Aircraft with tilting rotor structure

Abstract

The utility model discloses an aircraft with a tilt rotor structure, which comprises an aircraft, four tilt rotors and a supporting mechanism are arranged at the top of the aircraft, the supporting mechanism comprises four fixing blocks fixedly connected to the front side and the rear side of the bottom of the aircraft, the inner walls of the fixing blocks are movably connected with round rods through bearings, and the round rods are connected with the tilt rotors through bearings. A supporting frame is fixedly connected to the surface of the round rod, pulleys are installed on the left side and the right side of the bottom of the supporting frame, the supporting frame can turn over backwards through the round rod, and a driving mechanism is arranged at the bottom of the aircraft. When the aircraft is used, under the action of the supporting mechanism, the driving mechanism and the hanging mechanism, the bottom of the aircraft can hang goods and the supporting frame can be automatically folded, and the supporting mechanism and the driving mechanism share one power source, so that energy waste is reduced, and inconvenience in use caused by the fact that the aircraft cannot hang goods and the supporting frame is prone to hooking obstacles is avoided; therefore, the device has the advantage of being convenient to use.

Description

Technical Field

[0001] This utility model relates to the field of aircraft technology, specifically to an aircraft with a tilt rotor structure. Background Technology

[0002] Aircraft with a tiltrotor structure are called tiltrotor aircraft, also known as aerial "hybrids." These aircraft combine the advantages of helicopters and fixed-wing aircraft, enabling vertical takeoff and landing, hovering, and high-speed cruise flight. They have wide applications in various fields such as early warning, transportation, surveillance, emergency medical assistance, and military missions, bringing new breakthroughs and possibilities to the development of aircraft.

[0003] For example, Chinese Patent Application No. 202222020836.0 discloses a tilt-wing aircraft with a novel control structure, including a fuselage. Wing assemblies are provided on both sides of the fuselage. Each wing assembly includes a fixed wing section and a movable wing section, with the movable wing section located outside the fixed wing section. A power system is located in front of the movable wing section. A tilt control mechanism for controlling the movable wing section is installed inside the fuselage cabin. The tilt control mechanism includes a fixed support and a tilt shaft. A servo is mounted on the fixed support, a servo arm is mounted on the servo, a servo disc is mounted on the servo arm, a drive gear is mounted on the servo disc, and a driven gear is mounted on the tilt shaft. The driven gear meshes with the drive gear. This invention uses a tilt control mechanism inside the cabin to perform vector differential control on the movable wing sections and the power system on both sides of the wing, thereby achieving better flight performance, good wind resistance, simple control, and good maneuverability.

[0004] During the use of tiltrotor aircraft, the inability to mount cargo on their underside typically limits their ability to perform various missions. Furthermore, the non-foldable support frame increases the impact volume of the aircraft's underside, making it prone to snagging on obstacles such as tree branches and power lines when flying over trees or urban areas, potentially leading to loss of control or even damage.

[0005] Therefore, it is necessary to design and modify aircraft with tiltrotor structures to effectively prevent them from easily snagging on obstacles. Utility Model Content

[0006] To address the problems mentioned in the background art, the purpose of this utility model is to provide an aircraft with a tilting rotor structure, which has the advantages of ease of use and solves the problem of easily snagging on obstacles.

[0007] To achieve the above objectives, this utility model provides the following technical solution: an aircraft with a tilting rotor structure, comprising an aircraft, four tilting rotors disposed on the top of the aircraft, a support mechanism, the support mechanism comprising four fixed blocks fixedly connected to the front and rear sides of the bottom of the aircraft, a round rod movably connected to the inner wall of the fixed block via bearings, a support frame fixedly connected to the surface of the round rod, pulleys installed on the left and right sides of the bottom of the support frame, the support frame being able to flip backward via the round rod, and a drive mechanism disposed at the bottom of the aircraft.

