An electric locking mechanism applicable to carriers in a launch box

Abstract

The present invention discloses an electric locking mechanism applicable to a carrier in a launch box, which includes a cylinder barrel and a screw rod. An insertion pin is arranged inside the cylinder barrel. One end of the insertion pin is provided with a pin head and the other end is provided with a hole groove. A long nut is screwed in the hole groove, and the long nut is fixed to the insertion pin through a set screw. One end of the screw rod is screwed into the long nut and then extends into the hole groove of the insertion pin. The other end of the screw rod passes through a speed reducer and is fixedly connected to an internal transmission member of the speed reducer through a flat key. A visualization component is arranged on the cylinder barrel body of the cylinder barrel. The visualization component includes a spring mounting seat connected to the cylinder barrel body through screws. A guide groove is arranged on the cylinder barrel corresponding to the spring mounting seat. Two indexing pins are arranged on the spring mounting seat, and a sliding pin is arranged on the guide groove. The sliding pin is inserted on the outer wall of the insertion pin. The present invention drives the indexing pin through the sliding pin, realizes the visualization of the unlocking and locking of the insertion pin, and improves the safety of locking the carrier in the launch box.

Description

Technical Field

[0001] The present invention relates to the technical field of locking mechanisms, and particularly to an electric locking mechanism applicable to a carrier in a launch box. Background Art

[0002] Locking mechanisms are widely used in occasions where two components need to be connected and locked. Mechanical locking mechanisms are applied in different occasions according to different requirements.

[0003] The launch box is one of the important equipment in aerospace. The launch box has three functions. As a transport box, the carrier is placed on the guide rails inside the box, and buffer and positioning locking devices are used to prevent the carrier from being damaged due to impact and vibration during transportation. As a storage box, there is a temperature control device inside the box, which is filled with nitrogen and dry air, and the storage period can be extended after sealing. As a launch box, there are launch guide rails, a safety locking mechanism and cables inside the box, which are connected to the launch control system to implement pre-launch inspection, aiming and launch.

[0004] During the braking condition of the carrier in the launch box during transportation, if there is no limiting device, the carrier in the launch box will move forward due to inertia and damage the launch box cover, and may even slide out of the launch box, causing accidents. Therefore, it is necessary to lock and limit the carrier through a locking device during transportation. When the carrier is launched or taken out of the box, the limit needs to be released. Therefore, it is required that the locking device can lock and unlock.

[0005] Chinese Patent CN106500545A relates to a launch box locking mechanism, belonging to the field of aircraft technical support. The invention has a simple structure, low cost and short manufacturing cycle. Only the front locking device and the rear locking device can limit the front-back, left-right and up-down movements of the launch box. Among them, the up-down and left-right movements of the launch box feet are unlocked or locked by the movement of the sliding block. The front-back movement of the launch box feet is unlocked or locked by the movement of the screws on the positioning block. Moreover, the screw rod uses a trapezoidal thread and is self-locking during loading to ensure that the sliding block presses the launch box feet. Through experimental verification, the invention can quickly and safely lock the launch box.

[0006] With the progress of the times, the requirements for the locking device of the carrier in the launch box are becoming more and more strict. At present, the locking mechanism needs to lock the carrier inside the launch box. During operation, personnel are not allowed to enter, and it needs to be electrically controlled outside the launch box. It is also necessary to judge the working state of the plug outside the launch box. However, the traditional locking devices are all manually controlled and cannot meet the requirements. If it is changed to electric control, when connecting with the carrier, the working state of the plug inside the launch box cannot be judged outside, and an automatic recognition function is required. When power failure or maintenance occurs, the electric control fails, and personnel operation is required, and the automatic recognition fails, there is a hidden danger of safety accidents. Summary of the Invention

[0007] Aiming at the deficiencies of the prior art, the technical problem to be solved by the present invention is to provide an electric locking mechanism that can axially lock and unlock the carrier in the launch box and can automatically identify and visually identify the working state of the bolt.

[0008] To achieve the above object, the present invention provides the following technical solutions:

[0009] An electric locking mechanism applicable to the carrier in the launch box, comprising a speed reducer, a cylinder barrel, a bolt, and a screw rod. The cylinder barrel is internally provided with a bolt. One end of the bolt is provided with a bolt head, and the other end of the bolt is provided with a hole groove. A long nut is screwed in the hole groove. After the long nut is inserted into the bolt, it is fixed to the bolt by a set screw. The screw rod is threadedly connected to the long nut. One end of the screw rod with threads is screwed into the long nut and extends into the hole groove of the bolt. The middle part of the screw rod is located inside the cylinder barrel. The end of the screw rod away from the bolt head passes through the speed reducer, and the screw rod is fixedly connected to the internal transmission part of the speed reducer through a flat key;

[0010] A visualization component is provided on the cylinder barrel body. The visualization component includes a spring mounting seat connected to the cylinder barrel body by screws. A guide groove is provided on the cylinder barrel body corresponding to the spring mounting seat. A first indexing pin and a second indexing pin are arranged on the spring mounting seat. A sliding pin is provided on the guide groove. The sliding pin is inserted on the outer wall of the bolt, and one end of the sliding pin close to the spring mounting seat is processed with an inclined surface.

