335 results about "Wing configuration" patented technology

A case for an electronic device such as a tablet computer includes book configuration and stand configuration. In the stand configuration, the back panel of the holder, against which the electronic device is held, is disposed at an incline with respect to the front panel. The stand configuration is achieved through folding seams in the front panel and pockets in the back panel such that the front panel is folded back such that the front panel exterior surface generally faces the back panel exterior surface and respective front panel corners are folded along the folding seams and disposed within the back panel pockets.

A crosswind kite system adapted to operate in an alternate mode in high winds. The system may operate at reduced efficiency in high winds in order to moderate loading on the system during those high winds. The system may use multi-element airfoils which are actuated to reduce the coefficient of lift of the airfoils in order to moderate loading in high wind conditions. Other flight aspects may be controlled, including flying the crosswind kite in side slip to induce drag which may lower loading on the system.

An air vehicle, such as a manned or unmanned air vehicle, has a fuselage, a rotor / scissors wing, and a scissors wing. At helicopter mode, the rotor / scissors wing rotates to make the air vehicle fly like a helicopter to achieve vertical and / or short take-off and landing, hovering, and low speed flying. At airplane mode, the rotor / scissors wing and scissors wing form a scissors wings configuration to maximize the air vehicle's flying efficiency at a wide range of speed and flying conditions by adjusting the yaw angle of the rotor / scissors wing and scissors wing. During the conversion from helicopter mode to airplane mode, the scissors wing generates lift to offload the rotating rotor / scissors wing and eventually the offloaded rotor / scissors wing's rotating speed is slowed and stopped so that the rotor / scissors wing can be locked at a specific position and the conversion can be achieved. In a reverse order, the air vehicle can convert from airplane mode to helicopter mode. Either turbofan or turbojet engine, or turboshaft / turbofan convertible engine can be used to power the air vehicle.

An eyepiece for a head mounted display (“HMD”) includes a first end for receiving computer generated image (“CGI”) light and a second end disposed opposite the first end. The eyepiece also includes an image directing element to direct the CGI light out of the eyepiece in an eye-ward direction. The image directing element is disposed between the first end and the second end. At least one edge running between the first end and the second end is configured to reduce reflection of the CGI light back into the eyepiece.

A method of reducing the bending moment effect of wind gust loads acting on the wing of an aircraft involves adjusting the aerodynamic configuration of the wing so as to alter the distribution of lift generated by the wing during phases of flight in which critical wind gusts are expected to occur. Particularly, during climb and descent phases of flight below cruise altitude, the lift generated by outboard portions of the wings is reduced while the lift generated by inboard portions of the wings is increased. Thereby, the 1 g basis load acting on the outboard portions of the wings is reduced, and consequently the total load applied to the outboard portions of the wings, resulting from the 1 g basis load plus the additional wind gust load, is correspondingly reduced. This leads to a reduction of the bending moments effective on the wings, and of any rolling moment effective on the aircraft. The required adjustment of the lift distribution is preferably achieved by deflecting the ailerons of both wings symmetrically upward and / or deflecting the flaps of both wings symmetrically downward during climb and descent. The adjustment of the wing configuration is carried out dependent only on flight parameters such as the altitude, speed and gross weight, and does not require rapid sensing of the occurrence of a wind gust and rapid actuation of control surfaces to try to instantaneously counteract a wind gust as it occurs.

A vertical take-off and landing (VTOL) aircraft according to an aspect of the present invention comprises a fuselage, an empennage having an all-moving horizontal stabilizer located at a tail end of the fuselage, a wing having the fuselage positioned approximately halfway between the distal ends of the wing, wherein the wing is configured to transform between a substantially straight wing configuration and a canted wing configuration using a canted hinge located on each side of the fuselage. The VTOL aircraft may further includes one or more retractable pogo supports, wherein a retractable pogo support is configured to deploy from each of the wing's distal ends.

A plastic material sheet for use in vacuum thermoforming is formed of polymer material. Electrically conductive resistance elements, at least a portion of which are situated within sheet, conduct electrical current to heat the sheet. The elements are generally parallel to each other. They may be straight, have a generally zigzag configuration, a generally serpentine configuration, an arcuate configuration, or a grid-like configuration. The elements may each have a section that extends substantially beyond the edge of the sheet. They may be frangible. They may be embedded deeply within the sheet or may be situated proximate a surface of the sheet.

