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Virtual-Aircraft Design & Control of TransCRuiser – S&C study with CEASIOM Arthur Rizzi 1 , P. Eliasson 2 , T. Grabowski 3 , J. Vos 4 1 Royal Institute of Technology (KTH), Stockholm, 100 44, Sweden 2 Swedish Defence Research Institute (FOI), Stockholm, 164 90, Sweden - PowerPoint PPT Presentation
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Flygteknik-2010 – Norra LatinStockholm, 18-19 Oct 2010 1
Virtual-Aircraft Design & Control of TransCRuiser – S&C study with CEASIOM
Arthur Rizzi1, P. Eliasson2, T. Grabowski3, J. Vos4
1Royal Institute of Technology (KTH), Stockholm, 100 44, Sweden2Swedish Defence Research Institute (FOI), Stockholm, 164 90, Sweden
3Warsaw University of Technology (WUT), 00-665 Warsaw, Poland4CFS Engineering (CFSE), 1015 Lausanne Switzerland
Flygteknik-2010 – Norra LatinStockholm, 18-19 Oct 2010 2
Contents CEASIOM Design Tool – outcome of SimSAC
Analyze/improve flight dynamics Specification & Design to Canard Configuration Creation Tabular Aero Data
Comparison with WT data Prediction Flying Qualities - Low & transonic speeds
Static stability – static margin: tradeoffs Dynamic stability – linear & nonlinear (flight simulator)
Augmented Stability Demo Flight simulation
Flygteknik-2010 – Norra LatinStockholm, 18-19 Oct 2010 3
SimSAC EU-Project Partnership NO PARTNER COUNTRY
1 KTH SE
2 Alenia Aeronautica IT
3 Bristol University UK
4 CERFACS FR
5 CFS Engineering CH
6 Dassault Aviation FR
7 DLR DE
8 EADS-M DE
9 FOI SE
10 Liverpool University UK
11 J2 Aircraft Solutions UK
12 ONERA FR
13 Politecnico Milano IT
14 Saab Aerosystems SE
15 TsAGI RU
16 VZLU CZ
17 Warsaw University of Technology
PLEU FP 6 STREP projectProject coordinator: Prof. A. Rizzi, KTH
SimSAC: Simulating Aircraft Stability and Control Characteristics for Use in Conceptual Design
Flygteknik-2010 – Norra LatinStockholm, 18-19 Oct 2010 4
SimSAC Goal: Design Flight Control System Earlier
Design Conceptual
Phase Preliminary
Use of … Handbook methods
Linear Aerodyn
ROM CFD & Optimize
WT testing Flight testing
standard Very high high low very low Aero data
SimSAC Very low high high medium
• Compute Aerodyn Dataset• variable-fidelity CFD• predict flight dynamics
• Use in conceptual design
Aerodynamic Tools for S&C
Flygteknik-2010 – Norra LatinStockholm, 18-19 Oct 2010 5
CEASIOM Design Tool
Flight Dynamics
Flygteknik-2010 – Norra LatinStockholm, 18-19 Oct 2010 6
TCR Design: SAAB Specification
Flygteknik-2010 – Norra LatinStockholm, 18-19 Oct 2010 7
Configuration Re-Design
Original TCR: poor trim ability large , Different configurations investigated
Wing further fore (design parameter) Three lifting surfaces All-moving canard (vary location & size)
Design of wind tunnel model One moving surface for longitudinal control No engines
Flygteknik-2010 – Norra LatinStockholm, 18-19 Oct 2010 8
Design Choice – Static stability margin
0),(
),(2
1 2
Cm
CL
C
WSCVL
Trim condition
CGac
M
Static margin
LStatic stable
Ma = 0.12 0.65 0.85 0.97
AC = 38.9m 39.9 40.6 42.1
Kn = 4.7% 13.6% 19.5% 32.2%
CG = 38.3m
Kn grows with Ma
Response heavy at high speed
Dilemma !
Flygteknik-2010 – Norra LatinStockholm, 18-19 Oct 2010 9
Predict Flying Qualities: solve Flight Dyn Eqs
s – state vector (8)
A – inertia matrix F – general forces
gravitypropaero FFFVωV mmTranslation:
aeroMIωωωI Rotation:
LΘKinematics:
),(1 tdt
dsFA
s
Jss
dt
d
j
ji
s,
1 )( FAJ
Linearize ( stability derivatives...)
