Encyclopedia Astronautica
Home - Search - Browse - Alphabetic Index: 0- 1- 2- 3- 4- 5- 6- 7- 8- 9
A- B- C- D- E- F- G- H- I- J- K- L- M- N- O- P- Q- R- S- T- U- V- W- X- Y- Z

Soltan
Part of Titan Family
American orbital launch vehicle. The progenitor of the Titan 3 was this design, which used two, 3 segment, 100 inch diameter solid rocket boosters. The 100 inch segmented boosters had already been ground-fired by Aerojet. However the final decision was to develop the more-capable Titan 3C with 5 segment, 120 inch diameter solid rocket boosters.

Status: Study 1961. Payload: 8,030 kg (17,700 lb). Thrust: 6,021.00 kN (1,353,574 lbf). Gross mass: 388,560 kg (856,620 lb). Height: 40.40 m (132.50 ft). Diameter: 3.05 m (10.00 ft). Span: 15.70 m (51.50 ft). Apogee: 148 km (91 mi).

The original design submitted for the SLV-4 competition had two 2.54 m diameter solid boosters.

LEO Payload: 8,030 kg (17,700 lb) to a 148 km orbit at 28.00 degrees.

Stage Data - Soltan

  • Stage 0. 2 x 100 inch solid. Gross Mass: 115,350 kg (254,300 lb). Empty Mass: 12,000 kg (26,000 lb). Thrust (vac): 3,330.000 kN (748,610 lbf). Isp: 260 sec. Burn time: 80 sec. Isp(sl): 235 sec. Diameter: 2.54 m (8.33 ft). Span: 2.54 m (8.33 ft). Length: 15.60 m (51.10 ft). Propellants: Solid. Status: Development 1961. Three-segment solid motor proposed for the Solid Titan II in the SLV-4 competition. Aerojet test fired motors with up to five segments, producing an average thrust of 268,000 kgf for 120 seconds. The 100 inch diameter was dictated by the diameter of Aerojet's existing heat treating furnace. The segmented motor approach was dictated by the Air Force, since they required the motors to be moved by rail to Vandenberg, and a full-length motor could not be handled by the rail system. Aerojet fired four test motors, with the graphite nozzles disintegrating at 45 and 55 seconds into the burn in the last tests.
  • Stage 1. 1 x Titan 2-1. Gross Mass: 117,866 kg (259,850 lb). Empty Mass: 6,736 kg (14,850 lb). Thrust (vac): 2,172.231 kN (488,337 lbf). Isp: 296 sec. Burn time: 139 sec. Isp(sl): 258 sec. Diameter: 3.05 m (10.00 ft). Span: 3.05 m (10.00 ft). Length: 22.28 m (73.09 ft). Propellants: N2O4/Aerozine-50. No Engines: 2. Engine: LR-87-7. Status: In Production.
  • Stage 2. 1 x Titan 2-2. Gross Mass: 28,939 kg (63,799 lb). Empty Mass: 2,404 kg (5,299 lb). Thrust (vac): 444.819 kN (99,999 lbf). Isp: 316 sec. Burn time: 180 sec. Isp(sl): 160 sec. Diameter: 3.05 m (10.00 ft). Span: 3.05 m (10.00 ft). Length: 7.86 m (25.78 ft). Propellants: N2O4/Aerozine-50. No Engines: 1. Engine: LR-91-7. Status: Out of Production.

Family: orbital launch vehicle. Country: USA. Spacecraft: Dynasoar. Stages: Titan 2-1, Titan 2-2, 100 inch solid. Agency: Martin. More at: 8656.



Home - Search - Browse - Alphabetic Index: 0- 1- 2- 3- 4- 5- 6- 7- 8- 9
A- B- C- D- E- F- G- H- I- J- K- L- M- N- O- P- Q- R- S- T- U- V- W- X- Y- Z
© 1997-2016 Mark Wade - Contact
© / Conditions for Use