CN109186369B - Missile wing installation fixed establishment - Google Patents
Missile wing installation fixed establishment Download PDFInfo
- Publication number
- CN109186369B CN109186369B CN201810977846.9A CN201810977846A CN109186369B CN 109186369 B CN109186369 B CN 109186369B CN 201810977846 A CN201810977846 A CN 201810977846A CN 109186369 B CN109186369 B CN 109186369B
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- China
- Prior art keywords
- transmission rod
- transverse
- missile wing
- tooth transmission
- shell
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Classifications
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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
- F42B10/04—Stabilising arrangements using fixed fins
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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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- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Aviation & Aerospace Engineering (AREA)
- Combustion & Propulsion (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Clamps And Clips (AREA)
Abstract
The invention relates to an elastic wing mounting and fixing mechanism which comprises a self-locking nut (3), a longitudinal helical tooth transmission rod (4), a transverse helical tooth transmission rod (5), symmetrical clamping plates (6) and a shell (7), wherein the longitudinal helical tooth transmission rod (4) is inserted into a preset hole in a skin (1), a gear at the bottom of the longitudinal helical tooth transmission rod (4) is matched with a gear at one end of the transverse helical tooth transmission rod (5), the transverse helical tooth transmission rod (5) is screwed into threaded holes of the two symmetrical clamping plates (6), and the shell (7) is fixedly mounted with the elastic wing mounting and fixing mechanism. The invention greatly reduces the influence on the pneumatic performance, is convenient for the rapid disassembly and assembly of the missile wing, and greatly reduces the requirement on the matching precision in the processing of the installation surface of the missile wing.
Description
Technical Field
The invention belongs to the field of missile structural design, relates to a missile wing mounting and fixing mechanism, and particularly relates to a missile wing mounting and fixing mechanism for blind butt joint in a missile.
Background
The missile wing is a main provider of the lifting force when the missile flies, and the shape preservation of the missile wing is the guarantee of the good aerodynamic performance of the missile. However, in the existing structural design, the fixing mode of the missile body mounting seat is mostly adopted, and the mounting seat is generally thicker than the missile wing itself due to the fixing function, so that the following problems are easy to occur in practical application:
1) because the mounting seats are mostly welded or bound, the assembly consistency is difficult to ensure;
2) the common mounting seat adopts a connection form of a clamping notch, generally adopts transition fit for the transverse limiting function, and has high requirements on the processing precision of the mounting seat and the elastic wing;
3) because the machining precision and the assembling precision of the mounting seat are difficult to ensure higher levels, the practical performance and the simulation performance are easy to be inconsistent, and differences exist among individuals, so that certain difficulty is caused in the design of a control system;
4) the surface of the missile body is exposed out of the mounting seat, and a plurality of bulges are formed at the root parts of the missile wings, so that the aerodynamic performance of the missile wings and the whole missile is extremely adversely affected, and the relevant tactical and technical indexes of the missile are restricted.
Disclosure of Invention
The purpose of the invention is as follows:
the invention aims to provide a missile wing installation and fixation mechanism, which realizes installation and fixation of missile wings in blind butt joint in a missile and ensures the pneumatic appearance of the surface of a missile body.
The technical scheme adopted by the invention is as follows:
a mounting and fixing mechanism for an elastic wing comprises a self-locking nut 3, a longitudinal helical tooth transmission rod 4, a transverse helical tooth transmission rod 5, a symmetrical clamping plate 6 and a shell 7;
the missile skin 1 is provided with a preset hole, the longitudinal helical tooth transmission rod 4 is inserted into the preset hole on the skin 1 and is in threaded transmission through the self-locking nut 3, a gear at the bottom of the longitudinal helical tooth transmission rod 4 is matched with a gear at one end of the transverse helical tooth transmission rod 5, and the self-locking nut 3, the longitudinal helical tooth transmission rod 4 and the transverse helical tooth transmission rod 5 jointly form a set of threaded gear transmission mechanism which is used for transmitting power for the symmetrical clamping plate 6; threaded holes with opposite rotation directions are formed in the middle of the two symmetrical clamping plates 6, the transverse helical tooth transmission rod 5 is screwed into the threaded holes of the two symmetrical clamping plates 6, and the transverse helical tooth transmission rod 5 and the two symmetrical clamping plates 6 form a set of clamping and releasing mechanism; the shell 7 provides a mounting and fixing space for the missile wing mounting and fixing mechanism and provides an outer cladding.
