Folding assembly and vertical take-off and landing aircraft

Abstract

The utility model discloses a folding assembly and a vertical take-off and landing aircraft, and relates to the technical field of aircrafts, the folding assembly comprises a fixed wing, a folding wing and a locking piece, and the fixed wing is provided with a fixed wing locking hole; the folding wings are rotationally connected with the fixed wings, and folding wing locking holes are formed in the folding wings; the locking piece is connected with the fixed wing, the locking piece comprises a telescopic rod, the telescopic rod is connected with the locking piece in a sliding mode, the telescopic rod is in clearance fit with the locking hole, and the telescopic rod is in clearance fit with the locking hole of the folding wing; the telescopic rods can lock or unlock the folding wings so that the folding wings can be unfolded or folded. According to the technical scheme provided by the utility model, the problem that the volume space is limited when the light aircraft is transported, stored and maintained on land can be solved.

Description

Technical Field

[0001] This utility model relates to the field of aircraft technology, and in particular to a folding assembly and a vertical take-off and landing aircraft. Background Technology

[0002] Tiltrotor and tiltrotor vertical takeoff and landing (VTOL) aircraft are flight vehicles that can take off and land on the spot without a runway. During flight, the tiltrotor and tiltwing components tilt as the flight speed increases. During VTOL takeoff and landing, the thrust direction of the tiltrotor and tiltwing components is approximately perpendicular to the ground. After the aircraft takes off and exceeds a certain stall speed, the tiltrotor and tiltwing components complete their tilt. The lift generated by the tiltrotor is approximately perpendicular to the airflow direction, while the thrust output direction of the tiltrotor components is approximately horizontal to the airflow direction. This allows the aircraft to maintain flight performance and endurance by combining the lift from the wings and the thrust from the tiltrotor.

[0003] Lightweight fixed-wing aircraft face numerous limitations in takeoff and landing space, land transportation, storage, and maintenance due to their wingspan. This utility model's folding assembly can be used to solve these problems. Utility Model Content

[0004] The main purpose of this utility model is to propose a folding component and an aircraft, which aims to solve many problems caused by size limitations in take-off and landing space, land transportation, storage and maintenance of vertical take-off and landing aircraft, so as to make the aircraft have a wider range of application scenarios and practicality.

[0005] To achieve the above objectives, the present invention proposes a folding assembly comprising a fixed wing, a folding wing, and a locking member. The fixed wing has a fixed wing locking hole; the folding wing is rotatably connected to the fixed wing and has a folding wing locking hole; the locking member is connected to the fixed wing and includes a telescopic rod, which is slidably connected to the locking member. The telescopic rod is clearance-fitted with the locking hole and the folding wing locking hole; the telescopic rod can lock or unlock the folding wing to allow it to unfold or fold.

[0006] In one embodiment, the folding assembly further includes a rotating shaft connected to the folding wing and rotatably connected to the fixed wing, the rotating shaft being located at one end of the folding wing near the fixed wing.

[0007] In one embodiment, the folding assembly further includes a reset elastic element, the two ends of which are respectively connected to the fixed wing and the folding wing.

[0008] In one embodiment, the fixed wing is provided with a fixed wing beam, which connects the fixed wing and the rotating shaft, and the fixed wing beam is located at one end of the fixed wing near the rotating shaft.

[0009] In one embodiment, the folding assembly further includes a cable connected to the folding wing. The connection point between the cable and the folding wing is at a certain distance from the rotation axis. The cable can tighten the folding wing so that the end of the folding wing away from the fixed wing rotates downward and contacts the ground.

[0010] In one embodiment, the folding wing includes a first support member connected to the folding wing, the first support member being located at the end of the folding wing away from the fixed wing.

[0011] In one embodiment, the fixed wing has two fixed wing locking holes, the folding wing has two folding wing locking holes, the locking member is located between the two fixed wing locking holes, and the locking member includes two telescopic rods that can pass through the two fixed wing locking holes and the two folding wing locking holes respectively, so as to unfold or fold the folding wing.

[0012] In one embodiment, the fixed wing further includes a flaperon, which is rotatably connected to the fixed wing and is located at one end of the locking member.

