CN111426242B - Guided missile fixing mechanism - Google Patents
Guided missile fixing mechanism Download PDFInfo
- Publication number
- CN111426242B CN111426242B CN202010290662.2A CN202010290662A CN111426242B CN 111426242 B CN111426242 B CN 111426242B CN 202010290662 A CN202010290662 A CN 202010290662A CN 111426242 B CN111426242 B CN 111426242B
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- connecting rod
- missile
- base
- fixing mechanism
- rebound
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B39/00—Packaging or storage of ammunition or explosive charges; Safety features thereof; Cartridge belts or bags
- F42B39/22—Locking of ammunition in transport containers
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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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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B39/00—Packaging or storage of ammunition or explosive charges; Safety features thereof; Cartridge belts or bags
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- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Aviation & Aerospace Engineering (AREA)
- Combustion & Propulsion (AREA)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
Abstract
The invention provides a missile fixing mechanism which comprises a base, a connecting rod structure, a resetting structure and a starting device, wherein the base is fixedly connected with the connecting rod structure; the connecting rod structure is provided with a limiting block, the guided missile is arranged on the base, and the axis of the guided missile is parallel to the base; the missile fixing mechanism comprises a locking state and an unlocking state, and when the missile fixing mechanism is in the locking state, the limiting block is connected with the end surface of the missile; when the missile fixing mechanism is in an unlocking state, the limiting block is separated from the end surface of the missile, and is positioned outside the outer surface of the missile in the radial direction of the missile; the missile fixing mechanism can be switched from a locking state to an unlocking state under the action of the starting device, and the connecting rod structure can be reset under the action of the resetting structure. The missile launching device realizes the fixation and the unlocking of the missile through the mutual switching between the two states, acts on the tail part of the missile, solves the problem of insufficient installation space in the middle of the missile launching device, and can effectively adapt to the reverse launching form of the missile.
Description
Technical Field
The invention relates to the technical field of missile fixing, in particular to a missile fixing mechanism, and particularly relates to an axial missile fixing mechanism suitable for reversely launching a missile.
Background
The missile needs to be ensured to be reliably fixed in the axial direction during storage and transportation of the missile, the missile needs to be quickly unlocked to successfully complete launching during launching, and most of the existing missiles utilize a missile fixing mechanism to realize the functions of axial fixing and unlocking.
Research is carried out aiming at the missile fixing mode of various domestic missiles, and research shows that most of the existing missile fixing mechanisms are arranged in the middle or at the tail of the missile. When the mechanism is arranged in the middle part, the missile sliding block is hooked by the clamping hook to realize the axial limiting function, but enough mechanism installation space is required in the middle part of the launching device; when the missile is installed at the tail of the missile, the missile mainly plays a role in axial auxiliary support, and the missile can only carry out forward launching in the state. When the middle part of the launching device has no enough mechanism installation space and the missile needs to implement reverse launching, the bullet fixing mechanism cannot be applied. Therefore, a novel missile axial direction fixing mechanism which can be installed at the tail of a missile and can adapt to reverse launching is needed in the industry.
Patent document with publication number CN210162264U discloses a missile hanging rack and a missile hanging structure, and belongs to the technical field of missile loading. The missile hanger disclosed in the patent document comprises a first connecting rod, wherein a first hinge part is arranged in the middle of the first connecting rod, and the first connecting rod can rotate relative to the first hinge part; the middle part of the second connecting rod is provided with a second hinge part, and the second connecting rod can rotate relative to the second hinge part; one end of the third connecting rod is hinged with the upper end of the first connecting rod, and the other end of the third connecting rod is hinged with the upper end of the second connecting rod; the missile locking device comprises a first connecting rod, a second connecting rod and a third connecting rod, wherein a supporting column is fixedly connected to the first connecting rod, the supporting column can be driven to rotate when being driven to move, and a first hook is further arranged at the lower end of the first connecting rod and used for locking a missile to be loaded. The missile mounting structure disclosed by the patent document is simple in structure, light in weight and convenient to mount. However, the device adopts a fixed structure arranged in the middle of the missile, and when the middle of the launching device does not have enough mechanism installation space, the device is not suitable for use, and the device cannot realize reverse launching of the missile.
Disclosure of Invention
Aiming at the defects in the prior art, the invention aims to provide a missile fixing mechanism.
