A self-unlocking firing box lock and spring device

Abstract

This invention belongs to the field of missile launch technology, specifically relating to a self-unlocking launch box missile locking device to improve the low quality and economy of traditional automatic missile locking devices. It includes a missile locking actuation component, a tensioning component, and an adjustment component disposed within the launch box. A connecting belt connects the tensioning component and the adjustment component, with the tensioning component applying tension to the connecting belt, which is designed to break under the impact of high-temperature combustion gases. The missile locking actuation component is connected to the adjustment component. When the connecting belt is tensioned, the adjustment component drives the missile locking actuation component to lock the missile's orientation button. When the connecting belt breaks, the adjustment component releases the missile locking actuation component from the missile's orientation button. This self-unlocking launch box missile locking device achieves automatic pre-positioning, rapid locking, and automatic mechanism operation of the missile through a purely mechanical structure, and is easy to assemble, adjust, and maintain, resulting in high quality and economy.

Description

Technical Field

[0001] This invention belongs to the field of missile launch technology, and more specifically, relates to a self-unlocking launch box locking device. Background Technology

[0002] A missile launcher is a device used to load and launch missiles. It protects and supports the missiles, ensuring their safe launch.

[0003] In related technologies, launch boxes mostly adopt mechanical manual locking devices. Mechanical manual locking devices have a relatively simple structure and low cost, but because they require manual unlocking, they are difficult to meet the self-unlocking launch requirements commonly needed by multi-launcher systems.

[0004] Therefore, some design schemes incorporate an automatic missile locking device powered by a hydraulic cylinder or motor within the launch box. While this automatic locking device, powered by a hydraulic cylinder or motor, can automatically lock and unlock the missile through electrical components and a control system to meet the self-unlocking launch requirements of multi-launch systems, its production and maintenance costs are higher than purely mechanical devices. This results in lower quality-economic efficiency and hinders the overall quality-economic improvement of the weapon system, necessitating urgent improvement. Summary of the Invention

[0005] To improve the quality and economy of automatic cartridge locking devices, this invention provides a self-unlocking cartridge locking device for firing boxes.

[0006] The present invention provides a self-unlocking launch box locking device, which adopts the following technical solution:

[0007] A self-unlocking launch box missile locking device includes a missile locking actuation component, a tensioning component, and an adjustment component disposed in the launch box, wherein: a connecting belt is provided between the tensioning component and the adjustment component, the tensioning component is used to apply tension to the connecting belt, and the connecting belt is capable of breaking under the impact of high-temperature gas combustion; the missile locking actuation component is connected to the adjustment component, the adjustment component drives the missile locking actuation component to lock the missile's orientation button when the connecting belt is tensioned, and the adjustment component releases the missile locking actuation component from locking the missile's orientation button when the connecting belt breaks.

[0008] By adopting the above technical solution, the missile locking mechanism can lock the missile orientation button when the connecting belt is tightened. During missile ignition and launch, the high-temperature combustion gases impact the connecting belt, causing it to break under the impact and ablation of the gases, thus releasing the missile from the locking mechanism's constraint. Compared to traditional box-type missile locking devices with electrical components and control systems, this device meets the requirements for automatic unlocking without the involvement of electrical components and control systems. This results in low cost, ease of assembly, adjustment, and maintenance, and high cost-effectiveness.

[0009] As a further preferred embodiment, the missile locking and actuation assembly includes a sliding plate, a slider, and locking hooks; the sliding plate is connected to the launch box, and a guide groove is provided on the sliding plate, the extension direction of the guide groove being consistent with the missile launch direction; the slider is slidably installed in the guide groove, and the end of the slider away from the launch outlet of the launch box is connected to an adjustment assembly; two locking hooks are rotatably connected to the end of the slider near the launch outlet of the launch box; when the connecting band is tightened, the adjustment assembly tightens the slider, and the two locking hooks are restrained and clamped by the inner wall of the guide groove to form a directional button clamping cavity; when the connecting band breaks, the adjustment assembly releases the slider, and the directional button can drive the two locking hooks to move, causing the two locking hooks to protrude out of the guide groove, causing the two locking hooks to open and release the restraint on the positioning button.

