Abstract (EN):
For high temperature usage (200°C and above) such as in certain supersonic aircraft
structures, the composites used are either bismaleimides (BMI) or polyimides reinforced with
carbon fibres. The composite selected was Advanced Composites Group HTM552. It is a
carbon fabric 0/90° laminate of high strength carbon fibres in a 2 × 2 twill weave
impregnated with a BMI resin. To determine the mechanical behaviour of the BMI composite
as a function of temperature, the following tests were performed. The longitudinal E (E11) was
obtained dynamically by vibrating a free-free beam in flexure from –55 to 200°C. The
ultimate longitudinal strength (σ11) was determined using the 4-point flexure test. The through
thickness strength (σ22) was determined by bonding a piece of composite to steel blocks and
loading in tension normal to the fibre direction. Finally, the coefficient of thermal expansion
of the BMI composite was measured using strain gauges according to a method proposed by
Lord.
Idioma:
Português
Tipo (Avaliação Docente):
Científica