WO2025198577A1

WO2025198577A1 - Unmanned aerial vehicle

Info

Publication number: WO2025198577A1
Application number: PCT/UA2025/000009
Authority: WO
Inventors: Roman Mykolayovych ANTONOV
Original assignee: "juliet Lima" LLC
Current assignee: "juliet Lima" LLC
Priority date: 2024-03-19
Filing date: 2025-03-07
Publication date: 2025-09-25
Anticipated expiration: 2026-09-19
Also published as: UA158765U

Abstract

An unmanned aerial vehicle is disclosed, comprising a frame (1) of H-shape made of low-density materials, with four foldable racks (2) with cut-outs mounted at the ends of the frame (1). A cover (7), on top of which a rechargeable battery pack (5) is mounted, is fixed to the frame (1). A flight controller (6) is mounted beneath the cover (7) and connected to the rechargeable battery pack (5) by flexible conductors, while four electric motors (3) with propellers (4) are mounted at the ends of the frame (1) and connected to the flight controller (6) by flexible conductors. A load module, consisting of two holders (8), two plywood plates (9), a steel rod (10), and a plastic slider (11), is mounted beneath the cover (7). A communication module with antennas (12) is mounted on the frame (1). An upper swivel camera (13) is mounted on top of the cover (7), and a lower camera (14) is mounted beneath the cover (7).

Description

UNMANNED AERIAL VEHICLE

The utility model relates to unmanned combat aerial vehicles (UAVs). Such vehicles are used in the military sector and are designed to deliver pay loads over a certain distance. In particular, UAVs based on the utility model are used to destroy enemy infantry and military equipment.

BACKGROUND

Unmanned aerial vehicles (UAVs) are gradually becoming a part of our everyday life: they deliver goods, perform various research, analyse the environment, monitor territories, control objects, take photos and videos, are used in rescue operations, during military operations and find many other applications.

Patent No. 221643 for the russian utility model for a small unmanned aerial vehicle comprising a body bearing a support device on the outer surface for mounting a throwing device for proper portioned or single-piece or one-time unloading of a payload during flight, as well as a pitch adjustment mechanism in accordance with the payload release algorithm, characterised in that said support device for mounting the payload throwing device is made in the form of a rail-mounted along the longitudinal axis of the aerial vehicle, wherein the rail is equipped with quick-release means for fastening the payload throwing device, the throwing device is in the form of a pipe with a payload release assembly, and the aerial vehicle is equipped with a guidance device for releasing said payload connected with the launch assembly of the assembly of releasing the payload from the pipe. The UAV according to this patent can be either an aircraft type or a quadrocopter type. Its disadvantages are the relative complexity of the design and the small weight of the payload that the UAV can deliver. Furthermore, the UAV is equipped with a Picatinny rail and a device for throwing load. This further complicates the design and reduces the accuracy of the payload drop.

Patent No. 103209 for the Ukrainian utility model describes an unmanned multi-engine helicopter that contains six electric motors with propellers, each of which is separately mounted on the ends of the supporting beams mounted to the central body, and landing gear supports, which are fixedly mounted on the bearing beams, characterised in that the bearing beams are pivotally mounted to the central body and, for transportation, are rotated downward close to vertical with the engines, and the landing gear supports are made with a discretely adjustable height. This technical solution is based on the task of reducing the overall dimensions of unmanned multi-engine helicopters for their transportation and ensuring that the height of the landing gear can be changed when using target loads of different heights in order to reduce aerodynamic drag in cruise flight. However, the range of loads that said UAV can deliver is quite limited both in terms of types and weight; and the range of their delivery remains short. Also, the beams of the UAV are not foldable.

Also, UAV R-18 is known in the prior art (https://uk.wikipedia.Org/wiki/R18# a6o https://youtu.be/a2yr235Fcmo?si=OMSOEGCQqcQhh7RI\ a multi-rotor type UAV capable of delivering loads to medium distance and having both military and civilian applications. This UAV has been actively used in the Russian-Ukrainian war since 2019. It consists of a frame; eight beams with motors and propellers; a payload module with a three-section payload mounting system; mounted on the frame; two rechargeable batteries; a navigation antenna with a compass; and a camera module. Its total flight range is 20 km and the total duration of flight is 45 minutes. The laden weight of the UAV is 17 kg, and the weight of payload it can carry is only 5 kg. This design was chosen as a prototype. This UAV design has significant drawbacks. In particular, it is an octocopter, which means it has eight engines with propellers. In order to provide a longer overall range and flight duration, as well as a larger payload that can be delivered by the UAV, it needs very powerful batteries. The above characteristics significantly limit the range of military and civilian tasks that a UAV can perform, i.e. the capacity of the batteries installed does not meet today’s requirements for the delivery of goods in terms of their weight, shape and size, and delivery distance. Also, this UAV is quite large, and the peculiarities of its individual parts and components preclude the possibility of its compact (portable) assembly, and thus increase the time required for its assembly and deployment before direct use. Furthermore, Ukrainian and imported components are used in the production of this UAV, which makes it more expensive and excludes the possibility of mass production for the needs of the Armed Forces of Ukraine (AFU).

