CN114923373A - Large overload pushing pin device for parachute opening of shell steering engine - Google Patents
Large overload pushing pin device for parachute opening of shell steering engine Download PDFInfo
- Publication number
- CN114923373A CN114923373A CN202210318207.8A CN202210318207A CN114923373A CN 114923373 A CN114923373 A CN 114923373A CN 202210318207 A CN202210318207 A CN 202210318207A CN 114923373 A CN114923373 A CN 114923373A
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- Prior art keywords
- pushing
- pin shaft
- base body
- steering engine
- push pin
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
- F42B10/60—Steering arrangements
- F42B10/66—Steering by varying intensity or direction of thrust
Abstract
The invention discloses a large-overload pushing pin device for parachute opening of a shell steering engine, and belongs to the technical field of weapon equipment. The push pin shaft is arranged in the base body, a buffer component and a power unit are arranged in the push pin shaft, and two ends of the buffer component are respectively connected with the push pin shaft and the power unit; the power unit comprises an electrode and a fuel component, wherein the electrode comprises an electrode plug and a conductive pin, and the fuel component comprises a coating shell and fuel; a first sealing washer is arranged between the base body and the cover body. Under the pushing action of the power unit, the pushing pin shaft does not fall off or rotate, so that the effect of stable operation is achieved. Second seal ring and first seal ring's simultaneous action can continue to make and promote the intracavity and keep sealed to reach and promote the chamber and carry out axial sealed, promote the gaseous acting after the burning, avoid gas leakage, reach and impel fast, the stable release of guarantee steering wheel blade, thereby make the range of guided missile or shell more accurate.
Description
Technical Field
The invention relates to the technical field of weapon equipment, in particular to a large overload pushing pin device for parachute opening of a shell steering engine.
Background
The steering engine is a position (angle) servo driver and is suitable for control systems which need to change and maintain the angle continuously. The steering engine is internally provided with a push pin device which comprises a single-shaft push pin device, the single-shaft push pin device is mainly used for controlling the release of the blade of the steering engine after the missile or cannonball is taken out of the chamber, for some large and heavy large overload missiles or cannonballs, the push pin device with stronger driving force is needed, most of the existing large overload push pin devices for the parachute opening of the cannonball steering engine can not resist ultrahigh overload, the internal structure or irreversible damage can be caused under the ultrahigh overload, the action function can not be realized or the action capacity can not be reduced after the ultrahigh overload loading, and the shooting range of the missiles or the cannonballs can be influenced.
Disclosure of Invention
In order to solve the problems, the invention provides a large overload push pin device for parachute opening of a shell steering engine, which has the advantages of good sealing performance and high safety coefficient and can push ultrahigh loads.
In order to realize the purpose, the invention is realized by the following technical scheme:
a large overload pushing pin device for parachute opening of a shell steering engine comprises a base body and a cover body connected with the base body, wherein an operation cavity is arranged in the base body, a pushing pin shaft is arranged in the operation cavity, and the pushing pin shaft slides in the operation cavity along the axial direction;
a pushing cavity is formed in the pushing pin shaft, a buffering component and a power unit are arranged in the pushing cavity, and two ends of the buffering component are respectively connected with the pushing pin shaft and the power unit;
the power unit comprises an electrode and a fuel component, wherein the electrode comprises an electrode plug and a conductive pin connected with the electrode plug, and the fuel component comprises a coating shell and fuel arranged in the coating shell;
a first sealing washer is arranged between the base body and the cover body.
Further, the buffer component is a hollow support shell, and the hollow support shell slides along the shaft in the pushing cavity.
Furthermore, one end of the base body is provided with a mounting hole used for the push pin shaft to slide, the other end of the base body is a connecting end, and the connecting end, the first sealing washer and the cover body are sequentially fixed through bolts.
