Encyclopedia Astronautica

Kvant-1-1 LV
Credit: Energia
Russian orbital launch vehicle. From 1996-2001 RSC Energia carried out design studies on the Kvant-1 light launch vehicle with a low earth orbit payload capability of 1.8 to 3.0 metric tons. Market surveys seemed to indicate a need for a new launch vehicle of this class but development funding was not forthcoming.

The resulting two-stage launch vehicle used Liquid Oxygen/Kerosene propellants. Stage 1 used Soyuz core tooling and was equipped with a single RD-120 engine (from the Zenit-2 second stage) modified for sea level ignition together with a four chamber RD-0124-14D23 engine adapted from the Soyuz second stage. The second stage was the Molniya LM upper stage with an 11D58 engine. The flight control system was based on that of the Yamal spacecraft. The booster could use existing Zenit or Soyuz launch pads, or a railroad Mobile Launch Platform.

The selected design for the Kvant-1 had a launch mass of 83 metric tons and could deliver the following payloads to a 200 km reference orbit: from Plesetsk, 1.75 metric tons; Baikonur, 1.8 metric tons; or from an equatorial Sea Launch platform, 1.95 metric tons. Payload capability could be increased as needed by use of existing solid-propellant booster motors.

LEO Payload: 1,800 kg (3,900 lb) to a 200 km orbit at 51.60 degrees.

Stage Data - Kvant-1

  • Stage 1. 1 x Kvant-1. Gross Mass: 74,000 kg (163,000 lb). Empty Mass: 7,000 kg (15,400 lb). Thrust (vac): 1,102.200 kN (247,784 lbf). Isp: 335 sec. Burn time: 195 sec. Isp(sl): 297 sec. Diameter: 2.60 m (8.50 ft). Span: 2.60 m (8.50 ft). Length: 10.30 m (33.70 ft). Propellants: Lox/Kerosene. No Engines: 1. Engine: RD-120K. Status: Study. Comments: 4 RD-0124-14D23 verniers. Empty mass estimated.
  • Stage 2. 1 x Molniya 8K78M-3. Gross Mass: 6,660 kg (14,680 lb). Empty Mass: 1,160 kg (2,550 lb). Thrust (vac): 66.600 kN (14,972 lbf). Isp: 340 sec. Burn time: 250 sec. Diameter: 2.40 m (7.80 ft). Span: 2.56 m (8.39 ft). Length: 3.20 m (10.40 ft). Propellants: Lox/Kerosene. No Engines: 1. Engine: S1.5400A. Status: In Production. Comments: 700 kg BOZ ullage motors and stabilisation platform jettisoned prior to main stage burn.

Status: Design 1994.
Gross mass: 83,000 kg (182,000 lb).
Payload: 1,800 kg (3,900 lb).
Height: 29.00 m (95.00 ft).
Diameter: 2.60 m (8.50 ft).
Thrust: 1,000.00 kN (224,800 lbf).
Apogee: 200 km (120 mi).

More... - Chronology...

Associated Countries
Associated Engines
  • RD-0124-14D23 Kosberg Lox/Kerosene rocket engine. 298.640 kN. Propoed in 1993 for Angara stage 2 verniers, Kvant-1 stage 1 vernier. Designed 1986-1990. Isp=331s. Variant of RD-0124 with shortened nozzle for sea-level operation. More...

See also
Associated Manufacturers and Agencies
  • Korolev Russian manufacturer of rockets, spacecraft, and rocket engines. Korolev Design Bureau, Kaliningrad, Russia. More...

Associated Stages
  • Kvant-1 Lox/Kerosene propellant rocket stage. Loaded/empty mass 74,000/7,000 kg. Thrust 1,102.20 kN. Vacuum specific impulse 335 seconds. 4 RD-0124-14D23 verniers. Empty mass estimated. More...
  • Molniya 8K78M-3 Lox/Kerosene propellant rocket stage. Loaded/empty mass 6,660/1,160 kg. Thrust 66.60 kN. Vacuum specific impulse 340 seconds. Standardized improved version for Molniya-type communications satellite payloads. More...

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