Flygteknik-2010 – Norra LatinStockholm, 18-19 Oct 2010 10 10
Faero Interpolation Process - KrigingAero-data
M b p q r dot bdot deltaCTornado - x x x x x x x xWT *) - x - x * * * * xEdge x x x - - - - - xNSMB x x x - - - - - xLivMB x x x - - - - - x*) No CD
Database constructed•DACE Kriging toolbox:•Linear base model,•Input & output scaled (0,1)•Manual choice corr. length
Data from source
Mac
h
α
Flygteknik-2010 – Norra LatinStockholm, 18-19 Oct 2010 11 11
Total Length 63.87 mTotal Wingspan (bref) 44.66 mTotal Canard Span 12.00 mTotal Height 11.70 mFuselage Diameter 3.70 m MAC 16.06/11.77 m, Wing reference area Sref = 489 m2, Reference point, moment x = 35.00 m, z = 0 mCenter of gravity x = 38.33 m, z = 0 m
SAAB Howe Raymer Cessna USAF Torenbeek CeasiomTotal Structure 65 63 57 46 55 63 53Total Propulsion system14 14 17 31 17 8 28Total system 18 14 49 57 7 17 15Empty weight 97 91 122 133 79 88 96MTOW 210 203 234 245 191 199 208
Inertias Saab T CEAS.0 CEAS.1Ixx 5,17 10,35 15,17Iyy 4,67 21,62 17,52Izz 6,58 29,92 32,1Ixz 1,73 0 0,09
W&B/ACBuilder: J.Munoz, S Ricci, ...
Weight, Inertia & Balance
Flygteknik-2010 – Norra LatinStockholm, 18-19 Oct 2010 12 12
Control authority: Canard stall
WT data
Comparison
Cm() for zero canard deflection
Aero Data & Handling Qualities – Longitudinal Dynamics
Flygteknik-2010 – Norra LatinStockholm, 18-19 Oct 2010 13 13
120-180 m/s, 1km – 3kmM 0.35 – 0.50
M.35 M.50
Canard
Phugoid
Shortperiod
Trim & Flying Qualities – low speed
Trim Sensitivity small
Flygteknik-2010 – Norra LatinStockholm, 18-19 Oct 2010 14
M.65
Canard
M=1
Trim & Flying Qualities – transonic speed
Phugoid
Shortperiod
Transonic dip
Flygteknik-2010 – Norra LatinStockholm, 18-19 Oct 2010 15
220ms 250 270 286
Flow Physics transonic dip
Flygteknik-2010 – Norra LatinStockholm, 18-19 Oct 2010 16 16
Eigenvalues276 m/s 10km, = 0.5All modes stable (barely ...)
Flight simulation = -0.3o: Slooowly damped = -3.0o: See-saw pitchup ... Cobra manuver
AoA
attitude
Linear & NonLinear Stability – Stick fixed
Time HistoriesWind gust - disturb α small large
),(1 tdt
dsFA
s
Flygteknik-2010 – Norra LatinStockholm, 18-19 Oct 2010 17
Augmented Stability
SAS OFF
SAS ON
Flygteknik-2010 – Norra LatinStockholm, 18-19 Oct 2010 18
ON
OFF ONOFF
OFF
ON
Phugoid Short Period
Dutch Roll
Flying Qualities with Augmentation – low speed
Flygteknik-2010 – Norra LatinStockholm, 18-19 Oct 2010 19
Conclusions CEASIOM proven useful !
– Trim & static margin chosen correctly– Good canard sizing & placement
• Verified by WT no major pitfalls
– Stability Augmentation good flying qualities• Low-speed stick-fixed qualities improved• Transonic disturbance damped• Canard authority sufficient
– Allows concept designer to work with control tools to sort out:• What can be fixed by control system• What changes in configuration is needed
CEASIOM lives on !– Community of users Open software– Visit www.ceasiom.com– Join us !
Flygteknik-2010 – Norra LatinStockholm, 18-19 Oct 2010 20
Thanks
For Your Attention !
Flygteknik-2010 – Norra LatinStockholm, 18-19 Oct 2010 21
CEASIOM Predicts T-tail Flutter
Stick Model: beam elements & lump masses
Fin bending mode 1 1.6 Hz Hor. Tail roll mode 3 4.3 Hz
Flutter frequency [Hz]
Mach SMARTCAD NASTRAN®
0.50 3.46 3.61
0.70 3.43 3.56
0.85 3.38 3.49
0.97 3.25 3.39
V-g diagrams, sea-level
Clamped node
Flygteknik-2010 – Norra LatinStockholm, 18-19 Oct 2010 22
Aircraft Motion: Non-Linear Dynamical System
s – state vector (8)
A – inertia matrix F – general forces
gravitypropaero FFFVωV mmTranslation:
aeroMIωωωI Rotation:
LΘKinematics:
),(1 tdt
dsFA
s
888 sJ
s
dt
d
j
ji
s,
18
8
)( FAJ
linearize
Flygteknik-2010 – Norra LatinStockholm, 18-19 Oct 2010 23
WT Model
Flygteknik-2010 – Norra LatinStockholm, 18-19 Oct 2010 24 24
M.97
Airspeed, Altitude & Mach number
Flygteknik-2010 – Norra LatinStockholm, 18-19 Oct 2010 25
What if done by Handbook Method
Raymer volume coefficient
Handbook methods not applicable to unconventional
configs. such as the TCR
SMAC
Slc CC
C ~
0.1
lC = 28 m
SC = 60 m2
MAC = 11.77 m
S = 489 m2
cC ≈ 0.29
Flygteknik-2010 – Norra LatinStockholm, 18-19 Oct 2010 26
TCR Design: Specification
MTOW~ 180 t , R~ 10000 km ,No Pax~ 200 Mc = 0.97
‘Loose ideas’ to beWorked out:
Payload
Flygteknik-2010 – Norra LatinStockholm, 18-19 Oct 2010 27
Fused Aerodynamic Dataset
Mac
h
Flygteknik-2010 – Norra LatinStockholm, 18-19 Oct 2010 28
Flygteknik-2010 – Norra LatinStockholm, 18-19 Oct 2010 29
Fused Aerodynamic Dataset
Mac
h
Flygteknik-2010 – Norra LatinStockholm, 18-19 Oct 2010 30
Evolution of pitching moment & lift coefficients with Mach/speed Also breakpoints – no second-opinion – do we believe CFD ??
