RU219528U1 - SMALL UNMANNED VERTICAL TAKEOFF AND LANDING VEHICLE - Google Patents

Abstract

The utility model relates to the field of aviation technology and can be used in the design and construction of unmanned aerial systems with unmanned aerial vehicles. SUBSTANCE: small-sized vertical take-off and landing unmanned aerial vehicle contains a wing of high elongation, from above through a lodgement, repeating the upper contour of the wing, equipped with four primary projections and coaxially located four secondary projections in a cavity formed by two side and two end faces, connected to a flat constant thickness of the fuselage beam. The wing, from below through the lodgements, repeating the lower contour of the wing, equipped with two pairs of primary projections and two pairs of secondary projections coaxially located in the cavity formed by two side and two end faces, connected to rectangular-section pylons along the entire length, on which lifting electric motors are placed with screws. In the front part, the fuselage beam contains a power frame with an emphasis, and in the tail part on the cradle there is a stabilizer with an elevator (hereinafter referred to as RV), a keel with a rudder (hereinafter referred to as RN) and a fork, which is the third support of the UAV. In this case, the fuselage fairing mounted above the fuselage beam, covering the side faces of the beam and adjacent to them along the entire length, due to the elastic forces of the fairing walls, is brought under the stop of the power frame and fixed with one quick-release screw. EFFECT: increased operational manufacturability by reducing the time to prepare for a re-flight.

Description

The utility model relates to the field of aviation technology and can be used in the design and construction of unmanned aircraft systems with unmanned aerial vehicles (hereinafter referred to as UAVs) of aircraft type, including vertical takeoff and landing UAVs (hereinafter referred to as UAVs), intended for aerial surveillance, reconnaissance, detection, target designation and laser illumination of targets for guidance of guided munitions. UAV VVP can also be used in the civil sphere, for example, when detecting emergencies and monitoring areal and linear objects.

A convertible UAV VVP is known, designed to conduct reconnaissance and rescue operations, to protect state borders, as well as to inspect high-risk facilities, especially in hard-to-reach areas of the country (access mode: https://topwar.ru/180298-zala-vtol-novejshij- rossijskij-bespilotnik-konvertoplan.html, accessed February 2023). Convertible UAV combines the best qualities of aircraft and helicopter UAVs. The well-known UAV VVP is made according to the tailless aerodynamic scheme (a variation of the “flying wing” scheme) with wingtips bent upwards and a pushing electric power plant with a propeller. Under the right and left wing panels there are pylons with lifting electric motors fixed in pairs at their ends, equipped with propellers. The target load (hereinafter - CL) is located in the bow of the UAV body and has the ability to turn. The VVP UAV has a wingspan of 2.85 m, a maximum takeoff weight of 10.5 kg and a maximum flight speed of up to 110 km/h. Flight duration - 2 hours. The takeoff and landing of an unmanned vehicle is carried out in copter mode (according to helicopter). The marching power plant (hereinafter referred to as PU), fuel tank, onboard electronic equipment (hereinafter referred to as avionics), onboard cable network (hereinafter referred to as BKS) are located inside the wing and fuselage structure, access to which is carried out through special covers mounted on screws.

The disadvantages of the well-known convertible UAV GDP include:

technological complexity of manufacturing an airframe of an aircraft with an aerodynamic scheme of "tailless", manufactured using matrix technology;

technological complexity of the UAV UAV operation, including, in preparation for a re-flight (mounting and dismantling of avionics elements, including several batteries (hereinafter referred to as batteries), connecting and disconnecting BCS connectors in the engine compartment of a small-sized aircraft, etc. );

low maintainability of the UAV airframe.

Known collapsible UAV block design from the patent of the Russian Federation No. 173480 with a priority date of 27.10.2016, made according to the aerodynamic scheme "flying wing", modular design. The UAV contains parts of a composite wing and a fuselage connected by two rods inserted into the cylindrical guides of the fuselage, and the other ends of the rods are inserted into the corresponding holders installed in the wing consoles. The wing tips are connected to the wing consoles by means of rods that are inserted into coaxial holders installed in the wing consoles and in the tips. The fixation of the wing panels to the fuselage and the fixation of the wing tips to the wing panels is carried out using rubber ties attached to the fuselage and wing panels.

