A piece of aeronautic equipment intended to equip an aircraft, the equipment (25) including a part intended to be arranged at a skin (27) of the aircraft and elements for heating the part, characterized in that the heating elements include a thermodynamic loop including a closed circuit in which a heat transfer fluid circulates, the closed circuit including an evaporator (14) associated with functional elements (25a) of the aircraft forming a heat source giving off heat during their operation and a zone in which a condensation of the heat transfer fluid can occur in the appendage to heat it, and in that outside the evaporator (14), the circuit in which the fluid circulates is formed by a tubular channel with an empty section.

A piece of aeronautic equipment intended to equip an aircraft, the equipment piece (25) including at least one part intended to be arranged at a skin (27) outside of the aircraft and heating elements for that part, which include a thermodynamic loop including a closed circuit in which a heat transfer fluid circulates, the closed circuit including an evaporator and a zone in which condensation of the heat transfer fluid can occur in the appendage to heat it, outside the evaporator, the circuit in which the fluid circulates is formed by a tubular channel with an empty section, at least the part of the piece of equipment arranged outside the aircraft is made by additive manufacturing and includes a fastening base (120) for fastening on the skin of the aircraft from which support elements (130) for a Pitot tube (140) provided with lateral static pressure taps (150) extend.

A piece of aeronautic equipment intended to equip an aircraft, the equipment piece (25) including at least one part intended to be arranged at a skin (27) outside of the aircraft and heating elements for that part, which include a thermodynamic loop including a closed circuit in which a heat transfer fluid circulates, the closed circuit including an evaporator and a zone in which condensation of the heat transfer fluid can occur in the appendage to heat it, outside the evaporator, the circuit in which the fluid circulates is formed by a tubular channel with an empty section, at least the part of the piece of equipment arranged outside the aircraft is made by additive manufacturing and includes a fastening base (120) for fastening on the skin of the aircraft from which support elements (130) for a Pitot tube (140) provided with lateral static pressure taps (150) extend.

An inlet assembly of a nacelle includes an inlet cowl that has a leading edge, an outer side that extends from the leading edge to an outer aft edge, and an inner side that extends from the leading edge to an inner aft edge. An exterior surface of the inlet cowl is seamless along an entire length of the outer side from the leading edge to the outer aft edge. The inlet cowl includes a lipskin that has a metallic coating. The metallic coating defines the exterior surface of the inlet cowl along the leading edge and the entire length of the outer side.

An inlet assembly of a nacelle includes an inlet cowl that has a leading edge, an outer side that extends from the leading edge to an outer aft edge, and an inner side that extends from the leading edge to an inner aft edge. An exterior surface of the inlet cowl is seamless along an entire length of the outer side from the leading edge to the outer aft edge. The inlet cowl includes a lipskin that has a metallic coating. The metallic coating defines the exterior surface of the inlet cowl along the leading edge and the entire length of the outer side.

Embodiments of the present disclosure provide systems and methods for averting, shedding, or otherwise managing ice accretions that may develop during flight of an aircraft. Example systems and methods selectively modulate propeller parameters in a way that does not disrupt a flight trajectory; direct oil from a lubrication and cooling path to targeted sections of ice-prone surfaces to manage ice accretion in a way that does not unduly increase the total volume of oil, require larger pumps, or complicate the system; or generate heat at targeted areas of a propeller assembly by electric heating systems that utilize propeller motion.

Embodiments of the present disclosure provide systems and methods for averting, shedding, or otherwise managing ice accretions that may develop during flight of an aircraft. Example systems and methods generate heat at targeted areas of a propeller assembly by electric heating systems that utilize propeller motion.

An aircraft is provided which includes an airframe, a propulsion system and a thermal anti-icing system. The airframe includes a body and a plurality of wings. The body extends longitudinally along a centerline. The wings are disposed to opposing lateral sides of the body. Each of the wings projects spanwise out from the body. The propulsion system is connected to the airframe. The thermal anti-icing system is configured to heat a region of an exterior surface of the airframe longitudinally upstream of and laterally overlapping with the propulsion system.

An aircraft is provided which includes an airframe, a propulsion system and a thermal anti-icing system. The airframe includes a body and a plurality of wings. The body extends longitudinally along a centerline. The wings are disposed to opposing lateral sides of the body. Each of the wings projects spanwise out from the body. The propulsion system is connected to the airframe. The thermal anti-icing system is configured to heat a region of an exterior surface of the airframe longitudinally upstream of and laterally overlapping with the propulsion system.

A perforation forming system includes a laser device and a control unit operably connected to the laser device. The control unit is configured to control the laser device to laser drill a plurality of perforations through a lipskin that has a curved contour. The lipskin includes a metallic coating that defines an exterior surface of the lipskin and a composite panel that defines an interior surface of the lipskin. The control unit is configured to form the perforations by controlling the laser device to emit laser beams that impinge upon the interior surface of the lipskin and penetrate the composite panel before penetrating the metallic coating.