Yuzhnoye SDO Proprietary
COOPERATION BETWEEN THE US ENTITIES
AND YUZHNOYE SDO IN AEROSPACE DOMAIN
BACKGROUND
Yuzhnoye State Design Office named after
M.K.Yangel was founded in 1954 to initiate
development of strategic-purpose missile-weapon
complexes.
60 years of collaboration with SE PA Yuzhny
Machine-Building Plant, academic, science and
research, manufacturing enterprises of former Soviet
Union resulted in the development and production of
four generations of strategic missiles, represented by
13 modifications which formed the basis of strategic
missile forces. The world-class launch vehicles were
also produced (Kosmos, Interkosmos, Cyclone-2,
Cyclone-3, Zenit-2, Zenit-3SL, Zenit-2SLБ, Zenit3SLБ, Zenit-3SLБФ, Dnepr).
COMPETITIVE ADVANTAGES
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• 60 years of experience in designing, developing and manufacturing of rocket-space and spacecraft technologies;
• Rich experience in international cooperation with leading aerospace companies and organizations worldwide;
• Experienced in cooperation under International Standards within the frames of different International Programs;
• Flexible in applying and adapting standards required by a Customer/ Contractual Terms and Conditions;
• Possesses a complete technological cycle starting from designing spacecraft up to the launch of spacecraft using
launch-vehicles of its own development;
• Active in developing and commercializing new space and civil application technologies;
• Competitive pricing policy;
• Reliable and experienced Partner for new and already established partnership.
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PREREQUISITES FOR
COOPERATION WITH THE USA
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LEGAL PREREQUISITES FOR COOPERATION
To establish a long-term and fruitful cooperation between Ukraine and the USA in aerospace domain
significant business, political, legal and administrative efforts were made since 1990-s. The following
main legislation acts served as a background of such cooperation:
Memorandum of mutual understanding between the Ukrainian Government and the US Government
regarding space-rocket hardware and technologies transfer, as of May 13, 1994.
2)
Agreement between the Ukrainian Government and the US Government regarding protection of
technologies related to the Ukrainian launch vehicles, space-rocket hardware and technical data for Sea
Launch Project, as of September 29, 1999.
3)
Memorandum of mutual understanding between Ukrainian Government and the US Government
regarding cooperation in aerospace domain, as of September 29, 1999.
4)
Framework agreement between the Ukrainian Government and the US Government on cooperation and
use of outer space for peaceful purposes, as of March 21, 2008.
5)
Memorandum of mutual understanding between the Ukrainian Government and the US Government, as
of November 10, 2008.
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Yuzhnoye SDO Proprietary
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BENEFITS OF COOPERATION
Cooperation between Ukrainian and the US companies is advantageous and mutually beneficial due to
the following factors:
From the side of Ukraine:
From the side of the USA:
- Availability of the unique LOX-rich staged combustion
rocket engine technology;
- Possibility of technology transfer and training;
- Long-term and rich experience in launch vehicles and
liquid propellant engines development;
- Availability of highly skilled and experienced personnel
in space industry;
- Relatively inexpensive
technical base.
resources,
materials
and
- Engagement of facilities and infrastructure which
were left unused after retirement of the Space Shuttle
in joint projects;
- Involvement in joint projects of highly skilled
personnel left unemployed after the Space Shuttle
retirement;
- Sharing the US management traditions and culture;
- Sharing
commercialization
experience.
and
marketing
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Yuzhnoye SDO Proprietary
- Availability of the required manufacturing technologies
and infrastructure;
- Availability of significant experience in the
development of space-rocket complexes, launch
vehicles including manned flights, solid propulsion
systems, satellites and other space systems and
components;
CURRENT JOINT PROJECTS
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SEA LAUNCH PROJECT
Sea Launch Project envisages provision of launches for
commercial spacecraft by Zenit-SL ILV.
ILV launches are performed from the Odyssey floating
platform located in the equatorial area of the Pacific
Ocean.
In total, 36 launches of Zenit-SL ILV were implemented.
Technical specifications
Maximum lift-off mass, t
473
Number of stages
Payload mass injected
geostationary orbit, t
3
into
transfer
to
6.24
425
Engines thrust at launch, t
740
Length, m
59.6
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Yuzhnoye SDO Proprietary
Propellants mass, t
ANTARES PROJECT
Since 2007, Yuzhnoye SDO takes part in creation of Orbital Sciences
Corporation Antares rocket-space complex with middle class launch
vehicle designed for delivery of cargos to the International Space Station
after retirement of Space Shuttle. The launch vehicle will also be used for
injection of commercial and scientific purpose spacecraft having mass of
up to 7200 kg into Low Earth Orbit.
