26 results about "Tail structure" patented technology

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.

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.

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.

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.

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.

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.

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.

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 application provides a bionic fish multi-degree-of-freedom flexible tail structure, which comprises a driving assembly, a shape maintaining shell assembly and a flexible skin. The driving assembly is composed of at least two integrated double-degree-of-freedom motors in series. The output shaft of the transverse rotation degree-of-freedom end of the front motor is connected with the output shaft of the flapping degree-of-freedom end of the rear motor through a connecting piece. The output shaft of the flapping degree-of-freedom end of the frontmost motor is rotatably connected with the rear end surface support plate of the trunk unit through a trunk unit connecting piece. The output shaft of the transverse rotation degree-of-freedom end of the rearmost motor is rotatably connected with a tail fin skeleton through a tail fin connecting piece. The motors and the connecting piece are provided with connecting interfaces of the shape maintaining shell for connecting and fixing the shape maintaining shell at corresponding positions. The flexible skin is sleeved outside the shape maintaining shell assembly, and the internal contour of the flexible skin is complementary to the shape of the shape maintaining shell assembly. The application has the advantages of compact structure, large number of degrees of freedom, small movement resistance and mute characteristics.

The application discloses a tail wing device fusing efficient heat dissipation and a coaxial helicopter with the same, and relates to the technical field of helicopters. The tail wing device comprises a heat dissipation horizontal tail structure, which comprises a mounting frame and a heat dissipation fin group. The middle part of the mounting frame is provided with a hollow area penetrating through the top surface and the bottom surface. The mounting frame is provided with a cooling liquid inlet and a cooling liquid outlet. The heat dissipation fin group is distributed in the hollow area and fixed on the mounting frame. A plurality of ventilation and heat dissipation gaps penetrating through the top surface and the bottom surface are formed in the heat dissipation fin group. The inlet and the outlet of the cooling liquid flow channel in the heat dissipation fin group are in one-to-one correspondence with the cooling liquid outlet and the cooling liquid inlet. Left and right vertical tails are symmetrically arranged on the left and right sides of the mounting frame. The application can realize the dual goals of enhancing the heading / longitudinal attitude stability control ability and greatly improving the heat dissipation efficiency.

The application provides a bonding method of a helicopter tail structure, which separates a diagonal beam structure or a duct structure according to a process separation surface of a framework and a skin, determines a bonding reference of the structure, and sequentially designs a pre-assembly process and a bonding process according to an inside-out sequence after the reference is determined. All framework parts (which can contain a single-sided skin) are bonded for the first time, the skin is bonded for the second time, the structure is closed, a closed cavity structure is formed, an elastic pin is used for pressing between the bonding surfaces of the bonded parts, the pressing force acts on the bonding surface, and stress is avoided between the tooling and the parts and between the parts and the parts during the pressing process. No stress release occurs during the pressing process, so no bonding deformation occurs after bonding. During the elastic pin pressing process, the pressure and the softening thickness of the adhesive film change, the adaptive continuous pressing is achieved, and the bridging phenomenon is avoided.

This utility model provides an indoor roller blind head assembly with a receiving cavity, belonging to the field of roller blind accessories. It includes a head structure or a tail structure, which includes a sleeve inserted into the roller blind shaft. The sleeve has a receiving cavity for storing the roller blind edging on the side away from the roller blind shaft. The width of the receiving cavity is adapted to the width of the curtain edging, and the depth of the receiving cavity is adapted to the thickness of the roller blind edging. This allows the bulges formed by the edging accumulation when the curtain is rolled up to be stored in the receiving cavity, avoiding the formation of a shape with protruding ends. This not only improves the aesthetics of the roller blind but also avoids jamming or squeezing caused by the bulges, thus improving the user experience and service life of the roller blind.

1. Name of the product in this design: Spinning machine tail section. 2. Application of this design: This design is used for the tail structure of a spinning machine. 3. The key design feature of this product is its shape. 4. The image or photograph that best illustrates the design's key points: 3D view 1.

The utility model discloses a full-motion horizontal tail V-tail double-tail boom layout unmanned aerial vehicle, which belongs to the technical field of unmanned aerial vehicles and comprises a vehicle body, wings are respectively connected to two sides of the vehicle body, backward tail supporting rods are connected and mounted on the rear sides of the two wings, and a fixed horizontal tail is connected between the tail ends of the two tail supporting rods; the outer side of the tail end of the tail supporting rod is provided with a full-motion horizontal tail capable of being rotationally adjusted, and the upper portion of the tail supporting rod is connected with a V tail forming an obtuse angle with the fixed horizontal tail. A double-tail supporting rod structure is adopted, good structural support is provided, the overall stability is improved, a larger wingspan design space is provided, and high adaptability and flexibility are achieved; a V tail is matched with a rotationally adjustable full-motion horizontal tail structure, so that the unmanned aerial vehicle has higher redundancy in control, pitching motion of the unmanned aerial vehicle is effectively controlled, jolt and vibration caused by airflow disturbance are reduced, and flight stability is improved. The overall structure is simple, using is flexible, and practicability is good.

The utility model discloses a motorcycle subframe tail structure, which belongs to the technical field of motorcycles, and comprises two tail side beams, the two tail side beams are symmetrically distributed, a support plate is fixedly connected between the two tail side beams, a backseat connecting hole group is arranged on the support plate, the rear ends of the two tail side beams are fixedly connected with limit blocks, and the limit blocks are fixedly connected with the rear ends of the two tail side beams. An inserting opening is formed between each tail side beam and the corresponding limiting block, tail box supporting rods are slidably inserted into the two inserting openings, and rotating shafts are fixedly connected to the circumferential surfaces of the two tail box supporting rods; according to the tail structure of the auxiliary frame of the motorcycle, the rear seat supporting frame is composed of the two tail side beams and the supporting plate to support a rear seat of the motorcycle, the two tail box supporting rods and the two connecting plates form the tail box support to be used for installing a tail box of the motorcycle, and the tail box support is matched with the supporting mechanism and can be pulled out and assembled at any time in the rear seat supporting frame. When not in use, the device can be quickly stored, is convenient to carry, and is more convenient to install and use.

The utility model discloses a kind of stepped gill tooth multi-bleeding air jet narrow tail structures, static vane casing, crown static vane, sealing bush are sequentially arranged along the radial outer side to the inner side of rotor and mutually fixed, moving vane casing is fixed with static vane casing;Gill tooth sealing main part is set on the outer periphery of rotor and rotates integrally with rotor;Sealing bush, gill tooth sealing main part are set in the containing groove of rotor, along the direction of static vane casing to moving vane casing, the outer surface of gill tooth sealing main part is provided with multiple gill teeth of gradually reducing height, sealing bush is correspondingly provided with a section of stepped and the inner surface with the clearance of gill tooth;The bottom surface between the end wall of crown static vane and sealing bush is provided with cavity, the inner surface of sealing bush stepped is communicated with cavity, and the end wall of crown static vane is provided with multiple jet holes that communicate cavity and angle region.Jet hole is suppressed through gill tooth to reduce the leakage flow speed of compressor stage, and leakage flow is intercepted in gill tooth sealing structure, and angle region low-energy fluid accumulation is inhibited.