Aircraft

Abstract

An aircraft, comprising a fuselage (1), wherein wings (2) are respectively provided on the left and right sides of the fuselage (1); each wing (2) comprises a wing frame (3), a wing fabric (4) and a winding roller (5); the wing frame (3) comprises a root section (31), a middle section (32) and a tail section (33) which are sequentially distributed from near to far relative to the fuselage (1) in the left-right direction; one end of the root section (31) is rotatably connected to the fuselage (1); one end of the middle section (32) is rotatably connected to the other end of the root section (31), and the other end of the middle section (32) is rotatably connected to one end of the tail section (33); drive mechanisms (6) are respectively provided between the root section (31) and the fuselage (1), between the root section (31) and the middle section (32), and between the middle section (32) and the tail section (33), so as to drive the respective two components to rotate relative to each other, such that the wing frame (3) can be switched between an unfolded state and a folded state; a wing fabric passage slot (34) is provided in each of the root section (31) and the middle section (32); the winding roller (5) is rotatably mounted on the fuselage (1); and one side edge of the wing fabric (4) is connected to the winding roller (5), and the other side edge of the wing fabric (4) passes through the wing fabric passage slot (34) and is then connected to the tail section (33).

Description

A type of aircraft Technical Field

[0001] This invention relates to the field of flight equipment technology, and in particular to an aircraft. Background Technology

[0002] To reduce the size of aircraft when not in use and save storage space, some aircraft with deformable wings have appeared on the market. The wings of these aircraft, such as the one described in Chinese patent application number 2022111315387 entitled "Hybrid Structure Folding Wing," are deployed when in use and folded when not in use. This type of wing consists of a wingframe and wing fabric (skin). When the wingframe folds, the wing fabric wrinkles along with the wing, making it prone to damage and shortening its lifespan over time. Technical issues

[0003] The purpose of this invention is to provide an aircraft with advantages such as simple structure, scientific design, wing fabric that can be rolled up when the wing frame is folded so that the wing fabric will not wrinkle, and long service life. Technical solutions

[0004] The technical solution of this invention is implemented as follows: an aircraft includes a fuselage, a tail fin at the rear end of the fuselage, and wings on both the left and right sides of the fuselage; specifically, each wing includes a wing frame, wing fabric, and a take-up roller; wherein:

[0005] The wingframe includes a heel section, a mid-section, and a tail section. These three sections are distributed sequentially from closest to furthest from the fuselage in a left-right direction. One end of the heel section is rotatably connected to the fuselage. One end of the mid-section is rotatably connected to the other end of the heel section, and the other end of the mid-section is rotatably connected to one end of the tail section. The rotation axis of the heel section relative to the fuselage, and the rotation axes of the mid-section relative to each of the heel and tail sections, are all perpendicular to the horizontal plane. The connections between the heel section and the fuselage, between the heel section and the mid-section, and between the mid-section and the tail section are also perpendicular. Each section is equipped with a drive mechanism that drives the relative rotation of the two sections, so that the wing can switch between an extended state and a folded state in the left-right direction; in the extended state, the angle β formed by the length direction of the orthographic projection of the heel section, the middle section and the tail section on the horizontal plane and the front-rear direction is within the range of 30° to 75°; the heel section and the middle section are each provided with wing fabric passing through the gaps on their left and right sides, and the thickness of each wing fabric passing through the gaps is 1 to 3 times the thickness of the wing fabric; the length direction of all the wing fabrics passing through the gaps is coplanar, and the coplanar plane is parallel to the horizontal plane;

[0006] The two ends of the take-up roller are rotatably mounted on the machine body, and the central axis of the take-up roller is arranged in the front-to-back direction;

[0007] One side of the wing fabric is connected to the take-up roller, and the other side of the wing fabric passes through the heel section and the middle section in sequence, and then connects to the tail section after passing through the gap.

[0008] Each wing has a power source installed at the swivel joint between the heel section and the mid-section and / or the swivel joint between the mid-section and the tail section.

[0009] In this design, one side of the wing fabric is connected to a take-up roller mounted on the fuselage. The other side of the wing fabric passes through the heel section of the wing frame, and the middle section of the wing fabric passes through a gap before connecting to the tail section. The wing frame is designed to extend and fold in the left and right directions, allowing the wing fabric to be rolled up by rotating the take-up roller during the folding process. As a result, after the wing frame is folded, the wing fabric is wrapped around the take-up roller. This design ensures that the wing fabric will not wrinkle even after repeated folding during use, greatly improving the service life of the aircraft.

