39 results about "Tail structure" patented technology

The embodiment of the present application provides a handwriting pen and an electronic device assembly, and relates to the technical field of terminals. The handwriting pen comprises a pen body assembly and a sliding cover assembly. The pen body assembly comprises a head structure section and a tail structure section, the head structure section and the tail structure section are respectively located at two ends of the axial direction of the pen body assembly, and the tail structure section has a grounding portion. The sliding cover assembly is arranged outside the tail structure section, the sliding cover assembly comprises a metal structure, the sliding cover assembly is slidably arranged on the tail structure section through the metal structure, the sliding cover assembly can slide along the axial direction of the pen body assembly between an opening position away from the head structure section and a closing position close to the head structure section, and the metal structure has an electrical connection portion. When the sliding cover assembly is in the closing position, the metal structure is electrically connected with the grounding portion through the electrical connection portion. In this way, the sliding cover assembly of the handwriting pen has high strength and long service life, and the handwriting pen has low failure rate.

The invention discloses a salmonella virulent bacteriophage vBSalPNW15 and application thereof, the bacteriophage is separated from farm sewage, belongs to a long-tail bacteriophage family, has a regular icosahedron head and a long-tail structure, and keeps stable under the conditions that the pH is 4-13 and the temperature is 40-60 DEG C. Genomic analysis shows that the kit does not contain virulence genes and drug-resistant genes and is good in safety. The bacteriophage and cinnamyl aldehyde are combined to be used for preventing and treating salmonella infection, both the bacteriophage and cinnamyl aldehyde show a remarkable synergistic bacteriostatic effect (FICI = 0.5) in vitro and in vivo, and the bacteriophage and cinnamyl aldehyde can effectively inhibit growth of multi-drug-resistant salmonella, remove biological membranes, relieve tissue pathological damage and remarkably improve the survival rate of chicks. The invention provides a safe and efficient antibiotic replacement scheme for preventing and treating salmonella infection, and is suitable for the fields of livestock and poultry breeding and food safety.

The utility model discloses a fuselage and horizontal tail integrated structure for an eVTOL aircraft, and relates to the technical field of aircrafts. The integrated structure comprises a rear fuselage structure and a horizontal tail structure; the rear fuselage structure comprises a rear fuselage upper longitudinal beam, a rear fuselage lower longitudinal beam, a rear fuselage frame and a rear fuselage skin, the rear fuselage frame is welded between the rear fuselage upper longitudinal beam and the rear fuselage lower longitudinal beam, and the rear fuselage skin is connected with the rear fuselage frame through bolts; the horizontal tail structure comprises a horizontal tail front beam, a horizontal tail rear beam, horizontal tail box section ribs and a horizontal tail skin, a plurality of horizontal tail box section ribs are uniformly fixed between the horizontal tail front beam and the horizontal tail rear beam, and each horizontal tail box section rib is fixedly connected with the horizontal tail skin; the rear fuselage upper longitudinal beam is in glue joint with the horizontal tail front beam, the rear fuselage upper longitudinal beam is in glue riveting with the horizontal tail front beam through a metal connector, and the rear fuselage skin is in lap joint with the horizontal tail skin. According to the fuselage and horizontal tail integrated structure, the number of parts can be reduced, the assembly working hours can be shortened, the weight of an aircraft can be reduced, and the design of the aircraft is more reasonable.

An aircraft structure includes a fuselage, a tail structure, a hinge support structure, and at least one internal actuator. The tail structure is pivotally attached to the fuselage and includes a tailcone and horizontal stabilizers fixed to the tailcone. Each of the horizontal stabilizers have a stabilizer leading edge and a stabilizer trailing edge and extend in opposite directions from the tailcone, forming an H-tail or a U-tail configuration. The hinge support structure is fixed at least partially within the fuselage, pivotally coupling the fuselage and the tail structure. The at least one internal actuator actuates the tail structure, rotating the stabilizer leading edge up and down relative to the fuselage, thereby trimming the horizontal stabilizers for aircraft stabilization.

