CN111220032A - Four-channel linkage unlocking mechanism of small folding control surface - Google Patents
Four-channel linkage unlocking mechanism of small folding control surface Download PDFInfo
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- CN111220032A CN111220032A CN201911130789.1A CN201911130789A CN111220032A CN 111220032 A CN111220032 A CN 111220032A CN 201911130789 A CN201911130789 A CN 201911130789A CN 111220032 A CN111220032 A CN 111220032A
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- linkage
- lock ring
- lock
- control surface
- projectile body
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
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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
- F42B10/02—Stabilising arrangements
- F42B10/14—Stabilising arrangements using fins spread or deployed after launch, e.g. after leaving the barrel
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- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Chemical & Material Sciences (AREA)
- Aviation & Aerospace Engineering (AREA)
- Combustion & Propulsion (AREA)
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Abstract
A four-channel linkage unlocking mechanism of a small folding control surface comprises a projectile body, a linkage lock ring, an electromagnetic lock and a manual locking mechanism; the linkage lock ring is rotatably arranged in the projectile body and is connected with the projectile body through the lock ring guide groove; the manual locking mechanism enables the linkage locking ring to be in a locking position, and the locking folding control surface is in a folding state; the electromagnetic lock enables the linkage lock ring to keep a locking position; when the electromagnetic lock is electrified to work, the linkage lock ring is unlocked, the linkage lock ring rotates under the driving of the electromagnetic lock and the action of the spring, the locking of the folded control surface is unlocked, the folded control surface is automatically unfolded, and the working state of controlling the posture of the projectile body is achieved; the four-channel linkage unlocking mechanism simultaneously controls the locking and the unfolding of the four folding control surfaces through the linkage locking ring, and has the advantages of simple structure and good synchronism; in the unfolding process of the folding control surface, the electromagnetic lock actively drives the linkage lock ring, so that the device has the advantage of high reliability; therefore, the requirement of the newly developed certain small ground missile control surface unfolding control is met.
Description
Technical Field
The invention relates to the technical field of missile rudder surface unlocking, in particular to a four-channel linkage unlocking mechanism of a small folding rudder surface.
Background
The common ground-air and ground-ground missiles adopting small folding rudder surfaces in China and abroad mostly adopt a barrel-type launching mode; when the guided missile is installed in the barrel, the control surface is folded into the interior of the guided missile or the outer wall of the guided missile, and the folded control surface is limited in the launching barrel by means of the space of the barrel wall; when the missile is launched, the missile is pushed out of the launching barrel by the launching device, and at the moment when the missile is discharged from the barrel, the folded control surface is unfolded under the action of the control surface unfolding mechanism to enter a working state of controlling the posture of a missile body.
The newly developed small ground missile adopts a two-stage engine to work, and the folded control surface is not allowed to be unfolded after the missile is launched and before the ignition of the two-stage engine, so that the original cylindrical control surface unlocking mechanism cannot meet the use requirement, and a new control surface unlocking mechanism must be developed in a matched manner.
Disclosure of Invention
In order to overcome the defects in the background art, the invention discloses a four-channel linkage unlocking mechanism of a small folding control surface, which comprises a projectile body, a linkage lock ring, an electromagnetic lock and a manual locking mechanism; the linkage lock ring is rotatably arranged in the projectile body and is connected with the projectile body through the lock ring guide groove; when the manual locking mechanism works, the linkage locking ring is in a locking position, and the locking folding control surface is in a folding state; the electromagnetic lock enables the linkage lock ring to keep a locking position; when the electromagnetic lock is electrified to work, the locking of the linkage lock ring is released, the linkage lock ring rotates under the action of the electromagnetic lock and the spring, the locking of the folded control surface is released, the folded control surface is automatically unfolded, and the working state of controlling the posture of the projectile body is achieved.
