Hybrid structure folding triangular wing and aircraft

Abstract

The invention relates to the technical field of aviation, and particularly provides a foldable / unfoldable triangular fixed wing with a hybrid structure and an aircraft comprising the wing. The triangular wing supporting framework comprises a sliding rail, a wing leading edge beam, a wing trailing edge beam and a wing trailing edge beam sliding hinge assembly, and further comprises a skin stabilizing rib, and when the wing supporting framework is unfolded to the maximum wingspan, the skin stabilizing rib is limited and locked by the rotating sleeve connecting assembly. The number of rod pieces of the wing supporting framework structure is greatly reduced, the wing lift force is mainly generated by the inflatable skin, and therefore the wing structure is simple, and the weight of the wing is light.

Description

Technical Field

[0001] This invention relates to the field of aviation technology, specifically providing a foldable / deployable triangular fixed-wing wing with a hybrid structure and an aircraft including the wing. Background Technology

[0002] The wing is an important component of an aircraft, and folding wings are increasingly used in aircraft due to their space-saving design. Existing technologies, including Chinese patents (2016102280241, 2020107300708, 2024212063123) and US patents (US 10696376B2, US11584507B2), provide a triangular folding wing. This wing includes a foldable / deployable wing support frame composed of a slide rail, a foldable multi-triangular frame structure, skin support ribs, and skin connecting ribs, as well as upper and lower wing skins (partially inflatable skins) and folding flaps connected to the wing support frame. When subjected to the force of the wing folding / deployment device, the wing support frame can expand outwards to form a triangular fixed wing, providing lift for the aircraft, or fold towards the fuselage for easy storage and transportation.

[0003] The existing folding wing technology has the following problems:

[0004] 1. The foldable / deployable wing support frame structure is relatively complex, with many support rods and a relatively heavy weight.

[0005] 2. Due to the characteristics of the foldable / deployable wing support frame, the upper and lower skin surfaces of the wing are not interconnected and cannot be connected into a whole. Stability can only be maintained by the combined action of the wing support frame, skin support ribs, and skin connecting ribs, which makes the structural relationship between the wing skin and the wing support frame complicated.

[0006] 3. Due to the characteristics of its structure, it is impossible to install fixed flaps on the trailing edge of the wing. Folding flaps are complex, difficult to operate, and lack stability, which affects the aerodynamic control capability of the wing. Summary of the Invention

[0007] To address the above problems, this invention adopts a new concept and structure to solve the problems existing in the prior art, and provides a novel foldable / deployable hybrid triangular wing to provide lift for aircraft.

[0008] This invention provides a novel technical solution, an embodiment of which is a hybrid structure folding triangular wing, belonging to foldable / deployable fixed-wing wings.

[0009] The present invention provides a hybrid structure folding triangular wing, comprising a foldable / deployable triangular wing support frame made of rigid material and an inflatable skin made of flexible, airtight material. The triangular wing support frame includes: a slide rail, a leading-edge spar, a trailing-edge spar, and a sliding hinge assembly for the trailing-edge spar.

[0010] The slide rail is fixedly connected to the fuselage. The wing root of the wing leading edge spars is hinged to the fuselage through the wing root hinge point. The wing trailing edge spars sliding hinge assembly is slidably connected to the slide rail and can move back and forth along the slide rail. The wing root of the wing trailing edge spars is hinged to the wing trailing edge spars sliding hinge assembly. The wing tips of the wing leading edge spars and trailing edge spars are hinged to each other through the wing tip hinge points of the wing leading and trailing edge spars.

[0011] The triangular wing support frame also includes multiple generally parallel skin stabilizing ribs. The front end of the skin stabilizing rib is hinged to the lower surface of the wing leading edge spar via the wing leading edge spar hinge point. The rear end of the skin stabilizing rib is slidably connected to the rotating sleeve connecting assembly connected to the lower surface of the wing trailing edge spar. When the wing support frame is extended to its maximum wingspan, the skin stabilizing rib is limited and locked by the rotating sleeve connecting assembly.

[0012] Furthermore, the inflatable skin includes upper and lower surface skins that are closed on all four sides, and is connected to multiple skin spacer ribs, with through holes provided on the skin spacer ribs.

