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8/10/2019 Us 2627160 patent
1/5
F e b .
3 ,
1953 G . c .
MaODONALD 2 , 6 2 7 , 1 6 0
ROCKET
IGNITER
Filed
A p r i l
1 ,
1 9 4 7
2
SHEETSSHEET
1
Q w a s m m Q m m m
INVEN O R .
Wm ? -
AJMJ
8/10/2019 Us 2627160 patent
2/5
2 , 6 2 7 , 1 6 0
e b .
3 , 1953 G . c . MaGDONALD
ROCKET IGNITER
2
S H E E T S ~ S H E E T
2
iled April
1,
1 9 4 7
8/10/2019 Us 2627160 patent
3/5
P a t e n t e d
F e b .
3 , 1 9 5 3
UNITED STATES
2 , 6 2 7 , 1 6 0
PATENT
OFFICE
2,627,160
ROCKET
IGNITER
Gilmour C r a i g MacDonald, Ames,
Iowa
A p p l i c a t i o n A p r i l
1 , 1 9 4 7 , S e r i a l N o .
7 3 8 , 6 0 1
( 0 1 .
6 0 - 3 5 . 6 )
Granted
un d e r T i t l e 3 5 , U. S .
C o d e
( 1 9 5 2 ) ,
s e c . 266)
4 Claims.
This i n v e n t i o n
d e s c r i b e d
h e r e i n may e manu
factured
a n d u s e d
b y or f o r the G ov e r n m e n t for
governmental
p u r p o s e s ,
without
t h e
payment
' t o
me
f any r o y a l t y
t h e r e o n .
This
invention r e l a t e s
t o
rocket i g n i t i n g m e a n s
and m o r e
p a r t i c u l a r l y
t o
simple
m e a n s f o r i g n i t
i n g
t h e m a i n
r o c k e t p r o p e l l a n t charge c o i n c i
d e n t a l l y
w i t h
v e n t i n g t h e p r o p e l l a n t chamber.
I t i s an
o b j e c t
o f t h i s invention
t o
p r o v i d e
means whereby
an
e x p l o s i v e c h a r g e , employed
t o
rupture the
n o z z l e c l o s u r e o f a r o c k e t , a l s o i g n i t e s
t h e m a i n p r o p e ll a n t c h a r g e .
I t i s a
further
o b j e c t
o f
the invention t o
s i m
p l i f y s o l i d f u e l r o c k e t s , o f t h e
t y p e
p r o v i d i n g f o r
o p t i o n a l
d i r e c t i o n
o f t h r u s t through
the use
o f
dual o r m u l t i p l e
n o z z l e s , by
u t i l i z i n g
two
o r m o r e
o f the r o c k e t i g n i t i n g means h e r e i n d i s c l o s e d i n
s u b s t i t u t i o n
f o r
the conventional
r o c k e t
?ring
means.
C e r t a i n
important advantages i n improving
t h e low temperature
i g n i t i o n c h a r a c t e r i s t i c s
o f
rocket thrust u n i t s
accrue
t o t h i s invention i n that
the e x p l o s i v e
r u p t u r i n g
charge
and
t h e n o z z l e c l o
sure m e a n s may e s o
design ed
that
the
ruptur
ing charge prod uces only a small hole
i n
the
c l o
s u r e , t h e
b a l a n c e
o f t h e c l o s u r e blowing
and/or
e r o d i n g o u t o f t h e n o z z l e o n l y w h e n t h e p r e s s u r e
within the rocket c h a m b e r approaches the n o r
m a l operating p r e s s u r e .
By t h i s
means, the
r a t i o
o f p r o p e l l a n t
burning
s u r f a c e
t o
n o z z l e
area may
b e
i n c r e a s e d d u r i n g t h e
c r i t i c a l i g n i t i o n
p e r i o d ,
which will s u b s t a n t i a l l y improve i g n i t i o n
o f
t h e
p r o p e l l a n t ,
e s p e c i a l l y
a t
l o w t e m p e r a t u r e s .
A
urther
advantage o f t h i s invention i s that
the
rocket u n i t
may r e ma i n
permanently an d
h e r m e t i c a l l y s e a l e d a f t e r manufacture,
and
t h e
i n i t i a t i n g charge may e
i n s e r t e d i n
t h e
e x t e
r i o r p o r t i o n
o f
the
n o z z l e .
