The CO2 Project (Design with Constraint Solving)
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Transcript of The CO2 Project (Design with Constraint Solving)
The CO2 Project(Design with Constraint Solving)
Laurent ZIMMER
DASSAULT AVIATION
Research and Future Business Division
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• A National Research Project– Labelled by a network for Software Development of
the French Ministry of Research
Context
– Granted by the French Ministry of Economy, Finance and Industry
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• 6 partners
– 2 Industrial
– 2 Informatics Labs
– 2 Engineering Labs
Context
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Purpose
• To develop in parallel– A (mainly) interval constraint-based software
dedicated to engineering design called CE :• Modelling• Solving
– A relating design methodology:• inverted and integrated design• constraint formulation
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Basic Principle
Concept
Calculus Calculus
Sol2
Model
Sol 1 Sol N...Solution
Requirements
Req.
DV
PV
PV
DV+PV
Point to Point design Set-based design (Toyota)
Classical Design Process I.I. Design Process
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Methodology
To test the approach through many case studies:
• Academic case studies– preliminary aircraft vehicle design
• Industrial case studies– mechanical design problem– design of an Air Conditioning System (ACS)
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Software Development
• Every 6 months Release• Initial version of the tool:
– Hull consistency with decomposition (HC3)– Interval arithmetic directly implemented with the
floating point arithmetic instructions of the C++ compiler (outer rounding)
– infinite numbers are not processed
First Case-Study
Global Unmanned Aircraft Preliminary Design
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Problem Description
• Requirements resulting from mission profile:– Range, cruise speed, cruise altitude, volume of
payload ..
• Constraint Model:– 51 variables,35 equations and 26 inequalities,– 5 Geometrical Design Variables :
• Body diameter, Wing span, Wing root chord• Wing thickness/chord ratio, Wing aspect ratio
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PossibleDesigns
TL
Swl
arrow
delta
trapezoidalTiCRaT = T / L
wing thickness/chord ratio
Swl
wing leading sweep angle
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Some tests
• T1: Dimensioning (VC -> VP)– to fix the geometrical variables– Range = f(MachNo)
• T2: Reverse Computing– MachNo = f(Range)
• T3:Parametric Study– Range=f(Swl)
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T1
AspRat Bdepth Croot Span TiCRat MachNo Range
[0 , ns] [0 , ns] [0 , ns] [0 , ns] [0 , ns] [0 , ns] [0 ,ns]
2 0.5 4 [3.99 ,6.03] [0.166 , 79330.79] [0 , 2.1673990604568] [0, ns]
2 0.5 4 4 [0.482 , 55055.147] [0 , 0.8469449298259] [0 , ns]
2 0.5 4 4 0.483 [0 , 0.8467896833306] [0 , ns]
2 0.5 4 4 0.483 0.7 3496.159
H = 5000
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T2
H = 5000, Range = 3496
AspRat Bdepth Croot Span TiCRat MachNo Range
2 0.5 4 4 0.483 [0 , ns] 3496
2 0.5 4 4 0.483 [0.346 , 0.847] 3496
AspRat Bdepth Croot Span TiCRat MachNo Range
2 0.5 4 4 0.483 0.69987131 3496
AspRat Bdepth Croot Span TiCRat MachNo Range
2 0.5 4 4 0.483 0.82245094 3496
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T3
H Bdepth Croot Swl TiCRat MachNo Range
[0 , ns] [0 , ns] [0 , ns] [0 , ns] [0 , ns] [0 , ns] [0 ,ns]
10000 0.5 4 42 0.1 0.7 3879.405
10000 0.5 4 43 0.1 0.7 3873.318
10000 0.5…
4…
44…
0.1…
0.7…
3866.85…
1000 0.5 4 52 0.1 0.7 3796.78
10000 0.5 4 53 0.1 0.7 XXXXXX
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Results
• T1 is OK
• T2 is OK but not very efficient
• T3 is OK however parametric study is to automate
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reverse calculus vs direct parametric study
Range against MachNo
34903492349434963498350035023504350635083510351235143516351835203522352435263528353035323534
0.69 0.71 0.73 0.75 0.77 0.79 0.81 0.83
MachNo
Ran
ge
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Revised version
• A correct Interval Arithmetic Library implemented on a robust floating point library(Gaol F. Goualard 2000)
• A new propagation architecture implementing up-to-date consistency algorithms(L. Granvilliers & M. Christie)
• Some specialised solving strategies– parametric studies– optimisation (min, iterative approximating S. Preswitch 99)
Second Case-Study
Pressure Device Design
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PurposePurpose
Stiffened Plate
Stiffener Plate
Pressure2,5 Bar
Design of a Pressure device
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Design problem of a stiffened plateDesign problem of a stiffened plate
Design challenge • Increasing the mechanical resistance without decreasing the cost of
the resulting product
Design variables • Thickness of the plate
• Type of stiffeners,
• Type of material,
• number of longitudinal and lateral stiffeners
ny
nx
type de raidisseur
h
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Constraint Formulation
Not only analytical functions !
