RU181389U1 - MODULAR DESIGN OF THE UNMANNED AIRCRAFT VERTICAL TAKEOFF AND LANDING WITH COMBINED POWER PLANT - Google Patents

Abstract

The utility model relates to the field of aviation technology, namely to unmanned aerial vehicles of vertical take-off and landing (UAV GDP), and can be used to monitor the environment, in particular aerial photography and surveillance.

The technical result from the use of the utility model is the creation of an effective unmanned aerial vehicle of vertical takeoff and landing of a modular design with a combined power plant by expanding its functionality.

The technical result is achieved by the fact that in the modular design of an unmanned aerial vehicle of vertical take-off and landing with a combined power plant including a fuselage, a power element of a carrier beam, rigidly fixed inside the fuselage body, a wing with ailerons, attachment points, a power plant located in the fuselage body, the battery, the compartment for accommodating the payload, the wing 6 is made integral, on each console of the wing 6 are made pylons 7 with two lifting screws 8 for vertical take-off This and the landing, the power plant located in front of the fuselage body 1, contains a mid-flight engine 5 with a propeller 9, rotationally driven by liquid fuel by means of a fuel supply system from the fuel tank 17, the propeller 9 is located in front of the fuselage body 1 to ensure horizontal flight, a power composite beam 2, made in the form of a rectangular solid structure, inside which a truss filler is located, is introduced as a power element of the supporting beam, while composite beam 2 is located after the main engine 5, and its end is located outside the fuselage body 1, on-board equipment 4 and tail unit, including keel 12, rudder 13, stabilizer 14, elevator 15, are located and fixed with screws on the end of the power beam 2 the composite composite beam 2 is rigidly fixed to the lower part of the fuselage body 1 parallel to its axis using screws and base edges 10 made in the form of rectangular plates, the axes of which are perpendicular to the axis of the fuselage body 1, the base edges 10 are made They have curved ends, their lower part is attached to the composite power beam 2, curved ends are attached to the walls of the fuselage body 1 from the inside, and the fuselage body 1 is detachable, consisting of upper and lower parts interconnected by rivet nuts, in the upper part the body of the fuselage 1, inside it, compartments 16 are made, separated by a battery 3, one of which contains a fuel tank 17.

Description

The utility model relates to the field of aviation technology, namely to unmanned aerial vehicles of vertical take-off and landing (UAV GDP), and can be used to monitor the environment, in particular aerial photography and surveillance.

Known "Aircraft vertical take-off and landing" according to patent RU No. 141669, B64C 29/00, publ. 06/10/2014, B.I. No. 16, containing the fuselage, keel, landing gear, articulated wing, two lift-march fans, each of which consists of a multi-blade propeller with a variable pitch in a profiled ring with independently controlled rotation drive, a power plant that provides the necessary traction, with one or more than the engines used in all flight modes of the aircraft, the torque transmission unit, which is used as a mechanical gear from the engine to the drive shafts of the lift-march fans and the control device pitch Ia. In this case, the marching fans are fixed near the center of mass, symmetrically relative to the axis of the aircraft on a hollow power beam rigidly connected to the fuselage.

The disadvantage of this aircraft vertical takeoff and landing is the design feature of the fuselage body is one-piece, which reduces the functionality and makes the access to units and assemblies, uncomfortable and time-consuming in case of repair, and the lack of modularity of the structure does not allow easy assembly and disassembly for transport , which also reduces functionality. Also, the presence of an articulated wing leads to a complication of the design, an increase in weight and a decrease in "reliability and safety, which generally reduces the effectiveness of this aircraft of vertical take-off and landing.

Known vertical take-off and landing unmanned aerial vehicle with a fixed wing (CN No. 106672232 (A), B64C 27/08, B64C 27/26, publ. 05/17/2017) containing the fuselage, deflectable wing, ailerons, lifting propellers, lifting power plants propellers, wing rotation mechanism drive (tilting mechanism), tiltable horizontal stabilizer, keel, tail rotor powerplant, nose and rear wheel-mounted chassis. The drive of the wing rotation mechanism controls the angle of inclination of the wing and the horizontal stabilizer to realize mutual conversion of the vertical position of takeoff and landing and the plane state of flight of the aircraft. The propeller of the lift screw is located on each wing console. The tail rotor propulsion system provides direct movement to increase cruising performance. The power plants of the lifting screws and the power plant of the tail rotor have different speeds of rotation.

