FIRST STEPS TOWARD SPACE - Smithsonian Institution Libraries

NUMBER 10 191
FIGURE 9.—Indicating sensor for remote pickup of pressure.
control panel on a trailer were organized on the
launching range for preparation of rockets for
starting and for effecting launching.
After these measures had been undertaken,
within a short time drawings for manufacturing
R-03 and R-06 rockets were issued, the models
underwent wind-tunnel tests in the Central Institute
of Aerohydrodynamics (TSAGI), a series of
the rockets were manufactured, and required tests
were carried out on the test stand. A general view
of the final version of the R-03 rocket, and of the
M-3 engine for this rocket, is given in Figure 17.
The main characteristics of the rocket were:
diameter, 200 mm; length, 2600 mm; launching
weight, 34 kg; fuel weight, 12.5 kg; thrust, 120 kg;
time of engine operation, 21 sec; flight range,
8500 m.
Those of the R-06 rocket did not differ much
from the parameters established in Osoaviakhim.
Changes made in the design of this R-06 rocket,
when a series was manufactured, were limited to
replacement of starting equipment and introduction
of two-step starting of the engine, instead of a
prolonged one-step starting.
From early 1937 to February 1938, ten R-03
rockets and nine R-06 rockets were launched (see
Figure 18) at different angles to the horizon. Inflight
stability of the rocket depended greatly on
the speed and direction of the wind. Maximum
inclined flight range reached by the R-03 was
about 6 km, by the R-06, about 5 km.
Work on Improving the Rocket Design
Beginning in 1936, together with work on the
R-03 and R-06 rockets at KB-7, research and
development was undertaken on (1) engines and
fuel, and (2) providing in-flight stability for rockets.
FIGURE 10.—Tank suspension on dynamometer (pressure
pickup) for remote determination of lox weight in tank during
engine testing: 1, load cell; 2, tank containing lox.
ENGINES AND FUEL
Study of different ignition systems for combustible
mixtures proved that the most reliable
system was to use a multispark plug mounted on a
pipe through which hydrogen was supplied to the
chamber during launching. This device was inserted
into the chamber from the side of the
nozzle.
Experiments on finding thermal-protective coatings
for nozzle and chamber were carried out in
cooperation with the Kharkov Refractory Insti-
a &
FIGURE 11.—Rotameter circuit for remote measurement of
fuel flow rate, showing (right) connection of unit for telemetry
transmission of rotameter readings: 1, pickup; 2, selsyn.