CN113357973B - Controllable movable rudder wing lift angle device for PGK seeker - Google Patents
Controllable movable rudder wing lift angle device for PGK seeker Download PDFInfo
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- CN113357973B CN113357973B CN202110739438.1A CN202110739438A CN113357973B CN 113357973 B CN113357973 B CN 113357973B CN 202110739438 A CN202110739438 A CN 202110739438A CN 113357973 B CN113357973 B CN 113357973B
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- rudder wing
- outer ring
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- rudder
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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
- F42B10/26—Stabilising arrangements using spin
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Abstract
The invention relates to a controllable movable rudder wing lift angle device for a PGK seeker. The invention mainly solves the technical problem that the projectile body deviates from the trajectory in the conventional PGK. The technical scheme adopted by the invention is as follows: a controllable active rudder wing lift angle device for a PGK seeker, comprising an active wing and a rudder wing cylinder, wherein: the rudder wing device is characterized by further comprising a motor fixing plate, a stepping motor, an outer ring pressing block, a nut, a follower bearing, a lead screw, a set screw, a rudder wing shaft sleeve and a rudder wing main shaft, wherein the motor fixing plate is connected with a motor frame arranged in the rudder wing barrel and is positioned at the rear part in the rudder wing barrel, the stepping motor is fixed on the motor fixing plate through the screw, the lead screw is fixed on a rotating shaft of the stepping motor through the set screw, the nut is arranged on the lead screw, and the follower bearing is arranged in the outer ring and the outer ring of the follower bearing is connected with the outer ring through the screw. The invention has the advantages of simple mechanism, convenient assembly, low cost, easy guarantee of precision and the like.
Description
Technical Field
The invention belongs to the technical field of two-dimensional trajectory correction devices, and particularly relates to a controllable movable rudder wing lift angle device for a PGK seeker.
Background
The PGK (Precision Guidance Kit) Precision Guidance component is a ballistic correction module integrating a fuse, a ballistic detection device, an air control surface and a control circuit into a whole. The size, the installation method and the weight of the fuse are different from those of the traditional fuse, and the fuse can be directly reloaded to the fuse position of the traditional standard ammunition, so that the shooting precision of the uncontrolled ammunition can be greatly improved. At present, PGK becomes a hot spot of dispute research of military and major countries in the world, and China also develops the research and development work of various types of two-dimensional trajectory correction bullets adopting a PGK form.
The projectile adopting PGK to realize two-dimensional trajectory correction is also called double-spin projectile. The projectile rotates positively, the rotary wing cylinder rotates reversely relative to the projectile, and a bearing is arranged between the rotary wing cylinder and the projectile for isolation. When the rotating speed of the rotary wing cylinder is consistent with the rotating speed of the projectile in the positive rotation direction, the fixed wing air control surface can keep static in an inertial space, so that stable normal force is generated, and trajectory correction is realized. But it has disadvantages in practical applications. The disadvantages are that: when the PGK is applied to a low spin projectile, the PGK itself is driven by the motor and the gear train decelerates, causing the rotor barrel to spin backwards. However, the chamber is shot out after the uncontrolled missile and the PGK seeker are arranged, and because the lift angle of the air control surface is certain (4 degrees or 5 degrees) at the initial speed and the lift is constant, the projectile body can be driven to deviate from the trajectory for a period of time and distance, and the precision of the PGK is reduced.
Disclosure of Invention
The invention aims to solve the technical problem that a projectile body deviates from a trajectory in the conventional PGK and provides a controllable movable rudder wing lift angle device for a PGK seeker.
In order to solve the technical problems, the technical scheme adopted by the invention is as follows:
a controllable active rudder wing lift angle device for a PGK seeker, comprising an active wing and a rudder wing cylinder, wherein: the rudder wing main shaft is arranged in the rudder wing shaft sleeve, the rudder wing shaft sleeve is arranged in the rudder wing main shaft through a fixed screw, the movable wing piece is arranged on the rudder wing main shaft through the rudder wing main shaft and can rotate, and a guide lug boss is arranged on one side of the movable wing piece and connected with the outer ring through a guide chute.