TCR - CFDsim - Mach dependence
Flygteknik-2010 – Norra LatinStockholm, 18-19 Oct 2010 31
Design Loops
Flygteknik-2010 – Norra LatinStockholm, 18-19 Oct 2010 32
Design Process
Flygteknik-2010 – Norra LatinStockholm, 18-19 Oct 2010 33
Flight Simulation – Transonic Cruise
Flygteknik-2010 – Norra LatinStockholm, 18-19 Oct 2010 34
Baseline Design
Initial sizing with Saab in-house method.
Baseline design: input for CEASIOM.
Flygteknik-2010 – Norra LatinStockholm, 18-19 Oct 2010 35
CEASIOM Design Analysis: XML params
Flygteknik-2010 – Norra LatinStockholm, 18-19 Oct 2010 36
TCR T-tail flutter
Modal frequencies [Hz]Mode SMARTCAD NASTRAN®
1 1.60 1.602 2.63 2.623 4.32 4.344 4.63 4.595 8.16 8.166 8.71 8.697 13.32 13.258 18.87 18.109 18.93 18.76
10 20.07 21.48
Flutter dynamic pressure [Pa]Mach SMARTCAD NASTRAN®0.50 5.66∙104 6.55∙104
0.70 5.54∙104 6.43∙104
0.85 5.43∙104 6.16∙104
0.97 5.38∙104 5.92∙104
Flutter frequency [Hz]Mach SMARTCAD NASTRAN®0.50 3.46 3.610.70 3.43 3.560.85 3.38 3.490.97 3.25 3.39 V-g diagrams, M∞=0.50,
sea-level
Clamped node
Stick Model: beam elements & lump masses
Fin bending mode 1 1.6 Hz
Hor. Tail roll mode 3 4.3 Hz
Flygteknik-2010 – Norra LatinStockholm, 18-19 Oct 2010 37
Trim & longitudinal static stability
Results from SDSA, for h=10 km and V = 240 m/s (M=0.8)
Config. xW xC SC [m2] trim [deg] trim [deg] Static margin
(%MAC)
TCR-C2 0.26 0.13 65 2.7 9.0 4.54
TCR-C17 0.26 0.017 65 2.0 6.2 -2.88
TCR-C8 0.26 0.017 47 1.5 9.2 4.26
TCR-C15 0.26 0.12 72 2.5 8.2 3.13
TCR-C2 TCR-C17
Flygteknik-2010 – Norra LatinStockholm, 18-19 Oct 2010 38
Trim & longitudinal static stability
Results from SDSA, for h=10 km and V = 240 m/s (M=0.8)
Config. xW xC SC [m2] trim [deg] trim [deg] Static margin
(%MAC)
TCR-C2 0.26 0.13 65 2.7 9.0 4.54
TCR-C17 0.26 0.017 65 2.0 6.2 -2.88
TCR-C8 0.26 0.017 47 1.5 9.2 4.26
TCR-C15 0.26 0.12 72 2.5 8.2 3.13
TCR-C17 TCR-C8
Flygteknik-2010 – Norra LatinStockholm, 18-19 Oct 2010 39
Trim & longitudinal static stability
Results from SDSA, for h=10 km and V = 240 m/s (M=0.8)
Config. xW xC SC [m2] trim [deg] trim [deg] Static margin
(%MAC)
TCR-C2 0.26 0.13 65 2.7 9.0 4.54
TCR-C17 0.26 0.017 65 2.0 6.2 -2.88
TCR-C8 0.26 0.017 47 1.5 9.2 4.26
TCR-C15 0.26 0.12 72 2.5 8.2 3.13
C , static margin SC
distance W-C
Flygteknik-2010 – Norra LatinStockholm, 18-19 Oct 2010 40
Construct Windtunnel Model
• Exterior shape - Export IGES
• PoliMi designed interior structure
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