CN112683114A - Vibration reduction self-locking device of missile wing unfolding mechanism - Google Patents
Vibration reduction self-locking device of missile wing unfolding mechanism Download PDFInfo
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- CN112683114A CN112683114A CN202011539229.4A CN202011539229A CN112683114A CN 112683114 A CN112683114 A CN 112683114A CN 202011539229 A CN202011539229 A CN 202011539229A CN 112683114 A CN112683114 A CN 112683114A
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- mounting seat
- lower mounting
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- vibration reduction
- locking
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Abstract
The invention discloses a vibration reduction self-locking device of a missile wing unfolding mechanism, which is a novel modularized vibration reduction self-locking device and comprises an upper mounting seat, a lower mounting seat, an elastic fixing part and a sliding locking block, the upper mounting seat, the lower mounting seat and the sliding locking block are matched with each other through the design, realizes self-locking in the flying process, has the characteristics of simple structure, convenient installation, adjustable rigidity, high stability and good reliability, meanwhile, the shock absorber has the functions of reducing the impact of the whole structure and immediately self-locking after vibration reduction and buffering, effectively avoids the failure of the missile-borne equipment caused by the impact of the actuating cylinder, the structure can meet the requirement that the aeroelastic cannot shake back and forth in the working process, the stability of the aeroelastic in the sliding process is guaranteed, the rigidity can be flexibly adjusted according to vibration impact of multiple levels through a special structural form, and structural members with different sizes can be customized according to different aeroelastic weight grades.
Description
Technical Field
The invention belongs to the technical field of space, and particularly relates to a vibration reduction self-locking device of a missile wing unfolding mechanism.
Background
The missile wing unfolding mechanism can stretch or fold the missile wing, so that the size of the missile body and the size of the launching platform can be reduced, the designed size parameters of the missile wing can be enlarged, and the trajectory correction efficiency can be improved. At present, some common unfolding mechanisms are directly arranged on a projectile body, when the unfolding mechanisms are unfolded, all reaction force caused by impact of a ram on a projectile wing is applied to the projectile body, strong instantaneous impact can be brought to the projectile body, and the impact can damage some missile-borne equipment with weak vibration resistance. At present, relevant devices capable of achieving the vibration reduction function of the missile wing unfolding mechanism are not reported.
Disclosure of Invention
The invention aims to overcome the defects and provides a vibration reduction self-locking device of a missile wing unfolding mechanism.
In order to achieve the above purpose, the invention provides the following technical scheme:
a vibration reduction self-locking device of a missile wing unfolding mechanism comprises an upper mounting seat, a lower mounting seat, an elastic fixing part and a sliding locking block;
the upper mounting seat is of a plate-shaped structure, the front end of the upper mounting seat is provided with a groove, the inner surface of the groove is composed of an inclined plane and a vertical plane, and the upper mounting plate is used for mounting the missile wing unfolding mechanism;
the lower mounting seat is of a plate-shaped structure, and the front end of the lower mounting seat is provided with a boss with a hollow interior; the upper surface of the boss is parallel to the upper surface of the lower mounting seat, and the height of the boss is greater than the height of the groove of the upper mounting plate; the upper surface of the boss is provided with an opening along the flight direction, the sliding locking block comprises a sliding part and a locking part, the sliding part is clamped in the opening, so that the sliding locking block can slide along the flight direction, the locking part is arranged between the upper mounting seat groove and the lower mounting seat boss, and the upper mounting seat and the lower mounting seat are kept relatively static by using pressure and friction in the flight process, so that self-locking is realized;
the upper mounting seat and the lower mounting seat are fixed through elastic fixing parts on two sides, and the elastic fixing parts are used for slowing down the relative movement of the upper mounting seat and the lower mounting seat simultaneously, so that shock absorption is realized.
