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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

DIASP HELIPLATFLIGHT MODEL

POLITECNICO TORINO, DIASP, [email protected]

DIASP HELIPLATFLIGHT MODEL

POLITECNICO TORINO, DIASP, [email protected]