The missile fixing mechanism provided by the invention comprises a base, a connecting rod structure, a resetting structure and a starting device;
the missile launching device comprises a base, a reset structure, a starting device, a connecting rod structure, a limit block and a missile body, wherein the reset structure is respectively connected with the base and the connecting rod structure;
the missile fixing mechanism comprises a locking state and an unlocking state, and when the missile fixing mechanism is in the locking state, the limiting block is connected with the end surface of the missile; when the missile fixing mechanism is in an unlocking state, the limiting block is separated from the end surface of the missile, and is positioned outside the outer surface of the missile in the radial direction of the missile;
the missile fixing mechanism can be switched from a locking state to an unlocking state under the action of the starting device, and the connecting rod structure can be reset from the position of the unlocking state to the position of the locking state under the action of the resetting structure.
Preferably, the base is provided with a guide rail, and the missile is mounted on the guide rail and can slide on the guide rail.
Preferably, the connecting rod structure comprises a translational connecting rod, an anti-rebounding connecting rod and a rotating connecting rod, the translational connecting rod is arranged in parallel with the base, and a set distance exists between the translational connecting rod and the base when the missile fixing mechanism is in a locking state;
one end of the anti-rebounding connecting rod is connected with the base, the other end of the anti-rebounding connecting rod is connected with the translation connecting rod, one end of the rotation connecting rod is connected with the base, the other end of the rotation connecting rod is connected with the translation connecting rod, and one or more limiting blocks are arranged on the translation connecting rod;
the anti-rebounding connecting rod and the rotating connecting rod are arranged in parallel, and the translation connecting rod, the anti-rebounding connecting rod, the base and the rotating connecting rod form a parallelogram mechanism.
Preferably, the translational connecting rod is of a U-shaped structure, the guide rail on the base is positioned in the U-shaped structure, and two free ends of the U-shaped structure of the translational connecting rod are respectively provided with a limiting block.
Preferably, the rotating connecting rods are in one group or multiple groups, one group comprises two rotating connecting rods, and the two rotating connecting rods are respectively arranged at two sides of the U-shaped structure of the translation connecting rod;
a second pin shaft is arranged at one end of the rotating connecting rod, and a first pin shaft is arranged at the other end of the rotating connecting rod;
one end of the rotating connecting rod is connected with the base through a second pin shaft, and the other end of the rotating connecting rod is connected with the translation connecting rod through a first pin shaft.
Preferably, the anti-rebound connecting rods are one group or a plurality of groups, one group comprises two anti-rebound connecting rods, and the two anti-rebound connecting rods are respectively arranged at two sides of the U-shaped structure of the translational connecting rod;
a second pin shaft is arranged at one end of the anti-rebound connecting rod, and a first pin shaft is arranged at the other end of the anti-rebound connecting rod;
one end of the anti-rebound connecting rod is connected with the base through a second pin shaft, and the other end of the anti-rebound connecting rod is connected with the translation connecting rod through a first pin shaft.
Preferably, a convex block is arranged on one side of the anti-rebound connecting rod, which is far away from the U-shaped bottom of the translation connecting rod, and an included angle is formed between the convex block and the anti-rebound connecting rod to form an included angle limiting area.
Preferably, the reset structure comprises a reset spring, a spring seat and a support lug, the support lug is arranged on the side surface of the base, the spring seats are arranged on the support lug and the anti-rebound connecting rod, and two ends of the reset spring are respectively connected with the support lug and the spring seat on the anti-rebound connecting rod;
in the locking state, the distance between the support lug and the spring seat on the anti-rebound connecting rod enables the return spring to be in a pre-tensioned state;
the reset spring can drive the translational connecting rod to move along the direction back to the U-shaped bottom of the translational connecting rod in the axial direction of the missile and simultaneously drive the translational connecting rod to move along the direction close to the axis of the missile in the radial direction of the missile, so that the limiting block is driven to move along the direction back to the U-shaped bottom of the translational connecting rod in the axial direction of the missile and simultaneously drive the limiting block to move along the direction close to the axis of the missile in the radial direction of the missile.
Preferably, the support lug is arranged on one side of the anti-rebound connecting rod, which is provided with the lug, and is positioned on a movement path of the anti-rebound connecting rod when the anti-rebound connecting rod is reset from the position of the unlocking state to the position of the locking state, the shape of the support lug is matched with the shape of an included angle limiting area between the lug and the anti-rebound connecting rod, and when the anti-rebound connecting rod is in the position of the locking state, the support lug is positioned in the included angle limiting area between the lug and the anti-rebound connecting rod;
the lug is matched with the lug on the anti-rebound connecting rod, so that the anti-rebound connecting rod can be reset to the position of the locking state, and the movement is stopped.