[0011] Preferably, the head and tail of the bolt head are both circular, and the head and tail of the bolt head are connected by an arc surface. The radian of the arc surface is 1.2 - 1.3, and there is a gap between the tail of the bolt head and the inner wall of the cylinder barrel.

[0012] Preferably, a first sensor and a second sensor are provided on the cylinder barrel. A sensor adjustment seat is provided on the second sensor, and the sensor adjustment seat is fixed to the cylinder barrel by screws.

[0013] Preferably, a transition flange is provided at the end of the cylinder barrel close to the speed reducer. The transition flange is connected to the output flange provided on the speed reducer by bolts, and a servo motor is connected to the input flange of the speed reducer by screws.

[0014] Preferably, the outer ends of the first indexing pin and the second indexing pin are flush with the outer surface of the spring mounting seat. When the sliding pin contacts the first indexing pin or the second indexing pin, the outer end of the first indexing pin or the second indexing pin extends out of the spring mounting seat.

[0015] Preferably, a sealing ring is provided at the end of the cylinder barrel close to the speed reducer. The sealing ring passes through the screw rod and is fixed to the end of the cylinder barrel by flat head screws.

[0016] Preferably, a positioning shoulder is provided on the screw rod. A tapered roller bearing is provided between the left end of the positioning shoulder and the inner wall of the end of the cylinder barrel. A single-direction thrust cylindrical roller bearing is provided at the outer end of the cylinder barrel away from the pin head. A retaining washer and a round nut are sequentially provided at the outer end of the single-direction thrust cylindrical roller bearing. The retaining washer and the round nut are sleeved on the screw rod, and the round nut is located inside the sealing ring.

[0017] Preferably, an installation flange is sleeved on the outer wall of the cylinder barrel. The installation flange is connected to the launch box, and a part of the cylinder barrel near the pin head on one side of the installation flange is inserted into the installation hole of the launch box.

[0018] Preferably, a straight-through grease cup is provided on the cylinder barrel body.

[0019] Preferably, a manual wrench position is provided at the end of the screw rod away from the pin head.

[0020] Compared with the prior art, the present invention has the following beneficial effects:

[0021] (1) In the present invention, the screw rod is driven by a servo motor and a speed reducer for transmission. The screw rod drives the plug pin to move forward or backward through the screw drive with the long nut, and controls the locking and unlocking states of the plug pin. The screw rod and the long nut in the present invention make the long nut move forward through the screw drive mode, thereby driving the plug pin to move forward to achieve locking and unlocking in a labor-saving manner. At the same time, through the structural design of the pin head, the device is more labor-saving and locks tighter. The structure of the present invention is compact and reliable, and has high practicability. During operation, no manual operation is required.

[0022] (2) In the present invention, through the visualization component provided on the cylinder barrel, the different ejection states of the first indexing pin and the second indexing pin are driven by the screw rod transmission to judge whether the plug pin is locked or unlocked. The structure is ingenious, which can prevent the mechanism from being unable to judge the state when the sensor fails, resulting in safety accidents. At the same time, in the state of maintenance or power failure, by rotating the manual wrench position, the screw rod and the long nut can also make the long nut move forward through the screw drive mode, thereby driving the plug pin to move forward to achieve locking and unlocking. The operation of the locking mechanism can be manually controlled. Moreover, for the carrier in the launch box, the unlocking or locking state of the plug pin can also be known through the visualization component, which can prevent damage to the carrier and accidents. The present invention has the functions of being visible to the naked eye and automatic recognition through the visualization component and two sensors provided on the cylinder barrel, and plays a dual protection role when observing the working state of the plug pin unlocking or locking. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] Figure 1 is a schematic cross-sectional structure diagram of an electric locking mechanism applicable to a carrier in a launch box of the present invention;

[0024] Figure 2 is a top view schematic diagram of an electric locking mechanism for a carrier inside a launch box according to the present invention;

[0025] Figure 3 is a partial enlarged schematic diagram of an electric locking mechanism for a carrier inside a launch box according to the present invention;