The utility model relates to the technical field of automobile accessories, and discloses a spoiler structure and an automobile, the spoiler structure comprises an inner plate and an outer plate which are connected, the inner plate is used for being connected with an automobile body of the automobile, and the outer plate is located on the side, away from the automobile body, of the inner plate; the outer plate comprises a front end part, a middle part and a rear end part which are in smooth transition connection in sequence; the front end part is inclined towards the direction close to the inner plate; the middle part is of a curved-surface-shaped structure which is sunken towards the direction close to the inner plate; the rear end is of a duck tail structure and comprises a first flow guide face and a second flow guide face which are smoothly connected, the first flow guide face is connected with the middle, extends in the direction away from the middle and gradually tilts in the direction away from the inner plate, and the second flow guide face is connected to the end, away from the middle, of the first flow guide face and inclines in the direction close to the inner plate. According to the tail wing structure and the automobile, downward pressure can be provided for the automobile when the automobile runs at a low speed or the tail wing structure is not started, and the operation stability of the automobile is improved.

The utility model discloses a fixed wing aircraft vertical tail structure, including fuselage and vertical tail rudder surface, and be used for the hinge male seat of connecting between the fuselage with the vertical tail rudder surface, the top of vertical tail rudder surface is equipped with rudder surface top protection part, the top of fuselage and the side close to rudder surface top protection part are equipped with vertical tail protection part, vertical tail protection part with rudder surface top protection part is connected through screw no.

This invention discloses a multifunctional biomimetic robot for field exploration, comprising a body structure, a variable-radius slewing wheel-leg mechanism, a variable-stiffness connection mechanism, a flexible tail mechanism, and a front-end actuator. The body structure includes multiple base plates; the variable-stiffness connection mechanism includes multiple variable-stiffness connection components, with adjacent base plates connected by these components; the variable-radius slewing wheel-leg mechanism includes multiple variable-radius slewing wheel-leg components, each capable of both wheel-based and leg-based movement; the flexible tail mechanism possesses degrees of freedom for circumferential rotation and vertical bending; and the front-end actuator has obstacle removal and / or data acquisition functions. This design achieves high movement speed on flat terrain while simultaneously meeting the requirement for high obstacle-crossing capability on complex terrain. Furthermore, the body stiffness can be automatically adjusted, and the tail structure exhibits high controllability and flexibility.

A tail structure of a glass reinforced plastic pipe winding mold relates to the technical field of glass reinforced plastic pipe molds and comprises a tail shaft, the interior of the tail shaft is of a hollow structure, a step is arranged in the tail shaft, a hexagonal screw is arranged on the step, one end of the hexagonal screw extends out of the tail shaft, the other end of the hexagonal screw is sleeved with a spring, and the other end of the spring is sleeved on an ejector pin. The other end of the ejector pin extends out of the tail shaft, the ejector pin is sleeved with a gasket and a clamping spring, the gasket and the clamping spring are both arranged in the tail shaft, a plurality of round holes are formed in the outer wall of the tail shaft in the circumferential direction of the tail shaft at equal intervals, balls are arranged in the round holes, and the balls make contact with the ejector pin. According to the utility model, the ball can be ejected out by arranging the movable ejector pin, and the mold is locked by matching with the tensioning device, so that the problems that the mold is unstable and the pin is easy to fall off when the mold is fixed by using the pin traditionally are solved, the product stability is ensured, and the product quality is improved.

The application discloses a simulation device and detection method for the influence of tail structure deformation on shaft system vibration, which comprises a base, a multi-directional thrust applying device, a tail shaft, a thrust shaft, a thrust bearing and a motor which are sequentially connected on the base; a counterweight mechanism for simulating the gravity of a propeller is arranged on one end of the tail shaft close to the multi-directional thrust applying device; the thrust of the propeller is simulated through the multi-directional thrust applying device; the position change of the rear thrust bearing is changed through the height adjusting mechanism; in different shaft line states, the rotational speed of the shaft system is adjusted to measure preset data, and the bearing displacement value of the shaft system vibration meeting the preset requirements is obtained. The initial offset value and the flange offset value are obtained, and the pre-deformation value of the flange centering is obtained; the pre-deformation value is verified, and the data meeting the preset requirements are taken as the subsequent shaft system centering and installation process parameters. The shaft system vibration after launching can meet the design and specification requirements, the occurrence of abnormal vibration noise problems is reduced, and the ship delivery period is ensured.

