Aircraft access door quick release lock mechanism

Abstract

The application provides a kind of aircraft hatch quick-release lock mechanism, lock key support is fixedly connected with hatch, lock shell and adjustable support are fixedly connected with fuselage mouth frame and fuselage structure web respectively, both support lock tongue sliding along its axis, lock tongue keeps extending tendency under the action of compression spring, pull fork can drive lock tongue to unlock by sliding block passing through lock tongue, torsional spring force makes pull fork always in the state of facilitating lock tongue extension, there is a certain distance between unlocking surface of pull fork and sliding block for ice breaking, lock shell bottom supporting plate nut opening is in unlocked state, pull fork is driven to rotate by slender rod acting on pull fork groove, threaded fastener is screwed into supporting plate nut during flight mission to ensure sealing performance.The application has simple mechanism form, small space occupation, locking principle supports self-closing locking requirement, and has knocking mechanism, improves anti-jamming capacity of quick-release lock mechanism, thereby meeting various requirements of aircraft hatch quick-release lock at present.

Description

Technical Field

[0001] This invention belongs to the field of aircraft door mechanism design, and relates to an aircraft hatch quick-release locking mechanism, specifically a mechanism applied to an aircraft hatch for quickly locking or unlocking the hatch in the closed position. Background Technology

[0002] The locking mechanism of aircraft hatches prevents accidental opening when the hatch is closed, ensuring that the hatches are reliably locked in the closed position under normal operating conditions. Some small hatches on aircraft require rapid unlocking to meet the needs of quick maintenance or inspection. Some hatches not only need to meet airtightness or thermal tightness requirements but also self-closing and self-locking requirements, and the space where the hatches are located may be quite confined. Currently, most quick-release locks can only meet some of these requirements and cannot meet all of them simultaneously. Summary of the Invention

[0003] This invention provides a quick-release lock mechanism for aircraft hatches. In addition to meeting the requirement of quickly releasing the locked state of the hatch, this mechanism can also ensure the airtightness or thermal tightness of the operating interface. The mechanism is simple in form, occupies little space, supports the self-locking requirement in the locking principle, and has a knocking mechanism to improve the anti-jamming capability of the quick-release lock mechanism, thereby meeting the various requirements for quick-release locks of aircraft hatches.

[0004] The technical solution adopted in this invention is as follows:

[0005] A quick-release locking mechanism for an aircraft hatch, comprising a key support 1, a key bushing 2, a lock housing 3, a fork 4, a support plate nut 5, an adjustable support 6, a locking tongue 7, a slider 8, a torsion spring 9, a compression spring 10, a threaded fastener 11, a key pivot 12, and a slender rod for unlocking 13.

[0006] The key support 1 is fixedly connected to the cover. The key support 1 is provided with a double lug structure. The key shaft 12 passes through the double lug structure and is hinged. The key shaft 12 is covered with a key bushing 2.

[0007] The lock housing 3 is fixedly connected to the body frame, and the adjustable support 6 is fixedly connected to the body structure web plate. The two form a box-shaped structure. Through holes are made on the adjustable support 6 and on the opposite surfaces of the lock housing 3 and the adjustable support 6, for the lock tongue 7 to pass through and slide along its axis. Sliding grooves are provided at corresponding positions on both sides of the lock housing 3, and a round hole is provided on the bottom surface. The round hole is offset from the lock tongue 7, and a support plate nut 5 is fixed at the position of the round hole.

[0008] The threaded fastener 11, in conjunction with the support plate nut 5, seals the bottom round hole of the lock housing 3, ensuring the sealing performance of the fuselage during flight missions.

[0009] The locking tongue 7 extends out of the lock housing 3 at one end and, in the extended state, enters the double-ear structure of the key support 1 and is confined between the key bushing 2 and the key support 1. This position is the locking position of the quick-release lock mechanism. When the locking tongue 7 retracts and moves to avoid the key bushing 2, it is the unlocking position. The end of the locking tongue 7 is beveled to cooperate with the key bushing 2 to achieve self-locking.

[0010] The slider 8 passes vertically through the latch 7, with both ends restricted within the grooves of the lock housing 3, and can slide along the grooves to limit the range of motion of the latch 7.

[0011] The compression spring 10 is threaded onto the locking tongue 7, and its two ends are pressed against the adjustable support 6 and the slider 8, so that the locking tongue 7 always maintains an extended tendency.