The disadvantages of the known collapsible UAV include:

the technological complexity of manufacturing an aircraft airframe made using matrix technology with a system for precise positioning of rods and guides intended for assembling UAVs;

low operational reliability due to the use of four parts of the composite wing and the use of rubber ties to fix the consoles and wingtips;

low maintainability of the UAV airframe.

A collapsible unmanned aerial vehicle with horizontal flight of vertical takeoff and landing is known from RF patent No. 207716 with a priority date of 08/12/2021, which is a block structure containing wing panels, a fuselage and rods. The peripheral parts of these rods fit tightly into the coaxial holes in the wing consoles. The UAV contains a section of the fuselage support structure with a center section, which is a one-piece structure made of a composite material, consisting of a wing element located perpendicular to the longitudinal axis of the fuselage. Cylindrical holes are made in the wing part, designed to install rods for attaching pylons with lifting screws and cantilever parts of the wing. The supporting structure of the fuselage is closed by a fairing body.

The disadvantages of this technical solution include:

the technological complexity of manufacturing and repairing a unique structural element - a wing-fuselage section, with a system for precise positioning of rods and guides intended for assembling an UAV and a wing made using matrix technology;

low operational reliability due to the use of a unique structural element - a wing-fuselage section, with a system for precise positioning of rods intended for assembling UAVs, pylons with lifting screws and wing consoles;

technological complexity of operation, including in preparation for a re-flight (assembly and dismantling of airframe and avionics elements intended for regular replacement (reloading), by unscrewing and screwing a large number of fairing body fasteners along three frames and a wing-fuselage section) .

This decision on the technical essence is closest to the proposed utility model and is taken as a prototype.

The technical problem to be solved by the claimed utility model is the elimination of the above disadvantages of the prototype and the provision of high performance.

The technical result of the utility model is to increase the operational manufacturability (clause 3.17 of GOST R 56079-2014) by reducing the time to prepare for a re-flight. An additional technical result is an increase in repair manufacturability (clause 3.13 of GOST R 56079-2014) through the use of simplified structural forms, publicly available structural materials and positive technology during repairs.

To achieve these technical results, the claimed small-sized vertical take-off and landing unmanned aerial vehicle contains a wing of high elongation, from above, through a lodgement, which is a support surface that repeats the upper contour of the wing, equipped with four primary projections and coaxially located four secondary projections in a cavity formed by two lateral and two end faces connected to a flat constant thickness of the fuselage beam, the wing, from below through the lodgements, which are supporting surfaces repeating the lower contour of the wing, equipped with two pairs of primary projections and coaxially located with two pairs of secondary projections in the cavity formed by two side and two end faces, connected with pylons (beams) of rectangular section along the entire length, on which lifting electric motors with screws are placed. In the front part, the fuselage beam contains a power frame with an emphasis, and in the tail section on the cradle there is a stabilizer with an elevator (hereinafter referred to as RV), a keel with a rudder (hereinafter referred to as RN) and a fork, which is the third support of the UAV, and the stabilizer with RV, the rudder keel and forkil are made in the form of flat plates with roundings along the leading edge and thinning towards the trailing edge, while the keel and forkil are integral parts of the fuselage beam. On top of the fuselage beam, replaceable (after each flight) batteries are installed to power lifting electric motors (hereinafter referred to as EM) and other consumers of electricity, a fuel tank, a sustainer internal combustion engine and a set of avionics equipment that ensures the tasks of a small-sized UAV VVP as intended, which are covered by a fuselage fairing.

At the same time, the fuselage fairing, installed above the fuselage beam, covering the side faces of the beam and adjacent to them along the entire length, due to the elastic forces of the fairing walls, is brought under the stop of the power frame and fixed with one quick-release screw.

Additional advantages and essential features of the present utility model can be presented in the following particular embodiments.

In particular, the high elongation wing is made in one piece (one-piece).

