Hybrid structure folding wing and aircraft

Abstract

The utility model relates to the technical field of aviation, and particularly provides a folding wing with a mixed structure and an aircraft comprising the wing. The hybrid structure folding wing comprises a folding wing leading edge beam assembly, a rigid telescopic supporting rod, a folding wing trailing edge beam, a rigid sliding connecting rod, a rotating sleeve assembly and a wing root supporting beam, the front end of the rigid sliding connecting rod is hinged to one of hinge points of a main beam short rod and a secondary beam short rod of the wing leading edge beam assembly, and the rear end of the rigid sliding connecting rod is hinged to the other of hinge points of the main beam short rod and the secondary beam short rod of the wing root supporting beam. The rear end of the rotating sleeve assembly is in sliding connection with the rotating sleeve assembly, and the rotating sleeve assembly comprises a locking device. Under the acting force of the wing folding / unfolding device, the wings can be unfolded / folded in parallel in the vertical direction of the longitudinal axis of the aircraft body, the fixed wings are formed after the wings are unfolded, lift force can be provided for the aircraft, corresponding loads can be borne, the size and the area of the wings are reduced by multiple times after the wings are folded, and storage and transportation are convenient.

Description

Technical Field

[0001] This utility model relates to the field of aviation technology, specifically providing a novel hybrid structure folding wing with an improved integrated wing support frame structure and an aircraft including the wing. Background Technology

[0002] The wing is a crucial component of an aircraft, and folding wings are increasingly used in aircraft due to their space-saving design. In the prior art, Chinese patent ZL202222458702.7 provides a hybrid structure folding wing. Under the force of a wing folding / deploying device, the wing support frame can fold or deploy horizontally, simultaneously causing the connected inflatable skin to fold or deploy. When the wing is fully deployed, the inflatable skin inflates, bulges, and hardens, forming a shape that meets the aerodynamic requirements of the wing design, thus creating a hybrid structure folding wing that provides lift for the aircraft. When folded, the wing's volume is reduced several times, facilitating storage and transportation.

[0003] The main problems with existing technologies include:

[0004] 1. The wing root of the folding diamond continuous truss wing, composed of a main spar and a secondary spar, is a stress concentration area. Currently, this area is only connected and fixed by the main spar, secondary spar, and fuselage, making the structure relatively weak and requiring new technical measures to strengthen it.

[0005] 2. The folding wing support frame's leading edge spars and trailing edge spars are independent rigid structures with no rigid structural connection between them. When the wing is deployed, it cannot form a complete closed rigid wing support frame to support the connected flexible inflatable skin. When the wing is under stress, the deformation of the leading and trailing edge spars is inconsistent, making the aircraft using this wing difficult to control and endangering its safety.

[0006] Therefore, the above problems need to be improved. By improving the above problems, a new interconnected and integrated rigid foldable wing support frame system can be formed to meet the structural strength requirements of hybrid foldable wings. Utility Model Content

[0007] This application proposes the following improvement methods to address the above-mentioned problems. An embodiment of this utility model provides a hybrid structure folding wing, including a folding wing leading edge spars assembly, a rigid telescopic support rod, a folding wing trailing edge spars, a rigid sliding link, a rotating sleeve assembly, and a wing root support beam. The front end of the rigid sliding link is hinged to one of the hinge points of the main and secondary short rods of the wing leading edge spars assembly, and the rear end is slidably connected to the rotating sleeve assembly mounted on the trailing edge spars of the folding wing. The rotating sleeve assembly includes a locking device.

[0008] Furthermore, when the wing is fully deployed, the locking device in the rotating sleeve assembly locks the rigid sliding link, and the combination of the rotating sleeve assembly and the rigid sliding link connects the wing leading edge spars assembly and the folding wing trailing edge spars into a rigid integral structure.

[0009] Furthermore, one end of the rigid telescopic support rod is hinged to the fuselage through the rigid telescopic support rod wing root hinge point, and the other end is hinged to the first hinge point among the main and secondary beam short rod hinge points. After the wing is deployed, at the wing root of the wing leading edge beam assembly, it forms an interconnected triangular support structure with the main beam and secondary beam in the wing leading edge beam assembly.