[0013] The edges of the inflatable skin are connected to the wing leading edge spars, wing trailing edge spars, and multiple sliding connectors on the rails. The middle is slidably connected by several connectors and multiple skin stabilizing ribs. The inflatable skin fills the internal space enclosed by the triangular wing support frame, forming the main wing surface, which is made of flexible, airtight, and foldable material.

[0014] Furthermore, the hybrid structure folding triangular wing includes a trailing edge flaperon, which is connected to the rear of the trailing edge spars of the wing.

[0015] The flaps and ailerons are used for aerodynamic control of the wing.

[0016] Furthermore, the hybrid structure folding triangular wing also includes a wing folding / deploying device, which is used to pull the sliding hinge assembly of the wing trailing edge spar, drive the wing root of the trailing edge spar to move along the slide rail, push the wing support frame to expand outward or retract inward around the wing root hinge point of the wing leading edge spar, and at the same time drive the inflatable skin connected to the wing support frame to expand or fold.

[0017] Furthermore, the hybrid structure folding triangular wing also includes a wing skin inflation / deflation device and a skin pressure difference measurement and control device, used for inflating or deflation of the inflatable skin, and for measuring and controlling the skin pressure difference.

[0018] Furthermore, in the hybrid structure folding triangular wing, after the wing is fully deployed, the wing skin inflation / deflation device inflates the inflatable skin to the design pressure through the air vent. After inflation, the skin bulges, tightens, shapes, and hardens on the surface, forming a wing aerodynamic shape that conforms to the design together with the wing support frame. This shape can generate and withstand aerodynamic loads during the flight of the aircraft, thus constituting the hybrid structure folding triangular wing.

[0019] Furthermore, the hybrid structure folding triangular wing is a foldable / deployable triangular fixed wing. The main wing surface formed by the inflatable skin transfers the aerodynamic loads generated and borne by the aircraft during flight to the wing support frame, thereby providing lift for the aircraft.

[0020] Furthermore, the wing trailing edge spar sliding hinge assembly and the wing skin sliding connector are arranged on the same track.

[0021] The folding / unfolding process of the hybrid structure folding triangular wing is a reversible process.

[0022] Furthermore, the inflatable skin is inflated by a stamping process.

[0023] In another aspect, the present invention provides an aircraft including the above-mentioned hybrid structure folding triangular wing, wherein the aircraft is a hand-launched UAV, a catapult-launched UAV, a storage, transportation and launch integrated UAV, an airdrop UAV, a submarine-launched UAV, a flying car, a tail-seat vertical take-off and landing aircraft or a personal aircraft.

[0024] This invention includes the following features and advantages:

[0025] 1. The shape, volume, and area of ​​the folded and unfolded wings of this invention undergo significant changes. When unfolded, the wings form a triangular fixed wing, which can provide lift for aircraft in need. When folded, the wings are folded into the fuselage, and the wingspan, area, and volume are reduced by several times compared to the unfolded wings, making them easier to store and transport.

[0026] 2. The number of rods in the wing support frame structure of the present invention is greatly reduced, and the wing lift is mainly generated by the inflatable skin. Therefore, the wing structure is simple and the wing weight is light.

[0027] 3. In this invention, the inflatable skin of the wing is tensioned, supported, shaped, and stabilized by a rigid support frame. The lift generated by the inflatable skin is also transferred to the wing support frame. The internal pressure of the inflatable skin only needs to maintain its aerodynamic stability during flight. Therefore, the internal inflation pressure of the inflatable skin does not need to be very high (compared to a fully inflatable wing), and the pressure difference between the inside and outside of the skin is relatively easy to maintain within a low pressure range. The resulting benefits are reduced requirements for the inflation device, resulting in lighter weight; the requirements for skin thickness and strength are also reduced accordingly, further reducing weight; and the technical requirements for the manufacturing process are correspondingly reduced, leading to lower prices.

[0028] 4. This invention is applicable to various types of aircraft that have such requirements for wing deployment / folding, including flying cars, drones used in different scenarios, tail-sitting vertical take-off and landing aircraft, unmanned transport vehicles, etc., thereby enabling the creation of a series of new types of aircraft. Attached Figure Description

[0029] To more clearly illustrate the technical solutions of the embodiments of the present invention, the accompanying drawings used in the embodiments of this application will be briefly described 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 triangular wing of the present invention after it has been deployed;

[0031] Figure 2 This is a frontal view of the hybrid structure folding triangular wing of the present invention after it has been deployed;

[0032] Figure 3 This is a schematic plan view of the folded hybrid structure folding triangular wing of the present invention.

