Composite folding wing and split type aircraft

Abstract

The invention relates to the technical field of aircrafts, and provides a composite folding wing and a split type aircraft.The composite folding wing comprises a first wing body, a second wing body and a connecting piece; the first wing body is provided with a first rotor wing; the second wing body is provided with a second rotor wing; one end of the connecting piece is connected with one end of the first wing body through the first folding mechanism, and the other end is connected with one end of the second wing body through the second folding mechanism; the composite folding wing comprises a first form and a second form which can be switched mutually; in the first form, the first wing body, the connecting piece and the second wing body extend in the same straight line direction; and in the second form, the first wing body and the second wing body are correspondingly arranged in parallel at an interval, and the connecting piece is respectively vertical to the first wing body and the second wing body. The first wing body and the second wing body can be switched through the connecting piece, and the beneficial effect that the aircraft can be flexibly switched between vertical take-off and landing in a narrow space and efficient cruising is achieved.

Description

Technical Field

[0001] The present disclosure relates to the technical field of aircraft, and in particular to a composite folding wing and a split aircraft. Background Art

[0002] Wing folding technology is mostly used in fixed-wing aircraft. By folding the wings, the aircraft can take off or be stored in a narrow place, and the folding wings are generally achieved through a motor hinge combination or other mechanical structures.

[0003] If the existing wing folding technology is directly applied to composite wing aircraft, it may cause problems such as interference in the movement of the rotors. In addition, the rotors of composite wing aircraft are often distributed at both the proximal and distal ends of the wings. If only the wings at the outer ends of the rotors are folded, the effect of reducing the wingspan cannot be achieved. In particular, during vertical takeoff and landing of composite wing aircraft, if the size of the takeoff and landing platform is to be reduced, the wings should be folded during the transition from vertical takeoff and landing to level flight. If the part with the rotors is simply folded together, it will bring great challenges to the stable control of the flying car, and the folded rotors cannot be used, resulting in excessive power of the remaining rotors during takeoff and landing, which reduces the lifespan.

[0004] In view of this, the market is in urgent need of a new type of folding wing to solve the problem that the existing wing folding technology cannot be well adapted for application during the vertical take-off and landing of the aircraft, which can easily cause excessive power of other rotors and affect the vertical take-off and landing stability of the aircraft. Summary of the invention

[0005] The disclosed embodiments provide a composite folding wing and a split aircraft, in order to solve the problem that the existing wing folding technology cannot be well adapted for application during the vertical ascent and descent of the aircraft, easily causes excessive power of other rotors, and affects the vertical ascent and descent stability of the aircraft.

[0006] The composite folding wing provided by the embodiment of the present disclosure includes a first wing body, a second wing body and a connecting member;

[0007] The first wing body is provided with a first rotor for providing power;

[0008] The second wing body is provided with a second rotor for providing power;

[0009] One end of the connecting member is connected to one end of the first wing body through a first folding mechanism, and the other end is connected to one end of the second wing body through a second folding mechanism;

[0010] Wherein, the composite folding wing comprises a first form and a second form which can be switched to each other;

[0011] In the first form, the first wing body, the connecting member and the second wing body are extended along the same straight line direction;

[0012] In the second form, the first wing body and the second wing body are arranged parallel to each other and spaced apart from each other, and the connecting member is arranged perpendicular to the first wing body and the second wing body respectively.

[0013] In one possible implementation, in the first configuration, the second rotor is arranged in the same direction as the first rotor and can rotate in the same direction to generate lift;

[0014] In the second configuration, the second rotor is arranged in an opposite direction to the first rotor and is capable of rotating in the opposite direction to generate lift;

[0015] During the process of switching between the first form and the second form, the second rotor stops rotating, and the first wing body increases its rotation and generates lift alone.

[0016] In one embodiment, a support member is further provided in the first wing body, and a locking member is further provided in the second wing body;

[0017] In the first form, the support member and the locking member are spaced apart from each other;

[0018] In the second form, the support member and the locking member are disposed in abutment with each other and can be locked with each other to fix the first wing body and the second wing body.

[0019] In one possible implementation manner, the first folding mechanism and the second folding mechanism are both configured as self-locking folding mechanisms;

[0020] The first folding mechanism can self-lock and fix the first wing body and the connecting member at any angle;

[0021] The second folding mechanism can self-lock and fix the second wing body and the connecting member at any angle.

