Efficient folding composite eVTOL aircraft

Abstract

The invention discloses an efficient folding composite eVTOL aircraft, and relates to the technical field of aircrafts, a storage cabin is arranged in a fuselage, a straight wing folding driving part is arranged in the storage cabin, the straight wing folding driving part comprises a steering engine disc, long connecting rods are hinged to the two ends of the steering engine disc, straight wings are symmetrically arranged on the two sides of the fuselage, the output end of a rotary steering engine is connected with the straight wings, and the output end of the rotary steering engine is connected with the storage cabin. The sleeve is fixedly arranged on the rotary steering engine, the free end of the long connecting rod is hinged to the sleeve, the fixed supporting plate is arranged in the storage cabin, swing rods are hinged to the four corners of the top end of the fixed supporting plate, the free ends of the swing rods are connected with rotors, and the rotor folding driving part is fixedly arranged on the fixed supporting plate. By arranging the folding mechanism, efficient linkage folding of the straight wings and the rotor wings is achieved, so that the aircraft has the multi-mode capacity of vertical take-off and landing, high-speed cruising and compact storage and transportation at the same time, and the diversified application scene requirements are met.

Description

Technical Field

[0001] The present invention relates to the field of aircraft technology, and more specifically, to a highly efficient foldable composite eVTOL aircraft. Background Art

[0002] With the rapid development of low-altitude economy and new productivity, vertical take-off and landing aircraft (eVTOL) is a new type of aircraft that has developed rapidly in recent years and has become an important solution for future urban air traffic. Among them, the rotor-fixed-wing composite eVTOL aircraft has gradually become one of the most promising eVTOL aircraft because of its vertical take-off and landing performance and high-speed flight capability, stable and smooth transition and strong controllability.

[0003] However, existing aircraft usually have the following defects: 1. The folding mechanism is mostly achieved by rotating through mechanical parts such as connecting rods and ball joints. The bearing capacity of this type of structure is weak, especially when the aircraft is under high dynamic loads or complex flight conditions, the structural stability is difficult to ensure; 2. The impact is large during the deformation state conversion, resulting in uneven deformation and low service life of parts; 3. The wing root has limited bearing capacity due to space and structural limitations, and it can easily become a weak link in the design. In addition, there are safety hazards in using only one power system, which is difficult to meet the future aircraft's requirements for high efficiency and stability under complex working conditions. Summary of the invention

[0004] In order to overcome the defects of the prior art, the present invention proposes a highly efficient foldable composite eVTOL aircraft. Through the set folding mechanism, the efficient linkage folding of the straight wings and the rotors is achieved, so that the aircraft has the multi-modal capabilities of vertical take-off and landing, high-speed cruising and compact storage and transportation, meeting the needs of diverse application scenarios.

[0005] To achieve this object, the present invention adopts the following technical solutions:

[0006] The present invention provides a highly efficient folding composite eVTOL aircraft, comprising a fuselage, a straight wing folding mechanism and a rotor folding mechanism, wherein a storage cabin is arranged in the fuselage, the straight wing folding mechanism comprises a straight wing folding driving unit, a long connecting rod, a sleeve, a universal joint, a rotary servo and a straight wing, the straight wing folding driving unit is arranged in the storage cabin, the straight wing folding driving unit comprises a servo disc, both ends of the servo disc are hinged with long connecting rods, straight wings are symmetrically arranged on both sides of the fuselage, the rotary servo output end is connected to the straight wing, and the rotary servo is fixedly connected to the fuselage through a universal joint, the sleeve is fixedly arranged on the rotary servo, and the free end of the long connecting rod is hinged to the sleeve, the rotor folding mechanism comprises a fixed support plate, a rotor folding driving unit, a swing rod and a rotor, the fixed support plate is arranged in the storage cabin, the four corners of the top of the fixed support plate are hinged with swing rods, the free end of the swing rod is connected to the rotor, the rotor folding driving unit is fixedly arranged on the fixed support plate, and the output end of the rotor folding driving unit is connected to the swing rod.

