A spherical bearing structure providing vibration isolation in rotary wing aircraft

Abstract

The invention relates to a spherical bearing structure (10) that provides active vibration isolation and motion control of rotary wing systems such as rotary wing aircraft and wind turbines.

Description

[0001] A SPHERICAL BEARING STRUCTURE PROVIDING VIBRATION ISOLATION IN ROTARY WING AIRCRAFT

[0002] Technical Field

[0003] The invention relates to a spherical bearing structure that provides active vibration isolation and motion control of rotary wing systems such as rotary wing aircraft and wind turbines.

[0004] State the of Art

[0005] Vibrations pose a serious engineering problem in rotary wing aircraft used today, especially in systems such as helicopters and unmanned air vehicles. Vibrations occurred during the rotation of the wings and the operation of the engine and powertrain systems can adversely affect both pilot comfort and the structural integrity of the aircraft. These vibrations can reduce the performance of the aircraft, cause unwanted damage to the rotor shaft, and lead to material fatigue in the long term. In this context, providing vibration isolation in rotary wing vehicles is of great importance. The effectiveness of vibration isolation systems plays a critical role in damping and preventing the spread of vibrations occurring in the vehicle.

[0006] The spherical bearing structures used in rotary wing aircraft in the state of art stand out as an innovative approach in the design of such vibration isolation systems. These structures aim to minimize the effect of vibrations by providing a flexible connection when connecting the various parts of rotary wing aircraft, especially the rotor and structural elements. The spherical bearing structures offer significant advantages in applications requiring high precision. + Such structures also have the capacity to effectively control vibrations without increasing the weight of aircraft, thus improving the overall performance, comfort, and safety of rotary-wing aircraft. Thus, the overall performance, comfort and safety of rotary wing aircraft can be improved.

[0007] The vibration problems occurring in the mentioned wing structure necessitate the creation of a spherical bearing that can be placed at the wing root, can be actively controlled, has a gear geometry and provides angle control and vibration isolation in three axes. As a result of the research carried out, the document numbered EP2931604B1 was encountered. The relevant document relates to rotary-wing aircraft. The current technology does not independently control the angle of helicopter rotor blades. The angle of the entire rotor shaft system is directly controlled. However, it does not include a spherical bearing within the gear system that can actively isolate vibration from each blade.

[0008] Another document encountered as a result of the research is KR101 110608B1 . The said document concerns the helicopter rotor head. In the present art, a rotor head is mentioned, comprising a rubber seal to absorb the vibration and the impact generated during the rotation of the main wing and to prevent the vibration and impact from being transmitted to the rotating shaft and to prevent damage to the model helicopter. However, the present art does not have a gear structure on three different axes and there is no active vibration isolation feature.

[0009] As a result, due to the negativities described above and the inadequacy of existing solutions on the subject, it has become necessary to make a development in the relevant technical field.

[0010] Object of the Invention

[0011] The invention is inspired by current situations and aims to solve the above-mentioned negativities.

[0012] The main object of the invention is to provide a spherical bearing that provides active vibration isolation and control of rotary wing systems such as rotary wing aircraft and wind turbines.

[0013] Another object of the invention is to ensure the isolation of vibrations and control of wing angles in three different axes thanks to the first, second and third axis gears.

[0014] In order to achieve the above-mentioned objects, the invention is a spherical bearing structure that includes a blade connection that connects the blades, which are the propeller arms of aircraft or wind turbines with rotary wing systems, to the wing root and allows vibration reduction without using an active control system, wherein; it comprises: • A spherical gear placed at the wing root, located at the end of the blade connection, softens the blade vibrations and transmits them to the wing root and the body,

[0015] • A first axis gear, a second axis gear and a third axis gear connected to the spherical gear, which provides isolation and control of the vibration transmitted to the wing root in three different axes.

[0016] The structural and characteristic features of the invention and all its advantages will be understood more clearly thanks to the figures given below and the detailed description written by making reference to these figures, and therefore the evaluation needs to be made by taking these figures and detailed description into consideration.

[0017] Figures to Help Understand the Invention

[0018] Figure 1 is the view of the rotary wing vehicle wing root and blade connection.

[0019] Figure 2 is the view of the blade connection and spherical bearing.

