Abstract:
PURPOSE: A position estimation device and method using an acceleration sensor are provided to calculate gravity acceleration without a rotary motion component by using three shaft angular speed measured by a gyro sensor and three shaft acceleration measured by acceleration sensors. CONSTITUTION: First and second acceleration sensors measure three shaft acceleration. A gyro sensor measures three shaft angular speed of a position estimation device. A magnetic sensor detects an azimuth of the position estimation device. A sensor signal processor converts analog sensor signals to a sensor signal for digital calculation. [Reference numerals] (110) Controller; (120) Memory unit; (132) Display unit; (134) Touch sensing unit; (136) Pressurization sensing unit; (140) Interface unit
Abstract:
PURPOSE: Fault detector and detecting method for the pose control system of a spacecraft are provided to reduce the fault detection and enhance performance by minimizing the generation of a model filter. CONSTITUTION: A fault detector for the pose control system of a spacecraft comprise a first mutual interference multi-model fault detecting block(120) and a second mutual interference multi-model fault detecting block(130). The first mutual interference multi-model fault detecting block generates a plurality of upper filters. The upper filters comprise a normal model filter for a plurality of drivers and a fault model filter for each driver. The first mutual interference multi-model fault detecting block detects fault on the drivers from the upper filters using a mutual interference multi-model estimating technique.
Abstract:
PURPOSE: A logic circuit for detecting and recovering errors in a SRAM-based field programmable gate array is provided to perform error detection and an error selection function. CONSTITUTION: First circuit units(10,20) generate a first output value by using a time redundancy method about data 0 and data 1. A second circuit unit(30) receives the first output value from the first circuit units. The second circuit unit creates a time redundancy comparison output value and hardware spare comparison output value using the first output value. The second circuit unit detects errors of the first circuit units using the time redundancy comparison output value and hardware spare comparison output value.