[0010] Furthermore, the connection points where the heel sections of each wing rotate to connect with the fuselage are located near the front end of the fuselage; the take-up rollers of each wing are all cylindrical objects with a small front radius and a large rear radius.

[0011] Furthermore, the heel section and the middle section of each wing are rotatably connected by a pivot joint; the central axis of the pivot joint is perpendicular to the horizontal plane; each wing has a power source installed on the pivot joint between the heel section and the middle section and / or on the pivot joint between the middle section and the tail section.

[0012] Furthermore, each of the heel section, mid-section, and tail section of each wing is connected to a first rotating joint at one end, and the other end of each of the heel section and mid-section is connected to a second rotating joint; the first rotating joint of the heel section of each wing is rotatably connected to the fuselage, the second rotating joint of the heel section is rotatably connected to the first rotating joint of the mid-section, and the second rotating joint of the mid-section is rotatably connected to the first rotating joint of the tail section.

[0013] Furthermore, the driving mechanism includes an electric push rod, a first hinge rod, and a second hinge rod; one end of the first hinge rod is rotatably connected to one end of the second hinge rod, and one end of the electric push rod is rotatably connected to either the first hinge rod or the second hinge rod.

[0014] On the drive mechanism between the heel section and the body: the other end of the electric push rod is rotatably mounted on the heel section or the body, the other end of the first hinge rod is rotatably connected to the body, and the other end of the second hinge rod is rotatably connected to the heel section.

[0015] On the drive mechanism between the heel section and the middle section: the other end of the electric push rod is rotatably mounted on the heel section or the middle section, the other end of the first hinge rod is rotatably connected to the heel section, and the other end of the second hinge rod is rotatably connected to the middle section.

[0016] On the drive mechanism between the middle section and the tail section: the other end of the electric push rod is rotatably mounted on the middle section or the tail section, the other end of the first hinge rod is rotatably connected to the middle section, and the other end of the second hinge rod is rotatably connected to the tail section.

[0017] Furthermore, this solution also includes a winding drive device; the winding drive device is mounted on the fuselage and is used to drive the winding rollers of the two wings to rotate in opposite directions.

[0018] Furthermore, the power source has the following two structures: one is that the power source includes a drive motor and a propeller, the drive motor is mounted on the wing, and the axis of the drive motor's shaft is arranged in the front-to-back direction; the propeller is mounted on the drive motor's shaft.

[0019] The second type is where the power source includes an internal combustion engine and a propeller. The internal combustion engine is mounted on the wing, and the axis of the internal combustion engine's shaft is arranged in the front-to-back direction. The propeller is mounted on the internal combustion engine's shaft. Beneficial effects

[0020] The beneficial effects of this invention are: simple structure, scientific design, the wing fabric can be rolled up when the wing frame is folded so that the wing fabric will not wrinkle, and long service life. Attached Figure Description

[0021] Figure 1 is a three-dimensional structural diagram of Embodiment 1 in the wing-deployed state.

[0022] Figure 2 is a three-dimensional structural diagram of Embodiment 1 with the wings deployed and the wing fabric removed.

[0023] Figure 3 is an enlarged structural diagram of part A in Figure 1.

[0024] Figure 4 is an enlarged structural diagram of part B in Figure 2.

[0025] Figure 5 is a schematic diagram of the drive mechanism of Embodiment 1 in the folded state.

[0026] Figure 6 is a schematic diagram of the drive mechanism of Embodiment 1 in the unfolded state.

[0027] Figure 7 is a three-dimensional structural diagram of Embodiment 2 in the wing-deployed state.

[0028] Figure 8 is a front view structural diagram of Embodiment 2 in the wing deployment state.

[0029] Figure 9 is a schematic diagram of the structure of Example 2 in the folded wing state (wing fabric removed).

[0030] Figure 10 is a structural schematic diagram of the upper heel section of Embodiment 2.

