CN111998738A - Lock hook type cylinder shooting patrol missile wing unfolding and locking mechanism - Google Patents
Lock hook type cylinder shooting patrol missile wing unfolding and locking mechanism Download PDFInfo
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- CN111998738A CN111998738A CN202011011249.4A CN202011011249A CN111998738A CN 111998738 A CN111998738 A CN 111998738A CN 202011011249 A CN202011011249 A CN 202011011249A CN 111998738 A CN111998738 A CN 111998738A
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- elastic
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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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Abstract
The invention discloses a locking hook type barrel shooting patrol missile wing unfolding locking mechanism which comprises two elastic locking hooks, wherein the two elastic locking hooks are respectively arranged on a first missile wing root and a second missile wing root; a latch hook padlock boss arranged on the bomb body; when the first elastic wing and the second elastic wing are unfolded to a working state, the two elastic lock hooks are locked and buckled with the lock hook padlock lug boss; the elastic lock hook and the lock hook and lock pad are in non-contact, contact and deformation after extrusion in sequence in the matching moving process of the elastic lock hook and the lock hook and lock pad boss. The elastic locking hook is adopted to realize the locking of the elastic wings, the structure is simple, the requirement on the matching precision of parts in the locking process is low, the locking is not easy to lose after the locking, and the locking is reliable; adopt the elasticity latch hook to realize playing the wing locking, only need during the unblock instrument such as ordinary screwdriver can accomplish the unblock, be convenient for unblock used repeatedly, simple structure simultaneously, with play wing firm in connection, can used repeatedly many times.
Description
Technical Field
The invention belongs to the technical field of cartridge shooting and patrolling missiles, and particularly relates to a locking hook type cartridge shooting and patrolling missile wing unfolding and locking mechanism.
Background
The cartridge-shooting patrol missile is an organic combination of a small unmanned aerial vehicle technology and an accurate guidance ammunition technology, has the long-time air-lag reconnaissance capability of a small unmanned aerial vehicle, has the accurate hitting capability of an accurate guidance ammunition, can be used for carrying out long-time air-lag reconnaissance on a fixed target or a moving target which cannot be accurately positioned in advance in a preset area outside a sight distance (such as a long distance, an inverse slope, barrier shielding and the like), and can carry out real-time 'suicide type' attack after the target is found. The wings of the round-shooting patrol missile are folded and loaded in the launching tube during daily service and transportation, and are launched to take off through the launching tube during combat, and the wings of the round-shooting patrol missile are automatically unfolded and locked after the launching tube is launched.
The missile wing unfolding and locking mechanism is used for realizing synchronous, quick unfolding and reliable locking of the left wing and the right wing after the patrol missile is launched out of the barrel. If the missile wing is unfolded left and right asynchronously, the missile wing can quickly roll and fall off the ground after flying to the missile barrel, if the missile wing can not be reliably locked after being unfolded, the whole missile is subjected to unlocking resilience, the pneumatic appearance of the whole missile is greatly changed, the whole missile is subjected to static instability or over-static stability, and the falling off the ground can not be controlled, so that the missile wing unfolding locking mechanism is an important component for flying to the missile, and whether the flying to the missile barrel is shot and taken off successfully or not is directly related.
The locking mechanism adopted by the existing elastic wing unfolding locking mechanism is provided with a spring pin, the requirement on the matching precision of the spring pin and a pin hole on the elastic wing is high when the spring pin is locked, the unreliable locking risks of the spring pin, such as incapability of inserting the spring pin into the pin hole, lock losing after locking and the like exist, meanwhile, the virtual position of the elastic wing is large after locking, and the spring pin is easy to deform under stress under the condition of repeated locking and needs to be frequently replaced. The locking hook type barrel shooting patrol missile wing unfolding locking mechanism is low in locking matching requirement, simple, reliable and reusable, and can well solve the problems.
Disclosure of Invention
In order to solve the problems in the background art, the invention provides a locking hook type barrel shooting and patrolling missile wing unfolding and locking mechanism.