[0026] Wherein: 1, speed reducer; 2, cylinder barrel; 3, bolt; 4, screw rod; 5, pin head; 6, long nut; 7, set screw; 8, tapered roller bearing; 9, single-direction thrust cylindrical roller bearing; 10, sealing ring; 11, flat key; 12, sliding pin; 13, first indexing pin; 14, second indexing pin; 15, spring mounting seat; 16, first sensor; 17, second sensor; 18, sensor adjustment seat; 19, transition flange; 21, manual wrench position; 22, straight-through grease cup; 23, mounting flange; 24, positioning shoulder. Specific embodiments

[0027] The following describes the preferred embodiments of the present invention with reference to the accompanying drawings of the specification. It should be understood that the preferred embodiments described herein are only for the purpose of illustrating and explaining the present invention, and are not used to limit the present invention. And without conflict, the embodiments in the present invention and the features in the embodiments can be combined with each other.

[0028] Embodiment 1

[0029] An electric locking mechanism for a carrier inside a launch box includes a speed reducer 1, a cylinder barrel 2, a bolt 3, and a screw rod 4. The cylinder barrel 2 is internally provided with the bolt 3. One end of the bolt 3 is provided with a pin head 5, and the other end of the bolt 3 is provided with a hole groove. A long nut 6 is screwed in the hole groove. After the long nut 6 is inserted into the bolt 3, it is fixed to the bolt 3 by a set screw 7. The screw rod 4 is in threaded connection with the long nut 6. After the threaded end of the screw rod 4 is screwed into the long nut 6, it extends into the hole groove of the bolt 3. The middle part of the screw rod 4 is located inside the cylinder barrel 2. The end of the screw rod 4 away from the pin head 5 passes through the speed reducer 1, and the screw rod 4 is fixedly connected to the internal transmission member of the speed reducer 1 through a flat key 11;

[0030] The cylinder barrel 2 is provided with a visualization component on its barrel body. The visualization component includes a spring mounting seat 15 connected to the barrel body of the cylinder barrel 2 by screws. A guide groove is provided on the barrel body of the cylinder barrel 2 corresponding to the spring mounting seat 15. The spring mounting seat 15 is provided with a first indexing pin 13 and a second indexing pin 14. A sliding pin 12 is provided on the guide groove. The sliding pin 12 is inserted on the outer wall of the bolt 3. One end of the sliding pin 12 close to the spring mounting seat 15 is processed with an inclined surface.

[0031] When the screw rod 4 rotates, it drives the long nut 6 to move. Since the pin 3 is fixedly connected to the long nut 6, the pin 3 also moves accordingly. The movement of the pin 3 drives the sliding pin 12 to move, and further when the mandrels of the first indexing pin 13 and the second indexing pin 14 are ejected, the locking or unlocking state of the locking mechanism is visualized.

[0032] In this embodiment, the head and the tail of the pin head 5 are both circular, and the head and the tail of the pin head 5 are connected by an arc surface. The radian of the arc surface is 1.25, and there is a gap between the tail of the pin head 5 and the inner wall of the cylinder barrel 2.

[0033] In this embodiment, a first sensor 16 and a second sensor 17 are provided on the cylinder barrel 2. A sensor adjustment seat 18 is sleeved on the second sensor 17, and the sensor adjustment seat 18 is fixed on the cylinder barrel 2 by screws. The first sensor 16 and the second sensor 17 can automatically identify the locking or unlocking state of the lock.

[0034] In this embodiment, a transition flange 19 is provided at the end of the cylinder barrel 2 close to the speed reducer 1. The transition flange 19 is connected to the output flange provided on the speed reducer 1 by bolts. The input flange of the speed reducer 1 is connected with a servo motor by screws. The cylinder barrel 2 and the speed reducer 1 are connected by the transition flange 19 and the output flange, so that the positional relationship among the screw rod 4, the cylinder barrel 2 and the speed reducer 1 is stable and the overall structure is safe; the speed reducer 1 is connected with the servo motor to provide power for the whole mechanism.

[0035] In this embodiment, the outer ends of the first indexing pin 13 and the second indexing pin 14 are flush with the outer surface of the spring mounting seat 15. When the sliding pin 12 contacts the first indexing pin 13 or the second indexing pin 14, the outer ends of the first indexing pin 13 or the second indexing pin 14 extend out of the spring mounting seat 15. When the mandrel of the first indexing pin 13 is ejected, the pin head 5 is inside the cylinder barrel 2 and the locking mechanism is in the unlocked state. When the mandrel of the second indexing pin 14 is ejected, the pin head 5 extends out of the cylinder barrel 2 and the locking mechanism is in the locked state.

