Rotary folding wing of aircraft and aircraft

Abstract

The invention provides a rotary folding wing of an aircraft and the aircraft. The rotary folding wing comprises two symmetrical side wings, a connector (2), a driving mechanism and a limiting mechanism, a driving mechanism of the side wings is arranged on the connector (2), and the driving mechanism drives the side wings to open through a rocker arm structure; the connector (2) is provided with a groove cavity along the symmetry axis of the two rocker arms. A slotted hole is formed in the driving mechanism; a driving mechanism and a limiting mechanism of the side wings are arranged on the connector, the driving mechanism drives the side wings to open through the rocker arm structure, and the limiting mechanism limits the rotating angle of the rocker arm structure. After the aircraft is launched, the wings can be quickly unfolded and locked, so that the aircraft flies stably.

Description

Technical Field

[0001] The present invention is applicable to the field of aircraft design with folding wings, in particular to a rotating folding wing of an aircraft and an aircraft. Background Art

[0002] Folding wings can reduce the aircraft's lateral dimensions and packaging size, making it easier to store, transport, and launch, greatly increasing its applicability. Aircraft using folding technology have wings that fold before launch and quickly deploy afterward, ensuring stable flight. This has an immeasurable impact on improving the aircraft's maneuverability, combat effectiveness, and wartime survivability.

[0003] The wing folding and deployment mechanism ensures smooth wing folding and unfolding, and its performance directly impacts the speed, stability, and reliability of wing deployment. During wing deployment, the mechanism must both transmit load and meet specified motion requirements. The ability to quickly deploy and lock the wings is crucial to folding wing design and directly impacts the aircraft's ability to fly normally and successfully execute its mission. Summary of the Invention

[0004] The object of the present invention is to provide a rotating folding wing of an aircraft and an aircraft, wherein after the aircraft is launched, the wing can be quickly unfolded and locked so that the aircraft can fly stably.

[0005] A first aspect of the present invention provides a rotating folding wing for an aircraft, comprising: two symmetrical side wings, a connector 2, a driving mechanism, and a limiting mechanism;

[0006] The front ends of the two side wings are hinged to the connector 2 respectively. When the wings are folded, the tail ends of the two side wings are close to each other, and when the wings are opened, the tail ends of the two side wings are far away from each other.

[0007] The front ends of the two side wings are symmetrically connected to the connector 2 through the connecting shaft 3 and the rocker arm structure 4. The rocker arm structure 4 includes a rocker arm and a disc. The center of the disc is fixed to the connecting shaft 3. An oblong groove is opened along the length of the rocker arm.

[0008] The connector 2 is provided with a driving mechanism for the side wings, which drives the side wings to open through a rocker structure;

[0009] The connector 2 is provided with a groove cavity along the symmetric axis of the two rocker arms; the driving mechanism is provided with a slot hole;

[0010] The limiting mechanism includes a limiting hook 16, a torsion spring 17 and a pressure rod 18. The limiting hook 16 is hinged in the groove cavity of the connector through the torsion spring 17. The front end of the limiting hook 16 abuts against the driving mechanism, and the rear end of the limiting hook 16 is hinged to the pressure rod 18.

[0011] When the wings are unfolded to the set angle, the front end of the limit hook 16 slides into the slot of the drive mechanism under the drive of the torsion spring 17, preventing the drive mechanism from retreating and locking the wings in the unfolded position. At this time, the pressure rod 18 protrudes from the surface of the fuselage. By overcoming the torsion spring 17 and pressing the pressure rod 18 to release the lock on the drive mechanism, the unfolded wings can be folded.

[0012] Optionally, the driving mechanism includes a motor 9, a cam 11, a limit plate 12, a compression spring 10 and a pull rod 5;

[0013] The connector 2 is provided with a guide hole along the symmetrical axis of the two rocker arms. A slide groove is provided at the end of the guide hole away from the connecting shaft 3. The slide groove is vertically arranged on the connector 2. A baffle 7 is provided at the end of the guide hole close to the connecting shaft 3.

[0014] The motor 9 is arranged above the guide hole, and the output shaft of the motor 9 is connected to the cam 11; the limit plate 12 is arranged in the slide groove of the connector 2 and contacts the cam 11, and moves up and down as the cam 11 rotates; the limit plate 12 is provided with a through hole;

[0015] The pull rod 5 is located on the symmetrical axis of the two rocker arms and is movably embedded in the guide hole of the connector. One end of the pull rod 5 is connected to the two rocker arms, and the other end of the pull rod 5 rotates with the cam 11 and is restricted by the limit plate 12 in the guide hole of the connector 2 or passes through the limit plate 12.

