91 results about "Relative wind" patented technology

A vehicle-mounted generator is powered by relative wind produced by the combination of ambient wind and motion of the vehicle, or by movement of water when mounted on the hull of a water-borne vehicle. A rigid cylindrical housing forms an enclosed interior chamber. Wind asymmetrically enters the chamber through an inlet located on one side of a central longitudinal drive shaft, and exits through an outlet located at the top of the housing. A spiraling parabolic deck forms a floor of the interior chamber, and spirals around the central longitudinal shaft from the bottom of the housing to the outlet at the top. A turbine mounted on the drive shaft within the outlet converts energy of the exiting wind to mechanical energy. An electrical generator converts the mechanical energy into electrical energy for recharging a battery or powering an electric motor.

A wiper blade for cleaning motor vehicles is proposed, which is provided with a band-like, elongated, spring-elastic support element (12). The lower band surface (13) of the support element (12) oriented toward the window (22) has an elongated, rubber-elastic wiper strip (14), which can be placed against the window (22), disposed on it so that the longitudinal axes of these two parts are parallel and the upper band surface (11) of the support element (12) has a wind deflection strip (42) disposed on it, which extends in the longitudinal direction of the support element, is provided with an attack surface (54) oriented toward the main flow of the relative wind, and is comprised of an elastic material. A considerable weight savings for the wiper blade is achieved if the wind deflection strip (42, 142, or 242) has two diverging legs (44, 46), viewed in cross section, which are connected to each other at a common base (48) and whose free ends (50, 52) oriented toward the window (22) are supported on the wiper blade (10), and the attack surface (54) is embodied on the outside of the one leg (44).

The invention discloses an autonomous control method and device of a sailing ship and the sailing ship. The method includes the steps of setting at least one waypoint; acquiring navigation information of the sailing ship and setting the next waypoint from the position where the sailing ship is located as a target waypoint; determining an expected course vector according to the relative azimuth of the sailing ship and the target waypoint and the true wind direction; controlling the sail state of the sailing ship according to relative wind direction information; controlling the rudder angle according to the current course of the sailing ship and the expected course vector so as to reach or track the expected course; judging whether the sailing ship has reached the target waypoint or not, judging whether the target waypoint is a navigation terminal point if the sailing ship has reached the target waypoint, and ending the process if the target waypoint is the navigation terminal point. According to the autonomous control method and device of the sailing ship and the sailing ship, the complete control method for autonomous navigation of the sailing ship is provided for the autonomous navigation process of the sailing ship, and autonomous control over the sailing ship is systematically achieved through division of a course area, calculation of the expected course vector, control over the rudder angle, control over the unfolding area and the adjustment angle of a sail, assisted propelling of a propeller and the like.

The invention provides a calibration method and device of the back scattering coefficient of a space-borne scatterometer. The calibration method comprises the following steps: obtaining a back scattering coefficient corresponding to a wind vector unit in the space-borne scatterometer, the observation geometry of the back scattering coefficient, and reanalysis wind field data matched with the back scattering coefficient and the observation geometry; according to the observation geometry and the reanalysis wind field data matched with the observation geometry, calculating a relative wind direction matched with the observation geometry; according to the relative wind direction, constructing the observation sample set of the obtained back scattering coefficients; and according to a preset standard sample set, calibrating the observation sample set to obtain a calibration result to show whether the back scattering coefficient measured by the space-borne scatterometer is correct or not. The reanalysis sea surface wind field data is used for developing a quick evaluation method of the back scattering coefficient of the dual-cosine distribution characteristics of the wind direction on the basis of the back scattering coefficient, the quick evaluation of the back scattering coefficient can be realized in short time, evaluation accuracy is high through the reanalysis data, and meanwhile, the evaluation method is high in universality.

An alternate means of generating the power to drive the compressor section of gas turbine engines is described. Electric motors embedded within gas turbines would rotate the compressor, and receive the requisite power to perform the compression work from: 1) either a high-capacity APU generator, or 2) from a relative-wind driven turbine in a hybrid power-sharing arrangement. The electric motor provides enhanced control of N₁ rpm, assuring greater responsiveness to control inputs.

