An impact damping mechanism

Abstract

The present invention relates to a body (2) which is the aircraft, at least one airbag assembly (3) that is located on the body (2) and protects the pilot and / or the passenger, at least one sensor (4) that detects the active or inactive status of the airbag assembly (3), and at least one activation apparatus (5) that is located on the body (2) and enables the airbag assembly (3) to operate when triggered by the user.

Description

[0001] AN IMPACT DAMPING MECHANISM

[0002] This invention is related to the impact damping mechanism in aircraft.

[0003] Airbag blasting systems that are activated in the event of an impact in aircraft play a very important role in pilot safety. Seat systems in helicopters are of vital importance in terms of pilot comfort and safety. Since the seat ejection system in helicopters is not safe like in airplanes, alternative measures must be taken to ensure the pilot's survival in the event of a helicopter crash. The seat ejection system in helicopters is not safe like in airplanes. Because the helicopter propeller prevents the pilot from being thrown up and the rapid rotation of the propeller can cause serious damage. In addition, there is no canopy system that can break in helicopters. Helicopters usually spin and fall onto the fuselage floor and the pilot has no chance of jumping because the rotating helicopter parts can harm the pilot. For this reason, improvements and safety measures made in seat systems in helicopters are of great importance. The impact damping under-seat airbag system is used to dampen the impact in the event of a fall to the floor of the helicopter and to ensure that the pilot hits a softer surface. By means of a mechanism under the seat, the pilot can trigger the airbag system in an emergency. In addition, in explosions targeting helicopters, the seat systems can be activated to save the pilot's life. In this way, seat systems have been developed to ensure the safety of the pilot and help him survive.

[0004] In the Israeli patent document numbered WO2010018561 in the known state of the art, the design of a helicopter with an upward ejection feature is mentioned. There is a body positioned at least partially under one or more rotors that provide the helicopter with the ability to fly. A cockpit is coupled to the body, wherein the span of the rotors does not reach above the position of the cockpit. An ejection seat is located inside the cockpit, wherein the ejection seat is adapted to be ejected upward above the cockpit clearing the span of the rotors. In this way, the seat can be thrown upwards by clearing the area of the rotors. This design aims to increase the pilot's chance of survival in the event of a helicopter crash. In conventional helicopters, rotors prevent the pilot from being thrown upwards and can pose a safety risk. However, this design allows the pilot to be thrown upwards by using an ejection seat that clears the area of the rotors. In this way, it is aimed for the pilot not to be affected by the rotors during the crash of the helicopter and to get out safely.

[0005] In the United States patent document numbered US4655416 in the state of the art, a crashworthy helicopter cockpit having a pyrotechnic system actuated by a stroking pilot seat for repositioning the upper portion of the cyclic control stick upon a severe or crash landing that is independent of aircraft electric and hydraulic systems is mentioned. This system uses a pyrotechnic system that works with the movement of a seat attached to the pilot. This system allows the upper part of the helicopter (cyclic control stick) to be repositioned in the event of an accident. The cyclic control stick is a device that provides flight control of the helicopter and normally consists of a lever that the pilot controls manually. A crashworthy helicopter cockpit is designed to increase the safety and survival of the pilot in the event of a crash or a hard landing. This type of cockpit comprises emergency systems that can operate independently of failures in the electrical and hydraulic systems. A cyclic control stick that automatically repositions itself to the pilot can make it easier for the pilot to exit or take other precautions after a crash and provide a safer rescue. This pyrotechnic system allows the cyclic control stick to be automatically raised or moved to another position using an explosion or mechanical movement in the event of a crash. In this way, even if the helicopter overturns or is otherwise deformed after the crash, the pilot is prevented from losing control or getting trapped.

[0006] An impact damping mechanism developed with this invention prevents serious injuries to passengers in the event of a crash. The airbag reduces the impact and minimises head, neck, chest and upper body injuries.

[0007] Another aim of this invention is for the airbag to be activated by the pilot before the aircraft takes impact.