In particular, the high elongation wing is made detachable.

In particular, the high elongation wing is made according to positive technology.

In particular, the high elongation wing is made using matrix technology.

In particular, the fuselage beam is made in the form of a mixed design.

In particular, the fuselage beam is made in the form of a composite structure with a honeycomb core.

In particular, the fuselage beam is made in the form of a composite structure with cellular filler.

In particular, the fuselage beam is made in the form of a multilayer composite structure.

In particular, the fuselage beam is made of solid wood of low density.

In particular, the stabilizer with RV and the keel with PH and forkil are made in the form of a composite structure with a thin symmetrical airfoil using positive technology.

In particular, the stabilizer with RV and the keel with PH and forkil are made in the form of a composite structure with a thin symmetrical airfoil using matrix technology.

In particular, the fuselage fairing is made using a positive technology.

To clarify the essence of the proposed technical solution, consider the graphic images:

figure 1 - design fastening the fuselage beam to the wing;

figure 2 - General view of the UAV GDP;

figure 3 - design fastening pylons (beams) to the wing;

figure 4 - design of the quick-release fastening of the fuselage fairing, where:

1 - wing;

2 - wing lodgement;

3 - fuselage beam;

4 - lodgement of the pylon (beam);

5 - pylon (beam);

6 - power frame with an emphasis;

7 - stabilizer with RV;

8 - keel with launch vehicle;

9 - forkil;

10 - replaceable batteries;

11 - lifting electric motor (hereinafter - EM);

12 - fuel tank;

13 - sustainer internal combustion engine (ICE);

14 - set of avionics;

15 - fuselage fairing;

16 - quick-release mount (screw).

The description of the implementation of the utility model can be used as an example for a better understanding of its essence and is set out with reference to the figures attached to the present description. At the same time, the following details are intended not to limit the essence of the utility model, but to make it more clear.

Small-sized unmanned aerial vehicle vertical takeoff and landing, contains a wing (1) of large elongation (figure 1, figure 2 view A), from above, through the lodgement (2) representing a support surface, repeating the upper contour of the wing, equipped with four primary protrusions and coaxially with them located by four secondary protrusions in the cavity formed by two side and two end faces connected to a flat constant thickness of the fuselage beam (3). Wing (1), from below (figure 2, view A, figure 3) through the lodgements (4), which are supporting surfaces, repeating the lower contour of the wing, equipped with two pairs of primary protrusions and coaxially located with two pairs of secondary protrusions in the cavity formed by two side and two end faces, connected with pylons (beams) (5) of rectangular section along the entire length, on which lifting motors with screws are placed. In the front part, the fuselage beam (3) contains a power frame (6) with a stop, and in the tail part, on the cradle, there is a stabilizer (7) with an elevator (hereinafter - RV), a keel (8) with a rudder (hereinafter - RN) and the fork (9), which is the third support of the UAV, moreover, the stabilizer (7) with RV, the keel (8) with PH and the fork (9) are made in the form of flat plates with rounding along the front and thinning towards the rear edge, and the keel (8) and forkil (9) are integral parts of the fuselage beam (3). On top of the fuselage beam (3) there are replaceable (after each flight) batteries (10) for powering lifting electric motors (hereinafter referred to as EM) (11) and other consumers of electricity, a fuel tank (12) for a sustainer (13) internal combustion engine and a set of avionics equipment ( 14), which ensures the fulfillment of the tasks of the VAV UAV for its intended purpose, which are covered with a fairing (15) of the fuselage (figure 2, view B), made according to a positive technology, with a quick-release mount. The quick-release mount is designed for quick fixing and unfixing of parts.

At the same time, the fairing (15) of the fuselage (figure 4), installed above the fuselage beam (3), covering the side faces of the beam (3) and adjacent to them along the entire length, due to the elastic forces of the walls of the fairing (15), is brought under the stop of the power frame (6) and secured with one quick release screw (16).

