H∞ control of gasturbine engines for helicopters

Engines tests were conducted in order to demonstrate effectiveness and practicability of H^∞ control theory to helicopter engines. An engine control algorithm is designed by H^∞ control theory, which meets robust stability requirements and nominal performance requirements described in frequency domain. Simulation ad engine test results show that H^∞ controllers with feedforward element have better control performance than PI controller with feedforward element, especially, less power turbine speed overshoots are observed in rapid torque decreasing tests.