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Aviation History
1960
1960 - 0561.PDF
I LIGHT, 22 April 1960 561 DASSAULT MIRAGE Ill-C One SNECMA Atar 9C turbojet plus (optional) one SEPR 841 rocket pack. Data far these are given below. Dimensions and weights Span, 17ft; length, 45ft 5in; height, 14ft 9in; wing c-ea, 366 sq ft; t/c ratio, 3.5%; leading-edge sweep, 60° 34'; track, 10ft 10in- vbeelbase, 15ft 9in; empty weight, 12,3501b; gross weight, normally from 17,600 ; 22,860lb (see mission table); landing weight, 14,5501b. Performance Take-off run, 2,000 to 2,800ft depending on mission; climb in ; tercepter role, 30,000ft in 3 min, 72,000ft in 9 min; operational ceiling, 82.000ft; onomical cruise, M0.9 at 40,000ft; combat speed, Ml.8; max speed at 36,000ft! K2.3; landing run, with drag chute, 2,000 to 2,800ft. Powerplants Turbojet, sea-level thrust, 9,3701b dry or 14.1001b with after- burner; specific consumption, 1.0 dry or 2.075 with afterburner; dry weight, 2 7551b. Rocket, sea-level thrust either 1,650 or 3,37Olb (no intermediate value); max thrust at 52,000ft, 3,700lb; specific consumption at full thrust. 0.0048lb/lb/sec or sea level, 0.00435 at 52,OOOft; dry weight of complete pack, 450lb. between the beam, spars and rear root rib is divided into 28 cellsby pierced-and-flanged sheet-metal diaphragms, set normal to and parallel with the aircraft centreline, which preserve the aerofoilprofile. Upper and lower skins of the torsion box are each made from two thick panels cut on Onsrud millers. The stiffening ribslie normal to the centreline, and ridges (or bosses) support both the normal and parallel webs. The whole of this volume is anintegral tank, except for the triangular tip cell and a dry-tunnel at mid-span respectively for part of the aileron and elevator jacks. Ahead of the main beam the structure is cut out for the under-carriage, with a machined diagonal diaphragm carrying the front fulcrum for the leg and two fore-and-aft webs which support theair-brake hinges. Attached to the diagonal spar is the leading- edge, with close-set riblets braced by diaphragms, pairs inboardand single outboard. Push-pull control rods are mounted ahead of the diagonal spar; since the leading-edge is a fixture, accessis by handholes. Hinged trailing-edge sections are simple, with extruded-channelspars (open end facing forward) and closely spaced ribs. As the chord is considerable there is a second reinforcing spar. Elevatorsand ailerons are actuated at mid-span, and each has a boxed rib at that point incorporating a machined "bloater," the base of whichextends between the spars and provides a large leverage for the power-unit jack. The inboard trim flaps have their spars reinforcedby a torque tube, because the jack operates from inside the fuselage. Although the fin is subjected to high aerodynamic loading inbending and torsion, it does not suffer the concentrated loads of the undercarriage nor the weakening effect of the cut-out. Thereare three spars of built-up I-section, with pierced-and-flanged interspar ribs and diaphragms. Aft of the rear spar is a shroudstructure which shields the small rudder, which is similar in construction to the wing controls. Aerofoil surfaces are manufactured by Nord-Aviation, althoughmajor machining tasks, such as the wing skins, root ribs and main beam, are done at Argenteuil. Finishing of the skin panelsincluded shot-peening for stress relief. In addition to normal machining methods on large tools, Dassault has a chemical millingplant used for the rough-cut stage. Since the ability to use 1,000yd PSP strips was part of therequirement, the Mirage is fitted with medium-pressure (75-1151b/sq in) tyres. The main legs are pulled inboard byjacks attached to the root rib. The nose-wheel is mounted on a trail arm and a shimmy damper is fitted to the steering head onthe compression leg. All three wheels are carried on stub axles, so that they can be removed with only local jacking of the half fork.The engine is installed on trunnions accessible through hand- holes. The Atar and its afterburner are assembled beforeinstallation. Only the cylindrical tail cowling needs to be taken off for engine removal, and there are ample handholes and panelsfor ordinary servicing. A refractory shield is fitted to the rear fuselage round die engine combustion zone, jet pipe and variable-area nozzle. As revealed at present, the Mirage has an Atar 9 with a clamshell propelling nozzle, but the Mirage IV bomber has amulti-leaf convergent/divergent supersonic nozzle, and there would appear to be space for the latter in the fighter—if thegain in efficiency on relatively brief flights is worth the weight. In addition to die wing tanks there are flexible cells round theintake duct which bring the normal internal capacity to 480gal. Employed to boost combat performance, the rocket pack incor-porates die turbopump—driven by quill-shaft from the accessory gearbox—tubular thrust framework and stainless-steel acid tank.The fixed reaction chamber projects down at about 10°. By undoing six bolts, the pack can be replaced by a 90gal fuel tank.Accessibility and maintenance have been carefully studied. Radar is packaged in the nose. Radio, tank pressurization and some sys-tems components lie between the intake ducts and are reached by removing the upper panels. Engine accessories and servicing points
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