SOVIET DEVELOPMENT OF AN AIR-TO-AIR ROCKET

• Document Type: CREST
• Collection: General CIA Records
• Document Number (FOIA) /ESDN (CREST): CIA-RDP80-00810A001600270004-1
• Release Decision: RIPPUB
• Original Classification: S
• Document Page Count: 17
• Document Creation Date: December 16, 2016
• Document Release Date: November 27, 2002
• Sequence Number: 4
• Publication Date: July 9, 1953
• Content Type: REPORT

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CENTRAL INTELLIGENCE AGENCY
INFORMATION REPORT
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This Document contains information effecting the Na-
tional Defense of the United States, within the mean-
ing of Title .18, Sections 793 and 794, of the U.S. Code, as
amended. Its transmission or revelation of its contents
to or receipt by an unauthorized person is prohibited
by law. The reproduction of this form is prohibited.
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COUNTRY USSR
SUBJECT
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DATE OF INFO.
PLACE ACQUIRED
Soviet Development of an Air-to-
Air Rocket
REPORT NO.
DATE DISTR.
NO. OF PAGES
REQUIREMENT NO.
REFERENCES
9 July 1953
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The PutiIovo project dealt with an airborne rocket which was designed
for use by fighter planes against bomber flights. Technical background
information was derived from experience with the RIGOBS, formerly built
in Germany As is commonly known, the R100BS was equipped with a rocket
propulsion part, which was intended to increase the velocity increment
of the rocket projectile to 420 m./sec. The propelling Charge of the
RUM consisted ofapprotimately 21 or 21i kg. of diglycol tubular
powder or, 1.4 another variation, diglycol multiple-Channel profile powder.
The warhead of the German model was'imado up Of a large number of
incendiary fragments. The incendiary fragments were supposed to
penetrate the fuselage of the planese detonation of an explosive
charge, which was released in the immediate vicinity of a plane by
a proximity fuse. In Germany it was realized that such a weapon -
,could only be very effective as a surprise weapon and that/after
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a relatively dhorv period of time? it would be
pliegble to fight the fires, mused in the opm tank.
1Chja ammunitic?nlby means of automatic ex.
guishets, etc, In Germany it was planned as
the next development to replace the ince:ddiorY
fragments by small steel cylinders which woula be
filled with a Pyrosatz (pyro composition) giving
tracers-type effect. Then, when the tatim were
penetrated., the entire rabberization weed. be
term apart, and the holes would be no ionger self?
pealing? Gasoline would draili through these holes)
add the multitude of red-hot sparks, following
the fragment8! would set off the blaze. The
next -fabrication planned was to be incorporated
in Mine projactiles which carried the designation
NIKKI. It never want beyond preliminary planning
because at the time it was thought that incenditry
fragmentation alone was sufficient.
In the USSR the Germans were given the task of
fUrther developing and modernizing this project
4t first some designs were reconstructed in 4
toutIne manner* like the preliminary projects
Wetted on formerly In Germany. These designs
hta a Warhead placed in front of the actu
rocket chamber in which a large number
there were 28 to 31) of separate projectiles
were incorporated (depending upon the different
Taridtiods)0 The cap, which enclosed the
Single projectiles, was intended to be torn
into several pieces by a fuse and a detonation
laxyard so that the projectiles could be re-
leased. The Soviets did not like this Solution.
Por one thing, the length . was
so great that they had trouble 'amounting this
siissile under their fighter (interceptor) planed.,
? ?
After several years, during Which time the Otrmanp,
TrOtked on other teaks, it was suddenly decided
with great urgency to build a rocket which could
aSeimmodate a. large number of projectiles. It
?Vas snpposed to be able to penetrate developed
armor plate of a plane up to 8-10 mm. thiCkdOSOff-
illperiments in Germany previously had advanced-
te the point Where it could be said that a .
charge of approximately 400 g. tetramethylene-
trinitramine or tetremethylenetrinitramine.1-
tear
mixture was sufficient to
* apart the fuselage of a plane, even if it.
did not Penetrate the armor plate. This woUld
than cause the plane to lose its flight ability
that it is forced to crash-aand, even though
it does not crash on the spot. These facts had
l000d,ProviouslY theoretically calculated and the.
data rete taken over intact by the Soviets.
