Structural Loads in Design of Aircraft Components
Structural Loads in Design of Aircraft Components
(OP)
Hi All;
I am really confused about the application of loads that is either maneuver or aerodynamic loads at the same time or indivudiually while extracting margin of safety for each component under different loads
Could you please guide me in finding MoS...
Maneuver Loads:4G
Aerodynamic Forces and Moments: Fx Fy Fz Mx My Mz..are known
should i apply all those forces at the same time or individualy in ultimat eand limit load calculations?
thanks in advance
I am really confused about the application of loads that is either maneuver or aerodynamic loads at the same time or indivudiually while extracting margin of safety for each component under different loads
Could you please guide me in finding MoS...
Maneuver Loads:4G
Aerodynamic Forces and Moments: Fx Fy Fz Mx My Mz..are known
should i apply all those forces at the same time or individualy in ultimat eand limit load calculations?
thanks in advance





RE: Structural Loads in Design of Aircraft Components
Quando Omni Flunkus Moritati
RE: Structural Loads in Design of Aircraft Components
The relative sign of the various loads can depend on direction, so while the input from a pothole will be upwards and aft, the inputs from cornering may be - 0 or + at the same time. So you really need to consider what combinations are likely, and examine those, as it is possible that the worst case stress at one location is not caused by +1 +1 +1 loads.
Cheers
Greg Locock
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RE: Structural Loads in Design of Aircraft Components
sometimes we'll conservatively apply max/min envelope loads (ie the largest absolute value applied in both +ve and -ve directions). some OEMs, however, are adament that this is Wrong.
but if he has a specific loadcase, then he should apply those loads directly.
Quando Omni Flunkus Moritati
RE: Structural Loads in Design of Aircraft Components
Quando Omni Flunkus Moritati