Abstract
Given the high-power concentration of combustion engines used in military aviation, it is reasonable to measure the instantaneous surges in the sound pressure level. Therefore, a re�search question was raised regarding the differences in this level for various aircraft engines of the same type (F100-PW-229) to assess their size and statistical significance. The aim of the paper is to discuss the attempt to check the significant difference between the parameters of the acoustic level generated by the aircraft engines. The measurements were carried out for 32 engines of the F-16 Block 52+ multirole aircraft during takeoff process. The parameters of noise in the point system and in the octave distribution were subject to analysis. Statistical methods dedicated to assessing production stability, i.e. the Shewhart chart, were applied. The results of the analysis showed that the discrepancies generally do not exceed a value of +/− 3σ . Therefore, it can be concluded that the analogous results for F-16 noise are homo�geneous. Thus, the Shewhart chart method proved useful for assessing the homogeneity of these measurements.
Highlights
Air traffic and aircraft ground services generate noise, the main source of which are the engines operating in the air and on the tarmac [7, 12, 59]
One of the still unsolved problems related to the aircraft noise measurement is the assessment of the level and structure of noise in different examples of the same aircraft
In the paper the authors presented a novel approach to the analysis of acoustic signal using methods of statistical quality control
Summary
Air traffic and aircraft ground services generate noise, the main source of which are the engines operating in the air and on the tarmac [7, 12, 59]. No other approach than the subjective assessment of the nuisance of aircraft noise has been taken into account (frequently used and based on subjective popular survey evaluation) [9, 26, 45]. The manner in which the periodic and pre-flight maintenance of the F-16 aircrafts are performed determines their technical condition, which directly affects the emitted noise level. One of the possible indirect sources of this kind of knowledge may be the result of noise analysis using the Shewhart control charts This means that the measurement results of selected aircraft, which significantly differ from the established reference range, may indicate to poor technical condition and the further need to unplanned maintenance action
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