Page 121 - My FlipBook

ufacturing of High Temperature
Resistant Co-cured Composite Structures
using Carbon-BMI Prepreg
¡¡ Most of the airframe manufacturers
uses carbon-BMI prepreg to manu-
facture simple monolithic skin and
ribs and then assembled by fasten-
ers, where they lost composite real integral structure or simple component
advantages like reduction in part
count, elimination of fasteners,
reduced assembly elimination of
stress concentration zones due to
fastener holes and elimination of
fuel leakage etc.
¡¡ First time co-cured engine bay
door was developed and un-
dergone qualifications tests and
cleared by relevant regulatory au-
thorities for flights.
Level/Scale of Development : TRL-10,
Proven through successful
demonstration of autoclave moulding
technology and static structural testing
of Carbon-BMI Engine Bay Door of
LCA TEJAS.
Intellectural Property Rights (IPR):
Not Applicable
Major Plant Equipment and Machin-
ery Required
For the LCA-Tejas Program
• CSIR-NAL has developed co-cured
carbon BMI Engine Bay Door and
qualified the door by static structural
SS 10
test at room temperature and at high
temperature (180 deg C).
• CSIR-NAL has the processing
capability to produce highly contoured
to resist temperature up to 200 deg C
for any engineering field using carbon-
BMI prepregs.
Market potential
Application in fighter aircraft used in
LCA-Tejas
Major Raw Materials to be
Utilized
Autoclave, Cold storage, Clean room,
Prepreg cutting machine, Laser Tracker,
NDE equipments and assembly tools.
Commercialization
¡¡ Currently used to fabricate simple
skins and less contoured parts due
to BMI resin property at curing tem-
perature. However, its application
to develop cocured and integral
parts and the associated tooling is
available with a very limited com-
pany globally.
Available in Market : Used in LCA-
Tejas aircraft