Self-throwing launcher front cover

Abstract

The utility model discloses a kind of self-throwing launch can front covers, belong to the technical field of flying bomb airborne launch can, the self-throwing launch can front cover includes launch can barrel;Rectifier front cover, one end has opening;Connecting piece, one end is connected in the opening of rectifier front cover, the other end is screwed in launch can barrel;Elastic locking mechanism, for releasably connecting rectifier front cover and connecting piece, elastic locking mechanism is locked by radial expansion;When rectifier front cover is exerted external force, elastic locking mechanism is unlocked by radial contraction;Drive assembly, one end is installed in the opening end of rectifier front cover, the other end is slidably installed in launch can barrel.Therefore, by the setting of elastic locking mechanism, so that the self-throwing launch can front cover provided by the utility model can realize the purpose of automatic opening, more convenient to use.

Description

Technical Field

[0001] This utility model belongs to the technical field of airborne launch tubes for loitering munitions, specifically relating to a self-propelled launch tube front cover. Background Technology

[0002] With the development of information technology, warfare is increasingly becoming unmanned and information-based. Loitering munitions, due to their combined reconnaissance and strike capabilities, are widely used in modern warfare. A loitering munition is a precision munition capable of loitering over a target area and executing combat orders. It is a product of the organic integration of unmanned aerial vehicle (UAV) technology and munitions technology, primarily undertaking combat missions such as battlefield reconnaissance, target designation, precision strikes, damage assessment, communications relay, electronic warfare, air surveillance, and special payload delivery.

[0003] In addition to providing support, guidance, or sealing of the launch gases during launch, the launch tube also packages and protects the missile during pre-launch storage and transportation, and provides a sealed storage environment. A launch tube generally consists of a tube body, a cap, a missile locking device, an internal environmental parameter adjustment and detection device, and a test and launch control system.

[0004] Because airborne launchers are used in the air, the front cover cannot be opened manually before firing, so the ability for the front cover to open automatically is particularly important. Utility Model Content

[0005] The purpose of this utility model is to address the aforementioned shortcomings in the prior art by providing a self-propelled launch tube front cover, thereby solving the technical problem that the front cover of the airborne launch tube in the prior art cannot open automatically.

[0006] To achieve the above objectives, the technical solution adopted by this utility model is as follows: A self-propelled launch tube front cover, comprising: Launch tube body; The front fairing has an opening at one end; The connector has one end connected to the opening of the front cover of the rectifier and the other end screwed to the body of the launch tube; An elastic locking mechanism is used to releasably connect the rectifier front cover to the connector. The elastic locking mechanism achieves locking by radial expansion; when an external force is applied to the rectifier front cover, the elastic locking mechanism achieves self-unlocking by radial contraction. The drive assembly is mounted at one end on the opening of the rectifier front cover and at the other end on the launch tube body.

[0007] Furthermore, the connector includes: The first ring is connected to the opening of the front cover of the rectifier; The second ring is fixedly installed at one end of the first ring, and the inner diameter of the second ring is larger than that of the first ring. The inner sidewall of the second ring is provided with internal threads.

[0008] Furthermore, the elastic locking mechanism includes: Multiple elastic elements are provided. Multiple placement slots are provided on the outer side wall of the rectifier front cover. One end of each elastic element is installed in one of the multiple placement slots. The elastic elements and the placement slots are arranged in a one-to-one correspondence. There are multiple balls, which are installed at the other end of multiple elastic elements. The side wall of the first ring has multiple abutment holes that are adapted to the balls. The multiple abutment holes are arranged one-to-one with the multiple placement slots. One end of the ball extends out of the placement slot and abuts in the abutment hole, and the other end of the ball extends out of the abutment hole.

[0009] Furthermore, the plurality of placement slots are uniformly arranged on the rectifier front cover along the circumferential direction of the first ring.

[0010] Furthermore, the driving component includes: The ring has multiple through holes at one end, and the multiple through holes are evenly arranged along the circumferential direction of the ring. The bolts are in multiple quantities. The opening end of the rectifier front cover is provided with multiple threaded holes, and the multiple threaded holes are provided in a one-to-one correspondence with the multiple through holes. The multiple bolts pass through the multiple through holes and are screwed into the corresponding threaded holes. Multiple elastic buckles are provided, with one end of each elastic buckle fixedly mounted on the ring piece. The annular component has an annular groove on its inner sidewall that is adapted to the elastic buckle. The other end of the elastic buckle is rotatably installed in the annular groove, and the annular component is installed on the body of the launch tube.

