RU237242U1 - Unmanned aerial vehicle - Google Patents

Abstract

The utility model relates to unmanned and controlled transport-type aerial vehicles capable of vertical takeoff and landing. The design is adapted to accommodate flight with various payloads. The supporting frame for a tethered/autonomous quadcopter-based unmanned aerial vehicle contains horizontal blade propellers with brushless motors. The supporting X-shaped frame, made of composite materials, has a rectangular external shape with radial arms extending from it. A composite housing is attached to the frame, protecting the electronic components located within from external influences. The housing, in combination with the battery compartment, ensures the specified aerodynamic characteristics of the aircraft. Indicators are located on the housing, providing information on the current state of the aircraft. The technical result of the utility model is to improve the aerodynamic properties of the aircraft housing through the use of a housing made of perforated composite materials. 2 fig.

Description

The utility model relates to aviation technology, in particular to unmanned and controlled transport-type aerial vehicles with the ability to take off and land vertically, based on a quadcopter.

An unmanned aerial vehicle (RU 2666493 C1 IPC B64C 27/08 B64C 39/02, published 07.09.2018) consists of a central platform with at least eight electric motors with coaxial propellers with controlled rotation speed rigidly mounted at the ends of the axes, the other ends of which are rigidly attached to it and oriented relative to its center. Adjacent motors rotate in opposite directions; the electric motors are connected to a battery and a route computing system—a flight controller and motor controllers, a mobile control and monitoring unit, a video surveillance system, and a GPS navigation receiver. Furthermore, the electric motors and propellers are mounted within rings, the aerodynamic profile of which faces the ends of the propellers, which rotate within the ring with a relative clearance of 0.45-1.5% of the ring diameter.

However, this aircraft has two drawbacks. The first is that, due to the large surface area of the propeller rings, they create significant drag when moving horizontally. The second drawback is the inability to fly such aircraft in formation due to the lack of the necessary devices for synchronizing movement.

A multirotor unmanned aerial vehicle (RU 183717 U1 IPC B64C 27/00, B64C 39/02, published October 1, 2018) has been selected as the prototype. The proposed design allows for six degrees of freedom of control, achieved by independently adjusting the rotation angle of each of the four propeller holders within a range of ±60°. The onboard electronics enable the unmanned aerial vehicle to fly in urban areas or obstacle courses, as well as to perform formation flights according to a preset program in both autopilot and manual control modes. A multichannel electronics switch allows for power supply regulation during flight missions to reduce energy consumption.

The prototype under consideration has several drawbacks, namely the lack of choice of type and the ability to quickly replace the payload, reduced aerodynamic properties due to the open design when placing modules on the frame, and the difficulty in replacing batteries.

The utility model is aimed at solving the problems of expanding the technical and operational capabilities of unmanned aerial vehicles based on quadcopters, creating a design that ensures maximum versatility of the device, improving the aerodynamic properties of the device by improving the aerodynamic properties of the device body, without losing reliability and durability.

The technical result of the utility model is the improvement of the aerodynamic properties of the apparatus body by using a body made of composite materials with perforation.

The technical result is achieved due to the fact that in an unmanned aerial vehicle, containing in its design brushless motors with propellers fixed thereto, a supporting frame made of composite materials, a perforated housing, a power module, a battery, a regulator, a flight controller, an on-board computer and a communication module, the supporting frame is made monolithic together with the beams on which the motors are mounted in the upper part and the support legs in the lower part, and the flight controller, the on-board computer, the regulator, the power module and the communication module are mounted in the central part of the frame, and pads are fixed on the beams in such a way that between the pad and the frame a cavity is formed in which wires are placed that connect the regulator with each of the motors, while also on the central part of the frame a perforated housing is installed, in the upper part of which a battery compartment is installed with the possibility of detaching due to trapezoidal grooves made on the body of the device and mating trapezoidal grooves on the removable cover of the battery compartment and due to the quick-release electrical connector, one contact of which is fixed to the body of the device, and the opposite contact to the body of the battery compartment, a plate for placing the payload is attached to the lower part of the frame, and light indicators are installed on the body.

The use of a mechanical detachable trapezoidal connection to secure the battery housing to the device body, coupled with the use of a quick-release electrical detachable connection, allowed for secure battery fixation, reduced battery replacement time, and overall improved device performance.

