RU2784091C1 - Light aircraft wing folding mechanism and wing folding method - Google Patents

Abstract

FIELD: aircraft industry.

SUBSTANCE: inventions group relates to aircraft industry, namely to aircraft having a folding wing, and can be used in the design of light aircraft that must be stored in a confined space and moved on the ground. A wing folding mechanism is proposed, including a fixed wing section, a movable section - a wing console, several shear pins connecting the fixed and movable wing sections, a device for folding the wing, made with the possibility of extending the wing console from the fixed wing section in the direction of the tail section of the aircraft along the horizontal axis , parallel to the roll axis, turning the wing console relative to the horizontal axis, parallel to the pitch axis, and folding the wing console by turning about the vertical axis, parallel to the yaw axis, with the wing console located along the fuselage of the aircraft. The proposed method for folding the wing includes: extension of the movable wing section from the fixed wing section in the direction of the tail section of the aircraft along a horizontal axis parallel to the roll axis; rotation of the movable wing section about a horizontal axis parallel to the pitch axis; turning the movable wing section about a vertical axis, parallel to the yaw axis, towards the tail section of the aircraft and installing the movable wing section along the fuselage.

EFFECT: ensuring the safety of the wing folding process while increasing the reliability of the wing folding mechanism.

2 cl, 17 dwg

Description

SUBSTANCE: group of inventions relates to aircraft industry, namely to aircraft having a folding wing, and can be used in the design of light aircraft that must be stored in a confined space and moved on the ground.

The main task of the group of inventions is to create a flying vehicle (aircraft) with a folding wing, which reduces the transverse size of the aircraft when transporting it on public roads and the area occupied when storing the aircraft, in order to ensure transport mobility when using it.

It also provides for the possibility of transporting an aircraft with a folded wing on the ground by ground vehicles or independently due to the thrust of the propeller.

State of the art

Known aircraft, the design of which makes it possible to fold the wing panels along the longitudinal axis of the aircraft (US No. 2674422, https://www.uspto.gov). The aircraft contains a fuselage with a cabin and a tail boom, vertical and horizontal tails mounted on the beam, a three-wheeled landing gear with a nose wheel and main support, an engine with a pusher propeller installed behind the cabin, a center section with wing panels hinged to it with locks that fix the consoles in flight configuration. When folding, the wing consoles turn up - back relative to the center section and are installed along the fuselage with the toe up. When folded, the ends of the consoles rest on special units mounted on the horizontal tail. To ensure the stability and maneuverability of the vehicle when driving on the road, compensation is provided for the shift of the center of gravity back by turning the main landing gear around the axis of its attachment. The aircraft can move on the ground with a folded wing due to the thrust of the propeller, while the wing panels cover the rotating propeller, ensuring safety for surrounding people and vehicles.

The disadvantages of this design are:

- the complexity of ensuring the strength and rigidity of the connection of the consoles with the center section, associated with the location of this node on the main spar with a small spacing of the elements of the lugs of the swivel, limited by the thickness of the wing profile;

- turning the consoles up - back for a high-lying wing makes it difficult to carry out this operation manually by one person;

- the choice of the horizontal tail as a support for the folded wing panels causes additional loads acting on the design of the horizontal tail when the aircraft moves along the ground;

- in addition, rotation of the main landing gear around the axis of its fastening is impossible without applying significant efforts to lift the aircraft fuselage and carry out this operation manually by one person.

Known "Device for folding the wing" (RU No. 2727896, http://www1.fips.ru/), containing: a fixed and a rotary part of the wing, a hinge assembly connecting the wing consoles with the fixed part of the wing (center section). At the same time, the hinge assembly ensures the rotation of the wing console to the folded position, in which the plane of the chords of the wing console is vertical, and the end of the console is directed towards the tail of the aircraft.

The disadvantage of this wing folding device is the complexity of the design of the hinge assembly, which leads to a significant increase in the mass of the aircraft and an increase in the complexity of its manufacture.