[0011] Furthermore, the elastic buckle includes: The first block has an arc-shaped cross-section. One end of the first block is fixedly installed at the end of the ring plate away from the front cover of the rectifier, and the outer side wall of the first block is in contact with the inner side wall of the ring. The second block is fixedly installed at one end on the other end of the first block and is perpendicular to the first block. The other end of the second block is rotatably installed in the annular groove.

[0012] Furthermore, the length of the first block in the first direction is equal to the vertical distance between the side of the annular groove near the rectifier front cover and the side of the annular piece near the annular member.

[0013] Furthermore, the side of the second block near the bottom of the annular groove has an angle α with the straight line containing the first direction.

[0014] Furthermore, the included angle α has a range of 30°≤α≤70°.

[0015] Furthermore, it also includes multiple shear pins. The launch tube has multiple threaded through holes at one end near the rectifier front cover. One end of each of the multiple shear pins is screwed into the multiple threaded through holes and extends into the launch tube. The outer wall of the annular component has multiple pin holes. The multiple pin holes are arranged one-to-one with the multiple threaded through holes. One end of each of the multiple shear pins extending into the launch tube is inserted into the corresponding pin hole.

[0016] The self-propelled launcher front cover provided by this utility model has the following beneficial effects: 1. With the setting of the elastic locking mechanism, when the pushing force on the drive component is greater than the locking force provided by the elastic locking mechanism, the elastic locking mechanism unlocks itself, thereby pushing the drive component and the rectifier front cover out of the launch tube body; 2. The use of elastic elements and ball bearings provides shock absorption, reducing the likelihood of the loitering munition being subjected to strong impacts during the process of pushing the drive assembly and the front fairing open. Attached Figure Description

[0017] Figure 1 This is a schematic diagram of the structure of the self-propelled launch tube front cover provided in an embodiment of the present utility model; Figure 2 Another structural schematic diagram of the self-propelled launch tube front cover provided in this embodiment of the utility model; Figure 3 A cross-sectional view of the front cover of the self-propelled launcher provided in an embodiment of this utility model; Figure 4 A schematic diagram of the mounting structure of the rectifier front cover and the ring plate provided for an embodiment of this utility model; Figure 5 A schematic diagram of the structure of the rectifier front cover provided in an embodiment of this utility model; Figure 6 A schematic diagram of the installation structure of the ring and the elastic buckle provided in an embodiment of this utility model; Figure 7 This is a schematic diagram of the shear pin provided in an embodiment of the present invention.

[0018] The attached diagram shows the markings and corresponding component names: 1- Launch tube body, 2- Rectifier front cover, 21- Placement slot, 22- Threaded hole, 3- Connector, 31- First ring, 311- Abutment hole, 32- Second ring, 4- Elastic locking mechanism, 41- Elastic element, 42- Ball bearing, 5- Drive assembly, 51- Ring piece, 511- Through hole, 52- Bolt, 53- Elastic buckle, 531- First block, 532- Second block, 54- Ring element, 541- Ring groove, 542- Pin hole, 6- Shear pin. Detailed Implementation

[0019] The specific embodiments of this utility model are described below to enable those skilled in the art to understand this utility model. However, it should be understood that this utility model is not limited to the scope of the specific embodiments. For those skilled in the art, as long as various changes are within the spirit and scope of this utility model as defined and determined by the appended claims, these changes are obvious. All utility model creations utilizing the concept of this utility model are within the scope of protection.

[0020] This embodiment provides a self-propelled launch tube front cover, solving the technical problem that the front cover of an airborne launch tube cannot open automatically in the prior art. The self-propelled launch tube front cover includes a launch tube body 1, a front fairing 2, a connector 3, an elastic locking mechanism 4, and a drive assembly 5, wherein: refer to Figures 1-2 The launch tube body 1 is a hollow cylinder.

[0021] The front shroud 2 has an opening at one end. Specifically, the front shroud 2 includes a hemispherical shell and an annular shell. One end of the annular shell is fixedly installed at the opening end of the hemispherical shell, and the outer diameter of the annular shell is equal to the outer diameter of the opening end of the hemispherical shell.

[0022] One end of the connector 3 is connected to the opening of the front cover 2 of the rectifier, and the other end is screwed to the body of the launch tube 1. With the screwed connector 3, if the launch tube needs to be repaired, it is only necessary to rotate the connector 3 to separate the connector 3 from the body of the launch tube 1. In this way, maintenance or repair can be carried out quickly in the field when there are no tools.