In order to realize the purpose, the invention adopts the following technical scheme: a four-channel linkage unlocking mechanism of a small folding control surface comprises a projectile body and a linkage lock ring; four sections of lock ring guide plates are uniformly distributed on the inner wall of the projectile body, and the lock ring guide plates are arranged up and down along the axis of the projectile body to form four lock ring guide grooves; the linkage lock ring projectile body is coaxially and rotatably arranged in the inner cavity of the projectile body and is rotatably connected with the projectile body through a lock ring guide groove;
an electromagnetic lock is fixedly arranged on the inner wall of the projectile body, and an electromagnetic lock plate is arranged on the electromagnetic lock; when the electromagnetic lock is in a non-working state, the electromagnetic lock locks the electromagnetic lock plate, and the electromagnetic lock plate is fixedly connected with the electromagnetic lock; the upper end part of the electromagnetic lock plate is provided with a lock plate groove, the inner annular surface of the linkage lock ring is provided with a lock ring limiting block, and the lock ring limiting block is arranged in the lock plate groove at the upper end part of the electromagnetic lock plate;
the projectile body is movably provided with four folding control surfaces, and the upper end parts of the folding control surfaces are provided with control surface baffle grooves; four control surface stop pins are uniformly distributed on the lower surface of the linkage lock ring, and the control surface stop pins and the lock ring hooks are arranged in a staggered mode; the folding control surface is folded on the projectile body in the non-working state, and the control surface stop pin is arranged in the control surface stop groove.
Furthermore, when the electromagnetic lock is in a working state, the electromagnetic lock is electrified to unlock the electromagnetic lock plate, the electromagnetic lock plate rotates under the pushing action of the electromagnetic lock and the action of the spring, and the rotating axis of the electromagnetic lock plate is perpendicular to the axis of the projectile body.
Furthermore, a manual locking mechanism is fixedly arranged on the inner wall of the projectile body, and a manual shifting block is rotatably arranged on the manual locking mechanism; a manual upper locking groove is formed in the inner annular surface of the linkage locking ring; when the manual locking mechanism is in a working state, the manual shifting block rotates to enter the manual locking groove, and the linkage lock is pushed to rotate around the axis of the projectile body.
Furthermore, a key hole is formed in the manual locking mechanism, and a special key is matched with the key hole; when the manual locking mechanism is in a working state, the special key is inserted into a key hole of the manual locking mechanism, and the special key is rotated by hands to drive the manual shifting block to rotate.
Furthermore, the key hole is exposed on the outer surface of the projectile body, so that a special key can be conveniently rotated by hands during assembly of the four-channel linkage unlocking mechanism of the small folding control surface.
Furthermore, a reset spring is arranged on the manual shifting block, when the manual locking mechanism is in a non-working state, the manual shifting block automatically resets under the action of the reset spring, and is separated from the manual locking groove, so that the linkage locking ring is prevented from moving and interfering with the manual shifting block when rotating.
Furthermore, guide plate avoiding grooves are uniformly formed in the outer ring surface of the linkage lock ring and used for assembling the linkage lock ring and the projectile body, and the linkage lock ring is prevented from interfering with the lock ring guide plate in the assembling process to cause incapability of assembling.
Furthermore, four bullet hooks are uniformly and fixedly arranged on the inner wall of the bullet body, four lock ring hooks are uniformly and fixedly arranged on the upper surface of the linkage lock ring, and a spring is arranged between each bullet hook and each lock ring hook; the spring is a tension spring and is respectively connected with the elastic body hook and the lock ring hook through hooks at two ends of the spring; in the assembly process of the linkage lock ring, the manual shifting block rotates anticlockwise to enter the manual upper lock groove, the linkage lock is pushed to rotate anticlockwise around the axis of the projectile body, and the spring stretches to lengthen and accumulate deformation potential energy; the spring accumulated potential energy enables the linkage lock ring and the missile body to be always in a pre-tightening state, the connection rigidity of the linkage lock ring and the missile body is increased, and the linkage lock ring is prevented from generating severe vibration in the missile flying process.
