1474results about How to "Reduce structural weight" patented technology

An aircraft engine nacelle comprises: (a) an inlet lip and a skin having internal and external surfaces; (b) a noise abatement structure such as an acoustic panel located on the internal surface of the nacelle skin; and (c) an electrically powered de-icing system located on the external surface of the nacelle skin and in electrical connection to a power source. A method for de-icing and abating noise from an aircraft nacelle comprises: (a) providing a noise abatement structure such as an acoustic panel located on the internal surface of the nacelle skin; (b) providing an electrically powered de-icing system on the external surface of the nacelle skin; and (c) applying an electric current to the electrically powered de-icing system. The nacelle skin may be a perforated skin, and the de-icing system comprises a wire mesh bonded to the external surface of the perforated skin. The method and nacelle permit the use of noise abatement structures such as acoustic panels for noise reduction while advantageously avoiding detrimental high temperatures associated with conventional de-icing systems.

An offshore liquefied natural gas structure may receive, store, and process liquefied natural gas from carriers. A structure may be a gravity base structure. A structure may include a system of ballast storage areas, transfer equipment to offload liquefied natural gas from a carrier, docking equipment to allow direct mooring with carriers, platforms to elevate equipment, water intake systems to provide water to the structure, wave deflectors, and / or projections extending from a bottom of the structure. A portion of the structure may be composed of lightweight concrete. Pipelines may be coupled to the structure to export processed natural gas onshore. Living quarters, flare towers, and export line metering equipment may be included on the structure.

The invention discloses an exoskeleton rehabilitation robot for rehabilitation of a lower limb walking function and a control system and method thereof. The robot comprises a backrest, a hip joint power source, a hip joint component, a waist component, a thigh bar component, a knee joint power source, a knee joint component, a shank bar component, an ankle joint component and a foot pedal. According to the lower limb exoskeleton rehabilitation robot, a driving scheme is designed by utilizing a bionics principle, so that the initiative degree of freedom of the ankle joint is increased; through initiatively pulling the heel tendon muscles of the patients, the rehabilitation speed of the ankle joint function is improved; the waist component, a connection rod mechanism and the foot pedal adopt a carbon fiber composite material, so that the structure weights and volumes are lightened while the strength is kept; and a non-polar adjustable function is set for the waist width, thigh length and shank length, and flexible bandages are equipped, so that the wearing comfort level requirement of the users is satisfied to the greatest extent. The robot disclosed by the invention not only can be used as a tool for riding instead of walk for the patients with walking disability, but also can help the stroke patients to obtain walking ability again through initiative training.

An installation system designed specifically for thin reinforced natural stone panels used as exterior cladding, re-cladding, or over-cladding of buildings is comprised of a series of extruded aluminum shapes which, when properly applied to the back side of the thin reinforced stone panels, provide structural support for the thin panels and facilitate their installation and will also provide the means for the panels to be pre-assembled in order to obtain desired shapes or profiles and to be easily installed on the building. The series, or family, of extruded aluminum shapes are designed to mate or interlock to perform a variety of tasks such as perimeter frames, structural stiffeners, corner angle supports, interlocking sleeves, runner clips which facilitate attachment to various substrates of a building such as steel stud framing, aluminum curtain wall frames, brick or concrete walls or plywood sheathing.

The invention belongs to the technical field of aviation, relates to an unmanned aerial vehicle, and in particular relates to an unmanned logistics helicopter. The unmanned logistics helicopter comprises a body and rotor wings arranged on the body, wherein the body is of a cross-shaped structure; four body frames are fixed on the cross-shaped structure to support the body; central coaxial opposite-rotating double rotors are mounted at the central position of the body and are powered by an oil drive engine; four electric quad-rotor-wing supplying posture adjusting capacities are mounted at four tail ends of the cross-shaped structure and are powered by four brushless motors respectively; a cargo frame with a rectification shape is hung below the body through a cargo frame bracket. The unmanned logistics helicopter has the advantages of high endurance, safety, energy utilization and convenience in ground control, and can be put into use as an unmanned logistics aerial vehicle.

A technology for combining multiple layers of Ti-alloy sheet includes such steps as blanking, acid washing, baking, sticking protective film, coating welding inhibitor, removing said protective film, welding technological edges, installing die set, heating the forming apparatus, diffusion joining, pneumatic expansion shaping, cooling and removing said technological edges. Its product can be used for wing, fin, or blade.

