devinci ingenerie proprietary © 2005 devinci ingenierie atos v1.2 click on your mouse to continue
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DEVINCI INGENERIE Proprietary© 2005 DEVINCI INGENIERIE
ATOS V1.2
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DEVINCI INGENERIE Proprietary© 2005 DEVINCI INGENIERIE
WHAT IS AERONAUTICAL STRESS ANALYSIS ?
The Stress & Design Office
European StandardJoint Aviation Airworthiness
Standard JAR 25
Or
American StandardFederal Aviation
RequirementStandard FAR 25
to prove by the calculation that the aircraft can sustains all the loading
conditions that it will meet during its life
THE AIRCRAFT CONSTRUCTOR
THE AIRWORTHINESS AUTHORITIES
Airworthiness Certification Documents
(list of the critical M.S.)
Issue the Airworthiness Certificate
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DEVINCI INGENERIE Proprietary© 2005 DEVINCI INGENIERIE
The positioning of ATOS in the automatic sizing process of an aeronautical structure
Integrated Interface
DESIGN(Geometry)
Modular philosophy ensuring the autonomy of the process stages
GLOBAL FEM RESULTS(Stresses, Forces, Flows …)
Definition of new design
Update
Automatic generationof Stress Report
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DEVINCI INGENERIE Proprietary© 2005 DEVINCI INGENIERIE
MO
DE
L U
PD
AT
E (
man
ual
ly)
Integrated Interface(Automatic Calculations)
Extraction of stresses, forces, flows … from the global model for all the
elementary loading conditions
GEOMETRYSize of the structure parts
Files format : .xls or text(Generated manually)
INPUT
GLOBAL FEM RESULTS for several loading conditions(Stresses, Forces, Flows …)
Files format : .xls or text(Generated automatically by
the tools of the previous step)
GLOBAL FEM (COARSE 2D MODEL)
Elementary Loading
Conditions
INPUT
OU
TP
UT
The stress engineerchoose the calculated criteria
and the assumptions of calculation
Reserve Factors (margins of safety) or Optimized Geometry for each loading condition and combinations
Files format : .xls or text
DR
AW
ING
DE
FIN
ITIO
NU
PD
AT
E (m
anu
ally
)
Under the responsability of the aircraft constructor
Using specific constructor’s tools
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DEVINCI INGENERIE Proprietary© 2005 DEVINCI INGENIERIE
ATOS : A stress aeronautic software thought by stress aeronautic engineers
Integrated InterfaceSystematic calculation on n load cases and p
geometries
Input & Output data interfacing with
Excel or text files .csv type
Choice of the assumptions and
calculation methods
Calculation methods locking by the Process
Administrator
Calculation on single load case & geometry
Optimization of geometries on several load cases by iterative
method
Generation of input geometry data and formated loadings
data
User profil management
Files sessions management
Generation of calculation report
files2|
CALCULATION
1 - QUALITY & TRACABILITY OF PROCESS
3|
INTERFACINGOnline access to a
database of the methods programed in ATOS
4 - MANAGEMENT OF CALCULATION METHODS
4 MAIN FUNCTIONS(click to continue)
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DEVINCI INGENERIE Proprietary© 2005 DEVINCI INGENIERIE
THE TYPICAL STRUCTURES CALCULATED BY ATOS
FUSELAGE
Panel fuselage
Frames(orbital stiffeners)
Stringers(longitudinal stiffeners)
Floor track
Floor strut
Support Rod
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DEVINCI INGENERIE Proprietary© 2005 DEVINCI INGENIERIE
THE TYPICAL STRUCTURES CALCULATED BY ATOS
WING
Aft Spar
Front Spar
Middle Spar
Rib
Intrados Panel
Extrados Panel Stiffeners
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DEVINCI INGENERIE Proprietary© 2005 DEVINCI INGENIERIE
The Frames in C shape : RF calculation at U.L. & L.L.
Tension of flanges and skin, Local buckling of flanges, Lateral instability & Crippling of inner flange, inter-rivet buckling of outer flange & skin, Column buckling, Shear & instability of webs
Plates and Shells : RF calculation & Thicknesses optimization
Instability : compression, shear, bending, bi-compression & all combinations for all boundaries conditions
Failure & Elaticity : Von Mises, Rankine, Saint-Venant, Tresca, Max strain energy
Allowables calculation
Instability for plates and shells in compression, shear, bending, bi-compression & all combinations for all boundaries conditions
Super-stiffeners in instability : Crippling, Local buckling of flanges & web, Lateral instability of inner flange, inter-rivet buckling of outer flange & skin, Column buckling
Fastened stiffeners in I, Z, C, L, & T - Integral stiffeners in L, I & T
Plasticity corrections
Compression, bending & shear
Tension (Neuber)
Plastic Bending (Cozzone)
Material Data Base Management
Calculations in ATOS V1.2 at present
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DEVINCI INGENERIE Proprietary© 2005 DEVINCI INGENIERIE
Static - RF Calculations & Optimization
Stiffened panels in compression, shear, combination compression-shear & amplified bending
Junctions & Fittings calculations
Sections properties calculation
Lugs analysis
Beam analysis in several loading and boundary conditions
Optimization of frames
Development of high efficient Algorithms of Optimization
Automatic generation of Nastran bulk
DEVELOPMENTS IN PROGRESS
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