Quick release lock mechanism for aircraft covering cap

Abstract

A lock key support is fixedly connected with the covering cap, a lock shell and an adjustable support are fixedly connected with a fuselage opening frame and a fuselage structure web correspondingly and support a spring bolt to slide along the axis of the lock bolt, and the spring bolt keeps the extending tendency under the acting force of a pressure spring; the shifting fork can drive the spring bolt to be unlocked through the sliding block penetrating through the spring bolt, the shifting fork is always in the state of facilitating stretching out of the spring bolt through the acting force of the torsional spring, a certain distance is reserved between the unlocking acting face of the shifting fork and the sliding block to be used for breaking ice, and when a nut opening of a supporting plate at the bottom of the lock shell is unlocked, a long and thin rod acts on a shifting fork groove to drive the shifting fork to rotate. In a flight mission, a threaded fastener is screwed into a supporting plate nut to ensure the sealing performance. The mechanism is simple in form and small in occupied space, the locking principle supports the self-closing locking requirement, the knocking mechanism is arranged, the clamping stagnation prevention capacity of the quick-release lock mechanism is improved, and therefore various requirements for an aircraft covering cap quick-release lock at present are met.

Description

Technical Field

[0001] The invention belongs to the field of aircraft door mechanism design, and relates to an aircraft hatch quick-release lock mechanism, and in particular to a mechanism applied to an aircraft hatch for realizing quick locking or unlocking of the hatch in a closed position. Background Art

[0002] The locking mechanism of the aircraft cover can prevent the cover from opening accidentally when the hatch is closed, ensuring that the cover can be reliably locked in the closed position under normal operating conditions. In order to meet the needs of rapid maintenance or inspection, some small covers on some aircraft are required to be able to be quickly unlocked. Some covers must not only meet the requirements of air tightness or heat tightness, but also meet the requirements of self-closing and self-locking. In addition, the space where the cover is located may be relatively small. At present, most quick-release locks can only meet some of the above requirements, but cannot meet all the requirements at the same time. Summary of the invention

[0003] The present invention provides a quick-release lock mechanism for an aircraft mouth cover. In addition to meeting the requirement of quickly releasing the locked state of the mouth cover, the mechanism can also ensure the air tightness or heat tightness at the operation interface. The mechanism is simple in form and occupies a small space. The locking principle supports the self-locking requirement and is provided with a knocking mechanism to improve the anti-stuck ability of the quick-release lock mechanism, thereby meeting various current requirements for quick-release locks of aircraft mouth covers.

[0004] The technical solution adopted by the present invention is as follows:

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

[0006] The lock key support 1 is fixedly connected to the mouth cover, and a double-ear piece structure is arranged on the lock key support 1. The lock key shaft 12 penetrates into the double-ear piece structure and is hinged, and a lock key bushing 2 is arranged on the lock key shaft 12.

[0007] The lock shell 3 is fixedly connected to the fuselage mouth frame, and the adjustable support 6 is fixedly connected to the fuselage structure belly plate, and the two form a box-like structure. Through holes are made on the adjustable support 6 and on the opposite surfaces of the lock shell 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 the two side walls of the lock shell 3, and a circular hole is provided on the bottom surface. The circular hole and the lock tongue 7 are staggered, and a support plate nut 5 is fixed at the position of the circular hole.

[0008] The threaded fastener 11 cooperates with the support plate nut 5 to seal the circular hole at the bottom of the lock housing 3, thereby ensuring the sealing performance inside the fuselage during the flight mission.

[0009] The lock tongue 7 passes through one end of the lock housing 3, and penetrates into the double-ear structure of the lock key support 1 when the lock tongue 7 is extended, and is restricted between the lock key bushing 2 and the lock key support 1. This position is the locking position of the quick-release lock mechanism. When the lock tongue 7 contracts and moves to avoid the lock key bushing 2, it is the unlocking position. The end of the lock tongue 7 is made into an inclined surface for cooperating with the lock key bushing 2 to achieve self-locking.

[0010] The sliding block 8 vertically passes through the locking tongue 7 , and both ends are restricted in the sliding grooves of the lock housing 3 , and can slide along the sliding grooves to limit the movement range of the locking tongue 7 .

