Vertical take-off and landing aircraft

1. A multicopter vertical takeoff and landing (VTOL) aircraft comprising:

an airframe implemented with a spatial design,

a distributed control system,

the airframe including a central section and at least two peripheral sections,

the central section and the at least two peripheral sections being implemented with the spatial design,

each of the at least two peripheral sections including at least three interconnected standard engine compartments,

each engine compartment housing an engine unit, the engine unit including at least one engine, at least one horizontally rotatable propeller, and a control hardware having been installed within the respective engine compartment;

the control hardware comprising at least:

an individual power supply source for powering on the at least one engine;

an individual engine controller with an autopilot module, implemented as part of the distributed control system, configured to control the at least one engine of the respective engine compartment.

2. The VTOL aircraft according to claim 1 , wherein the at least two peripheral sections comprise standard modules, each standard module being constructed of a plurality of parts, with at least some of the plurality of parts being interchangeable between any two different standard modules.

3. The VTOL aircraft according to claim 1 , wherein the at least two peripheral sections are configured to be at least one of: folded upwards, folded downwards or be retracted under the VTOL aircraft when stored.

4. The VTOL aircraft according to claim 1 , wherein the at least two peripheral sections are located in a space limited by structural elements of the airframe, without encompassing any of the structural elements of the airframe inside, the peripheral section including:

at least two fastening points where the at least one engine unit is attached to the airframe, and wherein two neighboring sections have, at least, one fastening point in common between them.

5. The VTOL aircraft according to claim 1 , wherein the engine compartments with engine units have an in-line arrangement, symmetrical to each other and are located in at least one horizontal plane.

6. The VTOL aircraft according to claim 1 , wherein the engine compartments housing the engine units are arranged in a chess-board order, displaced to each other and located in at least one horizontal plane.

7. The VTOL aircraft according to claim 1 , wherein the at least one engine being supplied with power, in use, from at least one power supply source located directly on the engine unit located within an airstream produced by the at least one horizontally rotatable propeller.

8. The VTOL aircraft according to claim 7 , wherein the at least one power supply source of a given engine unit is configured to be selectively switched to supply power to another engine unit via a wired system of switches.

9. The VTOL aircraft according to claim 7 , wherein the at least one power supply source comprises at least one of: a set of fuel cells, radioisotope and nuclear sources of electric power.

10. The VTOL aircraft according to claim 1 , wherein the engine unit comprises, at least, two coaxially located electric engines.

11. The VTOL aircraft according to claim 1 , wherein each of the engine units is implemented as an autonomous unit having:

an electric engine

an independent power supply source,

an instrumentation set,

engine control appliances,

battery charging and control appliances,

an autonomous autopilot module,

the autonomous unit being integrated with other autonomous units as part of the VTOL aircraft functioning as one whole system of the flying vehicle.

12. The VTOL aircraft according to claim 1 , wherein each engine unit comprises at least one pneumatic engine, wherein power supply of each one of the at least one pneumatic engine is supplied from the compressor installed in the central section of the airframe via individual piping with a valve system with electric drives, regulating the flow of the compressed gas supplied to the at least one pneumatic engines and their thrust in response to commands from the distributed control system.

13. The VTOL aircraft according to claim 12 , wherein the at least one pneumatic engine comprises at least two coaxially arranged pneumatic engines.

14. The VTOL aircraft according to claim 12 , wherein the individual pipings are located either inside or outside the airframe.

15. The VTOL aircraft according to claim 12 , wherein each pneumatic engine unit is an autonomous unit with a separate channel of pneumatic energy transfer from the compressor and an instrumentation set operated in response to commands received from the distributed control system.

16. The VTOL aircraft according to claim 12 , further comprising a redundant compressor and redundant pipings with autonomously operated valves, wherein the redundant compressor is installed inside the central section of the airframe.

17. The VTOL aircraft according to claim 1 , wherein the central section comprises: a cockpit with a pilot seat and controls, control system, hand- and foot-operated controls, steering block and a compressor.

18. The VTOL aircraft according to claim 1 , further comprising a removable steering block configured to be used as an individual remote control for operating the VTOL aircraft in an unmanned mode.

19. The VTOL aircraft according to claim 1 , wherein each peripheral section of the at least two peripheral sections comprises a plurality of engine units that are controllable autonomously, the at least two peripheral sections being implemented with a total number of engine units, the total number having an equal number of engine units having propellers rotating clockwise and engine units having propellers rotating counterclockwise.

20. The aircraft according to claim 1 , wherein each engine unit is controllable autonomously, wherein each peripheral section has a plurality of engine units, each having an even number of contra-rotating propellers.