10 results about "Leading edge" patented technology

The sheet processing apparatus is provided with a second folding, conveying roller pair that discharges a folded sheet bundle with its folded portion being the leading edge and a folded bundle tray provided below the second folding, conveying roller pair on which the sheet bundle discharged by the second folding, conveying roller pair is to be stacked and that moves the stacked sheet bundle. Before a succeeding sheet bundle is discharged onto a preceding sheet bundle, the folded bundle tray moves the preceding sheet bundle in the upstream direction with respect to the sheet conveyance direction to place the trailing edge of the preceding sheet bundle at a position upstream of the leading edge of the succeeding sheet bundle. Thus, it is possible to provide a sheet processing apparatus that can stack folded sheet bundles with reliability and to improve the image forming efficiency.

A method of forming a fan blade includes the step of applying an adhesive layer around a leading edge of a fan blade body. The adhesive layer includes an adhesive film supported by a scrim cloth, and the adhesive layer contacts a portion of an inner surface of the fan blade body and a portion of an outer surface of the fan blade body. A leading edge sheath is positioned relative to the fan blade body such that a first flank and a second flank of the leading edge sheath is positioned over the portion of the inner surface and the portion of an outer surface, respectively, of the fan blade body. Pressure is applied to the first flank and the second flank of the leading edge sheath to secure the leading edge sheath to the blade body and curing the adhesive film.

An assembly including an airfoil and a platform on which the airfoil may be mounted, the surface of the platform presenting a circumferential depression between a leading edge and trailing edge of the airfoil, a deepest section of the depression being situated in an upstream half of the airfoil. A skeleton curve designates a curve of variations of a skeleton angle of the airfoil as a function of position along the axis of the wheel, and a linearized skeleton curve designates a curve of variations of an angle as a function of position along the axis of the wheel, the curve being a straight line connecting together points representing the skeleton angle respectively at 10% and at 90% of the axial extent of the airfoil from the leading edge. In a vicinity of the platform, the skeleton curve presents a raised portion that lies above the linearized skeleton curve.

The invention provides an aircraft aerodynamic layout method and device capable of meeting a wide-speed-domain waverider performance and a medium. The layout method comprises the following steps: establishing a basic shape, and drawing a grid for a computational domain of the basic shape; performing flow field calculation on the calculation domain of the basic shape by adopting a shock wave assembly method, and respectively performing calculation according to the state parameters of the ballistic points to obtain a flow field stability solution and a stable shock wave surface; for shock wave surfaces obtained by calculating flight Mach numbers from large to small, selecting a cutting position from the windward sides in the flow direction of the shock wave surfaces respectively, cutting theshock wave surfaces, taking obtained cutting lines as leading edge lines of the windward sides of the waverider, taking points on the cutting lines as starting points, and obtaining the waverider surfaces through a streamline tracking method. The length and the width of each cutting line are multiplied by a coefficient according to the actual length requirement of the wave rider design, the actual length requirement and the actual width requirement are met, and then the leeside of the wave rider is obtained according to the filling ratio requirement of the wave rider design.

An aircraft (1002) including a wing (1001), having a fixed wing (1005) with a wing tip device (1003) moveably mounted at the outer end thereof. The wing tip device (1003) is moveable between: a flight configuration; and a ground configuration. The wing tip device (1003) and the fixed wing (1005) are separated along an oblique primary cut plane (1013). The wing tip device (1003) and the fixed wing (1005) meet along an interfacing cut line (1035). The interfacing cut line (1035) includes a first length (1037) offset from the primary cut plane (1013) in a first direction; a second length (1041) that extends within a plane (P) containing the axis of rotation (1011), or a plane parallel thereto; and a transition section (1039) over which the interfacing cut line (1035) transitions from the first length to the second length. The second length may extend around the upper surface, around the leading edge and onto the lower surface.

The invention discloses a single-wing self-rotating landing device which can enable blades to generate lifting force through rotation in the falling process of a load thrown from the air, so that thefalling speed is decreased, and the load falls to the ground safely. The single-wing self-rotating landing device comprises a storage box, a leading edge balance weight and blades. According to actualengineering application conditions, an effective load needing to be decelerated can be placed in the storage box to be jointly regarded as a wing root balance weight, and the mass and the position ofthe front edge balance weight and the size and the shape of the blades are reasonably arranged respectively to achieve overall normal operation. The device is specially designed for air-drop objectsand air-drop loads with special requirements. The principle of the device is similar to that of maple seeds in the nature. The blades are pushed by air during falling, so that the whole device rotatesto generate lifting force and slow down the falling speed; and the device has the characteristics of simple structure, effectiveness and reliability.