RU63771U1 - SMALL UNMANNED AIRCRAFT (OPTIONS) - Google Patents

Abstract

The apparatus, made folding, has a fuselage with a tail and a wing with two consoles. The device features are the fuselage in the form of the bow (2) and the aft beam (3) connected to it by the connection unit (8) containing a three-stage hinge and a latch, rigid fastening of one wing console (6) to the bow and hinging the other console (5 ) with the possibility of its rotation and folding from the first, as well as the possibility of compact folding of the aerodynamic surfaces (29, 30) of the tail unit (7). Embodiments provide for the presence of a V-shaped or T-shaped tail unit with an upper or lower arrangement of horizontal tail units. Options also differ by means of installation and folding of the aerodynamic surfaces of the tail. EFFECT: reduced overall dimensions of the aircraft in the folded state for transportation and storage, simplified design of the units subjected to transformation and ease of maintenance of the aircraft due to the ease of transformation. Three overall dimensions in the folded position of the apparatus are determined, respectively, by the length of the aft beam (3), the length of the bow (2) of the fuselage and the sum of the diameters of these parts of the fuselage and the thickness of the wing consoles (5, 6).

3 independent and 3 dependent claims, 21 figures of drawings.

Description

The utility model relates to the field of small-sized aircraft, and more specifically to small-sized unmanned aerial vehicles.

The ability to transform to reduce the dimensions in the transport state and during storage is one of the most important requirements for small-sized aircraft, including unmanned ones.

There are various schemes of transformable aircraft.

So, in accordance with the USSR author's certificate No. 1821422 (publ. 06/15/1993, [1]) the wing consoles are folding folding 90 ° downward, and in accordance with the patent of the Russian Federation No. 2125524 (publ. 27.01.1999, [2 ]) - folding with 90 ° rotation up. Solutions similar to the latter are also described in patents of the Russian Federation No. 2183182 (publ. 10.06.2003, [3]) and No. 2228283 (publ. 10.05.2004, [4]).

The aircraft according to the patent of the Russian Federation No. 2183333 (publ. 04/20/2002, [5]) has a console with two sections that rotate around an axis parallel to the longitudinal axis of the device, and pressed against each other and the fuselage after folding by such a rotation.

According to the patent of the Russian Federation No. 2005663 (publ. 15.01.1994, [6]) each wing console is made rotatable and folding in such a way that the consoles are located along the fuselage on its sides. In the patent of the Russian Federation No. 2321477 (published on June 27, 2004, [7]) a similar solution is described, characterized in that the consoles are rotated together before folding them on the sides of the fuselage.

US Pat. No. 5,050,817 (published September 24, 1991, [8]) describes a similar solution [6], supplemented by the possibility of folding the ends of the consoles by turning them 90 ° after placing the consoles on the sides of the fuselage, as a result of which these ends occupy a position perpendicular the longitudinal axis of the apparatus, behind its fuselage, reducing the total length of the apparatus.

From the patent of the Russian Federation No. 2125523 (publ. 01/27/1999, [9]) there is a known aircraft layout with wing consoles folding along the fuselage, the planes of which at the same time occupy a horizontal position above the fuselage.

A common feature of the group of technical solutions described above [1] - [9] is that they are limited to the use of various means of folding the consoles. This is not enough to minimize the dimensions of the aircraft in a transport state and during storage.

The patent of the Russian Federation No. 2026781 (publ. 30.07.1994, [10]) describes an aircraft having wing consoles with folding end sections with the possibility of joint rotation of the consoles around the transverse axis of the fuselage and subsequent folding of the consoles with their placement on the sides of the fuselage. In addition, tail

plumage on a cantilever suspension of variable length with the possibility of moving it forward and reducing the length of the apparatus when folded. This technical solution provides an additional opportunity to reduce the dimensions of the aircraft in the folded state by reducing its length. However, the transverse dimensions due to the size of the tail unit remain unchanged.

Also known small-sized aircraft according to US patent No. 4,706,907 (publ. 17.11.1987, [11]). It has telescopically folding wing consoles, which after such folding can be lowered down by turning 90 ° around an axis parallel to the longitudinal axis of the device. The elements of the tail can be folded into a flat vertically oriented figure, after which the tail can be rotated around the horizontal transverse axis by 180 ° and take a position under the fuselage. After these transformations, the length of the apparatus can be further reduced due to the implementation of the fuselage of two telescopically folding parts. Creating telescopically folding wing consoles and fuselage parts is a technically challenging task, and the transformation process requires a large number of manipulations.

In the patent of the Russian Federation No. 2139795 (publ. 10/20/1999, [12]) an aircraft is described having a root and two central and end sections of the wing console. As a result of sectional folding, each end section is pressed with its lower side to the lower side of the corresponding central section, and the central section together with the end section pressed to it rotates 90 ° downward relative to the root section and occupies a vertical position on the side of the fuselage. In addition, the aft part of the fuselage is connected to the bow in a detachable manner and can be laid on top of the bow.

This technical solution from the point of view of design features of a small aircraft, related to its transformation into a state for transportation and storage, is closest to the proposed one.

In this design, which is closest to the proposed one, as well as in technical solutions for patents [10] and [11], it is possible to reduce the longitudinal dimension of the aircraft in a transport state and during storage. However, this possibility is limited by the framework of the two-keel scheme, since with a single-keel or rat-free scheme with a V-shaped plumage, the placement of the aft part after its rotation above the nose of the fuselage, proposed in the patent [12], is difficult. To reduce the longitudinal dimension by placing the aft part of the fuselage above its bow, the aircraft must be equipped with a complex hydraulic system. The transformation process itself is also complicated. In addition, as in the decision according to the patent [10], in the folded state of the aircraft its transverse dimensions remain unchanged, due to the size of the two-tail tail.

The proposed technical solution is aimed at obtaining a technical result, which consists in reducing the overall dimensions of the aircraft in the folded state to increase the convenience of its transportation and storage while simplifying the design of the units and the aircraft undergoing transformation as a whole, as well as simplifying the use and maintenance of the aircraft due to the ease of transformation . Below, when revealing a utility model and describing particular cases of its implementation, other types of achieved technical result will be named.

