GB2624297A

GB2624297A - A lock mechanism

Info

Publication number: GB2624297A
Application number: GB2314545.1A
Authority: GB
Inventors: Hakan Bozkurt Ahmet; Akcay Ali
Original assignee: Tusas Turk Havacilik Ve Uzay Sanayii AS
Current assignee: Tusas Turk Havacilik Ve Uzay Sanayii AS
Priority date: 2022-09-29
Filing date: 2023-09-22
Publication date: 2024-05-15
Also published as: GB202314545D0

Abstract

A hydraulic or pneumatic lock mechanism 1 for an aircraft or a spacecraft, for example for locking a canopy or cockpit closure, comprises a pin 5 movable in a chamber 8 between a retracted position and an extended position. The chamber is mounted to a body 2 of the aircraft and in the extended position the pin is received in a slot 4 associated with the canopy 3. The chamber is connected to a fluid storage tank 6 via a transmission line 7. A resilient member, for example a spring, is arranged between the chamber and the pin so as to absorb force exerted on the pin by the fluid, the resilient member biases the pin into the retracted position. There may be a plurality of locks arranged on the transmission line which are simultaneously operated. Each lock may have a resilient member having a different flexibility, or each pin may have a different cross section, or the transmission line may have a decreasing cross section in the direction of fluid coming from the tank.

Description

DESCRIPTION

A LOCK MECHANISM

This invention relates to a lock mechanism suitable for use in air and/or space vehicles.

Mechanical locks are mostly preferred in lock systems. The reliability of mechanical systems is high, but the use of such systems poses difficulties in aircraft systems in which volume and weight restrictions are quite high. Since they occupy a lot of space volumetrically, their maintenance or replacement of parts in case of failure are very difficult and they also pose difficulties in accessing many points of the system. For this reason, the use of lock mechanisms used in air and/or space vehicles is important and there is a need to develop a lightweight and effective lock system suitable for aviation structures.

The United States patent application document U520130269256A1, which is included in the known state of the art, describes a lock mechanism of a cockpit door on aircraft. A cockpit door is rotatably attached to a door frame with the help of conventional door hinges. The door frame is represented by a right and a left door trim. There are three pneumatically operable latches. These latches are configured in their deactivated position in a retracted position in which the end faces of the latches are aligned with the outer faces of the door trim. The bolts are preferably depressed by the return devices in the retracted position. The return devices are realized by springs, permanent magnets or similar devices. The latches are further configured to be moved to an extended position when supplied with pressurized air. In this position, the latches merge with the receiving holes, which are the edge of the corresponding cockpit door facing the left door trim. The cockpit door is closed to lock the cockpit door. If the latches are not supplied with pressurized air or if the air pressure drops below a certain value, the latches are retracted to their retracted deactivated position by the return devices to unlock the cockpit door.

The People's Republic of China patent application document CN109383815A, which is included in the known state of the art, mentions on a pneumatic system for unlocking an emergency airbag in an aircraft cabin. An open air supply pipe for a gas-operated lock and an airbag air supply pipe for the airbag are connected to a pressurized air supply unit. The pressurized air supply unit is switched on. A high-pressure gas enters the cylinder body from the locked air supply pipe through an air inlet. It tightens a ball and the ball rolls into a groove. The ball releases the restriction to compress a compact stack. The compact stack and rigid cover are released, releasing the pneumatic lock.

With a lock mechanism developed by the present invention, an effective locking is provided for ergonomic, practical and long locking lines.

An object of the present invention is to provide a lightweight lock system for air vehicles. Its lightweight and practical structure not only makes it easier for the user to use, but also positively affects the flight performance as it will reduce the weight.

The lock mechanism realized to achieve the object of the invention, as defined in the first claim and in the claims dependent thereon, comprises a body to be located in an air and/or space vehicle such as aircraft, helicopters, unmanned aerial vehicles, and spacecraft. A cover located on the body can be opened and closed to provide access into the body. At least one slot is located on the cover. At least one pin is located on the body opposite to the slot, enabling the cover to be fixed to the body by being at least partially inserted into the slot. A tank is provided in which a pressurized fluid is stored, which is configured in such a way that it does not freeze or change state at high altitude conditions so that it can maintain its functionality in any case. At least one transmission line, one end of which is connected to the tank and through which the fluid passes, is located on the body. At least one chamber is located on the transmission line such that the pin moves linearly within the chamber by fully contacting the lateral walls of the chamber so as not leave a gap. When the fluid enters the chamber, a locked position (L) is assumed by the cover, in which the pin moves towards the slot and enters the slot, and when the fluid is discharged from the chamber, an open position (0) is assumed by the cover, in which the pin moves away from the slot in the opposite direction and comes out of the slot. A triggering device provides the movement of the fluid for the movement of the cover between the open position (0) and the locked position (L).