Thus, there is a technical challenge to provide the design of an unmanned aerial vehicle that would have a design simple enough to allow it to be quickly assembled and deployed before use; relatively small weight and overall dimensions, and as a result, provide a better payload/laden weight ratio and the possibility of mass production for the needs of the Armed Forces of Ukraine.

STATEMENT OF THE UTILITY MODEL

The stated technical problem is solved by means of an unmanned aerial vehicle consisting of: frame 1 ; racks with cut-outs 2, fixed to the ends of the said frame 1 ; a cover 7 fixed to the said frame 1 ; a rechargeable battery pack 5 mounted on top of said cover 7, a servo 6 mounted beneath said cover 7 and connected to said rechargeable battery pack 5 by flexible conductors; electric motors 3 with propellers 4, mounted at the ends of said frame 1 and connected to said servo 7 by flexible conductors; a load module mounted beneath said cover 7 and consisting of two holders 8, two plywood plates 9, a steel rod 10 and a plastic slider 11 ; a communication module 12 with antennas mounted on said frame 1; an upper swivel camera 13 and a lower camera 14 mounted on top and beneath said cover 7, respectively; characterised in that characterised in that said unmanned aerial vehicle comprises four said racks with cut-outs 2 mounted at the ends of said frame 1; and four said electric motors 3 with propellers 4; wherein said frame 1 is H-shaped, said frame 1 being made of low density materials and said four racks with cut-outs 2 being mounted with the possibility of folding along the body of said frame 1.

The technical result of the unmanned aerial vehicle according to the utility model is a UAV that is simple in design, which allows it to be quickly deployed before use; small in weight and dimensions, which allows its transportation by one person; and also provides a better payload/laden weight ratio and the possibility of mass production at general-purpose industrial enterprises by low- skilled labour without the need to use additional equipment to install the load in the field.

DETAILED DESCRIPTION OF THE UTILITY MODEL

Brief description of the figures

The following figures describe in more detail the design of an unmanned aerial vehicle according to the utility model.

Figure 1 illustrates a general bottom view of an unmanned aerial vehicle according to the utility model, wherein:

1 — H-shaped frame;

2 — rack with a cut-out;

3 — electric motor;

4 — propeller;

5 — rechargeable battery pack;

6 — servo;

7 — cover;

8 — holder;

9 — plywood plate;

10 — steel rod;

11 — plastic slider;

12 — communication module with antennas;

13 — upper swivel camera;

14 — lower camera;

Figure 2 illustrates a general top view of an unmanned aerial vehicle according to the utility model, wherein:

1 — H-shaped frame;

2 — rack with a cut-out;

3 — electric motor;

4 — propeller;

5 — rechargeable battery pack;

7 — cover; 8 — holder;

12 — communication module with antennas;

13 — upper swivel camera;

Figure 3 illustrates a bottom view of an unmanned aerial vehicle according to the utility model, wherein:

1 — H-shaped frame;

2 — rack with a cut-out;

3 — electric motor;

4 — propeller;

6 — servo;

7 — cover;

8 — holder;

9 — plywood plate;

10 — steel rod;

11 — plastic slider;

12 — communication module with antennas;

13 — upper swivel camera;

14 — lower camera;

Figure 4 illustrates a general bottom view of an unmanned aerial vehicle according to the utility model with folded racks with cut-outs, wherein:

1 — H-shaped frame;

2 — rack with a cut-out;

3 — electric motor;

4 — propeller;

6 — servo;

7 — cover;

8 — holder;

9 — plywood plate;

10 — steel rod;

11 — plastic slider;

12 — communication module with antennas;

14 — lower camera;

The claimed UAV is part of a complex that also includes a set of ground equipment sufficient for its operation (means for planning and programming flight tasks, controlling and configuring the UAV, providing communication with the UAV via secure communication channels, receiving, recording and reproducing the type of information obtained during flights).

The general features of the claimed UAV :

- high payload capacity with small dimensions and weight;

- high speed and manoeuvrability;

- it can operate in difficult meteorological conditions; - relatively short deployment time;

- the complex can conduct reconnaissance in manual control mode in a given area;

The H-shaped frame 1 is the main structural element of the claimed UAV and provides all its aerodynamic and strength characteristics. It is designed for mounting all the UAV equipment, provides accommodation for on-board equipment, and all variants of target rigging and connecting cables. The H-shaped frame 1 is made of low-density materials.

Preferably, such materials are aluminium or carbon.

Preferably, the H-shaped frame 1 is made of standard aluminium profiles.

