Planetary rotor vertical take-off and landing aircraft

Abstract

The vertical take-off and landing aircraft includes a helicopter and a drone. One of the problems of the vertical take-off and landing aircraft is a plane crash problem caused by the vortex-ring state.SOLUTION: In the vertical take-off and landing aircraft of the present invention, the secondary rotor is attached to the primary rotor or the tip of the rotating arm. As a result, even if the fuselage of the airframe is at the same position in the hovering state, the secondary rotor does not rotate at the same position because the secondary rotor revolves and rotates by the rotation of the primary rotor as if the earth rotates around the sun, and therefore, the secondary rotor does not enter the vortex ring state.SELECTED DRAWING: Figure 1

Description

[Technical Field]

[0001] The present invention relates to a vertical take-off and landing aircraft. [Background technology]

[0002] Vertical take-off and landing aircraft include helicopters and drones. One of the problems with these aircraft is the risk of crashes caused by vortex ring states.

[0003] The vortex ring state, also known as settling with power, occurs when a helicopter, vertical take-off and landing aircraft, or drone descends rapidly, causing the downwash to be sucked back into the propeller, resulting in air circulating vertically around the propeller.

[0004] Downwash is the downward wind caused by the rotation of a propeller, and a vortex ring state is essentially a helicopter, VTOL aircraft, or drone falling into its own downwash.

[0005] A vortex ring state can cause a loss of lift, potentially leading to a crash. The occurrence of a vortex ring state is the number one or second leading cause of helicopter crashes. When rapidly descending helicopters, vertical take-off and landing aircraft, and drones, they are affected by downwash, so caution is required to prevent the occurrence of a vortex ring state.

[0006] As a specific means for preventing the occurrence of a vortex ring state, in the vertical take-off and landing aircraft of the present invention, the rotation axis of the primary rotor or arm attached to the fuselage of the aircraft is first rotated, which causes the primary rotor or arm to rotate.

[0007] Furthermore, the rotation axis of the secondary rotor attached to the tip of the primary rotor or arm is rotated in the opposite direction to the rotation axis of the primary rotor. This reverse rotation cancels out the torque generated by the primary rotor.

[0008] The secondary rotor rotates due to the rotation of the rotor shaft of the secondary rotor. The reason why the secondary rotor is attached to the underside of the primary rotor is to prevent the downwash generated by the secondary rotor from hitting the primary rotor and reducing the propeller efficiency of the secondary rotor.

[0009] The vortex ring state occurs when the rotor falls into its own self-generated downwash, as it rotates in the same position, such as during hovering.

[0010] However, with the secondary rotor of the present invention, even if the fuselage of the aircraft is in the same position during hovering, the rotation of the primary rotor causes the secondary rotor to revolve and rotate on its axis, just like the Earth revolving around the sun, so the secondary rotor does not rotate in the same position, and therefore the secondary rotor does not enter a vortex ring state. [Prior art documents] [Patent documents]

[0011] [Patent Document 1] Special Publication No. 2024-505614 Summary of the Invention [Problem to be solved by the invention]

[0012] The present invention aims to reduce crashes caused by vortex ring states. [Means for solving the problem]

[0013] As a specific means of preventing the occurrence of vortex ring states, the vertical take-off and landing aircraft of the present invention has secondary rotors attached to the tips of the rotating arms or primary rotors, thereby reducing crashes caused by vortex ring states. [Effects of the Invention]

[0014] The secondary rotor of the present invention does not rotate in the same position even when the fuselage of the aircraft is in the same position during hovering, because the rotation of the primary rotor causes the secondary rotor to revolve and rotate on its axis like the Earth revolving around the sun, and therefore the secondary rotor does not rotate in the same position, and therefore the secondary rotor does not enter a vortex ring state. [Brief explanation of the drawings]

[0015] [Figure 1] FIG. 1 is a plan view of a vertical take-off and landing aircraft of the present invention. [Figure 2] FIG. 2 is a rear view of the vertical take-off and landing aircraft of the present invention. DETAILED DESCRIPTION OF THE INVENTION [Example]

[0016] Figure 1 is a top plan view of a vertical take-off and landing aircraft according to an embodiment of the present invention. The aircraft has a rotating arm or primary rotor 1 on top of its fuselage 3, and a secondary rotor 2 (a rotating disk in the top view) at its tip.

[0017] 2 is a rear view of an embodiment of a vertical take-off and landing aircraft of the present invention. A primary rotor or arm rotation shaft 4 is provided on the fuselage 3, and a secondary rotor shaft 5 is provided at the tip of the primary rotor or arm 1, and secondary rotors 2 are provided.

[0018] As a result, even if the fuselage 3 of the aircraft is in the same position during hovering, the secondary rotor 2 of the present invention will not rotate in the same position because the rotation of the primary rotor 1 will cause the secondary rotor 2 to revolve and rotate on its axis just like the Earth revolving around the sun, and therefore the secondary rotor 2 will not enter a vortex ring state. [Industrial Applicability]

[0019] The present invention can be used in place of a vertical take-off and landing aircraft, a drone, or a helicopter. [Explanation of symbols]

[0020] 1. Primary rotor or arm 2. Secondary rotor (rotating disc in top view) 3. Torso 4. Primary rotor or arm rotation axis 5. Rotation shaft of secondary rotor

Claims

1. A vertical take-off and landing aircraft characterized by having a primary rotor or rotating arm with a secondary rotor at its tip.

2. 2. The vertical take-off and landing aircraft of claim 1, further comprising a secondary rotor that rotates in the opposite direction to the rotation of the primary rotor or the rotating arm.

3. 2. The vertical take-off and landing aircraft of claim 1, wherein a secondary rotor is attached to the underside of the primary rotor or the rotating arm.

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