** Proud Lifetime Member - Veteran of Foreign Wars of the United States **
New Atlas II AS Model Replica - 1/144 Scale NASA / Lockheed Martin Rocket Model.
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Background:
American orbital launch vehicle. The Atlas II booster was 2.7-meters longer than the Atlas I and included uprated Rocketdyne MA-5A engines. The Atlas I vernier engines were replaced with a hydrazine roll control system. The Centaur stage was stretched 0.9-meters compared to the Centaur I stage. Fixed foam insulation replaced Atlas I's jettisonable insulation panels. Higher performance RL10A-4 or RL10A-4-1 engines replaced Atlas II's RL10A-3-3A. The Atlas IIAS model added four Thiokol Castor IVA solid rocket boosters (SRBs) to the core Atlas stage to augment thrust for the first two minutes of flight.Status: Retired 2004. First Launch: 1993-12-16. Last Launch: 2004-08-31. Number: 30 . Payload: 8,610 kg (18,980 lb). Thrust: 3,546.30 kN (797,240 lbf). Gross mass: 234,000 kg (515,000 lb). Height: 47.50 m (155.80 ft). Diameter: 4.90 m (16.00 ft). Apogee: 185 km (114 mi).
The RL10A-4 and RL10A-4-1 engines were offered with or without extendable nozzles (which increased engine specific impulse, providing additional performance if required). The Atlas IIAS' first SRB pair was ignited at liftoff and burned for 54 seconds. The second pair was ignited in flight when vehicle loading constraints were satisfied. Both pairs were jettisoned shortly after their respective burnouts. The first Atlas IIAS successfully launched AC-108 / Telstar 401 on 15 December 1993.
LEO Payload: 8,610 kg (18,980 lb) to a 185 km orbit at 28.50 degrees. Payload: 3,630 kg (8,000 lb) to a GTO. Launch Price $: 105.000 million in 1994 dollars.
Stage Data - Atlas IIAS
- Stage 0. 4 x Castor 4A. Gross Mass: 11,743 kg (25,888 lb). Empty Mass: 1,529 kg (3,370 lb). Thrust (vac): 478.309 kN (107,528 lbf). Isp: 266 sec. Burn time: 56 sec. Isp(sl): 237 sec. Diameter: 1.02 m (3.34 ft). Span: 1.02 m (3.34 ft). Length: 9.12 m (29.92 ft). Propellants: Solid. No Engines: 1. Engine: Castor 4A. Status: In Production.
- Stage 1. 1 x Atlas MA-5AS. Gross Mass: 5,632 kg (12,416 lb). Empty Mass: 5,632 kg (12,416 lb). Thrust (vac): 2,093.700 kN (470,682 lbf). Isp: 299 sec. Burn time: 172 sec. Isp(sl): 263 sec. Diameter: 4.90 m (16.00 ft). Span: 4.90 m (16.00 ft).Propellants: Lox/Kerosene. No Engines: 2. Engine: RS-56-OBA. Status: In Production.
- Stage 2. 1 x Atlas IIAS. Gross Mass: 161,950 kg (357,030 lb). Empty Mass: 6,050 kg (13,330 lb). Thrust (vac): 386.300 kN (86,844 lbf). Isp: 316 sec. Burn time: 283 sec. Isp(sl): 220 sec. Diameter: 3.05 m (10.00 ft). Span: 3.05 m (10.00 ft). Length: 24.90 m (81.60 ft). Propellants: Lox/Kerosene. No Engines: 1. Engine: RS-56-OSA. Status: In Production.
- Stage 3. 1 x Centaur IIA. Gross Mass: 19,073 kg (42,048 lb). Empty Mass: 2,293 kg (5,055 lb). Thrust (vac): 185.012 kN (41,592 lbf). Isp: 449 sec. Burn time: 392 sec. Diameter: 3.05 m (10.00 ft). Span: 3.05 m (10.00 ft). Length: 10.10 m (33.10 ft). Propellants: Lox/LH2. No Engines: 2. Engine: RL-10A-4. Status: In Production.
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