The disadvantage of this aircraft vertical takeoff and landing is the design feature of the fuselage body is one-piece, which reduces the functionality of the aircraft and makes access to units and assemblies, uncomfortable and time-consuming in case of repair, and the lack of modularity of the structure does not allow simple assembly and disassembly for the implementation of transportation, which also reduces the functionality of the aircraft, and, in general, reduce the efficiency l aircraft.

The closest in technical essence and taken as a prototype is a small-sized unmanned aerial system of aircraft type for air surveillance and reconnaissance (patent RU No. 2473455, IPC ВСС 39/02, publ. 01/27/2013, BI No. 3), including a ground control station; airborne and ground-based radio communications, navigation and flight controls; a launching device and a payload bearing a collapsible unmanned aerial vehicle of modular design, including the nose, with the payload located in it, containing the nose fairing with a hole cut through it, covered with transparent material, the wing with ailerons, the fuselage containing the central spar, attachment points and locking connections of the bow, left and right wing to the fuselage, a power unit in the form of an electric motor, a regulating controller and a pushing propeller with folding with blades driven into rotational motion when power is supplied to the electric motor from the battery located in the lower central part of the fuselage, in the battery compartment, made with the possibility of undocking from the fuselage, the central spar of the fuselage of the unmanned aerial vehicle is made in the form of a removable composite tube, the middle part of which 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 compartment for accommodating the payload carrier in the form of a parachute system connected via fuselage attachment links.

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 and increases weight due to the strengthening of the nose. Used in the prototype fasteners and locking joints increase the mass of the aircraft, which, ceteris paribus, affects aerodynamic performance, reduces flight duration and safety. There is no space for installing more efficient massive payloads such as a fuel tank. Also, a structural drawback is the integral execution of the fuselage body, which makes access in the case of repair to units and nodes difficult, reducing functionality. A removable composite tube whose axis runs perpendicular to the axis of the fuselage is not strong enough, since under the influence of a bending moment from the side of the wings, it can collapse, which reduces reliability and safety, and generally reduces the efficiency of an unmanned aerial vehicle. The power plant is made in the form of an electric motor and cannot work from other energy sources, which also reduces the functionality and does not allow to increase the flight duration if necessary, which generally leads to a decrease in the efficiency of the unmanned aerial vehicle of vertical take-off and landing.

The solved problem of the proposed utility model is the creation of a simple and reliable unmanned aerial vehicle of vertical takeoff and landing of a modular design based on a composite power beam, a detachable fuselage body and a combined power plant.

The technical result of using the utility model is the creation of an effective unmanned aerial vehicle of vertical take-off and landing of a modular design by expanding its functionality and flight duration.

The technical result is achieved by the fact that in the modular design of an unmanned aerial vehicle of vertical take-off and landing with a combined power plant including a fuselage, a power element of a support beam rigidly fixed inside the fuselage body, a wing with ailerons, attachment points, a power plant located in the fuselage body, the battery, a compartment for accommodating the payload, according to which the wing is made whole, on each console of the wing are made pylons with two lifting screws for vertically rocket take-off and landing, the power plant located in the front of the fuselage body, contains a mid-flight engine with a propeller, rotationally driven by liquid fuel using a fuel supply system from the fuel tank, the propeller is located in the front of the fuselage body to ensure horizontal flight, as a power element of the load-bearing beam, a power composite beam is introduced, made in the form of a rectangular solid structure, inside of which there is a truss filler, while the power the composite beam is located after the main engine, and its end is located outside the fuselage body, the onboard equipment and tail unit, including the keel, rudder, stabilizer, elevator, are located and fixed with screws on the end of the power beam, the composite composite beam is rigidly fixed to the lower part of the body the fuselage parallel to its axis with screws and base edges made in the form of rectangular plates, the axes of which are perpendicular to the axis of the fuselage body, the base edges are made with bent to nets, their lower part is attached to the composite power beam, the curved ends are attached to the walls of the fuselage body from the inside, and the fuselage body is detachable, consisting of upper and lower parts interconnected by rivet nuts, in the upper part of the fuselage body, inside it, compartments are made, separated by a battery, one of which contains a fuel tank.

