RU179060U1 - Unmanned aerial vehicle vertical takeoff and landing - Google Patents

Abstract

The unmanned aerial vehicle of vertical take-off and landing of a combined aerodynamic scheme belongs to the field of the aviation industry, and can be used in the development of high-altitude unmanned aerial vehicles of vertical take-off and landing of a combined aerodynamic scheme for various purposes. It includes a cruciform wing 4 with consoles perpendicular to each other, on which the electric propeller motors 6 are located, characterized in that the consoles are mounted at right angles to each other so that the flight plane passes between two pairs of consoles symmetrically located relative to it, and the electric motors of the propeller drive 6, made with the possibility of changing the pitch, are located in removable removable nacelles 5 and are configured to change the direction rotation of the propellers 6, while the wings 4 are equipped with aerodynamic rudders 7 mounted on the wings 4 in the stream from the propellers 6, in addition, the device is equipped with a controlled on-board flight controller located in an airtight fuselage and controlling the device as by changing the speed of the air screws, and joint and differential change in their pitch. 2 s.p. f-ly, 5 ill.

Description

The utility model relates to the field of aviation industry, and can be used in the development of high-altitude unmanned aerial vehicles of vertical take-off and landing.

To assess the novelty and technical level of the claimed solution, we consider a number of technical means known to the applicant for a similar purpose, characterized by a combination of features similar to the claimed device.

Known unmanned aerial vehicle (patent US 20100252690 by Google) with vertical take-off and landing and the possibility of short hovering in the vertical position, with one main wing and with two propellers driven by rotation of engines located on opposite wing consoles parallel to the flight plane. The device is designed to deliver small loads and is equipped with a remote control station.

The disadvantage of this analogue is a purely airplane circuit of the apparatus, implying that the aircraft performs the main flight time in the “airplane” mode, and it can use the possibility of stationary hovering in the vertical position, raising or lowering it only for a short time, mainly in take-off modes landing. In addition, the lack of axial symmetry in the location of the aerodynamic surfaces leads to anisotropy of the aerodynamic qualities of the device, which is unacceptable when flying in conditions of gusty winds of different directions, especially during hovering and take-off and landing.

Known unmanned aerial vehicle (patent US 5114096) with vertical take-off landing Teilsitter scheme with one supporting wing (aircraft type), with four constant-pitch propeller drive motors located on vertically located (relative to the flight plane) planes of small area, designed for delivery small loads to customers of online stores.

The disadvantage of this analogue is also a purely airplane scheme, implying that the aircraft performs the main flight time horizontally in the “airplane” mode, and it can use the possibility of stationary hovering in the vertical position, raising or lowering it only for a short time, mainly on take-off and landing modes. In this device, the absence of axial symmetry in the location of the aerodynamic surfaces, the presence of the main bearing surface (wing), also leads to anisotropy of the aerodynamic qualities of the device, which is unacceptable when flying in gusty winds of different directions, especially during hovering and take-off and landing.

Known aircraft vertical takeoff and landing XPIusOne, http://xcraft.io/x-plusone-drone/, equipped with a cruciform wing, with consoles of approximately the same area, located perpendicular to each other, with consoles of the largest area, at the ends of each of which are located electric motors of propeller drive of non-adjustable pitch, located in the flight plane. The device has two flight modes: horizontally "in the plane", while the main axis of the device is horizontal, and the take-off and landing or hover "in the helicopter" mode, in which the main axis of the device is located vertically.

This design of an unmanned aerial vehicle of vertical takeoff and landing has been adopted by us as a prototype of the claimed technical solution.

The disadvantage of the prototype is a purely aircraft layout of the main bearing planes, implying that the lifting force is created only by planes located in the flight plane, and the second, vertically arranged pair of planes has an auxiliary function, and in this case, it is mainly intended only for mounting the other two propeller drive motors. In addition, the inability to control the pitch of the propellers and the direction of their rotation does not provide sufficient controllability of the aerodynamic scheme during flight, hovering and take-off and landing with the vertical position of the fuselage.

The objective of the utility model is to create a structurally simple, technologically advanced unmanned aerial vehicle vertical take-off and landing, designed to perform vertical take-off and landing and flight at altitudes of 4500-9000 m, for example, in the mountains; providing improved controllability of the selected aerodynamic scheme during flight, hovering and take-off and landing with the vertical position of the fuselage due to the different direction of rotation of the propellers with a change in the frequency of their rotation or using aerodynamic rudders located on the wing consoles and located in the air stream from the propellers; increase the compactness of the device in transport condition due to removable wing consoles.