[0010] By adopting the above technical solution, when the connecting belt is tightened, the adjusting component tightens the slider, and the two locking hooks are limited and clamped by the inner wall of the guide groove to form the directional button clamping cavity. The missile's guide button is clamped and positioned by the two locking hooks, realizing the locking and positioning of the missile in the launch box. When the missile is ignited and launched, the connecting belt breaks due to high temperature, and then the adjusting component releases the slider, so that the slider is no longer locked. At this time, the missile can drive the two locking hooks to move through the directional button, so that the two locking hooks protrude out of the guide groove. When the locking hooks protrude out of the guide groove, the inner wall of the guide groove no longer restricts the locking hooks. The directional button pulls the locking hooks to open the two locking hooks, and the locking hooks no longer limit the positioning button, realizing the missile's self-unlocking.

[0011] As a further preferred embodiment, the slider is connected to two leaf springs, each of which corresponds to one of the two locking hooks, and the two leaf springs drive the two locking hooks to rotate and open.

[0012] By adopting the above technical solution, after the two locking hooks protrude from the guide groove, the leaf spring can drive the two locking hooks to rotate and open through elastic force, so that the two locking hooks open on their own and release the lock on the missile orientation button.

[0013] As a further preferred embodiment, the adjustment assembly includes a lower support, a connecting rod assembly, and a flip arm rotatably mounted on the lower support. The lower support is connected to the launch box. One end of the connecting rod assembly is connected to the end of the slider away from the launch outlet of the launch box, and the other end is connected to a connector. The front end of the flip arm is bent to form a hooking part for hooking and connecting the connector. The rear end of the flip arm is connected to the connecting belt. When the connecting belt is tightened, the connecting belt pulls the flip arm, and the hooking part of the flip arm flips until the connecting rod assembly is hooked and positioned on the surface of the lower support.

[0014] By adopting the above technical solution, the tilting arm can simultaneously hook the connector of the connecting rod assembly when the connecting belt is tightened, allowing the missile locking actuator to be quickly locked, thus achieving rapid locking of the missile inside the launch box. After the connecting belt breaks, the tilting arm no longer hooks the connecting rod assembly, causing the missile locking actuator to release the lock on the missile's orientation button.

[0015] As a further preferred embodiment, the connecting rod assembly includes a pull rod and an extension rod. One end of the pull rod is connected to the end of the slider away from the launch outlet of the launch box, and the other end of the pull rod is detachably connected to the extension rod. The end of the extension rod away from the pull rod is fixedly connected to the connector.

[0016] By adopting the above technical solution, the pull rod and extension rod allow the adjustment component to tighten and loosen the slider, thereby meeting the locking and unlocking requirements of the missile in the launch box. When the connecting belt and adjustment component are adapted and installed at the tail of the missile, the pull rod and extension rod transmit the force of the adjustment component on the slider, allowing the missile locking actuator to be adapted to the locking and positioning of the missile's side positioning button. This results in a reasonable layout of the device, effective control of the launch box's cross-sectional area and length, and improved integration level of the weapon system.

[0017] As a further preferred embodiment, the end of the slide away from the launch outlet of the launch box is connected to an end cap, the end cap having a guide hole for the pull rod to pass through, and the end cap having an internal elastic element that applies a thrust to the slide away from the end cap.

[0018] By adopting the above technical solution, the end cap can guide the pull rod and limit the end of the slider away from the launch outlet of the launcher, making the operation of the device more stable; while the elastic element can apply elastic thrust to the slider, so that when the launch box is not loaded with missiles, the two locking hooks protrude from the guide groove, which facilitates the subsequent clamping of the missile launch button loaded into the launch box by the two locking hooks.

[0019] As a further preferred embodiment, the tensioning assembly includes an upper support, a tensioning rod, and a tensioning bolt. The upper support is connected to the launch box, the tensioning rod is movable on the upper support and connected to the connecting belt, and the tensioning bolt is threadedly connected to the upper support. The rod portion of the tensioning bolt abuts against the surface of the tensioning rod, and the tensioning bolt drives the tensioning rod away from the adjustment assembly.

[0020] By adopting the above technical solution, during use, the operator tightens the tension bolt by turning the knob, causing the rod of the tension bolt to spiral into the upper support, so that the tension rod moves away from the adjustment component under the push of the tension bolt, thereby realizing the adjustment of the tension of the connecting belt.

[0021] As a further preferred embodiment, the tensioning assembly further includes a locking nut, which is threaded onto the shank of the tensioning bolt and can be detachably pressed against the surface of the upper support.

