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COOPERATION BETWEEN THE US ENTITIESAND YUZHNOYE SDO IN AEROSPACE DOMAIN

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, Zenit-3SLБ, Zenit-3SLБФ, Dnepr).

BACKGROUND

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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.

COMPETITIVE ADVANTAGES

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PREREQUISITES FOR COOPERATION WITH THE USA

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1) 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.

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:

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LEGAL PREREQUISITES FOR COOPERATION

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Cooperation between Ukrainian and the US companies is advantageous and mutually beneficial due to the following factors:

- 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;

- 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 and marketing experience.

From the side of Ukraine:

- 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;

- Availability of the required manufacturing technologies and infrastructure;

- Relatively inexpensive resources, materials and technical base.

From the side of the USA:

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BENEFITS OF COOPERATION

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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 3

Payload mass injected into transfer to geostationary orbit, t

6.24

Propellants mass, t 425

Engines thrust at launch, t 740

Length, m 59.6

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April 21, 2013 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

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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.

Success rate of launches: 100%

ANTARES PROJECT

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TRAINING FOR NASAPROVIDED 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.

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). Y

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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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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.

ANTARES PROJECT DEVELOPMENT

Mass of payload

injected into Low Earth

Orbit, t

Mass of payload

injected into Geostationary Transfer Orbit,

t

5.07

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Phase 1

6.19

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Currently existing LV Phase 2 Phase 3

Phase 4

6.77

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8.1

1.7

12.7

6

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PROPOSALS FOR NASA SLS PROJECT

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.

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.

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Yuzhnoye SDO is proposing a cluster of RD-810/RD-815 prospective engines for SLS liquid strap-on boosters or a stage on the basis of RD-810 engine.

MAYAK-FLORIDA

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1st stage engine 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

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.

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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 airspace rocket system consists of the following separate units:- Three-stage launch vehicle;- Aircraft-carrier (Su-27);- Manufacturing and operational complex.

MICROSPACE-2

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.

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AIRBORNE LAUNCH SYSTEMS

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.

Essence of the Project: Utilization of heavy cargo aircraft which serves for dropping two/three-stage launch vehicle weighing 36-70 tons.

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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YUZHNOYE SDO LIQUID ROCKET ENGINES

PROPOSED FOR THE PROSPECTIVE AND EXISTING US SPACE PROJECTS

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RD-860

RD-860 AND RD-860L ENGINE FOR LANDING AND TAKE-OFF MODULES

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RD860

MEA-2

VG143

MEA-1

VG143

MEA-1

RD-860L

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RD-805

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 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

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UPPER STAGE ENGINES

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-861K

RD-809M

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 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-809K

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-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

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 RD-801 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.

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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.

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FIRST STAGE ENGINES

RD-801

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-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-810

RD-801M AND RD-810M

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-815

RD-880.1

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-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 is a single chamber, dual mode, with a single start, a turbopump propellants supply system and has LOX-rich staged combustion. RD-815 is a single chamber, dual mode, with a single start, a turbopump propellants supply system and has LOX-rich staged combustion.

RD-880.2

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.

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.

RD880RD815 RD882(2× RD880)

250.

9 (2

74.1

)

4310

mm

4260

mm

2410 mm

4470

mm

Engine thrust at sea level (in vacuum), tf

Thrust throttling range, % -50…110 -60…110 -60…110

125.

5 (1

37)

276

(301

.4)

301.

2 (3

28.8

)

501.

8 (5

48.2

)

552

(602

.8)

602.

4 (6

57.6

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1004

(1

096)

1104

(1

206)

PRELIMINARY CONCEPTUAL DESIGN OF THE ENGINES FAMILY WITH 250–500–1000 TF THRUST WITH OPTIMAL CONFIGURATIONS

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3792 mm 4670 mm

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SATELLITES AND SATELLITE COMPONENTS

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Envelope inside platform body

* Heat shields and cables are not shown

Payload instrumentation inside the platform can be installed on the base, mounting plate, and base block.

Payload instrumentation volume available inside the platform body is about 70 dm3

Frame modules cluster of platform body

Mounting plate

Base

Solar array panels

Payload Accommodation on MS-2 Platform

MS-2 PLATFORM

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POTENTIAL DIRECTIONS OF COOPERATION

Possible schemes of interaction:

1.Development;

2.Technology transfer;

3.Training;

4.Operations.

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CONTACT INFORMATION

Alexander Degtyarev

General Designer- General DirectorYuzhnoye SDO

Krivorozhskaya Str., 3Dniepropetrovsk 49008, UkraineTel.: +380 56 770 04 47Fax: +380 56 770 01 25E-mail: space@yuzhnoye.com