RU2321523C1 - Small-sized unmanned flying vehicle - Google Patents

Abstract

FIELD: aeronautical engineering; unmanned flying vehicles.

SUBSTANCE: proposed small-sized unmanned flying vehicle has fuselage and aerodynamic surfaces including folding wing mounted on fuselage and horizontal and vertical tails connected with it for turning and locking in required position. Wing has two outer panels; each panel has parting surface in root section and is made in form of root and tip sections which are interconnected for folding their surfaces to each other by means of attachment unit fitted with retainer of mutual position of root and tip sections and feathering hinge. Root section of outer wing panel is connected with fuselage for folding it together with tip section connected to it downward and turning it backward for folding along fuselage for stowed position of flying vehicle. Root section of outer wing panel is connected with fuselage by means of attachment unit fitted with retainer for locking the root section of outer wing panel in required position and one-axis hinge. Horizontal tail is made in form of two outer wing panels; each panel is connected with vertical tail for folding along vertical tail by means of its attachment unit which is fitted with retainer for locking the outer panel of horizontal tail in required position and feathering hinge.

EFFECT: reduction of overall dimensions of flying vehicle in folded position.

6 cl, 17 dwg

Description

The invention relates to the field of small aircraft, and more particularly to 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.

In US patent No. 5050817 (publ. 24.09.1991, [8]) a similar [6] solution is described, 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, it is planned to place the tail unit 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.

The patent of the Russian Federation No. 2139795 (publ. 10/20/1999, [11]) describes an aircraft 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, it is provided to rotate the two-keel tail of the fuselage together with the tail around the horizontal transverse axis so that it rests on top of the front.

In this design, as well as in the technical solution according to the patent [10], there is also an additional possibility of reducing the longitudinal dimension of the aircraft in the transport state and during storage. However, this possibility is limited by the framework of the two-keel scheme, since in the case of a single-keel or non-keel scheme with a V-shaped plumage, the placement of the rear part proposed in [11] after its rotation over the front of the fuselage is difficult. In addition, as in the decision on the patent [10], the dimensions due to the size of the tail unit remain unchanged.

Also known small-sized aircraft according to US patent No. 4706907 (publ. 11/17/1987, [12]). 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.

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.

Its disadvantages are due to the technical complexity of creating telescopically folding wing consoles. The transformation process requires a large number of manipulations. In addition, when implementing this technical solution in relation to an aircraft in an unmanned version having small transverse fuselage dimensions, a transformation scheme involving folding the wing consoles down even leads to an increase in the corresponding overall dimensions in the transport state compared to the flight state.

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 .

The proposed small unmanned aerial vehicle, like the one closest known to it, has a fuselage and aerodynamic surfaces. The latter include a folding wing mounted on the fuselage and connected with it with the possibility of its rotation and fixing the position, horizontal tail and vertical tail, rigidly connected with the fuselage.

To achieve the specified technical result in the proposed small unmanned aerial vehicle, unlike the closest known to it, the wing has two consoles, each of which has a connector surface in the root part and is made in the form of root and end sections. The latter are interconnected with the possibility of folding their surfaces to each other. The specified connection of the end and root sections of the wing console is made by means of a mounting unit provided with a latch for the relative position of these sections and an axial hinge. The root section of the wing console is connected to the fuselage with the possibility of folding it together with the end section attached to it and then turning back to fold along the fuselage when the small unmanned aerial vehicle is put into a state for transportation and storage. The specified connection of the root section of the wing console with the fuselage is made by means of a mounting unit provided with a position lock for the root section of the wing console and a two-stage hinge. The first axis of this hinge is perpendicular to the vertical plane of symmetry of the small unmanned aerial vehicle and is located below the wing in its position corresponding to the flight state of the small unmanned aerial vehicle. The second axis of the two-stage hinge is located near the connector surface of the corresponding wing console. The horizontal tail is made in the form of two consoles. Each of them is connected with a vertical tail with the possibility of folding along the vertical tail by means of its mounting unit, which is equipped with a position lock of the horizontal tail and an axial hinge.

