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Gene Addy Aviation Safety Program Co-Associate Principal Investigator
Current Research
Integrated Resilient Aircraft Controls Project
NASA Iced Aerodynamics and Controls
National Aeronautics and Space Administration NASA/CP—2009-215797 35 www.nasa.gov f th fli ht i f i f
Aviation Safety Program
ili l t control resilience for ensuring safe flight in the presence of adverse conditions. control design tools and techniques for enabling safe flight in the presence of adverse conditions. p ...to advance the state of aircraft flight control to provide onboard ...to arrive at a set of validated multidisciplinary integrated aircraft IRAC Scope: IRAC Goal: IRAC Goal:
Integrated Resilient Aircraft Controls (IRAC) Project
• • • Current airframe icing research at NASA is funded through: National Aeronautics and Space Administration NASA/CP—2009-215797 36 www.nasa.gov NextGen N i nces Disturban d Failures Aileron Damaged (F 18) rol cont Stuck Rudder s of Loss k d fl ), (F 15) l (p l ti i – aerodynamic and structural damage (wing and/or tail) – Static and dynamic actuator failure effects (single and multiple) – Unusual attitudes, stall/departure ex : locked stabilator (F-15) stabilator driven to local angle-of-attack ex.: locked stabilator (F 15), stabilator driven to local angle of attack, reduced control surface effectiveness due to icing ex.: destabilizing angle of attack feedback to the canards, wing d damage simulation (F-15), locked flaps (F-18), aerodynamic uncertainty caused by icing, engine degradation due to icing ex.: elevated AOA (pre-stall), stall – – – Failures Damage Upset
IRAC Project Plan
• • • Adverse conditions categorized as: Adverse conditions categorized as: National Aeronautics and Space Administration NASA/CP—2009-215797 37 www.nasa.gov y Dynamics Dr. T. Krishnamurthy Airframe and Structural k NRA’s Partnerships Steve Jacklin Steve Jacklin John Bosworth K i h Dr. David Cox and j Sally Viken and John Orme V&V Methods and Testbeds K l y D Dr. OA Guo t and Dynamics ti Integrated Resilient Aircraft Control Integrated Propulsion Control g l I Project Scientist: Dr. Nhan Nguyen i rincipal Investigator: Dr. Kalmanje Krishnakumar P i P Sally Viken John Orme Guidance Configurations Configurations
Aviation Safety Program
John Kaneshige Systems Analysis for Robust Project Manager: Sally Viken, Associate Project Manager: John Orme Technical Integration Manager Intelligent Flight Planning and
Integrated Resilient Aircraft Control
Control Gene Addy Gautam Shah and Integrated Dynamics and Flight Management Sub-Projects National Aeronautics and Space Administration NASA/CP—2009-215797 38 www.nasa.gov f i i l di i f g
IDFC- Modeling Overview
pp t f il Develop experimental and computational methods to model and predict aircraft responses during IRAC adverse conditions: damage, upset, failures, including icing. Develop models suitable for simulation, analysis, and flight control design Conventional modeling techniques provide limited to poor aircraft response prediction under IRAC adverse conditions where aerodynamics are characterized by separated aerodynamics are characterized by separated flows, vortical flows, shock waves, or nonlinear- unsteady behaviors. Develop advanced modeling and test techniques to characterize aircraft responses and validate via wind tunnel, simulation, and flight testing. Ensure scientific validation of models and control laws Characterize uncertainties, reduce risks, increase efficacy of designs - - - - - - Objective Objective Technical Challenge Technical Approach Significance National Aeronautics and Space Administration • • • • • NASA/CP—2009-215797 39 www.nasa.gov Ice Accretion Process Modeling Effects of ice contamination on aircraft aerodynamics CFD modeling of ice-contaminated aircraft aerodynamics Physics of ice accretion on complex geometries Computational modeling of ice accretions Ice-Contaminated Aerodynamics Modeling Advanced Ice Accretion Process Modeling Advanced – – Aircraft Icing Modeling Icing research in support of IRAC Project: • National Aeronautics and Space Administration NASA/CP—2009-215797 40 www.nasa.gov Model modeling that includes icing includes icing Iced Airframe Aerodynamic Control system CFD
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Ice Accretion Database
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Development of Iced Airframe Aerodynamic
National Aeronautics and Space Administration NASA/CP—2009-215797 41 www.nasa.gov Tail Damage g GTM Wind Tunnel Testing, NASA Langley 14x22 g Wing Damage Small scale models of a large commercial transport – both wind tunnel (3.5%) and flight (5.5%) available Generic Transport Model (GTM)
IRAC Testbed
• National Aeronautics and Space Administration NASA/CP—2009-215797 42 www.nasa.gov y
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p Use LEWICE ice accretion codes to predict ice shapes for full scale GTM Use ice shapes obtained from LEWICE in conjunction with CFD code USM3D to determine aerodynamic effects of ice on GTM Scale, using geometric scaling and engineering judgment from previous icing scaling research the ice shapes from LEWICE to obtain icing scaling research, the ice shapes from LEWICE to obtain aerodynamically similar ice shapes Manufacture these ice shapes, attach them to GTM wind tunnel model, and perform wind tunnel tests to study the effects of ice contamination on model aerodynamics Perform CFD study of ice contaminated, subscale GTM simulation for Intelligent Flight Planning and Guidance 1. 2. 3. 4. 5. 6. Provide data from wind tunnel study to researchers running GTM Investigate the effects of icing on GTM aerodynamics Investigate the effects of icing on GTM aerodynamics
Iced GTM aerodynamics studies
Objective • • Approach
National Aeronautics and Space Administration NASA/CP—2009-215797 43 www.nasa.gov Scale model S 3 with ice Scale model S-3 with ice shapes attached on wind tunnel force balance Artificial ice shapes attached Artificial ice shapes attached to scale model S-3 wing p p GTM method is based upon prior research with S-3.
LEWICE used to predict ice shapes National Aeronautics and Space Administration NASA/CP—2009-215797 44 www.nasa.gov Ultimately, full-scale testing is needed to provide validation
IRAC Icing Research Outcomes & Impact
• More thorough understanding and models, theoretical and empirical, of icing physics and ice accretion processes for complex (3D) airframe shapes Advanced 3D ice accretion prediction codes Advanced 3D ice accretion prediction codes CFD methods for iced aerodynamics Better understanding of aircraft iced aerodynamics and its effects on control surface effectiveness government agencies for both design and development as well as aircraft icing certification icing certification development, and certification • • • • 1. 3D ice accretion codes more widely accepted and used by industry and 2. Iced aerodynamics methods are employed by industry for design, 3. Perform validation exercises in order to achieve success Outcomes Marks of progress – impact on aircraft icing technology National Aeronautics and Space Administration NASA/CP—2009-215797 45 www.nasa.gov (NRA) t icing physics droplet dynamics icing physics, droplet dynamics – h A (Spain)
Airframe Icing Research Collaborations
American Kestrel – LEWICE2D dissemination and support Boeing – LEWICE3D development Goodrich – icing physics INTA (Spain) INTA ONERA (France) – iced aerodynamics NRC-Canada – thermal scaling for IPS operation and runback icing University of Tennessee Space Institute (UTSI) – aircraft health monitoring for icing Space Act Agreements International Agreements NASA R NASA Research Announcements (NRA) • • • National Aeronautics and Space Administration NASA/CP—2009-215797 46