Abstract: An assembly including a nacelle element, such as a cover, a device for locking the nacelle element, a key for locking/unlocking the locking device and an indicator for indicating the position of the locking device. This assembly includes a control device which is configured to be actuated by the key when the key is withdrawn from the locking device so as to make the indicator move from a first state to a second state, the state of the indicator being representative of the locked or unlocked position of the locking device.

Abstract: A thrust reverser for a turbojet aircraft nacelle includes a fixed structure, a movable structure and an actuator. The actuator extends along a main axis and is connected by a first connection to the fixed structure and by a second connection to the movable structure for the deployment of the movable structure between a direct jet position and a reverse jet position. The actuator is also connected to the fixed structure by a third connection arranged longitudinally between the first connection and the second connection. An axis of the third connection is radially eccentric from the main axis and the third connection allows a predetermined displacement of the actuator with respect to the fixed structure.

Abstract: The present invention relates to an immunocytokine comprising (a) a conjugate, and (b) an antibody or a fragment thereof directly or indirectly linked by covalence to said conjugate, wherein said conjugate comprises (i) a polypeptide comprising the amino acid sequence of the interleukin 15 or derivatives thereof, and (ii) a polypeptide comprising the amino acid sequence of the sushi domain of the interleukin 15R alpha (IL-15R?) or derivatives thereof; and uses thereof.

Abstract: A thrust reverser including a stationary structure, a lower door and an upper door. This reverser includes at least one deflector configured to be able to redirect forward from the stationary structure a portion of fluid exiting the reverser according to a trajectory oriented towards a lateral opening extending between the stationary structure and the upper door. Such a deflector makes it possible to improve the control of the air current lines acting on a tail unit and in particular on a control surface of an aircraft equipped with such a reverser when the latter is in thrust reversal configuration, thereby making it possible to improve the controllability of this aircraft.

Abstract: The present invention discloses compounds according to Formula I: Wherein R1, L1, R2, L2, R3, Cy, and the subscript n are as defined herein. The present invention relates to compounds, methods for their production, pharmaceutical compositions comprising the same, and methods of treatment using the same, for the prophylaxis and/or treatment of allergic diseases, inflammatory diseases, metabolic diseases, autoinflammatory diseases, autoimmune diseases, proliferative diseases, transplantation rejection, diseases involving impairment of cartilage turnover, congenital cartilage malformations, and/or diseases associated with hypersecretion of IFN?, IL12 and/or IL23 by administering the compound of the invention.

Abstract: The invention concerns a method for estimating the state of health (SOH) of an electrochemical element, comprising: initiating a charging or discharging operation of the electrochemical element; measuring values representing deformations of the electrochemical element while the charging or discharging operation is being performed, the deformation values measured forming a deformations image signal according to the quantity of electricity passing through the electrochemical element over time; comparing the deformations image signal and a reference image signal, one or more differences obtained by the comparison characterising an estimation of the ageing of the electrochemical element.

Abstract: A thrust reverser for an aircraft bypass turbojet engine nacelle has a generally annular shape around an axis and includes an annular frame for securing deflection grids. The frame has a first frusto-conical wall widening in the downstream direction and including an upstream peripheral edge configured to be attached to a casing of the turbojet engine. A downstream peripheral edge of the wall extends in the continuation of the wall and secures the upstream ends of the grids. A second annular wall extends radially outwards from an outer frusto-conical face of the first wall. The first and second walls are integrally formed and the second wall has axial openings through which actuators pass.

Abstract: The invention relates to an air intake of an aircraft turbojet engine nacelle extending along an axis X, in which an air flow circulates from upstream to downstream, the air intake comprising an inner wall and an outer wall which are connected by a leading edge and an inner partition so as to delimit an annular cavity, the air intake comprising means for injecting at least one hot air flow into the inner cavity and at least one ventilation orifice formed in the outer wall in order to allow the hot air flow to escape after heating the inner cavity, the air intake comprising at least one acoustic member positioned in the inner cavity facing the ventilation orifice so as to modify the acoustic resonance frequencies and/or to attenuate the acoustic waves formed in the inner cavity via the ventilation orifice.

Abstract: The invention relates to an assembly (601) which comprises a front frame (602) of a thrust reverser structure of an aircraft nacelle and at least one cascade (603). The assembly is characterized in that, when the cascade is fixed to the frame, the axial distance (L) that separates the first blading (605) upstream of the cascade from a covering area (606) between the extension of the cascade and the front frame is greater than or equal to once the mean height (h) of the cascade.

Abstract: The invention relates to an air intake of an aircraft turbojet engine nacelle, extending along an axis X, in which an air flow circulates from upstream to downstream, the air intake comprising an inner wall facing the axis X and an outer wall for guiding an external air flow, the walls being connected by a leading edge and an inner partition so as to delimit an annular cavity. The air intake comprises means for injecting at least one hot air flow into the inner cavity and at least one ventilation orifice formed in the outer wall to allow the hot air flow to escape after heating the inner cavity, the ventilation orifice comprising an upstream edge, the circumferential profile of which is discontinuous in order to generate turbulences, and a downstream edge, the radial profile of which is aerodynamic in order to limit the formation of pressure fluctuations.

