MOSCOW 2001

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BABAKIN SCIENCE RESEARCH CENTERSPACE RESEARCH
INSTITUTE RAS
SOLAR SAIL PROJECT
MOSCOW 2001
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SOLAR SAIL PROJECT
BABAKIN SCIENCE RESEARCH CENTER SPACE
RESEARCH INSTITUTE RAS
CONCEPT OF SOLAR SAIL PROJECT

• Destination Solar Sail spacecraft operational
  possibilities demonstration
• Launch data 2002
• Launch vehicle insertion by VOLNA LV (converted
  SLBM SS-N-18) launch from submarine from Barents
  Sea
• Flight configuration orbital flight H?840 km,
  H?832 km, i78
• Experiment duration about 3 months

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SOLAR SAIL PROJECT
BABAKIN SCIENCE RESEARCH CENTER SPACE
RESEARCH INSTITUTE RAS
REASONS FOR VOLNA LV CHOICE

1. Payload status is primary.
2. Nothing to change for launch vehicle
   configuration.
3. Nothing to change for launch preparation
   campaign.
4. High reliability, based on prototype flight
   history.
5. Affordable cost.
6. Experience of launches for civilian program.
7. Relatively flexible launch date.

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SOLAR SAIL PROJECT
BABAKIN SCIENCE RESEARCH CENTER SPACE
RESEARCH INSTITUTE RAS
VOLNA LAUNCH VEHICLE
LV VOLNA is being developed by State Rocket
Center Makeyev Design Bureau on the base of
SLBM SS-N-18. VOLNA can be launched from a
surfaced or submerged KALMAR (DELTA III) type
submarine. Payload of the LV VOLNA is
accommodated inside a protected capsule mounted
in the warhead section of the SLBM. VOLNA
reliability rate, based on SS-N-18 flight
history, is 0.95 (total number of launches 147,
among them successful 140). VOLNA LV was used
for insertion German scientific package during
micro-gravity experiment in 1995.
3-rd stage
Payload area
2-nd stagefuel tank
2-nd stageoxidizer tank
2-nd stageengine

• Basic characteristics
• Number of stages 3
• Propellant... liquid N2O4 UDMH
• Launch weight ..... 35.4 t
• Overall dimensions of LV
• length 14.2 m
• diameter .. 1.8 m
• Payload area volume.. 1.3 m3
• Payload mass
• into suborbital trajectory . up to 720 kg
• into LEO... up to 80 kg
• Launch point location.. Barents Sea
  (standard) Pacific Ocean (optional)

1-st stageoxidizer tank
1-st stagefuel tank
1-st stageengine
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SOLAR SAIL PROJECT
BABAKIN SCIENCE RESEARCH CENTER SPACE
RESEARCH INSTITUTE RAS
SPACECRAFT CONFIGURATION
Orbital platform(sail is stowed)
Sail deployed configuration
Protective cover
Antennas
Solar sail blades
Solar sail blades(stowed position)
Camera
Solar array (stowed position)
Attitude control thrusters
Equipment bay
Propulsion system
Launch configuration
Flight configuration
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SOLAR SAIL PROJECT
BABAKIN SCIENCE RESEARCH CENTER SPACE
RESEARCH INSTITUTE RAS
SPACECRAFT HARDWARE
Equipment Platform
Propellant Tanks
Sails Section
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SOLAR SAIL PROJECT
BABAKIN SCIENCE RESEARCH CENTER SPACE
RESEARCH INSTITUTE RAS
MISSION PROFILE
Spin-off and Solar Array deployment
Spacecraft spin-up. ? 2.5 rad/s
Orientation to the Sun
Protective cover separation
Apogee kickimpulse T 1123 s
Pressure reducing inside payload compartment
Kick motor separation
3-rd stage overturn.Spacecraft separation. T
378 s
VOLNA 2-ndstage separation3-rd stage ignition
Solar Sail deployment
VOLNA 2-ndstage ignition
VOLNA 1-st stage separation
VOLNA launch from the KALMAR (DELTA III) type
submarine
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SOLAR SAIL PROJECT
BABAKIN SCIENCE RESEARCH CENTER SPACE
RESEARCH INSTITUTE RAS
SOLAR SAIL TESTS
CHECK OF DEPLOYMENT OF THE SOLAR SAIL BLADE
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SOLAR SAIL PROJECT
BABAKIN SCIENCE RESEARCH CENTER SPACE
RESEARCH INSTITUTE RAS
SOLAR SAIL TESTS
DEPLOYMENT TEST WITH MODELING OF ZERO-GRAVITY
CONDITIONS
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