A highly efficient folded compound eVTOL aircraft

Abstract

The application discloses a kind of high-efficiency folding composite eVTOL aircraft, it is related to aircraft technical field, cabin is arranged in fuselage, straight wing folding drive part is set in cabin, straight wing folding drive part includes steering wheel disc, long connecting rod is hinged in steering wheel disc both ends, straight wing is symmetrically set in the both sides of fuselage, rotary steering wheel output end is connected with straight wing, sleeve is fixed on rotary steering wheel, and long connecting rod free end is hinged with sleeve, fixed support plate is set in cabin, four corners at the top of fixed support plate are hinged with swing rod, and rotor is connected in swing rod free end, and rotor folding drive part is fixed on fixed support plate.The application is folded by being set folding mechanism, realizes the efficient linkage folding of straight wing and rotor, so that aircraft has multimodal ability of vertical take-off and landing, high-speed cruise and compact storage simultaneously, satisfies the demand of diversified application scene.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of aircraft technology, and more particularly, to an efficient folding hybrid eVTOL aircraft. BACKGROUND

[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 transportation. Among them, the eVTOL aircraft with fixed wings and rotors has vertical take-off and landing performance and high-speed flight capability, and has the characteristics of smooth transition stability and strong controllability, and has gradually become one of the most promising eVTOL aircraft.

[0003] However, the existing aircraft usually has the following defects: 1. The folding mechanism is usually realized by connecting rods, spherical hinges and other mechanical parts to rotate. Such structure has weak carrying capacity, especially when the aircraft is under high dynamic load or complex flight conditions, the structural stability is difficult to guarantee; 2. The impact is large during the transformation of the deformation state, which leads to unsmooth deformation and low service life of the parts; 3. The wing root part is limited by space and structure, and has limited carrying capacity, which is easy to become a weak link in design, and only one set of power system exists Safety hazards, it is difficult to meet the needs of high efficiency and stability of future aircraft in complex working conditions. SUMMARY

[0004] In order to overcome the defects of the prior art, the present application provides an efficient folding hybrid eVTOL aircraft, which realizes efficient linkage folding of straight wings and rotors through the folding mechanism, so that the aircraft has multiple modal capabilities of vertical take-off and landing, high-speed cruising and compact storage and transportation, and meets the needs of diversified application scenarios.

[0005] To achieve this purpose, the present application adopts the following technical solutions:

[0006] The application provides a high-efficiency folding composite eVTOL aircraft, which comprises a fuselage, a straight wing folding mechanism and a rotor folding mechanism, a storage cabin is arranged in the fuselage, the straight wing folding mechanism comprises a straight wing folding driving part, a long connecting rod, a sleeve, a universal joint, a rotary rudder and a straight wing, the straight wing folding driving part is arranged in the storage cabin, the straight wing folding driving part comprises a rudder disc, long connecting rods are hingedly connected to both ends of the rudder disc, straight wings are symmetrically arranged on both sides of the fuselage, a rotary rudder output end is connected with the straight wing, the rotary rudder is fixedly connected to the fuselage through the universal joint, the sleeve is fixedly arranged on the rotary rudder, and the free end of the long connecting rod is hingedly connected with the sleeve, the rotor folding mechanism comprises a fixed support plate, a rotor folding driving part, a swing rod and a rotor, the fixed support plate is arranged in the storage cabin, swing rods are hingedly connected to four corners at the top end of the fixed support plate, the free end of the swing rod is connected with the rotor, and the rotor folding driving part is fixedly arranged on the fixed support plate and connected with the swing rod through an output end.

[0007] In the preferable technical scheme of the application, the straight wing folding driving part comprises a fixed support, a first driving rudder, 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 support is fixedly arranged in the storage cabin, the first driving rudder is arranged on the fixed support, the first driving rudder output end is connected with the first driving gear, the fixed support is further rotationally connected with the first rotating shaft and the second rotating shaft, the first rotating shaft is fixedly arranged with the first driven gear and the second driven gear, the first driven gear is engaged with the first driving gear, and the second rotating shaft is fixedly arranged with the third driven gear and the rudder disc, the second driven gear and the third driven gear are engaged.