[0013] This utility model also proposes a vertical takeoff and landing aircraft that combines a tilt wing, a tilt rotor, and a foldable fixed wing, including a flight component and a folding component, wherein the end of the fixed wing away from the folding wing is connected to the flight component.

[0014] In one embodiment, the flight assembly further includes a forward-tilting rotor and a second support member. The forward-tilting rotor is rotatably connected to the flight assembly and connected to the second support member. Rotation of the forward-tilting rotor can drive the second support member to rotate, so that the second support member supports the ground and ensures stable support of the aircraft on the ground.

[0015] This invention provides a folding assembly consisting of a fixed wing, a folding wing, and a locking component. The fixed wing and the folding wing each have locking holes. The folding wing and fixed wing are connected by a rotational connection to achieve the folding action. The locking component is connected to the fixed wing and includes a telescopic rod. The telescopic rod is slidably connected to the locking component and forms a clearance fit with the locking holes, allowing the telescopic rod to slide freely within both the fixed wing and folding wing locking holes. The telescopic rod can lock or unlock the folding wing. Before flight, the telescopic rod retracts and unlocks, causing the folding wing to rotate downwards and fold under the pull of the cable until it touches the ground for stable support. During flight, the cable relaxes, causing the folding wing to rotate upwards and unfold under the torque of the return elastic element and aerodynamic lift until it is fully unfolded and docked with the fixed wing. At this point, the telescopic rod extends, locking the folding wing and fixed wing together as a single unit. This design effectively utilizes the aerodynamic lift acting on the wings during flight to assist in the deployment of the folding wings, improving flight efficiency. When the flight speed is reduced to minimum for vertical landing, the gravity of the folding wings effectively assists in their downward folding, reducing the complexity of the folding wing's drive mechanism and the power of the drive unit. Simultaneously, during landing, the folding wings can act as landing gear supports, and also solve many problems caused by size limitations in takeoff and landing space, land transportation, storage, and maintenance, making the aircraft more versatile and practical. Furthermore, the design of this folding component is simple and effective, easy to implement, and adaptable to different flight conditions and mission requirements. Attached Figure Description

[0016] To more clearly illustrate the technical solutions in the embodiments of this utility model or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this utility model. For those skilled in the art, other drawings can be obtained based on the structures shown in these drawings without creative effort.

[0017] Figure 1 A front view schematic diagram of an embodiment of the folding component provided by this utility model;

[0018] Figure 2 A side view of another embodiment of the folding component provided by this utility model;

[0019] Figure 3 A top view schematic diagram of an embodiment of the folding component provided by this utility model installed on an aircraft wing;

[0020] Figure 4A top view schematic diagram of an embodiment of the vertical takeoff and landing aircraft provided by this utility model;

[0021] Figure 5 A side view of the structure of another embodiment of the vertical takeoff and landing aircraft provided by this utility model;

[0022] Figure 6 This is a front view schematic diagram of another embodiment of the vertical take-off and landing aircraft provided by this utility model.

[0023] Explanation of icon numbers:

[0024] 100. Folding assembly; 1. Fixed wing; 1a. Fixed wing locking hole; 2. Folding wing; 2a. Folding wing locking hole; 3. Locking element; 31. Telescopic rod; 4. Rotating shaft; 5. Reset elastic element; 11. Fixed wing spars; 6. Cable; 7. First support element; 200. Vertical takeoff and landing aircraft; 8. Flight assembly; 12. Flaps and ailerons; 9. Forward tilt rotor; 91. Nose propeller; 10. Second support element.

[0025] The realization of the purpose, functional features and advantages of this utility model will be further explained in conjunction with the embodiments and with reference to the accompanying drawings. Detailed Implementation

[0026] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the scope of protection of the present utility model.

[0027] It should be noted that if the embodiments of this utility model involve directional indicators (such as up, down, left, right, front, back, etc.), the directional indicators are only used to explain the relative positional relationship and movement of the components in a specific posture. If the specific posture changes, the directional indicators will also change accordingly.