The application discloses a novel bionic tail structure, which comprises a tail body, a fuselage and a gravity center offset device; the gravity center offset device is arranged on the fuselage; the tail body comprises a tail driving device and a tail actuator; the tail driving device comprises a tail mounting frame, a first driving mechanism for driving the tail actuator to change a shape and a second driving mechanism for driving the tail actuator to swing; the tail mounting frame is arranged at a tail portion of the fuselage; and the first driving mechanism and the second driving mechanism are both arranged on the tail mounting frame. The whole structure is compact, flexible and good in flexibility, and the gravity center offset device can effectively support the robot to complete wall surface transition or obstacle crossing.

According to the shield tail sealing simulation test device and test method, a shield tail structure is truly restored, and compared with an existing reduced scale model test device, the shield tail sealing simulation test device and test method are more suitable for actual engineering. The shield tail brush spacing, the number of sealing cavities and the shield tail gap can be changed according to parameters required by different projects by flexibly adjusting the structure of the device, shield tail structures of different projects are subjected to simulation reduction, engineering adaptability inspection of shield tail sealing grease is carried out, a basis is provided for model selection of shield tail sealing grease in shield tunnel construction, and the construction efficiency is improved. The problem that in current tunnel construction, type selection of shield tail sealing grease mainly depends on engineering experience is solved.

The present application relates to the field of folding unmanned aerial vehicle structure, especially to a folding cruise missile with redundant locking and interference prevention wing unfolding structure, comprising a fuselage, a front wing structure, a rear wing structure, a vertical tail structure, a power system and an on-board device; the front wing structure is connected with the fuselage through a threaded nut, the rear wing structure is connected with the fuselage through a bearing seat cooperating with bolts, the vertical tail structure is connected with the fuselage through bolts, and the on-board device is fixed in the fuselage through bolts or adhesive bonding; before the cruise missile is launched, the wings are folded and attached to the surface of the fuselage, after the launch, the front wing structure and the rear wing structure are unfolded simultaneously until locked, when the rear wing structure is unfolded to the position, the vertical tail structure starts to unfold until locked. The present application has a double-redundant wing locking structure, and has a structure for preventing the front and rear wing structures and the vertical tail structure from interfering with each other during unfolding, which can effectively improve the success rate and stability of the folding cruise missile in the cylindrical launching, and has the advantages of simple and compact structure.

This invention provides a design method, system, and application for adding a stern roller to a ship. The method includes using the bulkhead constituting the stern region as a cutting reference plane; determining a cutting position on the side of the cutting reference plane facing the stern; removing a section of hull structure between the cutting position and the stern to form a cut section; constructing a stern structure based on the stern region's shape data and the stern roller's design parameters; the stern structure includes a base for mounting the stern roller; the shape of the stern structure matches the shape of the stern roller, and the curvature of the stern structure at the cut section is consistent with that of the stern region; connecting the stern structure to the stern region at the cut section; and installing the stern roller onto the base. This invention can control the scope of modification while ensuring the integrity and structural strength of the original ship's main structure and enhancing the ship's towing capability.

The invention discloses a supersonic aircraft and an aircraft V-tail structure thereof, and relates to the technical field of aircrafts, the aircraft V-tail structure comprises a V-tail main body rotatably connected with an aircraft body and a V-tail rotating mechanism used for driving the V-tail main body to rotate relative to the aircraft body, and in a take-off stage and a low-speed stage, the V-tail rotating mechanism controls the V-tail main body to be located at an unfolding position; the maneuverability of the aircraft is improved; in the supersonic cruising stage, the V-tail rotating mechanism controls the V-tail body to be located at the horizontal folding position, and the V-tail body and the main wings of the fuselage are located in the same plane so that the propagation direction of shock waves can be dispersed. Due to the fact that the V-shaped tail body can rotate relative to the aircraft body, the V-shaped tail body is located at the unfolding position in the take-off stage and the low-speed stage, the maneuverability of the aircraft can be improved, and the flight safety and comfort are improved; in the supersonic cruise stage, the V tail body is located at the horizontal unfolding position, shock waves are shielded, reflected or refracted through the V tail, the path of tail airflow is changed, and the sound explosion intensity is remarkably reduced.

