A corner reflector emission system
By designing the launch tube and drive components to propel the projectile components, and combining the inertial separation of high-pressure gas and connecting ropes, the problem of the complex structure of the corner reflector device detaching from the projectile body was solved, achieving simplification and cost reduction.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- BEIJING STARNETO TECH CO LTD
- Filing Date
- 2025-05-23
- Publication Date
- 2026-05-26
AI Technical Summary
Existing corner reflector devices have complex and costly separation structures for detaching from the projectile.
It adopts a combined design of launch tube, drive component and projectile component, uses high pressure gas to propel the projectile component to launch, and achieves inertial separation of the projectile from the descent component and corner reflector by tautness in the air through the first connecting rope.
The separation structure was simplified, the cost was reduced, and the reliability and accuracy of the separation were improved through inertial separation.
Smart Images
Figure CN224285656U_ABST
Abstract
Description
Technical Field
[0001] This utility model relates to the field of corner reflector emission technology, and in particular to a corner reflector emission system. Background Technology
[0002] Corner reflectors, also known as radar reflectors, are radar wave reflecting devices made of metal sheets for various applications. When radar electromagnetic waves scan a corner reflector, the waves are refracted and amplified at the metal corner, generating a strong echo signal that forms a clear echo target on the radar screen. Currently, radar corner reflectors are mainly deployed on the sea or land by gravity sliding or external force launching, serving as artificially placed radar decoys for radar jamming.
[0003] To ensure the corner reflector device can descend slowly, a specialized descent control system is usually required. The descent control system and the corner reflector device are installed in the projectile body. The projectile is launched by a launching device, and then the descent control system and the corner reflector device are separated from the projectile body through mechanical and electrical structures.
[0004] However, traditional separation methods mainly rely on mechanical and electrical structures, which are complex and costly. Utility Model Content
[0005] The purpose of this invention is to provide a corner reflector launching system to alleviate the technical problem of complex separation structures used in the prior art for corner reflector devices to detach from the projectile body.
[0006] The corner reflector launching system provided by this utility model includes: a launching tube, a driving component, and a projectile component;
[0007] The launch tube has a launch chamber inside, which is used to accommodate the projectile component;
[0008] The drive member is connected to the launch tube, and the drive member is configured to deliver high-pressure gas into the launch tube to push the projectile component out of the launch tube for launch.
[0009] The interior of the projectile component is used to accommodate the descent control component and the corner reflector component. The outer surface of the projectile component is connected to the inner wall of the launch tube by a first connecting rope. The first connecting rope is configured to be taut to make the projectile component stop in the air so as to separate the descent control component and the corner reflector component from the projectile component.
[0010] In an optional embodiment, the corner reflector emitting system further includes a emitting base;
[0011] The launch base is used to mount on a fixed surface, and the launch base is rotatably connected to the launch tube so that the launch tube can rotate relative to the launch base.
[0012] In an optional embodiment, a bracket is provided on the launch base, and the launch tube is rotatably connected to the bracket;
[0013] The launch base is provided with an adjustment arm, which is connected to the launch tube and is used to adjust the angle between the launch tube and the launch base.
[0014] In an optional embodiment, the launch base further includes a drive connecting pipe;
[0015] One end of the drive connecting pipe is connected to the launching tube, and the other end of the drive connecting pipe is connected to the drive component. The drive connecting pipe is used to transmit the high-pressure gas generated by the drive component to the launching chamber.
[0016] In an optional embodiment, the outer surface of the projectile component is provided with a hanging ring, which is used to connect the first connecting rope.
[0017] In an optional embodiment, the projectile component includes a tail-end cartridge case;
[0018] The tail end cartridge case has a first chamber inside, and the descent control component is disposed in the first chamber.
[0019] In an optional embodiment, a second connecting rope is provided inside the tail end cartridge case, one end of the second connecting rope is connected to the descent control member, and the other end of the second connecting rope is connected to the tail end cartridge case.
[0020] In an optional embodiment, the projectile component further includes a front-end cartridge case;
[0021] A second chamber is formed inside the front end cartridge case, and the corner reflector component is disposed in the second chamber.
[0022] In an optional embodiment, the projectile component further includes a third connecting rope;
[0023] One end of the third connecting rope is connected to the descent control member, and the other end of the third connecting rope is connected to the corner reflector member.
[0024] In an optional embodiment, the front cartridge case includes two opposing cartridge case halves;
[0025] The two cartridge case halves merge to form the second chamber, and the front end faces of the two cartridge case halves merge to form a conical concave surface.
