Launching canister and rocket projectile

Abstract

The utility model relates to a launch canister, ignition device and rocket projectile, launch canister includes barrel body and two first connecting portion, barrel body is equipped with the launch chamber that the projectile body and engine stretch into and place, the two first connecting portion is both provided the side portion of barrel body, and the launch canister is equipped with the launch chamber that the launch body and engine stretch into. The first connecting part is provided with a first end which can be electrically connected with fire control positive and negative electrode wires, and is also provided with a second end which can be used for extending and contacting the connecting ends of the ignition positive and negative electrode wires to realize electric connection, so that the fire control positive and negative electrode wires are electrically connected with the ignition positive and negative electrode wires in a one-to-one correspondence manner respectively. According to the launch canister, the ignition device and the rocket projectile, the problem that the launch angle of the projectile body deviates due to the fact that the initial disturbance of an existing engine ignition mode is large is solved.

Description

Technical Field

[0001] This utility model relates to the field of individual weapon technology, and in particular to a launch tube, ignition device and rocket. Background Technology

[0002] Currently, the existing rocket engine ignition method generally uses an electrical connection between the tail connector and the corresponding connector on the launch tube to transmit the ignition signal. However, after successful ignition, the thrust generated by the engine combustion acts on the connector area on the launch tube, which generates a reaction force acting on the tail of the projectile, causing an initial disturbance to the projectile body and resulting in a deviation in the projectile's launch angle. Utility Model Content

[0003] The main purpose of this invention is to provide a launch tube, ignition device, and rocket, which aims to solve the problem that the existing engine ignition method has a large initial disturbance that causes the launch angle of the rocket to deviate.

[0004] To achieve the above objectives, this utility model proposes a launch tube, comprising a tube body and two first connecting portions. The tube body is provided with a launch cavity into which the projectile and engine extend. The two first connecting portions are both located on the side of the tube body. Each first connecting portion has a first end that can be electrically connected to the positive and negative wires of the fire control system. The first connecting portion also has a second end into which the connecting ends of the positive and negative wires of the ignition system can extend to make contact and achieve electrical connection, so that the positive and negative wires of the fire control system can be electrically connected to the positive and negative wires of the ignition system one-to-one.

[0005] According to some embodiments of the present invention, an installation hole is provided on the side wall of the cylinder, the second end of the first connecting part passes through and seals the installation hole, and the first end is located outside the cylinder.

[0006] According to some embodiments of the present invention, a short-circuit protection component is also included. The short-circuit protection component is detachably connected to the cylinder body and includes a short-circuit wire that can be electrically connected to the ignition positive and negative wires to achieve a short circuit.

[0007] According to some embodiments of the present invention, the short-circuit protection assembly further includes a housing and two conductive terminals into which the connecting ends of the ignition positive and negative wires can extend to make contact and achieve electrical connection. The housing is detachably installed on the cylinder. The two conductive terminals are both located on the side of the housing facing the cylinder and extend into the cylinder. The two ends of the short-circuit wire are respectively connected to the two conductive terminals.

[0008] This utility model also provides an ignition device, including fire control positive and negative wires, ignition positive and negative wires, an engine, and two second connecting parts. The two second connecting parts are respectively disposed on both sides of the engine. One end of the second connecting part is connected to the ignition positive and negative wires, and the other end is in contact with the connection end of the fire control positive and negative wires to achieve electrical connection. The positive and negative terminals of the engine are electrically connected to the ignition positive and negative wires in a one-to-one correspondence.

[0009] In addition, this utility model also provides a rocket, including a projectile body, a launch tube as described in any of the above claims, and the ignition device. The projectile body and the engine are both disposed in the launch tube. The engine is connected to one end of the projectile body facing the launch tube. Two first connecting parts disposed on the launch tube and two second connecting parts disposed on the engine are respectively electrically connected to each other, so that the positive and negative wires of the fire control are respectively electrically connected to the positive and negative wires of the ignition.