The invention discloses a two-dimensional solid wind speed and direction measuring instrument and a measuring method thereof. The two-dimensional solid wind speed and direction measuring instrument comprises a weather cylinder, pressure pipes and sensors, wherein small holes in the even number are distributed in the cylindrical surface of the weather cylinder; one end of each pressure pipe is communicated with the small holes in the cylindrical surface of the weather cylinder, and the other end of the pressure pipe is communicated with the sensors; and the sensors are used for measuring the pressure-intensity difference between two small holes, whose horizontal distance equals the diameter of the weather cylinder, in the cylindrical surface of the weather cylinder. The measuring method comprises that the measuring instrument is fixed, and the orientation of the measuring instrument is determined; when wind in the horizontal direction acts on the instrument, the pressure-intensity difference between each two points, whose horizontal distance equals the diameter of the weather cylinder, in the cylindrical surface of the weather cylinder of the measuring instrument is measured; according to the relations between wind pressure distribution and wind speed/direction, the wind speed and the wind direction relative to the weather cylinder are calculated via the obtained pressure-intensity differences; and according to the determined orientation of the measuring instrument, the practical wind direction is calculated. Compared with a common wind speed and direction indicator, the two-dimensional solid wind speed and direction measuring instrument disclosed by the invention has the advantages of being small in size, fast in response, and not easy to damage.

A system and method uses light signals to detect and display the position of an airborne vehicle, such as a helicopter, during takeoff or landing or low speed, low altitude operation. A transmitter on the vehicle emits light signals while an optical receiver retrieves reflected light signals. Using light detection and ranging techniques, various parameters, such as altitude, ground speed and relative wind, are calculated based on the Doppler shift within the reflected light signals. The signals are transmitted in three different directions to facilitate the measurements of different Doppler shifts. The parameters are also displayed on a screen or other visual device within the vehicle.

The adjustable angle inlet for turbojet engines provides for the adjustment of the nacelle inlet as the angle of attack of the aircraft changes. The adjustable inlet system thus assures that the nacelle inlet is always oriented directly into the relative wind as the angle of attack of the aircraft changes, e.g., during takeoff, landing, and high-G maneuvers where the aircraft reaches relatively high angles of attack. The adjustable angle inlet is adaptable to most turbojet-powered airplanes, but is particularly well suited for use with aircraft having their engines mounted on lateral pylons on the rear of the fuselage. The system operates according to signals received from an angle of attack sensor. The sensor controls an actuator, which rotates a shaft that is connected to the pivotally mounted inlet of the engine nacelle.

A protection device (10) in a disk brake arrangement for protecting a brake disk (12) from dirt particles. The protection device at least partly surrounds the brake disk (12), and the protection device (10) includes at least one protection means (13) that is mounted on the wheel suspension 11 and consists at least partly of a material of which the shape is influenced by heat. The protection means has a first end position which prevents dirt particles and relative wind from striking the brake disk directly and a second end position which allows relative wind to strike the brake disk directly so as thus to obtain cooling of the brake disk. The first end position occurs when the temperature of the protection means lies below a first temperature and the second end position occurs when the temperature of the protection means exceeds a second temperature.

The oblique flow blower impeller of the present invention focuses on improving fan efficiency and reducing noise, and improves these performances by improving the structure of the fan. An impeller (1) of a diagonal flow blower is formed by arranging a plurality of thin blades (6) on a roughly truncated cone-shaped hub (4), and the front edge (2) of the blades (6) is formed in the following shape: On the meridian surface of the blade (6), a concave curve is formed on the upper side of the outer peripheral side near the midpoint (BB) of the blade tip (5) of the hub (4) and the blade (6) relative to the wind. The more hub side near the point is formed as a convex curve relative to the upper side of the wind, and the radial cross-sectional shape of the blade (6) is formed as follows: the more blade tip (5) side near the midpoint is formed as a concave curve relative to the upper side of the wind , the more hub (4) side near the midpoint is formed as a convex curve relative to the upper side of the wind. And, the leading edge (2) is formed by a helical curve.

A wind turbine including yaw control comprising a controller receiving an input signal, and providing an output control signal to a yaw actuator. The input signal to the controller is based on: a first feedback signal that is indicative of the relative wind direction determined with respect to the wind turbine, wherein the first feedback signal is filtered with a first low pass filter; and a second feedback signal that is indicative of the activity of the yaw actuator. The control technique of the invention significantly improves the ability of a yaw system to maintain a zero degree yaw error during steady state wind conditions, or in other words to maintain an accurate heading of the nacelle pointing into the wind, as well as reducing the maximum yaw error experienced during yaw system activation.

The invention discloses a control method of a wind collecting-type vertical-shaft fan and a wind generating set thereof. The method is characterized in that the inflow wind speed, the relative wind speed, the attack angle of blades and the driving force of wind wheels are controlled by adjusting the position angle of a wind collecting system of the wind collecting-type vertical-shaft fan, thus being capable of controlling wind energy efficiency and fan power; a wind collecting-type vertical-shaft wind-driven generator mainly consists of a main shaft, a wind wheel, a tower post, bearings, a pedestal, a gear box, a generator and the wind collecting system, wherein the wind collecting system mainly consists of a wind guiding wing, a wind collecting wing and a driving and controlling component; and the purpose of controlling the wind energy efficiency and the fan power is achieved by adjusting and controlling azimuth angels of the wind guiding wing and the wind collecting wing.

