227 results about "Tail structure" patented technology

Spinal implants are disclosed that can be used for annular repair, facet unloading, disc height preservation, disc decompression, or for sealing a portal through which an intervertebral implant was placed. In some embodiments, an implant is placed within the intervertebral disc space, primarily within the region of the annulus fibrosus. In some embodiments, the implant is expandable. In some embodiments, the implant has a sealing tail structure comprising a tail flange and a linkage. In some embodiments, the sealing tail structure limits the extrusion or expulsion of disc material, either annulus fibrosus or nucleus, into the posterior region of the spine where it could impinge on nerves. In some embodiments, the tail structure is retained in place within the annulus fibrosus by means of an anchor. In some embodiments, the anchor is constructed from multiple components.

A hollow elliptical-cylindrical hull conformingly houses a hollow rectangular-prismatic cabin whereby the four longitudinal parallel outside edges of the latter make contact with the inside surface of the former. The fully constructed aircraft (either non-powered or powered) includes the integral hull-plus-cabin structure along with nose, tail and airfoil structures that are coupled therewith. The cabin conformingly accommodates hollow rectangular-prismatic modules useful for cargo storage. While the nose and / or tail structure is uncoupled from the integral hull-plus-cabin structure, the modules are inserted into the cabin and the cabin is sealed. The aircraft is lifted (e.g., via airplane, helicopter, rocket or balloon) to a particular elevation and released, whereupon the two wings fully emerge and the aircraft effects controlled flight until reaching its destination. After landing, the nose and / or tail structure is uncoupled from the integral hull-plus-cabin structure, the cabin is unsealed, and the modules are removed from the cabin.

An adaptive aircraft tail assembly includes a tail boom, and a tail structure. The tail structure has a plurality of control surfaces configured to alter or maintain flight characteristics of the aircraft. The tail structure also has at least (i) one or more photovoltaic cells, or (ii) at least one or more solar thermal collection cells, or (iii) both photovoltaic cells and solar thermal collection cells. The tail structure also includes a rotational pivot configured to rotationally attach the tail structure to the tail boom. Preferably, the plurality of control surfaces are configured so as to be manipulatable to rotate the tail structure about a central axis of the tail boom via the rotational pivot.

A tail structure for an aircraft or spacecraft, which adjoins a fuselage section of the aircraft or spacecraft, includes a support construction for supporting at least one craft component, and a bulkhead unit intended for the pressure-tight sealing of the fuselage section and able to be coupled both to the support construction and to the fuselage section so as to form a force flow path between the at least one craft component and the fuselage section.

The disposable high speed turbine dental drill hand piece has one handle made of molded engineering plastic, and the handle has one integrated back part for connection to the dental drill hand piece and the other end made into tail structure suitable for connecting with water pipe and air pipe easily. The handle features its front part in inserting structure with O-ring for sealing the air pipe and water pipe union. The back part of the handle may be in different sizes for fast connection to water pipe and air pipe of different sizes. The handle may have one non-return valve installed to avoid back flow of water. The handle has light weight, high strength, easy manufacture and installation and low cost and is suitable for use in disposable high speed turbine dental drill hand piece.

A system and method for assembling and operating a solar powered aircraft, composed of one or more modular constituent wing panels. Each wing panel includes at least one hinge interface that is configured to rotationally interface with a complementary hinge interface on another wing panel. When a first and second wing panel are coupled together via the rotational interface, they can rotate with respect to each other within a predetermined angular range. The aircraft further comprises a control system that is configured to acquire aircraft operating information and atmospheric information and use the same alter the angle between the wing panels, even if there are multiple wing panels. One or more of the wing panels can include photovoltaic cells and / or solar thermal cells to convert solar radiation energy or solar heat energy into electricity, that can be used to power electric motors. Further, the control system is configured to alter an angle between a wing panel and the horizon, or the angle between wing panels, to maximize solar radiation energy and solar thermal energy collection. A tail assembly for the aircraft includes a rotational pivot that allows the flight control surfaces to rotate to different orientations to avoid or reduce flutter loads and to increase solar radiation energy and / or solar thermal energy collection from photovoltaic cells and / or solar thermal cells the can be located on the tail structure associated with the flight control surfaces.

Systems, methods, and devices provide a vehicle, such as an aircraft, with rotors configured to function as a tri-copter for vertical takeoff and landing (“VTOL”) and a fixed-wing vehicle for forward flight. One rotor may be mounted at a front of the vehicle fuselage on a hinged structure controlled by an actuator to tilt from horizontal to vertical positions. Two additional rotors may be mounted on the horizontal surface of the vehicle tail structure with rotor axes oriented vertically to the fuselage. For forward flight of the vehicle, the front rotor may be rotated down such that the front rotor axis may be oriented horizontally along the fuselage and the front rotor may act as a propeller. For vertical flight, the front rotor may be rotated up such that the front rotor axis may be oriented vertically to the fuselage, while the tail rotors may be activated.