[0010] According to some embodiments of the present invention, two first connecting portions are arranged opposite each other in the radial direction of the cylinder, and each second connecting portion is arranged in a position corresponding to the first connecting portion. The first connecting portion and the second connecting portion are abutted together, and the two first connecting portions arranged opposite each other are close to each other, and the engine is positioned by the two second connecting portions.

[0011] According to some embodiments of the present invention, the second connecting part has an abutment groove at one end facing the first connecting part, and the second end of the first connecting part extends into the abutment groove and abuts against the groove wall.

[0012] According to some embodiments of the present invention, the launching tube further includes two adjusting components. Each adjusting component includes a fixing part and a spring. The fixing part is disposed on the outer side wall of the tube body, and a movable cavity is provided inside the fixing part. The spring is disposed inside the movable cavity and abuts against the first end of the first connecting part.

[0013] According to some embodiments of the present invention, the adjustment assembly further includes an adjustment part, which is threadedly connected to the fixed part and extends into the movable cavity. The adjustment part abuts against the end of the spring away from the first connecting part. The positive and negative wires of the fire control are electrically connected to the first connecting part through the adjustment part and the spring.

[0014] This utility model has at least the following beneficial effects:

[0015] In this invention, the cylindrical body is provided with a launching cavity into which the projectile and engine are inserted. The two first connecting parts are both located on the side of the cylindrical body. The first connecting part has a first end that can be electrically connected to the positive and negative wires of the fire control system. The first connecting part also has a second end into which the connecting end of the positive and negative wires of the ignition system can be inserted to make contact and achieve electrical connection, so that the positive and negative wires of the fire control system can be electrically connected to the positive and negative wires of the ignition system one by one. The engine and the projectile are mounted inside the launch tube. The ignition positive and negative wires are connected to the positive and negative terminals of the engine, respectively. Since the fire control positive and negative wires are electrically connected to the first end of the first connecting part, and the second end of the first connecting part is in contact with the connection end of the ignition positive and negative wires to achieve electrical connection, the fire control positive and negative wires and the ignition positive and negative wires are electrically connected in a one-to-one correspondence. The ignition signal is transmitted from the fire control positive and negative wires through the ignition positive and negative wires to the engine. After the engine receives the ignition signal, it completes ignition and launch, and the connection end of the first connecting part and the connection end of the ignition positive and negative wires are then disconnected. This invention achieves electrical connection through mutual contact between the first connecting part and the connecting ends of the ignition positive and negative wires. There is no fixed connection between the two, resulting in a smaller force when they are released. Furthermore, the first connecting part is located on the side of the cylinder, so the thrust of the engine during ignition and combustion will not act on the first connecting part. Therefore, compared with the prior art that uses two tail connectors to connect the engine for ignition, the first connecting part in this patent causes less initial disturbance to the projectile during ignition and launch. At the same time, this patent transmits the external ignition signal to the internal engine through the fire control positive and negative wires and the ignition positive and negative wires, which is more cost-effective than using tail connectors for signal transmission. Attached Figure Description

[0016] To more clearly illustrate the technical solutions in the embodiments of this utility model or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this utility model. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0017] Figure 1 A cross-sectional view of a rocket provided for an embodiment of this utility model;

[0018] Figure 2 A cross-sectional view of a launching tube and an ignition device provided in an embodiment of this utility model;

[0019] Figure 3 for Figure 2 A schematic diagram of the short-circuit protection component.

[0020] Explanation of reference numerals in the attached figures:

[0021] 100-Rocket; 1-Launch tube; 11-Cylinder body; 111-Mounting hole; 12-First connecting part; 13-Short circuit protection component; 131-Short circuit wire; 132-Shell; 133-Conductive terminal; 14-Adjusting component; 141-Fixing part; 142-Spring; 143-Adjusting part; 2-Ignition device; 21-Fire control positive and negative wires; 22-Ignition positive and negative wires; 23-Engine; 24-Second connecting part; 3-Projectile body. Detailed Implementation

[0022] The technical solutions in the embodiments of this utility model are described clearly and completely below. Obviously, the described embodiments are only some embodiments of this utility model, and not all embodiments. Based on the embodiments of this utility model, all other embodiments obtained by those skilled in the art without creative effort are within the protection scope of this utility model.

