CN106669180B - Flap aligning device of fixed-wing aircraft - Google Patents

Abstract

The invention relates to a double-folding wing device for a fixed-wing aircraft, which comprises a fuselage and a left wing and a right wing connected to both sides of the fuselage by symmetrical flipping. Both the left wing and the right wing include wing bodies connected to the roots of the wing bodies The positioning block set parallel to the plane of the wing body, the spar that runs through the inside of the wing body and exceeds the root of the wing body, the fuselage includes an upper fuselage and a lower fuselage, and the rear edges of the upper fuselage and the lower fuselage are connected by a rotating piece Together they form a <-shape that is easy to open and close. Both the upper fuselage and the lower fuselage are equipped with spar connectors that are convenient for the spars to be locked and locked together, and positioning slots that are convenient for the positioning blocks to be stuck. The spar connections There are grooves on the surface of the device and the fuselage to facilitate the clamping of the spar. The beneficial effect of the invention is that the clamped spar connector can realize the continuity of the whole aircraft spar and ensure the structural strength. The half-folding device has a simple structure and quick action, which can effectively reduce the transportation and carrying volume of the whole machine, and is convenient for the cable arrangement between the fuselage and the wing body.

Description

A device for folding wings of a fixed-wing aircraft

technical field

The invention relates to a wing-folding device for a fixed-wing aircraft.

Background technique

In the existing fixed-wing model airplanes, in order to facilitate transportation and carrying, the fuselage and wings are mostly connected detachably, and the disassembly process is cumbersome. The wing body is usually equipped with electronic equipment such as steering gear and wireless transceivers. Repeated disassembly and assembly will easily lead to poor contact between the wing body and the fuselage socket, which will affect flight safety and the service life of the whole machine.

Contents of the invention

The technical problem to be solved by the present invention is: based on the above problems, the present invention provides a wing-folding device for a fixed-wing aircraft.

A technical scheme adopted by the present invention to solve its technical problems is: a fixed-wing aircraft folding wing device, including a fuselage and a left wing and a right wing connected to both sides of the fuselage by symmetrical flipping, a left wing and a right wing. Each wing includes a wing body, a positioning block connected to the root of the wing body parallel to the plane of the wing body, a spar that runs through the inside of the wing body and exceeds the root of the wing body, and the fuselage includes an upper fuselage and a lower fuselage, the upper fuselage and the lower fuselage. The rear edge of the lower fuselage is connected together by rotating parts to form a <-shape that is easy to open and close. Both the upper fuselage and the lower fuselage are equipped with spar connectors that facilitate the spar clamping and mutual locking and facilitate positioning. There are positioning slots for block clamping, and the spar connector and the surface of the fuselage are provided with grooves for spar clamping.

Further, the left wing and the right wing are flipped and connected to both sides of the upper or lower fuselage through hinges, one side of the hinge is fixed to the bottom surface of the wing body root, and the other side is fixed to the surface of the upper or lower fuselage.

Further, the positioning slot is close to the rear edge of the fuselage, the rear edge of the fuselage is located inside the positioning slot, and the spar connector is located outside the positioning slot.

Further, the spar connectors on the upper fuselage and the lower fuselage are connected by a locking piece, the locking piece has an I-shaped sheet-like solid structure, and the spar connector is provided with a thread that runs through the upper fuselage and the lower fuselage. The through hole of the body, the locking piece passes through the through hole and rotates to lock the spar connectors.

The beneficial effect of the invention is that the clamped spar connector can realize the continuity of the whole aircraft spar and ensure the structural strength. The half-folding device has a simple structure and quick action, which can effectively reduce the transportation and carrying volume of the whole machine, and is convenient for the cable arrangement between the fuselage and the wing body.

Description of drawings

The present invention will be further described below in conjunction with the accompanying drawings.

Fig. 1 is a structural representation of the present invention;

Fig. 2 is the structural representation of left wing/right wing;

Fig. 3 is the assembly diagram of upper fuselage/lower fuselage;

Fig. 4 is the assembly schematic diagram of spar and spar connector;

Among them: 1. left wing, 2. right wing, 3. wing body, 4. hinge, 5. spar, 6. positioning block, 7. upper fuselage, 8. lower fuselage, 9. spar connection Device, 10. positioning groove, 11. locking piece.

Detailed ways

The present invention will now be further described in conjunction with specific examples, and the following examples are intended to illustrate the present invention rather than further limit the present invention.

