Aircraft with foldable wings, wing folding and unfolding method thereof and foldable wings

Abstract

The invention belongs to an aircraft, and provides an aircraft with foldable wings, a wing folding and unfolding method of the aircraft and the foldable wings to solve the technical problems that an existing foldable wing aircraft is large in structure occupied space, inconvenient to fold and unfold and insufficient in maneuverability. Wings in the aircraft comprise at least one front wing set and at least one rear wing set, each front wing set and each rear wing set comprise at least two wing modules, the wings adopt a modular design thought, each wing module comprises a frame body, an air column, a skin, a steering engine and a flap, the skin covers the upper portion of the frame body, the air column is arranged between the skin and the frame body, and in practical application, the steering engine is arranged between the steering engine and the frame body. And when the adjacent wing modules are folded and unfolded to preset positions, the relative positions of the adjacent frame bodies are locked through the locking pieces. The structural strength and stability of the aircraft are improved, and meanwhile the transportation and storage difficulty is effectively reduced.

Description

Technical Field

[0001] This application belongs to an aircraft, and particularly relates to an aircraft with deployable wings, a method for deploying and folding the wings thereof, and a deployable wing. Background Art

[0002] Folding-wing aircraft have become popular equipment due to their characteristics of being easy to store and transport. However, most of the current folding-wing aircraft on the market still have the problem of excessive volume due to their relatively large cross-sectional thickness even in the folded state, which seriously restricts their mobility and portability. From the perspective of structural design, many folding-wing aircraft use relatively strong and heavy fuselage frames and large-sized wings to ensure stability and load capacity during flight. Although the wings can be folded up during folding, a large amount of space is occupied by the complex folding hinge structure, making it difficult to compress the folded fuselage to an ideal compact size. This relatively large folding volume brings many inconveniences in practical applications. In terms of mobility, due to the still relatively large volume after folding, it is often difficult to quickly pass through narrow areas. Although aircraft with inflatable wing structures have significant advantages in terms of portability, etc., the wing strength is usually low, and the wings are prone to torsion during the manufacturing process, resulting in low practicality. In terms of convenience, the existing folding-wing aircraft are not convenient to deploy and fold, which also limits the application and popularization of folding-wing aircraft in more scenarios. Summary of the Invention

[0003] This application aims at the technical problems of existing folding-wing aircraft, such as large structural space occupation, inconvenient deployment and folding, and insufficient mobility, and provides an aircraft with deployable wings, a method for deploying and folding the wings thereof, and a deployable wing.

[0004] To achieve the above object, this application adopts the following technical solutions: In the first aspect, this application provides an aircraft with deployable wings, including wings, a vertical tail, a power equipment compartment, and at least one main fuselage; The wings include at least one front wing group and at least one rear wing group, and the front wing group and the rear wing group are respectively installed at both ends of the main fuselage; Each front wing group and each rear wing group include at least two wing modules, and adjacent wing modules are hinged; The wing module includes a frame, an air column, a skin, a servo and a flap; the skin covers the upper part of the frame; the air column is located between the skin and the frame, and the inside of the air column is connected to an external air source; the servo is installed on the frame and is located inside the skin; the flap is installed on the frame, and the flap is connected to the servo for driving the flap to move through the servo; A locking member is connected between the frames of adjacent wing modules for locking the relative positions between adjacent frames when the adjacent wing modules are deployed and folded to a preset position.

[0005] Further, the vertical tail is rigidly connected to either end of the main fuselage; the power equipment compartment is installed at the other end of the main fuselage.

[0006] Further, the frame includes at least three rigid ribs and at least two rib beam connecting columns located between the three rigid ribs; The rigid ribs are parallel to each other, the rib beam connecting columns are parallel to each other, and the rigid ribs and the rib beam connecting columns are perpendicular to each other.

[0007] Further, a plurality of grooves are uniformly formed on the upper surface of the rigid rib, and the number of grooves is the same as the number of air columns; The shape of the groove is adapted to the shape of the air column, and the air column is fixed in the groove; The air column extends between the two outermost rigid ribs.

[0008] Further, the flap is a rigid flap.