[0026] The corner reflector launching system provided by this utility model places the projectile component in the launching chamber and uses the driving force generated by the driving component to launch the projectile component, causing the projectile component to fly in the air. At this time, the first connecting rope is in a slack state. When the first connecting rope is taut, the projectile component stops in the air, thereby relying on the inertial descent component and the corner reflector component to separate from the projectile component, realizing the separation operation. This alleviates the technical problem of the complex separation structure used by the existing corner reflector device to detach from the projectile. Attached Figure Description
[0027] To more clearly illustrate the specific embodiments of this utility model or the technical solutions in the prior art, the drawings used in the description of the specific embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of this utility model. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.
[0028] Figure 1 A cross-sectional view of the overall structure of the corner reflector emitting system provided in this embodiment of the utility model;
[0029] Figure 2 A structural cross-sectional view of the projectile component in the corner reflector launching system provided in this embodiment of the utility model;
[0030] Figure 3 A schematic diagram of the structure of the corner reflector emitting system provided in this embodiment of the utility model;
[0031] Figure 4 A schematic diagram of the overall structure of the corner reflector emitting system provided in this embodiment of the utility model.
[0032] Icons: 10-First connecting rope; 20-Second connecting rope; 30-Third connecting rope; 100-Launch tube; 110-Launch base; 120-Support; 130-Adjusting arm; 140-Drive connecting tube; 200-Projectile body component; 210-Tail end cartridge case; 211-Hanging ring; 220-Front end cartridge case; 221-Conical concave surface; 300-Deceleration component; 400-Corner reflector component; 500-Drive component. Detailed Implementation
[0033] The technical solution of this utility model will now be clearly and completely described with reference to the accompanying drawings. Obviously, the described embodiments are only some, not all, of the embodiments of this utility model. Based on the embodiments of this utility model, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this utility model.
[0034] In the description of this utility model, it should be noted that the terms "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer," etc., indicating the orientation or positional relationship, are based on the orientation or positional relationship shown in the accompanying drawings and are only for the convenience of describing this utility model 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, and therefore should not be construed as a limitation of this utility model. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and should not be construed as indicating or implying relative importance.
[0035] In the description of this utility model, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "joining" 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 utility model according to the specific circumstances.
[0036] The specific embodiments of this utility model will be described in detail below with reference to the accompanying drawings. It should be understood that the specific embodiments described herein are for illustration and explanation only and are not intended to limit the scope of this utility model.
[0037] like Figure 1 , Figure 2 , Figure 3 and Figure 4 As shown, the corner reflector launching system provided in this embodiment includes: a launching tube 100, a driving component 500, and a projectile component 200; the launching tube 100 is a cylindrical structure with an opening at one end, and a launching chamber is formed inside the launching tube 100. During launching, the projectile component 200 is placed in the launching chamber.
[0038] The drive member 500 is connected to the launch tube 100 and is configured to deliver high-pressure gas into the launch tube 100 to eject the projectile member 200 from the launch tube 100 for launch.
[0039] Specifically, the drive component 500 can be configured as a marine high-pressure gas source or a gas generator. The generated high-pressure gas enters the launch chamber and has sufficient pressure to instantly push the projectile component 200 out of the launch tube 100.
[0040] The interior of the projectile component 200 can accommodate the deceleration component 300 and the corner reflector component 400. The outer surface of the projectile component 200 is connected to the inner wall of the launch tube 100 via a first connecting rope 10. The first connecting rope 10 is configured to be taut so that the projectile component 200 stops in the air, thereby separating the deceleration component 300 and the corner reflector component 400 from the projectile component 200.
[0041] After the projectile component 200 is launched from the launch tube 100 by the drive component 500, the projectile component 200 hovers in the air. When it reaches the designated airspace, the first connecting rope 10 is tightened, causing the main body of the projectile to stop. The descent component 300 and the corner reflector component 400 continue to fly forward due to inertia, thus separating the descent component 300 and the corner reflector component 400 relative to the projectile component 200.
[0042] The corner reflector launching system provided in this embodiment launches the projectile component 200 by placing it in the launching chamber and using the driving force generated by the driving component 500 to launch the projectile component 200, causing it to fly in the air. At this time, the first connecting rope 10 is in a slack state. When the first connecting rope 10 is taut, the projectile component 200 stops in the air, thereby relying on the inertial descent component 300 and the corner reflector component 400 to separate from the projectile component 200, thus achieving the separation operation. This alleviates the technical problem of the complex separation structure used by the corner reflector device to detach from the projectile in the prior art.
[0043] Based on the above embodiments, in an optional embodiment, the corner reflector emitting system provided in this embodiment further includes a emitting base 110; the emitting base 110 is used to be installed on a fixed surface, which can be specifically set as a ship-shaped carrier platform or the ground. When the fixed surface is a ship-shaped carrier platform, the driving component 500 is specifically set as a marine high-pressure gas source, and when the fixed surface is the ground, the driving component 500 is specifically set as a gas generator.