[0023] It should be noted that if the embodiments of this utility model involve directional indicators (such as up, down, left, right, front, back, etc.), the directional indicators are only used to explain the relative positional relationship and movement of the components in a certain specific posture (as shown in the figure). If the specific posture changes, the directional indicators will also change accordingly.

[0024] Furthermore, if the embodiments of this utility model involve descriptions such as "first" or "second," these descriptions are for descriptive purposes only and should not be construed as indicating or implying their relative importance or implicitly specifying the number of technical features indicated. Therefore, a feature defined with "first" or "second" may explicitly or implicitly include at least one of those features. Additionally, the meaning of "and / or" throughout the text includes three parallel solutions; for example, "A and / or B" includes solution A, solution B, or a solution where both A and B are satisfied simultaneously. Furthermore, the technical solutions of the various embodiments can be combined with each other, but this must be based on the ability of those skilled in the art to implement them. When the combination of technical solutions is contradictory or impossible to implement, it should be considered that such a combination of technical solutions does not exist and is not within the scope of protection claimed by this utility model.

[0025] This utility model provides a launch tube, an ignition device, and a rocket. Figures 1 to 3 This invention provides a specific embodiment of a launch tube, an ignition device, and a rocket.

[0026] like Figure 1 and Figure 2As shown, this utility model embodiment provides an ignition device 2, including a cylindrical body 11 and two first connecting parts 12. The cylindrical body 11 is provided with a launching cavity into which the projectile 3 and the engine 23 extend and are placed. The two first connecting parts 12 are both provided on the side of the cylindrical body 11. The first connecting part 12 has a first end that can be electrically connected to the positive and negative wires 21 of the fire control system. The first connecting part 12 also has a second end into which the connecting end of the positive and negative wires 22 of the ignition system can extend and make contact to achieve electrical connection, so that the positive and negative wires 21 of the fire control system and the positive and negative wires 22 of the ignition system are respectively electrically connected one-to-one.

[0027] In this utility model, the cylindrical body 11 is provided with a launching cavity into which the projectile 3 and the engine 23 are inserted. The two first connecting parts 12 are both provided on the side of the cylindrical body 11. The first connecting part 12 has a first end that can be electrically connected to the fire control positive and negative wires 21. The first connecting part 12 also has a second end into which the connecting end of the ignition positive and negative wires 22 can be inserted to make contact and achieve electrical connection, so that the fire control positive and negative wires 21 and the ignition positive and negative wires 22 are respectively electrically connected one-to-one. The engine 23 and the projectile 3 are installed inside the tube 11 of the launch tube 1. The ignition positive and negative wires 22 are respectively connected to the positive and negative terminals of the engine 23. Since the fire control positive and negative wires 21 are electrically connected to the first end of the first connecting part 12, and the second end of the first connecting part 12 is in contact with the connection end of the ignition positive and negative wires 22 to achieve electrical connection, the fire control positive and negative wires 21 and the ignition positive and negative wires 22 are electrically connected one-to-one. The ignition signal is transmitted from the fire control positive and negative wires 21 through the ignition positive and negative wires 22 to the engine 23. After receiving the ignition signal, the engine 23 completes ignition and launch, and the connection end of the first connecting part 12 and the connection end of the ignition positive and negative wires 22 is then disconnected. This invention achieves electrical connection through mutual contact between the first connecting part 12 and the connecting ends of the ignition positive and negative wires 22. There is no fixed connection between the two, resulting in a smaller force when they are released from contact. Furthermore, the first connecting part 12 is located on the side of the cylinder 11, so the thrust of the engine 23 during ignition and combustion will not act on the first connecting part 12. Therefore, compared with the prior art that uses two tail connectors to connect and ignite the engine 23, the first connecting part 12 in this patent causes less initial disturbance to the projectile 3 during ignition and launch. At the same time, this patent uses the fire control positive and negative wires 21 and the ignition positive and negative wires 22 to transmit the external ignition signal to the internal engine 23, which is more cost-effective than using tail connectors for signal transmission.