Like:• Cost models• Use of components of the shelf• A global physical model of the behaviour of
the plate
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Cost models(*******************************************************************)(* Définition du process de fabrication *)(*******************************************************************)
(* Temps de Découpe de la tôle *)h<=8E-3 -> T1=1/2;h>8E-3 -> T1=(1/2)*(L1+L2);T1>0;
(* Cassure des raidisseurs *)hauteur<=1E-2 -> T2=ny*(nx+1)/20;hauteur>1E-2 -> T2=ny*(nx+1)/10;T2>0;
Need of a trigger mechanismto express
Experience or Business rules
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Components of the shelf
IPE80 à IPE600 Carrés22 à carrés200
Catalogue of stiffeners
Catalogue of materials
Steel, Iron, Iron cast, Titanium ..
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Catalogues
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Global Physical Model
Finite Elements Model
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Global Physical Model
LearningCasebase
Approximation by a set of analytical functions
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Feedback
• The case study has been processed• The processing of non analytical knowledge is
not easy :– Finite Elements models– Interpolation tables– existing programs– ..
It is a real bottleneck for ICP
And Nowwe are working on
an industrial case study
An Aircraft Air Conditioning System Design
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Half closed motorised Air conditioning cycle
soute avion iquepressurisée
T M oteur C
a irdynam ique
giffard
vanne by-pass
pré-refro id isseuréchangeur princ ipa l
dess icant
Turbo-réacteur
vanne d 'arrê t
vanne d 'arrê t g iffard
vanne de régulation
pressurisationcarburant
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Close/Half-Close Cycle Design
Pre-coolingHeat Exchanger
Turbo
reactor
Atmosphere Cabin
Atmosphere
Main Heat Exchanger
Turbine
Compressor
motor
switch on
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Schéma d’architecture global du SCASchéma d’architecture global du SCA
T7 entre –40 °C et 71 °CSection d’ entrée
Ai
Ouvert
Fermé
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Variability in the Design Problem
Possible free parameters:• Motor Power• Ram Air section• Heat exchangers characteristics
Design is hard
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Cross-Flow Heat Exchangers
Lx
MAIN AIR
RAM AIR
Lz
Ly
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Dimensioning Heat Exchangers
Lx, Ly, Lz
Type of Exchange Surfacesdifferent typesdifferent properties (5)
Type of ExchangersCross-Flow, Multi-pass ...
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equations
u s ec t i o n
1 - 3
1
113r3r
4r
PT
T an
P
raq̂maq
λ 1,1.0λ
u s e u r 4 , 5
1²
2
11 MT a1rT 1
12
1²
MPη ad1 rP
6
11
11
11
1
21
11
ˆ
ˆˆ²ˆ1ˆ
ˆˆ
ˆˆ1
ˆ
ˆ2²ˆ1ˆ
2
ˆ²ˆ
m
em
c
c KA
AfK
G
11
21
PP
PP
7
r
merr
r
m
cr
rr
r
rrcr
r KA
AfK
G
21
21
11
2
31
21
ˆ
ˆˆ²ˆ1ˆ
ˆˆ
ˆˆ1
ˆ
ˆ2²ˆ1ˆ
2
ˆ²ˆ
2 r2 r
3 r2 r
PP
PPr é -r e f r o i d i s s e u r
8 , 91
21
1
12 r ε
TT
ε
εT
11
2 r1 r2 T
λ
T
λ
TT
1 0
32
32
22
3
42
32
ˆ
ˆˆ²ˆ1ˆ
ˆˆ
ˆˆ1
ˆ
ˆ2²ˆ1ˆ
2
ˆ²ˆ
m
em
c
c KA
AfK
G
33
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PP
PP
1 1
r
merr
r
m
cr
rr
r
rrcr
r KA
AfK
G
12
12
22
1
22
12
ˆ
ˆˆ²ˆ1ˆ
ˆˆ
ˆˆ1
ˆ
ˆ2²ˆ1ˆ
2
ˆ²ˆ
1 r1 r
2 r1 r
PP
PP
n g e u rc i p a l
1 2 , 1 32
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2
21r ε
TT
ε
εT
1
30
2 r
0
1 r4 T
-1λ
T
τ-1λ
TT
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State Space ConfigurationState Space Configuration
Critères Point 1COP 2,71
Mma (kg) non définiMra (kg) 101,00
M soute (kg) 67,40
Critères Point 2COP 0,60
Mma (kg) non définiMra (kg) 29,43
M soute (kg) 57,10
Critères Point 3COP 0,85
Mma (kg) 781,55Mra (kg) 135,39
Msoute (kg) 96,86
Critères Point 4COP 0,77
Mma (kg) 276,12Mra (kg) 186,45
M soute (kg) 42,33
Altitude
Temps
3000 m
16500 m
7500 m
6000 m
M=0.6
M=0.3
M=0.6
M=0.65
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Partial results
• We are able to dimension the ACS in a given configuration
• if we enlarge the search space:– type of exchange surfaces– type of exchangers– number of configurations
then we address a problem currently out of scope
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Conclusion
A lot of research effort remain to do if we want to fully address the field of Design
Interesting themes :– Hard mixed integer and real non linear problems– Large search spaces of numerical underconstraint
problems– Decision Support
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Decision Support Model of soft flexible interval constraints
• Easy and relevant engineer ’s preferences expression
• Automatic generation of Pareto Frontier
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