MG-19 Drone of Russia for flight into space

Main article: Unmanned aerial vehicle (drone, UAV)

2017: MG-19

Layout 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 "supporting body." The body of the device had a triangular shape in plan with a sweep angle along the front edge of 75 °.

Such sweep was chosen on the condition of maintaining the high bearing properties of the device with low resistance and aerodynamic heating of the leading edges at high flight speeds. The nose of the body had elliptical cross-sections with a half-axle 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 toe. The configuration of the VKS, made according to the "carrying body" scheme, provided a fairly high level of aerodynamic characteristics^[2].

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

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

The main problematic issue of creating the M-19 Aerospace Forces was the creation of a combined power plant. On it, as the main idea, the concept of the entire project was built. The power plant scheme bore elements of novelty, and the main thing 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 near the ground.

The combined propulsion system included:

• cruise nuclear rocket engine (NRM) including nuclear reactor with radiation protection
• Ten two-circuit turbojet engines (DTRDF) with heat exchangers in the inner and outer circuits and with afterburner
• hypersonic ramjet engines (GPVRD)
• two turbochargers to provide hydrogen pumping through DTRDF heat exchangers
• distribution unit with turbopump units, heat exchangers and pipeline valves, fuel supply control system.

Hydrogen was used as fuel for DTRDF and GPVRD, it was also a working medium in the closed circuit of the NRC. The combined propulsion system of the M-19 VKS assumed the phased inclusion 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 flight and provided for the following modes:

• Mode "take-off" and "initial acceleration" to speeds corresponding to Mach=2.5-2.7 at altitudes of 12-15 km. In this mode, DTRDF operates with air heating upstream of the turbine from the closed circuit with the reactor with the afterburner on.
• Flight mode "acceleration," corresponding to speeds М=2.7-5.0 at altitudes ~ 15 km. In this mode only DTRDF operate in autorotation mode with air heating at afterburner inlet from closed circuit with reactor with afterburner on. In the speed range, corresponding to the 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.

Notes