[0022] In one possible implementation, the self-locking folding mechanism includes a drive motor, a self-locking hinge, and a controller;

[0023] The driving motor is in driving connection with the self-locking hinge, and is used for driving the self-locking hinge to rotate;

[0024] The controller is electrically connected to the drive motor and is used for electrically controlling and adjusting the output rotation angle and rotation direction of the drive motor.

[0025] In one embodiment, the length of the second wing body is less than or equal to the length of the first wing body;

[0026] In the second configuration, the second wing can be completely folded and located within the length range of the first wing.

[0027] In one possible implementation, in the second form, the first rotor and the second rotor are respectively arranged at intervals along two different vertical directions.

[0028] In one possible embodiment, the composite folding wing further includes a third state;

[0029] In the third form, the first wing body and the connecting member are extended along the same straight line direction, and the connecting member is perpendicular to the second wing body;

[0030] The composite folding wing can be switched among the first shape, the second shape and the third shape.

[0031] In addition, the embodiment of the present disclosure further provides a split aircraft, which includes an aircraft module, a cockpit module, a chassis module and the above-mentioned composite folding wing;

[0032] The aircraft module comprises at least two composite folding wings which are symmetrically distributed with respect to each other.

[0033] In one possible implementation manner, when the split aircraft is in flight mode, the composite folding wing is correspondingly switched to the first form;

[0034] When the split-type aircraft is in the lifting mode, the composite folding wing switches to the second form accordingly.

[0035] Compared with the prior art, the technical solution provided by the embodiments of the present disclosure has the following advantages:

[0036] The composite folding wing provided by the disclosed embodiment can quickly switch the relative position of the first wing body and the second wing body through the first folding mechanism and the second folding mechanism in the connecting member during the process of switching back and forth between the flight mode and the take-off and landing mode, thereby achieving the beneficial effect of flexible conversion of the aircraft between vertical take-off and landing and efficient cruising in a narrow space; and during the switching process, the second rotor can first stop rotating and the first rotor can temporarily increase the output power to ensure that the switching process can maintain flight stability; and when switching to the form in which the first wing body and the second wing body are folded, the layout is more compact, reducing the size requirements for the take-off and landing site; in addition, the first rotor and the second rotor can also work together in the folded state to avoid overloading of a single rotor and improve the safety of take-off and landing. At the same time, the first rotor 11 can also offset the torque of the second rotor 12 to reduce the complexity of the aircraft's take-off and landing control.

[0037] In addition, the split aircraft provided in the embodiment of the present disclosure includes the above-mentioned composite folding wings, which can achieve the same beneficial effects and will not be repeated here.

[0038] It should be understood that the content described in this section is not intended to identify the key or important features of the embodiments of the present disclosure, nor is it intended to limit the scope of the present disclosure. Other features of the present disclosure will become easily understood through the following description. BRIEF DESCRIPTION OF THE DRAWINGS

[0039] The above and other objects, features and advantages of the exemplary embodiments of the present disclosure will become readily understood by reading the detailed description below with reference to the accompanying drawings. In the accompanying drawings, several embodiments of the present disclosure are shown in an exemplary and non-limiting manner, in which:

[0040] In the drawings, the same or corresponding reference numerals represent the same or corresponding parts.

[0041] Figure 1 A schematic diagram of a first state of a composite folding wing provided by an embodiment of the present disclosure is shown;

[0042] Figure 2 A schematic diagram of a second state of the composite folding wing provided by an embodiment of the present disclosure is shown;

[0043] Figure 3 A schematic diagram of a third state of the composite folding wing provided by an embodiment of the present disclosure is shown;

[0044] Figure 4 A schematic diagram of a split aircraft provided by an embodiment of the present disclosure is shown.

[0045] Explanation of the reference numerals in the figure: 1, first wing body; 11, first rotor; 12, support member;

[0046] 2. second wing body; 21. second rotor; 22. locking member;

[0047] 3. Connecting member; 31. First folding mechanism; 32. Second folding mechanism;

[0048] 4. Aircraft module; 5. Cockpit module; 6. Chassis module. DETAILED DESCRIPTION

[0049] In order to make the purpose, features, and advantages of the present disclosure more obvious and easy to understand, the technical solutions in the embodiments of the present disclosure will be clearly and completely described below in conjunction with the drawings in the embodiments of the present disclosure. Obviously, the described embodiments are only part of the embodiments of the present disclosure, not all of the embodiments. Based on the embodiments in the present disclosure, all other embodiments obtained by those skilled in the art without creative work are within the scope of protection of the present disclosure.

