233 results about "Strake" patented technology

The invention discloses a polyurethane elastomer and a preparation method thereof. The method comprises the following steps: evenly mixing polyurethane prepolymer with curing agent, removing foam, casting and curing to obtain the polyurethane elastomer, wherein the curing agent is composed of at least one of chain extender and cross-linking agent, catalyst and other additives. The Shaw hardness Aof the polyurethane elastomer prepared by the invention is 70-90A, the tensile strength thereof is not less than 14MPa, and the elongation at break thereof is not less than 360%; and the polyurethaneelastomer can resist hydrolysis, meets performance requirements for the spiral strake material in the deep-sea riser vortex-excited oscillation suppression device, and has important application value.

There is disclosed an apparatus comprising a plurality of strake elements, each strake element adapted to cover an arc-angle about a circumference of a structural element; and a mechanism adapted to attach the strake elements to each other to cover at least a portion of the circumference of the structural element.

An improved method and device for the reduction of aerodynamic drag and for improved performance of vehicles by increasing the pressure on the rear surface of the vehicle by generating a plurality of vortices along the top and side surfaces that flow in to the base wake region of the vehicle. An improved method and device for generating a reduction in the drag force on a moving object. The present invention is a simple device comprised of a minimum number of thin and slender small surfaces that are attached to or fabricated as part of the side and top exterior surfaces of a vehicle or vehicle component. The spacing and orientation of the small surfaces, comprising the device, are dependent upon the vehicle geometry and vehicle operating conditions. The plurality of adjacent small surfaces are located forward of the base area on the vehicle. The plurality of adjacent small surfaces and are distributed circumferentially over the side and top surfaces of the subject vehicle or vehicle component. To maximize the ability of each of the plurality of adjacent small surfaces to generate a vortex structure the small surfaces are aligned in planes that are perpendicular to the surface of the vehicle. Each of the plurality of adjacent small surfaces extends from the exterior top and side surfaces of the vehicle. The plurality of adjacent small surfaces is applied symmetrically to a vehicle, about a vertical plane passing through the centerline of the vehicle. Each of the plurality of adjacent small surfaces is orientated in a plane or surface that is at an angle to the local flow direction on the vehicle surface in the immediate vicinity of the present invention. The orientation and shape of the plurality of adjacent small surfaces are a function of the vehicle or vehicle component geometry.

The present invention discloses a compliant banding system for use in a marine environment comprising a flexible compliant member and an abaxial relatively rigid strap, both constructed to extend circumferentially around an underlying structure such as a strake or fairing collar. The strap maintains a fixed circumference while the compliant member flexes intermediate the strap and an underlying.

The invention provides a solar module which is composed of a surface sealing film, a transparent adhesive film, a solar cell, a lightweight adhesive film A and an isolated substrate which are stacked from the top to the bottom in order; and the isolated substrate is composed of an isolated film, a carbon-fiber sheet, a lightweight adhesive film B, a honeycomb core, a lightweight adhesive film C and the carbon-fiber sheet which are stacked from the top to the bottom in order, wherein the honeycomb core inside also needs to be appropriately added embedded parts according to concrete operating requirements. The technical scheme of a preparation method of the solar module comprises following steps: (1) making use of an oven to match with a vacuum air pump to process a pre-compacting treatment for a carbon-fiber prepreg; (2) meanwhile, processing a welding sequence of the solar cell; (3) processing a cutting sequence; (4) processing a laminating technology treatment; (5) processing post treatment procedures which in order are: removing raw edges, embedding strakes, arranging a junction box, measuring high voltage, cleaning the surface, measuring photo-electrical output characteristics, classifying components, and examining the appearance. The solar module has the advantages of lightweight, high efficiency and good low-temperature characteristics, and being very suitable to being applied in the stratosphere.

The invention discloses a section construction method of a hatch coaming and a ship side. A mounting structure at least comprises an outer plate component, a sheer strake component, a vertical wall component, an antitorsion box component, a vertical wall plate, a compartment component, a guide rail and a longitudinal framework, wherein the antitorsion box component comprises a hatch coaming component, and the hatch coaming component comprises upright columns. The section construction method further comprises the following steps: S1, fixing the outer plate component; S2, mounting the sheer strake component on one side of the outer plate component; S3, mounting the bottom of the vertical wall component on the outer plate component; S4, mounting the bottom of the antitorsion box component to the sheer strake component after mounting the hatch coaming component mounted with the upright columns to the antitorsion box component, and connecting one side of the antitorsion box component to the vertical wall component; S5, overlying and welding the vertical wall plate on the vertical wall component and the antitorsion box component; S6, mounting the compartment component and the guide rail on one side of the vertical wall plate far away from the outer plate component. The section construction method of the hatch coaming and the ship side disclosed by the invention realizes the integrated construction of ships, and provides necessary conditions for the batch ship building, and further lowers the requirements of the machining precision and brings about considerable economic benefits.