[0007] In a preferred technical solution of the present invention, the straight-wing folding drive unit includes a fixed bracket, a first driving servo, a first driving gear, a first rotating shaft, a first driven gear, a second driven gear, a second rotating shaft and a third driven gear. The fixed bracket is fixed in the storage cabin, and the first driving servo is arranged on the fixed bracket. The output end of the first driving servo is connected to the first driving gear. The fixed bracket is also rotatably connected with the first rotating shaft and the second rotating shaft. The first rotating shaft is fixed with the first driven gear and the second driven gear, and the first driven gear is meshed with the first driving gear. The second rotating shaft is fixed with the third driven gear and the servo disk, and the second driven gear is meshed with the third driven gear.

[0008] In a preferred technical solution of the present invention, the diameter of the second driven gear is smaller than the diameter of the first driven gear, and the diameter of the second driven gear is smaller than the diameter of the third driven gear.

[0009] In a preferred technical solution of the present invention, the rotor folding drive unit includes a second driving servo, a second driving gear, a fourth driven gear, a transmission belt, a transmission rod and a sliding rod. The second driving servo is fixedly mounted on the fixed support plate, and the output end of the second driving servo is connected to the second driving gear. Two parallel transmission belts are arranged at the bottom of the fixed support plate, and transmission rods are fixedly mounted on the transmission wheels of the transmission belts. A sliding rod is connected to the free end of the transmission rod, and the sliding rod is slidably connected to the sliding groove on the swing rod. A fourth driven gear is also coaxially fixedly mounted on the transmission wheels at the same end of the two transmission belts, and the two fourth driven gears are meshed with each other, and the second driving gear is meshed with one of the fourth driven gears.

[0010] In a preferred technical solution of the present invention, closable doors are provided on both sides of the fuselage.

[0011] The beneficial effects of the present invention are:

[0012] 1. Compared with existing variable configuration aircraft, the present invention can realize the folding of straight wings and rotors. When the four rotors are retracted into the fuselage, it has a better aerodynamic layout and can save more transportation and storage space. For example, when the aircraft is parked on a small apron or a narrow transport vehicle in an urban environment, the straight wings and rotors can be folded at the same time to reduce the size of the aircraft and make parking and transportation more convenient. At the same time, this design also enables the aircraft to better adapt to a variety of application scenarios. For example, when performing tasks in indoor environments or narrow passages, the retractable straight wings can effectively avoid collisions, improving the flexibility and adaptability of the aircraft.

[0013] 2. Compared with the existing wing folding mechanism, the present invention drives the overall deformation of the straight wing through a connecting rod structure, has a simple structure, is easy to drive, and effectively reduces the proportion of the folding mechanism in the overall mass of the aircraft. In addition, the transition of the straight wing from unfolding to folding can be achieved by driving the servo to operate continuously, which makes the operation and debugging of the motor simpler and the overall deformation process more stable. The deformation process is closely connected and has less impact, which can extend the service life of the deformation device.

[0014] 3. Compared with the existing unidirectional deformation mechanism, the present invention can realize one-time deformation in two directions in space, can better adapt to flight conditions, and has better versatility.

[0015] 4. The invention adopts the automatic folding rotor. The second driving gear drives the two fourth transmission gears to rotate, and then transmits the force to the transmission rod through the transmission belt and drives the swing rod to swing, so as to realize the function of retracting and unfolding the four rotors at the same time. This design ensures that the four rotors can quickly and accurately complete the folding action in different flight states, ensuring the flight performance, and the folding method is accurate and reliable.

[0016] 5. Using dual power sources to synchronously control the swing deformation of the straight wing and the retraction and extension of the rotor not only simplifies the power transmission path and reduces energy consumption, but also greatly improves the efficiency and synchronization of the folding operation. In actual application, the straight wing and the rotor can quickly and accurately complete the unfolding or folding action according to the preset program, greatly shortening the time of switching flight states and improving the response speed of the aircraft.

