2294 results about "Fixed wing" patented technology

The invention discloses a power transmission line inspection system based on a fixed-wing unmanned aerial vehicle. The power transmission line inspection system based on the fixed-wing unmanned aerial vehicle comprises a ground station and a fixed-wing unmanned aerial vehicle, wherein the ground station comprises a ground control system, an image receiving system, and a data processing system, the fixed-wing unmanned aerial vehicle comprises an unmanned aerial vehicle body, a remote sensing monitoring device, a real-time detection device, an image transmission system, an instruction receiving system, a power system, and a flying control system. The remote sensing monitoring device is used for collecting image information in an area of a power transmission line at a fixed time or a fixed distance or a fixed spot, the real-time detection device is used for collecting information in the area of the power transmission line in real time, and the remote sensing monitoring device and the real-time detection device are arranged on the unmanned aerial vehicle body in a front-and-back adjacent and direct-to-ground mode. The power transmission line inspection system based on the fixed-wing unmanned aerial vehicle is capable of conducting periodical or emergent macroscopic inspections on the power transmission line and accessory equipment of the power transmission line, so that labor intensity of manual power transmission line inspection work is greatly reduced, and power transmission line inspection efficiency is improved.

An embodiment of a system in accordance with the present invention can include an implant having a first wing, a spacer with a thickness and a second wing, wherein a first configuration of the second wing has a first height substantially similar to the thickness and wherein the second wing is adapted to be selectably arranged in a second configuration such that the second wing has a second height greater than the first height. The implant is then urged into position between adjacent spinous processes and subsequently arranged in a second configuration to fix the implant in position.

A vertical take-off and landing aircraft includes a fixed wing airframe having opposed left and right wings extending from left and right sides, respectively, of a fuselage having opposed leading and trailing extremities and an empennage located behind the trailing extremity. Four fixed, open and horizontal, vertical take-off and landing (VTOL) thrust rotors are mounted to the airframe in a quadrotor pattern for providing vertical lift to the aircraft, and a vertical, forward thrust rotor is mounted to the trailing extremity of the fuselage between the trailing extremity of the fuselage and the empennage for providing forward thrust to the aircraft. The four VTOL thrust rotors are coplanar being and operating in a common plane that is parallel relative to, and being level with, top surfaces of the left and right wings in and around a region of each of the four VTOL thrust rotors.

The Invention is a control system for a compound aircraft. A compound aircraft has features of both a helicopter and a fixed wing aircraft and provides redundant control options. The control system allows an authorized person to select any of plurality of control biases each which is designed to achieve an overall operational objective. The control system applies the selected control bias in allocating the control function among the redundant control options.

An aircraft including an airframe having a fuselage which extends longitudinally, and having fixed wings including a main wing, a horizontal tail wing and a vertical tail wing. A propeller-rotor torque transmission has a bevel gear which transmits the rotation of an input shaft simultaneously to a propeller shaft and to a rotor shaft. An engine gearbox supplies the above-mentioned input shaft with rotationalal motive power. The aircraft further includes a propeller collective pitch controller, a rotor collective pitch controller, an engine power controller which controls the output of the above-mentioned engine gearbox for the purpose of changing the rotational speed of the input shaft, and a flight control system having a directional (yaw) control system which controls the flight direction of the aircraft by controlling the positions of the above-mentioned control surfaces.

A system and apparatus for acquiring images of electric transmission line tower structures, equipment attached to said tower structures, and transmission lines suspended from said towers. The system uses a fixed wing aircraft and an arrangement of at least one still camera, means for detecting a tower structure, a data storage unit, and a central processing unit containing operational software. The central processing unit is connected to the camera, the means for detecting a tower structure, and the storage unit. The detection means is a laser altimeter or a combination of preset longitude / latitude coordinates for tower locations and a GPS unit which supplies continuous longitude / latitude coordinates for the aircraft location for comparison to those preset coordinates. The aircraft is flown along the transmission line at a predetermined altitude above the tops of said towers (60–100 feet). The still camera points rearwardly relative to the line of flight of the aircraft and take a picture from between two adjacent towers and along an exposure line directed downwardly at an angle to the line of flight, 30–60 degrees and preferably 45 degrees. The detecting means transmits a signal to the central processing indicative of the presence of a tower to be photographed. The central processing unit calculates the time delay necessary for said aircraft to fly past the tower to a predetermined exposure point located between the tower to be photographed and the next tower in said transmission line after the tower to be photographed. The still camera is activated at the exposure point to acquire an image of the tower structure. The data corresponding to the acquired image is transmitted to a data storage unit for later retrieval and examination to identify defects in the tower or the equipment or transmission lines suspended form the tower. The system is reset to continue acquiring images along the transmission lines. The system is also provided with a video capability to film the towers and transmission lines and the line right-of-way.