The invention relates to the field of liquid cooling, and provides an integrated liquid-cooling heat dissipation case. The integrated liquid-cooling heat dissipation case comprises a case body, a circuit board and a liquid-cooling heat dissipation system. A closed space composed of a plurality of wall boards is formed in the case body. The circuit board is arranged in the case body, and one or more heat emission devices are arranged on the circuit board. A liquid storage groove is formed in the bottom of the case body and used for storing cooling liquid. The liquid-cooling heat dissipation system comprises a pipeline, a heat dissipation mechanism, a pumping mechanism and a spraying mechanism. The pumping mechanism is used for pumping the cooling liquid in the liquid storage groove into the pipeline, the spraying mechanism is connected to one end of the pipeline and used for spraying the cooling liquid into the case body or directly spraying the cooling liquid to the heat emission devices, and the heat dissipation mechanism is arranged at the position, in front of the spraying mechanism, of the pipeline and used for transferring heat of the cooling liquid to the outside of the case body. By the adoption of the integrated structural design, the integrated liquid-cooling heat dissipation case can be used in hostile environments and is convenient to carry, reasonable in design, light in weight, high in heat exchange capability and low in cost.

The invention relates to an efficient vertical takeoff and landing aircraft, and discloses an efficient vertical takeoff and landing fixed-wing unmanned aerial vehicle, which comprises a fuselage, a wing, a horizontal tail, a vertical tail, a control surface, a power unit, a tilting mechanism and an undercarriage. The tilting mechanism controls the tilting angle of the wing and the horizontal tail to realize the mutual conversion of a vertical takeoff and landing state and a flat flight state of the aircraft. A propeller power unit is arranged on each of the wing and the horizontal tail, a part of lift at the vertical takeoff and landing stage is provided by the wing propeller power unit, and the tail propeller power unit is responsible for the aircraft pitch balance adjustment; the power device installed on the wing is closed in the flat flight state, and the tail propeller power unit provides forward thrust in order to improve the efficiency of the aircraft in a cruising state. Compared with the existing vertical takeoff and landing fixed-wing unmanned aerial vehicle design scheme, the flight aerodynamic efficiency of the aircraft in the fixed-wing flat flight state is taken into account while the layout is simplified, and reliability and practicability are relatively high.

An aircraft, preferably a large capacity passenger aircraft with two passenger decks, has a double-T tail assembly arranged on its tail section. The double-T tail assembly includes a double fin and rudder assembly and a tailplane and elevator assembly, and provides a significant increase in the usable passenger cabin space in the tail section of the aircraft. The double fin and rudder assembly has a U-shaped structure and comprises two upright stabilizer fins connected to each other by a horizontal torsion box that fixedly extends crosswise through the fuselage tail section within the floor of a cabin deck. The tailplane and elevator assembly is pivotably mounted on the upper tips of the two upright stabilizer fins in a double-T arrangement.

The invention relates to the field of drone design, in particular to a solar drone. The solar drone comprises a front wing, a rear wing, power systems, an energy system, task load pods and the like, wherein the front wing and the rear wing are connected with each other through a left drone body and a right drone body; and the power systems, the energy system and the task load pods are disposed on the drone bodies. The solar drone has the advantages that the drone adopts a serial-wing double-drone-body layout, front wing stress features are improved favorably, and structural weight is reduced; a lifting layout is used, all lifting faces provide positive lifting force, the pneumatic efficiency of the pneumatic layout can be increased, and high lifting force and high lift-drag ratio are achieved easily; a full-motion operating face is used, the area of the lifting faces where solar cells can be laid is maximized, and a large amount of energy conversion is achieved; and further, the front wing is not provided with the operating face, influence on structural design can be eliminated, and structural weight is reduced.

The invention relates to a linked landing gear cabin door folding and unfolding device and belongs to the technical field of aircraft manufacturing. The linked landing gear cabin door folding and unfolding device comprises a landing gear, a rotation shaft I, a rotation shaft II, a rotation shaft III, a rotation shaft IV, an upper supporting rod, a rocker arm I, a rocker arm II, a rocker arm III, a lower supporting rod, a folding and unfolding actuation cylinder, a connection rod I, a connection rod II, a connection rod III, a goose-shaped rocker arm, a support column protection plate and an airplane wheel protection plate. By virtue of the linked landing gear cabin door folding and unfolding device, the cabin door folding and unfolding actuation system is simplified, so that the occupying space of the device in an airplane is reduced and the structure weight is reduced; by virtue of the design of a linked mechanism, the order of folding and unfolding the landing gear, the airplane wheel protection plate and the support column protection plate is ensured, the control logic is simplified and the reliability is improved; the airplane protection plate is closed when the landing gear is unfolded, the pneumatic resistance can be reduced; the takeoff and landing performances of the airplane are improved; the damage to the airplane, caused by entrance of foreign materials in a landing gear cabin, can be avoided.