The self-locking nut is characterized in that grooves with guide grooves are formed in the shell side plates 7.1 on two sides of the shell 7, the guide inclination of each groove is matched with the thread pitch of the self-locking nut 3, hanging shafts are arranged on the side faces of the two symmetrical clamping plates 6 and can be installed in the grooves of the shell side plates 7.1, and strip-shaped elastic wing inserting holes are reserved in the upper surface of the shell 7.
The elastic wing clamping device is characterized in that short bolts are arranged on the inner side clamping surfaces of the symmetrical clamping plates 6 and can be inserted into the elastic wing preformed holes in the clamping process.
The self-locking nut is characterized in that the self-locking nut 3 is fixed on the upper surface of the shell 7 and is connected with the longitudinal helical tooth transmission rod 4 through threads.
The transmission device is characterized in that threads are arranged on the longitudinal helical tooth transmission rod 4 and the transverse helical tooth transmission rod 5, a small helical gear is arranged at one end of the transmission device, the longitudinal helical tooth transmission rod 4 and the transverse helical tooth transmission rod 5 are meshed through the gears to realize transmission, and the transverse helical tooth transmission rod 5 is connected with the symmetrical clamping plate 6 through the threads.
The invention has the beneficial effects that:
1) the bullet is arranged on the inner side of the bullet body, only the countersunk head is left outside the bullet body, the countersunk head screw at the butt joint part with the cabin section has no difference in appearance, and compared with an outer bullet mounting seat, the impact on the pneumatic performance is greatly reduced;
2) the symmetrical clamping mechanism can not only clamp the missile wing in the transverse direction, but also can radially tighten the missile wing under the guidance of the guide groove of the shell side plate groove in the clamping process so as to ensure that the missile wing is attached to the surface of a missile body;
3) the missile wing is mounted or dismounted only by rotating the exposed countersunk head screw without special tools, so that one-key clamping release is realized, and the missile wing is convenient to mount and dismount quickly;
4) the symmetrical clamping plates are driven by the helical tooth transmission rod to realize clamping, and can be used for self-adaptively clamping clamped objects with different thicknesses, so that the requirement on matching precision is greatly reduced in the aspect of machining of the missile wing installation surface.
Drawings
FIG. 1(a) is a side view of the structure of the mounting and fixing mechanism for the missile wing
FIG. 1(b) is a bottom view of the structure of the fastening mechanism for mounting the missile wing
FIG. 2 is a side view of the operation principle of the missile wing installation and fixation mechanism
FIG. 3 is an axonometric view of the working principle of the missile wing installation fixing mechanism
Wherein, 1-covering 2-elastic wing 3-self-locking nut 4-longitudinal skewed tooth transmission rod 5-transverse skewed tooth transmission rod 6-symmetrical clamping plate 7-shell
Detailed Description
The invention is described in further detail below with reference to the drawings.
The invention mainly comprises two sets of helical tooth transmission rods, symmetrical clamping plates and a shell. One set of helical transmission rod penetrates through the skin and is connected with a self-locking nut with a self-locking function arranged in the shell below the skin, and only a screw head with a cross-shaped groove for operation is exposed outside the skin. The symmetrical clamping plates are arranged on two side plates of the shell through two hanging shafts, threaded holes with different rotation directions are formed in the middles of the symmetrical clamping plates and are connected with the other set of helical gear transmission rods, small gears at the end heads of the two sets of helical gear transmission rods are meshed, and the two transmission rods are in a right-angle form. The shell connects the mechanisms into a whole and is fixed in the bomb, grooves with guide grooves are formed in two side plates, and the grooves are connected with hanging shafts of the symmetrical clamping plates.