This i s
i n
c o n t r a s t
with
t h e p r e s e n t
system
o f
i n s e r t i n g
an
i n t e r n a l
i g n i t e r p r i o r t o
u s e ,
w h i c h
may cause
s e r i o u s
i n t e r n a l e ? e c t s d u e
t o e x c e s s i v e
humidity, or the
hazardous p r a c t i c e o f handling
and s h i p p i n g t h e
u n i t
with
t h e
i g n i t e r i n
p l a c e
and with the ?ring
c i r c u i t
wires
a t t a c h e d .
Other
o b j e c t s
and advantages o f t h i s i n v e n
t i o n w i l l
be apparent
during the
c o u r s e o f the
f o l l o w i n g d e s c r i p t i o n , r e f e r e n c e b e i n g m a d e
t o
t h e a t t a c h e d
drawing
w h e r e i n :
Figure
1
d e p i c t s
a
l o n g i t u d i n a l
s e c t i o n
view
o f
a
p o r t i o n o f a r o c k e t t h r u s t u n i t
e m bo dy in g
my
i n v e n t i o n . Figu re 2
i s
a
s e c t i o n
view
s i m i l a r
t o
Figure l
but
d e p i c t i n g the detonation o f t h e rup~
t u r i n g
charge and
t h e
r e s u l t a n t r u p t u r e o f
t h e
blowout e l e m e n t .
Figu re
3 i s a
s e c t i o n
view s i m i
l a r t o F i g u r e 2
b u t d e p i ct i n g t h e c o n d i t i o n
o f t h e
1 0
25
45
50
2
b lowout elem ent when the
r o c k e t
i s
a t the
n o r
m a l
operating
p r e s s u r e .
Figure
4 i s a l o n g i t u d i
nal
s e c t i o n a l
view
o f
a
dual
n o z z l e
type
o f
rocket
m o to r
i l l u s t r a t i n g
t h e a p p l ic a t i o n t h e r e t o o f t h e
rocket i g n i t i n g m e a n s o f the i n v e n t i o n . F i g u r e 5
i s a
longitudinal s e c t i o n a l
view
o f
a
portion
of
a
rocket
thrust unit e m b o d y i n g a m o d i ? e d f o r m
o f c l o s u r e .
T u b e
i s screwed i n t o
n o z z l e
2 f o r m i n g
the
combustion chamb er con?ning
p r o p e l l a n t
3 and
i g n i t e r 4 . Blowout element 5 i s
secured
i n the
nozzle at the inner o r c h a m b e r e n d o f the l a t t e r
i n spaced r e l a t i o n t o the p r o p e l l a n t as s h o w n
and
e f f e c t s c l o s u r e
o f
the n o z z l e 2 u n t i l such t i m e
a s
rupturing charge 6 i s detonated
by
an e l e c t r i c a l
c u r r e n t p a s s i n g
through
t h e
conductor
1
o f the
? r i n g
c i r c u i t
( n o t
shown).
T h e r u p t u r i n g
c h a r g e
6 i s
p o s i t i o n e d
and s u p p o r t e d s u b s t a n t i a l l y a t
t h e
a x i a l center o f the
n o z z l e
2 b y m e a n s 8 , wh i c h
may
e a spider or oth e r
conventional
s t r u c t u r e .
Closure
e l e m e n t 5 as presently shown s a c u p
shap ed member
placed
i n
the
n o z z l e a s s h o w n
a n d
design ed
t o f a i l
a t pressures i n
e x c e s s o f the
normal
o p e r a t i n g
p r e s s u r e but l e s s than t h e de
ter m in ed
b u r s t i n g p r e s s u r e o f t h e
combustion
chamber.
