combined cycle engine (cce) large scale inlet for mode ......cce-limx model features pre-compression...

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

National Aeronautics and Space Administration

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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

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Phase 1: Inlet Characterization and

Performance Testing

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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?