A reconfigurable mechanism for a multi-wing aircraft

Abstract

The application discloses a folding and unfolding mechanism for a multi-wing aircraft, which comprises a base, a power source, a driving part and a driven part, the base is used for mounting wings, the driving part is driven by the power source to adjust the movement of the driven part on the base; further comprising a connecting rod mechanism I and an end wing support rod, the first end of the connecting rod mechanism I is connected with the end wing support rod, the second end of the connecting rod mechanism I is connected with the driven part, the connecting rod mechanism I is driven by the driven part to adjust the folding and unfolding movement I of the end wing support rod on the base, the end wing support rod is provided with a first wing; further comprising a connecting rod mechanism II and a side wing support rod, the first end of the connecting rod mechanism II is connected with the side wing support rod, the second end of the connecting rod mechanism II is connected with the driven part, the connecting rod mechanism II is driven by the driven part to adjust the folding and unfolding movement II of the side wing support rod on the base, the side wing support rod is provided with a second wing, and the folding and unfolding mechanism can solve the defects of the existing multi-rotor aircraft folding and unfolding structure.

Description

Technical Field

[0001] This invention relates to the field of aircraft wings, and more specifically to a retraction and deployment mechanism for multi-wing aircraft. Background Technology

[0002] Currently, for medium and large multi-rotor aircraft with many outriggers, it is difficult to achieve simultaneous folding and unfolding in multiple directions when using a single power system; or when medium and large multi-rotor aircraft have special transportation needs, it is impossible to achieve maximum folding.

[0003] Therefore, to solve the above problems, a retraction and deployment mechanism for multi-rotor aircraft is needed, which can overcome the shortcomings of the existing multi-rotor aircraft retraction and deployment structures. Summary of the Invention

[0004] In view of this, the purpose of the present invention is to overcome the defects in the prior art and provide a retraction and deployment mechanism for multi-rotor aircraft, which can solve the shortcomings of the existing multi-rotor aircraft retraction and deployment structure.

[0005] The present invention provides a retraction and extension mechanism for a multi-wing aircraft, comprising a base, a power source, an active component, and a driven component. The base is used to mount the wings, and the active component is driven by the power source to adjust the movement of the driven component on the base. It also includes a linkage mechanism I and an end wing strut. The first end of the linkage mechanism I is connected to the end wing strut, and the second end of the linkage mechanism I is connected to the driven component. The linkage mechanism I is driven by the driven component to adjust the end wing strut in a retraction and extension movement I on the base. A first wing is mounted on the end wing strut. Furthermore, it includes a linkage mechanism II and a side wing strut. The first end of the linkage mechanism II is connected to the side wing strut, and the second end of the linkage mechanism II is connected to the driven component. The linkage mechanism II is driven by the driven component to adjust the side wing strut in a retraction and extension movement II on the base. A second wing is mounted on the side wing strut.

[0006] Furthermore, the end wing strut has an end wing strut end I and an end wing strut end II, the first wing is mounted on the end wing strut end I, and the first end of the linkage mechanism I is connected to the end wing strut end II.

[0007] Furthermore, the base has a guide limiting hole, and the end wing support rod is connected to the guide limiting hole in a through manner. The end wing support rod end I and the end wing support rod end II are not located on the same side of the guide limiting hole at the same time.

[0008] Furthermore, the guide limiting hole is a circular hole opened laterally, the end wing support rod is driven to move on the base by the linkage mechanism I along the axial direction of the circular hole, and the end wing support rod is limited along the radial direction of the circular hole.

[0009] Furthermore, a slider I is connected to the end II of the end wing strut, and a groove I is provided on the base. The slider I is movably positioned in the groove I and is limited in its position. The linkage mechanism I is a planar two-bar linkage mechanism. The first link of the planar two-bar linkage mechanism is fixed to the driven member, and the second link of the planar two-bar linkage mechanism is hinged to the slider I.

[0010] Furthermore, the linkage mechanism II is a planar four-bar linkage. The first link of the planar four-bar linkage is fixed to the driven member. The first link of the planar four-bar linkage has a slider II. The base has a groove II. The slider II is movably disposed in the groove II and is limited in position. The fourth link of the planar four-bar linkage has a slider III. The base has a groove III and the slider III is movably disposed in the groove III and is limited in position. The side wing support is connected to the second link of the planar four-bar linkage.

