An aircraft may include a fuselage, a propulsion assembly configured to produce thrust for the aircraft, and a gimballing mechanism articulatably coupling the propulsion assembly to the fuselage and configured to rotate the propulsion assembly about a first axis of rotation defined through a center of mass of the propulsion assembly, and rotate the propulsion assembly about a second axis of rotation defined through the center of mass of the propulsion assembly. The first axis of rotation may be perpendicular to the second axis of rotation. The first axis of rotation may be perpendicular to the second axis of rotation.

A stabilization system for an aircraft includes a rear stabilizer system. The rear stabilizer system is disposed in a rear portion of the fuselage of the aircraft. The rear stabilizer system includes a rear rudder having a tilt fan configured to generate lift. The rear stabilizer system is configured to detect a failure of an engine and activate an emergency mode. The instructions when executed cause the system to receive flight dynamics from an onboard sensor; determine an existence and a location of the engine failure; and send a signal to the rear rudder based on the existence and the location of the engine failure. The rear rudder engages in a first position. The first position generates counter-torque propulsion towards the engine that failed.

A stabilization system for an aircraft includes a rear stabilizer system. The rear stabilizer system is disposed in a rear portion of the fuselage of the aircraft. The rear stabilizer system includes a rear rudder having a tilt fan configured to generate lift. The rear stabilizer system is configured to detect a failure of an engine and activate an emergency mode. The instructions when executed cause the system to receive flight dynamics from an onboard sensor; determine an existence and a location of the engine failure; and send a signal to the rear rudder based on the existence and the location of the engine failure. The rear rudder engages in a first position. The first position generates counter-torque propulsion towards the engine that failed.

A wing for an aircraft is disclosed including a main wing, a slat, and a connection assembly movable connecting the slat to the main wing. The connection assembly includes an elongate slat track, wherein the front end of the slat track is mounted to the slat, wherein the rear end and the intermediate portion of the slat track are mounted to the main wing by a roller bearing including a guide rail mounted to the main wing and a first roller unit mounted to the rear end of the slat track and engaging the guide rail. The roller bearing includes a second roller unit mounted to the main wing and engaging an engagement surface at the intermediate portion of the slat track.

A wing for an aircraft is disclosed including a main wing, a slat, and a connection assembly movable connecting the slat to the main wing. The connection assembly includes an elongate slat track, wherein the front end of the slat track is mounted to the slat, wherein the rear end and the intermediate portion of the slat track are mounted to the main wing by a roller bearing including a guide rail mounted to the main wing and a first roller unit mounted to the rear end of the slat track and engaging the guide rail. The roller bearing includes a second roller unit mounted to the main wing and engaging an engagement surface at the intermediate portion of the slat track.

A leading-edge device for an aircraft, the device comprising a flow body having a front skin, a back skin, a spar and an air inlet. The front skin is curved around a spanwise axis to form a bottom section and a top section. A leading edge of the flow body is arranged between the bottom section and the top section. The spar extends from the bottom section to the top section. The front skin, the back skin and the spar enclose at least one air chamber that is in fluid communication with the air inlet. An outlet portion is arranged at least directly adjacent to the bottom section of the front skin. The outlet portion comprises a plurality of air outlets for letting air from the at least one air chamber exhaust through the air outlets.

A leading-edge slat for an aircraft is proposed, which includes a front skin), a back skin, a spar and an air inlet for receiving air at an elevated temperature for de-icing or anti-icing. In the slat, at least one air chamber is created, which is supplied with said air. A first portion of the back skin is attached to the spar at a distance to the bottom section, wherein a second portion of the back skin is attached to the top section. Thereby, a region in front of the fixed leading edge is created, into which air from air outlets integrated into the back skin can be exhausted outside of the slat.

An aircraft includes a wing and a rotor pod mounted to the wing. The rotor pod includes a body having a forward end and an aft end. A propeller is mounted to the body of the rotor pod at the forward end. A control surface is mounted to the body of the rotor pod between the forward and aft ends and extends outwardly from the body. The control surface is displaceable relative to the body between a first control configuration and a second control configuration to control an attitude of the aircraft. The control surface in the first control configuration is closer to the propeller than the control surface in the second control configuration.

An aircraft includes a wing and a rotor pod mounted to the wing. The rotor pod includes a body having a forward end and an aft end. A propeller is mounted to the body of the rotor pod at the forward end. A control surface is mounted to the body of the rotor pod between the forward and aft ends and extends outwardly from the body. The control surface is displaceable relative to the body between a first control configuration and a second control configuration to control an attitude of the aircraft. The control surface in the first control configuration is closer to the propeller than the control surface in the second control configuration.

An aircraft includes a wing and a rotor pod mounted to the wing. The rotor pod includes a body having a forward end and an aft end. A propeller is mounted to the body of the rotor pod at the forward end. A control surface is mounted to the body of the rotor pod between the forward and aft ends and extends outwardly from the body. The control surface is displaceable relative to the body between a first control configuration and a second control configuration to control an attitude of the aircraft. The control surface in the first control configuration is closer to the propeller than the control surface in the second control configuration.