61 results about "Tail structure" patented technology

The invention discloses an aircraft tail structure and an aircraft, and relates to the technical field of aircraft tails, the aircraft tail structure comprises a first rigid shell assembly and a second rigid shell assembly, the front end of the first rigid shell assembly is arranged on an aircraft engine in the circumferential direction, and the rear end of the second rigid shell assembly is arranged on the aircraft engine in the circumferential direction; the front end of the second rigid shell assembly is arranged at the tail end of the first rigid shell assembly and connected with the tail end of the first rigid shell assembly in a sliding and sealing mode, and the tail end of the second rigid shell assembly is arranged on an engine jet pipe. The engine jet pipe drives the second rigid shell assembly to slide on the first rigid shell assembly, swing jet of the engine jet pipe is achieved through sliding sealing connection of the first rigid shell assembly and the second rigid shell assembly, and a flexible heat-proof skirt does not need to be used. And the rigid material is used, so that the bearing capacity of high external pressure and high axial direction and the long-time high-temperature scouring resistance are improved, and the device is not easy to damage.

The invention provides an ornithopter with multi-degree-of-freedom empennage collaborative movement and a control method.The ornithopter comprises a rack, empennage bodies and an empennage driving mechanism, each empennage body comprises an empennage support, a plurality of tail feather bodies, a traction rope guide wheel and a tail feather elastic rope, and one end of each tail feather body is sequentially hinged to one end of the empennage support; the number of the traction rope guide wheels is two, the traction rope guide wheels are arranged in the middle of the empennage support side by side, the tail feather elastic rope is sequentially connected to the multiple tail feather bodies, and the two tail feather bodies on the outermost side are each provided with a connecting part extending towards the other side of the hinged end. The empennage driving mechanism comprises an empennage connecting pipe assembly, a traction steering engine, a winding roll, a traction rope, an empennage torsion steering engine, an empennage deflection steering engine and an empennage pitching steering engine. According to the empennage structure, independent control or combined control of torsion, pitching, deflection and opening and closing actions can be achieved, and the problems that an existing ornithopter empennage mechanism is insufficient in motion freedom degree and lacks an efficient wing-empennage cooperative motion system are solved.

The utility model relates to the technical field of unmanned aerial vehicles, in particular to an unmanned eVTOL capable of being quickly mounted, dismounted and transported, which comprises a fuselage main body structure, a wing structure is arranged at the top of the fuselage main body structure, motor support arms are detachably connected to two sides of the bottom of the wing structure, and an empennage structure is arranged on the rear side of the fuselage main body structure. The fuselage main body structure comprises a framework, a skin is fixedly connected to the surface of the framework, cabin doors are detachably connected to the front side, the right side and the top of the fuselage main body structure, and the surfaces of the cabin doors are detachably connected with the skin. The wing has the advantages of being fast to disassemble, assemble and transport, according to the scheme, the whole wing is split in a three-section mode, the central wing and the fuselage main body are integrated and disassembled disorderly, the left outer wing and the right outer wing can be disassembled in the transportation process, space is saved, and transportation is convenient; separation of the outer wing and the central wing may be restricted by a latch.

The utility model belongs to the technical field of transportation, loading and unloading, and particularly relates to a hydraulic large tail plate structure for a low flat bed to conveniently transport, load and unload goods, which comprises a tail structure, a tail plate mechanism and a driving component, the tail structure comprises a tail, a lower hinged support, an upper hinged support and a limiting support block, the lower hinged support is arranged at the lower part of the tail end of the tail, and the tail plate mechanism is arranged on the tail end of the tail. An upper hinged support is arranged on the upper portion of the tail end of the vehicle tail, and a protruding limiting supporting block is arranged at the bottom of the upper hinged support. The tail plate mechanism is connected to the upper hinged support and comprises a supporting frame and a supporting plate, the supporting frame is hinged to the upper hinged support, and the supporting plate is arranged on the supporting frame; a driving component is hinged between the lower hinged support and the supporting frame, an integral hydraulic large tail plate is additionally arranged on the rear tail portion of the low flatbed transportation semitrailer, folding and unfolding of the tail plate are achieved through hydraulic driving operation, a supporting platform is provided through the tail plate, up-down loading and unloading are convenient, and labor and time are saved.

