CN113551569A - Missile-borne double-degree-of-freedom acupuncture ignition mechanism suitable for low-launching overload environment - Google Patents
Missile-borne double-degree-of-freedom acupuncture ignition mechanism suitable for low-launching overload environment Download PDFInfo
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- CN113551569A CN113551569A CN202110803147.4A CN202110803147A CN113551569A CN 113551569 A CN113551569 A CN 113551569A CN 202110803147 A CN202110803147 A CN 202110803147A CN 113551569 A CN113551569 A CN 113551569A
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42C—AMMUNITION FUZES; ARMING OR SAFETY MEANS THEREFOR
- F42C15/00—Arming-means in fuzes; Safety means for preventing premature detonation of fuzes or charges
- F42C15/24—Arming-means in fuzes; Safety means for preventing premature detonation of fuzes or charges wherein the safety or arming action is effected by inertia means
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Abstract
The invention discloses a spring-loaded double-degree-of-freedom acupuncture ignition mechanism suitable for a low-launching overload environment. Under the launching state, when the overload of the recoil increases to a certain degree, the deformation of the upper inertia spring and the lower inertia spring increases, and the fire cap seat and the sleeve move to the position where the firing pin can prick the firing cap under the action of downward inertia force, so that the firing cap fires. Under the condition of falling in service treatment, the fire cap seat and the sleeve reset after the falling overload is finished due to short impact action time. The missile-borne double-degree-of-freedom needling ignition mechanism provided by the invention effectively solves the contradiction between the service processing safety and the ignition reliability during the launching in the low-launching overload and non-rotating environment, and has the advantages of high safety, simple process structure and low cost.
Description
Technical Field
The invention belongs to the fuze ignition technology, and particularly relates to a missile-borne two-degree-of-freedom acupuncture ignition mechanism suitable for a low-launching overload environment.
Background
The mortar shell fuze, rocket shell fuze and other low recoil overload fuze missile-borne mechanical ignition mechanisms are usually used for the activation of thermal batteries and the ignition of self-destruction delay explosive disks, and the action mode mainly comprises that a firing pin punctures a fire cap, namely, an inertia overload action during firing is utilized, an inertia body compresses a safety spring to shift, and then the firing pin and the fire cap move relatively to puncture and fire. Such a missile-borne ignition machineThe safety of the structure relies on a safety spring. The safety falling height is closely related to the safety releasing stroke of the safety spring. In a low-emission overload environment, in order to meet the requirement of safety height drop of more than 1.5 m, a longer safety spring is required to release the safety stroke, and the safety stroke can be limited by the axial dimension of the fuse and is difficult to realize in the structural design of the fuse. The congratulation introduces a mechanical activation mechanism for low-emission overload of a forcedly-elastic reserve battery in a paper of a small-sized low-overload activation mechanism for a forcedly-elastic reserve battery (published in the journal of detection and control academy of academic journal of 2021, the structural principle of the mechanical activation mechanism is that a traditional spring-mass recoil safety mechanism is used for being associated with a mechanical two-degree-of-freedom needling ignition mechanism of the striker piercing fire cap, namely, only after the recoil safety of the spring-mass recoil safety mechanism is released, an inertial body (striker) in the mechanical ignition mechanism of the striker piercing fire cap is released, and then the recoil piercing motion is started. The reliable ignition environment for the given example is peak 1000gTrapezoidal emission overload curve with duration of 5 ms. In general, the structure shape is complex, the producibility is low, the occupied radial dimension is large, and the overload of the working environment is not low enough.
Disclosure of Invention
The invention aims to provide a missile-borne two-degree-of-freedom acupuncture ignition mechanism capable of distinguishing a low-launching overload environment from a service handling accidental falling environment. The mechanism has the advantages of high reliability, simple structure and low cost.
