12404 results about "Fuselage" patented technology

The present invention relates to a helicopter having a modular airframe, with multiple layers which can be connected easily, the layers which house the electronics (autopilot and navigation systems), batteries, and payload (including camera system) of the helicopter. The helicopter has four, six, and eight rotors, which can be easily changed via removing one module of the airframe. In one embodiment, the airframe has a vertical stacked appearance, and in another embodiment, a domed shape (where several of the layers are stacked internally). In one embodiment, there is a combination landing gear and camera mount. The helicopter allows for simple flight and usage by remote control, and non-remote control, users.

A vertical take-off and landing vehicle comprised of a fuselage having a front, a rear, and two lateral sides and a set of four thrusters set to the front, the left, the right, and the rear of said fuselage. The thrusters are either independently powered thrusters or could utilize a single power source. The thrusters, which are ducted fan units capable of providing a vertically upward force to the aircraft, are provided with such redundancy that the aircraft can hover with up to two thrusters inoperative. The thrusters are comprised of a set of two counter rotating propellers both of which creates lift. The two counter rotating propellers cancel out the torque effect normally created by using only one propeller. The Ducted fan units being movable between a first position in which they provide vertical lift and a second position in which they provide horizontal thrust using a set of servos and gears.

The MULTIBODY AIRCRANE performs relative positioning, predictive control, and ballast control to achieve very heavy-lifting tasks on land or sea. Such tasks allow station keeping and precise transfer of very heavy payloads between ships underway. This scalable multibody system features three subcomponents: AIRSHIP, SKYCRANE and LOADFRAME. This semi-autonomous system combines aerodynamic (kinetic) and aerostatic (buoyancy force) lift with efficient power and propulsion. During low-speed flight, the Airship and Skycrane are decoupled but linked via a reelable Tether Control Line. Beneath the Skycrane, centered on its hull, a patented NIST (National Institute of Standards and Technology) RoboCrane (featuring a computer controlled six degrees of freedom (DoF) cabling system,) is attached, to precisely suspend and control a Loadframe, with or without payload. During subsonic forward flight, these Airship and Skycrane are coupled as a single airframe (fuselage and delta wing.)

Disclosed is a bi-directional sliding-type portable terminal. The bi-directional sliding-type portable terminal comprises a phone body and a bi-directional sliding body. The phone body comprises a first section which is located on one side of the top surface thereof and within which a plurality of keys are mounted, and a second section which is located on the other side of the top surface thereof spaced apart from the first section and within which a camera lens housing is mounted. The bi-directional sliding body linearly moves on the phone body in a longitudinal direction while facing the phone body, opens the first section to expose the keys by moving toward the second section, and opens the second section to expose the camera lens housing by moving toward the first section.

The disclosed invention consists of several improvements to well known Quad Tilt-Rotor (QTR) aircraft. The first is that during a wing-borne flight, one pair of tilt-rotors, which can be substantially larger than the other pair, is feathered and stopped. This can promote vehicle aerodynamic efficiency and can be utilized to increase vehicle speed. Second is that the wings are not attached to the fuselage at a fixed angle of incidence like on conventional QTR aircraft, but can also be tilted in respect to the fuselage independently of the tilt-rotors. Furthermore, each rotor and each wing can be tilted with respect to fuselage to any tilt-angle without limit, which gives the vehicle unprecedented ability to position the fuselage in any attitude in respect to the vehicle direction of flight.

An unmanned air vehicle is provided, which includes an airframe and a parallel hybrid-electric propulsion system mounted on the airframe. The parallel hybrid-electric propulsion system includes an internal combustion engine and an electric motor. A hybrid controller is configured to control both the internal combustion engine and the electric motor. A propeller is connected to a mechanical link. The mechanical link couples the internal combustion engine and the electric motor to the propeller to drive the propeller. An alternate unmanned air vehicle includes a second propeller driven by the electric motor. In this alternate unmanned air vehicle, the internal combustion engine is decoupled from the electric motor.

