DESCRIPTION

The present invention relates to a multi-rotary wing drone with high load capacity, autonomy, ease of transport and use, which has the unique characteristic of being connected to other single units to increase their capacities such as: load, autonomy and reliability.

Reference is explicitly made to the aeronautical sector, in particular to Unmanned Aerial Vehicle (UAV) with the possibility of remote control or automatic flying capabilities.

At the state of the art some problems related to the use of rotary wing drones are unresolved or not sufficiently solved.

In particular there are problems relating to load capacity, autonomy, transportability and reliability.

In particular, there are multi-rotors that have pre-established dimensions and weights in the design phase which determine load capacity and autonomy based on a ratio between: propeller sizing, motors, vehicle weight and battery capacity. In general, a greater size of the drone implies a greater transportable load capacity and generally greater flight autonomy.

On the other hand, however, a large drone size leads to a problem of transportability due to size and assembly on site.

Currently the multi-rotors are built to carry small loads (e.g. in the order of few kgs) and to remain in flight for some tens of minutes (e.g. 40-60 min). To transport large loads the multi-rotors must be large with large engines, propellers and large and heavy batteries to generate enough energy for take-off.

The present invention has the purpose of solving all these problems with an innovative system of MODULAR MULTI-ROTARY WING DRONE POWERED BY ELECTRIC TURBINE GENERATOR that allows a Single unit to be connected to other identical units in order to increase the load capacity, autonomy, reliability, always keeping the transportability of the system easy and a feeding system composed of electric motors powered by a Turbine electric generator fueled with liquid fuel. In particular by:

• A carbon fiber frame with a hollow structure that is simple to construct in order to reduce the total number of components, to reduce the weight, to give to the whole system greater strength and that can act as a container for avionics, propellant and wiring;

• A square-shaped load-bearing system of rotors that, unlike others, does not converge as a connection point at the center of the multi-rotor, giving space for the installation of the generator and also a good distribution of weights over the entire frame (Fig. 2.2);

• Width of the MULTI-ROTOR DRONE between 220 and B00 cm so as to be able to place them on the load platform of a truck or with the possibility of stacking them for transport and storage on standard shipping containers;

• Use of 8 electric brushless motors with large diameter propellers, from 40 to 50 inches, in a double-motor quadricopter configuration superimposed on opposing propellers for each axis (4 coaxial rotors) able to obtain a thrust of 200 and up to 400kg (Fig.l);

• Electric propulsion system with Electric Turbine Generator with propellant tank that can be installed inside or outside the frame, capable of producing 30/50KW of energy;

• Physical connection system on all sides of the drone in order to create various flight and loading configurations by joining several drones together:

o This system allows the connection of various individual modules in order to increase the load capacity;

o Infinite possibility of configurations 1, 2, 2x2, 2x3, 2x4, 3x3, 2x5, 3x4, 3x5, 4x4, etc.

(see Fig. 4) making the load capacities variable while maintaining constant flight range and limited bulkiness during transport (see Fig. 5);

• The coupling system that allows to connect DATA and ENERGY lines between the various individual modules (see Fig. 2.1);

• In case of union between various modules, the System becomes redundant due to the fact that, in the event of a generator failure, the motors will be able to use the energy of the other generators connected;

• Redundant AVIONICS in every single unit and the possibility of each unit to act as backup electronics for the other units:

o When only one module is used, the unit will be defined as MASTER; o When multiple units are used, only one unit will be the MASTER and will act as flight controller for all others units. The others will become SLAVE and will be automatically configured by the system for the flight connected to the MASTER, only in case of failure of a MASTER, a SLAVE unit will become MASTER and take control over the others.

