combined cycle engine (cce) large scale inlet for mode ......cce-limx model features pre-compression...
TRANSCRIPT
National Aeronautics and Space Administration
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Thomas J. Stueber
NASA Glenn Research Center
Cleveland, Ohio
4th Propulsion Control and Diagnostics (PCD) Workshop
Cleveland OH, December 12, 2013
Combined Cycle Engine (CCE) Large Scale Inlet for Mode Transition Experiments (LIMX) Mode Transition Modeling and Control
Fundamental Aeronautics – Hypersonic Project
National Aeronautics and Space Administration
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Combined Cycle Engine (CCE)
Large-Scale Inlet for Mode Transition Experiments (LIMX).
CCE-LIMX
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Team
• NASA GRC Research Directorate:
– Communication, Instrumentation, and Controls Division
• Controls and Dynamics Branch (RHC)
– Jeffrey T. Csank, Thomas J. Stueber, Randy Thomas
• Digital Communications and Navigation (RHD)
– Joseph A. Downey, Jennifer M. Nappier, Binh V. Nguyen
– Aeropropulsion Division
• Inlet & Nozzle Branch (RTE)
– David Davis, Lancert E. Foster, Dave Saunders, John W. Slater
• NASA GRC Engineering Directorate:
– Systems Engineering and Analysis Division
• Propulsion & Control Systems Engineering (DSS)
– Dzu K. Le, Daniel R. Vrnak
• NASA GRC Facilities & Test Directorate:
– Testing Division, Wind Tunnel & Propulsion Test Branch.
• Industry Partners
– TechLand Research Inc. Bobby W. Sanders, Lois J. Weir
– Spiritech Advanced Products Inc., Eric J. Gamble, Dan Haid, Sal D’Alessandro,
Rich DeFrancesco.
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Outline
• Overview of CCE-LIMX Inlet System
• Control Affecters
• Control Design
• Phase-3 Test Plans
• Summary
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CCE-LIMX Model
Low-Speed Flow Path
(turbine engine)
High-Speed Flow Path
(DMSJ engine)
Dual Mode Scramjet
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CCE-LIMX Model Features
Pre-compression forebody plate
Isolator High-Speed Plug
Variable Ramp
High Speed Cowl Low-Speed Cowl / Splitter
Tunnel Floor
Tunnel Ceiling
Pivot for AoA
F l o w
Low-Speed Plug
30 feet
Angle of Attack
Overboard bypass
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Control Affecters
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Subsonic Volume Bleed Region
Phase 1: Inlet Characterization and
Performance Testing
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2 0
Phase 1: Inlet Characterization and
Performance Testing
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Phase 1: Inlet Characterization and
Performance Testing
National Aeronautics and Space Administration
www.nasa.gov
Phase 1: Inlet Characterization and
Performance Testing
National Aeronautics and Space Administration
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Control Design
Process
Shock
Position
Estimator
P2
Free-stream
• Pt0
• M0
• Tt0
Σ Set
Point Controller
e
P2
Pd
-
+
u
Geometry
• AOA
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Phase 1: Inlet Characterization and
Performance Testing
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Phase 2 Accomplishments
• Test matrix status Phase 2 Mach 4
– 642 experiments identified, ~89 hrs
• Main (LST1 and HST1) schedule—506 experiments, ~49 hrs
• First alternate (LST1 and HST2) schedule—68 experiments, ~20 hrs
• Second alternate (LST2 and HST2) schedule—68 experiments, ~20 hrs
– Reduced matrix—393 experiments selected, ~29 hrs
• Main schedule—378 experiments completed, 38.25 hrs
• Alternates—0 experiments completed
– Experiments:
• Step, Sinusoidal-Sweep, Sustained-Sinusoid
• Staircase, Transient Stability Index (Sit),
• Unstart, Buzz, Restart
• Test window: 8/29/2011 – 10/19/2011
• 11 run nights (data collection)
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Phase-3 Plans
• Open-Loop mode transition along schedule
– Transient stability index at operating points on schedule
• Closed-Loop mode transition along schedules
– Perturbation testing at each operating point:
• Step change
• Sinusoidal sweep
• Sinusoid pulse
– Perturbation testing during closed-loop mode transition.
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Summary
• Combined Cycle Engine (CCE) Large Scale Inlet for
Mode Transition Experiments (LIMX)
– Designed,
– Built,
– Installed in NASA GRC 10- x 10-foot SWT
– Completed Phase-1 and Phase-2 testing
– Preparing for Phase-3 testing.
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Questions?