The proposed small unmanned aerial vehicle is represented by three options for its implementation.

In accordance with the first embodiment, the proposed small-sized unmanned aerial vehicle, like the one closest to it known by the patent [12], has a fuselage with a tail unit and a folding wing containing two consoles. The fuselage contains the bow and stern parts and is configured to change their relative position. The wing consoles are mounted on the nose of the fuselage.

To achieve the specified technical result in the proposed small unmanned aerial vehicle according to the first embodiment, in contrast to the closest known to it, the first wing console is mounted rigidly, and the second is pivotally with the ability to fix it in a position corresponding to the flight state of a small aircraft, and with the possibility turning towards the first console in the condition of a small aircraft for transportation and storage.

The aft part of the fuselage is made in the form of a stern beam connected to the bow by a connection unit containing a three-degree hinge and a latch. The three-stage hinge is shifted forward relative to the rear end of the nose of the fuselage, and the latch is shifted back relative to the front end of the aft beam.

Moreover, the lower edge of the nose of the fuselage is located above the upper edge of the aft beam and the point of intersection of the three axes of rotation of the three-degree hinge is located on the extension of the longitudinal axis of the aft beam, and the latch is made with the possibility of fixing the aft beam in the flight state of a small unmanned aerial vehicle with its longitudinal axis oriented in parallel continuation of the longitudinal axis of the bow.

Plumage in the described first embodiment is made T-shaped in the form of vertical and horizontal plumage. In this case, the vertical tail is rigidly connected to the aft beam. The horizontal tail has two consoles. The latter are articulated with a vertical

plumage in its upper or lower part, or with a stern beam, with the possibility of rotation in the direction of vertical plumage in a state for transportation and storage and with the possibility of fixing in a position corresponding to the flight state of a small unmanned aerial vehicle.

The pivotally mounted wing consoles and horizontal plumage consoles can be fixed in a position corresponding to the flight state, in particular, using position fixers made in the form of plate spring locks.

The articulated joints of one of the wing consoles with the nose of the fuselage and the nose of the fuselage with the aft (aft beam) provide the ability to transform the aircraft into a state for transportation and storage by folding the wing consoles until one of the upper surfaces fits one another and rotates the aft beam relative to the nose of the fuselage. This, in turn, ensures minimization of the transverse and longitudinal dimensions of the aircraft in a state for transportation and storage. At the same time, factors complicating the design of the apparatus during telescopic execution of the wing consoles, inherent in the closest known technical solution, are eliminated. At the same time, due to the described mutual arrangement of the nose of the fuselage and the aft beam (the first above the second at the point of their connection with the mount) and the point of intersection of the rotation axes of the three-degree hinge, it is possible to move the aft of the fuselage (aft beam) forward by turning it. This also helps to reduce the size of the small aircraft in the state of transportation and storage.

The implementation of the connection between the nose of the fuselage and the aft beam using the connection node containing the retainer along with a three-degree hinge, located in this way, provides rigidity

the connection of these two parts of the fuselage in the flight state in combination with the simplicity of the design and ease of maintenance of the aircraft in the process of its transformation from one state to another.

The described alternative cases of constructive execution of the T-shaped tail unit in the proposed small-sized aircraft according to the first embodiment differ in the attachment location of the horizontal tail units. Due to the general peculiarity of performing this fastening in all cases — the ability to rotate these consoles — when the aircraft is switched from a flight state to a state for transporting storage, all three aerodynamic surfaces of the tail unit can be pressed against each other. In combination with the presence of a three-stage hinge as part of the attachment unit connecting the nose of the fuselage with the aft beam, this allows further rotations of these surfaces folded together with the aft beam in such a way as to minimize the size of the aircraft in a direction parallel to its vertical building axis . The aerodynamic surfaces of the tail unit, folded together, do not go beyond the dimensions determined by the total height of the nose of the fuselage with the stern beam and the thickness of the folded wing consoles.

The possibility of fixing the articulated wing consoles and horizontal tail consoles in a position corresponding to the flight state of a small unmanned aerial vehicle provides the necessary rigidity of the aircraft structure in this state.

The use of plate spring locks, as one of the various possible particular cases of the execution of fastening means in the required position of the articulated wing console and horizontal tail consoles, provides unification of elements and simplicity of design

combined with ease of maintenance. At the same time, such locks successfully fulfill the fixation function assigned to them and provide structural rigidity for a small unmanned aerial vehicle in flight condition.

All actions for transforming the proposed small-sized unmanned aerial vehicle according to the first embodiment from the flight state to the state for transportation and storage and vice versa are reduced to unlocking or fixing the connections of the bow and stern of the fuselage, one wing console and horizontal tail units and several simple turns, which simplifies use of the device and its maintenance.

In accordance with the second option, the proposed small-sized unmanned aerial vehicle, like the one closest to it known by the patent [12], has a fuselage with a tail unit and a folding wing containing two consoles. The fuselage contains the bow and stern parts and is configured to change their relative position. The wing consoles are mounted on the nose of the fuselage.

To achieve the specified technical result in the proposed small unmanned aerial vehicle according to the second embodiment, in contrast to the closest known to it, the first wing console is mounted rigidly, and the second is pivotally with the ability to fix it in a position corresponding to the flight state of the small aircraft, and with the possibility turning towards the first console in the condition of a small aircraft for transportation and storage.

The aft part of the fuselage is made in the form of a stern beam connected to the bow by a connection unit containing a three-degree hinge and a latch. The three-stage hinge is shifted forward relative to the rear end of the nose of the fuselage, and the latch is shifted back relative to the front end of the aft beam.

Moreover, the lower edge of the nose of the fuselage is located above the upper edge of the aft beam and the point of intersection of the three axes of rotation of the three-degree hinge is located on the extension of the longitudinal axis of the aft beam, and the latch is made with the possibility of fixing the aft beam in the flight state of a small unmanned aerial vehicle with its longitudinal axis oriented in parallel continuation of the longitudinal axis of the bow.