The connection of the root sections of the wing consoles with the fuselage by means of these attachment points equipped with two-stage hinges makes it possible to transform the aircraft into a state for transportation and storage by folding down the consoles and then placing them along the fuselage on its sides. This, in turn, ensures minimization of the vertical, transverse and horizontal dimensions of the aircraft in a state for transportation and storage, since these dimensions are determined almost exclusively by the geometric dimensions of the wing console. At the same time, factors complicating the design of the apparatus during telescopic execution of consoles, inherent in the closest known technical solution, are eliminated.

Due to the location of the first (oriented perpendicular to the vertical plane of symmetry of the small unmanned aerial vehicle) axis of rotation of the two-stage hinge below the wing in its position corresponding to the flight state of the small unmanned aerial vehicle, i.e. below the second axis of the hinge, the wing root section is advanced forward when it is folded along the fuselage. This helps to reduce the size of the small-sized aircraft in the transport state, since in the flight state the wing should be at a considerable distance from the nose of the fuselage, taking into account the balancing requirements and the general mass-inertial properties of the aircraft.

The execution of each of the wing consoles from two sections with the possibility of folding them with their surfaces to each other and the presence of their connection node equipped with a hinge help to ensure that the ends of the consoles, which, after folding and placement on the sides of the fuselage, do not protrude beyond the longitudinal dimension of the fuselage along with the tail. The fulfillment of this condition is achieved by combining this feature with the location of the first axis of rotation of the two-stage hinge below its second axis of rotation.

The fact that all the mentioned attachment points of the wing console sections and horizontal tail consoles are equipped with consoles position locks provides the required structural rigidity of the small unmanned aerial vehicle.

Preferably, this embodiment of the proposed small unmanned aerial vehicle, in which the axis of these two-degree hinges, perpendicular to the vertical plane of symmetry of the small unmanned aerial vehicle, are aligned with each other.

In the particular case of the proposed small unmanned aerial vehicle, the connection of each horizontal tail unit with vertical tail is made with the possibility of folding the horizontal tail unit down. In this case, the mounting unit of the horizontal tail assembly is located at the end of the vertical tail.

In another particular case, the connection of each console of the horizontal tail with a vertical tail is made with the possibility of folding the horizontal tail feathers up. In this case, the attachment unit of the horizontal tail assembly is located at the root of the vertical tail.

The latches of the sections of the wing consoles and horizontal tail consoles can be made in the form of plate spring locks.

The combination of the axes of the two-stage hinges perpendicular to the vertical plane of symmetry of the aircraft with each other simplifies their design and the construction of a small unmanned aerial vehicle as a whole.

In both of these particular cases, the connection of the horizontal plumage consoles with vertical plumage is completed, these consoles are combined with vertical plumage during the transformation of the aircraft. Due to this, they are located almost in the same plane with the wing consoles folded on the sides of the fuselage, which reduces the overall transverse dimension of the aircraft in a state for transportation and storage. Moreover, this result is achieved regardless of where the attachment points of the horizontal tail units are installed: at the end or at the root of the vertical tail.

The implementation of the position fixers of the wing consoles and horizontal tail units in the form of leaf spring locks provides structural rigidity for a small unmanned aerial vehicle in combination with simplicity of design and ease of maintenance.

All actions to transform the proposed small-sized unmanned aerial vehicle into a state for transportation and storage and vice versa come down to unlocking or fixing the connections of sections of the wing consoles and horizontal plumage consoles and a few simple turns, which simplifies operation.

The invention is illustrated by drawings, which show:

- figure 1 is a schematic representation of a General view of the proposed small unmanned aerial vehicle in flight condition, side view;

- figure 2 is the same, a top view;

- figure 3 is the same, front view;

- figure 4 - connection of the root and end sections of the wing console in flight condition;

- figure 5 - connection of the root section of the wing console with the fuselage;

- figure 6 - connection of the horizontal tail with the upper part of the vertical tail;

- Fig.7 - connection of the horizontal tail with the fuselage;

- on Fig - the preferred implementation of a two-stage hinge;

- figure 9 is a section of the wing console in the folded position corresponding to the state for transportation and storage of the aircraft;

- figure 10 - the position of the wing consoles after the implementation of the rotations of their end sections and the rotation of the root sections around the second axis of the two-stage hinge;

- figure 11 is the position of the wing consoles after the rotation around the first axis of the two-stage hinge;

- Fig.12 - horizontal plumage in the folded position with the location of the attachment points of the horizontal plumage consoles at the end of the vertical plumage;

- Fig.13 - horizontal plumage in the folded position when the location of the attachment points of the horizontal plumage consoles at the root of the vertical plumage;

- on Fig - the final position of the wing consoles and tail unit after making turns to enter the state for transportation and storage;

- Fig.15 is a schematic representation of a General view of the proposed aircraft in position for transportation and storage, side view;

- in Fig.16 is the same, a top view;

- Fig.17 is the same front view.