The present disclosure relates to a high performance Vertical Takeoff and Landing (VTOL) aircraft for executing hovering flight, forward flight, and transitioning between the two in a stable and efficient manner. The VTOL aircraft provides a highly stable, controllable and efficient VTOL aircraft. The preferred comprises: (1) a pusher propeller configuration with strategic placement which maximizes the effective use of thrust, (2) four propellers which allow for the highly-controllable and mechanically simple control methods used in multirotor aircraft, (3) electric motors which create mechanically simple, lightweight and reliable operation, (4) and a tandem wing configuration which is stable, controllable and efficient in both hovering and forward flight. The VTOL aircraft is capable of full runway, short runway or vertical takeoffs or landings, having unobstructed forward view for camera and sensor placement; and providing a compact, mechanically simple and low-maintenance VTOL aircraft design.

Anti-icing methods and aerodynamic structures having laminated resistive heaters for de-icing are described. Several of the inventive aspects utilize laminated resistive heaters comprising a carbon nanotube layer and / or capacitors to store and supply electricity. The invention also includes methods of making aerodynamic structures having de-icing or anti-icing functionality.

An ultrasonic surgical instrument is provided. The ultrasonic surgical instrument includes a housing having an elongated shaft extending therefrom. A first jaw member disposed at a distal end of the shaft is movable between open and clamping configurations. A pair of second jaw members disposed at the distal end of the shaft are movable between open and clamping configurations. A cutting blade extending to the distal end of the shaft is operably coupled to the housing. The pair of second jaw members and first jaw member are moveable to the clamping configuration to compress tissue of interest for removing moisture therefrom prior to the tissue of interest being treated.

A Blended Wing Body SUAV and MUAV is disclosed having a novel airfoil profile, wing configuration, rigging and tractor pull propeller placement that provide improved stability and safety characteristics over prior art SUAVs and MUAVs of comparable size and weight. This unique blended wing design includes wing twist on the outboard wing and an inverted “W” shaped planform to provide lateral and longitudinal stability, and smooth, even flight characteristics throughout the range of the expected flight envelope. These flight characteristics are crucial to providing a stable reconnaissance platform with favorable stall speeds, an increased payload and the ability to hand launch without the danger of exposing ones hands or wrist to a propeller.

A stent made of single nitinol wire or other biocompatible material having shape memory properties may be configured to define a flower-like configuration generally providing a proximal plane and a distal plane, each generally centered around a generally cylindrical passage and configured for maintaining patency of an anastomosis or other opening. The wire or other biocompatible material may include a shroud or other covering and may also include one or more loops configured to allow relatively secure engagement of sutures. Methods of deployment are also provided.

A mask apparatus for a respiratory treatment can permit delivery of breathable gas to a user. In one example, the mask may employ a frame and cushion to form a seal for both mouth and nose. The frame may be adapted for coupling with a respiratory treatment apparatus so as to permit communication of a pressurized gas from the respiratory treatment apparatus. The cushion, which may be foam, may have a substantially under the nose configuration or over the nose configuration. The mask may have a common plenum chamber for both nose and mouth. The cushion may further define a centrally open lip superior region. The cushion may be adapted to couple with the frame directly or to the frame in conjunction with a cushion support clip. Various features of the cushion may further promote sealing and comfort for the under the nose design.

The present invention is an unmanned air vehicle designed for reconnaissance, surveillance, data acquisition, and general research. The air vehicle is a monoplane that consists of several pieces that can easily be assembled using a minimal amount of tools. The air vehicle consists of a forward and aft fuselage section, two identical horizontal stabilizers, and four identical wing sections. The aircraft can fly with all four wing sections, or with just two wing sections (the short wing configuration). Each of the four wing sections of the air vehicle can be interchanged with any of the other wing sections for the purpose of minimizing assembly time and spare parts.

It is an object of the present invention to provide the entire airplane shape of a supersonic aircraft that can realize low sonic boom characteristics, and that can also minimize wave-drag. In order to achieve both sonic boom suppression and a reduction in wave-drag, the entire airplane shape of the supersonic aircraft of the present invention uses a variable forward swept wing configuration having a mechanism that can vary a forward sweep angle as the main wing configuration, rather than forming the fuselage shape with a blunt nose.

An infusion device for infusion capsules, particularly for espresso coffee machines, comprising a filter basket holder cylinder and a piston which can move with respect to each other from a configuration for loading and unloading at least one capsule for infusions into or from the filter basket holder cylinder to a dispensing configuration and vice versa, the device comprising first elements for movement of at least one of the filter basket holder cylinder and the piston for their first relative movement from the loading and unloading configuration to an intermediate configuration that is comprised between the loading and unloading configuration and the dispensing configuration and vice versa, and second elements for moving at least one of the filter basket holder cylinder and the piston for a second relative movement thereof from the intermediate configuration to the dispensing configuration and vice versa.