[0011] The compression spring 10 is passed through the lock tongue 7, and its two ends are pressed tightly on the adjustable support 6 and the slide block 8, so that the lock tongue 7 always maintains a tendency to extend.

[0012] The two ends of the fork 4 are hinged on the two side walls of the lock shell 3, which are located on the side above the lock tongue 7, and the slider 8 is between the two fork heads. A groove is provided on the fork head of the fork 4 facing the circular hole on the bottom surface of the lock shell 3. When unlocking, the slender rod 13 for unlocking passes through the circular hole and is pushed into the groove to push the fork 4 to rotate. The other fork head of the fork 4 drives the slider 8 to slide along the slide groove of the lock shell 3, driving the lock tongue 7 to shrink and avoid the lock key bushing 2 to achieve unlocking.

[0013] The torsion spring 9 is arranged on the fork 4, and its two ends act on the side wall of the lock housing 3 and the fork 4 respectively, so that the fork 4 always maintains a locking tendency, and when the lock tongue 7 is extended, under the action of the torsion spring 9, the fork head of the fork 4 without a groove maintains a certain gap with the slider 8, which is used for the fork 4 to knock on the slider 8, the 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 lock tongue 7 will not escape from the lock key bushing 2 due to inertia force.

[0015] Furthermore, when the locking tongue 7 is extended, a gap of 2.5 mm is maintained between the fork head of the shift fork 4 without a groove and the slider 8 .

[0016] The self-locking function of the quick-release lock mechanism relies on the inclined surface of the lock tongue 7. When the driving device of the opening mechanism turns from the open position to the closed position, the inclined surface of the lock tongue 7 contacts the lock key bushing 2, and the driving force for closing the cover is converted from the inclined surface to the force driving the lock tongue 7 to retract. As the cover closes, the lock tongue 7 retracts to avoid the lock key bushing 2. At this time, the cover is in the closed position, and the lock tongue 7 pops out under the action of the compression spring 10 without external force, completing the self-locking; the anti-stuck function of the quick-release lock mechanism relies on the gap between the shift fork 4 and the slider 8. The shift fork 4 leaves a gap with the slider 8 under the action of the torsion spring 9. When the mechanism is stuck, the shift fork 4 can knock on the slider 8, the lock tongue 7 and other components; the unlocking and sealing functions of the quick-release lock mechanism rely on the round hole at the bottom of the lock shell and the support plate nut. During the flight mission, 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 round hole on the bottom surface of the lock shell 3. When the cover needs to be released from the closed state before or after the flight mission, the threaded fastener is first removed, and then the unlocking slender rod 13 is extended into the lock shell 3 along the round hole to resist the groove of the shift fork 4, driving the shift fork 4 to drive the lock tongue 7 to retract, thereby releasing the lock and opening the cover.

[0017] The beneficial effects of the present invention are:

[0018] 1. The mechanism is simple and efficient. The present invention is easy to be arranged in a cover structure with limited size, saving the space occupied by the mechanism, not requiring too many installation connections, reducing the number of parts of the mechanism, and significantly saving the space for the mechanism layout of the cover;

[0019] 2. Wide application range. The mechanism movement form of the present invention is simple, the designability is strong, and it can meet the adjustment and optimization of various spaces. The present invention can be applied to various mouth covers.

[0020] 3. High reliability. The mechanism has a reliable movement stroke and can reliably lock the cover in the closed position. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 The utility model is an axonometric drawing of a quick-release lock mechanism of a cover.

[0022] Figure 2 The present invention is a schematic diagram of a lock tongue driven by a lock key bushing of a quick-release lock mechanism for a cover.

[0023] Figure 3 The present invention is a schematic diagram of the bottom of a lock shell of a quick-release lock mechanism for a cover.

[0024] Figure 4 The present invention is a schematic diagram of the unlocking operation of a quick-release lock mechanism of a cover.

[0025] Figure 5 The present invention is a schematic diagram of a quick-release lock mechanism of a cover in an unlocked state.

[0026] In the figure: 1 lock key support; 2 lock key bushing; 3 lock housing; 4 shift fork; 5 support plate nut; 6 adjustable support; 7 lock tongue; 8 slider; 9 torsion spring; 10 compression spring; 11 threaded fastener; 12 lock key shaft; 13 unlocking slender rod. DETAILED DESCRIPTION

[0027] The technical solution of the present invention is described clearly and completely below. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of them. All other embodiments improved or adjusted by ordinary technicians in this field based on the embodiments of the present invention belong to the protection scope of the present invention.

