Aerospace Instrument-Making Annotation << Back The unmanned flying vehicle route planning of multi-elevational flight using neural networks Leibov R.L. This paper presents an aircraft turbofan engine closed-loop control system single actuator failure impact mitigation. It is assumed that control variable concrete permanent value is known after actuator failure detection, isolation and concrete definition. Must be specified new required values of other control variables and corresponding new required values of selected observable variables close to its de-sirable values. The results of proposed actuator failure impact mitigation method application for aircraft turbofan engine maximal (takeoff) regime are presented. It is shown that nozzle throat area concrete actuator failure impact on turbofan engine thrust decrease might be accommodated by main combustion chamber fuel flow slight increase. Key words: linear model, aircraft turbofan engine, thrust, nozzle throat area, main combustion chamber fuel flow, control system, single actuator failure impact mitigation. Contacts: E-mail: r-leibov@mtu-net.ru Pp. 39-58.