Abstract
In scenarios like aircraft landing, Rapid Thrust Modulation (RTM) is required to achieve high-precision attitude and trajectory manipulations. However, the traditional manipulated variable in aero-engines, specifically the fuel flow, experiences sluggishness in adjusting thrust (Fn) due to combustion delays. In contrast, geometric variable areas, like the nozzle throat area (A8), offer rapid responsiveness but have limited thrust-adjusting capacity. Hence, the proposal of an innovative parallel Valve Position Control (VPC) scheme, combining redundant control inputs, emerges as a groundbreaking solution to enable RTM. In the pursuit of achieving RTM, the non-minimum phase thrust responses are first addressed, which has not been recognized previously to the best of the author's knowledge. This includes the implementation of a new valve position control (VPC) structure, incorporating a dual input Single Output (DISO) system, which is vital for optimizing response time and minimizing the delayed effects in combustion processes. After proper selection of operating conditions, the synthesis process of VPC is outlined by three key requirements, including: 1) realizing the 10 rad/s thrust bandwidth despite the combustion delay; 2) ensuring continuous modulation capability by mid-ranging the A8; 3) decoupling the A8 and thrust during flights. The VPC controller is implemented and compared with the classical Edmond algorithm in a turbofan engine. Results emphasize VPC's robustness in handling combustion delays, meeting specified requirements, and showcasing its potential as an effective RTM solution. Practically, the VPC system's architecture allows for critical rapid thrust changes within a 10 rad/s bandwidth, essential for operations like VSTOL aircraft maneuvers.
Published Version
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