Document
Semiannual Meeting of the US/French MoA !
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Task V !
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Environmentally Friendly Rotorcraft Concepts !
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2011-2014 !
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Principal Investigators !
P.-M. Basset, C. Schulte W. Johnson, C. Russell, H. Yeo !
ONERA ! NASA, US-Army !
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May 28-29, 2013 !
NASA-AFDD, Moffett Field, CA !
US/France MoA !
Helicopter Aeromechanics !
Management Overview !
Motivation: !
• Greenhouse gas concentrations have increased well
beyond their pre-industrial levels due to human activities !
• Aircraft emissions are
becoming regulated in
industrialized nations, so
future rotorcraft will need
to be designed for
minimal environmental
impact !
Task V Environmentally Friendly Rotorcraft Concepts !
US/France MoA !
Helicopter Aeromechanics !
Management Overview
Objectives: !
• Determine suitable metrics to measure environmental impact of rotorcraft, focusing first on air pollution !
• Integrate performance metrics with rotorcraft design codes !
• Generate rotorcraft designs with minimal environmental impact !
Outcomes : !
• Obtain an understanding of how targeting reduced emissions affects the rotorcraft design process !
• Advance the capability of existing rotorcraft design tools to include environmental performance metrics !
Tools: !
• Evaluation and predesign: NDARC and CREATION !
• Flight simulation: CAMRAD II and HOST !
Task V Environmentally Friendly Rotorcraft Concepts !
US/France MoA !
Helicopter Aeromechanics !
Management Overview !
2- Flight Perf. Metrics Definition !
1- Environmental Metrics Definition !
2.1- Definition of 3 baseline configs . !
1.1- Survey papers on available metrics !
( Heli , Tiltrotor , Compound) !
1.2- Proposals for env. impact metrics !
2.2- Definition of performance metrics !
- Revisit proposals in !
2.3- Initial comparisons of !
Year 1, Year 2, Year 3 !
ONERA/NASA calculations !
3- Metric Computation for Existing Concepts !
3.1- Environmental impact & flight performance analysis !
3.2- Comparison of NASA/ONERA computations on the 3 baseline configs. !
4- Designs With Environmental Constraints !
4.1- Integration of environmental constraints into the evaluation and design tools !
4.2- Use of NDARC/CREATION to generate alternate designs !
4.3- Comparison of environmentally friendly designs w.r.t. the 3 baseline configs. !
4.4- Joint paper !
Task V Environmentally Friendly Rotorcraft Concepts !
US/France MoA !
Helicopter Aeromechanics !
Management Overview !
Y 2011 ! Y 2013 ! Y 2014 ! Y 2012 !
Approved !
1- Environmental Metrics Definition !
SoW !
1.1- Survey papers !
1.2- Proposals of metrics !
! ! !
2- Perf. Metrics !
2.1- Baseline configurations !
2.2- Performance metrics definition !
2.3- Initial comparisons !
3- Metrics Computation !
3.1- Environmental impact & flight performance analysis !
3.2- Compare environmental & perf. calculations !
4- Design Integrating Env. Constraints !
4.1- Integrate environmental constraints in tools !
4.2- Alternate designs !
4.3- Comparisons !
4.4- Joint paper ! !
Task V Environmentally Friendly Rotorcraft Concepts !
US/France MoA !
Helicopter Aeromechanics !
Task V Action Items !
Personnel Exchange !
There is still interest, but budget constraints on the NASA Rotary Wing Program make personnel exchange infeasible through at least Oct. 2014 !
Task V Environmentally Friendly Rotorcraft Concepts !
US/France MoA !
Helicopter Aeromechanics !
Previous Completed Tasks !
1.1 and 1.2 – Env. Metrics !
Metric survey papers !
• Identified historic trends in pollution sources and concentrations !
• Examined the role of rotorcraft in generating air pollution !
• Identified several candidate metrics !
for evaluating rotorcraft designs !
• Metrics can be normalized by either !
time or distance and useful load !
(e.g.: metric per hour/mile per 100kg of useful load) !
• Total air pollution should be !
assessed; not just CO 2 !
• Initial focus on CO and !
NO emissions x !
%!
Aviation Radiative Forcing Components in 2005 !
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Task V Environmentally Friendly Rotorcraft Concepts !
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US/France MoA !
Helicopter Aeromechanics !
Previous Completed Tasks !
2.1 – Baseline Configs !
Defined three baseline configurations !
• 90 passenger capacity !
• 500 nm range !
(+($'# • 75,000 – 100,000 lb design gross weight !
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Helicopter Aeromechanics !
Previous Completed Tasks !
2.2 and 2.3 – Perf. Comparisons !
