A vertical take-off and landing aircraft

Abstract

The application discloses a vertical take-off and landing aircraft which can satisfy long-time hovering, flexibly adjust the pitch attitude during tilting, and has higher comprehensive flight energy efficiency under different flight modes. The aircraft comprises wings arranged on both sides of a fuselage, a tail wing arranged at the tail end of the fuselage, and a tilting rotor arranged at the end of the wing. A tail balance mechanism is arranged at the tail end of the fuselage and below the tail wing. The tail balance mechanism comprises a tail cover, a paddle slot arranged on the tail cover, and a balance propeller driven by a motor and arranged in the paddle slot. When the aircraft is vertically taking off or hovering, the tilting wing is synchronously tilted with the tilting rotor, the airflow impact of the downwash flow of the tilting rotor on the wing surface is reduced, and the flight energy efficiency is improved. The balance propeller cooperates with the tilting rotor to satisfy the pitch attitude switching, adjustment and stability effect during hovering and tilting, the balance propeller is stopped from rotating and is collected in the paddle slot during level flight, the balance propeller is consistent with the axis of the fuselage, and the wind resistance is reduced. When the aircraft is vertically landing or parking on the ground, the supporting legs of the folding linkage assembly of the tail supporting part are lowered, three-point support is formed with the landing wheels, and the aircraft is stably parked.

Description

Technical Field

[0001] This invention relates to the field of aircraft technology, and more specifically to a vertical takeoff and landing aircraft. Background Technology

[0002] The low-altitude economy is a comprehensive economic form that drives the integrated development of related fields through various low-altitude flight activities. Major products in the low-altitude sector include the much-discussed eVTOL (electric vertical takeoff and landing aircraft), drones (consumer and industrial grades), helicopters, and traditional fixed-wing aircraft. These can be applied to operational flights in urban air traffic, industry, agriculture, forestry, fisheries, and construction, as well as medical rescue, disaster relief, meteorological observation, marine monitoring, scientific experiments, education and training, and cultural and sports activities, making it a promising future industry favored by investors.

[0003] Currently, there are numerous configurations and layouts for eVTOL aircraft, with the mainstream types being pure rotorcraft, compound wingcraft, and tiltrotor aircraft. Each of these three categories has its advantages and disadvantages. Due to the system complexity and flight modes, although airworthiness is slightly more difficult, tiltrotor aircraft are superior to pure rotorcraft and compound wingcraft in terms of flight efficiency. Therefore, the development of tiltrotor eVTOLs has shown a clear trend towards technological breakthroughs in recent years.

[0004] Due to the distributed design of the motors, a highly efficient distributed multi-motor tilt-type eVTOL has been developed. Its core highlight is redundancy, meaning that even if one motor fails, the aircraft can continue to fly without crashing, ensuring safety. However, the excessive distribution of motors complicates the lift system, resulting in too many tilting mechanisms, excessively long cables, and complex control algorithms, which in turn increases the risk factors.

[0005] Later, a dual-motor design emerged. This approach requires only two main thrust systems, resulting in a simple and efficient configuration. Essentially, it moves two helicopter rotor systems to the wingtips of an aircraft. To ensure pitch stability, both large rotors employ cyclic torque control. However, cyclic torque significantly increases the overall weight, complexity, and risk of the aircraft. Furthermore, most current twin-rotor aircraft only tilt the rotor system during tilting. When hovering, the downwash generated by the rotors significantly impacts the upper wing surface, creating turbulent flow that causes aerodynamic disturbances and makes pitch control difficult, leading to increased energy consumption and reduced efficiency. This makes it unsuitable for long-duration hovering applications such as high-altitude photography and precision parachuting. It is also susceptible to external interference (wind disturbances), posing safety risks. Summary of the Invention

[0006] The purpose of this invention is to provide a vertical takeoff and landing aircraft that can meet the requirements of long-term hovering, flexible adjustment of pitch attitude during tilting, and higher overall flight energy efficiency in different flight modes.