[0028] Furthermore, if the embodiments of this utility model involve descriptions such as "first" or "second," these descriptions are for descriptive purposes only and should not be construed as indicating or implying their relative importance or implicitly specifying the number of technical features indicated. Therefore, a feature defined with "first" or "second" may explicitly or implicitly include at least one of those features. Additionally, the use of "and / or" or "and / or" throughout the text includes three parallel solutions. For example, "A and / or B" includes solution A, solution B, or a solution where both A and B are satisfied simultaneously. Furthermore, the technical solutions of the various embodiments can be combined with each other, but this must be based on the ability of those skilled in the art to implement them. When the combination of technical solutions is contradictory or impossible to implement, it should be considered that such a combination of technical solutions does not exist and is not within the scope of protection claimed by this utility model.

[0029] This utility model proposes a folding component 100.

[0030] Please see Figure 1 In one embodiment of this utility model, the folding assembly 100 includes a fixed wing 1, a folding wing 2, and a locking member 3. The fixed wing 1 has a fixed wing locking hole 1a, and the folding wing 2 has a folding wing locking hole 2a. The folding wing 2 and the fixed wing 1 are rotatably connected via a rotating shaft 4. The locking member 3 is connected to the fixed wing 1 and includes a telescopic rod 31. The telescopic rod 31 is slidably connected to the locking member 3 and is clearance-fitted with the fixed wing locking hole 1a and the folding wing locking hole 2a. The telescopic rod 31 can lock or unlock the folding wing 2 so that the folding wing 2 can be unfolded or folded.

[0031] In this embodiment, the fixed wing 1 is one of the main components of the folding assembly 100. It is fixed to both sides of the fuselage of the aircraft 200 and is responsible for generating lift during flight. The fixed wing 1 has a fixed wing locking hole 1a, which is located at the end of the fixed wing 1 away from the fuselage of the aircraft 200, facilitating the expansion of the fixed wing 1's function. The trailing edge of the fixed wing 1 is equipped with a controllable flaperon 12. The flaperon 12 is used to control the aircraft's roll motion during flight and to increase lift during takeoff and landing. The fixed wing 1 adopts a specific airfoil to generate lift during flight. The material of the fixed wing 1 typically needs to have high strength, lightweight, and fatigue resistance. Traditional materials for the fixed wing 1 include aluminum alloys and composite materials (such as carbon fiber reinforced plastics).

[0032] The folding wing 2 is the basic component for folding the folding assembly 100. The folding wing 2 aircraft 200 changes its state during different flight phases to adapt to different flight environments and performance requirements. Specifically, the folding wing 2 unfolds to generate lift during flight and folds to reduce the aircraft's volume and space during landing. The folding wing 2 typically involves complex mechanical structures, such as linkage mechanisms, gear mechanisms, and torsion spring-pulley mechanisms, which control the folding and unfolding of the folding wing 2. Alternatively, servo motors or hydraulic drives can be used to control and drive the folding and unfolding of the folding wing 2. In some designs, torsion springs are introduced at the hinges to assist in driving the rotation of the folding wing 2 in improving drive performance. The material selection for the folding wing 2 usually needs to balance lightweight and high strength. Traditional materials include aluminum alloys and carbon fiber composites to reduce weight while ensuring sufficient load-bearing capacity. In some designs, to reduce structural weight and improve flight efficiency, weight reduction is carried out while ensuring structural strength, such as by creating weight reduction holes and slots, using materials such as carbon fiber plates, polypropylene plastics, and aluminum alloys.

[0033] In one embodiment, the locking element 3 is generally bolted or welded to the fixed wing 1, and the locking element 3 includes a telescopic rod 31. The telescopic rod 31 is slidably connected to the locking element 3 via a lead screw or guide rail, and the telescopic rod 31 locks and unlocks with the fixed wing locking hole 1a on the fixed wing 1 and the folding wing locking hole 2a on the folding wing 2 through clearance fit. This design allows the telescopic rod 31 to lock the deployed folding wing 2 during flight, ensuring that the folding wing 2 remains fixed during flight, while it can be easily unlocked when landing or when folding is required, allowing the folding wing 2 to fold smoothly, facilitating the landing, parking, or transportation of the aircraft 200. This locking mechanism can be used in various foldable aircraft, such as tiltrotor aircraft or UAVs with folding wing 2 functionality, which can change their wingspan when needed to adapt to different flight conditions or space constraints. The folding assembly 100 improves the maneuverability and adaptability of the aircraft 200 during flight, reduces parking and transportation space after landing, and facilitates rapid deployment. Furthermore, the locking and unlocking function of the telescopic boom 31 ensures safety and stability during various flight phases. Regarding material properties, considering that the locking element 3 needs to withstand repeated mechanical stresses and possible extreme environmental conditions, the telescopic boom 31 and the fixed-wing locking hole 1a are typically made of high-strength, wear-resistant, and corrosion-resistant materials. These materials may include stainless steel, aluminum alloy, or titanium alloy, which ensure the reliability and durability of the locking element 3 during long-term use. For example, stainless steel has good corrosion resistance and sufficient strength, making it suitable for use in marine or chemical environments. Titanium alloy, due to its high strength-to-weight ratio and wear resistance, is suitable for applications requiring high safety. Aluminum alloy is lightweight and high-strength, suitable for applications requiring weight reduction. The selection of these materials must comprehensively consider factors such as the operating environment, safety requirements, and budget to ensure the performance and service life of the locking element 3.