[0008] The impact damping mechanism, which is realised to achieve the aim of the invention and defined in the first claim and the claims dependent on this claim, comprises a body which is the main structure or interior cabin of the aircraft, an airbag mechanism which comprises one or more airbags located inside the aircraft, and is used to prevent the aircraft from being damaged in a sudden crash or accident and to protect the people inside. Sensors are devices that monitor the operating status of airbag assemblies and determine when these airbags should be activated. Sensors can monitor the environmental conditions and speed of the aircraft and detect crashs or accidents. Activation apparatus is a device that enables the user (usually the pilot or passenger) to activate or deactivate the airbag assemblies as desired. For example, it is used for the pilot to activate the airbags by pressing a button in an emergency situation or to deactivate these features in a normal situation.

[0009] Said impact damping mechanism comprises at least one crank that is rotated around its own axis by being triggered by the user via the activation apparatus, and at least one connection piece that rotates freely from the end where it is connected to the crank by rotating the crank via the activation apparatus. The connection piece comprises a first position (I) in which the other end of the connection piece, which is not connected to the crank, is in constant contact with the sensor, preventing the airbag device from operating. The connection piece comprises a second position (II) in which the crank rotates around its own axis when the activation device is triggered by the user, and thus the connection piece changes position and does not contact the sensor. Since the connection piece does not contact the sensor when it is in the second position (II), the sensor detects that the airbag mechanism should operate.

[0010] In one embodiment of the invention, the impact damping mechanism comprises at least one seat in the body where the pilot or passenger sits. In order for the airbag mechanism to be activated by the user, the connection piece must be brought to the second position (II). When the connection piece is brought to the second position (II), the part under the seat is almost completely filled with the airbag mechanism.

[0011] In one embodiment of the invention, the impact damping mechanism comprises a first support piece that allows the seat to be mounted. The first support piece is connected or mounted to the floor under the seat. In addition, there is a second support piece that moves telescopically within the first support piece located on the seat. This second support piece can be used to adjust or change the height of the seat. In this way, the assembly and height of the seat are provided by the first and second support pieces. In one embodiment of the invention, the impact damping mechanism comprises at least one shaft located between a connection piece and a first support piece and at least one bracket that provides the movement of this shaft. The shaft connected to the connection piece at one end is connected to the first support piece at the other end. This shaft provides a connection between the connection piece and the first support piece. There is a channel on the bracket. This channel allows the shaft to make a linear movement inside the shaft. The brackets support the shaft to make a linear movement inside the channel and provide a secure connection. In this way, the shaft between the connection piece and the first support piece can make a linear movement through the channel, thus providing the connection and movement between these two parts. When the connection piece is in the second position (II), the shaft slides in the channel as the connection piece moves, thus broken the connection piece and the sensor.

[0012] In one embodiment of the invention, the impact damping mechanism comprises at least one pin located between the first support piece at both ends when the connection piece is in the first position (I) and connected to the first support piece, and moves towards the channel with the displacement of the shaft in the channel when the connection piece is in the second position (II). However, the pin allows the second support piece to move telescopically within the first support piece when the connection piece is in the second position (II).

[0013] In one embodiment of the invention, when the connection piece is in the first position (I), the pin is in contact with the first support piece and the second support piece, and the impact damping mechanism is designed to almost completely prevent the pilot or passenger from being harmed at the moment of impact in the first position (I). When the connection piece is in the second position (II), the pin almost completely breaks contact with the first support piece and the second support piece. In the second position (II), the first spring, which almost completely restricts the movement of the second support piece within the first support piece, comes into play. These springs absorb the energy at the moment of impact and greatly reduce the harm to the pilot or passenger. In this way, a system designed to increase safety is created.

[0014] In one embodiment of the invention, the impact damping mechanism comprises at least one second spring used to fix the pin located between the first support piece and the second support piece in the first position (I) and to strengthen the connection between these pieces. The first support piece and the second support piece are positioned opposite each other. The pin provides the connection between the first support piece and the second support piece and is fixed in the first position (I). The second spring ensures that the pin is positioned between the first support piece and the second support piece. The second spring strengthens and fixes the connection between the first support piece and the second support piece when the connection piece is in the first position (I).

