555 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 an H-shaped steel automatic welding roller way conveying system. Comprising a lower wing plate feeding line, a web feeding line, an upper wing plate feeding line, a lower wing plate and web assembly line, a T-shaped steel assembly welding straightening blanking transition line, a T-shaped steel assembly welding straightening blanking line, a web lifting turnover line, a T-shaped steel upper wing plate assembly line, an H-shaped steel assembly welding straightening blanking transition line and an H-shaped steel assembly welding straightening blanking line which are arranged in parallel in the same direction. The lower wing plate feeding line, the lower wing plate web assembling line, the T-shaped steel assembling, welding and correcting discharging line, the web feeding line, the upper wing plate feeding line, the T-shaped steel upper wing plate assembling line and the H-shaped steel assembling, welding and correcting discharging line are each composed of a plurality of roller bed units. The web lifting turnover line is composed of a plurality of lifting roller bed units; and the T-shaped steel assembling, welding and straightening blanking transition line and the H-shaped steel assembling, welding and straightening blanking transition line are respectively composed of a plurality of transition roller bed units. The problems that an existing H-shaped steel welding production line is high in labor intensity and low in efficiency, and safety factors exist in a working site can be solved.

A vertical take-off and landing aircraft with a multi-element lifting system with integrated propulsion. The multi-element lifting system may have an upper wing element, a lower wing element, and a control wing element which is located below the upper wing element and above, and rearward of, the lower wing element. The system uses internal propulsion units, such as internal ducted fans, which flow air below the upper wing element and above the lower wing element such that the air flows through the multi-element lifting system. The control wing element may be articulated to route air vertically downward to allow for short or vertical take-off and landing. An aircraft with a multi-element wing assembly and a multi-element tail assembly raised above the wing assembly. An aircraft which resides on the ground with the wing assembly and the tail assembly pitched up.

A vertical take-off and landing aircraft with a multi-element lifting system with integrated propulsion. The multi-element lifting system may have an upper wing element, a lower wing element, and a control wing element which is located below the upper wing element and above, and rearward of, the lower wing element. The system uses internal propulsion units, such as internal ducted fans, which flow air below the upper wing element and above the lower wing element such that the air flows through the multi-element lifting system. The control wing element may be articulated to route air vertically downward to allow for short or vertical take-off and landing. An aircraft with a multi-element wing assembly and a multi-element tail assembly raised above the wing assembly. An aircraft which resides on the ground with the wing assembly and the tail assembly pitched up.

Aerodynamic lifting structures, such as aircraft wings, having embedded engines and associated methods and systems are disclosed herein. A wing assemblies configured in accordance with embodiments of the present technology can include, for example, an upper wing portion, a lower wing portion, and a plurality of independent ducts positioned between the upper wing portion and the lower wing portion. Each duct can extend between a corresponding inlet positioned toward a leading portion of the wing assembly and a corresponding outlet positioned toward a trailing portion of the wing assembly. The wing assembly can further include a plurality of fans and a plurality of electric motors operably coupled to the plurality of fans. The fans and electric motors are positioned in the corresponding individual ducts and the fan is rotatable to propel fluid received in the inlet through the duct to create lift.

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 discloses a positioning device for an H-shaped steel assembly machine, which belongs to the technical field of H-shaped steel assembly machines and comprises a base, an inverted U-shaped frame is fixedly connected to the top of the base, and a lower wing plate is arranged in the middle of the top end of the base. According to the utility model, the lower wing plate is limited through the lower wing plate limiting wheel, the web plate is limited through the web plate limiting wheel, and the upper wing plate is limited through the first upper wing plate limiting wheel and the second upper wing plate limiting wheel, so that the lower wing plate, the web plate and the upper wing plate are positioned and the connection positions are welded during movement to form H-shaped steel; when a limiting structure needs to be adjusted according to the sizes of a lower wing plate, a web plate and an upper wing plate, a first motor drives a lead screw to rotate, the lead screw drives supports on the two sides to move in the opposite directions at the same time, positioning mechanisms on the two sides move in the opposite directions at the same time, H-shaped steel can be positioned in the center position, and it is avoided that when the H-shaped steel is positioned, the positioning precision is high. And the position of the H-shaped steel is deviated.

