A multi-rotor aircraft double-cantilever hidden multi-link automatic folding mechanism

Abstract

The present invention discloses a multi-rotor aircraft dual-cantilever concealed multi-link automatic folding mechanism, which includes a motor, wherein the left and right sides of the motor are respectively connected to two screw fixing seats, the two screw fixing seats are respectively connected to two T-shaped screws, the two T-shaped screws are respectively connected to two screw nuts, the two screw nuts are respectively connected to two screw nut connecting blocks, the two screw nut connecting blocks are respectively connected to two hinge blocks, the two hinge blocks are respectively connected to connecting rods via two pin shafts 1, the two connecting rods are respectively connected to two cantilever beams via two pin shafts 2, and a rotating shaft is provided inside each of the two cantilever beams. The mechanism can solve the problem of large volume of traditional multi-rotor aircraft, so that after the cantilever of the multi-rotor is folded, the volume is half that of the previous volume, thereby facilitating transportation. The concealed design greatly reduces wind resistance during the cantilever unfolding flight.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft, and in particular to a double-cantilever hidden multi-link automatic folding mechanism for a multi-rotor aircraft. Background Art

[0002] At present, there are many vertical take-off and landing fixed-wing aircraft appearing at home and abroad. Most of the vertical take-off and landing parts use electric multi-rotors. In actual use, in order to pursue the efficiency of the whole machine, a multi-rotor layout is generally adopted. This makes the volume of the entire aircraft relatively large, and it is not easy to transport after it is fully unfolded. Summary of the Invention

[0003] In response to the above technical problems in the related art, the present invention proposes a single-support elastic-driven cable reel, which can overcome the above shortcomings of the prior art.

[0004] To achieve the above technical objectives, the technical solution of the present invention is implemented as follows:

[0005] The two lever arrangement comprises two bosses, wherein the bosses are connected to each other with a pair of locks, and the bosses are connected to the two stop blocks, the bosses being connected at two stops each with a pair of locks.

[0006] Furthermore, friction gaskets are provided between the two cantilever beams and the joint pressure plate 1 and the joint pressure plate 2.

[0007] Furthermore, the first pin and the second pin are both provided with oil-free bushings.

[0008] Furthermore, the fixed base plate is connected to the side fixing plate via a slot, and the side fixing plate is connected to the first joint pressure plate and the second joint pressure plate via a slot.

[0009] The beneficial effects of the present invention are as follows: the double-cantilever hidden multi-link automatic folding mechanism of the multi-rotor aircraft of the present invention can solve the problem of large volume of traditional multi-rotor aircraft, so that after the cantilever of the multi-rotor is folded, the volume is half of that before, thereby facilitating transportation. The hidden design greatly reduces wind resistance during the flight process when the cantilever is unfolded. BRIEF DESCRIPTION OF THE DRAWINGS

[0010] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the embodiments. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0011] Figure 1 This is a schematic diagram of the structure of the double-cantilever hidden multi-link automatic folding mechanism of the multi-rotor aircraft according to an embodiment of the present invention. Figure 1 ;

[0012] Figure 2 This is a schematic diagram of the structure of the double-cantilever hidden multi-link automatic folding mechanism of the multi-rotor aircraft according to an embodiment of the present invention. Figure 2 ;

[0013] Figure: 1. Screw fixing seat, 2. Screw nut connecting block, 3. T-screw, 4. Screw nut, 5. Pin 1, 6. Pin 2, 7. Motor, 8. Friction gasket, 9. Fixed base plate, 10. Hinge support block, 11. Connecting rod; 12. Cantilever beam, 13. Joint pressure plate 1, 14. Joint pressure plate 2, 15. Rotating shaft, 16. Rotating shaft cover, 17. Side fixing plate. DETAILED DESCRIPTION

[0014] The technical solutions in the embodiments of the present invention are described clearly and completely below. Obviously, the embodiments described are only some embodiments of the present invention, not all embodiments. All other embodiments obtained by ordinary technicians in this field based on the embodiments of the present invention are within the scope of protection of the present invention.

