4518 results about "Airframe" patented technology

The present invention relates to a system for retrieving data from remote difficult to reach terrain, such as wilderness areas, etc. and in particular to a system comprised of one or more surface based data collectors in communication with one or more wireless transceivers adapted to transmit the collected data to an unmanned aerial vehicle adapted to fly within a predetermined distance from the data collector and receive data collected therefrom. The present invention further relates to an unmanned aerial vehicle adapted to fly a flight pattern relative to a moveable surface object or for controlling the position of a moveable surface object relative to the flight path of the unmanned aerial vehicle. Finally, the present invention relates to an improved unmanned aerial vehicle having airframe structural elements with electrical circuits adhered to the surfaces of the structural elements.

An advanced internal combustion-electric hybrid airplane, having at least double the flight range and flight duration than a conventional equivalent airplane, while using the same amount of any desirable fuel. This is achieved by using 2-3× smaller and ultra-lightweight engine for cruising, and ultra-lightweight electric motor powered by lithium batteries during take-off and climbing. The electric motor becomes a generator during cruising and descent, recharging said batteries. The airplane has also temporary silent electric stealth capability and added safety by the electric back-up power. Due to its high efficiency, the operational cost is substantially reduced. Additional features include highly advanced, minimum drag and weight airframe.

The invention relates to a flush-mounted aircraft, UAV or missile antenna system, which is an integral part of the fuselage (3) of an aircraft, UAV or missile. The antenna system comprises a surface (3) made of a conductive material and a resonant recess (4) formed in said conducting surface, wherein said recess is conformed to provide a resonant behaviour in a selected operating frequency, the antenna system further comprising a radiating element (2) located within said recess and a feeding element (5) within said recess coupled to said radiating element.

A fail-safe lug is carried by an engine frame member and receives a clevis carried by an engine mount member. The mount member includes side links that transmit transverse loads between the engines and the airframe and a thrust link that transmits axial, engine thrust loads between the engine and the airframe. A fail-safe pin is carried by the clevis and has an outer diameter that is smaller than an aperture in the lug and through which the pin passes, so that no loads are imposed on the fail-safe pin in normal operation. When one or more of the links are no longer capable of transmitting loads, the fail-safe arrangement becomes operative to accommodate the loads transmitted between the engine and the airframe.

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.

A method of forming a structural airframe component for an aircraft and an airframe structural component The method includes placing at least two components (1,2) in abutting relationship with each other and joining them together by friction stir butt welding (3), and the structural airframe component comprises a component manufactured according to the method of the invention.

A rotorcraft including a fuselage, one or more motor-driven rotors for vertical flight, and a control system. The motors drive the one or more rotors in either of two directions of rotation to provide for flight in either an upright or an inverted orientation. An orientation sensor is used to control the primary direction of thrust, and operational instructions and gathered information are automatically adapted based on the orientation of the fuselage with respect to gravity. The rotors are configured with blades that invert to conform to the direction of rotation.

A system and method for integrating air and ground transportation of passengers and cargo. The system comprises a plurality of universal passenger containers. The system further comprises a plurality of universal cargo containers. An airplane is provided with a hollow fuselage adapted to be loaded with a plurality of passenger and/or cargo containers. A flatbed trailer can be provided to carry a passenger or a cargo container. A tractor vehicle can be provided to transport flatbed trailers between airplanes, locations within the airport, and points of origin and destination outside the airport complex. A system can be provided to load and unload passenger and cargo containers into and out of airplanes at the airport. A system is provided comprised of an airport complex including take-off and landing runways, taxiways, airplane staging areas, apparatus for detection of weapons in passenger and cargo containers, and air terminals with arrival and departure gates and baggage handling conveyors. A system is also provided comprised of remote air terminals at strategic locations a distance from the airport complex.

A camera system is composed of a lens unit and a camera body. The lens unit has a built-in CCD. A magnet is embedded in a protrusion of the lens unit. A case of the camera body is made of a magnetic material. In virtue of this, it is possible to attach the lens unit to any position of the camera body on condition that functions of the camera body are not disturbed by the lens unit. Incidentally, a cable is utilized to perform data transmission and electric-power transfer between the lens unit and the camera body.