Furthermore, the pushing pin shaft comprises a pushing end and a sliding end, the pushing end is arranged outside the base body, and the sliding end is arranged in the operation cavity and axially slides on the inner wall of the base body from the connecting end to the mounting hole.
Furthermore, one end of the base body where the mounting hole is located is provided with a first step, the sliding end is provided with a second step, the second step axially slides along the inner wall of the base body, and the first step is matched with the second step.
Furthermore, a second sealing washer is arranged at the sliding end of the pushing pin shaft, and the second sealing washer is tightly connected with the inner wall of the base body and locks the pushing pin shaft through friction force.
Furthermore, the first sealing washer comprises an outer ring and an inner ring, the sliding end of the pushing pin shaft and the connecting end of the base body are arranged between the outer ring and the inner ring, and the power unit is arranged inside the inner ring.
Further, the length of the inner ring is not greater than the length of the power unit.
Further, the fuel is a combustible material.
Further, the combustible material is gunpowder, and the mass of the combustible material is 80-150 mg.
The invention discloses a large overload pushing pin device for parachute opening of a shell steering engine, which has the beneficial effects that:
(1) the pushing pin shaft runs in the mounting hole, and the running cavity in the base is a cavity with a fixed length, so that the pushing pin shaft can be pushed in the base according to a specific stroke, and the path is stable. The base that is equipped with the mounting hole simultaneously is equipped with first halfpace, and pushes away the end that slides of round pin axle and be equipped with the second halfpace, and first halfpace and second halfpace coincide each other, and under the power pack promotes the effect simultaneously, push away the pin axle and also do not deviate from, and the irrotational reaches steady operation's effect.
(2) According to the fuel injection device, the second sealing washer is set, and before fuel is driven, the second sealing washer can lock the push pin shaft at an initial position, so that the push pin shaft has a positioning effect. Meanwhile, the second sealing washer is beneficial to storage and transportation of the missile or shell, and the safety factor is improved.
(3) In the invention, the internal fuel is also in a fixed range, so that the pushing force pushed out by the push pin can be accurately controlled when the fuel is driven, and the action of the pushing force is not less than 3800N +/-5%. The operation cavity is of a fixed length, so that the pushing stroke of the pushing pin shaft is controllable, the stroke range is 18mm +/-0.2, and the reliability is high. The invention has the characteristics of high thrust maximum load capacity of 300kg, maximum stroke of pushing a steering engine blade of 18mm, high transient performance (the in-place time of 18mm movement is within 15 ms), high reliability (0.99 confidence coefficient 0.9) and the like.
(4) A first sealing washer is arranged between the base body and the cover body, the first sealing washer comprises an outer ring and an inner ring, and the outer ring is arranged outside the sliding ends of the base body and the pushing pin shaft and used for sealing the radial direction of the pushing cavity. And a second sealing washer is arranged at the sliding end of the push pin shaft, and the second sealing washer seals the push cavity under the extrusion action. When fuel pushes the pushing pin shaft to slide, the second sealing washer and the first sealing washer act simultaneously to keep the pushing cavity sealed, so that the pushing cavity is axially sealed, the combusted gas is promoted to work, air leakage is avoided, rapid propulsion is achieved, and the range of a missile or a shell is guaranteed. Through the accurate setting of formation and fuel, the leakproofness that excels in makes the range of guided missile or shell more accurate.
(5) Compared with the steering engine blade release device in the prior art, the single-shaft pin pushing device disclosed by the invention can meet the requirement of high thrust in a larger stroke, the initiating explosive device thrust device has high transient performance and high reliability, the device has high safety, and the initiating explosive device cannot fly out after being actuated. Meanwhile, the interior of the product is completely sealed, and the product has high storage stability. The design overcomes the defects of small thrust, low transient property, low reliability and the like of the prior design.
(6) In the invention, the buffer component is arranged in the pushing cavity, and can buffer the instant high-strength impact force generated by the power unit, effectively resist high overload impact and buffer the pushing cavity after crushing.