[0034] The technical solution of this utility model involves designing a folding assembly 100, which consists of a fixed wing 1, a folding wing 2, and a locking member 3. The fixed wing 1 and the folding wing 2 each have a fixed wing locking hole 1a and a folding wing locking hole 2a. The folding wing 2 is rotatably connected to the fixed wing 1 via a rotating shaft 4 to achieve the folding action. The locking member 3 is connected to the fixed wing 1 and includes a telescopic rod 31. The telescopic rod 31 is slidably connected to the locking member 3 and forms a clearance fit with the fixed wing locking hole 1a and the folding wing locking hole 2a, allowing the telescopic rod 31 to slide freely within these holes. The telescopic rod 31 can lock or unlock the folding wing 2. Through the extension and retraction of the telescopic rod 31, the folding wing 2 can be unfolded or folded under external force. Before flight, the telescopic rod 31 retracts and unlocks, causing the folding wing 2 to fold downwards and touch the ground under the pull of gravity and the cable 6, acting as landing gear to provide stable support for the aircraft. During flight, the folding wing 2 unfolds upwards and outwards under the torque of the reset elastic element 5 and the lift of the wing surface, ultimately aligning the fixed wing locking hole 1a and the folding wing locking hole 2a. The telescopic rod 31 extends, locking the folding wing 2, maximizing the lift generated by the fixed wing and folding wing, thus improving flight efficiency. This design effectively utilizes the gravity and lift of the folding wing, making the folding mechanism simple, effective, and easy to implement, while reducing the folding drive power. Simultaneously, the folding wing enables the aircraft to function as landing gear, adapting to various vertical takeoff and landing, landing, transportation, and storage requirements.

[0035] In one embodiment of this utility model, please refer to Figure 1 and Figure 2 The folding assembly 100 also includes a rotating shaft 4, which is connected to the fixed wing beam 11 of the folding wing 2. The rotating shaft 4 is rotatably connected to the fixed wing 1 and is located at the end of the fixed wing 1 near the folding wing 2.

[0036] In one embodiment, the rotatable connection between the fixed wing 1 and the folding wing 2 is achieved via a rotating shaft 4, which is welded or bolted to the fixed wing 1 and located at the end of the fixed wing 1 closest to the folding wing 2. Specifically, the folding wing 2 can rotate 180° relative to the fixed wing 1, with the end of the fixed wing 1 furthest from the folding wing 2 fixedly connected to the fuselage of the aircraft 200, the fixed wing 1 and the folding wing 2 rotatably connected, and the rotating shaft 4 located between the fixed wing 1 and the folding wing 2. The folding assembly 100 allows the aircraft 200 to achieve a compact size through the folding wings, facilitating storage and transportation, while also providing rapid deployment capabilities, enabling the aircraft 200 to quickly increase lift and improve aerodynamic efficiency and flight performance. Furthermore, the precise control of the deployment angle of the folding wing 2 via the cable 6 enhances the maneuverability and adaptability of the aircraft 200. In terms of materials, the rotating shaft 4, as a key component bearing shear forces, is typically made of high-strength, good toughness, and wear-resistant materials. For example, 40Cr quenched and tempered steel is often used to manufacture the rotating shaft 4 due to its excellent comprehensive properties, such as strength, toughness, and wear resistance. In addition, the surface of the rotating shaft 4 may require special treatment, such as plating or coating, to improve its corrosion resistance and reduce the coefficient of friction, thereby extending its service life and improving its reliability.