[0033] Figure 4 for Figure 1 A view at angle AA in the image;

[0034] Figure 5 for Figure 1 A view from the BB angle in the image;

[0035] Figure 6 for Figure 1 Screenshot of E in the image;

[0036] Figure 7 This is a cross-sectional view of the CC line in screenshot E;

[0037] Figure 8 This is a cross-sectional view of the DD line in screenshot E;

[0038] Figure 9 A plan view of a drone with a hybrid structure folding triangular wing after its wings have been unfolded.

[0039] Figure 10 for Figure 9 Top view;

[0040] Figure 11 A schematic diagram of the folded wings of a drone equipped with a hybrid folding triangular wing.

[0041] Number in the picture:

[0042] F – fuselage;

[0043] 1—Slide rail;

[0044] 2—The hinge point at the wing root of the leading edge spars;

[0045] 3—Sliding hinge assembly for the wing trailing edge spars;

[0046] 4—The hinge point at the wing root of the trailing edge spars;

[0047] 5—Wing leading edge spars;

[0048] 6—Wing trailing edge spars;

[0049] 7—The hinge points at the wing tips of the leading and trailing edge spars;

[0050] 8—Skin wing root sliding connector;

[0051] 9—Wing trailing edge flaps and ailerons;

[0052] 10 – Skin stabilizing ribs;

[0053] 11—Hinge point of the leading edge beam of the skin stabilizing rib;

[0054] 12—Skin stabilizing rib rear edge beam rotary sleeve connection assembly;

[0055] 13—Skin stabilizing rib sliding connector;

[0056] 14—Inflatable skin;

[0057] 15 – Skin spacer ribs;

[0058] 16 — Wing folding / deploying mechanism;

[0059] 17—Skin inflation / deflation device;

[0060] 18—Skin internal and external pressure difference measurement and control device; Detailed Implementation

[0061] To make the technical problem to be solved, the technical solution, and the beneficial effects of the present invention clearer, the present invention 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 invention and are not intended to limit the present invention.

[0062] The present invention provides a hybrid structure folding triangular wing that can be installed on an aircraft.

[0063] This invention provides a novel technical solution, an embodiment of which is a hybrid structure folding triangular wing, belonging to foldable / deployable fixed-wing wings.

[0064] The present invention provides a hybrid structure foldable triangular wing, comprising a foldable / unfoldable triangular wing support frame made of rigid material and an inflatable skin made of flexible, airtight material. The triangular wing support frame includes: a slide rail, a leading-edge spar, a trailing-edge spar, and a sliding hinge assembly for the trailing-edge spar. The slide rail is fixedly connected to the fuselage. The wing root of the leading-edge spar is hinged to the fuselage via a hinge point at the wing root. The sliding hinge assembly for the trailing-edge spar is slidably connected to the slide rail and can move back and forth along the slide rail. The wing root of the trailing-edge spar is hinged to the sliding hinge assembly for the trailing-edge spar. The wingtips of the leading-edge and trailing-edge spars are hinged to each other via hinge points at the wingtips of the leading and trailing-edge spars.

[0065] Furthermore, the wing support frame of the hybrid structure folding triangular wing also includes multiple generally parallel skin stabilizing ribs for maintaining wing surface stability. These skin stabilizing ribs are made of elastic rigid materials (including carbon fiber materials, etc.), with their front ends hinged to the lower surface of the wing leading edge spars and their rear ends slidably connected to a rotating sleeve connecting assembly connected to the lower surface of the wing trailing edge spars. They can rotate and slide within the sleeve of the rotating sleeve connecting assembly around the hinge point on the lower surface of the wing leading edge spars as the wing support frame folds / unfolds. When the wing is fully unfolded, it is limited and locked by the hinge point on the leading edge spars and the rotating sleeve connecting assembly on the trailing edge spars.

[0066] First Embodiment

[0067] Figure 1 This is a plan view of the hybrid structure folding triangular wing of the present invention after it has been unfolded. In the figure, the slide rail 1 is fixedly installed on the fuselage F.