Due to the adoption of the technical scheme, the invention has the following beneficial effects: the invention discloses a four-channel linkage unlocking mechanism of a small folding control surface, which comprises a projectile body, a linkage lock ring, an electromagnetic lock and a manual locking mechanism, wherein the projectile body is provided with a plurality of elastic bodies; the linkage lock ring is rotatably arranged in the projectile body and is connected with the projectile body through the lock ring guide groove; the manual locking mechanism enables the linkage locking ring to be in a locking position, and the locking folding control surface is in a folding state; the electromagnetic lock enables the linkage lock ring to keep a locking position; when the electromagnetic lock is electrified to work, the linkage lock ring is unlocked, the linkage lock ring rotates under the action of the electromagnetic lock and the spring, the locking of the folded control surface is unlocked, the folded control surface is automatically unfolded, and the working state of controlling the posture of the projectile body is achieved; the four-channel linkage unlocking mechanism simultaneously controls the locking and the unfolding of the four folding control surfaces through the linkage locking ring, and has the advantages of simple structure and good synchronism; in the unfolding process of the folding control surface, the electromagnetic lock actively drives the linkage lock ring, so that the device has the advantage of high reliability; therefore, the requirement of the newly developed certain small ground missile control surface unfolding control is met.
Drawings
FIG. 1 is a schematic diagram of a four-channel linkage unlocking mechanism of a small folding control surface;
FIG. 2 is a schematic view of the appearance of an elastomer;
FIG. 3 is a schematic view of the appearance of the interlocking ring;
fig. 4 is an appearance schematic diagram of a folded control surface.
In the figure: 1. a body of elastomer; 1.1, a lock ring guide plate; 1.2, an elastomer hook; 2. a linkage lock ring; 2.1, a lock ring hook; 2.2, a lock ring limiting block; 2.3, manually locking the groove; 2.4, a control surface stop pin; 2.5, a guide plate avoidance groove; 3. a spring; 4. an electromagnetic lock; 4.1, electromagnetic locking plates; 5. a manual locking mechanism; 5.1, manually shifting blocks; 6. folding the control surface; 6.1, a control surface baffle groove.
Detailed Description
The present invention will be explained in detail by the following examples, which are disclosed for the purpose of protecting all technical improvements within the scope of the present invention.
A four-channel linkage unlocking mechanism of a small folding control surface comprises a projectile body 1 and a linkage lock ring 2; four sections of lock ring guide plates 1.1 are uniformly distributed on the inner wall of the projectile body 1, and the lock ring guide plates 1.1 are arranged up and down along the axis of the projectile body to form four sections of lock ring guide grooves; the linkage lock ring 2 and the projectile body 1 are coaxially and rotatably arranged in the inner cavity of the projectile body 1 and are rotatably connected with the projectile body 1 through a lock ring guide groove;
four elastomer hooks 1.2 are uniformly and fixedly arranged on the inner wall of the elastomer 1, four lock ring hooks 2.1 are uniformly and fixedly arranged on the upper surface of the linkage lock ring 2, a spring 3 is arranged between the elastomer hook 1.2 and the lock ring hook 2.1, and the spring 3 is a tension spring;
an electromagnetic lock 4 is fixedly arranged on the inner wall of the bullet body 1, and an electromagnetic lock plate 4.1 is arranged on the electromagnetic lock 4; when the electromagnetic lock 4 is in a non-working state, the electromagnetic lock 4 locks the electromagnetic lock plate 4.1, and the electromagnetic lock plate 4.1 and the electromagnetic lock 4 are in a fixed connection state; a lock plate groove is formed in the upper end of the electromagnetic lock plate 4.1, a lock ring limiting block 2.2 is arranged on the inner annular surface of the linkage lock ring 2, and the lock ring limiting block 2.2 is arranged in the lock plate groove in the upper end of the electromagnetic lock plate 4.1 to prevent the linkage lock ring 2 from rotating;