The closest to the claimed device is the “Manual mechanism for folding the wing” (RU 2674387, http://www1.fips.ru), including: a device for folding the wing, connecting the fixed section of the wing with the rotary section, made with the possibility of extending the rotary section of the wing from the center section and the rotation of the rotary section around the transverse axis of the aircraft, as well as the rotation of this section around a vertical axis perpendicular to the transverse axis, with the location of the rotary section along the longitudinal axis of the aircraft perpendicular to the fixed section; elements of fastening of wing consoles.

The disadvantage of this wing folding mechanism is that when the wing console is extended from the center section, the only element connecting the outer section of the wing with the inner one is an extension tube, which must be made sufficiently massive to ensure the strength of the structure, and hold it in this position to rotate relative to the transverse, and then the vertical axes, which requires great physical effort, and can also lead to breakage of the wing if the wing folding operation is carried out carelessly

Known "Method of transforming a vehicle for ground and air transportation" (RU 2758223, http://www1.fips.ru), including the following steps:

- minimization of the surface area of the wings by turning the rear of the wings with flaps relative to the transverse axis of the vehicle;

- rotation of the folded wings relative to the longitudinal axis of the vehicle upwards;

- rotation of the folded wings from a vertical position back along the longitudinal axis of the vehicle;

- retraction of the tail unit forward to reduce the length of the vehicle.

The disadvantages of this method are: the complexity of the design, as well as the impossibility of carrying out the operations of folding the wing by one user without the use of mechanization.

The closest to the claimed method is the “Manual mechanism for folding the wing” (RU 2674387, http://www1.fips.ru), which provides an algorithm for converting the folding wing from the flight position to the transport position and vice versa, including:

- release of the locking elements holding the movable section of the wing in connection with the fixed section;

- extension of the movable wing section along the transverse axis of the aircraft, keeping it in the area of the wing tip;

- rotation of the movable wing section relative to the transverse axis of the aircraft with the toe of the wing down;

- rotation of the movable wing section relative to the vertical axis of the aircraft in the hinge of the extension tube, placement of the movable wing section parallel to the longitudinal axis of the aircraft;

- moving the movable wing section forward parallel to the longitudinal axis of the aircraft until the extension tube enters the fixed wing section;

- fastening the end of the movable section of the wing to the horizontal tail of the aircraft.

The return of the aircraft wing to the flight position is carried out in the reverse order.

This method of folding the wing of an aircraft has the same disadvantages that were cited when criticizing the design of the wing folding mechanism according to this patent.

The technical problem to be solved by this invention is to ensure the possibility of folding the aircraft wing by one person, increasing the reliability of the wing folding mechanism, and reducing the likelihood of wing breakage during its folding.

Disclosure of the essence of the invention

The technical result achieved by using the proposed device is to ensure the safety of the wing folding process while increasing the reliability of the wing folding mechanism.

The technical result of the proposed method is the expansion of the arsenal of technical means.

The essence of the technical solution of the proposed wing folding mechanism is that:

- wing folding mechanism, including a fixed wing section, a movable section (console) of the wing, several shear pins connecting the fixed and movable sections of the wing, a device for folding the wing, made with the possibility of extending the wing console from the fixed wing section in the direction of the tail of the aircraft along the axis , parallel to the roll axis, turning the wing console relative to the horizontal axis, parallel to the pitch axis and folding the wing console by turning about the vertical axis, parallel to the yaw axis, with the wing console located along the aircraft fuselage;

- the device for folding the wing is made in the form of an extension device installed in bearings fixed on the front and rear side members of the wing console, and equipped with a hinge;

- the extension device is movably connected to the guide bracket fixed on the side member of the fixed section of the wing, with the possibility of moving from the fixed section in the direction of the tail of the aircraft along an axis parallel to the axis of the roll of the aircraft and turning in the hinge relative to the horizontal axis parallel to the pitch axis;

- the root rib of the wing console is equipped with a fixed guide rail mounted on it, interacting with the supporting rail fixed on the power rib of the fixed wing section.