The invention discloses a multi-purpose protection device for a water jet propulsion system and a design method of the multi-purpose protection device. The multi-purpose protection device comprises a protection platform and a connecting assembly. The protection platform is horizontally arranged above the water jet propulsion system, and the outer edge of the protection platform completely covers all water jet propulsion devices of the water jet propulsion system. The multiple sets of connecting assemblies are arranged in the length direction of the protection platform at intervals. The protection platform is fixedly connected with a tail sealing plate at the rear end of the main ship body through a connecting assembly. The water jet propulsion system has the beneficial effects that the full-covering type protection platform is arranged above the water jet propulsion system, direct impact of external objects on the water jet propulsion device can be effectively blocked, damage to the water jet propulsion device due to accidental collision or impact is avoided, meanwhile, overall shielding protection is formed on the water jet propulsion system, and the water jet propulsion system is protected. And the equipment operation reliability and the ship tail structure safety are obviously improved.

The utility model discloses a fixing tool for an integrated busbar, which comprises a head structural block, a tail structural block and a plurality of middle structural blocks, the middle structural blocks can be connected end to end to form a whole, the tool adopts a structural connection design, and is combined with a connecting rod with a groove and the structural blocks for accurate positioning, so that stable butt joint among all parts is realized, and the working efficiency is improved. Compared with the prior art, poor contact or looseness caused by improper connection is avoided, meanwhile, the tool optimizes the insertion and extraction process of the tool through the connecting rod with the groove, installation personnel can quickly and easily assemble and disassemble the tool, the working efficiency is greatly improved, the structural design of the tool has very high universality, and the tool is suitable for popularization and application. The tool can adapt to various integrated busbars of different models, and the tool can flexibly adapt to the busbars of different sizes and shapes due to the adaptive design of the head structure block, the tail structure block and the middle structure block.

This application relates to the field of cable terminal design technology, specifically providing an optimized design method for the tail structure of a cable terminal. A multiphysics coupling model of the DC cable terminal based on electro-thermal-fluid fields is established using COMSOL simulation software. Based on this model, the tail structure of the cable terminal is optimized, including the restoration of the metal sheath and the optimization of heat dissipation windows on the conical support. Then, simulation analysis is performed on the natural convection velocity, air temperature distribution, and mechanical stress distribution in the tail pipe before and after the optimization. This simulation analysis verifies the heat dissipation effect and mechanical stress distribution after the optimized tail structure design, ensuring that the cable terminal achieves optimal heat dissipation in various application scenarios. This method provides a theoretical basis for tail structure design, enabling the design of cable terminals with good heat dissipation efficiency while considering installation convenience and mechanical safety during actual operation.

A method is provided of controlling the functionality of a substrate containing at least one nanopore. The method includes the steps of: introducing to the substrate a solution containing a molecular construct having a body formation which defines an aperture and a tail formation extending from the body formation; applying a potential difference across the substrate to thread the tail formation through the nanopore thereby docking the molecular construct to the substrate with the aperture aligned with the nanopore such that the sleeve formation lines the nanopore; and expelling the molecular construct from the substrate by varying the potential difference. A DNA construct for docking to a substrate having a nanopore is also provided, the construct having a body formation which defines an aperture, and a tail formation extending from the body formation for threading through the nanopore to dock the construct to the substrate with the aperture and nanopore in alignment.

The utility model discloses a multi-degree-of-freedom flapping-wing glider with an aerodynamic shape. The multi-degree-of-freedom flapping-wing glider comprises a bilaterally symmetrical fuselage assembly, a flapping-wing assembly and an empennage assembly capable of being quickly replaced. The fuselage assembly comprises a frame unit and two flapping wing adjusting units, each flapping wing assembly comprises a flapping wing frame, a composite turbulent flow structure and a turbulent flow plate, and the empennage assembly is of a triangular, trapezoidal or V-shaped structure and is connected with the frame unit through an empennage connecting piece. A streamline shell is arranged at the front end of the frame unit, two pitch angle adjusting motors are arranged in the middle, and an empennage steering engine is arranged at the tail. The flapping wing frame is of a structure with a thick front part and a thin tail part and is coated with a film wing; the wing tip of the flapping wing frame is provided with a composite spoiler structure, and the front part is provided with a strip-shaped spoiler, so that trailing vortex is effectively inhibited, airflow separation is delayed, and the lift-drag ratio is increased. The glider has the advantages of high aerodynamic efficiency, excellent structural strength, multi-degree-of-freedom accurate control and batch production consistency.