Yuzhnoye SDO is responsible for development of the First Stage Core
Structure and the launch vehicle hold-down bay, development as well as
for development and manufacturing of control-check-out and ground
equipment of onboard systems.
The first maiden launch
September 18, 2013
COTS demonstration flight, the first Cygnus
mission
January 9, 2014
First Commercial Resupply Service (CRS)
mission
July 13, 2014
Carrying of supplies for the ISS
Success rate of launches: 100%
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Yuzhnoye SDO Proprietary
April 21, 2013
TRAINING FOR NASA
PROVIDED BY YUZHNOYE SDO
On March 19-21 and March 26-28, 2013 consulting courses
were performed at the facilities of National Institute for Rocket
Propulsion System and NASA Engineering and Safety Center
(Huntsville, Alabama) for Marshall Space Flight Center
specialists.
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Yuzhnoye SDO Proprietary
On December 16-20, 2013 consulting courses on
Ukrainian launch systems and propulsion design
practices for representatives of American space industry
were provided at Kennedy Space Center (Florida).
YUZHNOYE PROPULSION TECHNOLOGIES
AT THE US MARKET
Yuzhnoye SDO has established cooperation with several
US companies regarding promotion of Ukrainian rocket
engine technologies and products to the US market
(particularly, for application at the existing and prospective
US launch vehicles) with the purpose of establishment of
Yuzhnoye SDO liquid rocket engines co-production in the
territory of the USA.
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PROSPECTIVE JOINT PROJECTS
MODERNIZATION OF THE EXISTING AND
CREATION OF NEW AMERICAN LAUNCH
VEHICLES AND AIRBORNE LAUNCH SYSTEMS
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ANTARES PROJECT DEVELOPMENT
Yuzhnoye SDO proposes Orbital Sciences Corporation to modernize Antares ILV by replacement
of currently used first stage engines by RD-801 or RD-810 liquid propellant engines developed by
Yuzhnoye SDO as well as replacement of the upper stage engine by RD-809K and RD-809M
engines developed by Yuzhnoye SDO.
Currently
existing LV
Mass of
payload
injected into
Low Earth
Orbit, t
-
Phase 2
Phase 3
6.19
6.77
8.1
12.7
-
-
1.7
6
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Yuzhnoye SDO Proprietary
Mass of
payload
injected into
Geostationary
Transfer Orbit,
t
5.07
Phase 1
Phase 4
PROPOSALS FOR NASA SLS PROJECT
In recent years, Yuzhnoye presented a number of proposals to the representatives of NASA and
the US aerospace industry related to possible application of Yuzhnoye’s liquid rocket engines and
liquid stages as strap-on boosters for NASA prospective SLS heavy lift launcher.
At the initial phase of SLS operation solid rocket boosters are planned to be used, however
NASA is also considering an option of applying liquid propellant systems.
Yuzhnoye SDO is proposing a cluster of RD810/RD-815 prospective engines for SLS liquid
strap-on boosters or a stage on the basis of RD810 engine.
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MAYAK-FLORIDA
In cooperation with the US partners, Yuzhnoye SDO
studies a possibility of creating a Project aimed at
development and co-production of Mayak launch
vehicles family, establishment and operation of
launch complex in Florida, USA, and marketing of
commercial space launch services.
4xRD-801
4xRD-810
4xRD-810 +
4 xGEM 60 / 2xGEM 60
4xRD-810 +
2 SRB
2nd stage engine
RD-809M
RD-801
RD-801
RD-801
3rd stage engine
-
-
- / RD-809M
- / RD-809M
Payload mass to LEO, t
8.2
14.4
20.85
42.3
Payload mass to GTO, t
2.15
5
7.7
13.7
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1st stage engine
AIRBORNE LAUNCH SYSTEMS
Microspace-2 airspace rocket system is designed for injection of
microsatellites in a wide range of orbit altitudes (500-1000 km) and
inclination (0 - 98). It can carry up to 40 kg of payload.
MICROSPACE-2
Microspace-2 airspace rocket system consists of the following
separate units:
- Three-stage launch vehicle;
- Aircraft-carrier (Su-27);
- Manufacturing and operational complex.
The following benefits of Microspace-2 should be mentioned:
- Growing demand in commercial pico- and nanosatellites launch market with mass from 1 kg to 40 kg;
- Considerable cost reduction and launching efficiency raising for pico- and nanosatellites injection into orbit;
- No need in launch sites construction.
The purpose of Space Clipper Project is ensuring of access to space that would not depend on geographical
position of a country and would provide dedicated launch for growing number of spacecraft.
Aerospace Rocket Complex Space Clipper consists of:
- Aviation complex (modified An-124-100 Ruslan
aircraft, ground-support equipment);
- Space rocket complex (two/three-stage launch
vehicle, on-board launch complex, technical base)
SPACE CLIPPER
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Essence of the Project: Utilization of heavy cargo aircraft
which serves for dropping two/three-stage launch vehicle
weighing 36-70 tons.
