CN113877108A - Ground fire extinguishing bomb rotating tail wing mechanism - Google Patents
Ground fire extinguishing bomb rotating tail wing mechanism Download PDFInfo
- Publication number
- CN113877108A CN113877108A CN202111071758.0A CN202111071758A CN113877108A CN 113877108 A CN113877108 A CN 113877108A CN 202111071758 A CN202111071758 A CN 202111071758A CN 113877108 A CN113877108 A CN 113877108A
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- Prior art keywords
- wing
- shell
- empennage
- root
- wing root
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- A—HUMAN NECESSITIES
- A62—LIFE-SAVING; FIRE-FIGHTING
- A62C—FIRE-FIGHTING
- A62C19/00—Hand fire-extinguishers in which the extinguishing substance is expelled by an explosion; Exploding containers thrown into the fire
Abstract
The invention discloses a rotary tail wing mechanism of a ground fire extinguishing bomb, and belongs to the field of fire extinguishing bombs. The invention comprises an empennage inner shell, an empennage outer shell, a wing root, a wing surface, a rotating shaft, a torsional spring, a rolling bearing, a bayonet lock, a pressure spring, a plug screw and a bottom screw. The locking mechanism consisting of bayonet lock, pressure spring and screw plug can make the tail wing withdraw to the range of elastic diameter under service state, and the wing pieces can be reliably opened and fixed after being launched. The airfoil surface is in a curling arc shape, accords with the aerodynamic structure of the guided missile body, and can provide enough lift force for the missile body in various external complex aerodynamic environments such as fire, hot air flow and the like. A rolling bearing is arranged between the empennage inner shell and the empennage outer shell, and the unstable influence of the wing surface rotation moment on the projectile body is eliminated by utilizing the relative movement of the bearing, so that the stable guidance of the projectile body is realized.
Description
Technical Field
The invention relates to a rotary tail wing mechanism of a ground fire extinguishing bomb, and belongs to the field of fire extinguishing bombs.
Background
The cold launching platform used by the existing fire extinguishing bomb has low gun tube precision, low projectile body launching speed and poor flying stability. The projectile body can be made to rotate to generate a gyro effect to enable the projectile body to be stable by adopting a rotation design, but the rotating speed is difficult to control within a certain range, so that a projectile body guidance control component is easy to generate larger errors, and the shooting precision is reduced. The rotating tail wing can well adjust the pneumatic environment of the projectile body in the flying process through the rotation of the wing surface, so that the projectile body can fly stably. When the existing rotating tail wing structure flies at low speed, because the airflow speed is low, the wing surface stress is not enough to support the wing surface to be in an open state all the time, and the phenomenon of wing surface retraction can occur, thereby causing the instability of a missile body.
Disclosure of Invention
The invention aims to provide a rotary tail wing mechanism of a ground fire extinguishing bomb, wherein the rotary tail wing mechanism is retracted to a bomb diameter range under a service state, a wing surface can be reliably opened and locked after being launched, the rotary tail wing mechanism can freely rotate in the flying process, and a bomb body is kept relatively static.
The purpose of the invention is realized by the following technical scheme:
the invention discloses a rotary tail wing mechanism of a ground fire extinguishing bomb, which comprises a tail wing inner shell, a tail wing outer shell, a wing root, a wing surface, a rotating shaft, a torsional spring, a rolling bearing, a clamping pin, a pressure spring, a plug screw and a bottom screw. The locking mechanism consisting of the bayonet lock, the pressure spring and the blocking screw ensures that the airfoil is always kept in an unfolded state in the flying process. The airfoil surface is in a curling arc shape, accords with the aerodynamic structure of the guided missile body, and can provide enough lift force for the missile body in various external complex aerodynamic environments such as fire, hot air flow and the like. A rolling bearing is arranged between the empennage inner shell and the empennage outer shell, and the unstable influence of the wing surface rotation moment on the projectile body is eliminated by utilizing the relative movement of the bearing, so that the stable guidance of the projectile body is realized.
The wing surface is screwed on the wing root through screws to form the wing surface component.
