2151 results about "Takeoff" patented technology

A method and apparatus for charging energy supplies in an unmanned aerial vehicle (UAV). The present invention relates to a UAV that comprises an inductive charging device that utilizes the electromagnetic field emanated by overhead / utility power lines, to charge the energy supplies. The UAV also includes a releasable latch for holding power lines to allow for the perching of the UAV on power lines during the charging process. The latch and the inductive charging device may be provided on a single device, a battery augmentation trap (BAT). The UAV may be perched in an upright orientation to allow for takeoff after the charging of energy supplies on the power line.

The Unmanned Aircraft Systems ground support platform is a portable, multifunctional apparatus to accommodate UAS (Drone, UAV) landings, takeoffs, idle time, maintenance, retail merchandise product display and package delivery support within the UAS recreational and business industry. The Unmanned Aircraft Systems ground support platform will provide stability and cleanliness of a Unmanned Aerial Vehicle. Ownership identification is intergraded into the base platform.

The present invention relates to a reduced scale industrial helicopter, with an integrated automatic flight control system, that includes core autopilot functions, GPS management, and full-function navigation systems. The autopilot technology includes rapid launch capability, real-time in-flight switching between one or more of a) remote control, b) autopilot-directed, c) ground station controlled, and d) home modes, and is upgradeable. The helicopter is used for high or low altitude surveillance, and can handle various payloads, including photographic missions. The helicopter may include onboard batteries and / or a unique battery unit disposed beneath the helicopter, and includes autonomous features such as automatic takeoff, automatic landing, safety return to home base, and predetermined mission plans.

A manned / unmanned aerial vehicle adapted for vertical takeoff and landing using the same set of engines for takeoff and landing as well as for forward flight. An aerial vehicle which is adapted to takeoff with the wings in a vertical as opposed to horizontal flight attitude which takes off in this vertical attitude and then transitions to a horizontal flight path. An aerial vehicle which controls the attitude of the vehicle during takeoff and landing by alternating the thrust of engines, which are separated in least two dimensions relative to the horizontal during takeoff. An aerial vehicle which uses a rotating platform of engines in fixed relationship to each other and which rotates relative to the wings of the vehicle for takeoff and landing.

An aerial vehicle adapted for vertical takeoff and landing using a set of wing mounted thrust producing elements and a set of tail mounted rotors for takeoff and landing. An aerial vehicle which is adapted to vertical takeoff with the rotors in a rotated, take-off attitude then transitions to a horizontal flight path, with the rotors rotated to a typical horizontal configuration. The aerial vehicle uses different configurations of its wing mounted rotors and propellers to reduce drag in all flight modes.

One embodiment of the invention sets forth a CAD application configured to perform quantity takeoff computations. The CAD application is further configured to organize a CAD drawing into a hierarchical representation of object families and associated object types, where instances of the object types represent drawing objects present in the CAD drawing. The CAD application is further configured to receive a selection of an object family and to parse the selection to determine the object types associated with the selection. The CAD application then creates a takeoff object for each of the object types associated with the selection and identifies instances, associated with object properties, of each of the object types of the selection. The CAD application quantifies the instances and associated properties to produce a quantity takeoff value. Advantageously, users are able to more quickly and easily estimate the cost of a design project associated with the CAD drawing.

A washing system for high temperature cleaning applications, such as carpet-cleaning, is disclosed that provides a consistent cleaning fluid temperature. The washing system utilizes multiple heat exchangers and multiple heat paths. The heating and power source is provided by a medium duty, diesel cycle engine. Multi-stage heating involves heat transfer from the engine's coolant to the cleaning fluid and heat transfer from the exhaust of the engine to the cleaning fluid via an intermediate medium. The system also includes a fluid clutch used to engage a power takeoff from the engine to operate the pump and blower of the washing plant. A failsafe source cutoff diverts the exhaust flow from thermal contact with an intermediate heat transfer oil.

An automatic takeoff thrust management system can be used in an aircraft with at least two engines. The management system comprises an aircraft status sensor or set of sensors capable of detecting establishment of takeoff climb conditions, and engine failure detectors respectively coupled to the at least two engines and capable of detecting engine failure. The management system further comprises thrust control modules respectively coupled to the at least two engines and capable of controlling the thrust of the engines, and a controller coupled to the aircraft status sensors, the engine failure detectors, and the thrust control modules. The controller reduces thrust by a selected amount upon detecting establishment of takeoff climb conditions and, if engine failure is detected, restoring thrust to an initial or a higher schedule.

