Patent application number | Description | Published |
20090070635 | METHOD OF IMPROVING THE INTEGRITY AND SAFETY OF AN AVIONICS SYSTEM - The present invention relates to a method of improving the integrity and safety of a system, this method making it possible, on the one hand, to detect and to locate an anomaly of a system, and on the other hand to estimate the impact of such an anomaly on the degradation of performance, with a view to attaining the safety level required and to making the data provided by this system safe, and this method is characterized in that it consists, in a system comprising sub-assemblies, in monitoring the proper operation of sub-assemblies by checking their respective transfer functions in the operational mode with the aid of stimuli dispatched to these sub-assemblies. | 03-12-2009 |
20100026567 | HYBRID INS/GNSS SYSTEM WITH INTEGRITY MONITORING AND METHOD FOR INTEGRITY MONITORING - The invention pertains to the monitoring of the integrity of position and speed information arising from a hybridization between an inertial reference system and a satellite-based positioning receiver. The invention relates more precisely to a navigation apparatus known in the art by the name INS/GNSS system (for “Inertial Navigation System” and “Global Navigation Satellite System”) hybridized in closed loop. | 02-04-2010 |
20100324822 | Navigation System Using Hybridization by Phase Measurements - The invention relates to a navigation system for aircraft comprising inertial sensors, a GNSS receiver and potentially a baro-altimeter. The measurements from the inertial sensors are hybridized with the code and phase measurements from the receiver within a main Kalman filter and, possibly, secondary filters. The said measurements are corrected for several types of errors, notably those due to the passage of the satellite signals through the ionospheric layers. The precision of the determination of the position of the aircraft is greatly improved, both in the horizontal plane and in the vertical direction. This is also the case for the corresponding protection radii, which allows margins to be created in order to satisfy the integrity constraints for the navigation solution. | 12-23-2010 |
20110084874 | HYBRID SYSTEM AND DEVICE FOR CALCULATING A POSITION AND FOR MONITORING ITS INTEGRITY - Hybrid system ( | 04-14-2011 |
20120004846 | AIR NAVIGATION DEVICE WITH INERTIAL SENSOR UNITS, RADIO NAVIGATION RECEIVERS, AND AIR NAVIGATION TECHNIQUE USING SUCH ELEMENTS - The present invention relates to an air navigation device with inertial sensor units and radio navigation receivers, and is characterized in that its radio navigation receivers are multiple-constellation receivers and in that their output data are hybridized with the data from the inertial sensor units. According to another feature of the invention, at least some of the inertial sensor units are of MEMS type. | 01-05-2012 |
20120212369 | METHOD AND SYSTEM FOR DETERMINING NAVIGATION PARAMETERS OF AN AIRCRAFT - Method for determining navigation parameters of an aircraft, characterized in that it consists at least in determining the geographic speed {right arrow over (V)}, expressed in a given local fixed coordinate system {{right arrow over (i)}, {right arrow over (j)}, {right arrow over (k)}}, based on the measurements m, of carrier phase increments Δφ | 08-23-2012 |
20120226395 | METHOD AND SYSTEM FOR DETERMINING THE ATTITUDE OF AN AIRCRAFT BY MULTI-AXIS ACCELEROMETRIC MEASUREMENTS - An inertial system measures the attitude of an aircraft consisting at least in determining the angle of pitch and/or the angle of heading and/or the angle of roll of the aircraft, each of the said angles of attitude being determined by successive double integration of their second derivative. A pair of accelerometers to determine the angle of pitch being are disposed on either side of the centre of gravity along an axis substantially merged with the longitudinal axis of the aircraft. A pair of accelerometers to determine the angle of heading are disposed on either side of the centre of gravity along an axis substantially merged with the transverse axis of the aircraft. A pair of accelerometers to determine the angle of roll are disposed on either side of the centre of gravity along a vertical axis perpendicular to the plane formed by the other axes. | 09-06-2012 |
20130030775 | Method for Determining the Position of a Mobile Body at a Given Instant and for Monitoring the Integrity of the Position of Said Mobile Body - A method for determining the position of a mobile body at a given instant and for monitoring the integrity of the position of said mobile body includes a step of determining a sustained position at the given instant by adding the integral of the hybrid speed between the preceding instant and the given instant to the position of the mobile body at the preceding instant; a step of determining the sustained protection radius associated with the sustained position by adding the integral of the hybrid speed protection radius between the preceding instant and the given instant to the position protection radius of the preceding instant; a step of determining a better position at the given instant, the better position being: when information from the first positioning device is available, the position associated with a better protection radius, the better protection radius being selected by comparing the intermediate protection radius with the sustained protection radius according to a predetermined selection criterion; and, when information from the intermediate positioning device is unavailable, the sustained position. | 01-31-2013 |