RU2812920C1 - Device for studying aerodynamic characteristics of air flow when using multi-rotor unmanned aircraft vehicles - Google Patents

Abstract

FIELD: aerodynamics.

SUBSTANCE: invention relates to equipment for aerodynamic research, in particular to methods for studying the characteristics of the action of inductive air flows from the propellers of multi-rotor unmanned aerial vehicles (MR UAVs), including large-sized MR UAVs on suspended equipment and its characteristics. A device for studying the aerodynamic characteristics of air flows when using multi-rotor unmanned aerial vehicles, including a frame inside which is located a power unit having an electric motor, the shaft of which is coupled with a propeller. The frame has a modular design, consisting of sections formed by guides, interconnected bushings and fasteners with a threaded connection. The power plant located in the upper part of the frame comprises a crosspiece, the beams of which repeat the position of the beams of a multi-rotor unmanned aerial vehicle and have a movable carriage with the ability to move along the beam of the power plant crosspiece. The movable carriage comprises an element that fixes its position on the beam of the crosspiece, the movable carriage is associated with an engine, the shaft of which is connected to the screw, the ends of the power plant crosspiece are located in holders that limit the amplitude of movement of the crosspiece, and in the centre of the crosspiece there is a platform for mounting equipment. Instruments for studying the aerodynamic characteristics of inductive air flows and the characteristics of suspended equipment are installed on a frame with a mesh located inside the frame and connected to it with hooks.

EFFECT: modular, collapsible design of the device, through which air flows are formed, similar to the inductive air flows created by the MR UAV, but without using the device itself, and also having the ability to install measuring instruments at different heights.

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Description

Field of technology

The invention relates to the field of aerodynamics, namely to equipment for carrying out aerodynamic research, in particular to methods for studying the characteristics of the action of inductive air flows from the propellers of multi-rotor unmanned aerial vehicles (MT UAVs), including large-sized MT UAVs on suspended equipment and its characteristics.

State of the art

There is a known utility model RU 200947 U1 “Unmanned Aerial Vehicle Test Stand”, IPC G01M 9/06, containing a support frame on which a vertical guide is fixedly fixed. A platform is movably mounted on the guide, on which a two-axis hinge, made in the form of a cardan joint, is fixedly fixed. The tiltrotor is mounted on a hinge with the ability to rotate in a horizontal plane. A load is suspended from a cable, the mass of which is selected in such a way that the platform, together with the tiltrotor installed on it, is in a certain equilibrium position.

The disadvantage of the above-described technical solution is the inability to install and use a power plant that simulates various standard sizes of MT UAVs, installation of measuring instruments, as well as the impossibility of increasing the structure in height due to the lack of a modular design (RU 200947 U1, http://new.fips.ru ).

Of the known technical solutions, the closest in technical essence to the claimed object is solution RU 186022 U1 “Test stand for lifting thrust of unmanned aerial vehicle propellers”, IPC G01L 5/13, B64C 11/00, containing a protective frame, a double-arm lever in the form of a rectangular beam , an electric motor mounted on one end of a double-armed lever, a support for the axis of rotation of the lever, located on a base consisting of longitudinal, transverse and vertical beams of square section, rigidly interconnected by diagonals, characterized in that a strain gauge is installed, which is installed on the other end of the double-armed lever , a battery and a controller, which are mounted on a double-armed lever, and the battery is connected to the electric motor through the controller, while the controller and strain gauge mounted on the double-armed lever are connected to a personal computer via a USB port using a communication wire.

The disadvantage of the above-described technical solution is the inability to install and use a power plant that simulates various standard sizes of MT UAVs, installation of measuring instruments, as well as the impossibility of increasing the structure in height due to the lack of a modular design (RU 186022 U1, http://new.fips.ru ).

The technical challenge to solve the above-described disadvantages is to develop a modular, collapsible design of the device, through which air flows are formed, similar to the inductive air flows created by the MT UAV, but without using the device itself, and also having the ability to install measuring instruments at different heights.