[0009] Further, adjacent wing modules are hinged by hinges.

[0010] Further, limiting protrusions are provided at both ends of the locking member; limiting holes are formed on the frame; The locking member is located in the limiting holes of adjacent wing modules, and the limiting protrusions at both ends of the locking member are respectively located outside the limiting holes of adjacent wing modules.

[0011] In a second aspect, the present application provides a wing folding and unfolding method for the above-mentioned aircraft with foldable wings, including: During folding: When the wing module is in an unfolded state, the air column is in a vacuum state, and the front wing group and the rear wing group are folded through the hinge structure between adjacent wing modules, and the main fuselage and the vertical tail are folded and located between the front wing group and the rear wing group; During unfolding: The wing module is unfolded by inflating the air column with an external air source, and adjacent frames are locked by the locking member.

[0012] Further, during folding, it further includes: The power equipment compartment is located between the front wing group and the rear wing group after folding; and adjacent wing modules are folded.

[0013] In a third aspect, the present application provides a foldable wing, including at least one front wing group and at least one rear wing group, and the front wing group and the rear wing group are respectively used to be installed at both ends of the main fuselage; Each front wing group and each rear wing group include at least one wing module, and adjacent wing modules are hinged; The wing module includes a frame, an air column, a skin, a servo and a flap; the skin covers the top of the frame; the air column is located between the skin and the frame, and the inside of the air column is connected to an external air source; the servo is installed on the frame and is located inside the skin; the flap is installed on the frame, and the flap is connected to the servo for driving the flap to move through the servo; A locking member is connected between the frames of adjacent wing modules for locking the relative positions between adjacent frames when the adjacent wing modules are folded and unfolded to a preset position.

[0014] Compared with the prior art, the present application has the following beneficial effects: The present application proposes an aircraft with deployable wings. The wings of the aircraft include a front wing group and a rear wing group. Each front wing group and each rear wing group include at least two wing modules. The wings adopt a modular design concept. The wing module includes a frame, an air column, a skin, a servo and a flap. The skin covers the top of the frame, and the air column is between the skin and the frame. In practical applications, when adjacent wing modules are folded and unfolded to a preset position, the relative positions between adjacent frames are locked through a locking member. In the folded state, through the modular structure layout, convenient folding and unfolding control can be achieved, so that the occupied space of the aircraft is greatly reduced in the folded state. At the same time, through the cooperation of various structural members in the wing module, the structural strength and flight stability of the aircraft after deployment are ensured, providing more new possibilities for the application environment, mobility and convenience of the aircraft.

[0015] The present application also proposes a wing folding and unfolding method for an aircraft with deployable wings, and a deployable wing, which have all the advantages of the above-mentioned aircraft with deployable wings. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] In order to more clearly illustrate the technical solutions of the embodiments of the present application, the following will briefly introduce the drawings required in the embodiments. It should be understood that the following drawings only show some embodiments of the present application, and therefore should not be regarded as limiting the scope. For those of ordinary skill in the art, other related drawings can be obtained based on these drawings without creative efforts.

[0017] Figure 1 It is a schematic diagram of the aircraft with deployable wings of the present application in the fully deployed state; Figure 2 It is a schematic diagram of a wing module in an embodiment of the present application (excluding the skin); Figure 3 For Figure 2 a schematic diagram of the frame in; Figure 4 For Figure 2 a schematic diagram after including the skin; Figure 5Schematic diagram of the folded aircraft with deployable wings in the embodiments of the present application; Figure 6 Schematic diagram of the front wing group including four wing modules in the embodiments of the present application; Figure 7 Schematic diagram during the folding process of the front wing group including four wing modules in the embodiments of the present application; Figure 8 Top view of the folded front wing group including four wing modules in the embodiments of the present application; Figure 9 is Figure 8 side view of; Figure 10 is Figure 9 left view of.

