RU221398U1 - Unmanned aerial vehicle - Google Patents

Abstract

The utility model relates to small-sized unmanned aerial vehicles (UAVs). The unmanned aerial vehicle contains a body with a propulsion power plant. In this case, the propulsion power plant includes one electric engine with a pulling folding propeller, and the body of the device is made according to the aerodynamic design of a “flying wing” with a low aspect ratio. Moreover, the propulsion power plant is moved forward of the hull by an amount that provides the required range of alignments, within which it is possible to change the mass of the payload and batteries without changing the position of the center of mass. Also, on the upper surface of the hull, a two-fin vertical tail is removably installed, designed to be installed vertically downwards on the end parts of the wings. Moreover, on the wing of the aircraft there is also installed, with the possibility of removal by means of brackets, a lifting power unit, which includes lifting engines with propellers and beams for placing lifting engines, in which the lifting motor control controllers are located, there are outputs for electrical power and signal connectors cables The technical result of the utility model is to increase the conversion speed of the aerodynamic design of the device by increasing the functionality of the structural elements. 3 ill.

Description

The utility model belongs to small-sized unmanned aerial vehicles (UAVs) and can be used as an aerial carrier of payloads of various types and dimensions with a total weight of up to 0.5 kg for an hour in a different range of altitudes and speeds in autonomous and/or remotely controlled flight modes in an area or along a route with the possibility of vertical takeoff and landing.

The unmanned aerial vehicle is part of an unmanned multi-purpose complex, which, with the help of selected UAV target load means, is capable of solving problems of collecting and processing information about objects and areas in order to provide consumers with the data necessary for the successful solution of various tasks in the course of their official and economic activities.

There are known designs of small-sized aircraft-type UAVs with a “flying wing” design with an electric power plant, capable of flying with a similar payload and launching from a catapult, from a shock absorber, from the operator’s hands, and landing using a parachute, as well as UAVs capable of performing a vertical takeoff and landing using lift engines.

Known are a small-sized unmanned aerial system (RU 127717, IPC B64F 1/04, V64S 39/02, published 05/10/2013), a vertical take-off and landing unmanned aerial vehicle (RU 199511, IPC V64S 27/30, published 09/04/2020) , unmanned aerial vehicle for vertical take-off and landing, designed for aerial topographic survey (RU208853, MPK V64S 27/28, published 01/18/2022), unmanned aerial vehicle (RU 228140, MPK V64S 39/02, V64S 39/00, publ . 11/27/2006), unmanned aerial vehicle (RU 2754277, MPK V64S 39/00, published 08/31/2021), unmanned aerial vehicle for vertical take-off and landing (RU 2767390, IPC V64S 39/02, V64S 27/22, V64S 27 /28, published 03/17/2022), a small-sized unmanned aircraft system (RU 2473455, IPC V64S 39/02, published 01/27/2013), which are close to this utility model in technical essence and the achieved result.

The main disadvantage of these devices is the lack of versatility, i.e. combining the capabilities of vehicles with vertical take-off and landing and vehicles with a launch system from a catapult or shock absorber.

The closest analogue is a collapsible unmanned aerial vehicle with horizontal flight for vertical takeoff and landing (RU 207716, IPC V64S 39/02, V64S 27/22, publ. 11/12/2021), which contains a wing-fuselage section, wing consoles, tightly mounted on cylindrical tubes connected to the section by means of axial holders installed in the cylindrical holes of the section, as well as pylons on which lifting screws are placed, and the pylons have cylindrical holes through which the pylons are installed on cylindrical tubes, between the section and the wing consoles, and also the tail part, on which the vertical tail is located and the bracket on which the horizontal tail is mounted, while in the front part of the wing-fuselage section a motor mount with an engine and a main propeller is installed, and the fairing body and hood are attached to the front frame, and the fairing body is also attached to the frames, the last of which has two holes for wiring rods to the rudder and elevator; among other things, the wing-fuselage section houses a fuel tank in the front part, an electric battery in the middle part and a flight control controller.

The design of the UAV RU 207716 allows for vertical takeoff and landing and does not require special launch systems, however, it does not have the ability to quickly dismantle the lifting power plant and launch the UAV from a catapult or shock absorber, and land with a parachute, in order to increase the flight range and payload.

The objective of the claimed utility model is the ability to quickly convert the aerodynamic design of a “flying wing” with a main engine with a pulling propeller into a design of a “flying wing” with a lifting power plant for the possibility of flight with vertical takeoff and landing.

The technical result of the utility model is to increase the conversion speed of the aerodynamic design of the device by increasing the functionality of the structural elements.

