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Aviation History
1972
1972 - 0054.PDF
38 FLIGHT International, 6 January 1972 MARS 3 Mars 3, or a test model, is shown in flight configuration, right, resting on a frame-stand in the assembly shed. Solar panels art deployed but the S-band antenna dish still retains a protective cover. The line marking the base of the descent capsule runs behind the central of three Conical VHF aerials, below which are two spherical tanks for attitude- control fuel. Scientific and attitude-control sensors are arrayed around the base IN PHOTOGRAPHS just released of the Soviet Mars 3 space craft, the overall assembly, including landing capsule, appears to be approximately 12ft, 3-6m in height. The pictures follow the standard Soviet practice of excluding any clues to accurate estimation of size. The total weight was given shortly after launch in May last year as 10,1501b, 4,604kg, of which more than half probably consisted of fuel. All evidence so far has indicated that both Mars 2 and Mars 3 are near-identical. Izvestia recently published an interview with the designers (un-named as usual but, significantly, not the chief designer), in which the apparently somewhat incongruous design was forcefully justified on the grounds of pure rationality. The spacecraft are built around the main hypergolic fuel tanks, which form the central cylinder. To this are attached the S-band directional antenna and two deployable solar panels. Fuel is carried through externally mounted lines to the engine concealed in the base. One of the lines, that from the lower tank, is considerably extended into a long loop fitted into a panel projecting from the side of the tank structure. The panel, aligned with the solar arrays, is possibly some form of fuel-conditioning system or space craft radiating device. The engine is attached to the base of the tank structure, according to the Izvestia report, and is completely enclosed in a doughnut-shaped compartment, or toroid, containing electronics and instruments. This compartment is attached to the main body cylinder by an enshrouding skirt. This arrangement was justified on the grounds that it minimised interconnection and facilitated inspection during assembly. The descent craft remains, as yet, somewhat enigmatic. It comprises a wide basin-like heat shield over a sphere resting in a toroid. Below this is a short cylinder from which projects an engine nozzle. In a diagram of the lander, the toroidal compartment was classified as the main parachute container and the sphere as the "automatic Mars station." The engine was, however, stated to be for spacecraft separation-thrust alone. This would suggest that no braking thrust was used, contradictory to Soviet statements. The heat shield is sized to provide maximum aerodynamic braking within the limits of weight and launch-vehicle dimensions. Atmospheric penetration at about 13,500 m.p.h., 21,600km/hr necessitated protection against tem peratures stated to reach several thousand degrees. According to Izvestia, use of a larger, collapsible shield was considered likely to increase the risk of failure. Instead,
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