Existing Structure:

Produced motors consist of electric motors. The reason they consist of electric motor are: their small size for the force they provide, ability to reach high rotational speed, stability in the rotational speed, and fast acceleration capability. The disadvantage of the drones with electric motors are their short flight time, and light cargo capability.

New Approach:

Making drones consist of combustion engines, or a hybrid of electric motor and combustion engine.

Our Proposal:

It is to create the structure of the combustion engine that will satisfy the above-mentioned approach. The combustion engines that consist of pistons have various structures, such as single or multiple pistons.

Our proposal is to make combustion engines for the drones consist of multiple pistons placed one-under-the-other, or side-by-side in a way that will allow extracting the requested power from the engine. The example for the pistons' onc-under-the-other placement is given in FIGURE-3, and examples to the placement of them side-by-side in various angles are given in FIGURE-4,5,6. The number of pistons placed one-under-the-other or side-by-side may vary according to requested power and created design. These structures consist of multiple piston groups (1).

Developed Innovation:

It is to place the gearbox (8) that regulates the ratio between the rotational speed of crank shaft (5) and propeller shaft (6) inside the body of the combustion engine (11) in a way that in reference to the direction that propeller shaft (6) leaves the engine, the shaft will be located below the body of the combustion engine (11), besides to preventing the oil leakage from the gearbox (8). In the developed engine, the ratio between the rotational speed of crank shaft (5) and propeller shaft (6) is set by the gearbox (8). The leakage of oil in the gearbox (8j to outside the engine through the moving shafts of the gearbox is prevented with the design placing the gearbox (8) below the point the propeller shaft (8), which rotates the propeller (7), leaves the engine.

FIGURES AND THEIR EXPLANATIONS:

FIGURE- 1 : Combustion engine for drones, that consists of two symmetric pistons, starter and charge generator (3).

FIGURE-2: Combustion engine for drones, that consists of two symmetrical pistons, with individual starters and charge generators (4).

FIGURE-3: Combustion engine for drones, that consists of four symmetrical pistons, with starter and charge generator (3).

FIGURE-4: Top view of combustion engine for drones, that consists of two pistons. FIGURE-5: Top view of combustion engine for drones, that consists of group(s) of three pistons.

FIGURE-6: Top view of combustion engine for drones, that consists of group(s) of four pistons.

FIGURE-7: The view of propeller position adjustment lever and propeller adjustment unit.

THE EXPLANATIONS OF NUMBERS USED IN THE FIGURE:

1 - Combustion engine piston group

1.1- Combustion engine piston group l

1.2- Combustion engine piston group_2

1.3- Combustion engine piston group_3

1.4- Combustion engine piston group_4

2- Piston

2.1- Piston l

2.2- Piston_2

2.3- Piston_3

2.4- Piston_4

3- Starter and charge generator

4- Individual starter and charge generator

4.1- Individual starter and charge generator 1 4.2- Individual starter and charge generator 2 5- Crank shaft

5.1- Crank shaft_l

5.2- Crank shaft_2 6- Propeller shaft

7- Propeller

8- Gearbox

9- Crank shaft gear 9.1- Crank shaft gear_l 9.2- Crank shaft gear_2

10- Propeller shaft gear

11 - Body of combustion engine

12- Propeller position adjustment lever shaft

13- Propeller position adjustment unit

DESCRIPTION:

The innerworkings of combustion engine for drones, is same as the innerworkings of the standard combustion engines that consist of pistons. The piston (2) within the combustion engine piston group (1) gets moved back and forward with the burst of fuel. The back and forward movement of the piston (2) creates rotational movement on the crank shaft (5). All the crank shafts (5) within the engine are connected to propeller shaft gear (10) through crank shaft gears (9) within the gearbox (8). It conveys the movement to propeller shaft (6) with these gears. The propeller shaft (6) is connected to the propeller (7). and rotates the propeller (V).

The ratio of propeller shaft gear (10) and crank shaft gears (9) within the gearbox (8) sets the ratio of rotational speeds of engine and propeller (7). Example: If the crank shaft gears (9) / propeller shaft gear (10) = 3, and the engine’s (crank shaft (5)) rotational speed is 5,000 RPM, then the rotational speed of propeller connected to it is 3 x 5.000 = 15.000 RPM.

The initial rotational movement required for starting the combustion engine is provided by either a common starter and charge generator (3), or by individual starters and charge generators (4). While the combustion engine operates, the common starter and charge generator (3) or the individual starters and charge generators (4) operate in generator mode, provide the required electrical energy for the drone’s electronic system, besides charging the batteries.

The innovation within the described invention is the placement of gearbox (8), which conveys rotational movement to propeller (7), and sets the ratio between the propeller shaft (8) and crank shaft (5), underside the engine in the embodiment of the body of combustion engine (11). Thus, the oil within the gearbox (8) will easily be preserved within the gearbox.

The design of combustion engine for drones that consist of multiple combustion engine piston groups (1) is to produce the required power for the drone. This design could be implemented in an embodiment that combustion engine piston groups (1) is made symmetrical or consist of varying angles as shown in Figure-4,5,6, or in an embodiment that places the combustion engine piston groups (1) one under other as shown in Figure-3 for extracting enough power.

The piston (2) within the combustion engine piston group (1) that moves with the force created by the burst of fuel conveys rotational movement to the crank shaft (5) of its group. For example:

Figure- 1 : The movement of piston_l (2.1 ) within the combustion engine piston group_l (1.1) creates rotational movement on the crank shaft 1 (5.1). The movement of piston_2 (2.2) within the combustion engine piston group_2 (1.2) creates rotational movement on the crank shaft_2 (5.2).

However, in Figure-3: The combustion engine piston group l ( 1.1) and combustion engine piston group_2 (1.2) are symmetrical. The embodiment is designed in a way that the combustion engine piston group l (1.1), combustion engine piston group_2 (1.2), and combustion engine piston group_3 (1.3), and combustion engine piston group_4 (1.4) are located one below another. In this embodiment:

• The pistons (2) within the combustion engine piston group 1 (1.1) and combustion engine piston group_3 (1.3) together generates the rotational movement on the crank shaft (5.1). • The pistons (2) within the combustion engine piston group 2 (1.2) and combustion engine piston group_4 (1.4) together generates the rotational movement on the crank shaft (5.2).

In this embodiment type, the pistons (2) within the combustion engine piston group (1) together generate the rotational movement on the crank shaft (5). That provides increase in the torque of the corresponding crank shaft (5).

In the developed invention, in addition to using a common starter and charge generator (3) that will start all the engines, individual starters and charge generators (4) could be used for each combustion engine.

The position of the propellers is adjusted in the aircrafts that consist of propellers. The reason is that the air density may be different on air from ground, it is desired to vary load on the engines, and to make the propellers reach the requested torque. For satisfying these demands, propeller position adjustment lever shaft (12) and propeller position adjustment unit (13) are involved in the designed combustion engine for drones. The propeller position adjustment lever shaft (12) connects to the propeller position adjustment unit (13) that is within the gearbox (8) or adjacent to it, by passing through the propeller shaft (6).