T h e
d e t o n a t i o n
o f
r u p t u r i n g
charge
6 which
may
r not em p lo y
the hollow
charge shape
shown)
r u p t u r e s the blowout element 5 , t h e
i n
candescent
p a r t i c l e s
f r o m
s a i d
detonation
and
r u p t u r e
t r a v e l l i n g
almost i n s t a n t a n e o u s l y t o t h e
i g n i t e r
4 w hich
i g n i t e s t h e
p r o p e l l a n t 3 i n t h e
u s u a l man n e r . In
the p r a c t i c a l
a p p l i c a t i o n
o f
the
i n v e n t i o n ,
the rupturing charge
may,
i f
d e s i r e d ,
be
s o
pro po rtioned a s t o q u a n t i t y , s i z e ,
e t c . ,
that
the
b l a s t i n g o r e x p l o s i v e e f f e c t
t h e r e o f w i l l sub
s t a n t i a l l y d i s i n t e g r a t e and
d e s t r o y
i t s a s s o c i a t e d
c l o s u r e o r blowout e l e m e n t . _ Im provem ent i n t h e
low temperature i g n i t io n c h a r a c t e r i s t i c s o f
the
r o c k e t
i s
o b t a i n a b l e , h o w e v e r , i f
t h e
charge i s
shap ed
t o
have a
rupturing
f o r c e e f f e c t i v e t o
pro
d u c e
only
a small vent
hol e in
the
closure
m ea n s .
The r e s u l t s
achieved
f r o m the u se o f
a
s h a p e d
charge are
a p pa r en t f r o m Figu res
1 an d
2 w h e r e
i n i s
s h o w n
a
rupturing
member f the
hollow
charge shape c o m p r i s i n g a
r i g h t
c y l i n d e r 6 o f
e x p l o s i v e
having a
c o n i c a l c a v i t y
9
i n
o n e
e n d
a n d
su ppo rted
within the
n o z z l e
2
a n d
n ea r the
outer
face
o f
b lowout elem ent
5 s o
that the
base
o f the
cone 9 f a c e s
the
blowout
e l e m e n t . T h e
d i
r e c t i o n a l
c o n t r o l and
d e e p
p e n e t r a t i o n v o b t a i n
a b l e
with such a
shaped
c h a r g e ' i s u s u a l l y c a l l e d
t h e
c a v i t y
e f f e c t pheno m eno n. T h e
pro
nounced d i r e c t i o n a l e f f e c t and
deep
p e n e t r a t i o n
w hich i s
obtainable
with a r i g h t c y l i n d e r o f ex
8/10/2019 Us 2627160 patent
4/5
2 , 6 2 7 , 1 6 0
3
p l o s i v e having
a
c o n i c a l c a v i t y
i n
one
e n d
have
l o n g
b een
k n o w n i n the
a r t and
the p h e n o m e n o n
i s
s o m e tim es
ref erred t o as
the
M o n r o e
e f f e c t
as
a
r e s u l t o f the i n v e s t i g a t i o n an d
s t u d i e s
made
b y
M o n r o e
i n
the U n ited
S t a t e s . Additional
i n
formation r e g a r d i n g
t h i s
p h e n o m e n o n and t h e
i n v e s t i g a t i o n s
by
Monroe and
o t h e r s w i l l be
f o u n d
o n
p a g e
18 of
the
w o r k
b y
Co lo nel
L e s l i e E .
Simon,
U n i t e d
S t a t e s
Army,
e n t i t l e d ,
German
Research in W o r l d War I I a n d pu b lished i n
10
1947
b y
J o h n
Wiley
8 : Sons, I n c . , New Yo r k .
Figure
2 o f
t h e drawings d e p i c t s t h e d e v i c e a t t h e
i n s t a n t
o f
detonation o f
t h e
r u p t u r i n g
charge
6
w h i c h , b y reason
o f the
c a v i t y e f f e c t p h e n o m
e n o n
ref erred t o above, p r o j e c t s a
thin to ngu e or
j e t
o f incandescent gas
u n d e r
extr em e pressure
which r u p t u r e s an d
p i e r c e
t h e blowout
element
as s h o w n a t
H ) .
Incandescent gas a n d
m e ta l p a r
t i c l e s f r o m the detonated charge a n d the r u p
tured element
t r a v e l
t o a n d s t r i k e the i g n i t e r
4
w hich f l a r e s
u p ,
i g n i t i n g the p r o p e l l a n t
3 i n
t h e
usual man n e r . F i g u r e
3
i l l u s t r a t e s the condition
o f the p a r t s f o l l o w i n g
a short
p er iod o f time a f t e r
the
rocket unit has r e a c h e d n o r m a l
operating
p r e s s u r e .
