A locking device for a light aircraft canopy

Abstract

The utility model discloses a locking device for a light aircraft canopy, and relates to the field of aircraft cabins. The device comprises a fixed lock seat, a dynamic lock seat and a pull rope; a guide block is fixedly connected to the top of the fixed lock seat, a lock pull rod is slidably connected to the guide block, and the rear end of the pin shaft rod is fixedly connected to the pull rope; a rocker arm is arranged on one side of the lock pull rod, a guide sliding hole is arranged on the rocker arm, a pin shaft rod is arranged in the guide sliding hole, the pin shaft rod is fixedly connected to the lock pull rod, the lower end of the rocker arm is fixedly connected to the rotating shaft, the rotating shaft is rotatably connected to the shaft seat, the shaft seat is fixedly installed on the fixed lock seat, and an inner handle is arranged at one end of the rotating shaft; the dynamic lock seat is located above the fixed lock seat, a lock sleeve is arranged at the bottom of the dynamic lock seat, and the lock sleeve is plugged and matched with the lock pull rod. The utility model adopts a latch form, has a simple and reliable structure, adopts an emergency pull rope to realize the opening outside the cabin, does not affect the aesthetics of the cabin, and can also reduce the influence of the protruding objects of the aircraft fuselage on the aerodynamic performance of the aircraft.

Description

Technical Field

[0001] The utility model relates to the field of aircraft cockpits, in particular to a locking device for a light aircraft cockpit cover. Background Art

[0002] In light aircraft, the entrance and exit of the cockpit is achieved by opening the hatch cover. According to regulations, the emergency exit of the aircraft must be able to be opened from both the inside and outside. As the only entrance and exit of small aircraft, the hatch cover needs to fully ensure the safety of opening and closing the hatch cover. Generally, light aircraft will have an emergency handle on the outside of the cabin. The control handle drives the hatch cover mechanism to move the lock pin out of the lock pin seat hole to open the hatch cover in an emergency state.

[0003] Although an emergency handle is set on the outside of the cabin, it is easy to operate. However, the protruding handle on the outside of the cabin not only affects the aesthetics, but also increases flight resistance during flight. Utility Model Content

[0004] Based on the above problems, the purpose of the utility model is to provide a light aircraft canopy locking device, and the utility model adopts the following technical solutions:

[0005] The utility model provides a light aircraft canopy locking device, comprising:

[0006] A fixed lock seat, a guide block is provided on the top of the fixed lock seat, a lock pull rod is slidably connected to the guide block, a rocker arm is provided on one side of the lock pull rod, a guide slide hole is provided on the rocker arm, a pin shaft rod is provided in the guide slide hole, the pin shaft rod is fixedly connected to the lock pull rod, the lower end of the rocker arm is fixedly connected to the rotating shaft, the rotating shaft is rotatably connected to the shaft seat, and an inner handle is provided at one end of the rotating shaft;

[0007] A dynamic lock seat, the bottom of which is provided with a lock sleeve, the lock sleeve is plugged into the lock pull rod; a pull rope, the pull rope is fixedly connected to the rear end of the pin shaft rod

[0008] Preferably, the pull rope is a steel wire rope.

[0009] Preferably, it comprises an outer box body, the outer box body is provided with a wire hole, the pull rope passes through the wire hole, a box cover is provided on the outer side of the outer box body, and a dismantling groove is provided on the box cover.

[0010] Preferably, a pull ring is provided at the free end of the pull rope, and the pull ring is located in the outer box body.

[0011] Preferably, a spring top ball is arranged on the shaft seat; a positioning groove is arranged on the outer wall of the rotating shaft; when the inner handle is rotated to the locking position, the spring top ball is embedded in the positioning groove.

[0012] Compared with the prior art, the beneficial technical effects of the utility model are:

[0013] The utility model adopts a latch form, has a simple and reliable structure, adopts an emergency pull rope to realize the opening outside the cabin, does not affect the aesthetics of the cabin, and can also reduce the influence of the protruding objects of the aircraft fuselage on the aerodynamic performance of the aircraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] The utility model will be further described below in conjunction with the accompanying drawings.

[0015] Figure 1 This is a structural schematic diagram of a light aircraft canopy locking device of the utility model;

[0016] Figure 2 for Figure 1 A partial enlarged view of the middle A;

[0017] Figure 3 The utility model is a schematic diagram of the installation and use of the light aircraft canopy locking device.

[0018] Explanation of the reference numerals in the accompanying drawings: 1. fixed lock seat; 2. guide block; 3. lock rod; 4. rocker arm; 401. guide slide hole; 5. pin shaft rod; 6. rotating shaft; 601. positioning groove; 7. shaft seat; 8. inner handle; 9. dynamic lock seat; 901. lock sleeve; 10. pull rope; 11. outer box body; 1101. wire hole; 12. box cover; 1201. demolition groove; 13. pull ring; 14. spring top bead; 15. machine body; 16. hatch cover. DETAILED DESCRIPTION

[0019] In order to make the technical problems, technical solutions and beneficial effects to be solved by the present invention more clearly understood, the present invention is further described in detail below in conjunction with the accompanying drawings and embodiments.

