CN115096146A - Control surface deflection and active sealing locking mechanism suitable for PGK wing bucket structure - Google Patents
Control surface deflection and active sealing locking mechanism suitable for PGK wing bucket structure Download PDFInfo
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- CN115096146A CN115096146A CN202210840392.7A CN202210840392A CN115096146A CN 115096146 A CN115096146 A CN 115096146A CN 202210840392 A CN202210840392 A CN 202210840392A CN 115096146 A CN115096146 A CN 115096146A
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- wing
- outer sleeve
- inner sleeve
- power transmission
- sleeve
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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
- F42B10/60—Steering arrangements
- F42B10/62—Steering by movement of flight surfaces
- F42B10/64—Steering by movement of flight surfaces of fins
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
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- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Steering-Linkage Mechanisms And Four-Wheel Steering (AREA)
- Transmission Devices (AREA)
Abstract
The invention discloses a control surface deflection and active sealing locking mechanism suitable for a PGK wing bucket structure, which comprises: a power transmission assembly; an outer sleeve and an inner sleeve which are internally and externally embedded and are in threaded connection with the power transmission assembly are adopted; the rudder wing is hinged with the outer sleeve through a rotating shaft and provided with a limiting shaft, and the limiting shaft extends into the guide grooves of the outer sleeve and the inner sleeve; the outer sleeve and the inner sleeve are in reverse threaded connection with the power transmission assembly, and the power transmission assembly can drive the outer sleeve and the inner sleeve to simultaneously extend or contract when rotating forwards or reversely, so that the deflection angles of the control surfaces of the control wings are restrained together, and the machine selection bias of the control surfaces is realized; and simultaneously, the wing barrel end face is attached to the adjacent structure when the outer sleeve and the inner sleeve extend out, and a gap is formed between the wing barrel end face and the adjacent structure when the outer sleeve and the inner sleeve contract, so that the wing barrel rotates. The invention can realize the deflection locking function of the control surface and the active sealing locking function.
Description
Technical Field
The invention belongs to the field of electric steering engines, and particularly relates to a control surface deflection and active sealing locking mechanism suitable for a PGK wing bucket structure.
Background
The guidance assembly is an ideal solution for achieving conventional cartridge guidance. The single-channel guidance control assembly for completing the adjustment of the lifting surface rolling direction through the wing barrel structure has relatively low cost and is more suitable for guidance transformation of conventional artillery ammunition. However, the rudder wing structure fixedly connected to the wing barrel structure has a constant initial installation angle, and before the control system works in the early stage of ammunition launching, uncontrolled random pneumatic overturning moment is introduced, so that the dispersion of uncontrolled ballistic trajectories is obviously increased, and the regulation and control capability of controlled ammunition is weakened.
Meanwhile, the wing-barrel structure rotates relative to the projectile body, and large gaps exist at two ends of the wing-barrel structure. Particularly, under some special and severe working conditions, such as underwater standby emission, a sealing structure needs to be designed in a targeted manner in order to avoid transmission failure caused by foreign matter invasion. The conventional dynamic sealing methods, such as oil seal, labyrinth seal and the like, have complicated maintenance process and cannot avoid the invasion of foreign matters under the conditions of long-term standing, non-working state and severe environment (sand wind and water immersion).
Disclosure of Invention
The invention aims to provide a control surface deflection and active sealing locking mechanism suitable for a PGK wing bucket structure, which is used for avoiding the problem of initial ballistic disturbance caused by the initial installation angle of the control surface and solving the sealing problem caused by the existence of a large gap at two ends of the wing bucket structure.
The technical solution for realizing the purpose of the invention is as follows:
a rudder surface deflection and active seal locking mechanism suitable for a PGK wing bucket structure comprises:
a power transmission assembly;
an outer sleeve and an inner sleeve which are internally and externally embedded and are in threaded connection with the power transmission assembly are adopted;
the rudder wing is hinged with the outer sleeve through a rotating shaft and provided with a limiting shaft, and the limiting shaft extends into the guide grooves of the outer sleeve and the inner sleeve;
the outer sleeve and the inner sleeve are in reverse threaded connection with the power transmission assembly, and the power transmission assembly can drive the outer sleeve and the inner sleeve to simultaneously extend or contract when rotating forwards or reversely, so that the deflection angles of the control surfaces of the control wings are restrained together, and the machine selection bias of the control surfaces is realized; and simultaneously, the wing barrel end face is attached to the adjacent structure when the outer sleeve and the inner sleeve extend out, and a gap is formed between the wing barrel end face and the adjacent structure when the outer sleeve and the inner sleeve contract, so that the wing barrel rotates.