The method is characterized in that:
1) the whole set of mechanism is arranged at the inner side of the projectile body and only exposes the operable screw head;
2) the two sets of helical tooth transmission rods are respectively connected with the self-locking nut and the symmetrical clamping plate;
3) the screw thread holes in the middle of the two symmetrical clamping plates have opposite rotating directions;
4) the shell side plate is provided with a groove with a guide groove and is connected with the hanging shaft of the symmetrical clamping plate;
5) the oblique teeth at the ends of the two sets of oblique tooth transmission rods are meshed and are in a right-angle form.
As shown in fig. 1, the present invention can be divided into three parts in terms of functional structure. The self-locking nut 3, the longitudinal helical transmission rod 4 and the transverse helical transmission rod 5 form a set of threaded gear transmission mechanism together, and the set of threaded gear transmission mechanism is used for transmitting power for the symmetrical clamping plates 6; the transverse helical tooth transmission rod 5 and the two symmetrical clamping plates 6 form a set of clamping and releasing mechanism, and the main functions of the invention are directly realized; the shell 7 provides a mounting and fixing space for the whole mechanism and provides an outer cladding. Wherein, the shell side plate 7.1 is provided with a groove with a guide groove, the guide slope of the groove is matched with the thread pitch of the self-locking nut 3, and the upper surface of the shell is provided with a strip-shaped elastic wing inserting hole. The middle of the two symmetrical clamping plates 6 is provided with threaded holes with opposite rotating directions, the side surfaces of the two symmetrical clamping plates are provided with hanging shafts, the hanging shafts can be arranged in grooves of the side plates 7.1 of the shell, and short bolts are arranged on the clamping surfaces and can be inserted into the preformed holes of the missile wings in the clamping process. The self-locking nut 3 is fixed on the upper surface of the shell 7 and is connected with the longitudinal helical tooth transmission rod 4 through threads. The two sets of helical transmission rods 4/5 are provided with screw threads, one end of each helical transmission rod is provided with a small helical gear, the two sets of helical transmission rods realize transmission through gear engagement, and the transverse helical transmission rod 5 is connected with the symmetrical clamping plate 6 through screw threads.
The working principle is as follows:
as shown in fig. 2-3, the mounting and fixing mechanism for the missile wing is mounted in the inner cavity of the missile body, and the operating end with the cross-shaped groove screw head of the longitudinal helical tooth transmission rod 4 penetrates out of the reserved hole position of the missile body. The missile wing is inserted from a strip-shaped insertion hole in the top of the shell 7, a universal tool is used for rotating the screw head of the longitudinal helical tooth transmission rod 4, the transverse helical tooth transmission rod 5 is driven to rotate through meshed helical teeth, two symmetrical clamping plates 6 are driven by threads on the transverse helical tooth transmission rod 5, and due to the fact that the rotation directions are opposite, opposite clamping movement is achieved, and a short bolt is inserted into a reserved hole of the missile wing. When the clamping action is carried out, the longitudinal helical tooth transmission rod 4 can move downwards to a certain degree under the action of the self-locking nut 3 in the rotating process, meanwhile, the symmetrical clamping plates 6 can also move downwards under the action of the guide grooves on the shell side plates 7.1 when moving in opposite centering, and the elastic wings are tensioned downwards through the short bolts. The two actions are performed synchronously, and the missile wing can be tensioned radially while being clamped transversely, so that the gap between the missile wing and the surface of the missile body is eliminated, and the missile wing is reliably fixed.