[0018] Wherein, 1 - vertical tail, 2 - power equipment compartment, 3 - main fuselage, 41 - front wing group, 42 - rear wing group, 5 - wing module, 6 - frame, 61 - rigid rib, 62 - rib beam connecting column, 7 - air column, 8 - skin, 9 - servo, 10 - flap, 11 - locking member, 12 - groove body, 13 - hinge. Detailed implementation manners

[0019] To make the objectives, technical solutions and advantages of the embodiments of the present application clearer, the technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present application. Obviously, the described embodiments are some but not all of the embodiments of the present application. Usually, the components of the embodiments of the present application described and illustrated in the accompanying drawings here can be arranged and designed in various different configurations.

[0020] Therefore, the following detailed description of the embodiments of the present application provided in the accompanying drawings is not intended to limit the scope of the present application claimed, but merely represents the selected embodiments of the present application. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present application without making creative efforts fall within the scope of protection of the present application.

[0021] It should be noted that: similar reference numerals and letters denote similar items in the following drawings. Therefore, once an item is defined in one drawing, it does not need to be further defined and explained in subsequent drawings.

[0022] In the description of the embodiments of the present application, it should be noted that if terms such as "upper", "lower", "horizontal", "inner", etc. are used to indicate the orientation or positional relationship, it is based on the orientation or positional relationship shown in the drawings, or the orientation or positional relationship in which the invention product is usually placed during use. This is only for the convenience of describing the present application and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation. Therefore, it should not be construed as a limitation to the present application. In addition, terms such as "first", "second", etc. are only used for distinguishing descriptions and cannot be understood as indicating or implying relative importance.

[0023] In addition, if the term "horizontal" appears, it does not mean that the component is required to be absolutely horizontal, but it can be slightly inclined. For example, "horizontal" only means that its direction is more horizontal relative to "vertical", and does not mean that the structure must be completely horizontal, but it can be slightly inclined.

[0024] In the description of the embodiments of the present application, it should also be noted that unless otherwise clearly specified and limited, if terms such as "set", "installed", "connected", "connected" are used, they should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be directly connected or indirectly connected through an intermediate medium, and it can be the communication inside two elements. For those of ordinary skill in the art, the specific meanings of the above terms in the present application can be understood according to specific circumstances.

[0025] In the application fields of airliners and aerospace vehicles, there are applications of folding and unfolding wing technologies to adapt to different working environments and flight conditions. In the modern aerospace field, the folding and unfolding wing technology flexibly adjusts its form according to different working environments and flight conditions, becoming the core technology to improve the performance of aircraft. An airliner shuttles between airports of different specifications and faces complex and changeable ground facility conditions. Especially for large wide-body airliners to achieve transoceanic long-distance flights and large-capacity passenger transportation, they often need an ultra-large wingspan to obtain sufficient lift and reduce fuel consumption, but they will encounter space bottlenecks at many small and medium-sized airports. Therefore, whether it is for civil aviation transportation or space exploration, the folding and unfolding wing technology, with its high environmental adaptability and functional flexibility, has become an important technical support for continuously promoting the development of the aerospace field.

[0026] Although the folding and unfolding wing technology has shown significant advantages in both the aerospace field and airliner applications, it still faces the technical bottleneck of occupying a relatively large space after folding. In the airliner field, even with a complex multi-section folding structure, the wingspan after folding still cannot fully fit the width of the parking bays and taxiways at small and medium-sized airports. This is mainly because the folding and unfolding wing needs to integrate complex hydraulic drive systems, mechanical transmission devices, and locking mechanisms inside the wing. These precision components are difficult to achieve extremely compact storage after folding, and to ensure structural strength and flight safety, necessary buffer spaces need to be reserved, resulting in a high overall volume. Spacecraft are also restricted by this problem. For example, during the launch phase, the folding wings of a spacecraft need to be stored inside the fairing, and the existing technology is difficult to further compress the size after folding, which limits the space utilization rate of the rocket fairing and the payload capacity of the spacecraft.

[0027] Based on the above situation, this application proposes an aircraft with foldable wings, its wing folding and unfolding method, and foldable wings. The following will make a detailed description of this application in combination with embodiments and drawings.

[0028] As an embodiment of the aircraft with foldable wings of this application, it may include wings, a vertical tail 1, a power equipment compartment 2, and at least one main fuselage 3.