[0007] The present invention achieves its purpose by adopting the following technical solution: a vertical take-off and landing aircraft, including wings on both sides of the fuselage, a tail fin at the tail end of the fuselage, tilt rotors at the ends of the wings, and a tail balancing mechanism at the tail end of the fuselage and below the tail fin. The tail balancing mechanism includes a tail cover, which has a propeller groove. A horizontally arranged balancing propeller driven by a motor is installed in the propeller groove, which satisfies the switching adjustment and stabilization effect of pitch attitude during hovering and tilting.

[0008] The tail balancing mechanism of the present invention also includes a tail support part that can be lowered or retracted on the tail cover, and each of the rear ends of the tilt rotor is provided with a landing wheel, which plays the role of supporting the entire aircraft at three points when landing.

[0009] The wing described in this invention includes a fixed wing, with a tilting rotor at the end of the fixed wing. The tilting rotor is located at the outer end of the tilting rotor, and the length of the tilting rotor is 0.75 to 1.25 times the radius of the tilting rotor. The tilting rotor and the tilting rotor tilt synchronously, which reduces the airflow impact on the wing surface from the downwash of the tilting rotor when hovering, while ensuring the lift of the fixed wing. At the same time, it avoids the need to increase the power to provide greater thrust when tilting, and avoids the tilting rotor being affected by excessive crosswind interference when hovering, thus affecting its stability.

[0010] Preferably, the length of the tilting wing is equal to the radius of the tilting rotor.

[0011] The tilting rotor of the present invention is provided with an aileron, and the tilting rotor is provided with a power cowling.

[0012] The tail support of the present invention includes a support leg driven by a folding linkage assembly, the support leg being located below the balance propeller; the motor is fixed to the upper part of the tail cover by a motor mounting base located above the balance propeller.

[0013] The folding linkage assembly of the present invention includes a bracket, the upper part of which is fixed inside the tail cover, and the support leg is hinged to the lower end of the bracket and located below the balance propeller outside the tail cover. The bracket and the support leg are further provided with a drive rod and a driven rod. One end of the drive rod is hinged to the driven rod, and the other end is hinged to the bracket via a spherical bearing. The two ends of the driven rod are respectively hinged to the drive rod and the support leg. An electric push rod is also connected between the bracket and the drive rod, and one end of the electric push rod is connected to one end of the drive rod near the driven rod.

[0014] The bracket of the present invention is equipped with an electronic speed governor. The tail cover is located above and below the electronic speed governor and has heat dissipation holes. The balance propeller is located outside the tail cover and below the electronic speed governor, so that the heat generated by the electronic speed governor is forcibly guided vertically by the balance propeller and dissipated through the heat dissipation holes to prevent the electronic speed governor from overheating.

[0015] An electronic speed controller (ESC) adjusts the speed of an electric motor based on control signals. Depending on the type of motor, ESCs can be divided into brushed ESCs and brushless ESCs. The ESC is a key component of the UAV's power system, responsible for receiving flight control signals and controlling the motor speed for stable flight.

[0016] The balanced propeller of this invention has two blades; during level flight, one blade is retracted into the propeller slot, making the balanced propeller aligned with the fuselage axis, thereby reducing wind resistance; the support legs are equipped with tail supports, and the lower end of the tail supports is equipped with a ground contact end, which is made of elastic cushioning material; during aircraft landing, it plays a role in smoothing and cushioning.

[0017] By adopting the above technical solution, the present invention has achieved its objective well. During vertical takeoff and landing or hovering, the tilting wing tilts synchronously with the tilting rotor, thereby reducing the airflow impact of the tilting rotor downwash on the wing surface during hovering. It can avoid at least 80% of the downwash impact, thus improving flight efficiency. The balancing propeller, in conjunction with the tilting rotor, satisfies the switching adjustment and stabilization effect of pitch attitude during hovering and tilting. During level flight, it stops rotating and is stored in the propeller slot, so that the stationary balancing propeller is aligned with the fuselage axis, thereby reducing wind resistance. During vertical landing or static parking on the ground, the outriggers driven by the folding linkage assembly of the tail support are lowered, forming a three-point support with the landing wheels to stabilize the aircraft. Attached Figure Description

