Cross-medium foldable wing aircraft

Abstract

The utility model relates to a cross-medium foldable wing aircraft which comprises a propeller motor, a fuselage, a wing middle section, wings, a front hydrofoil, a rear hydrofoil, a connecting rod mechanism, a carbon tube, a water propeller motor, an inflatable airbag, a water rudder, a vertical tail and a horizontal tail, a propeller motor, a front hydrofoil, a wing middle section, a rear hydrofoil and a carbon tube are sequentially arranged on the fuselage from front to back, and the wings are rotationally connected with the wing middle section through rotating shafts. Through mutual cooperation of the wing middle sections of the interlayer structures, the wings of the arc structures and the rotating mechanisms, inward folding and outward unfolding of the wings are achieved, the purpose of reducing resistance when the aircraft body sails in water can be achieved, and after the aircraft body is separated from the water, the wings are unfolded to achieve takeoff of the aircraft; through mutual cooperation of the front hydrofoil, the rear hydrofoil and the water rudder, the stability of the aircraft body in water is effectively improved, and cross-medium flight of the aircraft can be achieved in the mode.

Description

Technical Field

[0001] The utility model relates to the technical field of aircraft, in particular to a cross-medium foldable wing aircraft. Background Art

[0002] With the rapid development of aviation, aircraft are becoming increasingly advanced and diverse. To meet the diverse application scenarios of aircraft, aircraft design needs to be constantly innovated to meet these needs.

[0003] In modern aerospace and ocean exploration, single-medium aircraft or vehicles face numerous limitations. Traditional aircraft design primarily focuses on flight within the atmosphere, relying on aerodynamic principles to generate lift and achieve maneuverability. Their ability to operate on or under water is virtually nonexistent. With the growing global demand for marine resource development, maritime rescue, border control, marine scientific research, and military strategy, there is an urgent need for a new type of transportation that combines high-speed maneuverability in the air with adaptability on or under water. To this end, a cross-medium foldable-wing aircraft is provided. Utility Model Content

[0004] In response to the above-mentioned shortcomings of the existing technology, the utility model provides a cross-medium foldable wing aircraft. Through the mutual cooperation of the sandwich structure of the wing middle section, the arc structure of the wing and the rotating mechanism, the wings can be folded inward and unfolded outward, which can achieve the purpose of reducing the resistance of the fuselage when sailing in the water, and the wings can be unfolded after leaving the water to realize the take-off of the aircraft.

[0005] The utility model is achieved through the following technical solutions.

[0006] A cross-medium foldable wing aircraft comprises a propeller motor, a fuselage, a wing midsection, wings, a front hydrofoil, a rear hydrofoil, a connecting rod mechanism, a carbon tube, a water propeller motor, an inflatable airbag, a water rudder, a vertical tail, and a horizontal tail. The propeller motor, the front hydrofoil, the wing midsection, the rear hydrofoil, and the carbon tube are arranged on the fuselage in order from front to back. The wings are rotatably connected to the wing midsection via a rotating shaft. A rotary servo is arranged on the wing midsection, connected to the wings via a connecting rod mechanism and controls whether the wings are deployed perpendicular to the fuselage or folded parallel to the fuselage. An inflatable airbag is arranged below the wings, the water propeller motor is arranged on the carbon tube, the water rudder is arranged below the tail of the carbon tube, and the vertical tail and horizontal tail are arranged at the tail of the carbon tube. With the center of gravity properly distributed, the front hydrofoil is installed directly below the front section of the fuselage and the rear hydrofoil is installed at the rear section of the fuselage to achieve the purpose of providing lift. The front hydrofoil and the rear hydrofoil are installed on the front and rear sections of the fuselage respectively, supporting the entire aircraft on the water through support rods, and the airfoil's airfoil shape can provide lift as part of the lift of the entire aircraft.

[0007] Furthermore, the fuselage is fixed to the middle section of the wing via a U-shaped support plate and U-shaped support plate screws.

