77 results about "Speed accuracy" patented technology

A method and system for implicitly resolving pointing ambiguities in human-computer interaction by implicitly analyzing user movements of a pointer toward a user targeted object located in an ambiguous multiple object domain and predicting the user targeted object, using different categories of heuristic (statically and / or dynamically learned) measures, such as (i) implicit user pointing gesture measures, (ii) application context, and (iii) number of computer suggestions of each predicted user targeted object. Featured are user pointing gesture measures of (1) speed-accuracy tradeoff, referred to as total movement time (TMT), and, amount of fine tuning (AFT) or tail-length (TL), and, (2) exact pointer position. A particular application context heuristic measure used is referred to as containment hierarchy. The invention is widely applicable to resolving a variety of different types of pointing ambiguities such as composite object types of pointing ambiguities, involving different types of pointing devices, and which are widely applicable to essentially any type of software and / or hardware methodology involving using a pointer, such as in computer aided design (CAD), object based graphical editing, and text editing.

An internal combustion engine system is disclosed that improves regulation of engine speed relative to a speed setpoint. The system controls ignition timing, throttle plate actuation, fuel valve actuation or a combination thereof in accordance with maintaining a setpoint speed. The system also includes a transient air flow estimation for further improving setpoint speed accuracy.

The invention discloses an online fault tolerance control device of a speed sensor of a permanent magnet motor. A high rotation speed estimation module and a low rotation speed estimation module are used for respectively obtaining two estimated rotation speeds omega 2 and omega 3, a rotation speed accuracy calculation module is used for receiving the rotation speed omega 1 collected by the motor and the estimated rotation speeds omega 2 and omega 3 from the two rotation speed estimation modules through the speed sensor, a prior probability is obtained by a prior probability calculation method based on the maximum likelihood estimation, and a posterior probability is calculated by a fault tolerance control module according to the prior probability. When the posterior probability f(x1) is greater than the preset threshold, the speed sensor normally works, and the collected rotation speed omega 1 is directly used as the feedback rotation speed for outputting. Or else, the feedback rotation speed is calculated according to the collected rotation speed, the estimated rotation speed and the posterior probability. The device has the advantages that a motor driving system can realize the closed loop control within wide speed adjusting range under the condition of faults of the speed sensor, the rotation speed of the motor is smoothly switched in the fault tolerance control process, and the fault tolerance control effect is improved.

The present invention discloses a method and system of joint location based on T2 / R time difference and Doppler shift. The method comprises the following steps: S1, selecting two shortwave broadcasting stations with different signal frequencies as launch stations, obtaining their emission frequencies and coordinate positions, and calculating the big circle distances of the ground between the launch stations and an accepting station; S2, calculating the time difference data and Doppler shift data between a direct wave and a scattered wave according to the signal frequencies and the big circle distances of the ground; S3, jointing the obtained time difference data and the Doppler shift data to obtain an estimating equation of a target state, and obtaining a convergence result through calculation according to batch algorithms, namely the position and the flight speed of a flying target. Only two broadcasting stations are needed to be taken as sources of radiation to locate a moving aerial target, so that the aspects of the position precision and the speed precision are greatly improved for the targets in a uniform motion and a variable motion.

The invention relates to a laser tracker based combined operating test method for a dual-arm robot. The dual-arm robot comprises an operator A and an operator B, wherein a laser tracker is used to separately measure pose parameters of the operator A and post parameters of the operator B while the operator A and the operator B separately control a workpiece 1 and a workpiece 2 to work; and dual-armcombined pose accuracy and repeatability, dual-arm combined track accuracy and speed accuracy are obtained by calculating a deviation value and weighted average of pose parameters of the operator A and the operator B, so that accomplishing degree, on workpiece assembly combined operation, of the dual-arm robot is described. The laser tracker based combined operating test method solves the problemabout test precision of related matched data in current dual-arm robot combined operation, and the like very well.