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, and 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 these drawings without creative efforts.
FIG. 1 is a schematic structural view of the present invention;
1a cover body, 2 a first sealing gasket, 3 an electrode plug, 4 a second sealing gasket, 5a fuel part and 6 a coating shell; 7 buffer parts, 8 substrates, 9 push pin shafts, 10 conductive pins and 11 bolts;
101 a connecting hole;
201 outer ring, 202 inner ring;
801 mounting holes, 802 connecting ends, 803 first step;
901 push lumen, 902 glide end, 903 push end, 904 second landing.
Detailed Description
In order to make the technical solutions of the present invention better understood, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the specification 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 derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
Example 1
A large overload push pin device for parachute opening of a shell steering engine comprises a base body 8 and a cover body 1 connected with the base body 8, wherein an operation cavity is arranged in the base body 8, a push pin shaft 9 is arranged in the operation cavity, and the push pin shaft 9 slides in the operation cavity along the axial direction;
in the invention, a pushing cavity 901 is arranged in a pushing shaft 9, a buffer part and a power unit are arranged in the pushing cavity 901, and two ends of the buffer part are respectively connected with the pushing shaft 9 and the power unit;
in the invention, the power unit comprises an electrode and a fuel part 5, wherein the electrode comprises an electrode plug 3 and a conductive pin 10 connected with the electrode plug 3, and the fuel part 5 comprises a coating shell and fuel arranged in the coating shell;
in the invention, a first sealing gasket 2 is arranged between the base body 8 and the cover body 1.
One end of a conductive pin 10 of the power unit is inserted into the fuel, and the other end is led out to be communicated with an external power supply. When the power supply is switched on, the conductive pin 10 is connected with the electrode plug 3, so that the electrode plug 3 is electrified to ignite fuel in the electrode plug, the fuel is instantly combusted to generate gas, the gas does work on the pushing pin shaft 9 in a narrow space to push the pushing pin shaft 9 to push outwards, the pushing end 903 of the pushing pin shaft 9 is generally connected with a missile or a shell, and the missile or the shell is launched under the pushing of the pushing pin shaft 9.
In this embodiment, the buffer member is a hollow support shell, and the hollow support shell slides along the shaft in the pushing cavity 901. The buffer component is arranged in the pushing cavity 901, can buffer the instant high-strength impact force generated by the power unit, effectively resists the damage of the reverse impact of high overload to the power unit, the cover body 1 and the first sealing washer 2, fills fuel after the cover body 1 is opened, can continue to be used for many times, and is favorable for the service life of the device when repeatedly launched.
In this embodiment, one end of the base 8 is provided with a mounting hole 801 for sliding the push pin shaft 9, and the other end of the base 8 is a connection end 802. The thickness of the connecting end 802 of the base body 8 is smaller than that of the base body 8, and as the sliding end 902 of the push pin shaft 9 slides on the inner wall of the connecting end 802 of the base body 8, the first sealing washer 2 is sleeved outside the connecting end 802 of the base body 8, so that the operation cavity in the base body 8 and the push cavity 901 in the push pin shaft 9 are in a sealed state, which is beneficial to the work of the combusted gas.
In this embodiment, the push pin shaft 9 includes a pushing end 903 and a sliding end 902, the pushing end 903 is disposed outside the base 8, and the sliding end is disposed inside the operating cavity and slides axially on the inner wall of the base 8 from the connecting end 802 to the mounting hole 801.
The connecting end 802 of the base body 8, the first sealing washer 2 and the cover body 1 are fixed in sequence through the bolt 11. Specifically, the first sealing gasket 2 may be adhered to the inner surface of the cover 1, and the first sealing gasket 2 and the cover 1 are integrated.
