RU181714U1 - UAV VERTICAL TAKEOFF AND LANDING WITH POWER BEAM FROM COMPOSITE MATERIAL - Google Patents

Abstract

The utility model relates to the field of aviation, in particular to unmanned aerial vehicles of vertical take-off and landing (UAV GDP) and can be used to monitor the environment and aerial photography. The technical result from the use of the claimed invention is to expand the functionality of an unmanned aerial vehicle of vertical take-off and landing for by creating a structure easier, safer, more resistant to loads by performing a power beam with truss aggregate from composite material in the form of a volumetric cellular structure, which allows to increase altitude, range, reliability and flight safety. Power beam 2 with truss filler is a volumetric box-shaped, cellular structure in the form of regular pyramids along the entire length of the beam of composite material, for example, with zigzag rods located inside normal to the horizontal rectangular plates of the power beam 2, forming when connecting zigzag profiles with grooves on the inner 17 and outer sides 18, cell and in the form of regular pyramids 19, while the nose of the beam is made in the form of a compartment 11, which is formed by the internal volume of cells in the form of regular pyramids 19 and a set of side 21, transverse 20 and horizontal plates 13, the length of which is made predetermined due to the purpose of the unmanned aerial vehicle wherein the compartment 11 is made for use as a fuel tank and is sealed over its entire surface; holes are made on the upper horizontal surface of the sealed compartment, one of which is under the valve for feeding fuel 14, a second for receiving excess fuel 15 to be transferred into the internal combustion engine, the entire surface of the box structure is protected by a winding and is made of heat-resistant material 16. 5-yl.

Description

The utility model relates to the field of aviation, in particular to unmanned aerial vehicles of vertical take-off and landing (UAV GDP) with a power beam made of composite material and can be used for environmental monitoring and aerial photography.

The famous "Unmanned Aerial Vehicle" according to the patent of the Russian Federation 76888. publ. 10.10.2008, IPC В64С 39/02, В64С 39/04, comprising a fuselage with a two-beam tail, a propeller type propeller, wing, horizontal and vertical tail, steering machines, and landing gear, characterized in that the power part of the fuselage is made in in the form of a metal truss and contains a compartment with on-board electronic equipment (avionics) and a compartment with the main fuel tank attached to the power part of the fuselage: in the bow, a truss containing the compartment with the target load, in the rear part, the motor frame on which a propeller installation, the wing spars are in the upper middle part, the front chassis is lower in the front, the main chassis is lower in the middle part, the spars are made tubular with the possibility of their use as an additional fuel tank, the tail beams are made in the form of metal pipes and attached to the spars from the top The vertical tail is made in the form of two inclined keels with rudders and is placed at the ends of the tail beams, between which the horizontal tail is made, made in the form of a stabilizer with p height, the fuselage lining consists of a front fairing, a main fairing and an engine hood and is made with the possibility of access through removable parts to the target load blocks, avionics and engine blocks, and c. the upper part of the main fairing is a hatch that closes the compartment with a parachute located above the fuel tank.

The disadvantage of this design is the large mass of the structure due to the use of metal structures and components, the implementation of all structural elements of large dimensions with low permissible stresses, which impairs aerodynamic performance, and also reduces the duration and safety of the flight.

The closest in technical essence and taken as a prototype is “Small-sized unmanned aerial system of aircraft type for aerial surveillance and reconnaissance” according to patent RU No. 2473455, IPC ВСС 39/02 publ. 01/27/2013 B.I. No. 3., Of a modular design, including the nose, with the payload located in it, containing the nose fairing with a hole cut through it, with a transparent material closed, the wing with ailerons, the fuselage containing the central spar, attachment points and key joints of the nose, left and right parts of the wing to the fuselage, a power unit located in the fuselage and equipped with an engine with a propeller, the central spar of the fuselage of an unmanned aerial vehicle is made in the form of a removable composite tube, the middle part of which is tightly placed inside the cylindrical holder located in the fuselage, the longitudinal axis of which is perpendicular to the longitudinal axis of the fuselage. The peripheral parts of the tube fit tightly into the lateral cylindrical holders installed in the left and right parts of the wing. At the ends of the tube included in the side holders, disk inserts made of composite material are installed. One edge of the side holders is attached to the first ribs of the left and right parts of the wing adjacent to the fuselage, and the second edge of the side cylindrical holders passing through the second ribs of the left and right parts of the wing is rigidly attached to the first side members of the left and right parts of the wing relative to the front edge of the wing. The bow is made with the possibility of disconnecting from the fuselage and back docking to it. In the upper central part of the fuselage there is a parachute compartment for accommodating the payload carrier in the form of a parachute system connected by means of fasteners to the fuselage, as well as including a ground control station; airborne and ground-based radio communications, navigation and flight control devices, starting device.

