Outer throwing cover starting mechanism of cabin aircraft

Abstract

The invention belongs to the field of aviation, and relates to a cabin aircraft outer throwing cover starting mechanism. The device comprises a machine body opening cover, a cover throwing starting mechanism and a detonation firing mechanism. The cover throwing starting mechanism comprises an actuating pull rod, a limiting device, a steel cable winch, a fixed pulley, a steel cable, a cover throwing pull pin and a mounting support. In the process of throwing the cover outside the aircraft, the aircraft body opening cover is opened firstly, the steel cable which is bound and fixed to the actuating pull rod in advance is detached, then the steel cable is pulled, the actuating pull rod rotates to cut off the shear pin on the limiting device, then the throwing cover pull pin is driven to be pulled out, the detonation firing mechanism outputs a detonation detonation signal, and output of the throwing cover starting signal is completed.

Description

Technical Field

[0001] This invention belongs to the field of aviation and relates to a cockpit canopy ejection mechanism. Background Technology

[0002] When an aircraft is undergoing emergency rescue on the ground, in some situations, ground crew need to eject the canopy using external handling methods. Conventional canopy ejection devices have problems such as difficulty in starting and the risk of accidental injury to personnel during the activation process. Summary of the Invention

[0003] To address the aforementioned problems, this application provides a cockpit canopy ejection mechanism, comprising:

[0004] Fuselage hatch, hatch ejection mechanism and detonation firing mechanism;

[0005] The cover-throwing starting mechanism includes an actuating rod, a steel cable winch, a fixed pulley, a steel cable, a cover-throwing pin, and a mounting bracket.

[0006] The mounting bracket is fixed to the machine body structure. The steel cable winch and one end of the actuation rod are coaxially connected to the mounting bracket on the machine body. The actuation rod is mounted on a fixed pulley.

[0007] Part of the steel cable is wound in a steel cable winch, and part of it is detachably fixed to the end of the actuation rod after being wound around a fixed pulley. One end of the canopy ejection pin is connected to the actuation rod via a hinge, and the other end is inserted into the canopy ejection detonation firing device. Ground crew pulls the steel cable to pull the actuation rod to a preset angle, the canopy ejection pin is pulled out, the canopy ejection detonation firing device outputs a canopy ejection signal, triggering the canopy ejection.

[0008] Preferably, it also includes a limiting device hinged to the mounting bracket, which limits the rotation of the limiting device by a break-off pin. When the actuating pull rod moves to the break-off angle, the actuating pull rod contacts the limiting device and is limited. After the actuating pull rod is pulled further, the break-off pin breaks, and the limiting device rotates with the actuating pull rod.

[0009] Preferably, the breaking angle is less than the preset angle.

[0010] Preferably, it also includes a limiting device hinged to the mounting bracket. The limiting device restricts the rotation of the limiting device by a pull-off pin. When the actuating rod moves to a certain angle, the actuating rod contacts the limiting device and limits the movement. After the steel cable is pulled out to a preset extent, the cutting device on the steel cable contacts the pull-off pin and breaks the pull-off pin, and the limiting device rotates with the actuating rod.

[0011] Preferably, the fuselage cover (1) is located on the side wall of the fuselage, has a square opening, and the outer side of the cover is a wall panel, which is configured to be able to be quickly opened during ground emergency rescue.

[0012] Preferably, the throwing cover starting mechanism (2) is fixedly connected to the body structure inside the body cover (1) and is supported as a whole by the mounting bracket (10).

[0013] Preferably, the cable winch (6) is used for the automatic winding and unwinding of the cable (8).

[0014] Preferably, the actuating lever (4) makes a circular motion around the mounting support (10) during the pulling process, and amplifies the pulling force through the lever principle to efficiently pull out the cap removal pin (9).

[0015] Preferably, a plurality of fixed pulleys (7) are provided on the path of the steel cable (8).

[0016] Preferably, the other end of the steel cable is connected to a handle, the handle has a plug, and the end of the actuating lever is fitted with a socket for inserting the handle.