[0008] Furthermore, the leading edge of the mid-wing section is streamlined, and the mid-wing section contains a hollow interlayer. One end of the wing that is rotatably connected to the mid-wing section is located inside the interlayer. Two fixed hinges are installed on the left and right upper and lower surfaces of the trailing edge of the interlayer of the mid-wing section, respectively, so that the upper and lower surfaces of the trailing edge can be partially folded to accommodate the wing. The mid-wing section is used to connect and fix the fuselage and the wing, and the mid-wing section is provided with a rotating shaft mounting hole. The wing is arc-shaped where it connects to the fuselage and is provided with a circular mounting hole, so that the wing is not restricted by the mid-wing section when changing between the unfolded and folded states. The interlayer structure of the mid-wing section is connected to the wing via a rotating shaft, so that the state of the wing can be changed by rotating the rotating shaft.

[0009] Furthermore, the connecting rod mechanism includes a rotating rod and a pull rod. The middle of the rotating rod is connected to the output end of the rotary servo. The two ends of the rotating rod are connected to one end of the pull rod through a rotating rod screw. The other end of the pull rod is connected to the wings on both sides through the pull rod screw. The rotary servo drives the rotating rod to rotate, driving the pull rod to move. The pull rod drives the wings on both sides to unfold or fold, and forms a locked state when the rotary servo does not rotate.

[0010] Furthermore, the inflatable airbag is installed in the middle position of the lower surface of the wing, and is used to provide stable buoyancy when the aircraft is on the water surface. An inflatable and deflable hose extends above the inflatable airbag. The hose is closed in normal flight status. When inflation is required, the hose mouth can be opened normally for inflation. When the wading depth of the fuselage needs to be adjusted, the hose mouth can be opened to deflate, so as to achieve the purpose of adjusting the wading depth of the fuselage.

[0011] Furthermore, the carbon tube is detachably connected to the fuselage. While meeting strength requirements, by inserting a section of carbon tube into the rear section of the fuselage, the fuselage weight is reduced while reducing flow resistance. The detachable carbon tube facilitates the routing of the wiring harnesses for the water rudder, horizontal tail, and vertical tail.

[0012] Furthermore, the fuselage is also provided with a GPS positioning sensor and a radar antenna.

[0013] The water propeller motor is installed in the middle section of the carbon tube through a ring connector to provide power for the aircraft when it navigates in the water.

[0014] The water rudder is installed on the lower surface of the horizontal tail and vertical tail and is mainly used to control the heading. It generates a steering torque by changing the force of the water flow on the rudder blades.

[0015] Compared with the existing technology, the advantages of the present invention are: the present invention realizes the inward folding and outward unfolding of the wings through the mutual cooperation of the sandwich structure middle section of the wing, the arc structure of the wing and the rotating mechanism, which can achieve the purpose of reducing the resistance of the fuselage when sailing in the water, and the wings are unfolded after leaving the water to realize the take-off of the aircraft; the mutual cooperation of the front hydrofoil, the rear hydrofoil and the water rudder effectively improves the stability of the fuselage in the water, and the above method can realize the cross-medium flight of the aircraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 This is a schematic diagram of the wings of an aircraft of the present invention being unfolded;

[0017] Figure 2 This is a schematic diagram of the folding of the aircraft wings of the present invention;

[0018] Figure 3 This is a schematic diagram of the connection structure between the fuselage and the wing midsection of the present invention;

[0019] Figure 4 This is a schematic diagram of the folding wing and connecting rod mechanism structure of the utility model;

[0020] Figure 5 This is a schematic diagram of the folding wing and wing midsection installation structure of the utility model.

[0021] In the figure: 1. Propeller motor; 2. Fuselage; 3. Front hydrofoil; 4. Wing midsection; 5. Wing; 6. Connecting rod mechanism; 7. Inflatable airbag; 8. Rear hydrofoil; 9. Carbon tube; 10. Propeller motor; 11. Water rudder; 12. Horizontal stabilizer; 13. Vertical stabilizer; 14. U-shaped support plate; 15. U-shaped support plate screw; 16. Fixed hinge; 17. Rotating shaft; 18. Rotating rod; 19. Rotating servo; 20. Pull rod; 21. Rotating rod screw; 22. Pull rod screw; 23. Airbag; 24. Hose; 25. GPS positioning sensor; 26. Radar antenna DETAILED DESCRIPTION

[0022] The present invention will be further described below with reference to the accompanying drawings and specific embodiments, but they are not intended to limit the present invention.

