Abstract: This maintenance trolley (17) for the air intake (9) of the nacelle of an aircraft turbojet engine is notable in that it comprises a base (19) and a platform (23) cantilever-mounted on this base (19) and designed to enter said air intake (9) without contact therewith.

Abstract: The invention relates to a nacelle for a turbojet engine that includes an air intake structure capable of directing an air flow towards a fan of the turbojet engine, and a middle structure for surrounding said fan and to which is attached the air intake structure in order to provide aerodynamic continuity, wherein the air intake structure includes at least one inner panel attached to the middle structure and defining, with the latter, a nacelle fixed structure and at least one outer longitudinal panel removably attached to the fixed structure and including an air intake lip in order to define a removable air intake structure, wherein the removable air intake structure is provided with a locking device including at least one electric lock capable of interaction with a complementary retention structure.

Abstract: An air intake structure is mounted upstream of a mid-structure of a nacelle for an aircraft engine. The air intake structure includes an external wall incorporating a lip, a partition defining a deicing compartment in the lip, a deicing manifold extending in the compartment, and a duct for supplying hot air to the deicing manifold. In particular, the external wall is mounted movably with respect to the mid-structure between a rear position and a front position, and the duct is connected in a fixed manner to the mid-structure. The partition is fixed in a sealed manner inside the lip, and the duct is connected to the manifold by a disconnectable seal which is situated in an immediate vicinity of the partition.

Abstract: A turbojet engine nacelle includes an air intake structure having a longitudinal outer panel incorporating an air intake lip, a middle structure to which the air intake structure is attached, at least one inner panel including an acoustic shroud, rails guiding the outer panel able to allow a rectilinear movement of the outer panel, and a reinforcing member to react the mechanical loads of the guide rails. In particular, the reinforcing member reacts the loads of the guide rails beyond a predetermined deformation of the guide rails.

Abstract: A nacelle includes a central structure intended to surround a fan of a turbojet engine and an air intake structure attached to the central structure and able to channel a flow of air toward the fan. The nacelle includes at least one longitudinal outer panel incorporating an air intake lip. An inner panel includes an acoustic shell ring which downstream end is attached to an upstream end of the central structure and therewith forms a fixed structure of the nacelle. Guide means are entirely attached to the central structure for guiding the outer panel or panels and allowing substantially rectilinear movement of the outer panel towards the upstream end of the nacelle so that the air intake structure can be opened.

Abstract: The invention relates to a nacelle (1) for a turbojet engine, comprising: —an air intake structure able to channel a flow of air towards a fan of the turbojet engine and comprising at least one longitudinal outer panel (40) incorporating an air intake lip (4a), —a middle structure (5) intended to surround the said fan and to which the air intake structure is attached in such a way as to ensure aerodynamic continuity, —at least one inner panel (41) comprising an acoustic shroud (53), fixed at its downstream end to an upstream end of the middle structure (5) forming therewith a fixed structure of the nacelle (1), and —means (15) of guiding the outer panel or panels (40) which means are able to allow a substantially rectilinear movement of the outer panel (40) in the upstream direction of the nacelle (1) so as to be able to open the air intake structure, the said nacelle (1) comprising reinforcing means (90) designed to react the mechanical loads of the guide means (15) beyond a predetermined deformation thereof

Abstract: The invention relates to a nacelle for a turbojet engine that comprises an air intake structure (2) capable of directing an air flow towards a fan of the turbojet engine, and an intermediate structure for surrounding said fan and to which the air intake structure is attached in order to ensure aerodynamic continuity, wherein the air intake structure includes, on the one hand, at least one inner panel (21) attached to the intermediate structure and defining with the latter a fixed nacelle structure and, on the other hand, at least one longitudinal outer panel (20) removably attached to the fixed structure and including an air intake lip (2a) in order to form a removable air intake structure, characterised in that the air intake structure is provided with peripheral locking means including at least one locking means (10) attached to the inner panel or to the air intake lip and each capable of interacting with an additional retaining means (11) respectively attached to the air intake lip or to the inner panel.

Abstract: The invention relates to a nacelle for a turbojet engine that includes an air intake structure (2) capable of directing an air flow towards a fan of the turbojet engine, and a middle structure for surrounding said fan and to which is attached the air intake structure in order to provide aerodynamic continuity, wherein the air intake structure includes, on the one hand, at least one inner panel (21) attached to the middle structure and defining, with the latter, a nacelle fixed structure and, on the other hand, at least one outer longitudinal panel (20) removably attached to the fixed structure and including an air intake lip (2a) in order to define a removable air intake structure, characterised in that the removable air intake structure is provided with peripheral locking means including at least one electric lock (10) each capable of interaction with a complementary retaining means (11).

Abstract: This maintenance trolley (17) for the air intake (9) of the nacelle of an aircraft turbojet engine is notable in that it comprises a base (19) and a platform (23) cantilever-mounted on this base (19) and designed to enter said air intake (9) without contact therewith.

Abstract: The present invention relates to a turbojet engine nacelle (1) comprising:—an air intake structure (4) capable of channelling an airflow towards a fan of the turbojet engine and comprising at least one longitudinal external panel (40) incorporating an air intake lip (4a),—a central structure (5) intended to surround the said fan and to which the air intake structure (4) is attached in such a way as to ensure aerodynamic continuity,—at least one internal panel (41) comprising an acoustic shelving fixed at its downstream end to an upstream end of the central structure (5) therewith forming a fixed structure of the nacelle (1), and—guide means (15) for guiding the external panel or panels (40) which are capable of allowing substantially rectilinear movement of the external panel (40) towards the upstream end of the nacelle (1) so as to be able to open up the air intake structure (4), the guide mans (15) being entirely fixed to the central structure (5).

Abstract: The invention relates to an air intake structure that can be mounted upstream of a nacelle middle structure for an aircraft engine, and that particularly includes: an outer wall (7) including a lip (9) and that can be mounted relative to said middle structure so as to move between a rear position and a front position; a wall (11) defining a de-icing compartment (13) in said lip (9); at least one de-icing collector (15) extending in said compartment (13); and at least one hot-air supply duct (17) of said collector (15), that can be rigidly connected to said middle structure. The wall (11) is tightly secured inside said lip (9), and said supply duct (17) is connected to said collector (15) by removable sealing means (27, 29, 31, 35).