[0017] The mechanism described above has functions such as safety and limit, long lever arm drive, and automatic cable retraction and extension during operation, which can ensure safety when the cockpit canopy is thrown out in emergency situations on the ground. Attached Figure Description

[0018] Figure 1 This is a schematic diagram of the cockpit canopy ejection mechanism in the closed state provided by the present invention;

[0019] Figure 2 This is a schematic diagram of the working state of a cockpit external canopy ejection mechanism provided by the present invention. Detailed Implementation

[0020] To make the objectives, technical solutions, and advantages of this application clearer, the technical solutions in the embodiments of this application will be described in more detail below with reference to the accompanying drawings. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are only some embodiments of this application, not all embodiments. The embodiments described below with reference to the accompanying drawings are exemplary and intended to explain this application, and should not be construed as limiting this application. Based on the embodiments in this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application. The embodiments of this application will be described in detail below with reference to the accompanying drawings. A cockpit external canopy launching mechanism, such as... Figure 1 , Figure 2 As shown, it includes a fuselage hatch cover 1, a hatch ejection activation mechanism 2, and a detonation firing mechanism 3. The hatch ejection activation mechanism 2 includes an actuating rod 4, a limiting device 5, a cable winch 6, a fixed pulley 7, a steel cable 8, a hatch ejection pin 9, and a mounting bracket 10. (Fuselage hatch cover 1, hatch ejection activation mechanism 2, and detonation firing mechanism 3;)

[0021] Mounting support 10 is fixed to the machine body structure. One end of the steel cable winch 6 and the actuation rod 4 are coaxially connected to the machine body mounting support 10. The actuation rod 4 is mounted on a fixed pulley 7.

[0022] The steel cable 8 is partially wound in the steel cable winch 6, and part of it is detachably fixed to the end of the actuation rod 4 after being wound around the fixed pulley 7. One end of the canopy ejection pin 9 is connected to the actuation rod 4 via a hinge, and the other end is inserted into the canopy ejection detonation firing device 3. Ground crew pull the steel cable 8 to pull the actuation rod 4 to a preset angle, the canopy ejection pin 9 is pulled out, the canopy ejection detonation firing device outputs a canopy ejection signal, triggering the canopy ejection.

[0023] Preferably, it also includes a limiting device 5, which is hinged to the mounting bracket 10. The limiting device 5 restricts the rotation of the limiting device 5 by a pull-off pin. When the actuating rod 4 moves to the pull-off angle, the actuating rod 4 contacts the limiting device 5 and is limited. After the actuating rod 4 is pulled further, the pull-off pin breaks, and the limiting device 5 rotates with the actuating rod 4.

[0024] Preferably, the breaking angle is less than the preset angle.

[0025] Preferably, it also includes a limiting device 5, which is hinged to the mounting support 10. The limiting device 5 restricts the rotation of the limiting device 5 by a pull-off pin. When the actuating rod 4 moves to a certain angle, the actuating rod 4 contacts the limiting device 5 and limits the movement. After the steel cable 8 is pulled out to a preset extent, the cutting device on the steel cable 8 contacts the pull-off pin and destroys the pull-off pin. The limiting device 5 rotates with the actuating rod 4.

[0026] Preferably, the fuselage cover (1) is located on the side wall of the fuselage, has a square opening, and the outer side of the cover is a wall panel, which is configured to be able to be quickly opened during ground emergency rescue.

[0027] Preferably, the throwing cover starting mechanism (2) is fixedly connected to the body structure inside the body cover (1) and is supported as a whole by the mounting bracket (10).

[0028] Preferably, the cable winch (6) is used for the automatic winding and unwinding of the cable (8).

[0029] Preferably, the actuating lever (4) makes a circular motion around the mounting support (10) during the pulling process, and amplifies the pulling force through the lever principle to efficiently pull out the cap removal pin (9).

[0030] Preferably, a plurality of fixed pulleys (7) are provided on the path of the steel cable (8).