The technical result is achieved due to the fact that in an unmanned aerial vehicle containing a body with a cruising power plant, the cruising power plant includes one electric motor with a pulling folding propeller, and the body of the device is made according to the aerodynamic “flying wing” design with a small elongation, and the propulsion power plant is moved forward of the hull by an amount that provides the required range of alignments, within which it is possible to change the mass of the payload and batteries without changing the position of the center of mass; also, a two-fin vertical tail is removably installed on the upper surface of the hull, made with the possibility of installing it vertically down on the end parts of the wings, while on the wing of the aircraft there is also installed, with the possibility of removal by means of brackets, a lifting power unit, which includes lifting engines with propellers and lifting engine placement beams, in which lifting motor control controllers are located, there are outputs for connectors of electrical power and signal cables.

The two-fin vertical tail, which represents the end washers of the wing, is oriented downward for the purpose of convenient launching of the UAV from hands or a shock absorber, as well as the possibility of landing with a parachute “on the back” in order to prevent damage to the payload mounted on the lower part of the wing.

The wing has a low aspect ratio, which made it possible to refuse to give it a sweep along the leading edge and improve the aerodynamic quality on the one hand, and makes it possible to increase the structural height of the profile and reduce the weight of the wing structure while increasing the useful volume, on the other hand.

The main propulsion system's pulling propeller allows for the required range of alignments to be provided with a convenient location of the payload without the need to add a fuselage or front nacelle to the structure to increase internal volumes.

The beams for placing the lifting motors simultaneously serve as the chassis.

In the configuration for vertical take-off and landing, the vertical tail is represented by two fins located near the longitudinal axis of the aircraft on the upper surface of the wing to enable vertical take-off/landing “on the belly”.

A comparison of the proposed solution with known technical solutions shows that it has a new set of essential features that, together with known features, make it possible to successfully implement the task.

An example of the implementation of a utility model is presented in Figs. 1-3.

In Fig.1 - a general view of the UAV in a configuration without a lifting power plant is shown in axonometry;

in fig. 2 - in two projections (top view and bottom view).

In fig. 3 - a general view of the UAV in a configuration with a lifting power plant is presented in axonometry.

The UAV in a configuration without a lifting power plant (Fig. 1) contains a wing 1, elevons 2, a propulsion system 3, a vertical tail 4. The propulsion system includes a folding propeller and an electric motor with a control controller. The vertical tail 4 is double-finned, installed at the ends of the wing and facing down for ease of launch and the possibility of landing with a parachute “on the back” in order to preserve the electronic equipment located under the center of mass inside the wing and covered by hatch 5 (Fig. 2). The parachute is placed in a special compartment, covered by hatch 6. Hatch 7 (Fig. 2) serves to locate the telemetry module. A satellite navigation antenna is installed under hatch 8 (Fig. 2). Hatches 2 serve for access to the elevon servos.

A UAV in a configuration with a lifting power unit (Fig. 3) includes the same parts as a UAV in a configuration without a lifting power unit: wing 1, elevons 2, sustainer power unit 3, but is additionally equipped with a lifting power unit, including lifting engines with propellers 10, beams for placing lifting engines 11. The halves of the two-fin vertical tail 12 are mounted mirror-image relative to the plane of symmetry of the aircraft near the longitudinal axis of the aircraft in the area of the trailing edge of the wing and are oriented upwards. The beams for placing the lifting motors 11 simultaneously serve as a chassis. Inside the beams 11 there are controllers for controlling the lifting motors, there are outputs for connectors of electrical power and signal cables and brackets for fastening to the wing, allowing for quick installation or dismantling of the lifting power unit.

The design of the presented UAV provides for the ability to quickly install/dismantle the lifting power unit, which includes four lifting engines, four power regulators for these engines, four propellers, two beams for securing the engines to the UAV airframe, as well as beam mounting brackets, power supply wiring and connectors , power distributor for lifting motors. Installation and dismantling of a lifting power unit can be carried out in a short time using a minimum set of standard tools in factory or field conditions. The vertical tail, represented by two fins located at the ends of the wing, oriented downwards, attached to the lower surface of the wing, in case of conversion of the aircraft for vertical take-off, are mounted on the upper surface of the wing in the rear part in the area of the plane of symmetry of the aircraft.

Claims (1)

An unmanned aerial vehicle containing a body with a propulsion power plant, characterized in that the propulsion power plant includes one electric engine with a pulling folding propeller, and the body of the device is made according to the aerodynamic design of a “flying wing” with a low aspect ratio, and the propulsion power the installation is moved forward of the hull by an amount that provides the required range of alignments, within which it is possible to change the mass of the payload and batteries without changing the position of the center of mass; also, a two-fin vertical tail is removably installed on the upper surface of the hull, made with the possibility of installing it vertically down on the end parts of the wings , while on the wing of the aircraft there is also installed, with the possibility of removal by means of brackets, a lifting power unit, which includes lifting engines with propellers and lifting motor placement beams, in which lifting motor control controllers are located, there are outputs for electrical power and signal cables.

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