The invention discloses a ray pectoral fin-imitated piezoelectric coupling propulsive mechanism. The ray pectoral fin-imitated piezoelectric coupling propulsive mechanism comprises a crankshaft, guide rods, a swinging block, a piezoelectric compound fin, a fish body pedestal, a crankshaft support, a driving motor, a battery pack and a main control panel, wherein the crankshaft is arranged on the crankshaft support; the swinging block comprises a pin shaft and a swinging block support; the pin shaft is arranged on the swinging block support; the crankshaft support and the swinging block support are fixedly arranged on the fish body pedestal; one of the guide rods is arranged between one end of the swinging block and the crankshaft; the driving motor and the crankshaft are connected through a gear; the piezoelectric compound fin is arranged at the other end of the swinging block; the battery pack can provide a direct current power source; the main control panel is electrically connected with the piezoelectric compound fin; the crankshaft is a four-turn crankshaft; the guide rod is arranged on each turning shaft of the four-turn crankshaft. The ray pectoral fin-imitated piezoelectric coupling propulsive mechanism can reduce the structural size, the weight of the fish body, and can realize chordwise fluctuation propulsion.

The invention provides an aircraft capable of vertically taking off and landing at high speed. The aircraft comprises an aircraft body, a main wing, a horizontal tail, a vertical tail and a power system, wherein the power system consists of a turbo-shaft engine, a lift fan and two propellers; the lift fan is connected to the middle of the front end of the aircraft body through a main beam; an openable and closable cover plate is arranged on the upper part of the lift fan; an openable and closable flow guide blade grid is arranged on the lower part of the lift fan; the two propellers are arranged at two ends of the horizontal tail through a rotation mechanism which penetrates through the horizontal tail; the rotation mechanism drives the two propellers to synchronously rotate. By virtue of the aircraft, the lift fan adopts a pair of propellers rotating oppositely; the reaction torque can be self-balanced without a complicated reaction torque device, so that the structural weight of the lift fan is reduced; the flow guide blade grid is arranged on the lower part of the lift fan and can rotate along a rotary shaft of the blade grid; the direction of lift force is changed by changing the direction of air flow through the deflection of the blade grid; vertical taking-off and landing lift force can be provided, and partial thrust force during transition can be provided.

A preparation method of a lattice-gradient foamed aluminium composite material comprises the adhesive bonding and combination of a lattice metal material (including a ripple structure and a pyramid structure) and a cut foamed aluminium to obtain a multifunctional gradient composite porous material. The invention realizes the combination of a lattice metal material and foamed aluminium, and obtains a lattice-gradient foamed aluminium composite structural material sandwich plate with a geometric gradient. The lattice metal-gradient foamed aluminium composite material sandwich plate has wide application prospects in fields of safety protection, traffic transportation, mechanical manufacturing, and military affairs, has very effective performance with respect to structure weight reduction, impact deformation improvement, magnetic shielding and the like, can bring into play its high strength, high rigidity and excellent damping performance especially in mechanical manufacturing industry, and also has low manufacturing cost.

A hollow microsphere masonry dedicated thermal insulation mortar and a dedicated surface mortar, especially a wall self-insulation system-matching hollow microsphere masonry dedicated thermal insulation mortar and a dedicated surface mortar, relate to a constuction energy-saving technology. The hollow microsphere masonry dedicated thermal insulation mortar comprises, by weight, 20-30% of special cement, 2-6% of coal ash, 20-35% of quartz sand, 5-8% of master batch, 35-45% of hollow microphere, and 3-6% of coarse whiting; and the hollow microsphere masonry dedicated surface mortar comprises, by weight, 28-40% of ordinary Portland cement, 3-6% of coal ash, 7-10% polymer, 40-55% of quartz sand, 10-16% of hollow microsphere, and 1-3% of coarse whiting. With a low heat conductivity coefficient, excellent thermal insulation effect, high compression strength, high bonding strength, low contractibility, environment-friendly and fire-proof properties and notable composite economic results, the wall self-insulation system-matching dedicated thermal insulation mortar and a dedicated surface mortar provided in the invention can be widely popularized and used in wall self-insulation system buildings.