The lock mechanism of the invention comprises at least one apparatus, having at least one end connected to the chamber and the other end to the pin. The apparatus elongates towards the slot while the cover is brought to the locked position (L) and thus partially dampens the force exerted by the fluid on the pin, thereby preventing the pin from entering the slot unevenly and harshly. On the other hand, the apparatus shortens in the opposite direction to the slot by gradually becoming free, that is, gradually assuming its former position on which no force was exerted, as a result of a decrease in the force exerted by the fluid on the pin while the cover is brought to the open position (0), thus reducing the tensile force on the apparatus by the pin. When the cover is in the locked position (L), the tensile force exerted by the pin on the apparatus is almost equal to the tensile force exerted by the apparatus on the pin when the cover is in the open position (0).

In an embodiment of the present invention, the lock mechanism comprises a transmission line on which multiple chambers are located successively one after the other with distances in between them. When the trigger is activated to bring the cover to the locked position (L), there is a first pin that the fluid coming from the tank first contacts and a second pin that it contacts secondly along the transmission line. The apparatus connected to the first pin has less flexibility than the apparatus connected to the second pin. Based on the formula F=kx, the increase in the flexibility of the apparatus connected to the pins as they move away from the tank on the transmission line also increases the distance that each pin will travel. For this reason, the size of the slots against each pin is directly proportional to the distance the pins will travel. If the slot sizes are the same, it is enabled that the pin closest to the tank is placed into the slot and also the pin furthest from the tank is placed into the slot without damaging the slot. In order to make the flexibility properties different, the cross-sectional areas of the apparatus can be changed or the apparatus can be made from different materials.

Thus, it is enabled that each pin enters the slot against it almost simultaneously. In the event that a manufacturer-determined number of chambers, pins and apparatus are placed on the transmission line, the relationship between the apparatus connected to the first pin and the apparatus connected to the second pin also applies to each successively located pin and the apparatus connected to those pins.

In an embodiment of the invention, the lock mechanism comprises a chamber in which the first pin is located and which has a volume greater than the volume of the chamber in which the second pin is located. The cross-sectional area of the surface of the second pin in fluid contact is less than the cross-sectional area of the surface of the first pin making fluid contact. The amount of decrease in the volumes of the chambers as they move away from the tank on the transmission line is equal to the amount of decrease in the pin cross-sectional areas in fluid contact. Each pin fully contacts the lateral walls of the chamber in which it is located. Also in the event that a manufacturer-determined number of pins and chambers are placed on the transmission lines of a manufacturer-determined length, the relationship between the first pin, the second pin and the chambers in which they are located also applies to each successively placed pin and chamber. Thus, it is enabled that each pin enters the slot against it almost simultaneously.

In an embodiment of the invention, the lock mechanism comprises a transmission line whose cross-sectional area decreases and narrows in the direction of movement of the fluid (F) coming from the tank along the transmission line when the triggering device is activated to bring the cover to the locked position (L). The amount of narrowing throughout the transmission line is sufficient to enable each pin to enter into the slots almost simultaneously. Since the transmission line will extend from the tank in a narrowing manner, the fluid fills a chamber in a position in which the transmission line has a narrower cross-sectional area faster than it fills a chamber in a position in which the transmission line has a wider cross-sectional area. Thus, it is enabled that each pin enters the slot against it almost simultaneously.

In an embodiment of the invention, the lock mechanism comprises at least one channel located on the pin. At least one stopper extending over the chamber towards the interior of the channel contacts the bottom of the channel when the cover is in the locked position (L) and prevents the pin from coming out of the chamber completely. Since the channel will move so that it remains inside the stopper while the pin is moving, when the cover is in the lock position (L), the stopper is in a position to hit the lower wall of the channel and prevents the pin from coming out of the chamber completely.

In an embodiment of the present invention, the lock mechanism comprises a triggering device triggered by a user by means of a latch or by a control unit by means of electrical transmission. The triggering device located in the body enables the fluid to move along the transmission line.

In an embodiment of the present invention, the lock mechanism comprises at least one actuator coupled to the triggering device. The actuator is located at least partially in the tank in a movable and form-fitting manner with the tank. The actuator enables the fluid to enter the transmission line by moving towards the transmission line so that its volume in the tank increases and it stays in the tank with the activation of the triggering device.