A fixed-wing VTOL aircraft features an array of electric lift fans distributed over the surface of the aircraft. A generator is (selectively) coupled to the gas turbine engine of the aircraft. During VTOL operation of the aircraft, the engine drives the generator to generate electricity to power the lifting fans. Power to the lifting fans is reduced as the aircraft gains forward speed and is increasingly supported by the wings.

A tilt-rotor compound VTOL aircraft has a multiple-flow thrust generator(s) comprising a gas-powered tip-jet driven rotor(s) having a thrust-augmentation ratio of at least two; that tilts about the aircraft's pitch axis wherein the rotor's plane of rotation is substantially horizontal for VTOL operations and the rotor's plane of rotation is substantially vertical forward flight operations. A relatively small fixed-wing sustains the aircraft during forward flight. Compressed exhaust gas from the fan-jet engine(s) is ducted to a manifold having valves which control power to the multiple-flow thrust generator(s) and to the jet exhaust nozzle(s) as supplemental thrust for forward propulsion and yaw control. The manifold also serves to distribute compressed gas to the dead engine side of the aircraft in the event of a dead engine emergency, and to reaction jets for attitude control during VTOL operations. Thus this tilt-rotor aircraft is more efficient, faster, immensely lighter, less complex and less expensive to purchase and maintain than its shaft-driven counterparts.

A vehicle incorporating a hybrid propulsion system. In one form, the vehicle may be an aircraft such that the system includes gas turbine engines as a first motive power source, and one or more battery packs as a second motive power source. Through selective coupling to an electric motor that can in turn be connected to a bladed rotor or other lift-producing device, the motive sources provide differing ways in which an aircraft can operate. In one example, the gas turbine engines can provide operation for a majority of the flight envelope of the aircraft, while the battery packs can provide operation during such times when gas turbine-based motive power is unavailable or particularly disadvantageous. In another example, both sources of motive power may be decoupled from the bladed rotor such that the vehicle can operate as an autogyro. In another mode of operation, the movement of a bladed rotor can be both decoupled from the sources of propulsion as well as fixed relative to the aircraft such that the aerodynamic surfaces formed on the bladed rotors can act as a fixed wing. In another particular form, the vehicle may be ground-based or water-based.

A method of stabilizing a jet-powered tri-mode aircraft as the aircraft travels in a helicopter mode, a compound mode, and a fixed-wing mode is disclosed. The method includes receiving a plurality of velocity vector component values and velocity vector commands derived from either (1) a number of pilot operated controllers or (2) a commanded array of waypoints, which are used for fully automated flights, and a rotor speed reference value, which is decreased with increasing forward speed to unload the rotor, thereby permitting conditions for stopping the rotor in flight. Stabilization of the commanded velocity vector is achieved in all modes of flight using blended combinations of rotor swashplate controls and aerodynamic controls such as elevons, canards, rudders, and a horizontal tail. Stabilization to the commanded velocity vector includes a plurality of control constraints applied to the pilot stick controllers that prevent penetration of envelope limits.

The compound helicopter is a hybrid combination of a helicopter and a fixed wing aircraft. A conventional helicopter is modified with a nose-mounted tractor propeller to provide thrust for forward flight. Wings are added to provide lift during forward flight. With the propeller providing thrust and the wings lift during forward flight, the helicopter rotor blades are unloaded during cruising flight to allow increased forward speed by avoiding limitations of conventional helicopters, including retreating rotor blade stall and maximum rotor blade tip speeds. A single powerplant drives both the main rotor and the nose-mounted propeller. The compound helicopter employs high aspect ratio wings with large flaps that may be extended to reduce vertical drag during vertical flight and hovering operations.

