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Weapons of Mass Destruction (WMD)


Tu-113

The rapid development of air defense forces and means in the West in the late 1950s and early 1960s could significantly limit the capabilities of the Soviet Tu-95 and M-4 subsonic aircraft to break through air defense and deliver retaliatory nuclear strikes against targets in the United States and NATO countries. Before the developers of new aircraft technology, the issue of creating shock aviation systems capable of overcoming enemy air defenses at large supersonic speeds became acute.

Both in the USSR and in the USA, the main areas of work for the creation of intercontinental manned supersonic systems roughly coincided. The design of composite aviation systems based on the B-36 heavy intercontinental bombers developed in the series in the USA and Tu-95 in the USSR in combination with suspended supersonic bombers shock aircraft, armed with tactical atomic bombs. Another was the design of supersonic heavy aircraft - bombers or carriers of suspended aircraft and unmanned controlled airplane-projectiles.

In 1955, as one of the variants of suspension of the composite system, an unmanned supersonic long-range aircraft "113" (Tu-113), suspended under the fuselage Tu-95, was considered. The project in many respects was close to the work of OKB PV Tsybin on the manned pendant bomber "RS", under which at that time Tupolev prepared the carrier Tu-95N. The plane-projectile was to have a flight range of 3000-4000 km and a maximum speed of M = 2.5 at an altitude of 11,000-12,000 m.

By May 1955, preliminary materials for "113" (Tu-113) had been prepared. A suspended unmanned airplane-projectile with a wing of a small extension with a sweep of 60 was offered, two TR-D-20s or VK-11s were planned at its ends, then a transition to a ramjet was possible. All the equipment and most of the fuel were in a rather long fuselage. The tail was a normal scheme with traditional controls. A special feature of the aircraft were the fuselage and wing caisson tanks integrated into the design, the total fuel stock was 18 tons - up to 60% of the total weight of the aircraft.

To the tail part of the fuselage was attached the tail feather of a large sweep with traditional controls. In the forward part of the fuselage was the equipment of the guidance system on the target and the fuel tank, then on the flight there were a compartment with a nuclear warhead and fuel tanks. In the tail section of the fuselage, there was a control compartment for the projectile with aggregates and radio equipment. The total fuel reserve in the fuselage and wing caisson tanks integrated into the construction was 18,000 kg, the weighted return on fuel was about 60%.

As a carrier aircraft, it was intended to use a modified Tu-95 or Tu-96. The 113 aircraft was to be placed in a semi-submerged position in the carrier's cargo compartment, respectively, the dimensions of the projectile were selected from the conditions of the dimensions of this cargo compartment and the scope of the domestic Tu-95 carrier.

The dimensions of the projectile were chosen based on the dimensions of the cargo compartment and the distance between the internal nacelles of the Tu-95 bomber. The calculated mass "113" at the time of uncoupling was approximately equal to the mass of the aircraft "100" (30.7 tons).

The work on "113" (Tu-113) did not leave the stage of initial development, the OKB gave preference to the development of strategic air-missile systems based on the Tu-95 and Kh-20 airplanes (ARK Tu-95K-20). Later this line of work continued in the draft of the strategic system Tu-95S ("135") with a cruise missile S-30.

Description
Design OKB AN Tupolev
Notation "113"
type suspended unmanned air-to-surface missile
characteristics
Length of aircraft, m 23
Wing span, m 8
Wing area, m2 42
Wing extension 1.53
Starting weight, kg 30700
Weight of warhead, kg 3700
Fuel capacity, kg 18,000
Power point
Number of Engines 2
Engine DTRDF D-20 or VK-11
Engine thrust (afterburner), kgf
Flight data (estimated)
Cruising speed, km / h (M =) (2.5)
Flight height, m 11000-12000
Maximum flight range, km 3000-4000





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Page last modified: 16-02-2018 19:05:19 ZULU