[0010] Furthermore, the rigid telescopic support rod includes an active type and a driven type.

[0011] Furthermore, the rotating sleeve assembly also includes a sleeve hinge shaft, a movable lock cylinder, and a lock cylinder drive device to control the extension and retraction of the movable lock cylinder.

[0012] Furthermore, the hybrid structure folding wing also includes a trailing edge beam fixing section for fixing to the fuselage, which is pivotally connected to the folding trailing edge beam via a hinge point.

[0013] Furthermore, the hybrid structure folding wing also includes a trailing edge beam tension cable, one end of which is connected to the secondary beam slider, and the other end is connected to the wingtip of the folding trailing edge beam.

[0014] Furthermore, the hybrid structure folding wing also includes a slide rail, a secondary beam slider, a secondary beam slider locking device, a trailing edge beam fixing section, an inflatable skin, and a skin inflation / deflation device.

[0015] Furthermore, the secondary beam and slide rail are on top, and the main beam is below the secondary beam; or the main beam is on top, and the secondary beam and slide rail are below.

[0016] In another aspect, this utility model also provides an aircraft, including the above-described hybrid structure folding wing.

[0017] Furthermore, the aircraft is a tail-sitting vertical takeoff and landing aircraft, a flying car, a rotorcraft, a drone, or a single-person aircraft. This invention addresses the problems of existing technologies through the following methods.

[0018] 1. At the wing root of the folding diamond truss wing leading edge spar assembly, which consists of a main beam and a secondary beam, a rotatable, rigidly telescopic support rod is installed. One end of the rigidly telescopic support rod is hinged to the fuselage below the main and secondary beams, and the other end is hinged to the first connecting hinge point of the main and secondary beams. During the deployment / folding of the wing leading edge spar assembly, the main beam, secondary beam, and rigidly telescopic support rod move synchronously along the designed trajectory. After the wing leading edge spar assembly is deployed, the positions of the main beam, secondary beam, and rigidly telescopic support rod are locked, forming a stable, mutually supporting conical triangle at the wing root of the leading edge spar assembly. This strengthens the structure at the wing root of the leading edge spar assembly. Thus, the main beam, secondary beam, and rigidly telescopic support rod together constitute the structurally strengthened folding diamond continuous truss wing leading edge spar assembly (hereinafter referred to as: wing leading edge spar assembly).

[0019] 2. A rigid sliding link connects the wing leading-edge spars assembly and the trailing-edge spars at the second connecting hinge point of the wing leading-edge spars assembly. One end of the rigid sliding link is hinged to the second connecting hinge point of the main and secondary spars of the wing leading-edge spars assembly, and the other end is slidably connected to a rotating sleeve assembly hinged at the trailing-edge spars end. When the wing support frame is deployed, the rigid sliding link slides along the sleeve under the constraint of the rotating sleeve assembly and rotates with the rotating sleeve assembly, changing its position and length to adapt to the shape changes during wing deployment. When the wing support frame is fully deployed, the rigid sliding link slides to the designated position and is locked by the movable locking core in the rotating sleeve assembly. At this point, the rigid sliding link connects the wing leading-edge spars assembly and the wing trailing-edge spars into a single rigid frame.

[0020] Furthermore, the deployment process of the wing support frame is as follows: Under the force of the wing folding / deploying device, the wing leading edge spars assembly deploys horizontally, and the folding wing trailing edge spars deploy downwards synchronously, causing the rigid sliding link to move synchronously with the deployment of the wing leading edge spars assembly and the trailing edge spars. The wing leading edge spars assembly drives the rigid sliding link hinged to it to move outwards, and the folding wing trailing edge spars, through the rotating sleeve assembly connected to it, drives the rigid sliding link slidably connected to the rotating sleeve assembly to rotate and slide downwards inside the sleeve. When the wing leading edge spars and trailing edge spars are fully deployed, the rigid sliding link slides into place simultaneously. At this point, the movable locking core in the rotating sleeve assembly inserts into the corresponding slot on the rigid sliding link. One end of the rigid sliding link is fixed by the hinge point of the wing leading edge spars assembly, and the other end is locked by the rotating sleeve assembly on the wing trailing edge spars. Thus, the rigid sliding link connects the wing leading edge spars and trailing edge spars into a single unit through its own rigidity, forming an integrated wing support frame. The deployment / folding process of the wing support frame is reversible.