[0031] Preferably, the other end of the steel cable 8 is connected to a handle, the handle has a plug, and the end of the actuating lever 4 is equipped with a socket for inserting the handle.

[0032] During ground emergency rescue, ground crew first open the fuselage hatch 1, remove the steel cable 8 inserted on the actuation lever 4, and then start the steel cable winch 6 to pull the steel cable 8 to the outside of the fuselage until it is beyond a safe distance. Then, the steel cable 8 is pulled in the opposite direction of the flight through the fixed pulley 7. The actuation lever 4 then makes a circular motion around the mounting support 10, pulling the ejection pin 9 to pull out the detonation firing mechanism 3 and sending a signal to the onboard ejection system. After receiving the signal, the onboard system completes the ejection action.

[0033] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.

Claims

1. A cockpit outboard cover launch mechanism, characterized by, The utility model relates to a kind of emergency escape device of aircraft cabin, including: Machine body door cover (1), cover starting mechanism (2) and detonation firing mechanism (3); Wherein, cover starting mechanism (2) contains actuating pull rod (4), cable winch (6), fixed pulley (7), cable (8), cover pin (9) and mounting support (10); Mounting support (10) is fixedly connected on the machine body structure, and one end of cable winch (6) and actuating pull rod (4) is coaxially connected on the machine body mounting support (10), and the mounting fixed pulley (7) of actuating pull rod (4); Cable (8) is partially reeled in cable winch (6), and after being partially wound around fixed pulley (7), it is detachably fixed at the end of actuating pull rod (4), one end of cover pin (9) is connected with actuating pull rod (4) by hinge, and the other end is inserted into cover detonation firing device (3), ground staff pulls cable (8) to pull actuating pull rod (4) to preset angle, cover pin (9) is pulled out, cover detonation firing device outputs cover signal, triggers cabin cover to throw.

2. The out-of-cockpit cover launch mechanism of claim 1, wherein, Further comprising limiting device (5) hinged on mounting support (10), which limits the rotation of limiting device (5) by breaking pin shaft, when actuating pull rod (4) moves to breaking angle, actuating pull rod (4) contacts and limits limiting device (5), after pulling actuating pull rod (4) continuously, breaking pin shaft breaks, and limiting device (5) rotates with actuating pull rod (4).

3. The out-of-cockpit cover launch mechanism of claim 2, wherein, Breaking angle is less than the preset angle.

4. The out-of-cockpit canopy activation mechanism of claim 1, wherein, Further comprising limiting device (5) hinged on mounting support (10), which limits the rotation of limiting device (5) by breaking pin shaft, when actuating pull rod (4) moves to a certain angle, actuating pull rod (4) contacts and limits limiting device (5), after cable (8) is pulled out to preset degree, cutting device on cable (8) contacts and breaks breaking pin shaft, and limiting device (5) rotates with actuating pull rod (4).

5. The out-of-cockpit cover launch mechanism of claim 1, wherein, The machine body door cover (1) is arranged on the side wall of the machine body, which is a square opening, and the outer side of the door cover is a wall panel, which is configured to be quickly opened during ground emergency rescue.

6. The out-of-cockpit cover launch mechanism of claim 1, wherein, The cover starting mechanism (2) is fixedly connected to the machine body structure on the inner side of the machine body door cover (1) and is supported as a whole by the mounting support (10).

7. The out-of-cockpit cover launch mechanism of claim 1, wherein, The cable winch (6) is used for automatic winding and unwinding of the cable (8).

8. The out-of-cockpit canopy activation mechanism of claim 1, wherein, The actuating pull rod (4) makes circular motion around the mounting support (10) during pulling, and the pulling force is amplified by lever principle to efficiently pull out the cover pin (9).

9. The out-of-cockpit canopy activation mechanism of claim 1, wherein, A plurality of fixed pulleys (7) are arranged on the path of the cable (8).

10. The out-of-cockpit cover launch mechanism of claim 1, wherein, The other end of the cable (8) is connected with a handle, and the handle has a plug, and the end of the actuating pull rod (4) is provided with a socket for inserting the handle.

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