The present invention relates to an integral vibration-isolating platform for space vehicle. It is characterized by that between the space vehicle connection end frame and freight rocket end frame an elastic element and a damping element are mounted.

An aircraft comprises: a fuselage; a front pair of wings; a rear pair of wings; and a pair of bodies, each body interconnecting, at a distance from the fuselage, the front and rear wings that are situated on the same side of the fuselage.

The invention discloses a culvert-type vertical take-off and landing lifting body unmanned aerial vehicle and relates to the technical field of vertical take-off and landing unmanned aerial vehicles.The culvert-type vertical take-off and landing lifting body unmanned aerial vehicle comprises a fuselage (1), lifting force rotor wings (2), a take-off and landing culvert (3), tilting-rotating thrustculverts (7) and tilting-rotating thrust rotor wings (8). The take-off and landing culvert (3) is composed of a through hole penetrating through the upper surface and the lower surface of the fuselage (1), and the lifting force rotor wings (2) are arranged in the take-off and landing culvert (3). The tilting-rotating thrust culverts (7) are hinged to the rear end of the fuselage (1) through tilting-rotating control mechanisms (9), the tilting-rotating control mechanisms (9) are configured to be capable of enabling the included angle between the axis of each tilting-rotating thrust culvert (7)and the axis of the fuselage (1) to be variable, and the tilting-rotating thrust rotor wings (8) are arranged in the tilting-rotating thrust culverts (7). Under the conditions that the vertical take-off and landing capacity of the unmanned aerial vehicle is maintained and the overall weight of the unmanned aerial vehicle is not excessively increased, the flight speed of the unmanned aerial vehicle is increased, the flight stability of the unmanned aerial vehicle is improved, the rotor wing exposed problem is avoided through the culverts, and the flight safety and the take-off and landing hovering efficiency are improved.

The invention discloses an under-actuated picking tail end executing device and an under-actuated picking tail end executing method. The device comprises a hand executing mechanism, a driving mechanism and a support seat assembly, wherein the hand executing mechanism is connected with the driving mechanism through the support seat assembly, the hand executing mechanism is of a three-claw type structure, three claws are uniformly distributed on the edge of the outer periphery of a palm, the bottom of each claw is arranged on the palm through corresponding hinging assemblies, the middle of each claw is provided with a pulley, each pulley is connected with the palm through a steel wire rope, and the bottom of the palm is connected with the driving mechanism through a press block. According to the method, a wire winding tube rotates for winding the steel wire rope, the steel wire rope drives the claws to approach to fruits and to tightly clamp the fruits, after the fruits are tightly clamped, the wire winding tube drives the fruits, the claws and the palm to simultaneously rotate relative to a motor support seat, and the torsion fruit separation is realized. The device and the method provided by the invention have the advantages that the under-actuated principle is applied, the effects of tightly clamping the fruits at first and then realizing the torsion fruit separation are realized, the control of the whole work process is simple, the efficiency is high, meanwhile, the clamping force of the claws on the fruits can be preferably controlled, and the fruit damage phenomenon is avoided.

The invention provides a modular micro-satellite platform configuration, which comprises a bottom plate, a top plate, a first side plate, a second side plate, a third side plate, a fourth side plate, a payload interface module, a satellite and rocket docking module, an altitude control and integration electronic module, a mechanical solar wing module, a propelling module, an integrated solar cell array module and a power supply and distribution module, wherein each side plate is connected with the bottom plate and the top plate respectively, and each of the second and fourth side plates has an embedded frame structure to form a box plate type configuration structure with embedded frames; the satellite and rocket docking module is connected with the bottom plate; the integrated solar cell array module is connected with the top plate; the payload interface module is connected with the first side plate; the altitude control and integration electronic module is connected to the embedded frame of the second side plate; the propelling module is connected with the third side plate; the power supply and distribution module is connected to the embedded frame of the fourth side plate; the mechanical solar wing module is connected to the second and fourth side plates respectively. The modular micro-satellite platform configuration has the advantages of light weight, high bearing capacity, short production cycle and high reliability and universality.