[0022] By adopting the above technical solution, after the connecting belt is adjusted to a suitable tension, the operator tightens the locking nut so that the locking nut abuts against the surface of the upper support, thereby securing the tension bolt on the upper support.

[0023] As a further preferred embodiment, it also includes a guide rail fixed to the inner wall of the launch box, the guide rail having a track along the missile launch direction, the slide plate slidingly adapting to the track, and the slide plate being fixed in the track by a fixing member.

[0024] By adopting the above technical solution, the track on the guide rail can guide the slide plate, allowing the slide plate to be installed and adjusted in a straight direction inside the launch box, which facilitates the precise matching of the locking hook on the slide plate with the missile's orientation button; when the slide plate is fixed to the guide rail by the fastener, the inner wall of the track limits and reinforces the slide plate, improving the installation stability of the slide plate inside the launch box.

[0025] In summary, the present invention has at least the following beneficial technical effects:

[0026] 1. The locking mechanism is designed to lock the missile orientation button when the connecting belt is tightened. During missile ignition and launch, the high-temperature gas impacts the connecting belt, causing it to break under the impact and ablation of the gas, thus releasing the missile from the locking mechanism. Compared to traditional cylinder and motor-driven unlocking box-type missile locking devices, this device has no electrical components or control system involved, making it easy to assemble, adjust, and maintain. This allows the device to meet the requirements of automatic unlocking while maintaining high quality and economy.

[0027] 2. When loading the missile into the launch box, the positioning button on the missile presses the slider, causing the slider to slide and drive the two locking hooks into the guide groove. Then, the two locking hooks clamp the missile's orientation button, realizing the automatic pre-positioning of the missile's orientation button, eliminating the need for operators to adjust the missile locking mechanism. During this process, the slider will drive the connecting rod assembly, causing the connector at the end of the connecting rod assembly to move closer to the tilting arm. The operator located at the rear of the launch box can intuitively judge that the missile is in the pre-locked position inside the launch box based on the movement of the connector, shortening the inspection time for the missile loading status.

[0028] 3. The operator tensions the connecting belt using the tensioning assembly, causing the hook of the tilting arm to flip until the connecting head on the connecting rod assembly is hooked and positioned on the surface of the lower support, locking the slider and the locking hook on the slider. The two locking hooks are limited and clamped by the inner wall of the guide groove to form a directional button clamping cavity, clamping and positioning the missile's guide button inside the launch box, thus achieving rapid locking of the missile inside the launch box.

[0029] 4. When the missile is ignited and launched, the connecting belt breaks due to high temperature. The flip arm, which loses the tension of the connecting belt, no longer hooks the connecting rod assembly, so that the slider is no longer locked. At this time, the missile can drive the two locking hooks to move through the directional button, so that the two locking hooks protrude out of the guide groove. After the locking hooks protrude out of the guide groove, the inner wall of the guide groove no longer restricts the locking hooks. Then the spring drives the two locking hooks to open, so that the missile's positioning button quickly disengages from the locking hooks, realizing the missile's self-unlocking. Attached Figure Description

[0030] Figure 1 This is a schematic diagram of the overall structure of the self-unlocking launch box locking device in an embodiment of the present invention;

[0031] Figure 2 This is an exploded view of the locking mechanism in an embodiment of the present invention;

[0032] Figure 3 This is a cross-sectional view of the slider and pull rod in an embodiment of the present invention;

[0033] Figure 4 This is a cross-sectional view of the structure when the two locking hooks are retracted into the guide groove in an embodiment of the present invention;

[0034] Figure 5 This is a schematic diagram of the structure of the adjustment component in an embodiment of the present invention;

[0035] Figure 6 This is an exploded view of the lower support and the tilting arm in an embodiment of the present invention;

[0036] Figure 7 This is a schematic diagram of the overall structure of the connecting strip in an embodiment of the present invention;

[0037] Figure 8This is a schematic diagram of the tensioning component in an embodiment of the present invention.