[0017] 6. The angle between the straight wing and the fuselage can be changed during flight. The variable-angle wing deployment method allows the aircraft to adjust the wing angle according to different flight missions and environmental conditions, thereby changing the flight characteristics. For example, when performing reconnaissance missions at low altitude and low speed, the wing angle can be adjusted to improve maneuverability; when flying at high altitude and high speed, it can be adjusted to another angle to increase flight speed and stability. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1It is a structural schematic diagram of a highly efficient foldable composite eVTOL aircraft in a vertical take-off and landing state provided by a specific embodiment of the present invention;

[0019] Figure 2 yes Figure 1 Schematic diagram of the structure after the fuselage is removed;

[0020] Figure 3 It is a schematic diagram of the structure of the straight wing folding mechanism;

[0021] Figure 4 yes Figure 3 A partial enlarged view of the middle A;

[0022] Figure 5 is a schematic diagram of the structure of the rotor folding mechanism;

[0023] Figure 6 It is a schematic diagram of the structure of the aircraft in a fully recovered state;

[0024] Figure 7 It is a schematic diagram of the structure of the aircraft in a high-speed cruising state;

[0025] Figure 8 It is a structural diagram of the aircraft in a fully deployed state.

[0026] In the figure:

[0027] 1. Fuselage; 11. Storage compartment; 12. Cabin door; 2. Straight wing folding mechanism; 21. Straight wing folding drive unit; 211. Servo disc; 212. Fixed bracket; 213. First drive servo; 214. First drive gear; 215. First rotating shaft; 216. First driven gear; 217. Second driven gear; 218. Second rotating shaft; 219. Third driven gear; 22. Long connecting rod; 23. Sleeve; 24. Universal joint; 25. Rotating servo; 26. Straight wing; 3. Rotor folding mechanism; 31. Fixed support plate; 32. Rotor folding drive unit; 321. Second drive gear; 322. Fourth driven gear; 323. Transmission belt; 324. Transmission rod; 325. Slide rod; 33. Swing rod; 34. Rotor; 35. Slide groove. DETAILED DESCRIPTION

[0028] The technical solution of the present invention is further described below with reference to the accompanying drawings and through specific implementation methods.

[0029] like Figure 1-8As shown, an efficient folding composite eVTOL aircraft is provided in the embodiment, including a fuselage 1, a straight wing folding mechanism 2 and a rotor folding mechanism 3. A storage cabin 11 is arranged in the fuselage 1, and the straight wing folding mechanism 2 includes a straight wing folding drive unit 21, a long connecting rod 22, a sleeve 23, a universal joint 24, a rotary servo 25 and a straight wing 26. The straight wing folding drive unit 21 is arranged in the storage cabin 11, and the straight wing folding drive unit 21 includes a servo disc 211, and the two ends of the servo disc 211 are hinged with a long connecting rod 22. The straight wings 26 are symmetrically arranged on both sides of the fuselage 1, and the output end of the rotary servo 25 is connected to the straight wing 26. 6 is connected, and the rotary servo 25 is fixedly connected to the fuselage 1 through a universal joint 24, the sleeve 23 is fixedly arranged on the rotary servo 25, and the free end of the long connecting rod 22 is hinged to the sleeve 23, the rotor folding mechanism 3 includes a fixed support plate 31, a rotor folding drive unit 32, a swing rod 33 and a rotor 34, the fixed support plate 31 is arranged in the storage cabin 11, the four corners of the top of the fixed support plate 31 are hinged with the swing rod 33, the free end of the swing rod 33 is connected to the rotor 34, the rotor folding drive unit 32 is fixedly arranged on the fixed support plate 31, and the output end of the rotor folding drive unit 32 is connected to the swing rod 33. In this embodiment, the fuselage 1 adopts a streamlined structure to reduce wind resistance. Two rotors 34 are provided on each side of the fuselage 1, and the rotors 4 on both sides are arranged symmetrically. The storage compartment 11 is used to store the rotors 34. In this state, the aircraft has a better aerodynamic layout, which can reduce wind resistance when flying at high altitudes and make the flight process of the aircraft more stable. At the same time, it can also reduce the size of the aircraft and facilitate parking.The straight wing folding mechanism 2 is capable of controlling the folding or unfolding of the straight wing 26, and the rotor folding mechanism 3 is capable of controlling the folding or unfolding of the rotor 34. For example, when the aircraft is performing a mission in an indoor environment or a narrow passage, the straight wing 26 can be controlled to fold to avoid a collision, and the rotor 34 can be unfolded at the same time, and the rotor 34 provides flight power. When performing a mission in an outdoor environment or a large space such as high altitude, the rotor 34 is controlled to fold and the straight wing 26 is unfolded, and the straight wing 26 provides flight power. When it is necessary to park in a small apron in an urban environment or in a narrow transport vehicle, the straight wing 26 and the rotor 34 can be controlled to fold at the same time to reduce the size of the aircraft. The straight wing folding drive unit 21 is used to provide power for folding the straight wing 26. The steering gear disc 211 is an elliptical plate. One end of the two long connecting rods 22 is divided into The straight wing 26 is connected to the two ends of the elliptical plate, and the straight wing folding drive unit 21 can drive the steering gear disk 211 to rotate, thereby driving the long connecting rod 22 to move accordingly; one end of the universal joint 24 is fixedly installed on the fuselage 1, and its structural characteristics are utilized to enable the long connecting rod 22 to drive the straight wing 26 to rotate in the horizontal plane when swinging, so as to realize the folding of the straight wing 26; the sleeve 23 is made of carbon fiber material, which helps to reduce the weight of the aircraft; the set rotary steering gear 25 can drive the straight wing 26 to rotate in the vertical plane, and allows the aircraft to adjust the inclination angle of the straight wing 26 according to different flight missions and environments, thereby changing the flight characteristics, such as when performing reconnaissance missions at low altitude and low speed, the angle (angle of attack) of the straight wing 26 can be increased to improve maneuverability, and when flying at high altitude and high speed, the angle of the straight wing 26 can be reduced to improve the flight speed and stability. The fixed support plate 31 is made of wood and is horizontally installed on the top of the fixed bracket 212. One end of the swing rod 33 is hinged to the fixed support plate 31, so that it can swing in the horizontal plane, thereby driving the rotor 34 to extend or retract into the storage compartment 11, and the two swing rods 33 located on the same side of the fuselage 1 rotate in the same direction, and the swing rods 33 located on both sides of the fuselage 1 swing towards each other. When the swing rod 33 extends out of the storage compartment 11, the four rotors 34 are controlled to rotate, which can provide flight power for the aircraft.