A hybrid fixed wing aircraft converts into a roadworthy vehicle in a matter of seconds therefore operating efficiently in both air and ground transportation systems. The single piece wing is mounted on a skewed pivot that is on the lower portion of the fuselage and is operated by a pushbutton operating system. The aircraft includes telescopic twin boom tail design that when extended allows good pitch stability and damping. The aircraft's wing area may be increased with additional telescopic wing tip segments. This allows an increase in aspect ratio, hence improving efficiency at high loads. This feature will also creates a reduction in induced drag at cruise speed by simply retracting the tips in flight. The vehicle has a unique synchronized control system that switches from flight to ground mode without input from the operator, thereby providing a natural interface for the operator.

Systems and methods for transitioning an aircraft between helicopter and fixed wing flight modes are provided. In one embodiment, an aircraft comprises a plurality of wings each having a spar and a flap; a flap actuator configured to move the flap with respect to the spar; and a center section rotatably coupled to each spar. The center section includes at least one spar actuator configured to rotate at least one of the wings about a rotational axis of the spar when the aircraft transitions between helicopter and fixed wing flight modes.

Multi-wing hovering and gliding flapping Micro Air Vehicles (“MAV”) are disclosed. The MAV can have independent wing control to provide enhance energy efficiency and high maneuverability. Power to each wing can be controlled separately by varying the amplitude of the wing flapping, the frequency of the wing flapping, or both. The flapping frequency can be controlled such that it is at or near the natural frequency of the wings for improved energy efficiency. The wings can be controlled by a gear train, coil-magnet arrangement or many other actuation systems that enable variable frequency flapping, variable amplitude flapping, or a combination of both. The gear train mechanism provides gyroscopic stability during flight. The wing flapping can include a rotation, or feathering motion, for improved efficiency. The wings can be transitioned between flapping flight and fixed wing flight to enable gliding and hovering in a single configuration.

The lift, propulsion and stabilising system for vertical takeoff and landing aircraft of the invention consists of applying during vertical flight on, below or in the interior of the fixed-wing aircraft one or more rotors or large fans each one with two or more horizontal blades, said rotors are activated by means of turboshafts, turbofans or turboprops with a mechanical, hydraulic, pneumatic or electrical transmission, and the respective motors. Using lifting and / or stabilising and / or controlling fans and / or oscillating fins and / or air blasts. Placing the horizontal lifters near at least one end of the longitudinal axis and of the transverse axis of the aircraft. Generally said stabilising elements form 90° with one another and with the central application point of the rotor or application of that which results from the lift forces.

The invention discloses a flying automobile with front folding wings and rear folding wings are arranged in series. The front wings are arranged on two sides of the front part of an automobile body; the rear wings are arranged on two sides of the rear part of the automobile body; after being turned and folded, the front wings can be collected on two sides of the automobile body in parallel or collected in a front carriage in a vertical stacking manner; after being turned and folded, the rear wings can be collected on the rear upper side on the top of the automobile body; large-area solar battery panels are arranged on the surfaces of respective parts of the wings and the automobile body; when the wings are unfolded completely, the flying automobile is turned into a serially-arranged fixed wing airplane and becomes a giant solar charger, and the solar battery panels and batteries supply power; when the wings are folded, the appearance and the size of the flying automobile are the same as those of a common sedan; and an underwater propeller is arranged at the bottom of the automobile, so that the flying automobile can be landed on water and sails in the water. The flying automobile is well combined with functions of an airplane, an automobile and a ship and is environment-friendly and high in continuous voyage capacity and suitable for families.

A multi-mode unmanned aerial vehicle includes an elongated fuselage, a right and left fixed wing extending from a respective right and left side of the elongated fuselage, a right and left tilt wing attached at a first side to a free end of the respective right and left fixed wing, a right and left duct attached to a second side of the respective right and left tilt wing, a right and left winglet attached to the respective right and left duct opposite to the right and left tilt wing, a tilt tail located within a curved guide slot at a rear end of the elongated fuselage, a rear duct attached to the tilt tail, a tilting mechanism, and an integrated autonomous flight control system.