The installation of a plate at the bottom of the apparatus allows it to carry various types of payload.

Using the indicators on the device body allows you to quickly monitor the current state of the device.

The essence of the utility model is explained by the figures:

Fig. 1 shows a general view of the assembled apparatus in isometric view;

Fig. 2 shows the apparatus in disassembled isometric view.

The device consists of the following components:

1 - supporting frame made of composite materials;

2 - body made of composite materials;

3 - battery compartment;

4 - battery compartment cover;

5 - engine;

6 - propeller;

7 - beam overlay;

8 - leg;

9 - plate for placing payload;

10 - racks for attaching the payload plate;

11 - flight controller;

12 - on-board computer;

13 - regulator;

14 - power module;

15 - communication module;

16 - detachable connection contact;

17 - mating contact of the detachable connection.

The design is a monolithic X-shaped frame (1), containing four beams located at an angle of 90 degrees to each other. At the tops of the beams, four identical motors (5) are installed, designed to generate lift due to the rotation of the thrusters, with propellers (6) attached to them. Four legs (8) are attached to the bottom of the frame, designed for storage and servicing of the apparatus. Brushless motors (5) and legs (8) are attached to the frame (1) using screws. Various types of payload are attached to a perforated plate (9), which is connected to the frame (1) using struts (10) and damping bushings. The latter, in turn, prevent disruption of the payload due to vibrations of the frame (1). A cover plate (7) is secured to the top of each beam of the frame (1), creating a cavity between the cover plate and the frame into which the wires transmitting energy from the regulator (13) to each of the four engines (5) are placed. Placing the necessary wiring inside this cavity ensures its protection from external environmental factors and mechanical damage. The flight controller (11), on-board computer (12), regulator (13), power module (14), and communication module (15) are secured to the top of the supporting frame, ensuring all the actions necessary to perform the flight mission. A housing made of composite materials (2) is secured to the top of the frame (1), designed to improve the aerodynamic properties of the apparatus and protect the electronic components from external influences. The side walls of the housing (2) are perforated, providing additional cooling for the electronic modules inside the housing. The upper part of the housing has four openings for attaching indicators providing information on the state of the apparatus (e.g. battery charge, communication with the operator and other devices in the network, etc.). The battery compartment (3) is mounted on the rear of the housing (2) using trapezoidal blind dovetail grooves and secured with screws to the battery compartment cover (4). The housing (2) and the battery compartment (3) are provided with openings opposite each other, into which the switching contacts (16, 17) of the quick-release electrical connector for transmitting energy from the battery to the regulator (13) and the power module (14) are secured. This type of fastening, together with the use of quick-release connectors, ensures a rigid and reliable fixation of the compartment (3) on the apparatus, reduces the installation time of the compartment (3), ensures protection against reverse polarity of the power wires and improves the operational properties of the apparatus as a whole. Interaction of the operator with the apparatus and the apparatus with other apparatuses in the group is ensured via the communication module (15). The communication module (15) interacts with the flight controller (11) and the on-board computer (12) via a dedicated communication bus. The onboard computer (12), analyzing information received from the operator, from the inertial and satellite navigation systems, and the autopilot system from the flight controller (11), as well as information received from other devices, generates control signals for the flight controller (11), thereby adjusting its position in space in accordance with the flight mission or the operator's instructions, by sending signals to the controller (13). The power module (14) supplies energy to all necessary parts of the device.

By dismantling the legs (8), plate (9) and racks (10), the device can be used for educational and training purposes, which will significantly increase the operating time of the device.

Claims (1)

An unmanned aerial vehicle comprising in its design brushless motors with propellers fixed thereto, a supporting frame made of composite materials, a perforated housing, a power module, a battery, a regulator, a flight controller, an on-board computer and a communication module, characterized in that the supporting frame is made monolithic together with beams on which the motors are mounted in the upper part and support legs in the lower part, and the flight controller, the on-board computer, the regulator, the power module and the communication module are mounted in the central part of the frame, wherein pads are fixed on the beams in such a way that between the pad and the frame a cavity is formed in which wires are placed that connect the regulator with each of the motors, while a perforated housing is also mounted on the central part of the frame, in the upper part of which a battery compartment is mounted, a plate for placing a payload is attached to the lower part of the frame, and light indicators are mounted on the housing.