Furthermore, the locking part of the sliding locking block is a wedge block, and the sliding part comprises supporting legs, a fixing block and screws; the cross section of the wedge block is a right-angled triangle, a right-angled surface A is matched with a vertical surface in a groove at the front end of the upper mounting seat, a right-angled surface B is matched with the inner surface of a boss of the lower mounting seat, and an inclined surface C is matched with an inclined surface in a groove at the front end of the upper mounting seat; the supporting legs are arranged on the right-angle surface B and are fixed through fixing blocks and screws after extending out of the openings of the lower mounting seats.
Furthermore, the elastic fixing part is a rubber spring which is divided into two parts, each part comprises an outer frame and an inner rubber column, and the two parts of the rubber columns are connected through a connecting rod; each part can move around the rubber column of the other part through the connecting rod; the two parts are respectively and fixedly connected with the upper mounting seat and the lower mounting seat.
Further, when the aircraft is in a non-flight state, a gap is formed between the right-angle surface B and the inner surface of the boss at the front end of the lower mounting seat, and the gap is 0.5-1 mm.
Furthermore, the sliding locking block is made of rubber.
Furthermore, the number of the grooves of the mounting seat is more than or equal to 1; the number of the bosses of the lower mounting base is more than or equal to 1; the number of the mounting seat grooves is equal to that of the lower mounting seat bosses, and the mounting seat grooves correspond to the lower mounting seat bosses in position.
Furthermore, the number of the openings of the lug bosses of the lower mounting seat is more than or equal to 1 and is equal to the number of the supporting legs of the sliding locking block.
Furthermore, the rubber springs are not less than 2 and are installed in pairs, and the damping effect strength is adjusted by controlling the number of the rubber springs.
Furthermore, the upper mounting seat is made of metal.
Furthermore, the inclined plane in the groove of the upper mounting seat is provided with texture for increasing friction force.
Compared with the prior art, the invention has the following beneficial effects:
(1) the invention relates to a vibration reduction self-locking device of a missile wing unfolding mechanism, which is matched with an upper mounting seat and a lower mounting seat by designing the structures of a sliding part and a locking part of a sliding locking block, and ensures the relative rest of the upper mounting seat and the lower mounting seat by utilizing the pressure and friction force generated in the flight process to realize self-locking. The passive vibration reduction is adopted, so that the vibration reduction self-locking mechanism can realize effective slow release of instantaneous impact, the vibration reduction self-locking mechanism can keep stable immediately, and a series of problems that the instantaneous impact load of the unfolding mechanism is too large and the missile-borne equipment is damaged are effectively solved.
(2) According to the invention, the elastic fixing part is adopted to connect the upper mounting seat and the lower mounting seat, so that instantaneous impact is effectively and slowly released through elastic connection, and the number of the rubber spring groups can be adjusted according to the models of different unfolding mechanisms and the impact load of the actuating cylinder, therefore, the invention has the advantages of high reliability, adjustable rigidity and stable operation.
(3) The invention can adapt to the requirements of aeronautical bullets of any shape and size by changing the structures of the upper and lower mounting seats, and the mechanism has small occupied volume, small influence on other missile-borne equipment and high universality.
(4) The sliding locking block is detachable, simple and convenient in use method and reusable.
(5) The invention has no special requirements on materials and processing modes and has high adaptability.
(6) The position locking device has high reliability and can meet different requirements of military use, civil use and the like.
Drawings
FIG. 1 is a schematic structural view of a vibration-reducing self-locking device of a missile wing deployment mechanism according to the invention;
FIG. 2 is a schematic view of the sliding locking block of the present invention;
FIG. 3 is a schematic view of the rubber spring structure of the present invention;
FIG. 4 is a schematic diagram of the structure of the present invention;
FIG. 5 is a schematic view of the upper mounting base structure of the present invention;
FIG. 6 is a cross-sectional view of an upper mount of the present invention;
fig. 7 is a schematic view of the structure of the lower mounting seat of the present invention.
Detailed Description
The features and advantages of the present invention will become more apparent and appreciated from the following detailed description of the invention.