[0008] As a preferred embodiment of this utility model, the drive mechanism includes a dual-axis motor fixedly connected to the bottom of the aircraft. A long rod and a short rod are fixedly connected to the front and rear output ends of the dual-axis motor, respectively. A bevel gear one is fixedly connected to the end of the long rod and the short rod away from the dual-axis motor. A bevel gear two meshes with the surface of the bevel gear one. The inner wall of the bevel gear two is fixedly connected to the surface of the round rod. The bevel gear two can synchronously drive the support frame to rotate through the round rod. A mounting mechanism is provided at the bottom of the aircraft.

[0009] As a preferred embodiment of this utility model, the mounting mechanism includes a fixed plate fixedly connected to the bottom of the aircraft. Two sliding blocks are slidably connected to the inner wall of the fixed plate. A movable block is fixedly connected to the inner side of the sliding block. The inner wall of the movable block is threadedly connected to the surface of the long rod. A hanging rod is fixedly connected to the back of the movable block. The movable block can drive the hanging rod to move backward when the long rod rotates.

[0010] As a preferred embodiment of this utility model, a groove is provided on the rear side of the inner wall of the fixing plate. The groove can engage with the rear end of the hanging rod when it moves to the rear, thereby preventing the hung object from falling off and improving the hanging strength of the hanging rod.

[0011] As a preferred embodiment of this invention, protective boxes are fixedly connected to both the front and rear sides of the bottom of the aircraft, and the protective boxes can protect the drive mechanism to operate stably.

[0012] As a preferred embodiment of this invention, the surfaces of the long rod and the short rod are movably connected by bearings to a plurality of limiting plates, which can support the short rod and the long rod while stabilizing their rotation.

[0013] Compared with the prior art, the beneficial effects of this utility model are as follows:

[0014] 1. When this utility model is used, under the action of the support mechanism, the drive mechanism and the mounting mechanism, the bottom of the aircraft can be loaded with cargo and the support frame can be retracted, avoiding the inconvenience caused by the aircraft being unable to load cargo and the support frame easily getting caught on obstacles, thus giving it the advantage of being easy to use.

[0015] 2. This utility model achieves automatic tilting of the support frame by setting up a drive mechanism, thus improving operational efficiency. The dual-axis motor is driven by bevel gears, resulting in a compact structure and stable power transmission. Furthermore, this mechanism also provides a power source for the mounting mechanism, achieving functional integration and optimization. Attached Figure Description

[0016] Figure 1 This is a schematic diagram of the structure of this utility model;

[0017] Figure 2 This is a schematic diagram of the bottom of the structure of this utility model;

[0018] Figure 3 This is a schematic diagram of the drive mechanism of this utility model;

[0019] Figure 4 This is a schematic diagram of the mounting mechanism of this utility model.

[0020] In the diagram: 1. Aircraft; 2. Tilting rotor; 3. Fixed block; 4. Round rod; 5. Support frame; 6. Pulley; 7. Dual-axis motor; 8. Long rod; 9. Short rod; 10. Bevel gear one; 11. Bevel gear two; 12. Fixed plate; 13. Sliding block; 14. Movable block; 15. Hanging rod; 16. Groove; 17. Protective box; 18. Limiting plate. Detailed Implementation

[0021] 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 protection scope of the present utility model.

[0022] like Figures 1 to 4 As shown, the present invention provides an aircraft with a tilting rotor structure, including an aircraft 1, four tilting rotors 2 on the top of the aircraft 1, a support mechanism, and four fixed blocks 3 fixedly connected to the front and rear sides of the bottom of the aircraft 1. The inner wall of the fixed blocks 3 is movably connected to a round rod 4 through bearings. A support frame 5 is fixedly connected to the surface of the round rod 4. Pulleys 6 are installed on the left and right sides of the bottom of the support frame 5. The support frame 5 can be flipped to the rear by the round rod 4. A drive mechanism is provided at the bottom of the aircraft 1.

[0023] refer to Figure 3The drive mechanism includes a dual-axis motor 7 fixedly connected to the bottom of the aircraft 1. The output ends of the dual-axis motor 7 on the front and rear sides are respectively fixedly connected to a long rod 8 and a short rod 9. The ends of the long rod 8 and the short rod 9 away from the dual-axis motor 7 are fixedly connected to a bevel gear 10. The surface of the bevel gear 10 meshes with a bevel gear 2 11. The inner wall of the bevel gear 2 11 is fixedly connected to the surface of the round rod 4. The bevel gear 2 11 can synchronously drive the support frame 5 to rotate through the round rod 4. The bottom of the aircraft 1 is provided with a mounting mechanism.

