CN110108170B - Bidirectional locking device for transverse missile folding wings and locking method thereof - Google Patents
Bidirectional locking device for transverse missile folding wings and locking method thereof Download PDFInfo
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- CN110108170B CN110108170B CN201910329228.8A CN201910329228A CN110108170B CN 110108170 B CN110108170 B CN 110108170B CN 201910329228 A CN201910329228 A CN 201910329228A CN 110108170 B CN110108170 B CN 110108170B
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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 bidirectional locking device for a transverse missile folding wing and a locking method thereof. The existing bidirectional locking structure of the folding wing of the transverse missile needs two sets of mechanisms to lock two directions respectively. The locking mechanism comprises a first thrust pin, a first connecting rod, a second connecting rod, a trigger rod, an L-shaped crank, a pre-tightening spring, a second thrust pin, a second spring, a second bolt, a first spring and a first bolt. When the outer wing is unfolded to touch the trigger rod, the trigger rod drives the second connecting rod, the crank, the first connecting rod, the first thrust pin and the second thrust pin, the second clamping block is separated from the clamping groove of the second bolt, and the second bolt is ejected out along the second pin hole under the action of the second spring and inserted into the radial blind hole of the outer wing; the first clamping block is separated from the clamping groove of the first bolt, the first bolt is ejected out along the first pin hole under the action of the first spring, and the first bolt is inserted into the axial through hole of the outer wing. The invention realizes the bidirectional locking of the folding wing through the transmission of the crank and the connecting rod, and has simple mechanism and high locking reliability.
Description
Technical Field
The invention belongs to the field of weaponry, and particularly relates to a bidirectional locking device for a folding wing of a transverse missile and a locking method thereof.
Background
In order to facilitate storage and transportation of missiles and realize rapid deployment of the missiles, missile wing folding devices are widely applied to various tactical missiles at present, and the device can reduce the occupation of a missile body on radial space. In the transverse missile folding wing device, a chord-direction separation surface is usually arranged at the root or the middle part of a wing surface along the airflow direction, and the folding or unfolding process of the wing surface of the missile is completed on a separation surface rotating shaft.
After the missile is launched, the outer wing rotates around the axis under the action of the driving force, and the outer wing and the wing root are fixed by the locking device at a preset position. The existing missile folding wing locking modes comprise three modes of unfolding (radial direction of the missile), axial direction and bidirectional locking, wherein the one-way locking scheme is simple in design, but the locking device can cause the situation that a lock pin cannot be normally positioned under the condition that pneumatic loads are randomly distributed along the axial direction of the missile. The existing bidirectional locking structure has better environmental adaptability, but the structure is more complex, and two sets of electromechanical systems are needed to realize control. It is desirable to design a device that can combine a simple triggering system with a reliable lock in both directions.
Disclosure of Invention
One object of the present invention is to provide a device for the bidirectional (radial and axial) locking of airfoils for transverse folding wings, which has the advantages of simple mechanism, high locking reliability, etc. Another object of the present invention is to provide a locking method of the airfoil bi-directional locking device.
The technical scheme adopted by the invention is as follows:
the invention relates to a bidirectional locking device for a transverse missile folding wing. Two bosses are fixed on the end surface of the outer wing opposite to the wing root, and two radial blind holes arranged at intervals are arranged between the two bosses; the boss is provided with an axial through hole, and the axis of the axial through hole is vertical to the axis of the radial blind hole; chamfers are arranged at the inner end of the axial through hole and the top end of the radial blind hole; the bottom of the outer wing is fixedly provided with two first hollow cylinders which are coaxial and arranged at intervals, and the axes of the first hollow cylinders are parallel to the axis of the axial through hole. Two second hollow cylinders arranged at intervals are fixed at one end of the bottom of the wing root, the other two second hollow cylinders arranged at intervals are fixed at the other end of the bottom, and positioning grooves are formed in two ends of the top of the wing root; the four second hollow cylinders are coaxially arranged; one first hollow cylinder of the outer wing and the two second hollow cylinders at one end of the wing root form a revolute pair through a pin shaft, and the other first hollow cylinder of the outer wing and the two second hollow cylinders at the other end of the wing root form a revolute pair through a pin shaft; the tail parts of the two pin shafts are connected with compression nuts; a locking mechanism is arranged in each positioning groove.
