Abstract: A deformable aerospace structure includes a first layer and a second layer spaced from the first layer and defining a space therebetween. The space includes one or more reinforcement elements extending between the first layer and the second layer. The ends or portions of the reinforcement element(s) proximate to the first layer are connected thereto and ends or portions of the reinforcement element(s) proximate to the second layer are moveable with respect to ends or portions of adjacent reinforcement element(s) proximate to the second layer.

Abstract: 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.

Abstract: An aerospace surface heating apparatus includes opposing layers formed from a thermoplastic containing in excess of 20% by volume of an inorganic filler material, and at least one electrically powered heating element located between the opposing layers. A method for making a heater for an aerospace component includes forming an electrical heating element on a layer of glass fiber reinforced thermoplastic film substrate, applying two opposing thermoplastic layers on opposing sides of the intermediate layer, and applying heat and pressure to the layers to join the layers together, in which the thermoplastic material contains an inorganic filler material.

Abstract: An aircraft, such as an unmanned aerial vehicle or single-seat aircraft, including a main body and a pair of wing sections, each wing section including a front wing and a rear wing, wherein the front wing and the rear wing each include a first end that is connected to the main body, and a second end, wherein the second end of the front wing is connected to the second end of the rear wing. The main body is located between the pair of wing sections, and each wing section includes a propulsion unit located between the front wing and the rear wing of the wing section. Each propulsion unit may include a first rotor and a second rotor, which may be pivotable with respect to the rest of the aircraft.

Abstract: In manufacturing an electrothermal heater mat, there is provided a preform which comprises a laminated stack of dielectric layers which are made of thermoplastic material and include a central layer or group of layers which include(s) reinforcement and first and second outer groups of layers which do not include reinforcement. The preform includes a heater element and the preform has a first configuration. The preform is then heated to a temperature (e.g. 180° C.) between the glass-transition temperature of the thermoplastic material and the melting point of the thermoplastic material, and the heated preform is formed into a second configuration which is different to the first configuration so as to produce the heater mat.

Abstract: A rib can be manufactured comprising two opposing outer skins and a plurality of internal reinforcement members connecting the skins together.

Abstract: In a method of manufacturing an electrothermal heater mat, a heater element is deposited on a first one of the dielectric layers of the heater mat by using a laser blown powder process.

Abstract: A method of forming a component by applying a forming load to a blank of material against a mandrel, wherein the mandrel defines the shape of the component to be formed and applying a forming load as a combination of a localised force and localised friction heating.

Abstract: In manufacturing an electrothermal heater mat, there is provided a preform which comprises a laminated stack of dielectric layers which are made of thermoplastic material and include a central layer or group of layers which include(s) reinforcement and first and second outer groups of layers which do not include reinforcement. The preform includes a heater element and the preform has a first configuration. The preform is then heated to a temperature (e.g. 180° C.) between the glass-transition temperature of the thermoplastic material and the melting point of the thermoplastic material, and the heated preform is formed into a second configuration which is different to the first configuration so as to produce the heater mat.

Abstract: An electrical coupling for aerospace applications comprises an interposer arranged in use to electrically connect an electrical connector to an electrical circuit, the electrical connector comprising a plurality of electrical contacts and the electrical circuit comprising a plurality of electrical conductors. The interposer comprises a body arranged to surround each electrical contact within the connector.

Abstract: A noise attenuation panel comprises a sound absorbing honeycomb layer disposed between a perforated surface layer on an airflow facing side of the panel and a composite support layer on a second opposing side of said panel. The composite material support layer comprises an electrical heat source.

Abstract: An ice accretion apparatus comprises a column having a longitudinal axis, a side wall, and a central chamber having top and bottom ends. It also comprises a top unit which closes the top end of the chamber and includes a droplet discharge device for producing water droplets, a bottom unit which closes the bottom end of the chamber and includes a target, and chamber cooling means configured to cool the chamber during a test and thereby to cool the water droplets, whereby, in use during the test, a layer of accreted ice is built up on the target.

Abstract: Ice test devices include an ice adhesion test device. The ice adhesion test device comprises an ice adhesion test target in the form of a well in which, in use, a layer of accreted ice is built up. The target comprises a sample plate at the bottom of the well and an ice-engagement element positioned circumferentially around the sample plate and providing a side wall of the well, and wherein the sample plate is rotatable relative to the ice-engagement element. The ice adhesion test device also comprises torque means for applying a rotational torque between the sample plate and the ice-engagement element. The ice adhesion test device also comprises transducer means for, at least at a point at which the layer of accreted ice separates from the sample plate, measuring the rotational torque and/or the stress on the ice.

Abstract: 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.

Abstract: An electrothermal heater mat (3) is provided for an ice protection system for an aircraft (1) or the like. The heater mat (3) is a laminated heater mat and comprises dielectric layers (50-58), a heater element (501) and a conductive ground plane (71-74) for detecting a fault with the heater element (501). The dielectric layers (50-58) are made of thermoplastic material, and the ground plane (71-74) is formed by spraying metal such as copper onto the thermoplastic material of one of the dielectric layers.

Abstract: An ice-protection system has first and second zones of a leading edge of an aerodynamic or streamlined aerodynamic component, each zone having a de-icing apparatus and an ice-detection sensor positioned behind an elongated convex window as to be aero-conformal with the leading edge. The ice-detection sensor is in the form of a module and has a sensor head having a front face and abutments at ends of the window. The ice-detection sensors may have a central light emitter and a plurality of sensor elements peripheral to the light emitter. The ice-protection system also has a control system responsive to the ice-detection sensors to control the respective de-icing apparatus, and may activate automatically a sequence of operation.

Abstract: An isolation layer is arranged between two adjacent upright portions of a T-section stiffener, which is arranged on and bonded to a surface.

Abstract: Method forming a composite structure (9) comprising a main body and a flange. The composite structure is manufactured by laying-up a preform (7) on a mold (6). The preform (7) does not have the first and second bends and comprises a first part which corresponds to the main body of the composite structure and a second part which corresponds to the flange of the composite structure. The second part of the (preform (7) has a proximal portion which corresponds to the wall portion of the flange and a distal portion which corresponds to the lip portion of the flange. The preform (7) comprises a plurality of plies and uni-directional ply material extends from the first part of the preform (7) to the distal portion of the second part of the preform (7).