An aircraft

Abstract

The present application relates to a kind of aircraft, including fuselage, and the left and right sides of fuselage are each provided with wing;Wing includes wing support, wing cloth and winding roller;Wing support includes the heel segment, middle segment and tail segment sequentially distributed from near to far along the left and right direction distance fuselage;One end of heel segment is rotatably connected with fuselage;One end of middle segment is rotatably connected with the other end of heel segment, and the other end of middle segment is rotatably connected with one end of tail segment;Driving mechanism for driving the relative rotation between heel segment and fuselage, between heel segment and middle segment and between middle segment and tail segment is respectively arranged between heel segment and fuselage, between heel segment and middle segment and between middle segment and tail segment, so that wing support can be switched between unfolded state and folded state;Wing cloth is respectively arranged on heel segment and middle segment and passes through gap;Winding roller is rotatably installed on fuselage;One side of wing cloth is connected with winding roller, and the other side of wing cloth is connected with tail segment after passing through gap after wing cloth passes through gap.The present application has the characteristics that wing cloth can be wound when wing support is folded, so that wing cloth will not produce wrinkle.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of flying equipment, in particular to a flying vehicle. BACKGROUND

[0002] In order to make the flying vehicle smaller in size when not in use, so as to save storage space. Some flying vehicles with deformable wings have appeared on the market, the wings of the flying vehicle are in an unfolded state when in use, and in a folded state when not in use, as described in the technical solution of Chinese Patent Application No. 2022111315387, entitled "Hybrid Structure Folding Wing". The wing of such structure is composed of a wing frame and a wing cloth (skin), after the wing frame is folded, the wing cloth will be wrinkled following the folding of the wing, so that the wing cloth is easily damaged after a long period of use, and the service life is short. SUMMARY

[0003] The purpose of the present application is to provide a flying vehicle which has the advantages of simple structure, scientific design, wing cloth can be rolled up when the wing frame is folded, so that the wing cloth will not be wrinkled, long service life, etc.

[0004] The technical solution of the present application is as follows: a flying vehicle, comprising a fuselage, a tail wing is arranged at the rear end of the fuselage, and a wing is arranged on each of the left and right sides of the fuselage; in particular, the wing comprises a wing frame, a wing cloth and a rolling roller; wherein:

[0005] The wing frame comprises a heel section, a middle section and a tail section; the heel section, the middle section and the tail section are sequentially distributed from near to far along the left-right direction from the fuselage, 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; 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 rotation axis of the tail section relative to the middle section are all perpendicular to the horizontal plane; a driving mechanism for driving the relative rotation between the heel section and the fuselage, the heel section and the middle section, and the middle section and the tail section is arranged between each of them, so that the wing frame can be switched between an unfolded state and a folded state along the left-right direction; in the unfolded state, the length direction of the orthogonal projection of the heel section, the middle section and the tail section on the horizontal plane and the front-rear direction form an included angle β in the range of 30°-75°; a wing cloth passing gap is arranged on each of the heel section and the middle section, penetrating through the left and right sides thereof, the thickness of each wing cloth passing gap is 1-3 times the thickness of the wing cloth; the length directions of all wing cloth passing gaps are coplanar, and the common plane is parallel to the horizontal plane;

[0006] Both ends of the rolling roller are rotationally mounted on the fuselage, and the central axis of the rolling roller is arranged along the front-rear direction;

[0007] One side edge of the wing cloth is connected with a winding roller installed on the fuselage, and the other side edge of the wing cloth is connected with the tail section after passing through the gap of the wing cloth of the heel section and the middle section in turn.

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

[0009] In the scheme, one side edge of the wing cloth of the wing is connected with a winding roller installed on the fuselage, and the other side edge of the wing cloth is connected with the tail section after passing through the gap of the wing cloth of the heel section and the middle section in turn. The wing frame of the wing is designed to be telescopic and foldable in the left-right direction, so that the wing cloth can be wound by rotating the winding roller during folding, and the wing cloth is wound on the winding roller after the wing frame is folded. Therefore, the wing cloth will not be wrinkled when the wing is repeatedly folded in use, and the service life of the aircraft is greatly improved.

[0010] Further, the connection between the heel section of each wing and the fuselage is arranged close to the front end of the fuselage; and the winding roller of each wing is a column with a small radius at the front end and a large radius at the rear end.

[0011] Further, each of the heel section and the middle section and the middle section and the tail section is connected by a rotating shaft; the central axis of the rotating shaft is perpendicular to the horizontal plane; and each wing is respectively provided 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] Further, one end of each of the heel section, the middle section and the tail section is connected with a first rotating joint, and the other end of each of the heel section and the middle section is respectively connected with a second rotating joint; the first rotating joint of the heel section of each wing is rotatably connected with the fuselage, the second rotating joint of the heel section is rotatably connected with the first rotating joint of the middle section, and the second rotating joint of the middle section is rotatably connected with the first rotating joint of the tail section.

