Abstract: A turbomachine assembly, comprising a distributor with a tubular platform, an inner radial flange extending radially inwardly from the platform, and a plurality of vanes extending radially outwardly from the platform; a casing comprising an outer radial flange; an abutment axially holding the outer radial flange in contact with the inner radial flange; a support ring attached to the casing and radially supporting the abutment; wherein the abutment is formed of a head and a body releasably connected to the head.

Abstract: A turbomachine assembly, comprising a distributor with a tubular platform, an inner radial flange extending radially inwardly from the platform, and a plurality of vanes extending radially outwardly from the platform; a casing comprising an outer radial flange; an abutment axially holding the outer radial flange in contact with the inner radial flange; a support ring attached to the casing and radially supporting the abutment; wherein the abutment is formed of a head and a body releasably connected to the head.

Abstract: The device for automatic management of an actuator controlled by a servo-valve, includes a sensor for measuring the actual value of a parameter at the output of the actuator for a given control command, a computation unit for computing a theoretical value of said parameter, by applying the control command to a nominal performance model which models the operation of the actuator exhibiting nominal performance, a computation unit for computing the difference between the measured actual value of the parameter and the computed theoretical value of said parameter, a control unit for computing an adapted gain as a function of this difference, and a link for applying the adapted gain to the servo-valve for it to use it as gain value, so as to allow the actuator to restore nominal performance.

Abstract: A protection device including a unit for implementing a protection function that prevents the aircraft from flying under a given height with respect to the ground. The device includes a unit for determining the current values of parameters, and at least the current position of the aircraft and a current heading deviation of the aircraft with respect to a landing strip. A calculation unit is provided for calculating, during a landing on the landing strip, from data including said current values, a current longitudinal distance defined in the horizontal plane and necessary for bringing the aircraft into a position for deactivating the protection function. A checking unit is provided for checking whether a condition dependent on the current longitudinal distance is met, the protection function being automatically deactivated if the checking unit concludes that this condition is met.

Abstract: The device for automatic management of an actuator controlled by a servo-valve, includes a sensor for measuring the actual value of a parameter at the output of the actuator for a given control command, a computation unit for computing a theoretical value of said parameter, by applying the control command to a nominal performance model which models the operation of the actuator exhibiting nominal performance, a computation unit for computing the difference between the measured actual value of the parameter and the computed theoretical value of said parameter, a control unit for computing an adapted gain as a function of this difference, and a link for applying the adapted gain to the servo-valve for it to use it as gain value, so as to allow the actuator to restore nominal performance.

Abstract: A protection device including a unit for implementing a protection function that prevents the aircraft from flying under a given height with respect to the ground. The device includes a unit for determining the current values of parameters, and at least the current position of the aircraft and a current heading deviation of the aircraft with respect to a landing strip. A calculation unit is provided for calculating, during a landing on the landing strip, from data including said current values, a current longitudinal distance defined in the horizontal plane and necessary for bringing the aircraft into a position for deactivating the protection function. A checking unit is provided for checking whether a condition dependent on the current longitudinal distance is met, the protection function being automatically deactivated if the checking unit concludes that this condition is met.

Abstract: Disclosed is a vertical rudder control system for an aircraft. The system is comprised of a rudder trim compensation generator that is configured to generate a rudder trim compensation order to set the position of the rudder bar of the aircraft to a neutral position in which the rudder bar is controlled with nil (i.e., zero) pilot effort. The vertical rudder control system includes a flight control calculator for calculating rudder control orders to maintain the nil effort rudder bar position, with the calculation of the rudder control orders being based on a sum of the rudder bar position, determined by a detection unit, and the rudder trim compensation order. The rudder control orders are received by a rudder operating unit, which is used to deflect the vertical rudder by a deflection value based on the rudder control orders.

Abstract: The invention relates to a method for preparing a soluble inclusion complex comprising one or several active substances which are hardly soluble in an aqueous medium and are included in one or several host molecules, using the following successive stages: (a) bringing one or several active substances into contact with one or several host molecules; (b) initiating a molecular diffusion stage by bringing a dense pressurized fluid into contact with the mixture obtained in (a) in a static mode in the presence of one or several diffusing agents; (c) recovering the active substance-host molecule molecular complex formed; (d) adding and mixing an interaction agent with the active substance-host molecule molecular complex; (e) recovering the soluble inclusion compound thus formed. The invention also relates to the soluble inclusion compound obtained by the method, particularly a piroxicam-cyclodextrin-arginine compound.

