227results about How to "Improved aerodynamics" patented technology

Devices, systems and methods are disclosed which relate to providing wing designs with payload integration capabilities on existing modularly assembled unmanned aerial vehicles (UAVs). Exemplary embodiments of the present invention present a novel technique of adding payloads to existing UAVs while improving flight performance over existing techniques by maintaining a similar overall weight with improved aerodynamic properties. The technique includes using a reinforced foam core center wing with a fiberglass epoxy skin. A lightweight payload canopy cover integrates onto the center wing as an agnostic enclosure for payloads. The payload canopy cover may contain venting holes for the cooling of electronic payloads. The systems may also include common devices such as antennas, GPS, and batteries for use with a wide range of payloads.

An insulating holder for holding a beverage in a bottle or a can having a lower cylindrical enclosure which receives an upper cylindrical enclosure having a dome-shaped upper end. The upper cylindrical enclosure is adapted to cover the top portion of a bottle inserted into the lower cylindrical enclosure and to snuggly receive a can when inverted and inserted into the lower cylindrical enclosure. At least a portion of the lower cylindrical enclosure or upper cylindrical enclosure is made of a polyolefin elastomer foam. The insulating holder may be structured to retain various sizes of wine bottles.

A device for allowing a crossbow to be released from a drawn position without damaging the crossbow. The device may comprise an elongated member having a substantially cylindrical shape that can be positioned on the upper surface of the barrel of a crossbow. The device may comprise a notched end shaped to receive the bowstring of the crossbow and allows the device to be projected by the bowstring upon actuation of the crossbow's trigger lever.

A spoiler for a rotor blade of a wind turbine includes a spoiler body and at least one mounting band arranged along a longitudinal edge of the spoiler body for mounting the spoiler onto a surface of the rotor blade. The at least one mounting band adapts to a curvature of the rotor blade surface. The spoiler body and the at least one mounting band are formed as a single entity. Further, a rotor blade for a wind turbine includes such a spoiler mounted onto a surface of the rotor blade. Further, a wind turbine includes a number of rotor blades attached to a hub, wherein at least one rotor blade includes such a spoiler mounted onto a surface of the rotor blade.

The air guiding device has one or more air guiding bodies. Each air guiding body has an elongate attachment that extends in the longitudinal direction of the vehicle that bulges in a convex manner, is composed of a flexible or soft-elastic material and is embodied in the form of a half shell having a lateral elongate opening and can be adjusted automatically in the driving condition from a rest position into an operative position, in which it can be lowered in the direction of the roadway. In the rest position, the air guiding body is arranged close to the undersurface and, in the operative position, the air guiding body is held in a lowered position relative to the undersurface.

A handlebar for a bicycle has first and second laterally extending portions disposed outboard of a central attachment portion. Each of the first and second laterally extending portions is preferably winged-like in configuration to provide reduced air resistance. The first laterally extending portion includes an aerobar clamping mechanism, and the second laterally extending portion includes a second aerobar clamping mechanism. Each aerobar clamping mechanism includes a tapered receiving sleeve having an axis that is generally parallel to a travel axis of the handlebar. A collet having a major axis that extends in a plane generally parallel to the direction of travel of the bicycle is receivable within the receiving sleeve. The collet includes a plurality of axially extending slots that permits the diameter of the collet to be varied. The collet includes an aerobar receiving slot having a major axis that is generally co-linear with the axis of the collet, and is provided for receiving an aerobar. An axial mover member can be coupled to the collet, for axially moving the collet within the aerobar receiving sleeve. Axial movement of the collet within the aerobar receiving sleeve serves to tighten and increase the grip of the collet upon the aerobar.

The invention relates to an aircraft (1), preferably an unmanned aircraft (UAV), drone, or unmanned aerial system (UAS), comprising a rigid wing (2), which enables aerodynamic horizontal flight, and at least four rotors (4, 4'), which are driven by means of controllable electric motors (5) and which can be pivoted between a vertical starting position and a horizontal flight position by means of a pivoting mechanism (7), wherein all electric motors (5) and rotors (4) are arranged on the wing (2).