[0013] Further, the driving mechanism comprises an electric push rod, a first hinged rod and a second hinged rod; one end of the first hinged rod is rotatably connected with one end of the second hinged rod, and one end of the electric push rod is rotatably connected with one of the first hinged rod or the second hinged 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 with the fuselage, and the other end of the second hinged rod is rotatably connected with 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 with the heel section, and the other end of the second hinged rod is rotatably connected with the middle section.

[0016] The other end of the electric push rod is rotatably installed on the middle section or the tail section, the other end of the first hinged rod is rotatably connected with the middle section, and the other end of the second hinged rod is rotatably connected with the tail section.

[0017] Further, the scheme further comprises a winding driving device, the winding driving device is installed on the machine body, and the winding driving device is used for driving the winding rollers of the two wings to rotate in opposite directions.

[0018] Further, the structure of the power source has the following two kinds: one is that the power source comprises a driving motor and a paddle, the driving motor is installed on the wing, and the axis of the rotating shaft of the driving motor is arranged in the front-back direction; the paddle is installed on the rotating shaft of the driving motor.

[0019] Two is that the power source comprises an internal combustion engine and a paddle, the internal combustion engine is installed on the wing, and the axis of the rotating shaft of the internal combustion engine is arranged in the front-back direction; the paddle is installed on the rotating shaft of the internal combustion engine.

[0020] The present application has the advantages of simple structure, scientific design, long service life, etc. BRIEF DESCRIPTION OF DRAWINGS

[0021] Figure 1 It is a schematic diagram of the three-dimensional structure of example 1 in the wing unfolded state.

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

[0023] Figure 3 It is a schematic diagram of the three-dimensional structure of example 1 in the wing unfolded state. Figure 1 It is a schematic diagram of the enlarged structure of the middle A part.

[0024] Figure 4 It is a schematic diagram of the enlarged structure of the middle B part. Figure 2 It is a schematic diagram of the enlarged structure of the middle B part.

[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 in the wing unfolded state.

[0028] Figure 8 It is a schematic diagram of the front view structure of example 2 in the wing unfolded state. It is a schematic diagram of the front view structure of example 2 in the wing unfolded state.

[0029] Figure 9 Structure diagram of example 2 in wing folding state (removing wing cloth).

[0030] Figure 10 Structure diagram of upper heel section of example 2.

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

[0032] Example 1

[0033] As shown in Figure 1 , Figure 2 , Figure 3 , Figure 4 , the aircraft of the present embodiment comprises a fuselage 1, a tail 11 is arranged at the rear end of the fuselage 1, and wings 2 are arranged on the left and right sides of the fuselage 1 respectively; the wing 2 comprises a wing bracket 3, a wing cloth 4 and a winding roller 5; wherein:

[0034] The wing support 3 comprises 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 along the left-right direction from the fuselage 1, one end of the heel section 31 is rotationally connected with the fuselage 1; one end of the middle section 32 is rotationally connected with the other end of the heel section 31, and the other end of the middle section 32 is rotationally connected with 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 rotation axis of the tail section 33 relative to the middle section 32 are all perpendicular to the horizontal plane; a driving mechanism 6 is arranged between each of the heel section 31 and the fuselage 1, the heel section 31 and the middle section 32, and the middle section 32 and the tail section 33 to drive the relative rotation of the two, so that the wing support 3 can be switched between the unfolded state and the folded state along the left-right direction; in the unfolded state of the wing support 3, the included angle β between the length direction of the orthographic projection of each 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 of the wing support 3, the length direction of each of the heel section 31, the middle section 32 and the tail section 33 is parallel to the front-rear direction; a wing cloth passing gap 34 is arranged on each of the heel section 31 and the middle section 32 to pass through the wing cloth 4 on the left and right sides thereof, in this embodiment, the wing cloth passing gap 34 is formed on each of the heel section 31 and the middle section 32, the thickness of each wing cloth passing gap 34 is twice the thickness of the wing cloth 4; the length directions of all the wing cloth passing gaps 34 are coplanar, and the common plane is parallel to the horizontal plane;

[0035] Both ends of the winding roller 5 are rotationally mounted on the fuselage 1, and the central axis of the winding roller 5 is arranged along the front-rear direction;

[0036] One side edge of the wing cloth 4 is connected with the winding roller 5, and the other side edge of the wing cloth 4 sequentially passes through the wing cloth passing gaps 34 of the heel section 31 and the middle section 32 and is then connected with the tail section 33;

[0037] Each of the wings 2 is provided with a power source 7 at the rotationally connected positions of the heel section 31 and the middle section 32 and the middle section 32 and the tail section 33. Such a design enables the wing cloth 4 to be wound by rotating the winding roller 5 during the folding process of the wing support 3, so that the wing cloth 4 is wound around the winding roller 5 after the wing support 3 is folded, which prevents the wing cloth 4 from being wrinkled during repeated folding of the wings 2 in use, and greatly improves the service life of the aircraft.