[0008] In the preferable technical scheme of the application, the diameter of the second driven gear is smaller than that of the first driven gear, and the diameter of the second driven gear is smaller than that of the third driven gear.

[0009] In the preferable technical scheme of the application, the rotor folding driving part comprises a second driving rudder, a second driving gear, a fourth driven gear, a transmission belt, a transmission rod and a sliding rod, the second driving rudder is fixedly arranged on the fixed support plate, the second driving rudder output end is connected with the second driving gear, two parallel transmission belts are arranged on the bottom of the fixed support plate, transmission rods are fixedly arranged on the transmission wheels of the transmission belts, the free end of the transmission rod is connected with the sliding rod, the sliding rod is slidingly connected with the sliding groove on the swing rod, a fourth driven gear is fixedly arranged on the transmission wheel at the same end of the two transmission belts, the two fourth driven gears are engaged, and the second driving gear is engaged with one of the fourth driven gears.

[0010] In the preferable technical scheme of the application, the fuselage is further provided with openable and closable cabin doors.

[0011] The application has the following beneficial effects:

[0012] 1. Compared with existing variable configuration aircraft, the present application can realize the folding of straight wings and rotors, has a better aerodynamic layout when the four rotors are retracted in the fuselage, and can save transportation and storage space. For example, when the aircraft is parked in a small parking lot or 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, making it easier to park and transport. At the same time, this design also makes the aircraft better adapt to diverse application scenarios, such as 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 existing wing folding mechanisms, the present application deforms the straight wings as a whole through a linkage structure, which is simple in structure, convenient to drive, effectively reduces the proportion of the folding mechanism in the overall mass of the aircraft, and the transition of the straight wings from the unfolded to the folded state can be realized by driving the rudder continuously, which is more convenient for motor operation and debugging, and the overall deformation process is more stable; the deformation process is closely connected, with less impact, which can prolong the service life of the deformation device.

[0014] 3. Compared with existing single-direction deformation mechanisms, the present application can realize one-time deformation in two directions in space, better adapt to flight conditions, and have better versatility.

[0015] 4. The rotors are automatically folded, the present application drives the second drive gear to rotate two fourth transmission gears, and then transmits the force to the transmission rod through the transmission belt and drives the swing rod to swing, realizing the simultaneous retraction and expansion of the four rotors. This design ensures that the four rotors can quickly and accurately complete the folding action in different flight states, ensuring flight performance, and the folding implementation method has precision and reliability.

[0016] 5. The use of dual power sources to synchronize the control of straight wing swing deformation and rotor folding and unfolding actions not only simplifies the power transmission path, reduces energy consumption, but also greatly improves the efficiency and synchronization of folding operations. In actual application, the straight wings and rotors can quickly and accurately complete the unfolding or folding action according to the preset program, greatly shortening the time of flight state switching and improving the response speed of the aircraft.

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

[0018] Figure 1is a structural schematic diagram of a high-efficiency folded composite eVTOL aircraft in a vertical take-off and landing state provided in the specific embodiment of the present application.

[0019] Figure 2 is Figure 1 is a structural schematic diagram of the structure after removing the fuselage.

[0020] Figure 3 is a structural schematic diagram of a straight wing folding mechanism.

[0021] Figure 4 is Figure 3 is an enlarged view of the middle A.

[0022] Figure 5 is a structural schematic diagram of a rotor folding mechanism.

[0023] Figure 6 is a structural schematic diagram of the aircraft in a fully recovered state.

[0024] Figure 7 is a structural schematic diagram of the aircraft in a high-speed cruising state.

