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.

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.

A sensor assembly for monitoring a heater system for an aircraft probe sensor includes a current sensor module with a current sensor core and a high electromagnetically permeable enclosure around the current sensor core. An input wire pathway extends through the current sensor core and is configured to receive a heater input wire. A return wire pathway extends through the current sensor core and is configured to receive a heater return wire. A high electromagnetically permeable tube extends through the current sensor core and is configured to extend around one of the input wire and the heater return wire.

A system for monitoring performance of an aircraft windshield includes a sensor comprising a sensory contact and an evaluation unit. The sensory contact is in physical contact with one or more components of the windshield, and generates a signal representative of the performance of the component(s) of the windshield. An electrical connector is secured to the surface of the windshield facing the interior of the aircraft. The signal from the sensory contact passes through the connector to the evaluation unit. The evaluation unit acts on the signal to determine the performance of the component(s) of the windshield, wherein the evaluation unit is spaced from and out of physical contact with the windshield and the electrical connector, and is in electrical contact with the electrical connector.

A system for monitoring performance of an aircraft windshield includes a sensor comprising a sensory contact and an evaluation unit. The sensory contact is in physical contact with one or more components of the windshield, and generates a signal representative of the performance of the component(s) of the windshield. An electrical connector is secured to the surface of the windshield facing the interior of the aircraft. The signal from the sensory contact passes through the connector to the evaluation unit. The evaluation unit acts on the signal to determine the performance of the component(s) of the windshield, wherein the evaluation unit is spaced from and out of physical contact with the windshield and the electrical connector, and is in electrical contact with the electrical connector.

The present disclosure provides methods of coating a substrate. A method includes depositing a conductive coating including an electrically conductive material over the substrate to form a conductive layer having a sheet resistivity of about 10 Ω/□ to about 1000 Ω/□. The method includes depositing an anti-icing layer comprising nanomaterials over the conductive layer to form a coating system.

Pendulum dampers are described. The pendulum dampers include a damper body having a first end and a second end, with an axial direction defined between the first end and the second end with a heater bore passing through the damper body in the axial direction from a tail port at the second end toward the first end and a cartridge heater installed within the heater bore, the cartridge heater configured to generate heat and heat a material of the damper body.

Pendulum dampers are described. The pendulum dampers include a damper body having a first end and a second end, with an axial direction defined between the first end and the second end with a heater bore passing through the damper body in the axial direction from a tail port at the second end toward the first end and a cartridge heater installed within the heater bore, the cartridge heater configured to generate heat and heat a material of the damper body.

An air date probe includes a base portion, a strut portion extending from the base portion, and a tube assembly secured to an extending from the strut portion. One or more of the tube assembly or the strut portion includes a sleeve member having a sleeve outer surface positioned at a sleeve frustum angle relative to a sleeve member axis. A thin film heater is positioned at the sleeve outer surface, and the tin film heater and the sleeve member are positioned in a housing member. The housing member has a housing inner surface having a housing frustum angle such that the thin film heater is retained by compression between the housing member inner surface and the sleeve member outer surface.

A resistive heater system comprising a braided and flattened electrical lead connected to a heating blanket or coating at one end of the lead. The braided and flattened electrical lead comprises a folded-over section that forms an angle in the lead of 70 to 110°. The invention also includes an aircraft comprising the heater system. Nonlimiting examples of aircraft include helicopter, drone, and airplane.