A near-earth launch flow guiding device for a 40mm rocket launcher

Abstract

The present invention discloses a near-ground launch diversion device for a 40mm rocket launcher, which includes a disassembly and assembly mechanism and a retractable mechanism. The disassembly and assembly mechanism is installed at the tail of the rocket launcher and is used to fixedly connect the tail of the rocket launcher with the retractable mechanism; the retractable mechanism is used to deploy and retract the protective cover, which is deployed during operation and folded up when not in use; the present invention can prevent the high-temperature and high-pressure gas generated during the launch of the 40mm rocket from affecting the launch device, and at the same time prevent the blowing objects from blocking the line of sight.

Description

Technical Field

[0001] The present invention belongs to the field of individual rocket launcher protection equipment, and particularly relates to a near-ground launch diversion device for a 40mm rocket launcher. Background Art

[0002] When a 40mm rocket launcher launches a rocket at near ground, a large amount of high-temperature and high-pressure gas will be generated, blowing up a large amount of dust on the ground. If some precision instruments such as a ground fire control device are attached to the 40mm rocket launch, it may affect the launch device. At the same time, the blown-up objects will block the line of sight and affect the combat effectiveness. Therefore, a diversion device is needed to lead the high-temperature and high-pressure gas to a certain distance away from the launch device. Summary of the Invention

[0003] In view of this, the present invention provides a near-ground launch diversion device for a 40mm rocket launcher, which can prevent the high-temperature and high-pressure gas generated during the launch of the 40mm rocket from affecting the launch device, and at the same time prevent the blown-up objects from blocking the line of sight.

[0004] The technical solution of the present invention is realized as follows:

[0005] A near-ground launch diversion device for a 40mm rocket launcher includes a disassembly and assembly mechanism and a retracting and deploying mechanism. The disassembly and assembly mechanism is installed at the tail of the rocket launcher and is used to fixedly connect the tail of the rocket launcher to the retracting and deploying mechanism; the retracting and deploying mechanism is used to deploy and retract the protective cover, which is deployed during work and folded up when not in use.

[0006] Further, the disassembly and assembly mechanism includes an adjusting bolt and a clamp connection body; an annular groove is provided in the inner ring of the clamp connection body, and the width of the annular groove is the sum of the width of the flange at the tail of the rocket launcher and the width of the connection flange of the retracting and deploying mechanism; the adjusting bolt tightens the clamp connection body.

[0007] Further, the retracting and deploying mechanism includes a connection seat, a spring plunger, a link mechanism, a support steel ring, and a high-temperature resistant material protective cover;

[0008] One end of the connection seat is a connection flange, and the other end is a cylindrical structure; four groups of mounting holes are evenly distributed on the cylindrical surface, and each group of mounting holes includes a spring plunger mounting hole and a link mounting hole arranged along the axial direction;

[0009] The flange of the connecting seat and the flange at the tail of the rocket launcher are fixedly connected through a disassembly and assembly mechanism. Four spring plungers are respectively threadedly connected into the corresponding mounting holes of the connecting seat, and one end of the linkage mechanism is fixedly connected into the corresponding mounting hole of the connecting seat; the support steel ring is sleeved outside the linkage mechanism and fixedly connected with the linkage mechanism. The high-temperature resistant material protective cover is composed of an inner layer and an outer layer. One end of the inner layer protective cover is fixedly connected to the connecting seat through a flange, and the outer layer protective cover is bonded to the outer circular surface of the connecting seat and the support steel ring; the support steel ring serves as the support keel when the protective cover is retracted and extended, and the protective cover moves with the telescopic movement of the connecting rod. When the linkage mechanism extends to a certain distance, the steel ball on the spring plunger enters the connecting rod hole, realizing the locking of the linkage mechanism and preventing the connecting rod from continuing to extend to the dead point of the mechanism and being unable to retract.

[0010] Furthermore, the linkage mechanism includes multiple connecting rods connected end to end. The connecting rods are connected by pin shafts, and support steel rings are installed at the connection points of the connecting rods.

[0011] Furthermore, when the retractable mechanism needs to be retracted, axially press the support steel ring, the steel ball of the spring plunger retracts, the linkage mechanism is unlocked, and the retractable mechanism is retracted.