[0023] The elastic locking mechanism 4 is used to releasably connect the rectifier front cover 2 and the connector 3. The elastic locking mechanism 4 achieves locking through radial expansion. When an external force is applied to the rectifier front cover 2, the elastic locking mechanism 4 achieves self-unlocking through radial contraction. Thus, by setting the elastic locking mechanism 4, when the thrust on the rectifier front cover 2 is greater than the locking force provided by the elastic locking mechanism 4, the elastic locking mechanism 4 self-unlocks, thereby allowing the rectifier front cover 2 to be pushed out of the launch tube body 1. This enables the self-throwing launch tube front cover provided by this utility model embodiment to achieve automatic opening, making it more convenient to use.

[0024] One end of the drive assembly 5 is installed at the opening end of the rectifier front cover 2, and the other end is installed on the launch tube body 1. When the pushing force on the drive assembly 5 is greater than the maximum effort provided by the elastic locking mechanism 4, the connection between the drive assembly 5 and the launch tube body 1 is also disconnected. In this way, the setting of the drive assembly 5 makes it easier to push the rectifier front cover 2 away from the launch tube body 1.

[0025] Connector 3 includes a first ring 31 and a second ring 32, wherein: The first ring 31 is connected to the opening of the rectifier front cover 2. Specifically, the first ring 31 is sleeved on the outside of the annular shell.

[0026] The second ring 32 is fixedly installed at one end of the first ring 31, and the inner diameter of the second ring 32 is larger than the inner diameter of the first ring 31. The inner side wall of the second ring 32 is provided with an internal thread, and the outer side wall of the launch tube body 1 is provided with an external thread that matches the internal thread. The second ring 32 is screwed onto the launch tube body 1.

[0027] Optionally, the outer wall of the second ring 32 is provided with knurling, which increases friction and reduces the chance of slippage when rotating the connector 3, making it easier to assemble and disassemble the connector 3.

[0028] Optionally, a sealing ring is provided between the second ring 32 and the launch tube body 1. In this way, the airtightness between the rectifier front cover 2 and the launch tube body 1 is ensured by the setting of the sealing ring, while reducing the probability of the rectifier front cover 2 becoming loose.

[0029] The elastic locking mechanism 4 includes an elastic element 41 and a ball 42, wherein: There are multiple elastic elements 41. Multiple placement slots 21 are provided on the outer side wall of the rectifier front cover 2. One end of each elastic element 41 is installed in one of the multiple placement slots 21. The elastic elements 41 are arranged in a one-to-one correspondence with the placement slots 21. The arrangement of the elastic elements 41 provides continuous pressure.

[0030] Optionally, the elastic element 41 is a compression spring, which has a simple structure, reliable operation, and strong adaptability.

[0031] There are multiple balls 42, which are installed at the other end of multiple elastic elements 41. The side wall of the first ring 31 has multiple abutment holes 311 that are adapted to the balls 42. The multiple abutment holes 311 are arranged one-to-one with the multiple placement grooves 21. One end of the ball 42 extends out of the placement groove 21 and abuts in the abutment hole 311, and the other end of the ball 42 extends out of the abutment hole 311.

[0032] Optionally, the ball bearing 42 is a structural component made of high carbon steel.

[0033] With the above structure, the ball bearing 42 is connected by the elastic element 41. When the connecting member 3 is sleeved outside the rectifier front cover 2, the ball bearing 42 abuts against the abutment hole 311 and extends out of the abutment hole 311. At this time, the elastic element 41 is compressed. Through the cooperation of multiple elastic elements 41 and the ball bearing 42, the rectifier front cover 2 is firmly connected to the connecting member 3. When the rectifier front cover 2 is pushed, the rectifier front cover 2 begins to compress the ball bearing 42 and the elastic element 41. The ball bearing 42 is gradually compressed into the rectifier front cover 2. The rectifier front cover 2 continues to move away from the launch tube body 1. The elastic element 41 continues to be compressed. The ball bearing 42 comes out of the abutment hole 311. The force that locks the rectifier front cover 2 disappears, so that the rectifier front cover 2 is pushed out, thereby achieving the purpose of automatically opening the front cover.

[0034] Optionally, multiple placement slots 21 are evenly arranged on the rectifier front cover 2 along the circumferential direction of the first ring 31. In this way, the locking force on the rectifier front cover 2 is more uniform through the evenly arranged placement slots 21.