The invention belongs to the aircraft maintenance technology, and particularly relates to a repairing method for a honeycomb sandwich structure. The repairing method includes the steps that firstly, a placement layer and a honeycomb at the damaged portion are ground away, and a lower panel can not be damaged; secondly, a new honeycomb is prepared, and the surface of the honeycomb is glued; thirdly, the honeycomb is put in a cavity of the original honeycomb after being processed; and finally, placement layer replacement is carried out according to the original placement layer. Prepreg, glue film and glass cloth can not be spliced but in seamless butt joint. When the repaired structure is a surface concave as shown, the pneumatic outline can be repaired through filler. Raw materials are used for replacing the honeycomb and the placement layer, and the placement layer is repaired through a wet method. The strength design requirement is met, the structural weight after repairing is reduced, and good compatibility can be kept.

The invention discloses a three-dimensional three-phase photonic crystal structure based on the local resonance mechanism. The structure is formed through the steps that high-density cores are uniformly coated with elastic coating layers to form scattering units, and the scattering units are periodically arranged in a square array mode and connected with one another through low-density hard connecting bodies. A preparation method is characterized by comprising the steps that a two-dimensional periodic structure composed of the connecting bodies and the coating layers is prepared through a 3D printing technique based on photocuring molding, and after the high-density cores are arranged in the coating layers, the two-dimensional periodic structure is stacked layer by layer and assembled to form the complete three-dimensional periodic structure. The structure and the preparation method thereof have the advantages that low-frequency acoustic wide band gaps are obtained while the structure size and the structure weight are decreased, and by applying the 3D printing technique based on photocuring molding, the multi-phase complex three-dimensional photonic crystal structure is easier and more flexible to prepare.

The invention relates to a foamed aluminum-corrugated plate composite sandwich plate and a preparation method thereof. The method comprises the following steps: firstly, manufacturing a corrugated core body; welding the corrugated core body to a panel to form a corrugated plate; putting basal powder and a foaming agent in a mixing machine for uniform mixing, and then extruding the mixed powder into a primary blank; putting the blank in a mould for pressing, filling the inside of the corrugated plate with a pressed foaming prefabricated body, and putting the corrugated plate in an atmosphere furnace for foaming; and heating and keeping warm until the prefabricated body is expanded to form foamed aluminum with which pores of the corrugated plate are completely filled, and then cooling. By using a powder metallurgy method, the inside of lattice metal is foamed in situ to form the metallurgical-bonding foamed aluminum-corrugated plate composite sandwich plate. The excellent mechanical property of the lattice metal and the advantages of energy absorption, sound insulation, shock absorption and thermal insulation of the foamed aluminum are utilized, so that the multifunctional coupling is realized, and the structure and function integration material with the relatively excellent comprehensive performance is obtained. The bonding strength is effectively improved by virtue of metallurgical bonding, and the performance of the composite material is further improved.

The invention discloses a method of continuum structure non-probabilistic reliability topological optimization under the mixed constraints of displacements and stresses. According to the method, first, a continuum structure non-probabilistic reliability topological optimization model with weight lowering as an optimization objective is established; then, the vertex combination method is utilized to obtain upper and lower bounds of displacements and stresses, and thus corresponding reliability indexes are obtained; next, the non-probabilistic reliability indexes are replaced by utilizing optimization characteristic displacements so as to improve the convergency of problems, and the sensitivity of the optimization characteristic displacements to design variables is solved by utilizing the adjoint vector method and the compound function derivation law; finally, the design variables are updated with the method of moving asymptotes, repeated iteration is conducted until corresponding convergency conditions are met, and the optimal design scheme meeting reliability constraints is obtained. During the optimization design process, the comprehensive influence of uncertainty on the continuum structure property is reasonably represented, weight lowering can be effectively achieved, and it is guaranteed that the design itself gives consideration to both safety and economy.

The invention discloses a head injector of a low-thrust engine for electric discharge and ignition by utilizing nozzle clearance. The head injector provided by the invention comprises a high voltage positive electrode copper rod, a positive electrode wiring nut, a positive electrode insulating spacer, a seal locking nut, a seal extruding ring, a sealing pad, a casing, a sealing ring, an oxidizingagent swirler, a positive electrode insulating sleeve, an electric discharge circumferential seam adjusting block, an oxidizer nozzle outlet end cover and a fuel centrifugal nozzle. The size miniaturization of the head injector of the low-thrust engine can be realized, and because the electric discharge area of the nozzle ring seam is large and the interval can be adjusted, the spark plug single-point electric discharge fault caused by pollution can be avoided effectively.

