An optimized protection against ice on the inner and outer faces of an aircraft engine nacelle air intake with the air intake including an outer face and an inner face meeting at a line at the longitudinally extreme, called extremum line, an acoustic panel being installed on the inner surface of a part of the inner face. An elimination system based on vibration of the ice formed is put in place on at least a part of the outer face and an ice formation prevention system using a hot fluid is put in place on at least a part of the inner face and either an ice elimination system or an ice formation prevention system using a hot fluid is installed on the inner face and on the outer face, a marking line marking the boundary between the two systems.

An anti-icing protection system for an aircraft engine nacelle, the nacelle comprising an inner shroud, an air intake lip forming a leading edge of the nacelle, the protection system comprising a heat exchanger device including at least one heat pipe configured to transfer heat emitted by a heat source to the inner shroud.

An ice protection system comprises deicing zones each including an envelope defining an ice-protection area. Adjacent envelopes have spanwise edge regions flanking shared interzone borders. The edge regions are provided with nonlinear contours having features which project-and-recess in a direction generally parallel to the airstream direction.

An ice protection system comprises deicing zones each including an envelope defining an ice-protection area. Adjacent envelopes have spanwise edge regions flanking shared interzone borders. The edge regions are provided with nonlinear contours having features which project-and-recess in a direction generally parallel to the airstream direction.

A selectively deployable heated propulsor system which may be integrated into vehicles, airplanes, or any other machinery configured for flight. The system includes a structural feature that includes a mounted propulsor including a rotor and a motor mechanically coupled to the rotor allowing the rotor to rotate when in an activated mode. The mounted propulsor includes a chamber configured to support a first configuration where the propulsor and the rotor are stowed and heated in an enclosed environment, and a second configuration where the rotor is deployed.

A selectively deployable heated propulsor system which may be integrated into vehicles, airplanes, or any other machinery configured for flight. The system includes a structural feature that includes a mounted propulsor including a rotor and a motor mechanically coupled to the rotor allowing the rotor to rotate when in an activated mode. The mounted propulsor includes a chamber configured to support a first configuration where the propulsor and the rotor are stowed and heated in an enclosed environment, and a second configuration where the rotor is deployed.

An electrically powered aerial vehicle includes at least one motor where each motor includes a stator and a rotor, a motor housing having an inlet opening and a discharge opening for airflow, a plurality of rotor blades rotatable by the rotor, each of the plurality of rotor blades having a cavity running from a proximal end of the rotor blade towards a distal end of the rotor blade, and a blade hub coupled to the rotor blades at the proximal end of each rotor blade and coupled to the motor housing at the discharge opening. A chamber is defined in the blade hub and is in fluid communication with the discharge opening of the motor housing and the cavity of each rotor blade. The airflow is centrifugally drawn in from the motor housing through the discharge opening and transported through the chamber and into the cavities of the rotor blades when the rotor blades are rotating.

An anti-icing system at least includes: a precooler that exchanges heat between bleed air and outside air; and an anti-icing unit that receives the bleed air passed through the precooler. A bleed air flow rate adjusting section that adjusts a flow rate of the bleed air supplied to the anti-icing unit adjusts the flow rate of the bleed air to suppress pressure of the bleed air to a pressure upper limit or lower by using relationship r1 and relationship r2. The relationship r1 is a relationship between an altitude and a pressure upper limit of the bleed air. The relationship r2 is a relationship between the pressure upper limit and outside air temperature at which the temperature of the bleed air reaches allowable temperature of ducts and other members through which the bleed air flows. The relationship r2 is provided based on the altitude.

There is provided a pressure regulating shut-off valve comprising a valve body, at least one piston serving as a regulating piston and/or a shut-off piston, a solenoid valve, and a pressure relief valve; wherein the valve body defines an inlet and an outlet, and comprises at least a portion formed by an additive manufacturing process.

There is provided a pressure regulating shut-off valve comprising a valve body, at least one piston serving as a regulating piston and/or a shut-off piston, a solenoid valve, and a pressure relief valve; wherein the valve body defines an inlet and an outlet, and comprises at least a portion formed by an additive manufacturing process.