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Aircraft Design: A Systems Engineering Approach, M. Sadraey, Wiley, 2012

Chapter 3

Aircraft Conceptual Design

Figures

Figure 3.1. Aircraft conceptual design

Aircraft Design Requirements (Mission, Performance, Stability, Control, Cost, Operational, Time, Manufacturing)

Wing

configuration

Aircraft optimum configuration

Tail

configuration Engine

configuration

Landing gear

configuration

Structural

configuration

Mechanisms

configuration

Aircraft approximate 3-view (without dimensions)

Identify major components that the aircraft requires to satisfy the design requirements

Configuration optimization

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1. high wing 2. mid-wing 3. low wing

1.Rectangular 2. Tapered 3. Swept back 4. Delta

1. Monoplane 2. Biplane 3. Tri-plane

1. Fixed wing 2. Variable sweep

Figure 3.2. Wing configuration alternatives

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1. Conventional 2. T-tail 3. V-tail 4. H-tail

1. Aft tail 2. Canard 3. Three surfaces

Figure 3.3. Tail configuration alternatives

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:

1. Tractor (single engine) 2. Pusher (twin engine) Prop-driven jet

1. Tri-engine 2. Four engine (under wing)

Figure 3.4. Engine configuration alternatives

1. Tail gear 2. Tricycle

3. Multi-gear 4. Bicycle

Figure 3.5. Landing gear configuration alternatives

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1. Cabin 2. Cockpit

1.Tandem 2. Side-by-side

Figure 3.6. Fuselage configuration alternatives

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Boeing 747 (Courtesy Anne Deus)

Cessna 182 (Courtesy of Jenny Coffey)

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Eurofighter Typhoon (Courtesy of Antony Osborne) Figure 3.7. General aviation, civil-transport, and military aircraft

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1. Air ship Zeppelin NT (Lighter-than-air craft)

2. ATR-42 (Courtesy of Anne Deus)

Figure 3.8. Lighter-than-air craft versus heavier-than-air craft

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1. Beech 76 Duchess (Courtesy of Jenny Coffey)

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2. Global Hawk

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3. Radio controlled model aircraft

Figure 3.9. Manned aircraft, unmanned aircraft, and remote controlled aircraft

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Figure 3.10. Trade-off analysis process

Yes

No

Design requirements

(criteria/constraints)

Design

alternative 1

Design

alternative 2

Design

alternative 3

Design

alternative 4

Define analysis goal

Select and weight evaluation parameters (Mission, Performance,

Stability, Control, Cost, Operational, Time, Manufacturing)

Identify data needs (existing data, new data, estimating relationships)

Identify evaluation techniques (e.g. simulation)

Select and/or develop a model

Generate data and run model

Evaluate design alternatives

Accomplish a sensitivity analysis

Identify areas of risk and uncertainty

Recommend a preferred alternative

Select approach

Select a

different

approach

System definition

Is the approach

feasible?

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Figure 3.11. The Phases in the configuration design optimization

Design requirements

Establish design weights

Derive the optimization function

Select a baseline configuration

Apply constraints and design specs

Determine configuration design index (DI)

Final optimum configuration

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1. Boeing 747 (Courtesy Anne Deus)

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2. Stampe-Vertongen (Courtesy Jenny Coffey)

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3. Rutan 33 VariEze (Courtesy Jenny Coffey)

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4. F-15C Eagle (Courtesy Antony Osborne)

Figure 3.12. Four aircraft to be used in Example 3.2

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Figure 3.13. Canadian Vickers PBV-1A Canso A (Courtesy of Jenny Coffey)

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Figure 3.14. Commonwealth CA-18 Mustang (Courtesy of Jenny Coffey)

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Figure 3.15. Antonov An-140 (Courtesy of Antony Osborne)

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1. MD-11 (Courtesy of Anne Deus)

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2. De Havilland Vampire (Courtesy of Antony Osborne)

Figure 3.16. McDonnell Douglas MD-11 and De Havilland Vampire

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Figure 3.17. Saab MFI-17 Supporter (Courtesy of SAAB)

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1. F/A-18 2. Pilatus PC-7 3. Lockheed C-130 Hercules

Figure 3.18. F/A-18 Hornet, Pilatus PC-7, and Lockheed C-130 Hercules

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Figure 3.19. Solar Impulse (Courtesy of Vladimir Mykytarenko)