Ot the basis of these data, definite require-
MSntS were givenito the Germans to build such
reCkets.? in Germany the length of the device
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MIKI was approximately 2 me, but the Gernans
25X1 were expected to build a considerably shorter
prototype 'the required
.
25X1 data,' lwas on ene oraer oi about 1500 or
1600 mm. overall length. In the course of a
few weeks, about ten or fifteen variations were
workee on. Designs were made where it was
necescary to increase the diameter beeause
the length was decreased, causing greater
velocity decline and a reduction in the range
of action, This resulted in the issuance of
a? requirement to increase the size of the
propelling charge and the duration of flight.
This In turn reEulted in larger caliber
dimensions. A 3 previously mentioned, variations
existed which featured a cap consisting of
several parts. Upon approach of a plane,
these cap parts were supposed to flip open
And release the mines either by a time fuse
or possibly by the optical fuse, previously
developed in Germany, which detonated upon
approaching a plane. Other possibilities
were taken into consideration whereby the
mines were ejected toward the front. The
Germans completed several theoretical path-
of.eflight calculations* Along these lines,
they tried to construct the swinging action.
Prequently it showed that difficulties were
to be expected upon discharge of the pro-
jectiles from the magazine, During all this
designing, it proved to be more favorable
to pull a cloaed cap over the complete rocket
part and to use a ring magazine
(a magazine in which the single mines
are arranged around tee actual rocket as an
outer ring). Since a larger ogive was neces-
eery for more favorable aerodynamic conditions,
there was space available in the tip of the
missile into which more mines could be
arranged. Then, to balance the center of
gravity, it was necessary to place some
weight in the front so that the location of
the center of gravity became more favorable
and stability conditions were improved.
There was a rocket chamber for which the
Germans maintained that a caliber of 220 mm.
was suitable because a large nudber of tubes
wqs still in stock with this measurement,
aLeIREDDESCRIPT'ON_OPSOVIET AIRBORVE ROCKET
4* The magazine was made of a chromium steel which
resembled the Gelman ohrom-vaaadin steel 240,
and which had an alloyfable proof stress of
from 60-65 kg. per Em?-ewith a stremalafistim
APProximate4 85 kg4J This steel tass
had smother geed feature In, that it could, be
waded* It was Ideal *for such a fabriaatism4
Mho, pmans were able to increase the charge
to a 24 kg. maximum by corresponding development
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of the propelling charge with consideration of the
Maxim= possible by a presqueeze or choke ( TorkaelmmAr
ratio of burning surface to diameter of free
area of diaphl-alp. The Germans had previously reached
an. initial thrust of approximately 4600 kg./see, with
24 kg, of powder. The specific efficiency of the Soviet
powders was somewhat lower than that of Germano In
Germany they were able to reach a specific thrust of
from 200-210 (on special occasions). However, the
Soviet powders generally reached values of from
190-195 kg./sec.,
In. the mign the powders moat frequently placed at
the disposal of the Germans were a nitroglycerine
powder or nitrocellulose powder. The rocket part
located it the center had a 200?mm. outside diameter
with a total length of approximately 1100 mm. from
nose to trailing edge of the tail assembly. The
mines were arranged around this Chamber in rows of
two. The projectile had a caliber of approximately
50 mm. Several variations were worked on?of 415c,
5/0 55, and even 56ms4,-,*bidt, left a certah freedom
of movement according to the dimensions of the
rocket Chamber. Sometimes it was necessary to arrange
spacer strips around the circumference between one
or more ot the mines so that they would not get out
of place during the flight. Taking into consideration
the manufacturing tolerances, it was necessary to '
provide spaces. With this arrangements the Germans
Were able to place 16 mines around the circumference*
Two rows of mines were placed around the combustion
chember,,forming a ring between the propellant and the
outer ring of the magazine, for a total of 32 pro?
