Aircraft with novel foldable modular wings

Abstract

The invention discloses an aircraft with foldable modular novel wings, and relates to the field of aircrafts, the aircraft comprises a first stay bar, an aircraft body and a second stay bar, the aircraft body is mounted in the center of the opposite sides of the first stay bar and the second stay bar, and the two sides of the bottom of the second stay bar are symmetrically and rotatably connected with the foldable wings; the opposite sides of the first supporting rod and the second supporting rod are movably connected with a composite wing assembly, and mounting blocks are symmetrically mounted at the two ends of the composite wing assembly. According to the aircraft with the foldable modular novel wings, the first supporting rods, the aircraft body, the second supporting rods and the composite wing assemblies adopt an H-shaped aerodynamic layout, so that the overall structural rigidity can be greatly improved, the outer wing design with a higher aspect ratio is allowed, and the aspect ratio of the whole aircraft can be remarkably increased under the condition of lower structural weight; the vertical take-off and landing power units are ingeniously arranged on the first supporting rod and the second supporting rod and are integrated with the whole aircraft, so that the resistance during cruising flight is remarkably reduced, and the lift-drag performance of the aircraft can be greatly improved.

Description

Technical Field

[0001] The invention relates to the field of aircraft, in particular to an aircraft with a novel foldable modular wing. Background Art

[0002] The wing is an important part of an aircraft. Its main function is to provide lift. Together with the tail, it ensures that the aircraft has good stability. When it has an upward angle, it can provide some lateral stability for the aircraft. At its trailing edge, there are generally ailerons, spoilers and other devices for lateral control. In order to improve the aerodynamic effect of the wing, various forms of flaps, wing tangles and other lift-enhancing devices are increasingly installed in the front and rear of the wing to improve the take-off, landing or maneuverability of the aircraft; other components such as landing gear and engines are installed on the wing. Modern fighters and fighter-bombers often have a variety of external attachments under the wings, such as auxiliary fuel tanks and missiles, bombs and other military equipment. The internal space of the wing is often used to store landing gear, place some small equipment, accessories and store fuel. Especially for passenger aircraft, in order to ensure the safety of passengers, many aircraft do not store fuel in the aircraft body, but store all fuel in the wings. There are two types of fuel tanks for storing fuel: integral fuel tanks and soft fuel tanks. In order to reduce reset, many modern aircraft wing fuel tanks are integral fuel tanks.

[0003] The existing wing has weak load-carrying cruise capability, the composite wing vertical take-off and landing power group has large drag, the structural limitation of the aspect ratio is not large enough, and the horizontal tail or V-tail balances the negative lift, resulting in average lift-to-drag performance of the whole aircraft; the structure is heavy: when the vertical take-off and landing power group is installed, the wing needs to have higher rigidity, and the structure is in an unfavorable stress form and needs to be strengthened, resulting in weight increase; the hovering wind resistance is weak: in order to improve the cruise performance, a larger aspect ratio is required when hovering or vertical take-off and landing, and the wind load has a great impact on lateral control. At the same time, the research and development and manufacturing costs of a series of products with different mission requirements are high.

[0004] Therefore, it is necessary to propose an aircraft with a new type of foldable modular wing to solve the above problems. Summary of the invention

[0005] The main purpose of the present invention is to provide an aircraft with a new type of foldable modular wing, which can effectively solve the problems in the background technology.

[0006] To achieve the above object, the technical solution adopted by the present invention is: An aircraft with a novel foldable modular wing, comprising a first strut, an aircraft body, and a second strut, wherein the aircraft body is mounted in the middle of one side opposite to the first strut and the second strut, two sides of the bottom of the second strut are symmetrically rotatably connected with folding wings, and two sides of the top of the second strut are symmetrically mounted with reinforcement components; A composite wing assembly is movably connected to one side of the first support rod and the second support rod opposite to each other, and mounting blocks are symmetrically mounted at both ends of the composite wing assembly; A tail wing is arranged at one end of the composite wing assembly away from the first strut, and a rotor is rotatably connected in the inner cavity of the composite wing assembly and the tail wing.

[0007] Preferably, through grooves are symmetrically provided on both sides of the bottom of the first support rod, and spoilers are symmetrically installed in the inner cavities of the two through grooves.

