A blade for a rotor of a hover-capable aircraft is described comprising: a main body with a first outer surface; and a de-icing system for removing ice; the de-icing system, in turn, comprises: a first layer formed by a shape-memory material activatable so as to alter its shape according to a temperature-associable quantity, which is arranged on at least one outer surface of the main body; the de-icing system is characterized in that it comprises a second covering layer, which defines at least a portion of a second outer surface of the blade on which ice deposits; the second layer laid on top of the first layer on the opposite side of the main body is selectively movable under the action of the first layer so as to exert a mechanical action on the ice and remove it from the blade, and is adapted to protect the first layer from external agents.

A method of deicing an airfoil is provided. In preferred embodiments, the method comprises coupling a plurality of piezo-electric transducers (PETs) to an inside surface of an airfoil. The PETs are electrically coupled to a DC-DC converter and a first inverter. The PETs are driven by sweeping the driving frequency of the plurality of PETs over a frequency range that spans at least 10 kHz and 100 kHz. In preferred embodiments, some PETs are driven at a phase shift to the other PETs.

An arrangement for mechanically changing a surface includes an insulating layer, a pair of electrodes, which is arranged on or in the insulating layer, and a piezo element, which is arranged on or in the insulating layer. The piezo element is separated from the pair of electrodes by the insulating layer. The pair of electrodes is designed to generate in a region of the piezo element an electric field, which causes the piezo element to carry out a mechanical change of shape, in order in this way to mechanically change a surface of the arrangement. The pair of electrodes is also designed to generate the electric field such that the electric field has a minimum field strength in a surrounding area of the arrangement, in order in this way to generate a plasma in the surrounding area of the arrangement.

A blade for a rotor of a hover-capable aircraft is described comprising: a main body with a first outer surface; and a de-icing system for removing ice; the de-icing system, in turn, comprises: a first layer formed by a shape-memory material activatable so as to alter its shape according to a temperature-associable quantity, which is arranged on at least one outer surface of the main body; the de-icing system is characterized in that it comprises a second covering layer, which defines at least a portion of a second outer surface of the blade on which ice deposits; the second layer laid on top of the first layer on the opposite side of the main body is selectively movable under the action of the first layer so as to exert a mechanical action on the ice and remove it from the blade, and is adapted to protect the first layer from external agents.

A flow body for an aircraft with an integrated de-icing system. The flow body includes a front skin, an internal structural component, a lever having first and second ends, with an attachment point in-between, and an actuator. The actuator is spaced inside the front skin. The lever extends from the actuator to a front skin inner surface, the first end coupling with the front skin, and the second end coupling with the actuator. The attachment point is swivably supported on the internal structural component. The attachment joint is closer to the first end than the second end. The lever and the actuator apply an impulsive force in a transverse direction to the lever, such that the lever rotates around the attachment point, and such the first end urges the front skin to locally elastically deform for removing ice accretion from an outer side of the front skin.

A de-icing element having a skin with a surface to be de-iced, at least one excitation actuator attached to the skin, the excitation actuator configured to excite the skin according to at least one predetermined vibration mode generating a deformation of the skin, the deformation of the skin comprising at least one antinode and one node. The skin having a characteristic thickness generally constant with, locally, at least one thickness variation that is localized according to the predetermined vibration mode or modes.

Active superhydrophobic surface structures are actively-controlled surface structures exhibiting a superhydrophobic state and an ordinary state. Active superhydrophobic surface structures comprise an outer elastomeric covering defining an exposed surface, a controlled group of MEMS (micro-electro-mechanical system) actuators at least covered by the elastomeric covering, and, a controlled region of the exposed surface corresponding to the controlled group. The controlled region has a superhydrophobic state in which the controlled region is textured. The controlled region also has an ordinary state in which the controlled region is smooth (i.e., less textured than in the superhydrophobic state). Active superhydrophobic surface structures may be part of an apparatus that includes a controller and/or one or more sensors. The controller, sensors, and the controlled region may form a feedback loop in which the active superhydrophobic surface is actively controlled.

An aircraft flight surface deicing system includes an electromagnetic field generator and a deicing boot configured for attachment to an aircraft flight surface. The boot includes: one or more inflation regions including a first inflation region; one or more magnetic fluid reservoirs in fluid communication with the first inflation region, the one or more fluid reservoirs including a first fluid reservoir; a magnetic fluid contained in a combination of the first inflation regions and the one or more magnetic fluid reservoirs. In a first state, the magnetic fluid is contained in the first fluid reservoir and, in a deicing state, the electromagnetic field generator generates one or more fields that cause the magnetic fluid to exit the first fluid reservoir and travels along a length of the inflation region.

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.

A flow body for an aircraft with an integrated de-icing system. The flow body includes a front skin, an internal structural component, a lever having first and second ends, with an attachment point in-between, and an actuator. The actuator is spaced inside the front skin. The lever extends from the actuator to a front skin inner surface, the first end coupling with the front skin, and the second end coupling with the actuator. The attachment point is swivably supported on the internal structural component. The attachment joint is closer to the first end than the second end. The lever and the actuator apply an impulsive force in a transverse direction to the lever, such that the lever rotates around the attachment point, and such the first end urges the front skin to locally elastically deform for removing ice accretion from an outer side of the front skin.