The essence of the invention

The stated technical problem is solved due to the fact that the device contains a frame (1) in Fig. 1 modular design of sections (2) FIG. 1, 2, made of guides (2.1) Fig. 2, 3, located in space repeating the edges of a rectangular parallelepiped, and the power plant (3) FIG. 1, 4, simulating inductive air flows created by the UAV MT, installed in the upper part of the frame (1) FIG. 1, consisting of a cross (3.1) Fig. 4 with motors (3.3) attached to it FIG. 4, screws (3.4) fig. 4, flight controller, radio module, battery (not shown in the figure).

Frame (1) fig. 1 is a modular collapsible structure consisting of sections (2) FIG. 1, 2. Section (2) fig. 2 consists of guides (2.1) Fig. 2, 3, made of rigid durable material, for example, a wooden beam, located in space repeating the edges of a rectangular parallelepiped with the size of the sides, for example, two by two meters. Guides (2.1) fig. 2, 3 are connected to each other by means of connecting sleeves (2.2) Fig. 2, 3 and, for example, the threaded connection (2.3) of FIG. 2, 3. In a particular case of execution, a wing screw or wing nut is used.

Power plant (3) fig. 1, 4 is fixed in the upper part of the frame (1) FIG. 1, while the crosspiece (3.1) of FIG. 4 repeats the position of the rays of the UAV MT. On the rays of the cross (3.1) Fig. 4 the movable carriages (3.2) FIG. 4 with engines (3.3) fig. 4 and screws (3.4) Fig. 4. In the process of setting up the device, the carriages (3.2) move along the beams of the cross to the required location and are then fixed using, for example, threaded connections (3.5) Fig. 5. Selection of engines (3.3) fig. 4 is carried out in accordance with the requirements for UAV MT. Motors (3.3) fig. 4 are connected to the carriages (3.2) of Fig. 4 so that the motor axis is perpendicular to the ground level and the propellers operate parallel to the ground level to achieve the best simulation of the operation of the MT UAV. The ends of the cross (3.1) fig. 4 are installed in holders (1.1) Fig. 4, which limit its movement when the power plant transitions to a state of stationary hanging or maneuvering, preventing it from flying out of the frame (1) of FIG. 1 and damage the screws (3.4) Fig. 4. Also the use of holders (1.1) FIG. 4 is caused in an emergency situation, due to the fact that if one of the engines fails or the propeller breaks down, the UAV MT acts unpredictably, which can lead to the destruction of the aircraft itself, expensive suspended equipment, equipment for analyzing the required characteristics, as well as cause injury to personnel performing research work. The maximum permissible tilt of the power plant is no more than 15 degrees. In the center of the crosspiece (3.1) there is a platform, for example, round in shape, with a diameter of no more than 100 mm, for mounting a flight controller, radio module, electronic speed controller (ESC) and batteries. In a particular case of execution, the power plant (3) of FIG. 1, 4 operates from an electrical power supply. Under the power unit (3) Fig. 1, 4 the dispersion device is attached according to the standard mounting position to the MT UAV.

Power plant control (3) Fig. 1, 4 is carried out using a radio controller and remote control. It is advisable to use flight controllers of the Pixhawk series, due to the possibility of programming all parameters directly by the operator.

Instruments for studying the aerodynamic characteristics of inductive flows and the characteristics of suspended equipment are fixed on a frame with a mesh (4) Fig. 6, placed inside the frame (1) of FIG. 1 on eight hooks (4.1) fig. 6. In a particular case of execution, hooks (4.1) Fig. 6 are made in sets of different lengths and are painted in different colors, each of which indicates a specific length of the hook (4.1) of FIG. 6, which makes it easier to navigate in the process of selecting the required length of hooks (4.1) FIG. 6 when placing the frame with mesh (4) at the required height, FIG. 6. The positions of the power unit (3) at rest, during operation and during maneuvering are shown in Fig. 7, 8, 9 respectively.

