MG-19 Russian drone for space flight

Model MG19 Photo Creative Elements

MG-19 aerospace aircraft. MG-19 was developed on the basis of the previously developed VKS M-19^[1]

VKS M-19 was made according to the aerodynamic scheme "bearing hull." The body of the device had a triangular shape in plan with an angle of sweep along the leading edge of 75 °.

Such sweep was chosen based on the condition of maintaining the high carrying properties of the device with low resistance and aerodynamic heating of the front edges at high flight speeds. The nose of the body had elliptical cross sections with a half-axis ratio of 1/4.

MG-19 aerospace aircraft

The midship section was located at the point of transition of the bow of the hull to the stern, at a distance of 0.67 of the hull length from the sock. The configuration of the VKS, made according to the "bearing hull" scheme, provided a fairly high level of aerodynamic characteristics of^[2].

So, for example, the aerodynamic quality on subsonic was about -7.0, and on hypersonic about 3.0, which was confirmed by experimental studies at TsAGI.

Studies carried out to determine the optimal appearance of winged spacecraft making horizontal take-off and landing "in an airplane way" have shown that the most acceptable form of multi-mode VKS flying at pre-, super- and hypersonic speeds in conditions of intense heating is the form of the "supporting hull" type.

The main problematic issue of creating the VKS M-19 was the creation of a combined power plant. On it, as the main idea, the concept of the entire project was built. The scheme of the power plant bore elements of novelty, and the main thing that the developers coped with was that a special unit (heat exchanger) was proposed, thanks to which the radioactive circuit was completely isolated, which excluded radiation contamination of the atmosphere when the engine was turned on at the ground.

The combined propulsion system included:

• marching nuclear rocket engine (YARD) including nuclear reactor with radiation protection
• ten double-flow turbojet engines (DTRDF) with heat exchangers in internal and external circuits and with afterburner
• hypersonic ramjet engines
• two turbocompressors for hydrogen pumping through DTRDF heat exchangers
• distribution unit with turbopump units, heat exchangers and valves of pipelines, fuel supply control systems.

Hydrogen was used as fuel for DTRDF and GPVRD, it was also a working medium in the closed loop of the YARD. The combined propulsion system VKS M-19 involved the phased activation of various types of engines depending on the flight mode. The operation of the combined VKS power plant was regulated by optimal operating modes at all phases of the flight and provided for the following modes:

• The "rise" and "initial dispersal" mode to the speeds corresponding to numbers M=2.5-2.7 at the heights of 12-15 km. In this mode, DTRDF operates with air heating before the turbine from the closed circuit with the reactor when the afterburner is turned on.
• Flight mode "acceleration," which corresponds to speeds M = 2.7-5.0 at altitudes ~ 15 km. In this mode, only DTRDF operates in autorotation mode with air heating at the inlet to the afterburner from the closed circuit with the reactor when the afterburner is turned on. In the range of speeds corresponding to numbers M = 3.5-4.5, GPVRD are connected to DTRDF, which provide acceleration of the device to flight conditions: altitude -50 km, speed M ~ 16.0.

Шаблон:Topic Space

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