[0028] The present embodiment provides a quick-release lock mechanism for an aircraft cover, the quick-release lock mechanism comprising a lock key support 1, a lock key bushing 2, a lock housing 3, a shift fork 4, a support plate nut 5, an adjustable support 6, a lock tongue 7, a slider 8, a torsion spring 9, a compression spring 10, a threaded fastener 11, a lock key shaft 12, and an unlocking slender rod 13, as shown in FIG. Figure 1 and Figure 2 shown.

[0029] The lock key support 1 is fixedly connected to the mouth cover, and a double-ear piece structure is arranged on the lock key support 1. The lock key shaft 12 penetrates into the double-ear piece structure and is hinged, and a lock key bushing 2 is arranged on the lock key shaft 12.

[0030] The lock shell 3 is fixedly connected to the fuselage mouth frame, and the adjustable support 6 is fixedly connected to the fuselage structure belly plate, and the two form a box-like structure. Through holes are made on the adjustable support 6 and on the opposite surfaces of the lock shell 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 the two side walls of the lock shell 3, and a circular hole with a diameter of 10 mm is provided on the bottom surface. The circular hole and the lock tongue 7 are staggered, and a support plate nut 5 is fixed at the position of the circular hole.

[0031] The threaded fastener 11 cooperates with the support plate nut 5 to seal the bottom circular hole of the lock housing 3, thereby ensuring the sealing performance inside the fuselage during the flight mission. Figure 3 shown.

[0032] The lock tongue 7 passes through one end of the lock housing 3, and penetrates into the double-ear structure of the lock key support 1 when the lock tongue 7 is extended, and is restricted between the lock key bushing 2 and the lock key support 1. This position is the locking position of the quick-release lock mechanism. When the lock tongue 7 contracts and moves to avoid the lock key bushing 2, it is the unlocking position. The end of the lock tongue 7 is made into an inclined surface for cooperating with the lock key bushing 2 to achieve self-locking.

[0033] The sliding block 8 vertically passes through the locking tongue 7 , and both ends are restricted in the sliding grooves of the lock housing 3 , and can slide along the sliding grooves to limit the movement range of the locking tongue 7 .

[0034] The compression spring 10 is passed through the lock tongue 7, and its two ends are pressed tightly on the adjustable support 6 and the slide block 8, so that the lock tongue 7 always maintains a tendency to extend.

[0035] The two ends of the shift fork 4 are hinged on the two side walls of the lock housing 3, which are located on the upper side of the lock tongue 7, and the slider 8 is between the two fork heads. A groove is arranged on the fork head of the shift fork 4 facing the circular hole on the bottom surface of the lock housing 3. The slender rod 13 for unlocking passes through the circular hole and is pushed into the groove to push the shift fork 4 to rotate. The other fork head of the shift fork 4 drives the slider 8 to slide along the slide groove of the lock housing 3, driving the lock tongue 7 to shrink and avoid the lock key bushing 2 to achieve unlocking. Figure 4 and Figure 5 shown.

[0036] The torsion spring 9 is arranged on the fork 4, and its two ends act on the side wall of the lock housing 3 and the fork 4 respectively, so that the fork 4 always maintains a locking tendency, and when the lock tongue 7 is extended, under the action of the torsion spring 9, the fork head of the fork 4 without a groove maintains a 2.5mm gap with the slider 8, which is used for the fork 4 to knock on the slider 8, the 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 lock tongue 7. When the driving device of the opening mechanism turns from the open position to the closed position, the inclined surface of the lock tongue 7 contacts the lock key bushing 2, and the driving force for closing the cover is converted by the inclined surface into a force driving the lock tongue 7 to contract. As the cover closes, the lock tongue contracts to avoid the lock key bushing 2. At this time, the cover is in the closed position, and the lock tongue 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 lock key bushing 2 and the lock key support 1 to complete self-locking.