The locking mechanism comprises a locking support, a first anti-over pin, a first guide frame, a first thrust pin, a first connecting rod, a first support column, a second connecting rod, a second support column, a trigger rod, an L-shaped crank, a third support column, a second guide frame, a pre-tightening spring, a third guide frame, a second thrust pin, a second anti-over pin, a second spring, a second bolt, a first spring and a first bolt.
The locking bracket is provided with a first groove and a second groove, and is fixedly provided with a first cavity and a second cavity, the first groove is arranged on the side part of the first cavity, and the second groove is arranged between the first cavity and the second cavity; the bottom of the locking bracket is provided with an installation bottom plate, and four installation holes of the installation bottom plate are fastened on the positioning grooves of the wing roots through screws. The first guide frame is fastened on the first groove through a screw, a first guide hole is formed in the first guide frame, and the axis of the first guide hole is parallel to the mounting bottom plate; the second guide frame and the third guide frame are fastened on the second groove through screws, the second guide frame is provided with a second guide hole, and the third guide frame is provided with a third guide hole; the second guide hole and the third guide hole are coaxially arranged, the axes of the second guide hole and the third guide hole are both parallel to the mounting base plate, and the axis of the second guide hole is vertical to the axis of the first guide hole; the first support column, the second support column and the third support column are in interference fit with three supporting holes arranged on the locking bracket at intervals respectively; the first support, the second support and the third support are all perpendicular to the mounting base plate.
The first cavity is provided with a first pin hole with the axis parallel to the second guide hole and a trigger rod hole with the axis parallel to the first guide hole; a first side open groove and a first limit groove are formed in the side part of the first pin hole, the axis of the first limit groove is perpendicular to the mounting bottom plate, and the axis of the first side open groove is parallel to the axis of the first guide hole; the second cavity is provided with a second pin hole of which the axis is parallel to the first guide hole; a second limiting groove and two second side open grooves are formed in the side part of the second pin hole, the axis of the second limiting groove is perpendicular to the mounting bottom plate, and the axis of the second side open groove is parallel to the second guide hole; the two second side grooves are symmetrically arranged on two sides of the second pin hole.
The first bolt and the first pin hole form a sliding pair and are connected with the first pin hole through a first spring; the second bolt and the second pin hole form a sliding pair and are connected with the second pin hole through a second spring; chamfers are arranged at one end of the first bolt facing the axial through hole and one end of the second bolt facing the radial blind hole; the first spring and the second spring are both compression springs. The external thread at the bottom of the first anti-over-position pin is connected with the threaded hole at the side part of the first bolt, and the top of the first anti-over-position pin extends out of the first limiting groove; the external thread of the bottom of the second anti-dislocation pin is connected with the threaded hole in the side of the second bolt, and the top of the second anti-dislocation pin extends out of the second limiting groove.
One end of the first thrust pin is provided with a first clamping block which is integrally formed; the first thrust pin and the first guide hole of the first guide frame form a sliding pair; the first clamping block penetrates through the first side groove and is embedded into the clamping groove in the side portion of the first bolt. The middle part of the first connecting rod and the first support column form a revolute pair, and a chute at one end and the end of the first thrust pin, which is not provided with the first fixture block, form a chute pin pair through a pin; a first middle position of the second connecting rod and the second support form a rotating pair, and one end of the second connecting rod and the sliding groove at the other end of the first connecting rod form a groove pin pair through a pin; the trigger rod and the trigger rod hole form a sliding pair, two ends of the trigger rod and the trigger rod hole extend out of the trigger rod hole, one end of the trigger rod is provided with a hemispherical surface, and the other end of the trigger rod and a sliding groove at the second middle position of the second connecting rod form a groove pin pair through a pin; the bent angle of the L-shaped crank and the third support form a revolute pair, and the sliding groove at one end and the other end of the second connecting rod form a groove pin pair through a pin. One end of the second thrust pin is provided with a second clamping block which is integrally formed; the second thrust pin, a second guide hole of the second guide frame and a third guide hole of the third guide frame form a sliding pair; the second clamping block penetrates through the second side groove facing the inner side and is embedded into the clamping groove in the side part of the second bolt. The end of the second thrust pin, which is not provided with the second clamping block, and the sliding groove at the other end of the L-shaped crank form a groove pin pair through a pin; the pre-tightening spring is sleeved on the second thrust pin, one end of the pre-tightening spring is in contact with a convex ring integrally formed in the middle of the second thrust pin, and the other end of the pre-tightening spring is in contact with the second guide frame; the pre-tightening spring is a compression spring.
