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1128results about "Power plant arrangements/mounting" patented technology

Vertical takeoff and landing aircraft

InactiveUS6892980B2Superior and stable maneuverabilityEasy to operateAircraft navigation controlPropellersJet aeroplaneTurbofan
A vertical takeoff and landing (VTOL) aircraft is superior in maneuverability, safety, and mobility. The aircraft has turbofan engines with separate core engines having fan engines used commonly for cruising and lifting up. The thrust from the fan engines can be directed to all directions by supporting the fan engines of the turbofan engines with separate core engines with biaxial support so that the fan engines are rotatable in the direction of pitching and rolling. The fan engines are mounted on both sides of each of front and rear sings. With this construction, the VTOL aircraft can cruise and hover by tilting the fan engines about the two axes while using the fan engines commonly for cruising and hovering.
Owner:MITSUBISHI HEAVY IND LTD

Double ducted hovering air-vehicle

A dual ducted fan arrangement in which the duct components, engine, and avionics / payload pods are capable of being quickly disassembled to fit within common backpacking systems.. Each duct is identical in fan, stator, and control vane design. Assembly connections between ducted fans and electronic modules are also identical. An engine or APU drives the dual ducted fans through a splined shaft to a differential or through electric motors. Energy is transferred to the ducted fans by a single gear mounted to the stator hub. Relative speeds of the individual ducted fans are controlled through separate frictional or generator load control braking mechanisms on each of the splined shafts between the differential and ducted fans. In the electric motor case relative speed is through electronic speed control. The fans are counter rotating for torque balancing. The electronic module locations are vertically variable for longitudinal center of gravity for variations in payloads.
Owner:HONEYWELL INT INC

System and method for utilizing stored electrical energy for VTOL aircraft thrust enhancement and attitude control

ActiveUS20070057113A1Maximize engine efficiencyMaximize performance capabilityAircraft navigation controlPower plant arrangements/mountingCombustionAttitude control
A system and method are provided for ashort take-off and landing / vertical take-off and landing aircraft that stores required take-off power in the form of primarily an electric fan engine, and secondarily in the form of an internal combustion engine, wherein the combined power of the electric fan and internal combustion engines can cause the STOL / VTOL A / C to take-off in substantially less amount of time and space than other STOL / VTOL A / C, and further wherein the transition from vertical to horizontal thrust is carefully executed to rapidly rise from the take-off position to a forward flight position, thereby minimizing the necessity for a larger electric fan engine.
Owner:AURORA FLIGHT SCI CORP

Miniature hydro-power generation system

A miniature hydro-power generation system may produce electric power from a flow of liquid. The miniature hydro-power generation system may include a housing that includes a plurality of paddles positioned to extend outwardly from an outer surface of the housing. The system may also include a nozzle and a centering rod extending through the housing. The housing may rotate around the centering rod when a stream of liquid from the nozzle is directed at the paddles. A generator that includes a rotor and a stator may be positioned within a cavity of the housing. The rotor may be coupled with the housing and the stator may be coupled with the centering rod. The rotor may rotate around the stator at high RPM to generate electric power when the housing rotates. The electric power may supply a load and / or may be stored in an energy storage device.
Owner:ACCESS BUSINESS GRP INT LLC

Aeroengine nacelle

A nacelle (55) for a gas turbine engine (10), the engine (10) comprising accessories (34) mounted to a fan casing (28) and a core engine (9), the nacelle (55) substantially surrounds the engine (10) and comprises an intake (12) and a thrust reverser unit (31). The thrust reverser unit (31) is formed by two generally C-shaped portions (31a, 31b). The thrust reverser unit (31) is openable to provide access to the accessories (34) and the core engine (9). The nacelle (55) further comprises a fan containment casing (33) that is integral with the intake (12).
Owner:ROLLS ROYCE PLC

Gas turbine engine in-board cooled cooling air system

A system for supplying turbine cooling air flow includes a turbofan engine, a heat exchanger, and a door. The turbofan engine includes an engine case that has an inner volume within which at least a gas turbine engine is mounted, and a bypass flow passage that is defined by an outer fan duct and an inner fan duct and that is configured to direct fan air flow therethrough. The heat exchanger is disposed within the turbofan engine, is coupled to receive fluid and cooling air from the bypass flow passage, and is configured to transfer heat between fluid and the cooling air. The door is movably mounted in the turbofan engine and is movable between a closed position, in which the cooling air will not flow through the heat exchanger, and an open position, in which the cooling air may flow through the heat exchanger.
Owner:HONEYWELL INT INC

Septumization of Honeycomb Sandwiches

An acoustic liner having a honeycomb core is fabricated by forming septa in a sheet of material, and assembling the sheet of material and the core. During the assembly process, the septa are respectively inserted as a group into cells of the core.
Owner:THE BOEING CO

Unmanned air vehicle

An unmanned air vehicle for military, land security and the like operations includes a fuselage provided with foldable wings having leading edge flaps and trailing edge ailerons which are operable during ascent from launch to control the flight pattern with the wings folded, the wings being deployed into an open unfolded position when appropriate. The vehicle is contained within a pod from which it is launched and a landing deck is provided to decelerate and arrest the vehicle upon its return to land.
Owner:ISMAILOV ANVAR +1

System and method for supplying power for actuators on board an aircraft

The invention relates to a system and a method for supplying power to an aircraft comprising several generators supplying alternating current to several different primary electrical master boxes (10, 11, 12 and 13), the various aircraft loads being connected to each of these master boxes. This system comprises conventional master boxes (10, 11, 12 and 13) which supply power loads and at least one master box (40, 41) devoted to actuator loads, this at least one devoted master box being connected to conventional master boxes.
Owner:AIRBUS OPERATIONS (SAS)

