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Aircraft Loads, Free Body DiagramsDate: 07

th

May, 2012Place: CSG, BTP, Bangalore

Confidentiality

The material contained in this presentation represents proprietary and confidential information pertaining to

products, technologies and processes belonging to Creative Synergies Group (CSG) and the Customer. All information

in this presentation is to be treated in confidence. The names and trademarks used in this presentation are soleproperty of the respective companies and are governed / protected by the relevant trademark and copyright laws.

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02.AIRCRAFT LOADS & FREE BODY DIAGRAMS

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Special Loads Hoisting aircraft, towing aircraft,Fuselage pressurizing

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During specification of loads two terms used are:

Limit or applied loads:Maximum loads anticipated on the aircraft

during its lifetime.

Ultimate or design load:

Limit loads multiplied by a factor of safety(i.e. 1.5)

Design loads are to be carried by the aircraft without

failure. It indicates the reserve strength of the aircraft

against complete structural failure.

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Typical lift distribution for a wing

fuselage combination

(Spanwise view)

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Structural Loads/Stress

Five Types Of Stress

Tension

Compression

Bending force

Torsion

Shear force

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FREE BODY DIAGRAMS

In analyzing any technique, one should consider

all external forces, by accounting for effect of

each one of the body

The isolated body is considered a separate

mechanical system

Easier to identify forces & represent as vectors

Can help determine the application anddirection of forces acting on the body

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Direction & Point of Application of

External ForcesForce Direction of Force Point of Application

Weight (W) Downward Center of Gravity

NormalReaction (R)

Perpendicular Point of contact

Friction (F) Along surface Point of Contact

Buoyancy (B) Upward Center of buoyancy

Drag (D) Opposite flow Center of Gravity

Lift (L) Perpendicular to drag Center of Gravity

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Free Body Diagram

Magnitude

arrow length

Direction

arrow head Point of application

arrow tail

Weight (W)

Reactive force (R) Friction (F)

Fig 12.27

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