Burlak

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: 200 km Orbit. Payload: 550 kg (1,210 lb). to a: 1000 km polar orbit trajectory. Liftoff Thrust: 302.000 kN (67,892 lbf). Total Mass: 27,400 kg (60,400 lb). Core Diameter: 1.60 m (5.20 ft). Total Length: 19.00 m (62.00 ft). Launch Price $: 5.000 million. in: 1994 price dollars.

• Stage Number: 0. 1 x Stage: 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: Development ended 1992. Tupolev Bomber-variable geometry. Maximum release conditions: Belly-mounted, 9,977 kg at 2,451 kph at 18,292 m altitude

• Stage Number: 1. 1 x Stage: 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: Development ended 1992. 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 Number: 2. 1 x Stage: 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: Development ended 1992. 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.

1992 During the Year - Launch Vehicle: Burlak.

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