[0015] In one embodiment of the invention, the impact damping mechanism comprises a connection piece that is located between the crank and the shaft and allows the shaft to move linearly in the channel on the bracket when it is in the second position (II). It comprises a connection piece, one end of which is connected to the crank and the other end to the shaft. In the second position (II), the channel located in the bracket on the shaft allows the shaft to make a linear movement. When the crank is rotated, this rotational movement is transmitted to the connection piece and the shaft, and the shaft begins to move linearly in the channel on the bracket.

[0016] In one embodiment of the invention, the impact damping mechanism comprises an activation device, which is an arm, that moves the crank when the pilot or passenger pushes it towards the body floor. It comprises at least one rod that allows the crank to rotate around its own axis when the arm is triggered. When the arm is triggered, the rod moves from the point where it is connected to the crank around the centre of the crank to approach the body floor. The rods are located at both ends of the arm. When the arm is pushed towards the body floor, the part of the rod connected to the arm approaches the body floor.

[0017] In one embodiment of the invention, the impact damping mechanism comprises the activation apparatus, which is the flight control button, and at least one actuator that is located in connection with the crank and enables the crank to move when the activation apparatus is triggered by the user. The actuator enables the crank to rotate around its own axis.

[0018] In one embodiment of the invention, the impact damping mechanism comprises at least one airbag that is located inside the body and opens when the connection part is in the second position (II), at least one trigger that ensures the airbag is detonated according to the data transmitted by the sensor, and at least one gas source that fills the airbag when the trigger triggers the airbag mechanism. The airbag located inside the body is designed to protect the pilot and / or the passenger during a possible crash. The airbag is rapidly inflated at the moment of crash and protects the body of the pilot or passenger from the impact effects. The trigger reacts to the data received by the sensor. When the users detect that a crash is approaching or has occurred, they give the trigger the necessary command to detonate the airbag. The gas source rapidly transmits gas to the airbag when activated by the trigger and inflates it. This ensures that the airbag expands effectively at the moment of crash.

[0019] The impact damping mechanism implemented to achieve the aim of this invention is shown in the attached figures, and of these figures;

[0020] Figure 1 shows the schematic view of the Impact Damping Mechanism (1 ), Figure 2 shows the perspective view of the second position (II).

[0021] Figure 3 shows the schematic view of the Impact Damping Mechanism (1 ),

[0022] Figure 4 shows the schematic view of the Impact Damping Mechanism (1 ),

[0023] Figure 5 shows the perspective view of the first position (I), Figure 6 shows the perspective view of the second position (II).

[0024] Figure 7 shows the schematic view of the Impact Damping Mechanism (1 ),

[0025] Figure 8 shows the schematic view of the Impact Damping Mechanism (1 ),

[0026] The parts in the figures are numbered one by one and the equivalents of these numbers are given below.

[0027] 1. Impact Damping Mechanism

[0028] 2. Body

[0029] 3. Airbag Assembly

[0030] 4. Sensor

[0031] 5. Activation Apparatus

[0032] 6. Crank

[0033] 7. Connection Piece

[0034] 8. Seat 9. First support piece

[0035] 10. Second support piece

[0036] 1 1. Shaft

[0037] 12. Bracket

[0038] 13. Pin

[0039] 14. First Spring

[0040] 15. Second Spring

[0041] 16. Rod

[0042] 17. Actuator

[0043] 18. Airbag

[0044] 19. Trigger

[0045] 20. Gas Source

[0046] (I) First Position

[0047] (II) Second Position

[0048] The impact damping mechanism (1 ) comprises a body (2) which is the aircraft, at least one airbag assembly (3) that is located on the body (2) and protects the pilot and / or the passenger, at least one sensor (4) that detects the active or inactive status of the airbag assembly (3), and at least one activation apparatus (5) that is located on the body (2) and enables the airbag assembly (3) to operate when triggered by the user.

[0049] The impact damping mechanism (1 ) which is the subject of the invention comprises at least one crank (6) which is rotatable around its own axis, at least one connection piece (7) which moves freely rotatably from the end where it is connected to the crank (6) by rotating the crank (6), a connection piece (7) having a first position (I) which contacts the sensor (4) and thus ensures that the airbag assembly (3) is inactive, and a connection piece (7) having a second position (II) which is placed in a distance between the sensor (4) and the airbag assembly (3) when the activation apparatus (5) is triggered by the user and thus ensures that the airbag assembly (3) is active.