[0028] Because pyrotechnic devices such as ammunition require high sealing performance, in order to ensure the sealing performance of the inside of the cylinder 11, in some embodiments, such as... Figure 2As shown, a mounting hole 111 is provided on the side wall of the cylinder 11. The second end of the first connecting part 12 passes through and seals the mounting hole 111, while the first end is located outside the cylinder 11. With this configuration, the first connecting part 12 passes through and seals the mounting hole 111, and the first end of the first connecting part 12 is electrically connected to the fire control positive and negative wires 21 located outside the cylinder 11. This ensures the sealing performance of the launch tube 1 while transmitting the ignition signal from the external fire control positive and negative wires 21 to the inside of the cylinder 11.

[0029] To prevent accidental ignition triggering due to static electricity during storage and transportation, the ignition positive and negative wires 22 need to be short-circuited. Therefore, in some embodiments, such as... Figure 2 and Figure 3 As shown, the launch tube 1 also includes a short-circuit protection component 13, which is detachably connected to the tube body 11. The short-circuit protection component 13 includes a short-circuit wire 131 that can be electrically connected to the ignition positive and negative wires 22 to achieve a short circuit. This configuration ensures that during storage and transportation, the ignition positive and negative wires 22 are short-circuited via the short-circuit wire 131, preventing accidental ignition triggering. When normal use is required, the short-circuit protection component 13 is removed, de-short-circuiting the ignition positive and negative wires 22, allowing normal reception of the ignition signal.

[0030] Specifically, in some embodiments, such as Figure 2 and Figure 3 As shown, the short-circuit protection assembly 13 further includes a housing 132 and two conductive terminals 133 into which the connection ends of the ignition positive and negative wires 22 can extend to achieve electrical connection. The housing 132 is detachably mounted on the cylinder 11. The two conductive terminals 133 are both located on the side of the housing 132 facing the cylinder 11 and extend into the cylinder 11. The two ends of the short-circuit wire 131 are respectively connected to the two conductive terminals 133. Since the conductive terminals 133 are electrically connected to the connection ends of the ignition positive and negative wires 22, the two conductive terminals 133 are the ignition positive and negative terminals. By connecting the two ends of the short-circuit wire 131 to the two conductive terminals 133, short-circuit protection for the ignition positive and negative wires 22 can be achieved.

[0031] This utility model provides an ignition device 2, including a fire control positive and negative wire 21, an ignition positive and negative wire 22, an engine 23, and two second connecting parts 24. The two second connecting parts 24 are respectively disposed on both sides of the engine 23. One end of the second connecting part 24 is connected to the ignition positive and negative wire 22, and the other end is in contact with the connection end of the fire control positive and negative wire 21 to achieve electrical connection. The positive and negative terminals of the engine 23 are electrically connected to the ignition positive and negative wire 22 in a one-to-one correspondence.

[0032] In addition, this utility model also provides a rocket 100, including a projectile 3, a launch tube 1, and an ignition device 2. The projectile 3 and the engine 23 are both disposed inside the tube 11. The engine 23 is connected to the end of the projectile 3 facing the tube 11. Two first connecting parts 12 disposed on the tube 11 and two second connecting parts 24 disposed on the engine 23 are respectively electrically connected to each other, so that the fire control positive and negative wires 21 are respectively electrically connected to the ignition positive and negative wires 22 in a one-to-one correspondence.

[0033] It should be noted that, in this embodiment, the connection end of the ignition positive and negative wires 22 is the second connection part 24, and the connection end of the fire control positive and negative wires 21 is the first connection part 12.

