Encyclopedia Astronautica
Burlak



burlak2.jpg
Burlak
Russian air-launched winged orbital launch vehicle. Burlak air-launched satellite launcher was proposed in 1992 and studied by Germany in 1992-1994. Evidently based on secret anti-satellite missile. Air launched from Tu-160 bomber, released at 13,500 m altitude and Mach 1.7. Development estimated to cost only DM 50 million, but not proceeded with. Burlak/Diana variant would have been launched from Concorde.

LEO Payload: 1,100 kg (2,400 lb) to a 200 km orbit. Payload: 550 kg (1,210 lb) to a 1000 km polar orbit. Launch Price $: 5.000 million in 1994 dollars.

Stage Data - Burlak

  • Stage 0. 1 x Tu-160. Gross Mass: 205,442 kg (452,922 lb). Empty Mass: 99,773 kg (219,961 lb). Thrust (vac): 533.670 kN (119,974 lbf). Isp: 1,980 sec. Burn time: 58,000 sec. Isp(sl): 1,800 sec. Diameter: 13.71 m (44.98 ft). Span: 53.96 m (177.03 ft). Length: 53.35 m (175.03 ft). Propellants: Air/Kerosene. No Engines: 4. Engine: NK-231. Status: Out of Production. Comments: Tupolev Bomber-variable geometry. Maximum release conditions: Belly-mounted, 9,977 kg at 2,451 kph at 18,292 m altitude.
  • Stage 1. 1 x Burlak Stage 1. Gross Mass: 18,000 kg (39,000 lb). Empty Mass: 1,800 kg (3,900 lb). Thrust (vac): 357.900 kN (80,459 lbf). Isp: 320 sec. Burn time: 140 sec. Isp(sl): 270 sec. Diameter: 1.60 m (5.20 ft). Span: 1.90 m (6.20 ft). Length: 10.50 m (34.40 ft). Propellants: N2O4/UDMH. No Engines: 1. Engine: Burlak Stage 1. Status: Out of Production. Comments: Masses, thrust, specific impulse estimated based on total vehicle mass of 28.5 tonnes and first stage burn time of 140 seconds. Air launched from Tu-160 at 13,500 m, Mach 1.7 release conditions.
  • Stage 2. 1 x Burlak Stage 2. Gross Mass: 9,400 kg (20,700 lb). Empty Mass: 900 kg (1,980 lb). Thrust (vac): 98.000 kN (22,031 lbf). Isp: 330 sec. Burn time: 275 sec. Isp(sl): 230 sec. Diameter: 1.60 m (5.20 ft). Span: 1.60 m (5.20 ft). Length: 5.50 m (18.00 ft). Propellants: N2O4/UDMH. No Engines: 1. Engine: Burlak Stage 2. Status: Out of Production. Comments: Masses, thrust, specific impulse estimated based on total vehicle mass of 28.5 tonnes and first stage burn time of 140 seconds. Air launched from Tu-160 at 13,500 m, Mach 1.7 release conditions.

Status: Cancelled 1992.
Gross mass: 27,400 kg (60,400 lb).
Payload: 1,100 kg (2,400 lb).
Height: 19.00 m (62.00 ft).
Diameter: 1.60 m (5.20 ft).
Thrust: 302.00 kN (67,892 lbf).
Apogee: 200 km (120 mi).

More... - Chronology...


Associated Countries
Associated Engines
  • Burlak Stage 2 N2O4/UDMH rocket engine. 98 kN. Burlak stage 2. Development ended 1992. Isp=330s. Air launched from Tu-160 at 13,500 m, Mach 1.7 release conditions. More...
  • Burlak Stage 1 Russian N2O4/UDMH rocket engine. 360 kN. Burlak stage 1. Development ended 1992. Isp=320s. Air launched from Tu-160 at 13,500 m, Mach 1.7 release conditions. More...
  • NK-231 Kuznetsov turbofan engine. 226.5 kN. Tu-160. Development ended 1992. Turbofan engine used in Tu-160. Thrust is maximum sea level thrust; specific impulse is sea level value at that thrust. Isp=1980s. More...

See also
  • Winged In the beginning, nobody (except Jules Verne) thought anybody would be travelling to space and back in ballistic cannon balls. The only proper way for a space voyager to return to earth was at the controls of a real winged airplane. More...

Associated Stages
  • Burlak Stage 1 N2O4/UDMH propellant rocket stage. Loaded/empty mass 18,000/1,800 kg. Thrust 357.90 kN. Vacuum specific impulse 320 seconds. Masses, thrust, specific impulse estimated based on total vehicle mass of 28.5 tonnes and first stage burn time of 140 seconds. Air launched from Tu-160 at 13,500 m, Mach 1.7 release conditions. More...
  • Burlak Stage 2 N2O4/UDMH propellant rocket stage. Loaded/empty mass 9,400/900 kg. Thrust 98.00 kN. Vacuum specific impulse 330 seconds. Masses, thrust, specific impulse estimated based on total vehicle mass of 28.5 tonnes and first stage burn time of 140 seconds. Air launched from Tu-160 at 13,500 m, Mach 1.7 release conditions. More...
  • Tu-160 Mach 2 rocket launch aircraft. Loaded/empty mass 205,442/99,773 kg. Thrust 533.67 kN. Specific impulse 1980 seconds. Tupolev Bomber-variable geometry. Maximum release conditions: Belly-mounted, 9,977 kg at 2,451 kph at 18,292 m altitude More...

Burlak Chronology


1992 During the Year - . Launch Vehicle: Burlak.
  • Burlak air-launched satellite launcher was proposed - . Nation: Russia. Summary: The design was studied by Germany in 1992-1994. Development estimated to cost only DM 50 million, but not proceeded with..

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