SLS AB-825

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SLS AB-825

Part of SLS

SLS AB-825
Credit: © Mark Wade

American orbital launch vehicle. The AB-825 represented a medium launch vehicle of the USAF 1961 Space Launching System family. The AB-825 would have conducted earth orbit tests of partially-fuelled Lunex lunar lander stages, and also have boosted the Lunex manned glider on circumlunar test flights. It consisted of the 'A' stage and 'B' stages with 180 inch diameter short-length solid fuel booster motors.

AKA: Space Launching System AB-825. Status: Study 1961. Payload: 39,460 kg (86,990 lb). Thrust: 14,700.00 kN (3,304,600 lbf). Gross mass: 1,000,000 kg (2,200,000 lb). Height: 55.00 m (180.00 ft). Diameter: 7.62 m (24.99 ft). Span: 16.76 m (54.98 ft). Apogee: 560 km (340 mi).

LEO Payload: 39,460 kg (86,990 lb) to a 560 km orbit at 28.00 degrees. Payload: 10,890 kg (24,000 lb) to a translunar trajectory.

Stage Data - SLS AB-825

Stage 1. 2 x SLS SRB 2720. Gross Mass: 366,716 kg (808,470 lb). Empty Mass: 56,000 kg (123,000 lb). Thrust (vac): 8,130.000 kN (1,827,690 lbf). Isp: 260 sec. Burn time: 100 sec. Isp(sl): 235 sec. Diameter: 4.57 m (14.99 ft). Span: 4.57 m (14.99 ft). Length: 51.00 m (167.00 ft). Propellants: Solid. No Engines: 1. Status: Study 1961. Comments: Four such 180 inch segmented solid rocket motors provided first stage thrust for Project Lunex. A liquid propellant first stage was considered as an alternative, but the solid stage was the baseline. Empty mass, specific impulse estimated.

Stage 2. 1 x SLS Stage B. Gross Mass: 160,000 kg (350,000 lb). Empty Mass: 11,200 kg (24,600 lb). Thrust (vac): 1,778.651 kN (399,857 lbf). Isp: 424 sec. Burn time: 345 sec. Diameter: 7.62 m (24.99 ft). Span: 7.62 m (24.99 ft). Length: 25.00 m (82.00 ft). Propellants: Lox/LH2. No Engines: 2. Engine: J-2. Status: Study 1961. Comments: Translunar injection stage for Project Lunex. Masses estimated based on optimum apportioning of B+C stage total masses.

Stage 3. 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.

Family: orbital launch vehicle. Country: USA. Stages: SLS Stage A, SLS Stage B, SLS SRB 2720. Agency: USAF.

Photo Gallery

Lunex A-410 LV
Provisional drawing of Lunex A-410 launch vehicle.

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