• Performance Metrics
– Power required, broken down to components – Figure of merit and cruise L/D e
• Performance Comparisons
– Rotor power computed with both momentum theory and free wake – Good agreement for the 90-passenger helicopter – Good agreement between NDARC and CREATION engine !'#+, models !,'#)$ !!(#$" Task V Environmentally Friendly Rotorcraft Concepts !
% &'#() US/France MoA !
Helicopter Aeromechanics !
Ongoing Tasks
Helicopter Sizing in CREATION Case of study: Heavy transport helico 90 pax (inspired from a NASA study which provides a reference) Mission and Specifications: • 90 passagers • Range ≥ 1000 km -1 • Cruse speed ≥ 280 km.h • Cruse altitude= 12 000 ft • Mission profile: Concept H90 - NASA S-64F Mi 10 K Mi 26 Mi-6 CH 53 K CH 53 E 12000 ft Range ~1000 km V ≥ 150 kt = 278 km/h cruse HO-90 2 Wmto (kg) [m] 20000 30000 40000 50000 60000 Altitude Wempty (kg) 5000 10000 15000 20000 25000 30000 Wpayload (kg) 0 926 d_fin d_palier 5000 15000 25000 Distance [km] Task V Environmentally Friendly Rotorcraft Concepts !
US/France MoA !
Helicopter Aeromechanics !
Ongoing Tasks
Helicopter Sizing in CREATION Task V Environmentally Friendly Rotorcraft Concepts !
US/France MoA !
Helicopter Aeromechanics !
Ongoing Tasks
Helicopter Sizing in CREATION Presizing loops in ModelCenter 5 main steps: 1 – Initialization with modeling level 0 2 – Optimization loop with level 1 Goals: • Test on constraints Min( Wfuel ) • Evaluation models & engine presizing Max( Vcruse ) • Loop on weight Min(Noise) Min( Wempty ) 3 – Analysis of results + visualization 4 – More detailed presizing with levels 2 & 3 5 – Iteration between levels 1 & 3 Task V Environmentally Friendly Rotorcraft Concepts !
US/France MoA !
Helicopter Aeromechanics !
Ongoing Tasks
3.1 and 3.2 – Metric Computations
• Determine suitable metrics to measure
environmental impacts
• Determine quantity of pollutants emitted
• Compute metrics for existing designs
• Determine how application of metrics drives
rotorcraft designs
Task V Environmentally Friendly Rotorcraft Concepts !
US/France MoA !
Helicopter Aeromechanics !
Ongoing Tasks
1.2 – Environmental Metrics Definition ´ ` 1196 S Aubry, T Chaboud, M Dupeyrat, A E lie, N Huynh, T Lefebvre, and T Rivie re If the preliminary visual validation is successful, the
• Want to look at both
results provided by the IESTA models are then pro- cessed and analysed. They belong to three domains,
local and global
and include the following metrics.
effects
1. Traffic: aircraft trajectories, aircraft parameters, capacity figures (airport and runways capacity,
• Local effects are in
delays), and fuel consumption.
2. Noise: instantaneous noise, L , L , L and den A A Eq Max terms of air quality, effective perceived noise level (EPNL).
3. Pollutants: emissions and local air quality (LAQ)
which is a measure of
metrics.
NO x Concentration The IESTA acoustic chain allows the production of
pollutant quantities
tables showing the relation between the above-men- tioned noise metrics, their iso-contour surfaces, the
• Global effects are in
number of points of interest (hospitals, schools) and the number of inhabitants within the contours. These
terms of climate
metrics can also be represented on 2D static maps.
Aubry , S., et al. “Evaluating the local environmental impact of air traffic with air transport systems evaluation Fig. 9 Test simulation of the dispersion of a passive One can compare scenarios using a sensitivity analy-
change (warming)
infrastructure: outputs and validation walkthrough,” July tracer in the atmosphere around the sis (the same aircraft flying at a higher speed should 2011.
Toulouse-Blagnac airport with IESTA/Clean create more noise), while the display of colored iso- Airport (background: ß 2009 Google, ß 2009 lines enables an intuitive validation of the models by Tele Atlas) Task V Environmentally Friendly Rotorcraft Concepts !
the domain experts.
The concentrations of pollutants can be displayed achieved by comparing simulations of reference and with graphs showing the evolution over time of emis- candidate scenarios according to given criteria, which US/France MoA !
Helicopter Aeromechanics !
Evaluating Local Emissions
• IESTA – Air Transport System Evaluation
Infrastructure
Aircraft Trajectory Aircraft Local State Emissions Quantities Engine State Atmospheric Dispersion Task V Environmentally Friendly Rotorcraft Concepts !
US/France MoA !
Helicopter Aeromechanics !
