Abstract: A method for constructing at least two fleets of aircraft of different families for which each aircraft has a front part comprising windows, a framing of the windows and a windshield front fairing, comprising, for each aircraft, constructing a module composed of the framing of all of the windows allowing outward visibility from the cockpit and of the windshield front fairing whose form is identical and constant for all the aircraft of the fleets and independent of a form of the fuselages thereof, and constructing a section of fuselage of which at least a part of an edge of the fuselage is of a form identical to an edge of the module, such that the module can be assembled directly with the contiguous fuselage section, whatever the aircraft of the fleets.

Abstract: An aircraft canopy includes a window pane, a frame from a primary structure of the aircraft, and a flange fastened to the frame with fastening screw, characterized in that: the flange is secured to the peripheral edge of the window pane by engaging of at least one plate of the flange between plies of the window pane, so that flange and window pane form an all in one-piece assembly, at each fastening screw, a load-transferring and distributing member is arranged between an outer surface of the flange and the fasting screw, a cavity being provided in the flange for receiving the load-transferring and distributing member, the member having a recess for receiving the screw head.

Abstract: A method for constructing at least two fleets of aircraft of different families for which each aircraft has a front part comprising windows, a framing of the windows and a windshield front fairing, comprising, for each aircraft, constructing a module composed of the framing of all of the windows allowing outward visibility from the cockpit and of the windshield front fairing whose form is identical and constant for all the aircraft of the fleets and independent of a form of the fuselages thereof, and constructing a section of fuselage of which at least a part of an edge of the fuselage is of a form identical to an edge of the module, such that the module can be assembled directly with the contiguous fuselage section, whatever the aircraft of the fleets.

Abstract: An aircraft windshield that improves pilot and co-pilot's perception of the outside world. The windshield includes a transparent panel held inside a structure of the aircraft, in which the upper part and the lower part are bridged so that the loads applied to the panel are (at least partially) diverted. Due to part of the loads applied on the panel being diverted, it is possible to provide a larger window panel than currently available that offers better visibility to the outside.

Abstract: Method and system of simple, precise, rapid and automatic control to verify fit between a manufactured device and its digital mock-up modelling it beforehand. The system includes a scanner configured to produce a three-dimensional cloud of points representative of the device, as well as a processor and a memory configured to superpose the cloud of points on the digital mock-up, coordinate the cloud of points with polychrome images captured during the scanning of the device and stored in a memory, disperse the cloud of points into several sets of points, each set of points corresponding to an object identified in the polychrome images, establish a correspondence between the sets of points and nodes of a treelike structure identifying the digital mock-up, and evaluate a fit between the cloud of points and the digital mock-up by analyzing the correspondence between the sets of points and the nodes of the treelike structure.

Abstract: An aircraft canopy includes a window pane, a frame from a primary structure of the aircraft, and a flange fastened to the frame with fastening screw, characterized in that: the flange is secured to the peripheral edge of the window pane by engaging of at least one plate of the flange between plies of the window pane, so that flange and window pane form an all in one-piece assembly, at each fastening screw, a load-transferring and distributing member is arranged between an outer surface of the flange and the fasting screw, a cavity being provided in the flange for receiving the load-transferring and distributing member, the member having a recess for receiving the screw head.

Abstract: Method and system of simple, precise, rapid and automatic control to verify fit between a manufactured device and its digital mock-up modelling it beforehand. The system includes a scanner configured to produce a three-dimensional cloud of points representative of the device, as well as a processor and a memory configured to superpose the cloud of points on the digital mock-up, coordinate the cloud of points with polychrome images captured during the scanning of the device and stored in a memory, disperse the cloud of points into several sets of points, each set of points corresponding to an object identified in the polychrome images, establish a correspondence between the sets of points and nodes of a treelike structure identifying the digital mock-up, and evaluate a fit between the cloud of points and the digital mock-up by analyzing the correspondence between the sets of points and the nodes of the treelike structure.

Abstract: An aircraft windshield that improves pilot and co-pilot's perception of the outside world. The windshield includes a transparent panel held inside a structure of the aircraft, in which the upper part and the lower part are bridged so that the loads applied to the panel are (at least partially) diverted. Due to part of the loads applied on the panel being diverted, it is possible to provide a larger window panel than currently available that offers better visibility to the outside.

Abstract: Device intended for a double glazing including at least one outer glazing and one inner glazing separated by an intermediary space filled with a gas, used to isolate an inside environment from an outside environment, a pressure variation being liable to occur between these environments, for example in the case of an aircraft in flight, includes means for conserving the outer glazing and the inner glazing of this double glazing mainly parallel, independently of this pressure variation. The invention also concerns a double glazing including this device, the process for maintaining parallelism and software using the process.

Abstract: Wiper blade for a surface of double curvature type, the said wiper blade including a flexible longitudinal wiper and means for exerting a bearing force at at least one point of the said wiper along a direction Z mainly normal to the surface, also including a longitudinal 15 part, attached to the wiper at several points, and means to vary over time and in at least one segment of the longitudinal rod the rigidity in bending of this longitudinal rod in a plane XZ normal to the surface between previously chosen values. The longitudinal part is a metallic blade where the inertias on the two axes of its section are very different.

