RU217115U1 - UNMANNED AERIAL VEHICLE - COLEOPTER - Google Patents

Abstract

The utility model relates to aviation technology and can be used to create new designs of unmanned aerial vehicles - coleopters. The technical result of this utility model is to increase the flight range of an unmanned aerial vehicle. The specified technical result is achieved due to the fact that the unmanned aerial vehicle contains a fuselage made in the form of an annular wing, a payload unit, a radio-transparent fairing installed in the forward part of the payload unit, a propulsion fan, consisting of an inlet guide vane with fixed blades, designed for attaching the payload unit to the fuselage, the impeller and straightener, four independent aerodynamic rudders, an alternator, an internal combustion engine, the output shaft of which is connected by means of a coupling to the input shaft of the alternator and the impeller, a fuel tank located inside the fuselage , four servo deflectors of the aerodynamic rudders, shock absorbers of the landing gear and an annular skid landing gear, a set of on-board equipment installed in the payload unit, at the same time, shock absorbers of the landing gear on one side are symmetrically fixed to the fuselage, with on the other hand, they are symmetrically fixed to the annular skid chassis, at the same time, the internal combustion engine is located in the payload unit, while four aerodynamic rudders on one side are symmetrically attached to the lower part of the payload unit, on the other hand, they are attached to four servo deflectors of the aerodynamic rudders.

Description

The utility model relates to aviation technology and can be used to create new designs of unmanned aerial vehicles - coleopters.

Known, an unmanned aerial vehicle, consisting of an annular wing, a propulsion fan, a central body and at least four independent aerodynamic rudders, described in patent EP 2193994, class. B64C 39/02, published 06/09/2010.

The disadvantage of an unmanned aerial vehicle (coleopter) is that it has a short flight range, since an electric motor is used as a power plant.

The closest prototype, in the solution of which an attempt was made to partially solve the problem of increasing the flight range, is an unmanned aerial vehicle (coleopter) described in patent No. 2530906 of 10/18/2013.

Unmanned aerial vehicle (coleopter), described in patent No. 2530906 dated 10/18/2013, contains a fuselage made in the form of an annular wing, a payload unit, a radio-transparent fairing installed in the nose of the payload unit, a propulsion fan consisting of an inlet guide apparatus with fixed blades, designed to attach the payload unit to the fuselage, the impeller and straightener, four independent aerodynamic rudders.

This technical solution does not have a fuel tank, hence it can be concluded that an electric motor is used as a power plant, which is connected to the impeller of the propulsion fan.

The disadvantage of the prototype described in patent No. 2530906 dated 10/18/2013 is the low specific energy of the power supply system and low efficiency and, as a result, the short range of the unmanned aerial vehicle (coleopter) up to 100 km.

Based on this, the technical result of this utility model is to increase the flight range of an unmanned aerial vehicle.

The technical result is achieved due to the fact that the unmanned helicopter contains a fuselage made in the form of an annular wing, a payload unit, a radio-transparent fairing installed in the forward part of the payload unit, a propulsion fan, consisting of an inlet guide vane with fixed blades, designed for fastening payload unit to the fuselage, impeller and straightener, four independent aerodynamic rudders, additionally contains an alternator, an internal combustion engine, the output shaft of which is connected by means of a coupling to the input shaft of the alternator and the impeller, a fuel tank located inside the fuselage , four aerodynamic rudder deflection servos, landing gear shock absorbers and an annular skid landing gear, an on-board equipment complex installed in the payload unit, at the same time, landing gear shock absorbers on one side are symmetrically fixed to the fuselage, on the other hand, they are symmetrically attached to the annular skid chassis, at the same time, the internal combustion engine is located in the payload block, while four aerodynamic rudders on one side are symmetrically attached to the lower part of the payload block, on the other hand, they are attached to four aerodynamic deflection servomotors rudders.

The claimed utility model is illustrated by the following drawings: FIG. 1, which shows a general view of an unmanned aerial vehicle (coleopter); fig. 2, which shows a general view of an unmanned aerial vehicle (coleopter) in section; fig. 3, which shows a general view of the propulsion fan; fig. 4, which shows a block diagram of the onboard equipment complex.

Consider the structure and operation of a type of unmanned aerial vehicle - a coleopter (UAV) 1.

As can be seen from the drawing of FIG. 1, the UAV 1 contains a fuselage 2, made in the form of an annular wing, a payload unit 4, a radio-transparent fairing 3 installed in the bow of the payload unit 4, a propulsion fan 6, consisting of an inlet guide vane with fixed blades, designed to mount the unit payload 4 to the fuselage 2, impeller and straightener, four independent aerodynamic rudders 7, an internal combustion engine 5, a fuel tank located inside the fuselage 2, four servos 8 for deflecting aerodynamic rudders 7, landing gear shock absorbers 9 and an annular skid landing gear 10.

The complex of onboard equipment (not shown in the drawing) is installed in the payload unit 4, the shock absorbers of the landing gear 9 on the one hand are symmetrically fixed to the fuselage 2, on the other hand, symmetrically fixed to the annular skid chassis 10.

The internal combustion engine (ICE) 5 is located in the payload unit 4, four aerodynamic rudders 7 on the one hand are symmetrically attached to the lower part of the payload unit 4, on the other hand they are attached to four servos 8 for deflecting the aerodynamic rudders 7.