Preferably, the starting device comprises an explosion bolt and a bolt support, the bolt support is arranged on the base, and the bottom of the translational connecting rod U-shaped structure of the connecting rod structure is connected with the bolt support through the explosion bolt.
Compared with the prior art, the invention has the following beneficial effects:
1. the missile launching device is simple in structure and convenient to operate, can realize the fixation and the unlocking of the missile through the mutual switching between the locking state and the unlocking state, acts on the tail of the missile, solves the problem of insufficient installation space in the middle of the missile launching device, and can effectively adapt to the reverse launching form of the missile.
2. The invention adopts the technical characteristic that the reset spring is used as the reset structure, and can play a role of buffering when the starting device is driven instantly, namely, the missile fixing mechanism cannot switch modes instantly under the action of the pretension force of the reset spring, so that the missile is given a certain buffering time, and the damage probability of the missile is reduced.
3. The invention adopts the technical characteristics that the plurality of anti-rebound connecting rods and the plurality of rotating connecting rods are arranged in parallel and uniformly, so that the stress on two sides of the translation connecting rod is uniform, and the movement of the limiting block is more stable.
Drawings
Other features, objects and advantages of the invention will become more apparent upon reading of the detailed description of non-limiting embodiments with reference to the following drawings:
fig. 1 is a schematic perspective view of the present invention in a locked state with a missile secured thereto.
FIG. 2 is a schematic front view of the missile locking device in a locked state.
FIG. 3 is a side view of the invention in a locked position with a projectile secured thereto.
Fig. 4 is a schematic front view of the invention in an unlocked state and separated from the missile.
The figures show that:
base 1 reset spring 7
Rotating connecting rod 4 threaded pin 10
Guided missile 5 bolt support 11
Detailed Description
The present invention will be described in detail with reference to specific examples. The following examples will assist those skilled in the art in further understanding the invention, but are not intended to limit the invention in any way. It should be noted that it would be obvious to those skilled in the art that various changes and modifications can be made without departing from the spirit of the invention. All falling within the scope of the present invention.
In the description of the present application, it is to be understood that the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience in describing the present application and simplifying the description, but do not indicate or imply that the referred device or element must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the present application.
The invention discloses a missile fixing mechanism, and aims to provide an axial missile fixing mechanism which can make up for the shortage of the middle installation space of a launching device and meet the requirement of reverse launching. The explosion-proof device comprises a base 1, an explosion bolt 2, a translation connecting rod 3, a rotation connecting rod 4, an anti-rebound connecting rod 6, a spring seat 8, a return spring 7, a bolt support 11, a first pin shaft 9, a second pin shaft 12 and a threaded pin 10, wherein support lugs with pin shaft holes are arranged on the base 1 and are respectively positioned on two sides of the base 1; the lower ends of the rotating connecting rod 4 and the anti-rebound connecting rod 6 are respectively arranged on the support lugs of the base 1 through a first pin shaft 9; the upper ends of the rotating connecting rod 4 and the anti-rebounding connecting rod 6 are respectively connected with the translational connecting rod 3 through a second pin shaft 12, the second pin shaft 12 is provided with a through threaded hole along the axial direction, and the translational connecting rod 3 is provided with two limiting blocks; the threaded pins 10 are screwed into threaded holes of the second pin shafts 12 from the outer sides of the rotating connecting rod 4 and the anti-rebound connecting rod 6 respectively, support lugs are further arranged on the base 1 and close to the anti-rebound connecting rod 6, spring seats 8 are arranged on the support lugs and the anti-rebound connecting rod 6 respectively, two ends of a return spring 7 are connected with the support lugs and the spring seats 8 on the anti-rebound connecting rod 6 respectively, and the return spring 7 is in a pre-tensioned state in a locked state. The invention has convenient operation and high locking and releasing reliability.