[0038] In all the accompanying drawings, the same reference numerals are used to denote the same elements or structures, wherein:

[0039] 1. Launch box; 2. Locking mechanism; 21. Slide plate; 211. Guide groove; 22. Slider; 23. Locking hook; 24. Leaf spring; 25. Cover plate; 251. Notch; 26. End cap; 27. Elastic element; 3. Tensioning assembly; 31. Upper support; 311. Plate; 312. Rib; 32. Tensioning rod; 33. Tensioning bolt; 34. Locking nut; 4. Adjusting assembly; 41. Lower support; 411. Limiting plate; 42. Connecting rod assembly; 421. Pull rod; 422. Extension rod; 423. Screw sleeve; 43. Tilting arm; 431. Hook pull part; 44. Connector; 5. Connecting belt; 51. Magnesium strip; 52. Perforated clamping head; 6. Guide rail; 60. Track. Detailed Implementation

[0040] To make the objectives, technical solutions, and advantages of this invention clearer, the invention will be further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative and not intended to limit the invention.

[0041] In the description of this invention, it should be understood that the terms "center," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "inner," "outer," "clockwise," "counterclockwise," "axial," "radial," and "circumferential" indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this invention.

[0042] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of this invention, "a plurality of" means two or more, unless otherwise explicitly specified.

[0043] In this invention, unless otherwise explicitly specified and limited, the terms "installation," "connection," "linking," and "fixing," etc., should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in this invention according to the specific circumstances.

[0044] The following is in conjunction with the appendix Figure 1-8 The present invention will be described in further detail below.

[0045] This invention discloses a self-unlocking launch box locking device.

[0046] Reference Figure 1-8 The self-unlocking launch box locking device includes a locking actuation component 2, a tensioning component 3, and an adjustment component 4 disposed in the launch box 1. The tensioning component 3 and the adjustment component 4 are disposed on opposite inner walls of the launch box 1, and a connecting band 5 that can break under the impact of high-temperature gas is connected between the tensioning component 3 and the adjustment component 4. The locking actuation component 2 and the adjustment component 4 are located on the same inner wall of the launch box 1, and the locking actuation component 2 and the adjustment component 4 are connected.

[0047] When installing a missile, the connecting strap 5 is tightened, and the adjusting component 4 drives the missile locking actuator 2 to lock the missile's orientation button, thus locking the missile. When the missile is launched, the connecting strap 5 breaks due to the impact and ablation of the high-temperature combustion gases during missile ignition. The adjusting component 4 then releases the missile locking actuator 2 from locking the missile's orientation button, achieving self-unlocking of the missile. Compared to some common methods that use hook-and-pull locking to lock missiles and lock and unlock multiple limiting blocks on the missile, this device is particularly suitable for locking and unlocking small-caliber, multi-launcher missiles that only have one orientation button for locking.

[0048] Furthermore, refer to Figure 2 The missile locking and actuation assembly 2 includes a sliding plate 21, a slider 22, and locking hooks 23. The sliding plate 21 is connected to the launch box 1, and a guide groove 211 is formed on the surface of the sliding plate 21 facing away from the launch box 1. The extension direction of the guide groove 211 is consistent with the missile's launch direction. The slider 22 is slidably installed within the guide groove 211 along its extension direction, and the end of the slider 22 facing away from the launch outlet of the launch box 1 is connected to the adjustment assembly 4. Two locking hooks 23 are rotatably connected to the end of the slider 22 near the launch outlet of the launch box 1 via a rotating shaft. The rotation axes of both locking hooks 23 are perpendicular to the inner wall of the launch box 1 where the sliding plate 21 is located.

[0049] When the connecting belt 5 is tightened, the adjusting component 4 tightens the slider 22, so that the slider 22 and the two locking hooks 23 are fully accommodated in the guide groove 211; then the two locking hooks 23 are limited and hugged by the inner wall of the guide groove 211 to form a directional button clamping cavity, locking the missile's positioning button in the launch box 1, thus realizing the locking of the missile's directional button.

[0050] After the missile is ignited and launched, the connecting belt 5 breaks due to high temperature. Then, the adjusting component 4 releases the slider 22. At this time, the launched missile can move the two locking hooks 23 through the directional button, so that the two locking hooks 23 move out of the guide groove 211. When the locking hooks 23 protrude out of the guide groove 211, since the inner wall of the guide groove 211 no longer restricts the locking hooks 23, the directional button pulls the locking hooks 23, so that the two locking hooks 23 rotate and open, so that the positioning button separates from the locking hooks 23, realizing the missile's self-unlocking.