[0016] A travel groove is provided on the pull rod 5, in which a compression spring 10 is installed, one end of which is against the travel groove and the other end is against the inner side of the baffle 7. Under the push of the compression spring 10, the pull rod 5 passes through the limit plate 12 and drives the side wings to open through the rocker arm structure.

[0017] Optionally, the travel groove and the baffle 7 serve as a limiting mechanism to limit the rotation angle of the rocker arm structure and thus limit the deployment angle of the wing.

[0018] Optionally, the connector 2 body is a plate-like structure, the two side wings are symmetrically hinged to the lower surface of the connector 2 body through the connecting shaft 3, and the rocker arm structure 4 is located on the upper surface of the connector 2 body;

[0019] Two fork ear structures are provided on the upper surface of the connector 2 body, and the disc of the rocker arm structure 4 is located in the fork ears.

[0020] Optionally, an elastic retaining ring 14 is provided at the bottom of the chute;

[0021] One end of the limiting plate 12 located in the chute is sleeved with a spring 13, and an annular limiting step for compressing the spring 13 is provided on the limiting plate 12;

[0022] When the wing is in the folded state, the limit plate 12 moves upward under the action of the spring 13 to block the pull rod 5, preventing the pull rod 5 from passing through the limit plate 12, ensuring that the wing is in the folded state; when the motor 9 is started, it drives the cam 11 to force the limit plate 12 to compress the spring 13 downward and move, and the pull rod 5 is able to pass through the through hole on the limit plate 12. Under the push of the compression spring 10, the pull rod 5 passes through the limit plate 12, and drives the side wings to open through the rocker arm structure.

[0023] Optionally, the baffle 7 is detachably mounted on the guide hole by screws 6 .

[0024] Optionally, the motor 9 is installed above the guide hole through the support 8.

[0025] Optionally, the connector 2 is installed inside the aircraft body 15, and the side wings are installed outside the aircraft body 15.

[0026] A second aspect of the present invention provides an aircraft, which adopts the rotating folding wing as described in any one of the first aspects.

[0027] The advantages of the present invention are that the wing folding and unfolding mechanism is simple, the wings can be quickly unfolded and positioned and locked, and the wings can also be fixed when folding. The entire mechanism has high reliability and good manufacturability and interchangeability. 1) The motor is started by an electrical signal, and the rocker arm is pushed to rotate under the action of the compression spring to realize the rapid unfolding of the aircraft wings, which can provide lift to the aircraft in time and maintain flight stability. 2) Through the combined action of the baffle and the limit hook, the folding wings are locked after being unfolded to the set angle. The structure is simple and reliable, and it reduces the weight of the aircraft while meeting the size reduction requirement of the wing folding. 3) The locking of the wings after folding is achieved by the constraint of the pull rod by the limit plate, which effectively ensures that the state of the aircraft after folding is fixed. 4) The structure of this mechanism is simple, easy to implement, and saves space and weight. It can realize the folding, unfolding and locking functions of the wing surface. It is suitable for small aircraft and solves the technical difficulties of realizing the folding, unfolding and locking functions of the wings under small space and small volume conditions. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] Figure 1 This is a schematic diagram of the wing folded state;

[0029] Figure 2 This is a schematic diagram of the wing deployed;

[0030] Figure 3 This is a schematic diagram of the relationship between the limit plate, limit hook and pull rod in the AA view of the wing folded and locked state;

[0031] Figure 4 This is a diagram of the relationship between the limit plate, limit hook and pull rod in the BB view of the wing deployment and locking state;

[0032] Figure 5This is a schematic diagram of the relationship between the limit plate, cam and pull rod in the C-direction view;

[0033] Number name in the figure:

[0034] 1. Side wing, 2. Connector, 3. Connecting shaft, 4. Rocker arm structure, 5. Pull rod, 6. Screw, 7. Baffle, 8. Support, 9. Motor, 10. Compression spring, 11. Cam, 12. Limit plate, 13. Spring, 14. Elastic retaining ring, 15. Body, 16. Limit hook, 17. Torsion spring, 18. Compression rod. DETAILED DESCRIPTION

[0035] To make the purpose, technical solutions, and advantages of the embodiments of the present invention more clear, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, not all of them. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making any creative work are within the scope of protection of the present invention.