The technical solution for realizing the purpose of the invention is as follows: a bullet-loaded double-degree-of-freedom acupuncture ignition mechanism suitable for a low-launching overload environment comprises a fixed seat body, a fire cap seat, a fire cap, an upper inertia spring, a sleeve, a lower inertia spring and a firing pin; the fixing seat body is cylindrical, the top surface is a closed end, the bottom surface is an open end, and the fire cap seat, the upper inertia spring, the sleeve, the lower inertia spring and the firing pin are coaxially arranged in the inner cavity of the fixing seat body from top to bottom; the firing pin is closed or fixed by point riveting through the fixing seat body; the sleeve is a revolving body, a through hole is formed along the central axis of the sleeve, and the upper inertia spring and the lower inertia spring are symmetrical relative to the sleeve after being assembled; the fire cap is arranged in the fire cap seat; in the assembled state, the firing pin, the lower inertia spring, the sleeve, the upper inertia spring and the fire cap seat are filled in the inner cavity of the fixed seat body.
Compared with the prior art, the invention has the following remarkable advantages: the missile-borne double-degree-of-freedom acupuncture ignition mechanism can distinguish a low-launching overload environment from a falling environment, reliably activates a thermal battery, is used for self-destruction delay explosive tray ignition, and improves the safety of service processing and the action reliability in the launching environment.
Drawings
Fig. 1 shows a schematic structural view of a missile-borne two-degree-of-freedom acupuncture ignition mechanism for upward fire transfer such as for thermal battery activation in the operation of the present invention.
Fig. 2 shows a schematic structural diagram of the missile-borne two-degree-of-freedom acupuncture ignition mechanism for igniting the self-destruction delay explosive disk.
Fig. 3 is a schematic diagram of a second structure of the sleeve in the missile-borne two-degree-of-freedom needling ignition structure.
Detailed Description
The present invention is described in further detail below with reference to the attached drawing figures.
Referring to fig. 1, 2 and 3, a spring-loaded two-degree-of-freedom acupuncture ignition mechanism suitable for a low-emission overload environment is provided, wherein a fixed seat body 1, a fire cap seat 2, a fire cap 3, an upper inertia spring 4, a sleeve 5, a lower inertia spring 6 and a firing pin 7 form a two-degree-of-freedom structure.
The fixing seat body 1 is cylindrical, the top surface is a closed end, the bottom surface is an open end, and the fire cap seat 2, the upper inertia spring 4, the sleeve 5, the lower inertia spring 6 and the firing pin 7 are coaxially arranged in the inner cavity of the fixing seat body 1 from top to bottom; the firing pin 7 is closed or fixed by point riveting through the fixed seat body 1; the sleeve 5 is a revolving body, a through hole is formed along the central axis of the sleeve, and the upper inertia spring 4 and the lower inertia spring 6 are symmetrical relative to the sleeve 5; the fire cap 3 is arranged and fixed in the fire cap base 2 from the upper part of the fire cap base 2.
In the assembled state, the striker 7, the lower inertia spring 6, the sleeve 5, the upper inertia spring 4 and the cap holder 2 fill the inner cavity of the fixing holder body 1.
When need upwards pass a fire when being used for activating the thermal battery, set up first fire transmission hole in the blind end center of fixing base body 1.
Further, the firing pin 7 comprises a firing pin base, a firing pin rod and a firing pin point which are arranged on the top surface of the firing pin base, and the sum of the lengths of the firing pin rod and the firing pin point is greater than the height of the sleeve 5.
When the ignition device is used for ignition of a delayed self-destruction explosive disk, 2-6 second fire transfer holes are formed in a striker base of a striker 7, the axes of the second fire transfer holes are all parallel to the axis of the striker 7, and the second fire transfer holes are uniformly distributed in an annular shape around a needle point, as shown in figure 2.
Furthermore, the upper inertia spring 4 and the lower inertia spring 6 are both pre-pressing springs, the upper inertia spring 4 and the lower inertia spring 6 are both in a compression state, the springs are guaranteed to have certain pre-pressing amount at the initial motion moment, and the reaction force of the fire cap seat 2 and the firing pin 7 on the springs enables the whole elastic-loaded double-freedom-degree acupuncture ignition mechanism to keep balance in an assembly state.