The second bolts of the two locking mechanisms are respectively aligned with the two radial blind holes of the outer wing, and the ends of the second bolts, which are not connected with the second springs, face the radial blind holes; and in the axial direction of the axial through hole, the outer end faces of the first cavities of the two locking mechanisms are respectively provided with a distance from the inner end face of the boss at the corresponding end of the outer wing.
Further, the assembling process of the second thrust pin and the pre-tightening spring is as follows: and sleeving a pre-tightening spring into the second thrust pin, sleeving the first guide frame and the second guide frame into two ends of the second thrust pin respectively, and fastening the first guide frame and the second guide frame on the second groove.
The locking method of the bidirectional locking device for the folding wings of the transverse missile specifically comprises the following steps:
fixing the wing root on the missile body, enabling the outer wing to rotate around the pin shaft to be in a state of being attached to the missile body, and placing the missile body in the launching barrel. When the missile is separated, the outer wing is released from the limit, the outer wing is rotated and unfolded around the pin shaft under the action of driving force, when the outer wing is unfolded to touch the trigger rod on the end face opposite to the wing root, the trigger rod retracts to drive the second connecting rod, the crank, the first connecting rod, the first thrust pin and the second thrust pin, and at the moment, the axial through hole of the boss on the outer wing is coaxial with the first pin hole. The second thrust pin overcomes the elasticity of the pre-tightening spring, slides along the second guide frame and the third guide frame in the direction far away from the second side groove, and the second clamping block is separated from the clamping groove at the side part of the second bolt; and the second bolt is released from limitation, is popped out along the second pin hole under the action of the elastic force of the second spring, is inserted into the radial blind hole of the outer wing, and stops until the second over-position preventing pin is limited by the end part of the second limiting groove, so that radial locking is completed.
When the second thrust pin slides, the first thrust pin slides along the first guide frame in the direction away from the first side groove, the first clamping block is separated from the clamping groove in the side portion of the first bolt, the first bolt is released from limitation, is popped out along the first pin hole under the action of the elastic force of the first spring and is inserted into the axial through hole of the outer wing until the first anti-over-position pin is limited by the end portion of the first limiting groove, and the first bolt stops to complete axial locking.
The invention has the following beneficial effects:
1. the locking device only occupies the space on two sides of the missile wing, has small volume, and realizes the radial and axial bidirectional locking of the wing surface under the condition of not damaging the aerodynamic appearance of the folding wing surface.
2. The invention simultaneously triggers the movement of the radial bolt and the axial bolt through the movement of the crank and the connecting rod, thereby realizing locking and avoiding arranging two sets of independent locking mechanisms in the radial direction and the axial direction at the wing root.
3. The thickness difference between the wing root and the outer wing of the folding wing of the missile is utilized, and the original structure of the folding wing of the missile is not changed.
Drawings
FIG. 1 is a schematic view of the overall structure of the present invention in a folded state of the outer wing;
FIG. 2 is a schematic view of the overall structure of the locking mechanism of the present invention;
FIG. 3 is a schematic view of the outer wing and wing root assembly of the present invention;
FIG. 4 is an assembly view of part of the locking mechanism of the present invention;
FIG. 5 is a perspective view of the locking bracket of the present invention;
FIG. 6 is a top view of the locking mechanism of the present invention;
FIG. 7 is a cross-sectional view of the locking mechanism of the present invention;
FIG. 8 is a schematic view of the overall structure of the present invention in a radially locked condition;
FIG. 9 is a schematic view of the overall structure of the present invention in a bi-directional locked state;
fig. 10 is a mechanical movement diagram of the locking mechanism of the present invention.
