阅读说明：本技术 一种固体火箭安全保险结构及使用方法 (Solid rocket safety structure and use method ) 是由 张文雨 张裕林 支勤伍 吴建伟 李阳阳 周志勇 贾致 胡立鑫 于 2021-06-22 设计创作，主要内容包括：本发明提出一种固体火箭安全保险结构及使用方法,解决了传统的点火线路根据发射任务调整通路/短路状态而进行的复杂操作问题。一种固体火箭安全保险结构,包括盖体,盖体内腔设有圆形凹槽,圆形凹槽内设有导电筒,导电筒内设有保险销,保险销一端设有第二导电螺钉,另一端设有拉环,保险销靠近盖体的一端套设有第一压紧簧,盖体的外侧设有一字导电片,一字导电片两端与导电机构相连,盖体的中心设置有放置拉环的低槽和高槽,一字导电片与导电筒电导通。使用本发明的安全保险结构的火箭弹,能在储存时火箭弹点火线路处于短路状态,本技术方案结构简单,点火线路保险状态可根据任务随时调整,即可重复通/短路。(The invention provides a solid rocket safety structure and a using method thereof, which solve the problem of complex operation of a traditional ignition circuit by adjusting a path/short circuit state according to a launching task. The utility model provides a solid rocket safety insurance structure, includes the lid, the lid inner chamber is equipped with circular recess, be equipped with electrically conductive section of thick bamboo in the circular recess, be equipped with the safety catch in the electrically conductive section of thick bamboo, safety catch one end is equipped with the electrically conductive screw of second, the other end is equipped with the pull ring, the safety catch is close to the pot head of lid and is equipped with first compression spring, the outside of lid is equipped with a word conducting strip, a word conducting strip both ends link to each other with electrically conductive mechanism, the center of lid is provided with low groove and the high groove of placing the pull ring, a word conducting strip and electrically conductive section of thick bamboo electrically conductive expert. The rocket projectile using the safety structure can ensure that the ignition circuit of the rocket projectile is in a short circuit state during storage.)

1. A solid rocket safety insurance structure is characterized in that: the novel conductive cover comprises a cover body (1), wherein a circular groove is formed in the inner cavity of the cover body (1), a conductive barrel (5) is arranged in the circular groove, a safety pin (3) is arranged in the conductive barrel (5), a second conductive screw (13) is arranged at one end of the safety pin (3), a pull ring (10) is arranged at the other end of the safety pin, a first pressing spring (6) is sleeved at one end, close to the cover body (1), of the safety pin (3), a word conductive sheet (2) is arranged on the outer side of the cover body (1), two ends of the word conductive sheet (2) are connected with a conductive mechanism, a low groove (15) and a high groove (14) for placing the pull ring (10) are formed in the center of the cover body (1), and the word conductive sheet (2) is electrically conducted with the conductive barrel (5).

2. A solid-rocket safety structure as recited in claim 1, wherein: the conductive mechanism comprises through holes arranged at two ends of the cover body (1), a conductive pin (8) and a second pressing spring (9) are arranged in the through holes, and the second pressing spring (9) is connected with the linear conductive plate (2).

3. A solid-rocket safety structure as recited in claim 1, wherein: the width of the low groove (15) and the high groove (14) is slightly larger than the diameter of the pull ring (10), and the depth of the low groove (15) is larger than that of the high groove (14).

4. A solid-rocket safety structure as recited in claim 1, wherein: the linear conducting strip (2) and the conducting tube (5) are fixed on the cover body (1) through a first conducting screw (11).

5. A solid-rocket safety structure as recited in claim 1, wherein: the inner side wall of the cover body (1) is provided with internal threads.