YUZHNOYE SDO
LIQUID ROCKET ENGINES
PROPOSED FOR THE PROSPECTIVE
AND EXISTING US SPACE PROJECTS
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RD-860 AND RD-860L ENGINE FOR LANDING AND
TAKE-OFF MODULES
RD860
VG143
MEA-1
MEA-2
MEA-1
RD-860L
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Yuzhnoye SDO Proprietary
RD-860
VG143
UPPER STAGE ENGINES
RD-805 main engine is one-chamber, single mode, capable of multiple burns, having
turbopump propellants supply system, implemented in LOX-rich staged combustion scheme.
Vacuum thrust is 2025 kgf
RD-805
RD861К engine is designed to generate thrust and provide pitch and yaw control
during the powered leg of the Cyclone-4 LV upper stage flight. The engine is
developed with two versions of nozzle extension: 1) a metal nozzle extension;
2) a carbon-carbon composite nozzle extension. Vacuum thrust is 7916 kgf.
RD-809M is a four chamber single mode main engine, with multiple restarts, a
turbopump propellants supply system and LOX-rich staged combustion operation
cycle. Vacuum thrust is 9 tf.
RD-809M
RD-809K is a single chamber single mode main engine, with multiple restarts, a
turbopump propellants supply system and LOX-rich staged combustion operation
cycle. Vacuum thrust is 10 tf.
RD-801V engine is a single chamber liquid rocket engine using LOX-rich staged
combustion scheme. The engine is running on liquid oxygen and kerosene and
ensure single burn during flight. The engine is being developed on the basis of RD801 first stage engine by extending its nozzle. For the purpose of the stage flight
control, RD-801V engine is capable of gimbaling in two planes. Vacuum thrust is
141.7 tf.
RD-809K
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Yuzhnoye SDO Proprietary
RD-801V
RD-861K
FIRST STAGE ENGINES
RD-801 is a single-chamber dual mode main engine with single burn, turbopump propellant
supply system and application of LOX-rich staged combustion technology.
RD-810 is a single-chamber dual mode main engine with single burn, turbopump
propellant supply system and application of LOX-rich staged combustion technology.
RD-801
RD-801M and RD-810M modular liquid rocket engines comprising four
autonomous engine assemblies are designed for installation in the aft
section of 3900 mm in diameter.
RD-810
RD-815 is a single chamber, dual mode, with a single start, a turbopump
propellants supply system and has LOX-rich staged combustion.
RD-801M AND RD-810M
RD-880.1 is a single chamber, dual-mode with a single start, a
turbopump propellants supply system and has LOX-rich staged
combustion.
RD-815
RD-880.1
RD-880.2
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Yuzhnoye SDO Proprietary
RD-880.2 is a double-chamber dual mode main engine, with
a single start, a turbopump propellants supply system and
LOX-rich staged combustion scheme.
PRELIMINARY CONCEPTUAL DESIGN OF THE ENGINES FAMILY WITH
250–500–1000 TF THRUST WITH OPTIMAL CONFIGURATIONS
RD882
(2× RD880)
Thrust throttling
range, %
-60…110
-60…110
1104
(1206)
1004
(1096)
602.4
(657.6)
4670 mm
552
(602.8)
501.8
(548.2)
301.2
(328.8)
276
(301.4)
250.9
(274.1)
-50…110
3792 mm
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Yuzhnoye SDO Proprietary
Engine thrust at sea
level (in vacuum), tf
125.5
(137)
2410 mm
4470 mm
4310 mm
RD880
4260 mm
RD815
SATELLITES AND
SATELLITE COMPONENTS
Yuzhnoye SDO Proprietary
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MS-2 PLATFORM
Payload Accommodation on MS-2 Platform
Base
Solar array
panels
Frame modules cluster of
platform body
Mounting plate
Envelope inside platform body
Payload instrumentation volume available inside the platform body is about 70 dm3
* Heat shields and cables are not shown
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Yuzhnoye SDO Proprietary
Payload instrumentation inside the platform can be installed on the base, mounting plate, and base block.
POTENTIAL DIRECTIONS OF COOPERATION
Possible schemes of interaction:
Development;
2.
Technology transfer;
3.
Training;
4.
Operations.
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Yuzhnoye SDO Proprietary
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CONTACT INFORMATION
Alexander Degtyarev
General DesignerGeneral Director
Yuzhnoye SDO
Krivorozhskaya Str., 3
Dniepropetrovsk 49008, Ukraine
Tel.: +380 56 770 04 47
Fax: +380 56 770 01 25
E-mail: space@yuzhnoye.com
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