[0050] The embodiments of the present disclosure will be described in detail below with reference to the accompanying drawings.

[0051] Combination Figure 1 and Figure 2 As shown, the embodiment of the present disclosure provides a composite folding wing including a first wing body 1, a second wing body 2 and a connecting member 3; the first wing body 1 is provided with a first rotor 11 for providing power; the second wing body 2 is provided with a second rotor 21 for providing power; one end of the connecting member 3 is connected to one end of the first wing body 1 through a first folding mechanism 31, and the other end is connected to one end of the second wing body 2 through a second folding mechanism 32;

[0052] Among them, the composite folding wing includes a first form and a second form that can be switched between each other; in the first form, the first wing body 1, the connecting member 3 and the second wing body 2 are extended along the same straight line direction; in the second form, the first wing body 1 and the second wing body 2 are arranged in parallel and spaced apart from each other, and the connecting member 3 is arranged perpendicular to the first wing body 1 and the second wing body 2 respectively.

[0053] The composite folding wing provided by the embodiment of the present disclosure can be specifically but not limited to being suitable for the multi-modal flight requirements of a split aircraft, in which: a first rotor 11 for providing power is arranged in the first wing body 1, the first rotor 11 can be a multi-rotor or fixed-wing propeller, and the first rotor 11 can be but not limited to being arranged in the middle of the first wing body 1; a second rotor 21 is arranged in the second wing body 2, the second rotor 21 can also be a multi-rotor or fixed-wing propeller, and the second rotor 21 can be but not limited to being arranged in the middle of the second wing body 2; the connecting member 3 can be a rigid or semi-rigid structure, such as a metal connecting rod or a carbon fiber bracket, one end of which is hinged to the first wing body 1 through a first folding mechanism 31, and the other end is hinged to the second wing body 2 through a second folding mechanism 32; the first folding mechanism 31 and the second folding mechanism 32 can respectively allow the first wing body 1 and the second wing body 2 to rotate around the hinge axis by a specific angle, such as 90°.

[0054] The first form of the composite folding wing can be specifically but not limited to being set to a flight mode. In the first form: the first wing body 1, the connecting member 3 and the second wing body 2 extend along the same straight line direction to form an unfolded state; the first rotor 11 and the second rotor 21 can rotate in the same direction to jointly generate lift or thrust, which is suitable for high-speed cruising or long-distance flight.

[0055] The first form of the composite folding wing can be specifically but not limited to being set to a vertical take-off and landing mode. In the second form: the second wing body 2 rotates around the connecting member 3 by a specific angle, for example 180°, through the second folding mechanism 32, so that the first wing body 1 and the second wing body 2 are arranged parallel to each other, and the connecting member 3 is perpendicular to the two wing bodies respectively; the first rotor 11 and the second rotor 21 can rotate in opposite directions to jointly provide vertical lift and offset the reverse torque, so that the first rotor 11 and the second rotor 21 can be folded in their own length direction to reduce the occupied space in the length direction.

[0056] The composite folding wing switches from the first form to the second form during the dynamic process of form switching: the second rotor 21 can first stop rotating, the first rotor 11 can temporarily increase the output power to maintain flight stability, the first folding mechanism 31 and the second folding mechanism 32 work together to drive the second wing body 2 to rotate to a parallel position, and then the second rotor 21 restarts and switches the rotation direction; when switching from the second form to the first form, the first folding mechanism 31 and the second folding mechanism 32 can be used to perform reverse operations accordingly.

[0057] In summary, during the process of switching back and forth between the flight mode and the take-off and landing mode, the composite folding wing can quickly switch the relative position of the first wing body 1 and the second wing body 2 through the first folding mechanism 31 and the second folding mechanism 32 in the connecting member 3, thereby achieving the beneficial effect of flexible conversion of the aircraft between vertical take-off and landing and efficient cruising in a narrow space; and during the switching process, the second rotor 21 can first pause rotation and the first rotor 11 can temporarily increase the output power to ensure that the switching process can maintain flight stability; and when switching to the folded form of the first wing body 1 and the second wing body 2, the layout is more compact, reducing the size requirements for the take-off and landing site; in addition, the first rotor 11 and the second rotor 12 can also work together in the folded state to avoid overload of a single rotor and improve the safety of take-off and landing. At the same time, the first rotor 11 can also offset the torque of the second rotor 12 to reduce the complexity of the aircraft's take-off and landing control.