the projectile body 1 is movably provided with four folding control surfaces 6, and the upper end parts of the folding control surfaces 6 are provided with control surface baffle grooves 6.1; four control surface stop pins 2.4 are uniformly and fixedly arranged on the lower surface of the linkage lock ring 2, and the control surface stop pins 2.4 and the lock ring hooks 2.1 are arranged in a staggered manner; the folding control surface 6 is folded on the projectile body 1 in a non-working state, and the control surface stop pin 2.4 is arranged in the control surface stop groove 6.1 to prevent the folding control surface 6 from unfolding;
when the electromagnetic lock 4 is in a working state, the electromagnetic lock 4 is electrified to unlock the electromagnetic lock plate 4.1, the electromagnetic lock plate 4.1 is driven by the electromagnetic lock 4 to rotate clockwise, and the electromagnetic lock plate 4.1 drives the linkage lock ring 2 to rotate clockwise through the lock plate groove and the lock ring limiting block 2.2;
a manual locking mechanism 5 is fixedly arranged on the inner wall of the projectile body 1, and a manual shifting block 5.1 is rotatably arranged on the manual locking mechanism 5; a manual upper locking groove 2.3 is formed in the inner annular surface of the linkage locking ring 2; when the manual locking mechanism 5 is in a working state, the manual shifting block 5.1 rotates anticlockwise to enter the manual locking groove 2.3, and the linkage locking ring 2 is pushed to rotate anticlockwise around the axis of the projectile body 1;
the locking mechanism 5 is provided with a key hole which is matched with a special key; when the manual locking mechanism 5 is in a working state, the special key is inserted into a key hole of the manual locking mechanism, and the special key is rotated by hands to drive the manual shifting block 5.1 to rotate;
the key hole is exposed out of the outer surface of the missile body 1, and a special key is inserted into the key hole from the outside of the missile body 1 in the missile assembly process, so that the operation is very convenient;
the manual shifting block 5.1 is provided with a return spring, when the manual locking mechanism 5 is in a non-working state, the manual shifting block 5.1 automatically resets under the action of the return spring, and is separated from the manual upper locking groove 2.3, so that the linkage locking ring 2 is prevented from moving and interfering with the manual shifting block 5.1 when working and rotating;
guide plate avoiding grooves 2.5 are uniformly distributed on the outer annular surface of the linkage lock ring 2 and are used for assembling the linkage lock ring 2 and the elastomer 1, so that the linkage lock ring 2 is prevented from interfering with the lock ring guide plate 1.1 in the assembling process to cause that the assembly cannot be carried out;
the spring 3 is a tension spring and is respectively connected with the elastomer hook 1.2 and the lock ring hook 2.1 through hooks at two ends of the spring 3; in the assembly process of the linkage lock ring 2, the manual shifting block 5.1 rotates anticlockwise to enter the manual upper lock groove 2.3, the linkage lock ring 2 is pushed to rotate anticlockwise around the axis of the projectile body 1, the spring 3 is stretched to be lengthened, and deformation potential energy is accumulated; the deformation potential energy accumulated by the spring 3 enables the linkage lock ring 2 and the missile body 1 to be always in a pre-tightening state, and prevents the linkage lock ring 2 from generating severe vibration in the missile flying process.
The assembly process of the four-channel linkage unlocking mechanism of the small folding rudder surface is described as follows: during assembly, firstly, the four lock ring hooks 2.1 and the control surface stop pin 2.4 are arranged on the linkage lock ring 2, and then the linkage lock ring 2 is arranged in a lock ring guide groove of the projectile body 1; fixing a manual locking mechanism 5 on the inner wall of the projectile body 1; installing a folding control surface 6, folding the folding control surface 6 on the projectile body 1, and fixedly keeping the folding state; installing a spring 3; inserting a special key into the key hole, rotating the special key, rotating a manual shifting block 5.1 into a manual upper lock groove 2.3, and pushing a linkage lock ring 2 to rotate anticlockwise into a locking position; the lock ring limiting block 2.2 is arranged in a lock plate groove at the upper end of the electromagnetic lock plate 4.1, and the electromagnetic lock 4 is fixed on the inner wall of the projectile body 1; the special key is rotated reversely, and the manual shifting block 5.1 returns to the original position; and (5) pulling off the special key, and completing the assembly of the four-channel linkage unlocking mechanism of the small folding control surface.