Furthermore, 4 guide bosses are uniformly arranged on the outer ring, and inclined grooves are formed in the guide bosses.
Further, the angle of rotation of the movable wing is ± 10 °.
The invention has the beneficial effects that: the rear part in the rudder wing cylinder is additionally provided with the rudder wing adjusting mechanism, the original fixed wing is changed into the movable wing, the outer ring of the adjusting mechanism can rotate along with the rudder wing, the angle regulation of the wing in the circumferential direction is implemented in the rotating process, the flying direction of the projectile body can be adjusted at any time, the controllable lifting force of the projectile body when flying to a target is kept, the projectile body cannot yaw when coming out of a chamber, and the technical problem that the projectile body deviates from a trajectory in the conventional PGK is solved. Therefore, compared with the background art, the invention has the advantages of simple mechanism, convenient assembly, low cost, easy guarantee of precision and the like.
Drawings
FIG. 1 is a schematic structural view of the present invention;
FIG. 2 is a cross-sectional view A-A of FIG. 1;
FIG. 3 is a top view of FIG. 2;
FIG. 4 is a top view of FIG. 3;
FIG. 5 is a front view of the outer ring of the present invention;
FIG. 6 is a left side view of FIG. 5;
FIG. 7 is a schematic structural diagram of a control surface regulating mechanism of the invention;
FIG. 8 is a cross-sectional view B-B in FIG. 7;
FIG. 9 is a schematic structural diagram of the movable rudder wing of the present invention;
FIG. 10 is a cross-sectional view C-C of FIG. 9;
FIG. 11 is a top view of FIG. 9;
in fig. 1: 1-motor fixing plate, 2-stepping motor, 3-outer ring, 4-outer ring pressing block, 5-nut pressing block, 6-nut, 7-follow-up bearing, 8-lead screw, 9-set screw, 10-movable wing, 11-fixing screw, 12-rudder wing shaft sleeve, 13-rudder wing main shaft, 14-rudder wing cylinder, 15-front and rear cabin connecting seat, 16-guiding boss and 17-chute.
Detailed Description
The invention is further illustrated by the following examples in conjunction with the drawings.
As shown in fig. 1 to 11, the controllable movable rudder wing lift angle device for a PGK seeker in the present embodiment includes a movable wing 10 and a rudder wing barrel 14, wherein: the rudder wing device also comprises a motor fixing plate 1, a stepping motor 2, an outer ring 3, an outer ring pressing block 4, a nut pressing block 5, a nut 6, a follow-up bearing 7, a screw 8, a set screw 9, a rudder wing shaft sleeve 12 and a rudder wing main shaft 13, wherein the motor fixing plate 1 is connected with a motor frame arranged in a rudder wing cylinder 14 and is positioned at the rear part in the rudder wing cylinder 14, the stepping motor 2 is fixed on the motor fixing plate 1 by screws, the screw 8 is fixed on the rotating shaft of the stepping motor 2 through a set screw 9, the nut 6 is arranged on the screw 8, the follower bearing 7 is arranged in the outer ring 3, the outer ring of the follower bearing 7 is connected with the outer ring 3 through a screw, the outer ring press block 4 is arranged on one end surface of the outer ring 3 and fixes the follower bearing 7 in the outer ring 3, one end of the nut pressing block 5 is fixed on a nut 6, the U-shaped end of the nut pressing block 5 is clamped on an inner ring of a follow-up bearing 7, the middle part of the nut pressing block 5 is located in a long groove formed in a front cabin connecting seat 15 and a rear cabin connecting seat 15, the outer ring 3 is arranged at the rear part in a rudder wing cylinder 14 and can rotate, a rudder wing main shaft 13 is arranged in a rudder wing shaft sleeve 12, the rudder wing shaft sleeve 12 is arranged at the middle part of the bottom surface of a movable wing 10 through a fixing screw 11, the movable wing 10 is arranged on the rudder wing cylinder 14 through the rudder wing main shaft 13 and can rotate, and a circular shaft is arranged on one side of the movable wing 10 and penetrates through a circular arc groove formed in the rudder wing cylinder 14 to be connected with a chute designed on a guide boss of the outer ring 3. One end of the front and rear cabin connecting seat 15 is arranged on the motor fixing plate 1 and positioned in the inner ring of the follow-up bearing 7 to play a role in guiding, and the other end of the front and rear cabin connecting seat 15 is connected with the battery cabin. The motor fixing plate 1, the stepping motor 2, the outer ring 3, the outer ring pressing block 4, the nut pressing block 5, the nut 6, the follow-up bearing 7, the lead screw 8 and the set screw 9 form a control surface regulating mechanism. The movable wing 10, the fixing screw 11, the rudder wing shaft sleeve 12 and the rudder wing main shaft 13 form a movable rudder wing.