[0021] In summary, through the above technical improvements, an integrated wing support frame structure has been formed. When deployed, this wing support frame is an interconnected, stable, and complete rigid structure that can support the wing surface and bear the wing load.

[0022] The novel hybrid structure folding wing of this utility model can achieve the following objectives: the wing support frame is an integrated rigid support frame. When the wing support frame is unfolded, it is an interconnected, stable, and complete rigid structure that can support the wing surface and bear the wing load.

[0023] Furthermore, the wing support frame, inflatable skin, and related devices of this wing are combined to form a novel hybrid structure folding wing. Under the action of the wing folding / deploying device, the wing can be deployed / folded parallel to the longitudinal axis of the fuselage. After deployment, the wing forms a fixed wing, which can provide lift for the aircraft and bear the corresponding load. After folding, the volume and area of ​​the wing are reduced by several times, which facilitates storage and transportation. This invention is suitable for various types of aircraft that have such requirements for wing deployment / folding, thereby enabling the development of a series of new aircraft.

[0024] The main advantages of this utility model are:

[0025] 1. By adding rigid telescopic support rods, the wing root strength of the wing leading edge spars assembly was strengthened, and the wing folding / unfolding options were also increased.

[0026] 2. By adding a rigid sliding link and a rotating sleeve assembly, the leading edge spar assembly and the folding trailing edge spar are connected into a rigid integral wing support frame system, so that the inflatable wing skin can be connected to a stable wing support frame system.

[0027] 2. The implementation of the above two technical methods makes up for the defects of the existing technology and constitutes a "new type of hybrid structure folding wing" with complete and stable wing structure and controllable overall deformation, which can provide lift for the aircraft and bear the corresponding load.

[0028] In summary, the hybrid folding wing of this invention, when unfolded, forms a fixed-wing wing that can provide lift for the aircraft and bear corresponding loads. After folding, the volume and area of ​​the wing are reduced by several times, facilitating storage and transportation. This invention is applicable to various types of small and medium-sized, low-speed aircraft with horizontal wing unfolding / folding requirements, including tail-sitting vertical takeoff and landing aircraft, flying cars, rotorcraft, drones, or single-person aircraft, thereby generating a series of new types of aircraft. Attached Figure Description

[0029] To more clearly illustrate the technical solutions of the embodiments of this utility model, the accompanying drawings used in the embodiments of this application will be briefly introduced below. The accompanying drawings described below are only used to explain the technical solutions of this application.

[0030] Figure 1 This is a plan view of the hybrid structure folding wing of this utility model after it has been deployed (the left side shows the wing in the deployed state, and the right side shows the wing support frame in the deployed state).

[0031] Figure 2 This is a plan view of the hybrid structure folding wing of this utility model after folding (the left side shows the folded wing state, and the right side shows the folded wing support frame state).

[0032] Figure 3 for Figure 1 The view from angle AA (left side shows the wing in the deployed state, right side shows the wing support frame in the deployed state);

[0033] Figure 4 for Figure 1 A cross-sectional view of the BB line in the diagram;

[0034] Figure 5 for Figure 1 A cross-sectional view of the CC line in the diagram;

[0035] Figure 6 for Figure 1 A cross-sectional view of the DD line in the diagram;

[0036] Figure 7 for Figure 5 Enlarged view of section E (rotary sleeve assembly lock cylinder in the lowered state);

[0037] Figure 8 for Figure 5 Another enlarged view of section E (rotary sleeve assembly lock cylinder raised);

[0038] Figure 9 for Figure 5 Another enlarged view of the state of part E (rigid sliding link, rotating sleeve assembly in motion);

[0039] Figure 10 This is a cross-sectional view of the FF line;

[0040] Figure 11 A front view (wing deployed) of a multi-rotor tail-sitting vertical takeoff and landing aircraft equipped with the hybrid structure folding wing of this utility model.