Small-sized aircraft (Fig.1-3) contains:

- fuselage 1, which, in turn, consists of bow 2 and aft 3 parts;

- wing, console 6 of which consists of end 7 and root 8 sections;

- horizontal tail unit 10;

- vertical tail unit 12;

- engine 14 with screw 15.

The fuselage 1 (figure 1), consisting of bow 2 and aft 3 parts, is the main element of the airframe, designed to accommodate elements of the control system, navigation and payload, as well as the power supply system and other main functional systems. The fuselage has a power connection with the consoles 6 of the wing (figure 2, 3) and the tail unit, which includes a horizontal tail unit with consoles 10 (figure 2, 3) and a vertical tail unit 12 (figure 1).

The fuselage is made according to the structural power scheme, similar to the "beam". The nose part 2 of the fuselage is made of left 2.1 and right 2.2 (figure 2, 3) of the half-arches, bonded with an adhesive joint. The left half-arch 2.1 on the flight has a cutout for a removable cover 4 (Fig. 1), which is intended for mounting the main parts of the functional systems of the aircraft. The nose part 2 of the fuselage is bonded to the aft part 3 by means of an adhesive joint. The aft part 3 of the fuselage is made of a thin-walled conical shell formed from a composite bag based on arimide-carbon fabric and epoxy.

Consoles 6 of the wing (figure 2, 3) consist of end 7 and root 8 sections. The end 7 and root 8 sections of each console are connected to each other (Figs. 2, 4) using a fastener with a hinge 5 having an axis of rotation oriented along the horizontal construction of the aircraft. The attachment unit connecting the sections of the wing consoles also contains clamps 18 of the relative positions of the sections in the form of plate spring locks.

The root section 8 of each wing console is connected to the nose of the fuselage 2 using the mount, containing a two-stage hinge 11 (Fig.1, 5). The two-stage hinge 11 has a first (transverse) 17 and a second (longitudinal) 16 axis of rotation perpendicular to it. The first (transverse) axis 17 is perpendicular to the vertical plane of symmetry of the small unmanned aerial vehicle and is located below the wing console 6 in its position corresponding to the flight state of the small unmanned aerial vehicle (Fig. 1). The second axis 16 of the two-stage hinge 11 is located near the connector surface of the corresponding wing console and, in the case shown in FIG. 1, is oriented along the construction horizontal of a small unmanned aerial vehicle. As can be seen from figure 1, the first of these axes (axis 17) of the two-stage hinge 11 is located below its second axis 16.

In the position shown in FIG. 2, corresponding to the flight state, the right and left flight sections of the wing sections 8 of the wing consoles are fastened to each other by means of latches 9 of the relative positions of the root sections in the form of plate spring locks.

A wing may have a structural-power circuit similar to a "coffer wing", i.e. with supporting skin. The skin can be formed from a composite bag based on arimide-carbon fabric and epoxy. The casing is supported by a filler of foam polystyrene. The wing has no bodies for aerodynamic balancing of the aircraft in flight.

The vertical tail unit 12 is made in the form of a vertical aerodynamic surface with a rudder 21 necessary to control the aircraft in heading and roll. The vertical tail is attached to the aft 3 of the fuselage by means of standard torque assemblies. The steering surface can be made of fabric of technical arimide frame processing and supported by a package of honeycomb core with a hexagonal lattice width of 3.5 mm.

The horizontal tail consists of two consoles 10 (FIG. 2) and represents a bearing aerodynamic surface similar to a wing, but having steering surfaces 19 necessary for aerodynamic balancing of the aircraft in pitch and roll.

