An approach to seeker windows for aircraft comprises a window layer comprising an IR transparent material, the window layer comprising a first side and a second side substantially opposite the first side; and a heating layer on the first side or the second side of the window layer, the heating layer configured to apply a heating profile to the window layer to reduce thermal shock imparted to the window layer when the seeker window is exposed to hypersonic flight conditions.

Aircraft door (1) including a safety latch (7) having a first locking element (8) and a complementary second locking element (9) which is movable; a link (11) having at least one electroactive polymer portion (13) and adapted to take up: a lock position in which the electroactive polymer portion (13) is supplied with power and the movable second locking element (9) is engaged with the first locking element (8); and an unlock position in which the electroactive polymer portion (13) is not supplied with power and the movable second locking element (9) is kept away from the first locking element (8); a control unit (16) having a power supply (26) for the electroactive polymer portion (13).

An assembly is provided for an aircraft propulsion system. This assembly includes a first drain tube, a second drain tube, a container and a gas tube. The container fluidly couples the first drain tube to the second drain tube. The container is configured to receive fluid from the first drain tube. The gas tube is fluidly coupled with the container. The gas tube is configured to direct gas into the container for propelling the fluid received within the container into the second drain tube.

A separating element for a platform cabin comprises at least one leaf subjected to a return force toward its open position, and, for the or each leaf, a return member for returning the leaf toward its closed position and comprising a first end articulated at an articulation point movable jointly with the leaf. This return member also comprises a second end mounted movably relative to the partition between an active position and an inactive position, such that when the leaf is open and the second end is in the active position, the return member exerts, on the leaf, a return force returning the leaf toward its closed position, and when the leaf is open and the second end is in the inactive position, the return member is in a second configuration in which it does not exert a force returning the leaf toward its closed position.

A window frame system, comprising a window frame having an aperture there-through and circumferentially arranged window frame through-holes in a first window frame portion and a second window frame portion, and a stringer coupling with stringer coupling through-holes in a first stringer coupling portion and a second stringer coupling portion. In an overlapping arrangement, the first window frame portion and the first stringer coupling portion are adapted to overlap with their through-holes coaxially, wherein the respective through-holes of the two first portions have different diameters.

Systems and methods for securing an emergency exit door on an armrest of a seat are provided. A system includes a latch connected to an armrest of a seat of a vehicle. The latch is moveable relative to the armrest between a stowed position and a deployed position. The latch is structured and arranged to engage an edge of a door that is associated with an exit of the vehicle to hold the door on the armrest.

An aircraft fuselage includes a structure, considered in respect of all or part of the fuselage, with fuselage upper sub-structure constituting an upper part of the fuselage and a fuselage bottom sub-structure constituting a lower part of the fuselage. Openings in the structure of the fuselage are intended for the installation of windows or doors for exiting the fuselage. Furthermore, the fuselage upper sub-structure are the fuselage bottom sub-structure form fuselage sub-structures that are assembled with one another via at least one lintel in which all or some of the openings intended for installing the exit doors or windows are formed.

The invention is about a powered airbag for planes in case of uncontrollable falling which makes the plane fall vertically with the head up. The invention includes the bonnet cover of the head 1, the hinges of the bonnet cover 17, the head cover of the plane 12, the structural frame of the head the plane 13, the container of gas-creating material 8, Valve to activate the airbag 9. There is a difference that the structural frame of the head of the plane 13 has a powered airbag 11, the flexible soft tube 10 which connects the powered airbag 11 to the frame of the head of the plane 13

The invention is about a powered airbag for planes in case of uncontrollable falling which makes the plane fall vertically with the head up. The invention includes the bonnet cover of the head 1, the hinges of the bonnet cover 17, the head cover of the plane 12, the structural frame of the head the plane 13, the container of gas-creating material 8, Valve to activate the airbag 9. There is a difference that the structural frame of the head of the plane 13 has a powered airbag 11, the flexible soft tube 10 which connects the powered airbag 11 to the frame of the head of the plane 13

An ice protection system includes an aircraft surface and a gutter defined in the aircraft surface between raised rails. The gutter includes a mouth that narrows into a trailing portion of the gutter. The mouth is configured to channel water runback rivulets into the trailing portion of the gutter. The gutter can be a first gutter of a plurality of side by side gutters, each including a respective mouth narrowing into a respective trailing portion, wherein the gutters are separated from one another by respective rails.