The word "exemplary" is used exclusively herein to mean "serving as an example, embodiment, or illustration. Any embodiment described herein as "exemplary" is not necessarily to be construed as preferred or advantageous over other embodiments. While the various aspects of the embodiments are presented in drawings, the drawings are not necessarily drawn to scale unless specifically indicated.
The invention relates to a vibration reduction self-locking device of a missile wing unfolding mechanism, which comprises an upper mounting seat 1, a lower mounting seat 2, an elastic fixing part 3 and a sliding locking block 4; as shown in fig. 1.
The upper mounting base 1 is of a plate-shaped structure, the front end of the upper mounting base is provided with a groove, the inner surface of the groove is formed by an inclined plane and a vertical plane, the upper mounting base 1 is used for mounting the missile wing unfolding mechanism, and the lower bottom plate of the unfolding mechanism is fixed on the upper mounting base 1 through screws; as shown in FIGS. 5 to 6.
The lower mounting seat 2 is of a plate-shaped structure, a boss with a hollow interior is arranged at the front end of the lower mounting seat, the upper surface of the boss is parallel to the upper surface of the lower mounting seat, and the height of the boss is greater than the height of the groove of the upper mounting plate 1; as shown in fig. 7.
Furthermore, the inner cavity of the boss is cubic, and the boss comprises two side surfaces perpendicular to the upper surface of the lower mounting seat 2 and an upper surface parallel to the upper surface of the lower mounting seat;
because the appearance of the aerobomb, the installation mode between the range-extending assembly and the bomb body are different, the upper installation seat 1 and the lower installation seat 2 with different sizes can be customized according to different aerobomb weight grades and structure forms, and the number and the positions of screw holes are increased or reduced.
The opening along flight direction is seted up to the boss upper surface, and slip locking piece 4 includes sliding part and locking part, and the sliding part card is in the opening, makes slip locking piece 4 can slide along flight direction, and locking part is arranged in with 1 recess of last mount pad and down between the 2 bosss of mount pad, and locking part is in 1 recess of mount pad and in the 2 boss inner cavities of mount pad down simultaneously promptly. In the flying process, the upper mounting seat 1 and the lower mounting seat 2 are kept relatively static by using pressure and friction force, so that self-locking is realized; go up mount pad 1 and move a section distance forward under the effect of deployment mechanism inertial force to promote the sliding locking piece 4 and move forward, in certain extent, the slider can both effectively realize stepless auto-lock under the condition of arbitrary sliding distance, realizes the auto-lock back, under the effect of missile wing lift and body dead weight, whole self-locking mechanism that shakes of falling can not take place to rock.
Go up mount pad 1 and mount pad 2 down and fix through the elastic fixation part of both sides, the elastic fixation part is used for slowing down the relative motion of last mount pad 1 and mount pad 2 down simultaneously, realizes the shock attenuation.
Further, as shown in fig. 2, the locking part of the sliding locking block 4 is a wedge 7, and the sliding part comprises a leg 11, a fixing block 5 and a screw 6; the cross section of the wedge block 7 is a right triangle, a right-angle surface A is matched with a vertical surface in a groove at the front end of the upper mounting seat 1, a right-angle surface B is matched with the inner surface of a boss at the front end of the lower mounting seat 2, and an inclined surface C is matched with an inclined surface in a groove at the front end of the upper mounting seat 1; as shown in fig. 4. The supporting legs 11 are arranged on the right-angle surface B and extend out of the openings of the lower mounting seat 2 to be fixed through the fixing blocks 5 and the screws 6. The sliding locking block 4 is detachable and can be used repeatedly in experiments.