Abstract: A fly-by-wire control system for an aircraft including detection of pilot induced oscillations and a mobile control unit for such a system. According to the invention, provision is made for the pivotings of the mobile control unit to be damped by a controllable damper controlled by a detector that detects oscillations corresponding to pilot induced oscillations.

Abstract: The present invention relates to novel antibodies capable of binding specifically to the human insulin-like growth factor I receptor (IGF-IR). The invention likewise comprises the use of these antibodies as a medicament for the prophylactic and/or therapeutic treatment of cancers overexpressing IGF-IR, stimulated either by IGF1 and/or IGF2, or any pathology connected with the overexpression of said receptor as well as in processes or kits for diagnosis of illnesses connected with the overexpression of the IGF-IR and/or the IGF-I/Insulin hybrid receptor.

Abstract: The present invention relates to a compound of following formula (I): or a pharmaceutically acceptable salt or solvate of same, a tautomer of same, or a stereoisomer or mixture of stereoisomers of same in any proportions, such as a mixture of enantiomers, notably a racemic mixture; as well as to the use of same as a drug, notably intended for the treatment of cancer, inflammation and neurodegenerative diseases such as Alzheimer's disease; to the use of same as a kinase inhibitor; to the pharmaceutical compositions comprising same; and to methods for the preparation of same.

Abstract: The rudder control system (1) comprises means (10) for determining a compensation order for an actuator (6) of the aircraft rudder (7).

Abstract: The invention relates to a method and device for limiting the number of alarms generated by an anticollision system on board an airplane according to which the duration of a phase of capture of a setpoint altitude by the airplane is adjusted so that a theoretical time for collision with an intruder aircraft is greater than a predetermined threshold, when the airplane is close to said setpoint altitude and air traffic exists in the environment of said airplane.

Abstract: The invention describes a method and device for preventing useless alarms generated by an anticollision system on board an airplane and according to which the duration (dcap) of a phase of capture of a setpoint altitude (Zc) by the airplane is between a predetermined minimum execution deadline (dmin) and a predetermined maximum execution deadline (dmax).

Abstract: The present invention relates to a zinc sucrose octasulfate of the general formula I, a process for preparing same and its use in the pharmaceutical and/or cosmetic field wherein: 0?n?4 n is an integer Y represents OH, Cl, Br, I, NO3, C6H5O7, CH3CO2, CF3CO2, or —OCH3.

Abstract: The present invention relates to the use, as sole active ingredient, of dimethylaminoethanol (DMAE) in free form or in the form of salts or of esters and also of hydrates and solvates thereof, for the manufacture of a medicament for use in the treatment of a non-dementia mild cognitive impairment characterized by an amnestic syndrome of hippocampal type.

Abstract: This invention relates to a system for processing redundant signals, an associated method, as well as an aircraft comprising such a system, from a viewpoint of monitoring and passivation of erratic or oscillating failures affecting the sources of these redundant signals. The system comprises a module for calculation of a current useful signal from redundant signals; a monitoring/passivation module, able to detect an erroneous signal and to exclude the said erroneous signal from the calculation according to a criterion; and a means for toggling, as soon as an erroneous signal is detected, to a freeze mode freezing the output useful signal, and for returning, as soon as an erroneous signal no longer is detected, to a transmission mode where the current useful signal is transmitted as output useful signal.

Abstract: A piloting method and device for avoiding pilot induced oscillations filters a piloting order with a non-linear filtering function that is controlled by speed comparison information.

Abstract: The invention relates to an emollient composition for topical use that comprises a combination of glycerol, Vaseline and liquid paraffin as an active principle, in the form of an oil-in-water or water-in-oil emulsion. The invention also relates to: the use thereof for preparing a drug for treating dry skin conditions associated with certain dermatoses such as atopic dermatitis, ichthyosis conditions and psoriasis; the use thereof for preparing a drug for treating small superficial burns; and the use thereof for preparing a drug for preventing and/or treating and/or reducing the frequency and intensity of eczema attacks observed in patients suffering from atopic dermatitis.

Abstract: A terrain avoidance method and system for an aircraft includes a collision alarm device and an auto-pilot device including a first determination unit for determining a climbing order with optimal slope for the aircraft, a checking unit for checking whether a first altitude gain at the relief, by applying the optimal slope climbing order, is sufficient for clearing said relief, a finding unit for finding if at least one heading variation value exists, for which the corresponding altitude gain is sufficient to clear the relief, and a switching and calculating unit for applying to the aircraft, if the first altitude gain is sufficient, an optimal slope climbing order with an order to maintain the current heading and, if the first altitude gain is insufficient, a particular climbing order sufficient to clear the relief, with a heading order which corresponds to the selected heading variation value.