[0018] Figure 1 This is a schematic diagram of the structure of Embodiment 1 of the present invention; Figure 2 yes Figure 1 Enlarged structural diagram of mid-tail cover 9, propeller groove 8, and balance propeller 6; Figure 3 This is a schematic diagram of the structure of Embodiment 2 of the present invention; Figure 4 yes Figure 3 Enlarged structural diagram of the mid-tail support section 10; Figure 5 This is a schematic diagram of the structure of Embodiment 3 of the present invention; Figure 6 This is an enlarged schematic diagram of the electronic speed controller 16 and heat dissipation hole 17 in Embodiment 6 of the present invention; Figure 7 This is an enlarged schematic diagram of the tail support 18 and the ground contact end 19 in Embodiment 7 of the present invention.

[0019] In the diagram: 1. Fuselage, 2. Landing wheels, 3. Tiltrotor, 4. Wing, 5. Tail, 6. Balance propeller, 7. Motor, 8. Propeller slot, 9. Tail cowl, 10. Tail support, 11. Motor mount. 10-1. Bracket, 10-2. Electric actuator, 10-3. Spherical bearing, 10-4. Drive rod, 10-5. Driven rod, 10-6. Support leg. 12. Power cowl, 13. Tilter, 14. Aileron, 15. Fixed wing, 16. Electronic speed controller, 17. Heat dissipation vents, 18. Tail boom, 19. Ground contact tip. Detailed Implementation

[0020] The present invention will be further described below with reference to the accompanying drawings and embodiments. Example 1

[0021] Depend on Figures 1 to 2 It is known that a vertical takeoff and landing aircraft includes wings 4 on both sides of the fuselage 1, a tail fin 5 at the tail end of the fuselage 1, a tilt rotor 3 at the end of the wing 4, and a tail balancing mechanism at the tail end of the fuselage 1 and below the tail fin 5. The tail balancing mechanism includes a tail cover 9, and the tail cover 9 has a propeller groove 8. The propeller groove 8 has a horizontally arranged balancing propeller 6 driven by a motor 7, which satisfies the switching adjustment of pitch attitude and the stabilization effect when hovering and tilting.

[0022] The balanced propeller 6 described in this invention has two blades; during level flight, one of the blades is retracted into the propeller groove 8, so that the balanced propeller 6 is aligned with the axis of the fuselage 1, thereby reducing wind resistance. Example 2

[0023] Depend on Figures 3 to 4 It is understood that the tail balancing mechanism of the present invention also includes a tail support 10 that can be lowered or retracted on the tail cover 9, and each of the rear ends of the tilt rotor 3 is provided with a landing wheel 2, which plays the role of supporting the entire aircraft at three points when landing on the ground.

[0024] The tail support 10 of the present invention includes a support leg 10-6 driven by a folding linkage assembly, the support leg 10-6 being located below the balance propeller 6; the motor 7 is fixed to the upper part of the tail cover 9 by a motor mounting base 11 located above the balance propeller 6.

[0025] The folding linkage assembly of the present invention includes a bracket 10-1, the upper part of which is fixed inside the tail cover 9, and the support leg 10-6 is hinged to the lower end of the bracket 10-1 and located below the balance propeller 6 outside the tail cover 9. A drive rod 10-4 and a driven rod 10-5 are also provided between the bracket 10-1 and the support leg 10-6. One end of the drive rod 10-4 is hinged to the driven rod 10-5, and the other end is hinged to the bracket 10-1 via a spherical bearing 10-3. The two ends of the driven rod 10-5 are respectively hinged to the drive rod 10-4 and the support leg 10-6. An electric push rod 10-2 is also connected between the bracket 10-1 and the drive rod 10-4, and one end of the electric push rod 10-2 is connected to one end of the driven rod 10-5 of the drive rod 10-4.