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

[0026] in the figure:

[0027] 1, fuselage; 11, storage cabin; 12, cabin door; 2, straight wing folding mechanism; 21, straight wing folding driving part; 211, steering gear disc; 212, fixed support; 213, first driving steering gear; 214, first driving 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 steering gear; 26, straight wing; 3, rotor folding mechanism; 31, fixed support plate; 32, rotor folding driving part; 321, second driving gear; 322, fourth driven gear; 323, transmission belt; 324, transmission rod; 325, sliding rod; 33, swing rod; 34, rotor; 35, sliding groove. DETAILED DESCRIPTION

[0028] The technical solutions of the present application will be further described in combination with the drawings and through specific embodiments.

[0029] As Figures 1-8As shown, the embodiment provides a high-efficiency folding composite eVTOL aircraft, which comprises a fuselage 1, a straight wing folding mechanism 2 and a rotor folding mechanism 3. The fuselage 1 is provided with a storage cabin 11. The straight wing folding mechanism 2 comprises a straight wing folding driving part 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 driving part 21 is arranged in the storage cabin 11. The straight wing folding driving part 21 comprises a servo disc 211. The long connecting rod 22 is hingedly connected to both ends of the servo disc 211. The fuselage 1 is symmetrically provided with the straight wing 26 on both sides. The rotary servo 25 is connected to the straight wing 26. The rotary servo 25 is fixedly connected to the fuselage 1 through the universal joint 24. The sleeve 23 is fixedly arranged on the rotary servo 25. The free end of the long connecting rod 22 is hingedly connected to the sleeve 23. The rotor folding mechanism 3 comprises a fixed support plate 31, a rotor folding driving part 32, a swing rod 33 and a rotor 34. The fixed support plate 31 is arranged in the storage cabin 11. The swing rod 33 is hingedly connected to each of the four corners at the top end of the fixed support plate 31. The free end of the swing rod 33 is connected to the rotor 34. The rotor folding driving part 32 is fixedly arranged on the fixed support plate 31. The output end of the rotor folding driving part 32 is connected to the swing rod 33. In the embodiment, the fuselage 1 adopts a streamlined structure to reduce wind resistance. The fuselage 1 is provided with two rotors 34 on each side. The rotors 4 on both sides are symmetrically arranged. The storage cabin 11 is arranged for storing the rotors 34. In this state, the aircraft has a better aerodynamic layout, thereby reducing wind resistance during high-altitude flight and making the flight process of the aircraft more stable. Meanwhile, the aircraft size can be reduced for easy parking.The straight wing folding mechanism 2 is arranged to control the folding or unfolding of the straight wing 26, and the rotor folding mechanism 3 is arranged to control the folding or unfolding of the rotor 34. For example, when the aircraft performs a task in an indoor environment or a narrow channel, the straight wing 26 can be controlled to fold to avoid collision, while the rotor 34 is unfolded to provide flight power. When performing a task in an outdoor environment or a larger space such as high altitude, the rotor 34 is controlled to fold, and the straight wing 26 is unfolded to provide flight power. When it is required to be parked in a small parking lot or a narrow transport vehicle in an urban environment, 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 part 21 is arranged to provide power for folding the straight wing 26. The steering wheel 211 is an oval plate. One end of the two long connecting rods 22 is connected to the two ends of the oval plate, respectively. The straight wing folding drive part 21 can drive the steering wheel 211 to rotate, thereby driving the long connecting rod 22 to move. The universal joint 24 is fixedly installed on the fuselage 1. The structure of the universal joint 24 enables 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 rotary steering wheel 25 can drive the straight wing 26 to rotate in the vertical plane, and can adjust the angle of the straight wing 26 according to different flight tasks and environments, so as to change the flight characteristics. For example, when performing a reconnaissance task at low altitude and low speed, the angle (angle of attack) of the straight wing 26 can be increased to improve the maneuverability. 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 support 212. The swinging rod 33 is hingedly connected 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 cabin 11. The two swinging rods 33 on the same side of the fuselage 1 rotate in the same direction, and the swinging rods 33 on the two sides of the fuselage 1 swing in opposite directions. When the swinging rod 33 extends out of the storage cabin 11, the four rotors 34 are controlled to rotate, thereby providing flight power for the aircraft.

