BG3175U1 - Hybrid multicopter - Google Patents

Abstract

The utility model relates to an unmanned hybrid multicopter with at least six rotors carrying a camera or other payload. According to Fig. 1, the hybrid multicopter consists of a glider (fuselage) (1), below the plane of which are mounted two main horizontal rotors (2I and 2II), driven respectively by two shafts (3I и 3II) of an internal combustion engine (ICE) (4), receiving fuel from tanks (5I and 5II), as to the engine (4) are connected two electric generators (6I и 6II), charging respectively two accumulator batteries (7I и 7II), and the flight control is carried out with the use of at least four auxiliary horizontal rotors (8I ... 8IV), which are located on the periphery of the glider (1), and a payload (9) is mounted to the latter. Its application is in hybrid unmanned aerial vehicles powered by ICEs and electric motors used for surveillance, photography, tracking and fast transport of cargo by air from and to places and other operations, requiring vertical takeoff and landing. The advantages of the utility model are that thanks to the installation of the main horizontal rotors below the plane of the fuselage, the dynamic pressure, which is otherwise created by the air flow when it meets the fuselage, is reduced. Another advantage of the utility model is the use of two main horizontal rotors, directly driven by the internal combustion engine, as they rotate in opposite directions and thus eliminate the torque that each of them creates on the fuselage.

Description

4348 Descriptions to utility registration certificates № 07.1 / 15.07.2019 rapid transport of goods by air from and to places and other operations requiring vertical take-off and landing. The advantages of the utility model are that due to the installation of the main horizontal rotors below the plane of the fuselage, the dynamic pressure, which is otherwise created by the air flow when it meets the fuselage, is reduced. Another advantage of the utility model is the use of two main horizontal rotors, directly driven by the internal combustion engine, as they rotate in opposite directions and thus eliminate the torque that each of them creates on the fuselage.

claim, 1 figure

4349 Descriptions to utility model registration certificates № 07.1 / 15.07.2019 (54) HYBRID MULTI-COPTER

Field of technology

The utility model refers to an unmanned hybrid multi-helicopter with at least six rotors carrying a camera or other payload. The hybrid multi-helicopter consists of two main horizontal rotors located under the fuselage, which are used to create the main part of the lifting force and are driven directly by an internal combustion engine (ICE). The hybrid multi-helicopter uses at least four auxiliary horizontal rotors mounted on the periphery of the fuselage, whose function is flight control, and which are driven by electric motors (ED). The latter are supplied with electricity obtained from a generator connected to an internal combustion engine. The application is in hybrid unmanned aerial vehicles powered by internal combustion engines and ED, used for surveillance, photography, tracking and fast transport of goods by air from and to places requiring vertical takeoff and landing and other operations.

BACKGROUND OF THE INVENTION

An unmanned hybrid multi-rotor aircraft is known, having one main rotor powered by an internal combustion engine and four auxiliary rotors powered by ED, each of which is mounted above the plane of the glider [1]. Hybrid propulsion systems for multi-rotor unmanned aerial vehicles are also known, in which the design of the aircraft is not specified [2].

Disadvantages of the known hybrid multi-helicopters is the positioning of all rotors, and especially the main rotors with the largest dimensions, above the fuselage, which increases the dynamic pressure on the latter, as a result of which the power required to generate the required aerodynamic lift increases. which leads to a reduction in the efficiency of the flight and, above all, its duration.

Another disadvantage of the known hybrid multi-rotor aircraft is that it uses only one main horizontal rotor, powered by an internal combustion engine, whereby the torque compensation of the main rotor must be done with the help of small additional rotors. Since the latter are powered by electric motors, this compensation is ineffective.

Technical essence of the utility model

The task of the utility model is to create a hybrid multi-copter devoid of these shortcomings.

According to the utility model, the task is solved by creating an unmanned hybrid multi-copter, consisting of two main horizontal rotors located under the fuselage, which are used to create the main part of the lift and are driven directly by an internal combustion engine (internal combustion engine). ). The hybrid multi-helicopter uses at least four auxiliary horizontal rotors mounted on the periphery of the fuselage, whose function is flight control, and which are driven by electric motors. The latter are supplied with electricity obtained from a generator connected to an internal combustion engine. Thus, the total number of rotors is at least six.

Advantages of the utility model

The advantages of the utility model are that due to the installation of the main horizontal rotors below the plane of the fuselage, the dynamic pressure, which is otherwise created by the air flow when it meets the fuselage, is reduced. Another advantage of the utility model is the use of two main horizontal rotors, directly driven by the internal combustion engine as they rotate in opposite directions and thus eliminate the torque that each of them creates on the fuselage.

Explanation of the attached figure

An exemplary embodiment is shown in Figure 1, which is a diagram of the relative position of the rotors, their location relative to the fuselage (glider) and the place of installation of the engine, fuel tank, power generator, batteries and payload.

4350 Descriptions to certificates for registration of utility models № 07.1 / 15.07.2019

Example of implementation of the utility model

According to FIG. 1, the hybrid multi-copter consists of a glider (fuselage) 1, under the plane of which are mounted two main horizontal rotors 2 ¹ and 2 ^P , driven by two shafts 3 ¹ and 3 ⁿ , respectively, of an internal combustion engine 4 receiving fuel from tanks 5 ¹ and 5 ^P , as to the engine 4 are connected two electric generators 6 ¹ and 6 ^P , charging respectively two rechargeable batteries 7 ¹ and 7 ^P , and the flight control is carried out by means of at least four auxiliary horizontal rotors 8 ¹ ... 8 ^IV , which are located on the periphery of the glider 1, with a payload 9 attached to the latter.

Action of the utility model

The hybrid multi-helicopter works as follows.

By means of the aerodynamic force created by the rotors, the flight of the aircraft and its movement in the airspace in vertical and horizontal direction is achieved. The accelerated air flow after passing through the disks of the main two horizontal rotors does not meet the glider, which is located above them, and thus does not create dynamic pressure on the fuselage and the corresponding aerodynamic force in the downward direction, which is undesirable. Also, the use of two main horizontal rotors rotating in opposite directions eliminates the torque acting on the fuselage, which each of them creates individually. On the other hand, the placement of the remaining at least four horizontal rotors on the periphery of the glider helps to better control the flight and reduces the mutual interference of the main and auxiliary rotors. The main rotors are driven by internal combustion engines, and the auxiliary rotors are driven by ED, and the electricity is obtained from generators connected to internal combustion engines, buffered with batteries. In this way, the flight time, the flight range and the payload mass are maximized.

Claims (1)

Claims 1. A hybrid multi-copter consisting of a fuselage-glider, at least six horizontal rotors, an internal combustion engine, a fuel tank, electricity generators, accumulators and a payload, characterized in that below the plane of of the fuselage (1) are mounted two main horizontal rotors (2 ¹ and 2 ^P ), driven by two shafts (3 ¹ and 3 ⁿ ) respectively of the internal combustion engine (4) receiving fuel from tanks (5 ¹ and 5 ^P ) , two electric generators (6 ¹ and 6 ^P ) are connected to the engine (4), charging two rechargeable batteries (7 ¹ and 7 ^P ), respectively, and the flight is controlled by means of at least four auxiliary horizontal rotors ( 8 ¹ ... 8 ^IV ), which are located on the periphery of the glider (1), and a payload (9) is mounted to the latter.