[0023] like Figures 1 to 5As shown, a cross-medium foldable wing aircraft includes a propeller motor 1, a fuselage 2, a wing midsection 4, a wing 5, a front hydrofoil 3, a rear hydrofoil 8, a connecting rod mechanism 6, a carbon tube 9, a water paddle motor 10, an inflatable airbag 7, a water rudder 11, a vertical tail 12, and a horizontal tail 13; the propeller motor 1, the front hydrofoil 3, the wing midsection 4, the rear hydrofoil 8, and the carbon tube 9 are arranged on the fuselage 2 from front to back, the wing 5 is rotatably connected to the wing midsection 4 through a rotating shaft 17, a rotary servo 19 is arranged on the wing midsection 4, the rotary servo 19 is connected to the wing 5 through a connecting rod mechanism 6 and controls the wing 5 to unfold perpendicular to the fuselage 2 or fold parallel to the fuselage 2, an inflatable airbag 7 is arranged below the wing 5, the water paddle motor 10 is arranged on the carbon tube 9, the water rudder 11 is arranged below the tail of the carbon tube 9, and the vertical tail 12 and the horizontal tail 13 are arranged at the tail of the carbon tube 9. Under the condition of reasonable distribution of the center of gravity, the front hydrofoil 3 and the rear hydrofoil 8 are respectively installed under the fuselage 2 to provide lift. The front hydrofoil and the rear hydrofoil are respectively installed in the front and middle sections of the fuselage, and the entire aircraft is supported on the water by the support rods. The airfoil's airfoil can provide lift as part of the lift of the whole aircraft.

[0024] Furthermore, the fuselage 2 is fixed to the wing midsection 4 via a U-shaped support plate 14 and U-shaped support plate screws 15 .

[0025] Furthermore, the leading edge of the mid-wing section 4 is streamlined, and the mid-wing section 4 contains a hollow interlayer. One end of the wing 5, which is pivotally connected to the mid-wing section 4, is located within the interlayer. Two fixed hinges 16 are installed on the upper and lower surfaces of the trailing edge of the mid-wing section's interlayer, respectively, allowing the upper and lower surfaces of the trailing edge to be partially folded to accommodate the wing 5. The mid-wing section 4 is used to connect and secure the fuselage and wing, and is provided with a mounting hole for the rotation axis. The wing 5 is arc-shaped where it connects to the fuselage 2 and has a circular mounting hole, so that the wing 5 is not restricted by the mid-wing section 4 when changing between the unfolded and folded states. The interlayer structure of the mid-wing section 4 is connected to the wing 5 via a rotation axis 17, allowing the rotation of the rotation axis 17 to change the state of the wing 5.

[0026] Furthermore, the connecting rod mechanism 6 includes a rotating rod 18 and a pull rod 20. The middle of the rotating rod 18 is connected to the output end of the rotary servo 19. The two ends of the rotating rod 18 are connected to one end of the pull rod 20 through a rotating rod screw 21. The other end of the pull rod 20 is connected to the wings 5 ​​on both sides through a pull rod screw 22. The rotary servo 19 drives the rotating rod 18 to rotate, driving the pull rod 20 to move. The pull rod 20 drives the wings 5 ​​on both sides to unfold or fold. When the rotary servo 19 does not rotate, it forms a locked state.

[0027] Furthermore, the inflatable airbag 7 is installed in the middle position of the lower surface of the wing 5, and is used to provide stable buoyancy when the aircraft is on the water surface. An inflatable and deflable hose extends above the inflatable airbag 7. The hose is closed in normal flight status. When inflation is required, the hose mouth can be opened normally for inflation. When the wading depth of the fuselage needs to be adjusted, the hose mouth can be opened for inflation and deflation to achieve the purpose of adjusting the wading depth of the fuselage.

[0028] Furthermore, the carbon tube 9 is detachably connected to the fuselage 2. While meeting strength requirements, by inserting a section of carbon tube into the rear section of the fuselage 2, the fuselage weight is reduced while reducing flow resistance. The detachable carbon tube 9 facilitates the arrangement of the wiring harnesses for the water rudder, horizontal tail, and vertical tail.

[0029] Furthermore, the fuselage 2 is also provided with a GPS positioning sensor 25 and a radar antenna 26 .

[0030] The water propeller motor is installed in the middle section of the carbon tube through a ring connector to provide power for the aircraft when it navigates in the water.

[0031] The water rudder is installed on the lower surface of the horizontal tail and vertical tail and is mainly used to control the heading. It generates a steering torque by changing the force of the water flow on the rudder blades.