[0036] In this embodiment, a sealing ring 10 is provided at one end of the cylinder barrel 2 close to the speed reducer. The sealing ring 10 passes through the screw rod 4 and is fixed to the end of the cylinder barrel 2 by flat head screws. The sealing ring 10 can prevent oil leakage and external sundries from entering the cylinder barrel and affecting the use.

[0037] In this embodiment, a positioning shoulder 24 is provided on the screw rod 4. A tapered roller bearing 8 is provided between the left end of the positioning shoulder 24 and the inner wall of the end of the cylinder barrel 2. A single-direction thrust cylindrical roller bearing 9 is provided at the outer end of the cylinder barrel 2 away from the pin head 5. A stop washer and a round nut are successively provided at the outer end of the single-direction thrust cylindrical roller bearing 9. The stop washer and the round nut are sleeved on the screw rod 4, and the round nut is located inside the sealing ring. The installation of the tapered roller bearing 8 and the single-direction thrust cylindrical roller bearing 9 can support the rotation of the screw rod, reduce the friction coefficient during its movement, and ensure its rotation accuracy.

[0038] In this embodiment, an installation flange 23 is sleeved on the outer wall of the cylinder barrel 2. The installation flange 23 is connected to the launch box, and a part of the cylinder barrel 2 near the pin head 5 on one side of the installation flange 23 is inserted into the installation hole of the launch box.

[0039] In this embodiment, a straight-through grease cup 22 is provided on the cylinder barrel 2 of the cylinder body.

[0040] In this embodiment, a manual wrench position 21 is provided at the end of the screw rod 4 away from the pin head 5. When there is a power outage or during fault repair, the manual wrench position 21 can be rotated to ensure the normal use of the locking mechanism.

[0041] The working principle of an electric locking mechanism of the present invention applicable to a carrier in a launch box is as follows:

[0042] Connect the installation flange 23 to the launch box. The plug pin 3 and the cylinder barrel 2 near one end of the plug pin 3 extend into the interior of the launch box. Start the servo motor, and the servo motor drives the reduction gear 1 to drive the screw rod 4. When the screw rod 4 drives the sliding pin 12 on the plug pin 3 to slide to the position of the first indexing pin 13, the core shaft of the first indexing pin 13 is ejected, that is, the unlocked state can be seen externally. When the screw rod 4 drives the sliding pin 12 to slide past the first indexing pin 13 and reaches the position of the second indexing pin 14, the core shaft of the first indexing pin 13 returns, and the core shaft of the second indexing pin 14 is ejected. At this time, the pin head 5 of the plug pin 3 extends out of the cylinder barrel 2 and is connected to the carrier, presenting a locked state. When the plug pin 3 is in a locked or unlocked state, the first sensor 16 and the second sensor 17 on the cylinder barrel 2 can automatically identify the state of the plug pin 3, playing a dual protection role for transportation. When there is a power outage or during maintenance, the servo motor and the sensor cannot be used. By rotating the manual wrench position 21, the plug pin 3 can be telescopically extended and retracted, and through the visualization component, the locked or unlocked state of the plug pin 3 can be observed.

[0043] The basic concepts have been described above. Obviously, for those skilled in the art, the above detailed disclosure is only an example and does not constitute a limitation to this specification. Although not explicitly stated here, those skilled in the art may make various modifications, improvements, and deviations to this specification. Such modifications, improvements, and deviations are recommended in this specification, so such modifications, improvements, and deviations still fall within the spirit and scope of the exemplary embodiments of this specification.

[0044] In addition, those skilled in the art can understand that various aspects of this specification can be illustrated and described by several patentable types or situations, including any new and useful processes, machines, products, or combinations of substances, or any new and useful improvements to them. Accordingly, various aspects of this specification can be executed entirely by hardware, entirely by software including firmware, resident software, microcode, etc., or by a combination of hardware and software. The above hardware or software can all be referred to as "data blocks", "modules", "engines", "units", "components", or "systems". In addition, various aspects of this specification may be embodied as a computer product located in one or more computer-readable media, which includes computer-readable program codes.

[0045] It should be noted that if there are inconsistencies or conflicts between the descriptions, definitions, and / or uses of terms in the supplementary materials of this specification and the content described in this specification, the descriptions, definitions, and / or uses of terms in this specification shall prevail.

[0046] Finally, it should be understood that the embodiments described in this specification are only used to illustrate the principles of the embodiments of this specification. Other variations may also fall within the scope of this specification. Therefore, by way of example and not limitation, alternative configurations of the embodiments of this specification can be considered to be consistent with the teachings of this specification. Accordingly, the embodiments of this specification are not limited to those explicitly introduced and described in this specification.