Abstract: Device intended for a double glazing including at least one outer glazing and one inner glazing separated by an intermediary space filled with a gas, used to isolate an inside environment from an outside environment, a pressure variation being liable to occur between these environments, for example in the case of an aircraft in flight, includes means for conserving the outer glazing and the inner glazing of this double glazing mainly parallel, independently of this pressure variation. The invention also concerns a double glazing including this device, the process for maintaining parallelism and software using the process.

Abstract: The present invention relates to an aircraft window, of the type including a holding frame for securing the window to the fuselage of an aircraft and at least one pane mounted in the holding frame by a sealing system, the at least one pane having an inner surface and an outer surface, characterized in that: the pane includes, in a first state called the rest state, at least one concavity in its outer surface when there is no pressure difference between the outer surface and the inner surface of the pane, and the at least one concavity of the pane is at least partially eradicated in a second state in which there is a pressure difference between the outer surface and the inner surface of the pane.

Abstract: A front structure of an aircraft fuselage comprising landing gear pivoting about a main shaft and a stay shaft. The front structure also comprises a first reinforcing frame and a second reinforcing frame, the main shaft and the stay shaft being respectively connected to the first and second frames, and a device for the mechanical connection and transfer of forces connecting the stay shaft and the main shaft and transferring to the main shaft a portion of the forces induced by the wheels of the landing gear onto the stay shaft, the second frame and said device being perpendicular to one another.

Abstract: The present invention relates to an aircraft window, of the type including a holding frame for securing the window to the fuselage of an aircraft and at least one pane mounted in the holding frame by a sealing system, the at least one pane having an inner surface and an outer surface, characterized in that: the pane includes, in a first state called the rest state, at least one concavity in its outer surface when there is no pressure difference between the outer surface and the inner surface of the pane, and the at least one concavity of the pane is at least partially eradicated in a second state in which there is a pressure difference between the outer surface and the inner surface of the pane.

Abstract: Wiper blade for a surface of double curvature type, the said wiper blade including a flexible longitudinal wiper and means for exerting a bearing force at at least one point of the said wiper along a direction Z mainly normal to the surface, also including a longitudinal part, attached to the wiper at several points, and means to vary over time and in at least one segment of the longitudinal rod the rigidity in bending of this longitudinal rod in a plane XZ normal to the surface between previously chosen values. The longitudinal part is a metallic blade where the inertias on the two axes of its section are very different.

Abstract: Device intended for a double glazing including at least one outer glazing and one inner glazing separated by an intermediary space filled with a gas, used to isolate an inside environment from an outside environment, a pressure variation being liable to occur between these environments, for example in the case of an aircraft in flight, includes means for conserving the outer glazing and the inner glazing of this double glazing mainly parallel, independently of this pressure variation. The invention also concerns a double glazing including this device, the process for maintaining parallelism and software using the process.

Abstract: An aircraft in which it is possible to replace windshield panes of the mineral type with windshield panes of the organic type and vice versa, without the frame of the aircraft structure having to be modified. The pane is held in place on the frame by a window pane retainer specific to the pane. The frame has no through-holes opening to the outside of the aircraft for fastening the pane. The window pane retainer specific to a pane of the organic type has pins passing through the acrylic panes. The disclosed embodiments also relate to a method of replacing a pane of a first type with a pane of a second type.

Abstract: An aircraft in which it is possible to replace windshield panes of the mineral type with windshield panes of the organic type and vice versa, without the frame of the aircraft structure having to be modified. The pane is held in place on the frame by a window pane retainer specific to the pane. The frame has no through-holes opening to the outside of the aircraft for fastening the pane. The window pane retainer specific to a pane of the organic type has pins passing through the acrylic panes. The disclosed embodiments also relate to a method of replacing a pane of a first type with a pane of a second type.

Abstract: Device for attachment of an aircraft windshield. The device comprises a monoblock flange (14). The flange is fixed to the structure (12) of the aircraft by screws (16), so as to trap a peripheral edge of the windshield glass (10) between the flange and the structure. A dry monoblock seal (18) surrounds the peripheral edge of the windshield, such that the seal alone provides leak tightness between the inside and the outside of the aircraft. Preferably, the screws (16) are in contact with the flange (14) through plane surfaces perpendicular to the center lines of the screws. At least one second dry monoblock seal (20) may also be placed between the flange (14) and the structure (12).

Abstract: An aircraft cockpit window comprises a window pane (12) fitted with a frame (14), and guide rails (16, 18) on which the frame (14) is guided at three points (A, B, C) using two lower sets of rollers (20, 22) and an upper set of rollers (24). All these controls for locking/unlocking and opening the window pane are grouped on a handle (26) articulated on the lower edge of the frame (14), about an axis (28) that is preferably approximately vertical.