CN111998738B - Locking hook type barrel shooting fly bullet wingspan unlocking mechanism - Google Patents
Locking hook type barrel shooting fly bullet wingspan unlocking mechanism Download PDFInfo
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- CN111998738B CN111998738B CN202011011249.4A CN202011011249A CN111998738B CN 111998738 B CN111998738 B CN 111998738B CN 202011011249 A CN202011011249 A CN 202011011249A CN 111998738 B CN111998738 B CN 111998738B
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- lock hook
- boss
- padlock
- hook
- wing
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- 230000007246 mechanism Effects 0.000 title claims abstract description 24
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- 235000017166 Bambusa arundinacea Nutrition 0.000 claims description 2
- 235000017491 Bambusa tulda Nutrition 0.000 claims description 2
- 241001330002 Bambuseae Species 0.000 claims description 2
- 235000015334 Phyllostachys viridis Nutrition 0.000 claims description 2
- 239000011425 bamboo Substances 0.000 claims description 2
- 230000008878 coupling Effects 0.000 claims 1
- 238000010168 coupling process Methods 0.000 claims 1
- 238000005859 coupling reaction Methods 0.000 claims 1
- 239000008188 pellet Substances 0.000 description 12
- 229920000049 Carbon (fiber) Polymers 0.000 description 2
- 239000004917 carbon fiber Substances 0.000 description 2
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 2
- 230000001360 synchronised effect Effects 0.000 description 2
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- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 1
- 229910052782 aluminium Inorganic materials 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
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- 230000010354 integration Effects 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
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- 230000003068 static effect Effects 0.000 description 1
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Abstract
The application discloses a lock hook type barrel shooting fly bullet wingspan unlocking mechanism, which comprises two elastic lock hooks respectively arranged on a first missile wing root and a second missile wing root; a shackle padlock boss mounted on the body; when the first missile wing and the second missile wing are unfolded to a working state, both elastic lock hooks are locked and buckled with the boss of the shackle padlock; the elastic lock hook and the lock hook padlock boss are in buckling connection in sequence in the matching moving process of non-contact, contact and extrusion, and then the elastic lock hook deforms. The elastic lock hook is adopted to lock the missile wing, so that the structure is simple, the matching precision requirement among all parts in the locking process is low, the lock is not easy to lose after the locking, and the locking is reliable; the elastic lock hook is adopted to lock the missile wing, unlocking can be completed by only using tools such as a common screwdriver during unlocking, unlocking is convenient to reuse, and meanwhile, the elastic lock hook is simple in structure and firm in connection with the missile wing, and can be reused for a plurality of times.
Description
Technical Field
The invention belongs to the technical field of barrel-shooting and patrol missiles, and particularly relates to a lock hook type opening locking mechanism for a wing span of a barrel-shooting and patrol missiles.
Background
The cartridge shooting and patrolling missile is an organic combination of a small unmanned aerial vehicle technology and an accurate guided ammunition technology, has long-time air-stagnation reconnaissance capability of the small unmanned aerial vehicle, has accurate striking capability of the accurate guided ammunition, can be used for carrying out long-time air-stagnation 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 inclined plane, obstacle shielding and the like), and can carry out real-time suicide attack after the target is found. The wings of the cartridge-shot fly-round projectile are folded and then loaded in the launching cartridge during daily service and transportation, the cartridge-shot fly-round projectile is launched and taken off through the launching cartridge during battle, and each wing of the fly-round projectile is automatically unfolded and locked after being launched out of the launching cartridge.
The missile wing opening locking mechanism is used for realizing synchronous, quick unfolding and reliable locking of each left wing and each right wing after the flying projectile is launched out of the barrel. If the wings are unfolded left and right in a non-synchronous manner, the wings can roll quickly after the flying and ejecting cylinder is patrolled and fall to the ground out of control, if the wings cannot be locked reliably after being unfolded, the out-of-lock rebound occurs, the pneumatic appearance of the whole bullet can be changed greatly, the whole bullet is unstable or the static stability is too high, and the falling cannot be controlled, so that the wing opening locking mechanism is an important component of the flying bullet, and the direct relation is that whether the shooting and the taking-off of the flying bullet are successful or not.