[0015] like Figure 1-2As shown, the multi-rotor aircraft double-cantilever hidden multi-link automatic folding mechanism according to an embodiment of the present invention includes a motor 7, the left and right sides of the motor 7 are respectively connected to two screw fixing seats 1, the bottoms of the two screw fixing seats 1 are connected to the fixed base plate 9, one end of the fixed base plate 9 is connected to the side fixing plate 17, the two screw fixing seats 1 are respectively connected to two T-shaped screws 3, the two T-shaped screws 3 are both connected to the motor 7, the two T-shaped screws 3 are positive and negative teeth, and the two T-shaped screws 3 are respectively connected to two screw nuts 4, and the motor 7 can simultaneously drive the T-shaped screws 3 on both sides to rotate in the same direction. The T-shaped lead screws 3 on both sides are positive and negative teeth, so that the lead screw nuts 4 move toward each other, that is, they move away from each other at the same time, or approach each other at the same time. The two lead screw nuts 4 are respectively connected to the two lead screw nut connecting blocks 2, and the two lead screw nut connecting blocks 2 are respectively connected to the two hinge blocks 10. The two hinge blocks 10 are respectively connected to the connecting rods 11 through two pin shafts 5, and the two connecting rods 11 are respectively connected to the two cantilever beams 12 through two pin shafts 6. A rotating shaft 15 is provided inside the two cantilever beams 12, and a rotating shaft cover 16 is provided at the upper and lower ends of the two rotating shafts 15. The two groups of rotating shaft covers 16 are respectively connected to the joint pressure plate 13, The joint pressure plate 2 14 is connected, and the pin hole positioning prevents the rotating shaft 15 from rotating. The screw nut connecting block 2, the connecting rod 11, the cantilever beam 12, the joint pressure plate 1 13, the joint pressure plate 2 14, and the rotating shaft 15 constitute the crank slider mechanism principle, wherein the screw nut connecting block 2 is a slider, the rotating shaft 15 is a fixed hinge fulcrum, and the cantilever beam 12 is a crank. The side fixed plate 17 is connected to the joint pressure plate 1 13 and the joint pressure plate 2 14 through a slot. The fixed base plate 9, the joint pressure plate 1 13, the joint pressure plate 2 14, and the side fixed plate 17 are fastened by the slot limit, so that the position is accurate and the slot is better stressed, which plays a role in bearing the overall force. The side fixed plate 17 plays a role in mechanical limit limiting when folding and unfolding. The power mechanism is hidden in the internal space composed of the side fixed plate 17 and the fixed base plate 9 to prevent exposure and increase flight resistance.

[0016] Friction pads 8 are provided between the two cantilever beams 12 and the joint pressure plate 1 13 and the joint pressure plate 2 14 . The cantilever beams 12 play a lubricating role when rotating. In addition, they are wearing parts and can be easily replaced separately after being worn to a certain extent.

[0017] The above-mentioned pin shaft 1 5 and pin shaft 2 6 are both provided with oil-free bushings to reduce friction resistance.

[0018] The fixed base plate 9 is connected to the side fixing plate 17 via a slot, and the side fixing plate 17 is connected to the joint pressure plate 1 13 and the joint pressure plate 2 14 via a slot, so that the position is accurate and the slot is better stressed.

[0019] In order to facilitate understanding of the above technical solutions of the present invention, the above technical solutions of the present invention are described in detail below through specific usage methods.

[0020] During specific use, when the motor 7 drives the T-shaped screws 3 on both sides to rotate at the same time, the T-shaped screws 3 on both sides respectively drive the screw nuts 4 to move toward each other, thereby driving the cantilever beams 12 on both sides to rotate relative to each other around the rotating shaft 15 at the same time through the connecting rod 11, thereby realizing the folding function of the cantilever beam 12; when the screw nut 4 is close to the screw fixing seat 1, the cantilever beam is unfolded, and when the screw nut 4 is away from the screw fixing seat, the cantilever beam 12 is folded; the folding and unfolding positions are 90°, and each position has a side fixing plate 17 as an extreme limit; finally, by controlling the forward and reverse rotation of the motor 7, the unfolding and folding of the double cantilever beams can be automatically controlled.

[0021] To sum up, with the help of the above-mentioned technical solution of the present invention, the problem of large size of traditional multi-rotor aircraft can be solved, so that after the cantilever of the multi-rotor is folded, the volume is half smaller than before, which is convenient for transportation. The hidden design is adopted, so that the wind resistance is greatly reduced during the flight process when the cantilever is unfolded.

[0022] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention should be included in the scope of protection of the present invention.

Claims

1. A multi-rotor aircraft double-cantilever hidden multi-link automatic folding mechanism, characterized in that: The invention comprises a motor (7), wherein the left and right sides of the motor (7) are respectively connected to two screw fixing seats (1), the bottoms of the two screw fixing seats (1) are respectively connected to a fixed base plate (9), one end of the fixed base plate (9) is connected to a side fixing plate (17), the two screw fixing seats (1) are respectively connected to two T-shaped screws (3), the two T-shaped screws (3) are both connected to the motor (7), the two T-shaped screws (3) are positive and negative teeth, the two T-shaped screws (3) are respectively connected to two screw nuts (4), the two screw nuts (4 ) are respectively connected to the two screw nut connecting blocks (2), the two screw nut connecting blocks (2) are respectively connected to the two hinge support blocks (10), the two hinge support blocks (10) are respectively connected to the connecting rod (11) through two pin shafts (5), the two connecting rods (11) are respectively connected to the two cantilever beams (12) through two pin shafts (6), the two cantilever beams (12) are each provided with a rotating shaft (15) inside, and the upper and lower ends of the two rotating shafts (15) are each provided with a rotating shaft cover (16), and the two sets of rotating shaft covers (16) are respectively connected to the joint pressure plate one (13), The joint pressure plate 2 (14) is connected, the side fixing plate (17) is connected to the joint pressure plate 1 (13) and the joint pressure plate 2 (14), friction pads (8) are provided between the two cantilever beams (12) and the joint pressure plate 1 (13) and the joint pressure plate 2 (14), and the pin shaft 1 (5) and the pin shaft 2 (6) are provided with oil-free bushings.

2. The multi-rotor aircraft double-cantilever hidden multi-link automatic folding mechanism according to claim 1, characterized in that: The fixed base plate (9) is connected to the side fixing plate (17) through a slot, and the side fixing plate (17) is connected to the joint pressure plate 1 (13) and the joint pressure plate 2 (14) through a slot.

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