At
t h i s
phase
o f the
o p e r a t i o n , the pro
p e l l a n t 3 i s burning
o n
a l l exposed
surfaces an d
the n o z z l e
passage
i s s u b s t a n t i a l l y
c l e a r o f
a l l
o b s t r u c t i o n s ;
t h e blowout element 5
having been
b l o w n
a n d / o r
e r o d e d ? u s h with the internal n o z
z l e
s u r f a c e by t h e high temperature and p r e s s u r e
o f
the gases o f combustion. D u r i n g the
c r i t i c a l
i g n i t i o n
p e r i o d o c c u r r i n g
between
t h e
r e s p e c t i v e
c o n d i t i o n s
i l l u s t r a t e d
i n Figures
2
an d
3 ,
the
r a t i o
o f
p r o p e l l a n t
b u rn ing
s u r f a c e
t o n o z z l e area i s
substantially
increased with the r e s u l t
that
t h e
continued i g n i t i o n o f t h e
p r o p e l la n t , p a r t i c u l a r l y
at low temperatures,
i s m a t e r i a l l y p r o m o t e d
and
i m p r o v e d .
T h e
assembly
o f
blowout element
an d
ruptur
i n g
charge
s h o w n
i n Figures 1 and 2 i s designed
primarily for u se
with a rocket o f the unidirec
t i o n a l
or
s i n g l e n o z z l e t y p e . W i t h a
s i n g l e
rocket
o f
the dual
or
multiple
nozzle t y p e , t w o
or m o r e
assemblies o f blowout
element
an d ru ptu ring
c ha r g e are u s e d t o g i v e a choice o f
thrust
d i r e c
t i o n
o f
the
r o c k e t . This i s
i l l u s t r a t e d i n
Figure
4
w h e r e i n i s
shown
rocket thrust unit
o f
th e
dual
n o z z l e type comprising a r o c k e t body
having
op
p o s i t e l y
d i s p o s e d n o z z l e s
and
I 2 connected
with
a common
r o p e l l a n t
c h a m b e r I 3 contain
i n g
t h e
p r o p e l l a n t
I 4 and the
p r o p e l l a n t i g n i t e r s
l 5
an d
I 6 . E a c h
n o z z l e
i s s h o w n provided with
a c l o s u r e
o f
the type
i l l u s t r a t e d
i n Figur e 1
a n d
including
a
b l o w o u t e l e m e n t
5 ,
ru ptu ring
mem
her 6
o f
the h o l l o w charge
s h a p e , detonating
w i r e s 1 , and
charge-supporting
m ean s 8 . Th r ust
i n the
d e s i r e d
d i r e c t i o n i s obtained
b y
detonating
t h e
rupturing charge
i n t h e s e l e c t e d n o z z l e f o r
i g n i t i n g
t h e
p r o p e l l a n t c o i n c i d e n t l y
w i t h
v e n t i n g
the n o z z l e . In
Figure
4 ,
the blowout element 5
o f nozzlel
i s s h o w n
ruptured
and
the p r o p e l l a n t
I 4
i g n i t e d
b y detonation o f
i t s a s s o c i a t e d charge
6 while the blowout element 5 o f
the nozzle
[ 2 i s
s h o w n i n t a c t . I t i s e s s e n t i a l t o
the
m aintenance
o f the d i r e c t i o n
an d duration o f
the
thrust
that
f a i l u r e
o f
the blowout element o f the non-vented
nozzle
shou ld not occur d u ring the operating
p e
r i o d o f
the r o c k e t .
I t i s o b v i o u s , t h e r e f o r e ,
that
ea c h
nozzle
closure
or
b l o w o u t e l e m e n t u s e d
in
a
rocket
g i v i n g
a choice
o f
thrust d i r e c t i o n
m u s t
be a b l e ,
w h i l e
i n i t s non-ruptured c o n d i t i o n , t o
stand n o r m a l c h a m b e r p r e s s u r e s without f a i l u r e
an d
a t the s a m e
t i m e
b e protected
against
the
high
temperature
o f t h e g a s e s o f
c o m b u s t i o n .