An aerial vehicle adapted for vertical takeoff and landing using a set of wing mounted thrust producing elements and a set of tail mounted rotors for takeoff and landing. An aerial vehicle which is adapted to vertical takeoff with the rotors in a rotated, take-off attitude then transitions to a horizontal flight path, with the rotors rotated to a typical horizontal configuration. The aerial vehicle uses different configurations of its wing mounted rotors and propellers to reduce drag in all flight modes.

A power take-off for an electric vehicle. The power take-off includes a variable speed electric motor for driving at least one wheel of the vehicle. A transmission, including a neutral state, coupled to the electric motor. An auxiliary output shaft is coupled to the transmission. When the transmission is in the neutral state, the auxiliary output shaft will operate at a speed independent of wheel speed and dependent on the electric motor speed. When the transmission is operably engaged in other than the neutral state, the auxiliary output shaft will operate at a speed related to both the electric motor speed and the wheel speed.

A system and method for automating Air Traffic Control operations at or near an airport. as a complete standalone automated system replacing the need for a human controller to make aircraft movement decisions nor the need communicate with pilots, or as semi-automated, where a controller controls how the system operates. The system with related methods and computer hardware and computer software package, automatically manages manned aircraft, remote controlled UAV and airborne-able vehicles traffic at or near an airport, eliminates ATC-induced and reduce pilot-induced runway incursions and excursions, processes control messages related to aircraft or Pilots, communicates with Pilot over ATC radio frequency, receives aircraft positions, communicates control messages with the aircraft avionics, provides pilots a dynamic map with continuous display of nearby traffic operations, shows clearance and information related to runway operations, warns pilot of runway conditions and turbulence from other operations, warns when landing gear is not locked, displays the pilot emergency exits during takeoff roll, shows the pilot when and where to exit from the runway, shows the pilot where and when to cross a junction, calculates and displays pilot optimal speed and timing on taxiways and junctions for saving fuel, calculates congestions, calculates best taxiway routes, calculates when aircraft can cross a runway, provides directives and information to pilot over CPDLC display or dynamic map for airside operations, alerts and triggers breaks of the aircraft on wrong path or when hold-short bar is breached, displays emergency personnel with routing map and final aircraft resting position for emergency operations, takes over an aircraft operation when aircraft is hijacked or deviates from the flight plan, provide standalone or manned Remote Tower functionality, Records and retains all information related to airport airside operations including aircraft positions and conditions from sensors and reports for runways, junctions and taxiways, Records and retains aircraft data and cockpit voice to ground-based servers to eliminate black-box requirements, calculate future weather and airport capacity from aircraft at or nearby airport, coordinates handoff operations with other ATC positions, interfaces with ACDM systems, airport operations center, flow center and network operations center.

A method and system for air flight is shown. The blended lifting body system includes a lift module, a propulsion module, a payload module and a control system. A conventional control system morphs the other modules through variable buoyant lift, internal structures and a flexible exterior, and varies bio-inspired oscillation in the propulsion module in order to facilitate takeoff, flight and landing. The hybrid dynamic / morphing shape buoyant, dynamic lift-assisted (hybrid) air vehicle, employing aquatic-like (e.g. fin) propulsion was discussed, with many variations and examples.

A manned / unmanned aerial vehicle adapted for vertical takeoff and landing using the same set of engines for takeoff and landing as well as for forward flight. An aerial vehicle which is adapted to takeoff with the wings in a vertical as opposed to horizontal flight attitude which takes off in this vertical attitude and then transitions to a horizontal flight path. An aerial vehicle which controls the attitude of the vehicle during takeoff and landing by alternating the thrust of engines, which are separated in at least two dimensions relative to the horizontal during takeoff, and which may also control regular flight in some aspects by the use of differential thrust of the engines. A tailless airplane which uses a control system that takes inputs for a traditional tailed airplane and translates those inputs to provide control utilizing non-traditional control methods.