In an embodiment of the invention, the lock mechanism comprises a moment arm located between the triggering device and the actuator. The moment arm enables the actuator to be triggered by transferring the force applied by the user to the triggering device to the actuator.

In an embodiment of the present invention, the lock mechanism comprises chambers among which the successive ones are equally spaced along the transmission line. Thus, when the cover is in the locked position (L), the load to be created on the pins is distributed evenly over the pins. Thus, the deformation of the pins is prevented and the safety of the user is increased. Conditions in which the pins may break with an opening cover during flight are prevented.

In an embodiment of the invention, the lock mechanism comprises a cover that is a canopy that protects the cockpit, in which the user is located and provides the controls of the air and/or space vehicle, from noise or external influences such as meteorological effects. The cover may also be a cockpit door in air and/or space vehicles.

In an embodiment of the invention, the lock mechanism comprises an apparatus which is a spring. The apparatus can be any flexible material that stretches like rubber and restores to its original position, thus acting as a spring.

In an embodiment of the invention, the lock mechanism comprises a fluid which is a gas and/or a liquid. The lock mechanism can be a pneumatic or hydraulic locking system.

The lock mechanism realized to achieve the object of the present invention is shown in the accompanying figures, among which: Figure 1 -is a side view of a cover's open position (0). Figure 2 -is a side view of a cover's locked position (L).

Figure 3 -is a perspective view of the lock mechanism when a cover is in the open position (0).

Figure 4 -is a perspective view of the lock mechanism when a cover is in the locked position (L).

Figure 5 -is a sectional view of the apparatus, channel and stopper when a cover is in the open position (0).

Figure 6 -is a sectional view of the apparatus, channel and stopper when a cover is in the locked position (L).

The parts in the figures are individually given reference signs as following.

1. Lock mechanism 2. Body 3. Cover 4. Slot 5. Pin 501. First pin 502. Second pin 6 Tank 7. Transmission line 8. Chamber 9. Triggering device Apparatus 11 Channel 12 Stopper 13 Actuator 14. Moment arm (F) Fluid (0) Open Position (L) Locked Position The lock mechanism (1) comprises a body (2) which is located on an air and/or space vehicle, at least one cover (3) which is located on the body (2) and can be opened and closed to provide access into the body (2), at least one slot (4) located on the cover (3), at least one pin (5) which is located on the body (2) opposite to the slot (4) and is at least partially placed in the slot (4), thereby enabling the cover (3) to be fixed to the body (2), a tank (6) in which a fluid (F) is stored, at least one transmission line (7) which is located on the body (2) and one end of which is connected to the tank (6) so that the fluid (F) is passed therethrough, at least one chamber (8) which is located on the transmission line (7) and in which the pin (5) is movably located therein, a locked position (L) which is assumed by the cover (3) once the fluid (F) enters into the chamber (8) so that the pin (5) is moved towards the slot (4) to be inserted at least partially in the slot (4), an open position (0) which is assumed by the cover (3) once the fluid (F) is at least partially discharged from the chamber (8) so that the pin (5) is moved towards the surface of the chamber (8) that is connected to the transmission line (7) and is entirely removed from the slot (4), a triggering device (9) enabling the fluid (F) to be moved to bring the cover (3) from the open position (0) to the locked position (L) or from the locked position (L) to the open position (0). (Figure -1, Figure -2) The lock mechanism (1) according to the invention comprises at least one apparatus (10), at least one end of which is connected to the chamber (8) and the other end to the pin (5), which elongates towards the slot (4) by becoming stretched while the cover (3) is brought to the locked position (L), thus partially absorbing the force exerted by the fluid (F) on the pin (5), and which becomes free while the cover (3) is brought to the open position (0) and shortens towards the surface of the chamber (8) that is connected to the transmission line (7), thereby enabling the pin (5) to be entirely removed from the slot (4). (Figure -5, Figure -6) At least one cover (3) is provided, which is located on a body (2) of an air and/or space vehicle and can be opened and closed to provide access to the interior or into the body (2) of the air and/or space vehicle. At least one slot (4) is located on the cover (3). At least one pin (5) is located on the body (2) opposite to the slot (4) and enables the cover (3) to be fixed to the body (2) by being at least partially placed/inserted into the slot (4). A tank (6) is provided in which a pressurized fluid (F) is stored. Preferably, at least one transmission line (7) is located on the body (2), one end thereof being connected to the tank (6) so that the fluid (F) is passed therethrough. At least one chamber (8) is located on the transmission line (7) so that fluid (F) transfer can be made between the transmission line (7) and the chamber (8). The fluid (F) enters the chamber (8), making the pin (5) move towards the slot (4), upon which the pin (5) enters at least partially into the slot (4) and brings the cover (3) to a locked position (L). The fluid (F) goes through the chamber (8) via the transmission line (7) to the tank (6) so that the pin (5) moves towards the surface of the chamber (8) that is connected to the transmission line (7), and comes out of the slot (4), enabling the cover (3) to assume an open position (0). A user-triggered triggering device (9) provides the movement of the fluid (F) to bring the cover (3) from the open position (0) to the locked position (L) or from the locked position (L) to the open position (0). (Figure -3, Figure -4) At least one apparatus (10) is provided between the pin (5) and the chamber (8) in connection to the pin (5) and the chamber (8). When the triggering device (9) is active to bring the cover (3) to the locked position (L), the fluid (F) from the tank (6) fills the chamber (8) and applies pressure to the pin (5), enabling the pin (5) to enter into the slot (4). The apparatus (10) dampens some of the pressure exerted by the fluid (F) on the pin (5), enabling the pin (5) to enter into the slot (4) more evenly. When the triggering device (9) is active to bring the cover (3) to the open position (0), the fluid (F) moves from the chamber (8) to the transmission line (7) and then to the tank (6). Since the pressure exerted by the fluid (F) on the pin (5) will decrease, the tensile force exerted by the pin (5) on the apparatus (10) also decreases, and the apparatus (10) retracts the pin (5) to its former position so that it is removed from the slot (4).

