R-1 / SS-1 SCUNNER - Design
The main parts of the missile were: the head part, the instrument compartment, the fuel tank, the oxidant tank, the tail section with the engine. The main features of the design of the missile were the use of an undivided warhead using suspended (non-carrying) fuel tanks located in the power casing. The power shell of the rocket was a rigid frame of steel stringers and frames with a shell of sheet steel. The oxidizer and fuel tanks were made of aluminum alloy sheet.
For the stabilization, the rocket in flight used four powerful and heavy (weight about 300 kg) stabilizers. Two types of control bodies were required: air (installed on stabilizers) and gas-jet (located in the stream of combustion products flowing out of the nozzle) of the rudder.
The single-chamber liquid rocket engine operated on fuel - liquid oxygen and a 75% aqueous solution of ethyl alcohol. Fuel supply system - pumping, unclosed (exhausted in the turbine gas was discharged into the atmosphere). As the turbine working medium, steam gas was used, formed during the decomposition of hydrogen peroxide in the presence of a catalyst - a solution of sodium permanganate; The supply of peroxide and permanganate to the reactor was superseded. Thus, four liquid components were required to operate the engine. Their second costs were: 75 kg / s of liquid oxygen, 50 kg / s of alcohol and 1.7 kg / s of peroxide and sodium permanganate. At that, the specific impulse was 2021 m / s near the Earth and - 2366 m / s in the void. Such low values of the specific impulse were explained by the use of low-calorie fuel (water was added to the fuel.
The engine had a large mass, which was explained by the imperfection of the design of all its main units: the combustion chamber (low pressure, poor organization of combustion processes), the turbo-pump unit (low speed), the steam-gas generator (displacing component feeding system). The ignition of fuel in the combustion chamber at engine start-up was carried out by a pyrotechnic incendiary device. The parameters determining the speed, and, consequently, the range of the flight of the rocket were extremely low for P-1.
The rocket was equipped with an autonomous inertial control system, which included a stabilization loop for the angular position of the missile in the active section of the trajectory (BOT) of the flight and a range control machine in which a gyroscopic accelerator integrator was used. The control system had a considerable mass (the mass of the control devices was about 200 kg with a total mass of the instrument compartment of 520 kg) and was insensitive to the parallel demolition of the rocket. As a result, the accuracy of the rocket (1.5 km) should be assessed as low, bearing in mind that it corresponded to a flight range of only about 300 km.
The R-1 rocket was an analogue of the German V-2, which Soviet specialists, including researchers of the SRI-885, studied after the war in Germany. NII-885 created two basic divisions, one of which was headed by the chief designer of autonomous control systems Nikolai Pilyugin, the second - the chief designer of radio control systems Mikhail Ryazansky. Both of them were members of the Council of Chief Designers, created by Sergei Korolyov, and actively promoted their directions.
When creating the R-1, the autonomous V-2 control system was taken as a basis, but as the missile's range was increased, both control systems began to be used. "First, the original V-2 control system was thoroughly researched and fully reproduced, and on the basis of this experience, Soviet engineers began to create their own control system using the domestic element base and materials," the RCC reported.
When organizing the production of devices of the autonomous management system, specialists faced a number of problems - from the technological difficulties of the supplier enterprises to the complete absence of the required component base in the USSR. R-1 had a single-circuit control system - to control during the flight, only the angular position of the rocket's axis and the moment of switching off the engines could be monitored. The guidance was carried out according to the start-up tables for the target with the known coordinates - the direction of the launch and the time of the rocket engine operation were set.
The effectiveness of the action of the head part on targets was determined by the fact that the GC contained a charge of explosive (BB) of about 800 kg. The radius of destruction of urban buildings did not exceed 20-25 m, and the missile could only be used to hit large, weak targets with firing at squares.
The ground-based technological equipment of the complex included more than 20 special machines and units. Preparation of the rocket for launch was carried out by calculation of 11 people at two positions - technical and combat (starting). The main content of the work in the technical position was the verification of the missile systems, docking it with the head. Transportation of the missile to a combat position was carried out on the ground carriage 8U22 or 8U24, with the help of which the missile was then installed on the launch pad and used to prepare the missile for launch. On the rocket, after installing it in a vertical position, the control system was checked, fuel and steamgas generating facilities were refueled, and aiming was carried out. On the battle calculation, it was assigned a special responsibility to dress on the head of a vertically standing rocket of a removable turntable.
If this operation was not carried out with care, it was not ruled out that the support ring could be touched by the head of the detonator located on the top of its cone. When preparing the rocket for launch, manual operations with a rocket engine were also carried out - tuning the pressure reducers of a steam and gas generator, depending on the concentration and temperature of hydrogen peroxide. These parameters of the engine approached the nominal. An ignition device was installed in the engine chamber from below through the nozzle. The rocket was launched from a special armored vehicle with a control panel. Time for the preparation of the missile at the technical position was 2 - 4 hours, in the combat position - up to 4 hours. In this way, the combat readiness of the complex, i.e., the time from the receipt of the launch command to the start of the missile was at least 6-8 hours, after which it was necessary either to start it or to transfer the launch to the next day. The discharge of oxygen, fuel, system check and refueling required a long time.
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