A system for facilitating automated landing and takeoff of an autonomous or pilot controlled hovering air vehicle with a cooperative underbody at a stationary or mobile landing place and an automated storage system used in conjunction with the landing and takeoff mechanism that stores and services a plurality of UAVs is described. The system is primarily characterized in that the landing mechanism is settable with 6 axes in roll, pitch, yaw, and x, y and z and becomes aligned with and intercepts the air vehicle in flight and decelerates the vehicle with respect to vehicle's inertial limits. The air vehicle and capture mechanism are provided with a transmitter and receiver to coordinate vehicle priority and distance and angles between landing mechanism and air vehicle. The landing and takeoff system has means of tracking the position and orientation of the UAV in real time. The landing mechanism will be substantially aligned to the base of the air vehicle. With small UAVs, their lifting capacity is limited. Reducing sensing and computation requirements by having the landing plate perform the precision adjustments for the landing operation allows for increased flight time and / or payload capacity.

A smart airport automation system includes a subsystem that inputs weather and airport configuration data to determine an active runway in use and an airport state. Another subsystem inputs aircraft position and velocity data from available surveillance sources, known flight-intent information, and past aircraft trajectories to project future aircraft unconstrained trajectories. A third subsystem uses the projected trajectories and aircraft intent to determine desired landing and takeoff sequences, and desired adjacent aircraft spacing. A fourth subsystem uses such information to predict potential aircraft conflicts, such as a loss of acceptable separation between adjacent aircraft. A fifth subsystem packages the weather, airport configuration, aircraft state, desired landing / takeoff sequence, and potential conflict detection into a verbal advisory message that is broadcast on a local common radio frequency. A sixth subsystem uses the projected trajectory information to control the runway and taxiway lighting system.

In a power line takeoff clamp assembly and method of use thereof an electrical power distribution line is clamped to a body of the clamp assembly. A power takeoff supported by the body clamped to the power line generates direct current from alternating current flowing in the power line. One or more sensors supported by the body clamped to the power line sense one or more values related to an electrical current flowing in a power line. A wireless transceiver supported by the body clamped to the power line communicates data regarding the one or more sensed values. Each sensor and the wireless transceiver utilize direct current generated by the power takeoff for the operation thereof.

The present disclosure relates to a high performance Vertical Takeoff and Landing (VTOL) aircraft for executing hovering flight, forward flight, and transitioning between the two in a stable and efficient manner. The VTOL aircraft provides a highly stable, controllable and efficient VTOL aircraft. The preferred comprises: (1) a pusher propeller configuration with strategic placement which maximizes the effective use of thrust, (2) four propellers which allow for the highly-controllable and mechanically simple control methods used in multirotor aircraft, (3) electric motors which create mechanically simple, lightweight and reliable operation, (4) and a tandem wing configuration which is stable, controllable and efficient in both hovering and forward flight. The VTOL aircraft is capable of full runway, short runway or vertical takeoffs or landings, having unobstructed forward view for camera and sensor placement; and providing a compact, mechanically simple and low-maintenance VTOL aircraft design.

An aircraft has a bearing structure, the bearing structure having at least one central fuselage and two pylons each situated at a distance laterally from the fuselage. In addition, the aircraft has a wing structure, at least four hub rotors, and at least one thrust drive. Each hub rotor is fastened to the bearing structure, has a propeller having two propeller blades, and produces, through rotation of the propeller, an upward drive force acting in the vertical direction on the aircraft. The thrust drive is produces a thrust force acting in the horizontal direction on the bearing structure. The pylons each have two hub rotors, the hub rotors being configured to arrest respective propeller blades of a hub rotor in a position relative to the pylons. In the arrested position, the propeller blades of a hub rotor do not extend beyond the outer dimensions of the pylons.

The invention consists of a specific, matched arrangement of aeronautical elements which (1) eliminates aerodynamic interference of, and (2) adds variable-cycle propulsion to, the level flight mode of a four-propulsor tilt-wing VTOL (vertical takeoff & landing) aircraft, without an additional element of variable geometry. This is achieved by configuring the components such that the rotor planes on either side pass through each other in the transition maneuver to form adjacent, close-coupled, counter-rotating pairs in level flight.

A kinetic energy system which transfers the kinetic landing into recoverable electric energy for an aircraft. The system incorporates at least one wheel supporting the aircraft for landing and takeoff coupled with a dynamic functioning motor / generator mounted to and operated by rotation of the wheel to create electrical energy from kinetic energy. An induction shoe structurally connected to the aircraft and electrically connected to the motor / generator, which shoe draws the converted energy from the generator which supplies the load created by the inductively coupled induction shoe to the an ancillary load provided by the resistive heat sink on by the capacitor storage bank. This provides the generator circuit for conversion of the rotational energy of the wheel to electrical energy and creates braking drag. In exemplary embodiments, the system employs an energy storage system acting as the load to store electrical potential energy created by the generator. Additionally, the generator is employable as a motor, receiving energy from the storage system for traction power to the associated aircraft wheel. An induction grid or a surface mounted conductive layer mounted into or onto a runway is employed for transferring energy to and from the motor / generator.