[0051] As a preferred option, refer to Figure 1 In this embodiment, a guide rail 6 for guiding the installation of the slide plate 21 is fixed on the inner wall of the launch box 1. A track 60 is provided on the guide rail 6 along the launch direction of the missile. The slide plate 21 slides and adapts to the guide rail 6 along the extension direction of the track 60. The slide plate 21 is connected to the guide rail 6 by fasteners such as bolts, rivets, and pins.

[0052] In other embodiments, the slide plate 21 can also be directly fixed to the inner wall of the launch box 1 by bolts or other fasteners.

[0053] Furthermore, refer to Figure 2 , Figure 3 and Figure 4 Two leaf springs 24 are provided on the slider 22, located between the two locking hooks 23, with each leaf spring 24 corresponding to one of the two locking hooks 23. Specifically, one end of the leaf spring 24 is connected to the slider 22, and the other end is bent and protrudes from the surface of the slider 22. The protruding end of the leaf spring 24 abuts against the surface of the locking hook 23, applying a pushing force to the locking hook 23. With this design, the two leaf springs 24 drive the two locking hooks 23 to rotate and open through elastic force, increasing the rotational opening speed of the locking hooks 23 after they protrude from the guide groove 211, facilitating the rapid separation of the directional button and the locking hooks 23.

[0054] Furthermore, refer to Figure 2 The end of the slide plate 21 away from the inner wall of the launch box 1 is connected to a cover plate 25 by bolts. The cover plate 25 covers the guide groove 211 on the slide plate 21. The cover plate 25 also has a notch 251, which allows the missile's directional button to be inserted into the directional button clamping cavity between the two locking hooks 23.

[0055] Furthermore, refer to Figures 1-6The adjusting assembly 4 includes a lower support 41, a connecting rod assembly 42, and a tilting arm 43. The lower support 41 is connected to the launch box 1 by bolts. One end of the connecting rod assembly 42 is connected to the end of the slider 22 away from the launch outlet of the launch box 1, and the other end is connected to a connector 44. The middle part of the tilting arm 43 is rotatably mounted on the lower support 41 via a rotating shaft, and the axis of rotation is perpendicular to the sliding direction of the slider 22. The front end of the tilting arm 43 is bent to form a hooking part 431 for hooking the connector 44, and the rear end of the tilting arm 43 is connected to the connecting belt 5 via a connecting shaft.

[0056] When the connecting belt 5 is tightened, the connecting belt 5 pulls the rear end of the flipping arm 43, and then the hook part 431 of the flipping arm 43 flips until the connector 44 on the connecting rod assembly 42 is hooked and positioned on the lower support 41, so that the connector 44 is tightened on the lower support 41.

[0057] Furthermore, the connecting rod assembly 42 includes a pull rod 421 and an extension rod 422. One end of the pull rod 421 is connected to the end of the slider 22 away from the launch outlet of the launch box 1 by a pin. The other end of the pull rod 421 is detachably connected to the extension rod 422 by a screw sleeve 423. The end of the extension rod 422 away from the pull rod 421 is fixedly connected to the connector 44.

[0058] Reference Figure 6 In this embodiment, the connector 44 is a crossbar fixed to the end of the extension rod 422, and the extension rod 422 and the crossbar form a T-shaped rod group. In other embodiments, the connector 44 may also be a toothed plate fixed to the end of the extension rod 422, and the toothed plate has a toothed groove on a surface away from the inner wall of the launch box 1 for the adjustment assembly 4 to hook and connect.

[0059] Furthermore, refer to Figure 6 A limiting plate 411 is fixed on the lower support 41. The limiting plate 411 is located at the end of the tilting arm 43 near the locking spring actuation assembly 2. The surface of the limiting plate 411 has a guide hole for the extension rod 422 to pass through. The limiting plate 411 can block the connector 44 at the end of the extension rod 422, so that the extension rod 422 is prevented from being disengaged from the lower support 41, which facilitates the operator to quickly hook and lock the hook part 431 of the tilting arm 43 to the connector 44.

[0060] Furthermore, refer to Figure 2 and Figure 4 The end of the slide plate 21 facing away from the launch outlet of the launch box 1 is connected to an end cap 26. The end cap 26 has a guide hole for the pull rod 421 to pass through. The end cap 26 has an elastic element 27 inside. The elastic element 27 can be any of the following: spring, sheet, elastic pad, etc. One end of the elastic element 27 is elastically connected to the slider 22, and the opposite end is elastically connected to the inner wall of the end cap 26. The elastic element 27 applies a pushing force to the slider 22 facing away from the end cap 26.