The present disclosure provides a fuselage of an unmanned aerial vehicle. The fuselage comprises an upper plate, a lower plate opposite to the upper plate, a connecting plate, and a middle spacing plate; the connecting plate is connected between the upper plate and the lower plate; the upper plate, the lower plate, and the connecting plate are enclosed to define a receiving space; the upper plate, the lower plate, the connecting plate, and the middle spacing plate are integrally formed; the upper cavity is located between the middle spacing plate and the upper plate, and the lower cavity is located between the middle spacing plate and the lower plate; and a first mounting opening is defined in the upper plate allowing a component to enter the upper cavity, and a second mounting opening is defined in the lower plate allowing a component to enter the lower cavity.

Three-dimensional large scale bodies such as jumbo aircraft fuselages (14) are assembled in body sections around a central longitudinal assembly core (1) which itself is mounted at its ends and accessible all around along its length. Robots carrying tools for holding, transporting and precisely positioning preassembled wall shell sections, are movable along the central core (1). First, at least one floor grid (2 or 3) is releasably mounted to the core. Then, side wall shell sections (4, 5) are secured to the floor grids. Then, top and bottom wall shell sections (10, 8) are secured to the side wall shell sections (4, 5) to form a body section (BS) of the large scale body (14). Neighboring body sections are secured to each other along cross-seams. Upon completion, the floor grids are released from the core (1) and the core is removed preferably withdrawn longitudinally from the assembled large component or body.

The invention provides an unmanned plane route planning and remote synchronous control method, and relates to the field of unmanned plane control. The method provided by the invention can be wieldy applied to intelligent mobile equipment including mobile phones and panel personal computers. A system can be divided into two major parts, wherein an unmanned plane serves as an actuating end for measuring attitude angle, the longitude and latitude and the height information of an airframe, and sending the information to the intelligent mobile equipment through a wireless data transmission module or a Wi-Fi module, and synchronously receiving the information returned via the intelligent mobile equipment, and executing relevant flight operation. The intelligent mobile equipment can be inclined and rotated to acquire the angle data output via a gyroscope and an accelerometer on the equipment, thus, the unmanned plane can perform the same action as the equipment; and the intelligent mobile equipment has he functions of receiving and displaying data, and returning the information to the unmanned plane through an external wireless data transmission module or the Wi-Fi based on the command and flight information set on a touch screen. With the adoption of the method provided by the invention, the flexibility of an unmanned plane system can be improved; and the unmanned plane system can be simply operated just like playing a game.

The invention discloses an unmanned air vehicle with multiple rotary wings in a plane-symmetry layout, comprising a body, rotary wing assemblies and undercarriage, wherein, the number of the rotary wing assemblies is an even number more than or equal to 4; each rotary wing assembly comprises a rotary wing support arm, a rotary wing motor and a rotary wing, the rotary wing motor is fixed at the outer end of the rotary wing support arm; the rotary wing is arranged on a rotation shaft of the rotary wing motor and is driven by the rotary wing motor; the longitudinal symmetrical planes of the all rotary wing assemblies relative to the body are distributed in a bilateral symmetry mode, and are fixedly connected with the two sides of the body through the inner ends of the rotary wing support arms; an equipment compartment and a power source compartment separated front and back are arranged in the body, the equipment compartment comprises a navigation component, a flight control component and a communication component; the power source compartment comprises a battery for providing power to the electronic equipment of the whole air vehicle; the undercarriage is fixedly connected at the lower part of the body; and the flight control component is provided with a flight control computer with the functions of fault diagnosis of the multiple rotary wings and fault-tolerant flight control. The unmanned air vehicle has the advantages of novel appearance layout, concise internal structure, reliable system control and better engineering application value, and is easy for engineering implementation.

The invention is a modular vehicle having an air vehicle that can be coupled to cargo containers, land vehicles, sea vehicles, medical transport modules, etc. In one embodiment the air vehicle has a plurality of propellers positioned around a main airframe, which can provide vertical thrust and/or horizontal thrust. The propellers are mounted on supports which have an airfoil shape to generate additional lift. One or more of the propellers may be configured to tilt forward, backward, and/or side-to-side with respect to the airframe.