As shown in fig. 5 to 6, 4 guide bosses 16 are uniformly designed on the outer ring 3, and inclined slots 17 are formed on the guide bosses 16.
As shown in fig. 4, the movable wing 10 rotates by an angle of ± 10 °.
The working process of the invention is as follows: after the stepping motor 2 obtains the working signal, the rotating shaft thereof drives the screw rod 8 to rotate forwards and backwards together, so that the screw nut 6 connected with the screw rod 8 is driven to move forwards and backwards. The nut pressing block 5 moves along with the nut 6 and drives the follow-up bearing 7 to move back and forth. The inner ring of the follow-up bearing 7 moves back and forth, but the outer ring of the follow-up bearing 7 is matched with the arc groove arranged on the rudder wing cylinder 14 through the guide boss 16 on the outer ring 3 and rotates together with the rudder wing cylinder 14. The inclined slot 17 designed on the guiding boss of the outer ring 3 drives the movable wing piece 10 to rotate around the main shaft 13 of the rudder wing on the rudder wing cylinder 14 so as to adjust the angle of the wing piece at any time and control the flying direction of the projectile body.
Claims (2)
1. A controllable movable rudder wing lift angle device for PGK seeker comprises a movable wing (10) and a rudder wing cylinder (14), and is characterized in that: the rudder wing air compressor further comprises a motor fixing plate (1), a stepping motor (2), an outer ring (3), an outer ring pressing block (4), a nut pressing block (5), a nut (6), a follow-up bearing (7), a lead screw (8), a set screw (9), a rudder wing shaft sleeve (12) and a rudder wing main shaft (13), wherein the motor fixing plate (1) is connected with a motor frame arranged in a rudder wing cylinder (14) and is positioned at the rear part in the rudder wing cylinder (14), the stepping motor (2) is fixed on the motor fixing plate (1) through screws, the lead screw (8) is fixed on a rotating shaft of the stepping motor (2) through the set screw (9), the nut (6) is arranged on the lead screw (8), the servo bearing (7) is arranged in the outer ring (3), the outer ring of the servo bearing (7) is connected with the outer ring (3) through a screw, the outer ring pressing block (4) is arranged on one end face of the outer ring (3), one end of the nut pressing block (5) is fixed on a nut (6), the U-shaped end of the nut pressing block (5) is clamped on the inner ring of the servo bearing (7), the middle part of the nut pressing block (5) is positioned in a long groove formed in a front cabin connecting seat and a rear cabin connecting seat (15), the outer ring (3) is arranged at the rear part in the rudder wing cylinder (14), the rudder wing main shaft (13) is arranged in the rudder wing shaft sleeve (12), the rudder wing shaft sleeve (12) is arranged in the middle of the bottom surface of the movable wing piece (10) through a fixing screw, the movable wing piece (10) is arranged on a rudder wing cylinder (14) through a rudder wing main shaft (13) and can rotate, one side of the movable wing piece (10) is provided with a circular shaft, and the circular shaft passes through a circular arc groove arranged on the rudder wing cylinder (14) and is connected with a chute designed on a guide boss of the outer ring (3);
the outer ring (3) is uniformly provided with 4 guide bosses (16), and the guide bosses (16) are provided with chutes (17).