[0031] Explanation of reference numerals in the attached drawings: 1-Fuselage; 11-Tail; 2-Wing; 3-Wingframe; 31-Heel section; 311-Upper heel section; 312-Lower heel section; 32-Middle section; 321-Upper middle section; 322-Lower middle section; 33-Tail section; 331-Upper tail section; 332-Lower tail section; 34-Wing fabric passing through the gap; 35-First rotating joint; 36-Second rotating joint; 37-Connecting rod; 38-Wing rod; 39-Connector; 4-Wing fabric; 5-Rewinding roller; 6-Drive mechanism; 61-Electric push rod; 62-First hinge rod; 63-Second hinge rod; 7-Power source; 71-Mounting frame; 72-Drive motor; 73-Blade; 8-Shaft component; 9-Rewinding drive device; 91-Rewinding motor; 92-Drive gear; 93-Driven gear. Embodiments of the present invention

[0032] Example 1

[0033] As shown in Figures 1, 2, 3, and 4, an aircraft according to this embodiment includes a fuselage 1, a tail fin 11 at the rear end of the fuselage 1, and wings 2 on both the left and right sides of the fuselage 1; each wing 2 includes a wing frame 3, a wing fabric 4, and a take-up roller 5; wherein:

[0034] The wing frame 3 includes a heel section 31, a mid-section 32, and a tail section 33. These three sections are distributed sequentially from near to far from the fuselage 1 along the left-right direction. One end of the heel section 31 is rotatably connected to the fuselage 1. One end of the mid-section 32 is rotatably connected to the other end of the heel section 31, and the other end of the mid-section 32 is rotatably connected to one end of the tail section 33. The rotation axis of the heel section 31 relative to the fuselage 1, and the rotation axes of the mid-section 32 relative to the heel section 31 and tail section 33 are all perpendicular to the horizontal plane. Drive mechanisms 6 are provided between the heel section 31 and the fuselage 1, between the heel section 31 and the mid-section 32, and between the mid-section 32 and the tail section 33 to drive their relative rotation. The wing frame 3 can switch between an extended state and a folded state along the left and right directions. In the extended state, the angle β formed by the length direction of the orthographic projection of the heel section 31, the middle section 32, and the tail section 33 on the horizontal plane and the front-rear direction is 45°. In the folded state, the length direction of the heel section 31, the middle section 32, and the tail section 33 is parallel to the front-rear direction. The heel section 31 and the middle section 32 are each provided with a wing fabric through-gap 34 that runs through their left and right sides. In this embodiment, the wing fabric through-gap 34 is formed by processing the heel section 31 and the middle section 32. The thickness of each wing fabric through-gap 34 is twice the thickness of the wing fabric 4. The length direction of all the wing fabrics through-gap 34 is coplanar, and the coplanar plane is parallel to the horizontal plane.

[0035] The two ends of the take-up roller 5 are rotatably mounted on the machine body 1, and the central axis of the take-up roller 5 is arranged in the front-back direction.

[0036] One side of the wing fabric 4 is connected to the take-up roller 5, and the other side of the wing fabric 4 passes through the wing fabric through the gap 34 in sequence through the heel section 31 and the middle section 32 and is connected to the tail section 33.

[0037] Each wing 2 has a power source 7 installed at the rotatable connection between the heel section 31 and the mid-section 32, and at the rotatable connection between the mid-section 32 and the tail section 33. This design allows the wing fabric 4 to be wound up by rotating the winding roller 5 during the folding process of the wing frame 3. As a result, after the wing frame 3 is folded, the wing fabric 4 is wrapped around the winding roller 5. This prevents the wing fabric 4 from wrinkling even after repeated folding of the wing 2 during use, greatly improving the service life of the aircraft.

[0038] To ensure that the take-up roller 5 can smoothly wind up the wing fabric 4, as shown in Figures 1 and 2, the connection point between the heel section 31 of each wing 2 and the fuselage 1 is located near the front end of the fuselage 1; the take-up roller 5 of each wing 2 is a column with a small front radius and a large rear radius. To accommodate the structure of the wing frame 3, the unfolded wing fabric 4 is a right-angled trapezoidal structure, with the short base of the right-angled trapezoidal structure at the front. The waist of the right-angled trapezoidal structure, perpendicular to the two bases, is connected to the take-up roller 5. As a result, with the take-up roller 5 having a small front radius and a large rear radius, the wing fabric 4 will not wrinkle after being wound up by the take-up roller 5.

[0039] To make the installation structure of the power source 7 more reasonable, as shown in Figures 1 and 2, the heel section 31 and the middle section 32 of each wing 2 are rotatably connected by a pivot 8; the central axis of the pivot 8 is perpendicular to the horizontal plane; each wing 2 is equipped with a power source 7 on the pivot 8 between the heel section 31 and the middle section 32 and on the pivot 8 between the middle section 32 and the tail section 33. In this embodiment, the power source 7 is mounted on the pivot 8 by a mounting bracket 71.