The existing spring wing unlocking mechanism adopts a locking mechanism with a spring pin, the requirement on the matching precision of the spring pin and a pin hole on a spring wing is high when the spring pin is locked, the risk that the spring pin cannot be inserted into the pin hole, the locking is lost after locking and the like is unreliable exists, meanwhile, the virtual position of the spring wing is larger after locking, and the spring pin is easy to deform under the condition of repeated locking, so that the spring pin needs to be replaced frequently. The locking and matching requirements of the lock locking mechanism of the wingspan of the lock hook type cylindrical shooting fly bullet are low, the lock locking mechanism is simple and reliable, the lock locking mechanism can be repeatedly used for many times, and the problems can be well solved.
Disclosure of Invention
In order to solve the problems in the background technology, the invention provides a lock hook type lock locking mechanism for a wingspan of a cartridge shooting and patrol projectile.
In order to achieve the above purpose, the present invention provides the following technical solutions:
the utility model provides a lock hook formula section of thick bamboo is penetrated and is patrolled a missile wingspan lock mechanism, patrols a first missile wing root and second missile wing root and passes through the torsional spring and winds the coaxial rotation of missile wing center pivot and be connected, and the axis of rotation links firmly on the hull, and locking mechanical system includes:
two elastic lock hooks respectively arranged on the first missile wing root and the second missile wing root;
A shackle padlock boss mounted on the body; when the first missile wing and the second missile wing are unfolded to a working state, both elastic lock hooks are locked and buckled with the boss of the shackle padlock;
the elastic lock hook and the lock hook padlock boss are in buckling connection in sequence in the matching moving process of non-contact, contact and extrusion, and then the elastic lock hook deforms.
Specifically, the elastic shackle is arc-shaped, the end part of the elastic shackle is provided with a hook-shaped member, the shackle padlock boss is provided with an arc-shaped surface, the matching moving process of the elastic shackle and the shackle padlock boss is in sequence that the hook-shaped member on the elastic shackle is not contacted with the arc-shaped surface of the shackle padlock boss, the hook-shaped member 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 is deformed after extrusion, and the hook-shaped member on the elastic shackle is clamped into the shackle padlock boss and then is fastened.
Further, the two elastic lock hooks and the two arc-shaped surfaces on the lock hook padlock boss are arranged in a vertically staggered mode, and the two elastic lock hooks are correspondingly matched with the two arc-shaped surfaces on the lock hook padlock boss.
Further, two missile wing limiting bosses are arranged on the missile body, are respectively positioned at two sides of the shackle padlock boss, two gaps are formed between the two missile wing limiting bosses and the shackle padlock boss, and the two elastic shackle respectively pass through the two gaps when rotating; when the elastic latch hook is buckled with the latch hook padlock boss, the two latch wing limiting bosses are respectively used for limiting the blocking position of the first latch wing and the second latch wing.
Specifically, the body of the bullet comprises a front bulkhead of the body of the bullet, and two bullet wing limit bosses and a shackle padlock boss are both arranged on the front bulkhead of the body of the bullet.
Compared with the prior art, the invention has the beneficial effects that:
1. the elastic lock hook is adopted to realize the locking of the missile wing, the structure is simple, the matching precision requirement among all parts in the locking process is low, the lock is not easy to lose after the locking, and the locking is reliable;
2. The elastic lock hook is adopted to lock the missile wing, and unlocking can be completed only by using tools such as a common screwdriver and the like during unlocking, so that the missile wing is convenient to unlock and reuse, and meanwhile, the elastic lock hook is simple in structure, firm in connection with the missile wing and capable of being reused for a plurality of times;
3. the whole unfolding 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 for daily maintenance.
Drawings
FIG. 1 is an isometric view of the application in an expanded state;
FIG. 2 is a contracted state isometric view of the application;
FIG. 3 is an isometric view of a middle missile wing assembly;
FIG. 4 is a side view of the center body axle;
FIG. 5 is a cross-sectional view of the present application;
FIG. 6 is an isometric view of a spring shackle of the present application;
In the figure:
The novel missile wing comprises a first missile wing, a 2-elastic latch hook, a 3-missile body front bulkhead, a 4-missile body, a 5-second missile wing, a 6-first missile wing root, a 7-missile wing limiting boss, an 8-latch hook padlock boss, a 9-missile wing center rotating shaft, a 10-torsion spring and an 11-second missile wing root.
