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Baikal  
Initial Operational Capability (IOC): 2011
Total Production: ?
Origin: Russia
Corporations: Khrunichev Space Center and NPO Molniya
Parent System: Baikal
Initial Operational Capability (IOC): 2011
Total Production: ?
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Description: The Baikal is a reusable launch vehicle (RLV) being developed by Khrunichev Space Center and NPO Molniya on behalf of the Angara family of space launch vehicles. Its purpose is to reduce the operational launch vehicle cost and to minimize the drop fields. The new reusable booster is also available for other foreign launch vehicles. Integrated with the Angara launch vehicles, after lift-off the Baikal boosters will be detached from the launch vehicle at the second stage separation and then flight back and land onto the Plesetsk airfield. The Angara space launch vehicles are expected to operate from launch pads at Plesetsk, Russia.

The Baikal key elements are the RD-191 reusable liquid fuel rocket engine developing 212,000 kg of thrust, a foldable wing, an all-moving tail plane and an auxiliary turbojet engine developing 5,000 kg of thrust. The booster is fitted with a rocket steering system to exercise attitude control after the booster has completed its mission and is about to enter the Earth's atmosphere. After entering the atmosphere and undergoing preliminary deceleration Baikal begins gliding flight using its foldable wing, with flight controlled by aerodynamic surfaces. Then two air-breathing engines in the forward section ignite turning the descent into a powered flight. Controlled by its own navigation system, Baikal returns to the airfield near the originating launch pad to land on at 280 km/h using its retractable wheeled landing gear.

Baikal Applications


Space Systems Angara A3 Angara A5 Angara A5V Angara A7

Baikal Specifications

Service Life Flights: 10
Dimensions
Height: 8.50 meter (335 inch)
Length: 28.5 meter (1,122 inch)
Wingspan: 17.1 meter
Performance
Landing Run Distance: 1,200 meter
Max Range: 384 kilometer
Speed
Cruise Speed: 490 kph
Top Speed: 5.64 mach
Weight
Max Landing Weight: 18,000 kilogram
Max Takeoff Weight: 130,400 kilogram
Thrust: 212,600 kilogram (468,695 pound)
CEP: Circular Error Probable
Meters (m)   Kilometers (km)   Nautic Miles (nm)   Inch (in)   Yard (yd)   Foot (ft)   Millimeter (mm)
Pound (lb)   Kilogram (kg)   kN (KiloNewton)   Ton (t)
Meters per Second (mps)   Kilometers per Hour (kph)   Knot (kt)   Miles per Hour (mph)
Liter (l)   Galon (gl)
Year (yr)   Minutes (min)   Second (sec)
Shaft-Horse-Power (shp)

Operators & Related Equipment


OperatorsItems

Grand Total ?1
Propulsion Systems
RD-191x1
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