[0036] The features and illustrative embodiments of various aspects of the present invention will be described in detail below. In the detailed description below, many specific details are proposed in order to provide a comprehensive understanding of the present invention. However, it will be apparent to those skilled in the art that the present invention can be implemented without the need for some of these specific details. The following description of the embodiments is merely intended to provide a better understanding of the present invention by illustrating examples of the present invention. The present invention is in no way limited to any specific arrangement and method proposed below, but rather encompasses any improvements, replacements, and modifications to structures, methods, and devices without departing from the spirit of the present invention. In the accompanying drawings and the following description, well-known structures and techniques are not shown to avoid unnecessary ambiguity in the present invention.

[0037] In the description of the present invention, it should be noted that the directions or positional relationships indicated by terms such as "center," "up," "down," "left," "right," "vertical," "horizontal," "inside," and "outside" are based on the directions or positional relationships described in the accompanying drawings and are intended only to facilitate and simplify the description of the present invention and should not be construed as limiting the present invention. Furthermore, the use of ordinal numbers (e.g., "first and second," etc.) is intended to distinguish between objects and is not limited to this order, and should not be construed as indicating or implying relative importance.

[0038] In the description of the present invention, it should be noted that, unless otherwise specified or limited, the terms "mounted," "connected," and "connected" should be understood broadly, and may refer to direct connection or indirect connection through an intermediary. Those skilled in the art will understand the specific meanings of these terms in the present invention.

[0039] It should be noted that, in the absence of conflict, the embodiments of the present invention and the features in the embodiments can be combined with each other, and the embodiments can refer to and quote each other. The present invention will be described in detail below with reference to the accompanying drawings and in combination with the embodiments.

[0040] The present invention will be described in further detail below with reference to the embodiments and drawings, but the embodiments of the present invention are not limited thereto.

[0041] The present invention provides a folding wing of an aircraft and an aircraft. The folding wing comprises two symmetrical side wings and a connector. The front ends of the two side wings are respectively hinged to the connector. When the wings are folded, the tail ends of the two side wings are close to each other, and when the wings are opened, the tail ends of the two side wings are separated from each other. The front ends of the two side wings are symmetrically connected to the connector via a connecting shaft and a rocker arm structure. The rocker arm structure comprises a rocker arm and a disc. The center of the disc is fixed to the connecting shaft. An oblong slide groove is provided on the rocker arm, and the oblong slide groove is parallel to the rocker arm.

[0042] The folding wings of the aircraft, the connector body is a plate-like structure, the two side wings are symmetrically hinged on the lower surface of the connector body through the connecting axis, the rocker arm structure is located in the fork ear of the connector, and the connector is provided with a driving mechanism and a limiting mechanism for the side wings. The driving mechanism drives the side wings to open through the rocker arm structure, and the limiting mechanism limits the rotation angle of the rocker arm structure.

[0043] The folding wings of the aircraft described above have a drive mechanism comprising a motor, a cam, a limit plate, a compression spring, and a pull rod. When the aircraft is launched, the motor is activated at a set time, driving the cam to rotate, causing the limit plate to move up and down within the connector's slideway. The pull rod is located on the symmetrical axis of the two rocker arms and is movably embedded in the connector's guide hole. One end of the pull rod is connected to the rocker arm, while the other end is restrained in the connector's guide hole by the limit plate. The pull rod is provided with a travel groove, in which a compression spring is installed, enabling the pull rod to move forward under the force of the compression spring.

[0044] The folding wings of the aircraft are as follows: when the wings are in the folded state, the limit plate moves upward under the action of the spring to block the front end of the pull rod, preventing the pull rod from moving forward, thereby ensuring that the wings are in the folded state; when the motor is started, it drives the cam to force the limit plate to move downward, and when the pull rod can pass through the through hole on the limit plate, the pull rod moves forward under the push of the compression spring, driving the rocker arm to rotate, and the wings are unfolded accordingly.

[0045] The folding wings of the aircraft described above, the limiting mechanism includes a baffle and a limiting hook, the baffle is installed in the guide hole of the connector, and the limiting hook is hinged in the groove cavity of the connector through a torsion spring. When the wing is unfolded, the baffle limits the movement stroke of the pull rod through the length of the pull rod stroke groove. When the wing is unfolded to the set angle, the front end of the limiting hook under the pull rod will slide into the slot hole of the pull rod, preventing the pull rod from retreating and locking the wing in the unfolded position. The rear end of the limiting hook is hinged to the pressure rod. When the front end of the limiting hook slides into the slot hole of the pull rod, the rear end of the limiting hook drives the pressure rod to protrude from the surface of the fuselage under the action of the torsion spring. Only by pressing the pressure rod can the lock on the pull rod be released and the unfolded wings can be folded.