[0040] To make the structure of the wing 2 more reasonable, as shown in Figures 1 and 2, one end of each of the heel section 31, the middle section 32, and the tail section 33 of each wing 2 is connected to a first rotating joint 35, and the other end of each of the heel section 31 and the middle section 32 is connected to a second rotating joint 36. The first rotating joint 35 of the heel section 31 of each wing 2 is rotatably connected to the fuselage 1, the second rotating joint 36 of the heel section 31 is rotatably connected to the first rotating joint 35 of the middle section 32, and the second rotating joint 36 of the middle section 32 is rotatably connected to the first rotating joint 35 of the tail section 33.

[0041] To make the structure of the drive mechanism 6 of this aircraft more reasonable, as shown in Figures 5 and 6, the drive mechanism 6 includes an electric push rod 61, a first hinge rod 62 and a second hinge rod 63; one end of the first hinge rod 62 is rotatably connected to one end of the second hinge rod 63, and one end of the electric push rod 61 is rotatably connected to the first hinge rod 62.

[0042] On the drive mechanism 6 between the heel section 31 and the body 1: the other end of the electric push rod 61 is rotatably mounted on the heel section 31, the other end of the first hinge rod 62 is rotatably connected to the body 1, and the other end of the second hinge rod 63 is rotatably connected to the heel section 31.

[0043] On the drive mechanism 6 between the heel section 31 and the middle section 32: the other end of the electric push rod 61 is rotatably mounted on the middle section 32, the other end of the first hinge rod 62 is rotatably connected to the heel section 31, and the other end of the second hinge rod 63 is rotatably connected to the middle section 32.

[0044] On the drive mechanism 6 between the middle section 32 and the tail section 33: the other end of the electric push rod 61 is rotatably mounted on the middle section 32, the other end of the first hinge rod 62 is rotatably connected to the middle section 32, and the other end of the second hinge rod 63 is rotatably connected to the tail section 33.

[0045] To facilitate the winding of the wing fabric 4, as shown in Figures 2 and 4, this aircraft also includes a winding drive device 9. The winding drive device 9 is mounted on the fuselage 1 and drives the winding rollers 5 of the two auxiliary wings 2 to rotate in opposite directions. The winding drive device 9 includes a winding motor 91, a drive gear 92, and two driven gears 93. Each of the two driven gears 93 corresponds to one of the two winding rollers 5. The driven gears 93 are mounted on their corresponding winding rollers 5, rotate synchronously with the winding rollers 5, and mesh with each other. The winding motor 91 is fixed to the fuselage 1, and the drive gear 92 is connected to the shaft of the winding motor 91, meshing with one of the driven gears 93.

[0046] To make the structure of the power source 7 more reasonable, as shown in Figures 1 and 2, the power source 7 includes a drive motor 72 and a blade 73. The drive motor 72 is mounted on the wing 2, and the axis of the drive motor 72's rotating shaft is arranged in the front-rear direction; the blade 73 is mounted on the rotating shaft of the drive motor 72.

[0047] Example 2

[0048] The difference between this embodiment and Embodiment 1 is that each wing in Embodiment 1 has a single-layer structure, while the wing frame of each wing in this embodiment has a double-layer structure. This double-layer wing frame design makes the aircraft structurally stronger, more stable, and has a longer service life. As shown in Figures 7, 8, and 9, the heel section 31 of each wing 2 in this embodiment includes an upper heel section 311 and a lower heel section 312; the central axis of the upper heel section 311 is parallel to the horizontal plane, and the wing fabric passes through a gap on the upper heel section 311; the lower heel section 312 is located below the upper heel section 311, and the upper heel section 311 and the lower heel section 312 are connected together by a connecting rod 37; one end of each of the upper heel section 311 and the lower heel section 312 is rotatably connected to the fuselage 1, and the rotation axes of the upper heel section 311 and the lower heel section 312 relative to the fuselage 1 are collinear;

[0049] The intermediate section 32 includes an upper intermediate section 321 and a lower intermediate section 322; the central axis of the upper intermediate section 321 is coplanar with the central axis of the upper heel section 311, and the coplanar plane is parallel to the horizontal plane; the wing fabric passes through a gap on the upper intermediate section 321; the lower intermediate section 322 is located below the upper intermediate section 321, and the upper intermediate section 321 and the lower intermediate section 322 are connected together by a connecting rod 37; one end of the upper intermediate section 321 is rotatably connected to the other end of the upper heel section 311, and one end of the lower intermediate section 322 is rotatably connected to the other end of the lower heel section 312; the rotation axis of the upper intermediate section 321 relative to the upper heel section 311 is collinear with the rotation axis of the lower intermediate section 322 relative to the lower heel section 312.

