35 results about "Moment vector" patented technology

A source for inducing an electromagnetic magnetic field, comprising: a substrate, a conductive layer coupled to the substrate, and a planar coil coupled to the substrate, wherein the planar coil comprises non-concentric rings, and wherein the non-concentric rings are configured such that a drive current applied across the non-concentric rings provides a magnetic field, and wherein the magnetic field comprises a moment vector that is tilted at an angle from the normal to a plane of the planar coil. Also provided are a method of electromagnetic tracking, a method of manufacture of a planar coil, and an electromagnetic sensor.

The invention discloses a satellite posture all-round controlling method based on a magnetic moment device and a flywheel, relating to an all-round posture controlling method for completing a satellite orbit-injection phase by using the magnetic moment device and the flywheel. The invention solves the problems of low reliability and short service life of the traditional satellite posture all-round controlling technology. The satellite posture all-round controlling method comprises the following steps of: 1, setting controller parameters according to the requirement of a control system; 2, measuring a geomagnetic field intensity vector Bb, a satellite angular velocity vector Wb and a solar azimuth, and sending the measured data to a satellite controller; 3, calculating an expected control moment vector Tm and a control magnetic moment vector Mm, and sending the control magnetic moment vector Mm to the magnetic moment device; 4, acquiring an effective solar azimuth vector Alfa; 5, calculating a control input moment vector Tw and sending to the flywheel; and 6, jointly completing the satellite posture all-round control by the magnetic moment device according to the control magnetic moment vector Mm and the flywheel according to the control input moment vector Tw. The invention is suitable for the field of satellite posture control.

The invention relates to liquid crystal meter pattern visual detection methods, and provides a liquid crystal meter pattern visual detection method based on normalization Zernike moment and gray matching. The method aims to solve the problems that image error detection rate is high, flexibility is poor, and images are rotated and zoomed. The method includes the implementation steps that 1, an image to be detected and a template image are obtained; 2, a horizontal moving image to be detected and a horizontal moving template image are generated; 3, the Zernike moment of the horizontal moving image to be detected and the Zernike moment of the horizontal moving template image are calculated; 4, a scale normalization moment Znm is generated; 5, a moment vector Zsrc and a moment vector Ztem are established; 6, a determining feature vector J is established; 7, the degree of gray matching is obtained; 8, an updated determining feature vector J' is obtained; 9, the percent of similarity is obtained; 10, a detection result is obtained. The method is applied to the field of visual detection on liquid crystal meter patterns.

The invention discloses a control system arranged on a projectile body. The control system comprises a fixed wing canard rudder and a control assembly as a permanent magnet motor and a controller used for controlling the permanent magnet motor, wherein the control assembly is arranged at a control cabin on the front part of the projectile body; the permanent magnet motor comprises a rotor, a stator and a bearing; the stator is fixedly arranged on a longitudinal shaft of the projectile body; the rotor is arranged at the periphery of the stator; the rotor and the stator are connected through the bearing; the controller is arranged in the control cabin, and is connected with the longitudinal shaft through a control circuit; the fixed wing canard rudder is arranged on the outer wall of the rotor, and comprises two pairs of rudder plates with a fixed rudder angle; one pair of rudder plates is reverse in deflecting direction, and is used for providing external pneumatic angular moment needed for reverse rotation of the canard rudder; and the other pair of the rudder plates is the same in deflecting direction, and is used for providing pneumatic-control moment vector of posture adjustment of the projectile body. The control system arranged on the projectile body is arranged, so that cost and the size of the control cabinet of a mortar projectile can be greatly reduced, and a cost-benefit ratio is greatly increased.

The present invention belongs to the technical field of inertial navigation calibration, and particularly relates to a method for eliminating shaking impact of a rotation table during high precision inertial navigation system calibration. The method comprises: firstly establishing a direction cosine matrix between a real-time vector coordinate system and a starting moment vector coordinate system; then constructing a direction cosine matrix between the starting moment vector coordinate system and a starting moment earth coordinate system; and obtaining an attitude matrix between the real-time vector coordinate system and a geographic coordinate system, wherein attitude information of a stationary state end moment is obtained. With the present invention, the technical problem of impact on calibration precision by the rotation table shaking factor during a system level calibration process of the high precision inertial navigation system is solved; and gyro output information is adopted to real timely track attitude change of the inertial navigation system due to rotation table shaking so as to eliminate adverse effects caused by the rotation table shaking, improve inertial navigation system calibration precision, and reduce requirements on rotation table locking precision during the calibration process.

The invention provides an aircraft aerodynamic characteristic on-line identification method based on a backtracking self-adaptive algorithm. The aircraft aerodynamic characteristic on-line identification method comprises steps: (1) equivalently transforming the product term of the inverse of a rotational inertia matrix and a moment vector in an aircraft angular velocity kinetic equation into a Phi<T>(k)Theta* form, carrying out discretization processing on the transformed product term, and obtaining an aircraft angular velocity difference equation; wherein Phi<T>(k) represents a signal vector,Theta* represents a parameter truth vector, and the parameter truth vector is a column vector including an aerodynamic characteristic parameter to be identified; (2) establishing a mathematical modelof an angular velocity estimation virtual system, and making an angular velocity estimation error and a parameter estimation error be Phi<T>(k)[Theta(k)-Theta*], wherein Theta(k) represents an estimated value of the parameter truth vector; (3) establishing a backtracking performance formula of the angular velocity estimation error, combining a backtracking updating rule to obtain Phi (k) in realtime, resolving the Theta(k) by means of the backtracking self-adaptive algorithm, making the angular velocity estimation error omega-wave(k) approach zero, and resolving the aerodynamic characteristic parameter to be identified according to the value of the Theta(k). The aircraft aerodynamic characteristic on-line identification method has a lower calculated amount and a lower demand on the computer, and has operability.