[0037] In one embodiment of this utility model, please refer to Figure 2 The folding assembly 100 also includes a reset elastic element 5, with the two ends of the reset elastic element 5 connected to the fixed wing 1 and the folding wing 2, respectively.

[0038] In this embodiment, the folding assembly 100 also includes a reset elastic element 5. The two ends of the reset elastic element 5 are connected to the fixed wing 1 and the folding wing 2, respectively. The reset elastic element 5 is generally made of spring steel or shape memory alloy. The reset elastic element 5 provides the necessary torque when the folding wing 2 unfolds or folds, ensuring that the folding wing 2 can move smoothly to a predetermined position and maintain its position when needed. The design of the reset elastic element 5 needs to consider its elastic modulus, strength, deformation, and fracture properties to ensure that the material can return to its pre-stress state after the external force is removed. The reset elastic element 5 improves the reliability of folding and unfolding of the folding wing 2, reduces the influence of external forces on the wing surface position, and maintains good performance after multiple unfolding and folding operations. Furthermore, the use of the reset elastic element 5 can reduce additional unfolding drive power and locking mechanisms, thereby reducing the complexity and weight of the entire folding assembly 100. The reset elastic element 5 typically needs to have a high elastic modulus, good fatigue strength, and corrosion resistance. Commonly used materials include stainless steel, titanium alloys, or high-performance engineering plastics. These materials can maintain stable elastic properties under different environmental conditions while resisting fatigue failure under repeated loading. For example, shape memory alloys (such as nickel-titanium alloys) can remember their original shape after being deformed and return to their original shape when subjected to specific stimuli (such as temperature changes). This property makes them very useful in the resetting application of folding wings 2.

[0039] In one embodiment of this utility model, please refer to Figure 1 The fixed wing 1 is provided with a fixed wing beam 11, which is connected to the fixed wing 1. The fixed wing beam 11 is located at one end of the fixed wing 1 near the rotating shaft 4.

[0040] In one embodiment, the fixed wing 1 is equipped with a fixed wing spars 11. This design is typically used to ensure that the wing can be precisely positioned in a predetermined location when deployed or folded. Specifically, the fixed wing spars 11 are bolted or welded to the fixed wing 1, ensuring that the rotation axis 4 is located at the end of the fixed wing spars 11 near the folding wing 2. This arrangement allows the fixed wing spars 11 to interact directly with the rotation axis 4 or with the folding wing 2, limiting the rotation range of the folding wing 2, preventing it from exceeding its designed position, and ensuring the stability and safety of the wing during deployment and folding. Specifically, the rotation range of the folding wing 2 is 30° to 180°, meaning that when the folding wing 2 is fully folded, the angle between it and the fixed wing 1 is 30°, and when the folding wing 2 is fully deployed, the angle between it and the fixed wing 1 is 180°. The fixed wing spars 11 are typically made of high-strength and high-modulus materials, such as aluminum alloy or carbon fiber reinforced composite materials. These materials ensure that the fixed wing spars 11 maintains structural integrity and functionality during continuous use. In some applications, to improve the service life of the fixed wing sparle 11 and reduce maintenance, a special coating or treatment may be applied to the surface of the fixed wing sparle 11 to enhance its corrosion resistance. The fixed wing sparle 11 improves the reliability and safety of the entire folding assembly 100, ensuring that the folding wing is accurately positioned under various load conditions, thereby reducing potential risks caused by improper wing positioning.

[0041] In one embodiment of this utility model, please refer to Figure 1 and Figure 6 The folding assembly 100 also includes a cable 6, which is connected to the folding wing 2. The connection point between the cable 6 and the folding wing 2 is kept at a certain distance from the rotation axis 4. The cable 6 can tighten the folding wing 2 so that the end of the folding wing 2 away from the fixed wing 1 rotates downward and comes into contact with the ground.