[0012] Beneficial effects:

[0013] The present invention provides a near-earth launch diversion device for a rocket launcher, which can effectively protect the launch device. This device does not change the structure of the original 40mm rocket launcher, the operating mechanism is simple and convenient, the quality is light, it can be quickly retracted and extended, and it is convenient to carry. Brief Description of the Drawings

[0014] Figure 1 It is the overall assembly explosion diagram of the diversion device of the present invention.

[0015] Figure 2 It is the connection cross-sectional view and partial enlarged view of the disassembly and assembly mechanism of the present invention; (a) is the cross-sectional view, and (b) is the partial enlarged view.

[0016] Figure 3 It is the axonometric view of the disassembly and assembly mechanism of the present invention.

[0017] Figure 4 It is the explosion diagram of the retractable mechanism of the present invention.

[0018] Figure 5 It is the partial enlarged view of the spring plunger and the connecting rod of the present invention.

[0019] Figure 6 It is the cross-sectional view of the spring plunger.

[0020] Figure 7 It is the partial cross-sectional view of the spring plunger installation.

[0021] Among them, 1 - rocket launcher, 2 - disassembly and assembly mechanism, 3 - retraction mechanism, 1-1 - breech, 2-1 - clamp connection body, 2-2 - adjusting bolt, 3-1 - connecting seat, 3-2 - spring plunger, 3-3 - link mechanism, 3-4 - support steel ring, 3-5 - high-temperature resistant material protective cover. Detailed implementation mode

[0022] The present invention will be described in detail below with reference to the accompanying drawings and by way of examples.

[0023] The present invention provides a near-earth launch diversion device for a 40mm rocket launcher, as Figure 1 shown, which is composed of a disassembly and assembly mechanism 2 and a retraction mechanism 3. The disassembly and assembly mechanism is installed at the tail of the rocket launcher and is used to connect the retraction mechanism. The retraction mechanism is used to deploy and retract the protective cover, which is deployed during operation and folded up when not in use.

[0024] As Figure 2 (a)-(b) and Figure 3 show, the disassembly and assembly mechanism is composed of an adjusting bolt and a clamp connection body. The inner hole of the clamp connection body has an annular groove, and the width is the sum of the widths of the breech flange and the connecting seat flange. The adjusting bolt can tighten the clamp connection body.

[0025] As Figure 4 shown, the retraction mechanism is composed of a connecting seat, a spring plunger, a link mechanism, a support steel ring, and a high-temperature resistant material protective cover. The link mechanism is installed on the connecting seat, the support steel ring is connected to the link mechanism, and the high-temperature resistant material protective cover consists of two layers, an inner protective cover is installed on the connecting seat by a flange, and the outer protective cover is bonded to the outer circle of the connecting seat and the support steel ring. The support steel ring serves as the support keel when the protective cover is retracted and deployed, and the protective cover moves with the expansion and contraction of the link. The spring plunger is installed at the corresponding position of the connecting seat. When the link mechanism extends to a certain distance, as Figure 5 shown, the steel ball on the spring plunger enters the link hole, realizing the locking of the link mechanism and preventing the link from continuing to extend to the dead point of the mechanism and being unable to be retracted.

[0026] As Figure 2 , the breech flange 1-1 is aligned with the connecting seat flange 3-1, the disassembly and assembly mechanism is sleeved on the two flanges, and the two flanges are just inserted into the inner annular groove of the clamp body 2-1. Tighten the adjusting bolt 2-2 to hold the two flanges tightly, realizing the connection between the retraction mechanism 3 and the rocket launcher 1. When disassembling, loosen the adjusting bolt 2-2, and the retraction mechanism 3 can be disconnected from the rocket launcher 1.