[0030] Specifically, the straight wing folding driving part 21 comprises a fixed support 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 support 212 is fixedly arranged in the storage cabin 11. The first driving steering engine 213 is arranged on the fixed support 212. The first driving gear 214 is connected to the output end of the first driving steering engine 213. The first rotating shaft 215 and the second rotating shaft 218 are rotatably connected to the fixed support 212. The first driven gear 216 and the second driven gear 217 are fixedly arranged on the first rotating shaft 215. The first driven gear 216 is engaged with the first driving gear 214. The third driven gear 219 and the steering engine disc 211 are fixedly arranged on the second rotating shaft 218. The second driven gear 217 is engaged with the third driven gear 219. In the embodiment, the fixed support 212 is in a frame structure. The first driving steering engine 213 is fixedly arranged on the fixed support 212. The power shaft of the first driving steering engine 213 is vertically arranged downward. The first driving steering engine 213 is used for driving 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 vertically arranged. The first driving gear 214, the first driven gear 216, the second driven gear 217 and the third driven gear 219 are engaged with each other, so that the first driving steering engine 213 can drive the first rotating shaft 215 and the second rotating shaft 218 to synchronously and reversely rotate, thereby driving the steering engine disc 211 to rotate, realizing the driving of the unfolding or folding of the straight wing 26. In addition, the gear transmission structure composed of the first driven gear 216, the second driven gear 217 and the third driven gear 219 can make the swinging process of the straight wing 26 more stable and smooth, and can also improve the swinging speed of the straight wing 26, greatly improving the efficiency and synchronism of the folding operation.

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

[0032] Specifically, the rotor folding driving part 32 comprises a second driving rudder, 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 rudder is fixed on the fixed support plate 31, and the output end of the second driving rudder is connected with the second driving gear 321. The bottom of the fixed support plate 31 is provided with two parallel transmission belts 323, and the transmission wheels of the transmission belts 323 are fixed with the transmission rods 324. The free ends of the transmission rods 324 are connected with the sliding rods 325 which are slidably connected with the sliding grooves 35 on the swing rods 33. The fourth driven gears 322 are coaxially fixed on the transmission wheels at the same end of the two transmission belts 323, and the two fourth driven gears 322 are engaged with each other. The second driving gear 321 is engaged with one of the fourth driven gears 322. In the embodiment, the second driving rudder (not shown in the figure) is used to drive the second driving gear 321 to rotate, and then the second driving gear 321 and the fourth driven gear 322 are engaged to drive the two transmission belts 323 to rotate synchronously and reversely. The two swing 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 swing rods 33 on the left side of the fuselage 1 rotate counterclockwise at the same time, and the two swing rods 33 on the right side of the fuselage 1 rotate clockwise at the same time, so that the four swing rods 33 are folded and stored in the storage cabin 11 or unfolded from the storage cabin 11 at the same time. Each transmission belt 323 is composed of two transmission wheels and a belt connection, which is the existing technology. The number of transmission wheels and transmission rods 324 is equal and one-to-one corresponding, so that the transmission rod 324 can be driven to swing synchronously when the transmission wheel rotates. Since the sliding rod 325 can slide in the sliding groove 35, the swing rod 33 can be driven to swing synchronously when the transmission rod 324 swings, so as to realize the folding or unfolding of the rotor 34.

[0033] Specifically, the fuselage 1 is provided with openable and closable cabin doors 12 on both sides. In the embodiment, the cabin doors 12 are used to close the opening for communication between the storage cabin 11 and the outside, so as to ensure that the aircraft has a good aerodynamic layout after the rotor 34 is stored in the storage cabin 11.