A c c o r d i n g l y , the blowout element 5 i s m a d e o f
2 0
25
3 0
40
60
65
7 0
4
su ch material
a n d
design herein d i s c l o s e d a s
t o
withstand p r e s s u r e s i n the p r o p e l l a n t c h a m b e r i n
excess o f
the n o r m a l
operating pressures
but l e s s
than
the
determined
b u r s t i n g p r e s s u r e
o f
t h e
p r o p e l l a n t chamber. In a d d i t i o n , a p r o t e c t i v e
s h i e l d
l l
o f any s u i t a b l e heat i n s u l a t i n g mate
r i a l
i s
used with
the
blowout
elementy5
t o
i n s u
l a t e
the
e l e m e n t
f r o m
the
h eat
o f
the
hot
gases
o f the
c o m b u s t i o n c ha m b e r .
This insulating
ma
t e r i a l may e a p p l i e d , as s h o w n in F i g u r e 4 , as a
c o v e r i n g
l a y e r
u p o n the
s i d e o f
the element
f a c
i n g t h e
i g n i t e r
and
t h e
p r o p e l l a n t . U p o n
r u p t u r e
o f
the
blowout element b y detonation
o f
t h e
shaped e x p l o s i v e c h a r g e ,
i t s a s s o c i a t e d
i n s u l a t o r
i s
a l s o
r u p t u r e d
b y
th e j e t f o r m at i o n o f the
b l a s t
wh i c h t r a v e l s t o and i g n i t e s the
p r o p e l l a n t
i g n i t e r . In the
operation
o f
the
d u a l - n o z z l e
r o c k e t t h r u s t u n i t sh o w n
i n
Figure 4 ,
w h e n
t h e
b l o w o u t e l e m e n t
5
of
nozzle
I I i s v en t e d t o give
the
d e s i r e d
d i r e c t i o n
o f
t h r u s t , the blowout e l e
m e n t 5
o f n o z z l e I 2
i s l e f t
i n t a c t f o r the dura
tion
of
the thrust unless cancellation or n e u
t r a l i z a t i o n
o f
thrust
i s
d e s i r e d ,
i n
w h i c h
c a s e
i t
i s ruptured b y detonation o f i t s
a s s o c i a t e d
rup
t u r i n g
charge
6
t o vent
the
n o z z l e
l 2 f o r
s e t t i n g
u p
a
c o u n t e r t h r u s t .
H e n c e ,
w h i l e o n e nozzle of
the dual n o z z l e
r o c k e t
i s i n operation t o g i v e the
d e s i r e d d i r e c t i o n o f t h r u s t ,
the
other nozzle p ro
v i d e s
a u x i l i a r y
venting m e a n s wh i c h i s
o p e r a b l e
u n d e r m a n u a l d i r e c t i o n t o
vent
the propellant
c h a m b e r
t o c o n t r o l
the duration
o f
the
t h r u s t
a n d operable a l s o in
response
t o propellant cham
b e r
p r e s s u r e t o
automatically vent the
p r o p e l l a n t
c h a m b e r before pressures in the c h a m b e r i n
ex
cess of t h e
n o r m a l
o perating
p r es s ur e r e a c h
bursting
pressure.
Many
other
types o f c l o s u r e s are a l s o a p p l i
cable
t o t h i s i n v e n t i o n . A m o d i ? e d
f o r m
o f
closure is
i l l u s t r a t e d
in F i g u r e 5 .
The
l o s u r e or
blowout element
t h e r e i n d e p i c t e d
i s
p r e f e r a b l y
of m o u l d e d p l a s t i c
a n d has a m a i n b o dy
or
p lug
1 8
w h i c h
is
seated i n
the
nozzle
2 at
t h e
inner or
p r o p e l la n t chamber i d e
of
the
throat
or
r e
s t r i c t e d
portion I Q
o f
the
n o z z l e , i n
spaced
r e l a
t i o n t o the p r o p e l l a n t 3 , an d c l o s e s the n o z z l e
pa ssa g ew ay in t h e
manner
h o w n . P l u g
I 8
i s r e
tained i n
i t s
n o z z l e - c l o s i n g p o s i t i o n i n
any
con
v e n t i o n - a 1 a n d suitable
manner not
s h o w n )
a n d
has a
hollow
s t e m 2
w h i c h is an i n t e g r a l
part
o f
the p l u g . The t e m 2 | i s o n the outer face of the
plug and extends
l o n g i t u d i n a l l y o f the n o z z l e
f r o m
the plug
t o
the outer
or
f a r s i d e
o f the
n o z z l e
t h r o a t I S ,
t h e
diameter o f
t h e
stem
b e i n g
so
much l e s s
t h a n
the d i a m e t e r
of
the
nozzle
t h r o a t t h a t
the
stem i s s u b s t a n t i a l l y
spaced
f r o m
an d centered
b e t w e e n
the
enco m passing w a l l
o f the n o z z l e .
