Bu
çalışmada
verilen
görev
parametrelerine
göre
bir
model
roket
tasarlanmıştır.
Ayrıca
prototipinin
nasıl
üretildiği
ve
tasarım
aşamasında
hangi
parametrelerin
kullanıldığı
anlatılmıştır.
Tasarım
parametreleri
farklı
görevler
gereksinim
konfigürasyonları
için
tamamen
farklılık
gösterebilir.
makalenin
amacı
adımlarını
performans
analizlerini
açıklamaktır.
Roket,
başlangıçtan
itibaren
yüksek
apoje
daha
yük
taşıma
hedefiyle
adımları
gösterilmiş,
simülasyonlar
yapılmıştır
optimizasyon
sonuçları
değerlendirilerek
roketler
üretilmiştir.
Roketlerde
burun
konisi,
kanatçık
malzeme
mukavemeti
hesaplamaları,
belirsizliklerin
olumsuz
sonuçlarını
önlemek
amacıyla
detaylı
olarak
yapılmıştır.
Model
roketin
imalatı,
tasarımı
simülasyonu
başarıyla
gerçekleştirilmiştir.
Aerospace Science and Technology,
Год журнала:
2024,
Номер
146, С. 108911 - 108911
Опубликована: Янв. 23, 2024
The
first
goal
of
this
work
was
to
find
a
regression
law
for
(Polyvinyl
Chloride)
PVC
coupled
hydrogen
peroxide
on
10-N-scale
hybrid
thruster,
which
appears
be
suitable
small
satellites
when,
example,
manoeuvres
are
required
orbital
control
purposes.
Different
techniques
were
initially
analysed
in
order
reconstruct
the
ballistics
inside
combustion
chamber,
starting
from
experimental
data.
Subsequently,
even
if
different
lead
similar
results,
one
that
takes
into
consideration
greatest
number
measurements
chosen
post-processing,
and
three
curves
obtained
according
various
criteria.
resulting
laws
coming
selected
method
appear
agreement
with
results
constitute
powerful
means
designing
engines
fuel.
Finally,
performance
analysis
has
been
performed
in-space
thrust
specific
impulse
have
estimated.
shows
excellent
can
good
candidate
type
applications,
par
other
more
popular
polymeric
materials.
Aerospace,
Год журнала:
2023,
Номер
10(10), С. 901 - 901
Опубликована: Окт. 22, 2023
Hybrid
rocket
propulsion,
first
demonstrated
by
the
Russian
GIRD-09
in
1933,
combines
liquid
oxidizer
and
solid
fuel
for
thrust
generation.
Despite
numerous
advantages,
such
as
enhanced
safety,
controllability,
potential
environmental
benefits,
hybrid
propulsion
has
yet
to
achieve
its
full
space
applications.
In
recent
years,
research
on
gained
enormous
momentum
both
academia
industry.
Recent
accomplishments
altitude
record
student
rockets
(64
km),
launch
of
electric
pump-fed
rocket,
a
successful
25
s
hovering
test
highlight
rockets.
However,
although
community
is
growing
constantly,
industrial
utilizations
in-space
validations
do
not
exist.
this
work,
we
reassess
possibilities
engines
presenting
fields
applications
from
literature.
Most
importantly,
identify
technical
challenges
that
hinder
breakthrough
sector
evaluate
technologies
approaches
necessary
bridge
gaps
development.
Applied Sciences,
Год журнала:
2025,
Номер
15(5), С. 2696 - 2696
Опубликована: Март 3, 2025
This
paper
presents
the
design
and
experimental
evaluation
of
a
throttleable
pintle-centrifugal
injector
system
tailored
for
hybrid
rocket
engines,
aimed
at
improving
combustion
efficiency
enabling
precise
throttling
control.
The
novel
combines
principles
swirl
injection
pintle-based
throttling,
offering
fine
adjustment
oxidizer
flow
rates
to
optimize
dynamics.
Cold-flow
experiments
using
deionized
water
were
conducted
assess
injector’s
performance
across
range
pintle
strokes.
Results
demonstrate
that
stroke
effectively
regulates
pressure
drop
atomization
characteristics,
with
significant
improvements
observed
in
spray
cone
angle
droplet
size
distribution.
achieved
variation
ratio
4.162
rate
6.841,
indicating
strong
capacity
deep
throttling.
These
findings
highlight
potential
enhance
adaptability
motors,
promising
applications
modern
aerospace
propulsion
systems.