As can be seen from the drawing figure 2, the UAV 1 contains the fuselage 2, the payload unit 4, radiotransparent fairing 3, installed in the bow of the payload unit 4, the input guide vane 11 with fixed blades, the impeller 12 and straightener 13, four independent aerodynamic steering wheel 7, an internal combustion engine 5, the output shaft of which is connected by means of a clutch to the input shaft of the alternator 15 and the impeller 12, the fuel tank 14 is located inside the fuselage 2, four servo drives 8 deflections of the aerodynamic rudders 7, the shock absorbers of the landing gear 9 and the annular skid chassis 10, designed to dampen vibrations and shocks that occur at the moment the UAV 1 touches the runway during landing.

As can be seen from the drawing of FIG. 3, the propulsion fan 6 comprises an inlet guide vane 11 with fixed blades, designed to supply air to the impeller 12 and fasten the payload unit 4 to the fuselage 2, the impeller 12 and a straightener 13, designed to impart an axial direction to the air flow.

As can be seen from the drawing of FIG. 4, the control system of the UAV 1 consists of a complex of onboard equipment (OBE) 16 and a ground control station (GCC) 17.

OBE 16 contains onboard sensors 18, an onboard computer system (UAS) 19, a servo control unit 20, servo 8 controllers 21-24, a communication system 25, and a flight and navigation system (PNA) 26.

ICE 5 is designed to rotate the impeller 12, radiotransparent fairing 3 is designed to protect the OBE 16 from aerodynamic forces.

The rudders 7 provide control of the UAV 1 on the course, pitch and increase directional stability. In block 4, an optoelectronic system (OES) can be located for manual (visual) flight control of the UAV 1 by the operator of the NPU 17 using the communication channel formed by the communication system 25, which is part of the OBE 16 and NPU 17.

UAV 1 has two modes of operation and operates as follows. Autonomous flight mode.

The operator NPU 17 enters the flight task in the OBE 16 UAV 1. The flight task contains the flight path of the UAV 1, information about the type of landing point, launch and flight of the UAV 1 to a point with specified coordinates while maintaining speed.

Using the KBO 16 turns on the internal combustion engine 5. The UAV 1 using the fan-propulsor 6 and a pre-entered flight task, which is recorded in the memory of the UAV 19, performs vertical and horizontal flight along a given route (not shown).

PNK 26 performs: dead reckoning and correction of orientation angles, dead reckoning and correction of coordinates, dead reckoning and correction of speed parameters, reception of navigation signals from satellite navigation systems.

BVS 19 is designed to control all blocks and assemblies of the UAV 1. Four aerodynamic rudders 7 provide stability, controllability and balance of the UAV 1 in flight.

Manual flight control mode.

The control of the UAV 1 in space is carried out by the operator NPU 17 through communication channels using the OES (not shown), by visual observation.

The NPU operator 17, using the communication system 25, UAV 19, the servo control unit 20 and the controllers 21, 22, 23 and 24, controls the servos 8 that control the rudders 7.

The course control of the UAV 1 is provided by the control of the rudders 7, which is implemented via the mentioned circuit from the controls of the OBE 16 to the corresponding servo 8, which moves the rudders 7 to a given angle.

The control of the UAV 1 in pitch and roll is provided by the appropriate tilt of the rudders 7, taking into account the data that are received in real time from the onboard sensors 18 and PNK 26.

The transmission and reception of messages (commands) to control the UAV 1 occurs using the communication means 25, which are part of the OBE 16 and NPU 17.

The voltage for power supply of the KBO 16 is supplied from the DC generator 15.

The main technical characteristics of the UAV 1 are given in Table 1.

In this technical solution, the internal combustion engine 5 is connected to the impeller 12 and the generator 15 (not shown). In this case, the internal combustion engine 5 is located in the upper part of the payload block 4, as shown in the drawing of FIG. 2, which allows engineering and technical workers to quickly carry out operational and periodic maintenance of the internal combustion engine 5.

The presence of an internal combustion engine 5, a DC generator 15 and a fuel tank 14 located in the fuselage 2 makes it possible for the UAV 1 to be in flight for a long time and, as a result, to increase the flight range up to 400 km, which is 4 times higher than that of the prototype.

Based on the above, the technical result of this utility model is achieved.

The prototype UAV 1 was made on the basis of the Russian engine. Tests have shown that UAV 1 meets all the declared characteristics of Table 1.

Claims (1)

Unmanned aerial vehicle - a coleopter containing a fuselage made in the form of an annular wing, a payload unit, a radio-transparent fairing installed in the nose of the payload unit, a propulsion fan consisting of an inlet guide vane with fixed blades, designed to attach the payload unit to fuselage, impeller and straightener, four independent aerodynamic rudders, characterized in that it additionally contains an alternator, an internal combustion engine, the output shaft of which is connected by means of a coupling to the input shaft of the alternator and the impeller, a fuel tank located inside the fuselage , four servo deflectors of the aerodynamic rudders, shock absorbers of the landing gear and an annular skid landing gear, a set of on-board equipment installed in the payload unit, at the same time, shock absorbers of the landing gear on one side are symmetrically fixed to the fuselage, on the other On the other hand, they are symmetrically fixed to the annular skid chassis, at the same time, the internal combustion engine is located in the payload unit, while four aerodynamic rudders on one side are symmetrically attached to the lower part of the payload unit, on the other hand, they are attached to four servo deflectors of the aerodynamic rudders.

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