[0008] Preferably, first slots are symmetrically provided in the middle of both sides of the second support rod, two sides of the bottom of the second support rod are symmetrically rotatably connected with a rotating shaft, and two sides of the second support rod away from one end of the first support rod are symmetrically installed with rotating motors, and the rotating motors are installed on the outer wall of the rotating shaft through a coupling.

[0009] Preferably, the side of the top of the folding wing is installed at the bottom of the rotating shaft, and fixed seats are symmetrically installed on the opposite sides of the two folding wings. A second slot is opened in the middle of the fixed seat, and a card block is movably connected in the inner cavity of the first slot, and the bottom of the card block and the side of the fixed seat are both provided with inclined surfaces.

[0010] Preferably, the reinforcement component is communicated with the inner cavity of the first card slot, the first card slot and the fixing seat are matched in size, and the card block and the second card slot are matched in size.

[0011] Preferably, a fixing rod is installed in the center of the inner cavity of the reinforcement component, a spring is wound around the outer wall of the fixing rod, the top of the spring is installed on the top of the inner cavity of the reinforcement component, a limiting block is installed on the bottom of the spring, the limiting block is installed on the top of the clamping block, the limiting block is movably connected in the inner cavity of the reinforcement component, the clamping block is movably connected in the first clamping slot and the inner cavity of the reinforcement component, and the clamping block and the limiting block are both sleeved on the outer wall of the fixing rod.

[0012] Preferably, adjustment grooves are symmetrically provided on both sides of opposite sides of the first support rod and the second support rod, a double-headed bidirectional screw is rotatably connected in the inner cavity of the adjustment groove at one end, a guide rod is installed in the inner cavity of the other adjustment groove, a first gear is installed in the center of the outer wall of the double-headed bidirectional screw, a second gear is meshed with the side of the first gear, a servo motor is installed on the side of the second gear through a second rotating shaft, the servo motor is installed on the outer wall of the second support rod, and the second gear is rotatably connected in the inner cavity of the second support rod.

[0013] Preferably, an adjustment block is symmetrically installed in the middle of the opposite sides of the mounting blocks at both ends, and the adjustment block is movably connected in the inner cavity of the adjustment groove. The adjustment block at one end is sleeved on the outer wall of the guide rod, and the adjustment block at the other end is threadedly connected to the outer wall of the double-headed bidirectional screw.

[0014] Preferably, there are four composite wing assemblies, a positioning groove is provided on the side of the outer mounting block, and a positioning block is installed on the side of the inner mounting block, and the positioning block and the positioning groove have sizes that match and are located on the same axis.

[0015] Preferably, one end of the adjustment block is installed at one end of the tail wing, and the sides of the tail wing and the composite wing assembly are both provided with accommodating grooves, and the rotor is rotatably connected in the inner cavity of the composite wing assembly and the tail wing through the accommodating groove.

