CN115979074A - Missile empennage folding mechanism capable of unlocking folding and locking by utilizing steering engine and missile - Google Patents
Missile empennage folding mechanism capable of unlocking folding and locking by utilizing steering engine and missile Download PDFInfo
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- CN115979074A CN115979074A CN202211648460.6A CN202211648460A CN115979074A CN 115979074 A CN115979074 A CN 115979074A CN 202211648460 A CN202211648460 A CN 202211648460A CN 115979074 A CN115979074 A CN 115979074A
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Abstract
The invention discloses a missile empennage folding mechanism for releasing folding locking by using a steering engine and a missile. Missile fin folding mechanism includes: the inner wing is arranged on the steering engine rotating shaft; an outer wing foldably provided at an upper portion of the inner wing; the unfolding mechanism is arranged between the inner wing and the outer wing and used for driving the outer wing to rotate around the inner wing for unfolding; the unfolding locking mechanism is arranged between the inner wing and the outer wing and used for locking the unfolded outer wing; and the folding locking mechanism is embedded in the outer wing, and when the outer wing is in a folding state, the folding locking mechanism keeps a folding locking state. The invention utilizes the empennage steering engine as unlocking excitation of the folding empennage, does not increase redundant equipment, realizes dual purposes of one empennage steering engine, and simultaneously can provide certain locking torque for the steering engine rotating shaft when the steering engine is not electrified, thereby improving the reliability of folding locking.
Description
Technical Field
The invention relates to the technical field of missile empennages, in particular to a missile empennage folding mechanism for releasing folding locking by using a steering engine and a missile with the folding mechanism, which are suitable for folding locking and quick unfolding locking of a missile empennage.
Background
With the increasing application of the new generation of stealth combat platforms, the demand of the embedded launching missile is more and more prominent, and the requirement provides strict constraint for the space design envelope of the missile, so that the adoption of the folding tail wing technology is an effective way for improving the utilization rate of the limited space. By adopting the folding tail wing technology, the space occupied by the tail wing can be effectively reduced, the payload of the carrier can be increased, the fighting capacity of the carrier can be improved, and the overall arrangement space of the carrier body can be improved in a limited space. The empennage folding mechanism is used as a key part, and the folding mechanism is required to be simple in structure, stable, rapid and reliable in unfolding process and small in impact on the projectile body during unfolding.
At present, the folded tail wings are mostly restrained in the folded state by external restraint objects, for example, the folded tail wings are restrained by the inner walls of launching tubes or the folded tail wings are restrained by different soft objects such as cloth belts and copper wires. The method for restraining the folded state of the tail wing by adopting the external restraint object can limit the mounting occasions of the missile and possibly generate redundant objects to influence the safety of the carrier.
The information disclosed in this background section is only for enhancement of understanding of the general background of the invention and should not be taken as an acknowledgement or any form of suggestion that this information forms the prior art already known to a person skilled in the art.
Disclosure of Invention
The technical problem solved by the invention is as follows: aiming at the defects of the existing empennage folding technology, the empennage folding mechanism which is simple in mechanism design, safe, reliable, stable in unfolding and convenient for practical engineering application is provided. The folding locking device is used for folding and locking the tail wings of the guided missiles during hanging flight and automatically unfolding and locking the tail wings during flying.
According to one aspect of the invention, a missile empennage folding mechanism for unlocking folding locking by using a steering engine comprises:
the inner wing is arranged on the steering engine rotating shaft;
an outer wing foldably provided at an upper portion of the inner wing;
the unfolding mechanism is arranged between the inner wing and the outer wing and used for driving the outer wing to rotate around the inner wing and unfold;
the unfolding locking mechanism is arranged between the inner wing and the outer wing and used for locking the unfolded outer wing;
and the folding locking mechanism is embedded in the outer wing, and when the outer wing is in a folding state, the folding locking mechanism keeps a folding locking state.
Furthermore, the unfolding mechanism adopts a group of left-handed and right-handed rectangular torsion springs, and the cross section of the unfolding mechanism adopts a rectangular cross section.