The utility model relates to an electronic case of electrical-mechanical and thermal integration, which comprises a common motherboard, a plurality of angle strips, a plurality of cutting strips, a plurality of electrical connectors, a plurality of spring leaves, a corner pad and a plurality of circuit boards; wherein, the top part of the case is connected with the angle strips; each angle strip is magnetic sealed by the cutting strips; the common motherboard is positioned on the chassis of the case to realize the signal transmission between the circuit boards, and to make the specification to the circuit boards of different system equipments; the bottom of each circuit board is connected with the common motherboard through two electrical connectors; the top of each circuit board is connected with the top corner of the case; both ends of the circuit boards are positioned in the slots of the former board and the rear board of the case, and is fixed by the slots on both sides of the spring leaves and the corner pad to decrease vibration. The signal transmission of each circuit board in the case is operated by the common motherboard to reduce the number and the configuration weight of cables and the electric connectors which can save the space in satellites for the installation, and damping vibration within the combination of the spring leaves and the corner pad which is positioned on both sides of the slot in the circuit boards, and the purpose of vibration damping is good.

The invention discloses a continuum structure non-probability topologicaloptimization method based on bounded uncertainty. The method comprises the following steps: first establishingoptimization feature distance d which is a non-probability reliability index based on a non-probabilistic set-based reliability model in consideration of uncertainty effects of load, material characteristics, a design permissible value and other parameters under a finite sample conditionaccording to stress characteristics of the continuum structure; and the establishing a topologicaloptimization model based on a moving asymptotesoptimization algorithm; and acquiring the most configuration of the continuum structure under a given external storage and boundary condition through repeated iteration by taking the reliability as the constraint, the weight-losing as an optimization target and the relative density of a unit as the design variable. By use of the non-probability topologicaloptimization method disclosed by the invention, the comprehensive influence of the uncertainty to the structure configuration is reasonably represented in the process of performing the topologicaloptimization design, the effective weight-losing can be realized, and the design takes account of the security and the economy by itself.

The invention discloses fabricated blocks, a fabricated-block building system and a construction method thereof. The fabricated blocks comprise a main block and auxiliary blocks, wherein the auxiliary blocks comprise 1 / 2 blocks, T-shaped node blocks, corner blocks and end blocks; the main block is composed of two parallelly-arranged long transverse ribs and at least two short longitudinal ribs perpendicularly connected between the two long transverse ribs; the two ends of the main block are both in an H-shaped open structure, the main block is in mortise-and-tenon joint with a block (horizontally adjacent to the main block) by virtue of a tenon and a rabbet, and simultaneously a vertical through hole is formed between the main block and the block (horizontally adjacent to the main block); and a horizontal through hole is formed between the main block and a block (vertically adjacent to the main block) by virtue of opposite openings of U-shaped grooves on the short longitudinal ribs. According to the invention, the relatively complex construction operation of traditional blocks bonded by using mortars is simplified, and the working efficiency, anti-permeability performance and leakage resistance of the block are improved, meanwhile, the noise and dust of an operation field also can be reduced, and energies and raw materials can be saved, thereby satisfying the green and environmentally-friendly requirements of building construction and facilitating the implementation of housing industrialization.

The invention provides an online three-stage eddy flow dehydration device of a submarine pipeline. The online three-stage eddy flow dehydration device is applied to efficient dehydration of a water-containing well flow of an underwater production system. The dehydration device organically combines with an underwater manifold and the submarine pipeline to achieve online installation and operation of the submarine pipeline, and crude oil and production sewage integrated treatment and efficient oil-gas-water separation are achieved through an underwater three-stage eddy flow dehydration system and the device. A primary dehydrator is of a columnar single-cylinder structure, primary axial high-speed eddy flow crude oil dehydration treatment is carried out under the centrifugal separation effect in an eddy cone field, a secondary dehydrator is of a tubular short-three-cylinder structure, quick treatment of secondary axial layered eddy flow sewage is carried out according to an eddy flow field, a tertiary dehydrator is of a squirrel-cage long-cylinder structure, deep treatment of tertiary squirrel-cage parallel connection eddy flow sewage is carried out according to an eddy flow field, a crude oil supercharger pressurizes oil subjected to all stages of dehydration treatment to reach a same high pressure value, and then the oil converges to the same outward transportation seawater pipe for centralized outward transportation.