The ho llow
s t e m
2 |
c a r r i e s the
c y l i n d r i c a l r u p t u r i n g charge
6 a
which i s p l a c e d
in the b o re or cavity 2 2
o f
the
stem.
A c u p 2 3
o n
the
inn er f a c e o f
plu g
[ 8 provides a
r e c e p
t a c l e
f o r
the
i g n i t e r 4a w h i c h maybe e l l e t e d i n
place
or
r eta in e d
as
a p o w d e r
b y
any c o n v e n
t i o n a l retaining means, .
e . ,
a
f o i l c o v e r i n g .
This
type of
closure serves
as a carrier
for
b o t h the
c l o s u r e
r u p t u r i n g
charge
6 a
and
t h e p r o pe l l a n t
i g n i t e r
4 a . Closure 1 8 may
l s o
be design ed s o
that the
ru ptu ring
charge
l e a v e s
a
portion
o f
t h e
c l o s u r e i n t a c t
u n t i l
the
r o c k e t
approaches
the
normal o p e r a t i n g p re s s u r e when t h e c l o s u r e i s
broken
up
and
x p e l l e d .
I t w i l l
b e
u n d e r sto o d that the scope o f
t h i s
i n
vention i s not l i m i t e d
t o the exemplary s t r u c t u r e
i l l u s t r a t e d
and
s p e c i ? c a l l y d e s c r i b e d , but i s l i m
i t e d o n l y
b y the
s c o p e
o f
t h e
f o l l o w i n g c l a i m s .
8/10/2019 Us 2627160 patent
5/5
2 , 6 2 7 , 1 6 0
5
I c l a i m :
1 . In a r o c k e t t h r u st d e v i c e , t h e combination r
a
p r o p e l l a n t ,
a combustion c h a m b e r
c o n ?n i n g
the p r o p e l l a n t
an d having an o u t l e t n o z z l e , a
r u p t u r a b l e
blowout element
s e c u r e d i n
t h e
n o z z l e
a t
the inner
o r c h a m b e r e n d o f the
l a t t e r i n
spaced r e l a t i o n
t o
t h e
p r o p e l l a n t and c l o s i n g
t h e
n o z z l e a t such e n d , a p r o p e l l a n t i g n i t e r b etw een
the s a i d element an d
the
s a i d p r o p e l l a n t , m e a n s
f o r
r u p t u r i n g t h e
s a i d
element and i g n i t i n g t h e
p r o p e l l a n t
i g n i t e r
i n c l u d i n g
a charge
r
e x p l o s i v e
w i t h i n
t h e n o z z l e ,
s a i d e x p l o s i v e
b e i n g
o f
t h e
h o l l o w
charge
shape
comprising a
r i g h t c y l i n
der o f e x p l o s i v e having a c o n i c a l
c a v i t y
i n one
e n d and supporting means f o r the s a i d
charge
p o s i t i o n e d
i n
the
n o z z l e
adjacent
t h e o u t e r s i d e
o f the blowout element and supporting the s a i d
c h a r g e s u b s t a n t i a l l y s p a c e d f ro m
and
c e n t e r e d
b etw een the encompassing
w a l l o f t h e n o z z l e
with
the
base
o f the cone
facing the
blowout
element.
2 .
In
a
r o c k e t t h r u s t d e v i c e , the
combination
o f
a p r o p e l l a n t ,
a
c o m b u st i o n c h a m b e r c o n ?n i n g
t h e p r o p e l l a n t
and
having m u l t i p l e
o u t l e t
n o z z l e s
angularly d i s p o s e d t o g i v e a c h o i c e
o f
d i r e c t i o n
o f t h r u s t ,
a b lowout n o z z l e c l o s u r e i n
each n o z z l e
an d c l o s i n g the
same, a
p r o p e l l a n t
i g n i t e r
be
tween t h e
p r o p e l l a n t
a n d
each n o z z l e c l o s u r e , and
m e a n s o p e r a t i v e l y a s s o c i a t e d with
each
n o z z l e
f o r
blowing o u t t h e
n o z z l e c l o s u r e
and
i g n i t i n g
the p r o p e l l a n t
i g n i t e r ,
s a i d
m e a n s i n c l u d i n g
a
charge o f e x p l o s i v e w i t h i n t h e n o z z l e
and a d j a
cent the o u t e r s i d e o f
the
n o z z l e c l o s u r e .
