GERMAN VENGEANCE WEAPON, V-2
THE ROCKET BOMB
by authority erf AG of S, G-2, WDGS
UlftSsUication cnanged rc	\.ia .<
RESTRICTS
Capt. Inf
WAR DEPARTMENT
WAR DEPARTMENT GENERAL STAF - MILITARY INTELLIGENCE DIVISION G2
WASHINGTON 25. D.C
Кы/й Vi'->U*
"P О	111 43.0 I
By authority A.C.^Of S.^G-2
Pate.
GERMAN УЖЕАПСЕ WAPONX_ V-2
(The Rocket Bomb)
Development of в long range rocket has been on a priority basis with
German scientists for at least 5 years. The result of their intensive efforts
became apparent last September when the first rocket bomb, the so-called V-2
(or experimental model A-h), was launched against the United Kingdom.
Just as the 1908 automobile and the 1916 tank were forerunners of bigger
and better models, so today the I9UI4 rockets may be termed forerunners of
bigger and better types—Instruments which in the future may revolutionise
the science of warfare or the mode of transport in eras of peace. Today,
however, present knowledge of fuels imposes definite limitations on the distance
and speed of rockets. Until more potent fuels are developed and design is
radically altered, the performance of rockets is not likely to become unduly
spectacular over that now known.
GENERAL CHARACTERISTICS
The V-2 is a cylindrical instrument, V; feet 10 Inches in length and 5
feet 6 inches maximal diameter, having six sections as follows: (1) war
head 5 feet 7 inches; (2) radio compartment, Ji feet 7v inches; (3) liquid
oxygen tank, 9 feet 11 inches; (U) alcohol tank, 9 feet 11 inches; (M
hydrogen peroxide turbine unit and two pumps for the liquid oxygen and alcohol
plus other control equipment 7 feet 2 inches; and (6) combustion chamber, 5
feet. Four large external fins are located at the rear.
•The war head weighs 2,000 pounds of which 1,600 pounds is aluminumized
TNT explosive. The blast effect extending about one-fourth mile, is equivalent
to that of the V-l flying bomb. More severe damage, however, occurs in the
immediate' vicinity of the point of impact owing to the mass of the projectile
and its tremendous striking velocity which is approximately 3,700 feet per
second. The war head penetrates about one-half its length before detonating;
the explosion forming a crater about 3? feet in diameter and 15 feet deep.
RADIO COMPARTMENT
The radio compartment is divided equally into four sections by means of
radial olywood sheets This compartment houses the following equipment: (1)
Type E-230 receiver, also used in the German glide bombs He-293 and FxlUOQ, to
receive control signals for the elevators and ailerons; (2) a combination re-
ceiver transmitter used to retransmit a received signal on a different
frequency; (3) a 12-tvbe receiver;, transformers, and a panel mounting 12
relays; and (U) a modulator and transmitter.	,r n ~ r
fi *' Г ' 1	1 *| 4
The function of each of the radio sect 10^1	bken clearly . .
determined. Section one т>гг>ЬяЬ1у_сопЬго1я the
section two is suitable for measurement of slant range. Equipment in section
three is believed to control the elevator air vanes, the fuel cut-off, and an
over-riding control for section one, as well as such miscellaneous functions as
arming the var head. Section four hbuses equipment which might be exnected to
be used on the ground for transmitting to section three; its presence in the
projectile itself suggests two-way coded communication.
Recent rockets have contained equipment which makes them capable of
complete self-guidance, without any use of radio, to a predetermined range and
azimuth and over a preselected trajectory during the burning period. However,
it is believed that the existing radio equipment in the projectile is used to
make finer adjustments by means of radio-monitored gyros.
FUEL
The rocket obtains Its propulsive power from liquid oxygen and alcohol.
The xei^ht of fuels necessary to give an average range of 200 miles totals
about 9г tons and is consumed in 7^ seconds. As the alcohol burns, the liquid
oxygen furnishes the necessary accessory for combustion. Both liquids are fed
separately by turbine pumps into 18 jets which open into the combustion
chamber. The turbine pumps are operated by exhaust gases from a small
combustion daamber using hydrogen peroxide and c&lcium permanganate as fuels.