[0016] Compared with the prior art, the present invention provides an aircraft with a novel foldable modular wing, which has the following beneficial effects: The aircraft with a new foldable modular wing has an H-configuration aerodynamic layout of the first strut, the aircraft body, the second strut and the composite wing assembly, which can greatly improve the overall structural rigidity, allow for an outer wing design with a larger aspect ratio, and significantly increase the aspect ratio of the entire aircraft at a lower structural weight; the vertical take-off and landing power group is cleverly arranged on the first strut and the second strut, and is integrated with the entire aircraft design to significantly reduce the resistance during cruise flight, which can greatly improve the lift-drag performance of the aircraft and improve the load-bearing and cruise flight capabilities. At the same time, the H-configuration greatly improves the overall structural rigidity, and the installation of the power group will not increase the structural weight; the force form of the aircraft body can be comprehensively improved, the structural rigidity is significantly improved, and the structural weight is significantly reduced. The aircraft with a new type of foldable modular wing adopts a downward folding design. The folding wing is in a folded state during vertical takeoff and landing and hovering. At the same time, the rotor is located at the outermost end of the attitude control, which has high control efficiency. Under the action of wind load, the outer side of the power group does not produce a larger overturning moment that needs to be balanced, which significantly improves the hovering wind resistance. At the same time, vertical takeoff and landing can be achieved in the folded state, which significantly reduces the requirements for the take-off and landing site and solves the actual pain points of users. This aircraft with a new type of foldable modular wing is a high-cost solution for the research and development and manufacturing of a series of products with different mission requirements: it can adopt a modular design, and the first strut, the second strut, the aircraft body and the composite wing assembly can be replaced as needed, so as to quickly reconstruct aircraft solutions with different load capacities and endurances. Based on this, aircraft with different performances can be quickly reconstructed. Multiple aircraft share the same structural modules, which greatly reduces production costs. At the same time, the shared modules can significantly improve the maintainability of the aircraft. The aircraft with the novel foldable modular wing can drive the rotating shaft to rotate by starting the rotating motor, and the rotating shaft can drive the folding wing to rotate left and right after rotating, so that the folding wing can be unfolded and folded, so that it can be operated according to different flight plans, and through the fixed seat, when the folding wing is unfolded, it will drive the fixed seat to be inserted into the inner cavity of the first card slot, and through the spring, the card block can be inserted into the inner cavity of the fixed seat through the second card slot, so that the folding wing can be fixed in the unfolded state, so as to achieve a better reinforcement effect. The aircraft with the new foldable modular wing has inclined surfaces at the fixing seat and the card block. After the fixing seat contacts the card block, the card block will be squeezed into the inner cavity of the reinforcement component through the inclined surface. When the fixing seat completely enters the inner cavity of the first card slot, the spring can bounce the card block into the inner cavity of the second card slot. When the folding wing needs to be folded, the fixing seat can also quickly detach from the card block and the first card slot to complete the folding work. The aircraft with the novel foldable modular wing can drive the second gear to rotate by starting the provided servo motor. After the second gear rotates, it can mesh with the first gear, and at this time, it can drive the double-headed bidirectional lead screw to rotate. After the double-headed bidirectional lead screw rotates, the adjustment block at one end can be threadedly connected with the double-headed bidirectional lead screw, so that the composite wing components on both sides can be folded and unfolded, so that the state can be adjusted according to the flight plan. At the same time, the provided positioning grooves and positioning blocks can facilitate the merging of the composite wing components through the mounting blocks, which can achieve a better positioning effect. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 It is a schematic diagram of the overall structure of the present invention; Figure 2 The present invention Figure 1 The enlarged view of point A in the middle; Figure 3 It is a schematic diagram of the structure of the reinforcement assembly of the present invention; Figure 4 It is a structural schematic diagram of the bidirectional screw rod of the present invention; Figure 5 It is a schematic structural diagram of the composite wing assembly of the present invention.

[0018] In the figure: 1. first support rod; 2. through slot; 3. spoiler; 4. aircraft body; 5. second support rod; 6. adjustment slot; 7. double-headed bidirectional screw; 8. first gear; 9. second gear; 10. servo motor; 11. reinforcement assembly; 12. first slot; 13. rotating shaft; 14. rotating motor; 15. folding wing; 16. fixing rod; 17. spring; 18. limit block; 19. block; 20. fixing seat; 21. second slot; 22. inclined plane; 23. composite wing assembly; 24. receiving slot; 25. rotor; 26. mounting block; 27. positioning slot; 28. positioning block; 29. ​​adjustment block; 30. tail wing. DETAILED DESCRIPTION

[0019] In order to make the technical means, creative features, objectives and effects achieved by the present invention easy to understand, the present invention is further explained below in conjunction with specific implementation methods. Example

[0020] like Figure 1-Figure 3 As shown, an aircraft with a novel foldable modular wing comprises a first strut 1, an aircraft body 4 and a second strut 5, wherein the aircraft body 4 is mounted in the middle of the first strut 1 and the second strut 5 on opposite sides, folding wings 15 are symmetrically rotatably connected on both sides of the bottom of the second strut 5, reinforcement components 11 are symmetrically mounted on both sides of the top of the second strut 5, through grooves 2 are symmetrically opened on both sides of the bottom of the first strut 1, spoilers 3 are symmetrically mounted in the inner cavities of the two through grooves 2, first card grooves 12 are symmetrically opened in the middle of both sides of the second strut 5, and rotating shafts 13 are symmetrically rotatably connected on both sides of the bottom of the second strut 5, rotating motors 14 are symmetrically mounted on both sides of the second strut 5 away from one end of the first strut 1, and the rotating motor 14 is mounted on the outer wall of the rotating shaft 13 through a coupling, the side edges of the tops of the folding wings 15 are mounted on the bottom of the rotating shaft 13, and the two folding wings 15 are symmetrically mounted on the opposite sides of the two folding wings 15. A fixing seat 20 is installed, a second slot 21 is provided in the center of the fixing seat 20, a block 19 is movably connected in the inner cavity of the first slot 12, and a slope 22 is provided at the bottom of the block 19 and the side of the fixing seat 20, the reinforcement component 11 is communicated with the inner cavity of the first slot 12, the sizes of the first slot 12 and the fixing seat 20 are adapted, the sizes of the block 19 and the second slot 21 are adapted, a fixing rod 16 is installed in the center of the inner cavity of the reinforcement component 11, a spring 17 is wound around the outer wall of the fixing rod 16, the top of the spring 17 is installed on the top of the inner cavity of the reinforcement component 11, a limiting block 18 is installed at the bottom of the spring 17, the limiting block 18 is installed on the top of the block 19, the limiting block 18 is movably connected in the inner cavity of the reinforcement component 11, the block 19 is movably connected in the first slot 12 and the inner cavity of the reinforcement component 11, and the block 19 and the limiting block 18 are both sleeved on the outer wall of the fixing rod 16. Example