Plumage in the described second embodiment is made T-shaped in the form of vertical and horizontal plumage. The latter has two consoles rigidly connected to the aft beam, and the vertical tail is pivotally connected to the aft beam with the possibility of rotation towards one of the horizontal plumage consoles in a state for transportation and storage and with the possibility of fixing in a position corresponding to the flight state.

The pivotally mounted wing consoles and horizontal plumage consoles can be fixed in a position corresponding to the flight state, in particular, using position fixers made in the form of plate spring locks.

The articulated joints of one of the wing consoles with the nose of the fuselage and the nose of the fuselage with the aft (aft beam) provide the ability to transform the aircraft into a state for transportation and storage by folding the wing consoles until one of the upper surfaces fits one another and rotates the aft beam relative to the nose of the fuselage. This, in turn, ensures minimization of the transverse and longitudinal dimensions of the aircraft in a state for transportation and storage. At the same time, factors complicating the design of the apparatus during telescopic execution of the wing consoles, inherent in the closest known technical solution, are eliminated. Moreover, due to the described mutual arrangement

the nose of the fuselage and the aft beam (the first over the second at the point of their connection with the mount) and the point of intersection of the axes of rotation of the three-degree hinge, it is possible to move the aft of the fuselage (aft beam) forward by turning it. This also helps to reduce the size of the small aircraft in the state of transportation and storage.

The communication between the nose of the fuselage and the aft beam using a connection unit containing a retainer along with a three-degree hinge, located in this way, provides the rigidity of the connection of these two parts of the fuselage in the flight state, combined with the simplicity of the structural design and ease of maintenance of the aircraft during its transformation from one state to another.

With the described execution of the T-shaped tail unit of a small unmanned aerial vehicle according to the second embodiment with hinged mounting of the vertical tail unit, it is possible to turn the vertical tail unit towards one of the horizontal tail units, which allows it to be pressed to this console when the aircraft is transferred from the flight state to the state for transportation storage. In combination with the presence of a three-degree hinge in the structure of the aforementioned attachment node, this allows further rotations of the aerodynamic surfaces of the tail unit together with the aft beam to be adjusted in such a way as to minimize the size of the aircraft in a direction parallel to its vertical building axis. The aerodynamic surfaces of the tail unit do not go beyond the dimensions determined by the total height of the nose of the fuselage with the aft beam and the thickness of the folded wing consoles. The scope of the horizontal tail units not stackable with each other in this second embodiment exceeds the size of the aerodynamic surfaces of the tail feathers folded together in the first embodiment. However it is not

leads to an increase in the overall dimensions of the aircraft in a state for transportation and storage, since the specified span does not go beyond the space between the folded wing consoles and the rotated aft beam.

The possibility of fixing the articulated wing console and vertical tail in a position corresponding to the flight state of a small unmanned aerial vehicle provides the necessary rigidity of the aircraft structure in this state.

The use of plate spring locks, as one of the various possible particular cases of the execution of fastening means in the required position of the articulated wing console and vertical tail, ensures the unification of elements and simplicity of design in combination with ease of maintenance. At the same time, such locks successfully fulfill the fixation function assigned to them and provide structural rigidity for a small unmanned aerial vehicle in flight condition.

All actions to transform the proposed small-sized unmanned aerial vehicle according to the second embodiment from the flight state to the state for transportation and storage and vice versa come down to unlocking or fixing the connections of the bow and stern of the fuselage, one wing console and the vertical aerodynamic surface of the tail unit and several simple turns, which simplifies the use of the device and its maintenance.

In accordance with the third option, the proposed small unmanned aerial vehicle, like the one closest to it known by the patent [12], has a fuselage with a tail unit and a folding wing containing two consoles. The fuselage contains the bow and stern parts and is configured to change their relative position. The wing consoles are mounted on the nose of the fuselage.

To achieve the specified technical result in the proposed small unmanned aerial vehicle according to the third embodiment, in contrast to the closest known to it, the first wing console is mounted rigidly, and the second is pivotally with the possibility of fixing it in a position corresponding to the flight state of the small aircraft, and with the possibility turning towards the first console in the condition of a small aircraft for transportation and storage.

The aft part of the fuselage is made in the form of a stern beam connected to the bow by a connection unit containing a three-degree hinge and a latch. The three-stage hinge is shifted forward relative to the rear end of the nose of the fuselage, and the latch is shifted back relative to the front end of the aft beam.

Moreover, the lower edge of the nose of the fuselage is located above the upper edge of the aft beam and the point of intersection of the three axes of rotation of the three-degree hinge is located on the extension of the longitudinal axis of the aft beam, and the latch is made with the possibility of fixing the aft beam in the flight state of a small unmanned aerial vehicle with its longitudinal axis oriented in parallel continuation of the longitudinal axis of the bow.

The tail unit in the described third embodiment is made V-shaped and has two aerodynamic surfaces. The first of them is rigidly connected to the aft beam, and the second is pivotally connected to the first in its lower part or to the aft beam with the possibility of rotation in the direction of the first or in the direction opposite to it, in a condition for transportation and storage and with the possibility of fixing in a position corresponding to flight condition.

Securing the articulated wing console and the aerodynamic surface of the tail in a position corresponding to the flight

state, can be carried out, in particular, using position locks made in the form of plate spring locks.

The articulated joints of one of the wing consoles with the nose of the fuselage and the nose of the fuselage with the aft (aft beam) provide the ability to transform the aircraft into a state for transportation and storage by folding the wing consoles until one of the upper surfaces fits one another and rotates the aft beam relative to the nose of the fuselage. This, in turn, ensures minimization of the transverse and longitudinal dimensions of the aircraft in a state for transportation and storage. At the same time, factors complicating the design of the apparatus during telescopic execution of the wing consoles, inherent in the closest known technical solution, are eliminated. At the same time, due to the described mutual arrangement of the nose of the fuselage and the aft beam (the first above the second at the point of their connection with the mount) and the point of intersection of the rotation axes of the three-degree hinge, it is possible to move the aft of the fuselage (aft beam) forward by turning it. This also helps to reduce the size of the small aircraft in the state of transportation and storage.