Claims (5)
1. A mounting and fixing mechanism for an elastic wing comprises a self-locking nut (3), a longitudinal helical tooth transmission rod (4), a transverse helical tooth transmission rod (5), a symmetrical clamping plate (6) and a shell (7);
the missile wing skin (1) is provided with a preset hole, the longitudinal helical tooth transmission rod (4) is inserted into the preset hole on the missile wing skin (1) and is in threaded transmission through the self-locking nut (3), a gear at the bottom of the longitudinal helical tooth transmission rod (4) is matched with a gear at one end of the transverse helical tooth transmission rod (5), and the self-locking nut (3), the longitudinal helical tooth transmission rod (4) and the transverse helical tooth transmission rod (5) jointly form a set of threaded gear transmission mechanism which transmits power for the symmetrical clamping plate (6); threaded holes with opposite rotation directions are formed in the middle of the two symmetrical clamping plates (6), the transverse skewed tooth transmission rod (5) is screwed into the threaded holes of the two symmetrical clamping plates (6), and the transverse skewed tooth transmission rod (5) and the two symmetrical clamping plates (6) form a set of clamping and releasing mechanism; the shell (7) provides a mounting and fixing space for the missile wing mounting and fixing mechanism and provides an outer cladding.
2. The missile wing installation and fixation mechanism of claim 1 is characterized in that the shell side plates (7.1) at two sides of the shell (7) are respectively provided with a groove with a guide groove, the guide slope of the groove is matched with the thread pitch of the self-locking nut (3), the side surfaces of the two symmetrical clamping plates (6) are provided with hanging shafts which can be arranged in the grooves of the shell side plates (7.1), and strip-shaped missile wing insertion holes are reserved on the upper surface of the shell (7).
3. The missile wing installation and fixation mechanism as claimed in claim 2, wherein the inner side clamping surface of the symmetrical clamping plate (6) is provided with a short bolt which can be inserted into the missile wing prepared hole during the clamping process.
4. A missile wing installation fixing mechanism as claimed in claim 3 wherein the self-locking nut (3) is fixed on the upper surface of the shell (7) and is connected with the longitudinal skewed tooth drive rod (4) through screw threads.
5. The missile wing installation and fixation mechanism as claimed in claim 4, wherein the longitudinal helical gear transmission rod (4) and the transverse helical gear transmission rod (5) are provided with threads, one ends of the longitudinal helical gear transmission rod (4) and the transverse helical gear transmission rod (5) are provided with small helical gears, the longitudinal helical gear transmission rod (4) and the transverse helical gear transmission rod (5) realize transmission through gear meshing, and the transverse helical gear transmission rod (5) is connected with the symmetrical clamping plates (6) through threads.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810977846.9A CN109186369B (en) | 2018-08-24 | 2018-08-24 | Missile wing installation fixed establishment |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810977846.9A CN109186369B (en) | 2018-08-24 | 2018-08-24 | Missile wing installation fixed establishment |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109186369A CN109186369A (en) | 2019-01-11 |
| CN109186369B true CN109186369B (en) | 2020-10-16 |
Family
ID=64915991
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810977846.9A Active CN109186369B (en) | 2018-08-24 | 2018-08-24 | Missile wing installation fixed establishment |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109186369B (en) |
Family Cites Families (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3219158A (en) * | 1964-03-30 | 1965-11-23 | Ralph E Carter | Quick attach panel fastener |
| CN102363444B (en) * | 2011-09-09 | 2013-07-17 | 江西洪都航空工业集团有限责任公司 | Transverse folding mechanism for empennage |
| CN204549800U (en) * | 2015-01-08 | 2015-08-12 | 天津鼎天斯凯特机械有限公司 | A kind of sheet metal auxiliary hoisting device |
| CN207268591U (en) * | 2017-09-20 | 2018-04-24 | 成都云鼎智控科技有限公司 | A kind of expansion locking linkage for longitudinal folding missile wing |
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2018
- 2018-08-24 CN CN201810977846.9A patent/CN109186369B/en active Active
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| Publication number | Publication date |
|---|---|
| CN109186369A (en) | 2019-01-11 |
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