[0044] Furthermore, the launch base 110 is rotatably connected to the launch tube 100 so that the launch tube 100 can rotate relative to the launch base 110, thereby adjusting the angle of the launch tube 100 relative to the ground and adjusting the launch angle of the projectile component 200.
[0045] Specifically, a bracket 120 is provided on the launch base 110, and the launch tube 100 is rotatably connected to the bracket 120. The bracket 120 is fixed on the launch base 110, and the launch tube 100 and the bracket 120 can be connected by a hinge shaft, so that the launch tube 100 can rotate around the bracket 120.
[0046] An adjusting arm 130 is provided on the launch base 110. One end of the adjusting arm 130 is rotatably connected to the launch tube 100, and the other end of the adjusting arm 130 is rotatably connected to the launch base 110. The rotatable connection can be achieved by means of a rotating shaft to realize relative rotation. The adjusting arm 130 is telescopic and can be specifically configured as a telescopic rod, telescopic screw, or other structures. The angle between the launch tube 100 and the launch base 110 can be adjusted by the extension and retraction of the adjusting arm 130, thereby adjusting the launch angle of the projectile component 200.
[0047] Alternatively, the adjusting arm 130 can also be a fixed-length connecting tube or connecting rod structure. One end of the adjusting arm 130 is rotatably connected to the launch tube 100, and multiple locking points are spaced horizontally on the launch base 110. By selecting different locking points, the position of the adjusting arm 130 and the launch base 110 can be adjusted, thereby adjusting the angle between the launch tube 100 and the launch base 110, and consequently adjusting the launch angle of the projectile component 200. In an optional embodiment, the launch base 110 further includes a drive connecting pipe 140; one end of the drive connecting pipe 140 is connected to the launch tube 100, and the other end is connected to the drive component 500. The drive connecting pipe 140 is used to transmit the high-pressure gas generated by the drive component 500 to the launch chamber, thereby causing the high-pressure gas to push the projectile component 200 out of the launch tube 100.
[0048] In an optional embodiment, a hanging ring 211 is provided on the outer surface of the projectile component 200. The hanging ring 211 is located at one end of the projectile component 200 that extends into the launch tube 100, and the end of the first connecting rope 10 away from the launch tube 100 is connected to the hanging ring 211.
[0049] In an optional embodiment, the projectile component 200 includes a tail-end cartridge case 210; a first chamber is formed inside the tail-end cartridge case 210, and the deceleration component 300 is disposed in the first chamber.
[0050] Specifically, the tail-end cartridge case 210 has a cylindrical structure, with one end sealed. The sealed end is located near the launch tube 100. The tail-end cartridge case 210 forms a first chamber, thereby placing the deceleration member 300 inside the tail-end cartridge case 210. The tail-end cartridge case 210 effectively prevents the deceleration member 300 from scraping against the launch tube 100 during firing.
[0051] In an optional embodiment, a second connecting rope 20 is provided inside the tail end cartridge case 210. One end of the second connecting rope 20 is connected to the descent control member 300, and the other end of the second connecting rope 20 is connected to the tail end cartridge case 210.
[0052] Specifically, the second connecting rope 20 is located inside the tail end cartridge case 210. The second connecting rope 20 is used to connect the descent component 300 and the tail end cartridge case 210. When the first connecting rope 10 is taut, after the descent component 300 flies a certain distance relative to the projectile component 200, the second connecting rope 20 is taut, the descent component 300 stops, and the corner reflector component 400 continues to move forward due to inertia, thereby realizing the separation of the descent component 300 and the corner reflector component 400.
[0053] In an optional embodiment, the projectile component 200 further includes a front end cartridge case 220; a second chamber is formed inside the front end cartridge case 220, and the corner reflector component 400 is disposed in the second chamber.
[0054] Specifically, the front cartridge case 220 includes two oppositely arranged cartridge case halves; the two cartridge case halves merge to form a second chamber. It should be noted that the two cartridge case halves merge and are not fixedly connected, ensuring that during the flight, the two cartridge case halves can be split in half by wind force in the air, thereby ejecting the corner reflector component 400.
[0055] In order to ensure that the two cartridge case halves can unfold in the wind, the front end faces of the two cartridge case halves are merged to form a conical concave surface 221. The wind acts on the conical concave surface 221, thereby causing the two cartridge case halves to unfold in the wind.