In an embodiment of the invention, the lock mechanism (1) comprises a transmission line (7) on which multiple chambers (8) are located successively one after the other, a first pin (501) that the fluid (F) coming from the tank (6) contacts firstly and a second pin (502) it contacts secondly along the transmission line (7) once the triggering device (9) is being activated to bring the cover (3) to the locked position (L), an apparatus (10) which is connected to the first pin (502) and has less flexibility than the apparatus (10) connected to the second pin (501) for the pins (5) to be entered into the slots (4) almost simultaneously. Thus, the pins (5) are enabled to enter into the respective slots (4) located against them almost simultaneously.

In an embodiment of the invention, the lock mechanism (1) comprises a chamber (8) in which the second pin (502) is located and which has a lower volume than the chamber (8) in which the first pin (501) is located, and in compliance with the chamber (8), a second pin (502) having a surface cross-sectional area with a lower fluid (F) contact than the surface cross-sectional area of the first pin (501), in order for the pins (5) to be entered into the slots (4) almost simultaneously. Thus, the pins (5) are enabled to enter into the respective slots (4) located against them almost simultaneously.

In an embodiment of the invention, the lock mechanism (1) comprises a transmission line (7) whose cross-sectional area decreases in the direction of movement of the fluid (F) coming from the tank (6) along the transmission line (7) once the triggering device (9) is activated to bring the cover (3) to the locked position (L). Thus, the pins (5) are enabled to enter into the respective slots (4) located against them almost simultaneously.

In an embodiment of the invention, the lock mechanism (1) comprises at least one channel (11) located on the pin (5), at least one stopper (12) extending over the chamber (8) towards the interior of the channel (11) and preventing the pin (5) from coming out of the chamber (8) completely by contacting the bottom of the channel (11) when the cover (3) is in the locked position (L). Thus, it is prevented that the fluid (F) in the chamber (8) comes out of the chamber (8) and the pin (5) is completely removed from the slot (4), thereby preventing the lock from being unlocked during a flight while the cover (3) is in the locked position (L).

In an embodiment of the invention, the lock mechanism (1) comprises a triggering device (9) which is a latch located in the body (2), is triggered by a user or via electrical transmission, thereby enabling the fluid (F) to move along the transmission line (7). Thus, the cover (3) can move between the open position (0) and the locked position (L).

In an embodiment of the invention, the lock mechanism (1) comprises at least one actuator (13) connected to the triggering device (9), movably located in the tank (6) and enabling the fluid (F) in the tank (6) to enter into the transmission line (7) when the triggering device (9) is active. Thus, the fluid (F) in the tank (6) is transferred between the transmission line (7) and the tank (6) without leaking out of the tank (6).