[0011] Furthermore, the fourth link of the planar four-bar linkage has a cooperating end I, the slider I has a cooperating end II, the cooperating end I is connected to the cooperating end II through a cooperating link, the cooperating link has a connecting end I and a connecting end II, the connecting end I of the cooperating link is hinged to the cooperating end I, and the connecting end II of the cooperating link is movably and limitedly disposed on the cooperating end II.

[0012] Furthermore, the first end of the linkage mechanism II is located at the second link of the planar four-bar linkage mechanism. There are two side wing struts, and each side wing strut is provided with a corresponding second wing. The two side wing struts are arranged laterally on both sides of the first end of the linkage mechanism II.

[0013] Furthermore, a third wing is provided on the first end of the linkage mechanism II.

[0014] Furthermore, the operating plane of the planar two-bar linkage is perpendicular to the operating plane of the planar four-bar linkage.

[0015] The beneficial effects of the present invention are: the retraction and deployment mechanism for multi-rotor aircraft disclosed in the present invention can achieve simultaneous retraction and deployment in multiple directions when folding and unfolding through a single power system, thus solving the shortcomings of the existing retraction and deployment structure of multi-rotor aircraft. Attached Figure Description

[0016] The present invention will be further described below with reference to the accompanying drawings and embodiments:

[0017] Figure 1 This is a schematic diagram of the wing deployment structure of the present invention;

[0018] Figure 2 This is a schematic diagram of the end wing strut structure of the present invention;

[0019] Figure 3 This is a schematic diagram of the wing retraction structure of the present invention;

[0020] Figure 4 This is a schematic diagram of the driven component of the present invention. Detailed Implementation

[0021] Figure 1 As shown in the schematic diagram of the present invention, the horizontal direction is the length direction of the base 9, and the vertical direction is the width direction of the base 9. The retraction and extension mechanism for the multi-wing aircraft in this embodiment includes a base 9, a power source 8, an active component 7, and a driven component 6. The base 9 is used to mount the wings. The active component 7 is driven by the power source 8 to adjust the movement of the driven component 6 on the base 9. It also includes a linkage mechanism I and an end wing support rod 3. The first end of the linkage mechanism I is connected to the end wing support rod 3, and the second end of the linkage mechanism I is connected to the driven component 6. The linkage mechanism I is driven by the driven component 6 to adjust the retraction and extension movement I of the end wing support rod 3 on the base 9. A first wing is provided on the end wing support rod 3. It also includes a linkage mechanism II and a side wing support rod 1. The first end of the linkage mechanism II is connected to the side wing support rod 1, and the second end of the linkage mechanism II is connected to the driven component 6. The linkage mechanism II is driven by the driven component 6 to adjust the retraction and extension movement II of the side wing support rod 1 on the base 9. A second wing is provided on the side wing support rod 1. The system employs multiple linkage mechanisms to achieve the retraction and extension of multiple wings, enabling the simultaneous retraction and extension of eight pairs of wings on opposite sides from a single power source, maximizing the retraction and extension capabilities, and overcoming the shortcomings of existing multi-rotor aircraft retraction and extension structures.

[0022] In this embodiment, the end wing strut 3 has end 1 and end 2 of end wing strut 3, the first wing is mounted on end 1 of end wing strut 3, and the first end of the linkage mechanism 1 is connected to end 2 of end wing strut 3.

[0023] In this embodiment, the base 9 has a guide limiting hole, and the end wing support rod 3 is connected to the guide limiting hole in a through manner. The end I of the end wing support rod 3 and the end II of the end wing support rod 3 are not located on the same side of the guide limiting hole at the same time.

[0024] In this embodiment, the guide limiting hole is a circular hole opened laterally, the end wing support rod 3 is driven to move on the base 9 by the linkage mechanism I along the axial direction of the circular hole, and the end wing support rod 3 is limited along the radial direction of the circular hole.

[0025] In this embodiment, a slider I11 is connected to the end II of the end wing support rod 3, and the base 9 has a sliding groove I. The slider I11 is movably positioned in the sliding groove I and is limited in place. The linkage mechanism I is a planar two-bar linkage mechanism. The first link 13 of the planar two-bar linkage mechanism is fixed to the driven member 6, and the second link 4 of the planar two-bar linkage mechanism is hinged to the slider I11.