The method of attaching the fairing (15) of the fuselage, proposed in this utility model, leads to a significant reduction in the time to prepare for a re-flight, which increases the operational manufacturability (clause 3.17 of GOST R 56079-2014) of the VAV UAV, in contrast to the prototype. The technical solution of the prototype according to the method of fastening the fairing (15) of the fuselage, provides for fastening the fairing along three frames and side faces of the fuselage beam (with a screw pitch of 100 -150 mm) with sixteen screws, which leads to significant losses of time that are formed during group installation operations screws into the holes, leading the tool and positioning it, screwing a group of screws, moving to another workplace (position) along one side of the UAV fuselage, repeating the above operations and new transitions to other workplaces (positions) along the other side of the fuselage.

In particular embodiments, the following implementations of the wing are possible: a one-piece (one-piece) wing (1) of high elongation, or a wing (1) of high elongation can be made detachable, consisting of two or more parts. The wing (1) can be made according to the matrix manufacturing technology, or made according to the positive technology.

The following implementations of a flat constant thickness of the fuselage beam are possible: the fuselage beam (3) is made in the form of a mixed structure; the fuselage beam (3) is made in the form of a composite structure with a honeycomb filler; fuselage beam (3) is made in the form of a composite structure with cellular filler; the fuselage beam (3) is made in the form of a multilayer composite structure; the fuselage beam (3) is made of solid wood of low density.

The following implementations of the stabilizer with RV and the keel with PH and fork are possible: the stabilizer (7) with RV and the keel (8) with PH and fork (9) are made in the form of a composite structure with a thin symmetrical airfoil according to positive technology; stabilizer (7) with RV and keel (18) with launch vehicle and forkil (9) are made in the form of a composite structure with a thin symmetrical airfoil using matrix technology.

The variants of technological solutions for the flat fuselage beam (3), described above, are aimed at improving the repair manufacturability (paragraph 3.13 of GOST R 56079-2014) through the use of simplified structural forms, publicly available structural materials and positive technology during repair, which gives obvious and undeniable advantages over the prototype, the power beam (wing-fuselage section) of which with a truss filler is a three-dimensional box-shaped, cellular structure in the form of regular pyramids along the entire length of the beam made of composite material, with zigzag rods located inside, normal to the horizontal rectangular plates of the power beam, forming, when connecting zigzag profiles with grooves on the inner and outer sides, cells in the form of regular pyramids. From the above description it can be seen that the repair of the power beam (wing-fuselage section) of the prototype is practically impossible by the operating organization.

The technological solutions proposed in this utility model, incorporated in the design of the fuselage beam (3), fairing (15) of the fuselage, wing (1), stabilizer (7) with RV, keel (8) with LV and forkil (9) will allow the operating organization to carry out UAV airframe repairs using simplified technologies and publicly available (including retail and wholesale) structural materials.

As a result of the application of the proposed utility model, the time directly spent on the dismantling and installation of the fuselage fairing (15) is reduced by 83%, and the time spent on the full range of post-flight inspection, dismantling the fairing (15), refueling, changing (recharging) batteries , installation of the fairing (15), pre-flight preparation, formation and loading of the flight task, is reduced by 44%.