Quantifying Emissions
• Emissions index (EI): quantity emitted per quantity of fuel
burned
• CO , water vapor, SO , and soot have constant EI
2 4
• EINO depends on several variables
x – Engine technology (+($'# ,'$&& – Inlet pressure and temperature conditions (altitude) "*$&# – Throttle setting
• Very limited NO data for
x
turboshaft engines
! "#$%& Task V Environmentally Friendly Rotorcraft Concepts !
'$&& US/France MoA !
Helicopter Aeromechanics !
Quantifying NO Emissions
x
• Very little public emissions data for turboshaft engines
• Use NDARC engine output with turbofan NO data and DLR
x
fuel flow corrections to estimate EINO
x &!"
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US/France MoA !
Helicopter Aeromechanics !
Quantifying NO Impacts
x
50000" 45000" 40000" Short Lived Ozone O3S" 35000" Methane CH4" Long Lived Ozone O3L" 30000" Total NO effects Al#tude,)*) Total"NOx" x 25000" 20000" 15000" 10000" Assumed Constant 5000" 0" (100" (50" 0" 50" 100" 150" 200" Radia#ve)Forcing,)(mW/m )/(Tg(N)/year)) Task V Environmentally Friendly Rotorcraft Concepts !
US/France MoA !
Helicopter Aeromechanics !
Candidate Metric
ATR – Average Temp. Response
• Recently developed metric measuring global impact of aviation emissions • Based on radiative forcing caused by various emission species – CO , NO , water vapor, SO , soot, and aviation induced cloudiness 2 x 4 (AIC) • Expresses climate impact as integrated temperature change resulting from operation of a particular aircraft design ∞
A T R = Δ T ( t ) w ( t ) d t
∫
H s u s t , H
H
Dallara, E. S., Kroo, I., and Waitz, I., “Metric for Comparing Lifetime Average Climate Impact of Aircraft,” AIAA Journal , Vol. 49, No. 8, August 2011.
Task V Environmentally Friendly Rotorcraft Concepts !
US/France MoA !
Helicopter Aeromechanics !
ATR Inputs
(" r = 0 • Varying discount rates, r !#'" – Determines emphasis on short-term vs. long-term effects !#&" – Source of uncertainty !#%" r = 0.03 • Operating lifetime of 30 !"#$%&'$()*+,-.( years !#$" r = ∞ !"
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/#0"1(2.( H Task V Environmentally Friendly Rotorcraft Concepts !
US/France MoA !
Helicopter Aeromechanics !
Effects on Tiltrotor Sizing
• Evaluated ATR metric for the 90-passenger
tiltrotor design
• Computations using 2 different baseline engines
for NOx emissions
• Compared results with minimum fuel burn
solution
Task V Environmentally Friendly Rotorcraft Concepts !
US/France MoA !
Helicopter Aeromechanics !
Discount Rate and
Reference Engine
Relative Relative CF34 Reference Engine HTF7000 Reference Engine ATR ATR (Low NO ) (High NO ) x x &"!!# &"!!# %"$!# %"$!# )#*#!# )#*#!# %"!!# )#*#!"!'# %"!!# )#*#!"!'# )#*#+,-# )#*#+,-# !"#$%&"'()!'
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US/France MoA !
Helicopter Aeromechanics !
Design Summaries
Min ATR Min ATR ATR not Physical Characteristics r = ∞ r = 0 Considered HTF7000 NOx CF34 NOx Overall width ft 149.6 154.7 150.1 Rotor radius ft 34.4 35.7 34.5 Wing span ft 110.8 113.4 111.1 Performance Cruise altitude ft 31,000 17,000 28,000 Cruise speed kt 302.1 253.0 289.6 Engine max rated power hp 6,844 7,364 6,893 Empty weight lb 67,569 71,984 67,986 Max takeoff weight lb 119,772 128,875 120,632 Mission fuel burn lb 15,330 18,826 15,659 Takeaway: Targeting low NOx impact favors “low and slow” designs Task V Environmentally Friendly Rotorcraft Concepts !
US/France MoA !
Helicopter Aeromechanics !
Near-Term Schedule !
May ‘ 13 ! Jun ‘ 13 ! Aug ‘ 13 ! Jul ‘ 13 ! Sep ‘ 13 ! Oct ‘ 13 !
MoA meeting at NASA/AFDD !
a) Environmental performance comparisons on a mission profile (90 passenger helicopter) !
b) Evaluate flight performance of the tiltrotor and new compound concept !
Identify differences in !
performance models !
c) Environmental performance comparisons for the tiltrotor and compound !
MoA meeting at ONERA !
Task V Environmentally Friendly Rotorcraft Concepts !