[0041] Figure 12 for Figure 11 A top view of a multi-rotor tail-seated vertical takeoff and landing aircraft;

[0042] Figure 13 for Figure 11 A front view of a multi-rotor tail-seated vertical takeoff and landing aircraft with its wings folded.

[0043] Figure 14 for Figure 13 A top view of a multi-rotor tail-seated vertical takeoff and landing aircraft;

[0044] Number in the picture:

[0045] F – fuselage;

[0046] 1—Slide rail;

[0047] 2—Secondary beam slider;

[0048] 3—Secondary beam slider locking device;

[0049] 4—Rigid telescopic support rod;

[0050] 5—Upper main beam;

[0051] 6—Lower-level beam;

[0052] 7—Hinged joints of short members in the main and secondary beams;

[0053] 8—Secondary beam hinge point;

[0054] 9——Hinging point of main beam;

[0055] 10—Hinged joint at the root of the main beam;

[0056] 11—Hinge point at the root of the rigid telescopic support rod;

[0057] 12—Hinged joint point at the root of the secondary beam;

[0058] 13—Wing root support beam;

[0059] 14—Folded rear edge beam hinge point;

[0060] 15—Folded rear edge beam;

[0061] 15a – Rear edge beam fixed short section;

[0062] 16—Aileron of the trailing edge;

[0063] 17—Rotating sleeve assembly;

[0064] 18—Rigid sliding link;

[0065] 19—Tension cables of the rear edge beam;

[0066] 19a—Rear edge beam tension cable pivot;

[0067] 20 – Tensioning cables for the front and rear edge beams;

[0068] 21—Upper surface skin;

[0069] 22—Lower surface skin;

[0070] 23—Skin spacing cable;

[0071] 24—Differential pressure balancing valve;

[0072] 25 — Wing folding / deploying mechanism;

[0073] 26—Wing skin inflation / deflation device;

[0074] 27—Rotating sleeve hinge shaft;

[0075] 28—Electromagnet;

[0076] 29—Modible lock cylinder;

[0077] 30 — Spring. Detailed Implementation

[0078] To make the technical problem to be solved, the technical solution, and the beneficial effects of this utility model clearer, the present utility model will be further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the present utility model and are not intended to limit the present utility model.

[0079] This invention provides a novel hybrid structure folding wing that can be installed on an aircraft. Figure 1 This is a plan view of an aircraft using the hybrid structure folding wing of this utility model in the wing-deployed state. In the figure, the hybrid structure folding wing is installed on the fuselage F of the aircraft, and the wing is in the deployed state. The left side shows the fully deployed wing, and the right side shows the deployed wing support frame, forming a contrast between the two. Figure 2 This is a plan view of the aircraft, including the hybrid folding wing, in the folded wing state. The left side shows the folded wing state, and the right side shows the folded wing support frame state.

[0080] Furthermore, such as Figure 1 , Figure 2 and Figure 3As shown, the hybrid folding wing structure includes: a slide rail 1 fixed to the fuselage F, a secondary beam slider 2, a secondary beam slider locking device 3, a rigid telescopic support rod 4 (a bidirectional hydraulic rod is used in this embodiment), a folding diamond truss wing leading edge beam assembly, a folding trailing edge beam 15, a wing root support beam 13, a rotating sleeve assembly 17, and a rigid sliding link 18. These structures are interconnected through hinges and sliding connections to form the rigid foldable / unfoldable wing support frame shown in the figure. Specifically, the folding diamond truss wing leading edge beam assembly includes: an upper main beam 5 formed by connecting multiple members through main beam hinge points 9, and a lower beam 6 formed by connecting multiple members through secondary beam hinge points 8. The upper main beam 5 and the lower beam 6 are respectively hinged to each other through main and secondary beam short rod hinge points 7.