[0050] There is at least one airbag assembly (3) as a safety measure on the body of an aircraft (2). This assembly is designed to protect the pilot or the passenger in the event of a possible danger. At least one sensor (4) is used to detect and monitor the operating status of the airbag assembly (3). This sensor (4) continuously monitors whether the airbag assembly (3) is active or inactive. In order to ensure the safety of the user, there is at least one activation device (5) placed on the body (2). This activation device (5) initiates the operation of the airbag assembly (3) when triggered by the user. This triggering ensures that the airbag is quickly activated in a moment of danger or emergency. (Figure - 1 , Figure - 2, Figure - 3)

[0051] At least one crank (6) that can rotate around its own axis can be rotated by the user and there is at least one connection piece (7) that can move freely at its end connected to the crank (6). The connection piece (7) is in contact with the sensor (4). When the connection piece (7) is in the first position (I), it is in constant contact with the sensor (4) and keeps the airbag assembly (3) inactive. When the activation device (5) is triggered by the user, the connection piece (7) moves to the second position (II). In the second position (II), the connection piece (7) is positioned so that there is a distance between it and the sensor (4), thus allowing the airbag assembly (3) to be activated. When the user triggers the activation device (5), the connection piece (7) breaks contact with the sensor (4) and activates the airbag assembly (3). In the first position

[0052] (I), the end of the connection piece (7) that is not connected to the crank (6) contacts the sensor (4). (Figure - 4, Figure - 5, Figure - 6, Figure - 7, Figure - 8)

[0053] In one embodiment of the invention, the impact damping mechanism (1 ) comprises at least one seat (8) where the passenger and / or pilot sits inside the body (2), and an airbag assembly (3) located in the second position (II) in a manner that almost completely fills between the seat (8) and the floor of the body (2). In the second position

[0054] (II), there is an airbag assembly (3) located in a manner that almost completely fills between the seats (8) and the floor of the body (2). The airbag assembly (3) that is located between the seats (8) and the floor of the body (2) fills the space inside the aircraft. The airbag assembly (3) is designed to ensure the safety of the passenger or the pilot in the event of a potential crash. When a crash is detected or the airbag assembly (3) is activated, the airbag assembly (3) rapidly inflates and fills the space between the seats (8) and the floor of the body (2), thus helping to protect the passenger or the pilot from impact effects.

[0055] In one embodiment of the invention, the impact damping mechanism (1 ) comprises a first support piece (9) that enables the seat (8) to be mounted on the floor of the body (2), and a second support piece (10) that is located on the seat (8) and moves telescopically within the first support piece (9). In the second position (II), the second support piece (10) is movably located within the first support piece (9). In this way, the force applied to the seat (8) is reduced by the activation of the airbag assembly (3).

[0056] In one embodiment of the invention, the impact damping mechanism (1 ) comprises at least one shaft (1 1 ) that is located between the connection piece (7) and the first support piece (9) and is connected to the connection piece (7) at one end and to the first support piece (9) at the other end, and at least one bracket (12) that is connected to the first support piece (9) and enables the shaft (11 ) to move linearly within the channel by means of the channel located on it. In the second position (II), with the movement of the connection piece (7), the shaft (1 1 ) moves on the channel located on the bracket (12). In this way, it enables the airbag assembly (3) to be activated. The bracket (12) enables the seat (8) to be positioned on the floor of the body (2).

[0057] In one embodiment of the invention, the impact damping mechanism (1 ) comprises at least one pin (13) that is located on the first support piece (9), contacts the connection piece (7) and enables the first support piece (9) and the second support piece (10) to interlock in the second position (II). The pin (13) is located between the first support piece (9) and the second support piece (10) which are located opposite each other. The pin (13) contacts the sensor (4) at least at one end. In the first position (I), the shaft (1 1 ) prevents the pin (13) from moving towards the channel. In this way, in the first position (I), the pin (13) is constantly in contact with the sensor (4). In the second position (II), the end of the connection piece (7) connected to the shaft (1 1 ) moves linearly within the channel, allowing the pin (13) to move towards the channel. However, in the second position (II), the pin (13) restricts the movement of the second support piece (10) within the first support piece (9).

