Page 20 - December

PROFESSIONAL ADVICE
In the course of further research in 1996-1997
the concept of "Angara" was developed and refined.
Given the current situation in the country, the Space
Center named after M.V. Khrunichev proposed a
strategy for the phased creation of a heavy-class
launch vehicle using a universal rocket module in its
composition. This new concept retains all the key ideas
of the original "Angara" version and develops new
promising opportunities.
Now the system of launch vehicles "Angara"
began to cover carriers from a light class with a carrying
capacity in low reference orbits of 2 - 3.7 tons to a
heavy one with a carrying capacity of up to 24.5 tons,
and subsequently up to 28 tons.
The Angara launch vehicle family is based on
a universal rocket module (URM). It includes a block
of oxidizer and fuel tanks and an RD-191 engine. The
module is made according to the "monoblock" scheme
with supporting tanks. The single-chamber engine
RD-191, created at NPO Energomash, operates on
kerosene / liquid oxygen components. This engine is a
variant of the four-chamber engines RD-170 and RD-
171, installed on the first stages of MC Energia and MC
Zenit-2, respectively, and the two-chamber engine RD-
180, created for MC Atlas. Its thrust at the ground is
1923 kN, in the void - 2086 kN, the specific impulse of
thrust on the Earth is 3048 N * s / kg, in the void –3306
N * s / kg. To ensure control of the launch vehicle in
flight, the engine is fixed in a gimbal.
The filling weight of one universal rocket module is up to 127 tons, dry weight - 8.0 tons.
The length of the URM is 23 m, the diameter is 2.9 m. These dimensions were chosen based on
the technological equipment available at the rocket and space plant.
Fig. 3. System of launch vehicles "Angara"
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One such universal rocket module is the
first stage of two types of light-class launch
vehicles created under the Angara program. As
the second stages on these two PH variants,
oxidant conventionally called "Angara-1.1" and
tank О2 "Angara-1.2", the central part of the upper
stage "Briz-M" and the rocket block based on
the "I" block created for the rocket are used,
respectively - carrier "Soyuz-2".
fuel tank The medium-class launch vehicle will be
H2 formed by adding two universal modules (as
the first stage) to the Angara-1.2 light-class
launch vehicle.
The carrier of the heavy class "Angara-5A"
has the first stage formed of five blocks based
on a universal rocket module. Five engines of
the first stage are started at the same time at
the start of the rocket, but subsequently the
engine of the central block is throttled to 30%
of thrust and by the time the side modules are
emptied it retains sufficient fuel reserves to
continue the flight.
engine The emptied side modules are discarded
KVD1MZ and the center module is set to full thrust.
The use of universal rocket modules as
Fig. 2. "Breeze" upper stage part of launch vehicles and wide unification of
elements with other PHs will sharply reduce
the cost of manufacturing and operating the
Angara family of vehicles with high performance
characteristics, which will ensure the necessary
competitiveness in the world launch vehicle
market.
The dimensions and characteristics of
the universal rocket module make it possible
to consider the possibility of its use as part of
other launch vehicles, in particular, as part of
the Soyuz-2 PH.
As the second stage, either a stage based
on oxygen-kerosene components is considered,
similar to that used on the Angara-1.2 carrier,
but with an increased supply of fuel components,
or a universal oxygen-hydrogen unit (UKVB),
the characteristics of which remain the same
as "UKVB" for the carrier "Proton-M2 ".
Depending on the specific tasks on
the medium and heavy class "Angara"
carriers, the use of additional stages is
provided:
• oxygen-hydrogen upper stage ("KVRB");
• upper stage from PH "Proton-M" - "Breeze-M".
The payload is placed under a large-size
head fairing with a diameter of 4.35-5.1 m.
The oxygen-hydrogen upper stage
"KVRB" is a single-stage accelerator designed
for launching various spacecraft. The design of
the "KVRB" allows you to perform many hours
of flight in outer space and to repeatedly turn
PROFESSIONAL ADVICE
on the main engine during the flight.
The design and characteristics of the
"KVRB" allow it to be used in conjunction not
only with the PH "Proton-M", but also with
a number of existing and promising PH of
medium and heavy classes "Angara", "Zenith",
etc. This will significantly increase the energy
capabilities of these launch vehicles to launch
heavy payloads into high energy orbits.
Main characteristics of RB "KVRB":
dry weight - 3650 kg;
weight of the filled components - 18200 kg;
launch weight - up to 22,000 kg.
The KVRB block has a KVD1MZ engine
with a thrust in the void of 103 kN and a
specific impulse of thrust in the void of 4611 N
* s / kg. Developed at the Design Bureau for
Chemical Engineering named after A.M. Isaev.
The universal oxygen-hydrogen unit
"UKVB" is a stage of a launch vehicle equipped
with four engines of the KVD1MZ type, but
with a single start in flight.
The duration of the "UKVB" operation
in an independent flight is approximately 12
minutes.
The UKVB, like the KVRB, are designed
in such a way that, with minimal modifications,
they can be used both in the "Proton-M" launch
vehicle and in the "Angara" super-heavy class.
Main characteristics of the UKVB block:
dry weight - 7350 kg;
weight of the filled components - 44,000 kg;
launch weight - up to 51,500 kg.
The current stage of creating new launch
vehicles has the following features:
• layout (structural) diagrams can be formed
in an optimal way, taking into account the
experience of the missile carrier operation;
• a modular principle is used to reduce the time
and cost of developing and operating missile
carrier samples;
• creation of launch vehicles based on universal
rocket modules or basic elements;
• while developing the modules and basic
elements, components (engines, control
system, structure) are used that have optimal
flight performance at the moment.
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