The disadvantage of an unmanned aerial vehicle of a small-sized unmanned aerial system of an aircraft-type modular design is a design feature, according to which the nose is made with the possibility of detachment from the fuselage, which reduces the strength characteristics of the structure used in the prototype attachment points and lock joints increase the mass of the aircraft, which, all other things being equal conditions worsens aerodynamic performance, reduces flight duration and safety. Also, design flaws include the central spar of the fuselage of an unmanned aerial vehicle, which is made in the form of a removable composite tube, at the ends of which are mounted disk inserts made of composite material. A removable composite tube whose axis is perpendicular to the axis of the fuselage is not strong enough, since under the influence of a bending moment it can collapse, which reduces the reliability and safety, and in general the functionality of an unmanned aerial vehicle.

The solved problem of the proposed utility model is the creation of a simple, easy, safe and reliable unmanned aerial vehicle of vertical take-off and landing with an integral structure of the power beam made of composite material with high aerodynamic characteristics, maneuverability by placing the fuel tank directly in the power beam, thereby expanding functionality of an unmanned aerial vehicle, namely range, altitude, maneuverability, reliability and safety Oleta.

The technical result from the use of the claimed utility model is to expand the functionality of an unmanned aerial vehicle of vertical take-off and landing by creating a light, safe, more resistant to structural loads by making a power beam with truss aggregate made of composite material in the form of a volumetric cellular structure, which allows to increase the height, range reliability and flight safety.

The technical result is achieved by the fact that in the Unmanned Aerial Vehicle of vertical take-off and landing with a power beam made of composite material containing the fuselage, wing, horizontal and vertical tail, landing gear, airborne equipment, power element, power unit, according to which, the power element is made in the form integral power beam with truss filler, which is a volumetric box-shaped, cellular structure in the form of regular pyramids along the entire length of the beam made of composite material, with an arrangement inside the zigzag rods normal to horizontal rectangular plates of the power beam, when connecting zigzag profiles with grooves on the inner and outer sides, the cells are in the form of regular pyramids, while the nose of the beam is made in the form of a compartment, which is formed by the internal volume of the cells in in the form of regular pyramids and a set of side, transverse and horizontal plates, the length of which is made predetermined, due to the purpose of the unmanned aerial vehicle, depending on flight range, while the compartment is designed to be used as a fuel tank and sealed over its entire surface, holes are made on the upper horizontal surface of the sealed compartment, one of which is under the valve for supplying fuel, the second for receiving excess fuel transmitted to the internal combustion engine, the entire surface box-shaped design is protected by a winding and made of heat-resistant material.

To clarify the technical nature, consider the drawings, where:

- in FIG. 1 - Unmanned aerial vehicle of vertical take-off and landing with a power beam from a truss filler, top view;

- in FIG. 2 - Unmanned aerial vehicle of vertical take-off and landing with a power beam from a truss filler, side view;

- in FIG. 3 - zigzag rods;

- in FIG. 4 - power beam side view;

- in FIG. 5 - power beam in isometry.,

1 - fuselage body

2 - power beam

3 - tail

4 - on-board equipment

5 - power plant

6 - wing

7 - pylons

8 - screw

9 - marching screw

10 - base edge (rigid plate)

11 - a compartment for a fuel tank

12 - battery

13 - horizontal plates

14 - valve for supplying fuel

15 - valve for receiving excess fuel

16 - heat-resistant winding

17 - zigzag profile with a groove on the inside

18 - zigzag profile with a groove on the outside

19 - a cell in the form of a regular pyramid

20 - transverse plate

21 - side plate

UAV UAV contains a fuselage body 1, a composite composite beam 2 made of carbon fiber, in the form of a box-shaped rectangular solid structure, inside of which there is a truss filler and a fuel tank. The composite composite beam 2 is fixed to the lower part of the housing 1 with screws and extends inside the housing 1 parallel to its axis. Three base edges 10 serve to fix the power composite beam to the lower part of the fuselage body, and also serve to create rigidity of the fuselage body 1. The base edges 10 are rectangular with bent ends and are attached from the inside to the fuselage body 1 with rivet nuts.