Detailed Description
The following description of the embodiments of the present invention will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present invention, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
The invention provides the following technical scheme:
As shown in fig. 1-6, a lock hook type barrel shooting fly pellet wingspan unlocking mechanism, wherein fly pellet parts comprise a pellet body 4, a first pellet wing 1 and a second pellet wing 5, the first pellet wing 1 comprises a first pellet wing root 6, the second pellet wing 5 comprises a second pellet wing root 11, and the first pellet wing root 6 and the second pellet wing root 11 can be coaxially and rotatably connected around a pellet wing center rotating shaft 9 through a torsion spring 10. The locking mechanism includes:
two elastic lock hooks 2 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 missile wing 1 and the second missile wing 5 are unfolded to a working state, the two elastic latch hooks 2 are locked and buckled with the latch hook padlock boss 8;
The elastic latch hook 2 and the latch hook padlock boss 8 are in sequence in the matching moving process of non-contact, contact and extrusion, and then the elastic latch hook 2 deforms, and the elastic latch hook 2 is buckled with the latch hook padlock boss 8.
In some embodiments, the elastic latch hook 2 is made of 60Si 2 Mn, and is quenched and tempered at medium temperature.
The first missile wing 1 and the second missile wing 5 are installed in a vertically staggered mode, and the unfolding process is not interfered with each other.
The missile wing is formed by compounding and integrating a foam sandwich material, a carbon fiber skin, 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 consistent respectively.
Mounting grooves for mounting the torsion spring 10 are reserved in the first missile wing root 6 and the second missile wing root 11, and the torsion spring 10 is mounted in the mounting grooves; the torsion spring 10 adopts a center arm structure, the upper torsion arm and the lower torsion arm are respectively matched with torsion spring 10 mounting holes on the first missile wing root 6 and the second missile wing root 11, the torsion spring 10 is compressed and the torsion force is increased when the first missile wing 1 and the second missile wing 5 shrink, and the torsion spring 10 drives the missile wing to rotate to realize expansion when the missile wing constraint is released. Gaps are reserved between the first missile wing root 6 and the missile body and between the first missile wing root 6 and the second missile wing root 11 during installation, friction force during rotation of the first missile wing 1 and the second missile wing 5 is reduced, and smooth rotation of the first missile wing 1 and the second missile wing 5 is ensured.
The unfolding locking mechanism adopts a single center arm torsion spring 10 as the unfolding power of the first missile wing 1 and the second missile wing 5, the torsion spring 10 is compressed to generate torsion when the first missile wing 1 and the second missile wing 5 are folded, and the torsion after the constraint of the first missile wing 1 and the second missile wing 5 is released drives the first missile wing 1 and the second missile wing 5 to rotate around the central rotating shaft 9 of the missile wing so as to realize the simultaneous rapid unfolding of the first missile wing 1 and the second missile wing 5, so that the application has the advantages of simple structure, light weight, high reliability and better guarantee of the synchronization of the left-right wingspan unfolding.
When the unfolding locking mechanism needs unlocking, the tool is used for prying the elastic lock hook 2 to enable the elastic lock hook 2 to be separated from the lock hook padlock boss 8 on the front bulkhead 3 of the warhead, so that unlocking can be realized; after unlocking, the first missile wing 1 and the second missile wing 5 are respectively rotated backwards, so that missile wing storage can be realized.
As shown in fig. 2,4 and 6, the shape of the elastic shackle 2 is arc-shaped, the end part of the elastic shackle 2 is provided with a hook-shaped member, the shackle padlock boss 8 is provided with an arc-shaped surface, the matching moving process of the elastic shackle 2 and the shackle padlock boss 8 is sequentially that the hook-shaped member of the elastic shackle 2 is not contacted with the arc-shaped surface of the shackle padlock boss 8, the hook-shaped member of the elastic shackle 2 moves along the arc-shaped surface of the shackle padlock boss 8, the elastic shackle 2 is tightly attached to the arc-shaped surface of the shackle padlock boss 8 and deforms after extrusion, and the hook-shaped member of the elastic shackle 2 is clamped into the shackle padlock boss 8 and then is fastened.
As shown in fig. 1 and 5, two elastic shackle 2 and two arc surfaces on shackle padlock boss 8 are both arranged in a vertically staggered manner, and two elastic shackle 2 are correspondingly matched with two arc surfaces on shackle padlock boss 8.
As shown in fig. 2 and 4, two missile wing limiting bosses 7 are arranged on the missile body, the two missile wing limiting bosses 7 are respectively positioned at two sides of the shackle padlock boss 8, two gaps are formed between the two missile wing limiting bosses 7 and the shackle padlock boss 8, and the two elastic shackle 2 respectively passes through the two gaps when rotating; when the elastic latch hook 2 is buckled with the latch hook padlock boss 8, the two missile wing limiting bosses 7 are respectively used for blocking the first missile wing 1 and the second missile wing 5.
