Lunex B-825 LV
Provisional drawing of Lunex B-825 launch vehicle.
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.
More... - Chronology...
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).
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...
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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