[0038] In order to enable the winding roller 5 to evenly wind the wing cloth 4, the winding roller 5 is provided with a plurality of winding grooves 51 arranged along the circumferential direction thereof, and the wing cloth 4 is wound around the winding grooves 51. Figure 1 , Figure 2As shown, the connecting part of the heel section 31 of each wing 2 and the fuselage 1 is arranged close to the front end of the fuselage 1; each wing 2 has a winding roller 5 with a small radius at the front end and a large radius at the back end. In order to adapt to the structure of the wing support 3, the wing cloth 4 is in a right-angled trapezoidal structure after being unfolded, with the short bottom side at the front side, and the waist perpendicular to the two bottom sides in the right-angled trapezoidal structure being connected to the winding roller 5. Therefore, after the winding roller 5 with a small radius at the front end and a large radius at the back end winds the wing cloth 4, the wing cloth 4 will not be wrinkled.

[0039] In order to make the structure of the power source 7 more reasonable, as shown in Figure 1 , Figure 2 the heel section 31 of each wing 2 and the intermediate section 32, and the intermediate section 32 and the tail section 33 are respectively connected by a rotating shaft 8; the central axis of the rotating shaft 8 is perpendicular to the horizontal plane; the power source 7 is installed on the rotating shaft 8 between the heel section 31 and the intermediate section 32, and on the rotating shaft 8 between the intermediate section 32 and the tail section 33 of each wing 2, and the power source 7 of the embodiment is installed on the rotating shaft 8 through a mounting bracket 71.

[0040] In order to make the structure of the wing 2 more reasonable, as shown in Figure 1 , Figure 2 one end of each of the heel section 31, the intermediate section 32, and the tail section 33 of each wing 2 is connected with a first rotating joint 35, and the other end of each of the heel section 31 and the intermediate section 32 is connected with a second rotating joint 36; the first rotating joint 35 of the heel section 31 of each wing 2 is connected with the fuselage 1, the second rotating joint 36 of the heel section 31 is connected with the first rotating joint 35 of the intermediate section 32, and the second rotating joint 36 of the intermediate section 32 is connected with 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, as shown in Figure 5 , Figure 6 the driving mechanism 6 includes an electric push rod 61, a first hinged rod 62, and a second hinged rod 63; one end of the first hinged rod 62 is connected with one end of the second hinged rod 63, and one end of the electric push rod 61 is connected with the first hinged 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 installed on the heel section 31, the other end of the first hinged rod 62 is connected with the fuselage 1, and the other end of the second hinged rod 63 is connected with the heel section 31;

[0043] 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 hinged rod 62 is rotatably connected with the heel section 31, and the other end of the second hinged rod 63 is rotatably connected with the middle section 32.

[0044] 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 with the middle section 32, and the other end of the second hinged rod 63 is rotatably connected with the tail section 33.

[0045] In order to facilitate the wing cloth 4 to be rolled up, as shown in Figure 2 、 Figure 4 , the aircraft further comprises a rolling drive device 9; the rolling drive device 9 is mounted on the fuselage 1, and the rolling drive device 9 is used to drive the rolling rollers 5 of the two wings 2 to rotate in opposite directions. The rolling drive device 9 of the aircraft comprises a rolling motor 91, a driving gear 92 and two driven gears 93; the two driven gears 93 correspond to the two rolling rollers 5 one by one, the driven gear 93 is mounted on the corresponding rolling roller 5, the driven gear 93 rotates synchronously with the rolling roller 5, and the two driven gears 93 are engaged; the rolling motor 91 is fixed on the fuselage 1, the driving gear 92 is connected with the rotating shaft of the rolling motor 91, and the driving gear 92 is engaged with one of the driven gears 93.

[0046] In order to make the structure of the power source 7 more reasonable, as shown in Figure 1 、 Figure 2 , the power source 7 comprises a driving motor 72 and a paddle 73, the driving motor 72 is mounted on the wing 2, and the axis of the rotating shaft of the driving motor 72 is arranged in the front-back direction; the paddle 73 is mounted on the rotating shaft of the driving motor 72.

[0047] Embodiment 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 frame of each wing in this embodiment is a double-layer structure. The design of making the wing frame into a double-layer structure makes the structural strength of the aircraft higher, the stability better, and the service life longer. As shown in Figure 7 、 Figure 8 、 Figure 9As shown, 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 the 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, such as Figure 8 As shown, 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 on each wing 2 passing through the gap, such as Figure 10As shown, the upper tip section 311 and the upper middle section 321 of each wing 2 each include two wing spars 38 and two connecting heads 39; the two wing spars 38 of each of the upper tip section 311 and the upper middle section 321 are arranged vertically opposite to each other, and the two ends of each of the two wing spars 38 are connected between the two connecting heads 39, so that each of the upper tip section 311 and the upper middle section 321 forms the wing cloth passing gap between the two wing spars 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 rotatable joint between the heel section and the mid-section and / or the rotatable joint between the mid-section and the tail section. 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.

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 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.

5. An aircraft according to claim 4, 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°.

6. An aircraft according to claim 4, 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.

7. 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 machine body: the other end of the electric push rod is rotatably mounted on the heel section or the machine body, the other end of the first hinge rod is rotatably connected to the machine 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.

8. 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.

9. 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.

10. 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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