Abstract: A thrust reverser for an aircraft propulsion assembly, this reverser including a lower door and an upper door defining, in thrust reversal configuration, a deflection opening, through which a portion of the fluid not serving to produce the thrust reversal of the aircraft can exit the reverser downstream. The downstream edge of the lower door is offset towards the rear with respect to the downstream edge of the upper door so as to orient the fluid flow passing through the deflection opening vertically upwards. When the propulsion assembly is mounted at the rear portion of the fuselage of the aircraft, this makes it possible in particular to improve the supply of the control surface of the aircraft in the landing phase, in particular in crosswind conditions.

Abstract: The invention relates to an air intake of an aircraft turbojet engine nacelle, extending along an axis X, in which an air flow circulates from upstream to downstream, the air intake extending circumferentially around the axis X and comprising an inner wall, which faces the axis X in order to guide an inner air flow, and an outer wall, which is opposite the inner wall, for guiding an external air flow, the walls being connected by a leading edge and an inner partition so as to delimit an annular cavity. The air intake comprises means for injecting at least one hot air flow into the inner cavity and at least one ventilation orifice formed in the outer wall in order to allow the hot air flow to escape after heating the internal cavity, the air intake comprising at least one disruption member of the external air flow, positioned upstream of the ventilation orifice, which extends outwardly from the outer wall.

Abstract: A thrust reverser including a stationary structure, a lower door and an upper door. This reverser includes at least one deflector configured to be able to redirect forward from the stationary structure a portion of fluid exiting the reverser according to a trajectory oriented towards a lateral opening extending between the stationary structure and the upper door. Such a deflector makes it possible to improve the control of the air current lines acting on a tail unit and in particular on a control surface of an aircraft equipped with such a reverser when the latter is in thrust reversal configuration, thereby making it possible to improve the controllability of this aircraft.

Abstract: A thrust reverser including doors and at least one flexible deflector obstructing a lateral opening of the thrust reverser when the doors are open. Such a deflector allows better controlling the airflows in thrust reverser configuration and maximizing the counter-thrust force.

Abstract: The invention relates to a method for determining the value of one or more parameters relating to the state of health of at least one accumulator of a battery that is intended to provide electrical energy to an external application. A first state-of-health parameter related to the resistance of at least one electrochemical element of the battery is determined according to the method comprising:—a step (1) of determining the value of the state of charge of the electrochemica 1 element, expressed as a percentage of a maximum state of charge; —a step (2) of verifying whether the determined value of the state of charge belongs to a sought range; —a step of repeating, as long as the result of the verification step (2) is not positive, the determination step (1) and then the verification step (2); —calculating the value of the first parameter as a function of at least the value of the state of charge determined during the last determination step (1).

Abstract: The present invention discloses compounds according to Formula I: Wherein R1, L1, R2, L2, R3, Cy, and the subscript n are as defined herein. The present invention relates to compounds, methods for their production, pharmaceutical compositions comprising the same, and methods of treatment using the same, for the prophylaxis and/or treatment of allergic diseases, inflammatory diseases, metabolic diseases, autoinflammatory diseases, autoimmune diseases, proliferative diseases, transplantation rejection, diseases involving impairment of cartilage turnover, congenital cartilage malformations, and/or diseases associated with hypersecretion of IFN?, IL12 and/or IL23 by administering the compound of the invention.

Abstract: A thrust reverser for a turbojet aircraft nacelle includes a fixed structure, a movable structure and an actuator. The actuator extends along a main axis and is connected by a first connection to the fixed structure and by a second connection to the movable structure for the deployment of the movable structure between a direct jet position and a reverse jet position. The actuator is also connected to the fixed structure by a third connection arranged longitudinally between the first connection and the second connection. An axis of the third connection is radially eccentric from the main axis and the third connection allows a predetermined displacement of the actuator with respect to the fixed structure.

Abstract: An assembly including a nacelle element, such as a cover, a device for locking the nacelle element, a key for locking/unlocking the locking device and an indicator for indicating the position of the locking device. This assembly includes a control device which is configured to be actuated by the key when the key is withdrawn from the locking device so as to make the indicator move from a first state to a second state, the state of the indicator being representative of the locked or unlocked position of the locking device.

Abstract: The invention concerns a method for estimating the state of health (SOH) of an electrochemical element, comprising: initiating a charging or discharging operation of the electrochemical element; measuring values representing deformations of the electrochemical element while the charging or discharging operation is being performed, the deformation values measured forming a deformations image signal according to the quantity of electricity passing through the electrochemical element over time; comparing the deformations image signal and a reference image signal, one or more differences obtained by the comparison characterising an estimation of the ageing of the electrochemical element.

Abstract: The invention relates to an air intake of an aircraft turbojet engine nacelle extending along an axis X, in which an air flow circulates from upstream to downstream, the air intake comprising an inner wall and an outer wall which are connected by a leading edge and an inner partition so as to delimit an annular cavity, the air intake comprising means for injecting at least one hot air flow into the inner cavity and at least one ventilation orifice formed in the outer wall in order to allow the hot air flow to escape after heating the inner cavity, the air intake comprising at least one acoustic member positioned in the inner cavity facing the ventilation orifice so as to modify the acoustic resonance frequencies and/or to attenuate the acoustic waves formed in the inner cavity via the ventilation orifice.