A planet power descending branch anti-interference guidance control method with an online track generation function is designed for a system state space model in which a planet lander is interfered by multiple sources in a power descending branch. The planet power descending branch anti-interference guidance control method with the online track generation function comprises the steps that firstly, a planet lander power descending branch system state space model with multi-source interference is established; then, based on the state space model with interference, an interference observer with partial information known is designed; finally, based on the interference observer, the composite guidance control method with the online track generation function is designed. The planet power descending branch anti-interference guidance control method has the advantages that a track can be generated online, anti-interference performance is strong, the landing position and speed of the lander are high in precision, and the planet power descending branch anti-interference guidance control method is suitable for accurate guidance control over the planet lander in the power descending branch in the spaceflight field.

The invention relates to a vehicle positioning method and system based on dual-antenna GNSS heading and wheel speed assistance. The method includes steps: 1) in a vehicle stationary condition, calculating initial values of position and heading according to positions and headings of GNSS antennas, and obtaining initial values of the position and the heading of a vehicle; 2) estimating the heading of the vehicle according to the initial values of the position and the heading and an angular velocity measured by inertial navigation, and calculating the position corresponding to the heading; 3) calculating an inertial navigation position and an inertial navigation heading according to a rotating speed of a motor and the calculated position corresponding to the heading, and correcting the position and the heading by employing an adaptive Kalman filtering algorithm; and 4) inputting the corrected position and heading to step 2), repeating the above steps, and outputting the final heading andposition to further obtain vehicle positioning information. Compared with the prior art, according to the method and system, vehicle information sources are fully used, the problem of low precision of the output speed of a GNSS receiver at a low speed is solved, and the method and system is advantaged by easy debugging, high estimation precision and small calculation amount.

The invention belongs to the technical field of laser target simulation, and relates to a laser moving target simulator. The laser moving target simulator is characterized in that a laser is used forradiating laser light; through a movement control module, energy is adjusted by an energy adjusting unit, and the light spot size is adjusted by a light spot adjusting unit; a light spot movement unitis used for adjusting the direction and the pitching angle of the light spot, outputting the laser light and projecting the laser light to a laser light scattering screen to form diffuse reflection laser light; and an optical collimation subsystem is used for collimating the diffuse reflection laser light and providing approximately infinitely far laser light excitation for a tested laser light guiding head. According to the wide-range, high-precision, high-speed, high-stability and high-response-speed laser moving target simulator, a reliable testing platform is provided for guiding head developing and performance testing, the problems that a traditional laser moving target simulator is narrow in energy change range, poor in linearity, low in light spot position precision, speed precision and light spot adjusting precision and the like are solved, product development and finalization are accelerated, and a great effect is achieved in the stages of designing, developing, commissioningand the like of a laser guided weapon system.

The invention provides a method and device for measuring the navigation performance of an MEMS (Micro Electro Mechanical System) inertial group. The method comprises the following steps: collecting first output data of the MEMS inertial group standing at an initial position for preset time, and performing initial alignment, thereby obtaining an initial attitude matrix; collecting second output data output by an IMU (Inertial Measurement Unit) during a process that the MEMS inertial group translates from the initial position to a target position according to a preset locus; performing inertialnavigation resolving based on the initial attitude matrix and the second output data, thereby obtaining the locus and attitude measured by the IMU as well as speed at the target position; comparing the locus and attitude measured by the IMU as well as speed at the target position with refernece values, thereby obtaining error values, wherein the error values are measurement indexes for navigationperformance of the MEMS, the refernece values include a position reference, an IMU speed accuracy reference and an attitude measurement reference, the position reference is the actual length of the preset locus, the IMU speed accuracy reference is the zero speed in a static state, and the attitude measurement reference is the attitude of the MEMS inertial group at the initial position. The methodand the device can be used for reducing the difficulty in operation of measuring the navigation performance of the MEMS inertial group.