Aircraft

Abstract

The aircraft comprises an aircraft body, and wings are arranged on the left side and the right side of the aircraft body respectively. Each wing comprises a wing frame, wing cloth and a winding roller; each wing frame comprises a heel section, a middle section and a tail section which are sequentially distributed from near to far from the fuselage in the left-right direction; one end of the heel section is rotationally connected with the fuselage; one end of the middle section is rotationally connected with the other end of the heel section, and the other end of the middle section is rotationally connected with one end of the tail section; driving mechanisms for driving the heel section and the fuselage, the heel section and the middle section as well as the middle section and the tail section to rotate relatively are respectively arranged between the heel section and the fuselage, between the heel section and the middle section and between the middle section and the tail section, so that the wing frame can be switched between an unfolded state and a folded state; wing cloth penetrating gaps are arranged on the heel section and the middle section respectively; the winding roller is rotationally mounted on the machine body; one side edge of the wing cloth is connected with the winding roller, and the other side edge of the wing cloth penetrates through the wing cloth penetrating gap and then is connected with the tail section. The wing frame has the advantage that when the wing frame is folded, the wing cloth can be rolled, so that the wing cloth cannot be wrinkled.

Description

Technical Field

[0001] The present invention relates to the technical field of flight equipment, in particular to an aircraft. Background Art

[0002] In order to make the volume of the aircraft smaller when not in use, so as to save storage space. There are now some aircraft with deformable wings on the market. The wings of the aircraft are in an unfolded state when in use and in a folded state when not in use, as described in Chinese Patent Application No. 2022111315387, entitled "Hybrid Structure Folding Wing". The wings of such a structure are composed of wing frames and wing cloth (skin). After the wing frames are folded, the wing cloth will wrinkle as the wings are folded, so that the wing cloth is easily damaged after a long period of use and has a short service life. Summary of the invention

[0003] The object of the present invention is to provide an aircraft which has the advantages of simple structure, scientific design, wing cloth that can be rolled up when the wing frame is folded so that the wing cloth will not be wrinkled, and long service life.

[0004] The technical solution of the present invention is implemented as follows: an aircraft comprises a fuselage, a tail wing is arranged at the rear end of the fuselage, and wings are arranged on the left and right sides of the fuselage respectively; in particular, the wings comprise wing frames, wing cloths and winding rollers; wherein:

[0005] The wing frame includes a heel section, a middle section and a tail section; the heel section, the middle section and the tail section are distributed in sequence from near to far from the fuselage along the left and right direction; one end of the heel section is rotatably connected to the fuselage; one end of the middle section is rotatably connected to the other end of the heel section, and the other end of the middle section is rotatably connected to one end of the tail section; the rotation axis of the heel section relative to the fuselage, the rotation axis of the middle section relative to the heel section and the tail section are all perpendicular to the horizontal plane; between the heel section and the fuselage, between the heel section and the middle section, and between the middle section and the tail section Each of the two is provided with a driving mechanism for driving the two to rotate relative to each other, so that the wing frame can be switched between an unfolded state and a folded state in the left-right direction; when the wing frame is in the unfolded 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-back direction is within the range of 30° to 75°; each of the heel section and the middle section is provided with a wing cloth passing through a slit that passes through the left and right sides thereof, and the thickness of each wing cloth passing through the slit is 1 to 3 times the thickness of the wing cloth; the length directions of all the wing cloth passing through the slits are coplanar, and the common plane is parallel to the horizontal plane;

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

[0007] One side of the wing cloth is connected to the winding roller, and the other side of the wing cloth passes through the heel section and the middle section of the wing cloth in sequence, and then passes through the gap and is connected to the tail section;

[0008] Each wing is equipped with a power source at the rotational connection between the heel section and the middle section and / or the rotational connection between the middle section and the tail section.

[0009] One side of the wing cloth of the wing of the present invention is connected to a winding roller installed on the fuselage, and the other side of the wing cloth passes through the heel section of the wing frame and the wing cloth of the middle section in turn and then passes through the gap to be connected to the tail section. The wing frame of the wing is designed to be telescopic and foldable in the left and right directions, so that during the folding process of the wing frame, the wing cloth can be rolled up by rotating the winding roller, so that after the wing frame is folded, the wing cloth is wrapped around the winding roller. In this way, the wing cloth will not be wrinkled even if the wing is repeatedly folded during use, which greatly improves the service life of the aircraft.