jectiles. These 32 projectiles were equipped with tail
asSembliee, Which did not protrude much beyond their
own circumference* According to the German theoretical
calallations, insufficient stabilization was to be
expected. However, the projectiles ahould have flown
just about stable, but they would have shown a
Ter7 Slow damping out of the shock waves, which
was inevltable at ejection from the magazine. There....
fore, the Germans decided to equip these projectiles
With a folding tail aseembly. The possibility was
still kept opens though, for replacing the folding
tail assembly by a rimed...tail assembly. However, because
of aerodynamic clTectst it is not known whether it
would be possible tc dispense with the folding
assembly. This would have been more advantageous
for manufacture because it would haxelsaa cheaper id
imald hAve caused less distwbaues if additional stabilization had
not been necessary. This particular design, howeve4
Provided for an, explosive charge more or lees in
the cra.124riesti, part only so thaty way back in the
144:14, there was always free air space mainly to
ataS4r0?Wafteient stabilization.
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Previous diagrammetric sketches of the configuration
with the expected center of gravity were sent out for
a wind tunnel test. They were sent to an Institute
Zeigiet The location of this Institute was never
msAe known to the Germans. However, testa were made
andl the stability
tutor was sufficientl th .ro ef't could
continue as planned.
I li someone emce(i al:mut team Immo,
ri
-ended.. kuaiet questioning wa S thus discouraged.. I
the vestions were just ignored and. the cdveTwatisn
the rockets
eVween 250 and 285 mm in leftgth? depending upon.
Which type of head was used; with blunt head 250 mmit)
1 th ?give approximately 285 mm. total length.
ee pages 13 to rg - . It so happens that
e folding tail.assembly protrudes a little beyond
the aroumference of the projectile. Therefore
the 'mines were on the same leVelf.-
? Yor example, -viae even numhers were arrangea on tne
outside and reached all the way to the trailing edge.
The adjacent column of projeotiles was pushed for-
ward 70 mm. whereby a small sheet-Imetal cap of about
7045 mm length insured the correct spacing, The
next even number started with a column which bordered
the edge. The tail assemblies thereby did not hinder
each other. Naturally, the 70-mm. construction
length was lost, but this was the only possible way
to accommodate a stable projectile in this type
ring magazine. In the front part of the ogive was
enough space to allow easy arrangement of Oil:more
projectiles. To arrange a seventh mire in the center
was impossible because a special ejecting cylinder
WI ?h its own plunger was incorporated for the
ejection process,. The rocket was so planned that
a cylinder was screwed to the front part of the
rocket chamber. The cover plate or cap was pro-
Vided with a high-temperatur. irhibitor. Simul-
tezeovalY with the burning of the rocket charge, an
inhibitor composition was ignited which became
effective after about 1/10 of the burning period
of the rocket and detonated the ejection part, This
was very definitely a substitute solution which was
only provided because of a special request from
the Soviets.
7. The Germans were.. always fully convinced that universal
combat service of such a rocket would be practicable Only
if the actual battle distance of the fighter plane
could be token into consideration. Por the later
models, it was necessary to incorporate an adjustable
time fuse which at the moment of release muld still
take into consideration the actual shooting distance
between fighter plane and target. This was necessary
So that ejection would take place shortly before
reaching the target,areaq For the first phase, the
Soviets said they did not want anything like this;
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they only wanted to be sure of a high-temperature
tehibited-ejection process to test the function ef
tag thing*
The Germans were-required to use a high-temperature
tape already on handy which Was rather well designed
ail constructed. It was not directly ignited by '
the rocket charge itself. This would have caused
detonation especially at extremely low temperataresp.