[0081] Furthermore, such as Figures 1-4 As shown, the secondary beam slider 2 and the slide rail 1 are slidably connected. The lower beam 6 is connected to the secondary beam slider 2 through the secondary beam wing root hinge point 12. The upper main beam 5 is connected to the fuselage F through the main beam wing root hinge point 10. The rodless end of the rigid telescopic support rod 4 (bidirectional hydraulic rod) is hinged to the fuselage F through the rigid telescopic support rod wing root hinge point 11, and the other end is hinged to the first hinge point among the main and secondary beam short rod hinge points 7.

[0082] In other embodiments, the positions of the main beam and the secondary beam can also be interchanged. For example, the secondary beam and the slide rail are on top, and the main beam is below the secondary beam, with the two hinged together to form the wing leading edge beam assembly. The purpose of this arrangement is that, for an aircraft landing in level flight, when the wing is folded, the wing skin naturally droops under gravity and can be folded from below the main beam without being affected by the hinge point 7 of the main and secondary beam short rods.

[0083] Furthermore, such as Figure 1 and Figure 2 As shown, the trailing edge beam fixing section 15a, which is fixed to the fuselage F, is pivotally connected to the folding trailing edge beam 15 via the folding trailing edge beam hinge point 14. Figure 2 The folding trailing edge beam 15 folds upward around the trailing edge beam hinge point 14; the trailing edge beam tension cable 19 uses the trailing edge beam tension cable pivot 19a as the pivot point, one end is connected to the secondary beam slider 2, and the other end is connected to the wing end of the folding trailing edge beam 15, and its length is set so that it can pull the folding trailing edge beam 15 to fully unfold when the wing leading edge beam assembly is fully unfolded.

[0084] Furthermore, such as Figure 1 , Figure 2 , Figure 3 and Figure 5 As shown, the front end of the rigid sliding link 18 is hinged to the second hinge point of the main and secondary beam short rod hinge point 7 of the wing leading edge beam assembly, and the rear half is slidably connected to the sleeve in the rotating sleeve assembly 17.

[0085] Furthermore, such as Figure 5 , Figures 7-10 As shown, the rotating sleeve assembly 17 is connected to the wingtip of the folding trailing edge beam 15 via its rotating sleeve hinge shaft 27. The rotating sleeve assembly 17 also includes an electromagnet 28, a movable lock core 29, and a spring 30. The electromagnet 28 can be powered by the aircraft's power supply and works in conjunction with the spring 30 to control the extension and retraction of the movable lock core 29.

[0086] Furthermore, such as Figures 1-6 As shown, the wing also includes a skin: an upper surface skin 21 and a lower surface skin 22 made of flexible material, which are separated and constrained by skin spacing cables 23 to form an inflatable wing skin. The inflatable wing skin is connected to the following structure: an upper main beam 5, a folding trailing edge beam 15, a trailing edge beam fixed short section 15a, a wing root support beam 13, and a surrounding structure composed of front and trailing edge beam tension cables 20. The above-mentioned wing support frame and the inflatable wing skin connected thereto, together with related auxiliary devices including a wing folding / deployment device 25 and a wing skin inflation / deflation device 26, constitute the novel hybrid structure folding wing of this utility model. This wing is used to install on the fuselage F, forming the aircraft of this embodiment using the novel hybrid structure folding wing.

[0087] In this embodiment, the working process of the novel hybrid structure folding wing is as follows:

[0088] Wing deployment process:

[0089] In the folded state, the wing folding / deployment device 25 (in this embodiment, a hydraulic pump assembly) injects hydraulic oil into the rodless chamber of the hydraulic rigid telescopic support rod 4 to pressurize it. The rodless chamber end of the hydraulic rod uses the wing root hinge point 11 of the rigid telescopic support rod as the support hinge point. The hydraulic rod extends outward to push the first hinge point of the main and secondary beam short rod hinge points 7 that are hinged to it to move outward. This causes the secondary beam slider 2 to slide upward along the slide rail 1, so that the wing leading edge beam assembly unfolds outward in the horizontal direction with the wing root hinge point 10 of the main beam as the fixed rotation point. At the same time, it drives the wing skin and rigid sliding link 18 connected to it to unfold outward. Simultaneously, the secondary beam slider 2 pulls the trailing edge beam tension cable 19 connected to it to move synchronously, and changes direction through the trailing edge beam tension cable pivot 19a as the turning point, pulling the folding trailing edge beam 15 to unfold downward with the folding trailing edge beam hinge point 14 as the axis, driving the rotating sleeve assembly 17 installed at the wingtip of the folding trailing edge beam 15 to move synchronously.