Detailed Description
The invention is further described below with reference to the accompanying drawings.
As shown in fig. 1 and 2, the bidirectional locking device for the folding wing of the transverse missile comprises an outer wing 1, a wing root 2, a pin shaft 3, a compression nut 4 and a locking mechanism.
As shown in fig. 3, two bosses 1-1 are fixed on the end surface of the outer wing 1 opposite to the wing root 2, and two radial blind holes 1-3 arranged at intervals are arranged between the two bosses 1-1; the boss 1-1 is provided with an axial through hole 1-2, and the axis of the axial through hole 1-2 is vertical to the axis of the radial blind hole 1-3; two first hollow cylinders 1-4 which are coaxial and arranged at intervals are fixedly arranged at the bottom of the outer wing 1, and the axes of the first hollow cylinders 1-4 are parallel to the axes of the axial through holes 1-2.
As shown in fig. 3, two second hollow cylinders 2-1 arranged at intervals are fixed at one end of the bottom of the wing root 2, another two second hollow cylinders 2-1 arranged at intervals are fixed at the other end of the bottom, and positioning grooves 2-2 are formed in both ends of the top; the four second hollow cylinders 2-1 are coaxially arranged; one first hollow cylinder 1-4 of the outer wing 1 and two second hollow cylinders 2-1 at one end of the wing root 2 form a revolute pair through a pin shaft 3, and the other first hollow cylinder 1-4 of the outer wing 1 and two second hollow cylinders 2-1 at the other end of the wing root 2 form a revolute pair through the pin shaft 3, so that the outer wing 1 can rotate around the pin shaft 3; the tail parts of the two pin shafts 3 are connected with compression nuts; a locking mechanism is arranged in each positioning groove 2-2.
As shown in fig. 2, the locking mechanism includes a locking bracket 5, a first over-position prevention pin 6, a first guide frame 7, a first thrust pin 8, a first link 9, a first support 10, a second link 11, a second support 12, a trigger lever 13, an L-shaped crank 14, a third support 15, a second guide frame 16, a pre-tightening spring 17, a third guide frame 18, a second thrust pin 19, a second over-position prevention pin 20, a second spring 21, a second bolt 22, a first spring 23, and a first bolt 24.
As shown in fig. 4, the locking bracket 5 is provided with a first groove 5-1 and a second groove 5-3, and is fixedly provided with a first cavity 5-2 and a second cavity 5-4, the first groove 5-1 is arranged at the side of the first cavity 5-2, and the second groove 5-3 is arranged between the first cavity 5-2 and the second cavity 5-4; the bottom of the locking bracket 5 is provided with an installation bottom plate 5-5, and four installation holes of the installation bottom plate 5-5 are fastened on the positioning grooves 2-2 of the wing roots 2 through screws. The first guide frame 7 is fastened on the first groove 5-1 through a screw, a first guide hole is formed in the first guide frame, and the axis of the first guide hole is parallel to the mounting bottom plate 5-5; the second guide frame 16 and the third guide frame 18 are fastened on the second groove 5-3 through screws, the second guide frame 16 is provided with a second guide hole, and the third guide frame 18 is provided with a third guide hole; the second guide hole and the third guide hole are coaxially arranged, the axes of the second guide hole and the third guide hole are both parallel to the mounting bottom plate 5-5, and the axis of the second guide hole is vertical to the axis of the first guide hole; the first support column 10, the second support column 12 and the third support column 15 are in interference fit with three supporting holes arranged at intervals on the locking bracket 5 respectively; the first 10, second 12 and third 15 legs are all perpendicular to the mounting base 5-5.
