Abstract
This article presents the selected results of analytical and structural work conducted at the Air Force Institute of Technology (pl. ITWL) in the field of building a measuring apparatus for non-invasive monitoring of the technical condition of aircraft power units. Presented innovative FAM-C and FDM-A methods allow for observation of frequency modulation parameters as well as identification and diagnostic classification of particular mechanical subassemblies supplying the on-board generator and thus enable non-invasive monitoring of technical condition of the aircraft power unit and the aircraft propulsion system. The main purpose of this article is to present the measurement apparatus errors that occur in the signal conditioning system in the FAM-C and FDM-A methods. In spite of the fact that the measuring instrument was built on the basis of digital technology and that it uses typical solutions of electronic frequency measurement, due to the specificity of the applied diagnostic method there occur specific measuring errors which are presented in this article.
Highlights
IntroductionDiagnostics exerts a positive influence on improving and upgrading the operation and maintenance of technical facilities
To illustrate the essence of the FAM-C method, which uses the feedback of instantaneous frequency changes in the electromotive force generated in an on-board generator, the simplified mathematical model was assumed, which describes the dynamical phenomena in the selected kinematic pair installed in the aircraft power unit
In the case of frequencies based on half-period signals, phase shift errors resulting in the change of the duty cycle of the TTL signal should be considered
Summary
Diagnostics exerts a positive influence on improving and upgrading the operation and maintenance of technical facilities. It is not necessary to take into account the change in the technical condition of the aircraft caused by the simultaneous occurrence of several reasons. In detecting and identifying damages, the comparison method of a diagnostic model with the diagnostic model of a particular defect is used in complex technical facilities. A detailed description of the author’s FAM-C and FDM-A methods in the measurement path (power unit generator) in the aircraft engine was described in other papers by Prof. This paper is arranged as follows: Section 2 describes the FAM-C and FDM-A methods used in aircraft powerplant diagnostics based on the fundamental laws of physics. Concluding remarks are given at the end of Section 5
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