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Aviation History
1962
1962 - 0619.PDF
i LIGHT International, 19 April 1962 617 AND ITS FUTURE DEVELOPMENT OPPOSITE is a dramatic photograph of the launch at Cape Canaveral on October 27, 1961, of the first flight example of the Saturn S-l booster—the largest launch vehicle outside the Soviet Union. As we reported on April 5, the US National Aero nautics and Space Administration has invited 15 companies to submit proposals for the even larger Nova vehicle, but Saturn will remain the only large booster in the Western world for six years to come. The project had its inception at the Development Operations Division of the Army Ballistic Missile Agency at Huntsville, Alabama. Preliminary designs were sketched five years ago, and by the autumn of 1958 the S-l first-stage configuration had been settled. As described in Flight for August 5, 1960, propulsion is provided by eight Rocketdyne H-l engines, each rated at 188,0001b at sea level, the four outboard engines being hung on gimbals to provide trajectory control. Propellants are fed from nine cylindrical tanks, the central 105in-diameter tank and four 70in (Jupiter-calibre) tanks containing liquid oxgyen and the remaining four 70in tanks housing RP-1 fuel. Huntsville was transferred to NASA on July 1, 1960, becoming the George C. Marshall Space Flight Center. Since that time the Saturn programme has been Marshall's largest single project. Pro duction S-l stages have a diameter of 22ft, a length of 82ft and a propellant capacity of 750,0001b or 850,0001b. Manufacture will be undertaken at the NASA Michoud Plant, 15 miles east of New Orleans. Last November a contract was negotiated with Chrysler for the manufacture, checkout and launching of 20 Block 2 S-l boosters. An additional ten Block 1 boosters are being manufac tured by NASA at Marshall, to fill the gap before the first Michoud- built S-l is shipped to the Cape early in 1964. The Block 2 S-l will house 850,0001b of propellants, will incorporate several engine improvements, and be equipped with detachable fins (photograph immediate right). These fins are needed to maintain control in engine-out conditions with the C-l two-stage vehicle with an Apollo spacecraft payload. It was originally envisaged that the Saturn C-l would be a three-stage vehicle for deep-space missions with payloads not greater than 5,0001b. Early last year the emphasis shifted to Earth orbit with the heavy Apollo spacecraft (unmanned at first). This change in role is reflected in a new C-l configuration with but two stages. The second stage is the S-4, at present the largest rocket vehicle designed by the US aerospace industry. The contract for ten S-4s was placed with Douglas Aircraft in May 1960. Studies indicate that transport to the Cape can be accomplished by mounting the S-4 above the fuselage of a Douglas C-l 33. As the diagram shows, the stage is roughly 41ft 6in long, and has a diameter tapering from 18ft 6in to 13ft. Capacity is 100,0001b of liquid oxygen and liquid hydrogen, empty weight being 11,5021b. Engines were to have been four Pratt & Whitney LR-119s, each rated at 17,5001b at sea level, but difficulties with the basic LR-115 have led to a major redesign. In its final form the S-4 will be powered by six LR-115 (RL-10A-3) engines, each rated at 15,0001b and simi lar to the engines used in Centaur. Although the weight and com plexity of the S-4 are increased, the thrust/weight ratio and engine- out performance are improved. This two-stage C-l vehicle could place 20,0001b in Earth orbit. The next major development will be the C-2, consisting of an S-l A (Block 2) first stage; an S-2 second stage, with four Rocketdyne •1-2 engines; and an S-4 third stage. The S-2 is to be compatible with the much larger Nova, in which it will be the third (LN-3) stage; it is the first application of the 200,0001b J-2 oxygen/hydrogen engine, and when contracts are let it will be the largest vehicle ever tackled by US industry. The C-2 will be able to orbit 45,0001b and accelerate 15,0001b to escape velocity. Its ability to accomplish an A polio circumlunar mission is marginal. The latter will probably require the much larger C-3. This will introduce the new S-1B first stage, 33ft in diameter and powered by two Rocketdyne F-ls, each rated at 1,500,0001b. Mated with an S-2 and an S-4, this could orbit 80,0001b and accelerate 30,0001b to escape velocity. As we reported last November 9, further develop ments include the C-4. with four F-ls, and the C-5 with five. Last Left, Saturn C-l model; right, sketch of Saturn C-4 December NASA announced negotiations with the Boeing Company for an advanced S-1B first stage, with "a cluster" of F-l engines and a gross weight of some 5,000,0001b (sketch above). Teamed with an S-2 and an S-4B this could orbit 200,0001b and accelerate 80,0001b to escape velocity. NASA awarded Douglas the S-4B contract in the same month; this will retain the 18ft 6in diameter of the S-4, but will be 75ft long and have a single J-2 engine. SATURN C-1 LAUNCH SCHEDULE 1961 (October27) One R & B shot down the Atlantic Missle Range of vehicle SA-1. comprising prototype Block I S-l stage, water-ballasted S-4 dummy and (defunct) S-5 third stage. Thrust per engine, I65,000lb; vehicle height, I62ft; lift-off weight, 925,000lb. 1962 Test shots SA-2 and SA-3, similar to above. 1963 Test shot SA-4 similar to above. Two firings (SA-5 and SA-6) with Block 2 S-l booster with I88.000lh engines and 850,000lb propellant capacity, live S-4 second stage, extended payload adapter and instrument compartment, aerodynamic fins on booster and simulated Apollo spacecraft payload. Two further firings (SA-7 and SA-8) to test "boiler plate" Apollo. Vehicle height. I70ft; lift-off weight. 1,100,0001b. 1964 SA-9 and SA-10, similar to SA-7 and SA-8. General arrangement of Douglas-built S-4 stage
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