The following steps are performed in the method of constructing an aircraft: taking a subassembly comprising two wings that are rigidly fastened together, and fitting it to a fuselage wall; and fastening the subassembly to the wall by means of fastener elements that are distinct from the subassembly and that present main axes that are vertical.

The present invention discloses a fixed-wing and electric multi-rotor composite aircraft, including an electric multi-rotor dynamic system and a main controller, the fixed-wing dynamic system and electric multi-rotor dynamic system are mutually independent structurally, the main controller includes the fixed-wing control system and an electric multi-rotor control system which is used for controlling the operation of the electric multi-rotor dynamic system, the main controller is also used for controlling the fixed-wing control system and the electric multi-rotor control system to operate independently or synergistically, the rotor rotating plane of the electric multi-rotor dynamic system is parallel to the airframe central shaft. The aircraft is able to shift between two flying modes freely, and takes off, lands and flies like a helicopter as well as a fixed-wing aircraft. A fixed-wing aircraft-helicopter mixed mode can also be used in the take-off, landing and flying process.

The invention provides a fixed-wing multi-shaft aircraft, and belongs to the field of aircrafts. The fixed-wing multi-shaft aircraft comprises a fixed wing and a multi-shaft rotor wing rack which are connected with each other, and the multi-shaft rotor wing rack is provided with multiple rotor wing mechanisms; the rotor wing mechanisms comprise propellers and rotating shafts, the propellers are rotatably connected with drive devices, the drive devices are fixedly connected with the rotating shafts, and the rotating shafts are connected with rotating control mechanisms. The fixed-wing multi-shaft aircraft has the advantages of both a fixed-wing aircraft and a multi-shaft aircraft, can achieve a multi-shaft mode, a fixed-wing mode and a fixed-wing and multi-shaft mixed mode and also has the advantages of achieving vertical taking-off and landing and hovering and being high in flying speed and long in flying time.

A spherical plain bearing has an outer ring having a concave first bearing surface and an inner ring having a convex second bearing surface slidably disposed to the first bearing surface. The inner ring member also has a third bearing surface for engaging a pin to be mounted in the bearing. At least one bearing surface has a lubrication groove, and one of the outer ring and the inner ring is made from 440 stainless steel while the other is made from a precipitation-hardened martensitic stainless steel. Alternatively, the outer ring and the inner ring may be made from steel and a copper-beryllium alloy. In yet another alternative, the bearing need not have a lubrication groove, but may have a lubrication liner on the third bearing surface. A dropped hinge mechanism for a flap on a fixed wing aircraft has a hinge that includes such a bearing.

An aircraft propulsion system comprises a power plant driving a number of outboard propulsion units to propel a fixed wing aircraft.

The composite rotating fixed-wing aircraft consists of the coaxial counter-paddle, reverse gear, engine output shaft, engine with a starter-generator, wings, tail blades, landing device, culvert, steering gear, fairing, fuselage, motor, motor drive shaft, wing control unit of small angle of attack, aileron rudder surface, and tailplane rudder surface. Co-axial counter-blade is located in the upper part of the aircraft, which connects with the engine output shaft; the reverse gear is installed between the co-axial counter-propellers; the motor connects with motor drive shaft powered by the starter-generator of the engine; the wings are located on both sides of aircraft and connect with the fuselage; the tail blades are located at the aircraft tail, which are installed behinde motor drive shaft; the landing device is located under the lower part of the fuselage and fixed with it; the culvert connects with the landing device; the fairing is installed in the culvert and connects with the steering gear; the wing control unit of small angle of attack is installed on the wing. The aircraft design method has six steps with strict scientific idea; this invention has a wide range of practical value and application prospect.