[0058] In one embodiment, in a first form, the second rotor 21 is arranged in the same direction as the first rotor 11, and can rotate in the same direction to generate lift; in a second form, the second rotor 21 is arranged in an opposite direction to the first rotor 11, and can rotate in the opposite direction to generate lift; during the switching process between the first form and the second form, the second rotor 21 stops rotating, and the first wing body 1 increases its rotation and generates lift alone.

[0059] Specific, combined Figure 1To further explain in detail, in the first form, it can be specifically applied to the cruise mode, and the second rotor 21 and the first rotor 11 have the same rotation direction, for example, both are clockwise, and the two cooperate to generate thrust in the same direction, which is suitable for high-speed flight; in the second form, it can be specifically applied to the vertical take-off and landing mode, and the second rotor 21 and the first rotor 11 rotate in opposite directions, for example, the first rotor rotates clockwise and the second rotor rotates counterclockwise, and the two rotate in opposite directions to jointly provide lift and offset the anti-torque; and in the switching process: when converting from the first form to the second form, the second rotor 21 stops rotating, and the first rotor 11 maintains lift alone by increasing the rotation speed, for example, increasing it to 150% of the rated power, to avoid a sudden drop in lift during the switching process.

[0060] Of course, during the switching process of the composite folding wing, the start and stop of the second rotor 21 and the action timing of the first folding mechanism 31 and the second folding mechanism 32 in the connecting part 3 need to match to avoid mechanical interference. During the switching, the first rotor 11 temporarily increases power to ensure the stability of the aircraft attitude. After switching to the second form, the first rotor 11 and the second rotor 21 rotate in the opposite direction to eliminate the spin torque and reduce the burden on the flight control system.

[0061] In one embodiment, a support member 12 is further provided in the first wing body 1, and a locking member 22 is further provided in the second wing body 2; in the first form, the support member 12 and the locking member 22 are spaced apart from each other; in the second form, the support member 12 and the locking member 22 are docked with each other and can be locked with each other to fix the first wing body 1 and the second wing body 2.

[0062] Specific, combined Figure 1 and Figure 2 To further explain in detail, the support member 12 can be arranged on the side of the first wing body 1 facing away from the first rotor 11, for example, a raised buckle; the locking member 22 can be arranged at the corresponding position of the second wing body 2 facing away from the second rotor 21, for example, a lock head matching the buckle; in the second form: when the first wing body 1 and the second wing body 2 are folded parallel to each other, the support member 12 is docked with the locking member 22, and the relative positions of the two wing bodies are fixed by mechanical locking or electromagnetic adsorption.

[0063] The specific arrangement of the above-mentioned support member 12 and the locking member 22 can further lock and fix the first wing body 1 and the second wing body 2 in the second form, thereby improving the structural stability of the composite folding wing in the second form, making the overall force of the first wing body 1 and the second wing body 2 more uniform, and improving its service life and load-bearing capacity.

[0064] In addition, when the support member 12 and the locking member 22 are configured as an electromagnetic lock structure, they can also be released instantly through an electrical signal to meet emergency separation requirements.

[0065] In one embodiment, the first folding mechanism 31 and the second folding mechanism 32 are both configured as self-locking folding mechanisms; the first folding mechanism 31 can self-lock and fix the first wing body 1 and the connecting member 3 at any angle; the second folding mechanism 32 can self-lock and fix the second wing body 2 and the connecting member 3 at any angle.

[0066] Specific, combined Figure 1 and Figure 2 To further explain in detail, the first folding mechanism 31 and the second folding mechanism 32 can be configured as a self-locking folding mechanism, such as a hinge including a worm gear or ratchet structure, which can self-lock and fix the wing position at any rotation angle, such as in the range of 0° to 180°.

[0067] The specific arrangement of the first folding mechanism 31 and the second folding mechanism 32 enables the aircraft to flexibly adjust the wing angle according to mission requirements, and the self-locking mechanism does not require continuous power supply to avoid accidental deployment due to power interruption.

[0068] In one embodiment, the self-locking folding mechanism includes a drive motor, a self-locking hinge and a controller; the drive motor is transmission-connected to the self-locking hinge for driving the self-locking hinge to rotate; the controller is electrically connected to the drive motor for electrically controlling and adjusting the output angle and rotation direction of the drive motor.