The essence of the claimed utility model as a technical solution lies in the following set of essential features, sufficient to achieve the above technical result provided by the utility model.

An unmanned aerial vehicle with vertical take-off and landing, including a cruciform wing with consoles perpendicular to each other, on which electric propeller motors are located, is characterized by the fact that the wings are equipped with aerodynamic rudders mounted on the wings in the stream from the propellers, in addition, the apparatus is equipped with controlled by an on-board flight controller that manages the device both by changing the speed of the propellers, and joint and different socio change step.

This is the totality of the essential features of a utility model that provides a technical result in all cases to which the requested amount of legal protection applies.

In addition, the claimed technical solution is characterized by the presence of a number of additional optional features, namely

- aircraft batteries can be placed inside the wing consoles:

- removable removable consoles can be made of different lengths.

The technical result provided by the implementation of the claimed combination of essential features of the utility model consists in creating an unmanned aerial vehicle capable of flying at high altitudes through the use of electric propeller drive motors, the power of which does not depend on the flight altitude, as well as through the use of variable pitch propellers, with an increase in which the thrust of the screws at high altitudes can be increased; to carry out vertical take-off and landing, as well as hovering in place due to the creation of lifting force only by propeller thrust; to perform a flight in the vertical position of the fuselage ("in a helicopter"), and also horizontal flight in a horizontal position of the fuselage ("in a helicopter"), when the lifting force is created in a combined way, both due to the propulsion of the screws and due to the lifting force wings.

The essence of the claimed technical solution is illustrated by drawings, where in FIG. 1 shows a front view of the claimed apparatus, FIG. 2 is a side view, in FIG. 3 is a rear view, in FIG. 4 is an isometric view of a front view of the apparatus, in FIG. 5 is an isometric rear view of the apparatus.

An unmanned aerial vehicle for vertical take-off landing of a combined aerodynamic scheme includes an axisymmetric sealed fuselage 1, inside of which there is a payload (stern 2 and course photo of 3- or video cameras, batteries, flight controller of the aircraft control system, radio and video receiver with transmitter and etc.), the X-shaped wing 4, the nacelles 5 located on the wing consoles 4, inside of which the propeller motors 6 and the mechanism for changing their pitch are mounted. On the wing 4 in the stream from the propellers 6 are installed aerodynamic control wheels 7 at the yaw and pitch angles. The device can be equipped with landing racks located at the ends of the wing consoles 4, which can simultaneously be used to dissipate static electricity when flying in the clouds. The free intra-fuselage volume occupies an additional payload: either the transported cargo or additional batteries that increase the flight time of the aircraft.

The claimed aircraft operates as follows.

At start, being in a vertical position, after starting the engines, the device carries out vertical take-off, “in a helicopter”, only due to the propeller thrust. After gaining altitude and the required speed, the device switches to the horizontal flight mode “in the airplane”, at which the lifting force is created both by the propellers 6 pulling and by the wing lifting force 4. The process of turning from a vertical position to a horizontal one is performed either account aerodynamic rudders 7, located in the air stream from the propellers 6, or by the difference in the thrust of the propellers 6, located above and below the plane of flight.

Then, if necessary, if it is necessary to freeze in place or, if necessary, to land, the thrust of the propellers 6 and the speed of horizontal flight is reduced. Due to the influence of aerodynamic rudders or the difference in the thrust of the propellers located above and below the flight plane, the unmanned aerial vehicle is moved to a vertical position in which the lifting force is created only by the thrust of the propellers, and the aircraft hangs or, with a gradual decrease in thrust, lands.

The claimed aircraft can be used as an unmanned aerial vehicle for vertical take-off and landing to provide aviation support when performing various kinds of work, for example: mine rescue operations, at high altitudes (4500-9000 m), and also as an apparatus for conducting aerological studies in troposphere, monitoring the earth's surface in difficult atmospheric conditions with strong, gusty winds of different directions.

The claimed apparatus can be made using well-known equipment and materials manufactured by both domestic and foreign industry.

Claims (3)

1. An unmanned aerial vehicle of vertical take-off and landing, including a cruciform wing with consoles perpendicular to each other, on which electric propeller motors are located, characterized in that the wings are equipped with aerodynamic rudders mounted on the wings in the stream from the propellers, in addition the device is equipped with a controlled on-board flight controller that controls the device both by changing the rotational speed of the propellers, and joint and differential tional change of step. 2. The apparatus according to claim 1, characterized in that the batteries of the aircraft are located inside the wing consoles. 3. The apparatus according to claim 1, characterized in that the removable removable consoles are made of different lengths.

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