[0032] Working principle:

[0033] Aerial operation state: the wings 5 ​​are in the unfolded state, the propeller motor 1 provides power for the aircraft, and the wings 5 ​​provide lift for the aircraft.

[0034] Operation status on the water surface: When the aircraft switches from aerial operation to operation on the water surface, the propeller motor 1 stops working, the rotary servo 19 drives the rotating rod 18 to rotate, driving the pull rod 20 to move, and the pull rod 20 drives the wings 5 ​​on both sides to fold. When the fuselage adjusts the wading depth, the buoyancy is controlled by inflating and deflating the inflatable airbag, and the water propeller motor 10 starts to provide power for the aircraft to move on the water surface. The front hydrofoil and the rear hydrofoil provide lift for the aircraft to operate on the water surface, and the water rudder provides steering torque for the aircraft to operate; when it is necessary to switch to aerial operation, the rotary servo 19 drives the rotating rod 18 to rotate, driving the pull rod 20 to move, and the pull rod 20 drives the wings 5 ​​on both sides to unfold, and the propeller motor 1 starts.

[0035] The above description is only a preferred embodiment of the present invention and does not limit the implementation method and protection scope of the present invention. For those skilled in the art, it should be aware that all solutions obtained by equivalent substitutions and obvious changes made using the description and illustrations of the present invention should be included in the protection scope of the present invention.

Claims

1. A cross-medium foldable wing aircraft, characterized in that: The invention comprises a propeller motor (1), a fuselage (2), a wing midsection (4), a wing (5), a front hydrofoil (3), a rear hydrofoil (8), a connecting rod mechanism (6), a carbon tube (9), a water propeller motor (10), an inflatable airbag (7), a water rudder (11), a vertical tail (12), and a horizontal tail (13); the propeller motor (1), the front hydrofoil (3), the wing midsection (4), the rear hydrofoil (8), and the carbon tube (9) are sequentially arranged on the fuselage (2) from front to back; the wing (5) is connected to the wing midsection via a rotating shaft (17). (4) Rotational connection, a rotary steering gear (19) is provided on the middle section of the wing (4), the rotary steering gear (19) is connected to the wing (5) through a connecting rod mechanism (6) and controls the wing (5) to unfold perpendicular to the fuselage (2) or fold parallel to the fuselage (2), an inflatable airbag (7) is provided below the wing (5), the water propeller motor (10) is provided on the carbon tube (9), the water rudder (11) is provided below the tail of the carbon tube (9), and the vertical tail (12) and the horizontal tail (13) are provided at the tail of the carbon tube (9).

2. The cross-medium foldable wing aircraft according to claim 1, characterized in that: The fuselage (2) is fixed to the wing middle section (4) via a U-shaped supporting plate (14) and U-shaped supporting plate screws (15).

3. The cross-medium foldable wing aircraft according to claim 1, characterized in that: The leading edge of the mid-wing section (4) is streamlined, and the mid-wing section (4) contains a hollow interlayer. One end of the wing (5) rotatably connected to the mid-wing section (4) is located inside the interlayer, and two fixed hinges (16) are respectively installed on the upper surface and the lower surface of the trailing edge of the interlayer of the mid-wing section.

4. The cross-medium foldable wing aircraft according to claim 1, characterized in that: The connecting rod mechanism (6) includes a rotating rod (18) and a pull rod (20). The middle of the rotating rod (18) is connected to the output end of the rotary steering gear (19). The two ends of the rotating rod (18) are connected to one end of the pull rod (20) through a rotating rod screw (21). The other end of the pull rod (20) is connected to the wings (5) on both sides through a pull rod screw (22). The rotary steering gear (19) drives the rotating rod (18) to rotate, driving the pull rod (20) to move. The pull rod (20) drives the wings (5) on both sides to unfold or fold. When the rotary steering gear (19) does not rotate, a locked state is formed.

5. The cross-medium foldable wing aircraft according to claim 1, characterized in that: The inflatable airbag (7) is installed at the middle position of the lower surface of the wing (5), and an inflatable and deflable hose extends above the inflatable airbag (7).

6. The cross-medium foldable wing aircraft according to claim 1, characterized in that: The carbon tube (9) is detachably connected to the fuselage (2).

7. The cross-medium foldable wing aircraft according to claim 1, characterized in that: The fuselage (2) is also provided with a GPS positioning sensor (25) and a radar antenna (26).

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