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Blue Scout I

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AKA: Blue Scout 1;RM-89;XRM-89. Status: Retired 1962. First Launch: 1961-01-07. Last Launch: 1962-04-12. Number: 3 . Payload: 88 kg (194 lb). Thrust: 511.50 kN (114,990 lbf). Gross mass: 16,738 kg (36,900 lb). Height: 22.00 m (72.00 ft). Diameter: 1.02 m (3.34 ft). Apogee: 1,386 km (861 mi).

NASA began development of the Scout in the late 1960's to provide a low-cost, lightweight, all-solid-propellant space booster. The U.S. Air Force participated, but as usual divergence in requirements led to a different prime contractor and different configuration for the Air Force. The USAF program for System 609A, the Hyper Environmental Test System, resulted in a vehicle referred to as Blue Scout, with Ford Aeronutronics as the prime contractor. The Blue Scout I program was terminated in 1962 after only one success in three launches..

Payload: 88 kg (194 lb) to a 1386 km altitude, 2419 km range.

Stage Data - Blue Scout 1

• Stage 1. 1 x Algol 1. Gross Mass: 10,705 kg (23,600 lb). Empty Mass: 1,900 kg (4,100 lb). Thrust (vac): 470.934 kN (105,870 lbf). Isp: 236 sec. Burn time: 40 sec. Isp(sl): 214 sec. Diameter: 1.01 m (3.31 ft). Span: 1.01 m (3.31 ft). Length: 9.12 m (29.92 ft). Propellants: Solid. No Engines: 1. Engine: Algol 1. Other designations: Senior. Status: Out of Production. This rocket started as a Polaris test motor with a 40 inch diameter, which at the time was the largest solid motor ever tested. It had a nominal performance rating of 45 seconds duration and 45,000 kgf thrust. Variations included Algol I, I-D, II, II-A, II-B and possibly others. Another popular rating was 40KS-115,000 (52,000 kgf for 40 seconds), also known as Senior.

• Stage 2. 1 x Castor 2. Gross Mass: 4,424 kg (9,753 lb). Empty Mass: 695 kg (1,532 lb). Thrust (vac): 258.915 kN (58,206 lbf). Isp: 262 sec. Burn time: 37 sec. Isp(sl): 232 sec. Diameter: 0.79 m (2.59 ft). Span: 0.79 m (2.59 ft). Length: 6.04 m (19.81 ft). Propellants: Solid. No Engines: 1. Engine: TX-354-3. Status: In Production.

• Stage 3. 1 x Antares 1A. Gross Mass: 1,225 kg (2,700 lb). Empty Mass: 294 kg (648 lb). Thrust (vac): 60.497 kN (13,600 lbf). Isp: 256 sec. Burn time: 39 sec. Isp(sl): 233 sec. Diameter: 0.78 m (2.55 ft). Span: 0.78 m (2.55 ft). Length: 3.38 m (11.08 ft). Propellants: Solid. No Engines: 1. Engine: X-254. Status: Out of Production.

• HETS A1-1 Plasma / radio astronomy mission - . Nation: USA. Agency: USAF. Apogee: 1,600 km (900 mi).

• HETS A1-2 Plasma mission - . Nation: USA. Agency: USAF. Apogee: 10 km (6 mi).

• Reentry Test re-entry vehicle test flight - . Nation: USA. Agency: USAF. Apogee: 30 km (18 mi).