Vibration isolator system for rotating wing aircraft seats

Abstract

The present invention is a vibration isolator (10) system that provides improvements in comfort and health by reducing the vibrations to which rotary wing aircraft pilots are exposed. The system, based on the Quasi-zero Stiffness principle, has a honeycomb structure (20) consisting of hexagonal cells (30). Each cell (30) comprises an internal damping element (31), a cage structure (32) and damping heads (33). This design, supported by layers of wool (41), sponge (42) and plate (43) that distribute the pilot's weight evenly, ensures effective isolation of low-frequency vibrations. It aims to increase flight safety and comfort by reducing the physical discomfort experienced by pilots during long flights.

Description

[0001] Vibration Isolator System for Rotating Wing Aircraft Seats

[0002] FIELD OF THE INVENTION

[0003] The present invention relates to an improved vibration isolator system for providing vibration isolation for pilots of rotating wing aircraft, particularly helicopters.

[0004] In particular, the present invention relates to a vibration isolator system developed to provide vibration and impact isolation by easily integrating the same into the helicopter pilot seat.

[0005] PRIOR ART

[0006] The existing cushions used in helicopters to ensure pilot comfort are generally made of polyurethane, sponge or similar materials. However, these systems alone do not provide effective isolation of vibrations. This can lead to back pain, muscle injuries and other health problems as a result of long flights. Vibrations can cause significant damage to pilots' spine and muscular systems, with low-frequency vibrations, particularly experienced in the Z-axis, causing serious health problems. In the prior art, cushions made of polyurethane or sponge used for helicopter pilots cannot sufficiently reduce vibrations.

[0007] As a result of the patent search in the literature, patent number US10206512B2 was identified. The patent describes a seat cushion design with a honeycomb structure that aims to increase comfort by reducing pressure on the body. This structure aims to increase comfort, but does not contain a special structure for vibration or impact damping. In addition, it is not designed for use in vehicle seats exposed to low- frequency vibration, such as helicopters. Patent document numbered KR101948506B1 also mentions a cushion design with a honeycomb structure to support the body of the person sitting. The abovementioned cushion does not have vibration or impact dampening properties. Shuai G., et al. (2023), in their work titled “A quasi-zero-stiffness elastic metamaterial for energy absorption and shock attenuation, Engineering Structures” have also conducted a scientific study on a quasi zero stiffness 4-surface prismatic cellular vibration isolator. However, the study they carried out is not hexagonal, honeycomb shaped, multi-layered and composite structure as in this study.

[0008] As a result, the abovementioned problems and the problems that cannot be solved in the light of the state of the art have made it necessary to make an improvement in the relevant technical field.

[0009] BRIEF DESCRIPTION OF THE INVENTION

[0010] The present invention relates to a vibration isolator developed for rotary wing aircraft in order to eliminate the abovementioned disadvantages and to bring new advantages to the relevant technical field.

[0011] The main object of the present invention is to provide helicopter pilots with effective insulation against high vibration levels, especially low frequency (4-8 Hz) vibrations transmitted through the seat, thus reducing the risk of health problems for pilots and providing a comfortable flight experience.

[0012] Another object of the present invention is to reduce the risk of health problems such as back pain, back injuries and disc degeneration by minimizing the vibrations transmitted to the spine.

[0013] Another object of the present invention is to provide a reduction of up to 56% in high vibration directions such as the Z axis and to reduce vibration levels by 32% in the X and Y axes.

[0014] Another object of the present invention is to prevent loss of attention during flight and to increase flight safety by reducing the pilot's physical fatigue and vibration-related discomfort.

[0015] Another object of the present invention is to create a cushion with a vibration isolator that can be easily integrated into helicopter pilot seats. The present invention is a vibration isolator that can be integrated into a pilot seat for rotary wing aircraft and is characterized by having a honeycomb structure consisting of multiple hexagonal cells produced with Quasi-zero Stiffness technology so as to fulfil all the objects mentioned above and will be obtained from the following detailed description.

[0016] In order to understand the advantages of the present invention with its structure and additional elements, it shall be evaluated with the following defined figures.

[0017] BRIEF DESCRIPTION OF DRAWINGS

[0018] Figure 1 is the perspective view showing the honeycomb structure of the vibration isolator which is the subject of the invention.

[0019] Figure 2 is the detailed views of the cell structure in the vibration isolator which is the subject of the invention.

[0020] Figure 3 is the disassembled view of the cell structure in the vibration isolator which is the subject of the invention.

[0021] Figure 4 is a representative view of the cushion structure containing the vibration isolator which is the subject of the invention.