A vertical take-off and landing aircraft with a multi-element lifting system with integrated propulsion. The multi-element lifting system may have an upper wing element, a lower wing element, and a control wing element which is located below the upper wing element and above, and rearward of, the lower wing element. The system uses internal propulsion units, such as internal ducted fans, which flow air below the upper wing element and above the lower wing element such that the air flows through the multi-element lifting system. The control wing element may be articulated to route air vertically downward to allow for short or vertical take-off and landing. An aircraft with a multi-element wing assembly and a multi-element tail assembly raised above the wing assembly. An aircraft which resides on the ground with the wing assembly and the tail assembly pitched up.

The utility model provides a crane with a rail dust blowing device, which comprises a bridge frame and a hoisting mechanism arranged on the bridge frame, the bridge frame is an I-shaped steel rail, the hoisting mechanism comprises a hoisting winding drum and a traveling mechanism arranged on the hoisting winding drum, and the traveling mechanism is matched with the I-shaped steel rail. Dust blowing devices are arranged on the front side and the rear side of the walking direction of the walking mechanism respectively, air outlets of the dust blowing devices directly face a lower wing plate and / or a web plate of the I-shaped steel rail, and sundry collecting mechanisms are arranged on the two sides of the lower wing plate respectively. According to the crane with the rail dust blowing device, the dust blowing device is mounted on the hoisting mechanism, so that dust, sundries and the like on the rail can be cleaned, and the influence on normal operation of the crane due to large-scale accumulation of the dust, the sundries and the like on the rail is avoided.

The invention provides a supersonic-speed jet adopting supersonic-speed double wings and variant design, and belongs to the field of novel supersonic-speed civil aircrafts, a large-area truncated delta wing with edgings on the inner side is adopted, an engine nacelle is arranged on the upper portion of the outer end of the large-area truncated delta wing, and the supersonic-speed double wings are installed on the outer side of the nacelle; the front edges and the rear edges of the upper wing and the lower wing of the supersonic double-wing adopt intelligent materials to realize a variant function; the empennage can rotate around a mounting shaft in the longitudinal direction of the airplane to change the inclination angle; the front edge and the rear edge of the supersonic double-wing are deformed, and the inclination angle of the empennage is changed to jointly form a supersonic state and a subsonic state. The problem that the conventional double-wing non-design-point performance is poor is solved, high aerodynamic performance can be achieved within the flight envelope range, and it is guaranteed that an aircraft achieves ideal supersonic speed environment-friendly performance such as acoustic explosion and noise and aerodynamic efficiency.

The invention discloses a wing end standing vortex lift augmentation device which comprises a device upper surface, a device lower surface, a leading edge surface and a wing profile, a wing upper wing surface extends outwards to form the device upper surface, a wing lower wing surface extends outwards to form the device lower surface, and the extension length of the device upper surface is larger than that of the device lower surface. A distance exists between the upper surface and the lower surface of the device, and wingtips do not coincide with each other; the device upper surface, the device lower surface, the front edge surface and the airfoil profile jointly form a semi-closed cavity, when incoming flow exists in the semi-closed cavity, a wing end standing vortex rotating in the direction away from the central axis of the fuselage is formed in the semi-closed cavity, and the rotating direction of the wing end standing vortex is opposite to that of a wingtip vortex. According to the three-dimensional wing, airflow on the lower wing surface of the wing is prevented from flowing to the upper wing surface of the wing through the wing end standing vortex in the semi-closed cavity, so that the trend that the airflow on the lower wing surface of the wing is reversed upwards can be inhibited under the condition of not depending on physical obstruction, the lift force of the three-dimensional wing is effectively increased, and the induced resistance is reduced.

An underframe boundary beam connecting structure suitable for a railway vehicle with a drum-shaped vehicle body is provided. An underframe boundary beam is a through long roll bending piece, a section of the through long roll bending piece is of a channel structure, and has a side face, an upper wing face, and a lower wing face. The side face has an inclination angle consistent with a side wall plate, an upper end of an outer side of the side face is provided with a concave platen, and the side wall plate is lapped on the concave platen and fixed by a butt welding; an inner end of the lower wing face is provided with a downwards vertical flanging, a vertical plate is welded and fixed between the upper wing face and the lower wing face.