[0026] Same as Example 1. Example 3

[0027] Depend on Figure 5 As can be seen, the wing 4 of the present invention includes a fixed wing 15, and a tilting wing 13 is provided at the end of the fixed wing 15. The tilting rotor 3 is located at the outer end of the tilting wing 13. The tilting wing 13 and the tilting rotor 3 tilt synchronously, thereby reducing the airflow impact of the downwash of the tilting rotor 3 on the wing surface of the wing 4 when hovering. The length of the tilting wing 13 is 0.75 to 1.25 times the radius of the tilting rotor 3 (in this embodiment, the length of the tilting wing 13 is 0.75 times the radius of the tilting rotor 3, which can avoid 80% of the impact of the downwash of the tilting rotor 3 on the wing surface of the fixed wing 15). The tilting wing 13 and the tilting rotor 3 tilt synchronously, while ensuring the lift of the fixed wing 15, reducing the airflow impact of the downwash of the tilting rotor 3 on the wing surface of the wing 4 when hovering, and avoiding the need to increase the power to provide greater thrust when tilting, and avoiding the tilting wing 13 being affected by excessive crosswind interference when hovering, thus affecting stability.

[0028] The tilting wing 13 of the present invention is provided with an aileron 14, and the tilting rotor 3 is provided with a power cowling 12.

[0029] Same as Example 2. Example 4

[0030] In this embodiment, the length of the tilting wing 13 is 1.25 times the radius of the tilting rotor 3, which can avoid the full impact of the downwash of the tilting rotor 3 on the surface of the fixed wing 15.

[0031] Same as Example 3. Example 5

[0032] In this embodiment, the length of the tilting wing 13 is equal to the radius of the tilting rotor 3, which can avoid all the impact of the downwash of the tilting rotor 3 on the surface of the fixed wing 15, and achieves the best energy efficiency.

[0033] Same as Example 3. Example 6

[0034] Depend on Figure 6As can be seen, the bracket 10-1 of the present invention is provided with an electronic speed controller 16, and the tail cover 9 is provided with heat dissipation holes 17 above and below the electronic speed controller 16. The balance propeller 6 is located outside the tail cover 9 and below the electronic speed controller 16, so that the heat generated by the electronic speed controller 16 is forcibly guided vertically by the balance propeller 6 and discharged through the heat dissipation holes 17 to prevent the electronic speed controller 16 from overheating.

[0035] Same as Example 3. Example 7

[0036] Depend on Figure 7 As can be seen, the support leg 10-6 of the present invention is provided with a tail support 18, and the lower end of the tail support 18 is provided with a ground contact end 19, which is made of elastic cushioning material; when the aircraft lands, it plays a role in smooth cushioning.

[0037] Same as Example 6.

[0038] Working principle: Before takeoff, the tilting wing 13 and the tilting rotor 3 (power cowl 12) tilt synchronously, so that the tilting rotor 3 faces upward and the landing wheels 2 are downward. The tail support 10 lowers the outriggers 10-6, and the two landing wheels 2 and the outriggers 10-6 form a three-point support to make the entire aircraft park stably.

[0039] This invention has two flight modes: when taking off vertically or hovering, the tilt rotor 3 and the balance propeller 6 rotate simultaneously. At this time, the tilt rotor 3 faces upward and the landing wheel 2 is downward. Also, the legs 10-6 of the tail support 10 are retracted, which reduces the impact of the downwash generated by the tilt rotor 3 on the airflow surface of the wing 4, thereby stabilizing the fuselage 1 and improving flight efficiency. When switching to level flight mode, tiltrotor 13 and tilt rotor 3 (power cowl 12) tilt synchronously, so that tilt rotor 3 faces forward and landing wheel 2 is behind. At this time, balance propeller 6 stops rotating and one of the blades is put into the propeller groove 8, so that balance propeller 6 is aligned with the axis of fuselage 1, thereby reducing wind resistance. During vertical landing, the tilting wing 13 and the tilting rotor 3 (power cowl 12) tilt synchronously, so that the tilting rotor 3 faces upward and the landing wheels 2 are downward. The balancing propeller 6 rotates synchronously again. At the same time, the outrigger 10-6 driven by the folding linkage assembly of the tail support 10 is lowered. When landing, the two landing wheels 2 and the outrigger 10-6 form a three-point support to make the entire aircraft land smoothly.

