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RM-90 Blue Scout II - Wikipedia

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U.S. sounding rocket, 1961

Blue Scout II rocket

Function Expendable launch system
Sounding rocket Manufacturer Vought Country of origin United States Height 24 metres (79 ft) Diameter 1.02 metres (3 ft 4 in) Mass 16,874 kilograms (37,201 lb) Stages Four Mass 30 kilograms (66 lb) Family Scout Status Retired Launch sites Canaveral LC-18B Total launches 3 Success(es) 2 Failure(s) 1 First flight 1961-03-03 Last flight 1961-11-01 Powered by 1 solid Maximum thrust 471 kilonewtons (106,000 lbf) Specific impulse 236 sec Burn time 40 seconds Propellant Solid Powered by 1 TX-354-3 Maximum thrust 286 kilonewtons (64,000 lbf) Specific impulse 247 sec Burn time 27 seconds Propellant Solid Powered by 1 X-254 Maximum thrust 60 kilonewtons (13,000 lbf) Specific impulse 256 sec Burn time 39 seconds Propellant Solid Powered by 1 X-248A Maximum thrust 14 kilonewtons (3,100 lbf) Specific impulse 255 sec Burn time 40 seconds Propellant Solid

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The RM-90 Blue Scout II was an American sounding rocket and expendable launch system which was flown three times during 1961.[1][2][3] It was a member of the Scout family of rockets.[4] Blue Scout II was a military version of the NASA-operated Scout X-1, with adjustments to the payload fairings, engine nozzles and fins.[1][3]

Blue Scout II had a total length of 21.65 m and a finspan of 2.84 m.

It was capable of sending a 30 kg payload to a 300 km orbit at 28.00 degrees.[1] It was a four stage vehicle, with the following engines:[1][2][3][5]


Blue Scout II was used for two HETS test flights, and the launch of the Mercury-Scout 1 satellite for NASA.[1][2][6] This rocket and RM-89 Blue Scout I were replaced by Blue Scout Junior.[3]

Blue Scout II parameters[edit]

All three Blue Scout II launches occurred from Launch Complex 18B at the Cape Canaveral Air Force Station, the same launch pad used for the Blue Scout I.[1][2]

The first two launches were successfully conducted on 3 March and 12 April 1961 respectively, using vehicles D-4 and D-5.[1][2][7] They both carried HETS A2 plasma research experiments on suborbital trajectories.

The third launch was conducted on 1 November, using vehicle D-8, with the Mercury-Scout 1 satellite for NASA, which was intended to reach low Earth orbit.[6] The launch failed after the rocket went out of control, and was destroyed by the range safety officer 43 seconds after liftoff.[1][2]

Date Serial Agency Orbit Mission Description 1961 March 3 D-4 USAF Suborbital, 2540 km apogee[7] HETS A2-1 plasma mission 1961 April 12 D-5 USAF Suborbital, 1931 km apogee[7] HETS A2-2 plasma mission 1961 November 1 D-8 USAF 373 km × 643 km, 32.5° (planned)[6] Mercury-Scout 1 (failure)

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