The communication between the nose of the fuselage and the aft beam using a connection unit containing a retainer along with a three-degree hinge, located in this way, provides the rigidity of the connection of these two parts of the fuselage in the flight state, combined with the simplicity of the structural design and ease of maintenance of the aircraft during its transformation from one state to another.

With the described implementation of the V-shaped tail of a small unmanned aerial vehicle according to the third embodiment with a hinged installation of one of its aerodynamic surfaces (in both

alternative cases) it is possible to rotate this surface in the direction of another to approach it or in the opposite direction to move away from it.

In the first case, the aerodynamic surfaces of the tail can be folded one on top of the other, and the tail has a configuration similar to the configurations in the first embodiment. In combination with the presence of a three-stage hinge in the structure of the aforementioned attachment node, this allows further rotations of these surfaces folded together with the aft beam in such a way as to minimize the size of the aircraft in a direction parallel to its vertical construction axis. The aerodynamic surfaces of the tail unit, folded together, do not go beyond the dimensions determined by the total height of the nose of the fuselage with the stern beam and the thickness of the folded wing consoles.

In the second case, as a result of rotation of the pivotally mounted aerodynamic surface relative to the stationary one, these surfaces can be divorced to the maximum angle, as a result of which the overall dimension of the aerodynamic surfaces of the tail unit in the direction orthogonal to them will be minimal. In this case, the tail unit acquires a configuration similar to the configuration in the second embodiment. The aerodynamic surfaces of the tail unit do not go beyond the dimensions determined by the total height of the nose of the fuselage with the aft beam and the thickness of the folded wing consoles. The span of the aerodynamic surfaces of the tail unit in this case exceeds the size of the aerodynamic surfaces folded together in the previous case or in the second embodiment. However, this does not lead to an increase in the overall dimensions of the aircraft in a state for transportation and storage, since the specified span does not go beyond the space between the folded wing consoles and the turned aft beam.

The possibility of fixing the articulated wing console and the aerodynamic surface of the V-tail in a position corresponding to the flight state of a small unmanned aerial vehicle provides the necessary rigidity of the aircraft structure in this state.

The use of plate spring locks, as one of the various possible particular cases of the execution of fastening means for the pivotally mounted wing consoles and one of the aerodynamic surfaces of the tail unit, provides unification of elements and simplicity of design in combination with ease of maintenance. At the same time, such locks successfully fulfill the fixation function assigned to them and provide structural rigidity for a small unmanned aerial vehicle in flight condition.

All actions for transforming the proposed small-sized unmanned aerial vehicle according to the third embodiment from the flight state to the state for transportation and storage and vice versa are reduced to unlocking or fixing the connections of the bow and stern of the fuselage, one wing console and one aerodynamic surface of the tail unit and several simple turns, which simplifies the operation of the apparatus and its maintenance.

The proposed utility model is illustrated by drawings, which show:

- Fig.1-3 is a General view of the proposed small unmanned aerial vehicle in flight condition, respectively, with a T-tail at the top of the horizontal tail, with a T-tail at the bottom of the horizontal and with a V-tail plumage;

- figure 4 - connection of the wing consoles with the fuselage and with each other;

- figure 5 is an external view of the junction of the bow of the fuselage and the aft beam;

- figure 6 is a possible design of a three-stage hinge and retainer for connecting the bow of the fuselage with the aft beam;

- Fig.7 - T-shaped tail with the upper horizontal tail in positions corresponding to the flight state and the state for transportation and storage;

- on Fig - T-shaped tail with a lower location of the horizontal tail in positions corresponding to the flight state and the state for transportation and storage, with the articulation of the console of the horizontal tail with vertical tail;

- figure 9 is a T-shaped tail with a lower location of the horizontal tail in positions corresponding to the flight state and the state for transportation and storage, with the articulation of the horizontal tail feathers directly with the aft beam;

- figure 10 is a T-shaped tail with a lower location of the horizontal tail in the positions corresponding to the flight state and the state for transportation and storage, with a rigid connection of the console of the horizontal tail with the aft beam and articulated with it vertical tail;

- in Fig.11 and Fig.12 - V-tail in the articulation of one of its aerodynamic surfaces with another in positions corresponding to the flight state and the state for transportation and storage after turning this surface with its approach to the other and away from last;

- in Fig.13 and Fig.14 - V-tail in the hinged connection of one of its aerodynamic surfaces with the aft beam in positions corresponding to the flight state and the state for transportation and storage after turning this surface with its approach to another and with removal from the latter;

- Fig.15 is a General view of the proposed small unmanned aerial vehicle in an intermediate state in the process of converting it from a flight state to a state for transportation and storage;

- Fig.16-21 - small unmanned aerial vehicle in a state for transportation and storage in various special cases.

Small aircraft (Fig.1-3) contains:

- the fuselage 1, which, in turn, contains the bow 2 and the aft beam 3;

- wing 4 having two consoles 5 and 6;

- tail unit 7;

- node 8 connecting the bow of the fuselage with the aft beam.

Shown in figure 1-figure 3 cases of small-sized unmanned aerial vehicle in flight, possible within the framework of the above three options, differ in tail design - respectively, with a T-tail at the top of the horizontal console, with T- with a tail in the lower arrangement of the horizontal plumage consoles and with a V-tail. The scale of Fig.1-Fig.3 does not allow to show in detail the differences in the attachment of the aerodynamic surfaces of the tail in each of these cases, and they illustrate only the main features of the tail design used in the proposed small unmanned aerial vehicle. Therefore, in

particular. Figure 2 and Figure 3 at the same time correspond to different options or alternatives within the same option. Not reflected in figure 1-figure 3 features are illustrated by other drawings.