[0035] refer to Figures 3-4 The drive assembly 5 includes a ring plate 51, a bolt 52, a resilient buckle 53, and a ring-shaped component 54, wherein: One end of the ring piece 51 is provided with multiple through holes 511, which are evenly arranged along the circumferential direction of the ring piece 51. Optionally, the ring piece 51 is an open ring piece 51, which makes it easier for the elastic buckle 53 to be inserted into the annular groove 541.

[0036] There are multiple bolts 52, see reference. Figure 5 The rectifier front cover 2 has multiple threaded holes 22 at its open end, and the multiple threaded holes 22 are set one-to-one with multiple through holes 511. Multiple bolts 52 pass through multiple through holes 511 and are screwed into the corresponding threaded holes 22. In this way, the ring piece 51 is fixedly installed on the rectifier front cover 2 by bolts 52, which is convenient for disassembly and assembly.

[0037] refer to Figure 6 There are multiple elastic buckles 53, and one end of each elastic buckle 53 is fixedly installed on the ring piece 51. In this way, the elastic buckles 53 are more easily inserted into the annular groove 541. The multiple elastic buckles 53 make the connection between the ring piece 51 and the annular part 54 more secure.

[0038] The inner wall of the annular component 54 is provided with an annular groove 541 that is adapted to the elastic buckle 53. The other end of the elastic buckle 53 is rotatably installed in the annular groove 541. The annular component 54 is installed on the launch tube body 1. Specifically, it also includes multiple plug-in components, one end of which is installed on the end of the annular component 54 away from the front cover 2. The inner wall of the launch tube body 1 is provided with multiple plug-in slots that are adapted to the plug-in components. In this way, after the annular component 54 and the elastic buckle 53 are connected, the annular component 54 can continue to rotate so that the plug-in components can be inserted into the corresponding plug-in slots. At the same time, the plug-in components can also play a guiding role to prevent the front cover 2 from rotating when subjected to thrust, which would make it difficult or impossible for the front cover 2 to detach from the launch tube body 1.

[0039] Optionally, the elastic buckle 53 includes a first block 531 and a second block 532, wherein: The first block 531 has an arc-shaped cross-section. One end of the first block 531 is fixedly installed on the end of the ring plate 51 away from the front cover 2 of the rectifier. The outer side wall of the first block 531 is in contact with the inner side wall of the ring part 54. In this way, the arc-shaped first block 531 can fit the ring part 54 more closely, which makes it easier to rotate the ring part 54.

[0040] One end of the second block 532 is fixedly installed on the other end of the first block 531 and is set perpendicular to the first block 531. The other end of the second block 532 is rotatably inserted into the annular groove 541. Optionally, the second block 532 can be connected to the first block 531 by welding, bonding or hot melting, or it can be integrally formed.

[0041] Optionally, the length of the first block 531 in the first direction is equal to the vertical distance between the side of the annular groove 541 near the rectifier front cover 2 and the side of the ring plate 51 near the annular member 54. The first direction is the axial direction of the first ring 31. This avoids the annular member 54 from reciprocating in the first direction when the launch tube vibrates, thereby preventing damage to the elastic buckle 53.

[0042] Optionally, the side of the second block 532 near the bottom of the annular groove 541 has an angle α with the straight line of the first direction. In this way, by setting the angle α, it is easier for the elastic buckle 53 to be inserted into the annular groove 541.

[0043] Optionally, the included angle α can be in the range of 30°≤α≤70°. For example, the included angle α can be 30°, 40°, 50°, 6°, and 70°.

[0044] refer to Figure 7It also includes multiple shear pins 6. Multiple threaded through holes 511 are provided at one end of the launch tube body 1 near the front cover 2. One end of each shear pin 6 is screwed into the multiple threaded through holes 511 and extends into the launch tube. Multiple pin holes 542 are provided on the outer wall of the annular part 54. The multiple pin holes 542 are arranged one-to-one with the multiple threaded through holes 511. The ends of the multiple shear pins 6 that extend into the launch tube are inserted into the corresponding pin holes 542. In this way, the shear pins 6 are used to fix the annular part 54 when the launch tube is not firing; and when the thrust on the annular part 54 gradually increases, the shear pins 6 are sheared.

[0045] Although the specific embodiments of the utility model have been described in detail with reference to the accompanying drawings, this should not be construed as limiting the scope of protection of this patent. Various modifications and variations that can be made by those skilled in the art without inventive effort within the scope described in the claims still fall within the scope of protection of this patent.