As shown in fig. 5, the first cavity 5-2 is provided with a first pin hole 5-2-3 with an axis parallel to the second guide hole and a trigger rod hole 5-2-4 with an axis parallel to the first guide hole; a first side open groove 5-2-2 and a first limit groove 5-2-1 are formed in the side part of the first pin hole 5-2-3, the axis of the first limit groove 5-2-1 is perpendicular to the mounting bottom plate 5-5, and the axis of the first side open groove 5-2-2 is parallel to the axis of the first guide hole; a second pin hole 5-4-3 with the axis parallel to the first guide hole is formed in the second cavity 5-4; a second limiting groove 5-4-1 and two second side open grooves 5-4-2 are formed in the side part of the second pin hole 5-4-3, the axis of the second limiting groove 5-4-1 is perpendicular to the mounting bottom plate 5-5, and the axis of the second side open groove 5-4-2 is parallel to the second guide hole; the two second side grooves 5-4-2 are symmetrically arranged at two sides of the second pin hole 5-4-3; the provision of two second side slots 5-4-2 is a processing consideration, since the inner side of the second cavity 5-4 does not leave enough space for the milling cutter.
As shown in fig. 6, the first pin 24 and the first pin hole 5-2-3 form a sliding pair, and are connected with the first pin hole 5-2-3 through the first spring 23; the second bolt 22 and the second pin hole 5-4-3 form a sliding pair and are connected with the second pin hole 5-4-3 through a second spring 21; the first spring 23 and the second spring 21 are both compression springs. The external thread at the bottom of the first over-position preventing pin 6 is connected with the threaded hole at the side part of the first bolt 24, and the top of the first over-position preventing pin 6 extends out of the first limiting groove 5-2-1; the external thread at the bottom of the second over-position preventing pin 20 is connected with the threaded hole at the side of the second bolt 22, and the top of the second over-position preventing pin 20 extends out of the second limiting groove 5-4-1.
As shown in fig. 2, 7 and 10, one end of the first thrust pin 8 is provided with a first latch which is integrally formed; the first thrust pin 8 and the first guide hole of the first guide frame form a sliding pair; the first clamping block penetrates through the first side slot 5-2-2 and is embedded into a clamping groove in the side part of the first bolt 24. The middle part of the first connecting rod 9 and the first support column 10 form a revolute pair, and a chute at one end and the end of the first thrust pin 8, which is not provided with the first fixture block, form a chute pin pair through a pin; a first middle position of the second connecting rod 11 and the second support 12 form a rotating pair, and one end of the second connecting rod and a sliding groove at the other end of the first connecting rod 9 form a groove pin pair through a pin; the trigger rod 13 and the trigger rod hole 5-2-4 form a sliding pair, two ends of the sliding pair extend out of the trigger rod hole 5-2-4, one end of the sliding pair is provided with a hemispherical surface, and the other end of the sliding pair and a sliding groove at the second middle position of the second connecting rod 11 form a groove pin pair through a pin; the semispherical surface of the trigger rod 13 facilitates pushing the trigger rod 13 when the end surface of the outer wing opposite to the wing root 2 is contacted with the trigger rod 13; the bent angle of the L-shaped crank 14 and the third pillar 15 form a revolute pair, and the sliding groove at one end and the other end of the second connecting rod 11 form a groove-pin pair through a pin. One end of the second thrust pin 19 is provided with a second clamping block which is integrally formed; the second thrust pin 19, the second guide hole of the second guide frame 16 and the third guide hole of the third guide frame 18 form a sliding pair; the second block passes through the slot 5-4-2 on the second side facing the inner side and is embedded into the slot on the side of the second bolt 22. The end of the second thrust pin 19 without the second clamping block and the sliding groove at the other end of the L-shaped crank 14 form a groove pin pair through a pin; the pre-tightening spring 17 is sleeved on the second thrust pin 19, one end of the pre-tightening spring is contacted with a convex ring integrally formed in the middle of the second thrust pin 19, and the other end of the pre-tightening spring is contacted with the second guide frame 16; the pre-tightening spring is a compression spring and provides pre-tightening force to keep the locking mechanism in the initial state of fig. 7. The second thrust pin 19 and the preloaded spring are assembled as follows: the pre-tightening spring is sleeved on the second thrust pin 19, the first guide frame 16 and the second guide frame 18 are sleeved on two ends of the second thrust pin 19 respectively, and finally the first guide frame 16 and the second guide frame 18 are fastened on the second groove 5-3.