[0021] like Figure 1, Figure 2 , Figure 4 , Figure 5 As shown, an aircraft with a foldable modular novel wing, a composite wing assembly 23 is movably connected to the opposite side of the first strut 1 and the second strut 5, and mounting blocks 26 are symmetrically installed at both ends of the composite wing assembly 23, and adjustment grooves 6 are symmetrically opened on both sides of the opposite side of the first strut 1 and the second strut 5, a double-headed bidirectional screw 7 is rotatably connected in the inner cavity of the adjusting groove 6 at one end, and a guide rod is installed in the inner cavity of the other adjusting groove 6, a first gear 8 is installed in the middle of the outer wall of the double-headed bidirectional screw 7, a second gear 9 is meshed with the side of the first gear 8, a servo motor 10 is installed on the side of the second gear 9 through a second rotating shaft, the servo motor 10 is installed on the outer wall of the second strut 5, and the second gear 9 is rotatably connected in the inner cavity of the second strut 5, and adjustment blocks 29 are symmetrically installed in the middle of the opposite sides of the mounting blocks 26 at both ends, and the adjustment block 29 is movably connected in the inner cavity of the adjusting groove 6, one end of the adjustment block 29 is sleeved on the outer wall of the guide rod, and the other end of the adjustment block 29 is threadedly connected to the outer wall of the double-headed bidirectional screw 7. Example

[0022] like Figure 1 , Figure 5 As shown, an aircraft with a new type of foldable modular wing is shown, a tail 30 is provided at one end of a composite wing assembly 23 away from the first strut 1, a rotor 25 is rotatably connected in the inner cavity of the composite wing assembly 23 and the tail wing 30, there are four composite wing assemblies 23, a positioning groove 27 is provided on the side of an outer mounting block 26, a positioning block 28 is installed on the side of an inner mounting block 26, the positioning block 28 is adapted to the size of the positioning groove 27 and is on the same axis, an end adjustment block 29 is installed at one end of the tail wing 30, and a receiving groove 24 is provided on the side of the tail wing 30 and the composite wing assembly 23, and the rotor 25 is rotatably connected in the inner cavity of the composite wing assembly 23 and the tail wing 30 through the receiving groove 24.

[0023] The first strut 1, the aircraft body 4, the second strut 5 and the composite wing assembly 23 adopt an H-configuration aerodynamic layout, which can greatly improve the overall structural rigidity, allow the design of an outer wing with a larger aspect ratio, and significantly increase the aspect ratio of the entire aircraft at a lower structural weight; the vertical take-off and landing power group is cleverly arranged on the first strut 1 and the second strut 5, and is integrated with the overall design to significantly reduce the resistance during cruise flight, which can greatly improve the lift-drag performance of the aircraft and improve the load-bearing and cruise flight capabilities. At the same time, the H-configuration greatly improves the overall structural rigidity, and the installation of the power group will not increase the structural weight; it can comprehensively improve the force form of the aircraft body, significantly improve the structural rigidity, and significantly reduce the structural weight.

[0024] The folding wing 15 adopts a downward folding design, and is in a folded state during vertical take-off and landing and hovering. At the same time, the rotor 25 is located at the outermost end of the attitude control, which has high control efficiency. Under the action of wind load, the outer side of the power group does not produce a larger overturning moment that needs to be balanced, which significantly improves the hovering wind resistance. At the same time, the folded state realizes vertical take-off and landing, significantly reducing the requirements for the take-off and landing site, and solving the actual pain points of users.