[0034] Working principle:

[0035] When performing tasks in an indoor environment or narrow channel, the first drive steering engine 213 drives the first drive gear 214 to rotate, the first drive gear 214 drives the first driven gear 216 to rotate, the first driven gear 216 drives the second driven gear 217 to rotate, the second driven gear 217 drives the third driven gear 219 to rotate, thereby synchronously rotating the steering engine disc 211, the steering engine disc 211 rotates through the long connecting rod 22 to drive the straight wing 26 to rotate to one side of the fuselage 1, at the same time, rotating the steering engine 25 will drive the straight wing 26 to rotate to the vertical direction, thereby completing the folding operation of the straight wing 26, at the same time, the second drive steering engine drives the second drive gear 321 to rotate, the second drive gear 321 drives the two fourth driven gears 322 to synchronously and reversely rotate, thereby driving the transmission rod 324 to swing, the transmission rod 324 swings to drive the swing rod 33 and the rotor 34 to extend out of the storage cabin 11, thereby providing the aircraft with flight power by the rotor 34;

[0036] When performing tasks in an outdoor environment or a larger space such as high altitude, the first drive steering engine 213 and the second drive steering engine are reversed, at this time, the swing rod 33 and the rotor 34 are re-folded and stored in the storage cabin 11, and the straight wing 26 is unfolded, thereby providing the aircraft with flight power by the straight wing 26.

[0037] When it is necessary to be parked in a small parking apron in the city environment or a narrow transport vehicle, the straight wing 26 and the rotor 34 can be folded at the same time to reduce the volume of the aircraft.

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

Claims

1. A high efficiency folded compound eVTOL aircraft characterized by: The utility model relates to a kind of foldable aircraft, including fuselage (1), straight wing folding mechanism (2) and rotor folding mechanism (3), fuselage (1) is provided with storage cabin (11) inside, straight wing folding mechanism (2) includes straight wing folding drive part (21), long connecting rod (22), sleeve (23), universal joint (24), rotary servo (25) and straight wing (26), straight wing folding drive part (21) is set in storage cabin (11), straight wing folding drive part (21) includes rudder disc (211), long connecting rod (22) is hinged in both ends of rudder disc (211), straight wing (26) is symmetrically provided on both sides of fuselage (1), rotary servo (25) output end is connected with straight wing (26), and rotary servo (25) is fixedly connected to fuselage (1) by universal joint (24), sleeve (23) is fixed on rotary servo (25), and long connecting rod (22) free end is hinged with sleeve (23), rotor folding mechanism (3) includes fixed support plate (31), rotor folding drive part (32), swing rod (33) and rotor (34), fixed support plate (31) is set in storage cabin (11), swing rod (33) is hinged in four corners of the top end of fixed support plate (31), and rotor (34) is connected to the free end of swing rod (33), and rotor folding drive part (32) is fixed on fixed support plate (31), and rotor folding drive part (32) output end is connected with swing rod (33); The straight wing folding drive part (21) includes fixed support (212), first drive servo (213), first drive gear (214), first rotating shaft (215), first driven gear (216), second driven gear (217), second rotating shaft (218) and third driven gear (219), the fixed support (212) is fixed in the storage cabin (11), the first drive servo (213) is provided on the fixed support (212), the first drive servo (213) output end is connected with the first drive gear (214), the fixed support (212) is also rotatably connected with the first rotating shaft (215) and the second rotating shaft (218), the first rotating shaft (215) is fixedly provided with the first driven gear (216) and the second driven gear (217), the first driven gear (216) is engaged with the first drive gear (214), the second rotating shaft (218) is fixedly provided with the third driven gear (219) and the rudder disc (211), the second driven gear (217) and the third driven gear (219) are engaged; 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); The rotor folding driving part (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 fixed on the fixed support plate (31), the second driving steering engine output end is connected with the second driving gear (321), the bottom of the fixed support plate (31) is provided with two parallel transmission belts (323), the transmission wheels of the transmission belts (323) are all fixed with the transmission rods (324), the free end of the transmission rod (324) is connected with the sliding rod (325), the sliding rod (325) is slidably connected with the sliding groove (35) on the swing rod (33), coaxially fixed with the fourth driven gear (322) on the transmission wheel at the same end of the two transmission belts (323), the two fourth driven gears (322) are engaged, and the second driving gear (321) is engaged with one of the fourth driven gears (322).

2. The high efficiency folded compound eVTOL aircraft of claim 1 wherein: The fuselage (1) is also provided with openable and closable cabin doors (12) on both sides.

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