The missile fixing mechanism provided by the invention comprises a base 1, a connecting rod structure, a resetting structure and a starting device, as shown in figures 1 to 4; the reset structure is respectively connected with the base 1 and the connecting rod structure, the starting device is respectively connected with the base 1 and the connecting rod structure, the base 1 is connected with the connecting rod structure, the connecting rod structure is provided with a limiting block, and the missile 5 is arranged on the base 1; the missile fixing mechanism comprises a locking state and an unlocking state, and as shown in figures 1-3, when the missile fixing mechanism is in the locking state, the limiting block is connected with the end surface of the missile 5; as shown in fig. 4, when the missile fixing mechanism is in an unlocked state, the limiting block is separated from the end surface of the missile 5, and in the radial direction of the missile 5, the limiting block is positioned outside the outer surface of the missile 5; the missile fixing mechanism can be switched from a locking state to an unlocking state under the action of the starting device, and the connecting rod structure can be reset from the position of the unlocking state to the position of the locking state under the action of the resetting structure.
When the missile fixing mechanism is switched from the locking state to the unlocking state, the limiting block gradually releases the axial constraint on the missile 5, and after the axial constraint on the missile 5 is completely released, the missile 5 starts to move reversely, so that the reverse unlocking and launching of the missile 5 are realized.
When the limiting blocks axially fix the guided missiles 5, the guided missiles 5 are always kept in surface-to-surface contact, and the stress concentration phenomenon at the tail parts of the guided missiles 5 is reduced. The mechanism is arranged at the tail part of the missile 5, has enough installation space, is convenient to operate, effectively reduces installation time, and is convenient to implement reverse launching. In order to check the reliability of the ejection mechanism, the ejection mechanism is subjected to actual effect verification, an expected effect is achieved during ejection test, and the ejection mechanism is proved to meet the design requirement.
The base 1 is provided with a guide rail, and the guided missile 5 is arranged on the guide rail and can slide on the guide rail.
The connecting rod structure comprises a translational connecting rod 3, an anti-rebounding connecting rod 6 and a rotating connecting rod 4, the translational connecting rod 3 is arranged in parallel with the base 1, and when the missile fixing mechanism is in a locking state, a set distance exists between the translational connecting rod 3 and the base 1; one end of an anti-rebounding connecting rod 6 is connected with the base 1, the other end of the anti-rebounding connecting rod 6 is connected with the translational connecting rod 3, one end of the rotating connecting rod 4 is connected with the base 1, the other end of the rotating connecting rod 4 is connected with the translational connecting rod 3, and one or more limiting blocks are arranged on the translational connecting rod 3; the anti-rebound connecting rod 6 and the rotating connecting rod 4 are arranged in parallel, and the translation connecting rod 3, the anti-rebound connecting rod 6, the base 1 and the rotating connecting rod 4 form a parallelogram mechanism.
The translational connecting rod 3 is of a U-shaped structure, a guide rail on the base 1 is positioned in the U-shaped structure, and two free ends of the U-shaped structure of the translational connecting rod 3 are respectively provided with a limiting block. Preferably, the two sides of the U-shape of the translational connecting rod 3 are parallel to the guide rail, and the U-shaped bottom of the translational connecting rod 3 is positioned on the motion path of the missile 5 in the locking state.
The rotary connecting rods 4 are one group or multiple groups, one group comprises two rotary connecting rods 4, and the two rotary connecting rods 4 are respectively arranged at two sides of the U-shaped structure of the translation connecting rod 3; a second pin shaft 12 is arranged at one end of the rotating connecting rod 4, and a first pin shaft 9 is arranged at the other end of the rotating connecting rod 4; one end of the rotating connecting rod 4 is connected with the base 1 through a second pin shaft 12, and the other end of the rotating connecting rod 4 is connected with the translational connecting rod 3 through a first pin shaft 9.
The anti-rebound connecting rods 6 are one group or multiple groups, one group comprises two anti-rebound connecting rods 6, and the two anti-rebound connecting rods 6 are respectively arranged at two sides of the U-shaped structure of the translation connecting rod 3; a second pin shaft 12 is arranged at one end of the anti-rebound connecting rod 6, and a first pin shaft 9 is arranged at the other end of the anti-rebound connecting rod 6; one end of the anti-rebound connecting rod 6 is connected with the base 1 through a second pin shaft 12, and the other end of the anti-rebound connecting rod 6 is connected with the translational connecting rod 3 through a first pin shaft 9.
PreferablyThe second pin 12 is internally provided with a threaded hole, and the threaded pins 10 are screwed into the threaded holes of the second pins 12 from the outer sides of the rotating link 4 and the anti-rebounding link 6. As shown in fig. 3, second round pin axle 12 and threaded pin 10 are the notch cuttype, if only adopt second round pin axle 12 (inside no screw hole), at the mechanism motion process, because factors such as vibration can cause second round pin axle 12 to appear the axial float phenomenon, screw in threaded pin 10 in the screw hole in second round pin axle 12 can effectively restrict second round pin axle 12 axial float, promote mechanism operational reliability.