Further, the unfolding locking mechanism comprises a locking pin and a compression spring, the locking pin and the compression spring are installed in the locking pin hole of the inner wing, and in the unfolding state, the locking pin is inserted into the locking pin hole of the outer wing under the action of the compression spring to lock the outer wing.
Further, folding locking mechanical system is including installation piece, couple pivot, torsion spring, couple and couple locking block, the installation piece in bury in outer wing one side, the couple is in can rotate around the couple pivot under the torsion spring effect, the couple locking block sets up in the couple inslot of body of bullet.
Further, during folding, will the couple is rotatory 90 around the couple pivot, and folding outer wing again makes the couple breach hooks couple locking piece, accomplishes outer wing folding locking, couple breach surface with the face contact is kept to couple locking piece lower surface.
Furthermore, when the outer wing needs to be unfolded, the steering engine receives an instruction to deflect a preset angle, the hook is separated from the constraint of the hook locking block, and the hook is recovered into the mounting block under the action of the torsion spring.
Furthermore, the interface of the inner wing and the outer wing adopts a broken line type design.
Further, the deployment mechanism comprises:
the front spring seat is arranged in the front rotating shaft hole of the inner wing;
the rotating shaft penetrates through the rear rotating shaft hole of the inner wing, penetrates through the rotating shaft hole of the outer wing and penetrates through the front rotating shaft hole of the inner wing;
the middle spring seat penetrates to the middle part of the rotating shaft and is fixedly connected with the rotating shaft and the outer wing;
pins at two ends of the left-handed rectangular torsion spring are respectively inserted into pin grooves of the front spring seat and the middle spring seat;
the rear spring seat is arranged in the inner wing rear rotating shaft hole;
and pins at two ends of the right-handed rectangular torsion spring are respectively inserted into pin grooves of the middle spring seat and the rear spring seat.
Furthermore, the outer wing and the inner wing are provided with inclined planes at the rotating shaft hole, and after the outer wing and the inner wing are unfolded in place, the two inclined planes are mutually attached.
According to another aspect of the invention, a missile is provided, which comprises the missile tail wing folding mechanism for unlocking folding by using the steering engine.
Compared with the prior art, the invention has the advantages that:
(1) The tail wing of the invention is folded and locked only by utilizing the self parts of the missile under the condition of no external constraint object, no redundancy is generated, and the influence on the aircraft during launching can be effectively reduced;
(2) The tail wing steering engine is used as unlocking excitation of the folding tail wing, redundant equipment is not added, the tail wing steering engine has two purposes, and meanwhile, when the steering engine is not powered on, a rotating shaft of the steering engine can provide a certain locking torque, so that the reliability of folding and locking is improved;
(3) The unfolding mechanism of the invention adopts the rectangular torsion spring as a power source, the section of the spring is rectangular, the torsion moment can be improved, the outer envelope size of the spring is reduced, the spring linearly outputs the spring force in the unfolding process, the unfolding process is rapid and stable, and the phenomena of clamping stagnation, pause and impact and the like are not easy to occur;
(4) Except the empennage steering engine, other pure mechanical parts have simple structure and high reliability, have no inflammable and explosive dangerous goods such as initiating explosive devices, high-pressure gas and the like, and have remarkable advantages in the aspects of test, transportation, storage and the like;
(5) The locking pin of the locking mechanism adopts a redundant design, so that the impact resistance of the locking pin can be effectively improved, and the reliability of unfolding locking is improved by double insurance.
The method and apparatus of the present invention have other features and advantages which will be apparent from or are set forth in detail in the accompanying drawings and the following detailed description, which are incorporated herein, and which together serve to explain certain principles of the invention.
Drawings
The above and other objects, features and advantages of the present invention will become more apparent by describing in more detail exemplary embodiments thereof with reference to the attached drawings, in which like reference numerals generally represent like parts.
Fig. 1 is a schematic view showing a deployed state of a tail according to an embodiment of the present invention.
FIG. 2 is a schematic view of a deployment mechanism according to an embodiment of the invention.