A kind of folding wing device of fixed-wing aircraft as shown in Figure 1-4, comprises fuselage and the left wing 1 and the right wing 2 that are connected to both sides of the fuselage by symmetrical flipping, the left wing 1 and the right wing 2 are both Comprising the wing body 3, the positioning block 6 connected to the root of the wing body 3 parallel to the plane of the wing body 3, the spar 5 that runs through the inside of the wing body 3 and exceeds the root of the wing body 3, the fuselage includes an upper fuselage 7 and a lower body. Fuselage 8, the trailing edge of upper fuselage 7 and lower fuselage 8 are connected together by rotating parts and form the < type that is convenient to open and close. The spar connectors 9 and the positioning slots 10 for locking the positioning block 6 are locked together, and the spar connector 9 and the surface of the fuselage are provided with grooves for the spar 5 to be stuck.

The left wing 1 and the right wing 2 are connected to both sides of the upper fuselage 7 or the lower fuselage 8 through the hinge 4. One side of the hinge 4 is fixed on the bottom surface of the wing body 3 roots, and the other side is fixed on the upper fuselage 7 or the lower fuselage. Body 8 surface.

The positioning slot 10 is close to the rear edge of the fuselage, and the spar connector 9 is located outside the positioning slot 10 . This arrangement makes the locking of the spar connector more secure.

The spar connector 9 on the upper fuselage 7 and the lower fuselage 8 is connected by a locking member 11, the locking member 11 is in an I-shaped sheet structure, and the spar connector 9 is provided with a thread that runs through the upper fuselage 7. and the through hole of the lower fuselage 8, the locking member 11 passes through the through hole and rotates to lock the spar connectors 9.

During the action, the wings are first flattened, and then the fuselage is closed. At this time, the positioning block falls into the positioning groove and is pressed by the fuselage. The spar is fastened and connected by the spar connector, and the locking piece passes through the spar connector. Through holes, and rotate to lock the spar connectors, and the whole machine unfolding action is completed. The left and right spars fall into the grooves of the spar connectors, and the left and right spar connectors connect the left and right spars. The ends of the spars fill the entire groove, which can ensure the continuity of the structure; the positioning blocks fall into the positioning grooves of the fuselage , the position of the wing relative to the fuselage can be further limited to prevent the wing from loosening.

When transporting, the wing is bent upwards to the top of the fuselage, the fuselage is closed, the spar connector is fastened, and it is packed in a transport box for easy transportation.

The clamped spar connector can realize the continuity of the whole aircraft spar and ensure the structural strength. The folding device has a simple structure and quick action, which can effectively reduce the transport volume of the whole machine and facilitate wiring.

The spar connector is embedded in the inner surface of the fuselage, or integrally formed with the fuselage. The spar is cylindrical or square column-shaped, and the corresponding groove is semi-cylindrical or semi-square column-shaped. The rotating parts of the upper fuselage and the rear edge of the lower fuselage are hinges.

Inspired by the above-mentioned ideal embodiment according to the present invention, through the above-mentioned description content, relevant workers can make various changes and modifications within the scope of not departing from the technical idea of the present invention. The technical scope of the present invention is not limited to the content in the specification, but must be determined according to the scope of the claims.

Claims (2)

1. a flap aligning device of a fixed-wing aircraft is characterized in that: comprises a fuselage, a left wing (1) and a right wing (2) which are symmetrically connected with the two sides of the fuselage in a turnover way, wherein the left wing (1) and the right wing (2) both comprise wing bodies (3) and positioning blocks (6) which are connected with the root parts of the wing bodies (3) and are arranged in parallel with the plane of the wing bodies (3), the wing beam connector (9) which is convenient for the wing beam (5) to be clamped and locked together and the positioning groove (10) which is convenient for the positioning block (6) to be clamped are arranged on the upper machine body (7) and the lower machine body (8), and the wing beam connector (9) and the surface of the machine body are provided with grooves which are convenient for the wing beam (5) to be clamped;

The left wing (1) and the right wing (2) are connected to two sides of the upper fuselage (7) or the lower fuselage (8) in a turnover mode through hinges (4), one side of each hinge (4) is fixed to the bottom surface of the root of the wing body (3), and the other side of each hinge (4) is fixed to the surface of the upper fuselage (7) or the lower fuselage (8);

the positioning groove (10) is close to the rear edge of the machine body, the rear edge of the machine body is located on the inner side of the positioning groove (10), and the wing beam connector (9) is located on the outer side of the positioning groove (10).

2. The fixed-wing aircraft antipodal flap device according to claim 1, wherein: go up fuselage (7) and connect through retaining member (11) between wing spar connector (9) on lower fuselage (8), retaining member (11) are I shape slice solid construction, set up the through-hole that runs through last fuselage (7) and lower fuselage (8) on wing spar connector (9), retaining member (11) pass the through-hole and rotatory locking between wing spar connector (9).