[0034] To improve ignition reliability, in some embodiments, both the fire control positive and negative wires 21 and the ignition positive and negative wires 22 are provided in two sets, and the first connection portion 12 and the second connection portion 24 are each provided in four sets. With this configuration, when one of the ignition components 3 fails, the ignition signal can be transmitted to the engine 23 to complete ignition through the electrical connection between the other set of fire control positive and negative wires 21 and the ignition positive and negative wires 22.

[0035] When the rocket 100 is aimed, the tube 11 of the launch tube 1 is tilted, and the engine 23 may move slightly within the tube 11, causing a deviation in the launch angle and affecting launch accuracy. Therefore, in some embodiments, such as Figure 2As shown, two first connecting portions 12 are arranged opposite each other radially on the launch tube 1, and each second connecting portion 24 is arranged corresponding to the position of the first connecting portion 12. The first connecting portions 12 and the second connecting portions 24 are abutted together. The two oppositely arranged first connecting portions 12 are close to each other, and the mounting base 2 is positioned by the two second connecting portions 24. With this arrangement, the angle of the engine 23 can be fixed by the cooperation of the two oppositely arranged first connecting portions 12 and the two second connecting portions 24, avoiding angular deviation of the engine 23 due to the tilt of the launch tube 1. Furthermore, since the first connecting portions 12 and the second connecting portions 24 are abutted together, when the rocket 100 is loaded on the UAV, the two oppositely arranged first connecting portions 12 can also form a clamping groove to clamp the engine 23.

[0036] To improve the stability of the electrical connection between the fire control positive and negative wires 21 and the ignition positive and negative wires 22, in some embodiments, such as Figure 2 As shown, the second connecting part 24 has an abutment groove at one end facing the first connecting part 12. The second end of the first connecting part 12 extends into the abutment groove and abuts against the groove wall. This arrangement increases the contact area between the first connecting part 12 and the second connecting part 24 through the mutually abutting groove wall and the second end of the first connecting part 12, and prevents relative movement between the first connecting part 12 and the second connecting part 24 during the transportation of the rocket 100. This improves the stability of the electrical connection between the fire control positive and negative wires 21 and the ignition positive and negative wires 22, and ensures the stable transmission of the ignition signal.

[0037] To avoid significant initial disturbance to the projectile 3 caused by the contact between the second end of the first connecting part 12 and the abutment groove of the second connecting part 24 during launch, in some embodiments, such as Figure 2 As shown, the launching tube 1 further includes an adjusting assembly 14, which includes a fixing part 141 and a spring 142. The fixing part 141 is located on the outer wall of the tube body 11, and a movable cavity is provided inside the fixing part 141. The spring 142 is located inside the movable cavity and abuts against the first end of the first connecting part 12. With this configuration, when not launched, the first connecting part 12 and the second connecting part 24 are abutted against each other under the elastic force of the spring 142. When launched, the engine 23 moves axially in the tube body 11, driving the second connecting part 24 to move. The abutting groove of the second connecting part 24 applies a force to the second end of the first connecting part 12, causing the first connecting part 12 to move away from the second connecting part 24, thereby reducing the initial disturbance to the projectile 3.

[0038] Furthermore, in some embodiments, such as Figure 2 As shown, the adjustment assembly 14 further includes an adjustment part 143, which is threadedly connected to the fixed part 141 and extends into the movable cavity. The adjustment part 143 abuts against the end of the spring 142 away from the first connecting part 12. The fire control positive and negative wires 21 are electrically connected to the first connecting part 12 through the adjustment part 143 and the spring 142. With this configuration, the operator can tighten the adjustment part 143, causing it to move radially relative to the fixed part 141 in the launch tube 1, thereby compressing the spring 142 and increasing its elastic force. This elastic force is transmitted to the engine 23 through the first connecting part 12 and the second connecting part 24, thereby adjusting the preload between the tube 11 and the engine 23. This ensures that the first connecting part 12, while clamping the engine 23, minimizes the initial disturbance to the projectile 3 during launch.

