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651 results about "Error state" patented technology

Patient-worn energy delivery apparatus

A patient-worn energy delivery apparatus for imparting electrical therapy to the body of a patient responsive to an occurrence of a treatable condition includes a voltage converter for converting electrical energy from an initial voltage to a final voltage, and a defibrillator electrically coupled between the converter and the patient and having an energy reservoir for receiving the electrical energy. The defibrillator produces preshaped electrical pulses such as defibrillation pulses and cardioversion pulses. The apparatus additionally includes an energy delivery controller electrically coupled to the patient and the converter and the defibrillator. The controller causes the converter to provide the electrical energy to the defibrillator at a specific charging rate in response to an energy level in the reservoir. The apparatus may include a plurality of electrodes interposed between the defibrillator and the patient and each electrode preferably has an impedance reducing means contained therein. One embodiment of the apparatus may include a H-bridge to produce a positive-going pulse segment and the negative-going pulse segment within the biphasic exponential signals. The apparatus periodically measures the energy as it is being delivered to the patient and can pre-emptively stop or truncate the pulse in the event an error condition is detected, such as an overvoltage condition or if the energy level approaches a predetermined level. The electrical components which store and release the energy minimize the size and expense of the apparatus, while isolating the microcomputer from the high energy levels as the therapeutic pulse is delivered.
Owner:ZOLL MEDICAL CORPORATION

Fault-tolerance autonomous navigation method of multi-sensor of high-altitude long-endurance unmanned plane

The invention discloses a fault-tolerance autonomous navigation method of a multi-sensor of a high-altitude long-endurance unmanned plane. The method comprises the following steps of: firstly, carrying out theory analysis on work environment and work characteristics of three navigation sensors including GPS (Global Position System), CNS (astronomy) and SAR (Synthetic Aperture Radar), and establishing an observation linearity measurement equation by combining a geography system based on a position combined observation principle of inertia / GPS, inertia / astronomy and inertia / SAR under an airborne geography system; then analyzing error characteristics of a navigation sensor and simulating the output during the fault of GPS, and establishing a corresponding fault detection algorithm unit to carry out fault detection and isolation on a filter; and finally, designing and completing an inertia / GPS combined navigation system mathematic model based on the assistance of astronomy and SAR, and optimally evaluating the error state of the inertia navigation by means of federated filtering. The invention has high navigation precision, and can fully play the role of evaluating the error state quantity of an airborne inertia navigation system by the combined navigation of the multi-sensor under the geography system.
Owner:NANJING UNIV OF AERONAUTICS & ASTRONAUTICS

Speedometer-assisted vehicle-mounted dynamic alignment method

ActiveCN108180925AAvoid the limitations of standing stillIncrease flexibilityDistance measurementGyroscopeSimulation
The invention relates to a speedometer-assisted vehicle-mounted dynamic alignment method. The method is technically characterized by comprising steps as follows: in an inertial navigation system, inertial navigation calculation is performed, and attitude heading, speed and position information is output and updated; mileage decomposition is performed by use of an attitude angle of vehicle displacement increment output and inertial navigation calculation of a speedometer, and speedometer navigation position calculation is completed; an error model of the inertial navigation system and an errormodel of navigation position calculation are taken as equations of propagation of an error state, an attitude angle error of the inertial navigation system is estimated and calibrated by use of a Kalman filter. Deep integration is performed through the Kalman filter by use of displacement increment information provided by the vehicle-mounted speedometer and gyroscope and accelerator data providedby an inertial measurement assembly, in the running process of a vehicle, a combined navigation technology of accurate alignment of attitude heading and correction function of position errors is completed, the starting process of the vehicle-mounted navigation system can be simplified, the reaction time is shortened and the maneuvering characteristics of a carrying vehicle are improved.
Owner:TIANJIN NAVIGATION INSTR RES INST

Double-shaft continuous rotation-based hybrid type platform inertial navigation system calibration method

The invention discloses a double-shaft continuous rotation-based hybrid type platform inertial navigation system calibration method. The method comprises the following steps: (1) performing coarse alignment to obtain a coarse initial attitude matrix; (2) controlling an outer ring shaft and a platform body shaft of a platform system to rotate at the same angular speed, enabling an inner ring shaftto be under a locked state, and acquiring gyroscope and accelerometer output in the rotating process; (3) resolving an error state equation and an observation equation and calibrating gyroscope scalefactor error, gyroscope mounting error and accelerometer equivalent zero offset; (4) controlling an outer ring frame angle, an inner ring frame angle and a platform body frame angle to lock in a zerostate, rotating the platform body shaft by 180 degrees and locking, and acquiring output data of the gyroscope; (5) controlling the outer ring frame angle, the inner ring frame angle and the platformbody frame angle to lock in the zero state, rotating the outer ring shaft by 180 degrees and locking, and acquiring output data of the gyroscope; and (6) calculating the constant drift of the gyroscope. By the method, the calibration time is effectively shortened and the calibration efficiency is improved.
Owner:BEIJING INST OF AEROSPACE CONTROL DEVICES
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