Active surface structures comprise an exposed surface, a controlled group of MEMS (micro-electro-mechanical system) actuators, and a controlled region of the exposed surface corresponding to the controlled group. The controlled region has a first state, and a second state that is less textured than the first state. Active 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 surface structure is actively controlled.

Viscoelastic icephobic surfaces of the present disclosure include organogel particle beads dispersed in an elastomer matrix. The surfaces are highly repellant to ice formation, easy and cost efficient to apply, and have long term durability for harsh outdoor applications.

A method and system for detecting and determining icing conditions. The method includes: creating a statistical model from test data in which set of data from n data inputs are each plotted as a point in n-dimensional space, and wherein the n-dimensional space is divided into a plurality of regions each representative of a different icing condition according to the data in that region; for a set of current data from n data inputs, using the model to classify the icing condition indicated by the current data, by: obtaining current data from n data inputs; providing the current data as input data to the model; determining the region of the model in which the current data set is located; and identifying the icing condition indicated by the current data set according to the determined region.

Viscoelastic icephobic surfaces of the present disclosure include organogel particle beads dispersed in an elastomer matrix. The surfaces are highly repellant to ice formation, easy and cost efficient to apply, and have long term durability for harsh outdoor applications.

Viscoelastic icephobic surfaces of the present disclosure include organogel particle beads dispersed in an elastomer matrix. The surfaces are highly repellant to ice formation, easy and cost efficient to apply, and have long term durability for harsh outdoor applications.

A temperature monitoring unit may be removably installed inside an aircraft wing structure for monitoring temperature conditions along the span of the wing. The wing structure has a temperature-sensitive device (162) for monitoring a temperature condition, which is attached to a support frame (173). The support frame and attached temperature-sensitive device may be installed as a unit within the wing structure. The support frame may be configured for sliding engagement inside the wing structure, for example, with a set of tracks.

A rotorcraft provided with a yaw motion control system comprising a fairing and a rotor provided with blades, the blades being arranged in the fairing and able to rotate about an axis of rotation of the rotor, the fairing comprising a casing defining an air stream, the air stream extending in a direction of flow of the air within the fairing from an intake section towards an outlet section. The rotorcraft comprises an ice protection system comprising at least one grille arranged upstream of the air stream in the air flow direction, the grille facing the intake section parallel to the axis of rotation and the casing, no grille facing at least one unprotected section of the intake section in a direction parallel to the axis of rotation.

A rotorcraft provided with a yaw motion control system comprising a fairing and a rotor provided with blades, the blades being arranged in the fairing and able to rotate about an axis of rotation of the rotor, the fairing comprising a casing defining an air stream, the air stream extending in a direction of flow of the air within the fairing from an intake section towards an outlet section. The rotorcraft comprises an ice protection system comprising at least one grille arranged upstream of the air stream in the air flow direction, the grille facing the intake section parallel to the axis of rotation and the casing, no grille facing at least one unprotected section of the intake section in a direction parallel to the axis of rotation.

An aircraft line or harness fastening system with a clamp attaching the line or harness to the aircraft. A bobbin within the clamp surrounds the line or harness, wherein the bobbin is smaller than the clamp and is circular in shape to enable rotation of the bobbin within the clamp. The bobbin includes two separate complementary parts that fit together around the line or harness. Each of the two separate complementary parts include a tab and a recess, wherein the tab of one of the complementary parts fits into the recess on the other of the complementary parts.

The present invention is directed to a coated substrate including a substrate that is part of an aerospace, a wind turbine, or a marine structure; and an exterior coating on the substrate, the exterior coating including an icephobic or a low ice adhesion composition including an indicator that is an additive that is detectable or measurable as the exterior coating wears; wherein the indicator provides indicia of wear of the exterior coating; and a method of inspecting the exterior coating on the substrate.