A tunable earphone includes a body, a front cavity, a rear cavity and a decorating plat. The body includes a small air hole and a large air hole. The front cavity and the rear cavity are respectively disposed on the body. The decorating plate covers the rear cavity and includes a receiving groove, a shielding member and a channel. The shielding member and the channel are disposed in the receiving groove. When the decorating plate is rotated to a first position, the shielding member shields the large air hole, the channel corresponds to the small air hole, so that the front cavity communicates with the rear cavity through the channel. When the decorating plate is rotated to a second position, the shielding member shields the small air hole, the channel corresponds to the large air hole, so that the front cavity communicates with the rear cavity through the channel.

A shell component for an aircraft fuselage includes a fuselage skin panel, a plurality of stringers extending in an aircraft lengthwise direction, and a plurality of frames extending crosswise relative to the stringers. The stringers and the frames are respectively welded onto the skin panel with the addition of a weld filler material. Each frame includes a frame root portion and a frame profile portion connected to each other. The frame root portion has cut-out notches receiving the stringers passing therethrough. The frame root portion is welded to the skin panel at the areas between the cut-out notches, and may be welded to the respective stringer in each cut-out notch. The stringers and frames are fabricated from webs and flanges, whereby a premanufactured grid of flanges may be used. The result is a very strong, yet simple shell component structure, that may be manufactured with a simple welding process, at a low cost and with low effort.

An aircraft having a vertical take-off and landing (VTOL) propulsion system. The aircraft includes a fuselage, the VTOL propulsion system, at least one forward thruster, a power source used for both the VTOL propulsion system and forward thruster, fore and aft wings and a plurality of spars attached to and spanning the space between the two wings. The VTOL propulsion system includes a plurality of VTOL cells (including a motor, motor controller, and propeller) attached in a spaced relation along each spar. The VTOL cells are used exclusively for vertical flight or hovering and are powered down as the aircraft develops forward flight velocity and corresponding wing lift. During forward flight the VTOL propellers are articulated to allow the aircraft to take on a low drag configuration. The present invention is suitable for use in manned or un-manned aircraft of any scale.

An aircraft for use in fixed wing flight mode and rotor flight mode is provided. The aircraft can include a fuselage, wings, and a plurality of engines. The fuselage can comprise a wing attachment region further comprising a rotating support. A rotating section can comprise a rotating support and the wings, with a plurality of engines attached to the rotating section. In a rotor flight mode, the rotating section can rotate around a longitudinal axis of the fuselage providing lift for the aircraft similar to the rotor of a helicopter. In a fixed wing flight mode, the rotating section does not rotate around a longitudinal axis of the fuselage, providing lift for the aircraft similar to a conventional airplane. The same engines that provide torque to power the rotor in rotor flight mode also power the aircraft in fixed wing flight mode.

An improvement on the structure of electric nose suction-washer consists of a body for grip and for casing a motor mechanism. At the tip of the body are the suctioning and washing units of the motor mechanism for sucking nasal fluid or washing the nasal cavity. Therein, the body is cylindrical at a suitable place of which is a droplet shaped protrusion for easy gripping. Inside a bottom of the body encases the battery case where a spring plate exists for ease of replacing batteries and for forming power connection to the motor mechanism. The inner wall of the battery case is a plurality of vertical ridges for positioning and fastening the battery case.

An insulation blanket is disclosed that contains fire-blocking materials for preventing rapid penetration of fire into an aircraft fuselage in case of a fire outside the aircraft. The insulation blanket contains at least one layer of fiberglass or other thermal-acoustic insulation material without fire-blocking properties, and one or more layers of fire-blocking material. The fire blocking material is wider than the thermal-acoustic insulation so that it may be folded against and attached to adjacent structural frame members of the fuselage. In the alternative, a thermal-acoustic insulation material is used that has fire-blocking properties instead of the separate layers of fire-blocking and thermal-acoustic insulation materials. A method for installing insulation blankets according to the present invention is disclosed, whereby a fire-blocking insulation portion of the blanket is folded against and attached to frame members of the aircraft using attachment posts or spring clips.

An aircraft is provided comprising a fuselage and a central monitoring system positioned within the fuselage. A plurality of seating elements is also positioned within said fuselage. Each of the plurality of seating elements includes a plurality of seat options integrated into the seating element and an electronics control system integrated into the seating element. The electronics control system includes a seat processor having logic adapted to monitor an operational status of each of the seat options and communicate the operational status to the central monitoring system via wireless communication.