[0020] Description of Piece References

[0021] 1. Blade

[0022] 2. Blade Connection

[0023] 3. Spherical gear

[0024] 4. First axis gear

[0025] 5. Second axis gear

[0026] 6. Third axis gear

[0027] 7. Wing root

[0028] 10. Spherical bearing structure

[0029] Detailed Description of the Invention In this detailed description, the preferred embodiments of the spherical bearing structure (10) which is the subject of the invention are described only for the purpose of a better understanding of the subject.

[0030] The spherical bearing structure which is the subject of the invention provides the reduction of vibrations without using an active control system and comprises a blade connection (2) which provides the connection of the blades (1 ), which are the propeller arms of aircraft or wind turbines with rotary wing systems, with the wing root (7). In order to reduce the aforementioned vibrations, the spherical bearing structure comprises a spherical gear (3). The spherical gear (3) is located at the wing root (7) and at the end of the blade connection (2), softens the blade vibrations and transmits them to the wing root (7) and the body. However, the spherical bearing structure (10) which is the subject of the invention comprises a first axis gear (4), a second axis gear (5) and a third axis gear (6) which are connected to the spherical gear (3) and provide isolation and control of the vibration transmitted to the wing root (7) in three different axes.

[0031] The spherical gear joint structure (10) which is the subject of the invention aims to increase passive vibration isolation for rotary wing aircraft, especially helicopters. Passive vibration isolation refers to mechanical solutions that are implemented to reduce vibrations in helicopters without using any active control systems. Vibration in helicopters occurs due to rotor rotation and aerodynamic effects, and these vibrations can reduce passenger comfort, as well as shorten equipment life and reduce pilot task efficiency. Passive vibration isolation comprises passive components designed to limit the spread of vibrations and their impact on equipment. The solution offered by the spherical bearing structure (10), which is the subject of the invention, is to isolate the vibration transmitted to the wing root in three different axes, thanks to the spherical bearing feature provided by the spherical gear (3) placed at the wing root of the blade. In this configuration, angle and vibration isolation control is performed on three different axes thanks to the first axis gear (4), the second axis gear (5) and the third axis gear (6). There are gear lines on the main spherical gear (3) that allow rotation in different directions. The spherical bearings placed on helicopter blades help control vibration and angle by flexibly regulating the angular movements of the blade. These bearings are used specifically to facilitate the angular movements of the rotor blades, both up and down (flap), forward and backward (lead-lag), and in the direction of rotation (pitch). Thanks to the main spherical gear (3), the connection to the wing root and the control of the wing are performed. The spherical bearing structure (10) with gear geometry softens this movement, prevents the vibrations from being transferred to the body and ensures the efficient operation of the rotor. Lead- lag movement, also known as forward-backward oscillation, is caused by changes in rotor rotation speed and aerodynamic forces. The spherical bearing structure (10) with gear geometry balances these movements and prevents structural overloads by reducing the forces transmitted to the rotor shaft. Pitch control is a critical function that adjusts the lifting force and steering of the helicopter. By varying the pitch angle, the pilot optimizes the lifting force generated by the rotor blades at different points during each revolution. The spherical bearing structure (10) with gear geometry allows the pitch angle to be adjusted smoothly, thus increasing both manoeuvrability and control precision. From a vibration control perspective, these joints prevent the spread of low-frequency vibrations from the blades, improving pilot comfort and protecting equipment. It also absorbs impacts by facilitating flexible blade movements and extends the life of rotor components. Therefore, spherical bearings contribute to the safe and comfortable flight performance of helicopters by providing both vibration isolation and precise angular control.

Claims

CLAIMS1. A spherical bearing structure (10) that allows the reduction of vibrations without using an active control system, including a blade connection (2) that connects the blades (1 ), which are the propeller arms of aircraft or wind turbines with rotary wing systems, to a wing root (7), characterized by comprising;• A spherical gear (3) placed at the wing root (7), located at the end of the blade connection (2), softens the blade vibrations and transmits them to the wing root (7) and a body,• A first axis gear (4), a second axis gear (5) and a third axis gear (6) connected to the spherical gear (3) that provides isolation and control of the vibration transmitted to the wing root (7) in three different axes.

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