[0030] Specifically, the straight-wing folding drive unit 21 includes a fixed bracket 212, a first driving servo 213, a first driving gear 214, a first rotating shaft 215, a first driven gear 216, a second driven gear 217, a second rotating shaft 218 and a third driven gear 219. The fixed bracket 212 is fixed in the storage cabin 11. The first driving servo 213 is arranged on the fixed bracket 212. The output end of the first driving servo 213 is connected to the first driving gear 214. The first rotating shaft 215 and the second rotating shaft 218 are also rotatably connected to the fixed bracket 212. The first driven gear 216 and the second driven gear 217 are fixed on the first rotating shaft 215. The first driven gear 216 is meshed with the first driving gear 214. The third driven gear 219 and the servo disc 211 are fixed on the second rotating shaft 218. The second driven gear 217 is meshed with the third driven gear 219. In this embodiment, the fixed bracket 212 is a frame structure; the first driving servo 213 is fixedly installed on the fixed bracket 212, and the power shaft of the first driving servo 213 is arranged vertically downward, and the first driving servo 213 is used to drive the first driving gear 214 to rotate, thereby providing power for the folding or unfolding action of the straight wing 26; the first rotating shaft 215 and the second rotating shaft 218 are both arranged vertically, and through the meshing transmission structure between the first driving gear 214, the first driven gear 216, the second driven gear 217 and the third driven gear 219, the first driving servo 213 can drive the first rotating shaft 215 and the second rotating shaft 218 to rotate synchronously in the opposite direction, thereby driving the servo disc 211 to rotate, and realizing driving the straight wing 26 to unfold or fold. In addition, the gear transmission structure composed of the first driven gear 216, the second driven gear 217, the third driven gear 219 and other components can, on the one hand, make the swinging process of the straight wing 26 more stable and smooth, and on the other hand, it can also increase the swinging speed of the straight wing 26, greatly improving the efficiency and synchronization of the folding operation.

