Abstract: System for analyzing anomalies in pharmaceuticals includes a server configured to host a neural network having an inference engine and a training engine, a database of images of in-process biologics; a first user interface module for displaying to a user particle morphologies in the images; a second user interface module for displaying to the user a training of the neural network; a third user interface module for displaying to the user an inference of images chosen by the neural network to fit selected criteria, wherein the neural network is a convolutional neural network, and training includes providing test images to the training engine to teach the neural network to recognize specific particle morphologies. The user provides images of the in-process biologics from the database, and the inference engine identifies anomalous particle morphologies in the user-provided images. A fourth user interface module provides a report about particle morphologies in the images.

Abstract: Device for machining an end of an elementary panel for its subsequent friction stir welding, the elementary panel comprising a metal body defining two opposite faces, the machining device comprising a chassis, at least two guiding members configured to guide a first face of the elementary panel, at least one machining tool mounted on the chassis, the machining tool being positioned between the two guiding members and at least one pressure member mounted on the chassis and configured to exert a pressure on a second face of the elementary panel so as to press the elementary panel against the guiding members along the horizontal reference direction.

Abstract: Device for machining an end of an elementary panel for its subsequent friction stir welding, the elementary panel comprising a metal body defining two opposite faces, the machining device comprising a chassis, at least two guiding members configured to guide a first face of the elementary panel, at least one machining tool mounted on the chassis, the machining tool being positioned between the two guiding members and at least one pressure member mounted on the chassis and configured to exert a pressure on a second face of the elementary panel so as to press the elementary panel against the guiding members along the horizontal reference direction.

Abstract: Using crystalline silica, mixed with cement powder, to reduce the heating of the cement paste caused by the hydration of said powder, during a process of packaging of radioactive waste, a formulation for the packaging of radioactive waste by cementing, which comprises such silica, a method for packaging radioactive waste implementing this formulation, and a package for packaging of radioactive waste which is obtained by this method.

Abstract: Using crystalline silica, mixed with cement powder, to reduce the heating of the cement paste caused by the hydration of said powder, during a process of packaging of radioactive waste, a formulation for the packaging of radioactive waste by cementing, which comprises such silica, a method for packaging radioactive waste implementing this formulation, and a package for packaging of radioactive waste which is obtained by this method.

Abstract: A mount for an aircraft turbojet engine. The mount includes a central box formed by an assembly of two side panels joined via transverse ribs and two side boxes secured to a forward part of the box and arranged either side thereof, each side box including an aft closure frame. One of the ribs forming the box includes two side extensions made in a single piece with the rib and respectively projecting from the two side panels outwardly from the box, the two extensions being fixedly mounted on the frame of each of the two side boxes, respectively.

Abstract: The invention relates to a turbojet suspension pylon for an aircraft, the pylon being provided with a rigid structure (10) comprising a longitudinal central box (22). According to the invention, the rigid structure also comprises two lateral boxes (24a, 24b) fixed to a forward part of said central box (22), the pylon also comprising a first (6a) and a second (6b) engine forward suspension designed to resist forces applied along the longitudinal direction (X) of the pylon, these first and second suspensions being arranged on the two lateral boxes respectively.

Abstract: A mount for an aircraft turbojet engine. The mount includes a central box formed by an assembly of two side panels joined via transverse ribs and two side boxes secured to a forward part of the box and arranged either side thereof, each side box including an aft closure frame. One of the ribs forming the box includes two side extensions made in a single piece with the rib and respectively projecting from the two side panels outwardly from the box, the two extensions being fixedly mounted on the frame of each of the two side boxes, respectively.

Abstract: The invention relates to a turbojet suspension pylon for an aircraft, the pylon being provided with a rigid structure (10) comprising a longitudinal central box (22). According to the invention, the rigid structure also comprises two lateral boxes (24a, 24b) fixed to a forward part of said central box (22), the pylon also comprising a first (6a) and a second (6b) engine forward suspension designed to resist forces applied along the longitudinal direction (X) of the pylon, these first and second suspensions being arranged on the two lateral boxes respectively.