RU226535U1 - UNMANNED AIRCRAFT LAUNCHING DEVICE - Google Patents

Abstract

The utility model relates to the field of aviation, in particular to the designs of vertical take-off and landing aircraft. The device for launching unmanned aerial vehicles contains a body and engines with lifting propellers. In this case, the body consists of hollow vertical cylindrical bodies, which in the upper part are rigidly connected to each other by beams. At the same time, engines and a power supply are located inside the housing shells, and lifting screws are installed on top of the engines, across the plane of the housing. In this case, a guide with a release mount rigidly connected to it is installed between the cylindrical bodies. The device is also equipped with a control and communication system. The technical result is to expand the possibility of using an aircraft from various launch sites of limited size. 2 ill.

Description

The utility model relates to the field of aviation, in particular to the designs of vertical take-off and landing aircraft.

A vertical take-off and landing aircraft is known (RU 180474 of 2018), consisting of a fuselage, a high wing, including a rectangular center section in plan and trapezoidal consoles, two longitudinal beams fixed under the center section to the left and right of the plane of symmetry of the aircraft, mounted on the front and the rear ends of the beams of lifting propellers with vertical axes of rotation, equipped with individual engines, the tail V-shaped empennage, the pusher propeller located behind the tail unit and rotated by its own engine, and the four-wheeled landing gear, the wing consoles, and the tail unit have straight, unswept rear edges, the tail is made according to an inverted V pattern, the rotation axis of the ailerons, flaps and rudders located on the trailing edges of the wing and tail are perpendicular to the longitudinal axis of the aircraft, the pusher propeller engine is installed in the engine nacelle above the rear fuselage.

The disadvantage of this device is the presence of lifting propellers with vertical axes of rotation, equipped with individual engines, which are used only for takeoff and landing and are not used during horizontal flight of the aircraft.

An unmanned aerial vehicle for vertical take-off and landing is also known (patent RU 216772 of 2023), containing a fuselage, the body of which is detachable, and the parts of the fuselage are interconnected by rivet nuts, a compartment inside the fuselage for the location of the payload, which is divided into two compartments along both sides of the battery located on the central part of the wing inside the fuselage body, a wing with ailerons, a tail unit, struts that absorb shock loads from the surface on which the aircraft lands, a sustainer propeller group, a power plant located in the fuselage body, lifting propellers for vertical takeoff and landing with a power plant located underneath and attached to pylons, on-board equipment. Lifting propellers for vertical takeoff and landing are mounted on pylons in a panel located above the fuselage, and to improve aerodynamics, movable walls are located on the top and bottom of the panel, which deviate perpendicular to the plane of the panel during takeoff and landing and form a smooth surface when closed during horizontal flight , the tail is made according to a U-shaped pattern, and the elements of the vertical tail are attached to consoles on which screws are located, providing lateral static stability.

The disadvantage of this technical solution is the design feature that consists in the presence of lifting propellers for vertical takeoff and landing, which create additional drag, affect the aerodynamics of the aircraft, and also increase the weight of the aircraft.

The closest in technical essence to the declared utility model is a vertical take-off and landing aircraft (RU 2790454 of 2023), the device is equipped with a wing or wings with rigidly fixed at least two straight elements passing perpendicularly through the plane of the wing and rigidly connecting a pair of propulsors with thrust parallel to the plane of the wing and directed across the wing; in lifting mode, the plane of the wing and the thrust of the propulsors are perpendicular to the ground; the apparatus is transferred to the horizontal mode when the balance of the thrust of the propulsors is disturbed; in horizontal flight, the lifting force of the wing and the horizontal thrust of the propulsors are used.

The disadvantage of this technical solution is the complexity of the design and control of the operation of the traction propulsors of the aircraft in the mode of ascent, descent and maneuvering at minimum speeds, that is, the operation of the propulsors in the mode of a multi-rotor helicopter - multicopter and during horizontal flight, when part or all of the propulsors are switched to the horizontal thrust mode .

The objective of the invention is to create a device that makes it possible to ensure the take-off mode of an aircraft-type aircraft from limited areas and maintain high performance characteristics during cruising flight.

The technical result is to expand the possibility of using an aircraft from various launch sites of limited size.

The required technical result is achieved by the fact that in the device for launching unmanned aerial vehicles, the housing consists of hollow vertical cylindrical housings, which in the upper part are rigidly connected to each other by beams, while the engines and power supply are located inside the shells of the housings, and on top of the engines, across the plane of the housing , lifting screws are installed, while a guide with a release mount rigidly connected to it is installed between the cylindrical bodies, the device is also equipped with a control and communication system.

The essence of the utility model is illustrated by the drawing, where

in fig. 1 and 2 - a device for launching unmanned aerial vehicles, which includes:

1 - control and communication system;

2 - guide with unlockable fastening;

3 - engines with lifting screws;

4 - cylindrical bodies;

5 - aircraft-type unmanned aerial vehicle;

6 - connecting beams;

7 - engine of an unmanned aerial vehicle.

The drone launcher works as follows:

To launch an aircraft-type unmanned aerial vehicle (5), it is mounted on a guide with a release mount (2). Motors with lifting screws (3) in cylindrical housings (4) are started remotely from the control point via a radio channel through the control and communication system (1). After the engines gain power, the device takes off. At a given altitude, at the command of the control point, the engine of the unmanned aerial vehicle (7) is started and the mount is opened. Next, the aircraft-type unmanned aerial vehicle (5) moves along the guide and sets off on an independent flight.

The guide with the unlockable mount (2) is made curved so that when undocking and launching, the aircraft-type unmanned aerial vehicle (5) does not touch the launcher with its wings and keel, and starts with a descent and subsequent climb.

Next, the aircraft-type unmanned aerial vehicle (5) performs an independent flight in accordance with the tasks assigned to it. The unmanned aerial vehicle launch device, controlled from the control point, returns to the launch point and lands. The drone launcher can be used repeatedly to launch multiple aircraft. The number of launched unmanned vehicles will be limited by the fuel reserves for operating the engines with lifting propellers (3), after which refueling (recharging) is necessary and it will be possible to continue launching the aircraft.

The use of a launcher for unmanned aerial vehicles will allow them to be used to perform surveillance, communication, target designation tasks, and, if necessary, destroy detected objects. It will allow you to realize all the advantages of aircraft-type unmanned vehicles and use them in various physical and geographical conditions of the area in the absence of special launch sites.

The ability to stay in the air for a long time, save fuel during takeoff, and monitor extended areas will ensure the demand for UAV launch devices by various departments.

Claims (1)

A device for launching unmanned aerial vehicles containing a housing and engines with lifting screws, characterized in that the housing consists of hollow vertical cylindrical housings, which in the upper part are rigidly connected to each other by beams, while inside the shells of the housings there are engines and a power supply, and on top of the engines , across the plane of the body, lifting screws are installed, while a guide with a release mount rigidly connected to it is installed between the cylindrical bodies; the device is also equipped with a control and communication system.