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MTK-VP

Specialists of TsKBEM previously developed spacecraft of the Soyuz type, whether that in addition to the advantages of large winged spacecraft have significant drawbacks, the main of which are a large mass of the wing and fuselage, covered with a powerful heat- protection, and the need to build very long and costly strips for horizon- planting similar systems. At the same time, they are widely used in parachute-rocket systems of soft landing showed not only high reliability at low cost, but also acceptable characteristics for accuracy of landing.

Therefore, in parallel, another variant of the reusable system is born in the MKBM, named MTK-VP (Reusable transport ship of vertical landing). This was seen by developers as a wingless aircraft of the "bearing body" type of about 90 tons, consisting of a cockpit in the front conical part, a cylindrical- the cargo compartment in the central part and the conical tail section with remote control for maneuvering in orbit.

It was assumed that the launch will be used RL RLA-130V modular type starting mass of 2380 tons. The first step was formed six blocks attached to the sides of the central unit being the second stage. On each lateral block, an oxygen-kerosene RD-123 liquid rocket engine was installed 600 tons. on the central block was installed two oxygen-hydrogen LPRE 11D122. After working in orbit, the device enters the atmosphere and maneuvers from the side range up to 800km. The body of the device has a small (about 1.0-1.25) aerodynamic- quality at hypersonic speeds. For balancing and control with Air and gas-dynamic steering wheels are used. The vertical landing speed is extinguished by the parachute system. Under the domes, the device is reduced in horizontal position. tion. The residual vertical speed is extinguished by the engines of soft landing, and horizontal speed - the produced ski chassis.

In any case, it was possible to use the ships of this type only if there was a launch vehicle of the type RLA-130V of a modular type with a starting mass of 2380 tons in serial production. The weight characteristics of the MTCVP were also impressive. MTKVP - descent on parachutes. Suffice it to say that the MTCVP was calculated for the same lifting capacity, that the Buran and OS-120 are 30 tons when put into orbit, and 20 tons when descending from it. The weight of the OK after separation from the LV and the reset of the CAC unit was 88 tons. The same figure for OC-120 was 119 tons, and for "Space Shuttle" - 114 tons. Comparing the landing masses: MTKVP - 66.4 tons, OS-120 - 89.4 tons and 84.8 tons for "Space Shuttle".

According to the plan of the creators of the system, in the case of immediate deployment of the development, its flight test design could begin in 1980. With a more detailed analysis of the scheme by May 1976, the need increase its hypersonic aerodynamic quality to increase the lateral range became clear. The problem was solved by placing triangular influxes on the body, increasing the to the tail. The calculated lateral range of the ship with such a triangular cross section the hull increased to 1800km. But MKP-VP had serious shortcomings. In the first turn high heating surface temperature during descent (up to 1900 degrees.

It is problematic that it is reusable), and a long cycle of post-flight recovery. It was not for nothing that later Lozino-Lozinsky spoke about the ITC-VP as "a half-one-time". Subsequently, the scheme of the winged ship prevailed and from the concept of MTC VP They refused in favor of the orbital ship (OK), which was called "Buran". Ideas, laid down in the design of the ITC VP, were used in the development of the rescue system, The lateral accelerators of the new launch vehicle, called "Energia".