[0025] A high-cost solution for the development and manufacturing of a series of products facing different mission requirements: a modular design can be adopted, and the first strut 1, the second strut 5, the aircraft body 4 and the composite wing assembly 23 can be replaced as needed, so as to quickly reconstruct aircraft solutions with different loads and endurances. Based on this, aircraft with different performances can be quickly reconstructed. Multiple aircraft share structural modules, and the production cost is greatly reduced. At the same time, the shared modules can significantly improve the maintainability of the aircraft.

[0026] By starting the rotating motor 14, the rotating shaft 13 can be driven to rotate. After the rotating shaft 13 rotates, the folding wing 15 can be driven to rotate left and right, so that the folding wing 15 can be unfolded and folded, so that it can be operated according to different flight plans. Through the fixed seat 20, when the folding wing 15 is unfolded, the fixed seat 20 will be driven to insert into the inner cavity of the first slot 12. Through the spring 17, the card block 19 can be inserted into the inner cavity of the fixed seat 20 through the second slot 21, so that the folding wing 15 can be fixed in the unfolded state, so as to achieve a better reinforcement effect.

[0027] Through the inclined surface 22 at the fixing seat 20 and the block 19, after the fixing seat 20 contacts the block 19, the block 19 will be squeezed into the inner cavity of the reinforcement component 11 through the inclined surface 22. When the fixing seat 20 completely enters the inner cavity of the first slot 12, the spring 17 can bounce the block 19 into the inner cavity of the second slot 21. When the folding wing 15 needs to be folded, the fixing seat 20 can also quickly detach from the block 19 and the first slot 12 to complete the folding work.

[0028] By starting the set servo motor 10, the second gear 9 can be driven to rotate. After the second gear 9 rotates, it can mesh with the first gear 8, and at this time it can drive the double-headed bidirectional screw rod 7 to rotate. After the double-headed bidirectional screw rod 7 rotates, the adjustment block 29 at one end can be threadedly connected with the double-headed bidirectional screw rod 7, so that the composite wing assemblies 23 on both sides can be folded and unfolded, so that the state can be adjusted according to the flight plan. At the same time, through the provided positioning groove 27 and positioning block 28, it is convenient for the composite wing assembly 23 to be merged through the mounting block 26, which can achieve a better positioning effect.

[0029] It should be noted that the present invention is an aircraft with a foldable modular new type of wing. When in use, the composite wing assembly 23 and the folding wing 15 are adjusted according to the flight plan, and the servo motor 10 is started to drive the second gear 9 to rotate, so that the second gear 9 is meshed with the first gear 8, thereby driving the bidirectional screw rod 7 to rotate. After the bidirectional screw rod 7 rotates, the adjustment block 29 at one end is threadedly connected with it, so that the four composite wing assemblies 23 on both sides can be unfolded and merged; Start the rotating motor 14, and drive the folding wing 15 to rotate through the rotating shaft 13. After the folding wing 15 rotates, it drives the fixing seat 20 to enter the inner cavity of the first slot 12. After the fixing seat 20 enters the inner cavity of the first slot 12, it will contact the block 19, and squeeze the block 19 into the inner cavity of the reinforcement component 11 through the inclined surface 22. When the fixing seat 20 completely enters the inner cavity of the first slot 12, the spring 17 bounces the block 19 into the inner cavity of the second slot 21 through the limit block 18. At this time, the folding wing 15 is reinforced by the fixing seat 20.

[0030] The above shows and describes the basic principles and main features of the present invention and the advantages of the present invention. It should be understood by those skilled in the art that the present invention is not limited to the above embodiments. The above embodiments and descriptions are only for explaining the principles of the present invention. Without departing from the spirit and scope of the present invention, the present invention may have various changes and improvements, which fall within the scope of the present invention to be protected. The scope of protection of the present invention is defined by the attached claims and their equivalents.

Claims

1. An aircraft with a novel foldable modular wing, comprising a first strut (1), an aircraft body (4), and a second strut (5), characterized in that: The aircraft body (4) is mounted in the middle of one side opposite to the first support rod (1) and the second support rod (5); two sides of the bottom of the second support rod (5) are symmetrically connected to folding wings (15); and two sides of the top of the second support rod (5) are symmetrically mounted with reinforcement components (11); A composite wing assembly (23) is movably connected to one side of the first support rod (1) and the second support rod (5) opposite to each other, and mounting blocks (26) are symmetrically mounted at both ends of the composite wing assembly (23); A tail wing (30) is provided at one end of the composite wing assembly (23) away from the first strut (1), and a rotor (25) is rotatably connected in the inner cavity of the composite wing assembly (23) and the tail wing (30).