Further, a through hole is opened along the central axis of the sleeve 5, through which the firing pin 7 penetrates to pierce the firing cap 3 upon firing. The top surface and the bottom surface of the sleeve 5 are respectively provided with an annular bulge, the central hole of the annular bulge is the same as the through hole of the sleeve 5 in diameter and communicated with the through hole of the sleeve 5, the outer diameter of the annular bulge is smaller than that of the sleeve 5, and the two annular bulges are respectively used for fixing the upper inertia spring 4 and the lower inertia spring 6.
Further, the sleeve 5 is formed by two identical punched structures welded together coaxially bottom to bottom, as shown in fig. 3.
Under the constraint of limited axial dimension, the invention uses the principle and experience of the fuse double-freedom-degree recoil safety mechanism for reference, designs the fuse needle puncturing ignition mechanism into a double-freedom-degree shock absorber by the lengthening of the firing pin and the design of the through hole of the intermediate inertia body, and can adapt to the ignition with low launching overload reliability and meet the safety requirement of service handling accidental falling.
In the assembled position, the upper inertia spring 4 and the lower inertia spring 6 are both in a compressed state, and spring resistance forces act on the cap holder 2, the sleeve 5 and the striker 7, respectively. When no external force is applied, the reaction force of the fixed seat body 1 and the firing pin 7 enables the whole missile-borne two-degree-of-freedom acupuncture ignition mechanism to keep a balanced state. When the fire cap seat 2 and the sleeve 5 receive the downward inertial force to act, the reaction force of the fixing seat body 1 to the fire cap seat 2 is gradually reduced, and when the reaction force is zero, the fire cap seat 2 is at the critical point of motion. The cap mount 2 will then move out of contact with the mount body 1 and begin to move downwardly, compressing the lower inertia spring 6, acting on the two degree of freedom needle ignition mechanism in response to the downward inertial force. When the sleeve 5 shown in fig. 3 is used, the upper inertia spring 4 and the lower inertia spring 6 are assembled to contact with the bottom of the sleeve 5, so that the working length of the spring is increased, and the working direction in the chamber is longer. Before the lower inertia spring 6 is compressed to the limit position, the response time is longer, and the service handling accidental falling environment and the low-emission overload environment can be more easily distinguished.
Under the condition of handling falling in accident, the fire cap seat 2, the sleeve 5, the upper inertia spring 4, the lower inertia spring 6 and the striker 7 are overloaded by falling impact. The missile-borne double-freedom-degree acupuncture ignition mechanism does not move immediately when being subjected to impact overload, and starts to move after being counteracted with the reaction force in the whole missile-borne double-freedom-degree acupuncture ignition mechanism. When the reaction force is zero, the missile-borne double-degree-of-freedom acupuncture ignition mechanism is at the critical point of motion, the spring begins to compress and deform as the impact overload continues to increase, the sleeve 5 begins to move downwards, and the fire cap seat 2 and the fire cap 3 are separated from the contact with the fixed seat body 1. The spring is slightly deformed by the overload of the recoil and has large resistance at the beginning, and the resistance increasing degree is correspondingly reduced along with the gradual increase of the deformation of the spring. When the lower inertia spring 6 is compressed to the limit position, the sleeve 5 further moves downward and collides with the lower inertia spring 6 compressed to the limit position. Due to the fact that impact action time is short when the vehicle falls, the sleeve 5 can rebound immediately after colliding with the lower inertia spring 6, and ignition cannot be triggered.
