4960 results about "Rudder" patented technology

A propelling and driving system for boats having an outboard rudder propeller. The system provides the boat with reliable and comparatively good maneuverability. The system comprises at least two rudder propellers, each having driving motors configured in the form of a permanent magnet-excited synchronous machine. The stator winding of each synchronous machine has three winding phases connected to a three-phase alternating current, which are connected to the supply system of the boat. A modular controlling and regulating device comprising standardized modules is provided for each of the rudder propellers.

The invention relates to a method and a system for a semi-physical simulation test of visual unmanned aerial vehicle flight control and belongs to the technical field of visual system simulation. The method includes building a dynamic model of an unmanned aerial vehicle system, initializing the dynamic model, enabling an unmanned aerial vehicle to fly along the track provided by the ground, feeding flight rudder quantity information to the dynamic model to be updated, driving a three-dimensional model of the unmanned aerial vehicle through the updated dynamic model to conduct simulation and outputting simulation image and data in real time. A system based on the method is further provided. The method and the system provide effective ways and development environment for design, experiments and verification of the flight control law, have the advantages of being simple, flexible, quick, vivid and real-time, improve simulation efficiency of a flight control system, reduce test risk and test cost of the unmanned aerial vehicle and shorten development period.

The present invention is directed to the manufacture of and the use of an aerodynamic flow control device having a compact array of a plurality of fluidic actuators in planar, curved, circular and annular configurations. The compact array of fluidic actuators of the invention may be designed to produce oscillating or pulsed jets at the exit ports with frequencies in the range of 1-22 kHz. They may be integrally manufactured along with the wing sections, flaps, tail and rudder of airplane, the inlet or exit geometries of a jet engine. When supplied with a source of fluid such as air, these arrays of actuators produce a set of fluid jets of random phase of high velocity and influence the main stream of air over the subject surface. The beneficial effects of modifying flow using the present invention include increased lift, reduced drag, improved performance and noise reduction in jet engines.

An apparatus and method using GPS for dynamically adjusting side-to-side positioning of a farm implement along a geographical path. The apparatus includes a global positioning system (GPS) antenna disposed on the farm implement, a GPS receiver coupled to the GPS antenna for determining a location of the GPS antenna, and a dual guidance computer for comparing the location to stored geographical coordinates of a desired path or providing a guide signal for offsetting the lateral position of an adjustable hitch or angling a wheel or ground rudder in a steerable implement for guiding the implement along the path; and a range extent signal for maintaining the offset of the hitch or steering angle of the implement within its dynamic range.

An unmanned aerial vehicle adapted for hover and short/vertical take-off and landing (S/VTOL) is disclosed. The vehicle comprises: a body having an aspect-ratio less than two and having therein a payload volume, at least one propeller located forward of the body, at least one rudder. The body may have an inverse Zimmerman planform which provides lift as air flows across the body in horizontal flight/fixed wing mode, and further adapted such that during hover and/or short/vertical take-off and landing (S/VTOL) the vehicle operates as a rotorcraft with the body oriented with the at least one propeller substantially above the body. The vehicle is suited to a method of inspection, such as power line inspection where large distances can be analysed efficiently by flying in fixed wing mode, but by transitioning to hover mode allows detailed inspection of selected areas.

The wave powered (WP) propulsion systems developed in great amount for boats are not in use because of small effectiveness caused by rocking process reducing propellor stroke relatively water. Submarines and special quasi-dipped watercrafts deprived of this disadvantage. Their bodies keeps stable the propellors mounted on conning towers or special props owing to the body's great mass. This factor multiplies the WP propellor effectiveness meeting Navy and Merchant fleet requirements. The invention includes designs of: spare WP propulsion plant embedded into submarine diving rudders or folded into pockets of the submarine sail, quasi-dipped watercraft carrying multiple foil WP propulsion system, quasi-dipped tug towing submerged tank, self optimized foil propellor. Experiences with submarine models equipped by the WP propellers have shown excellent results. Expected velocities for submarine 4-7 knots, for the quasi-dipped watercraft 5-15 knots. The folded spare WP propulsion plant does not interrupt submarine functioning.

The invention discloses a special-purpose unmanned helicopter obstacle-avoidance system for mountain-area electrical network routing inspection and a work flow thereof. The special-purpose unmanned helicopter evadible system comprises an on-board signal acquisition module and an on-board obstacle-avoidance analysis module in a flight control system. The on-board signal acquisition module comprises a millimeter wave radar ranging sensor. The millimeter wave radar ranging sensor is connected to a signal pre-processing module and is used for transforming analog signals into digital signals, and transmitting the environmental information to the on-board obstacle-avoidance analysis module by a communication port. Corresponding instructions are transmitted to a control computer of the flight control system by the on-board obstacle-avoidance analysis module. Corresponding instructions are transmitted to an unmanned helicopter rudder control system by the control computer of the flight control system. The special-purpose unmanned helicopter obstacle-avoidance system avoids artificial intervention, ensures that the unmanned helicopter with the special-purpose unmanned helicopter obstacle-avoidance system can keep a safe distance to an electric power circuit at any time under complex mountain area terrain conditions, and prevents that the unmanned helicopter crashes the electric power circuit and other barriers because of sharp-edged gust disturbance or GPS errors.

The present invention is a 2 passenger aircraft capable of vertical and conventional takeoffs and landings, called a jyrodyne. The jyrodyne comprises a central fuselage with biplane-type wings arranged in a negative stagger arrangement, a horizontal ducted fan inlet shroud located at the center of gravity in the top biplane wing, a rotor mounted in the shroud, outrigger wing support landing gear, a forward mounted canard wing and passenger compartment, a multiple vane-type air deflector system for control and stability in VTOL mode, a separate tractor propulsion system for forward flight, and a full-span T-tail. Wingtip extensions on the two main wings extend aft to attach to the T-tail. The powerplants consist of two four cylinder two-stroke reciprocating internal combustion engines. Power from the engines is distributed between the ducted fan and tractor propeller through the use of a drivetrain incorporating two pneumatic clutches, controlled by an automotive style footpedal to the left of the rudder pedals. When depressed, power is transmitted to the ducted fan for vertical lift. When released, power is transmitted to the tractor propeller for forward flight. The aircraft can also takeoff and land in the conventional manner with a much larger payload, and is easily converted to amphibious usage. Landing gear is a bicycle arrangement with outriggers. The aircraft combines twin engines, heavy-duty landing gear, controlled-collapse crashworthy seats with a low stall speed and high resistance to stalls to eliminate any region of the flight regime where an engine or drivetrain failure could cause an uncontrollable crash.