Cankaya Patent Marka ve Danismanlik Ltd. Sti.

This invention relates to a body (2) in an aircraft, a cockpit (3) in the form of a cabin on the body (2), in which the pilot is located, a panel (4) located in the cockpit (3), on which the avionic devices are positioned and which is accessible to the pilot, a plurality of beams (301) forming the side walls of the cockpit (3), arranged longitudinally opposite each other so that the cockpit (3) is located between them, at least one damper (5) located in the cockpit (3), damping the loads on the panel (4) in the cockpit (3).

This invention, relates to a body (2), a door (3) on the body (2), which allows the user access to the body (2) or prevents access to the body (2), at least one hinge (4) on the door (3), allowing the door (3) to be supported on the body (2) and allowing the door (3) to be opened by pivoting around the axis on which it is supported on the body (2), at least one trigger (5) to trigger the door (3), a first hinge channel (6) located on the hinge (4) and having a through opening, at least one hinge pin (7) located on the hinge (4) and extending along its length, a closed position (I) in which the door (3) encloses the body (2) in a form-fitting manner, the door (3) being closed on the body (2), an open position (II) in which the hinge pin (7) contacts the first hinge channel (6) within the first hinge channel (6), the door (3) being moved outwardly from the body (2) by means of rotation of the hinge (4) from the closed position (I) to allow the user to access the body (2), an emergency trigger position (III) in which the hinge pin (7) protrudes from the first hinge channel (6) and there is a distance between the first hinge channel (6) and the hinge pin (7), in which the trigger (5) is triggered in the event that the user needs to be evacuated from the body (2), an evacuation position (IV) in which the door (3) is brought from the emergency trigger position (III) so that the hinge (4) and the body (2) move independently of each other, and the door (3) and hinge (4) are pushed out of the body (2), allowing the user to evacuate from the body (2), at least one latch (8) located on the door (3), which allows the door (3) to be locked, at least one latch holder (9) located on the body (2), which enables the door (3) to be locked in the closed position (I) by being placed in the latch (8), and which enables the door (3) to be opened in the open position (II) when it is brought out of the latch (8) so as to keep a distance between it and the latch (8).

The invention relates to at least one load (2) carried on the aircraft (F), at least one carrying apparatus (3) attached to the aircraft (F) in a detachable manner enabling the load (2) to be carried on the aircraft (F), at least one body (4) located on the aircraft (F) and enabling the positioning of the carrying apparatus (3) on the aircraft (F), multiple holes (5) located on the body (4) and enabling equipment to be mounted on the body (4) by the user, at least one main pin (6) inserted into the hole (5) in a rotatable manner by the user and enabling the carrying of the carrying apparatus (3) by means of the body (4), at least one holder (7) located on the body (4) in a manner to be rotatable around the point where it is mounted and attached to the carrying apparatus (3) in a detachable manner, and a first state (I) in which the main pin (6) contacts the holder (7) from one end on the body (4), preventing the rotation of the holder (7) and enabling the carrying of the load (2) on the aircraft (F).

The present invention relates to a body (G), at least one rotary part (2) arranged on the body (G) and rotatably connected relative to the body (G), at least one bracket (S) located on the body (G), at least one support rod (3) pivotably connected to the bracket (S), at least one actuator (4) connected to the rotary part (2), which is a trigger exerting a force along the direction along which it extends, and which causes the rotary part (2) to rotate, at least one reaction rod (5) which is a structural part connected at one end to the rotary part (2) and at the other end to the support rod (3), at least one shaft (6) rotating with the rotary part (2) about the axis along which it extends, in order to rotate the rotary part (2), a first lever (7), which is a structural part extending outwardly from the shaft (6) and connected to the actuator (4), allowing the force of the actuator (4) to be transmitted to the shaft (6).

This invention, relates to a body (2), at least one control rod (3) located in the body (2) and moved by the user's triggering, at least one joint (4) located at one end of the control rod (3) and moving together with the control rod (3), at least one lever (5) on the body (2), which moves the joint (4) when triggered by the user, at least one main spring (6), one end of which is mounted on the joint (4) and the other end on the lever (5) and whose tension is adjusted by moving the lever (5) together with the lever (5) when the lever (5) is triggered and moved by the user, at least one adjustment mechanism (7) located on the body (2) and allowing the main spring (6) to be held at a tension set by the user, a first position (I) in which the main spring (6) is in a tension predetermined by the user, a second position (II) in which the main spring (6) is held in tension different from the amount of tension it has in the first position (I) by triggering the user's joint (4) and the weight of the control rod is balanced.

This invention relates to a body (2) in an aircraft, at least one engine (3) located on the body (2), generating the power required for the flight of the aircraft, an waste air (H) generated in the engine (3) due to the operation of the engine (3), at least one exhaust (4) located on the engine (3) and transferring the waste air (H) generated in the engine (3) outside the body (2), cold air (C) from the atmosphere, passing over the body (2) and contacting the exhaust (4) surface, at least one apparatus (5) that surrounds the exhaust (4) so as to be opposite to the outer surface of the exhaust (4) for the passage of cold air (C) in contact with the surface of the exhaust (4) and creates a cold air (C) corridor between the exhaust (4) and the exhaust (4) so that the heat generated on the surface of the exhaust (4) as a result of the waste air (H) generated by the engine (3) is removed by cold air (C), at least one opening (6) on the exhaust (4), allowing cold air (C) to enter through the exhaust (4) so that the cold air (C) mixes with the waste air (H), a flap (7) located on the exhaust (4) extending from the edge of the opening (6), allowing cold air (C) to pass through the apparatus (5) into the exhaust (4), a first position (I) in which the flap (7) is positioned to cover the opening (6), thereby preventing the passage of fluid.

The present invention comprises a body (2) forming the aerodynamic surface of the aircraft, at least one opening (3) disposed on the body (2) and providing access to the outside of the body (2), at least one hatch (4) movably disposed on the body (2) and making the opening (3) at least partially accessible, a first bracket (5) disposed on the body (2) and allowing connection of the hatch (4) with the body (2), at least one second bracket (6) on the hatch (4) for connecting the hatch (4) with the body (2), a first position (I) in which the hatch (4) is arranged so as to substantially completely cover the opening (3), a second position (II) in which the opening (3) is rotated away from the opening (3) by rotating the opening (3) so that the first bracket (5) is the center of rotation, and a pivoting member (7) located between the first bracket (5) and the second bracket (6) so as to allow the opening (3) to perform a pivoting movement.

The present invention comprises a body (G), a trigger (A) disposed on the body (G) which generates force and/or power, multiple output components (O) disposed on the body (G) to which the force and/or power generated by the trigger (A) is transferred, a trigger shaft (2) suitable for transferring the force and/or power generated by the trigger (A), an output shaft (3) suitable for transferring the force generated by the trigger (A) to the output component (O) by means of the trigger shaft (2), at least one rotary arm (4) which is a structural part for transferring force and/or power between the trigger shaft (2) and the output shaft (3), at least one guide (5) located on the body (G) and having a groove therein so as to allow the trigger shaft (2) to move freely in linear direction.

This invention relates to a body (2), at least one opening (A) located on the body (2), at least one structural part (3) disposed on the body (2), which is positioned on the body (2) to provide substantially complete closure of the opening (A), at least one mounting surface (201) on the body (2), forming the periphery of the opening (A), which allows the structural part (3) to be mounted on the body (2).

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