A sandwich structure architecture for high speed impact resistant structure includes sandwich skins which enclose a sandwich core formed by a plurality of spacing layers and a plurality of trigger layers, wherein these layers are stacked alternatively in the core. The walls of the trigger layers are thicker than the walls of the spacing layers and/or the walls of the trigger layers include at least one part inclined with respect to the walls of the spacing layers. The spacing and the trigger layers are made of the same type of material, preferably composite materials or metallic materials. The structure is capable of absorbing high-speed impacts, and at the same time can be used as load carrying structure in aircraft fuselages, wings, vertical or horizontal stabilizers.

An airplane has main propulsion engines and a first fuel supply for the main propulsion engines. The airplane further has an auxiliary propulsion engine and a second fuel supply for the auxiliary propulsion engine, this second fuel supply being separate from the first fuel supply. The auxiliary propulsion engine can be switched on independently from the main propulsion engines. Such airplane has increased safety, since it will be possible to maintain flight, particularly when at high altitude, even if all main propulsion engines have failed.

An anterior part of a nacelle of an aircraft propulsion unit. A rigidifying frame annular about a longitudinal axis of extension of the nacelle is at the rear end of the anterior part. An annular shield is in front of the rigidifying frame and connects an internal peripheral edge of the rigidifying frame to an internal structure. The shield has a portion extending towards the external panel beyond the internal peripheral edge of the rigidifying frame, the portion forming a non-zero angle with respect to the rigidifying frame to form a free space with respect to the rigidifying frame behind the portion. The shield can thus deform in the event of an impact of a foreign object entering through the air inlet lip, without the rigidifying frame itself being deformed, thereby absorbing all or some of the impact energy. A nacelle can have such an anterior part, and an aircraft can have such a nacelle.

An airplane has main propulsion engines and a first fuel supply for the main propulsion engines. The airplane further has an auxiliary propulsion engine and a second fuel supply for the auxiliary propulsion engine, this second fuel supply being separate from the first fuel supply. The auxiliary propulsion engine can be switched on independently from the main propulsion engines. Such airplane has increased safety, since it will be possible to maintain flight, particularly when at high altitude, even if all main propulsion engines have failed.

A real-time aircraft bird congestion indicator system for measuring congestion in an airspace between aircraft and birds uses one or more radars to continuously survey an airspace around an airport or aerodrome and continuously generate aircraft tracks and bird tracks in the airspace. A congestion processor connected to the radar(s) receives the aircraft and bird tracks and processes them to periodically generate a congestion indicator that measures the congestion in the airspace. A display processor connected to the congestion processor receives the congestion indicator which is updated periodically by the congestion processor and displays the congestion indicator to a user, generates an alert if the congestion indicator falls outside set operating limits, and/or sends the congestion indicator or alert to another system.

Described herein is an aircraft. The aircraft includes a peripheral assembly, such as a sensor probe. The aircraft further includes a release assembly connecting the peripheral assembly to a portion of the aircraft. The release assembly is configured to separate the peripheral assembly and the portion upon receipt of a threshold force. The release assembly may be configured to allow for the quick release, such as via a snap-fit connection, between the peripheral assembly and the portion of the aircraft.

An in-flight impact protection system for aircraft. An aircraft having a panel, with a sensor disposed on the aircraft and adapted to transmit a signal and receive a reflection of the signal. A controller coupled to the sensor and adapted to receive the reflection from the sensor to determine whether an object is near the aircraft's panel. An inflation device, which includes a tube member, is coupled to the controller and positioned inside the aircraft, proximate the panel. After determining that the object is near the panel, the controller can activate the inflation device so that the tube member inflates, thereby buttressing at least a portion of the panel. The panel can be a windshield, fuselage member, or other suitable component.

In one aspect, a device for preventing bird strikes to an engine. The device includes a projector mounted on a component of the engine. The projector is positioned to project an image outside of the engine. In another aspect, an engine for an aircraft. The engine includes an engine component and a projector mounted on the engine component. The projector is positioned to project an image outside of the engine.

A real-time aircraft bird congestion indicator system for measuring congestion in an airspace between aircraft and birds uses one or more radars to continuously survey an airspace around an airport or aerodrome and continuously generate aircraft tracks and bird tracks in the airspace. A congestion processor connected to the radar(s) receives the aircraft and bird tracks and processes them to periodically generate a congestion indicator that measures the congestion in the airspace. A display processor connected to the congestion processor receives the congestion indicator which is updated periodically by the congestion processor and displays the congestion indicator to a user, generates an alert if the congestion indicator falls outside set operating limits, and/or sends the congestion indicator or alert to another system.

A leading edge for an airfoil of an aircraft includes a leading plate with a convex side and a concave side, and at least one container filled with a non-Newtonian fluid. The leading edge is configured to be secured to the torsion box of the airfoil. The at least one container is arranged between the concave side of the leading plate and the torsion box of the airfoil. An airfoil is also provided including such a leading edge. A method is provided for assembling such a leading edge.