[0090] Specifically, during the deployment of the wing's leading and trailing edge spars, the rotating sleeve assembly 17 constrains the rigid sliding link 18 to its hinge point on the leading edge spars assembly. Figure 1The axis is the second hinge point (in the middle), and it rotates and slides along the designed trajectory.

[0091] Furthermore, when the hydraulic rigid telescopic support rod 4 is fully extended, it pushes the wing leading edge beam assembly to fully unfold into place, the secondary beam slider locking device 3 locks the lower layer beam 6, and at the same time, the folding trailing edge beam 15 is also unfolded into place by the pull of the trailing edge beam tension cable 19.

[0092] Furthermore, under the pull of the rotating sleeve assembly 17 at the leading edge spars and trailing edge spars of the wing, the rigid sliding link 18 rotates and slides along the rotating sleeve assembly 17. When the slot of the rigid sliding link 18 corresponds to the position of the movable locking core 29, the spring 30 in the rotating sleeve assembly 17 pushes the movable locking core 29 into the slot of the rigid sliding link 18, locking the rigid sliding link 18. Figure 5 , Figure 7 As shown. At this point, the rigid sliding link 18 connects the wing leading-edge spars and the wing trailing-edge spars into a single rigid structure, forming an integrated wing support frame, as shown. Figure 1 , Figure 3 , Figure 5 As shown.

[0093] Furthermore, when the wing support frame is fully deployed, the inflatable wing skin connected to the rods of the wing support frame is unfolded and flattened until it is fully supported.

[0094] Furthermore, after the wing support frame and the inflatable wing skin are fully deployed and supported, the wing skin inflation / deflation device 26 inflates the inside of the inflatable wing skin, causing it to bulge, tighten, shape, and harden its surface. At this time, the skin and the wing support frame together form a shape that meets the aerodynamic requirements of the wing design, and the structure is equivalent to a fixed wing. It can provide lift for the aircraft and bear and transmit loads. In addition, the trailing edge flaps 16 are mounted on the folding trailing edge spars 15 and can adjust the aerodynamic state of the wing.

[0095] At this point, the new hybrid structure folding wing has completed its deployment process. The deployed structure is shown in the reference image. Figure 1 and Figure 3 .

[0096] Wing folding process:

[0097] The steps for the hybrid structure folding wing of this utility model to change from the unfolded state to the folded state include: the wing skin inflation / deflation device 26 starts the deflation mode to expel most of the air in the inflatable skin, and the skin tension is reduced.

[0098] Furthermore, the aircraft power supply energizes the electromagnet 28, causing the upper and lower electromagnets 28 to generate like magnetic poles, thus creating a repulsive force. This pushes the electromagnet connected to the movable lock core 29 upward, causing the movable lock core 29 to be pulled out of the slot of the rigid sliding link 18, unlocking the rigid sliding link 18. Subsequently, the wing folding / deploying device 25 injects hydraulic oil into the rod-side cavity of the hydraulic rigid telescopic support rod 4, pushing the hydraulic rod to retract. This pulls the first hinge point of the main and secondary beam short rod hinge points 7, which are hinged to it, to move inward. This causes the secondary beam slider 2 to slide downward along the slide rail 1, causing the wing leading edge beam assembly to retract horizontally in the direction of fuselage F with the main beam wing root hinge point 10 as the fixed rotation point. At the same time, it causes the wing skin and rigid sliding link 18 connected to it to move inward, and pulls the folding trailing edge beam 15 to fold upward with the folding trailing edge beam hinge point 14 as the axis.