Wain the ease of a misfire, the ejection process
would have started simultaneously* This special
.fnee which was on hand in the MR worked in Suck
a way that, due to the gas pressure tuside* a small
Plunger was activated? The plUnger struck the
twee cap and the fuse cap an the inside ignited the
high-temperature charge. If a misfire happened new,
nothing could go wrong*. Only the gases from the
fuse 0413,whichsera practically haxmlessjnot the
pocket chamber gasesscould enter the front part of
the ogivq. This fuse was supposed to have Proven
its merits previously in other fabrications. This
fuse ,as then incorporated anqsjoining the fusepial
cylindrical pipe was pr@vided Which reached practically
to the front of the magazine. On the inside of
this, cylinder, another tubesheld in this position
by a shear pinjwas inserted Without special sealing.
Au ordinary steel plug was provided at the end of
this Pipe which provided for tightening of the bail-
eihaPed magazine housing through a half-round-headed
scree. The tightening was done in such a manner
that the front row and the back row of the taWthwl
mine columns were mounted into the space around the
eitbustichamber. Then the egive projectiles were
pit-in by:tems CI mounting aid and held in place
by I rubber band or a paper strip and than
the hell was pushed over the assembly. At the teont they
J'ad a reinforcement ring: so that the projectile*
Were arrested there* The projectiles in tht, trent
part had to be placed at an angle; otherwis4 they
W01114 dered each other because of their
told ' 1 assemblies. Therefore, a lager
4iame 50 mm. was' formed* This 5040*, was
Wen through the ejecting pipe. The projectiles
are the same size in front as in the back. In '
Other words, they are interchangeable. The in-
Bide, ring of the combustion chamber wee a pressed
deirdrawn sheet-metal ring, which was connected
Wit the chamber cover by spot welding. This
ring served for centering purposes while the actual
a04041ne bell contained a bracing ring which in
itself insured centering to the previously-nen-
timed sheet-metal ring and then spotwelded to the
okaaber. In this manner@ good centering was
4OSUred. The tall assembly consisted of a deep-
draWn,sheetthinetal body which was closed off at the
frOmt. by a sheet-metal cover. This sheet-metal
cover was :9re3sed over the body. It was welded
at.4he'COUfleetion at the end of the rocket where
it wag joined with the combustion chamber* In
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this manner, the whole thing was firm4 connected.
Per a seal, a small groove with a rubber band fitted
in weR used so that no outside moisture could enter.
It was Pushed on in mounting and everything was tightened
by a aerew.I
The short mounts were used which, according to German
experience, proved much more advantageous where accuragy
of hit was a factor. At the front of the mount wee
a buttez sad, on the back side, two guard -studs. MA
guard studs were mounted even with the rear oenterEng
So that necessary stiffness of the magazine housing
was insured. Am a propelling charge in the rocket,
a three-channel powder of prismatio-pressed pieces
Was used which left small powder rests in the form
of a triangular ,wedge (gusset). Theoretically a
large amount of the powder was supposed to have beim
left over. Howeverp experiments on the test stand
proved that these supposed 'left-overs" had also burned.
It cannot be assumed thatylf these powder wleft-overs*
Were not burned and were discharged through the jet .
nozzle, they would in any way damage the aircraft.
It mould have been better to avoid these wedges
altogether, but they were available in the above form
and the Soviets insisted they be used. However,
according to former German experience, they had to
deal with these powder left-avers quite often: How
ever,, the pilot was never really bothered with this
problem. The magazine bodies were rolled from 2 mm.
sheet metal, with a longitudinal welding seam, and the
head was pressed on. It was planned to deep-draw the
head later on, but these were technological things
about which the Germans did not bother. The stabilizing
wings were about 620 mm.
cou.La nave Peen somewnat smaller or larger. The
Germans always pointed out that, without wind tunnel
tests, such things cannot be tied down emphatically.
It was then required that aerodynamic calculationT be
carried out.