[0010] Furthermore, the connection point where the heel section of each wing is rotatably connected to the fuselage is arranged close to the front end of the fuselage; the winding roller of each wing is a cylinder with a small front end radius and a large rear end radius.

[0011] Furthermore, the heel section and the middle section, and the middle section and the tail section of each wing are rotatably connected via a rotating shaft; the central axis of the rotating shaft is perpendicular to the horizontal plane; and each wing is equipped with a power source on the rotating shaft between the heel section and the middle section and / or on the rotating shaft between the middle section and the tail section.

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

[0013] Further, 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 one of the first hinge rod or the second hinge rod;

[0014] On the driving mechanism between the heel section and the fuselage: the other end of the electric push rod is rotatably mounted on the heel section or the fuselage, the other end of the first hinged rod is rotatably connected to the fuselage, and the other end of the second hinged rod is rotatably connected to the heel section;

[0015] On the driving 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 hinged rod is rotatably connected to the heel section, and the other end of the second hinged rod is rotatably connected to the middle section;

[0016] On the driving 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 hinged rod is rotatably connected to the middle section, and the other end of the second hinged rod is rotatably connected to the tail section.

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

[0018] Furthermore, there are two structures of the power source: one is that the power source includes a drive motor and blades, the drive motor is installed on the wing, and the axis of the drive motor's shaft is arranged along the front-to-back direction; the blades are installed on the drive motor's shaft.

[0019] The second type is that the power source includes an internal combustion engine and blades, the internal combustion engine is installed on the wing, the axis of the rotating shaft of the internal combustion engine is arranged along the front-rear direction; and the blades are installed on the rotating shaft of the internal combustion engine.

[0020] The invention has the advantages of simple structure, scientific design, the wing cloth can be rolled up when the wing frame is folded, so that the wing cloth will not be wrinkled, and the service life is long. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 It is a schematic diagram of the three-dimensional structure of Example 1 when the wings are unfolded.

[0022] Figure 2 It is a schematic diagram of the three-dimensional structure of Example 1 with the wing unfolded and the wing cloth removed.

[0023] Figure 3 for Figure 1 Schematic diagram of the enlarged structure of part A.

[0024] Figure 4 for Figure 2 Schematic diagram of the enlarged structure of part B.

[0025] Figure 5 It is a schematic diagram of the structure of the driving mechanism of Example 1 in the folded state.

[0026] Figure 6 It is a schematic diagram of the structure of the driving mechanism of Example 1 in the unfolded state.

[0027] Figure 7 It is a schematic diagram of the three-dimensional structure of Example 2 when the wings are unfolded.

[0028] Figure 8 This is a schematic diagram of the main structure of Example 2 when the wings are unfolded.

[0029] Fig. 9 This is a schematic diagram of the structure of Example 2 when the wing is in a folded state (the wing cloth is removed).

[0030] Fig.10 This is a schematic structural diagram of the upper heel section of Example 2.

[0031] Explanation of the reference numerals: 1-fuselage; 11-tail; 2-wing; 3-wing frame; 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 cloth passing through the gap; 35-first rotating joint; 36-second rotating joint; 37-connecting rod; 38-wing rod member; 39-connecting head; 4-wing cloth; 5-winding roller; 6-driving mechanism; 61-electric push rod; 62-first articulated rod; 63-second articulated rod; 7-power source; 71-mounting frame; 72-driving motor; 73-blade; 8-rotating shaft member; 9-winding drive device; 91-winding motor; 92-driving gear; 93-driven gear. DETAILED DESCRIPTION

[0032] Example 1

[0033] like Figure 1 , Figure 2 , Figure 3 , Figure 4 As shown, an aircraft of this embodiment includes a fuselage 1, a tail 11 is provided at the rear end of the fuselage 1, and wings 2 are provided on the left and right sides of the fuselage 1; the wings 2 include wing frames 3, wing cloths 4 and winding rollers 5; wherein:

[0034] The wing frame 3 includes a heel section 31, a middle section 32 and a tail section 33; the heel section 31, the middle section 32 and the tail section 33 are sequentially distributed from near to far in the left and right direction away from the fuselage 1, one end of the heel section 31 is rotationally connected to the fuselage 1; one end of the middle section 32 is rotationally connected to the other end of the heel section 31, and the other end of the middle section 32 is rotationally connected to one end of the tail section 33; the rotation axis of the heel section 31 relative to the fuselage 1, the rotation axis of the middle section 32 relative to the heel section 31 and the tail section 33 are all perpendicular to the horizontal plane; a driving mechanism 6 for driving the relative rotation of the two is respectively provided between the heel section 31 and the fuselage 1, between the heel section 31 and the middle section 32, and between the middle section 32 and the tail section 33, so that The wing frame 3 can be switched between an unfolded state and a folded state along the left and right directions; when the wing frame 3 is in the unfolded 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°; when the wing frame 3 is 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 cloth passing slit 34 penetrating the left and right sides thereof. In this embodiment, the wing cloth passing slit 34 is formed by processing the heel section 31 and the middle section 32, and the thickness of each wing cloth passing slit 34 is twice the thickness of the wing cloth 4; the length directions of all the wing cloth passing slits 34 are coplanar, and the common plane is parallel to the horizontal plane;

[0035] The two ends of the winding roller 5 are rotatably mounted on the fuselage 1, and the central axis of the winding roller 5 is arranged along the front-to-back direction;

[0036] One side of the wing cloth 4 is connected to the winding roller 5, and the other side of the wing cloth 4 passes through the heel section 31 and the middle section 32 in sequence, and then passes through the gap 34 and is connected to the tail section 33;

[0037] Each wing 2 is provided with a power source 7 at the rotational connection between the heel section 31 and the middle section 32 and at the rotational connection between the middle section 32 and the tail section 33. Such a design allows the wing frame 3 to roll up the wing cloth 4 by rotating the roll-up roller 5 during the folding process, so that after the wing frame 3 is folded, the wing cloth 4 is wound around the roll-up roller 5, so that the wing cloth 4 will not be wrinkled even if the wing 2 is repeatedly folded during use, thereby greatly improving the service life of the aircraft.

[0038] In order to make the reel 5 able to smoothly reel the wing cloth 4, Figure 1 , Figure 2As shown, the connection point where the heel section 31 of each wing 2 is rotatably connected to the fuselage 1 is arranged near the front end of the fuselage 1; the reeling roller 5 of each wing 2 is a cylinder with a small front face radius and a large rear face radius. In order to adapt to the structure of the wing frame 3, the wing cloth 4 is a right-angled trapezoidal structure after unfolding, and the short bottom side of the right-angled trapezoidal structure is at the front side. The waist of the right-angled trapezoidal structure that is perpendicular to the two bottom sides is connected to the reeling roller 5, so that after the reeling roller 5 adopts a structure with a small front face radius and a large rear face radius, the wing cloth 4 will not be wrinkled after the reeling roller 5 reels the wing cloth 4.

[0039] In order to make the structure of the power source 7 installation more reasonable, as Figure 1 , Figure 2 As shown, the heel section 31 and the middle section 32 of each wing 2 and the middle section 32 and the tail section 33 are rotatably connected via a rotating shaft member 8; the central axis of the rotating shaft member 8 is perpendicular to the horizontal plane; each wing 2 is respectively provided with a power source 7 installed on the rotating shaft member 8 between the heel section 31 and the middle section 32 and the rotating shaft member 8 between the middle section 32 and the tail section 33. The power source 7 of this embodiment is installed on the rotating shaft member 8 via a mounting frame 71.

[0040] In order to make the structure of wing 2 more reasonable, Figure 1 , Figure 2 As shown, one end 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 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 rotationally connected to the fuselage 1, the second rotating joint 36 of the heel section 31 is rotationally connected to the first rotating joint 35 of the middle section 32, and the second rotating joint 36 of the middle section 32 is rotationally connected to the first rotating joint 35 of the tail section 33.

[0041] In order to make the structure of the driving mechanism 6 of the aircraft more reasonable, Figure 5 , Figure 6 As shown, the driving 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 driving mechanism 6 between the heel section 31 and the fuselage 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 fuselage 1, and the other end of the second hinge rod 63 is rotatably connected to the heel section 31;

[0043] On the driving 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 driving 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 hinged rod 62 is rotatably connected to the middle section 32, and the other end of the second hinged rod 63 is rotatably connected to the tail section 33.