Figure 1 corresponds to the first alternative to the implementation of a small unmanned aerial vehicle according to the first embodiment, when the horizontal plumage consoles are mounted pivotally with fastening to the vertical plumage in its upper part.

Figure 2 corresponds to the second and third alternatives for the implementation of a small unmanned aerial vehicle according to the first embodiment, when the vertical tail is rigidly connected to the aft beam, and the horizontal tail console is pivotally mounted to the vertical tail in its lower part or pivotally mounted directly to the aft beam. This figure also corresponds to the implementation of a small unmanned aerial vehicle according to the second embodiment, in which the horizontal tail plinths are mounted rigidly on the aft beam, and the vertical tail is articulated.

Figure 3 corresponds to both alternatives for the implementation of a small unmanned aerial vehicle according to the third embodiment, in which the tail is V-shaped and one of its aerodynamic surfaces is mounted rigidly on the aft beam, and the other is articulated on the first or pivotally on the aft beam.

The main element of the glider of the proposed small unmanned aerial vehicle is the fuselage 1. It is designed to accommodate elements of the control system, navigation and payload, as well as the power supply system and other basic functional systems. Structurally, the nose of the fuselage 2 and the aft beam 3 can be a shell with a load-bearing sheathing.

The nose part 2 of the fuselage has a power connection with one of the wing consoles 4 and a hinged connection with the other.

Figure 4 shows a front view of the nose 2 of the fuselage with wing consoles 5 and 6 mounted on it. The right (in the direction of flight) console 6 is fixed on the nose of the fuselage 2 rigidly and occupies the same position, depicted by a solid line, in the flight state of the aircraft and in the state for transportation and storage. The left console 5 is installed by means of a hinge 11 and occupies a position also shown by a solid line in the flight state of the aircraft. In this position, the console 5 is fixed using a plate spring lock 12. The hinge 11 in the case shown in the drawing is structurally connected to the console 6, fixedly mounted on the nose 2 of the fuselage. It can also be connected directly with the nose of the fuselage. In both cases, the movable console 5 is connected with the nose of the fuselage 2 with the possibility of rotation of this console around the axis of the hinge 11, which is stationary relative to the nose of the fuselage.

The plate elements and the engagement elements 9 of the plate spring lock 12 are mounted on the movable console 5, and the counterpart 10 of the spring lock on the bow 2 of the fuselage. Part 10 of the castle, mounted on the nose of the fuselage, contains a plate lever 13, when pressed, the lock opens.

When translating the aircraft into a state for transportation and storage, the console 5 is rotated in the direction shown by the arrow towards the stationary console 6 up to the abutment to it. The pivot axis of the hinge 11 is oriented so that when the movable console 5 is rotated until the upper sides of both consoles touch, the edges of one console are opposite the corresponding edges of the other console.

The nose part 2 of the fuselage and the aft beam 3 are interconnected by the connection unit 8 (see Figure 1-Figure 3). Connection node, appearance

which is shown in FIG. 5, contains a three-stage hinge 15 and a latch 16. The positions of the three-stage hinge and a latch are spaced along the length of the aircraft: the three-stage hinge 15 is shifted forward relative to the rear end of the nose 2 of the fuselage, and the latch 16 is shifted back relative to the front end of the aft beam 3 This helps to increase the bond strength and rigidity of the apparatus in flight. In more detail, one of the possible implementations of the connection node in this particular case is shown in Fig.6.

The nose part 2 of the fuselage and the aft beam 3 are interconnected by the connection unit 8 (see Figure 1-Figure 3). The connection node, the appearance of which is shown in Figure 5, contains a three-stage hinge 15 and a latch 16. The positions of the three-stage hinge and a latch are spaced along the length of the aircraft: the three-stage hinge 15 is shifted forward relative to the rear end of the nose part 2 of the fuselage, and the latch 16 is shifted back relative to the front end of the aft beam 3. This helps to increase the strength of the connection and the rigidity of the apparatus in flight. In more detail, one of the possible implementations of the connection node in this particular case is shown in Fig.6.

The three-stage hinge 15, when shown in FIG. 6, is an eye 15.1 with a sleeve 15.2 expanded in it and a spherical bearing 15.3. The hinge 15 is connected to the aft beam 3 through an eye 15.1 fixed to it and to the nose of the fuselage 2 through a support 15.8, on which the base 15.9 of the spherical bearing 15.3 is mounted. At the same time, the intersection point 15.7 of the three rotation axes of this hinge, located on the extension of the longitudinal axis 17 of the aft beam 3 shown in FIG. 6, is located, like the axis 17 itself, below the longitudinal axis 18 of the nose of the fuselage 2, and the lower edge 19 of the nose of the fuselage located above the upper edge 20 of the aft beam. This provides the necessary freedom.

turns of the aft beam relative to the nose of the fuselage. The intersection point 15.7 of the axes of the three-degree hinge 15 is shifted forward relative to the rear end of the nose of the fuselage 2. Due to this, after folding the fuselage by turning the aft beam at an angle of about 90 ° around the axis of rotation of the hinge 15.4, passing through the support 15.8, the aft beam does not go beyond the size determined by the length of the nose 2 of the fuselage.

The latch 16, shown in Fig.6, is made in the form of a pipe 16.1, which on the one hand is connected through the power element 16.2 to the rear end of the nose part 2 of the fuselage by means of lock nuts 16.3, 16.4, and on the other hand, through the locking screw 16.5 - with the aft beam 3. Given the fact that the position of the point of intersection of the axes of the three-degree hinge 15 is constant, the presence of the latch 16 in the assembly 8 provides a rigid connection of the bow of the fuselage 2 and the stern beam 3 in the flight state of the aircraft.

To unlock the two parts of the fuselage, it is enough to disconnect the nozzle 16.1 and the locking screw 16.5. After that, the relative orientation of the bow of the fuselage 2 and the aft beam 3 can be set to any within the limits determined by the specific design of the three-stage hinge 15.

In the following figures 7-14, the solid lines show the position of the aerodynamic surfaces of the tail in the flight position of a small unmanned aerial vehicle, and the dashed lines indicate the position in the state for transportation and storage.

