60 results about "Pitch angle" patented technology

A system and device for detecting yaw and changes in pitch angle for use with navigational and positional devices. The system and device include a multi-axis magnetic field sensing device and a controller. Preferably, the magnetic field sensing device is a multi-axis magnetic compass that is capable of sensing variations in pitch and yaw. The controller is adapted to process yaw and pitch rotational data to determine a positive or a negative change in pitch.

The invention discloses a star observation method based on error angle adaptive adjustment and an astronomical telescope, and the method comprises the steps: querying the right ascension and declination information of a target star according to a star database; obtaining a first pitch angle and a first horizontal angle of the target star according to the query result and the current geographic position and time of the star observation device; ccording to the pre-stored error angle, eliminating an error of the first pitch angle / the first horizontal angle to obtain a second pitch angle / a secondhorizontal angle, wherein the error angle is obtained according to a third pitch angle and a third horizontal angle of the selected reference star body and a fourth pitch angle and a fourth horizontalangle of the star body shot by the equipment at the angle; and adjusting the star observation device to a second pitch angle and a second horizontal angle, and shooting an image. Error calibration does not need to be carried out after the telescope is started, self-adaptive adjustment is carried out according to the pre-calculated error angle, and the angle after error elimination is automatically adjusted for observation.

The invention relates to a rapid calibration method for a directional antenna angle based on celestial body tracking scanning. The method comprises the following steps: S1, obtaining a forecast azimuth angle and a forecast pitch angle pointed by an antenna beam; S2, scanning a celestial body target at the forecast azimuth angle or the forecast pitch angle through a preset time point; S3, acquiringthe radiation noise intensity of the celestial body target under different forecast azimuth angles or forecast pitch angles; S4, acquiring the maximum radiation noise intensity in the radiation noiseintensity, and acquiring a superimposed azimuth angle or a superimposed pitch angle corresponding to the maximum radiation noise intensity; and S5, iteratively and repeatedly executing the steps S2 to S4, judging whether the obtained superposed azimuth angle and the superposed pitch angle meet calibration precision at the same time, and if so, finishing calibration of the azimuth angle or the pitch angle pointed by the antenna beam. The method is low in cost, is not liable to be affected by weather conditions, and can work all day long.

In one embodiment and method of the present invention, an optical interference fly height (FH) test apparatus for measuring FH is disclosed, in accordance with an embodiment of the present invention, to include a slider, a transparent disk, means for directing a light beam directed between the slider and the disk, and means for iteratively measuring an estimated FH using at least two points of measurement on the slider when the slider is moved away from the disk at a pitch angle, wherein the estimated FH is computed as a function of the pitch angle and during each iteration, a previously-estimated FH is used to converge the estimated FH so that the estimated FH is within a predetermined range from the actual FH.

Systems and methods for calculating L* in the magnetosphere with essentially the same accuracy as with a physics based model at many times the speed by developing a surrogate trained to be a surrogate for the physics-based model. The trained model can then beneficially process input data falling within the training range of the surrogate model. The surrogate model can be a feedforward neural network and the physics-based model can be the TSK03 model. Operatively, the surrogate model can use parameters on which the physics-based model was based, and / or spatial data for the location where L* is to be calculated. Surrogate models should be provided for each of a plurality of pitch angles. Accordingly, a surrogate model having a closed drift shell can be used from the plurality of models. The feedforward neural network can have a plurality of input-layer units, there being at least one input-layer unit for each physics-based model parameter, a plurality of hidden layer units and at least one output unit for the value of L*.

The present invention provides an attitude fusion enhanced measurement method and system based on inertial navigation technology. The method includes step 1, acquiring attitude data detected by each sensor, and performing data initialization; step 2, performing strapdown calculation on the initialized attitude data; Step 3, correct the attitude data corresponding to each sensor; Step 4, use feedback control to correct the gyro zero point according to the corrected acceleration data and magnetometer data; Step 5, output the corrected attitude data. The invention has a magnetic anomaly detection function, and the magnetic correction does not affect the pitch angle and roll angle correction; based on the nonlinear theory, better convergence speed and control precision are provided.

The invention discloses an accurate geosynchronous orbit synthetic aperture radar system parameter calculation method, which comprises the following steps: S1, obtaining a zero Doppler center through pitch-yaw attitude guidance, and obtaining a yaw angle and a pitch angle which need to be adjusted; S2, realizing attitude guidance equivalently through an antenna phase center scanning method, and obtaining an adjusted lower visual angle and an adjusted squint angle; and S3, calculating Doppler parameters according to the beam angle changing in real time. According to the method, real-time change of the beam angle in the synthetic aperture is fully considered, accurate calculation of Doppler parameters is completed, and the problem of insufficient accuracy of the Doppler parameters is solved.