Further, the elastic fixing component is a rubber spring 3, as shown in fig. 3, the rubber spring 3 is divided into two parts, each part comprises an outer frame 8 and an inner rubber column 10, and the two rubber columns 10 are connected through a connecting rod 9; each part can move around the rubber column 10 of the other part relatively through the connecting rod 9; the two parts are respectively fixedly connected with the upper mounting seat 1 and the lower mounting seat 2, the upper part is fixed on the left side and the right side of the upper mounting seat 1 through screws, the lower part is fixed on the left side and the right side of the lower mounting seat 2 through screws, and the lower mounting seat 2 is fixed on the projectile body through screws. The connecting rod 9 can play a guiding role, and when the expansion mechanism impacts, the upper mounting seat 1 is guided to move around the rubber column on the lower part of the rubber spring 3 and then is in sliding fit with the sliding locking block 4 to realize locking.
Further, when the aircraft is in a non-flight state, a gap is formed between the right-angle surface B and the inner surface of the boss at the front end of the lower mounting seat 2, and the gap is 0.5-1 mm.
Further, the sliding locking block 4 is made of rubber.
Furthermore, the number of grooves of the mounting seat 1 is more than or equal to 1; the number of the bosses of the lower mounting seat 2 is more than or equal to 1; the number of the grooves of the mounting seat 1 is equal to that of the bosses of the lower mounting seat 2, and the positions of the grooves correspond to those of the bosses of the lower mounting seat.
Furthermore, the number of the openings of the bosses of the lower mounting seat 2 is more than or equal to 1 and is equal to the number of the support legs 11 of the sliding locking block 4.
Further, the rubber springs 3 are more than or equal to 2 and are installed in pairs, the damping effect strength is adjusted by controlling the number of the rubber springs 3, namely, the number of pairs of the rubber springs can be flexibly adjusted according to different impact loads and the mass of the unfolding mechanism (including the missile wing), and the proper rigidity and damping are adjusted by controlling the number of the rubber springs 3.
Further, the material used for the upper mounting seat 1 is metal.
Furthermore, the inclined plane in the groove of the upper mounting seat 1 is provided with uneven textures for increasing the friction force between the upper mounting seat and the sliding locking block 4.
The specific vibration reduction process is as follows: the lower mounting seat 2 is fixed on the projectile body, and the upper mounting seat 1 is provided with an unfolding mechanism. When the initiating explosive device is in operation, the projectile body flies forward, after the deceleration, the upper mounting base 1 moves forward relative to the lower mounting base 2 under the action of inertia force, the sliding locking block 4 is pushed to move forward, after a short time, the elastic wings are unfolded by the unfolding mechanism, the upper mounting base 1 moves backwards and obliquely upwards under the action of the lifting force of the elastic wings, the sliding locking block 4 is extruded, the sliding locking block 4 is made of rubber, the friction force of the inclined plane of the groove of the lower mounting base 2 and the pressure of the inner surface of the boss of the upper mounting base 1 and the vertical plane of the groove of the lower mounting base 2 are kept immovable, and the whole device forms self-locking. After self-locking, the unfolding mechanism fixed on the upper mounting seat 1 cannot shake in the aeroelastic flying state. The stability of the aeroelastic flight is ensured.
The projectile body flies forwards, after the projectile body decelerates, the upper mounting base 1 moves forwards for a certain distance under the action of the inertia force of the unfolding mechanism and pushes the sliding locking block 4 to move forwards, after a short time, the unfolding mechanism enables the projectile wings to unfold, the upper mounting base 1 moves backwards and upwards obliquely under the action of the lifting force of the projectile wings, due to the existence of the rubber spring 3, the upper mounting base 1 undergoes the motion process of forward acceleration, forward deceleration, backward acceleration and backward deceleration, and in the range of the operation area, the mechanism can realize effective self-locking under the condition that the sliding locking block 4 slides for any distance. Therefore, the mechanism can realize stepless self-locking in the working range of the mechanism.