The tail unit 7 can be made in the form of a T-tail unit (Figs. 7-10), comprising a vertical tail unit 23 and a horizontal tail unit with two consoles 27, 28, or in the form of a V-shape tail unit (FIG. 11, 13) with two aerodynamic surfaces 29, 30.

In the T-shaped tail assembly, the vertical tail 23 is made in the form of a vertical aerodynamic surface.

In the cases shown in Fig.7-9, the rigid attachment of the aerodynamic surface of the vertical tail 23 to the aft beam 3 can be carried out, for example, by means of typical moment nodes.

Consoles 27, 28 of the horizontal tail are aerodynamic bearing surfaces similar to wing consoles 4 but having steering surfaces necessary for aerodynamic balancing of the aircraft in pitch and roll.

In the cases shown in Fig. 7 and Fig. 8, the horizontal plumage consoles 27, 28 are mounted on the vertical plumage 23 using hinges 31, 32 with rotation axes, the orientation of which allows the cantilevers to rotate until they fit to the aerodynamic surface of the vertical plumage 23. The cases shown in Fig. 7 and Fig. 8 differ from each other in what part of the vertical plumage the horizontal plumage consoles are connected: in Fig. 7 - from the top, in Fig. 8 - from the bottom. Above, with a brief description of the figures of the drawings, these two cases were characterized, respectively, as the upper and lower horizontal plumage.

Fig.7 corresponds to the first, and Fig.8 is a second alternative to the first embodiment of the proposed small unmanned aerial vehicle.

In Fig. 9, as in Fig. 8, the lower position of the horizontal tail is shown. However, the consoles 27, 28 are connected through hinges 31, 32 not with the vertical tail, but directly with the aft beam 3.

This figure corresponds to the third alternative of the first embodiment of the proposed small unmanned aerial vehicle.

To fix the horizontal plumage consoles in a position corresponding to the flight state, their fixation means are used, made in the cases shown in Figs. 7 and 9 in the form of plate spring locks 36.

To translate the aircraft into a state for transportation and storage in the cases illustrated by figures 7-9, rotate the consoles 27, 28 in the direction shown by the arrows in the direction of the vertical tail. As can be seen from Fig.7-Fig.9, in the cases shown in these figures, the rotation was carried out to the closest approach of the consoles 27, 28 (practically - until reaching fit) to the aerodynamic surface of the vertical tail 23.

Figure 10, as in the previous two, also shows the bottom location of the horizontal tail. However, unlike the previous figures, the horizontal plumage consoles 27, 28 are rigidly mounted on the aft beam 3, and the vertical tail 23 is mounted on the aft beam using swivel 33. The orientation of the axis of rotation of the latter allows the aerodynamic surface of the vertical plumage to be tilted towards one of the consoles horizontal plumage (in this case, in the direction shown by the arrow, in the direction of the console 28) until reaching the closest approximation to it. As already indicated above, this figure shows both positions of the vertical tail. As can be seen from Figure 10, in the case shown on it, the rotation was carried out almost until the fit of the aerodynamic surface of the vertical tail 23 to the console 28 horizontal tail.

This figure corresponds to the second embodiment of the proposed small unmanned aerial vehicle.

To fix the aerodynamic surface of the vertical tail in a position corresponding to the flight state, the means of its fixation are used, made in the case shown in Fig. 10 in the form of a plate spring lock 37.

In the V-shaped tail assembly shown in FIG. 11 and FIG. 12, one aerodynamic surface (in this case, surface 29) is fixed rigidly to the aft beam, and the other aerodynamic surface (in this case, surface 30) is connected to the first using the hinge 34 and is fixed in the flight position by means of its fixation, made in the case shown in Fig.11 and Fig.12 in the form of a plate spring lock 38.

These two figures correspond to the first of the alternatives of the third embodiment of the proposed small unmanned aerial vehicle related to the articulation of one of the aerodynamic surfaces of the V-tail.

In the V-shaped tail assembly depicted in FIG. 13 and FIG. 14, one aerodynamic surface (in this case, surface 29) is fixed to the stern beam and the other aerodynamic surface (in this case, surface 30) is attached hinge 35 and is fixed in flight position by means of its fixation, made in the case shown in Fig.13 and Fig.14 in the form of a plate spring lock 38.

These two figures correspond to the second of the alternatives of the third embodiment of the proposed small unmanned aerial vehicle related to the articulation of one of the aerodynamic surfaces of the V-tail.

When any tail unit is made from the number shown in FIGS. 11 to 14 for transferring the aircraft from the flight state to the state for transportation and storage, the articulated aerodynamic surface 30 can either be turned towards the rigidly fixed surface 29 to approach it, or on the contrary, it is turned in the opposite direction to move away from it.

In the case illustrated by FIG. 11 and FIG. 13, for turning the aircraft into a state for transportation and storage, the articulated aerodynamic surface 30 is rotated in the direction shown by the arrow toward the rigidly mounted surface 29. As can be seen from FIG. 11 and FIG. .13, in the case shown on them, the rotation was carried out to the closest approach of the aerodynamic surface 30 (practically - until reaching the fit) to the aerodynamic surface 29.

These two figures correspond to the first of the alternatives of the third embodiment of the proposed small unmanned aerial vehicle, related to the direction of possible rotation of the articulated aerodynamic surface of the V-tail.

In the case illustrated by FIG. 12 and FIG. 14, for turning the aircraft into a state for transportation and storage, the articulated aerodynamic surface 30 is rotated in the direction shown by the arrow, away from the rigidly mounted surface 29. As can be seen from FIG. 12 and FIG. 14, in the case shown therein, the rotation is carried out until the greatest distance of the aerodynamic surface 30 from the aerodynamic surface 29 is reached. However, a rotation at a smaller angle may be sufficient, since it is only important, h Oba the mutual reversal airfoils angle formed by them height was less than the total height of the fuselage bow aft girder with thickness and folded wing panels.