The technical result of the claimed solution is the possibility of studying the characteristics of the action of inductive air flows from the propellers of multi-rotor unmanned aerial vehicles without using the devices themselves due to design features that allow changing the position of the engines, rotation speed, number, power and dimensions of the propellers, as well as the height of their location . The dismountable modular design of the installation provides the possibility of convenient transportation and storage, as well as increasing the installation height by a multiple of one section when studying large-sized MT UAVs.

Brief description of drawings:

In fig. 1 is a schematic representation of a device for studying the aerodynamic characteristics of air flows when using multi-rotor unmanned aerial vehicles. Axonometric projection.

In fig. 2 is a schematic representation of a frame section. Axonometric projection.

In fig. 3 - schematic representation of the guide connection unit. Lengthwise cut.

In fig. 4 - schematic representation of the power plant. Axonometric projection.

In fig. 5 is a schematic representation of the beam of the crosspiece of the power plant with a movable carriage. Axonometric projection.

In fig. 6 is a schematic representation of a frame with a mesh. Axonometric projection.

In fig. 7, 8, 9 - schematic representations of various positions of the power plant.

General form.

Brief description of structural elements:

1 - frame;

1.1 - holder;

2 - section;

2.1 – guide;

2.2 – bushing;

2.3 – threaded connection;

3 - power plant;

3.1 - cross;

3.2 - carriage;

3.3 – engine;

3.4 – screw;

3.5 - threaded connection;

4 - frame with mesh;

4.1 - hook.

Implementation of the declared decision

The claimed solution works as follows.

Sections (2) of Fig. are formed. 2 frames (1) fig. 1, connecting the guides (2.1) of FIG. 2 using bushings (2.2) and fixing the bushings (2.2) with fasteners with a threaded connection (2.3). The frame (1) Fig. is assembled. 1, installing sections (2) of FIG. 2 on top of each other, and fix the sections (2) together with fasteners with a threaded connection (2.3). If necessary, secure the frame (1) with braces in the corners on four sides. Next, the power unit (3) of Fig. is assembled. 4, mounting on the crosspiece (3.1) carriages (3.2) with motors (3.3) and propellers (3.4), as well as suspended equipment, a flight controller, a radio module, an electronic speed controller (ESC) and batteries. Before installing the power unit (3) FIG. 1 on the upper part of the frame (1) the location of the carriages (3.2) is adjusted. 4 in accordance with the requirements of UAV MT. Next, the power unit (3) Fig. is installed. 1 onto the upper part of the frame (1), fixing the crosspiece (3.1) Fig. 4 using holders (1.1). Fix the frame with the mesh (4) Fig. 6 on the frame (1) using hooks (4.1). The instruments necessary for research are placed on a frame with a mesh (4) Fig. 6. Next, the power plant (3) Fig. is started. 1 and check its operation by simulating takeoff, landing and maneuvering of the UAV MT Fig. 7, 8, 9.

Claims (3)

1. A device for studying the aerodynamic characteristics of air flows when using multi-rotor unmanned aerial vehicles, including a frame, inside of which there is a power unit having an electric motor, the shaft of which is coupled with a propeller, characterized in that the frame has a modular design consisting of sections formed by guides , interconnected by bushings and fasteners with a threaded connection, the power unit, located in the upper part of the frame, contains a crosspiece, the rays of which repeat the position of the rays of a multi-rotor type unmanned aerial vehicle and have a movable carriage with the ability to move along the beam of the power unit crosspiece, while the movable the carriage contains an element that fixes its position on the beam of the crosspiece, the movable carriage is connected to an engine, the shaft of which is connected to the propeller, the ends of the crosspiece of the power plant are located in holders that limit the amplitude of movement of the crosspiece, and in the center of the crosspiece there is a platform for mounting equipment, instruments for studying aerodynamic characteristics of inductive air flows and characteristics of suspended equipment are mounted on a frame with a mesh located inside the frame and connected to it with hooks. 2. The device according to claim 1, characterized in that the motor shaft has a transverse arrangement relative to the movable carriage. 3. The device according to claim 1, characterized in that the hooks for fixing the frame with the mesh are made in sets of different lengths, and the hooks of each set have their own color, indicating the length of the hook in this set.

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