Claims

1. A self-propelled launcher front cover, characterized in that, include: Launch tube body (1); The front fairing (2) has an opening at one end; The connector (3) is connected at one end to the opening of the front cover (2) and at the other end to the body of the launch tube (1); An elastic locking mechanism (4) is used to releasably connect the rectifier front cover (2) and the connector (3). The elastic locking mechanism (4) locks by radial expansion. When an external force is applied to the rectifier front cover (2), the elastic locking mechanism (4) unlocks by radial contraction. The drive assembly (5) is installed at one end of the opening of the rectifier front cover (2) and at the other end of the launch tube body (1).

2. The self-propelled launch tube front cover according to claim 1, characterized in that, The connector (3) includes: The first ring (31) is connected to the opening of the rectifier front cover (2); The second ring (32) is fixedly installed at one end of the first ring (31), and the inner diameter of the second ring (32) is larger than the inner diameter of the first ring (31). The inner sidewall of the second ring (32) is provided with internal threads.

3. The self-propelled launch tube front cover according to claim 2, characterized in that, The elastic locking mechanism (4) includes: There are multiple elastic elements (41). The outer side wall of the rectifier front cover (2) is provided with multiple placement slots (21). One end of each elastic element (41) is installed in the multiple placement slots (21), and the elastic elements (41) and the placement slots (21) are arranged in a one-to-one correspondence. There are multiple balls (42), which are installed at the other end of multiple elastic members (41). The side wall of the first ring (31) is provided with multiple abutment holes (311) that are adapted to the balls (42). The multiple abutment holes (311) are arranged one-to-one with the multiple placement grooves (21). One end of the ball (42) extends out of the placement groove (21) and abuts against the abutment hole (311), and one end of the ball (42) extends out of the abutment hole (311).

4. The self-erecting launch tube front cover of claim 3, wherein, Multiple placement slots (21) are evenly arranged on the rectifier front cover (2) along the circumferential direction of the first ring (31).

5. The self-propelled launch tube front cover according to claim 2, characterized in that, The driving component (5) includes: The ring plate (51) has multiple through holes (511) at one end, and the multiple through holes (511) are evenly arranged along the circumferential direction of the ring plate (51). The bolts (52) are in multiple quantities. The opening end of the rectifier front cover (2) is provided with multiple threaded holes (22), and the multiple threaded holes (22) are provided in a one-to-one correspondence with the multiple through holes (511). The multiple bolts (52) pass through the multiple through holes (511) and are screwed into the corresponding threaded holes (22). Multiple elastic buckles (53) are provided, with one end of each elastic buckle (53) fixedly mounted on the ring piece (51). The annular component (54) has an annular groove (541) on its inner side wall that is adapted to the elastic buckle (53). The other end of the elastic buckle (53) is rotatably installed in the annular groove (541). The annular component (54) is installed on the launch tube body (1).

6. The self-propelled launch tube front cover according to claim 5, characterized in that, The elastic buckle (53) includes: The first block (531) has an arc-shaped cross-section. One end of the first block (531) is fixedly installed on the end of the ring (51) away from the rectifier front cover (2), and the outer side wall of the first block (531) is in contact with the inner side wall of the ring (54). The second block (532) is fixedly installed at one end on the other end of the first block (531) and is arranged perpendicular to the first block (531). The other end of the second block (532) is rotatably installed in the annular groove (541).

7. The self-erecting launch tube front cover of claim 6, wherein, The length of the first block (531) in the first direction is equal to the vertical distance between the side of the annular groove (541) near the rectifier front cover (2) and the side of the ring plate (51) near the annular member (54).

8. The self-erecting launch tube front cover of claim 7, wherein, The side of the second block (532) near the bottom of the annular groove (541) has an angle α with the straight line of the first direction.

9. The self-erecting launch tube front cover of claim 8, wherein, The included angle α has a range of 30°≤α≤70°.

10. The self-erecting launch tube front cover of claim 5, wherein, It also includes multiple shear pins (6). Multiple threaded through holes (511) are provided at one end of the launch tube body (1) near the front cover (2). One end of each of the multiple shear pins (6) is screwed into the multiple threaded through holes (511) and extends into the launch tube. Multiple pin holes (542) are provided on the outer wall of the annular part (54). The multiple pin holes (542) are arranged one-to-one with the multiple threaded through holes (511). One end of each of the multiple shear pins (6) extending into the launch tube is inserted into the corresponding pin hole (542).

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