[0012] The fork 4 is hinged at both ends to the two side walls of the lock housing 3. It is located on the side above the bolt 7, and the slider 8 is between the two forks. The fork 4 facing the round hole on the bottom surface of the lock housing 3 has a groove. When unlocking, the slender rod 13 passes through the round hole and pushes into the groove to push the fork 4 to rotate. The other fork of the fork 4 pushes the slider 8 to slide along the groove of the lock housing 3, causing the bolt 7 to retract and avoid the key bushing 2 to achieve unlocking.

[0013] The torsion spring 9 is mounted on the shift fork 4, with its two ends acting on the side wall of the lock housing 3 and the shift fork 4 respectively, so that the shift fork 4 always maintains the locking tendency. When the lock tongue 7 is extended, under the action of the torsion spring 9, the fork head of the shift fork 4 without the groove maintains a certain gap with the slider 8, which is used to knock the slider 8 and lock tongue 7 and other components when the quick release lock mechanism is stuck.

[0014] Furthermore, the spring force of the compression spring 10 should ensure that under any overload, the locking tongue 7 will not dodge the locking key bushing 2 due to inertia.

[0015] Furthermore, when the latch 7 is extended, the fork head of the shift fork 4 without a groove maintains a 2.5mm gap with the slider 8.

[0016] The self-locking function of the quick-release lock mechanism relies on the inclined surface at the latch 7. When the cover is turned from the open position to the closed position by the drive device of the opening mechanism, the inclined surface of the latch 7 contacts the key bushing 2. The driving force for closing the cover is transformed from the inclined surface into the force driving the latch 7 to retract. As the cover closes, the latch 7 retracts to avoid the key bushing 2. At this time, the cover is in the closed position, and the latch 7 is ejected under the action of the compression spring 10 without external force, thus completing the self-locking. The anti-jamming function of the quick-release lock mechanism relies on the gap between the shift fork 4 and the slider 8. Under the action of the torsion spring 9, the shift fork 4 leaves a gap with the slider 8. When the mechanism is stuck, the fork 4 can strike the slider 8 and the locking tongue 7. The unlocking and sealing functions of the quick-release lock mechanism rely on the round hole at the bottom of the lock case and the support plate nut. During the flight mission, in order to ensure the sealing performance inside the fuselage, the threaded fastener 11 and the support plate nut 5 are used to block the round hole at the bottom of the lock case 3. Before and after the flight mission, when it is necessary to release the closed state of the cover, first remove the threaded fastener, and then use the unlocking slender rod 13 to extend into the lock case 3 along the round hole to abut against the groove of the fork 4, drive the fork 4 to drive the locking tongue 7 to retract, thereby releasing the lock and opening the cover.

[0017] The beneficial effects of this invention are as follows:

[0018] 1. Simple and efficient mechanism. This invention is easy to arrange in a cap structure with limited dimensions, saving space occupied by the mechanism, requiring no excessive installation connections, reducing the number of parts in the mechanism, and significantly saving space for the cap mechanism layout;

[0019] 2. Wide range of applications. The mechanism of this invention has a simple movement form and strong design flexibility, which can meet the adjustment and optimization of various spaces. This invention can be widely applied to various lids.

[0020] 3. High reliability. The mechanism's movement stroke is reliable, ensuring the cover is securely locked in the closed position. Attached Figure Description

[0021] Figure 1 This is an isometric drawing of a quick-release locking mechanism for a lid.

[0022] Figure 2 This is a schematic diagram of the locking key bushing driving the locking tongue in a quick-release cover locking mechanism.

[0023] Figure 3 This is a schematic diagram of the bottom of the lock housing of a quick-release cover lock mechanism.

[0024] Figure 4 This is a schematic diagram of the unlocking operation of a quick-release locking mechanism for a lid.

[0025] Figure 5 This is a schematic diagram of the unlocked state of a quick-release locking mechanism for a lid.

[0026] In the diagram: 1. Locking key support; 2. Locking key bushing; 3. Lock housing; 4. Shift fork; 5. Support plate nut; 6. Adjustable support; 7. Locking tongue; 8. Slider; 9. Torsion spring; 10. Compression spring; 11. Threaded fastener; 12. Locking key pivot; 13. Slender rod for unlocking. Detailed Implementation

[0027] The technical solution of the present invention will now be clearly and completely described. Obviously, the described embodiments are merely some embodiments of the present invention, and not all embodiments. All other embodiments derived by those skilled in the art based on the embodiments of the present invention through modifications or adjustments are within the protection scope of the present invention.

