Abstract: Methods and systems for operating an aircraft engine having a compressor are described. The method comprises determining, based on actual operating parameters of the aircraft engine, a compressor mass flow limit for an aerodynamic stability of the aircraft engine; determining an actual compressor mass flow of the compressor of the aircraft engine, wherein the actual compressor mass flow is based on measured values of the aircraft engine; comparing the actual compressor mass flow to the compressor mass flow limit; and governing operation of the aircraft engine to cause an alternative compressor mass flow when the actual compressor mass flow reaches or is anticipated to reach the compressor mass flow limit.

Abstract: A system for sensor thermal management and stabilization comprises a sensor block, one or more sensors mounted on the sensor block, one or more heaters mounted on the sensor block, a chassis coupled to the sensor block, a thermal conductor moveably coupled between the sensor block and the chassis, and a thermal control actuation mechanism operatively connected to the thermal conductor. The thermal control actuation mechanism is operative to cause the thermal conductor to vary a total thermal conductance from the sensor block to the chassis by moving the thermal conductor toward the chassis or away from the chassis. The total thermal conductance is varied to provide an optimized thermal stability and optimized environmental range of applicability for the one or more sensors.