The second bolts 22 of the two locking mechanisms are respectively aligned with the two radial blind holes 1-3 of the outer wing 1, and the ends of the second bolts 22 which are not connected with the second springs 21 are arranged towards the radial blind holes 1-3; along the axial direction of the axial through hole, the outer end faces of the first cavities 5-2 of the two locking mechanisms are respectively provided with a distance from the inner end face of the boss 1-1 at the corresponding end of the outer wing 1.
Chamfers are arranged at the inner end of the axial through hole 1-2, the top end of the radial blind hole 1-3, the end of the first bolt 24 facing the axial through hole and the end of the second bolt 22 facing the radial blind hole, so that the first bolt 24 is easily inserted into the axial through hole, and the second bolt 22 is easily inserted into the radial blind hole 1-3.
The locking method of the bidirectional locking device for the folding wings of the transverse missile specifically comprises the following steps:
the wing root 2 is fixed on the missile body, the outer wing 1 rotates around the pin shaft to be in a state of being attached to the missile body, and the missile body is placed in the launching barrel. When the missile is separated, the outer wing 1 is not limited, the outer wing rotates and expands around the pin shaft 3 under the action of driving force, when the outer wing 1 expands to the position where the end surface opposite to the wing root 2 touches the trigger rod 13, the trigger rod 13 retracts (V in figure 10 is the retraction speed of the trigger rod 13) to drive the second connecting rod 11, the crank 14, the first connecting rod 9, the first thrust pin 8 and the second thrust pin 19, and at the moment, the axial through hole 1-2 of the boss 1-1 on the outer wing 1 is coaxial with the first pin hole 5-2-3. The second thrust pin 19 overcomes the elastic force of the pre-tightening spring 17, and slides along the second guide frame 16 and the third guide frame 18 in the direction away from the second side slot 5-4-2, so that the second clamping block is separated from the clamping groove at the side part of the second bolt 22; the second bolt 22 is released from the limitation, is ejected along the second pin hole 5-4-3 under the action of the elastic force of the second spring 21, and is inserted into the radial blind hole 1-3 of the outer wing 1 until the second over-position preventing pin 20 is limited by the end part of the second limiting groove 5-4-1, the second bolt stops, the radial locking is completed, and the state that the radial locking is completed when the second bolt 22 is ejected is shown in fig. 8.
When the second thrust pin 19 slides, the first thrust pin 8 slides along the first guide frame 7 in the direction away from the first side slot 5-2-2, the first clamping block is separated from the clamping groove on the side of the first bolt 24, the first bolt 24 is free from limitation, is ejected out along the first pin hole 5-2-3 under the action of the elastic force of the first spring 23 and is inserted into the axial through hole 1-2 of the outer wing 1 until the first anti-over-position pin 6 is limited by the end of the first limiting groove 5-2-1, the first bolt stops, and axial locking is completed. The bi-directional (radial and axial) locked state is shown in fig. 9.
Claims (3)
1. The utility model provides a two-way locking device for folding wing of horizontal guided missile, includes outer wing, wing root, round pin axle, gland nut and locking mechanical system, its characterized in that: two bosses are fixed on the end surface of the outer wing opposite to the wing root, and two radial blind holes arranged at intervals are arranged between the two bosses; the boss is provided with an axial through hole, and the axis of the axial through hole is vertical to the axis of the radial blind hole; chamfers are arranged at the inner end of the axial through hole and the top end of the radial blind hole; two first hollow cylinders which are coaxial and arranged at intervals are fixedly arranged at the bottom of the outer wing, and the axes of the first hollow cylinders are parallel to the axis of the axial through hole; two second hollow cylinders arranged at intervals are fixed at one end of the bottom of the wing root, the other two second hollow cylinders arranged at intervals are fixed at the other end of the bottom, and positioning grooves are formed in two ends of the top of the wing root; the four second hollow cylinders are coaxially arranged; one first hollow cylinder of the outer wing and the two second hollow cylinders at one end of the wing root form a revolute pair through a pin shaft, and the other first hollow cylinder of the outer wing and the two second hollow cylinders at the other end of the wing root form a revolute pair through a pin shaft; the tail parts of the two pin shafts are connected with compression nuts; a locking mechanism is arranged in each positioning groove;
the locking mechanism comprises a locking bracket, a first anti-over-position pin, a first guide frame, a first thrust pin, a first connecting rod, a first support column, a second connecting rod, a second support column, a trigger rod, an L-shaped crank, a third support column, a second guide frame, a pre-tightening spring, a third guide frame, a second thrust pin, a second anti-over-position pin, a second spring, a second bolt, a first spring and a first bolt;