The horizontal plumage consoles 10 are mounted on the vertical plumage 12 (Fig.6) or on the aft part of the fuselage (Fig.7) using attachment points containing hinges 23 with an axis of rotation oriented along the horizontal plane of the aircraft. Mentioned mounting nodes may contain position locks of the horizontal plumage consoles, made in the form of plate spring locks (not shown in the drawings), similar to locks 9, 18, fixing the position of the sections of the wing consoles.

The steering surfaces can be made of fabric of technical arimide frame processing and supported by a package of honeycomb core with a hexagonal lattice width of 3.5 mm.

The proposed small unmanned aerial vehicle can be equipped with an electric motor 14 with a screw 15.

The presence of an engine and a propeller is not necessary if a small unmanned aerial vehicle is intended for use only in planning mode.

The preferred structural embodiment of the two-stage hinges connecting the root sections of the wing consoles with the fuselage, in which the first (transverse) axis of rotation of these hinges is common to both of them, is illustrated in Fig. 8. This design contains a base 25, longitudinal hinges 27 with axles 16 oriented parallel to the horizontal of the aircraft, and a transverse hinge 26 with axis 17 perpendicular to the axles 16 and located horizontally. The base 25 is designed for mounting on the nose 2 of the fuselage. The position of the bases 25 shown in FIG. 8 corresponds to the location of the nose portion 2 of the fuselage “on its side”, i.e. as in figure 5. Therefore, the horizontal axis 17 of the transverse hinge in both of these figures appears to be located vertically. The transverse hinge 26 with the axis 17 penetrates the nose 2 of the fuselage (see figures 1, 5). Longitudinal hinges have platforms 28 designed for attaching to them the root parts 8 of the wing consoles (see figure 5).

In the described preferred embodiment, the connection of the root sections of the wing consoles with each other is provided by means of plate spring locks 18 (Fig. 2), plate elements 24 and engagement elements 22 of which are fixed on racks 20 mounted on platforms 28 of longitudinal hinges 27. Assembled, the root section of one from the wing consoles is fixed between the upper pads 28 in FIG. 8 and the spring elements 24 of the spring locks, and the root section of the other wing console is between the lower pads 28 in FIG. 8 and the gear elements 22 innyh locks. In this case, the struts 20 penetrate the root part of the wing console.

The connection of the consoles of the horizontal tail unit with the fuselage or tail unit and their fixation in the position corresponding to the flight state can be performed similarly to that described above.

Hinges 23 for connecting the root and end sections of the wing consoles and means for fixing them in a position corresponding to the flight state can be performed similarly to the upper part of the structure shown in Fig. 8, disconnected from the elements 26, 17 related to the transverse hinge. This part with bases 25 is attached to the end of the root section of the wing console remote from the fuselage, and with platforms 28 with plate elements 24 of spring locks, to the end section. In this case, the root section should also have elements similar to the elements 22 of the engagement of the spring locks.

It is possible to use other, different from the described, suitable means for connecting the sections of the wing consoles with each other and the fuselage and the horizontal tail units with the fuselage, as well as means for fixing them in the desired position, including various known means.

The proposed small unmanned aerial vehicle operates and is used as follows.

In the working (flight) state, the wing is in a steady horizontal position and sections of its consoles are fixed with plate spring locks 9, 18 (Fig. 2). Consoles 10 of the horizontal tail are fixed by attachment points with hinges 23 (FIGS. 2, 6, 7) with a longitudinal axis of rotation and corresponding clamps (not shown in the drawings).

To translate into a position corresponding to the state for transportation and storage, the end sections 7 of the wing consoles are released from communication with the root sections 8, provided by means of plate spring locks 18 (2, 4), and deployed relative to the longitudinal axis of the hinges 5 and root sections 8 wing consoles in the position shown in Fig.9.

Then, the root sections 8 of the wing consoles are released from the power connections provided by the plate spring locks of the fastening 9 (Fig. 2), and are deployed relative to the longitudinal axis 16 (Figs. 1, 5) of the two-stage hinge 11 to the position shown in Fig. 10. Then they are deployed around the transverse axis 17 of this hinge (Fig.1, 5) to the position shown in Fig.11.