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.

An anti-bird strike reinforcement for the leading edge of an A-shaped aircraft tail, wherein a reinforcement support plate is fixed between the side panels on both sides of the anti-bird strike reinforcement, and the open end of the anti-bird strike reinforcement is fixedly connected to the leading edge auxiliary beam of the aircraft tail. The anti-bird strike reinforcement is located between the leading edge skin and the leading edge auxiliary beam in the leading edge of the aircraft tail, and is distributed between 0 and 100% of the wingspan along the span of the aircraft tail. The present invention improves the rigidity of the reinforcement support plate, effectively cuts the bird body, changes the frontal impact into a side impact, disperses the impact energy, and ensures the integrity of the tail structure and the aerodynamic shape of the tail. The present invention can ensure that the leading edge of the tail has sufficient strength and rigidity, thereby structurally reducing the structural mass of the tail, better meeting the lightweight requirements of the aircraft structural design, and resolving the contradiction between better anti-bird strike performance and lighter total tail mass in the tail structural design of a certain type of aircraft, providing a new solution for the future aircraft tail structural design.

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 relates to the technical field of shield tunneling, in particular to a shelling type shield tail structure which comprises a shield tail shell and a connecting shell, the connecting shell is connected to the outer surface of the shield tail shell in a sleeved mode, a fixing groove is formed in the surface of the shield tail shell, and a connecting groove and a clamping groove are formed in the face, making contact with the shield tail shell, of the connecting shell. Limiting grooves are formed in the two sides of the inner wall of the clamping groove, a circular groove is formed in the inner wall of the connecting groove, an abutting spring is fixedly connected to the inner side of the circular groove, an abutting plate is fixedly connected to the surface of the abutting spring, and a rotating rod is inserted into the inner side of the connecting shell. The shield tail shell is elastically connected with the rotating rod, under the abutting connection of the pressing block and the connecting groove, the effect of supporting the mounting position of the connecting shell on the shield tail shell is achieved, under the abutting contact of the pressing block and the fixing groove, slurry is prevented from permeating through a connecting gap between the rotating rod and the shield tail shell, and the using effect of the shield tail shell is improved.

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 invention discloses a V-shaped empennage and fuselage connecting structure and belongs to the technical field of aircraft design, the fuselage is of a square structure, six pairs of single-lug connectors in two rows are symmetrically arranged on the top of the fuselage, two V-shaped empennages comprise front beams, middle beams, rear beams, front beam connectors, rear beam connectors, ribs and empennage wallboards, the front beam connectors and the rear beam connectors are of inflection structures, and the front beam connectors and the rear beam connectors are of an inflection structure. The upper end of the middle beam is in lap joint with the front beam and the rear beam respectively, the lower end of the middle beam is connected with the single-lug connector on the fuselage, the middle beam is also of an inflection structure, the upper portion of the middle beam is parallel to the front beam and the rear beam, the lower portion of the middle beam is a connector connected with the single-lug connector on the fuselage, and the structure solves the assembly problem that the butt joint installation angle of the V-shaped empennage structure and the fuselage is large. In addition, the scale container loading efficiency is optimized, the empennage fuselage interface is simple, and the empennage fuselage interface is easy to install, the empennage load transfer efficiency is improved, and meanwhile the reliability of the load transfer system is remarkably 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.

An assembly is provided for a rotorcraft. This rotorcraft assembly includes a fuselage, a tail structure, an air system and a plurality of tail rotors. The tail structure is configured as or otherwise includes a tail boom. The tail boom projects longitudinally along a centerline out from the fuselage to a distal end. The air system includes an air flowpath. The air flowpath passes from the fuselage into the tail boom and extends longitudinally within the tail boom towards the distal end. The tail rotors are connected to the tail structure at the distal end.

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.

