Abstract: A method of improving the measurement accuracy of a digital ice rate sensor by providing an enhanced surface finish on a magnetostrictive oscillator detector probe by measuring the surface roughness of the detector probe, comparing the measured value to a critical value, and authorizing the probe for use in the digital ice rate sensor if surface roughness is within the critical value. Surface roughness may be measured optically or with a surface profilometer. Remedial steps taken if surface roughness is not within the critical value include reworking the probe surface finish and investigating the manufacturing process.

Abstract: A method of improving the measurement accuracy of a digital ice rate sensor by providing an enhanced surface finish on a magnetostrictive oscillator detector probe by measuring the surface roughness of the detector probe, comparing the measured value to a critical value, and authorizing the probe for use in the digital ice rate sensor if surface roughness is within the critical value. Surface roughness may be measured optically or with a surface profilometer. Remedial steps taken if surface roughness is not within the critical value include reworking the probe surface finish and investigating the manufacturing process.

Abstract: A system includes a device having a first surface configured to be exposed to airflow about an exterior of an aircraft, the device including a first self-compensating heater configured to heat the first surface, a first current monitor configured to sense a first measurement value representing electrical current flow through the first self-compensating heater, one or more processors, and computer-readable memory encoded with instructions that, when executed by the one or more processors, cause the system to receive aircraft flight condition data and produce an icing condition signal based upon the first measurement value and the aircraft flight condition data.

Abstract: A system includes a device having a first surface configured to be exposed to airflow about an exterior of an aircraft, the device including a first self-compensating heater configured to heat the first surface, a first current monitor configured to sense a first measurement value representing electrical current flow through the first self-compensating heater, one or more processors, and computer-readable memory encoded with instructions that, when executed by the one or more processors, cause the system to receive aircraft flight condition data and produce an icing condition signal based upon the first measurement value and the aircraft flight condition data.