Safety device for changing half-rotor to heli-rotor of flying vehicle

Abstract

To provide a safety device for changing a half-rotor installed to the center of a flying vehicle to a heli-rotor to provide safety of the flying vehicle.SOLUTION: A safety device for changing a half-rotor to a heli-rotor of a flying vehicle includes right and left rotors comprising inside rotor blades 9, 10 provided with outside rotor blades 1, 11, which function as half-rotors in normal operation state and simultaneously eject and deploy the outside rotor blades 1, 11 with centrifugal force as necessary, thereby selecting heli-functional normal operation or landing safely with auto-rotation.SELECTED DRAWING: Figure 2

Description

Detailed Description of the Invention - Industrial Application Field

[0001] This invention relates to a safety device for an eVTOL aircraft in the event of battery depletion or blade damage during flight.

Background Art

[0002] Currently, various flying vehicles are emerging. However, it is conceivable that some propellers may become inoperable during emergencies, or flight may become impossible due to a decrease in battery capacity. Although some are equipped with parachutes, there are still concerns as they are not completely safe and failures may occur during development. The problems to be solved by the invention

[0003] This invention aims to solve this problem and enable a safe landing on the ground during emergencies. Means for solving the problems

[0004] As a result, it was found that by providing a safety device in the center of the flying vehicle that can convert the half-rotor of the flying vehicle of the present invention into a helicopter rotor, a safe landing on the ground can be achieved. The reason for using a half-rotor is to avoid compromising the convenience of the eVTOL aircraft. Actions and Examples

[0005] Next, the structure and actions of the present invention will be described with examples. Structure of the present invention This invention installs a helicopter function on a flying vehicle and will be described with electric power. An emergency auxiliary power source must also be provided. [1] To be variable into a helicopter rotor, inner rotor blades 9 and 10 are provided with outer rotor blades 1 and 11, and the outer rotor blades 1 and 11 are ejected and deployed during emergencies. The present invention is designed to land safely in autorotation. If it is loadable, it can operate in helicopter mode with a backup battery or other power sources. [2] In case of emergency, the rotor angle of attack is operated to ±0, and the igniter is ignited by a firing column (not shown in the figure) to cause the gas generating agent 23 to ignite and expand, pulling out the piston rod 24. This can also be an electromagnetic servo. In this way, the movement of the outer rotor blades 1 and 11 is made free. Due to centrifugal force, the outer rotor blades 1 and 11 are ejected. At this time, the synchronous wires 19 and 25 circulate inside the left and right inner rotor blades 9 and 10 through the guides of the U-shaped grooves provided at A and A' of the spool 21 and are connected to the synchronous shafts 18 and 26, so they are synchronously ejected and deployed. In this way, it becomes a helicopter mode and can transition to autorotation flight or normal helicopter flight. The structure for synchronization during deployment is to prevent a situation where one side may experience a delay in deployment for some reason. [3] Since the synchronous shafts 18 and 26 penetrate inside the blades, the hub system of the inner rotor blades 9 and 10 is designed as a semi-articulated hinge type where the rotor rotates with the hinge shaft 14 as shown in Figures 3 and 4, and the hinge shaft 14 is designed at the lower part of the rotor. [4] Structurally, the synchronous shafts 18 and 26 cannot be made thick, but since a large tension is applied, a carbon shaft is effective. However, the shaft design must be bendable and twistable. It will be bendable naturally because it is long, and it will be twistable because twist occurs when giving an angle of attack during normal flight. Also, carbon wires are suitable for the synchronous wires 19 and 25. The shafts 18, 26 and the wires 19, 25 can be made of other materials if they have sufficient strength. [5] The size of the air intake 27 is used to adjust the negative pressure during ejection and deployment, preventing the synchronous shafts 18 and 26 from colliding with the stopper.

Embodiment

[0006] When in the half-rotor state of the present invention, an appropriate angle of attack is given to bear a part of the lift, but most of it should be borne by other blades. Also, reverse stress and one-sided excessive lift are offset by the helicopter function or dealt with by the gyro function. When the rotor blades are ejected and deployed, it is necessary to approach the optimal autorotation speed for the aircraft. If there is insufficient rotation in that state, the rotation can be increased with the backup battery or the autorotation operation can be entered. Alternatively, if it is to be operated in helicopter mode, it should be made to approach approximately 600 rpm. The autorotation is performed by the pilot, but the AI can find a safe open space and automatic autorotation is also possible. Effects of the Invention

[0007] Although flying cars have been developed without paying attention to safety, the safety is ensured by this invention, and further development of eVTOL is expected.

Brief Description of the Drawings

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Description of Signs

Claims

【Claim 1】 Outer rotor blades 1 and 11 are provided on the left and right inner rotor blades 9 and 10, which function as a half rotor in the normal operating state. However, in case of emergency, the piston rod 24 that fixes the synchronous shafts 18 and 26 is pulled out to allow the outer rotor blades 1 and 11 to move freely. The outer rotor blades 1 and 11 are ejected by centrifugal force. At this time, the synchronous wires 19 and 25 circulate inside the left and right inner rotor blades 9 and 10 through the left and right wire guides A and A' and are connected to the synchronous shafts 18 and 26, so that they are synchronously ejected and deployed. A safety device for converting the half rotor of a flying vehicle into a helicopter rotor.

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