And a convex block is arranged on one side of the anti-rebounding connecting rod 6, which is far away from the U-shaped bottom of the translation connecting rod 3, and an included angle is formed between the convex block and the anti-rebounding connecting rod 6 to form an included angle limiting area.
Preferably, it isWhen the missile fixing mechanism is in a locking state, the anti-rebound connecting rod 6 is vertically arranged with the base 1; one side of the anti-bounce connecting rod 6, which is back to the course of the missile 5, extends in a direction parallel to the base 1 and back to the course of the missile 5 to form a convex block, and an included angle between the convex block and the anti-bounce connecting rod 6 is 90 degrees.
PreferablyThe number of the rotation connecting rods 4 and the number of the anti-rebound connecting rods 6 are two, the translation connecting rod 3, the rotation connecting rod 4, the anti-rebound connecting rod 6 and the base 1 can enclose a parallelogram, the switching from the locking state to the unlocking state can be realized by clockwise rotating the rotation connecting rod 4 and the anti-rebound connecting rod 6 by taking the first pin shaft 9 as the shaft (clockwise direction in the main view shown in fig. 2), and the switching from the unlocking state to the locking state can be realized by anticlockwise rotating the rotation connecting rod 4 and the anti-rebound connecting rod 6 by taking the first pin shaft 9 as the shaft (anticlockwise direction in the main view shown in fig. 2).
The reset structure comprises a reset spring 7, a spring seat 8 and a support lug, the support lug is arranged on the side surface of the base, the spring seats 8 are arranged on the support lug and the anti-rebound connecting rod 6, and two ends of the reset spring 7 are respectively connected with the support lug and the spring seat 8 on the anti-rebound connecting rod 6; in the locking state, the distance between the support lug and the spring seat 8 on the anti-rebound connecting rod 6 enables the return spring 7 to be in a pre-tensioned state; the reset spring 7 can drive the translational connecting rod 3 to move along the direction back to the U-shaped bottom of the translational connecting rod in the axial direction of the missile 5 and simultaneously drive the translational connecting rod 3 to move along the direction close to the axis of the missile 5 in the radial direction of the missile 5, so that the limiting block is driven to move along the direction back to the U-shaped bottom of the translational connecting rod in the axial direction of the missile 5 and simultaneously drive the limiting block to move along the direction close to the axis of the missile 5 in the radial direction of the missile 5.
The support lug is arranged on one side of the anti-rebound connecting rod 6 with the lug and is positioned on a movement path of the anti-rebound connecting rod 6 when the anti-rebound connecting rod is reset from the unlocking state position to the locking state position, the shape of the support lug is matched with the shape of an included angle limiting area between the lug and the anti-rebound connecting rod 6, and when the anti-rebound connecting rod 6 is in the locking state position, the support lug is positioned in the included angle limiting area between the lug and the anti-rebound connecting rod 6; the lug cooperates with the lug on the anti-rebound link 6 to enable the anti-rebound link 6 to return to the position of the locked state, i.e. stop movement.
PreferablyThe support lug is arranged on a motion path of a lug on an anti-rebound connecting rod 6 of the connecting rod structure when the lug is reset from an unlocking state position to a locking state position, and when the anti-rebound connecting rod 6 of the connecting rod structure is reset to be vertical to the base 1, one side of the lug, which is far away from the axis of the missile 5, is connected with the support lug; the shape of the support lug is matched with the shape of a lug on an anti-rebound connecting rod 6 of the connecting rod structure; the support lug is matched with a lug on the anti-rebound connecting rod 6 of the connecting rod structure, so that the anti-rebound connecting rod 6 of the connecting rod structure is perpendicular to the base 1 after the resetting is finished. Preferably, base 1 connects four lugs that have the round pin shaft hole, and four lugs are located the both sides of base 1 respectively, and all are equipped with spring holder 8 on keeping away from two lugs of base 1 right-hand member face.
