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Preliminary and main stage
worked fine
but the rocket flight did not proceeded correctly
rising to a height only 1100 meters
it fell to 12 kilometers from the
start
at takeoff. the rocket
rotates
around its axis
cranking of the rockets caused
the system Failure
and lost the control
the rocket flew with
51 degrees angle to the directrix of shooting.
As a result of improper
takeoff
cable mast thrown from the starting place
for 30 meters to one side
and the launch pad for 19 meters to another
side
Cables connected with the mast was thrown out of the channel
in the fall of explosion created
crater 14 meters
at depth
up to three meters
twenty-second twenty-third
and twenty-fourth of September
during prelaunch
of missile Number 3 tests
identified a number of defects
in devices and rocket ground
power
one of them was instability
in "zenith" contacts detachable sleeves
electrical command's signals
transferred from the ground to rocket
by two 108
wires cables
each 81 meters long
connector
consists of two
parts are connected by split
clutch
in one half coupling
with 104 pin socket
In another 104 pin
when two halves
sleeves connects together pins going into receptors
create socket contact
split halves couplings with pin sockets were
molded poorly
insulating mass was not melted properly
and pins by insertion into the slots
squeezed insulating mass
then the contact was filled with insulation mass from socket
which led to the instability
of contacts
to eliminate instability
Connector have been removed and cables
soldered directly
September 25 Rocket Number 3
launch did not take place
Preliminary stage will not run
but Wood's alloy was early
melted
ignition device fired
and through the additional cooling
nozzle's zone
into the combustion chamber poured alcohol
there was a fire. which was quickly put out
at the second attempt launch missile number 3
command
drainage was sussesfull
ignition
executed successfully
On preliminary stage normally
depressurized
main oxygen valve drops pressure
and preliminary
oxygen valve openes and the liquid
oxygen enters through nozzles in
combustion chamber
but on a rocket Number 3 valve
did not opened
and oxygen did not entered in the chamber
And alcohol penetrated through additional
cooling nozzle belt
burned in the chamber
in the study the reasons for the failure
found that on the walls
of compensator of oxygen valve
was left lubricant oil
under the influence liquid oxygen
frozen oil
and the movement of the rod of the valve
preliminary stage was
impossible/blocked
seventh of October launch of a rocket Number 5 was unsuccessful
because of the same reason
6 attempts was made and time were spent
to try to open the valve
all of them ended in a failure
September 27 Rocket Number 8 ignition were successful
Preliminary
stage passed
then on command "main stage"
engine stalled
on preliminary
stage
and command sequence's circuit
returned to intial position
Start scheme is designed such than on failing
command inside any device or in main
electrical circuit
than
control system resets to its original position
as demonstrated on research of the failure on
Rocket Number 8 reson for reset
was due
because of the firing
switch / connector
from the first position to fourth
commands passed over firing switch
system executed command
but in the fifth position with the command
"preliminary stage" in progress because of
instability in contact
switch circuit was disconnected
and the command has not passed
and reset to its original
position
Lasted 20 minutes fire
burned Regulators and
electrics
located in the tail of the rocket
Rocket No. 8 on removed from start position
there was no more launch that rocket
and it was sent for repair
October eleventh made
secondary attempt to launch missile Number 5
Ignition was successful
but preliminary stage was not and
Return (reset) into the home position
in a few hours Attempting to re-start
repeated couple hours later without success
as shown conducted
research
launch did not take place because of
short
"break-OFF" in the "lift-off" circuits
the "loft-off" contact at entry
of the preliminary stages
shut off power of "onboard" instruments
(instruments) functionality that needs to begin only after
separation of the missile from the launch pad
"lift-off" contact located in the stabilizer
of the rocket
When the rocket is stays on the table
"lift-off" switch is ON
and these devices are switched off
When at the start Rocket lifts off
from the launch table
springy contacts
disconnects and "lift-off" switch to "OFF" state
and dependent relays turns-on onboard
devices
On eleventh of October
on attempt to launch rocket number 5
after engine's ignitions
at preliminary stages
accompanied by strong vibration
"lift off" switch
consequently
by hundredths of a second has opened (OFF position)
early
that was enough for "lift-off"
relay
to lost the power and to reset the circuit
to home position
October 16
launch of the rocket number two
did not take place because of short time
disconnect in "lift-off" contact
caused by vibration from the strong
claps at launch time.
twenty-fifth October of the same
reason
did not take place launch of missile number 12
to eliminate bounce effect
on remaining missiles
"lift-off" switch was replaced
by six-pole plug
possessing for these conditions necessary vibration resistance
Lack of testing of the missile and its parts at Development Departments as well as the poor quality of manufacture of individual parts and components. have led to failure of numerous missile's tests. Analizing of faults. fixing missiles and eliminating defects. as shown in the film. on testing range took a lot of time and efforts that noticeably lengthened tests.
On October 10. launch the rocket number 1
lift-off was normal
according to information received from the U-2 was found
place where the missile landed
team of surveyors
goes by U-2 plains for precise
determination of its location and
measurement of a crater
rocket flew 288 kilometers
and deviated left by 5
kilometers
on the site of the crash
crater a diameter of 19 meters
and a depth of four meters
13th October launch of rocket number 9 lift-off was normal
rocket flew 242 kilometers
and away to the left 5.14 km
October 25 The missile Number 6
twenty-first October launch
of a rocket Number 6 was successful missile
flew 257 kilometers and deviated
left at 2.5
kilometers
On October 23. launch of the rocket number 10
launch of the rocket number 10
after elimination defects in the engine
detected day before
was normal
but the cable mast
as well as on previous launch
was broken
in slow-motion is seen. The cable
mast breaks
when the rocket climbed over the launch table
to a height of 12-15 meters
rocket flew 254.6 kilometers
and away to the left
to 0.49
kilometers
Here's a shot of the same moment with a
close
in the future these position
To avoid problem
the cable mast was mounted at a smaller angle to the
the flow of exhaust gases
fixes and elimination of defects
shown in film and a number of other defects
allowed to make a
some normal launches
November 1 launch number 3 rocket flew 284 kilometers
and away to the left _1.3 kilometers
3rd November launch Number 12
rocket flew 271.5 kilometers
and away to the left _2.3
kilometers
On November 4 launch of number 2
rocket flew 208 5 kilometers
and away to the left of 0.15 kilometers
November 5 launch number 11
rocket flew 253 kilometers
and deviated to the left _1.4
kilometers
Testing of R-1 of the first series shown that our industry and design. Despite a number of serious shortcomings and failures, partially exposed by tests. Achieved primarily goal - to build a missile like the V-2 with Soviet(domestic) materials.