The invention relates to the technical field of bionic fishtail structures, and provides a bionic fishtail structure and an underwater bionic robot. The two ends of a fishbone structure are connected with a driving adapter and a tail fin structure correspondingly, the end, away from the fishbone structure, of the driving adapter is used for being connected with a driving device, and the fishbone structure is driven by the driving device to do reciprocating swing motion; the gradient variable stiffness structure covers the fishbone structure; the hyperelastic memory alloy wire penetrates through the fishbone structure, and the two ends of the hyperelastic memory alloy wire are connected with the driving adapter and the tail fin structure respectively. The driving adapter, the fishbone structure, the tail fin structure, the gradient variable stiffness structure and the hyperelastic memory alloy wire are matched with one another, elastic reset of the hyperelastic memory alloy wire can assist the driving device to enable the fishbone structure to passively swing, underwater stress changes are adapted, the simulation performance of the fishtail structure is improved, and the service life of the fishbone structure is prolonged. A fish body-tail fin propelling mode is simulated, the excellent flexible maneuvering performance is achieved, the noise level is lowered, and the concealment is improved.

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 utility model discloses a bionic frog jumping robot with a coiling trigger type structure. The bionic frog jumping robot comprises a trunk shell, a spring, a hollow shaft, a pull wire, a tail structure, front legs and rear legs. The upper end of the hollow shaft is slidably connected with the trunk shell, the lower end of the hollow shaft is fixedly connected with the tail structure, the hollow shaft is sleeved with the spring, a driving device and a rotating shaft are arranged in the trunk shell, a barbell sleeve is detachably and fixedly arranged on the tail structure, and the two ends of the pull wire are fixedly connected with the rotating shaft and the barbell sleeve respectively. The two ends of the rear legs are hinged to the trunk shell and the tail structure respectively, when the trunk shell compresses the spring to a certain degree, the barbell sleeve is separated from the tail structure, and the take-off action occurs at the moment when the pulling force of the pull wire disappears. According to the device, energy is effectively accumulated through the unique winding device, energy is instantly released through an automatic release mechanism, and efficient energy storage and powerful jumping are achieved; the device is simple in structure and easy to operate, and has good controllability and stability.

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 bidirectional telescopic connecting device comprises a soft cover shell, end blocking parts are arranged at the two ends of the soft cover shell, long-strip-shaped openings are formed in the two end blocking parts, a first connecting piece and a second connecting piece are arranged in the soft cover shell, a soft piece is connected between the tail end of the first connecting piece and the tail end of the second connecting piece, and the two ends of the first connecting piece and the tail end of the second connecting piece are provided with long-strip-shaped openings. The head end of the first connecting piece and the head end of the second connecting piece penetrate through the two long-strip-shaped openings respectively and stretch out of the soft cover shell. The first connecting piece and the second connecting piece are fixed at the head and the tail of the luggage case extension zipper, so that the head and tail structure of the extension zipper can be shielded, and the overall aesthetic feeling of the luggage case is improved; when the extension zipper is unzipped, the first connecting piece and the second connecting piece can stretch out through the long-strip-shaped opening to achieve two-way extension, after the extension zipper is completely unzipped, the folding part in the extension zipper is completely unfolded, at the moment, the first connecting piece and the second connecting piece are pulled through the soft piece, and therefore the structural strength of the head and the tail of the extension zipper is enhanced; and the damage caused by excessive stress is avoided.

The invention relates to the technical field of unmanned helicopter transportation equipment, in particular to an unmanned helicopter tail fixing device and a transportation cabin, the unmanned helicopter tail fixing device comprises a mounting base, a lifting assembly, a clamping assembly and a damping assembly, the lifting assembly is connected to the mounting base, and the clamping assembly is upwards connected to the lifting assembly; according to the fixing device for the tail of the unmanned helicopter, the fixing device for the tail of the unmanned helicopter is arranged, then the lifting assembly on the fixing device is matched with the clamping assembly to fix the tail of the unmanned helicopter, and meanwhile, vertical and horizontal buffering and damping of the damping assembly are matched, so that the tail of the unmanned helicopter is fixed; the tail structure of the unmanned helicopter is rapidly, reliably and safely fixed, and the problem that the tail of the unmanned helicopter is prone to being damaged due to the fact that the tail of the unmanned helicopter is subjected to extra transportation loads along with vehicle jolting is solved.

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.