Applied in the design of the wing folding mechanism, the original combination of connecting the wing console and the fixed wing section with the help of an extension device fixed to the wing console, movably installed in the guide bracket, fixed on the spar of the fixed wing section, supporting rail, fixed on the power rib of the fixed wing section, interacting with guide rail fixed on the root rib of the wing console, as well as shear pins mounted on the spar of the fixed section of the wing, the root rib and the rear spar of the wing console, included in the grooves made in the spar and power rib of the fixed section of the wing, allows you to transfer the aerodynamic load from wing consoles to the center section in the flight position, as well as to increase the reliability of the wing folding mechanism.

Brief description of the drawings

The essence of the invention is illustrated by the following description and the accompanying illustrations, which show:

fig. 1 - isometric view from the front - from above the aircraft, equipped with a wing folding mechanism, in the flight position;

fig. 2 is an isometric view of the front - top of an aircraft equipped with a wing folding mechanism with the wing console extended;

fig. 3 is a side view of an aircraft equipped with a wing folding mechanism when the movable part of the wing is rotated about a transverse axis parallel to the pitch axis;

fig. 4 - isometric front - top of the aircraft, equipped with a mechanism for folding the wing in the folded position of the wing console;

fig. 5 is a rear isometric view from above of the wing folding mechanism in the extended position;

fig. 6 - cross section of the wing folding mechanism at the point of contact

supporting and guide rails;

fig. 7 is a rear isometric view of a fragment of the extension device;

fig. 8 is a rear isometric view of the fixed part of the wing;

fig. 9 - a fragment of the power rib of the center section;

fig. 10 is a rear isometric view of a fragment of the wing console;

fig. 11 - fragment of the root rib of the wing console;

fig. 12 - fastening of the extension device in the spars of the wing console;

fig. 13 is a side view of the wing folding mechanism in the rotated position of the wing console relative to the transverse axis;

fig. 14 - block diagram of the algorithm for folding the wing console;

fig. 15 - block diagram of the algorithm for unfolding and installing the wing console in the flight position;

fig. 16 is a diagram of the action of the moment of force from the mass of the wing in the proposed device for folding the wing;

fig. 17 is a diagram of the action of the moment of force from the mass of the wing in the prototype.

Where:

1 - fixed part of the wing;

2 - moving part (console) of the wing;

3- spar of the fixed section of the wing;

4 - front spar of the wing console;

5 - rear spar of the wing console;

6 - power rib;

7 - root rib;

8 - extension device;

9 - hinge of the extension device;

10 - front bearing;

11 - rear bearing;

12 - guide bracket;

13 - supporting rail;

14 - guide rail;

15- power front pin;

16 - groove for the power front pin;

17 - rear power pin;

18 - locking pin;

19 - groove for the rear power pin;

20 - groove for the locking pin;

21 - clamp of the extension device;

22 - rotary handle;

23 - groove for the clamp of the extension device;

M is the center of mass of the wing console;

G _k - weight of the wing console;

L _g - shoulder action of the weight of the wing;

M _gk - the moment of forces from the action of the weight of the wing console.

In FIG. Figures 1-4 show isometric views of an aircraft equipped with a wing-fold mechanism at various stages of the operation of the wing-fold mechanism. from flying to fully folded.

In the flight position, the fixed section 1 of the wing and the console 2 of the wing form a single structure (Fig. 1). The spar 3 of the fixed section of the wing and the spar of the front 4 of the wing console overlap each other and are interconnected by means of a power front pin 15 (Fig. 5), a groove 16 in the front spar of the wing console (Fig. 10), as well as an extension device 8 installed movably in the guide bracket 12, fixed in the spar of the fixed section of the wing (Fig. 8). In addition, the connection of the fixed section of the wing with the wing console in the flight position is carried out using the locking pin 18, which is included in the groove 20 in the power rib of the fixed wing section, and the power rear pin 17 (Fig. 11), fixed on the root rib of the wing console, included into the groove 19, made in the power rib of the fixed section of the wing (Fig. 9).

