Abstract: The present invention refers to a liposome comprising: a) a phospholipid; b) cholesterol (chol); c) a conjugate comprising a cholesterol moiety, a polyethylene glycol (PEG) moiety and a peptide moiety comprising a RGD sequence, wherein the PEG moiety is covalently attached to the cholesterol moiety by one end via a bond of the type alkyl ether and is covalently attached to the peptide moiety comprising the RGD sequence by the other end: d) a non-lipid cationic surfactant present in a percentage of less than 30% mol in respect to the total mol of the components of the liposome a), b), c) and d); and e) alpha-galactosidase (GLA) enzyme present in a ratio of micrograms of GLA in respect to the total milligrams of the components of the liposome a), b), c) and d) of between and including 2 to 35. It also refers to a pharmaceutical composition that comprises it and to the liposome or the pharmaceutical composition for use as a medicament, in particular for use in the treatment of Fabry disease.

Abstract: An aircraft fuselage is configured to receive two tanks designed to contain liquid hydrogen. The fuselage includes a first section for a cockpit, a second section for a passenger cabin and a third section (T3) distinct from the first section (T1) and from the second section (T2). The third section (T3) includes two housings each to house a tank. The two housings are arranged symmetrically with respect to a vertical plane of symmetry (P1). This arrangement of the tanks in a section distinct from the other sections allows them to be located as close as possible to the motors that they have to supply.

Abstract: Embodiments for commercial freighter configuration for aircraft with composite wings. One embodiment is cargo floor structure for a wing center section of an aircraft. The cargo floor structure includes over wing floor beams extending longitudinally between a rear spar and a front spar of the aircraft. The over wing floor beams are coupled with an upper skin panel of a composite wing. The cargo floor structure also includes intercostals extending spanwise across the over wing floor beams. The intercostals suspended over the upper skin panel of the composite wing. The cargo floor structure also includes a truss box structure disposed between a middle pair of the over wing floor beams and configured to shear a spanwise load from the intercostals into the upper skin panel of the composite wing.

Abstract: The invention relates to a method for automatically detecting clogging of a sensor pipe extending between a pressure sensor and an exhaust manifold of an internal combustion engine, wherein the pressure sensor enables to record a signal representative of the relative pressure over time. The method includes at least one of the following steps: a) determining, while the engine runs in a steady operation state, an average amplitude of oscillations of the signal over a first period of time, the sensor pipe being considered clogged when said average amplitude is lower than a first threshold; b) monitoring, from the time the engine has been turned off, the signal over a second period of time, the sensor pipe being considered clogged when the integral of the signal is greater than a second threshold.

Abstract: Embodiments for commercial freighter configuration for aircraft with composite wings. One embodiment is cargo floor structure for a wing center section of an aircraft. The cargo floor structure includes over wing floor beams extending longitudinally between a rear spar and a front spar of the aircraft. The over wing floor beams are coupled with an upper skin panel of a composite wing. The cargo floor structure also includes intercostals extending spanwise across the over wing floor beams. The intercostals suspended over the upper skin panel of the composite wing. The cargo floor structure also includes a truss box structure disposed between a middle pair of the over wing floor beams and configured to shear a spanwise load from the intercostals into the upper skin panel of the composite wing.

Abstract: An aircraft with rear mounted engines, comprising a vertical tail plane and a horizontal tail plane, in which the engines are mounted on top of the horizontal tail plane, such that the horizontal tail plane comprises an inner fixed part attached to the fuselage of the aircraft, the inner fixed part comprising an elevator, and two outer movable parts, each one of the outer movable parts being located at each side end of the horizontal tail plane which is furthest away from the fuselage of the aircraft, such that both the inner fixed part and the outer movable parts are at least partially subjected to a flow coming from the engines when the engines are in use.

Abstract: An aircraft with a system for rearward mounting and dismounting an engine, the engine being placed inside the rear part of the aircraft when mounted. The system for rearward mounting and dismounting the engine comprises a first removable attachment device arranged to attach the engine to the fuselage in the rear part of the aircraft, internal supports fixed in the rear part of the aircraft, at least two longitudinal detachable rails, to be placed on the internal supports and under the engine, and a slider to attach to the engine via a second removable attachment device, to be placed on the longitudinal detachable rails.

Abstract: An aircraft with rear mounted engines, comprising a vertical tail plane and a horizontal tail plane, in which the engines are mounted on top of the horizontal tail plane, such that the horizontal tail plane comprises an inner fixed part attached to the fuselage of the aircraft, the inner fixed part comprising an elevator, and two outer movable parts, each one of the outer movable parts being located at each side end of the horizontal tail plane which is furthest away from the fuselage of the aircraft, such that both the inner fixed part and the outer movable parts are at least partially subjected to a flow coming from the engines when the engines are in use.

Abstract: The invention provides an aircraft with a trimmable horizontal stabilizer (13) that not requires a cut-out in resistant areas of the rear fuselage and that occupies less space that in conventional horizontal stabilizers. The rear fuselage (5) comprises at least a first section (9) having a resistant fuselage and a second section (11), aft of the first section, having a non-resistant fuselage (i.e. a fairing). The load-bearing structure (30) of the horizontal stabilizer and the trimming actuator (50) are disposed inside said second section (11). The pivot element (41) is mounted on its forward side and coupled to the first section (9) of the rear fuselage. The connection fitting (21) is mounted on its rearward side and the trimming actuator (50) is disposed so that it exerts a force in the direction of the Z-axis of the aircraft on the connection fitting (21) during a trimming operation.