[0042] In this embodiment, cable 6 serves as a key connection and tensioning element. One end of cable 6 is connected to the folding wing 2, and the other end can be connected to the cabin of the aircraft 200 or have a separate tensioning device. This arrangement allows cable 6 to apply tension to the folding wing 2 to achieve folding, ensuring that the end of the folding wing 2 away from the fixed wing 1 can abut against the ground or other supporting surface for support when the aircraft lands. This design is typically used to ensure the stability of the folding wing 2 in its deployed state and its compactness in its folded or transported state. Cable 6 can improve the stability of the folding wing 2 after folding, ensuring that the folding wing 2 remains in the correct position under various operating conditions. In addition, the design of cable 6 helps to provide additional support when the folding wing 2 is deployed, reducing the load on the fixed wing 1, the folding wing 2, and the folding assembly 100, thereby improving the reliability and durability of the entire structure. In terms of material properties, cable 6 is typically made of high-strength, wear-resistant, and corrosion-resistant materials to ensure reliability and durability in long-term use. Common cable materials include stainless steel wire rope, aramid fiber, or polyester fiber, which provide the required strength and flexibility while maintaining a relatively light weight.

[0043] In one embodiment of this utility model, please refer to Figure 4 and Figure 5 The folding wing 2 includes a first support member 7, which is connected to the folding wing 2 and is located at the end of the folding wing 2 away from the fixed wing 1.

[0044] In one embodiment, the first support member 7 is part of the folding wing 2 structure. The first support member 7 is generally a roller or support structure. It is directly connected to the folding wing 2 via bolts or clips to ensure necessary support for the aircraft 200 when the folding wing 2 is folded and in contact with the ground, maintaining the stability and strength of the first support member 7. The first support member 7 is located at the free end of the folding wing 2, i.e., the end furthest from the fixed wing 1. Its streamlined shape reduces aerodynamic drag during flight, improving the stability and efficiency of the aircraft 200. The first support member 7 may include reinforcing ribs, support beams, a shell, or other structural elements to enhance the rigidity, load-bearing capacity, and aerodynamic shape of the folding wing 2. The use of the first support member 7 improves the reliability and durability of the folding wing 2, especially during frequent deployment and folding. The material selection for the first support member 7 needs to consider strength, weight, and corrosion resistance. Commonly used materials include aluminum alloys, titanium alloys, and carbon fiber composites. These materials have a high strength-to-weight ratio, providing sufficient strength and rigidity while maintaining a lightweight structure.

[0045] In one embodiment of this utility model, please refer to Figure 1 and Figure 2The fixed wing 1 has two fixed wing locking holes 1a, and the folding wing 2 has two folding wing locking holes 2a. The locking member 3 is located between the two fixed wing locking holes 1a. The locking member 3 includes two telescopic rods 31. The two telescopic rods 31 can be respectively inserted into the two fixed wing locking holes 1a and the two folding wing locking holes 2a so that the folding wing 2 can be unfolded or folded.

[0046] In this embodiment, the fixed wing 1 has two fixed wing locking holes 1a, and a locking member 3 is located between these two fixed wing locking holes 1a. The locking member 3 includes two telescopic rods 31. The folding wing 2 also has two corresponding folding wing locking holes 2a. The locking member 3 connects the two locking holes of the fixed wing 1 and the folding wing 2 through the two telescopic rods 31. The telescopic rods 31 can slide between the fixed wing locking holes 1a and the folding wing locking holes 2a to accommodate the locking and unlocking of the folding wing 2. When the folding wing 2 needs to be deployed or folded, the telescopic rods 31 can be locked or unlocked to fix or release the movement of the folding wing 2. This design allows the folding wing 2 to have precise positioning when deployed and folded, ensuring the stability of the wing and the reliability of the structure during flight. The design of the telescopic rods 31 provides flexible locking and unlocking functions, making the deployment and folding process of the folding wing 2 smoother and more controllable. Through the design of the two telescopic rods 31, the load can be evenly distributed, giving the folding wing 2 the ability to resist shear force, bending moment, and torque, and reducing local stress concentration caused by locking and unlocking.

[0047] In one embodiment of this utility model, please refer to Figure 3 The fixed wing 1 also includes a flaperon 12, which is rotatably connected to the fixed wing 1 and is located at one end of the locking member 3.