8 bayonet locks are respectively arranged in step holes on the end surface of the empennage shell, the head parts of the bayonet locks extend out of the middle end surface of the shell, a pressure spring is arranged at the rear part of the bayonet locks, and finally a blocking screw is arranged to compress the pressure spring and the bayonet locks. The pin is not higher than the two middle end surfaces of the empennage shell after being pressed back, and the motion of the wing root is influenced. After the clamping pin is ejected, the clamping pin has enough length to be contacted with the groove on the wing root, so that the wing root is locked.
The grooves at the two ends of the bottom of the wing root of the 4 wing surface parts are clamped on the clamping pins for positioning, the rotating shaft is connected in series from the shaft hole of the end surface of the tail wing shell, and when the rotating shaft extends out of the middle end surface of the wing root, the rotating shaft is rotated into the left torsion spring and the right torsion spring, and finally the rotating shaft is continuously connected to the other end surface of the tail wing shell through the wing root.
A rolling bearing is arranged between the empennage inner shell and the empennage outer shell, one end of the empennage inner shell limits the rolling bearing through a step, and the other end of the empennage inner shell limits the rolling bearing through a bottom screw.
Preferably, the bayonet head projects 5mm beyond the intermediate end face of the housing.
The invention discloses a working method of a rotary tail wing mechanism of a ground fire extinguishing bomb, which comprises the following steps:
before launching, the clamping pin is pressed back into the hole of the empennage shell by using a tool, the wing root is folded back, the wing surface and the wing root are folded back to the elastic diameter together, and the wing surface is fixed by using a fixing ring without unfolding. Before the projectile body is launched, the fixing ring is withdrawn, and the projectile body is loaded into the launching barrel. After the projectile body is launched, the tail wing is separated from the constraint of the launching barrel, and the wing surface part is unfolded under the action of the torsion spring. When the wing surface and the wing root move to the convex part on the shell, the opening edge in the middle of the wing root is pressed against the convex part on the shell, so that the unfolding movement of the wing root is stopped. Meanwhile, after the wing root moves and unfolds, the clamping pin is popped out under the pressure of the pressure spring and clamped into the groove at the bottom of the wing, so that the wing root is locked and cannot rebound, the whole unfolding and locking process of the wing surface is completed, the wing surface can freely rotate in the flying process, and the projectile body is kept relatively static.
Advantageous effects
1. The invention discloses a rotary tail wing mechanism of a ground fire extinguishing bomb, which can enable a tail wing to be retracted to a bomb diameter range in a service state, and wing pieces can be reliably unfolded and fixed after being launched.
2. The invention discloses a rotary tail wing mechanism of a ground fire extinguishing bomb, wherein the appearance of a wing surface adopts a curled arc form, the rotary tail wing mechanism accords with the aerodynamic structure of a guided bomb body, and can provide enough lift force for the bomb body under various external complex aerodynamic environments such as fire, hot air flow and the like.
3. The invention discloses a rotary tail wing mechanism of a ground fire extinguishing bomb, which eliminates the unstable influence of wing surface rotary torque on a bomb body by utilizing the relative movement of a rolling bearing, so that the bomb body realizes guidance control in a relatively stable pneumatic environment.
Drawings
FIG. 1 is an isometric view of a tail mechanism of the present invention;
FIG. 2 is a front view of the tail mechanism of the present invention;
FIG. 3 is a cross-sectional view A-A of the tail mechanism of the present invention;
FIG. 4 is a cross-sectional view B-B of the tail mechanism of the present invention;
FIG. 5 is a cross-sectional view C-C of the tail mechanism of the present invention;
FIG. 6 is a view of the surface components of the tail mechanism of the present invention;
FIG. 7 is a fragmentary view of the bayonet assembly of the tail mechanism of the present invention;
wherein:
the novel wind-driven generator comprises a tail wing inner shell 1, a tail wing outer shell 2, a wing root 3, a wing surface 4, a rotating shaft 5, a torsion spring 6, a rolling bearing 7, a clamping pin 8, a clamping pin 9, a compression spring 10, a plug screw and a bottom screw 11.
Detailed Description
For a better understanding of the objects and advantages of the present invention, reference should be made to the following detailed description taken in conjunction with the accompanying drawings and examples.