An outer gripping portion of a bicycle handlebar includes a mounting section and a bracket section. The mounting section has a first cross-sectional shape. The bracket section has a second cross-sectional shape and is releasably coupled to the mounting section to form a first gripping section. The first and second cross-sectional shapes of the mounting section and the bracket section have flush longitudinal edges that mate together to form a first annular gripping surface of the first gripping section. Preferably, the bicycle handlebar includes a pair of outer gripping portions coupled to opposite ends of a transverse portion.

A cross bar for mounting a vehicle topper to a roof of a vehicle has a center section with a substantially rectangular cross section. Tapered sections are attached at a proximal end to each side of the center section. Outer plates are located on the distal end of each respective tapered section. The tapered sections increase in cross sectional area from their distal end to their proximal end.

The invention relates to a ship-based net collision recovery unmanned aerial vehicle, comprising an airframe, an airfoil, ailerons, a horizontal tail, an elevating rudder, vertical tails, rudders, an engine and a propeller, wherein the airfoil is mounted on the airframe and adopts an upper single-airfoil layout; the left side and the right side of the airfoil are respectively provided with one aileron; the horizontal tail is mounted at the upper end of the tail part of the airframe and adopts double vertical fin layout; the left and right vertical tails are connected with the wing ends of the horizontal tail respectively; the horizontal tail has a 1.5-degree mounting angle; the front edge of the horizontal tail is higher than the rear edge of the horizontal tail; the elevating rudder is arranged on the rear edge of the horizontal tail; the rudders are arranged on the rear edges of the vertical tails; the engine is mounted at the tail end of the airframe and is used for driving the propeller to rotate. The unmanned aerial vehicle has the characteristics that the endurance time is long, so a flight mission with high requirement on endurance is convenient to carry out during navigation; the wind-resistant ability is strong and the stability is high, so the unmanned aerial vehicle is applicable to the flight emission under a complicated sea condition; catapult-assisted take-off and high-precision net collision zero-distance recovery are adopted, so the unmanned aerial vehicle is applicable to emission and recovery on a narrow space on naval vessels; the whole machine adopts modular design, so containerized transportation is facilitated and the occupied space on the naval vessel is reduced.

A sub-caliber bullet with an aerodynamic shape has long-range accuracy due to a high muzzle velocity and reduced time of flight to a target. The bullet has a forward portion, a mid-portion and an aft portion. The forward portion has a density in excess of 10/cm³ while the mid-portion has a lower density. The bullet has an aspect ratio of at least 5:1 and a diameter, d, that satisfies a Power Law equation:

d=D*(x/L)ⁿ

where D is a maximum bullet diameter, L is the length, x is a distance rearward from a nose of the bullet and n is a Power Law exponent that is between 0.5 and 0.75. In some embodiments, a blind bore extends into the mid-portion from the aft portion and a sustainer propellant within the blind bore ignites as the bullet exits a gun muzzle to provide a velocity boost and to overcome aerodynamic drag.

A golf ball has a substantially spherical outer surface comprised of a plurality of non-circular dimples. The dimples are formed by a plurality of lobes extending from a central hub, wherein each lobe is defined by a curved outer segment. The curved outer segments form at least a portion of the perimeter of the dimple. The dimples are comprised of at least four lobes. The dimples can also be comprised of a plurality of radiating arms emanating from a location proximate the hub of the dimple.

A golf ball includes a spherical outer surface and a plurality of dimples formed thereon. The dimples have an inner land surface with at least one spiral depression either disposed or superimposed on the inner land surface to energize or agitate the airflow over the dimpled surfaces to increase the aerodynamic performance of the golf ball. The spiral depression may turn clockwise or counterclockwise and can be either spaced apart, touching or overlapping each other. While the dimples may be circular, polygonal, triangular or elliptical, dimples having a cross section greater than 0.18 inch are preferred. The dimples may also comprise spiral depressions directly on the spherical surface of the ball.

A particular arrangement of vortex generators for an airfoil is described. The vortex generators are provided in pairs, preferably on a wind turbine blade, wherein by arranging the vortex generators according to specified characteristics, a surprising improvement in blade performance is provided over the prior art systems.