These two figures correspond to the second of the alternatives of the third embodiment of the proposed small unmanned aerial vehicle, related to the direction of possible rotation of the articulated aerodynamic surface of the V-tail.

In all cases of the tail unit, the release of the articulated aerodynamic surfaces of the tail unit, fixed in flight using a plate spring

locks 36-38, before moving to a position corresponding to the state for transportation and storage, is carried out in the same way as described above for the articulated wing console.

You can use other than the described, suitable means of fixing the wing console and the aerodynamic surfaces of the tail, as well as for fixing the relative position of the bow of the fuselage and the aft beam, including a variety of known means.

Before transforming the aircraft from the flight state to the state for transportation and storage, the nose of the fuselage and the aft beam are unlocked by disconnecting the nozzle 16.1 of the retainer 16 from the locking screw 16.5, as well as the unlocking of the wing console 4 and the aerodynamic surfaces of the tail unit, which were previously fixed with the corresponding plate spring locks. Then, the pivotally mounted wing console is rotated until it rests on the other console and the aft beam is rotated about 90 ° around the axis of the hinge 15, which occupies a vertical position in flight.

The general view that the aircraft acquires at this stage of transformation is shown in FIG. 15 for a T-tail with a lower arrangement of horizontal tail consoles. A similar view at this stage of transformation has an aircraft with an upper arrangement of horizontal plumage consoles or with a V-shaped tail.

Next, the vertical plumage is brought into a position corresponding to the state for transportation and storage, as described above in the discussion of Fig.7-Fig.14.

Then, the orientation of the aft beam 3 is adjusted together with the tail unit 7 mounted on it, the aerodynamic surfaces of which are folded in the manner described above in order to minimize the dimensions of the aircraft in the direction corresponding to the direction of the longitudinal axis 18 of the nose part 2 of the fuselage, and in the direction orthogonal to the folded consoles 5, 6 wings. To minimize the first of these dimensions, the angle of rotation of the aft beam 3 around the axis of rotation 15.4 of the hinge 15 is adjusted (see Fig. 6; this axis is parallel to the vertical construction axis of the aircraft). To minimize the second of these dimensions, the aft beam 3 is rotated together with the tail unit around the axis of rotation of the hinge 15, which coincides with the longitudinal axis 17 of the aft beam 3 (see Fig. 6). This rotation ensures that the tail unit does not go beyond the size defined by the sum of the diameters of the bow of the fuselage 2 and the aft beam 3 and the thickness of the wing consoles 5, 6. If the consoles 5, 6 in the flight state of the aircraft are completely recessed into the bow 2 and do not protrude beyond it, then the thickness of only one console is included in the mentioned amount. Figure 4 shows partially recessed consoles. The foregoing is illustrated in FIG. 16, in which, as an example, three projections of an apparatus with a V-tail are provided, the aerodynamic surfaces of which are mounted and folded, as shown in FIG. 11 and FIG. 13. On the right projection of Fig.16 shows the position of the aft beam 3, rotated in this way together with the aerodynamic surfaces 29, 30 of the tail unit 7.

From Fig.16 it is seen that two large sizes ("length" and "width") of the apparatus when folded are determined mainly by the length of the aft beam 2 and the nose 2 of the fuselage, and the smaller size ("thickness") is determined mainly , the sum of the diameters of the same parts of the fuselage and the thickness of the wing console. The foregoing also applies to the other cases described above for performing the tail unit and turning its aerodynamic surfaces, other than those shown in FIG. 16. For several such cases on

Fig.17-Fig.21 presents images of the aircraft at the final position of its parts, corresponding to the state for transportation and storage.

From Fig.16-Fig.21 also shows that in the conditions of the aircraft shown in these figures, the position of the aft beam 3 can be further adjusted due to the presence of the third degree of freedom of the three-stage hinge 15. By rotating the aft beam 3 around the axis of rotation of the hinge 15, whose direction in this state is parallel to or close to the longitudinal axis of the bow 2, it is easier to “fit” the rear end of the aft beam 3 together with the tail into the above dimension, determined by the sum of the bow diameters 2 Asti fuselage and aft beams 3 together with a projecting beyond the bow of the total thickness of the folded wing panels.

Fig.17-Fig.19 relate to an aircraft with a T-shaped tail (Fig.17 - at the top, and Fig.18 and Fig.19 - at the bottom of the consoles of horizontal plumage). Fig and Fig relate to an aircraft with a V-shaped tail.

In this case, Figs. 17, 18 and 20 illustrate cases where all three aerodynamic surfaces of the T-tail or both aerodynamic surfaces of the V-tail are compactly folded to fit against each other, and Fig. 19 and Fig. 21 - cases where the vertical aerodynamic surface of the T-shaped plumage is pressed against one of the consoles of the horizontal plumage, and the aerodynamic surfaces of the V-shaped plumage are deployed.

Transformation of the proposed aircraft from a state for transportation and storage in flight state is carried out in the reverse order described.

Achieving the ratio of the dimensions of the aircraft in a state for transportation and storage, corresponding to the above

size, is a technical result common to all three proposed options for its implementation in all the alternative cases described, along with the general principle of transformation and the simplicity and ease of maintenance provided by it.

All actions to transform the proposed small-sized unmanned aerial vehicle into a state for transportation and storage and vice versa, which are reduced to fixing or fixing the wing console and the aerodynamic surfaces of the tail unit and the connection of the bow with the stern beam and several simple turns, can be performed by unskilled personnel , far from aviation and not having mastered its traditions.

The proposed small unmanned aerial vehicle can be equipped with a piston or electric motor with a screw. Such engines can be installed in the nose 2 of the fuselage. The device can be equipped with a rocket or turbojet engine placed in the aft beam. The presence of an engine is not necessary if the small unmanned aerial vehicle is intended for use only in planning mode.

To fix the wing consoles and horizontal tail in a position corresponding to the state for transportation and storage, the proposed aircraft can be additionally equipped with appropriate means. However, such means may not be available, since the packaging in which the apparatus is placed in this state is capable of fulfilling their role.