the locking bracket is provided with a first groove and a second groove, and is fixedly provided with a first cavity and a second cavity, the first groove is arranged on the side part of the first cavity, and the second groove is arranged between the first cavity and the second cavity; the bottom of the locking bracket is provided with an installation bottom plate, and four installation holes of the installation bottom plate are fastened on the positioning grooves of the wing roots through screws; the first guide frame is fastened on the first groove through a screw, a first guide hole is formed in the first guide frame, and the axis of the first guide hole is parallel to the mounting bottom plate; the second guide frame and the third guide frame are fastened on the second groove through screws, the second guide frame is provided with a second guide hole, and the third guide frame is provided with a third guide hole; the second guide hole and the third guide hole are coaxially arranged, the axes of the second guide hole and the third guide hole are both parallel to the mounting base plate, and the axis of the second guide hole is vertical to the axis of the first guide hole; the first support column, the second support column and the third support column are in interference fit with three supporting holes arranged on the locking bracket at intervals respectively; the first support column, the second support column and the third support column are all perpendicular to the mounting bottom plate;
the first cavity is provided with a first pin hole with the axis parallel to the second guide hole and a trigger rod hole with the axis parallel to the first guide hole; a first side open groove and a first limit groove are formed in the side part of the first pin hole, the axis of the first limit groove is perpendicular to the mounting bottom plate, and the axis of the first side open groove is parallel to the axis of the first guide hole; the second cavity is provided with a second pin hole of which the axis is parallel to the first guide hole; a second limiting groove and two second side open grooves are formed in the side part of the second pin hole, the axis of the second limiting groove is perpendicular to the mounting bottom plate, and the axis of the second side open groove is parallel to the second guide hole; the two second side grooves are symmetrically arranged at two sides of the second pin hole;
the first bolt and the first pin hole form a sliding pair and are connected with the first pin hole through a first spring; the second bolt and the second pin hole form a sliding pair and are connected with the second pin hole through a second spring; chamfers are arranged at one end of the first bolt facing the axial through hole and one end of the second bolt facing the radial blind hole; the first spring and the second spring are both compression springs; the external thread at the bottom of the first anti-over-position pin is connected with the threaded hole at the side part of the first bolt, and the top of the first anti-over-position pin extends out of the first limiting groove; the external thread at the bottom of the second anti-over-position pin is connected with the threaded hole at the side part of the second bolt, and the top of the second anti-over-position pin extends out of the second limiting groove;
one end of the first thrust pin is provided with a first clamping block which is integrally formed; the first thrust pin and the first guide hole of the first guide frame form a sliding pair; the first clamping block penetrates through the first side groove and is embedded into the clamping groove in the side part of the first bolt; the middle part of the first connecting rod and the first support column form a revolute pair, and a chute at one end and the end of the first thrust pin, which is not provided with the first fixture block, form a chute pin pair through a pin; a first middle position of the second connecting rod and the second support form a rotating pair, and one end of the second connecting rod and the sliding groove at the other end of the first connecting rod form a groove pin pair through a pin; the trigger rod and the trigger rod hole form a sliding pair, two ends of the trigger rod and the trigger rod hole extend out of the trigger rod hole, one end of the trigger rod is provided with a hemispherical surface, and the other end of the trigger rod and a sliding groove at the second middle position of the second connecting rod form a groove pin pair through a pin; the bent angle of the L-shaped crank and the third support form a rotating pair, and a chute at one end and the other end of the second connecting rod form a chute pin pair through a pin; one end of the second thrust pin is provided with a second clamping block which is integrally formed; the second thrust pin, a second guide hole of the second guide frame and a third guide hole of the third guide frame form a sliding pair; the second clamping block penetrates through the second side slot facing the inner side and is embedded into the clamping slot at the side part of the second bolt; the end of the second thrust pin, which is not provided with the second clamping block, and the sliding groove at the other end of the L-shaped crank form a groove pin pair through a pin; the pre-tightening spring is sleeved on the second thrust pin, one end of the pre-tightening spring is in contact with a convex ring integrally formed in the middle of the second thrust pin, and the other end of the pre-tightening spring is in contact with the second guide frame; the pre-tightening spring is a compression spring;
the second bolts of the two locking mechanisms are respectively aligned with the two radial blind holes of the outer wing, and the ends of the second bolts, which are not connected with the second springs, face the radial blind holes; and in the axial direction of the axial through hole, the outer end faces of the first cavities of the two locking mechanisms are respectively provided with a distance from the inner end face of the boss at the corresponding end of the outer wing.
