Martin Astrorocket

Martin winged orbital launch vehicle design of 1962. Early two-stage-to-orbit shuttle study, using storable propellants, Dynasoar-configuration delta wing orbiter and booster.

Martin's "Astrorocket" would have been launched vertically because the designers felt the VL mode frees design from gross liftoff weight constraints (Martin regarded about 450t as the upper limit for a HTHL TSTO). The vertical takeoff mode would provide additional mission flexibility since no rocket powered horizontal launch sled would be required. The Astrorocket would have used storable propellants on both stages so consequently the liftoff weight was high: 1134t. The payload capability to a 555km orbit was only 2.27t and the crew of three astronauts could stay in orbit for up to two weeks. Both stages carry turbojets for powered landing and self-ferry between launch sites. The liftoff thrust would be 13,350KN and stage separation would occur at an altitude of 64km while the vehicle is travelling at 9600km/h.

Crew Size: 3. Flyaway Unit Cost 1985$: 36.000 million.

Stage Data - Martin Astrorocket

• Stage 1. 1 x Astrorocket-1. Gross Mass: 981,859 kg (2,164,628 lb). Empty Mass: 132,000 kg (291,000 lb). Thrust (vac): 14,700.000 kN (3,304,600 lbf). Isp: 293 sec. Burn time: 164 sec. Isp(sl): 258 sec. Diameter: 7.00 m (22.90 ft). Span: 40.00 m (131.00 ft). Length: 65.00 m (213.00 ft). Propellants: N2O4/Aerozine-50. No Engines: 9. Status: Study 1962. Comments: Delta wing configuration. LR87-derivative engines.

• Stage 2. 1 x Astrorocket-2. Gross Mass: 151,927 kg (334,941 lb). Empty Mass: 23,500 kg (51,800 lb). Thrust (vac): 2,150.000 kN (483,330 lbf). Isp: 345 sec. Burn time: 181 sec. Isp(sl): 230 sec. Diameter: 3.00 m (9.80 ft). Span: 20.00 m (65.00 ft). Length: 30.00 m (98.00 ft). Propellants: N2O4/Aerozine-50. No Engines: 1. Status: Study 1962. Comments: X-20 Dynasoar configuration. LR87-derivative engines.