The starting device comprises an explosion bolt 2 and a bolt support 11, the bolt support 11 is arranged on the base 1, and the bottom of the U-shaped structure of the translational connecting rod 3 of the connecting rod structure is connected with the bolt support 11 through the explosion bolt 2; after the explosive bolt explodes, the bottom of the translational connecting rod 3 loses support, and under the action of the impact force emitted by the guided missile 5, the translational connecting rod 3 moves in the direction far away from the end face of the guided missile 5 in the axial direction of the guided missile 5 and simultaneously drives the translational connecting rod 3 to move in the direction far away from the axis of the guided missile 5 in the radial direction of the guided missile 5, so that the limiting block is driven to move in the direction far away from the axis of the guided missile 5 in the radial direction of the guided missile 5 while driving the limiting block to move in the direction far away from the axis of the guided missile 5 in the axial direction of the guided missile 5, and the normal emission of the guided missile is not influenced.
After the explosive bolt explodes, explosive impact force is generated, under the action of the pretension force of the reset spring 7, the translational connecting rod 3, the anti-rebounding connecting rod 6, the base 1 and the rotating connecting rod 4 form a parallelogram mechanism which cannot rotate instantaneously, so that the missile 5 is given a certain buffering time, and the missile 5 is reset after being launched.
While the basic embodiment of the present application has been described above, the present application will be described in more detail with reference to preferred embodiments and/or variations of the basic embodiment.
In a more specific preferred embodimentAs shown in fig. 1-4, the invention is arranged in a missile launching device and comprises a base 1, an explosion bolt 2, a translational connecting rod 3, a rotating connecting rod 4, an anti-bounce connecting rod 6, a return spring 7, a spring seat 8, a first pin shaft 9, a threaded pin 10, a bolt support 11 and a second pin shaft 12, wherein the base 1 is provided with four lugs with pin shaft holes, the four lugs are respectively positioned at two sides of the base 1, and the two lugs far away from the right end surface of the base are respectively provided with the spring seat 8; the lower ends of the rotating connecting rod 4 and the anti-rebound connecting rod 6 are respectively arranged on the support lugs of the base 1 through a first pin shaft 9; the upper ends of the rotating connecting rod 4 and the anti-rebounding connecting rod 6 are respectively connected with the translational connecting rod 3 through a second pin shaft 12, the second pin shaft 12 is provided with a through threaded hole along the axis direction, the translational connecting rod 3 is provided with two limiting blocks, and the anti-rebounding connecting rod 6 and the rotating connecting rod 4 far away from the right end face of the base are both provided with a spring seat 8; the threaded pins 10 are screwed in the threaded holes of the second pin shafts 12 from the outer sides of the rotating connecting rod 4 and the anti-rebounding connecting rod 6 respectively; the bolt support 11 is screwedThe nail is arranged on the base 1; the middle part and the end part of the explosive bolt 2 are both provided with threads, a middle thread section is arranged on the bolt support 11, and an end thread section passes through a round hole on the end surface of the translational connecting rod 3 and is screwed up through a nut; one side of the return spring 7 is hooked on a spring seat 8 on a support lug of the base 1, and the other side of the return spring is hooked on the spring seat 8 on the connecting rod structure.
As shown in fig. 1-3, arrows in the drawings indicate course, when the guided missile 5 is loaded in place along a guide rail on the base 1 in the forward direction by using a slide block of the guided missile 5, the rotating connecting rod 4 and the anti-rebounding connecting rod 6 are respectively installed with the translational connecting rod 3 and the base 1 into a whole to form a parallelogram mechanism, the parallelogram mechanism is anticlockwise rotated until the left side surfaces of two limiting blocks on the translational connecting rod 3 are attached to the right end surface of the guided missile 5, and then the explosion bolt 2 and the translational connecting rod 3 are connected into a whole through a nut; the return springs 7 are respectively hooked in the grooves of the spring seats 8, and the return springs 7 have certain tension in the state, so that the missile 5 is limited axially.
As shown in fig. 4, an arrow in the figure indicates a course, after the missile 5 sends out a launching instruction, the explosive bolt 2 is detonated to generate an explosive impact force, the parallelogram mechanism cannot rotate instantaneously under the pretension action of the return spring 7, the missile 5 is given a certain buffer time, then the parallelogram mechanism rotates clockwise under the impact force to cause the translational connecting rod 3 to move rightwards and downwards, and after the axial constraint on the missile 5 is completely relieved, the missile 5 starts to move reversely, so that the missile 5 unlocks reversely to launch.