Small unmanned aerial vehicle vertical takeoff and landing operates as follows. The UAV is assembled: to the wing (1) of high elongation (figure 1), from above, through the lodgement (2), which is a support surface that repeats the upper contour of the wing, equipped with four primary protrusions and coaxially located four secondary protrusions in the cavity formed by two side and two end faces (by analogy with LEGO: US patent No. 3005282, patent dated Oct. 24, 1961. TOY BUILDING BRICK, Godtfred Kirk Christiansen, Billund, Denmark.), the primary projections of which are inserted with an interference fit into the wing holes coaxial with them (1), and the secondary protrusions are inserted with an interference fit into the coaxial holes of a flat constant thickness of the fuselage beam (3) of a mixed design (figure 2, view A), precisely positioning the wing (1) and the fuselage beam (3) and eliminating all six degrees of freedom . Additionally, the wing (1), lodgement (2) and fuselage beam (3) are bolted together (figure 1). To the wing (1), from below (figure 2, view A, figure 3) through the lodgement (4) which is a support surface that repeats the lower contour of the wing, equipped with two primary protrusions and coaxially located with two secondary protrusions in the cavity formed by two side and two end faces (by analogy with the technical solution from US patent No. 3005282), the primary protrusions of which are inserted with an interference fit into the coaxial holes of the wing (1), and the secondary protrusions are inserted with an interference fit into the coaxial holes of the pylon (beam) (5) of rectangular section along the entire length of which are placed lifting motors (11) with screws, precisely positioning the wing (1) and pylon (beam) (5) and eliminating all six degrees of freedom. Additionally, the wing (1), lodgement (4) and pylon (beam) (5) are bolted together. In front of the fuselage beam (3) a power frame (6) with a stop is installed, and in the tail part of the fuselage beam (3) a stabilizer (7) with an elevator, a keel (8) with a rudder and a fork (9) are installed through the cradle, which is the third support of the UAV, moreover, the stabilizer (7) with RV, the keel (8) with PH and the fork (9) are made in the form of flat plates with roundings along the front and thinning towards the rear edge, and the keel (8) and fork (9) are integral parts of the fuselage beam (3). Replaceable (after each flight) batteries (10) are installed on top of the fuselage beam (3) for powering lifting electric motors (EM) (11) and other consumers, a fuel tank (12), a sustainer (13) internal combustion engine and a set of avionics equipment (14) , which ensures the fulfillment of the tasks of the VAV UAV according to its intended purpose, which are closed with a fairing (15) of the fuselage (figure 2, view B), made using a positive technology, with a quick-release mount.

At the same time, the fairing (15) of the fuselage (figure 4), installed above the fuselage beam (3), covering the side faces of the beam (3) and adjacent to them along the entire length, due to the elastic forces of the walls of the fairing (15), is brought under the stop of the power frame ( 6) and secured with one quick release screw (16).

After assembling the UAV, the GDP is operated as follows. After the pre-flight preparation, the lifting (11) and sustainer (13) engines are started, the lifting (11) engines are switched to takeoff mode and the VVP UAV starts vertical takeoff. After gaining a predetermined altitude, the sustainer (13) engine is switched to the nominal mode and when the predetermined speed of the UAV VVP is reached, it switches to horizontal flight, the lifting (11) engines are turned off. For the UAV landing, the VVP reduces the horizontal flight speed, the lifting (11) engines are turned on, the sustainer (13) engine is stopped. Further, the VVP UAV begins its vertical descent until landing.

After landing, a post-flight inspection is carried out, the quick-detachable screw (16) is released, the fairing (15) of the fuselage is removed, the replaceable batteries (10) are replaced, the fuel tank (12) is refueled, the fairing (15) of the fuselage is installed, which is fixed using one quick-detachable (designed for quick fixing and unfixing of parts) of the screw (16), the flight task is loaded. UAV with GDP is ready for re-flight.

Thus, an increase in operational manufacturability and an increase in repair manufacturability is achieved due to the fact that the inventive small-sized vertical take-off and landing unmanned aerial vehicle contains a wing of large elongation, from above, through a lodgement, which is a support surface that repeats the upper contour of the wing, equipped with four primary projections and coaxially located by four secondary ledges in the cavity formed by two side and two end faces connected to a flat fuselage beam of constant thickness, the wing, from below through the lodgements, which are supporting surfaces, repeating the lower contour of the wing, equipped with two pairs of primary ledges and coaxially located with two pairs of secondary protrusions in the cavity formed by two side and two end faces, connected with pylons (beams) of rectangular section along the entire length, on which lifting electric motors with screws are placed. In the front part, the fuselage beam contains a power frame with a stop, and in the tail section on the cradle there is a stabilizer with RV, a keel with LV and a fork, which is the third support of the UAV, moreover, the stabilizer with RV, the keel with LV and the fork are made in the form of flat plates with roundings along the leading edge and thinning towards the trailing edge, and the keel and forkil are integral parts of the fuselage beam. On top of the fuselage beam, replaceable batteries are installed to power the lifting EMs and other consumers of electricity, a fuel tank, a main engine and a set of avionics equipment that ensures the tasks of a small-sized VVP UAV as intended, which are covered by a fuselage fairing. At the same time, the fuselage fairing, installed above the fuselage beam, covering the side faces of the beam and adjacent to them along the entire length, due to the elastic forces of the fairing walls, is brought under the stop of the power frame and fixed with one quick-release screw.

