Aeroplane Structure

Question 1

General Structure

Answer 1

Beam.
Beams in aircrafts are often made from light weight aluminium alloys or advanced composite to optimise strength to weight ratios.These materials resists corrosion and fatigue while supporting dynamic loads during flights.
They are intergral to semi-monocoque designs,and internal beams(eg.spars,ribs,lingerons)work together to distribute stress.
Examples.A wing spar a primary beam-support bending loads from the wings lift.In metal aircraft, it is typically an I-beam or box-beam design made of aluminium alloys,optimisatied to handle tension on the lower flange and compression on the upper flange.This design aligns with the general principles that beams resists bending by balancing compression and tensile stress.

Question 2

Fatigue life

Answer 2

Refers to the number of stress cycles a material can endure before failing due to repetitive loading. In aviation,this concept is critical for ensuring the structural integrity of metal airplane components which experience cyclic stresses during takeoff,turbulence, loading and other operational phases.
Airplane structure.
i)Fuselage-The main body,often constructed from aluminium alloys in semi-monocoque design (stressed skin reinforced by frames and stringers.
ii)Wing load-bearing structure with spars,ribs and skins,designed to withstand aerodynamic forces and fuel loads.
iii)Empennage-Horizontal and vertical stabilizer with control surfaces(elevators,rudder)
iv)Undercarriage-Landing gear assemblies that absorbs impacts loads.

Question 4

Beams.

Answer 4

Beams in aircrafts are often made from light weight aluminium alloys or advanced composite to optimise strength to weight ratios.These materials resists corrosion and fatigue while supporting dynamic loads during flights.
They are intergral to semi-monocoque designs,where the outer-skins(stresses skin)and internal beams(eg.spars,ribs,lingerons)work together to distribute stress.
Examples.wing spars as a beams.
A wing spar a primary beam-support bending loads from the wing lifts.In metal aircraft,it is typically an I-beam or box beam design made of aluminium alloys,optimisatied to handle tension on the lower flange and compression on the upper flange.This designs aligns with the general principle that beams resist bending by balancing compression and tensile stress.