In order to achieve the purpose, the invention provides the following technical scheme:
the utility model provides a latch hook formula section of thick bamboo is penetrated and is patrolled flying bomb missile wing and expand locking mechanical system, patrols first missile wing root of flying bomb and second missile wing root and passes through the torsional spring and connect around the coaxial rotation of bullet wing center pivot, and the axis of rotation links firmly on the bullet body, and locking mechanical system includes:
the two elastic lock hooks are respectively arranged on the first missile wing root and the second missile wing root;
a latch hook padlock boss arranged on the bomb body; when the first elastic wing and the second elastic wing are unfolded to a working state, the two elastic lock hooks are locked and buckled with the lock hook padlock lug boss;
the elastic lock hook and the lock hook and lock pad are in non-contact, contact and deformation after extrusion in sequence in the matching moving process of the elastic lock hook and the lock hook and lock pad boss.
Specifically, the elastic lock hook is arc-shaped, a hook piece is formed at the end of the elastic lock hook, an arc-shaped surface is arranged on a boss of the lock hook padlock, the elastic lock hook and the boss of the lock hook padlock are in non-contact in sequence in the matching moving process, the hook piece on the elastic lock hook is in contact with the arc-shaped surface of the boss of the lock hook padlock, the hook piece on the elastic lock hook moves along the arc-shaped surface of the boss of the lock hook padlock, the elastic lock hook is tightly attached to the arc-shaped surface of the boss of the lock hook padlock and deforms after being extruded, and the hook piece on the elastic lock.
Furthermore, the two elastic lock hooks and the two arc-shaped surfaces on the lug boss of the lock hook padlock are arranged in a vertically staggered mode, and the two elastic lock hooks and the two arc-shaped surfaces on the lug boss of the lock hook padlock are correspondingly matched.
Furthermore, two elastic wing limiting bosses are arranged on the bomb body and are respectively positioned on two sides of the lock hook padlock boss, two gaps are formed between the two elastic wing limiting bosses and the lock hook padlock boss, and the two elastic lock hooks respectively penetrate through the two gaps when rotating; when the elastic lock hook is buckled with the lock hook and padlock lug boss, the two elastic wing limiting lug bosses are respectively used for limiting the clamping position of the first elastic wing and the second elastic wing.
Specifically, the bullet body is including before the body of bullet bulkhead, and two spacing bosss of bullet wing and latch hook padlock boss are all installed before the body of bullet on the bulkhead.
Compared with the prior art, the invention has the beneficial effects that:
1. the elastic locking hook is adopted to realize the locking of the elastic wings, the structure is simple, the requirement on the matching precision of all parts in the locking process is low, the locking is not easy to lose after the locking, and the locking is reliable;
2. the elastic locking hook is adopted to realize the locking of the elastic wing, the unlocking can be completed only by tools such as a common screwdriver and the like during the unlocking, the unlocking is convenient to be repeatedly used, and meanwhile, the structure is simple, the elastic locking hook is firmly connected with the elastic wing, and the elastic locking hook can be repeatedly used for many times;
3. the whole unfolding and locking mechanism is high in integration level, simple in mechanism, small in size, light in weight, simple in assembly, easy to operate, easy to reuse, low in cost and convenient to maintain daily.
Drawings
FIG. 1 is an expanded axial side view of the present application;
FIG. 2 is a side axial view of the present application in a contracted state;
FIG. 3 is an axial side view of the middle missile wing assembly;
FIG. 4 is a side view of the middle projectile body axis;
FIG. 5 is a cross-sectional view of the present application;
FIG. 6 is a side view of the resilient latch hook shaft of the present application;
in the figure:
1-a first missile wing, 2-an elastic lock hook, 3-a missile body front partition frame, 4-a missile body, 5-a second missile wing, 6-a first missile wing root, 7-a missile wing limiting boss, 8-a lock hook padlock boss, 9-a missile wing central rotating shaft, 10-a torsion spring and 11-a second missile wing root.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments 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.
The invention provides the following technical scheme:
as shown in fig. 1-6, a latch-hook type barrel shooting patrol missile wing unfolding locking mechanism, wherein some parts of the patrol missile include a missile body 4, a first missile wing 1 and a second missile wing 5, the first missile wing 1 includes a first missile wing root 6, the second missile wing 5 includes a second missile wing root 11, and the first missile wing root 6 and the second missile wing root 11 are coaxially and rotatably connected around a missile wing central rotating shaft 9 through a torsion spring 10. The locking mechanism includes:
the two elastic locking hooks 2 are respectively arranged on the first missile wing root 6 and the second missile wing root 11;
a shackle padlock boss 8 mounted on the body 4; when the first elastic wing 1 and the second elastic wing 5 are unfolded to be in a working state, the two elastic lock hooks 2 are locked and buckled with the lock hook padlock lug bosses 8;
wherein, the process is removed in order for contactless, contact, extrusion back elastic latch hook 2 takes place deformation, elastic latch hook 2 and the lock hook padlock boss 8 lock joint for the cooperation of elastic latch hook 2 and lock hook padlock boss 8.