[0045] In order to facilitate the winding of the wing cloth 4, Figure 2 , Figure 4 As shown, the aircraft also includes a winding drive device 9; the winding drive device 9 is installed on the fuselage 1, and the winding drive device 9 is used to drive the winding rollers 5 of the two wings 2 to rotate in opposite directions. The winding drive device 9 of the aircraft includes a winding motor 91, a driving gear 92 and two driven gears 93; the two driven gears 93 correspond to the two winding rollers 5 one by one, and the driven gears 93 are installed on the corresponding winding rollers 5, and the driven gears 93 rotate synchronously with the winding rollers 5, and the two driven gears 93 are meshed; the winding motor 91 is fixed on the fuselage 1, the driving gear 92 is connected to the rotating shaft of the winding motor 91, and the driving gear 92 is meshed with one of the driven gears 93.

[0046] In order to make the structure of the power source 7 more reasonable, Figure 1 , Figure 2 As shown, the power source 7 includes a driving motor 72 and a blade 73 . The driving motor 72 is installed on the wing 2 , and the axis of the rotating shaft of the driving motor 72 is arranged along the front-back direction; the blade 73 is installed on the rotating shaft of the driving motor 72 .

[0047] Example 2

[0048] The difference between this embodiment and embodiment 1 is that each wing of embodiment 1 is a single-layer structure, while the wing frames of each wing of this embodiment are double-layer structures. The double-layer structure of the wing frames makes the aircraft have higher structural strength, better stability and longer service life. Figure 7 , Figure 8 , Fig. 9As shown, the heel section 31 of each wing 2 of 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 a slit for the wing cloth to pass through is formed 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 middle section 32 includes an upper middle section 321 and a lower middle section 322; the central axis of the upper middle section 321 is coplanar with the central axis of the upper heel section 311, and the coplanar surface is parallel to the horizontal plane; a slit for the wing cloth to pass through is formed on the upper middle section 321; the lower middle section 322 is located below the upper middle section 321, and the upper middle section 321 and the lower middle section 322 are connected together by a connecting rod 37; one end of the upper middle section 321 is rotatably connected to the other end of the upper heel section 311, and one end of the lower middle section 322 is rotatably connected to the other end of the lower heel section 312, and the rotation axis of the upper middle section 321 relative to the upper heel section 311 and the rotation axis of the lower middle section 322 relative to the lower heel section 312 are colinear;

[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 heel section 311, and the coplanar surface 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, and the rotation axis of the upper tail section 331 relative to the upper middle section 321 is colinear with the rotation axis of the lower tail section 332 relative to the lower middle section 322.

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

[0052] In order to facilitate the formation of the wing cloth on each wing 2 through the gap, such as Fig.10As shown, the upper heel section 311 and the upper middle section 321 of each wing 2 each include two wing rods 38 and two connecting heads 39; the two wing rods 38 of the upper heel section 311 and the upper middle section 321 are arranged vertically opposite to each other, and the two ends of the two wing rods 38 are respectively connected between the two connecting heads 39, so that the upper heel section 311 and the upper middle section 321 each form the wing cloth passing gap between the two wing rods 38.

Claims

1. An aircraft, comprising a fuselage, a tail fin at the rear end of the fuselage, and wings on the left and right sides of the fuselage; characterized in that: The wing comprises a wing frame, a wing cloth and a winding roller; wherein: The wing frame includes a heel section, a middle section and a tail section; the heel section, the middle section and the tail section are distributed in sequence from near to far from the fuselage along the left and right direction; one end of the heel section is rotatably connected to the fuselage; one end of the middle section is rotatably connected to the other end of the heel section, and the other end of the middle section is rotatably connected to one end of the tail section; the rotation axis of the heel section relative to the fuselage, the rotation axis of the middle section relative to the heel section and the tail section are all perpendicular to the horizontal plane; between the heel section and the fuselage, between the heel section and the middle section, and between the middle section and the tail section Each of the two is provided with a driving mechanism for driving the two to rotate relative to each other, so that the wing frame can be switched between an unfolded state and a folded state in the left-right direction; when the wing frame is in the unfolded 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-back direction is within the range of 30° to 75°; each of the heel section and the middle section is provided with a wing cloth passing through a slit that passes through the left and right sides thereof, and the thickness of each wing cloth passing through the slit is 1 to 3 times the thickness of the wing cloth; the length directions of all the wing cloth passing through the slits are coplanar, and the common plane is parallel to the horizontal plane; The two ends of the winding roller are rotatably mounted on the machine body, and the central axis of the winding roller is arranged along the front-back direction; One side of the wing cloth is connected to the winding roller, and the other side of the wing cloth passes through the heel section and the middle section of the wing cloth in sequence, and then passes through the gap and is connected to the tail section; Each wing is equipped with a power source at the rotational connection between the heel section and the middle section and / or the rotational connection between the middle section and the tail section.