When the missile fixing mechanism (namely the missile fixing mechanism) axially fixes the missile, the translational connecting rod 3 is always in surface-to-surface contact with the missile 5, and the stress concentration phenomenon at the tail of the missile due to the action of the missile fixing mechanism is reduced. The missile fixing mechanism is arranged at the tail part of the missile 5, has enough installation space, is convenient to operate, effectively reduces installation time, and facilitates implementation of reverse launching.
The foregoing description of specific embodiments of the present invention has been presented. It is to be understood that the present invention is not limited to the specific embodiments described above, and that various changes or modifications may be made by one skilled in the art within the scope of the appended claims without departing from the spirit of the invention. The embodiments and features of the embodiments of the present application may be combined with each other arbitrarily without conflict.
Claims (7)
1. A missile fixing mechanism is characterized by comprising a base (1), a connecting rod structure, a resetting structure and a starting device;
the missile launcher comprises a base (1), a connecting rod structure, a resetting structure, a starting device and a missile launcher, wherein the resetting structure is respectively connected with the base (1) and the connecting rod structure, the base (1) is connected with the connecting rod structure, a limiting block is arranged on the connecting rod structure, and a missile (5) is arranged on the base (1);
the missile fixing mechanism comprises a locking state and an unlocking state, and when the missile fixing mechanism is in the locking state, the limiting block is connected with the end surface of the missile (5); when the missile fixing mechanism is in an unlocking state, the limiting block is separated from the end face of the missile (5), and in the radial direction of the missile (5), the limiting block is positioned outside the outer surface of the missile (5);
the missile fixing mechanism can be switched from a locking state to an unlocking state under the action of the starting device, and the connecting rod structure can be reset from the position of the unlocking state to the position of the locking state under the action of the resetting structure;
the connecting rod structure comprises a translational connecting rod (3), an anti-rebounding connecting rod (6) and a rotating connecting rod (4), the translational connecting rod (3) and the base (1) are arranged in parallel, and when the missile fixing mechanism is in a locked state, a set distance exists between the translational connecting rod (3) and the base (1);
one end of an anti-rebounding connecting rod (6) is connected with the base (1), the other end of the anti-rebounding connecting rod (6) is connected with the translation connecting rod (3), one end of the rotating connecting rod (4) is connected with the base (1), the other end of the rotating connecting rod (4) is connected with the translation connecting rod (3), and one or more limiting blocks are arranged on the translation connecting rod (3);
the anti-rebounding connecting rod (6) and the rotating connecting rod (4) are arranged in parallel, and the translation connecting rod (3), the anti-rebounding connecting rod (6), the base (1) and the rotating connecting rod (4) form a parallelogram mechanism;
the reset structure comprises a reset spring (7), a spring seat (8) and a support lug, the support lug is arranged on the side surface of the base, the spring seats (8) are arranged on the support lug and the anti-rebound connecting rod (6), and two ends of the reset spring (7) are respectively connected with the support lug and the spring seat (8) on the anti-rebound connecting rod (6);
when in a locking state, the distance between the support lug and the spring seat (8) on the anti-rebound connecting rod (6) enables the return spring (7) to be in a pre-stretched state;
the reset spring (7) can drive the translational connecting rod (3) to move along the direction back to the U-shaped bottom of the translational connecting rod in the axial direction of the missile (5) and simultaneously drive the translational connecting rod (3) to move along the direction close to the axle center of the missile (5) in the radial direction of the missile (5), so that the limiting block is driven to move along the direction back to the U-shaped bottom of the translational connecting rod in the axial direction of the missile (5) and simultaneously driven to move along the direction close to the axle center of the missile (5) in the radial direction of the missile (5);
the support lug is arranged on one side of the anti-rebound connecting rod (6) with the convex block and is positioned on a movement path when the anti-rebound connecting rod (6) is reset from the position of the unlocking state to the position of the locking state, the shape of the support lug is matched with the shape of an included angle limiting area between the convex block and the anti-rebound connecting rod (6), and when the anti-rebound connecting rod (6) is positioned at the position of the locking state, the support lug is positioned in the included angle limiting area between the convex block and the anti-rebound connecting rod (6);
the lug is matched with a lug on the anti-rebound connecting rod (6) to enable the anti-rebound connecting rod (6) to reset to the position of the locking state, namely stop moving.
2. Missile fixing mechanism according to claim 1, characterized in that the base (1) is provided with rails on which the missile (5) is mounted and can slide.
