Abstract. Pressure-pulsation measurements in aircraft testing depend on the sensing element, connecting passages, housing cavities and supply circuit. This study separates their effects on frequency response, local temperature compensation and uncertainty under explicit assumptions relevant to semiconductor sensors intended for extreme conditions. Thin-plate and second-order models, viscothermal tube transfer matrices and an additive decibel uncertainty model are checked through limiting cases, independent calculations and Monte Carlo propagation. A single bandwidth boundary cannot jointly identify natural frequency and damping. A lower frequency estimate near 195 kHz requires an assumed 65 kHz bandwidth and damping of 0.01–0.10. For a neck 0.8 mm in diameter and 1 mm long, with a 1 mm³ cavity, the complete cascade has a peak at 25.728 kHz and a bandwidth of 7.981 kHz. A 20 mm probe of radius 0.40 mm reduces the bandwidth to 0.981 kHz. Cavity thermal losses and diaphragm acoustic back-loading are neglected. With assumed temperature coefficients and a 6 V supply, the restricted topology provides 13.846 percent of the required local compensation; zeroing the first derivative does not establish stability across the temperature range. Two illustrative budgets give expanded uncertainties of 2.491 and 0.980 dB for a coverage factor of two, and 95 percent interval half-widths of 2.214 and 0.950 dB. The results are conditional computational examples, without new experimental validation or verified accuracy claims for a particular sensor. The work provides a basis for testing the model assumptions and for designing a subsequent measurement protocol.

Keywords: piezoresistive sensor, frequency response, cavity resonance, acoustic probe, parameter identification, temperature compensation, measurement uncertainty, numerical verification.