On the power beam 2, in the fuselage body, the wing 6 is rigidly attached using a spacer using two bushings and a retainer. The wing 6 has ailerons at the ends and consists of two consoles, each of which has pylons 7 with two screws 8 at the ends. At the end of the composite power beam 2, there is a tail unit 3 (including a keel, rudder, stabilizer, elevator) and an onboard equipment system 4 (which includes a digital half-duplex information transmission system, navigation module, servo drive). The power plant 5 is located in front of the UAV UAV hull. Marching propeller 9 is rotationally driven by the engine of the power plant 5, when fuel is supplied through valve 14, valve 15 is used to receive excess fuel from the power plant 5. The vertical take-off and landing screws 8 are rotationally driven when power is supplied from the battery 12.

Power beam construction production:

The assembly of the structure of the power beam, which is made in the form of an integral structure of a truss filler, which is a volumetric box-shaped, cellular structure in the form of regular pyramids along the entire length of the beam of composite material, for example, carbon fiber reinforced plastic, with zigzag rods located inside, normal to horizontal rectangular plates power beams, forming when connecting profiles with a groove on the inside and profiles with a groove on the outside, cells in the form of regular pyramids 19, d why it is necessary to connect one zigzag profile with a groove on the inner side 17 with a zigzag profile and a groove on the outer side 18, and a zigzag profile with a groove on the inside of the angle 17 will be above the profile with a groove on the outer side 18, and the profiles themselves will be in a vertical position and are perpendicular to each other; which makes it possible to make an unmanned aerial vehicle simpler, easier, more resistant to structural loads by making a power beam with a truss filler made of composite material in the form of a volumetric cellular structure; the remaining profiles are similarly assembled, creating a mesh structure; wherein the nose of the beam is made in the form of a compartment 11 and a set of side 21, transverse 20 and horizontal plates 13, the length of which is predetermined, due to the purpose of an unmanned aerial vehicle, for example, UAVs GDP, designed for a flight range of up to 3 km has one specified compartment length the power beam, and the UAV GDP, designed for a flight range of up to 10 km, has a different specified length of the power beam compartment., while the compartment 11 is sealed over its entire surface and is used as a fuel tank, and its implementation in the internal volume of the cells, in the form of regular pyramids formed by the above method, prevents rapid fuel overflow during sharp maneuvers of an unmanned aerial vehicle, which increases reliability, flight characteristics of the aircraft, namely maneuverability.

Along the length of the sealed surface, the rods of zigzag profiles are glued to the plates with resin; on the upper horizontal surface of the sealed compartment 11, holes are drilled for the fuel valves 14, 15. Then, on the remaining length of the beam, the zigzag profiles are installed above and below so that the profile rods enter the holes under them in the plates, and 2 zigzag profile rods enter one groove of the plate ; The last stage of assembly is the winding of the assembled beam with heat-resistant fabric 16, which allows to increase the overall safety of UAV UAVs in case of fire in the internal volume of the power beam.

Compared with well-known analogues, in terms of its technical and economic advantages, the claimed technical solution allows expanding the functionality of an unmanned aerial vehicle of vertical take-off and landing by making the structure lighter, safer, more resistant to loads by making an integral power beam with truss filler, which is a volumetric box-shaped, cellular structure in the form of regular pyramids along the entire length of the beam made of composite material, with zigzags located inside shaped rods forming when connecting zigzag profiles with grooves on the inside and outside of the cell in the form of regular pyramids, which reduces the weight of the filler, and the nose of the power beam in the form of a compartment, which is formed by the internal volume of the cells in the form of regular pyramids and a set side, transverse and horizontal plates, sealed over its entire surface, allows you to use the inner space as a fuel tank, while due to the cellular structure, preventing conductive rapid overflow of fuel during sharp maneuvers of the aircraft, increased agility and reliability, which also makes it possible to increase the height, range, reliability, and safety of flight.

Claims (1)

Unmanned aerial vehicle of vertical take-off and landing with a power beam made of composite material containing the fuselage, wing, horizontal and vertical tail, landing gear, airborne equipment, power element, power unit, characterized in that the power element is made in the form of an integral power beam with truss filler , which is a volumetric box-shaped, cellular structure in the form of regular pyramids along the entire length of a beam of composite material, with zigzag rods located inside, but normal to the horizontal plates of a rectangular shape of the power beam, forming when connecting zigzag profiles with grooves on the inner and outer sides, cells, in the form of regular pyramids, while the nose of the beam is made in the form of a compartment, which is formed by the internal volume of cells in the form of regular pyramids and a set lateral, transverse and horizontal plates, the length of which is made predetermined, due to the purpose of the unmanned aerial vehicle, depending on the flight range, while the compartment is made for used as a fuel tank and sealed over its entire surface, holes are made on the upper horizontal surface of the sealed compartment, one of which is for a valve for supplying fuel, the second for receiving excess fuel transmitted to the internal combustion engine, the entire surface of the box structure is protected by a winding and made of heat-resistant material.

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