[0029] The wings include at least one front wing group 41 and at least one rear wing group 42, and the front wing group 41 and the rear wing group 42 are respectively installed at both ends of the main fuselage 3. The front wing group 41 and the rear wing group 42 are arranged at both ends of the main fuselage 3, meeting the aerodynamic layout requirements of traditional aircraft and facilitating the achievement of moment balance. Each front wing group 41 and each rear wing group 42 include at least two wing modules 5, and adjacent wing modules 5 are hinged. It should be noted that the number of the front wing group 41 and the rear wing group 42 can be different, and the wing modules 5 included in the front wing group 41 and the rear wing group 42 can also be different. For example, it includes three front wing groups 41 and one rear wing group 42, and two main fuselages 3 are arranged between each front wing group 41 and the rear wing group 42. The number of the front wing group 41 and the rear wing group 42, as well as the number of the wing modules 5, can all be adjusted according to actual needs. The adjacent wing modules 5 are connected by a hinged connection method to achieve multi-section folding or unfolding functions. The wing module 5 includes a frame 6, an air column 7, a skin 8, a servo 9, and a flap 10. The skin 8 covers the upper part of the frame 6; the air column 7 is located between the skin 8 and the frame 6, and the inside of the air column 7 is connected to an external air source; the servo 9 is installed on the frame 6 and is located inside the skin 8; the flap 10 is installed on the frame 6, and the flap 10 is connected to the servo 9 for driving the flap 10 to move through the servo 9. A locking member 11 is connected between the frames 6 of adjacent wing modules 5 for locking the relative positions between adjacent frames 6 when the adjacent wing modules 5 are folded and unfolded to a preset position.

[0030] It should be noted that the air column 7, as a flexible support element, adjusts the bending stiffness of the wing by inflating and deflating, and may be used to achieve adaptive deformation during flight. The skin 8 covers the frame 6. In practical applications, high-strength flexible materials can be used to balance airtightness and tear resistance. The servo 9 is built into the skin 8 and drives the flap 10 to deflect to achieve roll / pitch control. The vertical tail 1 provides yaw stability, and the power equipment compartment 2 integrates an engine or a motor. In addition, the locking member 11 between the wing modules 5 can be locked at a preset position, such as fully deployed or folded state, to ensure the structural rigidity during the flight phase when fully deployed.

[0031] In this application, the wing adopts a modular design, which is convenient for increasing or decreasing the number of wing modules 5 according to mission requirements and improving mission adaptability. The combination of the air column 7 and the locking member 11 realizes the switching between the rigid flight and the flexible folding state, breaking through the problems of insufficient rigidity of traditional folding wings or complex deployment mechanisms. In practical applications, flutter can be suppressed by inflating, or gust loads can be absorbed by deflating. The linkage between the flap 10 and the servo 9 can also realize a variable-camber wing and optimize the lift-drag ratio in different flight phases.

[0032] As Figure 1 shown, it is a schematic diagram of the aircraft with deployable wings in the fully deployed state in this application. It includes two main fuselages 3. Each front wing group 41 and rear wing group 42 are divided into three segments by the two main fuselages 3, and each segment includes four wing modules 5. In practical applications, the number of wing modules 5 can be determined according to actual requirements. The vertical tail 1 is rigidly connected to either end of the main fuselage 3, and the power equipment compartment 2 is installed at the other end of the main fuselage 3.

[0033] As Figure 2 shown, it is a schematic diagram of a wing module 5 in this embodiment (excluding the skin). As Figure 3 shown, it is a schematic diagram of the Figure 2 frame. As Figure 4 shown, it is a schematic diagram of the Figure 2 after including the skin. Among them, the frame 6 includes three rigid ribs 61 and six rib beam connecting columns 62 located between the two rigid ribs 61. The rigid ribs 61 are parallel to each other, the rib beam connecting columns 62 are parallel to each other, and the rigid ribs 61 and the rib beam connecting columns 62 are perpendicular to each other. In this embodiment, three of the six rib beam connecting columns 62 are evenly distributed, two are concentratedly arranged, and the last one is located at the flap 10. The rigid ribs 61 and the rib beam connecting columns 62 together form the entire frame 6 to ensure the overall structural strength of the wing module 5.

