CN113357973A - Controllable movable rudder wing lift angle device for PGA seeker - Google Patents
Controllable movable rudder wing lift angle device for PGA seeker Download PDFInfo
- Publication number
- CN113357973A CN113357973A CN202110739438.1A CN202110739438A CN113357973A CN 113357973 A CN113357973 A CN 113357973A CN 202110739438 A CN202110739438 A CN 202110739438A CN 113357973 A CN113357973 A CN 113357973A
- Authority
- CN
- China
- Prior art keywords
- rudder wing
- outer ring
- wing
- screw
- rudder
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Images
Classifications
-
- 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
Landscapes
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Transmission Devices (AREA)
Abstract
The invention relates to a controllable movable rudder wing lift angle device for a PGA seeker. The invention mainly solves the technical problem that the projectile body deviates from the trajectory in the conventional PGA. The technical scheme adopted by the invention is as follows: a controllable active rudder wing lift angle device for a PGA 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 PGA (PGA) seeker.
Background
The PGK (precision Guidance kit) precision Guidance component is a ballistic correction module integrating fuze, ballistic detection device, air control surface and 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 that uses PGK to achieve two-dimensional trajectory modification is also known as a double spin projectile. The projectile rotates forwards, the rotary wing cylinder rotates backwards 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 has disadvantages in practical application. 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 PGA seeker are added, because the lift angle of the air control surface is certain (4 degrees or 5 degrees) at the initial speed, the lift is constant, the projectile body can be driven to deviate from the trajectory for a period of time and distance, and the PGK precision is reduced.
Disclosure of Invention
The invention aims to solve the technical problem that a projectile body deviates from a trajectory in the conventional PGA and provides a controllable movable rudder wing lift angle device for a PGA seeker.
In order to solve the technical problems, the invention adopts the technical scheme that:
a controllable active rudder wing lift angle device for a PGA seeker, comprising an active wing and a rudder wing cylinder, wherein: the rudder wing main shaft is characterized by further comprising a motor fixing plate, a stepping motor, an outer ring pressing block, a nut, a follow-up 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 cylinder and is positioned at the rear part in the rudder wing cylinder, 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, the follow-up bearing is arranged in the outer ring, an outer ring of the follow-up bearing is connected with the outer ring through the screw, the outer ring pressing block is arranged on one end surface of the outer ring, one end of the nut pressing block is fixed on the nut, a U-shaped end of the nut pressing block is clamped on the follow-up bearing, the middle part of the nut pressing block is positioned in a long groove arranged in a front and rear cabin connecting seat, the, the rudder wing shaft sleeve is arranged in the middle of the bottom surface of the movable wing piece through a fixing screw, the movable wing piece is arranged on the rudder wing barrel through the rudder wing main shaft and can rotate, and a circular shaft is arranged on one side of the movable wing piece and penetrates through an arc groove formed in the rudder wing barrel to be connected with a chute designed on the outer ring guide boss.
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 invention adds a rudder wing adjusting mechanism at the rear part in the rudder wing cylinder, changes the original fixed wing into a movable wing, the outer ring of the adjusting mechanism can rotate along with the rudder wing, and the angle regulation of the wing in the circumferential direction is implemented in the rotating process, so that the flying direction of the projectile body can be adjusted at any time, the lifting force of the projectile body is kept controllable when flying to a target, the projectile body cannot yaw when coming out of the chamber, and the technical problem that the projectile body deviates from the trajectory in the existing PGA 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 figures and examples.
As shown in fig. 1 to 11, the controllable movable rudder wing lift angle device for PGA seeker in this embodiment includes a movable wing 10 and a rudder wing cylinder 14, wherein: the rudder wing rudder propeller device comprises a motor 1, a motor 2, a step motor 2, a step motor 8, a set screw 9, a step screw 8, a step screw 6, a step screw 4, a step screw 3 and a step screw 3, a follower bearing 7, and a follower bearing 3, and fix the outer ring 3 in the outer ring 3 and fix the outer ring 3 in the outer ring 3, the outer ring with the follower bearing 7 in the outer ring 3, one end of the screw of the nut 6, one end of the nut of the press block 5, one end of the press block 5 is fixed on the one end of the nut press block 5 is fixed on the nut 6, the nut press block 5, the U-shaped end of the nut 6, the nut press block 5 is blocked in the bearing 7, the middle part of the nut press block 5 is positioned in an elongated slot arranged on a front and rear cabin connecting seat 15, the outer ring 3 is arranged at the rear part in a rudder wing cylinder 14 and can rotate, the 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 piece 10 through a fixing screw 11, the movable wing piece 10 is arranged on the rudder wing cylinder 14 through the 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 penetrates through a circular arc slot arranged on the rudder wing cylinder 14 and is 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 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 (3)
1. Controllable movable rudder wing lift angle device for PGA seeker, comprising movable wing (10) and rudder wing cylinder (14), 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 spindle (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 follow-up bearing (7) is arranged in the outer ring (3), the outer ring of the follow-up bearing (7) is connected with the outer ring (3) through screws, and the outer ring pressing block (4) is arranged on one end face of the outer ring (3), one end of the screw pressing block (5) is fixed on a screw (6), the U-shaped end of the screw pressing block (5) is clamped on an inner ring of a follow-up bearing (7), the middle of the screw pressing block (5) is located 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 of the rudder wing cylinder (14), a rudder wing main shaft (13) is arranged in a rudder wing shaft sleeve (12), the rudder wing shaft sleeve (12) is arranged in the middle of the bottom surface of the movable wing (10) through a fixing screw, the movable wing (10) is arranged on the rudder wing cylinder (14) through a rudder wing main shaft (13) and can rotate, a circular shaft is arranged on one side of the movable wing (10), and the circular shaft penetrates through a circular arc groove formed in the rudder wing cylinder (14) and is connected with a chute designed on a guide boss of the outer ring (3).