Fig. 3 is a schematic view of a folded state of the rear wing according to an embodiment of the present invention.
FIG. 4 is an expanded schematic view of a fold lock mechanism according to an embodiment of the present invention.
Detailed Description
Preferred embodiments of the present invention will be described in more detail below. While the following describes preferred embodiments of the present invention, it should be understood that the present invention may be embodied in various forms and should not be limited by the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the invention to those skilled in the art.
The invention discloses a missile tail wing folding mechanism for releasing folding locking by using a steering engine. The steering engine is fixed with the missile body through a screw, a steering engine rotating shaft is inserted into an inner wing mounting hole and fixedly connected with an inner wing, a locking pin and a compression spring are mounted in the inner wing locking pin hole, the inner wing and an outer wing are connected through an unfolding locking mechanism, the outer wing can rotate around the rotating shaft under the action of a rectangular torsion spring, and the folding locking mechanism is embedded in the outer wing. The invention can realize that the tail wing of the missile is folded and locked and automatically and rapidly unfolded and locked only by the parts of the missile under the condition of no external constraint object, and has safe and reliable structure.
The invention provides a missile empennage folding mechanism for releasing folding locking by using a steering engine, which comprises:
the inner wing is arranged on the steering engine rotating shaft;
an outer wing foldably provided at an upper portion of the inner wing;
the unfolding mechanism is arranged between the inner wing and the outer wing and used for driving the outer wing to rotate around the inner wing for unfolding;
the unfolding locking mechanism is arranged between the inner wing and the outer wing and used for locking the unfolded outer wing;
and the folding locking mechanism is embedded in the outer wing, and when the outer wing is in a folding state, the folding locking mechanism keeps a folding locking state.
The missile empennage folding mechanism is used for folding and locking the missile empennages during hanging flight and automatically unfolding and locking the missile empennages during flying. The missile body is provided with a steering engine mounting hole, the steering engine is fixedly connected with the missile body through a screw, and a steering engine rotating shaft is inserted into the inner wing mounting hole and is fixedly connected with the inner wing through a screw. The locking pin and the compression spring are mounted in the inner wing locking pin hole. In the unfolded state, the locking pin is inserted into the outer wing locking pin hole under the action of the compression spring to lock the outer wing. After the folding locking mechanism is unlocked, the outer wing can rotate around the inner wing to be unfolded under the action of the unfolding mechanism. The folding locking mechanism is embedded in the outer wing, and when the folding locking mechanism is in a folding state, the folding locking mechanism keeps the folding locking state. The rotating shaft fairing cap is arranged at the rear end of the rotating shaft hole behind the inner wing through a screw.
Preferably, the folding locking mechanism comprises an installation block, a hook rotating shaft, a torsion spring, a hook and a hook locking block, the installation block is connected with the outer wing through a screw, and the hook can rotate around the hook rotating shaft under the action of the torsion spring. When the folding hook is folded, the hook is manually rotated by 90 degrees around the hook rotating shaft, and then the tail wing is folded, the hook extends into the hook groove of the elastic body hook, so that the hook notch hooks the hook locking block, and the tail wing folding locking is completed.
Preferably, when folding the locking, couple breach surface and couple locking piece lower surface keep face contact, increase the frictional force between couple and the couple locking piece.
Preferably, when the tail wing is unfolded automatically, the steering engine deflects 13 degrees after receiving an instruction, the hook is separated from the restraint of the hook locking block, the hook is recovered into the mounting block under the action of the torsion spring, the outer wing is unfolded rapidly under the action of the unfolding mechanism, and after the outer wing is unfolded in place, the locking mechanism locks the outer wing rapidly to complete unfolding and locking of the tail wing. After the folding and locking are released, the hook is recovered into the mounting block around the hook rotating shaft under the action of the torsion spring and keeps in a mold shape with the profile of the outer wing.