[0027] The retraction mechanism 3 can be made as a whole. First, screw four spring plungers 3-2 into the holes of the connecting seat 3-1. There is an inner hexagon wrench groove on the back of the spring plunger 3-2, and the outer circumference is threaded (see Figure 6), screw the spring plunger into the inner hole of the connecting seat until the end face of the plunger is flush with the end face of the connecting seat. When the steel ball of the spring plunger aligns with the upper hole on the connecting rod mechanism, the steel ball slides into the connecting rod hole, playing a positioning role (see Figure 7 ). Then fixedly connect the connecting rod 3-3 with the connecting seat 3-1. Install the other connecting rods in sequence. Connect the connecting rods with pin shafts, and fixedly install the support steel rings 3-4 at the corresponding connection points of each connecting rod. The outer protective cover is bonded to the connecting seat and each support steel ring 3-4. One end flange of the inner protective cover is connected to the end face of the connecting seat 3-1, and the other end is bonded to each support steel ring 3-4. During use, axially pull the outermost support steel ring, and the telescopic mechanism 3 can be telescoped. When stretched to a certain distance, the steel ball in the spring plunger 3-2 pops up and gets stuck in the connecting rod hole, realizing the positioning of the telescopic mechanism 3. In this way, the high-temperature and high-pressure gas generated by the rocket projectile sprays out along the flow guiding device at a certain distance away from the launching device. When retracting, axially press the support steel ring 3-4, and the steel ball of the spring plunger 3-2 is pressed back into the spring plunger body by the connecting rod, unlocking, and each steel ring contracts axially, and the telescopic mechanism 3 retracts, so that the volume of the flow guiding device can be reduced, facilitating carrying.

[0028] In summary, the above are only the preferred embodiments of the present invention and are not used to limit the protection scope of the present invention. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included within the protection scope of the present invention.

Claims

1. A near-earth launch flow guiding device for a 40mm rocket launcher, characterized in that, It includes a disassembly and assembly mechanism and a retractable mechanism. The disassembly and assembly mechanism is installed at the tail of the rocket launcher and is used to fixedly connect the tail of the rocket launcher to the retractable mechanism. The retractable mechanism is used to deploy and retract the protective cover, which is deployed during operation and folded up when not in use. The retractable mechanism includes a connecting seat, spring plungers, a linkage mechanism, a support steel ring, and a high-temperature resistant material protective cover. One end of the connecting seat is a connecting flange, and the other end is a cylindrical structure. Four groups of mounting holes are evenly distributed on the cylindrical surface. Each group of mounting holes includes a spring plunger mounting hole and a connecting rod mounting hole arranged axially. The flange of the connecting seat is fixedly connected to the flange at the tail of the rocket launcher through the disassembly and assembly mechanism. Four spring plungers are respectively threadedly connected to the corresponding mounting holes on the connecting seat, and one end of the linkage mechanism is fixedly connected to the corresponding mounting hole on the connecting seat. The support steel ring is sleeved outside the linkage mechanism and fixedly connected to the linkage mechanism. The high-temperature resistant material protective cover consists of an inner layer and an outer layer. One end of the inner layer protective cover is fixedly connected to the connecting seat through a flange, and the outer layer protective cover is bonded to the outer cylindrical surface of the connecting seat and the support steel ring. The support steel ring serves as the support keel when the protective cover is retracted and deployed, and the protective cover moves with the expansion and contraction of the connecting rod. When the linkage mechanism extends to a certain distance, the steel ball on the spring plunger enters the connecting rod hole, realizing the locking of the linkage mechanism and preventing the connecting rod from continuing to extend to the dead point of the mechanism and being unable to retract.

2. The near-earth launch flow guiding device for a 40mm rocket launcher according to claim 1, characterized in that, The disassembly and assembly mechanism includes an adjusting bolt and a clamp connection body. An annular groove is provided in the inner ring of the clamp connection body, and the width of the annular groove is the sum of the width of the flange at the tail of the rocket launcher and the width of the connecting flange of the retractable mechanism. The adjusting bolt tightens the clamp connection body.

3. The near-earth launch flow guiding device for a 40mm rocket launcher according to claim 1, wherein, The linkage mechanism includes multiple connecting rods connected end to end. The connecting rods are connected by pins, and support steel rings are installed at the connection points of each connecting rod.

4. The near-earth launch flow guiding device for a 40mm rocket launcher according to claim 1, characterized in that, When the retractable mechanism needs to be retracted, axially press the support steel ring, the steel ball of the spring plunger retracts, the linkage mechanism is unlocked, and the retractable mechanism is retracted.

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