Encyclopedia Astronautica
SLS A-410



lunexlvb.jpg
Lunex B-825 LV
Provisional drawing of Lunex B-825 launch vehicle.
a410.jpg
SLS A-410
Credit: © Mark Wade
American orbital launch vehicle. The smallest identified member of the SLS family, selected to place the Air Force Lunex lunar lander re-entry vehicle in a low earth orbit for initial tests, was the A-410. This consisted of the 'A' Lox/LH2 stage supplemented by 100-inch diameter solid fuel booster rockets.

LEO Payload: 9,070 kg (19,990 lb) to a 560 km orbit at 28.00 degrees.

Stage Data - SLS A-410

  • Stage 1. 4 x SLS SRB 388. Gross Mass: 88,000 kg (194,000 lb). Empty Mass: 13,000 kg (28,000 lb). Thrust (vac): 2,083.900 kN (468,479 lbf). Isp: 260 sec. Burn time: 90 sec. Isp(sl): 235 sec. Diameter: 2.58 m (8.46 ft). Span: 2.58 m (8.46 ft). Length: 16.40 m (53.80 ft). Propellants: Solid. No Engines: 1. Status: Study 1961. Comments: Booster for SLS A series launch vehicles.
  • Stage 2. 1 x SLS Stage A. Gross Mass: 59,000 kg (130,000 lb). Empty Mass: 6,000 kg (13,200 lb). Thrust (vac): 889.325 kN (199,928 lbf). Isp: 424 sec. Burn time: 250 sec. Diameter: 4.28 m (14.04 ft). Span: 4.28 m (14.04 ft). Length: 15.00 m (49.00 ft). Propellants: Lox/LH2. No Engines: 1. Engine: J-2. Status: Study 1961. Comments: Smallest Lox/LH2 stage planned for SLS series. Empty mass estimated. Sized for rail transport within USA.

AKA: Space Launching System A-410.
Status: Study 1961.
Gross mass: 420,000 kg (920,000 lb).
Payload: 9,070 kg (19,990 lb).
Height: 27.00 m (88.00 ft).
Diameter: 7.62 m (24.99 ft).
Span: 18.60 m (61.00 ft).
Thrust: 7,553.00 kN (1,697,981 lbf).
Apogee: 560 km (340 mi).

More... - Chronology...


Associated Countries
See also
  • SLS In the mid-1950's, US Air Force-funded studies identified the optimum long-term solution for space launch. The studies indicated the desirability of segmented solids for a first stage to achieve low cost, high reliability and flexibility of basic booster size by adding or subtracting segments. Studies further showed that oxygen-hydrogen propellants, with their very high specific impulse, were a preferred choice for upper stages, where mass was more important. This choice also resulted in minimum systems cost. More...

Associated Manufacturers and Agencies
  • USAF American agency overseeing development of rockets and spacecraft. United States Air Force, USA. More...

Associated Stages
  • SLS SRB 388 Solid propellant rocket stage. Loaded/empty mass 88,000/13,000 kg. Thrust 2,083.90 kN. Vacuum specific impulse 260 seconds. Booster for SLS A series launch vehicles. More...
  • SLS Stage A Lox/LH2 propellant rocket stage. Loaded/empty mass 59,000/6,000 kg. Thrust 889.33 kN. Vacuum specific impulse 424 seconds. Smallest Lox/LH2 stage planned for SLS series. Empty mass estimated. Sized for rail transport within USA. More...

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