[0026] In this embodiment, the linkage mechanism II is a planar four-bar linkage. The first link 14 of the planar four-bar linkage is fixed to the driven member 6. The first link 14 of the planar four-bar linkage has a slider II. The base 9 has a groove II. The slider II is movably disposed in the groove II and is limited in position. The fourth link of the planar four-bar linkage has a slider III. The base 9 has a groove III and the slider III is movably disposed in the groove III and is limited in position. The side wing support 1 is connected to the fourth link 10 of the planar four-bar linkage.

[0027] In this embodiment, the fourth link of the planar four-bar linkage has a cooperating end I, and the slider I11 has a cooperating end II12. The cooperating end I is connected to the cooperating end II12 through a cooperating link 5. The cooperating link 5 has a connecting end I and a connecting end II. The connecting end I of the cooperating link 5 is hinged to the cooperating end I, and the connecting end II of the cooperating link 5 is movably and limitedly disposed on the cooperating end II12.

[0028] In this embodiment, the first end of the linkage mechanism II is located at the second link of the planar four-bar linkage mechanism. There are two side wing support rods 1, and each side wing support rod 1 is provided with a corresponding second wing. The two side wing support rods 1 are arranged laterally on both sides of the first end of the linkage mechanism II.

[0029] In this embodiment, a third wing is provided on the first end of the linkage mechanism II.

[0030] In this embodiment, the operating plane of the planar two-bar linkage is perpendicular to the operating plane of the planar four-bar linkage.

[0031] As shown in the figure, a power source 8 is installed at the bottom of the base 9. The driving component 7 is a screw, and the driven component 6 is screwed to the screw. The output shaft of the power source 8 drives the screw to rotate, causing the driven component 6 to shift, thereby driving the linkage mechanism I and linkage mechanism II to achieve simultaneous opening and closing of the first wing located on linkage mechanism I and the second wing located on linkage mechanism II. The first wing and the second wing have different running lengths and running angles. The movement direction of the end wing support rod 3 is parallel to the lateral direction. The base 9 has a circular hole for guiding and limiting the end wing support rod 3, through which the end wing support rod 3 passes. At the circular hole, the two ends of the end wing support rod 3 are respectively connected to the first wing and the slider I11. The slider I11 is movably mounted on the base 9 with a lateral limit. The linkage mechanism I is a planar two-bar linkage mechanism. The running direction of the planar two-bar linkage mechanism is parallel to the lateral direction. The first link 13 of the planar two-bar linkage mechanism is fixed to the driven member 6, and the second link 4 of the planar two-bar linkage mechanism is hinged to the slider I11. When the driven member 6 is driven by the screw, the retraction and extension of the first wing can be realized through the planar two-bar linkage mechanism. In this scheme, the linkage mechanism I and the end wing support rod 3 are two sets arranged laterally on both sides of the driven member 6.

[0032] As shown in the figure, the linkage mechanism II is a planar four-bar linkage. The operating plane of the planar four-bar linkage is perpendicular to the operating plane of the planar two-bar linkage. The first link 14 of the planar four-bar linkage is fixed to the driven member 6. The first link 14 of the planar four-bar linkage has a slider II. The base 9 has a groove II. The slider II is movably positioned within the groove II. The slider II on the first link 14 of the planar four-bar linkage is the middle part of the first link. The first link 14 of the planar four-bar linkage extends out of the groove II and is hinged to the second link of the planar four-bar linkage. The movement direction of the first link 14 of the planar four-bar linkage is the same as the movement direction of the driven member 6, from bottom to top. The second link of the planar four-bar linkage is hinged to the third link 2 of the planar four-bar linkage. The third link 2 of the planar four-bar linkage is hinged to the fourth link of the planar four-bar linkage. The fourth link of the mechanism is movably limited on the base 9, and the movement direction of the fourth link of the planar four-bar linkage is longitudinal. The fourth link of the planar four-bar linkage has a slider III, which is located at the bottom of the fourth link. The base 9 has a groove III, and the slider III is movably limited within the groove III. The side wing support rod 1 is connected to the second link of the planar four-bar linkage. The side wing support rod 1 consists of two rods arranged laterally on both sides of the second link of the planar four-bar linkage. Furthermore, a third wing is provided on the first end of the linkage mechanism II. The third wing is installed on the second link of the planar four-bar linkage, so that when the linkage mechanism II drives the second wing to retract or extend, it can also retract or extend the third wing, thereby improving the retraction and extension capability of the multi-wing aircraft and improving space utilization. In this scheme, the linkage mechanism II and the side wing support rod 1 are two sets arranged longitudinally on both sides of the driven member 6.