Preferably, the deployment mechanism comprises: the front spring seat is arranged in the front rotating shaft hole of the inner wing; the rotating shaft penetrates through the rear rotating shaft hole of the inner wing, penetrates through the rotating shaft hole of the outer wing and penetrates through the front rotating shaft hole of the inner wing; the middle spring seat penetrates to the middle part of the rotating shaft and is fixedly connected with the rotating shaft and the outer wing; pins at two ends of the left-handed rectangular torsion spring are respectively inserted into pin grooves of the front spring seat and the middle spring seat; the rear spring seat is arranged in the rear rotating shaft hole of the inner wing; and pins at two ends of the right-handed rectangular torsion spring are respectively inserted into pin grooves of the middle spring seat and the rear spring seat.
Preferably, the outer wing and the inner wing are provided with inclined planes at the rotating shaft hole, and after the outer wing and the inner wing are unfolded in place, the two inclined planes are mutually attached to prevent the tail wing from being excessively unfolded, and the impact on the locking mechanism is reduced.
Preferably, the deployment mechanism employs a set of left-handed and right-handed rectangular torsion springs, with a rectangular cross-section.
Preferably, the steering engine can be used for releasing folding and locking of the tail wing when the missile is thrown, and can also be used for deflecting the tail wing when the missile flies. When the steering engine is not electrified, the rotating shaft of the steering engine can provide 0.3 N.m locking torque.
Preferably, the interface of the inner wing and the outer wing adopts a broken line type design, so that the interference of the inner wing and the outer wing is reduced.
The invention is further described with reference to the following drawings and specific examples, which are not intended to be limiting. It should be noted that the embodiments and features of the embodiments of the present invention may be combined with each other without conflict.
Example one
Referring to fig. 1, the missile tail folding mechanism for unlocking folding locking by using a steering engine includes an inner wing 2, a rotating shaft fairing cap 3, an outer wing 4, a folding locking mechanism, an unfolding mechanism and an unfolding locking mechanism. The locking mechanism comprises a locking pin 5 and a compression spring 6.
As shown in fig. 2, the unfolding mechanism includes a front spring seat 8, a rotating shaft 9, a middle spring seat 10, a left-handed rectangular torsion spring 11, a right-handed rectangular torsion spring 12, and a rear spring seat 13. As shown in fig. 3 and 4, the folding locking mechanism includes a hook locking block 14, a hook 15, a hook rotation shaft 16, a torsion spring 17, and a mounting block 18.
In this embodiment, body of bullet 1 shows as body of bullet cabin section intercepting part, and steering wheel 7 passes through M4 screw installation to body of bullet 1, and steering wheel 7 pivot inserts 2 steering wheel pivot holes in the inner wing, forms clearance fit to fasten through M4 screw. The locking pin 5 and the compression spring 6 are installed in the locking pin hole of the inner wing 2, the locking pin 5 and the locking pin hole of the inner wing 2 slide freely, when the outer wing 4 is unfolded in place, the locking pin 5 is inserted into the locking pin hole of the outer wing 4 under the action of the compression spring 6, and the outer wing is locked; when folding, the locking pin 5 is completely retracted into the locking pin hole of the inner wing 2 by using a tool, and the locking of the unfolding state of the outer wing is released.
The outer wing 4 is connected with the inner wing 2 through the unfolding mechanism, and the front spring seat 8 is installed in a rotating shaft hole of the inner wing 2 to form clearance fit. The rotating shaft hole of the inner wing 2 is coaxial with the rotating shaft hole of the outer wing 4, the rotating shaft 9 penetrates through the rotating shaft hole of the outer wing 4 from the rotating shaft hole behind the inner wing 2 until penetrating into the rotating shaft hole in front of the inner wing 2, and the rotating shaft 9 forms clearance fit with the rotating shaft holes of the inner wing 2 and the outer wing 4. The middle spring seat 10 penetrates through the middle part of the rotating shaft 9 and is fastened with the rotating shaft 9 and the outer wing 4 by M3 screws. Pins at two ends of the left-handed rectangular torsion spring 11 are respectively inserted into pin grooves of the front spring seat 8 and the middle spring seat 10, and the left-handed rectangular torsion spring is pre-tightened by the tool rotating the front spring seat 8. The rear spring seat 13 is mounted in the rear rotating shaft hole of the inner wing 2 through an M3 screw to form clearance fit. Pins at two ends of the right-handed rectangular torsion spring 12 are respectively inserted into pin grooves of the middle spring seat 10 and the rear spring seat 13, and the right-handed rectangular torsion spring 12 is pre-tightened by the rear spring seat 13 rotated by a tool. The rotating shaft fairing 3 is installed to the rear rotating shaft end of the inner wing 2 through an M3 screw.