• The system will be equipped with a system of global positioning sensors with the possibility of correction of positioning error (RTK - Real Time Chinematik), anti-collision and obstacle detection, data transmission and stereoscopic navigation and positioning cameras;

• The possibility of being able to use a SINGLE UNIT SYSTEM will allow the transport of the same stacked on trucks or in shipping containers in an easy way and to be able to connect the same between them only in the place where they will actually be used (see Fig. 5)

The invention is now illustrated with reference to the attached drawings, given by way of example and not of limitation, in which:

• Fig.l: The stylized shape and the main components of the drone and their positioning, in particular are described:

o 1.1 redundant avionics composed of various sensors such as gyroscopes, accelerometers, positioning system

o 1.2 tank for liquid propellant

o 1.3 connection and coupling system between drones

o 1.4 buffer batteries

o 1.5 connection and coupling system between drones

o 1.6 connection and coupling system between drones

o 1.7 tank for liquid propellant

o 1.8 connection and coupling system between drones

o 1.9 buffer battery

o 1.10 liquid propellant turbine electric generator

• Fig.2: The peculiarity of the frame and the connection system between two drones are described which makes the system modular o 2.1 Docking plate between drones that allows the physical connection between individual units, data transfer and electricity

o 2.2 Structure of the support frame of square-shaped motors for motor support and structural to the connection system between modules

• Fig.S: The connection system between four drones is described through the use of four connection plates.

• Fig.4: Some configurations that can be obtained by connecting several drones to each other are described

o 4.1 single module

o 4.2 dual module configuration

o 4. S three modules online (Sxl)

o 4.4 four online modules (4x1)

o 4.5 four modules (2x2)

o 4.6 six modules (3x2)

o 4.7 eight modules (4x2)

o 4.8 nine modules (3x3)

o 4.9 ten modules (5x2)

• Fig.5: Describes the stowage system and the possibility of transport by container. In fact the individual modules will be stackable and will have a size suitable for being inserted inside a container. In the figure in particular it can be seen that in a 40 ft container is possible to store 35 single units by 5 stacks of 7 modules.

o 5.1 Stack of 7 single units stacked

o 5.2 40 ft. open top standard container.

The single drone will be built in composite and light materials; within each vehicle a TURBINE generator will be installed with liquid propellant for the production of sufficient electricity to guarantee the functioning of the on-board electronics and all the engines.

The load capacity and autonomy will depend on the amount of propellant on board and how many individual units will be used. The energy produced will be directly used by the engines and will also be used to maintain a buffer battery system to ensure the operation of the UAV for a few minutes in the event of a generator failure and sufficient for an emergency landing.

The drone will be equipped with a self-learning flight controller that adapts to the multiple configurations that the system can take based on the number of individual modules physically connected. a. The system is equipped with an avionics and flight controller capable of modifying flight parameters based on the number of individual units connected and their positioning.

b. Only one drone in the configuration will have control over the other units and will be defined MASTER CONTROLLER; will send the reconfiguration data to the other units called SLAVE CONTROLLERS

c. The SLAVE CONTROLLERS will remain in STANDBY leaving the control o the MASTER controller. Only in the event of a possible failure of the MASTER controller will a SLAVE controller become MASTER based on a self-assigned priority level

d. The system will be able to manage failures of FLIGHT, SENSOR, MOTOR and POWER SUPPLY CONTROLLERS based on the number of connected modules

e. The system is equipped with a special telemetry system (ground/air/ground) for continuous monitoring of both the systems and the flight data.

The system was designed to allow the assemble of individual drones in order to create a larger drone made up of several individual units with the aim of increasing the load capacity of the drone by using multiple drones of the same type physically joined together.

The drone can be used in all those situations in which things are transported from point A to point B where high load capacity, autonomy, take-offs and landings are required in narrow spaces and where pilots' lives could be at risk; some practical examples of use can be summarized in:

• transport at high altitude

• transport of things or objects of various sizes and weights in which the drone can be adapted to size and weight of the object to be transported

• search & rescue operations in difficult and / or dangerous environment

• transport of objects and / or scientific research in hostile environments

• virtually unlimited civil protection operations