It should be further noted that the first sealing washer 2 comprises an outer ring 201 and an inner ring 202, and a space is provided between the outer ring 201 and the inner ring 202, and the space mainly accommodates the sliding end 902 of the push pin shaft 9 and the connecting end 802 of the base body 8. A combustion chamber is formed between the cladding shell of the power unit and the inner wall of the inner ring 202, and the length of the inner ring 202 can be slightly smaller than or equal to the length of the combustion chamber and is arranged inside the inner ring 202. A connection hole 101 is formed at the center of the cover 1, and the connection hole 101 mainly receives the conductive pin 10 to facilitate the contact of the conductive pin 10 with an external power source. The conductive pin 10 is arranged inside the cover body 1, so that the electrical input end is in short circuit, accidental fuel combustion can be prevented, and the safety performance is higher.
According to the invention, a first sealing washer 2 is arranged between the base body 8 and the cover body 1, the first sealing washer 2 comprises an outer ring 201 and an inner ring 202, and the outer ring 201 is arranged outside the sliding ends 902 of the base body 8 and the push pin shaft 9 and is used for sealing the radial direction of the push cavity 901. And a second sealing washer 4 is arranged on the sliding end 902 of the push pin shaft 9, and the second sealing washer 4 seals the push cavity 901 due to the squeezing action. When the fuel pushes the push pin shaft 9 to slide, the second sealing washer 4 and the first sealing washer 2 act simultaneously to continuously enable the push cavity 901 to keep sealed, so that the push cavity 901 is axially sealed, the gas after combustion is promoted to do work, air leakage is avoided, quick pushing is achieved, the blades of the steering engine are quickly released, and instant launching of guided missiles or shells is facilitated. Through the accurate settlement to stroke and fuel, the leakproofness that excels in makes to impel more stably, fast, is favorable to the quick release of steering wheel blade to make the control and the transmission of guided missile or shell more fast, stable.
It should be further noted that the electrode plug 3 is formed by sintering glass and expandable alloy together with the electrode, and has a conductive function. Electrode plug 3 is disposed between the fuel and conductive pin 10 to facilitate ignition of the fuel.
It should be further noted that the push pin shaft 9 includes a pushing end 903 and a sliding end 902, the pushing end 903 is disposed outside the base 8, and the sliding end is disposed inside the operating cavity and slides axially on the inner wall of the base 8 from the connecting end 802 to the mounting hole 801.
It should be further noted that, one end of the base 8 where the mounting hole 801 is located is provided with a first step 803, the sliding end 902 is provided with a second step 904, and the second step 904 slides axially along the inner wall of the base 8, i.e. slides from the connecting end 802 close to the base 8 to the mounting hole 801 direction according to the driving force of combustion, i.e. the missile or shell outside the push pin shaft 9 is launched. Because the first step 803 and the second step 904 are matched with each other, when the sliding end 902 of the push pin shaft 9 is pushed to the end of the mounting hole 801 by the pushing force, the matching between the first step 803 and the second step 904 ensures that the serious consequence caused by the push pin shaft 9 falling out is avoided.
It should be further noted that the sliding end 902 of the push pin shaft 9 is provided with a second sealing washer 4, and the second sealing washer 4 is tightly connected with the inner wall of the base body 8 and locks the push pin shaft 9 through friction. Before the fuel is unburned, the sliding end 902 of the push pin shaft 9 and the connecting end 802 of the base 8 sealingly connect the push pin shaft 9 to the base 8 by compressing the second sealing washer 4. The second sealing washer 4 is an O-shaped ring, has elasticity and can deform. After the fuel burns, the push pin shaft 9 is pushed out by the generated instant larger pushing force, and the pushing force generated by the burning is far greater than the friction force of the second sealing washer 4, so that the push pin shaft 9 can move forwards in the axial direction. But the friction force of the radial second sealing washer 4 still exists, so that the thrust pin shaft 9 can be prevented from rotating in the radial direction, and the thrust pin shaft 9 can be used for stably pushing out and quickly releasing the steering engine blades.