[0068] Specifically, the wing root of the leading edge spade 5 is hinged to the fuselage F via the wing root hinge point 2; the wing trailing edge spade sliding hinge assembly 3 is slidably connected to the slide rail 1; the wing root of the trailing edge spade 6 is hinged to the wing trailing edge spade sliding hinge assembly 3; and the wingtips of the leading edge spade 5 and the trailing edge spade 6 are hinged to each other via the wingtips hinge points 7. These structures together constitute the main body of the foldable / deployable triangular wing support frame of this application. Figure 1 , Figure 2 , Figure 3 As shown, where Figure 2 This is a frontal view of the triangular wing after it has been deployed; Figure 3 This is a planar schematic diagram of the triangular wing after it has been folded.

[0069] In one embodiment, the wing trailing edge spars sliding hinge assembly 3 includes: a slider slidably connected to the slide rail 1 and left and right trailing edge spars root hinge points 4 connected integrally by connecting ribs, such as... Figure 1 , Figure 3 , Figure 6 , Figure 8 As shown, where Figure 6 for Figure 1 Enlarged view of the area indicated by the dashed line.

[0070] Furthermore, the foldable / deployable triangular wing support frame also includes multiple substantially parallel skin stabilizing ribs 10. The front end of each skin stabilizing rib 10 is hinged to the lower surface of the wing leading edge spars 5 via a hinge point 11. The rear end of each skin stabilizing rib 10 is slidably connected to a rotating sleeve connecting assembly 12 connected to the lower surface of the wing trailing edge spars. The tail end of each skin stabilizing rib 10 is locked and limited by the rotating sleeve connecting assembly 12. The limiting length of each skin stabilizing rib 10 is the length of the wing support frame when deployed to its maximum wingspan (fully deployed), such as... Figure 1 , Figure 5 , Figure 6 As shown.

[0071] Furthermore, the slide rail 1 and the skin stabilizing rib 10 are roughly parallel, and are simultaneously hinged and slidably connected to the wing leading-edge spars 5 and the wing trailing-edge spars 6 via the fuselage F, forming a rigid triangular wing support frame. Under the force of the wing folding / deploying device 16, this wing support frame can move along the slide rail 1 about the wing root hinge point 2 of the wing leading-edge spars, deploying outwards or folding inwards, as shown below. Figure 1 , Figure 2 , Figure 3 As shown.

[0072] Furthermore, such as Figures 1 to 8As shown, the hybrid structure folding triangular wing also includes an inflatable skin 14. The inflatable skin 14 is composed of upper and lower surface skins that are connected by multiple skin spacer ribs 15 and are closed on all four sides. The shape of the skin spacer ribs 15 determines the cross-sectional shape of the inflatable skin 14, which conforms to the aerodynamic shape of the wing. The holes on the skin spacer ribs 15 form gas channels between the upper and lower surface skins. The inflatable skin 14 is made of a flexible airtight material.

[0073] Furthermore, such as Figures 1 to 8 As shown, the edge of the inflatable skin 14 is connected to the leading edge spars 5, the trailing edge spars 6, and multiple skin root sliding connectors 8 on the slide rail 1. The middle is slidably connected by the skin stabilizing rib sliding connector 13 and the skin stabilizing rib 10. The inflatable skin 14 fills the internal space enclosed by the triangular wing support frame and forms the main wing surface.

[0074] Furthermore, such as Figure 1 and 3 As shown, the trailing edge flap 9 of the wing is connected to the rear of the trailing edge spars 6 of the wing, forming the wing adjustment surface.

[0075] In summary, such as Figures 1 to 8 As shown, in this embodiment, a hybrid structure folding triangular wing is formed by a rigid triangular wing support frame that can be folded / unfolded and an inflatable skin that fills its internal space.

[0076] The process of folding and unfolding a hybrid structure folding delta wing is as follows: under the force of the wing folding / unfolding device 16 ( Figure 1 The sliding hinge assembly 3 of the trailing edge beam of the wing drives the wing root of the trailing edge beam 6, which is hinged to it, to move downward along the slide rail 1, pushing the wing support frame to unfold outward with the wing root hinge point 2 of the leading edge beam of the wing as the center, and at the same time driving the inflatable skin 14 connected to the wing support frame to unfold accordingly.