[0099] Furthermore, when the hydraulic rigid telescopic support rod 4 retracts to its full extent, it pulls the wing leading edge spar assembly to fully fold and retract, simultaneously causing the wing skin and folding trailing edge spar 15 to fold and retract to their final positions, completing the final folding. After the wing is fully folded, it folds horizontally into the fuselage F, changing its shape; its volume and area are reduced by several times, such as... Figure 2 As shown.

[0100] It should be understood that in this utility model:

[0101] There are other methods for folding / unfolding the wings, such as using a chain drive to directly pull the secondary beam slider 2 up and down along the slide rail 1; or using a winch cable to pull the secondary beam slider 2 up and down along the slide rail 1; for small aircraft, a single slide rail can be used, with the secondary beam slider 2 connected to the secondary beams of both wings, and the wings can be unfolded by mechanically or manually pushing and pulling the secondary beam slider 2 up and down along the slide rail 1.

[0102] Other implementation schemes may include different implementation methods for wing folding / deployment. The rigid telescopic support rod 4 is divided into active and passive types. The passive type rigid telescopic support rod does not provide power to drive wing folding / deployment. The hydraulic rigid telescopic support rod 4 in the first embodiment is active, while the passive type rigid telescopic support rod 4 can be used in other implementation schemes.

[0103] In some embodiments, such as for some smaller models, the rigid telescopic support rod 4 may not need to be installed.

[0104] In other embodiments, the wing leading edge spars and trailing edge spars can also employ independent mechanical devices to perform wing folding / deployment actions.

[0105] Other embodiments may further include a rigid sliding link 18 and a rotating sleeve assembly 17 combined to connect the wing leading edge spars assembly and the folding trailing edge spars into a whole. The rotating sleeve assembly 17 includes a mechanical or electromagnetic, or a combination of mechanical and electromagnetic, locking device. The function of the rotating sleeve assembly 17 is to constrain the rigid sliding link 18 to rotate and slide along a designed trajectory. When the wing is deployed, the rigid sliding link 18 is locked, making it a fixed rigid link between the wing leading edge spars assembly and the folding trailing edge spars, connecting the wing leading edge spars assembly and the folding trailing edge spars 15 into a unified structure. Further, the rotating sleeve assembly includes a sleeve hinge shaft, a rotating sleeve, a movable lock core, and a lock core drive device. The rotating sleeve, the movable lock core, and the lock core drive device are combined into a rotating sleeve assembly. The sleeve hinge shaft is vertically fixed to the wingtip of the wing trailing edge spars. The rotating sleeve assembly and the sleeve hinge shaft are hinged together and can rotate around the sleeve hinge shaft, together forming the rotating sleeve assembly.

[0106] For some smaller models, other embodiments may also include: the rotating sleeve assembly 17 and the rigid sliding link 18 can be locked by manual operation.

[0107] Other embodiments may also include variations in the rigid sliding link 18 and the rotating sleeve assembly 17. Regardless of the variation, as long as the rigid sliding link 18 is locked after the wing is deployed, connecting the wing leading edge spar assembly and the folding trailing edge spar 15 into an integrated structure, it falls within the scope of this utility model.

[0108] Second embodiment:

[0109] refer to Figures 11-14 This embodiment is a cross-shaped base multirotor tail-sitting vertical takeoff and landing aircraft with a novel hybrid structure folding wing.

[0110] Furthermore, Figure 11 This is a front view of a multirotor tail-sitting vertical takeoff and landing aircraft with its wings deployed. Figure 12 yes Figure 11 Top view; Figure 13 This is a front view of a multirotor tail-sitting vertical takeoff and landing aircraft with its wings folded. Figure 14 yes Figure 13 Top view.

[0111] Furthermore, such as Figure 11 , Figure 12 As shown, before takeoff, the aircraft's wings are fully deployed and inflated to form fixed-wing wings.

[0112] In this embodiment, the multiple rotors mounted on the cross-shaped base constitute a vector power platform. After the aircraft takes off vertically, the power output of each rotor can be controlled by the flight control system to control the aircraft to change from a vertical state to a horizontal flight state, and the aircraft's attitude in the air can also be adjusted and controlled.