The present invention provides an aircraft having one or more fixed wings in a flying wing configuration, where the aircraft further includes a high performance co-flow jet (CFJ) circulating about at least a portion of an aircraft surface to produce both lift and thrust rather than a conventional propulsion system (i.e., a propeller or jet engine).

An aircraft configuration that may reduce the level of noise, infrared radiation, or combination thereof directed towards the ground from an aircraft in flight. An embodiment of an aircraft includes a fuselage, two forward swept wings, at least one engine mounted to the aircraft and higher than the wings, and vertical stabilizers mounted on each wing outboard of the outermost engine. The leading edge of the wing may extend forward of the leading end of the engine, and the trailing edge of the aft deck may extend aft of the trailing end of the engine. The aft deck may include an upwardly rotatable pitch control surface at the trailing edge of the deck. Engine types may vary, including but not limited to turbofans, prop-fans, and turbo-props. Main wings may be mounted above the longitudinal axis of the fuselage, and canards may likewise be mounted above or below the axis.

A flight-operable, truly modular aircraft has an aircraft core to which one or more of outer wings members, fuselage, cockpit, leading and trailing edge couplings, and empennage and tail sections can be removably coupled and / or replaced during the operating life span of the aircraft. In preferred embodiments the aircraft core houses the propulsive engines, avionics, at least 80% of the fuel, and all of the landing gear. The aircraft core is preferably constructed with curved forward and aft composite spars, that transfer loads across the center section, while accommodating a mid-wing configuration. The aircraft core preferably has a large central cavity dimensioned to interchangeably carry an ordnance launcher, a surveillance payload, electronic countermeasures, and other types of cargo. Contemplated aircraft can be quite large, for example having a wing span of at least 80 ft.

An autogyro, or aircraft with a rotating wing, has an airframe providing a motorcycle-like configuration for the rider. The motorcycle-like straddle-type seat locates the rider in front of the rotating wing, behind a teardrop shaped simulated fuel tank, and above the motorcycle engine used for turning the front-mounted propeller. A motorcycle-like handlebar controls the aircraft, including the adjustment for the rotating wing axis of rotation with respect to the aircraft and the engine throttle. Additional controls for operating the aircraft on the ground, such as wheel brakes and the steering, are also controlled from the handlebar.

A biomimetic pitching and flapping mechanism including a support member, at least two blade joints for holding blades and operatively connected to the support member. An outer shaft member is concentric with the support member, and an inner shaft member is concentric with the outer shaft member. The mechanism allows the blades of a small-scale rotor to be actuated in the flap and pitch degrees of freedom. The pitching and the flapping are completely independent from and uncoupled to each other. As such, the rotor can independently flap, or independently pitch, or flap and pitch simultaneously with different amplitudes and / or frequencies. The mechanism can also be used in a non-rotary wing configuration, such as an ornithopter, in which case the rotational degree of freedom would be suppressed.

An adjustable foldable bed frame comprises an outer assembly having a body section and a leg section. Each section has a substantially rectangular periphery with an opening and is pivotally coupled together by a pair of first coupling members for movement between an open configuration whereby the sections are co-planar, and a closed configuration whereby the sections are parallel with each other. An inner assembly having a body component and a leg component are positioned within the opening of the body section and the leg section, respectively. The body component comprises a torso portion which is independently adjustable from a flat configuration to a plurality of reclined configurations. The leg component comprises a calf portion which is independently adjustable from a flat configuration to a plurality of elevated configurations. A connecting bracket assembly fixedly couples adjacent adjustable foldable bed frames such that adjacent torso and calf portions are adjustable together.

The invention relates to a solar unmanned aircraft. In order to overcome the problems of difficult flight control and bad stability of the flying wing solar unmanned aircrafts, the invention adopts the configuration of tip winglets(5) arranged at the outer segments of a large aspect-ratio high wing, a V shaped empennage and a wing(4); the wing(4) is connected with and a fuselage(7) through a bridge wing(3) and a controlling rudder(9) is arranged on the V shaped empennage(8) to realize the pitching and yawing control of the aircraft. Combining the characteristic of the high energy conversion efficiency of a flexible thin film solar battery, the invention lays the flexible thin film solar battery(6) on the wing(4). An engine and propeller propulsion system (1) adopts a haul-in-type, and an equipment cabin (2) is arranged at the front part of the fuselage(7). The solar unmanned aircraft improves the lift-drag ratio of the aerial vehicle, prolongs the operation time and effectively improves the horizontal and the vertical stabilities and maneuverability of the aircraft, thus relieving the problems of bad stability and bad maneuverability of the flying wing configuration.

The present invention provides an aircraft having one or more fixed wings in a flying wing configuration, where the aircraft further includes a high performance co-flow jet (CFJ) circulating about at least a portion of an aircraft surface to produce both lift and thrust.