As shown in fig. 1 and 2, the rotary tail mechanism for a ground fire extinguishing bomb disclosed in this embodiment, as a rotary tail mechanism capable of stably guiding a fire extinguishing bomb to fly in a cold launching environment, as shown in fig. 4, includes a tail inner casing 1, a tail outer casing 2, a wing root 3, a wing surface 4, a rotating shaft 5, a torsion spring 6, a rolling bearing 7, a latch 8, a compression spring 9, a plug screw 10, and a bottom screw 11. The locking mechanism consisting of the bayonet lock 8, the pressure spring 9 and the stop bolt 10 ensures that the airfoil 4 is always kept in an unfolded state in the flying process. The airfoil 4 is in a curling arc shape, accords with the aerodynamic structure of the guided missile body, and can provide enough lift force for the missile body in various external complex aerodynamic environments such as fire, hot air flow and the like. A rolling bearing 7 is arranged between the empennage inner shell 1 and the empennage outer shell 2, and the unstable influence of the rotating moment of the wing surface 4 on the projectile body is eliminated by utilizing the relative movement of the bearing, so that the projectile body is stably guided.
As shown in fig. 6, the airfoil 4 is screwed to the root 3 to constitute an airfoil member.
As shown in fig. 7, 8 bayonet pins 8 are respectively installed in the step holes on the end face of the empennage shell 2, the head of each bayonet pin 8 extends out of the middle end face of the shell by 5mm, the rear part of each bayonet pin 8 is provided with a pressure spring 6, and finally, a plug screw 10 is installed to compress the pressure spring 9 and the bayonet pin 8. The bayonet lock 8 is pressed back to be not higher than the two middle end surfaces on the empennage shell, and the movement of the wing root 3 is influenced. After the bayonet 8 is ejected, the bayonet has enough length to contact with the groove on the wing root 3, so that the wing root 3 is locked.
As shown in fig. 4, the grooves at the two ends of the bottom of the wing root 3 of the 4 wing surface parts are clamped on the clamping pins 8 for positioning, the rotating shaft 5 is connected in series from the shaft hole of the end surface of the tail wing shell 2, after the rotating shaft 5 extends out from the middle end surface of the wing root, the rotating shaft is rotated to the left and right torsion springs 6, and finally the rotating shaft 5 continues to pass through the wing root 3 to the other end surface of the tail wing shell 2.
As shown in fig. 4, a rolling bearing 7 is arranged between the empennage inner shell 1 and the empennage outer shell 2, one end of the empennage inner shell 1 limits the rolling bearing 7 through a step, and the other end of the empennage inner shell limits the rolling bearing 7 through a bottom screw 11.
The invention discloses a working method of a rotary tail wing mechanism of a ground fire extinguishing bomb, which comprises the following steps:
before launching, use the frock to press the bayonet lock back to in the downthehole of fin shell, make the wing root turn back smoothly, turn back the wing together with the wing root to the bullet footpath, use the fixed ring fixed wing face not to expand. Before the projectile body is launched, the fixing ring is withdrawn, and the projectile body is loaded into the launching barrel. After the projectile body is launched, the tail wing is separated from the constraint of the launching tube, the wing surface part is unfolded under the action of the torsion spring, and when the wing surface and the wing root move to the convex part on the shell, the opening edge in the middle of the wing root is abutted against the convex part on the shell, so that the unfolding movement of the wing root is stopped as shown in fig. 5. Meanwhile, after the wing root moves and unfolds, the clamping pin is popped out under the pressure of the pressure spring and clamped into the groove at the bottom of the wing, so that the wing root is locked and cannot rebound, and the whole unfolding and locking process of the wing surface is finished.
The above detailed description is intended to illustrate the objects, aspects and advantages of the present invention, and it should be understood that the above detailed description is only exemplary of the present invention and is not intended to limit the scope of the present invention, and any modifications, equivalents, improvements and the like made within the spirit and principle of the present invention should be included in the scope of the present invention.