It should be further noted that the fuel in the present invention is a combustible material, and the combustible material is generally a combustible material, including an electrically combustible material such as gunpowder and petroleum, and is generally preferably gunpowder for easy cladding. The mass of the gunpowder material is 80 mg.
Example 2
In addition to embodiment 1, the connection hole 101 of the lid body 1 can be provided as an M10 interface end, and the structure of the device is not damaged when an impact is applied under a high overload of 20000 g.
The electric signal input only needs direct current 5A, the electric conduction initiates fuel combustion, the pushing force effect generated by the combustion is not lower than 3800N +/-5%, the pushing stroke of the pushing pin shaft 9 is controllable, the stroke range is 18mm +/-0.2, the small pushing product can generate high driving force to do work, and the electric pushing device has the characteristics of good safety and high reliability.
The invention has good sealing performance, and can be stored for 12 years for a long time; the safety performance is high, 5min of the 1A1W load condition can not act accidentally, and even if other accidental conditions act, the push pin shaft 9 can not be separated to cause serious results.
Reference herein to "an embodiment" means that a particular feature, structure, or characteristic described in connection with the embodiment can be included in at least one embodiment of the invention. The appearances of the phrase in various places in the specification are not necessarily all referring to the same embodiment, nor are separate or alternative embodiments mutually exclusive of other embodiments. It is explicitly and implicitly understood by one skilled in the art that the embodiments described herein may be combined with other embodiments.
Finally, it should be noted that: the embodiments of the present invention are disclosed only as the preferred embodiments of the present invention, which are only used for illustrating the technical solutions of the present invention and not for limiting the same; although the present invention has been described in detail with reference to the foregoing embodiments, it will be understood by those skilled in the art; the technical solutions described in the foregoing embodiments may still be modified, or some technical features may be equivalently replaced; and such modifications or substitutions do not depart from the spirit and scope of the corresponding technical solutions of the embodiments of the present invention.
Claims (10)
1. The utility model provides a big overload of shell steering wheel parachute-opening promotes device, including the base member and with the lid that the base member is connected, its characterized in that: an operation cavity is arranged in the base body, a push pin shaft is arranged in the operation cavity, and the push pin shaft slides in the operation cavity along the axial direction;
a pushing cavity is formed in the pushing pin shaft, a buffering component and a power unit are arranged in the pushing cavity, and two ends of the buffering component are respectively connected with the pushing pin shaft and the power unit;
the power unit comprises an electrode and a fuel component, wherein the electrode comprises an electrode plug and a conductive pin connected with the electrode plug, and the fuel component comprises an enveloping shell and fuel arranged in the enveloping shell;
a first sealing washer is arranged between the base body and the cover body.
2. The large overload pushing pin device for the parachute opening of the cannonball steering engine as recited in claim 1, wherein: the buffer component is a hollow support shell which slides along the shaft in the pushing cavity.
3. The large overload pushing pin device for the parachute opening of the cannonball steering engine as recited in claim 1, wherein: one end of the base body is provided with a mounting hole for the push pin shaft to slide, the other end of the base body is a connecting end, and the connecting end, the first sealing washer and the cover body are sequentially fixed through bolts.
4. The large overload pushing pin device for the parachute opening of the cannonball steering engine as recited in claim 3, wherein: the pushing pin shaft comprises a pushing end and a sliding end, the pushing end is arranged outside the base body, and the sliding end is arranged in the operation cavity and axially slides on the inner wall of the base body from the connecting end to the mounting hole.
5. The big overload push pin device for parachute opening of the cannonball steering engine as claimed in claim 4, wherein: one end of the base body where the mounting hole is located is provided with a first step, the sliding end is provided with a second step, the second step axially slides along the inner wall of the base body, and the first step is matched with the second step.
