7th EUROPEAN WORKSHOP ONAIRCRAFT DESIGN EDUCATION (EWADE 2005)
Laurea Specialistica in Ing Aerospaziale(MSc in Aerospace Eng.)
Corso: PROGETTO DI AEROMOBILI(Course: AIRCRAFT DESIGN )
Credits: 10 - Total hours: 115 (L. 80 + E. 35)
Prof. Ing. Giulio ROMEO, Giacomo FRULLAIng. Enrico CESTINO, Fabio BORELLO
POLITECNICO TORINO, Dept. of Aerospace Engineering
email: [email protected]
PRELIMINARY
AIRCRAFT
DESIGN
Weight
Estimation
Aerodynamic Analysis
Structural
Analysis
Aeroelastic
Analysis
Flight Mechanics /
DynamicsCost
Analysis
LA SCIENZA DEL PROGETTO DI AEROMOBILI Prof. Ing. Giuseppe GABRIELLI
G. ROMEO – Aircraft Design, Politecnico Torino, DIASP, [email protected]
G. ROMEO – Aircraft Design, Politecnico Torino, DIASP, [email protected]
Theories and/or empirical methods concerning a single design aspect
Use of commercial software and/or self-developed software to solve specific problems
Preliminary aircraft design by integration of the previously developed tools
G. ROMEO – Aircraft Design, Politecnico Torino, DIASP, [email protected]
Weight EstimationBy adopting empirical methods, commonly found in literature (Torenbeek, Jenkinson, Stanford Univ., Howe, Raymer, etc…) and statistical data, students develop a software to evaluate total aircraft mass and masses of each of the sub-systems (structure, propulsion group, crew, equipments…)
FRAZIONI DI PESO DEL MAXIMUM TAKE-OFF WEIGHT
950022%
7711.8%3456
8%650615%
610.14%
3750.87%
901021%
31517%
20295%
709617%
5101.19%
4160.97%
Wing Horizontal tail Vertical Tail Fuselage Landing gear NacellesPropulsive Implant Implants Not usable fluid Crew Fuel weight Payload
Overall Aircraft Weight Breakdown
(Avro RJ100)
CONTRIBUTI AL PESO STRUTTURALE
315122%
709650%
202915%
7716%
5104%
4163%
Wing
Horizontal tail
Vertical Tail
Fuselage
Landing gear
Nacelles
PERCENTUALI DI PESO DEI DIVERSI IMPIANTI
390260%
68110%
4086%
3185%
5909%
610.94%
1843%
3636%
Auxiliary power unity (APU) Instruments and navigational equipment Hydraulics and pneumatics system (wing)Hydraulics and pneumatics system (tail) Electrical system Electronics systemFurnishings Air conditioning and anti-ice
G. ROMEO – Aircraft Design, Politecnico Torino, DIASP, [email protected]
Weight Estimation
Systems Breakdown
Structure Breakdown
G. ROMEO – Aircraft Design, Politecnico Torino, DIASP, [email protected]
Aerodynamic AnalysisAirfoil Wing Aircraft
The panel code XFOIL has been used to study airfoil performances in subsonic
flows…
… and to draw Cl-αand polar curves
G. ROMEO – Aircraft Design, Politecnico Torino, DIASP, [email protected]
Aerodynamic AnalysisAirfoil Wing Aircraft
XFOIL results and Prandtl lifting line theory are
implemented in a software developed by students in
order to study wing aerodynamic behaviour
Wing Polar
G. ROMEO – Aircraft Design, Politecnico Torino, DIASP, [email protected]
Aerodynamic AnalysisAirfoil Wing Aircraft
Parasite drags due to aircraft components are evaluated through empirical methods, allowing
aircraft polar to be plottedWing and Aircraft Polar
Parasite Drag Breakdown
Structural AnalysisG. ROMEO – Aircraft Design, Politecnico Torino, DIASP, [email protected]
The structural analysis of wing-box is carried out by a preliminary structural design program developed by students.First attempt wing-box geometry and
materials are defined and stress/strain state computed
Structural AnalysisG. ROMEO – Aircraft Design, Politecnico Torino, DIASP, [email protected]
A CATIA V5 model is built to outline a 3D external & internal
configuration and to define geometries for
MSC PATRAN…
G. ROMEO – Aircraft Design, Politecnico Torino, DIASP, [email protected]
Structural Analysis… and a more accurate analysis is achieved through FEM
(MSC NASTRAN )
G. ROMEO – Aircraft Design, Politecnico Torino, DIASP, [email protected]
Flight Mechanics / DynamicsMain flight qualities as
well as static and dynamic stability are
evaluated.
static longitudinal stability evaluation
dCmCG / dα < 0
CmCG = 0 for α = 0
Short Period Analysis
Phugoid Analysis
Argand Diagrams
Root Locus
G. ROMEO – Aircraft Design, Politecnico Torino, DIASP, [email protected]
Flight Mechanics / Dynamics
Aeroelastic AnalysisG. ROMEO – Aircraft Design, Politecnico Torino, DIASP, [email protected]
Static aeroelastic problems :
• Divergence Speed
• Aileron Reversal
Both FEM approach &Influence Coefficients
approach are used
G. ROMEO – Aircraft Design, Politecnico Torino, DIASP, [email protected]
Aeroelastic AnalysisDynamic Aeroelastic problem:
•FlutterFrequency ratio
V- g method
Damping• Typical Section Approach
• Theodorsen Aerodynamic Theory
Cost AnalysisG. ROMEO – Aircraft Design, Politecnico Torino, DIASP, [email protected]
DOC - TOTALE DIRECT OPERATING COST/HOUR
Crew costs19%
Standing charges15%
Maintenance cost21%
Fuel cost28%
Airport charges17%
standing charges crew costs airport charges fuel cost maintenance cost
CASH DOC - TOTAL CASH DIRECT OPERATING COST/HOUR
airport charges20%
maintenance cost25%
fuel cost33%
crew costs22%
crew costs airport charges fuel cost maintenance cost
COST MODEL
POLITECNICO TORINO, DIASP, [email protected]
Operative Costs
Total Life Cycle CostDIASP HELIPLAT
Airframe Structure DesignAircraft Structural Integrity
Design Philosophies: • “safe life”• “fail safe• “damage tolerance”
G. ROMEO – Aircraft Design, Politecnico Torino, DIASP, [email protected]
Design of Advanced Composite StructureG. ROMEO – Aircraft Design, Politecnico Torino, DIASP, [email protected]
Buckling & Post-buckling of CFRP Panels Under Combined Loads
Design of Advanced Composite StructureG. ROMEO – Aircraft Design, Politecnico Torino, DIASP, [email protected]
Non-linear Analysis of CFRP Wing Box Under Bending or Torsion
b = 5.8 m - W = 20kgDIASP HELIPLAT SUPER DIMONA
POLITECNICO TORINO, DIASP, [email protected]
FLIGHT MODEL
Top Related