To clarify the technical nature, consider the drawings:

FIG. 1 - Modular design of UAV UAV with combined power plant in isometry;

FIG. 2 - Longitudinal section of the Modular design of the UAV UAV GDP with a combined power unit section AA - side view;

FIG. 3 - The modular design of the UAV UAV GDP with a combined power plant with a top cover undocked from the body;

FIG. 4 - Cross section of the Modular design of the UAV UAV GDP with a combined power plant of the BB section - front view, where

1 - the fuselage body,

2 - power beam,

3 - battery

4 - on-board equipment,

5 - marching engine,

6 - wing

7 - pylons,

8 - lifting screws

9 - sustainer (propeller) propeller,

10 - base edge

11 - ailerons,

12 - keel

13 - rudder,

14 - stabilizer

15 - elevator,

16 - compartment for the payload,

17 - a fuel tank.

UAV UAV contains a detachable fuselage body 1, consisting of upper and lower parts and a power composite beam 2, made in the form of a rectangular solid structure, inside of which there is a truss filler. The composite composite beam 2 is fixed to the lower part of the body with screws and passes inside the fuselage body 1 parallel to its axis. The fuselage body 1 has an elongated shape with a compartment for accommodating the payload 16 inside, divided into two small compartments by means of a battery 3 mounted on the central part of the wing 6 inside the fuselage body 1. Base edges 10 serve to fix the composite power beam 2 to the lower part of the body the fuselage 1, and also serve to create rigidity of the fuselage body 1. The base edges 10 have a rectangular shape with curved ends, by which they are attached to the side of the fuselage body 1 with rivets nuts, and their lower part is attached to the power composite beam 2.

To the composite power beam 2 located after the main engine, wing 6 is rigidly attached using a spacer using two bushings and a retainer. The wing 6 has ailerons 11 at the ends and consists of two consoles, on each of which pylons 7 are installed with two lifting screws 8 at the ends. At the end of the composite power beam 2, extending outside the fuselage body 1, there is a tail unit including a keel 12, rudder 13, stabilizer 14, elevator 15 and onboard equipment 4 system (which includes a digital half-duplex information transmission system, navigation module, servo drive). The combined power plant consists of a mid-flight engine 5 and a mid-flight propeller 9 located in the front of the fuselage body 1, and is rotationally driven by liquid fuel supplied by the fuel supply system from the fuel tank 17, which is located in one of the compartments separated by the battery 3, for the location of the payload 16.

The assembly of UAV UAV modular design with a combined power plant is as follows:

To both wing consoles 6 are connected pylons 7 with two lifting screws 8 at the ends of each pylon and secured with screws. The wing 6 with installed pylons 7 with lifting screws 8 is attached to the power composite beam 2 with truss filler inside by means of spacers, bushings and a retainer. The tail unit is attached to the end of the power composite beam 2, including the keel 12, rudder 13, stabilizer 14, elevator 15 and the avionics system 4. Further, the lower part of the power composite beam 2 is rigidly attached from the inside to the lower part of the fuselage body 1 when using screws and base edges 10, the curved ends of which are attached to the walls of the fuselage body 1, and the lower part to the composite power beam 2. In the front part of the fuselage body 1, the main engine 5 is installed with the main propeller 9 for horizontal flight, and the fuel tank 17. On the central part of the wing 6, inside the fuselage body, the battery 3 in a thin-walled container is attached using the lock, bushings and screws, while it divides the compartment inside the fuselage body into its upper sections , one of which contains a fuel tank 17, which allows you to set inside an additional effective payload to the payload in the form of a parachute system in the second compartment. The detachable fuselage body 1, consisting of the upper and lower parts, allows for quick access, repair and replacement of parts and assemblies in the event of a breakdown of this UAV GDP, which increases the functionality of this UAV GDP, modularity, and generally makes the UAV GDP effective. The upper part of the fuselage body 1 is docked with the lower part of the fuselage body 1 and fixed.

The inventive device operates as follows:

UAV UAV is controlled from the ground control station (NSU) by the flight operator. Before the flight starts, the operator creates the required flight program and writes it to the memory card, which is installed in the BKU (airplane control unit). Then the charged battery 3 is installed on the central part of the wing 6 inside the fuselage body 1 UAV UAV. The operator starts the mid-flight engine 5, which is located in the front of the fuselage at idle, due to this the rotation of the mid-flight propeller 9 begins. After a certain period of time, the elevating propellers 8 are turned on and the UAV is torn off from the ground. After gaining the necessary height, the marching propeller 9 is turned on, and after a short period of time (10-20 s) the lifting propellers 8 are turned off. After this, this UAV GDP is able to move horizontally. If it is necessary to fly vertically or hover in the air (for example, for observation or aerial photography), the propellers 8 are turned on and the march propeller 9 is turned off. When landing, the march propeller 9 is turned off and the propellers 8 are turned on, the UAV GDP is lowered.