[0113] Specifically, during the vertical takeoff and landing phase, the multi-rotor provides lift. Once the aircraft transitions to level flight, the fixed-wing wings provide lift, at which point the multi-rotor aircraft transforms into a fixed-wing aircraft. This significantly reduces the power required for flight, saves energy, and extends the aircraft's range.

[0114] Furthermore, during the landing phase, the flight control vectoring platform transitions the aircraft from level flight to a vertical flight. At this point, the wings no longer generate lift but are subject to airflow disturbances, reducing stability and controllability. To mitigate this, the flight control system folds the new hybrid folding wing. The folded wings are brought together on either side of the fuselage, significantly reducing the wingspan and wing area, thus drastically decreasing the aircraft's frontal area. This changes the aircraft's attitude from... Figure 11 Posture change Figure 13 This attitude allows the aircraft to land in a manner similar to that of a cross-shaped multirotor, greatly improving the stability and safety of the landing.

[0115] This embodiment shows that the novel hybrid structure folding wing's ability to fold / unfold horizontally is very suitable for tail-sitting vertical takeoff and landing aircraft, enabling it to accomplish scenarios that are impossible with existing technologies, enhancing the safety of aircraft landing, and expanding the application prospects of tail-sitting vertical takeoff and landing aircraft.

[0116] The above description is only a preferred embodiment of the present utility model and is not intended to limit the present utility model. Any modifications, equivalent substitutions and improvements made within the principles of the present utility model should be included within the protection scope of the present utility model.

Claims

1. A hybrid structure folding wing, comprising a folding wing leading edge spars assembly, a rigid telescopic support rod, a folding wing trailing edge spars, a rigid sliding link (18), a rotating sleeve assembly (17), and a wing root support beam, characterized in that: The front end of the rigid sliding link (18) is hinged to one of the hinge points (7) of the main and secondary beam short rods of the wing leading edge beam assembly, and the rear end is slidably connected to the rotating sleeve assembly (17) mounted on the folding trailing edge beam (15). The rotating sleeve assembly (17) contains a locking device.

2. The hybrid structure folding wing according to claim 1, characterized in that: When the wing is fully deployed, the locking device in the rotating sleeve assembly (17) locks the rigid sliding link (18), and the combination of the rotating sleeve assembly (17) and the rigid sliding link (18) connects the wing leading edge spars assembly and the folding wing trailing edge spars (15) into a rigid integral structure.

3. The hybrid structure folding wing according to claim 1, characterized in that: One end of the rigid telescopic support rod (4) is hinged to the fuselage (F) through the rigid telescopic support rod wing root hinge point (11), and the other end is hinged to the first hinge point among the main and secondary beam short rod hinge points (7). After the wing is deployed, at the wing root of the wing leading edge beam assembly, it forms an interconnected triangular support structure with the main beam (5) and secondary beam (6) in the wing leading edge beam assembly.

4. The hybrid structure folding wing according to claim 2, characterized in that: Rigid telescopic support rods (4) include active and passive types.

5. The hybrid structure folding wing according to claim 1, characterized in that: The rotating sleeve assembly (17) also includes a sleeve hinge shaft, a movable lock cylinder, and a lock cylinder drive device.

6. The hybrid structure folding wing according to claim 1, characterized in that: It also includes a rear edge beam tension cable (19), one end of which is connected to the secondary beam slider (2), and the other end is connected to the wing end of the folded rear edge beam (15).

7. The hybrid structure folding wing according to claim 1, characterized in that: It also includes slide rails, secondary beam sliders, secondary beam slider locking devices, rear edge beam fixing short sections, inflatable skins, and skin inflation / deflation devices.

8. The hybrid structure folding wing according to claim 1, characterized in that: The secondary beam and guide rail are on top, and the main beam is below the secondary beam; or the main beam is on top, and the secondary beam and guide rail are below.

9. An aircraft, characterized in that, Including the hybrid structure folding wing according to any one of claims 1 to 8.

10. The aircraft according to claim 9, characterized in that, The aircraft can be a tail-sitting vertical takeoff and landing aircraft, a flying car, a rotorcraft, a drone, or a single-person aircraft.

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