[0069] Specifically, the self-locking folding mechanism is specifically configured to include a drive motor, a self-locking hinge and a controller, and the drive motor can be specifically configured to be a stepper motor and is transmission-connected to the self-locking hinge to drive the second wing body 2 to rotate; the controller is electrically connected to the drive motor, and can preset the folding angle, such as the 90° second part, and control the motor to accurately output the angle.

[0070] In this way, the control center in the aircraft can send instructions through the controller, driving the motor to drive the self-locking hinge to rotate to the target angle and then automatically lock it.

[0071] The specific setting method of the above-mentioned self-locking folding mechanism has the beneficial effects of simple structure, being able to programmatically and accurately control the folding angle of the second wing body 2, and being adaptable to different flight scenes. The folding process of the self-locking folding mechanism can also be controlled by wireless signals, so as to be suitable for unmanned aerial vehicles.

[0072] In one embodiment, the length of the second wing body 2 is less than or equal to the length of the first wing body 1 ; in the second form, the second wing body 2 can be completely folded and located within the length range of the first wing body 1 .

[0073] Specific, combined Figure 1 and Figure 2To further explain in detail, the length of the second wing body 2 is specifically set to be less than or equal to the length of the first wing body 1, so that in the second form, the second wing body 2 can be located within the projection range of the first wing body 1 after being fully folded. For example, the length of the second wing body 2 is 70% of the first wing body 1, and the two are parallel and have no protruding parts after folding.

[0074] The specific arrangement of the second wing body 2 can minimize the overall size of the composite folding wing after folding, and enable the take-off and landing process to be carried out in a smaller scene environment.

[0075] In one embodiment, in the second form, the first rotor 11 and the second rotor 21 are respectively arranged at intervals along two different vertical directions.

[0076] Specific, combined Figure 2 To further explain in detail, in the second form, the first rotor 11 and the second rotor 21 are respectively arranged to be spaced along two different vertical directions. For example, the first rotor 11 can be located on the upper surface of the first wing body 1, and the second rotor 21 can be located on the lower surface of the second wing body 2. The vertical spacing between the two is 0.3m-1.0m. The vertical staggered arrangement of the two can, on the one hand, adopt an upper and lower layout structure to lower the overall center of gravity of the aircraft and improve take-off and landing stability. On the other hand, it can also avoid the interference of the positions of the first rotor 11 and the second rotor 21.

[0077] In one embodiment, the composite folding wing also includes a third form; in the third form, the first wing body 1 and the connecting member 3 are extended along the same straight line direction, and the connecting member 3 is perpendicular to the second wing body 2; the composite folding wing includes the ability to switch between the first form, the second form and the third form.

[0078] Specific, combined Figure 3 To further explain in detail, in the third form, the first wing body 1 and the connecting member 3 are kept unfolded in a straight line, and the second wing body 2 is rotated 90° around the second folding mechanism 32 to be perpendicular to the connecting member 3, forming a "T"-shaped layout. In this way, the composite folding wing in the third form can be applied to the hovering / transportation mode. At this time, the second rotor 21 in the second wing body 2 can provide actual flight stability in the horizontal direction, which is used to resist crosswind, horizontal off-load, turning and other flight scenarios.

[0079] The above-mentioned composite folding wing can switch between a first form, a second form and a third form, and can be respectively applied to all operating scenarios such as cruising, take-off and landing, and transportation, thereby fully improving the functional diversity of the composite folding wing.

[0080] In addition, the embodiment of the present disclosure also provides a split aircraft, which includes an aircraft module 4, a cabin module 5, a chassis module 6 and the above-mentioned composite folding wings; the aircraft module 4 includes at least two composite folding wings that are symmetrically distributed with each other.

[0081] Specific, combined Figure 4 In further details, the split aircraft can be, but is not limited to, a split flying car, a split airplane, etc., because the aircraft module includes at least two symmetrically distributed composite folding wings such as a left wing and a right wing. Moreover, the wings on both sides of the aircraft module 4 can switch their forms independently without affecting each other, so as to be more flexibly adapted to complex and changeable flight scenarios.

[0082] The split aircraft includes the above-mentioned composite folding wing, and can achieve all the beneficial effects of the above-mentioned composite folding wing, which will not be described in detail here.

[0083] In one possible implementation manner, when the split aircraft is in flight mode, the composite folding wings correspondingly switch to a first form; when the split aircraft is in lifting mode, the composite folding wings correspondingly switch to a second form.