3. Missile fixing mechanism according to claim 1, characterized in that the translatory connecting rod (3) is a U-shaped structure, the guide rail on the base (1) is located inside the U-shaped structure, and two free ends of the U-shaped structure of the translatory connecting rod (3) are provided with a limiting block respectively.
4. Missile fixing mechanism according to claim 3, characterized in that the rotation links (4) are in one or more groups, one group comprising two rotation links (4), the two rotation links (4) being arranged on either side of the U-shaped structure of the translatory link (3) respectively;
a second pin shaft (12) is arranged at one end of the rotating connecting rod (4), and a first pin shaft (9) is arranged at the other end of the rotating connecting rod (4);
one end of the rotating connecting rod (4) is connected with the base (1) through a second pin shaft (12), and the other end of the rotating connecting rod (4) is connected with the translational connecting rod (3) through a first pin shaft (9).
5. Missile fixing mechanism according to claim 3, characterized in that the anti-bounce links (6) are in one or more groups, one group comprising two anti-bounce links (6), the two anti-bounce links (6) being arranged on each side of the U-shaped structure of the translatory link (3);
a second pin shaft (12) is arranged at one end of the anti-rebound connecting rod (6), and a first pin shaft (9) is arranged at the other end of the anti-rebound connecting rod (6);
one end of the anti-rebounding connecting rod (6) is connected with the base (1) through a second pin shaft (12), and the other end of the anti-rebounding connecting rod (6) is connected with the translational connecting rod (3) through a first pin shaft (9).
6. Missile fixing mechanism according to claim 3, characterized in that the anti-bounce link (6) is provided with a lug on the side remote from the U-shaped bottom of the translatory link (3), the lug and the anti-bounce link (6) having an angle therebetween forming an angle-defining zone.
7. Missile fixing mechanism according to claim 3, characterized in that the activation means comprise an explosive bolt (2), a bolt support (11), the bolt support (11) being arranged on the base (1), the U-shaped structural bottom of the translatory link (3) of the link arrangement being connected to the bolt support (11) by means of the explosive bolt (2).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010290662.2A CN111426242B (en) | 2020-04-14 | 2020-04-14 | Guided missile fixing mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010290662.2A CN111426242B (en) | 2020-04-14 | 2020-04-14 | Guided missile fixing mechanism |
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| Publication Number | Publication Date |
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| CN111426242A CN111426242A (en) | 2020-07-17 |
| CN111426242B true CN111426242B (en) | 2022-07-01 |
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| CN202010290662.2A Active CN111426242B (en) | 2020-04-14 | 2020-04-14 | Guided missile fixing mechanism |
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Families Citing this family (6)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN114313270B (en) * | 2020-09-29 | 2023-11-03 | 海鹰航空通用装备有限责任公司 | Built-in missile cabin mechanism containing soft oil tank and invisible aircraft with built-in missile cabin mechanism |
| CN113091530B (en) * | 2021-03-03 | 2023-03-14 | 上海机电工程研究所 | Floating device suitable for infrared missile air feed mechanism |
| CN113237395B (en) * | 2021-04-26 | 2022-11-08 | 上海机电工程研究所 | Bullet fixing device based on lever mechanism |
| CN113357962B (en) * | 2021-05-19 | 2023-01-20 | 上海机电工程研究所 | Auxiliary supporting device for restraining radial runout of guided missile |
| CN113998135B (en) * | 2021-10-18 | 2023-11-28 | 上海机电工程研究所 | Axial locking and releasing assembly for fracture-resistant unmanned aerial vehicle |
| CN114719675B (en) * | 2022-03-09 | 2023-07-07 | 上海机电工程研究所 | Synchronous unlocking mechanism of plug mechanism and bullet fixing device |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN101017074B (en) * | 2007-02-07 | 2010-11-17 | 东华大学 | Automatically agilely leveling system for missile launching platform |
| CN104457419B (en) * | 2014-10-27 | 2016-09-21 | 北京航天长征飞行器研究所 | A kind of rocket bomb transmitting case auxiliary support mechanism |
| CN105953646B (en) * | 2016-04-29 | 2017-10-03 | 上海机电工程研究所 | A kind of firing box plug push-pull structure anti-rebounding device |
| CN106225570B (en) * | 2016-08-18 | 2017-11-24 | 上海机电工程研究所 | A kind of connector adaptively plugs together device |
| CN107482375B (en) * | 2017-07-03 | 2019-08-09 | 上海机电工程研究所 | The anti-resetting apparatus of emitter hot-line insertion and extraction mechanism |
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