Claims (13)

1. Small-sized vertical takeoff and landing unmanned aerial vehicle (hereinafter - UAV VVP), containing a wing, rectangular pylons, along the entire length of which lifting electric motors with propellers are placed, a fuselage beam, on which the vertical tail is located, and a lodgement, on which horizontal plumage, while in front of the main engine with a propeller is installed, on top of the fuselage beam there are replaceable batteries for powering lifting electric motors and other consumers of electricity, a fuel tank, a main engine and a set of avionics equipment that ensures the tasks of a small-sized UAV GDP for its intended purpose, which are closed by a fuselage fairing, characterized in that the wing is made with a large elongation, from above, through a lodgement, which is a support surface that repeats the upper contour of the wing, equipped with four primary projections and coaxially located four secondary projections in a cavity formed by two side and two end faces, connected with a flat constant thickness of the fuselage beam of mixed design; wing, from below through lodgements, which are supporting surfaces that exactly repeat the lower contour of the wing, equipped with two pairs of primary projections and two pairs of secondary projections coaxially located in the cavity formed by two side and two end faces, connected to rectangular pylons along the entire length; in the front part, the fuselage beam contains a power frame with an emphasis, and in the tail section on the cradle there is a stabilizer with an elevator (hereinafter referred to as RV), a keel with a rudder (hereinafter referred to as RN) and a forkil, which is the third support of the UAV, and the stabilizer with RV, the rudder keel and forkil are made in the form of flat plates with roundings along the leading edge and thinning towards the trailing edge, and the keel and forkil are integral parts of the fuselage beam; at the same time, the fuselage fairing mounted above the fuselage beam, covering the side faces of the beam and adjacent to them along the entire length, due to the elastic forces of the fairing walls, is brought under the stop of the power frame and fixed with one quick-release screw. 2. Small-sized vertical takeoff and landing unmanned aerial vehicle according to claim 1, characterized in that the high elongation wing is made in one piece. 3. Small unmanned aerial vehicle vertical takeoff and landing according to claim 1, characterized in that the wing of high elongation is made detachable. 4. Small-sized vertical takeoff and landing unmanned aerial vehicle according to claim 1, characterized in that the high elongation wing is made according to positive technology. 5. Small-sized vertical takeoff and landing unmanned aerial vehicle according to claim 1, characterized in that the high elongation wing is made using matrix technology. 6. Small-sized vertical takeoff and landing unmanned aerial vehicle according to claim 1, characterized in that the fuselage beam is made in the form of a mixed structure. 7. Small-sized vertical takeoff and landing unmanned aerial vehicle according to claim 1, characterized in that the fuselage beam is made in the form of a composite structure with a honeycomb filler. 8. Small-sized vertical takeoff and landing unmanned aerial vehicle according to claim 1, characterized in that the fuselage beam is made in the form of a composite structure with a cellular filler. 9. Small-sized vertical takeoff and landing unmanned aerial vehicle according to claim 1, characterized in that the fuselage beam is made in the form of a multilayer composite structure. 10. A small-sized vertical take-off and landing unmanned aerial vehicle according to claim 1, characterized in that the fuselage beam is made of a single piece of low-density wood. 11. A small-sized vertical take-off and landing unmanned aerial vehicle according to claim 1, characterized in that the stabilizer with RV and the keel with PH and forkil are made in the form of a composite structure with a thin symmetrical airfoil according to positive technology. 12. A small-sized vertical take-off and landing unmanned aerial vehicle according to claim 1, characterized in that the stabilizer with RV and the keel with PH and forkil are made in the form of a composite structure with a thin symmetrical airfoil using matrix technology. 13. A small-sized vertical take-off and landing unmanned aerial vehicle according to claim 1, characterized in that the fuselage fairing is made using a positive technology.