[0061] Before the operator loads the missile into the launch box 1, the connecting belt 5 is in a relaxed state. At this time, under the elastic force of the elastic element 27, the locking hook 23 at the end of the slider 22 protrudes from the guide groove 211, and the connector 44 and the flip arm 43 are separated. At this time, the two locking hooks 23 are in an open state driven by the leaf spring 24, which makes it easy for the missile's positioning button to be assembled in the two locking hooks 23.

[0062] After the operator loads the missile into launch box 1, the positioning button on the missile presses the slider 22, causing the slider 22 to slide and drive the two locking hooks 23 into the guide groove 211. Then, the two locking hooks 23 clamp and hold the missile's orientation button, achieving automatic pre-positioning of the missile's orientation button, eliminating the need for the operator to adjust the missile locking actuator 2. During this process, the slider 22 will drive the connecting rod assembly 42, causing the connector 44 at the end of the connecting rod assembly 42 to move closer to the flipping arm 43. The operator, located at the rear of launch box 1, can visually determine whether the missile is in the pre-locked position inside launch box 1 based on the movement of the connector 44. Then, the operator tensions the connecting belt 5 through the tensioning assembly 3, causing the hook part 431 of the flipping arm 43 to flip until the connector 44 on the connecting rod assembly 42 is hooked and positioned on the lower support 41, locking the slider 22 and the locking hooks 23 on the slider 22, thus locking the missile inside launch box 1.

[0063] Furthermore, refer to Figure 7 The connecting belt 5 includes a magnesium belt 51 and perforated clamping heads 52 bolted to both ends of the magnesium belt 51. One perforated clamping head 52 on the magnesium belt 51 is detachably connected to the rear end of the tilting arm 43, and the other perforated clamping head 52 on the magnesium belt 51 is detachably connected to the tensioning assembly 3. The magnesium belt 51 is made of magnesium alloy sheet, which has stable mechanical properties at room temperature but rapidly decreases mechanical properties at high temperatures.

[0064] Furthermore, refer to Figure 8 The tensioning assembly 3 includes an upper support 31, a tensioning rod 32, and a tensioning bolt 33. The upper support 31 includes a plate 311 and two perforated ribs 312 integrally formed on the plate 311. The plate 311 in the upper support 31 is connected to the launch box 1. The two ends of the tensioning rod 32 pass through the holes of the two ribs 312, and the middle part of the tensioning rod 32 passes through a perforated clamping head 52 on the magnesium strip 51. The tensioning rod 32 and the holes of the two ribs 312 are clearance-fitted, allowing the tensioning rod 32 to move within the upper support 31.

[0065] The tensioning bolt 33 is threadedly connected to the rib plate 312 in the upper support 31. The shank of the tensioning bolt 33 extends into the hole in the rib plate 312 and abuts against the surface of the tensioning rod 32. The tensioning bolt 33 can be screwed to move the tensioning rod 32 away from the adjusting assembly 4, thereby tightening or loosening the magnesium strip 51.

[0066] Furthermore, the tensioning assembly 3 also includes a locking nut 34, which is threaded onto the shank of the tensioning bolt 33 and can be detachably pressed against the surface of the upper support 31. After the connecting belt 5 is adjusted to a suitable tension, the operator tightens the locking nut 34, causing it to contact the surface of the upper support 31, thus securing the tensioning bolt 33 to the upper support 31.

[0067] The above are all preferred embodiments of the present invention and are not intended to limit the scope of protection of the present invention. Therefore, all equivalent changes made in accordance with the structure, shape and principle of the present invention should be covered within the scope of protection of the present invention.