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

[0039] like Figure 4 As shown, when the cover needs to be opened before or after the flight mission, first remove Figure 3 The threaded fastener 11 is inserted into the lock body along the 10mm hole, and then the slender rod 13 for unlocking is extended into the groove of the fork 4 to drive the fork 4 to retract the lock tongue 7 and disengage from the lock key bushing 2, thereby releasing the lock and opening the cover; at the same time, the anti-stuck function of the quick-release lock mechanism relies on the gap between the fork 4 and the slider 8. The fork 4 has a 2.5mm gap with the slider 8 under the action of the torsion spring 9. When the mechanism is stuck, the fork 4 can knock on the slider 9, the lock tongue 7 and other components.

[0040] The above-described embodiments merely express the implementation methods of the present invention, but they should not be understood as limiting the scope of the present invention. It should be pointed out that for those skilled in the art, several modifications and improvements can be made without departing from the concept of the present invention, which all belong to the protection scope of the present invention.

Claims

1. An aircraft cover quick release lock mechanism, characterized in that: The quick-release lock mechanism comprises a lock key support (1), a lock key bushing (2), a lock housing (3), a shift fork (4), an adjustable support (6), a lock tongue (7), a slider (8), a compression spring (10), and an unlocking slender rod (13); The key lock support (1) is fixedly connected to the cover, and the key lock bushing (2) is hinged on the key lock support (1); The lock housing (3) is fixedly connected to the fuselage frame, and the adjustable support (6) is fixedly connected to the fuselage structure web, and the two form a box-shaped structure. Through holes are formed on the adjustable support (6) and on the opposite surface of the lock housing (3) and the adjustable support (6), so that the lock tongue (7) can pass through and slide along its axis. Slide grooves are provided at corresponding positions on the two side walls of the lock housing (3), and a circular hole is provided on the bottom surface, and the circular hole and the lock tongue (7) are arranged in a staggered manner. When the lock tongue (7) is in an extended state, one end thereof protruding from the lock housing (3) is restricted between the lock key bushing (2) and the lock key support (1), and this position is a locking position of the quick release lock mechanism. When the lock tongue (7) is retracted and moves away from the lock key bushing (2), it is an unlocking position. The end of the lock tongue (7) is formed with an inclined surface, and is used to cooperate with the lock key bushing (2) to achieve self-locking. The sliding block (8) vertically passes through the lock tongue (7), and its two ends are restricted in the slide groove of the lock housing (3), and can slide along the slide groove; The compression spring (10) is passed through the lock tongue (7), and its two ends are pressed tightly against the adjustable support (6) and the slider (8), so that the lock tongue (7) always maintains a tendency to extend; The two ends of the shift fork (4) are hinged on the two side walls of the lock housing (3), and are located on the upper side of the lock tongue (7), and the slider (8) is between the two fork heads. A groove is arranged on the fork head of the shift fork (4) facing the circular hole on the bottom surface of the lock housing (3). When unlocking, a slender rod (13) for unlocking passes through the circular hole and is pushed into the groove to push the shift fork (4) to rotate, and the other fork head of the shift fork (4) moves the slider (8) to drive the lock tongue (7) to contract to achieve unlocking.

2. The aircraft cover quick release lock mechanism according to claim 1, characterized in that: A support plate nut (5) is fixed at the circular hole position on the bottom surface of the lock housing (3), and a threaded fastener (11) cooperates with the support plate nut (5) to seal the circular hole on the bottom surface of the lock housing (3). The threaded fastener (11) is removed when unlocking.

3. The aircraft cover quick release lock mechanism according to claim 1, characterized in that: The shift fork (4) is provided with a torsion spring (9), the two ends of which act on the side wall of the lock housing (3) and the shift fork (4) respectively. When the lock tongue (7) is in an extended state, under the action of the torsion spring (9), a certain gap is maintained between the fork head of the shift fork (4) without a groove and the slider (8), so as to knock the slider (8) to break ice when the quick release lock mechanism is stuck.

4. The aircraft cover quick release lock mechanism according to claim 3, characterized in that: When the locking tongue (7) is in the extended state, a gap of 2.5 mm is maintained between the fork head of the shift fork (4) without a groove and the slider (8).

5. The aircraft cover quick release lock mechanism according to claim 1, characterized in that: The spring force of the compression spring (10) should ensure that under any overload, the lock tongue (7) will not escape from the lock key bushing (2) due to inertia force.

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