In the process of this turn, the root section of the wing, mounted on the axis 16, is advanced forward, since the transverse axis 27 is located below each of the longitudinal axes 16. The foregoing is easier to understand using FIG. 1, if we imagine that the console 6 is facing the viewer after lowering it down as a result of rotation around axis 16 is further rotated together with this axis and other elements of the hinge 11 counterclockwise 90 ° around axis 17.

In the case of FIG. 10, the folding of the end sections of the wing consoles occurs so that the end section 7 is pressed with its lower side to the lower side of the root section 8. This further minimizes the lateral overall dimension of the aircraft when folded, as folded Thus, the end sections occupy a position behind the nose part 2 of the fuselage above its tail part 3. For this, as can be seen from Figs. 1, 6, the axis 16 of each longitudinal hinge 27 (named above the second two-axis Foam pivot) located at the top, and the transverse axis two-stage hinge 17 (the aforesaid first pivot axis two-stage) - approximately the middle height of the nose portion of the fuselage 2, wherein said height is greater than the width of a root portion 8 console 6 wing.

The horizontal plumage consoles 10 are released from power connections with each other and, as a result of rotation around the longitudinal horizontal axis of the hinges 23 (Figs. 1, 6, 7), occupy the position shown in Fig. 12 (when executed in accordance with Fig. 6, i.e. at the location of the attachment points of the consoles 10 at the end of the vertical tail unit 12), or to the position shown in Fig. 13 (in the case corresponding to FIG.

The final position of all consoles after the transfer of the aircraft to the state for transportation and storage is shown in Fig. 14.

On Fig, 16, 17 shows respectively a side view of the aircraft from the side, top and front in this state.

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, they may be absent, since their role is able to fulfill the packaging in which the apparatus is placed in this state.

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

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 area of natural or man-made disasters), reconnaissance, target designation, electronic countermeasures, etc.

Claims (7)

1. A small unmanned aerial vehicle containing the fuselage and aerodynamic surfaces, including a folding wing mounted on the fuselage and connected with it with the possibility of rotation and fixation, horizontal tail and vertical tail, rigidly connected with the fuselage, characterized in that the wing has two consoles, each of which in the root part has a connector surface and is made in the form of root and end sections, the latter are interconnected with the possibility of folding to their surfaces and to each other, this connection is made by means of a mounting unit provided with a fixer of the relative position of the root and end sections of the wing and an axial hinge, while the root section of the wing console is connected to the fuselage with the possibility of folding it together with the end section attached to it and then turning back for folding along the fuselage when translating a small unmanned aerial vehicle into a state for transportation and storage, the specified connection of the root section of the wing console with the fuselage it is made by means of a mounting unit equipped with a position lock for the root section of the wing console and a two-stage hinge, the first axis of this hinge is perpendicular to the vertical plane of symmetry of the small unmanned aerial vehicle and is located below the wing in its position corresponding to the flight state of the small unmanned aerial vehicle, and the second axis of the two-stage hinge located near the connector surface of the corresponding wing console, horizontal tail is made in the form of two x consoles, each of them is connected with the vertical empennage, with folding along the vertical tail via its attachment site, which is provided with a clamp position console horizontal tail and the axial joint. 2. The aircraft according to claim 1, characterized in that the axes of these two-stage hinges, perpendicular to the vertical plane of symmetry of a small unmanned aerial vehicle, are aligned with each other. 3. The aircraft according to claim 1 or 2, characterized in that the position locks of the sections of the wing consoles and horizontal tail units are made in the form of plate spring locks. 4. The aircraft according to claim 1 or 2, characterized in that the said connection of each console of the horizontal tail unit with vertical tail is made with the possibility of folding the horizontal tail panel and the mounting unit of the horizontal tail unit is located at the end of the vertical tail unit. 5. The aircraft according to claim 4, characterized in that the position locks of the sections of the wing consoles and horizontal tail units are made in the form of plate spring locks. 6. The aircraft according to claim 1 or 2, characterized in that the said connection of each horizontal tail unit with vertical tail is made with the possibility of folding the horizontal tail unit up and the mounting unit of the horizontal tail unit is located at the root of the vertical tail unit. 7. The aircraft according to claim 6, characterized in that the position locks of the sections of the wing consoles and horizontal tail consoles are made in the form of plate spring locks.

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