Example 1
The front end of the upper mounting seat 1 is provided with two triangular grooves, and the positions of the grooves correspond to the positions of the sliding locking blocks 4 during mounting, so that wedge blocks can be placed in the grooves and cannot be squeezed between the upper mounting seat and the lower mounting seat; the front end of the lower mounting seat 2 is provided with two bosses, each boss is provided with two mounting openings for clamping the sliding locking block 4, and two supporting legs 11 of the sliding locking block 4 penetrate through gaps on the bosses of the lower mounting seat 2 and are fixed above the bosses through fixing blocks 5 and screws 6.
The invention has been described in detail with reference to specific embodiments and illustrative examples, but the description is not intended to be construed in a limiting sense. Those skilled in the art will appreciate that various equivalent substitutions, modifications or improvements may be made to the technical solution of the present invention and its embodiments without departing from the spirit and scope of the present invention, which fall within the scope of the present invention. The scope of the invention is defined by the appended claims.
Those skilled in the art will appreciate that those matters not described in detail in the present specification are well known in the art.
Claims (10)
1. A vibration reduction self-locking device of a missile wing unfolding mechanism is characterized by comprising an upper mounting seat (1), a lower mounting seat (2), an elastic fixing part (3) and a sliding locking block (4);
the upper mounting seat (1) is of a plate-shaped structure, the front end of the upper mounting seat is provided with a groove, the inner surface of the groove is composed of an inclined plane and a vertical plane, and the upper mounting plate (1) is used for mounting the missile wing unfolding mechanism;
the lower mounting seat (2) is of a plate-shaped structure, and the front end of the lower mounting seat is provided with a boss with a hollow interior; the upper surface of the boss is parallel to the upper surface of the lower mounting seat (2), and the height of the boss is greater than the height of the groove of the upper mounting plate (1); an opening along the flight direction is formed in the upper surface of the boss, the sliding locking block (4) comprises a sliding part and a locking part, the sliding part is clamped in the opening, so that the sliding locking block (4) can slide along the flight direction, the locking part is arranged between the groove of the upper mounting seat (1) and the boss of the lower mounting seat (2), and the upper mounting seat (1) and the lower mounting seat (2) are kept relatively static by pressure and friction in the flight process, so that self-locking is realized;
go up mount pad (1) and mount pad (2) down and fix through the elastic fixation part of both sides, elastic fixation part is used for slowing down the relative motion of last mount pad (1) and mount pad (2) down simultaneously, realizes the shock attenuation.
2. The vibration reduction and self-locking device of the missile wing deployment mechanism is characterized in that the locking part of the sliding locking block (4) is a wedge block (7), and the sliding part comprises a supporting leg (11), a fixed block (5) and a screw (6); the cross section of the wedge block (7) is a right-angled triangle, a right-angled surface A is matched with a vertical surface in a groove at the front end of the upper mounting seat (1), a right-angled surface B is matched with the inner surface of a boss of the lower mounting seat (2), and an inclined surface C is matched with an inclined surface in a groove at the front end of the upper mounting seat (1); the supporting legs (11) are arranged on a right-angle surface B and are fixed through fixing blocks (5) and screws (6) after extending out of the openings of the lower mounting seat (2).
3. The vibration reduction and self-locking device of the missile wing deployment mechanism is characterized in that the elastic fixing part is a rubber spring (3), the rubber spring (3) is divided into two parts, each part comprises an outer frame (8) and an inner rubber column (10), and the two parts of the rubber columns (10) are connected through a connecting rod (9); each part can move around the rubber column (10) of the other part relatively through the connecting rod (9); the two parts are respectively and fixedly connected with the upper mounting seat (1) and the lower mounting seat (2).
4. The vibration reduction and self-locking device of the missile wing deployment mechanism is characterized in that a gap is formed between the right-angle surface B and the inner surface of the boss at the front end of the lower mounting seat (2) in a non-flying state, and the gap is 0.5-1 mm.
5. The vibration reduction and self-locking device of the missile wing deployment mechanism is characterized in that the sliding locking block (4) is made of rubber.