3 . In a
rocket
thrust
d e v i c e ,
the combination o f
a p r o p e l l a n t ,
a
c o m b u st i o n c h a m b e r c o n ? n in g the
propellant a n d having two o r m o r e o u t l e t n o z z l e s
a n g u l a r l y d i s p o s e d t o g i v e a c h o i c e o f d i r e c t i o n o f
t h r u s t ,
a
r u p t u r a b l e
blowout element
i n
each
n o z z l e
a t
the inner o r c h a m b e r e n d
o f
the
n o z z l e
an d c l o s i n g the n o z z l e a t such e n d , a p r o p e l l a n t
i g n i t e r between
t h e p r o p e l la n t and
each
r u p t u r
a b l e
b lowout
element,
a n d
m e a n s o p e r a t i v e l y a s
s o c i a t e d
with
each n o z z l e f o r
r u p t u r i n g the e l e
C a
1 5
20
25
30
40
6
ment and i g n i t i n g t h e
p r o p e l l a n t
i g n i t e r ,
i n c l u d
i n g
a shaped c h a r g e o f e x p l o s i v e m a t e r i a l wi t h i n
t h e
n o z z l e an d adjacent
t h e o u t e r
s i d e o f the
blowout e l e m e n t .
4 . In a rocket thrust d e v i c e , the combination
o f
a
p r o p e l l a n t ,
a
combustion c ha m b e r co n? n ing
t h e
p r o p e l l a n t
and
having
m u l t i p l e o u t l e t n o z z l e s
angularly d i s p o s e d
t o
g i v e
a
c h o i c e
o f d i r e c t i o n
o f
t h r u s t ,
a b lowout n o z z l e
c l o s u r e i n
ea c h nozzle
an d c l o s i n g the same, s a i d
c l o s u r e
being f o r m e d
o f a material having s u f f i c i e n t
p h y s ic a l s t r e n g t h
t o
r e ma i n i n t a c t a t
combustion c h a m b e r
p r e s
sure i n excess o f the n o r m a l
operating
p r es s ur e
but l e s s
than the
d e t e r m i n e d
bursting pressure
o f t h e combustion chamber, a p r o p e l l a n t i g n i t e r
between
t h e p r o pe l l a n t
and each n o z z l e
c l o s u r e ,
a c l o s u r e p r o t e c t i v e s h i e ld o f
heat-insulating
m a t e r i a l
p o s i t i o n e d
between
each n o z z l e
c l o s u r e
an d p r o p e l l a n t i g n i t e r , and m ean s
o p e r a t i v e l y
a s s o c i a t e d with each n o z z l e
f o r
blowing out the
n o z z l e c l o s u r e
and
i g n i t i n g
t h e
p r o p e l l a n t i g n i t e r ,
s a i d
m e a n s
including
a charge
o f e x p l o s i v e
within
t h e n o z z l e an d adjacent the o u t e r s i d e o f the
n o z z l e
c l o s u r e .
GILMOUR CRAIG MAcDONALD.
REFERENCES CITED
T h e following references are
o f
record i n the
? l e
o f
t h i s p a t e n t :
UNITED
STATES
PATENTS
Number
Name Date
4 0, 092 Dib bl e __________ - _ S e p t . 29, 1 8 6 3
2,423,837 Martin ____________ July 1 5 , 1 9 4 7
2, 455, 015
Mace
____________ _
Nov.
30, 1 9 4 8
2, 457, 839 Skinner
__________
_
Ja n .
4 ,
1 9 4 9
FOREIGN PATENTS
N u m b e r
Country Date
330, 4 93 Great Britain ____ _- June
2 ,
1 9 3 0
8 6 4 , 8 2 2
France ____________ _
Feb.
1 9 4 1