[0034] The upper surface of the rigid rib 61 is evenly and continuously provided with a plurality of grooves 12, and the number of the grooves 12 is the same as that of the air columns 7. Moreover, the shape of the groove 12 is adapted to the shape of the air column 7 for accommodating the air column 7, and the air column 7 extends between the two outermost rigid ribs 61. When the air column 7 is in the deployed state, it can limit the position of the air column 7 to ensure safety. When the air column 7 is in the contracted state, it also has a limiting effect to prevent the air column 7 from shifting and affecting the next deployment. In practical applications, as long as it can be ensured that the air column 7 can well support the skin 8 in the deployed state, the air column 7 may not extend entirely between the two rigid ribs 61, and other placement methods can be adopted.

[0035] In this embodiment, the flap 10 is a rigid flap. The rigid flap provides precise aerodynamic control, and the flexible air column 7 realizes variable structural stiffness. In practical applications, the internal pressure of the air column 7 can be adjusted synchronously when the flap 10 moves. For example, during the takeoff phase, the air column 7 is pressurized to increase the wing stiffness and bear the additional torque brought by the deflection of the flap 10. Another example is that during the cruise phase, the air column 7 is depressurized to reduce the structural mass and cooperate with the 100° deflection angle of the flap to achieve the best aerodynamic efficiency.

[0036] In this embodiment, the adjacent wing modules 5 are hinged by hinges 13. The structure of the locking member 11 is that both ends of the locking member 11 are provided with limiting protrusions, and limiting holes are opened on the frame 6. The locking member 11 is located in the limiting holes of the adjacent wing modules 5, and the limiting protrusions at both ends of the locking member 11 are respectively located outside the limiting holes of the adjacent wing modules 5. It should be noted that Figure 2 In order to more clearly show the structural relationship, the locking member 11 is shown on one side of the frame 6, and the structure of the hinge 13 is shown on the other side. In practical applications, both sides have the locking member 11 and the hinge 13 at the same time. After reaching the deployed or folded state through the hinge 13, it is fixed by the locking member 11. In addition, in other embodiments of the present application, the hinge 13 can be replaced by other existing hinge structural members. The locking member 11 can also be replaced by other structural members that can achieve locking.

[0037] Such as Figure 5 shown, is a schematic diagram after folding of this embodiment. From Figure 5It can also be seen that the present application combines modular design and the ingenious overall structure of the wing module 5, and can greatly reduce the occupied space when the wing is in the folded state. In the folded state, the space occupied by the air column 7 is small, and the height is about 1 / 2 of that of the rigid wing. In the unfolded state, the rigid ribs 61 on both sides of the wing module 5 are connected by the locking members 11, and the structural strength is relatively large. The skin 8 located on the outer surface is tightened in the inflated state of the air column 7 to maintain the airfoil shape. The servo 9 is located inside the skin 8, which can effectively reduce the aerodynamic drag. In addition, due to the modular design of the wing module 5, the number of wing modules 5 and the number of the main fuselage 3 can be added or reduced according to requirements, without having to re-produce or manufacture a new aircraft.

[0038] The present application can not only achieve the compression and folding of the aircraft, improve the convenience of transportation and storage, but also provide sufficient structural strength and aerodynamic performance after the wing is unfolded to meet the requirements of high-altitude long-endurance flight. In addition, aiming at the problems of large folding volume and low stiffness of the inflatable structure in the prior art, the present application is a semi-rigid inflatable aircraft. By combining the modular structure layout and optimizing the folding and unfolding control, through the reasonable combination and structural optimization of each component, the compact folding and efficient unfolding of the folding-wing aircraft are realized, enabling the aircraft to occupy a small space in the folded state, while ensuring the structural strength and flight stability after unfolding, providing a new solution for the development of folding-wing aircraft.

[0039] As Figure 6 shown, it is a schematic diagram of the front wing group 41 including four wing modules 5. Figure 7 It is a schematic diagram during the folding process of the front wing group 41 including four wing modules. Figure 8 It is a top view of the front wing group 41 including four wing modules 5 after folding. Figure 9 It is Figure 8 a side view. Figure 10 It is Figure 9 a left view. From Figures 6 to 10 ..., it is the whole process of the front wing group 41 from unfolding to folding. It should be noted that the unfolding and folding methods of the rear wing group 42 are the same as those of the front wing group 41.