2. The controllable movable rudder wing lift angle device for PGA seeker as claimed in claim 1, wherein: the outer ring (3) is evenly provided with 4 guide bosses (16), and the guide bosses (16) are provided with chutes (17).
3. A controllable active rudder wing lift angle device for PGA seeker according to claim 1 or 2, wherein: the rotating angle of the movable wing pieces (10) is +/-10 degrees.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110739438.1A CN113357973B (en) | 2021-06-30 | 2021-06-30 | Controllable movable rudder wing lift angle device for PGK seeker |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110739438.1A CN113357973B (en) | 2021-06-30 | 2021-06-30 | Controllable movable rudder wing lift angle device for PGK seeker |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN113357973A true CN113357973A (en) | 2021-09-07 |
| CN113357973B CN113357973B (en) | 2023-01-03 |
Family
ID=77537573
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110739438.1A Active CN113357973B (en) | 2021-06-30 | 2021-06-30 | Controllable movable rudder wing lift angle device for PGK seeker |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN113357973B (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115096146A (en) * | 2022-07-18 | 2022-09-23 | 南京理工大学 | Control surface deflection and active sealing locking mechanism suitable for PGK wing bucket structure |
| CN115371501A (en) * | 2022-09-19 | 2022-11-22 | 山西华洋吉禄科技股份有限公司 | Rudder wing linkage structure of precision guidance assembly and control method |
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 |
-
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 |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115096146A (en) * | 2022-07-18 | 2022-09-23 | 南京理工大学 | Control surface deflection and active sealing locking mechanism suitable for PGK wing bucket structure |
| 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 |
| CN115371501A (en) * | 2022-09-19 | 2022-11-22 | 山西华洋吉禄科技股份有限公司 | Rudder wing linkage structure of precision guidance assembly and control method |
| 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 |
Also Published As
| Publication number | Publication date |
|---|---|
| CN113357973B (en) | 2023-01-03 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN113357973B (en) | Controllable movable rudder wing lift angle device for PGK seeker | |
| CN215984224U (en) | Controllable movable rudder wing lift angle device for PGK seeker | |
| US4665332A (en) | Electric generator assembly for a projectile | |
| CA2926626C (en) | Fin deployment mechanism for a projectile and method for fin deployment | |
| US20080315032A1 (en) | Techniques for providing surface control to a guidable projectile | |
| CN105021089B (en) | High initial speed projectile transmitting device and launching technique | |
| CN110220001B (en) | Driving device for gas regulating valve of solid attitude and orbit control engine | |
| KR101967749B1 (en) | A missile wing operating device using a linear motor | |
| CN113310361A (en) | Ballistic trajectory correction actuating mechanism | |
| CN108916264B (en) | Torque limiter used for building and based on magnet control steel ball driving | |
| CN209689505U (en) | A kind of coaxial double-oar tail portion push type miniature missile | |
| US3747529A (en) | Electromagnetic generator for a rifled projectile | |
| CN112683107B (en) | Launching mechanism based on rigid thimble | |
| WO2015167384A1 (en) | Device and method for launching warheads at high velocity | |
| CN113503773A (en) | Rotating holder for PGK and control method thereof | |
| CN115355769B (en) | Variable static stability tactical missile pneumatic layout and application thereof | |
| ES271926U (en) | Training projectile | |
| US3157124A (en) | Spin stabilized hollow charge projectile | |
| CN209399847U (en) | A kind of projectile bullet support with response type obturator ring and separation windage face | |
| CN216954211U (en) | A rotatory cloud platform for PGK | |
| CN212109763U (en) | Ballistic correction fuse driving module | |
| KR20160090695A (en) | Apparatus for actuating control-fin of guided missile | |
| CN209689503U (en) | A kind of electricity duct tail portion push type miniature missile | |
| CN215447612U (en) | Ballistic trajectory correction actuating mechanism | |
| CN109708535A (en) | A kind of coaxial double-oar tail portion push type miniature missile |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| CB02 | Change of applicant information |
Address after: 030008 No. 86, Yangxing South Street, Jiancaoping District, Taiyuan City, Shanxi Province Applicant after: SHANXI HUAYANG JILU TECHNOLOGY CO.,LTD. Address before: 030008 No. 86, Yangxing South Street, stainless steel industrial park, Taiyuan, Shanxi Province Applicant before: SHANXI HUAYANG JILU TECHNOLOGY CO.,LTD. |
|
| CB02 | Change of applicant information | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |