35results about How to "Reduce aerodynamic force" patented technology

An aircraft having a variable geometry for adapting the flight characteristics to different flight situations includes a fuselage with a pair of wings projecting on both sides of the fuselage in the transverse direction (y), each of which wings has an inner wing section arranged stationarily with respect to the fuselage and an outer wing section adjacent thereto and pivotable about a pivot axis. The pivot axis is oriented in a direction deviating from the longitudinal direction (x) of the aircraft by a maximum of 40°.

A turbomachine assembly comprising: an annular compression section; a casing formed by an outer annular shell (204) and an inner annular shell (206) secured inside the outer shell by means of a plurality of radial support arms (208); an annular combustion section housed inside the casing; and an annular turbine section. The air coming from the compression section presents rotary motion with an angle of inclination relative to a longitudinal axis (X-X) of the turbomachine, and the combustion section includes angular distribution means for determining air flow direction so as to impart on the gas leaving the combustion section rotary motion with an angle of inclination that is equal to or greater than the angle of inclination of the air leaving the compression section, said angular distribution means being formed by the support arms (208), each of which presents an angle of inclination relative to the longitudinal axis (X-X) of the turbomachine that is greater than or equal to the angle of inclination of the air leaving the compression section.

An axial-flow fan structure is disclosed, having a localized area expansion between the rotor (i.e. front rotating impeller) and stator blades (i.e. rear stationary or fixed blades, sometimes called de-swirl vanes). The area expansion is provided by utilizing an impeller having a (slightly) falling tip contour (FTC).

The invention discloses a plug cap for an air inlet path of an engine. The plug cap comprises a plug head and a connecting rod; the plug cap is an arc-shaped structure which is formed by enabling an end cover to rotate around an axis in a nose cone of the engine; the end surface consists of an L-like shaped curve, and line segments OM and ON which are separately connected to two end points of the curve C through a point O; the line segments OM and ON rotate to form a pneumatic molded surface; after the L-like shaped curve rotates, the initial section, the middle section and the tail section of the L-like shaped curve separately form a first side surface, a second side surface and a third side surface; the first side surface is adaptive to the lower conical surface of the nose cone of the engine; the third side surface is adaptive to the outer wall of a lip of the air inlet path of the engine; a gap is formed between the second side surface and the outer wall of the lip of the air inlet path; when the plug cap is closed, the first side surface and the third side surface are fitted to the plug head; an angle MON of the end surface is divided into two parts by a straight line passing through the point O, the part close to the nose cone is an upper angle being 14-20 degrees, and the other part is a lower angle being 16-17 degrees; and in the airflow direction, the projective plane of the plug head completely covers the lip of the air inlet path of the engine.

Aerodynamic forces contribute to disk and actuator vibration leading to track positioning errors in storage devices such as hard disk drives. The invention provides a variety of dampening mechanisms and a method of dampening to alleviate these problems.

The present invention generally relates to a wiper blade for wiping a windshield, and more particularly to wiper blade including a spoiler that forms an air flow allowing the wiper blade to be in close contact with the windshield. The wiper blade according to the present invention has a frame, a spoiler receiving the frame therein and forming an upper surface of the wiper blade and a wiper lip extending downwardly from the frame to contact a windshield. The wiper blade includes the following: a frame including an adaptor coupler at a midway portion; a spoiler receiving the frame and provided next to either side of the adaptor coupler, the spoiler having a cross-section including leg sides of a front surface and a rear surface and a topside of a top surface; and an adaptor mounted to the adaptor coupler and connecting the frame to a wiper arm. A width of the top surface connecting the front surface and the rear surface of the spoiler is maximal near the adaptor coupler and becomes narrower toward a longitudinal end of the spoiler.

The invention relates to a stay cable with a porous hollow housing for a cable stayed bridge. The stay cable consists of a high-strength galvanized steel wire, a surface sheath, a spiral fin and a porous housing from inside to outside respectively, wherein the high-strength galvanized steel wire is fixedly arranged in the surface sheath; the surface sheath and the porous housing are concentric circular tubes; a certain gap is remained between the porous housing and the surface sheath; at least one spiral rib which is coaxial with the circular tubes is arranged in the space of the gap; the internal and external spiral edges of the spiral rib are fixedly adhered to the tube walls of the surface sheath and the porous housing respectively. According to the stay cable, the regularity of karman vortex shedding of the cable and the regularities of axial flow and axial vortex can be broken by the axial porous housing of the cable, and the relevancy of pneumatic acting force of the stay cable in the axial direction of the stay cable is reduced, so that the conditions for occurrence of dry cable galloping are damaged.

Systems and methods for mechanically rotating an aircraft about its center-of-gravity (C_G) are disclosed. The system can enable the rear, or main, landing gear to squat, while the nose landing gear raises to generate a positive angle of attack for the aircraft for takeoff or landing. The system can also enable the nose gear and main gear to return to a relatively level fuselage attitude for ground operations. The system can include one or more hydraulically linked hydraulic cylinders to control the overall height of the nose gear and the main gear. Because the hydraulic cylinders are linked, a change on the length of the nose cylinder generates a proportional, and opposite, change in the length of the main cylinder, and vice-versa. A method and control system for monitoring and controlling the relative positions of the nose gear and main gear is also disclosed.

The invention belongs to the field of magnetic levitation rail transit, and provides a magnetic levitation rail beam which comprises a bottom plate and two or more main beams arranged on the upper surface of the bottom plate, and a ventilation structure is arranged on the bottom plate. By means of the arrangement, the ventilation structure is arranged on the bottom plate, high-speed air flow generated above the bottom plate when a train runs can be guided out through the ventilation structure, aerodynamic force generated by the high-speed air flow to the bottom plate can be reduced, and therefore the adverse effect of the aerodynamic force on a rail is reduced.