Gas turbine engine

InactiveUS7886520B2Facilitate static pressure reductionAircraft navigation controlPower plant arrangements/mountingNacelleEngineering
Within a turbine engine a heat exchanger may be provided to cool compressor air flows to be utilized for cabin ventilation or other functions. A fluid flow acting as a coolant for the heat exchanger is generally drawn from the by-pass duct of the engine and a dedicated outlet duct is provided such that the exhausted fluid flow from the heat exchanger is delivered along the conduit duct to a low pressure region. In such circumstances, an appropriate pressure differential across the heat exchanger is maintained for operational efficiency when required, whilst the exhausted fluid flow is isolated and does not compromise the usual engine ventilation vent exit area sizing. Over-sized ventilation vents would create an aerodynamic step and therefore drag upon the thrust of the engine. Typically, the outlet end of the outlet duct has a variable geometry to enable adjustment in the pressure differential across the heat exchanger such that an air fan valve used to control flow rate through the heat exchanger may not be required.
Owner:ROLLS ROYCE PLC

Hazard avoidance system

A hazard avoidance system for a vehicle utilizes data related to a location of a collision threat, conditions at the location, and vehicle operating parameters to select a light illumination routine that is optimal to attract the attention of and repel a collision hazard.
Owner:UNITED STATES OF AMERICA +1

Method of Using a Device Capable Of Controlled Flight

There is provided a method of using a device capable of controlled flight in a surrounding environment, the device comprising: lifting means for providing lift to the device; object-retaining means for holding an object to be affixed to a target site; and a dispensing assembly for dispensing an adhesive, wherein the method comprises: controlling the lifting means so as to controllably fly the device in the surrounding environment; and using the device to affix an object held by the object-retaining means to a target site in the surrounding environment by dispensing an adhesive from the dispensing assembly. Thus, an aerial device, for example a robotic device, may be used to fly to a desired location and affix an object at the desired location, by dispensing, ejecting or otherwise applying an adhesive.
Owner:IMPERIAL INNOVATIONS LTD

Aircraft Having A Ring-Shaped Wing Structure

The aircraft includes a boomerang-shaped front wing (4), curving gibbously to the front, having a leading edge (4F), a trailing edge (4B) and the first and second airfoil tips (4E1, 4E2), a boomerang-shaped rear wing (6), curving gibbously to the back, having a leading edge (6F), a trailing edge (6B) and the third and forth airfoil tips 86E1, 6E2), the first wing box (8L) connecting the first airfoil tip of the front wing and the third airfoil tip of the rear wing, the second wing box (8R) connecting the second airfoil tip of the front wing and the fourth airfoil tip of the rear wing. The trailing edge of the front wing, the leading edge of the rear wing, and the internal surfaces of the wing boxes form a center opening (9) having, at least in part, elliptical shape.
Owner:RIEKEN WILLIAM D +2

Vtol aerial vehicle

A vertical take off and landing (VTOL) aircraft, which may be a UAV aircraft, is disclosed. The VTOL is capable of vertical takeoff and landing, hovering and traveling of slow speeds. In addition the VTOL permits high-speed forward flight that allows for increasing the range of the aircraft.
Owner:FRONTLINE AEROSPACE

High Altitude Aircraft, Aircraft Unit and Method for Operating an Aircraft Unit

InactiveUS20140252156A1Unlimited flying timePower installationsAircraft controlFlight vehiclePropeller
A high-altitude unmanned stratosphere aerial vehicle includes a fuselage, wings, control surfaces, and a propulsion system including an engine and a propeller. Each wing has a plurality of hoses and wing spars extending in a direction perpendicularly to the longitudinal fuselage axis and are surrounded by a skin forming a wing covering that determines the cross-sectional contour of the wing, the cross-sectional contour forming a laminar flow airfoil that generates high lift when there is low flow resistance. At the free end facing away from the fuselage, each wing has a winglet extending transversely to the longitudinal wing axis. The winglet has a movable control surface, which allows an aerodynamic side force to be generated so as to bring the aerial vehicle to a banked position.
Owner:AIRBUS DEFENCE & SPACE

Vertical take-off and landing aircraft

A vertical take-off and landing aircraft is provided with a plurality of thrust generators which generate thrust substantially vertically upward with respect to the aircraft; a first prime mover which drives the thrust generators, and an occupant seat. At least one of the thrust generators is disposed at either a front section of the aircraft or a rear section of the aircraft, and the remaining thrust generator or thrust generators are disposed at either the rear section or the front section, whichever the at least one of the thrust generators is not disposed at. The prime mover and a sitting surface of the occupant seat are disposed between the at least one of the thrust generators at the front section of the aircraft and the at least one of the thrust generators at the rear section of the aircraft, and in a position lower than all of the thrust generators. The center of gravity of the vertical take-off and landing aircraft is below the center of the aircraft and hangs down when the aircraft is in flight due to the thrust generated by the thrust generators.
Owner:TOYOTA JIDOSHA KK

Lenticular airship

An airship may include a hull substantially shaped as an oblate spheroid, one or more frame members defining a support structure, wherein the support structure forms at least a partial support for the hull, at least one horizontal stabilizing member operably coupled to a lower surface of the airship, and at least one horizontal stabilizing member having a first end and a second end. The at least one horizontal stabilizing member may define an anhedral configuration. The airship may also include a vertical stabilizing member having a first end pivotally coupled to the airship and a second end oriented to remain below an upper surface of the airship. The vertical stabilizing member may be configured to pivot within a vertical plane, and the first end of the vertical stabilizing member and the first end of the at least one horizontal stabilizing member may be operably coupled to one another.
Owner:LTA
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