[0033] As shown in the figure, the fourth link of the planar four-bar linkage has a cooperating end I, and the slider I 11 has a cooperating end II 12. The cooperating end I is connected to the cooperating end II 12 through a cooperating link 5. The cooperating link 5 has a connecting end I and a connecting end II. The connecting end I of the cooperating link 5 is hinged to the cooperating end I, and the connecting end II of the cooperating link 5 is movably and limitedly positioned on the cooperating end II 12. The use of the cooperating link 5 improves the simultaneous linkage between the linkage I and the linkage II, and also makes the operation of the linkage II more stable. The cooperating end II 12 has a clearance for the movement of the connecting end II to prevent the mechanism from jamming, which is used to control the braking distance of the slider and prevent the mechanism from locking up. The use of the cooperating link 5 also provides power to the fourth link of the planar four-bar linkage, improving the smoothness of the operation of the linkage II.

[0034] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention and are not intended to limit it. Although the present invention has been described in detail with reference to preferred embodiments, those skilled in the art should understand that modifications or equivalent substitutions can be made to the technical solutions of the present invention without departing from the spirit and scope of the technical solutions of the present invention, and all such modifications or substitutions should be covered within the scope of the claims of the present invention.

Claims

1. A retraction and deployment mechanism for a multi-wing aircraft, characterized in that: The system includes a base, a power source, an active component, and a driven component. The base is used to mount the wing. The active component is driven by the power source to adjust the movement of the driven component on the base. It also includes a linkage mechanism I and an end wing strut. The first end of the linkage mechanism I is connected to the end wing strut, and the second end of the linkage mechanism I is connected to the driven component. The linkage mechanism I is driven by the driven component to adjust the end wing strut's retraction / extension movement I on the base. The end wing strut is equipped with a first wing. The system further includes a linkage mechanism II and a side wing strut. The first end of the linkage mechanism II is connected to the side wing strut, and the second end of the linkage mechanism II is connected to the driven component. The linkage mechanism II is driven by the driven component to adjust the side wing strut's retraction / extension movement II on the base. The side wing strut is equipped with... The system includes a second wing; the end wing strut has an end wing strut end I and an end wing strut end II, the first wing is mounted on the end wing strut end I, and the first end of the linkage mechanism I is connected to the end wing strut end II; the base has a guide limiting hole, the end wing strut is connected to the guide limiting hole by passing through it, and the end wing strut end I and the end wing strut end II are not simultaneously located on the same side of the guide limiting hole; the guide limiting hole is a circular hole opened laterally, the end wing strut is driven to move on the base along the axial direction of the circular hole by the linkage mechanism I, and the end wing strut is limited along the radial direction of the circular hole; a slider I is connected to the end wing strut end II, the base has a sliding groove I, and the slider I is limited in its movable design. Placed within the slide groove I, the linkage mechanism I is a planar two-bar linkage, with the first link fixed to the driven member and the second link hinged to the slider I; the linkage mechanism II is a planar four-bar linkage, with the first link fixed to the driven member and a slider II on the first link, a slide groove II on the base, and the slider II being movably and limited within the slide groove II; the fourth link of the planar four-bar linkage has a slider III, a slide groove III on the base, and the slider III being movably and limited within the slide groove III; the side wing support is connected to the second link of the planar four-bar linkage; the fourth link of the planar four-bar linkage... The linkage mechanism has a cooperating end I and a cooperating end II. The cooperating end I is connected to the cooperating end II via a cooperating link. The cooperating link has a connecting end I and a connecting end II. The connecting end I of the cooperating link is hinged to the cooperating end I, and the connecting end II of the cooperating link is movably and limited on the cooperating end II. The first end of the linkage mechanism II is located at the second link of the planar four-bar linkage. There are two side wing support rods, and each side wing support rod is provided with a corresponding second wing. The two side wing support rods are arranged laterally on both sides of the first end of the linkage mechanism II. A third wing is provided on the first end of the linkage mechanism II. The operating plane of the planar two-bar linkage is perpendicular to the operating plane of the planar four-bar linkage.

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