[0058] In an embodiment of the invention, the impact damping mechanism (1 ) comprises at least one preloaded first spring (14) that is located on the first support piece (9) and the second support piece (10), almost completely prevents the pilot or the passenger from being harmed during the impact, and almost completely restricts the movement of the second support piece (10) within the first support piece (9) by almost completely broken the contact of the pin (13) with the first support piece (9) and the second support piece (10) when the connection piece (7) is in the second position (II). The first spring (14) at least partially dampens the force affecting the bottom of the seat (8) when the airbag assembly (3) is active in the second position (II). The upward movement of the seat (8) is dampened by the sudden activation of the airbag assembly (3).

[0059] In one embodiment of the invention, the impact damping mechanism (1 ) comprises the first support piece (9) and the second support piece (10) located opposite each other, at least one second spring (15) that is located on the pin (13) so as to extend along the length between the first support piece (9) and the second support piece (10) and ensures that the pin (13) is positioned between the first support piece (9) and the second support piece (10) when in the first position (I) The second spring (15) keeps the pin (13) between the first support piece (9) and the second support piece (10) so that the airbag assembly (3) is not active in the first position (I) and ensures that the pin (13) contacts the sensor (4).

[0060] In one embodiment of the invention, the impact damping mechanism (1 ) comprises a connection piece (7), one end of which is connected to the crank (6) and the other end to the shaft (1 1 ), and which is moved by the linear movement of the shaft (1 1 ) in the channel located on the bracket (12) when in the second position (II). While the end of the connection piece (7) connected to the shaft (1 1 ) moves in the channel, the end connected to the crank (6) moves together with the crank (6).

[0061] In one embodiment of the invention, the impact damping mechanism (1 ) comprises an activation apparatus (5), which is an arm that allows the crank (6) to rotate around its own axis when the pilot or passenger pushes it towards the floor of the body (2), and at least one rod (16), one end of which is connected to the centre of the crank (6) and the other end to the activation apparatus (5), and which moves around the centre of the crank (6) from where it is connected to the crank (6) to approach the floor of the body (2) when the activation apparatus (5) is triggered, and rotates the crank (6). The end of the rod (16) connected to the activation apparatus (5) moves in a way that it approaches the body (2) floor. When the activation apparatus (5) is triggered by the user, the rod (16) rotates the crank (6) from the end where it is connected to the crank (6). In this way, the end of the connection piece (7) connected to the shaft (1 1 ) slides linearly in the channel and ensures that the contact of the pin (13) with the sensor (4) is broken. The airbag assembly (3) is activated when the sensor (4) contact is broken. In an embodiment of the invention, the impact damping mechanism (1 ) comprises the activation apparatus (5), which is the flight control button, at least one actuator (17) that is located on the crank (6) and triggers the crank (6) to rotate around its own axis when the connection piece (7) is in the second position (II) when the activation apparatus (5) is triggered by the user. By the user triggering the activation apparatus (5), the actuator (17) connected to the crank (6) is made to rotate the crank (6) around its own axis.

[0062] In one embodiment of the invention, the impact damping mechanism (1 ) comprises at least one airbag (18) that is located inside the body (2) and is designed to protect the pilot and / or passenger, at least one trigger (19) that triggers the detonation of the airbag (18) according to the data received from the sensor (4), and a pressurized gas source (20) that inflates the airbag (18) quickly and effectively by means of the trigger (19). There is an airbag (18) that is located on the floor of the body (2), in the part where the pilot and / or passenger sits, and is opened by the gas source (20) when the crash is detected by the sensor (4) and opened by means of the trigger in a way that almost completely fills the space between the seat (8) and the floor of the body (2).