The wing 6 provides the creation of lifting force, and the ailerons 11 located on each wing console serve to provide lateral controllability of the aircraft. Track control is carried out by the rudder 13.

When the fuel tank 17 is installed inside the fuselage body 1, in its upper part, in the payload compartment 16, the UAV UAV flight duration increases, since with a decrease in the battery’s charge, the UAV UAV can run on liquid fuel, thereby increasing the flight range, increasing maneuverability, and in general, the UAV’s efficiency increases in GDP by expanding its functionality.

Dismantling UAV GDP is carried out in the reverse order:

Undocking the upper part of the fuselage body 1 from the bottom. Disconnecting the battery 16 from the wing 6. Disconnecting the bottom of the fuselage body 1. Disconnecting the main engine 5 with the propeller 9 and the fuel tank 17. Disconnecting the wing 6 with pylons 7 and screws 8 at their ends from the bottom of the fuselage body 1. Sequential disconnection from composite power beam 2 made of truss aggregate, airborne equipment 4 and tail unit.

According to its technical and economic advantages, in comparison with the known analogues, the proposed utility model allows you to create an effective, i.e. reliable and durable, unmanned aerial vehicle of vertical take-off and landing due to the introduction of a rectangular rectangular shaped power beam with truss filler, which makes the UAV GDP design modular and makes the proposed UAV GDP easier to assemble, disassemble and transport. The composite power beam is rigidly fixed inside the body at the bottom of the fuselage with screws and base edges for fixing the beam, for example, along the length of the power beam with three base edges whose axes are perpendicular to the axis of the fuselage. The base edges are made with curved ends, their lower part is attached to the composite power beam, and the curved ends are attached to the walls of the fuselage body from the inside. Base edges increase the rigidity of the fuselage body and make this UAV GDP safe and durable. A detachable housing, consisting of upper and lower parts, allows for quick access, repair and replacement of parts and assemblies in the event of a breakdown of this UAV GDP, which increases the functionality of this UAV GDP and its modularity, that is, the possibility of a complete analysis of UAV GDP for more convenient transportation and subsequent assembly for operation. The compartment located inside the fuselage body in its upper part is divided into compartments separated by a battery located on the central part of the wing inside the body, which allows you to install an additional effective payload inside the fuel tank. Pylons installed on both wing consoles with lifting screws serve for vertically take-off and landing of this UAV, which also increases its functionality and its scope. The implementation of the combined power plant allows the UAV UAV to operate from the main engine and the fuel supply system from the fuel tank, thereby increasing the flight time, i.e. UAV range of GDP, and overall efficiency.

Claims (1)

The modular design of an unmanned aerial vehicle of vertical take-off and landing with a combined power plant, including the fuselage, the power element of the carrier beam, rigidly fixed inside the fuselage body, the wing with ailerons, attachment points, the power plant located in the fuselage body, the battery, the compartment for placing useful load, characterized in that the wing is made whole, on each console wing made pylons with two lifting screws for vertical take-off and landing, power set the wok located in the front of the fuselage body contains a main engine with a propeller, rotationally driven by liquid fuel, using the fuel tank feed system, the propeller is placed in the front of the fuselage to ensure horizontal flight, as a load-bearing component a composite composite beam was introduced, made in the form of a rectangular one-piece structure, inside of which there is a truss aggregate, while the composite composite beam is located after the engine, and its end is located outside the fuselage body, on-board equipment and tail unit, including keel, rudder, stabilizer, elevator, located and fixed by screws, are located on the end of the power beam, and the power composite beam is rigidly fixed to the bottom of the fuselage body parallel to its axis using screws and base edges made in the form of rectangular plates, the axes of which are perpendicular to the axis of the fuselage body, the base edges are made with bent ends, their lower part is attached to positive power beam, the bent ends are attached to the walls of the fuselage body from the inside, and the fuselage body is detachable, consisting of upper and lower parts interconnected by rivet nuts, in the upper part of the fuselage body, compartments are made, separated by a battery, one of which contains a fuel tank.

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