2. The bidirectional locking device for folding wings of lateral missiles as claimed in claim 1, characterized in that: the assembly process of the second thrust pin and the pre-tightening spring is as follows: and sleeving a pre-tightening spring into the second thrust pin, sleeving the first guide frame and the second guide frame into two ends of the second thrust pin respectively, and fastening the first guide frame and the second guide frame on the second groove.
3. The locking method of the bidirectional locking device for the folding wings of lateral missiles as claimed in claim 1 or 2, wherein: the method comprises the following specific steps:
fixing the wing root on the missile body, rotating the outer wing around the pin shaft to a state of being attached to the missile body, and placing the missile body in a launching barrel; when the missile is separated, the outer wing is not limited, the outer wing is rotated and unfolded around the pin shaft under the action of driving force, when the outer wing is unfolded to touch the trigger rod on the end surface opposite to the wing root, the trigger rod retracts to drive the second connecting rod, the L-shaped crank, the first connecting rod, the first thrust pin and the second thrust pin, and at the moment, the axial through hole of the boss on the outer wing is coaxial with the first pin hole; the second thrust pin overcomes the elasticity of the pre-tightening spring, slides along the second guide frame and the third guide frame in the direction far away from the second side groove, and the second clamping block is separated from the clamping groove at the side part of the second bolt; the second bolt is released from the limitation, is ejected out along the second pin hole under the action of the elastic force of the second spring and is inserted into the radial blind hole of the outer wing until the second over-position preventing pin is limited by the end part of the second limiting groove, and the second bolt stops to complete radial locking;
when the second thrust pin slides, the first thrust pin slides along the first guide frame in the direction away from the first side groove, the first clamping block is separated from the clamping groove in the side portion of the first bolt, the first bolt is released from limitation, is popped out along the first pin hole under the action of the elastic force of the first spring and is inserted into the axial through hole of the outer wing until the first anti-over-position pin is limited by the end portion of the first limiting groove, and the first bolt stops to complete axial locking.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201910329228.8A CN110108170B (en) | 2019-04-23 | 2019-04-23 | Bidirectional locking device for transverse missile folding wings and locking method thereof |
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| CN201910329228.8A CN110108170B (en) | 2019-04-23 | 2019-04-23 | Bidirectional locking device for transverse missile folding wings and locking method thereof |
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| CN110108170A CN110108170A (en) | 2019-08-09 |
| CN110108170B true CN110108170B (en) | 2021-05-11 |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN102226671B (en) * | 2011-05-26 | 2013-03-13 | 浙江理工大学 | Redundant locking type longitudinal expansion mechanism of folding wing |
| US8894004B1 (en) * | 2013-06-11 | 2014-11-25 | The United States Of America As Represented By The Secretary Of The Navy | Folding articulating wing mechanism |
| CN204461240U (en) * | 2015-01-21 | 2015-07-08 | 浙江理工大学 | Twice-folded aerofoil horizontal spreading mechanism |
| CN104677199B (en) * | 2015-01-21 | 2016-07-13 | 浙江理工大学 | A kind of single driving folds rudder face synchronous expansion mechanism more |
| CN208254325U (en) * | 2018-03-20 | 2018-12-18 | 浙江理工大学 | The guided missile synchronous drive-type secondary folding unfolding mechanism of single power source |
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