[0050] The tail section 33 includes an upper tail section 331 and a lower tail section 332; the central axis of the upper tail section 331 is coplanar with the central axis of the upper tail section 311, and the coplanar plane is parallel to the horizontal plane; the lower tail section 332 is located below the upper tail section 331, and one end of the lower tail section 332 is connected to one end of the upper tail section 331; the other end of the upper tail section 331 is rotatably connected to the other end of the upper middle section 321, and the other end of the lower tail section 332 is rotatably connected to the other end of the lower middle section 322; the axis of rotation of the upper tail section 331 relative to the upper middle section 321 is collinear with the axis of rotation of the lower tail section 332 relative to the lower middle section 322.

[0051] To make the structure of this embodiment more reasonable, as shown in Figure 8, the angle α formed by the central axis of each of the lower heel section 312, lower middle section 322 and lower tail section 332 of each wing 2 and the horizontal plane is in the range of 5° to 20°. In this embodiment, the angle α formed by the central axis of each of the lower heel section 312, lower middle section 322 and lower tail section 332 of each wing 2 and the horizontal plane is 10°.

[0052] To facilitate the formation of the wing fabric passing through the gap on each wing 2, as shown in Figure 10, each of the upper heel section 311 and upper middle section 321 of each wing 2 includes two wing rods 38 and two connectors 39; the two wing rods 38 of each of the upper heel section 311 and upper middle section 321 are arranged vertically opposite each other, and the two ends of each of the two wing rods 38 are respectively connected between the two connectors 39, so that the upper heel section 311 and upper middle section 321 each form the gap through which the wing fabric passes between the two wing rods 38.

Claims

1. An aircraft, comprising a fuselage, a tail fin at the rear of the fuselage, and wings on the left and right sides of the fuselage; characterized in that: The wing includes a wing frame, wing fabric, and a take-up roller; wherein: The wingframe includes a heel section, a mid-section, and a tail section. These three sections are distributed sequentially from closest to furthest from the fuselage in a left-right direction. One end of the heel section is rotatably connected to the fuselage. One end of the mid-section is rotatably connected to the other end of the heel section, and the other end of the mid-section is rotatably connected to one end of the tail section. The rotation axis of the heel section relative to the fuselage, and the rotation axes of the mid-section relative to each of the heel and tail sections, are all perpendicular to the horizontal plane. The connections between the heel section and the fuselage, between the heel section and the mid-section, and between the mid-section and the tail section are also perpendicular. Each section is equipped with a drive mechanism that drives the relative rotation of the two sections, so that the wing can switch between an extended state and a folded state in the left-right direction; in the extended state, the angle β formed by the length direction of the orthographic projection of the heel section, the middle section and the tail section on the horizontal plane and the front-rear direction is within the range of 30° to 75°; the heel section and the middle section are each provided with wing fabric passing through the gaps on their left and right sides, and the thickness of each wing fabric passing through the gaps is 1 to 3 times the thickness of the wing fabric; the length direction of all the wing fabrics passing through the gaps is coplanar, and the coplanar plane is parallel to the horizontal plane; The two ends of the take-up roller are rotatably mounted on the machine body, and the central axis of the take-up roller is arranged in the front-to-back direction; One side of the wing fabric is connected to the take-up roller, and the other side of the wing fabric passes through the heel section and the middle section in sequence, and then connects to the tail section after passing through the gap. Each wing has a power source installed at the swivel joint between the heel section and the mid-section and / or the swivel joint between the mid-section and the tail section.

2. The aircraft according to claim 1, characterized in that: The connection points between the heel section of each wing and the fuselage are located near the front end of the fuselage; the take-up rollers of each wing are all cylindrical bodies with a small front radius and a large rear radius.

3. The aircraft according to claim 1, characterized in that: Each wing is rotatably connected to the heel section and the middle section, and to the tail section, via a pivot joint; the central axis of the pivot joint is perpendicular to the horizontal plane; each wing has a power source mounted on the pivot joint between the heel section and the middle section and / or on the pivot joint between the middle section and the tail section.