The installation block 18 is connected with the outer wing 4 through an M3 screw, the hook 15 is installed to the installation block 18 through the hook rotating shaft 16, one end pin of the torsion spring 17 is in contact with the installation block 18, the other end of the torsion spring is in contact with the hook 15, after installation, the torsion spring 17 can provide certain pretightening force, the hook 15 is enabled to be attached to the installation block 18, and the outer surface of the hook 15 is in a molded shape with the wing surface of the outer wing 4. The hooking locking block 14 is mounted to the inner wall of the bullet body 1 by means of M4 screws.
The missile tail folding mechanism of the embodiment has the following working process:
the unfolded state of the tail wing is shown in figure 1, two locking pins 5 are respectively inserted into locking pin holes of the outer wing 4 under the action of a compression spring 6 to lock the outer wing 4, the hook 15 is quickly attached to the mounting block 18 under the action of a torsion spring 17, and the outer surface of the hook 15 is in molded fit with the wing surface of the outer wing 4.
The folding state of the tail wing is as shown in figure 3, when the tail wing is folded, the locking pin 5 is completely retracted into the locking pin hole of the inner wing 2 by using a tool, the locking state of the outer wing 4 is released, the outer wing 4 is manually folded towards one side, meanwhile, the hook 15 is manually unfolded, the hook 15 extends into the hook groove of the missile body 1, the hook locking block 14 enters the notch of the hook 15, the hook 15 is locked, the folding state locking is completed, and meanwhile, potential energy storage required by the unfolding of the outer wing 4 is completed by the left-handed rectangular torsion spring 11 and the right-handed rectangular torsion spring 12. The torsional moment generated by the left-handed rectangular torsion spring 11 and the right-handed rectangular torsion spring 12 further improves the friction force between the hook 15 and the hook locking block 14, so that the folding locking is more reliable.
When the wing is unfolded, the steering engine 7 deflects by 13 degrees, so that the hook 15 is separated from the hook locking block 14 to be in contact with the tail wing for folding and locking, the outer wing 4 is unfolded quickly under the action of the left-handed rectangular torsion spring 11 and the right-handed rectangular torsion spring 12, meanwhile, the hook 15 is quickly attached to the mounting block 18 under the action of the torsion spring 17, and the outer surface of the hook 15 and the wing profile of the outer wing 4 are kept in a mold closing state. When the outer wing is unfolded in place, the inclined plane at the position of the rotating shaft hole of the outer wing 4 is contacted with the inclined plane at the position of the rotating shaft hole of the inner wing 2, the outer wing 4 is prevented from being unfolded excessively, the impact of the outer wing 4 on the locking pin 5 is reduced, and meanwhile, the two locking pins 5 are respectively inserted into the locking pin holes of the outer wing 4 under the action of the compression spring 6 to lock the outer wing.
Here, it should be noted that what is not described in detail in this specification can be realized by those skilled in the art through the description in this specification and the prior art.
While embodiments of the present invention have been described above, the above description is illustrative, not exhaustive, and not limited to the disclosed embodiments. Many modifications and variations will be apparent to those of ordinary skill in the art without departing from the scope and spirit of the described embodiments.
Claims (10)
1. The utility model provides an utilize steering wheel to remove missile fin folding mechanism of folding locking which characterized in that includes:
the inner wing is arranged on the steering engine rotating shaft;
an outer wing foldably provided at an upper portion of the inner wing;
the unfolding mechanism is arranged between the inner wing and the outer wing and used for driving the outer wing to rotate around the inner wing for unfolding;
the unfolding locking mechanism is arranged between the inner wing and the outer wing and used for locking the unfolded outer wing;
and the folding locking mechanism is embedded in the outer wing, and when the outer wing is in a folding state, the folding locking mechanism keeps a folding locking state.