[0084] Specific, combined Figure 2 and Figure 3 In further detail, when the split aircraft is in flight mode, the composite folding wing switches to the first form to form a symmetrical straight wing layout to maximize flight efficiency; when the split aircraft is in lifting mode, the composite folding wing switches to the second form to form a folding storage layout to ensure lift while offsetting torque. The lift load is dispersed by the first rotor 11 and the second rotor 21, the motor life is extended, and the complexity of flight control during the lifting process is reduced.

[0085] In addition, the terms "first" and "second" are used for descriptive purposes only and should not be understood as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one of the features. In the description of the present disclosure, the meaning of "plurality" is two or more, unless otherwise clearly and specifically defined.

[0086] The above are only specific embodiments of the present disclosure, but the protection scope of the present disclosure is not limited thereto. Any technician familiar with the technical field can easily think of changes or substitutions within the technical scope disclosed in the present disclosure, which should be included in the protection scope of the present disclosure. Therefore, the protection scope of the present disclosure should be based on the protection scope of the claims.

Claims

1. A composite folding wing, characterized in that: include: A first wing body (1) is provided with a first rotor (11) for providing power; A second wing body (2) is provided with a second rotor (21) for providing power; A connecting member (3), one end of which is connected to one end of the first wing body (1) through a first folding mechanism (31), and the other end of which is connected to one end of the second wing body (2) through a second folding mechanism (32); Wherein, the composite folding wing comprises a first form and a second form which can be switched to each other; In the first form, the first wing body (1), the connecting member (3) and the second wing body (2) are extended along the same straight line direction; In the second form, the first wing body (1) and the second wing body (2) are arranged parallel to each other and spaced apart from each other, and the connecting member (3) is arranged perpendicular to the first wing body (1) and the second wing body (2), respectively.

2. The composite folding wing according to claim 1, characterized in that: In the first form, the second rotor (21) is arranged in the same direction as the first rotor (11), and can rotate in the same direction to generate lift; In the second state, the second rotor (21) is arranged in an opposite direction to the first rotor (11) and is capable of rotating in the opposite direction to generate lift; During the process of switching between the first form and the second form, the second rotor (21) stops rotating, and the first wing body (1) increases its rotation and generates lift alone.

3. The composite folding wing according to claim 1, characterized in that: The first wing body (1) is further provided with a support member (12), and the second wing body (2) is further provided with a locking member (22); In the first form, the support member (12) and the locking member (22) are spaced apart from each other; In the second form, the support member (12) and the locking member (22) are arranged to be butted against each other and can be locked with each other to fix the first wing body (1) and the second wing body (2).

4. The composite folding wing according to claim 1, characterized in that: The first folding mechanism (31) and the second folding mechanism (32) are both configured as self-locking folding mechanisms; The first folding mechanism (31) can self-lock and fix the first wing body (1) and the connecting member (3) at any angle; The second folding mechanism (32) can self-lock and fix the second wing body (2) and the connecting member (3) at any angle.

5. The composite folding wing according to claim 4, characterized in that: The self-locking folding mechanism includes a driving motor, a self-locking hinge and a controller; The driving motor is in driving connection with the self-locking hinge, and is used for driving the self-locking hinge to rotate; The controller is electrically connected to the drive motor and is used for electrically controlling and adjusting the output rotation angle and rotation direction of the drive motor.

6. The composite folding wing according to claim 1, characterized in that: The length of the second wing body (2) is less than or equal to the length of the first wing body (1); In the second form, the second wing (2) can be completely folded and located within the length range of the first wing (1).

7. The composite folding wing according to claim 6, characterized in that: In the second form, the first rotor (11) and the second rotor (21) are respectively arranged at intervals along two different vertical directions.

8. The composite folding wing according to any one of claims 1 to 7, characterized in that: The composite folding wing also includes a third state; In the third form, the first wing body (1) and the connecting member (3) are extended along the same straight line direction, and the connecting member (3) and the second wing body (2) are arranged perpendicularly; The composite folding wing can be switched among the first shape, the second shape and the third shape.

9. A split-type aircraft, characterized in that: It comprises an aircraft module (4), a cockpit module (5), a chassis module (6) and the composite folding wing according to any one of claims 1 to 8; The aircraft module (4) comprises at least two composite folding wings which are symmetrically distributed with respect to each other.

10. The split-type aircraft according to claim 9, characterized in that: When the split aircraft is in flight mode, the composite folding wing is correspondingly switched to the first form; When the split-type aircraft is in the lifting mode, the composite folding wing switches to the second form accordingly.

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