In an embodiment of the invention, the lock mechanism (1) comprises a moment arm (14), of which one end is connected to the triggering device (9) and the other end to the actuator (13), and once a force is exerted on the triggering device (9), which actively transfers the force exerted on the triggering device (9) to the actuator (13). Thus, the force exerted on the triggering device (9) is transferred to the actuator (13) without any loss.

In an embodiment of the invention, the lock mechanism (1) comprises chambers (8) among which the successive ones are equally spaced along the transmission line (7) so that the load to be created by the cover (3) on the body (2) is evenly distributed.

Thus, hazards are prevented by which the pins (5) are deformed and thus the pins (5) break off during a flight such that the lock is unlocked.

In an embodiment of the present invention, the lock mechanism (1) comprises a cover (3) which is a canopy that provides access and protection to the cockpit. Thus, the cockpit is reliably protected from external influences.

In an embodiment of the present invention, the lock mechanism (1) comprises an apparatus (10) which is a spring.

In an embodiment of the invention, the lock mechanism (1) comprises a fluid (F) which is a gas and/or a liquid.

Claims

CLAIMS1 A lock mechanism comprising a body which is located on an air and/or space vehicle, at least one cover which is located on the body and can be opened and closed to provide access into the body, at least one slot located on the cover, at least one pin which is located on the body opposite to the slot and is at least partially placed in the slot, thereby enabling the cover to be fixed to the body, a tank in which a fluid is stored, at least one transmission line which is located on the body and one end of which is connected to the tank so that the fluid is passed therethrough, at least one chamber which is located on the transmission line and in which the pin is movably located therein, a locked position which is assumed by the cover once the fluid enters into the chamber so that the pin is moved towards the slot to be inserted at least partially in the slot, an open position which is assumed by the cover once the fluid is at least partially discharged from the chamber so that the pin is moved towards the surface of the chamber that is connected to the transmission line and is entirely removed from the slot, a triggering device enabling the fluid to be moved to bring the cover from the open position to the locked position or from the locked position to the open position, characterized by at least one apparatus, at least one end of which is connected to the chamber and the other end to the pin, which elongates towards the slot by becoming stretched while the cover is brought to the locked position, thus partially absorbing the force exerted by the fluid on the pin, and which becomes free while the cover is brought to the open position and shortens towards the surface of the chamber that is connected to the transmission line, thereby enabling the pin to be entirely removed from the slot.
2 Lock mechanism according to claim 1, characterized by multiple chambers being located successively one after the other on the transmission line, a first pin being contacted firstly and a second pin being contacted secondly by the fluid coming from the tank along the transmission line once the triggering device is being activated to bring the cover to the locked position, and the apparatus connected to the first pin having less flexibility than the apparatus connected to the second pin for the pins to be entered into the slots almost simultaneously.
3 Lock mechanism according to claim 2, characterized by the chamber in which the second pin is located having a lower volume than the chamber in which the first pin is located, and in compliance with the chamber, the second pin having a surface cross-sectional area with a lower fluid contact than the surface cross-sectional area of the first pin, in order for the pins to be entered into the slots almost simultaneously.
4 Lock mechanism according to claim 1, characterized by the transmission line having a cross-sectional area decreasing in the direction of movement of the fluid coming from the tank along the transmission line once the triggering device is activated to bring the cover to the locked position.
Lock mechanism according to any of the above claims, characterized by at least one channel being located on the pin, at least one stopper extending over the chamber towards the interior of the channel and preventing the pin from coming out of the chamber completely by contacting the bottom of the channel when the cover is in the locked position.
Lock mechanism according to any of the above claims, characterized by the triggering device being a latch that is located in the body, being triggered by a user or via electrical transmission, thereby enabling the fluid to move along the transmission line.
Lock mechanism according to any of the above claims, characterized by at least one actuator being connected to the triggering device, movably located in the tank and enabling the fluid in the tank to enter into the transmission line when the triggering device is active.
Lock mechanism according to claim 7, characterized by a moment arm, one end thereof being connected to the triggering device and the other end thereof to the actuator, and once a force is exerted on the triggering device, actively transferring the force exerted on the triggering device to the actuator.
Lock mechanism according to claim 7, characterized by the successive chambers being equally spaced along the transmission line such that the load to be created by the cover on the body is evenly distributed.
10. Lock mechanism according to any of the above claims, characterized by the cover being a canopy providing access and protection to the cockpit.
11. Lock mechanism according to any of the above claims, characterized by the apparatus being a spring.
12. Lock mechanism according to any of the above claims, characterized by the fluid being a gas and/or a liquid. 9