[0031] Specifically, the diameter of the second driven gear 217 is smaller than the diameter of the first driven gear 216 , and the diameter of the second driven gear 217 is smaller than the diameter of the third driven gear 219 .

[0032] Specifically, the rotor folding drive unit 32 includes a second driving servo, a second driving gear 321, a fourth driven gear 322, a transmission belt 323, a transmission rod 324 and a sliding rod 325. The second driving servo is fixedly mounted on the fixed support plate 31, and the output end of the second driving servo is connected to the second driving gear 321. Two parallel transmission belts 323 are arranged at the bottom of the fixed support plate 31, and transmission rods 324 are fixedly mounted on the transmission wheels of the transmission belts 323. The free end of the transmission rod 324 is connected to a sliding rod 325, and the sliding rod 325 is slidably connected to the slide groove 35 on the swing rod 33. A fourth driven gear 322 is also coaxially fixedly mounted on the transmission wheels at the same end of the two transmission belts 323, and the two fourth driven gears 322 are meshed with each other, and the second driving gear 321 is meshed with one of the fourth driven gears 322. In this embodiment, the second driving servo (not shown) is used to drive the second driving gear 321 to rotate, and then drive the two transmission belts 323 to rotate synchronously in the opposite direction through the meshing structure of the second driving gear 321 and the fourth driven gear 322. The two swinging rods 33 on the same side of the fuselage 1 are controlled and driven by the same transmission belt 323 to swing, that is, the two swinging rods 33 on the left side of the fuselage 1 will rotate counterclockwise at the same time, and the two swinging rods 33 on the right side of the fuselage 1 will rotate clockwise at the same time, so that the four swinging rods 33 can be folded and stored in the storage compartment 11 or unfolded from the storage compartment 11 at the same time. Each transmission belt 323 is composed of two transmission wheels and a belt connection, which is an existing technology. The number of transmission wheels and transmission rods 324 is equal and one-to-one corresponding, so that the transmission rods 324 can be driven to swing synchronously when the transmission wheels rotate. Since the slide rod 325 can slide in the slide groove 35, when the transmission rod 324 swings, the swing rod 33 is driven to swing synchronously, so as to realize the driving of the rotor 34 to fold or unfold.

[0033] Specifically, both sides of the fuselage 1 are provided with doors 12 that can be opened and closed. In this embodiment, the doors 12 are used to close the opening of the storage compartment 11 communicating with the outside world, so as to ensure that after the rotor 34 is stored in the storage compartment 11, the aircraft has a good aerodynamic layout.

[0034] Working principle:

[0035] When performing tasks in an indoor environment or a narrow passage, the first driving servo 213 drives the first driving gear 214 to rotate, and the first driving gear 214 rotates to drive the first driven gear 216 to rotate, and the first driven gear 216 rotates to drive the second driven gear 217 to rotate, and the second driven gear 217 drives the third driven gear 219 to rotate, so that the servo disc 211 rotates synchronously, and the rotation of the servo disc 211 drives the straight wing 26 to rotate toward one side of the fuselage 1 through the long connecting rod 22, and at the same time, the rotating servo 25 drives the straight wing 26 to rotate to a vertical direction, thereby completing the folding operation of the straight wing 26, and at the same time, the second driving servo drives the second driving gear 321 to rotate, and the rotation of the second driving gear 321 drives the two fourth driven gears 322 to rotate synchronously in the opposite direction, thereby driving the transmission rod 324 to swing, and the swing of the transmission rod 324 drives the swing rod 33 and the rotor 34 to extend out of the storage cabin 11, and then the rotor 34 provides flight power for the aircraft;

[0036] When performing tasks in an outdoor environment or in a large space such as a high altitude, the first driving servo 213 and the second driving servo are reversed, and the swing rod 33 and the rotor 34 are refolded and stored in the storage cabin 11, while the straight wing 26 is unfolded, and the straight wing 26 provides the aircraft with flight power;

[0037] When the aircraft needs to be parked on a small parking area or in a narrow transport vehicle in an urban environment, the straight wings 26 and the rotors 34 can be controlled to be folded at the same time to reduce the size of the aircraft.

