A High-altitude High-speed Long-endurance Unmanned Reconnaissance Aircraft Engine Parameters To Monitor Research

Aeronautical engine parameter monitor and electrical control system is to enable stable and reliable operation of engine in any environment and any work state, and to exert its maximal performance efficiency. As the aircraft and engine develops, higher requirements are imposed on engine control, more parameters are to be measured and adjusted, and number of control loops keeps increasing. Extensive variables must be controlled concertedly as they are correlated and mutual-influencing. Therefore, requirement on aircraft/engine integrated control increases.X high-altitude long-endurance (HALE) unmanned reconnaissance aerial vehicle flies autonomously with flight control system. The flight control system takes the role of conventional pilots. Engine throttle operation, state monitoring and fault handling are monitored and handled by flight control system. The flight control system needs to know the work state and health state of engine, and to make appropriate adjustment and control as required by the mission. Flight control system shall be interconnected to the engine control system. Thus, the control system of the WP** engine installed on the UAV is changed from original hydro-mechanical control to new-developed digital electronic control (with improved hydro-mechanical control kept as backup), which enables the engine control, state monitoring, failure handling, real-time communication and parameter recording on command by FCS.The task of this thesis is to develop and define engine parameter monitoring concept for the UAV engine electrical control system as a basis for the development of the engine electrical control system components (including engine electronic controller, auto throttle system and corresponding airborne components), definition of control plan, preparation of control software, monitoring of parameters and detection of failures.This thesis, along with trial production of related products, and verification through test and flight test, will provide experience and guidance for the development of related systems on subsequent aircraft models.