[0048] In one embodiment, the fixed wing 1 also includes flaperons 12, which are important flight control surfaces combining the functions of flaps and ailerons. Specifically, the flaperons 12 are typically mounted on the trailing edge of the fixed wing 1 and can deflect in both directions to achieve the dual function of flaps and ailerons. When the flaperons 12 on both wings deflect downwards simultaneously, they act as flaps to increase lift, which is particularly important for takeoff and landing. When the flaperons 12 deflect in the opposite direction, they act as ailerons, enabling roll control during flight. The design of the flaperons 12 helps to shorten the takeoff and landing distances of the aircraft, and the application of flaperons improves the aircraft's maneuverability and safety in flight. The flaperons 12 are typically made of high-strength, lightweight materials, such as aluminum alloys or composite materials, to ensure sufficient strength and rigidity while minimizing the overall weight of the aircraft. These materials also have good fatigue resistance to withstand repeated deflection maneuvers during flight.

[0049] This utility model also proposes a vertical takeoff and landing aircraft 200, please refer to [link / reference needed]. Figure 4 and Figure 5 The vertical takeoff and landing (VTOL) aircraft 200 includes a flight component 8 and a folding component 100. The specific structure of the VTOL aircraft 200 is as described in the above embodiments. Since this VTOL aircraft 200 adopts all the technical solutions of all the above embodiments, it possesses at least all the beneficial effects brought about by the technical solutions of the above embodiments, which will not be elaborated upon here. The fixed wing 1, at the end furthest from the folding wing 2, is connected to the flight component 8.

[0050] In this embodiment, the vertical takeoff and landing (VTOL) aircraft 200 integrates a flight component 8 and a folding component 100. Due to the folding component 100 design, the VTOL aircraft 200 can be folded up during ground operations and vertical takeoff and landing, significantly reducing its space requirements and making storage and transportation more convenient. The rapid deployment mechanism of the folding wing 2 allows the VTOL aircraft 200 to quickly transition from storage or transportation mode to flight mode, improving its utilization efficiency. Through the flaps and ailerons 12 on the fixed wing 1, the VTOL aircraft 200 can achieve better roll and lift control during flight, thereby improving its maneuverability and controllability. The design of the VTOL aircraft 200 allows it to be used in various application scenarios, such as carrying payloads for reconnaissance, observation, surveillance, cargo transportation, or agricultural spraying drones, or carrying manned cockpits for manned aircraft carriers, demonstrating multi-functional adaptability and flexibility.

[0051] In one embodiment of this utility model, please refer to Figures 4 to 6 The flight assembly 8 also includes a forward tilt rotor 9 and a second support member 10. The forward tilt rotor 9 is rotatably connected to the flight assembly 8 and is connected to the second support member 10. Rotation of the forward tilt rotor 9 can drive the second support member 10 to rotate so that the second support member 10 supports the ground.

[0052] In one embodiment, the combination of the forward tilt rotor 9 and the second support member 10 provides support for the front end of the VTOL aircraft 200, enabling the VTOL aircraft 200 to have greater flexibility and stability when switching between VTOL and horizontal flight modes. Specifically, the forward tilt rotor 9 is rotatably connected to the flight assembly 8 to adapt to different flight modes. For example, in VTOL mode, the forward tilt rotor 9, along with the front rotor 91, rotates to 90 degrees perpendicular to the ground, with the front rotor 91 providing upward thrust, and the forward tilt rotor 9 having minimal impact on the thrust of the front rotor; while when tilting to transition to forward flight mode, the angle of the forward tilt rotor 9 needs to be gradually reduced to a position close to 0 degrees horizontal, so that the forward tilt rotor 9 provides lift and the front rotor 91 provides forward thrust. The forward-tilt rotor 9 is connected to the second support member 10, which extends rearward from the position of the forward rotor 91. During flight, the second support member 10 rotates with the forward-tilt rotor 9 to a near-0-degree horizontal position to reduce air resistance. During vertical takeoff and landing (VTOL) of the aircraft 200, the second support member 10 rotates with the forward-tilt rotor 9 to a near-vertical angle, acting as the nose landing gear to support the weight of the VTOL aircraft 200 and providing a certain altitude and stable support for mounting the cockpit or cargo hold underneath. The design of the second support member 10 may include one or more retractable struts. The material selection for the forward-tilt rotor 9 and the second support member 10 needs to consider strength, weight, and corrosion resistance. Commonly used materials include aluminum alloys and carbon fiber composites. These materials not only provide the required strength and rigidity but also maintain the structural lightness, thereby improving the performance of the VTOL aircraft 200. In summary, this vertical takeoff and landing aircraft 200 design, by combining a forward-tilting rotor 9 and a second support 10 with a fixed wing 1 and a folding wing 2, provides an efficient, flexible, and stable flight solution suitable for a variety of flight conditions and mission requirements.