Claims (4)
1. The utility model provides a ground fire extinguishing bomb rotary tail wing mechanism which characterized in that: the tail wing comprises a tail wing inner shell, a tail wing outer shell, a wing root, a wing surface, a rotating shaft, a torsion spring, a rolling bearing, a clamping pin, a pressure spring, a plug screw and a bottom screw; the locking mechanism consisting of a clamping pin, a pressure spring and a blocking screw ensures that the airfoil always maintains an unfolded state in the flying process; the shape of the airfoil surface adopts a curling arc shape, so that the airfoil surface accords with the aerodynamic structure of the guided missile body, and can provide enough lift force for the missile body in various external complex aerodynamic environments such as fire, hot air flow and the like; a rolling bearing is arranged between the empennage inner shell and the empennage outer shell, and the unstable influence of the wing surface rotation moment on the projectile body is eliminated by utilizing the relative movement of the bearing, so that the stable guidance of the projectile body is realized.
2. A rotary fin mechanism for a ground fire extinguishing bomb as claimed in claim 1, wherein: the wing surface is screwed on the wing root through screws to form a wing surface part;
8 clamping pins are respectively arranged in step holes on the end surface of the empennage shell, the heads of the clamping pins extend out of the middle end surface of the shell, a pressure spring is arranged at the rear part of the clamping pins, and finally a blocking screw is arranged to compress the pressure spring and the clamping pins; the clamp pin is pressed back to be not higher than the two middle end surfaces on the empennage shell, so that the motion of the wing root is influenced; after the clamping pin is popped out, the clamping pin has enough length to be contacted with the groove on the wing root, so that the wing root is locked;
grooves at two ends of the bottom of the wing root of the 4 wing surface parts are clamped on the bayonet pins for positioning, a rotating shaft is connected in series from a shaft hole of the end surface of the tail wing shell, when the rotating shaft extends out of the middle end surface of the wing root, a left torsion spring and a right torsion spring are rotated on the rotating shaft, and finally the rotating shaft continuously passes through the wing root to the other end surface of the tail wing shell;
a rolling bearing is arranged between the empennage inner shell and the empennage outer shell, one end of the empennage inner shell limits the rolling bearing through a step, and the other end of the empennage inner shell limits the rolling bearing through a bottom screw.
3. A rotary fin mechanism for a ground fire extinguishing bomb as claimed in claim 1, wherein: the head of the clamping pin extends out of the middle end face of the shell by 5 mm.
4. A rotary fin mechanism for a ground fire extinguishing bomb as claimed in claim 1, 2 or 3, wherein: before launching, the clamping pin is pressed back into the hole of the empennage shell by using a tool, the wing root is folded back, the wing surface and the wing root are folded back to the elastic diameter together, and the wing surface is fixed by using a fixing ring without unfolding. Before the projectile body is launched, the fixing ring is withdrawn, and the projectile body is loaded into the launching barrel. After the projectile body is launched, the tail wing is separated from the constraint of the launching barrel, and the wing surface part is unfolded under the action of the torsion spring. When the wing surface and the wing root move to the convex part on the shell, the opening edge in the middle of the wing root is pressed against the convex part on the shell, so that the unfolding movement of the wing root is stopped. Meanwhile, after the wing root moves and unfolds, the clamping pin is popped out under the pressure of the pressure spring and clamped into the groove at the bottom of the wing, so that the wing root is locked and cannot rebound, the whole unfolding and locking process of the wing surface is completed, the wing surface can freely rotate in the flying process, and the projectile body is kept relatively static.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111071758.0A CN113877108A (en) | 2021-09-14 | 2021-09-14 | Ground fire extinguishing bomb rotating tail wing mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111071758.0A CN113877108A (en) | 2021-09-14 | 2021-09-14 | Ground fire extinguishing bomb rotating tail wing mechanism |
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| Publication Number | Publication Date |
|---|---|
| CN113877108A true CN113877108A (en) | 2022-01-04 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111071758.0A Pending CN113877108A (en) | 2021-09-14 | 2021-09-14 | Ground fire extinguishing bomb rotating tail wing mechanism |
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| CN (1) | CN113877108A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114470578A (en) * | 2022-01-07 | 2022-05-13 | 北斗时空位置服务(北京)有限公司 | System-guiding fire extinguishing bomb |
-
2021
- 2021-09-14 CN CN202111071758.0A patent/CN113877108A/en active Pending
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114470578A (en) * | 2022-01-07 | 2022-05-13 | 北斗时空位置服务(北京)有限公司 | System-guiding fire extinguishing bomb |
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