6. The vibration reduction self-locking device of the missile wing deployment mechanism according to claim 1, wherein the number of the grooves of the mounting seat (1) is more than or equal to 1; the number of the bosses of the lower mounting seat (2) is more than or equal to 1; the number of the grooves of the mounting seat (1) is equal to that of the bosses of the lower mounting seat (2), and the grooves correspond to the bosses of the lower mounting seat in position.
7. The vibration reduction self-locking device of the missile wing spreading mechanism is characterized in that the number of openings of bosses of the lower mounting seat (2) is more than or equal to 1 and is equal to the number of supporting legs (11) of the sliding locking block (4).
8. The vibration reduction self-locking device of the missile wing deployment mechanism is characterized in that the rubber springs (3) are more than or equal to 2 and are installed in pairs, and the damping effect strength is adjusted by controlling the number of the rubber springs (3).
9. The vibration reduction and self-locking device of the missile wing deployment mechanism is characterized in that the upper mounting seat (1) is made of metal.
10. The vibration reduction and self-locking device of a missile wing deployment mechanism according to claim 9, wherein the inclined surface in the groove of the upper mounting seat (1) is provided with texture for increasing friction.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011539229.4A CN112683114B (en) | 2020-12-23 | 2020-12-23 | Vibration reduction self-locking device of missile wing unfolding mechanism |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011539229.4A CN112683114B (en) | 2020-12-23 | 2020-12-23 | Vibration reduction self-locking device of missile wing unfolding mechanism |
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| CN112683114A true CN112683114A (en) | 2021-04-20 |
| CN112683114B CN112683114B (en) | 2022-11-11 |
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| US6880780B1 (en) * | 2003-03-17 | 2005-04-19 | General Dynamics Ordnance And Tactical Systems, Inc. | Cover ejection and fin deployment system for a gun-launched projectile |
| US20100294879A1 (en) * | 2009-05-19 | 2010-11-25 | Agency For Defense Development | Wing assembly and apparatus for launching flying object using the same |
| CN106323101A (en) * | 2016-09-08 | 2017-01-11 | 北京精密机电控制设备研究所 | Missile-borne rudder wing spreading locking mechanism based on pin pusher actuation |
| US20180112959A1 (en) * | 2016-10-26 | 2018-04-26 | Simmonds Precision Products, Inc. | Wing deployment and lock mechanism |
| CN209470593U (en) * | 2018-11-23 | 2019-10-08 | 江西洪都航空工业集团有限责任公司 | Folded surface buffer unit in place |
| CN111059965A (en) * | 2019-12-27 | 2020-04-24 | 中国航天科工集团八五一一研究所 | Small-diameter missile wing piece unfolding mechanism with limiting and self-locking functions |
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2020
- 2020-12-23 CN CN202011539229.4A patent/CN112683114B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6880780B1 (en) * | 2003-03-17 | 2005-04-19 | General Dynamics Ordnance And Tactical Systems, Inc. | Cover ejection and fin deployment system for a gun-launched projectile |
| US20100294879A1 (en) * | 2009-05-19 | 2010-11-25 | Agency For Defense Development | Wing assembly and apparatus for launching flying object using the same |
| CN106323101A (en) * | 2016-09-08 | 2017-01-11 | 北京精密机电控制设备研究所 | Missile-borne rudder wing spreading locking mechanism based on pin pusher actuation |
| US20180112959A1 (en) * | 2016-10-26 | 2018-04-26 | Simmonds Precision Products, Inc. | Wing deployment and lock mechanism |
| CN209470593U (en) * | 2018-11-23 | 2019-10-08 | 江西洪都航空工业集团有限责任公司 | Folded surface buffer unit in place |
| CN111059965A (en) * | 2019-12-27 | 2020-04-24 | 中国航天科工集团八五一一研究所 | Small-diameter missile wing piece unfolding mechanism with limiting and self-locking functions |
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| CN112683114B (en) | 2022-11-11 |
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