The invention discloses a space-borne real-time occultation prediction method, which comprises first obtaining the position velocity of the spacecraft according to the positioning equipment of the occultation detector, and calculating the orbital parameters of the spacecraft; and then calculating the orbital parameters of the spacecraft and all navigation stars after 10s position, and calculate the pitch angle, azimuth angle, tangent point height and antenna azimuth angle of all navigation stars, and judge whether the obtained pitch angle Elv, tangent point height Hight and antenna azimuth angle meet the threshold of occultation events, if satisfied , then extrapolate the time for 30s and 1min, and repeat the above calculation and judgment process respectively. If all are satisfied, it is determined that the navigation star is an occultation. The present invention judges occultation events by adopting continuous arc segments by inertial navigation equipment, thereby enhancing the accuracy of forecast results, the method is simple and easy, and has important application value for real-time forecast.

The invention discloses a multi-parameter alternating search-based metrewave radar low elevation height measurement method, mainly solves the problem that the error in the height measurement of up and down positions in the prior art is large. The method comprises the following implementation steps: extracting a target signal from a radar echo to obtain a covariance matrix of the target signal; calculating a synthesis steering vector by using a direct steering vector and a reflected steering vector; estimating the pitch angle of a direct wave to obtain an estimated value; estimating the pitch value of a reflected wave to obtain an estimated value; performing alternating search on a ground reflection coefficient magnitude, a ground reflection coefficient phase, the pitch angle of the direct wave and the pitch angle of the reflected wave to obtain the estimated values of each parameter; judging whether the alternating search is finished or not; searching the pitch angle of the direct wave to obtain the estimated value of the pitch angle of the direct wave, namely the precise elevation of a target; and obtaining the target height. The method does not depend on precise radar position altitude parameters; the adaptive capacity of radar to the position is enhanced; the height measurement precision is improved; and the method can be used for target positioning and tracking.

The invention relates to an active classification and positioning method for underwater targets based on a reliable acoustic path. First, the active detection method is used to obtain a two-dimensional pitch angle-distance map in the target scene, and a pitch angle-distance curve is drawn according to the reliable acoustic path. Utilize the curve to classify the target to extract the pitch angle and distance of the underwater target, combine the sound field information to convert the pitch angle and distance of the underwater target into the horizontal distance and depth, and obtain the positioning result. The present invention can effectively target the target in the deep sea environment position.

The invention discloses an attitude measuring method and device. First obtain the pitch angle, roll angle, geomagnetic three-component and angle change, and then calculate the attitude quaternion by solving the pitch angle, roll angle, and geomagnetic three-component, and then filter the attitude quaternion and angle change to obtain The quaternion output data; finally, the angle transformation is performed on the quaternion output data to obtain the attitude result. The invention compensates the obtained three components of pitch angle, roll angle and geomagnetism through the obtained angle variation, avoids magnetic interference and high-frequency shaking, improves measurement accuracy and realizes dynamic measurement.

The invention relates to a monitoring device for a three-dimensional posture, a mechanical device and a monitoring method for the three-dimensional posture. The monitoring device comprises a circuit board, a tri-axial accelerometer, a tri-axial magnetometer, three mutually vertical uniaxial gyroscopes and a processing control module, wherein the tri-axial accelerometer, the tri-axial magnetometer and the uniaxial gyroscopes are arranged on one side of the circuit board, and the processing control module is arranged on the other side; and the processing control module is used for performing preset deviation compensation on a linear acceleration output by the tri-axial accelerometer and a magnetic field strength output by the tri-axial magnetometer, respectively calculating a pitch angle, a roll angel and a course angle of a carrier by referring to a gravity vector on the position of the tri-axial accelerometer and an earth magnetic field vector on the position of the tri-axial magnetometer, performing coordinate transformation on the linear acceleration output by the tri-axial accelerometer and the magnetic field strength output by the tri-axial magnetometer, and then adopting a data fusion algorithm for correcting the pitch angle, the roll angel and the course angle of the carrier and performing error compensation on a rotating angular velocity output by a three-axis gyroscope. According to the invention, the measurement and regulation precision for the three-dimensional posture of the carrier can be effectively promoted.