A substantially cylindrical buoyancy module for a marine riser includes a plurality of buoyancy elements separated along at least one helical separation plane.

A vortex-induced vibration (VIV) suppression device including a body having a wall dimensioned to at least partly envelope a tubular member in an interior area of the body. The device further including a fin protruding outward from an exterior surface of the wall and a stand-off member positioned along an interior surface of the wall. The stand-off member dimensioned to space the body away from the tubular member and having a protruding portion formed by the interior surface of the wall and an indention portion formed by the exterior surface of the wall.

The invention relates to a helical strake vortex induced vibration inhibiting device. The device is characterized by comprising a plurality of strip strakes, a plurality of chucks and a ligature, wherein the strakes are alternately arranged on the outer wall of a marine riser, and are helically arranged along the axial direction of the marine riser; the chucks are alternately fixed on the marine riser, and a plurality of grooves are formed on each chuck; and each strake is arranged in the groove of the chuck corresponding, and is fastened in the chuck through the ligature. The device has a simple structure, and the strakes can adopt a continuous structure to facilitate marine on-site assembly, thus the efficiency of marine on-site assembly is remarkably improved, and the device has remarkable economic benefits, and can be applied to the marine riser widely.

There is disclosed a system comprising a structural element, at least one helical strake about the structural element, and at least one ramp to provide a transition from the structural element to the helical strake.

A method for manufacturing a strake is provided. The method includes: providing a first thermoplastic laminate panel; providing a second thermoplastic laminate panel; attaching the first thermoplastic laminate panel to the second thermoplastic laminate panel such that at least a portion of the attachment surface of the first thermoplastic laminate panel is attached to the attachment surface of a portion of the second thermoplastic laminate panel, which attached portions form a body of the strake; forming a first flange from a portion of the first thermoplastic laminate panel; and forming a second flange from a portion of the second thermoplastic laminate panel.

Improved supersonic laminar flow wing structure, on a supersonic aircraft, having one or more of the following:

• • strake extending forwardly of the wing inboard extent,
  • raked wing tip,
  • reversed fillet at strake or fuselage junction,
  • inboard leading edge flap extending over less than about 15% of the inboard wing panel span,
  • hybrid plain-split flap having a lower surface portion deflectable downwardly relative to plain flap extent.

The invention belongs to the technical field of laying of marine risers and relates to a sleeve for a marine riser. When in use, the sleeve for the marine riser is fixedly connected outside the marine riser, the sleeve for the marine riser comprises a pair of semi-circular ring-shaped shells which are manufactured according to the outer diameter of the marine riser and have the same size, spiral strakes and spiral grooves are arranged on the outer surfaces of the two semi-circular ring-shaped shells in a staggered manner, when the two shells are combined into an annular column, the spiral strakes or grooves distributed on the outer surfaces of the two shells are combined into a spiral structure. By adopting the sleeve for the marine riser, the cost can be reduced, the vortex-induced vibration of the marine riser can be effectively controlled, and the unification of economy and safety can be realized.

The invention relates to a vertical lifting aerodyne employing tiltable ducted wheels. A fuselage adopts the streamline design, two sides of the fuselage are provided with large strake wing body-fused horizontal fixed stub wings, tilting systems are designed at the tail ends of the stub wings and connected with the earth-space dual purpose ducted wheels, the ducted wheels are overturned towards the inner side of the fuselage through the tilting systems, and thus the vertical lifting aerodyne can run on the ground, take off and land vertically and fly in the air with any attitude. Six stub wings are designed at both sides of the fuselage in total, so that six ducted wheels are required in total. The vertical lifting aerodyne has the advantages that the technology of fusing the streamline fuselage and wing bodies is adopted, and thus the structure weight is light, the internal capacity is large, the air resistance is small; control over the flight attitudes is realized through controlling power differentials of the six wheels, the design of control rules is simple, and the control is convenient.

A vertical stabilizer is configured to minimize the rate of change of cross-sectional area of the vehicle or device to which the vertical stabilizer is mounted. One or more “waisted” areas can be included at the tip and/or the root of the vertical stabilizers, as well as over the distance from tip to root of the vertical stabilizer. In some situations, a strake is mounted on the vehicle or device, such as an aircraft, and the vertical stabilizer is mounted to the tip of the strake. The strake can also be area ruled with one or more “waisted” sections at the juncture of the vertical stabilizer. Applying area ruling to the vertical stabilizer helps to further reduce the drag of the vehicle or device.