[0020] like Figure 1 and 2 As shown, the present embodiment discloses a light aircraft canopy locking device, including a fixed lock seat 1, a dynamic lock seat 9 and a pull rope 10. A guide block 2 is fixedly connected to the top of the fixed lock seat 1, a lock pull rod 3 is slidably connected to the guide block 2, and the rear end of the pin shaft rod 5 is fixedly connected to the pull rope 10. A rocker arm 4 is provided on one side of the lock pull rod 3, a guide slide hole 401 is provided on the rocker arm 4, a pin shaft rod 5 is provided in the guide slide hole 401, the pin shaft rod 5 is fixedly connected to the lock pull rod 3, the lower end of the rocker arm 4 is fixedly connected to the rotating shaft 6, the rotating shaft 6 is rotatably connected to the shaft seat 7, the shaft seat 7 is fixedly installed on the fixed lock seat 1, and an inner handle 8 is provided at one end of the rotating shaft 6.

[0021] The dynamic lock seat 9 is located above the fixed lock seat 1 , and a lock sleeve 901 is provided at the bottom of the dynamic lock seat 9 , and the lock sleeve 901 is plugged and matched with the lock rod 3 .

[0022] In this embodiment, the pull rope 10 is a steel wire rope.

[0023] In this embodiment, the outer box body 11 is provided with a wire hole 1101, and the pull rope 10 passes through the wire hole 1101. A box cover 12 is provided on the outer side of the outer box body 11, and a demolition groove 1201 is provided on the box cover 12. A pull ring 13 is provided at the free end of the pull rope 10, and the pull ring 13 is located in the outer box body 11.

[0024] In this embodiment, a spring top bead 14 is provided on the shaft seat 7; a positioning groove 601 is provided on the outer wall of the rotating shaft 6; when the inner handle 8 is rotated to the locked position, the spring top bead 14 is embedded in the positioning groove 601.

[0025] The operating principle of the utility model is as follows:

[0026] like Figure 3 As shown, a light aircraft is provided with a canopy 16 on the fuselage 15 of the aircraft. The rear of the canopy 16 is hinged to the fuselage 15, and the canopy 16 can be flipped backward. The canopy locking structure in this embodiment is arranged on the side of the canopy 16. Specifically, the fixed lock seat 1 is fixedly mounted on the fuselage 15, the dynamic lock seat 9 is fixedly mounted on the canopy 16, and the outer box body 11 is embedded and fixed on the fuselage 15. The outer box body 11 is located behind the fixed lock seat 1.

[0027] After the hatch cover 16 is flipped forward and closed, the lock sleeve 901 rotates and moves to the position of the fixed lock seat 1. At this time, the inner handle 8 is rotated to drive the lock rod 3 forward through the rocker arm 4 until it is inserted into the lock sleeve 901, so that the hatch cover 16 is locked. When the inner handle 8 is rotated to the locked position, the spring top ball 14 is embedded in the positioning groove 601. This can prevent the lock rod 3 from being unlocked by the overload force of a certain heading during flight.

[0028] When in an emergency situation, when the crew members are seriously injured or in a coma and cannot open the emergency hatch from the inside, external rescue personnel can break open the box cover 12 and then open the box body 11 outside the cabin. By pulling the pull ring 13 backward with force, the lock rod 3 can be pulled out of the lock sleeve 901, so that external rescue can be achieved in the emergency situation.

[0029] The dismantling groove 1201 provided on the box cover 12 facilitates rescue personnel to dismantle the box cover 12 .

[0030] The embodiments described above are only descriptions of the preferred methods of the present invention, and are not intended to limit the scope of the present invention. Without departing from the design spirit of the present invention, various modifications and improvements made to the technical solutions of the present invention by ordinary technicians in this field should fall within the protection scope determined by the claims of the present invention.

Claims

1. A light aircraft canopy locking device, characterized in that: include: A fixed lock seat (1), wherein a guide block (2) is arranged on the top of the fixed lock seat (1), a lock pull rod (3) is slidably connected to the guide block (2), a rocker arm (4) is arranged on one side of the lock pull rod (3), a guide slide hole (401) is arranged on the rocker arm (4), a pin shaft rod (5) is arranged in the guide slide hole (401), the pin shaft rod (5) is fixedly connected to the lock pull rod (3), the lower end of the rocker arm (4) is fixedly connected to a rotating shaft (6), the rotating shaft (6) is rotatably connected to a shaft seat (7), and an inner handle (8) is arranged at one end of the rotating shaft (6); A dynamic lock seat (9), wherein a lock sleeve (901) is provided at the bottom of the dynamic lock seat (9), and the lock sleeve (901) is plugged and matched with the lock pull rod (3); A pull rope (10), wherein the pull rope (10) is fixedly connected to the rear end of the pin shaft rod (5).

2. The light aircraft canopy locking device according to claim 1, characterized in that: The pull rope (10) is a steel wire rope.

3. The light aircraft canopy locking device according to claim 1, characterized in that: The invention comprises an outer box body (11), wherein the outer box body (11) is provided with a wire hole (1101), and the pull rope (10) passes through the wire hole (1101); a box cover (12) is provided on the outer side of the outer box body (11), and a dismantling groove (1201) is provided on the box cover (12).

4. The light aircraft canopy locking device according to claim 3, characterized in that: A pull ring (13) is provided at the free end of the pull rope (10), and the pull ring (13) is located in the outer box body (11).

5. The light aircraft canopy locking device according to claim 1, characterized in that: A spring top ball (14) is arranged on the shaft seat (7); a positioning groove (601) is arranged on the outer wall of the rotating shaft (6); when the inner handle (8) is rotated to the locked position, the spring top ball (14) is embedded in the positioning groove (601).

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