[0028] This embodiment provides a quick-release lock mechanism for an aircraft hatch. The quick-release lock mechanism includes a key support 1, a key bushing 2, a lock housing 3, a fork 4, a support plate nut 5, an adjustable support 6, a locking tongue 7, a slider 8, a torsion spring 9, a compression spring 10, a threaded fastener 11, a key pivot 12, and a slender unlocking rod 13. Figure 1 and Figure 2 As shown.

[0029] The key support 1 is fixedly connected to the cover. The key support 1 is provided with a double lug structure. The key shaft 12 passes through the double lug structure and is hinged. The key shaft 12 is covered with a key bushing 2.

[0030] The lock housing 3 is fixedly connected to the body frame, and the adjustable support 6 is fixedly connected to the body structure web plate. The two form a box-shaped structure. Through holes are made on the adjustable support 6 and on the opposite surfaces of the lock housing 3 and the adjustable support 6, for the lock tongue 7 to pass through and slide along its axis. Sliding grooves are provided at corresponding positions on both sides of the lock housing 3, and a 10mm diameter round hole is provided on the bottom surface. The round hole is offset from the lock tongue 7, and a support plate nut 5 is fixed at the position of the round hole.

[0031] The threaded fastener 11, in conjunction with the bracket nut 5, seals the bottom circular hole of the lock housing 3, ensuring the sealing performance of the fuselage interior during flight missions. Figure 3 As shown.

[0032] The locking tongue 7 extends out of the lock housing 3 at one end and, in the extended state, enters the double-ear structure of the key support 1 and is confined between the key bushing 2 and the key support 1. This position is the locking position of the quick-release lock mechanism. When the locking tongue 7 retracts and moves to avoid the key bushing 2, it is the unlocking position. The end of the locking tongue 7 is beveled to cooperate with the key bushing 2 to achieve self-locking.

[0033] The slider 8 passes vertically through the latch 7, with both ends restricted within the grooves of the lock housing 3, and can slide along the grooves to limit the range of motion of the latch 7.

[0034] The compression spring 10 is threaded onto the locking tongue 7, and its two ends are pressed against the adjustable support 6 and the slider 8, so that the locking tongue 7 always maintains an extended tendency.

[0035] The fork 4 is hinged at both ends to the side walls of the lock housing 3, located above the bolt 7, with the slider 8 between the two forks. The fork 4 facing the circular hole on the bottom surface of the lock housing 3 has a groove. A slender rod 13, used for unlocking, passes through the circular hole and pushes into the groove to rotate the fork 4. The other fork 4 then moves the slider 8 along the groove of the lock housing 3, causing the bolt 7 to retract and avoid the key bushing 2, thus unlocking the lock. Figure 4 and Figure 5 As shown.

[0036] The torsion spring 9 is mounted on the shift fork 4, with its two ends acting on the side wall of the lock housing 3 and the shift fork 4 respectively, so that the shift fork 4 always maintains the locking tendency. When the lock tongue 7 is extended, under the action of the torsion spring 9, the fork head of the shift fork 4 without the groove maintains a 2.5mm gap with the slider 8. This is used to strike the slider 8 and lock tongue 7 and other components when the quick-release lock mechanism is stuck.

[0037] like Figure 2 As shown, the self-locking function of the quick-release lock mechanism relies on the inclined surface at the latch 7. When the opening mechanism's drive device moves from the open position to the closed position, the inclined surface of the latch 7 contacts the key bushing 2. The driving force for closing the latch is transformed from the inclined surface into the force that drives the latch 7 to retract. As the latch closes, the latch retracts to avoid the key bushing 2. At this time, the latch is in the closed position, and the latch 7 is not driven by external force. It is driven by the lock's own compression spring 10 to pop out and extend between the key bushing 2 and the key support 1, thus completing the self-locking.

[0038] like Figure 3 As shown, the sealing function of the quick-release lock mechanism relies on the 10mm round hole at the bottom of the lock housing 3 and the support plate nut 5. During flight missions, in order to ensure the sealing performance inside the fuselage, the threaded fastener 11 is used in conjunction with the support plate nut 5 to block the 10mm round hole.