As shown in fig. 4, the body of the bullet comprises a front bulkhead 3 of the body of the bullet, and two bullet wing limit bosses 7 and a shackle padlock boss 8 are both arranged on the front bulkhead 3 of the body of the bullet.
In some embodiments, the front bulkhead 3 is positioned at the forefront end of the body, and the front bulkhead 3 and the carbon fiber skin of the body are combined into a whole; the front bulkhead 3 of the bullet is made of 7075T6, and the surface is anodized.
Although embodiments of the present invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made therein 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 lock hook formula section of thick bamboo is penetrated and is patrolled a missile wingspan locking mechanism, patrols a missile part spare part and includes the hull, first missile wing and second missile wing, and first missile wing includes first missile wing root, and the second missile wing includes second missile wing root, and first missile wing root and second missile wing root pass through torsional spring rotatable coupling, its characterized in that, locking mechanical system includes:
two elastic lock hooks respectively arranged on the first missile wing root and the second missile wing root;
A shackle padlock boss mounted on the body; when the first missile wing and the second missile wing are unfolded to a working state, both elastic lock hooks are locked and buckled with the boss of the shackle padlock;
the elastic lock hook and the lock hook padlock boss are in buckling connection in sequence in the matching moving process of non-contact, contact and extrusion, and then the elastic lock hook deforms.
2. The lock hook type barrel shooting fly bullet wingspan unlocking and fixing mechanism according to claim 1, wherein the elastic lock hook is arc-shaped, a hook-shaped piece is formed at the end part of the elastic lock hook, an arc-shaped surface is arranged on the lock hook padlock boss, the elastic lock hook and the lock hook padlock boss are in sequence of non-contact, the hook-shaped piece on the elastic lock hook is contacted with the arc-shaped surface of the lock hook padlock boss, the hook-shaped piece on the elastic lock hook moves along the arc-shaped surface of the lock hook padlock boss, the elastic lock hook is tightly attached to the arc-shaped surface of the lock hook padlock boss, and after extrusion, the elastic lock hook is deformed, and the hook-shaped piece on the elastic lock hook is clamped into the lock hook padlock boss and then is buckled.
3. The lock hook type barrel shooting fly bullet wingspan unlocking mechanism of claim 2, wherein the two elastic lock hooks are arranged in a vertically staggered manner with the two arc-shaped surfaces on the boss of the lock hook padlock, and the two elastic lock hooks are correspondingly matched with the two arc-shaped surfaces on the boss of the lock hook padlock.
4. The lock hook type barrel shooting fly bullet wingspan unlocking and locking mechanism according to claim 3, wherein two bullet wing limiting bosses are arranged on the bullet body, the two bullet wing limiting bosses are respectively positioned at two sides of the lock hook padlock boss, two gaps are formed between the two bullet wing limiting bosses and the lock hook padlock boss, and the two elastic lock hooks respectively pass through the two gaps when rotating; when the elastic latch hook is buckled with the latch hook padlock boss, the two latch wing limiting bosses are respectively used for blocking and limiting the first latch wing and the second latch wing.
5. The lock catch type barrel shooting fly bullet wingspan unlocking mechanism of claim 4 wherein the bullet body comprises a bullet body front bulkhead, and both the two bullet wing limit bosses and the lock catch padlock boss are mounted on the bullet body front bulkhead.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011011249.4A CN111998738B (en) | 2020-09-23 | Locking hook type barrel shooting fly bullet wingspan unlocking mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011011249.4A CN111998738B (en) | 2020-09-23 | Locking hook type barrel shooting fly bullet wingspan unlocking mechanism |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN111998738A CN111998738A (en) | 2020-11-27 |
| CN111998738B true CN111998738B (en) | 2024-06-25 |
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Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN212253860U (en) * | 2020-09-23 | 2020-12-29 | 中国工程物理研究院总体工程研究所 | Lock hook type cylinder shooting patrol missile wing unfolding and locking mechanism |
Patent Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN212253860U (en) * | 2020-09-23 | 2020-12-29 | 中国工程物理研究院总体工程研究所 | Lock hook type cylinder shooting patrol missile wing unfolding and locking mechanism |
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