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.

An induction-heating system includes a susceptor located proximate to a flight surface of an aircraft. The susceptor comprises an array of wires arranged along a first axis. The array of wires is constructed of a ferromagnetic material having a selected Curie temperature. The induction-heating system also includes an electrically conductive coil including a plurality of coil windings oriented substantially perpendicular with respect to the first axis of the array of wires. The electrically conductive coil is configured to generate a magnetic field oriented substantially parallel with respect to the first axis of the array of wires. The electrically conductive coil is positioned to induce induction heating within the ferromagnetic material of the susceptor when the susceptor is below the selected Curie temperature.

An induction-heating system includes a susceptor located proximate to a flight surface of an aircraft. The susceptor comprises an array of wires arranged along a first axis. The array of wires is constructed of a ferromagnetic material having a selected Curie temperature. The induction-heating system also includes an electrically conductive coil including a plurality of coil windings oriented substantially perpendicular with respect to the first axis of the array of wires. The electrically conductive coil is configured to generate a magnetic field oriented substantially parallel with respect to the first axis of the array of wires. The electrically conductive coil is positioned to induce induction heating within the ferromagnetic material of the susceptor when the susceptor is below the selected Curie temperature.

A thermal management system for a sensor module is disclosed that includes a housing enclosing the sensor module and having a bottom wall with a reception port formed therein, and a thermal isolation puck installed within the reception port formed in the bottom wall of the housing for reducing the rate at which thermal energy from a heater located within an adjacent flush static plate is lost to the housing.

A thermal management system for a sensor module is disclosed that includes a housing enclosing the sensor module and having a bottom wall with a reception port formed therein, and a thermal isolation puck installed within the reception port formed in the bottom wall of the housing for reducing the rate at which thermal energy from a heater located within an adjacent flush static plate is lost to the housing.

A carbon nano tube (CNT) conduit heater system includes a CNT sheet having a first surface and a second surface. A first busbar is electrically coupled to the CNT sheet. A second busbar is electrically coupled to the CNT sheet. The second busbar is arranged substantially parallel to the first busbar. A first protective layer is disposed on the first surface and a second protective layer is disposed on the second surface, wherein the second protective layer is joined to the first protective layer encapsulating the CNT sheet the first busbar and the second busbar forming a heater assembly having a first side and a second side.

A carbon nano tube (CNT) conduit heater system includes a CNT sheet having a first surface and a second surface. A first busbar is electrically coupled to the CNT sheet. A second busbar is electrically coupled to the CNT sheet. The second busbar is arranged substantially parallel to the first busbar. A first protective layer is disposed on the first surface and a second protective layer is disposed on the second surface, wherein the second protective layer is joined to the first protective layer encapsulating the CNT sheet the first busbar and the second busbar forming a heater assembly having a first side and a second side.

Provided are embodiments including a system for performing health monitoring. The system includes a measurement device configured to measure pressure of an environment, a heating element of the heater section coupled to the measurement device, a first sensing element operably coupled to a first region of the measurement device, and a second sensing element operably coupled to a second region of the measurement device. The system also includes a programmable logic that is configured to generate a status signal or flag based at least in part on conditions of the first region or the second region of the measurement device, a processing system configured to control the heating element responsive to reaching a threshold temperature, and a display configured to display a status of the first region or second region of the measurement device based at least in part on the status signal or flag.

A flow body for an aircraft is disclosed having a stiffening structure and a flow surface at least partially enclosing the stiffening structure, the flow surface having a leading edge and a trailing edge at a distance to each other in a chordwise direction, the flow body including a first heating device attached to or integrated into the flow surface in a first chordwise section, a second heating device attached to or integrated into the surface body in a second chordwise section. The first chordwise section and the second chordwise section are distanced from each other, the first chordwise section is closer to the leading edge than the second chordwise section, and at least the second heating device comprises an electric heater.

Provided are embodiments including a system for performing health monitoring. The system includes a measurement device configured to measure pressure of an environment, a heating element of the heater section coupled to the measurement device, a first sensing element operably coupled to a first region of the measurement device, and a second sensing element operably coupled to a second region of the measurement device. The system also includes a programmable logic that is configured to generate a status signal or flag based at least in part on conditions of the first region or the second region of the measurement device, a processing system configured to control the heating element responsive to reaching a threshold temperature, and a display configured to display a status of the first region or second region of the measurement device based at least in part on the status signal or flag.