The utility model relates to an aviation dynamic differential pressure propeller. The airfoil profile of the aviation dynamic differential pressure propeller comprises an upper airfoil surface and a lower airfoil surface, the section lines of the airfoils are all composed of curves of a monotonically decreasing function from the front edge to the rear edge. The structure is simple, and when the lower wing surface does work on windward airflow, the flow speed is reduced, the static pressure intensity is increased, and upward thrust is generated; the upper airfoil does not do work, airflow flows back, static pressure is reduced, upward pulling force is generated by the airfoils, so that the lift force of the upper airfoil and the lower airfoil is upward at the same time, the sum of the lift force is larger than the lift force of an existing single-face airfoil, and then the efficiency of the propeller wing is further improved by optimizing the lift-drag ratio. A front edge point is accurately positioned by adopting a wing section line rear corner, a spanwise line, a relative velocity line and a backward moving distance, a shock wave is weakened to be low-sound-velocity object surface static pressure, and the damage effect of the shock wave is avoided.

The utility model discloses an environment-friendly energy-saving drain board which comprises a drain board body. A water seepage opening is formed in one side of the drainage plate body, a first boss is arranged on one side of the water seepage opening, a second boss is arranged on one side of the first boss, and a bottom plate is arranged on the other side of the first boss. Wherein a lower wing plate is arranged on the other side of the drain board body, and all the extending wing plates are arranged on the other side of the lower wing plate; wherein a penetrating groove is formed in the other side of the extending wing plate, a filter cloth is arranged on one side of the penetrating groove, and a reinforcing rib is arranged on one side of the filter cloth, so that a gap is conveniently formed between the soil and the drainage plate, the filter cloth forms a recess between the boss I and the boss II, and the effect of rapidly draining water is facilitated; the bottom plate is fixedly connected to one side of the first boss on one side, the double-layer drainage effect of the drainage plate is conveniently achieved, the splicing flatness of the drainage plate is conveniently improved by arranging the lower wing plate and the extending wing plate, and therefore rapid drainage of the drainage plate is facilitated.

The invention discloses a two-stage friction energy dissipation type self-resetting beam column joint structure, and relates to the technical field of structural damping. The cantilever beam is vertically arranged on the middle-section side wall of the stand column; the splicing beam and the cantilever beam are arranged at an interval, and the free end of the cantilever beam is arranged opposite to the free end of the splicing beam; an upper wing plate of the cantilever beam is connected with an upper wing plate of the splicing beam; a lower wing plate of the cantilever beam is connected with a lower wing plate of the splicing beam; a two-stage friction energy consumption device is arranged between the free end of the cantilever beam and the free end of the splicing beam; two disc spring reset devices are arranged on the two faces of a web of the cantilever beam side by side respectively. Different lengths of the arc-shaped long holes in the friction plate are used for controlling graded friction energy consumption of nodes under different seismic intensities; the friction plate can return to the initial position through the disc spring reset device, the problem of residual displacement of the friction plate is solved, residual deformation of a structure after an earthquake is effectively reduced, and post-earthquake loss of a building structure is reduced.

The invention relates to a self-adaptive variable-pitch blade which comprises a skin and a spar with anisotropy, the skin wraps the spar to form the blade, the thickness direction of the spar is arranged in the vertical direction, the width direction of the spar is arranged in the horizontal direction, and the thickness of the end, close to a blade root of the blade, of the spar is larger than the width of the end, close to the blade root, of the spar. When the rotating speed of the blades is changed, the bending moment force borne by the blades is also changed, under the action of the bending-torsion coupling effect, the wing spar can convert the borne bending moment force into torsion force, then the propeller pitch of the blades is promoted to be changed, synchronous change of the propeller pitch and the rotating speed of the blades is achieved, and the influence trends of the propeller pitch and the rotating speed on the flight state are the same; therefore, the flight state of the aircraft can be rapidly adjusted.

The invention relates to the technical field of aviation equipment, and discloses a wing-shaped structure suitable for anti-icing and deicing, which comprises a shell and an electric heating piece, an electric heating piece is arranged in a shell, a first heating layer is formed on the upper wing face and the lower wing face of the inner wall of the shell, a second heating layer is formed on the front edge of the inner wall of the shell, the first heating layer and the second heating layer are electrically connected, and the first heating layer and the second heating layer are connected with an external power source through an electrode layer so that power can be supplied to the electric heating piece, and temperature distribution of different parts can be controlled. After the electrode layer conducts electricity, a first temperature area is formed on the first heating layer, a second temperature area is formed on the second heating layer, and the temperature of the first temperature area is lower than that of the second temperature area, so that it is guaranteed that the front edge of the airfoil structure is kept at the high temperature, and the deicing and anti-icing requirements are met. According to the airfoil structure suitable for anti-icing and deicing, differentiated heating can be conducted according to icing characteristics of different parts of the airfoil structure, it is guaranteed that the anti-icing and deicing requirements are met, meanwhile, energy consumption is reduced, and the energy utilization rate is increased.