10, The outer form had to be tested In the wind tunnel:
Necessary values were reported to the Germans. After
they knew what the CA, CM, and OW values were, it
was possible to figure the neutral point and possibly
find a suitable design which could have possibly
carried even more projectiles. There is a possibility
that dome of the projectiles had been moved toward the
rear. However, the center of gravity would have
moved quite a bit towards the rear: This questiaa
could have only been cleared up through wind tunnel
tests. Wind tunnel testa were mAdo, with -ellp magazine,
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ifermans were told only that the mines were all right.
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1.1* The Soviets were not ignite satisfied with the design
as Ouch. The rocket velocity increase caused by the
'repelling force was to have reached approximately
,50,misec. with this design. They indeed wanted a,
performance of 450 moisec.) still better yet, 520 milsee.
This regnirmaent naturally was not easily realized
25X1 any more with this caliber. The last requirements'
25X1 I pwere ao adjusted that a greater number ox.
es should have been incorporated. The Germano
worked out several projects where the total number of
mines was between 54 and 60 pieces. Here they had
larger rocket chambers and, in. one case, chambers of
240 mm. With the 240-mm. rocket chambers', the Germans
Still did not achieve any velocity increase but only the
fact that the ahembers could accom=date 60 projectiles. The
enlargement of the rocket-propelling charger and the
outside diameter of the rocket chamber of 240 mm, made
it possible to accommodate more projectiles because
of the increased length so that three rows at 18 each
made 54 mines in the cylindrical part. Six mines in
the ogive made a total number of 60 small projedtiles.
With all thips the rocket velocity remained in. the SEM
range. Because of this, the requirement was handed
down to increase performance to reach at least 420 to
450 mWsec, Other designs were worked on which were
260 or 280 mm. The
Principle of the ring magazine remained, however,
which has the following advantages: (a) shorter
length, meaning easy handling and loading on the plane
itself, and (b) trouble-free ejection of the pro-
jectiles from the magazine. A rotation of the whole
rocket was again done by interference Atrillp during
the teat period. I V In the
later model, the entire stabilizing surraces.were
aligned to a slant at a all angle of about two-three
ees so that the necessary revolutions were insured.
Oe page ?3j. The theoretical path of flight
Galt:Inlet/ens showed, however, that it was more sdven-
tageons to let a component of the impulse become
effective in tangential direction. This caused a
noticeable rotation directly after release from the
plane. Releasing disturbances, occurring from ?time
to time, caused by a swinging of the plane or
other disturbances of the rockets or possibly inter-
ference from a nearby rocket* etc., were held to a .
minimum in this manner. In such a case, it *as favorable
to have a noticeable rotation immediately Upon re-
lease. The rotation resulted in a helicoidal path
Of flight reducing a one-sided disturbance of the
rocket to about one-third of the original value.
The Germans carried out several ballistic caleulatiOns
which resulted in the optimal number of rotations.
12. Releasing disturbances were also taken into consideration,
resulting in a favorable opening angle too wide for
the projectiles, This means that the rocket would have
to get Tory close to target if the projectiles open
with such a wide angle. This caused certain diffi-
eulties because small mistakes in distance estimation
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refult in sizeable diffetenees In the target area,
Vixes,bad scatter had to be taken into consideration*
The GerMans were therefore interested in effecting
ejection at a greater distance* At greater distances,
they were not dependent upon use of a projectile with
ogival fuse, Such an ogival fuse was available but
=Suited or the Purpose* The blocking of the fuse
had to Coeur through rotation, The Germans were
able to use A fuse which was rotation-activated like
4 normal artillery fuse, and armed by the spin of the
shall, This fuse was given a lighter weight-spring
suspension to open at a small number of rotations,
The rotations of the mines were obtained through inter-
10014ng of the folding tail assembly of the Projectile
itself because the wings were Slightly slanted, The
necessary number of rotations was obtained without
any great difficulty and activation of the fuse was .
assured during the course of flight* Such a fuse ? ?