4. An aircraft according to claim 1, characterized in that: Each wing has a first rotating joint connected to one end of its heel section, middle section, and tail section, and a second rotating joint connected to the other end of each heel section and middle section. The first rotating joint of the heel section of each wing is rotatably connected to the fuselage, the second rotating joint of the heel section is rotatably connected to the first rotating joint of the middle section, and the second rotating joint of the middle section is rotatably connected to the first rotating joint of the tail section.

5. An aircraft according to claim 1 or 4, characterized in that: Each wing heel section includes an upper heel section and a lower heel section; the central axis of the upper heel section is parallel to the horizontal plane, and the wing fabric passes through a gap formed on the upper heel section; the lower heel section is located below the upper heel section, and the upper and lower heel sections are connected together by a connecting rod; one end of each of the upper and lower heel sections is rotatably connected to the fuselage, and the rotation axes of the upper and lower heel sections relative to the fuselage are collinear; The middle section includes an upper middle section and a lower middle section; the central axis of the upper middle section is coplanar with the central axis of the upper heel section, and the coplanar plane is parallel to the horizontal plane; the wing fabric is formed through a gap on the upper middle section; the lower middle section is located below the upper middle section, and the upper middle section and the lower middle section are connected together by a connecting rod; one end of the upper middle section is rotatably connected to the other end of the upper heel section, and one end of the lower middle section is rotatably connected to the other end of the lower heel section; the rotation axis of the upper middle section relative to the upper heel section is collinear with the rotation axis of the lower middle section relative to the lower heel section. The tail section includes an upper tail section and a lower tail section; the central axis of the upper tail section is coplanar with the central axis of the upper tail section, and the coplanar plane is parallel to the horizontal plane; the lower tail section is located below the upper tail section, and one end of the lower tail section is connected to one end of the upper tail section; the other end of the upper tail section is rotatably connected to the other end of the upper middle section, and the other end of the lower tail section is rotatably connected to the other end of the lower middle section; the axis of rotation of the upper tail section relative to the upper middle section is collinear with the axis of rotation of the lower tail section relative to the lower middle section.

6. An aircraft according to claim 5, characterized in that: The angle α formed by the centerline of each wing's lower heel section, lower middle section, and lower tail section with the horizontal plane is in the range of 5° to 20°.

7. An aircraft according to claim 5, characterized in that: Each wing's upper heel section and upper middle section includes two wing rods and two connectors. The two wing rods of the upper heel section and upper middle section are arranged vertically opposite each other, and the two ends of each wing rod are connected between the two connectors, so that the wing fabric passes through the gap between the two wing rods in the upper heel section and upper middle section.

8. An aircraft according to claim 1, characterized in that: The driving mechanism includes an electric push rod, a first hinge rod, and a second hinge rod; one end of the first hinge rod is rotatably connected to one end of the second hinge rod, and one end of the electric push rod is rotatably connected to either the first hinge rod or the second hinge rod. On the drive mechanism between the heel section and the body: the other end of the electric push rod is rotatably mounted on the heel section or the body, the other end of the first hinge rod is rotatably connected to the body, and the other end of the second hinge rod is rotatably connected to the heel section. On the drive mechanism between the heel section and the middle section: the other end of the electric push rod is rotatably mounted on the heel section or the middle section, the other end of the first hinge rod is rotatably connected to the heel section, and the other end of the second hinge rod is rotatably connected to the middle section. On the drive mechanism between the middle section and the tail section: the other end of the electric push rod is rotatably mounted on the middle section or the tail section, the other end of the first hinge rod is rotatably connected to the middle section, and the other end of the second hinge rod is rotatably connected to the tail section.

9. An aircraft according to claim 1, characterized in that: It also includes a winding drive device; the winding drive device is mounted on the fuselage and is used to drive the winding rollers of the two wings to rotate in opposite directions.

10. An aircraft according to claim 1 or 3, characterized in that: The power source includes a drive motor and blades. The drive motor is mounted on the wing, and the axis of the drive motor's shaft is arranged in the front-to-back direction. The blades are mounted on the drive motor's shaft.

11. An aircraft according to claim 1 or 3, characterized in that: The power source includes an internal combustion engine and a propeller. The internal combustion engine is mounted on the wing, and the axis of the internal combustion engine's shaft is arranged in the front-to-back direction. The propeller is mounted on the internal combustion engine's shaft.

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