An integrated or detachable tail structure is provided for enhancing retention of an associated earpiece within the ear of a user. In one example, an earpiece comprises a main body and a tail structure. The main body contains one or more electronic components. The tail structure is coupled to the main body, has a semi-circular shape, and when compressed and placed within an outer ear of the user, engages at least three distinct anatomical features of the outer ear, including the antitragus, the antihelix, and the helical crus.

The utility model provides an aircraft tail structure assembling device. The embodiment of the utility model provides an aircraft tail structure assembling device which is used for carrying and assembling a tail structure of an aircraft and comprises a first platform, a clamping assembly and a moving assembly. The clamping assembly is arranged on the first platform, the clamping assembly comprises two clamping pieces arranged in the first direction in a spaced mode, and the two clamping pieces can clamp the tail structure; the clamping piece can move in the second direction relative to the first platform so as to adjust the height of the clamped tail structure, the clamping piece can rotate relative to the first platform so as to adjust the posture of the clamped tail structure, and the second direction intersects with the first direction. The moving assembly can drive the first platform to move in the space.

This invention relates to a probe tail structure with elastic contact points, as well as a probe and a probe clip. The key feature is that at least one pair of elastic flaps are provided on the periphery of the probe tail. These elastic flaps are inclined and open towards the contact point, with the widest point of each flap being larger than the width of the probe's mounting hole in its free state. When the probe is assembled and in use, the elastic flaps are constrained by the hole wall and undergo inward elastic deformation, thereby continuously applying an elastic positive pressure to the contact point from the probe tail. This invention replaces the hard clip at the probe tail with elastic flaps, achieving elastic contact between the probe tail and the space converter contact point. This ensures the probe tail remains in contact with the space converter contact point at all times, avoiding the wear and metal adhesion problems caused by repeated contact and separation between the probe tail and the contact point in traditional structures.

1. The name of the design product: lead bait tail. 2. The use of the design product: bait tail structure for fishing. 3. The design points of the design product: in shape. 4. The picture or photo that best indicates the design points: perspective view 1.

The utility model discloses a split tail-free zipper tail structure and a zipper, which belong to the technical field of zippers and comprise a square component and a bolt component which are matched with each other. An elastic clamping block with deformability is arranged in the square block component, and an abutting notch matched with the elastic clamping block is formed in the front end of the plug pin component. When the plug pin component is inserted into the square block component, the elastic clamping block generates elastic deformation through the guide inclined face until the abutting notch reaches the locking position of the elastic clamping block, the elastic clamping block recovers deformation and forms irreversible mechanical interlocking with the abutting notch, and when the elastic clamping block is subjected to external force exceeding a threshold value, the elastic clamping block and the abutting notch are locked. And when the elastic clamping block is broken, the tail system structure is converted into an open tail state. According to the split type tail system structure, the transportation cost is greatly reduced, the assembly operation is convenient and fast due to the design of the plug pins and the guide inclined planes, and the contradiction between the transportation economy and the assembly reliability is effectively balanced.

This utility model relates to a tailstock structure for a billiard cue, comprising a tailstock body. The tailstock body has a first elongated hole extending along its length at its larger diameter end and a second elongated hole extending along its length at its smaller diameter end. Both the first and second elongated holes are blind holes. A first carbon fiber tube is inserted into the first elongated hole, abutting the bottom of the hole. A balsa wood post is inserted into the second elongated hole, with one end abutting the bottom of the hole and the other end flush with the opening of the second elongated hole. This utility model enables more uniform quality in the tailstock portion of the billiard cue, and provides better strength, stiffness, and feel.

The present application relates to the technical field of bionic robot, and particularly discloses a flexible crocodile tail structure driven by a swing rod, which comprises a swing rod, a driving mechanism, an active flexible tail section and a driven flexible tail section; the swing rod is provided with a plurality of elastic connecting members; the driving mechanism is connected with the swing rod; the active flexible tail section is connected with the swing rod through the plurality of elastic connecting members; the active flexible tail section is provided with a first elastic reset member; when the active flexible tail section swings, the first elastic reset member converts at least part of kinetic energy into elastic potential energy to provide kinetic energy for subsequent swing; the driven flexible tail section is provided with a second elastic reset member; when the driven flexible tail section swings, at least one second elastic reset member converts at least part of kinetic energy into elastic potential energy to provide kinetic energy for subsequent swing; the flexible crocodile tail structure driven by the swing rod can control the active flexible tail section and the driven flexible tail section by controlling swing of the swing rod only, and the control difficulty is low; high-frequency driving can be realized.