The working process of the four-channel linkage unlocking mechanism of the small folding rudder surface is described as follows: when the electromagnetic lock 4 inputs working current, the electromagnetic lock 4 pushes the electromagnetic lock plate 4.1 to rotate clockwise, the electromagnetic lock plate 4.1 further pushes the linkage lock ring 2 to rotate clockwise, the control surface stop pin 2.4 fixed on the linkage lock ring 2 is separated from the control surface stop groove 6.1, and the folded control surface 6 is unlocked; the folding control surface 6 is automatically unfolded and enters a working state of controlling the posture of the projectile body.
The present invention is not described in detail in the prior art.
Claims (8)
1. A four-channel linkage unlocking mechanism of a small folding control surface is characterized in that: comprises a projectile body (1) and a linkage lock ring (2); a plurality of sections of lock ring guide plates (1.1) are uniformly distributed on the inner wall of the projectile body (1) along the circumferential direction, and the lock ring guide plates (1.1) are arranged up and down along the axis of the projectile body to form lock ring guide grooves; the linkage lock ring (2) is in a ring plate shape, coaxially and rotatably arranged in the inner cavity of the projectile body (1), and is rotatably connected with the projectile body (1) through a lock ring guide groove;
an electromagnetic lock (4) is fixedly arranged on the inner wall of the projectile body (1), and an electromagnetic lock plate (4.1) is arranged on the electromagnetic lock (4); when the electromagnetic lock (4) is in a non-working state, the electromagnetic lock (4) locks the electromagnetic lock plate (4.1), and the electromagnetic lock plate (4.1) is fixedly connected with the electromagnetic lock (4); a lock plate groove is formed in the upper end of the electromagnetic lock plate (4.1), a lock ring limiting block (2.2) is arranged on the inner annular surface of the linkage lock ring (2), and the lock ring limiting block (2.2) is arranged in the lock plate groove in the upper end of the electromagnetic lock plate (4.1);
the missile body (1) is movably provided with a folding control surface (6), and the upper end part of the folding control surface (6) is provided with a control surface baffle groove (6.1); control surface stop pins (2.4) are uniformly distributed on the lower surface of the linkage lock ring (2); the folding control surface (6) is folded on the projectile body (1) in a non-working state, and the control surface stop pin (2.4) is arranged in the control surface stop groove (6.1).
2. The four-channel linkage unlocking mechanism of the small folding rudder surface as claimed in claim 1, which is characterized in that: when the electromagnetic lock (4) is in a working state, the electromagnetic lock plate (4.1) is unlocked by electrifying, and the electromagnetic lock plate (4.1) rotates under the pushing of the electromagnetic lock (4) and the action of the spring (3).
3. The four-channel linkage unlocking mechanism of the small folding rudder surface as claimed in claim 1, which is characterized in that: a manual locking mechanism (5) is fixedly arranged on the inner wall of the projectile body (1), and a manual shifting block (5.1) is rotatably arranged on the manual locking mechanism (5); a manual upper locking groove (2.3) is formed in the inner annular surface of the linkage locking ring (2); when the manual locking mechanism (5) is in a working state, the manual shifting block (5.1) rotates to enter the manual locking groove (2.3) to push the linkage locking ring (2) to rotate around the axis of the projectile body (1).
4. The four-channel linkage unlocking mechanism of the miniature folding rudder surface as claimed in claim 3, which is characterized in that: a key hole is formed in the locking mechanism (5), and a special key is matched with the key hole; when the manual locking mechanism (5) is in a working state, the manual shifting block (5.1) is driven to rotate by a special key.
5. The four-channel linkage unlocking mechanism for the miniature folding rudder surface as claimed in claim 4, which is characterized in that: the key hole is exposed out of the outer surface of the projectile body (1).