In some embodiments, the elastic latch hook 2 is made of 60Si2Mn, and carrying out quenching and medium-temperature tempering treatment.
The first missile wing 1 and the second missile wing 5 are installed in a vertically staggered mode, and the unfolding processes are not interfered with each other.
The missile wing is formed by compounding and integrating a foam sandwich material and a carbon fiber skin with an aluminum wing root and an elastic lock hook 2, and the weight and the rotational inertia of the first missile wing 1 and the second missile wing 5 are basically kept consistent respectively.
Mounting grooves for mounting torsion springs 10 are reserved in the first missile wing root 6 and the second missile wing root 11, and the torsion springs 10 are mounted in the mounting grooves; the torsion spring 10 adopts a central arm structure, the upper torsion arm and the lower torsion arm are respectively matched with mounting holes of the torsion spring 10 on the first elastic wing root 6 and the second elastic wing root 11, the torsion spring 10 is compressed and the torsion force is increased when the first elastic wing 1 and the second elastic wing 5 are contracted, and the torsion spring 10 drives the elastic wings to rotate to realize expansion when the elastic wing constraint is relieved. Leave the clearance between first missile wing root 6 and the body of a bullet, and when installing between first missile wing root 6 and the second missile wing root 11, reduce frictional force when first missile wing 1 and second missile wing 5 rotate, guarantee that first missile wing 1 and second missile wing 5 rotate smoothly.
Unfolding locking mechanical system adopts single central arm torsional spring 10 as first missile wing 1 and the power that expandes of second missile wing 5, torsional spring 10 is compressed and produces torsion when first missile wing 1 and the folding of second missile wing 5, first missile wing 1 of first missile wing 1 and the constraint of second missile wing 5 are relieved back torsion drive first missile wing 1 and second missile wing 5 rotate around missile wing center pivot 9 and realize that first missile wing 1 and second missile wing 5 expand fast simultaneously, make this application simple structure, light in weight, the reliability is high, and it opens the synchronism to better guarantee to control the wingspan.
When the unlocking mechanism needs to be unlocked after being unfolded, a tool is used for prying the elastic lock hook 2 to enable the elastic lock hook 2 to be separated from a lock hook padlock boss 8 on the elastic front bulkhead 3, and then the unlocking can be carried out; after the unlocking, the first missile wing 1 and the second missile wing 5 are respectively rotated backwards, and the missile wing can be stored.
As shown in fig. 2, 4 and 6, the elastic latch hook 2 is arc-shaped, a hook is formed at the end of the elastic latch hook 2, an arc-shaped surface is arranged on the latch boss 8 of the latch hook, the matching moving processes of the elastic latch hook 2 and the latch boss 8 of the latch hook are sequentially non-contact, the hook on the elastic latch hook 2 is in contact with the arc-shaped surface of the latch boss 8 of the latch hook, the hook on the elastic latch hook 2 moves along the arc-shaped surface of the latch boss 8 of the latch hook, the elastic latch hook deforms after the elastic latch hook 2 is tightly attached to the arc-shaped surface of the latch boss 8 of the latch hook and is squeezed, and the hook on the elastic latch hook 2 is clamped.
As shown in fig. 1 and 5, the two elastic latch hooks 2 and the two arc-shaped surfaces on the latch boss 8 of the latch hook are arranged in a vertically staggered manner, and the two elastic latch hooks 2 are correspondingly matched with the two arc-shaped surfaces on the latch boss 8 of the latch hook.
As shown in fig. 2 and 4, the body of the bullet is provided with two elastic wing limiting bosses 7, the two elastic wing limiting bosses 7 are respectively positioned at two sides of a shackle padlock boss 8, two gaps are formed between the two elastic wing limiting bosses 7 and the shackle padlock boss 8, and the two elastic shackle 2 respectively penetrates through the two gaps when rotating; when the elastic lock hook 2 is buckled with the lock hook padlock lug boss 8, the two elastic wing limiting lug bosses 7 are respectively used for clamping the first elastic wing 1 and the second elastic wing 5.