A method for calibrating a wind direction measurement for a wind turbine is provided. The method including: measuring plural samples of a relative wind direction representing a difference angle between a real wind direction and an orientation of a measurement equipment, in particular a direction orthogonal to a rotor blade plane, to obtain plural measured relative wind directions; deriving a measured relative wind direction change based on the measured relative wind directions; measuring plural samples of a performance parameter indicating a performance of the wind turbine; deriving a performance change based on the plural samples of the performance parameter; determining a correlation value between the measured relative wind direction change and the performance change; measuring further plural samples of the relative wind direction; and correcting the further measured relative wind directions based on the correlation value, to obtain corrected further measured relative wind directions.

The invention relates to a resistance and lift compound wind power device, in which the wing airfoil-vane of the wind wheel being a special structure with a curved surface is made of sheet. A plurality of air vanes are fixed on the rotation axis of the wind wheel being as the torque output shaft via a link rod. The intersection angle between the chord of each airfoil-vane and the link rod fixing the vanes is an angle of 60~70 degrees. Its character is that the wind vane has the compound action of resistance and lift. When the line speed of the wind vane approaches to the rated wind speed, the backward resistance produced by the wind vane and the quadratic of the relative wind speed of the wind vane forms direct proportion, so that it has automatic speed-limiting function.

The invention discloses a sea surface brightness temperature imaging simulation method based on a one-dimensional synthetic aperture microwave radiometer. The method comprises the following steps of:constructing initial background field data (frequency f, sea surface temperature Ts, seawater salinity S, incident angle [Theta], sea surface wind speed W, sea surface relative wind direction phi, atmospheric water vapor content V, cloud liquid water content L) to provide data support for sea surface brightness temperature imaging simulation; calculating the brightness temperature of the scene mode at the top of the atmosphere at different incident angles with a frequency of 6.9 GHz by using a microwave radiation transmission forward model according to the observation characteristics of the multi-incident angle of the one-dimensional synthetic aperture microwave radiometer; receiving a scene brightness temperature signal by the small antenna array of the one-dimensional synthetic aperturemicrowave radiometer to generate an electrical signal, and performing pairwise complex correlation on antenna output voltages to obtain a visibility function; and reconstructing a sea surface brightness temperature image by mathematical operations such as inverse Fourier transform. The method provides technical support for remote sensing sea surface temperature of satellite-bone one-dimensional synthetic aperture microwave radiometer.

The invention discloses a self-amending method of a standard error of a ship-based wind speed and direction transducer, which can improve the measurement accuracy of a device through online study. The technical scheme is that the self-amending method of the standard error of the ship-based wind speed and direction transducer is characterized by comprising the following steps: when relative wind speed value VR, sailing wind speed Vs and real wind speed VT satisfy 0.5<=VR-(VS+-VT)<=0.5, and the real wind speed VT >= 5.0 m/s, the standard error alpha is equal to DR; when the relative wind speed value VR, sailing wind speed Vs and real wind speed VT satisfy -0.5<=VR-(VT-VS)<= 0.5, and the real wind speed VT >= 5.0 m/s, the standard error alpha is equal to DR-180; when above limit conditions are satisfied, an amending window of the standard error is opened, a standard error value alpha 1 is obtained; along with the ship sailing under different gestures, the n standard error values are obtained and respectively marked as alpha 1, alpha 2, ...alpha n. When the n standard error value is obtained, one maximum value and one minimum value are rejected, and the remaining (n-2) values carry out the arithmetic mean, thus the standard error is obtained; the measurement result of wind speed and direction is amended by using the obtained standard error: DR=DR-alpha, and the record is amended; then the error amending in this turn is completed.

The invention discloses a method for determining a minimum turning radius based on a sailboat sail attack angle, and the method comprises the steps: building a sailboat model based on the internal relation between a sail acting force coefficient and the sail attack angle through the comprehensive consideration of sail boosting force and side thrust in combination with the parameters of a target sailboat; integrating rudder stress factors, and establishing a rudder stress model. A sailboat motion model is established by using a response type three-degree-of-freedom ship manipulation separation(MMG) method, the common influence of a sail and a rudder on the rotation performance of the sailboat is comprehensively considered, and a relative wind direction angle and a sail attack angle range capable of assisting the target sailboat to rotate are selected, so that a sail attack angle strategy for realizing the minimum rotation radius of the target sailboat is obtained, and quantitative dataare provided for virtual anchoring of the unmanned sailing ship under the condition of the minimum turning radius.