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The size and complexity of the motors necessitated massive facilities for motor and propellant production, static testing, and supporting activities. The
Florida facility construction combined these facilities into a single integrated facility. The diameter of the rocket motors made transport by rail impossible, as casings were restricted to a 156-inch diameter. To solve this problem Aerojet constructed a new canal leading to their facility in Florida which allowed for delivery of the boosters by barge.
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70:. Aerojet won out in the end when Thiokol's test chamber burst at 56% of proving pressure during a stress test. The burst was due to signals from a new Acoustical Non-Destructive Test system being ignored, as conventional strain gauges showed no problem. On the flip side, the Aerojet chambers survived testing due to changes in heat treatment of the material and welding practices.
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The test director was Will
Spratling, and the program manager for the motor development was Dick Cottrell, Vice President of the Aerojet Solid Rocket Plant. Due to the large undertaking of the 260-inch motor development, many Aerojet staff had to move to a new Florida facility headed by Paul Datner.
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Two tests of the boosters (SL-1 and SL-2) were carried out and were reportedly visible up to 80 miles away. The results from the test firings of test motors SL-1 and SL-2 showed a maximum thrust value of 3.5 million pounds (15.7 meganewtons) and a burn time of 114 seconds. The firings used six tons
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31 miles away. The SL-3 motor was also test-fired using improvements based on the two previous firings. It resulted in the largest single motor ever fired on Earth at 5.6 million pounds (26.2 meganewtons) of thrust. Since SL-3 used the same casing design and materials as the previous boosters, the
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In the 1960s, the 260 was initially designed to test the feasibility of solid rocket motors for space exploration, including use on the lower stage of the
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change in thrust was obtained from adding a nozzle to the end. The third test motor (SL-3) remains in the test silo to this day.
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Investigation of
Hydrotest Failure of Thiokol Chemical Corporation 260-Inch-Diameter SL-1 Motor Case (NASA TM X-1194)
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The
Metallurgy, Behavior, and Application of the 18-Percent Nickel Maraging Steels (NASA SP-5051)
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66:. Development of the motors was originally given as parallel contracts to Aerojet and
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282:"SL-1: 260-inch solid rocket motor test firing – Aerospace Projects Review Blog"
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182:. Indianapolis, IN, U.S.A.: American Institute of Aeronautics and Astronautics.
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155:. Las Vegas, NV, U.S.A.: American Institute of Aeronautics and Astronautics.
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176:"The History of Large Solid Rocket Motor Development in the United States"
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propellant a second, producing a column of white-hot fire visible in
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35th AIAA/ASME/SAE/ASEE Joint
Propulsion Conference and Exhibit
307:"STATUS OF THE 260-INCH DIAMETER SOLID ROCKET MOTOR PROGRAM"
149:"Methods used for Space Shuttle SRB thrust shape design"
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220:"THE 260 - The Largest Solid Rocket Motor Ever Tested"
218:Crimmins; Cousineau; Rogers; Shell (June 1999).
174:Andrepont, Wilbur; Felix, Rafael (1994-06-27).
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180:30th Joint Propulsion Conference and Exhibit
46:constructed and tested in the mid-1960s by
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377:This article about aircraft engines is a
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34:Aerojet 260 motor test, 25 September 1965
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127:1,858,300 lb (842,910.7 kg)
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201:Hall, A. M.; Slunder, C. J. (1968).
381:. You can help Knowledge (XXG) by
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153:14th Joint Propulsion Conference
286:www.aerospaceprojectsreview.com
27:Experimental solid rocket motor
305:Ciepluch, Carl (8 June 1967).
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147:Baker, J. (1978-07-25).
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42:was an experimental
339:www.astronautix.com
262:www.astronautix.com
188:10.2514/6.1994-3057
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433:Rocketdyne engines
428:Solid-fuel rockets
161:10.2514/6.1978-986
111:80.7 feet (24.6m)
103:260 inches (6.6m)
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422:Categories
344:2023-05-02
291:2022-10-29
267:2023-05-01
258:"AJ-260-2"
134:References
100:Diameter
335:"AJ-260"
64:Saturn V
246:. NASA.
207:. NASA.
108:Length
68:Thiokol
58:History
48:Aerojet
18:AJ-260
319:1 May
310:(PDF)
223:(PDF)
124:mass
84:Miami
379:stub
321:2023
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