In the launching environment, the fire cap base 2, the sleeve 5, the upper inertia spring 4, the lower inertia spring 6 and the firing pin 7 are overloaded by recoil. The missile-borne double-freedom-degree acupuncture ignition mechanism does not move immediately when the recoil overload occurs, but starts to move after being counteracted with the reaction force in the whole missile-borne double-freedom-degree acupuncture ignition mechanism. When the reaction force is zero, the missile-borne double-degree-of-freedom acupuncture ignition mechanism is at the critical point of motion, the spring begins to compress and deform as the recoil overload continues to increase, the sleeve 5 begins to move downwards, and the fire cap seat 2 and the fire cap 3 are separated from the contact with the fixed seat body 1. The spring is slightly deformed by the overload of the recoil and has large resistance at the beginning, and the resistance increasing degree is correspondingly reduced along with the gradual increase of the deformation of the spring. When the lower inertia spring 6 is compressed to the limit position, the sleeve 5 further moves downward and collides with the lower inertia spring 6 compressed to the limit position. Because the launching overload action time is too long, the sleeve 5 collides with the lower inertia spring 6 and then moves upwards, and then is pressed on the firing pin 7 by the squat overload, and gradually approaches to a static state. Then the fire cap base 2 and the fire cap 3 move downwards along with the compression deformation of the upper inertia spring 4 until the fire cap 2 contacts with the firing pin 7, and the firing pin 7 stimulates the firing cap 3 to initiate ignition.
In conclusion, the invention applies the technical principle of the double-freedom-degree shock absorber, the through hole is formed in the center of the inertial body, the firing pin is lengthened to penetrate through the spring and the through hole in the center of the inertial body along the central axis, the launching environment and the service handling accidental falling environment can be reliably distinguished under the smaller size constraint, and the acupuncture ignition under the low-overload launching environment is realized.
The two-degree-of-freedom recoil insurance mechanism referred to by the invention has been discussed in detail in the literature, and is shown in Cao & Ink 'theory research of two-degree-of-freedom recoil insurance mechanism of fuze' (Master academic paper of Nanjing university of science, 2007, 6 months), and the height of the recoil mechanism can be ensured to be 3 m and the height of the recoil mechanism can be 300 m after the optimization designgLeft and right transmission overload environments.
Claims (7)
1. The utility model provides a bullet carries two degree of freedom acupuncture ignition mechanisms suitable for low transmission overload environment which characterized in that: comprises a fixed seat body (1), a fire cap seat (2), a fire cap (3), an upper inertia spring (4), a sleeve (5), a lower inertia spring (6) and a firing pin (7); the fixing seat body (1) is cylindrical, the top surface is a closed end, the bottom surface is an open end, and the fire cap seat (2), the upper inertia spring (4), the sleeve (5), the lower inertia spring (6) and the striker (7) are coaxially arranged in the inner cavity of the fixing seat body (1) from top to bottom; the firing pin (7) is closed or riveted and fixed through the fixing seat body (1); the sleeve (5) is a revolving body, a through hole is formed along the central axis of the sleeve, and the upper inertia spring (4) and the lower inertia spring (6) are symmetrical relative to the sleeve (5) after being assembled; the fire cap (3) is arranged in the fire cap seat (2); in the assembly state, the firing pin (7), the lower inertia spring (6), the sleeve (5), the upper inertia spring (4) and the fire cap seat (2) are filled in the inner cavity of the fixing seat body (1).
2. The missile-borne two-degree-of-freedom acupuncture ignition mechanism suitable for the low-launching overload environment as claimed in claim 1, wherein the two-degree-of-freedom acupuncture ignition mechanism comprises: a through hole is formed along the central axis of the sleeve (5), and during ignition, the firing pin (7) penetrates through the through hole to prick the ignition cap (3).
3. The missile-borne two-degree-of-freedom acupuncture ignition mechanism suitable for the low-launching overload environment as claimed in claim 1, wherein the two-degree-of-freedom acupuncture ignition mechanism comprises: when upward fire transfer is needed, a first fire transfer hole (8) is formed in the center of the closed end of the fixing seat body (1).
4. The missile-borne two-degree-of-freedom acupuncture ignition mechanism suitable for the low-launching overload environment as claimed in claim 2, wherein the two-degree-of-freedom acupuncture ignition mechanism comprises: when the ignition device is used for igniting a self-destruction delay explosive disk, 2-6 second fire transfer holes (9) are formed in a firing pin seat of a firing pin (7), the axes of the second fire transfer holes are all parallel to the axis of the firing pin (7), and are uniformly distributed in an annular shape around the pin tip.