[0024] As a technical optimization of this utility model, the automatic flipping of the support frame 5 is achieved by setting a drive mechanism, thereby improving operational efficiency. The dual-axis motor 7 is driven by bevel gears, resulting in a compact structure and stable power transmission. In addition, this mechanism also provides a power source for the mounting mechanism, realizing functional integration and optimization.

[0025] refer to Figure 4 The mounting mechanism includes a fixed plate 12 fixedly connected to the bottom of the aircraft 1. Two sliding blocks 13 are slidably connected to the inner wall of the fixed plate 12. A movable block 14 is fixedly connected to the inner side of the sliding block 13. The inner wall of the movable block 14 is threadedly connected to the surface of the long rod 8. A hanging rod 15 is fixedly connected to the back of the movable block 14. The movable block 14 can drive the hanging rod 15 to move to the rear when the long rod 8 rotates.

[0026] As a technical optimization of this utility model, by setting up a mounting mechanism, the aircraft 1 can carry cargo, improving its practicality and multi-mission capability. The threaded connection design between the movable block 14 and the long rod 8 allows the mounting rod 15 to move stably to the rear and engage with the groove 16, ensuring the stability of the load.

[0027] refer to Figure 4 The rear side of the inner wall of the fixing plate 12 is provided with a groove 16. The groove 16 can engage with the rear end of the hanging rod 15 when it moves to the rear side, thereby preventing the hanging object from falling and improving the hanging strength of the hanging rod 15.

[0028] As a technical optimization of this utility model, the stability and safety of the mounting mechanism are further enhanced by setting a groove 16 on the rear side of the inner wall of the fixing plate 12. When the mounting rod 15 is engaged in the groove 16, it can prevent the mounted object from falling off during flight due to vibration or airflow, thereby improving the mounting strength of the aircraft 1.

[0029] refer to Figure 2 Protective boxes 17 are fixedly connected to the front and rear sides of the bottom of the aircraft 1. The protective boxes 17 can protect the drive mechanism and ensure stable operation.

[0030] As a technical optimization of this utility model, the protective box 17 protects the drive mechanism from interference and damage from the external environment, ensuring its stable operation. At the same time, the protective box 17 also serves to insulate sound and reduce vibration, improving the overall performance and comfort of the aircraft 1.

[0031] refer to Figure 3 Multiple limiting plates 18 are movably connected to the surfaces of the long rod 8 and the short rod 9 via bearings. The limiting plates 18 can support the short rod 9 and the long rod 8 while stabilizing their rotation.

[0032] As a technical optimization of this utility model, by setting the limiting plate 18, additional support and stability are provided for the long rod 8 and the short rod 9, preventing them from swaying or deviating during rotation. This helps to improve the transmission efficiency and stability of the drive mechanism, ensuring the normal operation of the aircraft 1 under various working conditions.

[0033] The working principle and usage of this utility model: This aircraft 1 combines tiltrotors 2 with an innovative support, drive, and mounting mechanism. When the aircraft 1 needs to take off or fly, the four tiltrotors 2 provide the necessary lift and maneuverability. In particular, its support mechanism comes into play when the aircraft 1 needs to be parked on the ground or uneven terrain or to perform certain tasks. The support mechanism consists of four fixed blocks 3, which are movably connected to a round rod 4 via bearings. A support frame 5 is fixed on the round rod 4. When the support frame 5 needs to be deployed, the drive mechanism is activated. A dual-axis motor 7 drives the long rod 8 and the short rod 9 to rotate, transmitting power to the round rod 4 through the meshing of bevel gear 10 and bevel gear 2 11, causing the support frame 5 to rotate 90 degrees forward around the round rod 4. The pulleys 6 at the bottom of the support frame 5 help reduce friction with the ground, facilitating the movement of the aircraft 1. When retraction is needed, the dual-axis motor 7 can be reversed. Furthermore, the mounting mechanism allows the aircraft 1 to carry cargo on its bottom. Driven by the drive mechanism, the long rod 8 rotates, causing the hanging rod 15 to move rearward via the threaded movable block 14. When the hanging rod 15 moves to the groove 16 on the rear side of the inner wall of the fixed plate 12, it engages with the groove, ensuring that the load is secure and does not fall off (the cargo is supported and mounted using existing hooks and ropes). This avoids the inconvenience caused by the aircraft 1's inability to mount cargo and the support frame 5 easily getting caught on obstacles, thus giving it the advantage of ease of use.