6. A use method of the solid rocket safety structure of claim 1-5, wherein:

s1) when the rocket projectile does not need to be launched, the pull ring (10) is positioned in the low groove (15), and under the action of the first compression spring (6), the safety pin (3) is contacted and communicated with the conductive cylinder (5), namely, the ignition circuit lead is communicated through the conductive cylinder (5) and is in a short-circuit safety state;

s2) when the rocket projectile needs to be launched, the pull ring (10) is lifted upwards and rotated and placed in the high groove (14), so that the safety pin (3) is separated from the conductive cylinder (5), and the ignition circuit lead is connected with an external power supply and is in a state to be launched.

Technical Field

The invention relates to the technical field of rocket projectile ignition line safety, in particular to a solid rocket safety structure and a using method thereof.

Background

In order to ensure the safety of the rocket projectile ignition circuit, the lead of the rocket projectile ignition circuit is in a short-circuit state in a storage state and can be normally communicated with an external power supply when the rocket projectile ignition circuit is to be launched. The method for realizing the requirement is more, for example, the ignition circuit wires are directly lapped together and then connected with an external power supply when the ignition circuit is to be launched. However, such operation is extremely inconvenient, particularly in a battlefield atmosphere, and it is highly likely to cause erroneous operation, resulting in accidental or abnormal ignition of the ignition circuit.

Disclosure of Invention

The invention provides a solid rocket safety structure and a using method thereof, which solve the problem of complex operation of a traditional ignition circuit by adjusting a path/short circuit state according to a launching task.

The technical scheme of the invention is realized as follows:

the utility model provides a solid rocket safety insurance structure, includes the lid, the lid inner chamber is equipped with circular recess, be equipped with electrically conductive section of thick bamboo in the circular recess, be equipped with the safety catch in the electrically conductive section of thick bamboo, safety catch one end is equipped with the electrically conductive screw of second, the other end is equipped with the pull ring, the safety catch is close to the pot head of lid and is equipped with first compression spring, the outside of lid is equipped with a word conducting strip, a word conducting strip both ends link to each other with electrically conductive mechanism, the center of lid is provided with low groove and the high groove of placing the pull ring, a word conducting strip and electrically conductive section of thick bamboo electrically conductive expert.

Furthermore, the conductive mechanism comprises through holes arranged at two ends of the cover body, a conductive pin and a second compression spring are arranged in the through holes, and the second compression spring is connected with the linear conductive plate.

Further, the width of the low groove and the high groove is slightly larger than the diameter of the pull ring, and the height of the low groove is larger than that of the high groove.

Furthermore, the linear conducting strip and the conducting tube are fixed on the cover body through the first conducting screw.

Further, the inside wall of lid is provided with the internal thread.

A use method of a solid rocket safety insurance structure comprises the following steps:

s1) when the rocket projectile does not need to be launched, the pull ring is positioned in the low groove, and under the action of the first compression spring, the safety pin is contacted and communicated with the conductive cylinder, namely, the ignition circuit lead is communicated through the conductive cylinder and is in a short-circuit safety state;

s2) when the rocket projectile needs to be launched, the pull ring is lifted upwards and rotated and placed in the high groove, so that the safety pin is separated from the conductive cylinder, and the ignition circuit lead is connected with an external power supply and is in a state to be launched.

The beneficial effect that this technical scheme can produce: the rocket projectile using the safety structure can ensure that the ignition circuit of the rocket projectile is in a short-circuit state during storage. After the rocket shell is loaded into the rocket gun, the safety pin is separated from the conductive cylinder by lifting and rotating the pull ring, and the ignition circuit is in a state of waiting for ignition by connecting the ignition circuit lead with an external power supply. If the launching task is cancelled, the pull ring can be rotated and retreated to the original position, the safety pin is communicated with the conductive cylinder in a contact manner, and the ignition circuit is in a short-circuit state; the technical scheme has simple structure, and the safety state of the ignition circuit can be adjusted at any time according to tasks, namely, the ignition circuit can be repeatedly switched on/off.

Drawings

In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the drawings without creative efforts.

FIG. 1 is a front view of the present invention;

FIG. 2 is a top view of the present invention;

FIG. 3 is a right side view of the present invention;

FIG. 4 is a schematic structural view of a tab;

fig. 5 is a schematic structural view of the conductive cylinder.