An aircraft flap comprises an upper wing surface and a lower wing surface which are opposite to each other, and a cavity is defined by the upper wing surface and the lower wing surface; the noise reduction device is arranged in the cavity and comprises a first noise reduction structure, the first noise reduction structure comprises a perforated plate and an upper part and a lower part, the upper part is embedded in the upper wing surface, and the lower part is embedded in the lower wing surface; a second noise reduction structure including foam metal, disposed between the upper portion and the lower portion of the first noise reduction structure, and attached to the first noise reduction structure; and the third noise reduction structure comprises a super-structure partition plate and is embedded into the second noise reduction structure. According to the composite superstructure design integrating the three noise reduction structures together, the structural stability of the noise reduction device can be guaranteed, and meanwhile, the jet flow installation noise of the aircraft engine can be effectively reduced.

A giant airliner structure comprises an airliner body and at least two layers of wings arranged on the two sides of the airliner body, a steering rudder is arranged between the upper and lower adjacent wings. The method has excellent environmental protection property and economical efficiency, and specifically comprises the steps that the core plate structure is adopted, and the labor cost needed in the production process is remarkably reduced; the structural design is simple, the maintenance difficulty is reduced, and the maintenance cost is reduced; the passenger-engine ratio is extremely low, and the manufacturing cost is greatly reduced; the weight ratio of the passenger plane is extremely low, and oil is greatly saved; the wings are short, the airport applicability is wide, and the opportunities of business are increased.

The invention provides a pressure-torsion test device and a use method thereof, and belongs to the technical field of building structure tests. In the pressure-torsion test device, a foundation ground beam, a middle main beam and a side main beam are detachably connected with three-in-one stand columns on the two sides respectively; the fixed end of the vertical electro-hydraulic servo loading device is installed on the lower flange of the middle main beam, and the movable end of the vertical electro-hydraulic servo loading device is connected with a pressure loading area on the top of the pressure-torsion loading force arm. The horizontal electro-hydraulic servo loading device is connected with the side main beam through a suspension connecting assembly, the fixed end of the horizontal electro-hydraulic servo loading device is installed on a side stand column of the three-in-one stand column in a central symmetry mode, and the movable end of the horizontal electro-hydraulic servo loading device is connected with the two ends of a pressing-twisting loading force arm. The lower flange of the compression-torsion loading force arm and the upper flange of the foundation ground beam are respectively provided with a test piece installation area. The compression-torsion test device provided by the invention is simple and convenient to mount and operate, the load position can be freely configured according to the size of a test piece, the load provided by the device can be self-balanced, and the defects of the existing compression-torsion test device in data accuracy and operation simplicity and convenience are overcome.

The utility model discloses an aluminum alloy girder of a container transportation semitrailer. The aluminum alloy girder comprises a front section structure, a gooseneck structure and a rear section structure, the front section structure and the rear section structure are I-shaped aluminum structures; the gooseneck structure comprises a gooseneck upper wing plate structure and a gooseneck lower wing plate structure; the gooseneck upper wing plate structure comprises an upper wing plate front end part, an upper wing plate arc-shaped part and an upper wing plate rear end part which are connected in sequence; the top surface of the front end part of the upper wing plate is propped against the bottom surface of the front-section upper wing plate, and the bottom surface of the rear end part of the upper wing plate is propped against the top surface of the rear-end upper wing plate; the gooseneck lower wing plate structure comprises a lower wing plate front end part, a lower wing plate arc-shaped part and a lower wing plate rear end part which are connected in sequence; the top face of the front end of the lower wing plate abuts against the bottom face of the front section lower wing plate, and the top face of the rear end of the lower wing plate abuts against the top face of the rear end lower wing plate. Structural structure defects and deformation caused by welding can be reduced, the welding workload is reduced, and compared with a traditional girder, the girder is more reliable and more environmentally friendly.