[0040] Based on the above structure, the present application also proposes a wing folding and unfolding method for an aircraft with foldable wings, which may include: (1) During folding: When the wing module 5 is in the unfolded state, the air column 7 is in a vacuum state. The front wing group 41 and the rear wing group 42 are folded through the hinge structure between adjacent wing modules 5, and the main fuselage 3 and the vertical tail 1 are folded and located between the front wing group 41 and the rear wing group 42; (2) During unfolding: The air column 7 is inflated by an external air source to unfold the wing module 5, and the adjacent frames 6 are locked by the locking members 11.

[0041] During specific operations, in the non-expanded state, the inside of the air column 7 of each front wing group 41 and rear wing group 42 is in a vacuum state, and the skin 8 is closely attached above the rigid rib 61, and can be folded by a W-shaped structure through a hinge structure ( Figure 7 as shown). The main fuselage 3 and the vertical tail 1 can be folded between the front wing group 41 and the rear wing group 42 through a U-shaped structure. The power equipment compartment 2 can be horizontally folded by 90° and stored between the front wing group 41 and the rear wing group 42. In addition, by disconnecting the connection between the wing modules 5 in the rear middle section, the main fuselage 3 can be folded twice by 90°, and the rear folding structure located at the rear can be arranged on both sides of the front folding structure. After the overall structure is folded, it can present an approximate columnar shape for placement. When it needs to be unfolded, in the folding mode, an external inflation device or a disposable high-pressure gas cylinder is used as the gas source to inflate the air column 7. The air columns 7 of each front wing group 41 and rear wing group 42 can be connected through rubber hoses. Under the action of air pressure, the front wing group 41 and the rear wing group 42 are unfolded into a straight line, and the rigid ribs 61 on both outer sides are locked after being connected by the locking parts 11. In addition, after the mission is completed, it can also be refolded by manual / electric exhaust and unlocking the locking parts 11.

[0042] When the aircraft of the present application is in the folded state, through the rotation and sliding of the modular wing module 5, the overall structure can be made compact, and the occupied space is significantly reduced, which is convenient for storage and transportation. During the unfolding process, the air column 7 is gradually inflated, so that the wing module 5 returns to the working state. At the same time, relying on the semi-rigid material and the frame 6 to provide the necessary stiffness, it is ensured that there is still sufficient structural strength and aerodynamic performance after inflation. In addition, the present application optimizes the folding and unfolding control method to ensure the stability and controllability of the folding and unfolding process, and avoid structural deformation or aerodynamic performance degradation during unfolding. In practical applications, the order of unfolding of each component and the inflation rate can also be coordinated by means of an intelligent control system, so that the entire folding and unfolding process proceeds smoothly, and the reliability and adaptability of the aircraft in the high-altitude environment are improved. Therefore, the present application not only improves the structural strength and stability of the aircraft, but also effectively reduces the difficulty of transportation and storage.

[0043] Finally, it should be noted that the present application also proposes a foldable and unfoldable wing, which includes at least one front wing group 41 and at least one rear wing group 42. The front wing group 41 and the rear wing group 42 are respectively used to be installed at both ends of the main fuselage 3. The specific structure is the same as the relevant structure in the aforementioned aircraft, and will not be elaborated here. That is, the foldable and unfoldable wing of the present application can be used on various aircraft that require wing folding and unfolding, and is not limited to the specific structure of the present application.

[0044] The above are only the preferred embodiments of the present application and are not intended to limit the present application. For those skilled in the art, various modifications and variations can be made to the present application. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present application shall be included within the protection scope of the present application.