In particular, the H-shaped frame 1 is made of standard aluminium profiles or carbon pipes. It is also used as a body for electronics installation and provides protection of the electronics from precipitation and dust. For additional cooling, an optional fan can be installed to blow the components. On the underside of the frame, there are the racks with cut-outs 2 configured to be folded along the body of the H-shaped frame 1. These racks with cut-outs 2 are mounted to the H- shaped frame body 1 with rivets. The special cut-outs on the racks 2 and the method of their attachment make it possible to make the legs compact and identical to each other when folded, which reduces the number of parts, simplifies the process of assembly, repair and maintenance of the UAV. The H-shaped frame 1 can be easily modified for larger diameters of the propellers 4, and also allows to change the number of the electric motors 3, change the length and method of mounting the racks with cut-outs 2. The body of the H-shaped frame 1 is coated with paint or varnish to add weather-resistance properties.

The aerodynamic design of the UAV according to the utility model is a quadrocopter, i.e. it includes four electric motors 3 with the propellers 4 (see Figures 1 to 4).

The UAV’s propulsion system consists of an electric motor group and provides thrust and orientation of the UAV in the air. The propulsion system does not perform any other functions. In addition to the electric motors 3, it includes the rechargeable battery pack 5 and the servo 6.

The payload module is mounted beneath the cover 7 and consists of two holders 8, two plywood plates 9 connecting said holders 8 to each other, the steel rod 10 installed in the holes of one of the holders 8, and the plastic slider 11 that can be moved along the steel rod 10 (see Figures 1 to 4). Before the UAV is used, the ammunition is placed in the middle of two holders 8 and secured in them with the help of the steel rod 10 and the plastic slider 11.

The ammunition for the UAV according to the utility model is anti-tank-shaped charge grenades.

The navigation equipment of the UAV according to the utility model provides sufficient information to perform manual piloting of the UAV, determine the position and air parameters of the UAV and display them to an external pilot. It includes a module for communication with the antennas 12, as well as the upper swivel camera 13 and the lower camera 14. The antenna communication module 12 contains a GNSS receiver that receives and processes signals from satellite navigation systems. The cameras 13 and 14 provide UAV control, target search and surveillance tasks at any time of the day in good and moderate weather conditions. The communication module with the antennas 12, installed on the UAV according to the utility model (see Figures 1 to 4) ensures the transmission of control signals, data and commands between the UAV’s on-board systems and the ground control station.

The design of the UAV and other components of the complex ensures safe and reliable operation of the complex. To ensure safe operation, the UAV design is foldable. The possibility of folding is provided by rivets, which, in particular, connect the racks with cut-outs 2 to the H-shaped frame 1 (see Figures 1, 2 and 4). Due to the fact that in the folded form the racks with cut-outs 2 are located along the H-shaped frame 1, the UAV according to the utility model is very compact in size. When deploying the UAV, the operator unfolds the racks with cut-outs 2 relative to the H-shaped frame 1 , installs the rechargeable battery pack 5 on it and connects it to the servo 6 and the electric motors 3 with the propellers 4, unfolds the antennas of the communication module 12 and turns on the upper swivel camera 13 and the lower camera 14. Deployment of the complex is performed without the use of specialised tools, does not require special skills from the operator and takes an average of 5 minutes. The design of the complex ensures interchangeability of its components and the possibility of improving its technical and operational characteristics.

Comparative characteristics of the prototype and the unmanned aerial vehicle according to the utility model are shown in Table 1.

Table 1 Thus, as we can see, the use of the UAV according to the utility model in comparison with the prototype achieves the desired technical result, namely: The UAV has three times less weight and dimensions compared to the prototype; the payload/laden weight ratio is 1.5 times better. This is achieved through the use of low-density materials in the production of the UAV. The time required to deploy the UAV before its use has also been reduced by three times, and there is no need to use additional equipment to mount load in the field. The UAV also has a simple design compared to its analogues, and the use of standard aluminium profiles in the manufacture of the H-shaped frame body 1 significantly reduces the cost of the production process and allows for quick mass production at general-purpose industrial enterprises by low-skilled labour.

Claims

UTILITY MODEL CLAIMS

1. An unmanned aerial vehicle comprising:

- frame;

- racks with cut-outs fixed to the ends of the said frame;

- a cover fixed to the said frame; a rechargeable battery pack mounted on top of said cover, a servo mounted beneath said cover and connected to said rechargeable battery pack by flexible conductors; electric motors with propellers mounted at the ends of said frame and connected to said servo by flexible conductors;

- a load module mounted beneath said cover and consisting of two holders, two plywood plates, a steel rod and a plastic slider; a communication module with antennas mounted on the said frame; an upper swivel camera and a lower camera mounted on top and beneath said cover, respectively; characterised in that said unmanned aerial vehicle comprises four said racks with cut-outs mounted at the ends of said frame; and four said electric motors with propellers; wherein said frame is H-shaped, said frame being made of low density materials and said four racks with cut-outs being mounted with the possibility of folding along the body of said frame.

2. An unmanned aerial vehicle according to claim 1, characterised in that the frame is made of aluminium or carbon fibre.

3. An unmanned aerial vehicle according to claim 1 or 2, characterised in that the frame is made of standard aluminium profiles.