2. The device for controlling the lift angle of the movable rudder wing of a PGK seeker as claimed in claim 1, wherein: the rotating angle of the movable wing pieces (10) is +/-10 degrees.
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CN202110739438.1A CN113357973B (en) | 2021-06-30 | 2021-06-30 | Controllable movable rudder wing lift angle device for PGK seeker |
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CN202110739438.1A CN113357973B (en) | 2021-06-30 | 2021-06-30 | Controllable movable rudder wing lift angle device for PGK seeker |
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CN113357973B true CN113357973B (en) | 2023-01-03 |
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CN115096146B (en) * | 2022-07-18 | 2023-07-18 | 南京理工大学 | Control surface deflection and active sealing locking mechanism suitable for PGK wing barrel structure |
CN115371501B (en) * | 2022-09-19 | 2023-04-28 | 山西华洋吉禄科技股份有限公司 | Rudder wing linkage structure of accurate guidance assembly and control method |
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US4546940A (en) * | 1979-09-27 | 1985-10-15 | Kurt Andersson | Projectile, adapted to be given a rotation on firing, which makes the projectile spin-stabilized |
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DE102015013913A1 (en) * | 2015-10-27 | 2017-04-27 | Deutsch Französisches Forschungsinstitut Saint Louis | Full-caliber, spin-stabilized steer bullet with a long range |
CN108286918A (en) * | 2017-12-29 | 2018-07-17 | 中国航天空气动力技术研究院 | A kind of how shaft-driven annular rudder control unit |
WO2020086152A2 (en) * | 2018-08-31 | 2020-04-30 | Bae Systems Information And Electronic Systems Integration Inc. | Reduced noise estimator |
CN111141183A (en) * | 2020-01-10 | 2020-05-12 | 蓝箭航天空间科技股份有限公司 | Power tail cabin and rocket |
CN111207630A (en) * | 2020-01-10 | 2020-05-29 | 蓝箭航天空间科技股份有限公司 | Rocket flight attitude control method |
CN112346473A (en) * | 2020-11-25 | 2021-02-09 | 成都云鼎智控科技有限公司 | Unmanned aerial vehicle attitude control system, flight control system and attitude control method |
CN215984224U (en) * | 2021-06-30 | 2022-03-08 | 山西华洋吉禄科技股份有限公司 | Controllable movable rudder wing lift angle device for PGK seeker |
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2021
- 2021-06-30 CN CN202110739438.1A patent/CN113357973B/en active Active
Patent Citations (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4546940A (en) * | 1979-09-27 | 1985-10-15 | Kurt Andersson | Projectile, adapted to be given a rotation on firing, which makes the projectile spin-stabilized |
EP3023671A1 (en) * | 2014-11-21 | 2016-05-25 | HS Wroclaw Sp. z o.o. | Rotary actuator and a method of driving the same |
DE102015013913A1 (en) * | 2015-10-27 | 2017-04-27 | Deutsch Französisches Forschungsinstitut Saint Louis | Full-caliber, spin-stabilized steer bullet with a long range |
CN108286918A (en) * | 2017-12-29 | 2018-07-17 | 中国航天空气动力技术研究院 | A kind of how shaft-driven annular rudder control unit |
WO2020086152A2 (en) * | 2018-08-31 | 2020-04-30 | Bae Systems Information And Electronic Systems Integration Inc. | Reduced noise estimator |
CN111141183A (en) * | 2020-01-10 | 2020-05-12 | 蓝箭航天空间科技股份有限公司 | Power tail cabin and rocket |
CN111207630A (en) * | 2020-01-10 | 2020-05-29 | 蓝箭航天空间科技股份有限公司 | Rocket flight attitude control method |
CN112346473A (en) * | 2020-11-25 | 2021-02-09 | 成都云鼎智控科技有限公司 | Unmanned aerial vehicle attitude control system, flight control system and attitude control method |
CN215984224U (en) * | 2021-06-30 | 2022-03-08 | 山西华洋吉禄科技股份有限公司 | Controllable movable rudder wing lift angle device for PGK seeker |
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