[0056] In an optional embodiment, the projectile component 200 further includes a third connecting rope 30; one end of the third connecting rope 30 is connected to the deceleration component 300, and the other end of the third connecting rope 30 is connected to the corner reflector component 400. When the second connecting rope 20 is taut, the corner reflector component 400 continues to move forward relative to the deceleration component 300 due to inertia until the third connecting rope 300 is taut, so as to further realize the separation of the corner reflector component 400 and the deceleration component 300.
[0057] Optionally, a rear end cap is provided at the tail of the two cartridge case halves. The rear end cap is provided with a perforation for the third connecting rope 30 to pass through, thereby connecting the second connecting rope 20 to the descent control member 300 and the corner reflector member 400.
[0058] The corner reflector launching system provided in this embodiment allows the projectile component 200 to fly in the air after being pushed out of the launching tube 100 by the driving component 500. At this time, the first connecting rope 10 is in a slack state, allowing the projectile component 200 to fly smoothly. When the projectile component 200 reaches the designated airspace, the first connecting rope 10 tightens, causing the projectile component 200 to stop in the air. Due to inertia, the deceleration component 300 and the corner reflector component 400 continue to fly forward, thereby achieving automatic separation between the two. By reasonably setting the strength and length of the first connecting rope 10, it can be tightened quickly when the projectile component 200 reaches the designated position, thereby accurately triggering the separation action. This separation method based on physical inertia is more reliable than traditional mechanical separation methods and reduces the dependence on additional energy or complex control systems.
[0059] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of this utility model, and are not intended to limit it. Although the utility model has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some or all of the technical features therein. Such modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the embodiments of this utility model.
Claims
1. A corner reflector emitting system, characterized in that, include: Launch tube (100), drive component (500), and projectile component (200); The launch tube (100) has a launch chamber inside, which is used to accommodate the projectile component (200); The drive member (500) is connected to the launch tube (100), and the drive member (500) is configured to deliver high-pressure gas into the launch tube (100) to eject the projectile member (200) from the launch tube (100) for launch; The interior of the projectile component (200) is used to accommodate the descent control component (300) and the corner reflector component (400). The outer surface of the projectile component (200) is connected to the inner wall of the launch tube (100) via a first connecting rope (10). The first connecting rope (10) is configured to be taut to stop the projectile component (200) in mid-air, thereby separating the descent control component (300) and the corner reflector component (400) from the projectile component (200).
2. The corner reflector emitting system according to claim 1, characterized in that, The corner reflector emitting system also includes a emitting base (110); The launch base (110) is used to be mounted on a fixed surface, and the launch base (110) is rotatably connected to the launch tube (100) so that the launch tube (100) can rotate relative to the launch base (110).
3. The corner reflector emitting system according to claim 2, characterized in that, A bracket (120) is provided on the launching base (110), and the launching tube (100) is rotatably connected to the bracket (120); An adjusting arm (130) is provided on the launching base (110). The adjusting arm (130) is connected to the launching tube (100) and is used to adjust the angle between the launching tube (100) and the launching base (110).
4. The corner reflector emitting system according to claim 2, characterized in that, The launch base (110) also includes a drive connecting pipe (140); One end of the drive connecting pipe (140) is connected to the launching tube (100), and the other end of the drive connecting pipe (140) is connected to the driving component (500). The drive connecting pipe (140) is used to transmit the high-pressure gas generated by the driving component (500) to the launching chamber.
5. The corner reflector emitting system according to claim 1, characterized in that, The outer surface of the projectile component (200) is provided with a hanging ring (211), which is used to connect the first connecting rope (10).
6. The corner reflector emitting system according to claim 1, characterized in that, The projectile component (200) includes a tail-end cartridge case (210); The tail-end cartridge case (210) has a first chamber inside, and the descent control member (300) is disposed in the first chamber.
7. The corner reflector emitting system according to claim 6, characterized in that, A second connecting rope (20) is provided inside the tail end cartridge case (210). One end of the second connecting rope (20) is connected to the descent control member (300), and the other end of the second connecting rope (20) is connected to the tail end cartridge case (210).
8. The corner reflector emitting system according to claim 7, characterized in that, The projectile component (200) also includes a front end cartridge case (220); The front end cartridge case (220) has a second chamber inside, and the corner reflector component (400) is disposed in the second chamber.
9. The corner reflector emitting system according to claim 8, characterized in that, The projectile component (200) also includes a third connecting rope (30); One end of the third connecting rope (30) is connected to the descent member (300), and the other end of the third connecting rope (30) is connected to the corner reflector member (400).
10. The corner reflector emitting system according to claim 9, characterized in that, The front end cartridge case (220) includes two oppositely arranged cartridge case halves; The two cartridge case halves merge to form the second chamber, and the front end faces of the two cartridge case halves merge to form a conical concave surface (221).