[0038] The present invention is described by preferred embodiments, and those skilled in the art will appreciate that various changes or equivalent substitutions may be made to these features and embodiments without departing from the spirit and scope of the present invention. The present invention is not limited to the specific embodiments disclosed herein, and other embodiments falling within the claims of this application are within the scope of protection of the present invention.

Claims

1. An efficient foldable composite eVTOL aircraft, characterized by: The invention comprises a fuselage (1), a straight wing folding mechanism (2) and a rotary wing folding mechanism (3); a storage compartment (11) is arranged in the fuselage (1); the straight wing folding mechanism (2) comprises a straight wing folding driving unit (21), a long connecting rod (22), a sleeve (23), a universal joint (24), a rotary steering gear (25) and a straight wing (26); the straight wing folding driving unit (21) is arranged in the storage compartment (11); the straight wing folding driving unit (21) comprises a steering gear disc (211); both ends of the steering gear disc (211) are hinged with a long connecting rod (22); straight wings (26) are symmetrically arranged on both sides of the fuselage (1); an output end of the rotary steering gear (25) is connected to the straight wing (26); and the rotary steering gear (25) is connected to the straight wing (26). The rotor folding mechanism (3) is fixedly connected to the fuselage (1) via a universal joint (24); the sleeve (23) is fixedly arranged on the rotary steering gear (25); and the free end of the long connecting rod (22) is hinged to the sleeve (23); the rotor folding mechanism (3) comprises a fixed support plate (31), a rotor folding driving unit (32), a swing rod (33) and a rotor (34); the fixed support plate (31) is arranged in the storage cabin (11); the four corners of the top of the fixed support plate (31) are hinged to the swing rod (33); the free end of the swing rod (33) is connected to the rotor (34); the rotor folding driving unit (32) is fixedly arranged on the fixed support plate (31); and the output end of the rotor folding driving unit (32) is connected to the swing rod (33).

2. The highly efficient foldable composite eVTOL aircraft according to claim 1, characterized in that: The straight wing folding driving unit (21) comprises a fixed bracket (212), a first driving steering engine (213), a first driving gear (214), a first rotating shaft (215), a first driven gear (216), a second driven gear (217), a second rotating shaft (218) and a third driven gear (219); the fixed bracket (212) is fixedly arranged in the storage cabin (11); the first driving steering engine (213) is arranged on the fixed bracket (212); an output end of the first driving steering engine (213) is connected to a first The driving gear (214) is also rotatably connected to a first rotating shaft (215) and a second rotating shaft (218) on the fixed bracket (212); a first driven gear (216) and a second driven gear (217) are fixedly arranged on the first rotating shaft (215); the first driven gear (216) is meshed with the first driving gear (214); a third driven gear (219) and the steering gear disc (211) are fixedly arranged on the second rotating shaft (218); the second driven gear (217) is meshed with the third driven gear (219).

3. The highly efficient foldable composite eVTOL aircraft according to claim 2, characterized in that: The diameter of the second driven gear (217) is smaller than the diameter of the first driven gear (216), and the diameter of the second driven gear (217) is smaller than the diameter of the third driven gear (219).

4. The highly efficient foldable composite eVTOL aircraft according to claim 2, characterized in that: The rotor folding drive unit (32) comprises a second driving steering engine, a second driving gear (321), a fourth driven gear (322), a transmission belt (323), a transmission rod (324) and a sliding rod (325); the second driving steering engine is fixedly mounted on the fixed support plate (31); the output end of the second driving steering engine is connected to the second driving gear (321); two parallel transmission belts (323) are arranged at the bottom of the fixed support plate (31); and the transmission belts (323) are arranged in parallel. A transmission rod (324) is fixedly provided on each transmission wheel, a sliding rod (325) is connected to the free end of the transmission rod (324), and the sliding rod (325) is slidably connected to the sliding groove (35) on the swing rod (33), and a fourth driven gear (322) is coaxially fixedly provided on the transmission wheel located at the same end of the two transmission belts (323), and the two fourth driven gears (322) are meshed with each other, and the second driving gear (321) is meshed with one of the fourth driven gears (322).

5. The highly efficient foldable composite eVTOL aircraft according to claim 1, characterized in that: Openable doors (12) are also provided on both sides of the fuselage (1).

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