The invention provides a semi-annular empennage which is arranged at the tail part of an aircraft, and the semi-annular empennage starts from the lower part of a wing, extends upwards along an arc-shaped path to exceed the tail end of the tail part of the aircraft, and forms a semi-annular pneumatic structure in a vertical plane; the front edge of the semicircular empennage is in a sweepback structure, and the arc-shaped extending highest point of the semicircular empennage is located behind the tail end of the aircraft tail. The semi-annular empennage is of a semi-annular open structure and has the obvious weight reduction advantage. The semi-annular empennage extends upwards from the lower portion of the wing, high-speed airflow on the upper surface of the fuselage avoids a connecting area of the semi-annular empennage, and interference of the airflow on the aerodynamic configuration of the empennage is avoided. Due to the lower open structure and the sweepback structure exceeding the tail end of the aircraft tail, the situation that the aircraft tail structure shields control airflow is effectively avoided, and the problem that control surface control fails in a large attack angle state is solved; and meanwhile, the lower open structure also facilitates maintenance of the fuselage and the engine below the empennage.

This utility model discloses a tail structure for an air cushion conveyor. A tail movable section is inserted into the tail end of a fixed tail section. A tail cleaning section is connected to the tail end of the movable tail section, and a tail shaft section is connected to the tail end of the cleaning section. A tail roller is located within the tail shaft section. The lower return belt passes over the tail roller, reverses direction, and becomes the upper carrying belt. Rollers are located at the bottom of the movable tail section and the cleaning tail section, supported by a ground rail extending along the length of the conveyor. A tensioning frame is located behind the tail shaft section, and a steel wire rope is connected to the tail end of the tail shaft section. The steel wire rope passes over a pulley on the tensioning frame and is suspended from the top of a counterweight block. This air cushion conveyor's tail structure features a large tension adjustment range, minimal tension fluctuation impact, and automatic removal of accumulated material at the tail.

The invention discloses a shield tunneling machine shield tail opening deviation rectifying protection device and method.The shield tunneling machine shield tail opening deviation rectifying protection device comprises two reinforcing frames arranged on a shield tail, each reinforcing frame is arranged around an operation hole, a reinforcing supporting assembly is connected between the two reinforcing frames, and the reinforcing supporting assembly is connected with the shield tail opening deviation rectifying protection device. Each reinforcing frame is connected with a reinforcing vibration reduction assembly. According to the technical scheme, the reinforcing frames are arranged around the operation hole, the shield tail structure around the operation hole can be supported and reinforced, meanwhile, diffusion caused by structure weakening caused by the operation hole is prevented, meanwhile, the strength between the two reinforcing frames is improved through the reinforcing supporting assemblies, the overall stability is improved, and the service life of the shield tail structure is prolonged. And finally, vibration generated in shield tail opening deviation rectification and other construction processes is weakened through the reinforced vibration reduction assembly, and the safety of the shield tail is further guaranteed.

The invention provides a double-screw-shaft-driven bionic underwater robot based on magnetic linkage and an operation method, multiple groups of connecting columns are fixed on the tail end surface of a fish head structure, the tail parts of the connecting columns are connected with a fish tail structure through skeleton rods, and a first driving disc and a second driving disc are symmetrically and rotatably mounted on the tail end surface of the fish head structure; a first spiral line shaft is fixedly installed on the first driving disc, a second spiral line shaft is fixedly installed on the second driving disc, and the other end of the first spiral line shaft and the other end of the second spiral line shaft are rotationally installed on the inner side wall of the fishtail structure. A first link mechanism capable of swinging is movably arranged outside the first spiral line shaft, and one end of the head of the first link mechanism is hinged to the connecting column through a connecting rod; a second link mechanism capable of swinging is movably arranged outside the second spiral line shaft, and one end of the head of the second link mechanism is hinged to the connecting column through a connecting rod. The robot achieves efficient advancing and flexible steering through an innovative double-spiral-shaft cooperative driving mechanism, and is simple in structure, low in energy consumption, high in adaptability and suitable for the fields of ocean monitoring, underwater rescue and the like.