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Advanced shock position control for mode transition in a turbine based combined cycle engine inlet model
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Stueber, Thomas J. Csank, Jeffrey T. |
| Copyright Year | 2013 |
| Description | A dual flow-path inlet system is being tested to evaluate methodologies for a Turbine Based Combined Cycle (TBCC) propulsion system to perform a controlled inlet mode transition. Prior to experimental testing, simulation models are used to test, debug, and validate potential control algorithms. One simulation package being used for testing is the High Mach Transient Engine Cycle Code simulation, known as HiTECC. This paper discusses the closed loop control system, which utilizes a shock location sensor to improve inlet performance and operability. Even though the shock location feedback has a coarse resolution, the feedback allows for a reduction in steady state error and, in some cases, better performance than with previous proposed pressure ratio based methods. This paper demonstrates the design and benefit with the implementation of a proportional-integral controller, an H-Infinity based controller, and a disturbance observer based controller. |
| File Size | 699515 |
| Page Count | 18 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_20130014335 |
| Archival Resource Key | ark:/13960/t79s6rm1c |
| Language | English |
| Publisher Date | 2013-05-01 |
| Access Restriction | Open |
| Subject Keyword | Aircraft Propulsion And Power Controllers Simulation Engine Inlets Propulsion Inlet Flow Computerized Simulation Feedback Control Turbine Engines Mach Number Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