Abstract: To optimize the structure of an aircraft tail section, an aircraft rear section comprises a fuselage section, a tail section, and a vertical stabilizer comprising a box-section structure which comprises a box-section upper part extending on the outside of the tail section, and a box-section lower part housed inside the tail section, such that the tail section is wholly supported by the box-section structure.

Abstract: The invention provides an aircraft with a trimmable horizontal stabilizer (13) that not requires a cut-out in resistant areas of the rear fuselage and that occupies less space that in conventional horizontal stabilizers. The rear fuselage (5) comprises at least a first section (9) having a resistant fuselage and a second section (11), aft of the first section, having a non-resistant fuselage (i.e. a fairing). The load-bearing structure (30) of the horizontal stabilizer and the trimming actuator (50) are disposed inside said second section (11). The pivot element (41) is mounted on its forward side and coupled to the first section (9) of the rear fuselage. The connection fitting (21) is mounted on its rearward side and the trimming actuator (50) is disposed so that it exerts a force in the direction of the Z-axis of the aircraft on the connection fitting (21) during a trimming operation.

Abstract: Aircraft having attached to the rear fuselage (31) a propulsion system (13) by means of upstream pylons (17); the aircraft comprising a vertical tail plane (21) attached to the rear fuselage (31); the rear fuselage (31) extending from a rear pressure bulkhead (27) to the aircraft tail (29), comprising a skin (35) and a plurality of frames (37, 37?, 37?) arranged perpendicularly to a central longitudinal axis (33), and having a curved shape with at least a vertical symmetry plane (A-A); the vertical tail plane (21) comprising a torsion box with left and right skins, frontal and rear spars (51, 53) and a plurality of ribs (55); the aircraft also comprising a resistant structure connecting said vertical tail plane (21) with the rear fuselage (31) that acts as a redundant load path in failure events of the propulsion system (13) that can produce damages in the rear fuselage (31).

Abstract: A lid with a detachable sealing joint, the lid having a crown-type shell having an inner surface and an external surface, a sealing joint upon the inner surface of the shell; a detachable hydrophilic coating; and a coating compatible with the sealing joint upon the detachable hydrophilic coating; such that the detachable hydrophilic coating and the compatible coating form an adhesive interface between the crown and the sealing joint. The detachable hydrophilic coating having at least a water solid polymer, for example polyvinyl pyrrolidone; at least a cross-linking agent, for example, butanediol; and at least a solvent, for example, water. It also describes a method for manufacturing a lid with a detachable sealing joint and a method for bottling beverages using lids with a detachable sealing joint of the invention.

Abstract: Compositions comprising eucalyptol and/or ocimene and/or farnesol are provided for use as bumblebee pheromones. The compositions are useful in agriculture to assist in the pollination of angiosperm plant species. Such compositions can attract insects of the genus Bombus (bumblebee) to angiosperm plants where the composition is applied to the plant, or to the environment of the plant.

Abstract: According to the invention, the components of the system have been optimised such that they interact and complement each other and such that one cannot operate without the other in the formation of refractory moulds for multiple metal castings in the production of fixed dental prostheses. The invention also relates to a mechanical metal device for positioning increased length refractory cylinders in standard horizontal centrifuges, thereby increasing the number of fixed dental prostheses that can be cast at one time.

Abstract: A lid with a detachable sealing joint, the lid having a crown-type shell having an inner surface and an external surface, a sealing joint upon the inner surface of the shell; a detachable hydrophilic coating; and a coating compatible with the sealing joint upon the detachable hydrophilic coating; such that the detachable hydrophilic coating and the compatible coating form an adhesive interface between the crown and the sealing joint. The detachable hydrophilic coating having at least a water solid polymer, for example polyvinyl pyrrolidone; at least a cross-linking agent, for example, butanediol; and at least a solvent, for example, water. It also describes a method for manufacturing a lid with a detachable sealing joint and a method for bottling beverages using lids with a detachable sealing joint of the invention.

Abstract: The present invention provides a container closure, including: a metal closure shell having a top surface and a bottom surface, the top and bottom surfaces having at least one varnish coating thereon; a detachable sealing liner in contact with a portion of the bottom surface; and a print layer containing a polyester ink and interposed between the bottom surface and the liner; wherein the liner includes a PVC resin, wherein the print layer is in direct contact with the liner and the varnish coating on the bottom surface. Other embodiments include methods for making and using the closure.

Abstract: Method and system for transmitting messages to subscribers of a telephone network during the set-up stage of incoming calls prior to the off-hook from a local exchange to at least one telephone terminal through an access system. The access system simulates, on one hand, the operation of a telephone terminal towards the local switching exchange such that it receives, from the local switching exchange and by means of an access node located in the access system, a first message preferably modulated and demodulates and stores it for subsequent replication; and, on the other hand, simulates the operation of a local switching exchange towards the telephone terminal such that it generates and transmits to the telephone terminal and by means of a network termination located in the access system, a second message preferably modulated which is a replication of the first message.