In the figure: the cover body comprises a cover body 1, a linear conducting strip 2, a safety pin 3, an insulating sleeve 4, a conducting tube 5, a first pressing spring 6, a sealing gasket 7, a conducting pin 8, a second pressing spring 9, a pull ring 10, a first conducting screw 11, a sealing ring 12, a second conducting screw 13, a high groove 14 and a low groove 15.

Detailed Description

The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be obtained by a person skilled in the art without inventive effort based on the embodiments of the present invention, are within the scope of the present invention.

Example 1

As shown in fig. 1 to 5, the embodiment provides a safety structure of a solid rocket, including a cover body 1, a circular groove is formed in an inner cavity of the cover body 1, a conductive cylinder 5 is arranged in the circular groove, the conductive cylinder 5 is connected with the cover body 1 through a sealing ring 12, a sealing gasket 7 is arranged at an outer edge of the conductive cylinder 5 to play a role of sealing, a safety pin 3 is arranged in the conductive cylinder 5, a second conductive screw 13 is arranged at one end of the safety pin 3, a pull ring 10 is arranged at the other end of the safety pin, and the pull ring 10 is convenient for lifting the safety pin 3 by hand and separating and contacting with the conductive cylinder 5 to fix the position of the safety pin 3; the left end sleeve of the safety pin 3 is provided with an insulating sleeve 4, one end sleeve of the safety pin 3 close to the cover body 1 is provided with a first compression spring 6, the outer side of the cover body 1 is provided with a linear conducting strip 2, the two ends of the linear conducting strip 2 are connected with a conducting mechanism, the center of the cover body 1 is provided with a low groove 15 and a high groove 14 for placing a pull ring 10, and the linear conducting strip 2 is electrically conducted with a conducting barrel 5.

The outer side of the cover body 1 is provided with a linear groove for placing a linear conducting strip 2.

The conductive mechanism is communicated with the external power supply anode through the rocket projectile tail, the conductive mechanism is electrically communicated with the linear conductive sheet, and the ignition circuit anode lead, the conductive cylinder 5, the linear conductive sheet 2 and the external power supply anode are electrically communicated to form an anode passage. The second conductive screw 13 is an M4 screw, and the negative lead of the ignition circuit and the negative lead of the rocket projectile body are connected to the M4 screw together, so as to be communicated with the safety pin 3. Namely, the ignition circuit negative electrode lead, the M4 screw, the safety pin 3 and the rocket projectile body negative electrode lead form a negative electrode passage.

The use process of the invention is as follows:

in the storage state of the rocket bomb, the pull ring 10 is positioned in the special lower groove 15 of the pull ring 10 on the outer side of the cover body 1. Under the action of the first compression spring 6, the safety pin 3 is in contact with the conductive cylinder 5 to be communicated, namely, the ignition circuit is communicated with the conductive wire, and is in a short-circuit safety state. When the rocket projectile is in a cocked state, the tab 10 is lifted upwards and rotated to be placed in a dedicated placement slot 14 of the tab 10. Thus, the safety pin 3 is separated from the conductive cylinder 5, and the ignition circuit lead is connected with an external power supply and is in a state to be emitted. When the firing is not needed, the pull ring 10 is lifted upwards and rotated, and is placed again in the special low groove 15 of the pull ring 10, and the ignition line lead is connected again to be in a short circuit state.

The rocket projectile using the ignition circuit safety structure can adjust the ignition circuit safety state at any time according to the use task, and is simple and convenient to operate.

Example 2

Preferably, the conductive mechanism comprises through holes arranged at two ends of the cover body 1, a conductive pin 8 and a second pressing spring 9 are arranged in the through holes, and the second pressing spring 9 is connected with the linear conductive plate 2. The linear conducting plate 2 is communicated with the positive pole of an external power supply through 2 groups of second compression springs 9 and conducting pins 8 and through the tail of a rocket projectile.