had a liquidation, igeof a disintegratingfarrangement,
so that the projectiles would not cause greater harm :
on the ground thelatc the enemy planes, The liquidator
was necessary, The Germans were told to write the
technical soecifioations for it. I
The aermans were told o however, not to use such a
fume for the first experiments but to use Fuse 66 (fan
igniter) r which they .
incorporatea into tne project moiniya. Basically
this was possible* However, the blunt shape caused
such a quick velocity decrease of the projectiles
that an Ineffectiveness of the projectile in the
bottle range appeared imminent, because the necessarY
final speed Was not sufficient to penetrate the
fuSelage of the plane. It was not necessary to
penetrate the armored-plate behina the fuselage be-
cause the ignition delay was adjusted to approxi-
mately 20 cm, The detonation occurred before the
armor plate was reached and caused considerable
damage to the fuselage of the plane, so much se that
ftrther flight was impossible,
33. The action distance of 800-1000 m., for which this
equipment was originally designed, could atill be
Obtained, The Germans were not forced to open the
magazine ,Which was not immediately emptied atter
'Combustion of the rocket-propelling Charge, but a
/0.1411s1Usl distance of 0,1 seoqp (sic) was covered before
ejection was possible* However, in many instances,
the'distahee had to be increased somewhat so that
the projectile was close enough to the target, Hare
it opened up and from then on the projectiles resumed
their own path of flight,
14. The mine* themselves are without a propellent, On
different occasions, the Soviets required the Germans
to Use,neetet projectiles there, too. However, the
GOTmauS did not spend much time on this proied4 because
(1) thvaaCked the time for it, and (2) because such
a. project did not look promising to them, Difficulties
were. to be expected in igniting the small projectiles
with certainty* It was far more advantageous in this
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case to to keep the large projectile with its greater
-ballistic coefficient and let it continue it flight
and to nsleage the indiiidtal easily?manufactured projectiles
close to the target. Upon Soviet reqeest, variations
were worked omovhich made it possible to tighten from
the back each of the 16 columns separately with
a special tightening device so that the projectiles
were fitted in rattle?free. In my opinion, this was
in unjustified additional expenditure, It was easier
to adjust them by cardboard enclosures at the time of
initallation. It was cheaper and did not require as
much additional weight. However, it was desired and
I delivered one magazine with an adjusting device and
additional weight, As previously msntioned, several
variations were worked out.
RIGS PRIORITY PLACED OR PROJECT BY SOVIETS
*14. Apparently much Importance was placed upon the entire
pkeject. This was also shown by the fact thav4on
several occasions active military personnel conferred
with the eermans, This proved conclusively that
active groups were counting on such a missile. I
'this design in
-particular presents an extremely effective weapon
in the fight against larger bomber squadrons or groups
of several heedred planes. The reason that a bomber
group is such a likely target is thats as a group,
it ie limited in its maneuverability. It is almost
IPPoseible to maneuver in it and one is forced to
more or less maintain a given course, However, with
such 4 glide missiles there are no correction
poesibilities during the flight, and the target can
only be reached if this target cannot turn about.
16. The Soviets said very often what is the use, if
today a single very fast plane appears carrying an
atom bomb? What can this missile do in such a cape?
The Germans said it was best then to remain on the ,
ground, that it was silly to shoot against such a
plane,as it could not be hit anyway,
17. It is also to be mentioned here that the Germane
designed rocket?propelling parts with all ballistic
calculations about flight characteristics and
fabricated them, too, The Germaas provided a tuYere
plate in the place of a central jet with a nozzle
scroll 'consisting of several single nozzles, Theme
, nozzle eprolle-had 'EU advantage inasmuch ao they nide
it possible to dispense with the tangential nozzlep.
