Patent application number | Description | Published |
20110291879 | SYSTEM AND METHOD FOR DETECTING AND DETERMINING REMOTE ATMOSPHERIC ANOMALIES - A system for detecting and determining remote atmospheric anomalies is furnished with a movable-beam anemometry probe for measuring the orthogonal projection onto the sighting axis, named the radial component, of a relative velocity remotely, with respect to a remote air mass by Doppler frequency shift. The system comprises means for determining wind heterogeneities remotely, on the basis of at least two successive measurements, at one and the same remote point, of the radial component of the relative velocity of the system with respect to the remote air mass, by said anemometry probe, the line of sight of said anemometry probe comprising said remote point during said successive measurements. | 12-01-2011 |
20120089362 | System for Determining the Airspeed of an Aircraft - A system for determining the true airspeed vector, defined by a magnitude and by a direction, of an aircraft comprising a fuselage, comprises four laser anemometers each having a single measurement path so as to measure a local component of the true airspeed and being distributed in different locations around the fuselage of the aircraft; and means for calculating the magnitude and direction of the true airspeed vector of the aircraft using the four measurements of components of the true airspeed. | 04-12-2012 |
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 |
20130145836 | Probe for Measuring a Local Angle of Attack and Method Implementing Same - A probe for measuring a local angle of attack designed to be fixed to a wall and a method implementing the probe are provided. The probe comprises at least three pressure sampling ports disposed over a nose of the probe body, pressure measurement means associated with the pressure sampling ports and calculation means capable of determining an angle of attack of the flow with respect to the main direction of the probe body as a function of the pressures measured by the pressure measurement means. The calculation means are configured for choosing from amongst the pressure sampling ports those allowing the best measurement precision of the local angle of attack to be obtained and for calculating the local angle of attack with respect to the main direction using the pressure measurements carried out in the chosen pressure sampling ports. | 06-13-2013 |
20140020479 | DEVICE FOR MAINTAINING AND ANALYZING AN AERODYNAMIC PROBE - A device for maintaining and analyzing an aerodynamic probe of stagnation pressure type intended to be installed in an aircraft comprises a channel with a first end that is intended to penetrate into the probe, and means for creating in the channel an air depression relative to the ambient pressure and means for recovering any particles sucked into the channel. | 01-23-2014 |
Patent application number | Description | Published |
20140047761 | CENTRIFUGAL FLUID RING REACTOR - The Centrifugal Fluid Ring Reactor employs a centrifugal impeller and a fluid barrier to mix multi-phase fluids and repeatedly move the mixture through a reaction zone, where the mixture contacts catalysts and/or is subjected to electromagnetic, mechanical, nuclear, or sonic energy to create ions, free radicals or activated molecules, which initiate or promote a desired reaction. It can be used to convert carbon dioxide, methane and other gaseous carbon sources into liquid fuel at ambient temperature and pressure. | 02-20-2014 |
20140113980 | CENTRIFUGAL FLUID RING PLASMA REACTOR - The Centrifugal Fluid Ring Plasma Reactor employs a centrifugal impeller and a fluid barrier to mix multi-phase fluids and repeatedly move the mixture through a reaction zone, where the mixture contacts catalysts and/or is subjected to electromagnetic, mechanical, nuclear, and/or sonic energy to create ions, free radicals or activated molecules, which initiate or promote a desired reaction. In one embodiment, high-voltage electromagnetic energy is applied to Cobalt and Tungsten/Thorium electrodes in the reaction zone to create plasma. The Centrifugal Fluid Ring Plasma Reactor is suitable for converting carbon dioxide and methane into useful fuel products and for performing other multi-phase chemical reactions. | 04-24-2014 |