As shown in fig. 4, the bomb body comprises a bomb body front bulkhead 3, and two bomb wing limiting bosses 7 and a latch hook padlock boss 8 are both arranged on the bomb body front bulkhead 3.
In some embodiments, the bullet body front partition frame 3 is positioned at the foremost end of the bullet body, and the bullet body front partition frame 3 and the bullet body carbon fiber skin are compounded and integrally formed; the bullet front partition frame 3 is made of 7075T6 material, and the surface of the bullet is anodized.
Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the invention, the scope of which is defined in the appended claims and their equivalents.
Claims (5)
1. The utility model provides a latch hook formula section of thick bamboo is penetrated and is patrolled all-wing missile wing and expand locking mechanical system, patrols all-wing missile part spare part and includes that body of bullet, first bullet wing and second bullet wing, first bullet wing includes first bullet wing root, and the second bullet wing includes second bullet wing root, and first bullet wing root and second bullet wing root pass through torsional spring rotatable coupling, and its characterized in that, locking mechanical system includes:
the two elastic lock hooks are respectively arranged on the first missile wing root and the second missile wing root;
a latch hook padlock boss arranged on the bomb body; when the first elastic wing and the second elastic wing are unfolded to a working state, the two elastic lock hooks are locked and buckled with the lock hook padlock lug boss;
the elastic lock hook and the lock hook and lock pad are in non-contact, contact and deformation after extrusion in sequence in the matching moving process of the elastic lock hook and the lock hook and lock pad boss.
2. The shackle type tubular projectile missile wing unfolding and locking mechanism as claimed in claim 1, wherein the elastic shackle is arc-shaped, a hook is formed at the end of the elastic shackle, an arc-shaped surface is arranged on a shackle padlock boss, the matching and moving processes of the elastic shackle and the shackle padlock boss are sequentially non-contact, the hook on the elastic shackle is in contact with the arc-shaped surface of the shackle padlock boss, the hook on the elastic shackle moves along the arc-shaped surface of the shackle padlock boss, the elastic shackle is tightly attached to the arc-shaped surface of the shackle padlock boss and deforms after being pressed, and the hook on the elastic shackle is clamped into the rear lock of the shackle padlock boss.
3. The mechanism of claim 2, wherein the two elastic latch hooks and the two arc-shaped surfaces on the latch boss of the latch hook are vertically staggered, and the two elastic latch hooks are correspondingly matched with the two arc-shaped surfaces on the latch boss of the latch hook.
4. The latch hook type cylinder shooting and patrolling flying projectile missile wing unfolding and locking mechanism is characterized in that two wing limiting bosses are arranged on a missile body, the two wing limiting bosses are respectively positioned on two sides of a latch hook and padlock boss, two gaps are formed between the two wing limiting bosses and the latch hook and padlock boss, and the two elastic latch hooks respectively penetrate through the two gaps when rotating; when the elastic lock hook is buckled with the lock hook and padlock lug boss, the two elastic wing limiting lug bosses are respectively used for limiting the blocking of the first elastic wing and the second elastic wing.
5. The locking mechanism for unfolding the missile wing of the locking hook type missile launcher according to claim 4, wherein the missile body comprises a missile body front partition frame, and two missile wing limiting bosses and a locking hook padlock boss are both arranged on the missile body front partition frame.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011011249.4A CN111998738A (en) | 2020-09-23 | 2020-09-23 | Lock hook type cylinder shooting patrol missile wing unfolding and locking mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011011249.4A CN111998738A (en) | 2020-09-23 | 2020-09-23 | Lock hook type cylinder shooting patrol missile wing unfolding and locking mechanism |
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| Publication Number | Publication Date |
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| CN111998738A true CN111998738A (en) | 2020-11-27 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202011011249.4A Pending CN111998738A (en) | 2020-09-23 | 2020-09-23 | Lock hook type cylinder shooting patrol missile wing unfolding and locking mechanism |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111824421A (en) * | 2020-06-15 | 2020-10-27 | 成都大学 | A anti-riot bullet shooting mechanism and bullet shooting device for unmanned aerial vehicle |
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2020
- 2020-09-23 CN CN202011011249.4A patent/CN111998738A/en active Pending
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111824421A (en) * | 2020-06-15 | 2020-10-27 | 成都大学 | A anti-riot bullet shooting mechanism and bullet shooting device for unmanned aerial vehicle |
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