American low cost orbital launch vehicle. Low-cost hybrid launch vehicle proposed by AMROC in the 1980's.
LEO Payload: 1,818 kg (4,008 lb) to a 217 km orbit. Launch Price $: 8.000 million in 1985 dollars. Flyaway Unit Cost $: 19.000 million in 1987 dollars.
Stage Data - Industrial Launch Vehicle
- Stage 0. 12 x AMROC. Gross Mass: 31,000 kg (68,000 lb). Empty Mass: 5,900 kg (13,000 lb). Thrust (vac): 931.330 kN (209,371 lbf). Isp: 284 sec. Burn time: 75 sec. Isp(sl): 283 sec. Diameter: 1.83 m (6.00 ft). Span: 1.83 m (6.00 ft). Length: 19.50 m (63.90 ft). Propellants: Lox/Solid. No Engines: 1. Engine: H1500. Other designations: Aquila. Status: Development 1988.
- Stage 1. 4 x AMROC. Gross Mass: 31,000 kg (68,000 lb). Empty Mass: 5,900 kg (13,000 lb). Thrust (vac): 931.330 kN (209,371 lbf). Isp: 284 sec. Burn time: 75 sec. Isp(sl): 283 sec. Diameter: 1.83 m (6.00 ft). Span: 1.83 m (6.00 ft). Length: 19.50 m (63.90 ft). Propellants: Lox/Solid. No Engines: 1. Engine: H1500. Other designations: Aquila. Status: Development 1988.
- Stage 2. 2 x AMROC. Gross Mass: 31,000 kg (68,000 lb). Empty Mass: 5,900 kg (13,000 lb). Thrust (vac): 931.330 kN (209,371 lbf). Isp: 284 sec. Burn time: 75 sec. Isp(sl): 283 sec. Diameter: 1.83 m (6.00 ft). Span: 1.83 m (6.00 ft). Length: 19.50 m (63.90 ft). Propellants: Lox/Solid. No Engines: 1. Engine: H1500. Other designations: Aquila. Status: Development 1988.
- Stage 3. 1 x AMROC. Gross Mass: 31,000 kg (68,000 lb). Empty Mass: 5,900 kg (13,000 lb). Thrust (vac): 931.330 kN (209,371 lbf). Isp: 284 sec. Burn time: 75 sec. Isp(sl): 283 sec. Diameter: 1.83 m (6.00 ft). Span: 1.83 m (6.00 ft). Length: 19.50 m (63.90 ft). Propellants: Lox/Solid. No Engines: 1. Engine: H1500. Other designations: Aquila. Status: Development 1988.
AKA: Aquila.
Status: Design 1988.
Gross mass: 591,180 kg (1,303,320 lb).
Payload: 1,818 kg (4,008 lb).
Height: 70.00 m (229.00 ft).
Diameter: 1.83 m (6.00 ft).
Thrust: 11,136.70 kN (2,503,630 lbf).
Apogee: 217 km (134 mi).
More... - Chronology...
Associated Countries
Associated Engines
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H1500 Notional Lox/Solid hybrid rocket engine. 931.3 kN. Design 1988. Isp=284s. Used on Industrial Launch Vehicle launch vehicle. More...
See also
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LCLV Various independently-funded launch vehicles have been advocated, designed, and even developed over the years. A lot of these are attempts to build low-cost launch vehicles using simpler technology. Often such projects begin based on a low cost liquid fuel technology but end up just trying to sell various combinations of Castor solid fuel stages. These enterprises often discover there's more to coming up with a reliable launch vehicle than slashing together a bunch of 'off the shelf' rocket motors and lighting the fuse.... On the other hand, if there is ever a breakthrough in less expensive access to space, it will come through one of these entrepreneurial schemes... More...
Associated Manufacturers and Agencies
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eAc American manufacturer of rocket engines and rockets. eAc, USA. More...
Bibliography
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Interplanetary Spacecraft,
Associated Stages
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AMROC Lox/Solid propellant rocket stage. Loaded/empty mass 31,000/5,900 kg. Thrust 931.33 kN. Vacuum specific impulse 284 seconds. More...
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