[0077] Furthermore, after the wing support frame is deployed to its maximum wingspan and locked, the inflatable skin 14 is fully stretched and deployed. The edges of the inflatable skin 14 are tensioned and fixed by the wing leading edge spars 5, the wing trailing edge spars 6, and multiple skin root sliding connectors 8 on the slide rail 1. The middle is connected and fixed by skin stabilizing rib sliding connectors 13 and multiple skin stabilizing ribs 10, as shown. Figure 1 , Figure 2 As shown.

[0078] Furthermore, the wing skin inflation / deflation device 17 inflates the inflatable skin 14 to a predetermined pressure through the air vent. The inflated skin bulges, tightens, shapes, and hardens, forming, together with the wing support frame, the desired aerodynamic shape of the wing, thus constituting a hybrid structure folding triangular wing, such as... Figure 1 , Figure 2 , Figures 4-8 As shown.

[0079] Furthermore, the inflatable skin 14 is equipped with a skin pressure difference measurement and control device 18, which is used to monitor and control whether the pressure difference between the inside and outside of the wing meets the expected requirements.

[0080] In summary, when fully deployed, the hybrid-structure folding triangular wing forms a triangular fixed-wing wing, which can provide lift for the aircraft, such as... Figure 1 , Figure 2 As shown.

[0081] The folding / deploying process of the hybrid structure folding triangular wing is reversible. During folding, the wing skin inflation / deflation device 17 first discharges most of the gas from the inflatable skin 14, reducing its tension. Then, under the force of the wing folding / deploying device 16, the wing trailing edge spar sliding hinge assembly 3 is unlocked and pulled, causing the wing root of the hinged wing trailing edge spar 6 to move upward along the slide rail 1, causing the wing support frame to retract towards the fuselage. Simultaneously, the skin stabilizing rib 10 and the inflatable skin 14 fold and retract, ultimately folding and retracting the wing to the fuselage. Figure 3 As shown.

[0082] Furthermore, such as Figure 3 and Figure 5 As shown in this embodiment, as the wing support frame folds, the skin stabilizing rib 10 is unlocked by the rotating sleeve connecting assembly 12 and slides out from the sleeve of the rotating sleeve connecting assembly 12. During the wing folding into the fuselage, some of the skin stabilizing ribs 10 cross at the tail. Because the skin stabilizing rib 10 has a certain elasticity and is in a long cantilever support state, there is a cross space above and below the cross position, so the cross process can be completed.

[0083] It should be understood that:

[0084] In other embodiments, the slide rails may be of different types or numbers, including a method that uses separate slide rails for each of the left and right wings.

[0085] In addition, the skin stabilizing rib 10 can also be configured as a forward-extending type, that is, by interchanging the positions of the aforementioned skin leading edge spar hinge point 11 and skin trailing edge spar rotating sleeve hinge assembly 12, so that the skin stabilizing rib 10 slides outward from the wing leading edge spar when the wing is folded. This approach is suitable for the requirements of some aircraft types, especially tail-seat vertical takeoff and landing aircraft.

[0086] In other embodiments, the wing trailing edge spar sliding hinge assembly 3 and the wing skin sliding connector 8 are arranged on the same track.

[0087] The folding / unfolding of the hybrid structure folding triangular wing of this application can also be done in a variety of ways, including: using various forms of mechanical unfolding, rubber band elastic unfolding, aerodynamic unfolding, drag chute unfolding, and manual unfolding / folding for small aircraft.

[0088] In other embodiments, the left and right wings may be folded / unfolded independently.

[0089] There are several ways to inflate pneumatic skins, including: inflating with high-pressure gas cylinders, using inflating / deflating mechanical devices, inflating with chemical reaction gases, and a combination of both methods.

[0090] In other embodiments, the number of skin stabilizing ribs 10 is variable, and drones used in some scenarios may not have skin stabilizing ribs 10.

[0091] Other embodiments also include using a stamping method to inflate the inflatable skin, that is: stamping holes are provided at specific positions of the hybrid structure folding triangular wing, and the inflatable skin is automatically inflated through the stamping holes during the flight of the aircraft, and the pressure difference between the inside and outside is automatically maintained to maintain the aerodynamic shape of the wing and provide lift for the aircraft.

[0092] Second embodiment:

[0093] refer to Figures 9-11 This embodiment is a drone that uses a hybrid structure folding triangular wing.