The Germans could provide these nozzles with a small:
slanting angle, seen in axial direction,and produced
a tangential component with this, Several variations
were intended, one of which had the mouth of the
venturi out off at a certain angle. The jet axis,
however, remained completely parallel to the main
axis of the rocket; only the mouth was out at an
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angle to obtain a small spinning effect. The Gamma
are not sure how close this thing came up to the exPects-
tions*
The projectiles were proviaea
With a detonator. Single parts, of course, could not
be seen, but it was _Possible to see the rocket fired)
and suddenly, at a distance from the rocket, a number
Of single bursting -points were noticed*
any var p-
tione had been built. Possibly gust as m: Ay variations
were built as, were designed,- Some of them had approxil!*..
mately 24 bursting points; other types were present
With about 50 bursts, . lsome had as many
Am To ny. AO burata. There were so maavl
25X1 distinct 1j
differences could be noted, because le mines apparently
continued their flight on a clean pitch circle aad were
not distributed over a large area after a ragged flight*
There were pronounced rings over which these bursting
points were distributed with rather equal distances*
It was also noted that there were designs with diff-
erent scrolls in each, Here, for example, were
two scrolls because the ogival mines run on a small
cone slope whereas the ring projectiles were in the
outside scroll. The Germane also had designs which
carried another intermediate stage to adjust them
as much as possible to the ogivel
such figures in the Sky Where three scrolls were one
in the other* Apparently these projects were propelled
by several systems because,if the Soviets decide to
Wild a large number of one piece of equipment, they
consider it quite urgent. For previous developments,
great sums of money were seldom invested. Usually
pieces numbered from 2-5 because they wanted to
test the overall function only. For subsequent ex-
periments? the Soviets may have ordered 15-20 pieces;
but,whenever they deciiled to invest great sums of
money, it was deemeCtOod assurance for materialization
? must have existed. On the other hand, these things were
started right away with rather large expenditures*
19, Regarding the ejection process, the ejection cylinder
located in the head in the ogive,with the pipe plunger
contained therein, only accommodated a small ejection
Charge of approximately 30 g. black powder (composition
unknown). This ejection charge with a larger pres-
sure in-the neighborhood of 100 kg./cm?
25X1 produced-such a
pressure that the thrust was strong enough to shear
throggh the shear pia at the top (indicated on tbe
drawing)* This pressure fran the plunger was then
transferred to the entire housing, the housing accel-
erated towards the front; while,through the same
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impulse, the inner rocket part, together with stabiliser*
wag retarded. The ejection process for the PreJeetileS,
accommodated In the ring magazine, was completely
trotblo-free. They could not leave their positions
'Until the housing was pushsa off. The rotation pre-
sent permitted the mines to emerge radially without
any greater releasing disturbances and Pent them On
their WAY after the tail assembly wings opened up.
jSpecial aerodynamic help to open the Wngs was not.
neoeseary. The rocket rotation had previonalY been
tr*naferred to the mine bodies. This rotation Was
sufficient to open up the tail assembly wings in
radial direction. Once they opened up radially, the
Upset pressure on the interference strips was
Anfficient to move them to their final position,
00 'hat the projectiles could continue their flight
with the Winge:Angled in an arrow-shape setting.
the'Vrojeetil-es.in the front part Were so constructed
that, after election, they possessed the tendency
through their inertia to remain relatively implaPe4
.he rocket chamber WAS accelerated forward so that
the specifically lighter-weight housing was Zeroed
Several meters ahead of the actual projectile
After u'short period of time. The Germans cOnduoted
ebtPutations of how great this speed had to be
.ocmi4etely tn offset 't,he dapping by velocity pressure
.)and to expand several meters with safety, the
reason being that the projectiles lying in between
0044 be ejected without running the danger Of being
pulled back into the housing while the housing .
wag -being, retarded by the air pressure.- All these
things had been theoretically considered* The
.00.X.Mans were not told ha* they worked out innirealitru
.bat what they 'saw In the Sky was not unfavorable.
e Iags l'51j nrst is the ?dame of the
ane; then point-oX release, from the control
.4'44 ,of the plane. Next is the period of combustion.
of 'abproximately 0.85 seconds. The heavier-lreight'.
