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Aviation History
1962
1962 - 0090.PDF
90 FLIGHT International, 18 January * %•> ATLAS ATLAS ICBM DATA The following are basic data for the Atlas as the SM-65 ICBM; comparable figures for space vehicles cannot be given, for almost every shot is unique. Dimensions Overall length, 75ft lOin with Mk 2 re-entry vehicle, 82ft 6in with Mk 3 or Mk 4 and about 79ft with Mk 5; tank diameter, 10ft; diameter of re-entry vehicle adapter, 4ft; distance across booster skirt; 16ft. Weights Lift-off weight, approximately 255,0001b (Atlas D) or 260,0001b (Atlas E with Mk 4 vehicle); weight with re-entry vehicle but with tanks empty, approxi mately 20,0001b; weight of tank and sustainer, without booster section and payload, approximately 8,0001b. Propulsion Atlas D; Rocketdyne MA-2 cluster, comprising two 150,0001b (sea level rating) LR-89-3 boosters plus 57,0001b LR-105-3 sustainer. Also two 1,0001b LR-I0I-5, 6 or 7 verniers. Atlas E: Rocketdyne MA-3 cluster, comprising two 165,0001b LR-89-5 boosters, plus 57,0001b LR-105-5 sustainer. All engines operate on liquid oxygen and RP-I fuel, and are gimbal mounted. Performance Original design range, 5,500 n.m.; effective operational range, about 9,000 n.m.; burn-out Mach number 26 to 27. In this drawing the artist illustrates the principal features (ft Atlas ICBM. Although the main drawing depicts the entire mjs complete booster section, which is jettisoned some I45sec aftjr) shown separately for obvious reasons of clarity. No single At a$ J built to precisely the standard shown here, although in general tr, > is based on a D-series vehicle in the key these abbreviations apply: GH, gaseous helium; LH, liquid helium; LN, liquid nitrogen; Lox, liquid oxygen. Fuel is RP-/ wide-cut. 1 Lox tank, I20in diam, 2,503 cu ft, 26 Ib/sq in 2 Fuel tank, I20in diam, 1,542 cu ft, 60lb/sq in 3 Lox dome upper bulkhead 4 Inter-tank bulkhead, butt-welded petals 5 Fuel-tank aft bulkhead, stiffened to bear sustainer thrust 6 LH bottles with LN jackets (one for sustainer, five jettisoned with booster) 7 LH bottle without LN jacket, not jettisoned with booster 8 GH to pressurize Lox tank 9 GH to pressurize fuel tank (opposite side) wrapped strip, 36in X 10 AISI.30I O.OiOin 11 AISI.30I 36m 0.020m 12 AlSl.30l,36in 0.040in max 13 Each strip butt-welded and strapped 14 Each tank section "stove-piped," then seam- and spot-welded 15 24in access covers sealed by close- weave cheesecloth 16 Lox boil-off valve 17 Anti-slosh baffle assembly, not part of basic tank structure 18 Main Lox pipe (in and out), bifurcated at top against start suction 19 Welded doubler plates 20 Flexible contraction bellows 21 Lox butterfly valve and booster pull- off coupling 22 Adapter sleeve for (21) 23 Fuel butterfly valve and booster pull- off coupling 24 Adapter sleeve for (23) 25 Support bracing for (23) 26 Sustainer-engine gimbal and thrust pad 27 End-support struts for (46)
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