The present invention relates to an integrated controller unit (10) for controlling at least one engine motor (26) and at least one servo motor (28), comprising a power link section (12) for connecting the controller unit (10) to an external power supply (14) and supplying power to the individual sections of the controller unit (10), a data link section (16) for connecting the controller unit (10) to an external data source, a computing section (18) operatively connected with the power link section (12) and the data link section (16) for receiving data from the external data source, performing computing tasks based on the received data and outputting control commands, an engine interface section (20) for driving the at least one engine motor (26), and a servo interface section (22) for driving the at least one servo motor (28), wherein the engine interface section (20) and the servo interface section (22) are both operatively connected to the computing section (18) and adapted to drive the at least one engine motor (26) and the at least one servo motor (28), respectively, based on control commands output by the computing section (18).

The invention concerns an aircraft propulsion system comprising at least one member (1, 3, 4, 8) in contact with a turbulent flow of a stream (F), characterised in that said member is covered, at least partially, by a piezoelectric structure (S) such as a piezoelectric film, said structure (S) comprising a grooved structure (5, 6, 7, 9) comprising a series of grooves, in contact with the flow of the stream, the grooves extending in the direction of flow of the stream, the grooved structure comprising at least one geometric parameter (h, s, w) configured to adapt depending on at least one parameter of the flow of the stream and/or an operating point of the propulsion system and/or an engine speed of the propulsion system.

An ice removal apparatus for an aircraft is provided comprising a laminate structure encapsulating an electrically operable heater. The laminate structure comprises a plurality of layers and at least two layers are configured to be selectively movable relative to each other to increase the separation of the two layers, thereby removing ice.

A method for de-icing or anti-icing an aircraft portion having at least one piezoelectric element fastened on the inner face of the aircraft portion includes, during a design phase of the aircraft portion, placing the piezoelectric element on an area of the aircraft portion to determine frequencies of resonance and increased dynamic coupling, and during the de-icing or anti-icing of the aircraft portion, the same piezoelectric element is excited according to the natural frequencies of the area.

A microelectronic module for cleaning a surface is described. The microelectronic module comprises at least one voltage converter for converting a provided first voltage into a higher, lower, or identical second voltage. The module also comprises at least one actuator. The actuator comprises at least one generator for generating an ionic current, an electrical plasma, harmonic components and/or an electrostatic field from the second voltage which is provided by the voltage converter. At least the voltage converter and the actuator are disposed on a thin-film, planar substrate. At least most of at least one object adhering to the surface is removed by the actuator.

A defrosting device includes an actuator including: a stationary portion and a movable portion configured to alternately move away from and move towards the stationary portion, and an intermediate element including a loading portion configured to be pushed by the movable portion of the actuator when the movable portion of the actuator moves away from the stationary portion, and a movement transmission portion configured to move according to the movement of the loading portion and to push a part to be defrosted to deform the part to be defrosted. The movable portion of the actuator and the loading portion of the intermediate element are not connected to one another, such that the loading portion of the intermediate element cannot pull the movable portion of the actuator to move same away from the stationary portion.

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.

We describe an ice protection system used for removing ice and/or other accretions from a structure. An actuator, coupled to a structure, is driven to generate vibrations in the structure. A controller drives the actuator using a signal that comprises a frequency chirp over a first period of time, and the controller controls the frequency chirp and the first period such that vibrations generated in the structure by the actuator propagate through the structure to coincide at a desired area of the structure remote from the actuator to remove ice and/or other accretions from the desired area of the structure.

An aircraft may include a fuselage, and a moisture accumulation prevention system that prevents moisture from accumulating on at least one structure within the fuselage. The moisture accumulation prevention system includes at least one ultrasonic element coupled to the structure(s). The ultrasonic element(s) operates at a frequency that prevents moisture particles from adhering to a surface of the structure(s).

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.