5. The missile-borne two-degree-of-freedom acupuncture ignition mechanism suitable for the low-launching overload environment according to any one of claims 1 to 4, characterized in that: the upper inertia spring (4) and the lower inertia spring (6) are both pre-pressing springs.
6. The missile-borne two-degree-of-freedom acupuncture ignition mechanism suitable for the low-launching overload environment as claimed in claim 2, wherein the two-degree-of-freedom acupuncture ignition mechanism comprises: the top surface and the bottom surface of the sleeve (5) are respectively provided with an annular bulge, a central hole of the annular bulge is communicated with the through hole of the sleeve (5) in the same diameter, the outer diameter of the annular bulge is smaller than that of the sleeve (5), and the two annular bulges are respectively used for fixing the upper inertia spring (4) and the lower inertia spring (6).
7. The missile-borne two-degree-of-freedom acupuncture ignition mechanism suitable for the low-launching overload environment according to any one of claims 1 to 6, characterized in that: the sleeve (5) is formed by coaxially welding the bottom to the bottom of two identical punched structures together in a spot welding manner.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110803147.4A CN113551569B (en) | 2021-07-15 | 2021-07-15 | Missile-borne two-degree-of-freedom acupuncture ignition mechanism suitable for low-launch overload environment |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202110803147.4A CN113551569B (en) | 2021-07-15 | 2021-07-15 | Missile-borne two-degree-of-freedom acupuncture ignition mechanism suitable for low-launch overload environment |
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| CN113551569A true CN113551569A (en) | 2021-10-26 |
| CN113551569B CN113551569B (en) | 2022-06-28 |
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Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB126339A (en) * | 1916-12-22 | 1919-05-15 | Archibald Percy Thomas | Improvements in and relating to Fuses for Projectiles. |
| US2054510A (en) * | 1933-10-09 | 1936-09-15 | Remondy Leon Emile | Percussion fuse for projectiles, bombs and the like |
| GB708351A (en) * | 1950-08-08 | 1954-05-05 | Energa | Improvements in or relating to projectile fuzes |
| CN107314722A (en) * | 2017-04-24 | 2017-11-03 | 重庆长安工业(集团)有限责任公司 | Suitable for low speed, low overload, micro- rotating environment Zhe Fa insurance institutions |
| CN109520382A (en) * | 2018-08-30 | 2019-03-26 | 重庆长安工业(集团)有限责任公司 | Flush type flame reflection igniting high reliability firing device |
| CN109612351A (en) * | 2018-11-07 | 2019-04-12 | 航宇救生装备有限公司 | A kind of delay firing lock using low overload |
| CN112525021A (en) * | 2020-08-17 | 2021-03-19 | 西安机电信息技术研究所 | Small-size in-chamber environment sensitive mechanism |
-
2021
- 2021-07-15 CN CN202110803147.4A patent/CN113551569B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB126339A (en) * | 1916-12-22 | 1919-05-15 | Archibald Percy Thomas | Improvements in and relating to Fuses for Projectiles. |
| US2054510A (en) * | 1933-10-09 | 1936-09-15 | Remondy Leon Emile | Percussion fuse for projectiles, bombs and the like |
| GB708351A (en) * | 1950-08-08 | 1954-05-05 | Energa | Improvements in or relating to projectile fuzes |
| CN107314722A (en) * | 2017-04-24 | 2017-11-03 | 重庆长安工业(集团)有限责任公司 | Suitable for low speed, low overload, micro- rotating environment Zhe Fa insurance institutions |
| CN109520382A (en) * | 2018-08-30 | 2019-03-26 | 重庆长安工业(集团)有限责任公司 | Flush type flame reflection igniting high reliability firing device |
| CN109612351A (en) * | 2018-11-07 | 2019-04-12 | 航宇救生装备有限公司 | A kind of delay firing lock using low overload |
| CN112525021A (en) * | 2020-08-17 | 2021-03-19 | 西安机电信息技术研究所 | Small-size in-chamber environment sensitive mechanism |
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| CN113551569B (en) | 2022-06-28 |
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