2. The missile empennage folding mechanism for unfolding and locking by using the steering engine as claimed in claim 1, wherein the unfolding mechanism adopts a group of left-handed and right-handed rectangular torsion springs, and the section of the unfolding mechanism is a rectangular section.
3. The missile tail fin folding mechanism for unlocking folding and locking by using the steering engine as claimed in claim 1, wherein the unfolding locking mechanism comprises a locking pin and a compression spring, the locking pin is arranged in a locking pin hole of the inner wing, and in the unfolding state, the locking pin is inserted into a locking pin hole of the outer wing under the action of the compression spring to lock the outer wing.
4. The missile tail wing folding mechanism capable of being unlocked by a steering engine according to claim 1, wherein the folding locking mechanism comprises an installation block, a hook rotating shaft, a torsion spring, a hook and a hook locking block, the installation block is embedded in one side of the outer wing, the hook can rotate around the hook rotating shaft under the action of the torsion spring, and the hook locking block is arranged in a hook groove of the missile body.
5. The missile tail folding mechanism using the steering engine to relieve folding and lock as claimed in claim 4, wherein: when folding, will the couple is rotatory 90 around the couple pivot, and the outer wing is folded again, makes the couple breach hooks couple locking piece, accomplishes the folding locking of outer wing, couple breach surface with the face contact is kept to couple locking piece lower surface.
6. The missile empennage folding mechanism capable of unlocking and locking by using the steering engine as claimed in claim 4, wherein when the outer wing needs to be unfolded, the steering engine receives an instruction to deflect a preset angle, the hook is separated from the constraint of the hook locking block, and the hook is retracted into the mounting block under the action of the torsion spring.
7. The missile empennage folding mechanism for unfolding and locking by using the steering engine as claimed in claim 1, wherein the interface of the inner wing and the outer wing adopts a broken line type design.
8. The missile tail folding mechanism using the steering engine to unlock the fold as claimed in claim 1, wherein the unfolding mechanism comprises:
the front spring seat is arranged in the front rotating shaft hole of the inner wing;
the rotating shaft penetrates through the rear rotating shaft hole of the inner wing, penetrates through the rotating shaft hole of the outer wing and penetrates through the front rotating shaft hole of the inner wing;
the middle spring seat penetrates to the middle part of the rotating shaft and is fixedly connected with the rotating shaft and the outer wing;
the pins at two ends of the left-handed rectangular torsion spring are respectively inserted into the pin grooves of the front spring seat and the middle spring seat;
the rear spring seat is arranged in the inner wing rear rotating shaft hole;
and pins at two ends of the right-handed rectangular torsion spring are respectively inserted into pin grooves of the middle spring seat and the rear spring seat.
9. The guided missile empennage folding mechanism for unlocking folding and locking by using the steering engine as claimed in claim 8, wherein the outer wing and the inner wing are provided with inclined planes at the rotating shaft hole, and after the outer wing and the inner wing are unfolded in place, the two inclined planes are attached to each other.
10. A missile, characterized in that the missile tail folding mechanism comprises a missile tail wing folding mechanism which is unlocked by a steering engine according to any one of claims 1 to 9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211648460.6A CN115979074A (en) | 2022-12-21 | 2022-12-21 | Missile empennage folding mechanism capable of unlocking folding and locking by utilizing steering engine and missile |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211648460.6A CN115979074A (en) | 2022-12-21 | 2022-12-21 | Missile empennage folding mechanism capable of unlocking folding and locking by utilizing steering engine and missile |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN115979074A true CN115979074A (en) | 2023-04-18 |
Family
ID=85971672
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202211648460.6A Pending CN115979074A (en) | 2022-12-21 | 2022-12-21 | Missile empennage folding mechanism capable of unlocking folding and locking by utilizing steering engine and missile |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN115979074A (en) |
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2022
- 2022-12-21 CN CN202211648460.6A patent/CN115979074A/en active Pending
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