[0022] REFERENCE NUMBERS

[0023] 10 Vibration Isolator

[0024] 20 Honeycomb Structure

[0025] 30 Cell

[0026] 31 Damping Element

[0027] 32 Cage Structure

[0028] 33 Damping Upper Head

[0029] 34 Damper Lower Head

[0030] 40 Cushion

[0031] 41 Wool

[0032] 42 Sponge

[0033] 43 Plate DETAILED DESCRIPTION OF THE INVENTION

[0034] In this detailed description, the novelty of the present invention is described by means of examples only for clarifying the subject matter such that no limiting effect is created.

[0035] The present invention provides a vibration isolator (10) in a honeycomb structure (20) that can be integrated into the helicopter pilot's seat. As seen in Figure 1 , the honeycomb structure (20) consists of multiple layers of hexagonal cells (30) and each cell (30) is specially designed to isolate vibrations. The main technology of the invention is vibration isolation based on the Quasi-zero Stiffness principle. QuasiZero Stiffness isolation system is a nonlinear vibration isolation structure that has high static stiffness characteristics to improve the carrying capacity and deformation resistance, and can reduce the natural frequency of the system with low dynamic stiffness characteristics. This structure is produced with a 3D printer. The main material used in the construction of the vibration isolator (10) was chosen as thermoplastic polyurethane (TPU).

[0036] As seen in Figure 1 and Figure 2, the honeycomb structure (20), which is the basic building block of the vibration isolator (10), consists of hexagonal shaped cells (30). These cells (30) ensure that vibrations are damped in different directions on each axis and effectively distribute and reduce the vibrations encountered by the helicopter during flight. The geometric structure of the hexagonal cells (30) allows the energy density of the vibrations to be distributed homogeneously among the cells (30). Each cell (30) in the honeycomb structure (20) is equipped with internal damping elements (31 ) capable of absorbing vibration. The said damping elements (31 ) prevent the propagation of vibrations by absorbing the vibration energy contained in the cells (30). The damping elements (31 ) have been specifically selected to ensure the absorption of low frequency vibrations (especially in the 4-8 Hz range). The damping elements (31 ) are surrounded by a cage structure (32) to ensure effective dissipation of vibrations between the cells (30). The cage structure (32) has a hexagonal form and ensures that the cells (30) are connected to each other and that vibrations are isolated in each cell (30). There is a damping upper head (33) and a damping lower head (34) to ensure the fixing of the internal damping elements (31 ) within the cage structure (32). As seen in Figure 4, the integration of the vibration isolators (10) into the seat cushion (40) is achieved by placing them on the wool (41 ), polyurethane sponge (42) and plate (43) layers, respectively. The plate (43) and the polyurethane sponge (42) form the support structure of the vibration isolator (10) and ensure that the pilot's weight is distributed evenly across all cells (30). The resulting cushion (40) is placed with the wool (41 ) part on top and the vibration isolator (10) in contact with the seat surface. Wool (41 ) is used as a natural vibration dampener and increases pilot comfort during long-distance flights. The wool (41 ) material helps to both effectively reduce vibrations and provide ventilation.

[0037] The vibration isolator (10) is designed to both increase comfort and protect pilot health. The isolator (10) effectively isolates vibrations with the help of its high static stiffness and low dynamic stiffness properties, minimizing the vibrations reaching the pilot's spine. In the experimental tests, it was observed that the vibrations were reduced by 56% in the measurements made in the Z axis and a 32% reduction was achieved in the X and Y axes.

Claims

CLAIMS1. A vibration isolator (10) that can be integrated into a pilot seat for rotary wing aircraft, characterized by having a honeycomb structure (20) consisting of multiple hexagonal cells (30) produced with Quasi-zero Stiffness technology.

2. A vibration isolator (10) according to claim 1 , characterized by comprising a damping element (31 ) that prevents the vibrations from spreading by absorbing the vibration energy of said cells (30); a cage structure (32) that surrounds the said damping element (31 ) and ensures that the vibrations are effectively distributed among the cells (30); and at least one damping head (33, 34) that allows the damping elements (31 ) to be fixed to the cage structure (32).

3. A vibration isolator (10) according to any of the preceding claims, characterized by being made of thermoplastic polyurethane material.

4. A vibration isolator (10) according to any of the preceding claims, characterized by being produced with a 3D printer.

5. A vibration isolator (10) according to any of the preceding claims, characterized by providing low frequency (4-8 Hz) vibration isolation.

6. A pilot seat cushion (40) with vibration isolator (10) according to any one of the preceding claims.

7. A pilot seat cushion (40) according to claim 6, characterized by comprising wool (41 ), polyurethane sponge (42), plate (43) and vibration isolator (10) respectively.

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