DOI 10.17586/0021-3454-2024-67-10-867-877
UDC 62-799; 621.3.084.2; 621.3.087.45
DEVELOPMENT OF A DIAGNOSTIC SYSTEM FOR A HYBRID POWER PLANT OF A LIGHT AIRCRAFT
Moscow Aviation Institute, Department o Technologies for the Production of Instruments and Information Systems for Aircraft Control;
A. A. Zhukov
JSC "Russian Space Systems"; Moscow Aviation Institute, Department o Technologies for the Production of Instruments and Information Systems for Aircraft Control; Professor
Reference for citation: Borisov D. A., Zhukov A. A. Development of a diagnostic system for a hybrid power plant of a light aircraft. Journal of Instrument Engineering. 2024. Vol. 67, N 10. P. 867–877 (in Russian). DOI: 10.17586/0021-3454-2024-67-10-867-877.
Abstract. An approach to constructing a diagnostic system for a light aircraft hybrid power plant (HPP) is proposed. A HPP assembled according to a parallel scheme using an internal combustion engine (ICE) and an electric power plant (EPP) is considered as the object being diagnosed. The necessary monitored operating parameters reflecting the technical condition of the HPP are determined. The significance of the selected monitored parameters of the ICE and EPP is shown. The influence of the speed, air and fuel pressure, air, fuel, exhaust gas and cylinder head temperature on the ICE condition, as well as the EPP parameters — voltage, current, battery temperature and electric motor temperature — is considered. Based on the specified parameters, the sensors are selected taking into account their operating conditions and design solutions for the HPP prototype. A structural diagram of the hardware is developed based on a microcontroller and external analog-to-digital converters used to digitize the temperature sensors. The possibility of recording parameters in a “black box” and transmitting information to the on-board data bus during operation of the light aircraft is presented.
Abstract. An approach to constructing a diagnostic system for a light aircraft hybrid power plant (HPP) is proposed. A HPP assembled according to a parallel scheme using an internal combustion engine (ICE) and an electric power plant (EPP) is considered as the object being diagnosed. The necessary monitored operating parameters reflecting the technical condition of the HPP are determined. The significance of the selected monitored parameters of the ICE and EPP is shown. The influence of the speed, air and fuel pressure, air, fuel, exhaust gas and cylinder head temperature on the ICE condition, as well as the EPP parameters — voltage, current, battery temperature and electric motor temperature — is considered. Based on the specified parameters, the sensors are selected taking into account their operating conditions and design solutions for the HPP prototype. A structural diagram of the hardware is developed based on a microcontroller and external analog-to-digital converters used to digitize the temperature sensors. The possibility of recording parameters in a “black box” and transmitting information to the on-board data bus during operation of the light aircraft is presented.
Keywords: diagnostic system, hybrid engine, hardware implementation, hybrid engine parameters, diagnostic complex sensors
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