[0046] See the attached drawings, Figure 1 、 Figure 2 、 Figure 3 As shown, the folding wing of the present application is mainly composed of a side wing 1, a connector 2, a connecting shaft 3, a rocker arm structure 4, a pull rod 5, a motor 9, a compression spring 10, a limit plate 12, a body 15, a limit hook 16 and a pressure rod 18.

[0047] When the wings are folded, the tail ends of the two wings 1 are close together; when the wings are extended, the tail ends of the two wings 1 are separated. In practice, the wings 1 are mounted outside the aircraft's fuselage 15, and the connector 2 is mounted inside. The connector 2 is a plate-like structure, with the two wings 1 symmetrically hinged to its lower surface via connecting shafts 3. The rocker structure 4 is located in the fork ears of the connector 2. The connector 2 is equipped with a drive mechanism and a limit mechanism for the wings 1. The drive mechanism drives the wings 1 to open via the rocker structure 4, while the limit mechanism limits the rotation angle of the rocker structure 4.

[0048] The rocker arm structure 4 includes a rocker arm and a disc. The center of the disc is fixed to the connecting shaft 3. An oblong chute is opened on the rocker arm, and the oblong chute is parallel to the rocker arm.

[0049] like Figure 3 、 Figure 4 、 Figure 5 As shown, the driving mechanism includes a pull rod 5, a motor 9, a compression spring 10, a cam 11 and a limit plate 12.

[0050] The pull rod 5 is located on the symmetrical axis of the two rocker arm structures 4 and is movably embedded in the guide hole of the connector 2. One end of the pull rod 5 is connected to the rocker arm structure 4, and the other end of the pull rod 5 is restricted in the guide hole of the connector 2 by a limit plate 12. The pull rod 5 is provided with a travel groove, in which a compression spring 10 is installed. The pull rod 5 can move forward under the push of the compression spring 10. The limit plate 12 is installed in the slide groove of the connector 2. The upper end of the limit plate 12 contacts the cam 11, and the lower end of the limit plate 12 is installed in the spring 13 in the slide groove of the connector 2. The spring 13 is fixed in the slide groove of the connector 2 with an elastic ring 14. The spring 13 can force the upper end of the limit plate 12 to always contact the cam 11. When the side wing 1 is in the folded state, the limit plate 12 moves upward under the action of the spring 13 to block the front end of the pull rod 5, preventing the pull rod 5 from moving forward, ensuring that the side wing 1 is in the folded state; when the aircraft is launched, the motor 9 is started at the set time, and the motor 9 drives the cam 11 to rotate, and the cam 11 forces the limit plate 12 to move downward. When the pull rod 5 can pass through the through hole on the limit plate 12, the pull rod 5 moves forward under the push of the compression spring 10, driving the rocker arm 4 to rotate, and the side wing 1 is unfolded.

[0051] The motor 9 is mounted on the guide hole through the support 8.

[0052] like Figure 3 、 Figure 4 As shown, the limiting mechanism comprises a baffle 7 and a limiting hook 16. Baffle 7 is mounted within the guide hole of connector 2 using screws 6. Limiting hook 16 is hinged within the slot of connector 2 via a torsion spring 17. When wing 1 is deployed, the pull rod 5 moves forward through the through hole of baffle 12. When baffle 7 contacts the rear end of the pull rod 5's travel slot, it prevents further forward movement. Simultaneously, the front end of limiting hook 16 below connector 2, driven by torsion spring 17, slides into the slot below the pull rod 5, preventing the pull rod 5 from retreating and locking wing 1 in the deployed position. The rear end of limiting hook 16 is hinged to a pressure rod 18. When the front end of limiting hook 16 slides into the slot of pull rod 5, the torsion spring 17 forces the rear end of limiting hook 16 to protrude from the surface of body 15. Only by pressing pressure rod 18 can the lock on pull rod 5 be released, allowing the deployed wing 1 to be folded.

[0053] The above specific implementation methods are detailed descriptions of the present invention. It cannot be considered that the specific implementation methods of the present invention are limited to these descriptions. For ordinary technicians in the technical field to which the present invention belongs, they can make several simple deductions and substitutions without departing from the concept of the present invention, which should be regarded as falling within the scope of protection of the present invention.