[0053] The above description is merely an exemplary embodiment of the present utility model and does not limit the patent scope of the present utility model. Any equivalent structural transformations made based on the technical concept of the present utility model and the contents of the present utility model specification and drawings, or direct / indirect applications in other related technical fields, are included within the patent protection scope of the present utility model.

Claims

1. A folding assembly for use in an aircraft, characterized in that, include: Fixed wing (1), the fixed wing (1) is provided with a fixed wing locking hole (1a); Folding wing (2), the folding wing (2) is rotatably connected to the fixed wing (1), and the folding wing (2) is provided with a folding wing locking hole (2a); as well as Locking member (3), the locking member (3) is connected to the fixed wing (1), the locking member (3) includes a telescopic rod (31), the telescopic rod (31) is slidably connected to the locking member (3), the telescopic rod (31) is clearance-fitted with the fixed wing locking hole (1a), and the telescopic rod (31) is clearance-fitted with the folding wing locking hole (2a); The telescopic rod (31) can lock or unlock the folding wing (2) to allow the folding wing (2) to unfold or fold.

2. The folding assembly as claimed in claim 1, characterized in that, The folding assembly also includes a rotating shaft (4), which is connected to the folding wing (2) and rotatably connected to the fixed wing (1). The rotating shaft (4) is located at one end of the folding wing (2) near the fixed wing (1).

3. The folding assembly as described in claim 2, characterized in that, The folding assembly also includes a reset elastic element (5), the two ends of which are connected to the fixed wing (1) and the folding wing (2), respectively.

4. The folding assembly as described in claim 3, characterized in that, The fixed wing (1) is provided with a fixed wing beam (11), which connects the fixed wing (1) and the rotating shaft (4). The fixed wing beam (11) is located at one end of the fixed wing (1) near the rotating shaft (4).

5. The folding assembly as claimed in claim 4, characterized in that, The folding assembly also includes a cable (6) connected to the folding wing (2). The connection point between the cable (6) and the folding wing (2) is kept at a certain distance from the rotation axis (4). The cable (6) can tighten the folding wing (2) so that the end of the folding wing (2) away from the fixed wing rotates downward and comes into contact with the ground.

6. The folding assembly as claimed in claim 5, characterized in that, The folding wing (2) includes a first support member (7) connected to the folding wing (2) and located at the end of the folding wing (2) away from the fixed wing (1).

7. The folding assembly as described in any one of claims 1 to 6, characterized in that, The fixed wing (1) has two fixed wing locking holes (1a), the folding wing (2) has two folding wing locking holes (2a), the locking member (3) is located between the two fixed wing locking holes (1a), the locking member (3) includes two telescopic rods (31), the two telescopic rods (31) can be respectively inserted into the two fixed wing locking holes (1a) and the two folding wing locking holes (2a) so that the folding wing (2) can be unfolded or folded.

8. The folding assembly as claimed in claim 7, characterized in that, The fixed wing (1) also includes a flaperon (12), which is rotatably connected to the fixed wing (1) and is located at one end of the locking member (3).

9. A vertical takeoff and landing aircraft, characterized in that, include: Flight components (8); and In any one of claims 1 to 8, the fixed wing (1) is connected to the flight assembly (8) at one end away from the folding wing (2).

10. The vertical takeoff and landing aircraft as described in claim 9, characterized in that, The flight assembly (8) also includes a forward tilt rotor (9) and a second support member (10). The forward tilt rotor (9) is rotatably connected to the flight assembly (8), and the forward tilt rotor (9) is connected to the second support member (10). The rotation of the forward tilt rotor (9) can drive the second support member (10) to rotate, so that the second support member (10) supports the ground when the aircraft lands.

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