2. An aircraft according to claim 1, characterized in that: The connection point where the heel section of each wing is rotatably connected to the fuselage is arranged close to the front end of the fuselage; the winding roller of each wing is a cylinder with a small front end surface radius and a large rear end surface radius.

3. An aircraft according to claim 1, characterized in that: The heel section and the middle section, and the middle section and the tail section of each wing are rotatably connected via a rotating shaft; the central axis of the rotating shaft is perpendicular to the horizontal plane; each wing is equipped with a power source on the rotating shaft between the heel section and the middle section and / or on the rotating shaft between the middle section and the tail section.

4. An aircraft according to claim 1, characterized in that: One end of the heel section, middle section and tail section of each wing is connected to a first rotating joint, and the other end of the heel section and middle section is connected to a second rotating joint; the first rotating joint of the heel section of each wing is rotationally connected to the fuselage, the second rotating joint of the heel section is rotationally connected to the first rotating joint of the middle section, and the second rotating joint of the middle section is rotationally connected to the first rotating joint of the tail section.

5. An aircraft according to claim 1 or 4, characterized in that: The heel section of each wing 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 a slit for the wing cloth to pass through is formed on the upper heel section; the lower heel section is located below the upper heel section, and the upper heel section and the lower heel section are connected together by a connecting rod; one end of each of the upper heel section and the lower heel section is rotatably connected to the fuselage, and the rotation axes of the upper heel section and the lower heel section relative to the fuselage are collinear; The middle section comprises 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; a slit for the wing cloth to pass through is formed 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, and the rotation axis of the upper middle section relative to the upper heel section is colinear 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 heel 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, and the rotation axis of the upper tail section relative to the upper middle section is colinear with the rotation axis 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 central axis of each of the lower heel section, the lower middle section and the lower tail section of each wing and the horizontal plane is in the range of 5° to 20°.

7. An aircraft according to claim 5, characterized in that: The upper heel section and the upper middle section of each wing respectively include two wing rods and two connecting heads; the two wing rods of the upper heel section and the upper middle section are respectively arranged vertically opposite to each other, and the two ends of each wing rod are respectively connected between the two connecting heads, so that the upper heel section and the upper middle section respectively form the wing cloth passing gap between the two wing rods.

8. An aircraft according to claim 1, characterized in that: The driving mechanism comprises 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 one of the first hinge rod or the second hinge rod; On the driving mechanism between the heel section and the fuselage: the other end of the electric push rod is rotatably mounted on the heel section or the fuselage, the other end of the first hinged rod is rotatably connected to the fuselage, and the other end of the second hinged rod is rotatably connected to the heel section; On the driving 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 hinged rod is rotatably connected to the heel section, and the other end of the second hinged rod is rotatably connected to the middle section; On the driving 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 hinged rod is rotatably connected to the middle section, and the other end of the second hinged 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 installed on the fuselage, and the winding drive device 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 comprises a driving motor and blades. The driving motor is mounted on the wing, and the axis of the rotating shaft of the driving motor is arranged along the front-rear direction; the blades are mounted on the rotating shaft of the driving motor.

11. An aircraft according to claim 1 or 3, characterized in that: The power source comprises an internal combustion engine and blades. The internal combustion engine is mounted on the wing, and the axis of the rotating shaft of the internal combustion engine is arranged along the front-rear direction; the blades are mounted on the rotating shaft of the internal combustion engine.

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