2. The aircraft with a novel foldable modular wing according to claim 1, characterized in that: Through slots (2) are symmetrically provided on both sides of the bottom of the first support rod (1), and spoilers (3) are symmetrically installed in the inner cavities of the two through slots (2).

3. The aircraft with a novel foldable modular wing according to claim 1, characterized in that: A first clamping groove (12) is symmetrically provided in the middle of both sides of the second support rod (5); both sides of the bottom of the second support rod (5) are symmetrically connected to a rotating shaft (13); and both sides of the second support rod (5) away from one end of the first support rod (1) are symmetrically installed with a rotating motor (14); the rotating motor (14) is installed on the outer wall of the rotating shaft (13) via a coupling.

4. The aircraft with a novel foldable modular wing according to claim 3, characterized in that: The side edge of the top of the folding wing (15) is mounted on the bottom of the rotating shaft (13); a fixing seat (20) is symmetrically mounted on opposite sides of the two folding wings (15); a second slot (21) is provided in the middle of the fixing seat (20); a clamping block (19) is movably connected in the inner cavity of the first slot (12); and a bottom of the clamping block (19) and a side edge of the fixing seat (20) are both provided with an inclined surface (22).

5. The aircraft with a novel foldable modular wing according to claim 4, characterized in that: The reinforcing component (11) is in communication with the inner cavity of the first clamping slot (12); the first clamping slot (12) and the fixing seat (20) are matched in size; and the clamping block (19) and the second clamping slot (21) are matched in size.

6. The aircraft with a novel foldable modular wing according to claim 5, characterized in that: A fixing rod (16) is installed in the middle of the inner cavity of the reinforcement component (11); a spring (17) is wound around the outer wall of the fixing rod (16); the top of the spring (17) is installed on the top of the inner cavity of the reinforcement component (11); a limiting block (18) is installed on the bottom of the spring (17); the limiting block (18) is installed on the top of a clamping block (19); the limiting block (18) is movably connected in the inner cavity of the reinforcement component (11); the clamping block (19) is movably connected in the first clamping slot (12) and the inner cavity of the reinforcement component (11); and the clamping block (19) and the limiting block (18) are both sleeved on the outer wall of the fixing rod (16).

7. The aircraft with a novel foldable modular wing according to claim 1, characterized in that: Adjustment grooves (6) are symmetrically provided on two sides of opposite sides of the first support rod (1) and the second support rod (5); a double-headed bidirectional screw (7) is rotatably connected in the inner cavity of the adjustment groove (6) at one end; a guide rod is installed in the inner cavity of the other adjustment groove (6); a first gear (8) is installed in the middle of the outer wall of the double-headed bidirectional screw (7); a second gear (9) is meshed with the side of the first gear (8); a servo motor (10) is installed on the side of the second gear (9) through a second rotating shaft; the servo motor (10) is installed on the outer wall of the second support rod (5); and the second gear (9) is rotatably connected in the inner cavity of the second support rod (5).

8. The aircraft with a novel foldable modular wing according to claim 1, characterized in that: An adjustment block (29) is symmetrically installed in the middle of the opposite sides of the mounting blocks (26) at both ends. The adjustment block (29) is movably connected in the inner cavity of the adjustment groove (6). One end of the adjustment block (29) is sleeved on the outer wall of the guide rod, and the other end of the adjustment block (29) is threadedly connected to the outer wall of the double-headed bidirectional screw rod (7).

9. The aircraft with a novel foldable modular wing according to claim 1, characterized in that: There are four composite wing components (23), a positioning groove (27) is provided on the side of the outer mounting block (26), and a positioning block (28) is installed on the side of the inner mounting block (26), and the positioning block (28) and the positioning groove (27) have sizes that match and are located on the same axis.

10. The aircraft with a novel foldable modular wing according to claim 8, characterized in that: The regulating block (29) at one end is mounted on one end of the tail wing (30), and the sides of the tail wing (30) and the composite wing assembly (23) are both provided with a receiving groove (24), and the rotor (25) is rotatably connected in the inner cavity of the composite wing assembly (23) and the tail wing (30) through the receiving groove (24).

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