[0039] Specifically, the fire control positive and negative wires 21 are welded to the adjusting part 143, the fire control positive and negative wires 21 are electrically connected to the first connecting part 12 through the adjusting part 143 and the spring 142, and the ignition positive and negative wires 22 are welded to the second connecting part 24. This configuration, through the electrical connection between the adjusting part 143, the spring 142, the first connecting part 12, and the second connecting part 24, enables the transmission of the ignition signal from the fire control positive and negative wires 21 from outside the launch tube 1 to the ignition positive and negative wires 22 inside the launch tube 1.

[0040] The above description is only a preferred embodiment of the present utility model and is not intended to limit the present utility model. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present utility model should be included within the protection scope of the present utility model.

Claims

1. A launching tube, characterized in that, The device includes a cylindrical body and two first connecting parts. The cylindrical body has a launching cavity into which the projectile and engine are inserted. The two first connecting parts are both located on the side of the cylindrical body. Each first connecting part has a first end that can be electrically connected to the positive and negative wires of the fire control system. The first connecting part also has a second end into which the connecting end of the positive and negative wires of the ignition system can be inserted to make contact and achieve electrical connection, so that the positive and negative wires of the fire control system can be electrically connected to the positive and negative wires of the ignition system one by one.

2. The launching tube as described in claim 1, characterized in that, An installation hole is provided on the side wall of the cylinder, and the second end of the first connecting part passes through and seals the installation hole, while the first end is located outside the cylinder.

3. The launching tube as described in claim 1, characterized in that, It also includes a short-circuit protection component, which is detachably connected to the cylinder body. The short-circuit protection component includes a short-circuit wire that can be electrically connected to the ignition positive and negative wires to achieve a short circuit.

4. The launching tube as described in claim 3, characterized in that, The short-circuit protection assembly also includes a housing and two conductive terminals into which the connection ends of the ignition positive and negative wires can extend to make contact and achieve electrical connection. The housing is detachably installed on the cylinder. The two conductive terminals are both located on the side of the housing facing the cylinder and extend into the cylinder. The two ends of the short-circuit wire are respectively connected to the two conductive terminals.

5. A rocket, characterized in that, The device includes a projectile, an ignition device, and a launch tube as described in any one of claims 1 to 4. The ignition device includes fire control positive and negative leads, ignition positive and negative leads, an engine, and two second connecting parts. The projectile and the engine are both disposed within the launch tube. The engine is connected to one end of the projectile facing the launch tube. Two first connecting parts on the launch tube and two second connecting parts on the engine are respectively electrically connected to each other. The two second connecting parts are respectively disposed on both sides of the engine. One end of each second connecting part is connected to the ignition positive and negative leads, and the other end is in contact with the connection end of the fire control positive and negative leads to achieve electrical connection. The positive and negative terminals of the engine are electrically connected to the ignition positive and negative leads one-to-one.

6. The rocket as described in claim 5, characterized in that, Two first connecting parts are arranged opposite each other in the radial direction of the cylinder, and each second connecting part is arranged in a position corresponding to the first connecting part. The first connecting parts and the second connecting parts are abutted together. The two first connecting parts arranged opposite each other are close to each other, and the engine is positioned through the two second connecting parts.

7. The rocket as described in claim 6, characterized in that, The second connecting part has an abutment groove at one end facing the first connecting part, and the second end of the first connecting part extends into the abutment groove and abuts against the groove wall.

8. The rocket as described in claim 7, characterized in that, The launching tube also includes two adjusting components. Each adjusting component includes a fixing part and a spring. The fixing part is located on the outer wall of the tube body and has a movable cavity inside. The spring is located inside the movable cavity and abuts against the first end of the first connecting part.

9. The rocket as described in claim 8, characterized in that, The adjustment assembly further includes an adjustment part, which is threadedly connected to the fixed part and extends into the movable cavity. The adjustment part abuts against the end of the spring away from the first connecting part. The positive and negative fire control wires are electrically connected to the first connecting part through the adjustment part and the spring.

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