COMBUSTION CHAMBER
The jets spray the two fuels evenly into the front of the combustion
chamber. The chamber has two walls extending almost its entire length. A
portion of the alcohol, fed into the rear between the Inner and outer walls,
flows to the front where it combines with the oxygen in the jets. This has
the dual effect of partly cooling the chamber and preheating the alcohol.
Through four annular rings distributed along the entire length of the chamber,
alcohol is injected to provide additional cooling for the chamber.
CONTROLS
Control of the rocket is exercised by vanes whose surfaces act upon
both the air-stream and the exhaust-stream. There are four large external
fins each having a small control vane on its outer rear portion. Each
external control vane Is connected by a chain and sprocket to a corresponding
internal control vane In the exhaust-stream causing each pair to act as a unit.
Steering is accomplished internally by means of azimuth and pitch gyros.
The radio eouipment may be used to monitor the gyros, to determine the position
and velocity, and to cut off the fuel at the appropriate time. Complete
control of the rocket must be accomplished during the burning time which is
about 7U seconds for a 200 mile range. Beyond that''tim^ the ^.ntbrnal
controls have no effect and only a slight effect may be expected from thq -
external controls.
	' 'WJECTORY
L 4	л
The trajectory of the V-2 fs predetermined before firing The projectile
is launched vertically from a special firing table. Its initial speed is
slow but increases rapdily. At the end of the burning time of 7U seconds, a
maximum speed of some 3,000 feet per second has been attained at a height of 19
miles. At this point, 600,000 horsepower 5s developed. The maximum altitude
for a 200 mile range is 58 miles and a time of flight of minutes. Theoreti-
cally the calculated maximum range is 230 miles although the maximum recorded
thus far is 210 miles. At its maximum altitude, the speed of the rocket is
3,800 feet per second increasing on its downward path to 5,300 feet per
second owing to lack of air resistance in the stratosphere. When the rocket
reaches the lower atmosphere where air density is greater, the speed decelerates
to a striking velocity of about 3,700 feet per second.
LAUNCHING
Unlike the V-l, the V-2 requires only a very simple launching mechanism
and site. The 'launching equipment is portable, consisting only of a metal
table with a water sprayer for cooling- This may be set upon any hard surface
such as a paved road. One site discovered in France, although undoubtedly
never used, was located on a leveled area having a group of concrete slabs
emplaced in a manner apparently Intended to aid the correct and rapid arrange-
ment of the various vehicles required for the fueling and preparation of the
projectile. The prepared sites in France were found to be constructed on, or
level with, existing tree-lined roads making them easy to camouflage and difficult
to detect from the air except when actually in use.
The function of the so-called "large sites" along the French coast that
were originally believed connected with the rocket bombs still remains unknown.
It is thought that one was intended for the manufacture of hydrogen peroxide,
previously noted as employed in the rocket. The construction of the others
had not progressed sufficiently to determine their purpose.
The projectile is complete, minus the fuels, when brought to the launching
site. After it is placed in firing position, the various fuels are pumped into
their respective containers within the weapon. Separate vehicles carry the
liquid oxygen, alcohol, and hydrogen peroxide to the rocket.
In flight, the rocket is accompanied by a tail of fire and leaves a vapor
trail that resolves into a slightly persistent white smoke. This makes it
possible for Allied air crews to sight the rocket and make a report of its flight.
For the Assistant Chief of Staff, G-2:
Chief,
б////'
R. A. OSMUN, 4A/e^
Brigadier General,
Military Intelligence Service.
£AR6£ ЯОС££Г (V-2J/>ЛА/££77££
Sectionalized drawing showing arrangement of interior. Small insert
photo below words 1 'Radio Compartment” shows rocket leaving tail of
flame as it rises from the earth after launching.
fl 1	. '
MOUNT FOR LARGE ROCKETS
(V-2)
<	2.5 M	.
THREAD DEVICE FOR RAISING
AND LOWERING THE TABLE
FEET INCORPORATE BALL JOINT
FOR ELEVATING
MOUNTING RING
AND SELF-LEVELLING DEVICE
FIRING TABLE
SPRAY UNIT
MOUNTED UNDER TABLE
WATER USED TO COOL TABLE
ROCKET TRAJECTORY
ALTITUDE IN MILES
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