[0034] In summary, when this utility model is used, under the action of the support mechanism, the drive mechanism and the mounting mechanism, the bottom of the aircraft 1 can be loaded with cargo and the support frame 5 can be retracted. This avoids the inconvenience caused by the aircraft 1 being unable to load cargo and the support frame 5 easily getting caught on obstacles, thus giving it the advantage of being easy to use and solving the problem of it easily getting caught on obstacles.

[0035] It should be noted that, in this document, relational terms such as "first" and "second" are used only to distinguish one entity or operation from another, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Furthermore, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such process, method, article, or apparatus.

[0036] Although embodiments of the present invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the present invention, the scope of which is defined by the appended claims and their equivalents.

Claims

1. An aircraft with a tiltrotor structure, comprising an aircraft (1), wherein four tiltrotor blades (2) are disposed on the top of the aircraft (1), characterized in that: The support mechanism includes four fixed blocks (3) fixedly connected to the front and rear sides of the bottom of the aircraft (1). The inner wall of the fixed block (3) is movably connected to a round rod (4) through a bearing. The surface of the round rod (4) is fixedly connected to a support frame (5). The left and right sides of the bottom of the support frame (5) are equipped with pulleys (6). The support frame (5) can be flipped to the rear through the round rod (4). The bottom of the aircraft (1) is provided with a drive mechanism.

2. An aircraft with a tiltrotor structure according to claim 1, characterized in that: The drive mechanism includes a dual-axis motor (7) fixedly connected to the bottom of the aircraft (1). The output ends of the dual-axis motor (7) on the front and rear sides are respectively fixedly connected to a long rod (8) and a short rod (9). The ends of the long rod (8) and the short rod (9) away from the dual-axis motor (7) are fixedly connected to a bevel gear (10). The surface of the bevel gear (10) is meshed with a bevel gear (11). The inner wall of the bevel gear (11) is fixedly connected to the surface of the round rod (4). The bevel gear (11) can synchronously drive the support frame (5) to rotate through the round rod (4). The bottom of the aircraft (1) is provided with a mounting mechanism.

3. An aircraft with a tiltrotor structure according to claim 2, characterized in that: The mounting mechanism includes a fixed plate (12) fixedly connected to the bottom of the aircraft (1). Two sliding blocks (13) are slidably connected to the inner wall of the fixed plate (12). A movable block (14) is fixedly connected to the inner side of the sliding block (13). The inner wall of the movable block (14) is threadedly connected to the surface of the long rod (8). A hanging rod (15) is fixedly connected to the back of the movable block (14). The movable block (14) can drive the hanging rod (15) to move to the rear when the long rod (8) rotates.

4. An aircraft with a tiltrotor structure according to claim 3, characterized in that: The inner wall of the fixing plate (12) has a groove (16) on the rear side. The groove (16) can engage with the rear end of the hanging rod (15) when it moves to the rear side, thereby preventing the hanging object from falling and improving the hanging strength of the hanging rod (15).

5. An aircraft with a tiltrotor structure according to claim 1, characterized in that: The aircraft (1) has protective boxes (17) fixedly connected to both the front and rear sides of its bottom. The protective boxes (17) can protect the drive mechanism and ensure stable operation.

6. An aircraft with a tiltrotor structure according to claim 2, characterized in that: The surfaces of the long rod (8) and the short rod (9) are movably connected by bearings to a plurality of limiting plates (18), which can support the short rod (9) and the long rod (8) while stabilizing their rotation.

Images