Embodiments of the invention are directed to an unmanned air vehicle (UAV) system and a small unmanned air vehicle (SUAV) system for deploying and towing a sensor in a tow medium, and to methods related thereto. A UAV-sensor towing package comprises a fixed-wing UAV including a control and signal processing platform, a long range data RF link operably connected to the control and signal processing platform, a UAV wireless data link operably connected to the control and signal processing platform, and a tow body deployment system operably connected to the control and signal processing platform; a tow line attached at an end thereof to the UAV; a tow body attached to another end of the tow line; and a communications link including a transmitter / receiver component coupled to the tow line, and a T / R wireless data transmission link (194) operably connected with the transmitter / receiver component and the UAV wireless data link.

A compound Vertical TakeOff and Landing (VTOL) aircraft. In a specific embodiment, the VTOL aircraft includes a gas-powered tip-jet driven rotary-wing and a fixed-wing that is capable of providing necessary lift to the aircraft during certain forward-flight regimes so that lift from the rotary-wing is not required. This enables slowing of the rotor, thereby reducing drag during forward flight and enabling flight above and below mu-1. Valves and accompanying ducting are employed to control compressed gas flow to the rotary-wing. Various reaction jets are employed for attitude control during VTOL and transition operations. The aircraft further includes a jet exhaust nozzle to provide forward thrust to facilitate forward flight.

The present invention relates to an aircraft comprising a fuselage (100) comprising a fuselage axis (101), a first wing arrangement (110) and a second wing arrangement (120). The first wing arrangement (110) is mounted to the fuselage (100) such that the first wing arrangement (110) is tiltable around a first longitudinal wing axis (111) of the first wing arrangement (110) and such that the first wing arrangement (110) is rotatable around the fuselage axis (101). The second wing arrangement (120) comprises at least one propulsion unit (122), wherein the second wing arrangement (120) is mounted to the fuselage (100) such that the second wing arrangement (120) is tiltable around a second longitudinal wing axis (121) of the second wing arrangement (120) and such that the second wing arrangement (120) is rotatable around the fuselage axis (101). The first wing arrangement (110) and the second wing arrangement (120) are adapted in such a way that, in a fixed-wing flight mode, the first wing arrangement (110) and the second wing arrangement (120) do not rotate around the fuselage axis (101). The first wing arrangement (110) and the second wing arrangement (120) are further adapted in such a way that, in a hover flight mode, the first wing arrangement (110) and the second wing arrangement (120) are tilted around the respective first longitudinal wing axis (111) and the respective second longitudinal wing axis (121) with respect to its orientations in the fixed-wing flight mode and that the first wing arrangement (110) and the second wing arrangement (120) rotate around the fuselage axis (101).

The invention relates to an ARM and FPGA (Field Programmable Gate Array) architecture based autopilot of a fixed wing unmanned aerial vehicle, which belongs to the technical field of an embedded-control unmanned aerial vehicle. The autopilot uses two processors. The main processor is responsible for controlling calculation while the slave processor is responsible for collecting and outputting signals. The slave processor is designed as a peripheral device of the main processor. The main processor can operate the slave processor by way of operating the self storage space, so that extra workload due to data exchange between two processors is reduced, work is divided clearly, and the system response speed is fast. A design ideal of a top layer module with multiple bottom layers is adopted with distinct gradations, and operation is carried out by using a state machine in reading of an A / D (Analog / Digital) module, so that the work efficiency is higher.

The invention relates to a convertible aircraft operating method. According to the invention, the aircraft comprises: a fuselage, standard fixed wings which are equipped with ailerons, a tail unit with flight-control surfaces, engines, a rotor with blades, a transmission which is placed between the engines and the rotor and which is equipped with rotor clutch and braking means, a landing gear, means for transition from helicopter mode to gyroplane mode and vice versa, and means for direct or reverse transition from gyroplane / helicopter mode to aeroplane mode. The lift for a range of low speeds is produced by means of the rotor, while the lift for a range of high speeds is produced by means of the wings. In addition, the lift for a range of intermediate speeds can be produced using the wings and the rotor in gyroplane mode simultaneously, and take-off and landing can be performed in gyroplane mode or in helicopter mode with the engines coupled to the rotor. The aircraft comprises a hybrid helicopter / gyroplane / aeroplane aircraft and, as such, can perform the direct or reverse transition to aeroplane mode from both helicopter mode and gyroplane mode.