[0094] Furthermore, Figure 9 A plan view of a drone with a hybrid structure folding triangular wing after its wings have been unfolded. Figure 10 for Figure 9 A top-down view of the drone; Figure 11 This is a plan view of a drone with a hybrid folding triangular wing after its wings have been folded.

[0095] Furthermore, the drone in the second embodiment can be used in different application scenarios, including hand-launched drones, catapult-launched drones, integrated storage, transportation and launch drones, airdrop drones, submarine-launched drones, etc.

[0096] In other embodiments, the aforementioned hybrid folding triangular wing can also be used in personal aircraft for low-altitude flight.

[0097] The above description is merely a preferred embodiment of the present invention and is not intended to limit the present invention.

[0098] Any modifications, equivalent substitutions, and improvements made within the principles of this invention shall be included within the scope of protection of this invention.

Claims

1. A hybrid structure folding triangular wing, comprising a foldable / deployable triangular wing support frame made of rigid material, and an inflatable skin (14) made of flexible, airtight material, characterized in that: The triangular wing support frame includes: a slide rail (1), a wing leading edge spars (5), a wing trailing edge spars (6), and a wing trailing edge spars sliding hinge assembly (3). The slide rail (1) and the fuselage (F) are fixedly connected; The wing root of the leading edge spars (5) is hinged to the fuselage (F) through the wing root hinge point (2). The sliding hinge assembly (3) of the trailing edge spars is slidably connected to the slide rail (1) and can move back and forth along the slide rail (1). The wing root of the trailing edge spars (6) is hinged to the sliding hinge assembly (3). The wing tips of the leading edge spars (5) and the trailing edge spars (6) are hinged to each other through the wing tip hinge points (7) of the leading and trailing edge spars. The triangular wing support frame also includes multiple roughly parallel skin stabilizing ribs (10). The front end of the skin stabilizing rib (10) is hinged to the lower surface of the wing leading edge beam (5) through the wing leading edge beam hinge point (11). The rear end of the skin stabilizing rib (10) is slidably connected to the rotating sleeve connecting assembly (12) connected to the lower surface of the wing trailing edge beam. When the wing support frame is extended to the maximum wingspan, the skin stabilizing rib (10) is limited and locked by the rotating sleeve connecting assembly (12).

2. The hybrid structure folding triangular wing according to claim 1, characterized in that, The inflatable skin (14) includes upper and lower surface skins that are closed on all four sides, and is connected to multiple skin spacer ribs (15), and the skin spacer ribs (15) are provided with through holes.

3. The hybrid structure folding triangular wing according to claim 1, characterized in that, The periphery of the inflatable skin (14) is connected to the wing leading edge spar (5), the wing trailing edge spar (6) and multiple skin root sliding connectors (8) on the slide rail (1), and the middle is slidably connected by skin stabilizing rib sliding connectors (13) and skin stabilizing ribs (10).

4. The hybrid structure folding triangular wing according to claim 1, characterized in that, It also includes a trailing edge flaperon (9), which is connected to the rear of the trailing edge spar (6).

5. The hybrid structure folding triangular wing according to claim 1, characterized in that, It also includes a wing folding / deploying device (16), which is used to pull the wing trailing edge beam sliding hinge assembly (3), drive the wing root of the trailing edge beam (6) to move along the slide rail (1), push the wing support frame to unfold outward or retract inward with the wing root hinge point (2) of the wing leading edge beam as the center, and at the same time drive the inflatable skin (14) connected to the wing support frame to unfold or fold.

6. The hybrid structure folding triangular wing according to claim 1, characterized in that, It also includes a wing skin inflation / deflation device (17) and a skin pressure difference measurement and control device (18) for inflation or deflation of the inflatable skin (14) and for measuring and controlling the pressure difference between the inside and outside of the skin.

7. The hybrid structure folding triangular wing according to claim 1, characterized in that, The wing trailing edge spar sliding hinge assembly (3) and the wing skin sliding connector (8) are set on the same track.

8. The hybrid structure folding triangular wing according to claim 1, characterized in that, The inflatable skin (14) is inflated by stamping.

9. An aircraft comprising a hybrid structure folding triangular wing according to any one of claims 1-8, wherein the aircraft is a hand-launched UAV, a catapult-launched UAV, a storage, transport and launch integrated UAV, an airdropped UAV, a submarine-launched UAV, a flying car, a tail-seat vertical takeoff and landing aircraft, or a personal aircraft.

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