In the extended position of the wing console (Fig. 2, Fig. 5), the connection of the wing console with the center section is carried out due to the extension device 8, the extension of which from the guide bracket 12 is limited by the latch 21 (Fig. 12) located at the end of the extension device 8, which is included in groove 23 (Fig. 7, Fig. 8), made in the guide bracket 12. In this case, the load from the mass of the wing console is transmitted through the latch 21 of the extension device 18 and the guide bracket 12 to the fixed section of the wing.

In the position of the wing console rotated relative to the transverse axis (Fig. 3, Fig. 13), the load from the mass of the wing console is transmitted through the extension device 8 and the guide bracket 12 to the fixed section of the wing 1.

In FIG. 4 shows the position of the wing folding mechanism when the wing console 2 is rotated about a vertical axis parallel to the yaw axis of the aircraft.

In this position, the load from the mass of the wing console is perceived by the extension device 8 and the horizontal tail of the aircraft, on which a fixation lock (not shown) of the wing console in the folded position is installed.

Implementation of the invention.

The technical result of the claimed invention is achieved due to the fact that the folding wing mechanism contains:

- fixed section 1 of the wing associated with the center section and the spar 3 of the fixed part of the wing;

- movable section 2 (console) of the wing, including the front spar 4, made with the possibility of connection with the spar 3 of the fixed part of the wing; several shear pins connecting the fixed and movable sections of the wing;

- a device for folding the wing, made in the form of an extension device 8, which allows to extend the movable wing section from the fixed section in the direction of the tail of the aircraft along the horizontal axis parallel to the roll axis, rotate the movable wing section relative to the horizontal axis parallel to the pitch axis, rotate the movable wing section relative to the vertical axis parallel to the yaw, and the installation of the movable wing section in a plane parallel to the roll axis, along the fuselage of the aircraft.

At the same time, the extension device, with one end, is installed in the guide bracket 12, fixed on the side member of the fixed part of the wing, and with the other - in the bearings installed in the front 4 and rear 5 spars of the movable wing section. The wing console is equipped with a guide rail 12, fixedly fixed on the root rib 7 of the wing console, and interacting with the supporting rail 14, fixed on the power rib 6 of the fixed wing section.

At least two shear pins 15 and 17 connecting the fixed and movable wing sections are located along an axis parallel to the roll axis, one of which 15 is fixed on the spar 3 of the fixed wing section and enters the groove 16 made in the front spar 4 of the movable section wing, and the second 17 is fixed on the root rib 7 of the console, and with its end enters the groove 19, made in the power rib 6 of the fixed section of the wing. At the same time, another shear pin 18, connecting the fixed and movable sections of the wing, is located along an axis parallel to the pitch axis and is connected to the handle 22, fixed on the rear spar of the movable section of the wing, and with its end enters the groove 20, made in the power rib of the fixed wing sections.

The claimed technical solution works as follows. In the flight position (Fig. 1) the console 2 of the wing is connected to the fixed section 1 of the wing with a power front pin 15 (Fig. 5) entering the groove 16 (Fig. 10) in the front spar of the wing console, as well as an extension device 8 installed movably in guide bracket 12 fixed in the spar of the fixed section of the wing (Fig. 7, Fig. 8). In addition, the connection of the fixed wing section with the wing console in the flight position is carried out due to the locking pin 18, which is included in the groove 20, made in the power rib of the fixed wing section, and the power rear pin 17 (Fig. 11), fixed on the root rib of the wing console included in the groove 19, made in the power rib of the center section (Fig. 9). In this case, all loads from the wing console are transferred to the center section through the shear pin 15, shear pins 17 and 18 and the extension device 8, fixed in the guide bracket 12, installed in the spar of the fixed section of the wing.

After the flight and landing at the airfield, the wing consoles are folded, the algorithm of which is shown in Fig. 14. To do this, the center section and wing consoles are undocked by removing the shear pin 18 from the groove 20 made in the power rib of the fixed wing section. Next, the wing console is pulled out from the fixed section of the wing in the direction of the tail of the aircraft until the lock 21 of the extension device 8 contacts the blind end of the groove 23 in the guide bracket 12. In this case, the root rib of the wing console slides on the guide rail 13 along the supporting rail 14, fixed on the power rib of the center section, and the front spar 4 of the wing console is displaced from the pin of the power front 15. In addition, when the wing console moves back, the pin, the power rear 17 comes out of contact with the groove 19, separating the root rib of the wing console and the power rib of the center section.

