Publication Date:
2019-08-13
Description:
A dual flow-path inlet for a turbine based combined cycle (TBCC) propulsion system is to be tested in order to evaluate methodologies for performing a controlled inlet mode transition. Prior to experimental testing, simulation models are used to test, debug, and validate potential control algorithms which are designed to maintain shock position during inlet disturbances. One simulation package being used for testing is the High Mach Transient Engine Cycle Code simulation, known as HiTECC. This paper discusses the development of a mode transition schedule for the HiTECC simulation that is analogous to the development of inlet performance maps. Inlet performance maps, derived through experimental means, describe the performance and operability of the inlet as the splitter closes, switching power production from the turbine engine to the Dual Mode Scram Jet. With knowledge of the operability and performance tradeoffs, a closed loop system can be designed to optimize the performance of the inlet. This paper demonstrates the design of the closed loop control system and benefit with the implementation of a Proportional-Integral controller, an H-Infinity based controller, and a disturbance observer based controller; all of which avoid inlet unstart during a mode transition with a simulated disturbance that would lead to inlet unstart without closed loop control.
Keywords:
Aircraft Propulsion and Power
Type:
NASA/TM-2013-217824
,
E-18574
,
27th Propulsion Hazards Joint Subcommittee Meeting; Dec 03, 2012 - Dec 17, 2012; Monterey, CA; United States|33rd Exhaust Plume and Signatures Joint Subcommittee Meeting; Dec 03, 2012 - Dec 17, 2012; Monterey, CA; United States|45th Combustion/33rd Airbreathing Propulsion Joint Subcommittee Meeting; Dec 03, 2012 - Dec 07, 2012; Monterey, CA; United States|33rd Airbreathing Propulsion Joint Subcommittee Meeting; Dec 03, 2012 - Dec 07, 2012; Monterey, CA; United States
Format:
application/pdf
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