Compared with the prior art, the invention has the following remarkable advantages:
(1) the invention can realize the deflection and the limit of the rudder wing through the two sleeves which are embedded inside and outside, and compared with the common mode of realizing the deflection of the rudder wing, the sleeve type rudder surface deflection locking mechanism has simpler structure, is beneficial to saving the limited internal space of the mechanism and is more beneficial to realizing the deflection and the limit of the rudder wing in a tiny space.
(2) The invention avoids the problem of initial ballistic disturbance caused by the mounting angle of the control surface. Because the deflection angle of the rudder wing is restrained by the inner sleeve and the outer sleeve and can be deflected in a controlled manner under the action of the power transmission assembly, the attack angle of the rudder wing can be restrained to be zero during launching, the initial disturbance is reduced, and the position and the posture of the projectile are adjusted and controlled by selecting the rudder wing after launching.
(3) The wing barrel end face sealing device can ensure the close fit of the wing barrel end face and the adjacent structure in the storage standing and standby launching stages, realizes reliable sealing, and solves the problem of transmission failure caused by foreign matter invasion due to the large gaps at the two ends of the wing barrel structure.
(4) The mechanism can enter a sealing state or a working state only by driving the power transmission assembly, and the sealing is not required to be designed specifically, so that the space can be saved, and the mechanism is convenient to realize in a limited space.
(5) Compared with the common dynamic sealing method, such as oil seal, labyrinth seal and the like, the invention basically does not need maintenance and can be kept still and sealed for a long time in a non-working state and a severe environment.
Drawings
FIG. 1 is a cross-sectional view of a telescopic rudder surface deflection and active seal locking mechanism in a screwed-in state suitable for a PGK wing bucket structure.
Fig. 2 is a structural diagram of a telescopic rudder surface deflection and active seal locking mechanism in a unscrewed state suitable for a PGK wing bucket structure.
FIG. 3 is a structural diagram of an outer sleeve in a sleeve type control surface deflection locking and active sealing locking mechanism.
FIG. 4 is a block diagram of the inner sleeve of the telescopic control surface yaw lock and active seal lock mechanism.
FIG. 5 is a block diagram of the power transmission assembly in the telescopic rudder surface deflection locking and active seal locking mechanism.
FIG. 6 is a block diagram of the rudder wings in the telescopic rudder surface deflection locking and active seal locking mechanism.
Detailed Description
The invention is further described with reference to the following figures and embodiments. The specific embodiments described herein are merely illustrative of the invention and do not delimit the invention.
Unless the context clearly dictates otherwise, the elements and components of the present invention may be present in either single or in multiple forms and are not limited thereto. Although the steps in the present invention are shown and described using reference numbers, the order of the steps is not limited to any order, and the order of steps may be modified unless otherwise indicated or unless the order of steps or performance of certain steps requires otherwise. It is to be understood that the term "and/or" as used herein refers to and encompasses any and all possible combinations of one or more of the associated listed items.
Referring to fig. 6, the rudder surface deflecting and active sealing locking mechanism 1 for a pgk (project guide kit) wing barrel structure provided in this embodiment includes an outer sleeve 2, an inner sleeve 3, a power transmission assembly 4 and a rudder wing 5. The inner sleeve 3 is connected with the power transmission assembly 4 through anticlockwise threads; the outer sleeve 2 is connected with the power transmission assembly 4 through clockwise threads; a rotating shaft 14 is arranged at the lower part of the side end of the rudder wing 5, the rotating shaft 14 is hinged on the outer sleeve 2, a limiting shaft 13 is arranged at the upper part of the side end of the rudder wing 5, and the limiting shaft 13 extends into the guide grooves of the inner sleeve and the outer sleeve; the whole locking mechanism 1 uses two sleeves which are embedded inside and outside, opposite movement (clockwise rotation of the outer sleeve 2 and anticlockwise rotation of the inner sleeve 3) of sleeve structures is realized under the driving of the power transmission assembly through pre-designed clockwise and anticlockwise threads, and not only can the deflection locking effect of a control surface be realized, but also the active sealing locking effect can be realized. When the deflection locking action of the control surface is realized, the deflection angle of the control surface can be restrained by utilizing the inner sleeve and the outer sleeve together, the machine selection bias of the control surface can be realized, and the problem of initial disturbance of a trajectory caused by the installation angle of the control surface is avoided; when realizing the sealed locking effect of initiative, on the one hand keep silent and stand by the stand-by launch stage in the storage and ensure wing bucket terminal surface and close on the closely laminating of structure, realize reliable sealed, on the other hand separates wing bucket terminal surface and close on the structure in the course of the work, forms the clearance, ensures the nimble rotation of wing bucket.