The proposed small-sized unmanned aerial vehicle, when equipped with appropriate equipment, can be used as a dual-purpose tool for solving surveillance tasks (for example, the state of power lines, situations in the natural or man-made area)

catastrophes), military intelligence, target designation, electronic countermeasures, etc.

Information sources

1. USSR Author's Certificate No. 1821422, publ. 06/15/1993.

2. Patent of the Russian Federation No. 2125524, publ. 01/27/1999.

3. Patent of the Russian Federation No. 2183182, publ. 06/10/2003.

4. Patent of the Russian Federation No. 2228283, publ. 05/10/2004.

5. Patent of the Russian Federation No. 2183333, publ. 04/20/2002.

6. Patent of the Russian Federation No. 2005663, publ. 01/15/1994.

7. Patent of the Russian Federation No. 2321477, publ. 06/27/2004.

8. US Patent No.5,050,817, publ. 09/24/1991.

9. Patent of the Russian Federation No. 2125523, publ. 01/27/1999.

10. Patent of the Russian Federation No. 2026781, publ. 07/30/1994.

11. US Patent No.4,706,907, publ. 11/17/1987.

12. Patent of the Russian Federation No. 2139795, publ. 10/20/1999.

Claims (6)

1. A small unmanned aerial vehicle containing a fuselage with a tail and a folding wing having two consoles, the fuselage contains a bow and aft parts and is configured to change their relative position, wing consoles are mounted on the bow of the fuselage, characterized in that the first wing console mounted rigidly, and the second - pivotally with the possibility of fixing it in a position corresponding to the flight state of a small unmanned aerial vehicle, and with the possibility of turning to the side Well, the first console is in the state of a small unmanned aerial vehicle for transportation and storage, the aft part of the fuselage is made in the form of a stern beam connected to the nose by a connection unit containing a three-degree hinge that is shifted forward relative to the rear end of the nose of the fuselage, and a latch that is shifted back relative to the front end of the aft beam, while the lower edge of the nose of the fuselage is located above the upper edge of the aft beam and the intersection point of the three axes of rotation of the three-step of the hinge is located on the extension of the longitudinal axis of the aft beam, and the latch is made with the possibility of fixing the aft beam in the flight state of a small unmanned aerial vehicle with the orientation of its longitudinal axis parallel to the extension of the longitudinal axis of the bow, the tail unit is made T-shaped in the form of vertical and horizontal tail while the vertical tail is rigidly connected to the aft beam, and the horizontal tail has two consoles pivotally connected with a vertical tail in the upper or lower part, or with the aft beam, with the possibility of rotation in the direction of vertical plumage in a state for transportation and storage and with the possibility of fixing in a position corresponding to the flight state. 2. The aircraft according to claim 1, characterized in that the pivotally mounted wing consoles and horizontal plumage consoles are fixed in a position corresponding to the flight state by position fixers made in the form of plate spring locks. 3. A small unmanned aerial vehicle containing a fuselage with a tail and a folding wing having two consoles, the fuselage contains a bow and aft parts and is configured to change their relative position, wing consoles are mounted on the bow of the fuselage, characterized in that the first wing console mounted rigidly, and the second - pivotally with the possibility of fixing it in a position corresponding to the flight state of a small unmanned aerial vehicle, and with the possibility of turning to the side Well, the first console is in the state of a small unmanned aerial vehicle for transportation and storage, the aft part of the fuselage is made in the form of a stern beam connected to the nose by a connection unit containing a three-degree hinge that is shifted forward relative to the rear end of the nose of the fuselage, and a latch that is shifted back relative to the front end of the aft beam, while the lower edge of the nose of the fuselage is located above the upper edge of the aft beam and the intersection point of the three axes of rotation of the three-step of the hinge is located on the extension of the longitudinal axis of the aft beam, and the latch is made with the possibility of fixing the aft beam in the flight state of a small unmanned aerial vehicle with the orientation of its longitudinal axis parallel to the extension of the longitudinal axis of the bow, the tail unit is made T-shaped in the form of vertical and horizontal tail the latter has two consoles rigidly connected to the aft beam, and the vertical tail is pivotally connected to the aft beam with the possibility of turning in side one of the consoles of horizontal plumage in a condition for transportation and storage and with the possibility of fixing in a position corresponding to the flight state. 4. Aircraft according to claim 3, characterized in that the pivotally mounted wing consoles and the vertical tail are secured in a position corresponding to the flight state by position fixers made in the form of plate spring locks. 5. A small unmanned aerial vehicle containing a tail fuselage and a folding wing having two consoles, the fuselage contains a bow and aft parts and is configured to change their relative position, wing consoles are mounted on the nose of the fuselage, characterized in that the first wing console mounted rigidly, and the second - pivotally with the possibility of fixing it in a position corresponding to the flight state of a small aircraft, and with the possibility of rotation in the direction of the first con salt in the state of a small aircraft for transportation and storage, the aft fuselage is made in the form of a stern beam connected to the bow by a connection unit containing a three-degree hinge that is shifted forward relative to the rear end of the nose of the fuselage, and a latch that is shifted back relative to the front end of the aft beam, while the lower edge of the nose of the fuselage is located above the upper edge of the aft beam and the intersection point of the three axes of rotation of the three-degree hinge is on continuation of the longitudinal axis of the aft beam, and the latch is made with the possibility of fixing the aft beam in the flight state of a small unmanned aerial vehicle with the orientation of its longitudinal axis parallel to the extension of the longitudinal axis of the bow, the tail unit is V-shaped and has two aerodynamic surfaces, the first of which is rigidly connected with the aft beam, and the second is pivotally connected to the first in its lower part or to the aft beam with the possibility of rotation towards the first or side, positive to it, in a condition for transportation and storage and with the possibility of fixing in a position corresponding to the flight state. 6. Aircraft according to claim 5, characterized in that the pivotally mounted wing consoles and the aerodynamic surface of the tail unit are fixed in a position corresponding to the flight state by position fixers made in the form of plate spring locks.