6. The large overload pushing pin device for the parachute opening of the cannonball steering engine as recited in claim 3, wherein: and a second sealing washer is arranged at the sliding end of the push pin shaft, is tightly connected with the inner wall of the base body and locks the push pin shaft through friction force.
7. The large overload pushing pin device for the parachute opening of the cannonball steering engine as recited in claim 4, wherein: the first sealing washer comprises an outer ring and an inner ring, the sliding end of the push pin shaft and the connecting end of the base body are arranged between the outer ring and the inner ring, and the power unit is arranged inside the inner ring.
8. The large overload pushing pin device for the parachute opening of the cannonball steering engine as recited in claim 7, wherein: the length of the inner ring is not greater than the length of the power unit.
9. The big overload push pin device for parachute opening of the cannonball steering engine as claimed in claim 1, wherein: the fuel is a combustible material.
10. The big overload push pin device for parachute opening of the cannonball steering engine of claim 9, wherein: the combustible material is gunpowder, and the mass of the combustible material is 80-150 mg.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210318207.8A CN114923373A (en) | 2022-03-29 | 2022-03-29 | Large overload pushing pin device for parachute opening of shell steering engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210318207.8A CN114923373A (en) | 2022-03-29 | 2022-03-29 | Large overload pushing pin device for parachute opening of shell steering engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN114923373A true CN114923373A (en) | 2022-08-19 |
Family
ID=82805293
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210318207.8A Pending CN114923373A (en) | 2022-03-29 | 2022-03-29 | Large overload pushing pin device for parachute opening of shell steering engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114923373A (en) |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE102005035829A1 (en) * | 2005-07-30 | 2007-02-01 | Diehl Bgt Defence Gmbh & Co. Kg | Roll-decoupled fin assembly for artillery shell has guide vane mounted on bearing tube which is located on sleeve-like base body and rotatably and axially adjustable from inactive position into active position |
| CN106323101A (en) * | 2016-09-08 | 2017-01-11 | 北京精密机电控制设备研究所 | Missile-borne rudder wing spreading locking mechanism based on pin pusher actuation |
| CN109595997A (en) * | 2019-01-02 | 2019-04-09 | 西安微电子技术研究所 | The synchronization four-way folding wings locking unfolding mechanism and its method of anti high overload impact |
| CN113357971A (en) * | 2021-06-16 | 2021-09-07 | 重庆航天工业有限公司 | Pushing pin mechanism |
| CN113738739A (en) * | 2020-05-28 | 2021-12-03 | 四川美创达电子科技有限公司 | Multipoint marketing device |
| CN215513562U (en) * | 2021-09-09 | 2022-01-14 | 杭州富嘉汽车部件有限公司 | Automobile guard plate with shock-absorbing function |
-
2022
- 2022-03-29 CN CN202210318207.8A patent/CN114923373A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE102005035829A1 (en) * | 2005-07-30 | 2007-02-01 | Diehl Bgt Defence Gmbh & Co. Kg | Roll-decoupled fin assembly for artillery shell has guide vane mounted on bearing tube which is located on sleeve-like base body and rotatably and axially adjustable from inactive position into active position |
| CN106323101A (en) * | 2016-09-08 | 2017-01-11 | 北京精密机电控制设备研究所 | Missile-borne rudder wing spreading locking mechanism based on pin pusher actuation |
| CN109595997A (en) * | 2019-01-02 | 2019-04-09 | 西安微电子技术研究所 | The synchronization four-way folding wings locking unfolding mechanism and its method of anti high overload impact |
| CN113738739A (en) * | 2020-05-28 | 2021-12-03 | 四川美创达电子科技有限公司 | Multipoint marketing device |
| CN113357971A (en) * | 2021-06-16 | 2021-09-07 | 重庆航天工业有限公司 | Pushing pin mechanism |
| CN215513562U (en) * | 2021-09-09 | 2022-01-14 | 杭州富嘉汽车部件有限公司 | Automobile guard plate with shock-absorbing function |
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