The invention relates to a construction method for reinforcing a landslide through prefabricated high-bending-resistance anti-slide piles, and belongs to the technical field of slope reinforcing engineering. In order to solve the problems that a traditional anti-slide pile is insufficient in flexural rigidity and difficult to reinforce after construction, the I-shaped anti-slide pile structure is adopted and is formed by connecting an upper wing plate pile, a lower wing plate pile and a web pile through a mortise and tenon joint structure, and the flexural rigidity is 3.69 times and 4.15 times that of a square pile and a round pile respectively. During construction, the upper wing plate piles are firstly driven to penetrate through the sliding surface, then the unit piles are formed through mortise and tenon connection of the web piles and the lower wing plate piles, and the continuous underground diaphragm wall is formed by repeatedly driving and utilizing the side mortise and tenon structures of the adjacent pile bodies. Water-absorbent resin (the water absorption rate is larger than or equal to 80 g / g) is smeared at the mortise and tenon joint, the functions of sealing and reducing the pore water pressure are achieved, and the slope stability is improved. The anti-slide pile is suitable for landslide reinforcement of soft soil and complex stratums, modular expansion construction can be achieved, adaptability is high, and the mechanical property and engineering applicability of the anti-slide pile are effectively improved.

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.

The invention discloses a fixed wing ejection type unmanned aerial vehicle launching device and a design method thereof, and belongs to the field of unmanned aerial vehicles. The launching device comprises an ejection frame sliding rail, an ejection support, a supporting assembly, an ejection support and a launching rib. The two ejection supports are installed on the ejection frame sliding rails in a sliding mode. Supporting assemblies are fixedly installed at the top ends of the ejection supports and used for supporting and limiting the ejection supports. The two ejection supports are symmetrically installed below the wings on the two sides, correspond to the two launching ribs symmetrically installed in the wings on the two sides in a one-to-one mode and are fixedly connected with the launching ribs. And the bottom surface of the launching rib is glued and fixed with the inner wall of the lower airfoil skin. The end, facing the rear edge of the wing, of the ejection support is in separable limiting fit with the supporting assembly, so that the ejection support can only move in the ejection direction. According to the device, a long-strip-shaped supporting mode is adopted, the stress path is researched, so that the force transmission path is reasonable, loads are evenly distributed, the stress concentration phenomenon is avoided, and the design research of the force transmission path provides actual technical guidance for engineering practice.

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.

The utility model belongs to the technical field of pull heads, and particularly relates to a detachable pull head assembly which comprises a lower wing plate, an upper wing plate and a cap arranged on the upper wing plate, a pull piece is arranged on the cap, an assembly convenient to disassemble is arranged between the lower wing plate and the upper wing plate, an insertion hole is formed in the lower wing plate, an insertion column is fixed to the bottom of the upper wing plate, and the insertion column is fixed to the bottom of the upper wing plate. When the pull rod is pulled outwards, the pull rod drives the limiting sliding disc to slide in the limiting sliding cavity and compresses the spring, the limiting head moves along with the limiting sliding disc, at the moment, the limiting head is separated from the limiting hole, limiting between the limiting head and the inserting column is relieved, then the inserting column is pulled outwards and pulled out of the inserting hole, and disassembling of the pull head is completed. When the puller is damaged, the puller does not need to be integrally replaced, only damaged parts need to be independently replaced, and the disassembly process is convenient and fast.

The embodiment of the invention relates to the technical field of aerodynamic layout of supersonic aircrafts, and discloses a two-dimensional rhombic double-wing aerodynamic force prediction method, device and equipment and a medium. According to the emission position of the oblique shock wave, the aerodynamic parameters of the oblique shock wave, the emission position of the expansion wave, the aerodynamic parameters of the expansion wave and a predetermined first slip line, predicting aerodynamic force between the two rhombic wings; when the two expansion waves intersect, the aerodynamic force between the rhombic double wings is predicted according to the flow field properties of the two expansion waves before intersection and a predetermined second slip line; wherein the expansion wave is generated by the midpoint of the lower wing in the two-dimensional rhombic double wings; the intersected expansion wave is a fan-shaped area, and the Prandtt-Mayer expansion fan of the intersected expansion wave is emitted from the vertex of the fan-shaped area. According to the method, the complex flow field characteristics under double-wing flow can be accurately described, and the precision and efficiency of aerodynamic force prediction are improved.

The invention relates to a subframe assembly (1) for an electrified motor vehicle, the subframe assembly (1) comprising a side member (14) forming a hollow profile housing a side member reinforcement (12), a battery support (13) for housing an electric traction battery, the battery support (13) being fixed rigidly to the side member reinforcement (12), and at least one reinforcement plate (11) located opposite the battery support (13) and housed between the side member reinforcement (12) and a lower flange (141) of the side member (14). The reinforcement plate (11) is configured to allow attachment through it of the side member reinforcement (12) to the lower flange (141) of the side member (14) on one side, and, on the other side, of the battery support (13). Figure to be published with the abbreviation: Fig. 3

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.