Claims

CLAIMS1. An impact damping mechanism (1 ) comprising a body (2) that is an aircraft, at least one airbag assembly (3) that is located on the body (2) and protects the pilot and / or the passenger, at least one sensor (4) that detects the active or inactive status of the airbag assembly (3), and at least one activation apparatus (5) that is located on the body (2) and enables the airbag assembly (3) to operate when triggered by the user, characterised by at least one crank (6) which is rotatable around its own axis, at least one connection piece (7) that moves freely from the end to which it is connected to the crank (6) by rotating the crank (6), the connection piece (7) that has a first position (I) which makes contact with the sensor (4) and thus inactivates the airbag device (3), and the connection piece (7) that has a second position (II) which is positioned at a distance from the sensor (4) when the activation device (5) is triggered by the user, thus enabling the airbag assembly (3) to be activated.

2. An impact damping mechanism (1 ) according to Claim 1 , characterised by at least one seat (8) where the passenger and / or pilot sits inside the body (2), and an airbag assembly (3) located in the second position (II) in a manner that almost completely fills between the seat (8) and the floor of the body (2).

3. An impact damping mechanism (1 ) according to Claim 1 or 2, characterised by a first support piece (9) that allows the seat (8) to be mounted on the floor of the body (2), and a second support piece (10) that moves telescopically within the first support piece (9) located on the seat (8).

4. An impact damping mechanism (1 ) according to Claim 3, characterised by at least one shaft (1 1 ) that is located between the connection piece (7) and the first support piece (9) and is connected to the connection piece (7) at one end and to the first support piece (9) at the other end, and at least one bracket (12) that is connected to the first support piece (9) and enables the shaft (1 1 ) to move linearly within the channel by means of the channel located on it.

5. An impact damping mechanism (1 ) according to Claim 3 or 4, characterised by at least one pin (13) that is located on the first support piece (9), contacts the connection piece (7) and enables the first support piece (9) and the second support piece (10) to interlock in the second position (II).

6. An impact damping mechanism (1 ) according to Claim 5, characterised by at least one preloaded first spring (14) that is located on the first support piece (9) and the second support piece (10), almost completely prevents the pilot or the passenger from being harmed during the impact, and almost completely restricts the movement of the second support piece (10) within the first support piece (9) by almost completely broken the contact of the pin (13) with the first support piece (9) and the second support piece (10) when the connection piece (7) is in the second position (II).

7. An impact damping mechanism (1 ) according to Claim 5 or 6, characterised by the first support piece (9) and the second support piece (10) located opposite each other, at least one second spring (15) that is located on the pin (13) so as to extend along the length between the first support piece (9) and the second support piece (10) and ensures that the pin (13) is positioned between the first support piece (9) and the second support piece (10) when in the first position (!)■8. An impact damping mechanism (1 ) according to Claims 4 to 7, characterised by the connection piece (7), one end of which is connected to the crank (6) and the other end to the shaft (1 1 ), and which is moved by the linear movement of the shaft (1 1 ) in the channel located on the bracket (12) when in the second position (II).

9. An impact damping mechanism (1 ) according to any of the previous claims, characterised by an activation apparatus (5), which is an arm that allows the crank (6) to rotate around its own axis when the pilot or passenger pushes it towards the floor of the body (2), and at least one rod (16), one end of which is connected to the centre of the crank (6) and the other end to the activationapparatus (5), and which moves around the centre of the crank (6) from where it is connected to the crank (6) to approach the floor of the body (2) when the activation apparatus (5) is triggered, and rotates the crank (6).

10. An impact damping mechanism (1) according to Claims 1 to 7, characterised by the activation apparatus (5), which is the flight control button, at least one actuator (17) that is located on the crank (6) and triggers the crank (6) to rotate around its own axis when the connection piece (7) is in the second position (II) when the activation apparatus (5) is triggered by the user.

11. An impact damping mechanism (1 ) according to any of the previous claims, characterised by at least one airbag (18) that is located inside the body (2) and is designed to protect the pilot and / or passenger, at least one trigger (19) that triggers the detonation of the airbag (18) according to the data received from the sensor (4), and a pressurized gas source (20) that inflates the airbag (18) quickly and effectively by means of the trigger (19).

Images