At the next stage, the movable wing section is rotated relative to a horizontal axis parallel to the pitch axis, using the hinge 9 of the extension device 8. When the wing console is rotated, the guide rail 13 comes out of contact with the supporting rail 14 and the wing console is held in a vertical position by means of the extension device 8 (Fig. 12). In this case, the moment of forces M _Gk from the weight G _k of the wing console, applied at the center of mass M, acting on the shoulder L _G of the wing console relative to the fulcrum of the extension device 8 in the fixed section of the wing (Fig.16) is much less than in the variant (Fig. 17) extension of the wing console proposed in the prototype (RU 2674387), which suggests a higher reliability of the proposed version of the wing folding mechanism.

Next, the wing console is rotated relative to the vertical axis parallel to the yaw axis in the rearward direction and installed along the fuselage, as well as fastened to the vertical tail.

This operation is performed sequentially from one and the other side of the aircraft.

The unfolding of the movable part of the wing occurs in the reverse order (Fig. 15).

This technical solution can be used as a personal vehicle for business and sports purposes, as well as for patrol and search tasks by the Ministry of Emergency Situations and other structures.

Claims (19)

1. The mechanism for folding the wing of a light aircraft, including: - fixed section of the wing connected with the center section and the spar of the fixed part of the wing; - movable section - the wing console, including the front spar, made with the possibility of connection with the spar of the fixed wing section; - several shear pins, made with the possibility of connecting the fixed and movable sections of the wing; - several grooves made respectively in the fixed and movable sections of the wing, which include the corresponding shear pins; - a device for folding the wing, made in the form of an extension device, with the possibility of extending the movable wing section from the fixed wing section, turning the movable wing section about a horizontal axis parallel to the pitch axis, turning the movable wing section about a vertical axis parallel to the yaw axis, and installing a movable wing section wing sections along the fuselage, characterized in that - a device for folding the wing, made in the form of an extension device, ensures the extension of the movable section - the wing console from the fixed section of the wing in the direction of the tail of the aircraft along a horizontal axis parallel to the axis of the roll of the aircraft; - a device for folding the wing, made in the form of an extension device, with one end installed in a guide bracket fixed on the side member of the fixed part of the wing, and with the other end in bearings installed in the front and rear side members of the movable section of the wing; - the movable section - the wing console is equipped with a guide rail fixedly connected to the root rib of the movable section - the wing console, interacting with the supporting rail fixed on the power rib of the fixed wing section; - at least two shear pins connecting the fixed and movable wing sections are located along the roll axis, while one is fixed on the spar of the fixed wing section and enters the groove made in the front spar of the movable wing section, and the second is fixed on the root rib of the console and its end enters the groove made in the power rib of the fixed section of the wing; - at least one more shear pin connecting the fixed and movable sections of the wing is located along the pitch axis and connected to the handle fixed on the rear spar of the movable section of the wing, and with its end enters the groove made in the power rib of the fixed section of the wing. 2. The method of folding the wing of a light aircraft, including: - release of the shear pin connecting the fixed wing section with the movable wing section by turning the handle for fixing the movable wing section; - extension of the movable section of the wing from the fixed section until the fixation of the extension device connecting the fixed and movable sections of the wing; - rotation of the movable section of the wing about a horizontal axis parallel to the pitch axis; - rotation of the movable wing section relative to the vertical axis, parallel to the yaw axis, in the backward direction and installation of the movable wing section along the fuselage; - fastening and fixing the end of the movable section of the wing on the tail section of the aircraft; characterized in that the extension of the movable wing section from the fixed section is carried out in the direction of the tail section of the aircraft along a horizontal axis parallel to the roll axis.

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