The sleeve type control surface deflection locking and active sealing locking mechanism 1 is provided with anticlockwise threads 11 and clockwise threads 12 at two ends of an output stage of the power transmission assembly 4, and the diameter of the middle position of the power transmission assembly 4 is designed to be slightly larger than the diameters of the two ends (a shaft shoulder structure) so as to limit the axial positions of the inner sleeve 3 and the outer sleeve 2; the outer surface of the inner sleeve 3 is provided with an arc-shaped first guide groove 10 for limiting the positions of the inner sleeve 3 and the outer sleeve 2 after being screwed in, and the inner surface of the inner sleeve 3 is provided with a counterclockwise thread 9; the outer sleeve 2 is provided with a transverse second guide groove 7 for matching with a limit shaft 13 of the rudder wing 5, a hole 8 is formed in the outer surface for matching with a rotating shaft 14 of the rudder wing 5, the inner part of the outer sleeve is designed into inner surfaces (stepped holes) with different inner diameters, the inner surface with a larger diameter is embedded with the inner sleeve 3, and the inner surface with a smaller diameter is provided with a clockwise thread 6; the inner sleeve 3 and the outer sleeve 2 are respectively connected with the power transmission assembly 4 through a counterclockwise thread 9 and a clockwise thread 6; the rudder wing 5 is hinged with the hole 8 of the outer sleeve 2 through a rotating shaft 14, and a limit shaft 13 extends into the first guide groove 10 of the inner sleeve 3 and the second guide groove 7 of the outer sleeve 2.
When the locking mechanism 1 realizes the locking action of the deflection of the control plane, the deflection of the control wing 5 is realized, the power transmission assembly 4 rotates, the inner sleeve 3 and the outer sleeve 2 are driven to rotate along the threads through the anticlockwise threads 11 and the clockwise threads 12 at the two ends, the opposite movement (clockwise rotation and anticlockwise rotation of the outer sleeve) of the inner sleeve 3 and the outer sleeve 2 is realized, the movement of the inner sleeve and the outer sleeve drives the limiting shaft 13 of the control wing 5 to move in the guide groove of the inner sleeve by taking the rotating shaft 14 as the center of a circle, the rotating shaft 14 of the control wing 5 correspondingly rotates in the hole 8 of the outer sleeve 2, and the deflection of the control wing 5 is finally realized. Therefore, the deflection angle of the rudder wing is restrained by the inner sleeve and the outer sleeve and can be controlled to deflect under the action of the power transmission assembly 4, the attack angle of the rudder wing can be restrained to be zero during launching, initial disturbance is reduced, and the position and posture of the projectile are adjusted and controlled by biasing the rudder wing 5 after launching.
When the sleeve type control surface deflection and active sealing locking mechanism 1 realizes the active sealing locking function, if the locking mechanism 1 is in a storage standing state and a standby launching state, the outer sleeve 2 and the inner sleeve 3 are tightly attached to adjacent structures, so that the sealing function is realized; when the locking mechanism 1 is to work, the power transmission assembly 4 rotates to enable the inner sleeve 3 and the outer sleeve 2 to be screwed into threads through the anticlockwise threads 11 and the clockwise threads 12, so that the end parts of the inner sleeve 3 and the outer sleeve 2 are separated from adjacent structures to form a certain gap, and the flexible rotation of the wing-barrel structure during working is guaranteed.
The invention uses two sleeves which are embedded inside and outside, and realizes the opposite movement of sleeve structures (the outer sleeve rotates clockwise and the inner sleeve rotates anticlockwise) under the driving of the power transmission assembly through the pre-designed clockwise and anticlockwise threads, thereby realizing the deflection locking function of the control surface and the active sealing locking function; when the deflection locking function of the control surface is realized, the deflection angle of the control surface can be restrained by utilizing the inner sleeve and the outer sleeve together, the machine selection bias of the control surface can be realized, and the problem of initial disturbance of a trajectory caused by the installation angle of the control surface is avoided; when realizing the sealed locking effect of initiative, on the one hand keep silent and stand by the stand-by launch stage in the storage and ensure wing bucket terminal surface and close on the closely laminating of structure, realize reliable sealed, on the other hand separates wing bucket terminal surface and close on the structure in the course of the work, forms the clearance, ensures the nimble rotation of wing bucket.