[0039] like Figure 4 As shown, when the hatch needs to be unsealed before or after a flight mission, first remove the... Figure 3 The threaded fastener 11 is then used to unlock the lock body. The slender rod 13 is inserted into the lock body through the 10mm hole and presses against the groove of the shift fork 4. The shift fork 4 drives the lock tongue 7 to retract and disengage from the lock key bushing 2, thereby unlocking and opening the cover. At the same time, the anti-jamming function of the quick-release lock mechanism relies on the gap between the shift fork 4 and the slider 8. Under the action of the torsion spring 9, the shift fork 4 leaves a 2.5mm gap with the slider 8. When the mechanism jams, the shift fork 4 can strike the slider 9 and the lock tongue 7.

[0040] The above embodiments are merely illustrative of the implementation methods of the present invention, but should not be construed as limiting the scope of the present invention. It should be noted that those skilled in the art can make various modifications and improvements without departing from the concept of the present invention, and these modifications and improvements all fall within the protection scope of the present invention.

Claims

1. An aircraft access door quick-release lock mechanism, characterized by, The quick release lock mechanism comprises a lock key support (1), a lock key bushing (2), a lock shell (3), a fork (4), an adjustable support (6), a lock tongue (7), a sliding block (8), a compression spring (10), and an unlocking slender rod (13); The lock key support (1) is fixedly connected with the cover, and the lock key bushing (2) is hingedly connected to the lock key support (1); The lock shell (3) is fixedly connected with the body frame, and the adjustable support (6) is fixedly connected with the web plate of the body structure, and the lock shell (3) and the adjustable support (6) form a box-shaped structure, the adjustable support (6) and the opposite surface of the lock shell (3) are provided with through holes, the lock tongue (7) passes through the through holes and slides along the axis, the two side walls of the lock shell (3) are provided with sliding grooves, and the bottom surface is provided with a circular hole, and the circular hole is arranged in a staggered manner with the lock tongue (7); When the lock tongue (7) is in the extended state, the end of the lock tongue (7) is limited between the lock key bushing (2) and the lock key support (1), the position is the locking position of the quick release lock mechanism, the lock tongue (7) is in the retracted state and hides the lock key bushing (2), the end of the lock tongue (7) is provided with an inclined surface, and the inclined surface is used for cooperating with the lock key bushing (2) to realize self-locking; The sliding block (8) vertically passes through the lock tongue (7), and the two ends of the sliding block (8) are limited in the sliding grooves of the lock shell (3) and can slide along the sliding grooves; The compression spring (10) is arranged on the lock tongue (7), and the two ends of the compression spring (10) are pressed against the adjustable support (6) and the sliding block (8), so that the lock tongue (7) always maintains the extending trend; The fork (4) is hingedly connected to the two side walls of the lock shell (3) and is located above the side surface of the lock tongue (7), and the sliding block (8) is located between the two fork heads, the fork head of the fork (4) facing the circular hole in the bottom surface of the lock shell (3) is provided with a groove, when unlocking, the unlocking slender rod (13) passes through the circular hole and is inserted into the groove to push the fork (4) to rotate, the other fork head of the fork (4) drives the sliding block (8) to retract the lock tongue (7) to realize unlocking.

2. An aircraft access door quick-release lock mechanism as defined in claim 1 wherein, The bottom surface of the lock shell (3) is fixedly provided with a supporting plate nut (5), the threaded fastener (11) is matched with the supporting plate nut (5) to seal the circular hole in the bottom of the lock shell (3), and the threaded fastener (11) is removed when unlocking.

3. The quick-release lock mechanism for an access door of an aircraft of claim 1, wherein, The torsional spring (9) is arranged on the fork (4), and the two ends of the torsional spring (9) are arranged on the side wall of the lock shell (3) and the fork (4) respectively, when the lock tongue (7) is in the extended state, the fork head of the fork (4) without the groove keeps a certain gap with the sliding block (8) under the action of the torsional spring (9), and the fork head is used for knocking the sliding block (8) to break the ice when the quick release lock mechanism is stuck.

4. A quick-release lock mechanism for a hatch cover of a marine vessel as defined in claim 3, wherein When the lock tongue (7) is in the extended state, the fork head of the fork (4) without the groove keeps a gap of 2.5 mm with the sliding block (8).

5. The quick-release lock mechanism for an access door of an aircraft of claim 1, wherein, The spring force of the compression spring (10) should ensure that the lock tongue (7) cannot hide the lock key bushing (2) due to inertial force under any overload.

Images