Methods and systems are generally described that inhibit debris (such as ice) accretions and/or remove debris (such as ice) accretions from the exterior surface of an aircraft. In some embodiments, the invention is a system for an aircraft comprising: a component of the aircraft having a surface; a plurality of piezo-kinetic actuators each positioned proximate to a portion of the surface; and a control unit coupled to the plurality of actuators, the control unit configured to actuate one or more of the actuators at one or more frequencies; wherein the actuators are each configured to introduce a displacement of the surface in three dimensions to inhibit a formation of ice on at least the portion of the surface and to break up existing ice formations on at least the portion of the surface.

Methods and systems are generally described that inhibit debris (such as ice) accretions and/or remove debris (such as ice) accretions from the exterior surface of an aircraft. In some embodiments, the invention is a system for an aircraft comprising: a component of the aircraft having a surface; a plurality of piezo-kinetic actuators each positioned proximate to a portion of the surface; and a control unit coupled to the plurality of actuators, the control unit configured to actuate one or more of the actuators at one or more frequencies; wherein the actuators are each configured to introduce a displacement of the surface in three dimensions to inhibit a formation of ice on at least the portion of the surface and to break up existing ice formations on at least the portion of the surface.

A hazard warning system can be utilized in an aircraft. The hazard warning system can include a processing system for determining a high altitude ice crystal (HAIC) condition and causing a warning of the HAIC condition to be displayed. An avionic display can be used to display the warning of the HAIC condition.

A hazard warning system can be utilized in an aircraft. The hazard warning system can include a processing system for determining a high altitude ice crystal (HAIC) condition and causing a warning of the HAIC condition to be displayed. An avionic display can be used to display the warning of the HAIC condition.

Methods and apparatus for detecting surface deformation of aircraft surfaces are disclosed. An example apparatus includes a sensor system to monitor an aircraft surface, the sensor system including a first sensor and a second sensor. A surface monitoring system receives signals from the first sensor and the second sensor and based on the signals received, the surface monitoring system is to: detect a surface deformation on the aircraft surface; analyze one or more environmental conditions or aircraft parameters; and classify a severity of a detected surface deformation based on the one or more environmental conditions or aircraft parameters to determine if the detected surface deformation impacts aircraft performance or safety.

An anti-icing system at least includes: a precooler that exchanges heat between bleed air and outside air; and an anti-icing unit that receives the bleed air passed through the precooler. A bleed air flow rate adjusting section that adjusts a flow rate of the bleed air supplied to the anti-icing unit adjusts the flow rate of the bleed air to suppress pressure of the bleed air to a pressure upper limit or lower by using relationship r1 and relationship r2. The relationship r1 is a relationship between an altitude and a pressure upper limit of the bleed air. The relationship r2 is a relationship between the pressure upper limit and outside air temperature at which the temperature of the bleed air reaches allowable temperature of ducts and other members through which the bleed air flows. The relationship r2 is provided based on the altitude.

An anti-icing system at least includes: a precooler that exchanges heat between bleed air and outside air; and an anti-icing unit that receives the bleed air passed through the precooler. A bleed air flow rate adjusting section that adjusts a flow rate of the bleed air supplied to the anti-icing unit adjusts the flow rate of the bleed air to suppress pressure of the bleed air to a pressure upper limit or lower by using relationship r1 and relationship r2. The relationship r1 is a relationship between an altitude and a pressure upper limit of the bleed air. The relationship r2 is a relationship between the pressure upper limit and outside air temperature at which the temperature of the bleed air reaches allowable temperature of ducts and other members through which the bleed air flows. The relationship r2 is provided based on the altitude.

A method of determining ice accretion on a surface of an aircraft can include supplying a known power to a heating element formed in a patch, wherein the patch includes a temperature sensor. A controller module can compare a sensed thermal signature with a threshold signature and determine the presence of ice accretion on the aircraft.

In some examples, a system includes a receiver configured to receive temperature data for a region of airspace from a data source external to the vehicle. The system also includes processing circuitry configured to determine one or more moisture values for the region of airspace based on radar returns received by a weather radar onboard the vehicle. The processing circuitry is further configured to determine a potential for icing at a location within the region of airspace based on the one or more moisture values and further based on the temperature data received from the data source. The processing circuitry is also configured to generate an output based on the determined potential for icing at the location.

In some examples, a system includes a receiver configured to receive temperature data for a region of airspace from a data source external to the vehicle. The system also includes processing circuitry configured to determine one or more moisture values for the region of airspace based on radar returns received by a weather radar onboard the vehicle. The processing circuitry is further configured to determine a potential for icing at a location within the region of airspace based on the one or more moisture values and further based on the temperature data received from the data source. The processing circuitry is also configured to generate an output based on the determined potential for icing at the location.