FIRST STEPS TOWARD SPACE - Smithsonian Institution Libraries
FIRST STEPS TOWARD SPACE - Smithsonian Institution Libraries
FIRST STEPS TOWARD SPACE - Smithsonian Institution Libraries
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196 SMITHSONIAN ANNALS OF FLIGHT<br />
FIGURE 19.—R-04 liquid-propellant spinning rocket: 1,<br />
powder charges for additional spinning of rocket during<br />
flight; 2, fuel tank; 3, oxidizer tank; 4, engine.<br />
empennage was designed and developed to provide<br />
in-flight stability by imparting high speeds to the<br />
rocket on escape from the launching frame. At the<br />
same time various techniques of parachute opening<br />
were tested. Six vertical launchings of the R-07<br />
rocket were effected. These showed that, with adequate<br />
selection of the empennage, when the rocket<br />
left the launching frame at a speed not less than<br />
40-50 m/sec it was possible to ensure satisfactory<br />
in-flight stability of the rocket.<br />
The following methods of parachute opening<br />
were tested at the same time on the R-07m rocket:<br />
1, By firing a Bickford fuse with an incandescent<br />
filament at launching (opening mechanism activated<br />
after a fixed time lapse); 2, by firing Bickford fuse<br />
from a firing pin with a blasting cap when the<br />
rocket was boosted during launching (parachute<br />
opened after a fired time lapse); and 3, by means of<br />
a gyroscope which closed the fuse igniter contact<br />
when the rocket deflected 50° from the vertical<br />
(the opening depended on the position of the<br />
rocket). The last method proved to be the most<br />
reliable for opening the parachute after the rocket<br />
reached the maximum altitude.<br />
removable cap<br />
parachute head<br />
Sf<br />
manometer<br />
signaling device<br />
oxygen tank<br />
gyroscope<br />
alcohol tank<br />
operating<br />
alcohol valve<br />
engine<br />
section along SD<br />
oxygen starter<br />
valve<br />
oxygen<br />
operating<br />
valve<br />
section along AB<br />
alcohol<br />
starter valve<br />
FIGURE 20.—ANIR-5 rocket (with gyroscope rigidly connected<br />
to rocket frame).<br />
A rocket with a combine engine (suggested by<br />
V.S. Zuyev) was one of the variants of a liquidpropellant-engine<br />
rocket having increased speeds on<br />
emergence from the launching device. The Ml7<br />
engine (Figure 21) was designed in KB-7 and developed<br />
on the test stand. First a powder grain<br />
burned out in the engine. At the same time plugs<br />
covering the outlet of the atomizers burned out. On<br />
completion of the powder-grain burning, when the<br />
supply pressure of liquid propellants exceeded the<br />
pressure in the chamber, the engine changed from<br />
solid-propellant to liquid-propellant operation. The<br />
wooden grid which earlier supported the powder<br />
grain burned out during the liquid-propellant<br />
phase.<br />
One project to ensure in-flight stability of the<br />
rocket involved monitoring the rocket by means of<br />
a projected infrared beam. Stability was effected by<br />
means of a photoelectric device (as a sensor)<br />
mounted on the rocket and an actuating mechanism<br />
consisted of four microthrusters creating the required<br />
thrust in response to operation of the photoelectric<br />
device (named ENIR-7).<br />
Under an assignment from DB-7, UFTI (R.N.
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