Claims

1. A rotating folding wing of an aircraft, characterized in that: include: Two symmetrical side wings, a connector (2), a driving mechanism and a limiting mechanism; The front ends of the two side wings are respectively hinged on the connector (2); when the wings are folded, the tail ends of the two side wings are close to each other; when the wings are opened, the tail ends of the two side wings are far apart; The front ends of the two side wings are symmetrically connected to the connector (2) through a connecting shaft (3) and a rocker arm structure (4). The rocker arm structure (4) comprises a rocker arm and a disc. The center of the disc is fixed to the connecting shaft (3). An oblong sliding groove is provided along the length of the rocker arm. The connector (2) is provided with a driving mechanism for the side wings, and the driving mechanism drives the side wings to open through a rocker arm structure; The connector (2) is provided with a groove cavity along the symmetric axis of the two rocker arms; the driving mechanism is provided with a slot hole; The limiting mechanism comprises a limiting hook (16), a torsion spring (17) and a pressure rod (18); the limiting hook (16) is hinged in the groove cavity of the connector through the torsion spring (17); the front end of the limiting hook (16) abuts against the driving mechanism, and the rear end of the limiting hook (16) is hingedly connected to the pressure rod (18); When the wing is unfolded to a set angle, the front end of the limit hook (16) slides into the slot of the drive mechanism under the drive of the torsion spring (17), preventing the drive mechanism from retreating and locking the wing in the unfolded position. At this time, the pressure rod (18) protrudes from the surface of the fuselage. By overcoming the torsion spring (17) and pressing the pressure rod (18) to release the lock of the drive mechanism, the unfolded wing can be folded.

2. The rotary folding wing of an aircraft according to claim 1, characterized in that: The driving mechanism comprises a motor (9), a cam (11), a limit plate (12), a compression spring (10) and a pull rod (5); The connector (2) is provided with a guide hole along the symmetrical axis of the two rocker arms, and a slide groove is provided at one end of the guide hole away from the connecting shaft (3), and the slide groove is vertically arranged on the connector (2); a baffle (7) is provided at one end of the guide hole close to the connecting shaft (3); The motor (9) is arranged above the guide hole, and the output shaft of the motor (9) is connected to the cam (11); the limit plate (12) is arranged in the slide groove of the connector (2) and contacts the cam (11), and moves up and down as the cam (11) rotates; a through hole is provided on the limit plate (12); The pull rod (5) is located on the symmetrical axis of the two rocker arms and is movably embedded in the guide hole of the connector. One end of the pull rod (5) is connected to the two rocker arms, and the other end of the pull rod (5) rotates with the cam (11) and is restricted by the limit plate (12) in the guide hole of the connector (2) or passes through the limit plate (12). A travel groove is provided on the pull rod (5), in which a compression spring (10) is installed, one end of which is against the travel groove and the other end is against the inner side of the baffle (7). Under the push of the compression spring (10), the pull rod (5) passes through the limit plate (12) and drives the side wings to open through the rocker arm structure.

3. The rotary folding wing of an aircraft according to claim 2, characterized in that: The travel groove and the baffle (7) serve as a limiting mechanism for limiting the rotation angle of the rocker arm structure and further limiting the expansion angle of the wing.

4. The rotary folding wing of an aircraft according to claim 1, characterized in that: The connector (2) body is a plate-like structure, and the two side wings are symmetrically hinged to the lower surface of the connector (2) body through the connecting shaft (3), and the rocker arm structure (4) is located on the upper surface of the connector (2) body; Two fork ear structures are provided on the upper surface of the connector (2) body, and the disc of the rocker arm structure (4) is located in the fork ears.

5. The rotary folding wing of an aircraft according to claim 2, characterized in that: An elastic retaining ring (14) is provided at the bottom of the chute; One end of the limiting plate (12) located in the chute is sleeved with a spring (13), and an annular limiting step for compressing the spring (13) is provided on the limiting plate (12); When the wing is in the folded state, the limit plate (12) moves upward under the action of the spring (13) to block the pull rod (5), preventing the pull rod (5) from passing through the limit plate (12), thereby ensuring that the wing is in the folded state; when the motor (9) is started, the cam (11) is driven to force the limit plate (12) to compress the spring (13) downward and move, and when the pull rod (5) is able to pass through the through hole on the limit plate (12), the pull rod (5) passes through the limit plate (12) under the push of the compression spring (10), and the side wings are driven to open through the rocker arm structure.

6. The rotary folding wing of an aircraft according to claim 2, characterized in that: The baffle (7) is detachably mounted on the guide hole by means of screws (6).

7. The rotary folding wing of an aircraft according to claim 2, characterized in that: The motor (9) is installed above the guide hole through the support (8).

8. The rotary folding wing of an aircraft according to claim 4, characterized in that: The connector (2) is installed inside the aircraft body (15), and the side wings are installed outside the aircraft body (15).

9. An aircraft, characterized in that: A rotary folding wing according to any one of claims 1 to 8 is used.

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