Improved Thrust Performance Optimization Method for UAVs Based on the Adaptive Margin Control Approach

This study proposes a strategy for improving the thrust performance of fixed-wing UAV turbine engines from perspective aircraft/engine integration. In engine control process, inlet distortion caused by angle attack change is taken into account, index calculated in real time predicting attack, and influence on model analyzed mechanically. Then, pressure ratio command adjusted according to new compressor surge margin requirement finally improve performance. To verify effectiveness algorithm, an adaptive disturbance rejection controller designed flight complete simulation horizontal acceleration. The results show that, with this strategy, turbofan can more than 8% under safety conditions.