It will be evident to those skilled in the art that the invention is not limited to the details of the foregoing illustrative embodiments, and that the present invention may be embodied in other specific forms without departing from the spirit or essential attributes thereof. The present embodiments are therefore to be considered in all respects as illustrative and not restrictive, the scope of the invention being indicated by the appended claims rather than by the foregoing description, and all changes which come within the meaning and range of equivalency of the claims are therefore intended to be embraced therein. Any reference sign in a claim should not be construed as limiting the claim concerned.
Furthermore, it should be understood that although the present specification describes embodiments, not every embodiment includes only a single embodiment, and such description is for clarity purposes only, and it is to be understood that all embodiments may be combined as appropriate by one of ordinary skill in the art to form other embodiments as will be apparent to those of skill in the art from the description herein.
Claims (4)
1. A rudder surface deflection and active seal locking mechanism suitable for a PGK wing bucket structure, comprising:
a power transmission assembly;
an outer sleeve and an inner sleeve which are internally and externally embedded and are in threaded connection with the power transmission assembly are adopted;
the rudder wing is hinged with the outer sleeve through a rotating shaft and provided with a limiting shaft, and the limiting shaft extends into the guide grooves of the outer sleeve and the inner sleeve;
the outer sleeve and the inner sleeve are in reverse threaded connection with the power transmission assembly, and the power transmission assembly can drive the outer sleeve and the inner sleeve to simultaneously extend or contract when rotating forwards or reversely to jointly restrict a control plane deflection angle of the control wing and realize the machine selection offset of the control plane; and simultaneously, the wing barrel end face is attached to the adjacent structure when the outer sleeve and the inner sleeve extend out, and a gap is formed between the wing barrel end face and the adjacent structure when the outer sleeve and the inner sleeve contract, so that the wing barrel rotates.
2. The rudder surface deflection and active seal locking mechanism for a PGK wing bucket structure according to claim 1, wherein when the active seal locking action is achieved: when the sleeve type active sealing locking mechanism is in a storage standing state and a standby launching state, the outer sleeve and the inner sleeve are attached to the adjacent structure to realize a sealing effect; when the wing bucket structure is to work, the power transmission assembly rotates to enable the inner sleeve and the outer sleeve to be screwed into the threads, so that the end parts of the inner sleeve and the outer sleeve are separated from the adjacent structure, a gap is formed, and the rotation of the wing bucket structure during work is guaranteed.
3. The rudder surface deflecting and active sealing locking mechanism suitable for the PGK wing bucket structure according to claim 1, wherein a shaft shoulder structure is arranged in the middle of the outer part of the power transmission assembly and used for limiting the screwed positions of the inner sleeve and the outer sleeve.
4. The rudder surface deflecting and active sealing locking mechanism for PGK wing bucket structures according to claim 1, wherein the inner sleeve is connected with the power transmission assembly through a counterclockwise thread; the outer sleeve is connected with the power transmission assembly through clockwise threads.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210840392.7A CN115096146B (en) | 2022-07-18 | 2022-07-18 | Control surface deflection and active sealing locking mechanism suitable for PGK wing barrel structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210840392.7A CN115096146B (en) | 2022-07-18 | 2022-07-18 | Control surface deflection and active sealing locking mechanism suitable for PGK wing barrel structure |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN115096146A true CN115096146A (en) | 2022-09-23 |
| CN115096146B CN115096146B (en) | 2023-07-18 |
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| CN202210840392.7A Active CN115096146B (en) | 2022-07-18 | 2022-07-18 | Control surface deflection and active sealing locking mechanism suitable for PGK wing barrel structure |
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| CN109000521A (en) * | 2018-07-24 | 2018-12-14 | 湖北泰和电气有限公司 | Rudder wingfold device, micro missile and rudder wingfold method |
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2022
- 2022-07-18 CN CN202210840392.7A patent/CN115096146B/en active Active
Patent Citations (8)
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| US20090283627A1 (en) * | 2008-05-16 | 2009-11-19 | Raytheon Company | Methods and apparatus for air brake retention and deployment |
| US20120223180A1 (en) * | 2009-11-13 | 2012-09-06 | Bae Systems Plc | Guidance device |
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| CN112829924A (en) * | 2020-12-31 | 2021-05-25 | 上海机电工程研究所 | Retractable duck steering mechanism |
| CN113503773A (en) * | 2021-06-28 | 2021-10-15 | 山西华洋吉禄科技股份有限公司 | Rotating holder for PGK and control method thereof |
| CN113357973A (en) * | 2021-06-30 | 2021-09-07 | 山西华洋吉禄科技股份有限公司 | Controllable movable rudder wing lift angle device for PGA seeker |
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| CN115096146B (en) | 2023-07-18 |
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