shaft is provided with an intermediate support structure and a lower stop structure, the lower end of the upper joint is supported by the intermediate support structure, the lower end of the lower joint is supported by the lower stop structure, and the upper joint and the lower joint are spaced in the axial direction, the upper joint and the lower joint are rotatably connected with the fixed shaft through friction-reducing members. The intermediate support structure is arranged on the fixed shaft to space the upper joint and the lower joint, when the wings are unfolded, the friction force generated by the existing lower holder due to bearing the weight of the upper wing is eliminated, the friction forces borne by the upper wing and the lower wing are closer, and the synchronization of the unfolding of the upper wing and the lower wing is improved.