types naturally have a somewhat longer period
..of.0101.41PtiOnp of about 1.2 seconds, and some riven ?
with longer combustion periods. After the end of
the combustion period, after about 0.1 seconds, the
WS-technical fuse started its function. This
1014 ?the Shortest period of delay that is practical -
.?possible. In reality, it was desirable for this
21444 of time, between theend of combustion of
ii. rocket and .ejection of the mines to be several
000744o, 130 that ejection process could have been .
lidhed ShOrtly before rftaching the actual'
Point*. if the target point was passed,
epnda thereafter, the detonator would auto,-
? 4044.17 4104Arge so that no loaded missiles
004k-roe& the grounds.
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Legend to page 13
Translation oe Parts
1. liquidation
2. Target Level
3* Ejection of Projectiles
4, Ali Of Combustion
50 Launching Point
6, Plight Path of 6 Projectiles from Ogive
70 /light Path of 2x16 from Ring Magazine
8, plug magazine Rocket for Bomber Formations from Fighter
Planes
Information Radlatai_ka.10;1210,sa
Arppelling Charge -.Nitroglycerine Powder. 6 Profile
Otieks+ 1 Powder Tube 630'48/16
Weight of Powder Waarge
Total Impulse
Combustion Period
Nominal Gas Pressure
'leading Dimensions*
Outside Diameter of Combustion Chamber
Ontsido Diameter of Ring Magazine
Total %length of Rocket
Expansion of Tail Assembly
Number of Projectiles in Ogive
Number of projectiles luting Magazine
26.
? Total
24 kg.
g 4600 kg,/sec,
f 0.65 see._ ,,
p 120 ki./cmto
220 sm.
325m,
1475 nolo
620 Mal
6 Pieces
places
pieces
25X1
ftights Rocket Chamber with Jet Approximately 31 kg.
Charge 24 kg.
Projectiles. 38 Pieoes at Approximately
1.1 kg. each 42 kg.
Magazine, Ejection Cylinder. Stabilizer,
etc.?kg.
Total Weight Approximately 130F kg.
Acceleration of Speed by Rocket, Nominally 350 m,./soc.
Sucoee&irLR
Outside Diameter of Combustion Chamber 240 mmo
Outside Diameter of Ring Magazine 340 as.
Number of Projectiles in Ogive 6 pieces
Number of Projectiles in Ring Magazine 3x18 apieces
Total 1.11 pieces
Weight of Rocket Chamber 40 kg.
"Wight of Charge 31 kg.
Weight of the 60 Projectiles 66 kg.
Magazineo etc* 8 kg.
kg.
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Legend_ to page 13 ( cont inued)
)104.1.3241 Impusla Appro=kmately 5900 kg.jsec?
Aoceleration. of Speed -of Rocket 330 malice,
Ite0ireptents for Further Variations
A0o4eration of Speed Through Rocket 450 nr/see?
Total Number ot Projectiles 45 p floes
Igniter for Xj.ection Adjustable
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'legend tc, page 16
translation Projectile for Airborne Rocket
Variation I
Nesse Pape; highly sensitive with 0,5 110/sec. ignition
lag and disintegrating device (liquidator)
Centrifugally armed by rotation ot projectiles
?implosive OhargeS TIZNIThoTOVENS 4 TNTEMINYElaiTNI?
lanuLEPPI (50/50)
Addition of Aluminum orPyrosculiffil
Tail Assembly of 4 Wings (Stiff Tail Assembly
ris.1)
Sstimated Weights;
,lmplosive
0?420
proleotile Housing and Stabilizer
4%430 kg,
21, Nose louse (Var. I)
0,230 kg,
Total. Weight Approx.
1.100 kg.
Variation. I;
Nose Puses ,Neconetruction of Impact Generator Pus* (66)
Due to bad Aerodynamic shapingf., lowering
of .range of effectiveness -
Without."Itiquidator
Bmplosive Charge and. Tail Assembly same as Var??
but without orossing
tot Greater thaA Tar, I
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