Claims

1. An aircraft with deployable wings, comprising wings, a vertical tail (1), a power equipment compartment (2) and at least one main fuselage (3); characterized in that: The wings include at least one front wing group (41) and at least one rear wing group (42), and the front wing group (41) and the rear wing group (42) are respectively installed at both ends of the main fuselage (3); Each front wing group (41) and each rear wing group (42) include at least two wing modules (5), and adjacent wing modules (5) are hinged to each other; The wing module (5) includes a frame body (6), an air column (7), a skin (8), a servo (9) and a flap (10); the skin (8) covers the upper part of the frame body (6); the air column (7) is located between the skin (8) and the frame body (6), and the inside of the air column (7) is connected to an external air source; the servo (9) is installed on the frame body (6) and is located inside the skin (8); the flap (10) is installed on the frame body (6), and the flap (10) is connected to the servo (9) for driving the flap (10) to move through the servo (9); A locking member (11) is connected between the frame bodies (6) of adjacent wing modules (5) for locking the relative positions between adjacent frame bodies (6) when the adjacent wing modules (5) are deployed and folded to a preset position.

2. The aircraft with a deployable wing according to claim 1, characterized in that: The vertical tail (1) is rigidly connected to any end of the main fuselage (3); the power equipment compartment (2) is installed at the other end of the main fuselage (3).

3. The aircraft with deployable wings according to claim 1, characterized in that: The frame body (6) includes at least three rigid ribs (61) and at least two rib beam connecting columns (62) located between two rigid ribs (61); The rigid ribs (61) are parallel to each other, the rib beam connecting columns (62) are parallel to each other, and the rigid ribs (61) and the rib beam connecting columns (62) are perpendicular to each other.

4. The aircraft with deployable wings according to claim 3, characterized in that: A plurality of grooves (12) are uniformly formed on the upper surface of the rigid rib (61), and the number of the grooves (12) is the same as the number of the air columns (7); The shape of the groove (12) is adapted to the shape of the air column (7), and the air column (7) is fixed in the groove; The air column (7) extends between the two outermost rigid ribs (61).

5. The aircraft with deployable wings according to claim 1, characterized in that: The flap (10) is a rigid flap.

6. The aircraft with deployable wings according to claim 1, characterized in that: Adjacent wing modules (5) are hinged through a hinge (13).

7. The aircraft with a deployable wing according to claim 1, characterized in that: Both ends of the locking member (11) are provided with limit protrusions; limit holes are formed on the frame body (6); The locking member (11) is located in the limit holes of adjacent wing modules (5), and the limit protrusions at both ends of the locking member (11) are respectively located outside the limit holes of adjacent wing modules (5).

8. A method for folding and unfolding the wing of an aircraft with a deployable wing according to any one of claims 1 to 7, characterized in that, Including: When folding: When the wing module (5) is in an undeployed state, the inside of the air column (7) is in a vacuum state, and the front wing group (41) and the rear wing group (42) are folded through the hinge structure between adjacent wing modules (5), and the main fuselage (3) and the vertical tail (1) are folded and located between the front wing group (41) and the rear wing group (42); When deploying: The air column (7) is inflated through an external air source to deploy the wing module (5), and the adjacent frame bodies (6) are locked by the locking member (11).

9. The wing folding and unfolding method of the aircraft with foldable wings according to claim 8, characterized in that, When folding, it further includes: The power equipment compartment (2) is located between the front wing group (41) and the rear wing group (42) after folding; and the folding is performed between adjacent wing modules (5).

10. A deployable wing, characterized in that: It includes at least one front wing group (41) and at least one rear wing group (42), and the front wing group (41) and the rear wing group (42) are respectively used to be installed at both ends of the main fuselage (3); Each front wing group (41) and each rear wing group (42) include at least one wing module (5), and adjacent wing modules (5) are hinged to each other; The wing module (5) includes a frame body (6), an air column (7), a skin (8), a servo (9) and a flap (10); the skin (8) covers the upper part of the frame body (6); the air column (7) is located between the skin (8) and the frame body (6), and the inside of the air column (7) is connected to an external air source; the servo (9) is installed on the frame body (6) and is located inside the skin (8); the flap (10) is installed on the frame body (6), and the flap (10) is connected to the servo (9) for driving the flap (10) to move through the servo (9); A locking member (11) is connected between the frame bodies (6) of adjacent wing modules (5) for locking the relative positions between adjacent frame bodies (6) when the adjacent wing modules (5) are folded and unfolded to a preset position.

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