Systems and methods for operating a twin scroll turbocharged engine with a junction configured to selectively control exhaust gas delivery to an exhaust gas recirculation system and a twin scroll turbine are provided.

A vertical take off and landing (VTOL) aircraft is designed to be so efficient that it can be commercially competitive with runway dependent aircraft operating in a range of 100 to 1000 miles. Improvements include a high efficiency tilting rotor and wing design that enable both vertical takeoff and efficient high speed cruising, a high aspect ratio wing, and a variable speed propulsion system that is efficient in both hover and cruise flight. Preferred aircraft use thin inboard and outboard wings, thin rotor blades, and use efficient lightweight design to achieve unusually low empty weight fraction. Inventive methods include utilization of advanced design and analysis techniques, which allow for accurate prediction of an aircraft's physical behavior.

The invention provides for a vertical takeoff and landing capable aerial vehicle with multiple rotors that is designed to carry agricultural sensors and telemetry allowing for real time control of agricultural equipment in accord with sensor data. The ability to carry a suite of agricultural sensors combined with multiple rotors will allow the craft to operate quickly in hovering and longitudinal flight over rows of farm fields and other vegetation and use an NDVI imager and other sensors to take data readings and real time imagery which will allow farmers and other personnel to determine vegetation type, need for chemical applications, plant fertilization, irrigation requirements, and other vegetation features including types of vegetation present. This will allow for precision agricultural, vegetation, and crop management and for farmers it will increase the efficiency of precision agriculture operations.

Status information on plane, passenger, cargo, crew, fuel, food, baggage, maintenance, weather and any other process used to manage airport operations, including expediting aircraft turnaround time for takeoff, is gathered into a common decision support database. The system includes decision support tools to increase the sharing of information between airline, airport, contractors and the Federal Aviation Administration (FAA), to more efficiently and safely manage the service, maintenance and operations of aircraft.

A lift assembly having a drum rotatably mounted to a frame and linearly translatable with respect to the frame. A plurality of head blocks are connected to the frame along a helical mounting path, wherein linear translation of the drum during takeoff or take-up maintains a predetermined fleet angle between a take off point from the drum and the head block.

The present invention includes improvements to cross-flow fans and cross-flow fan propelled aircraft including improved control, a dynamically adjustable vortex wall and internal housing, a vortex tube, vertical takeoff and landing rotorcraft configurations, the inclusion of an optimized oscillating blade fan, a wavy vortex wall, power plant refinements, dual leading and trailing edge configurations, stability improvements, tip plates, tapered wings, tapered fans, a fan construction method, and underwater applications.

A vehicle includes a wing and a control surface pivotably coupled to the wing and configured to pivot about a range of motion. A propulsor is coupled to the control surface and configured to rotate between a first position associated with a hover flight mode and a second position associated with a forward flight mode. The propulsor is aerodynamically actuated between the first position and the second position due to aerodynamics about the wing. The propulsor may rotate from an initial flight mode, such as a takeoff mode, to a second flight mode, such as a forward flight mode.

A drive train includes an internal combustion engine (“ICE”) coupled to a transmission having a power takeoff port. A transfer device couples an electric motor to the transmission via the port. The electric motor is enabled in a certain configuration to selectively power the drive train during at least certain intervals when the ICE is powered off.

A vertical-takeoff aircraft with a wing. A first drive unit and a second drive unit are swivellably mounted on the wing. The first drive unit and the second drive unit are arranged on the wing at a distance from a wing-end of the wing. A first distance between the first drive unit and a longitudinal axis of the aircraft is approximately equal to a second distance between the second drive unit and the longitudinal axis of the aircraft. The first drive unit and the second drive unit are swivellable into a horizontal flying position and a vertical flying position. In the horizontal flying position the first drive unit is arranged above a wing surface and the second drive unit below the wing surface on the wing. In the vertical flying position the first drive unit and the second drive unit are arranged in an approximately horizontal plane. The first drive unit and the second drive unit each have a swivel arm, wherein the swivel arms are swivellably mounted on the wing.