Claims

1. A self-unlocking launch box locking device, characterized in that, It includes a locking mechanism (2), a tensioning mechanism (3), and an adjusting mechanism (4) disposed in the launch box (1), wherein: A connecting belt (5) is provided between the tensioning component (3) and the adjusting component (4) to connect the two. The tensioning component (3) is used to apply tension to the connecting belt (5). The connecting belt (5) is capable of breaking under the impact of high-temperature gas. The locking mechanism (2) is connected to the adjusting mechanism (4). When the connecting band (5) is tightened, the adjusting mechanism (4) drives the locking mechanism (2) to lock the missile's orientation button. When the connecting band (5) breaks, the adjusting mechanism (4) releases the locking mechanism (2) from locking the missile's orientation button. The locking mechanism (2) includes a sliding plate (21), a slider (22), and a locking hook (23); The slide plate (21) is connected inside the launch box (1). A guide groove (211) is provided on the slide plate (21). The extension direction of the guide groove (211) is consistent with the launch direction of the missile. An end cap (26) is connected to the end of the slide plate (21) away from the launch outlet of the launch box (1). The slider (22) is slidably installed in the guide groove (211), and the end of the slider (22) away from the launch outlet of the launch box (1) is connected to the adjustment component (4); the end cover (26) has an elastic element (27) built in it, and the elastic element (27) applies a thrust to the slider (22) in a direction away from the end cover (26); Two locking hooks (23) are rotatably connected to one end of the slider (22) near the launch outlet of the launch box (1); two leaf springs (24) are connected to the slider (22), and the two leaf springs (24) correspond one-to-one with the two locking hooks (23), and the two leaf springs (24) drive the two locking hooks (23) to rotate and open; The adjustment assembly (4) includes a lower support (41), a connecting rod assembly (42), and a flip arm (43) rotatably mounted on the lower support (41). The lower support (41) is connected to the launch box (1). One end of the connecting rod assembly (42) is connected to the end of the slider (22) away from the launch outlet of the launch box (1), and the other end is connected to a connector (44). The front end of the flip arm (43) is bent to form a hook part (431) for hooking and connecting the connector (44). The rear end of the flip arm (43) is detachably connected to the connecting belt (5). When the connecting belt (5) is tightened, the connecting belt (5) pulls the rear end of the flipping arm (43), and the hook part (431) of the flipping arm (43) flips until the connecting rod group (42) is hooked and positioned on the lower support (41). The adjusting component (4) tightens the slider (22), and the two locking hooks (23) are limited and hugged by the inner wall of the guide groove (211) to form a directional button clamping cavity. When the connecting band (5) breaks, the adjusting component (4) releases the slider (22), and the directional button can drive the two locking hooks (23) to move, so that the two locking hooks (23) protrude out of the guide groove (211), so that the two locking hooks (23) open and release the limit on the positioning button.

2. The self-unlocking launch box locking device according to claim 1, characterized in that, The connecting rod assembly (42) includes a pull rod (421) and an extension rod (422). One end of the pull rod (421) is connected to the end of the slider (22) away from the launch outlet of the launch box (1). The other end of the pull rod (421) is detachably connected to the extension rod (422). The end of the extension rod (422) away from the pull rod (421) is fixedly connected to the connector (44).

3. The self-unlocking launch box locking device according to claim 2, characterized in that, The end cap (26) has a guide hole for the pull rod (421) to pass through.

4. The self-unlocking launch box locking device according to claim 1, characterized in that, A limiting plate (411) is fixed on the lower support (41). The limiting plate (411) is located at one end of the flip arm (43) near the locking spring actuation assembly (2). The surface of the limiting plate (411) is provided with a guide hole for the extension rod (422) to pass through.

5. The self-unlocking launch box locking device according to claim 1, characterized in that, The tensioning assembly (3) includes an upper support (31), a tensioning rod (32), and a tensioning bolt (33). The upper support (31) is connected to the launch box (1). The tensioning rod (32) is movable on the upper support (31) and is connected to the connecting belt (5). The tensioning bolt (33) is threadedly connected to the upper support (31). The rod of the tensioning bolt (33) abuts against the surface of the tensioning rod (32). The tensioning bolt (33) drives the tensioning rod (32) away from the adjusting assembly (4).

6. The self-unlocking launch box locking device according to claim 1, characterized in that, The tensioning assembly (3) also includes a locking nut (34), which is threaded onto the rod of the tensioning bolt (33) and can be separably pressed against the surface of the upper support (31).

7. The self-unlocking launch box locking device according to claim 1, characterized in that, It also includes a guide rail (6) fixed to the inner wall of the launch box (1), and a track (60) is provided on the guide rail (6) along the launch direction of the missile. The sliding plate (21) is adapted to slide with the track (60), and the sliding plate (21) is fixed in the track (60) by a fastener.

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