6. The four-channel linkage unlocking mechanism of the miniature folding rudder surface as claimed in claim 3, which is characterized in that: the manual shifting block (5.1) is provided with a return spring, and when the manual locking mechanism (5) is in a non-working state, the manual shifting block (5.1) automatically resets under the action of the return spring to be separated from the manual locking groove (2.3).
7. The four-channel linkage unlocking mechanism of the small folding rudder surface as claimed in claim 1, which is characterized in that: and guide plate avoiding grooves (2.5) are uniformly distributed on the outer annular surface of the linkage lock ring (2).
8. The four-channel linkage unlocking mechanism of the small folding rudder surface as claimed in claim 1, which is characterized in that: bullet hooks (1.2) are uniformly and fixedly arranged on the inner wall of the bullet body (1), lock ring hooks (2.1) are uniformly and fixedly arranged on the upper surface of the linkage lock ring (2), and a spring (3) is arranged between the bullet hooks (1.2) and the lock ring hooks (2.1); the spring (3) is a tension spring and is respectively connected with the elastomer hook (1.2) and the lock ring hook (2.1) through hooks at two ends of the spring (3).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911130789.1A CN111220032B (en) | 2019-11-18 | 2019-11-18 | Four-channel linkage unlocking mechanism of small folding control surface |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911130789.1A CN111220032B (en) | 2019-11-18 | 2019-11-18 | Four-channel linkage unlocking mechanism of small folding control surface |
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| Publication Number | Publication Date |
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| CN111220032A true CN111220032A (en) | 2020-06-02 |
| CN111220032B CN111220032B (en) | 2022-05-27 |
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| CN201911130789.1A Active CN111220032B (en) | 2019-11-18 | 2019-11-18 | Four-channel linkage unlocking mechanism of small folding control surface |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113375511A (en) * | 2021-07-15 | 2021-09-10 | 北京新风航天装备有限公司 | Folding, fixing and unfolding mechanism for control surface |
| CN113624074A (en) * | 2021-07-21 | 2021-11-09 | 上海机电工程研究所 | Locking and unlocking device for folding rudder of guided missile |
| CN114408163A (en) * | 2022-02-08 | 2022-04-29 | 中天长光(青岛)装备科技有限公司 | Miniature steering engine with foldable rudder blade |
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| EP0499907A2 (en) * | 1991-02-20 | 1992-08-26 | DIEHL GMBH & CO. | Projectile having deployable fins |
| US20130193265A1 (en) * | 2012-01-27 | 2013-08-01 | Tda Armements S.A.S. | Steering Section for Guided Munition |
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| CN108871103A (en) * | 2018-06-14 | 2018-11-23 | 湖北三江航天红峰控制有限公司 | A kind of miniature missile folds the delay unfolding mechanism of rudder piece |
| CN110230955A (en) * | 2019-06-28 | 2019-09-13 | 浙江理工大学 | Retaining mechanism and its expansion locking method is unfolded in submersible folding wings synchronous horizontal |
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2019
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| US4860969A (en) * | 1987-06-30 | 1989-08-29 | Diehl Gmbh & Co. | Airborne body |
| EP0499907A2 (en) * | 1991-02-20 | 1992-08-26 | DIEHL GMBH & CO. | Projectile having deployable fins |
| US20130193265A1 (en) * | 2012-01-27 | 2013-08-01 | Tda Armements S.A.S. | Steering Section for Guided Munition |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113375511A (en) * | 2021-07-15 | 2021-09-10 | 北京新风航天装备有限公司 | Folding, fixing and unfolding mechanism for control surface |
| CN113624074A (en) * | 2021-07-21 | 2021-11-09 | 上海机电工程研究所 | Locking and unlocking device for folding rudder of guided missile |
| CN114408163A (en) * | 2022-02-08 | 2022-04-29 | 中天长光(青岛)装备科技有限公司 | Miniature steering engine with foldable rudder blade |
| CN114408163B (en) * | 2022-02-08 | 2023-09-08 | 中天长光(青岛)装备科技有限公司 | Steering wheel with foldable rudder piece |
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| CN111220032B (en) | 2022-05-27 |
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