Claims

1. A vertical takeoff and landing aircraft, comprising wings (4) on both sides of a fuselage (1), a tail fin (5) at the tail end of the fuselage (1), and tiltrotor (3) at the ends of the wings (4), characterized in that... A tail balancing mechanism is provided at the tail end of the fuselage (1) and below the tail fin (5). The tail balancing mechanism includes a tail cover (9), which has a propeller groove (8) and a balancing propeller (6) driven by a motor (7) inside the propeller groove (8).

2. A vertical takeoff and landing aircraft according to claim 1, characterized in that... The tail balancing mechanism also includes a tail support (10) located on the tail cover (9), and the rear end of the tilt rotor (3) is provided with a landing wheel (2).

3. A vertical takeoff and landing aircraft according to claim 1, characterized in that... The wing (4) includes a fixed wing (15), and a tilting wing (13) is provided at the end of the fixed wing (15). The tilting rotor (3) is located at the outer end of the tilting wing (13), and the length of the tilting wing (13) is 0.75 to 1.25 times the radius of the tilting rotor (3).

4. A vertical takeoff and landing aircraft according to claim 2, characterized in that... The wing (4) includes a fixed wing (15), and a tilting wing (13) is provided at the end of the fixed wing (15). The tilting rotor (3) is located at the outer end of the tilting wing (13), and the length of the tilting wing (13) is 0.75 to 1.25 times the radius of the tilting rotor (3).

5. A vertical takeoff and landing aircraft according to claim 2 or 4, characterized in that... The tail support (10) includes a support leg (10-6) driven by a folding linkage assembly, the support leg (10-6) being located below the balance propeller (6); the motor (7) is fixed above the tail cover (9) by a motor mounting base (11) located above the balance propeller (6).

6. A vertical takeoff and landing aircraft according to claim 5, characterized in that... The folding linkage assembly includes a leg (10-6) hinged to the lower end of a bracket (10-1); A drive rod (10-4) and a driven rod (10-5) are also provided between the bracket (10-1) and the foot (10-6). One end of the drive rod (10-4) is hinged to the driven rod (10-5), and the other end is hinged to the bracket (10-1) via a spherical bearing (10-3). The two ends of the driven rod (10-5) are respectively hinged to the drive rod (10-4) and the foot (10-6). An electric push rod (10-2) is also connected between the bracket (10-1) and the drive rod (10-4), and one end of the electric push rod (10-2) is connected to one end of the proximal follower rod (10-5) of the drive rod (10-4).

7. A vertical takeoff and landing aircraft according to claim 1, 2, 3, 4, or 6, characterized in that... The bracket (10-1) is equipped with an electronic speed controller (16), the tail cover (9) is located above and below the electronic speed controller (16) and has heat dissipation holes (17), and the balance propeller (6) is located below the electronic speed controller (16).

8. A vertical takeoff and landing aircraft according to claim 5, characterized in that... The bracket (10-1) is equipped with an electronic speed controller (16), the tail cover (9) is located above and below the electronic speed controller (16) and has heat dissipation holes (17), and the balance propeller (6) is located below the electronic speed controller (16).

9. A vertical takeoff and landing aircraft according to claim 7, characterized in that... The balanced propeller (6) has two blades; the support legs (10-6) are provided with tail support (18), and the lower end of the tail support (18) is provided with a ground contact end (19), which is made of elastic buffer material.

10. A vertical takeoff and landing aircraft according to claim 8, characterized in that... The balanced propeller (6) has two blades; the support legs (10-6) are provided with tail support (18), and the lower end of the tail support (18) is provided with a ground contact end (19), which is made of elastic buffer material.

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