The positive electrode lead of the ignition circuit is connected to the first conductive screw 11, namely the positive electrode lead of the ignition circuit, the first conductive screw 11, the conductive cylinder 5, the linear conductive sheet 2 and the positive electrode of the external power supply are communicated to form a positive electrode passage.

Other structures of this embodiment are the same as those of embodiment 1.

Example 3

Preferably, the width of the low groove 15 and the width of the high groove 14 are slightly larger than the diameter of the pull ring 10, the height difference of the low groove 15 and the high groove 14 is 2-4 mm, and the low groove 15 and the high groove 14 are 90 degrees with each other.

The special function of the pull ring 10 at the center of the outer side of the cap body 1 is to place the low groove 15 and the high groove 14 mainly for placing the pull ring 10 in a through or short circuit state. When the pull ring 10 is placed at the position of the lower groove 15, the safety pin 3 is contacted and communicated with the conductive cylinder 5 under the action of the first pressing spring 6, namely, the ignition line is communicated with a wire, and the short-circuit safety state is realized. When the pull ring 10 is lifted and rotated 90 degrees to be placed at the position of the high groove 14, the safety pin 3 is separated from the conductive cylinder 5 due to a certain height difference between the low groove 15 and the high groove 14, so that the ignition circuit is disconnected and is normally communicated with an external power supply to be in a state to be fired. When firing is not desired, pull ring 10 is lifted upward and rotated 90 degrees to rest in the lower slot 15 position and the ignition line conductors reconnect to provide a short circuit condition.

Other structures of this embodiment are the same as those of embodiment 1.

Example 4

Preferably, the linear conducting strip 2 and the conducting tube 5 are fixed on the cover body 1 through the first conducting screw 11. The first conductive screw 11 electrically connects the linear conductive sheet 2 and the conductive barrel 5, and the first conductive screw 11 is an M5 screw.

The conductive cylinder 5 and the linear conductive sheet 2 are respectively fixed on the inner side and the outer side of the cover body 1 through M5 screws and communicated, so that the connection is stable, the disassembly is convenient, and the complex process of molding the conductive cylinder 5 and the linear conductive sheet 2 on the cover body 1 is omitted.

Other structures of this embodiment are the same as those of embodiment 1.

Example 5

Preferably, the inside wall of lid 1 is provided with the internal thread, through internal thread and rocket projectile tail connection.

Other structures of this embodiment are the same as those of embodiment 1.

A use method of a solid rocket safety insurance structure comprises the following steps:

s1) connecting the cover body 1 with the tail of the rocket projectile, electrically connecting the positive pole of an external power supply with the linear conducting strip 2 through a conducting mechanism, electrically connecting the linear conducting strip 2 with the conducting tube 5, electrically connecting the conducting tube 5 with the positive pole lead of the ignition circuit to form a positive pole passage, connecting the negative pole lead of the ignition circuit and the negative pole lead of the rocket projectile body to the second conducting screw 13, and electrically connecting the second conducting screw 13 with the safety pin 3 to form a negative pole passage;

s2) when the rocket projectile does not need to be launched, the pull ring 10 is positioned in the low groove 15, and under the action of the first compression spring 6, the safety pin 3 is contacted and communicated with the conductive cylinder 5, namely, the ignition circuit lead is communicated through the conductive cylinder 5 and is in a short-circuit safety state;

s3) when the rocket projectile needs to be launched, the pull ring 10 is lifted upwards and rotated to be placed in the high groove 14, so that the safety pin 3 is separated from the conductive cylinder 5, and the ignition circuit lead is connected with an external power supply to be in a state to be launched.

Further, in the step 1, an external power supply is electrically conducted with the conductive pin 8 through the rocket projectile tail, and the conductive pin 8 is electrically conducted with the linear conductive sheet 2 through the second compression spring 9.

The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents, improvements and the like that fall within the spirit and principle of the present invention are intended to be included therein.