Claims

1. An electric locking mechanism applicable to a carrier in a launch box, comprising a speed reducer (1), a cylinder barrel (2), a bolt (3), and a screw rod (4). It is characterized in that: A bolt (3) is arranged inside the cylinder barrel (2). One end of the bolt (3) is provided with a bolt head (5), and the other end of the bolt (3) is provided with a hole groove. A long nut (6) is screwed in the hole groove. After the long nut (6) is inserted into the bolt (3), it is fixed to the bolt (3) by a set screw (7). The screw rod (4) is in threaded connection with the long nut (6). After the threaded end of the screw rod (4) is screwed into the long nut (6), it extends into the hole groove of the bolt (3). The middle part of the screw rod (4) is located inside the cylinder barrel (2). The end of the screw rod (4) far from the bolt head (5) passes through the speed reducer (1), and the screw rod (4) is fixedly connected to the internal transmission part of the speed reducer (1) through a flat key (11). A visualization component is arranged on the cylinder barrel (2) of the cylinder. The visualization component comprises a spring mounting seat (15) connected to the cylinder barrel (2) by screws. A guide groove is arranged on the cylinder barrel (2) corresponding to the spring mounting seat (15). A first indexing pin (13) and a second indexing pin (14) are arranged on the spring mounting seat (15). A sliding pin (12) is arranged on the guide groove. The sliding pin (12) is inserted on the outer wall of the bolt (3), and one end of the sliding pin (12) close to the spring mounting seat (15) is processed with an inclined surface.

2. An electric locking mechanism applicable to a carrier in a launch box according to claim 1. It is characterized in that: The head and tail of the bolt head (5) are both circular. The head and tail of the bolt head (5) are connected by an arc surface. The radian of the arc surface is 1.2 - 1.

3. A gap is arranged between the tail of the bolt head (5) and the inner wall of the cylinder barrel (2).

3. An electric locking mechanism applicable to a carrier in a launch box according to claim 1. It is characterized in that: A first sensor (16) and a second sensor (17) are arranged on the cylinder barrel (2). A sensor adjustment seat (18) is arranged on the second sensor (17). The sensor adjustment seat (18) is fixed to the cylinder barrel (2) by screws.

4. An electric locking mechanism applicable to a carrier in a launch box according to claim 1. It is characterized in that: A transition flange (19) is arranged at the end of the cylinder barrel (2) close to the speed reducer (1). The transition flange (19) is connected to the output flange arranged on the speed reducer (1) by bolts. The input flange of the speed reducer (1) is connected with a servo motor by screws.

5. An electric locking mechanism applicable to a carrier in a launch box according to claim 1. It is characterized in that: The outer ends of the first indexing pin (13) and the second indexing pin (14) are flush with the outer surface of the spring mounting seat (15). When the sliding pin (12) contacts the first indexing pin (13) or the second indexing pin (14), the outer end of the first indexing pin (13) or the second indexing pin (14) extends out of the spring mounting seat (15).

6. An electric locking mechanism applicable to a carrier in a launcher box according to claim 1, characterized in that: A sealing ring (10) is provided at one end of the cylinder barrel (2) close to the speed reducer. After the sealing ring (10) penetrates the screw rod (4), it is fixed to the end of the cylinder barrel (2) by a flat head screw.

7. An electric locking mechanism applicable to a carrier in a launcher box according to claim 6, characterized in that: A positioning shoulder (24) is provided on the screw rod (4). A tapered roller bearing (8) is provided between the left end of the positioning shoulder (24) and the inner wall of the end of the cylinder barrel (2). A single-direction thrust cylindrical roller bearing (9) is provided at the outer end of the cylinder barrel (2) away from the pin head (5). A stop washer and a round nut are sequentially provided at the outer end of the single-direction thrust cylindrical roller bearing (9). The stop washer and the round nut are sleeved on the screw rod (4), and the round nut is located inside the sealing ring (10).

8. An electric locking mechanism applicable to a carrier in a launcher box according to claim 1, characterized in that: An installation flange (23) is sleeved on the outer wall of the cylinder barrel (2). The installation flange (23) is connected to the launcher box. A part of the cylinder barrel (2) on one side of the installation flange (23) close to the pin head (5) is inserted into the installation hole of the launcher box.

9. An electric locking mechanism applicable to a carrier in a launcher box according to claim 1, characterized in that: A straight-through grease cup (22) is provided on the cylinder barrel (2) body.

10. An electric locking mechanism applicable to a carrier in a launcher box according to claim 1, characterized in that: A manual wrench position (21) is provided at the end of the screw rod (4) away from the pin head (5).

Images