Adjustable Single-use lancet device that includes a body. A trigger is mounted to the body. A skin engaging end includes a lancet opening through which a lancet needle extends. A holding member is movably mounted within the body and includes a front end a rear end. The front end receives a lancet needle. A stop surface moves with the holding member. A cam disk includes cam surfaces which can be contacted by the stop surface. The cam disk is configured to rotate at least partially. The cam disk rotates about an axis that is not parallel to an axis running through at least one of the lancet opening and the holding member. Once caused to move to the extended position by the trigger, the holding member is prevented from moving back to the retracted position. This Abstract is not intended to define the invention disclosed in the specification, nor intended to limit the scope of the invention in any way.

A vertical takeoff and landing (VTOL) air vehicle disclosed. The air vehicle can be manned or unmanned. In one embodiment, the air vehicle includes two shrouded propellers, a fuselage and a gyroscopic stabilization disk installed in the fuselage. The gyroscopic stabilization disk can be configured to provide sufficient angular momentum, by sufficient mass and/or sufficient angular velocity, such that the air vehicle is gyroscopically stabilized during various phases of flight. In one embodiment the fuselage is fixedly attached to the shrouded propellers. In another embodiment, the shrouded propellers are pivotably mounted to the fuselage.

A tilt-rotor aircraft (1) comprising a pair of contra-rotating co-axial tiltable rotors (11) on the longitudinal centre line of the aircraft. The rotors (11) may be tiltable sequentially and independently. They may be moveable between a lift position and a flight position in front of or behind the fuselage (19).

A vertical takeoff and landing aircraft having a fuselage with three wings and six synchronously tilt-able propulsion units, each one mounted above, below, or on each half of the aforementioned three wings. The propulsion units are vertical for vertical flight, and horizontal for forward flight. The aircraft wings are placed such that the rear wing is above the middle wing which is placed above the front wing. The placement of each of the propulsion units relative to the center of gravity of the aircraft about the vertical axis inherently assures continued stability in vertical flight mode, following the loss of thrust from any one propulsion unit. The placement of the propulsion units, viewing the aircraft from the front, is such that each propulsion units' thrust wake does not materially disturb the propulsion unit to its rear. When engine driven propellers or rotors are utilized, flapped wing panels are attached outboard of the forward and/or rearward propulsion units to provide yaw control during vertical flight.

A VTOL vehicle comprising a fuselage having forward and aft propulsion units, each propulsion unit comprising a propeller located within an open-ended duct wall wherein a forward facing portion of the duct wall of at least the forward propulsion unit is comprised of at least one curved forward barrier mounted for horizontal sliding movement to open the forward facing portion to thereby permit air to flow into the forward facing portion when the VTOL vehicle is in forward flight.

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.

A supersonic aircraft comprises a wing, a fuselage, a plurality of fuel tanks contained within the wing and/or fuselage, and a fuel transfer system communicatively coupled to the plurality of fuel tanks and capable of transferring fuel among the plurality of fuel tanks. The aircraft further comprises at least one sensor capable of indicating a flight parameter and a controller. The controller is coupled to the one or more sensors and to the fuel transfer system. The controller can transfer fuel among the plurality of fuel tanks and adjust the aircraft center of gravity to reduce trim drag and increase aircraft range.

A hybrid propulsion aircraft is described having a distributed electric propulsion system. The distributed electric propulsion system includes a turbo shaft engine that drives one or more generators through a gearbox. The generator provides AC power to a plurality of ducted fans (each being driven by an electric motor). The ducted fans may be integrated with the hybrid propulsion aircraft's wings. The wings can be pivotally attached to the fuselage, thereby allowing for vertical take-off and landing. The design of the hybrid propulsion aircraft mitigates undesirable transient behavior traditionally encountered during a transition from vertical flight to horizontal flight. Moreover, the hybrid propulsion aircraft offers a fast, constant-altitude transition, without requiring a climb or dive to transition. It also offers increased efficiency in both hover and forward flight versus other VTOL aircraft and a higher forward max speed than traditional rotorcraft.